Piper Comanche Service Manual

Weighing 1B24 Leveling Airplane - PA-24-180, 250, 260 (Serial Nos. 24-4000 to 24-4246, 24-4248 to 24-4299) and PA-24-400 1C1 Leveling Airplane - PA-24-260 (Serial Nos. 24-4247, 24-4300 and up) 1C1 Landing Gear Strut Exposure 1Cé Brake Reservoir - PA-24-180, 250 (Serial Nos. 24-1 to 24-2298 incl) 1C9 Brake Reservoir - PA-24-180, 250 (Serial Nos. 24-2299 and up); PA-24-260 and PA-24-400 1C9 Fuel Strainer and Drain - PA-24-180, 250 (Serial Nos. 24-2299 and up); and PA-24-260 1C11 Fuel Selector and Drain - PA-24-400 icn Qil Suction Screen 1C20 Qil Pressure Screen 1C20 Lubrication Chart - General - PA-24-180 and PA-24-250 1D1 Lubrication Chart - General - PA-24-260 1D2 Lubrication Chart - General - PA-24-400 iD3 Lubrication Chart - Control Column - PA-24-180, 250, 260 and 400 1D4 Lubrication Chart - Step Lock Mechanism - PA-24-180, 250, 260 and 400 1D5 Lubrication Chart - Flap Track - PA-24-180, 250, 260 and 400 1D6 Lubrication Chart - Nose Landing Gear - PA-24-400 1D7 Lubrication Chart - Nose Landing Gear - PA-24- 180, 250 and 260 1D8 Lubrication Chart - Stabilator - PA-24-180, 250, 260 and 400 1D9 Lubrication Chart - Rudder Control - PA-24-180, 250, 260 and 400 1D10 Lubrication Chart - Bellcrank - PA-24-180, 250, 260 and 400 1D11 Lubrication Chart - Propeller - PA-24-180, 250, 260 and 400 iD12 Lubrication Chart - Main Landing Gear - PA-24-180, 250, 260 and 400 1D13 Typical Muffler Fatigue Areas 1D17 Exhaust System Inspection Points - PA-24-180, 250 and 400 1D18 Exhaust System Inspection Points - PA-24-260 1D19 Landing Light Installation 1E9 Wing Attachment Fittings 1E12 Flap Roller Installation (Electrically Operated) 1E14 Revised: 8/15/98 1A6 PIPER COMANCHE SERVICE MANUAL 4-5. 4-6. 4-7. 4-7a. 4-Tb. 4-Tc. 4-8. 4-9. 4-10. 4-11. 4-12. 4-13. 4-14, 5-1. 5-la. 5-2. 5-3. 54. 5-5. 5-6. 5-7. 5-8. 5-9. 5-10. 5-11. 5-12. 5-13. 6-1. 6-2. 6-3. 6-4. 6-5. 6-6. 6-7. 6-8. 6-8a. 6-8b. 6-8c. 6-9. LIST OF ILLUSTRATIONS (continued) Subject Aileron Bearing Installation Door Installation Door Locking Mechanism - PA-24-250 (Serial Nos. 24-2844 to 24-3284) Door Locking Mechanism - PA-24-250 (Serial Nos. 24-3285 and up); PA-24-260 and PA-24-400 Stabilator Balance Weight Checking Stabilator Free Play Checking and Balancing Rudder Fuselage Skin Diagram - PA-24-180, PA-24-250 and PA-24-260 (Serial Nos. 24-4000 to 24-4246, 24-4248 to 24-4299) Wing and Empennage Skin Diagram - PA-24-180, PA-24-250 and PA-24-260 (Serial Nos. 24-4000 to 24-4246, 24-42438 to 24-4299) Fuselage Skin Diagram - PA-24-260 (Serial Nos. 24-4247, 24-4300 and up) Wing and Empennage Skin Diagram - PA-24-260 (Serial Nos. 24-4247, 24-4300 and up) Fuselage Skin Diagram - PA-24-400 Wing and Empennage Skin Diagram - PA-24-400 Typical Access 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 Neutral Rudder Position Checking Rudder Travel Rudder and Rudder Trim Controls Clamping Rudder Pedals in Neutral Position Stabilator and Stabilator Trim Controls Checking Stabilator Travel in Up Position Stabilator Adjustment Points Special Fabricated Tools Nose Gear Oleo Strut (Serial Nos. 24-1 to 24-214 incl.) Grid No. 1E14 1E17 . 1E18 1E19 1E24 1F2 1F5 1F6 1F7 1F8 1F9 1F10 1F11 1F12 1F19 1F23 1G2 1G4 1G4 1G6 1G15 1G1S5 1G16 1G18 1G21 1H1 1H4 1H16 1H24 Nose Gear Oleo Strut Assembly - PA-24-180, PA-24-250 (Serial Nos. 24-215 and up; PA-24-260 and PA-24-400 Nose Landing Gear Installation Clamping Rudder Pedals in Neutral Position Rudder Pedals at Neutral Angle Installations of Plumb Bob Attachment Tool and Alignment Jig Nose Gear Door 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 Main Landing Gear Installation (Left) Revised: 8/15/98 1A7 115 1110 1113 1113 1114 1116 1120 1122 1122 1123 1J2 PREFACE PIPER COMANCHE SERVICE MANUAL Figure No. 6-10. 6-11. 612. 6-13. 6-14. 6-15. 6-16. 6-19. 6-20. 6-21. 6-22. 6-23. 6-24. 6-25. 6-26. 6-27. 6-28. 6-29. 6-30. 6-31. 6-32. 6-33. 6-34, 6-34a. 6-35. 6-36. 6-37. 6-37a. 6-38. 6-39. 6-40. 641. 6-42. 6-43. 7-1. 7-2. 7-3. 74. PREFACE LIST OF ILLUSTRATIONS (continued) Subject Adjustment of Main Landing Gear Drag Link Aligning Main Gear Landing Gear Retraction System Landing Gear Retraction Transmission Assembly Landing Gear Retraction System Instailation Nose Gear Drag Link Clevis Landing Gear Up Limit Switch Torque Wrench and Adapter Installation, (Serial Nos. 24-1 to 24-4782 incl.; 24-4784 to 24-4803 incl.) Torque Wrench and Adapter Installation, (Serial Nos. 24-4783; 24-4804 and up) Landing Gear Down Safety Lock Installation Landing Gear Warning Switch Installation Landing Gear Wamning Indicator Nose Wheel Assembly Main Wheel Assembly (Cleveland) - PA-24-180 and PA-24-250 Main Wheel Assembly (Cleveland) - PA-24-260 and PA-24-400 Main Wheel Assembly (Goodrich) - PA-24-400 Brake Assembly (Cleveland) - PA-24-180 and PA-24-250 (Serial Nos. 24-1 to 24-3295) Grid No, 1J6 137 1J10. 1J12 1317 1718 1119 1724 1K1 1K2 1K3 1K5 1K6 1K8 1K9 1K10 1K12 Brake Assembly (Cleveland) - PA-24-180 and PA-24-250 (Serial Nos. 24-3296 & up); PA-24-260 and PA-24-400 1K14 Brake Assembly (Goodrich) - PA-24-400 1K15 Replacing Brake Disc 1K16 Bleeding Brakes 1K17 Brake System Installation - PA-24-180 and PA-24-250 (Serial Nos. 24-1 to 24-2174 incl., 24-2176 to 24-2298 incl.) 1K18 Brake System Installation - PA-24-180 and PA-24-250 (Serial Nos. 24-2175, 24-2298 and up); PA-24-260 and PA-24-400 1K19 Brake Cylinder Instaliation 1K21 Brake Master Cylinder - PA-24-180 and PA-24-250 (Serial Nos. 24-1 to 24-2174 incl., 24-2176 to 24-2298 incl.) 1K23 Parking Brake Valve 1L1 Brake Master Cylinder - PA-24-180 and PA-24-250 (Serial Nos. 24-2175, 24-2299 and up); PA-24-260 and PA-24-400 1L3 Brake Cylinder Installation 114 Fabricated Plumb-bob Tool 1L7 Fabricated Nose Whee! Alignment Jig 1L8 Fabricated Spanner Wrench 1L9 Inspection of Rod End Bearing 1L11 Main Gear Wear Limits 1L14 Nose Gear Wear Limits 1L16 Propeller Installation (McCauley) 2A14 Typical Nicks and Removal Method 2A15 Propeller Instatlation (Hartzell) 2A18 Woodward Propeller Governor Adjustment Points 2A21 Revised: 8/15/98 1A8 ‘E.Lgm.iflm PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (continued) Subject 7-5. Hartzell Propeller Governor Adjustment Points 7-6. Engine Installation - PA-24-180 7-6a. Cockpit Control Spring Back 7-7. Carburetor 7-8. Magneto Inspection 7-9. Lead Positioning 7-10. Impulse Coupling 7-11. Magneto Timing Marks 7-12. Timing Pointer 7-13. Timing Plate Installed on Breaker Compartment 7-14. Breaker Compartment With Cast Timing Marks 7-15. Engine Timing Marks 7-16. Ignition System Retard Breaker Magneto Installation 7-17. Removing Seized Spark Plug TA-1. Propeller Installation (McCauley) - PA-24-250 TA-2. Typical Nicks and Removal Method TA-3. Propeller Installation (Hartzell) - PA-24-250 TA4. Propeller Installation (Hartzell) - PA-24-260 7A-5. Woodward Propeller Governor Adjustment Points TA-6. Hartzell Propeller Governor Adjustment Points TA-7. Engine Installation - PA-24-250 TA-8. Engine Installation - PA-24-260 (Serial Nos. 24-4000 thru 24-4803, less 24-4783) 7A-9. Engine Installation - PA-24-260 (Serial Nos. 24-4783 and 24-4804 and up) 7A-10. Carburetor TA-11. Schematic Diagram of RSA Fuel Injector System- PA-24- 250 & PA-24-260 TA-12. Idle and Mixture Adjustment (Fuel Injector) 7A-13. Fuel Air Bleed Nozzle 7A-14. Magneto Inspection 7TA-15. Lead Positioning 7TA-16. Impulse Coupling TA-17. Magneto Timing Marks TA-18. Timing Pointer 7A-19 Timing Plate Installed on Breaker Compartment 7A-20. Breaker Compartment with Cast Timing Marks TA-21. Engine Timing Marks TA-22. Ignition System Retard Breaker Magneto Installation 7A-23. Removing Seized Spark Plugs 7B-1. Propeller Installation 7B-2. Typical Nicks and Removal Methods 7B-3. Propeller Governor Adjustment Points 7B-4. Engine Installation - PA-24-400 7B-5. Schematic Diagram of RSA Fuel Injector System - PA-24-400 7B-6. 1dle Speed and Mixture Adjustment (Fuel Injector) 7B-7. Fuel Air Bleed Nozzle 7B-8. Magneto Timing Marks Revised: 8/15/98 1A9 Grid No. 2A22 2B1 - 2BS 2B6 2B8 2B9 2B9 2B10 2B10 2B11 2B11 2B12 2B1S 2B17 2C7 2C8 2C10 2C12 2C16 2C17 2C21 2D1 2D7 2D11 2D14 2D16 2D17 2D19 2D20 2D20 2D21 2D21 2D22 2D22 2D24 2E2 2E4 2E22 2E23 2F2 2F3 2F8 2F10 2F12 2F14 PREFACE PIPER COMANCHE SERVICE MANUAL Figure No. 7B-9. 7B-10. 7B-11. 7B-12. 7B-13. 7B-14. 7TB- 15. 7C-1. 7C-2. 7C-3. 7C-4. 7C-5. 7C-5a. 7C-5b. 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. 8-3. 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. 8-18. 8-19. PREFACE LIST OF ILLUSTRATIONS (continued) Subject Grid No, Reworked Plain Washer 2F14 Filed Notch on Cam 2F15 Installation of Rotor Holding Tool and Timing Pointer 2F15 Alignment of Cam in Inspection Hole ) 2F16 Engine Timing Marks 2F17 Ignition System Retard Breaker Magneto Installation 2F20 Removal of Seized Spark Plug 2F22 Propeller Installation 2G12 Typical Nicks and Removal Methods 2G13 Propeller Govemnor 2G15 Engine Installation - PA-24-260 Turbo 2G22 Schematic Diagram of Turbocharger System 2G23 Lockwiring V-Band Couplings 2G24 Indicator Probe Installation 2H3 Schematic Diagram of RSA Fuel Injector System - PA-24-260 Turbo 2H7 Fuel Injector 2H9 Fuel Air Bleed Nozzle 2H10 Contact Points 2H12 Rotor Holding Tool Installed 2H14 Timing Kit Installed 2H14 Aligning Timing Marks Single Contact Assembly Magneto 2H15 Forming Leads in Breaker Compartment 2H15 Engine Timing Marks 2H16 Magneto Timing Marks 2H16 Removing Frozen Spark Plug 2H19 Turbo Oil Flow Check 2H22 Fuel Cell Installation (Main/Inboard) 2114 Fuel System Schematic - PA-24-180 2115 Fuel System Schematic - PA-24-250 (Serial Nos. 24-105 to 24-2298) 2116 Fuel System Schematic - PA-24-250 (Serial Nos. 24-2299 & up) and PA-24-260 2117 Fuel System Schematic - PA-24-260 Turbo 2118 Fuel System Schematic - PA-24-400 2120 Bayonet Fasteners 2121 Button Fasteners 2121 Checking Sender Unit 2124 Checking Fuel Gauge 2124 Three Position Fuel Valve - PA-24-180 and PA-24-250 213 Five Position Fuel Valve - PA-24250 and PA-24-260 215 Fuel Valve and Filter - PA-24-400 215 Fuel Strainer Disassembled - PA-24-400 2]7 Bendix Plunger Fuel Pump (Early) 2]9 Bendix Plunger Fuel Pump (Late) 2J9 Exploded View Bendix Rotary Fuel Pump 2712 Primer Pump (Carburetor Induction System) 215 Fabricated Fuel Quantity Transmitter Checking Jig 2J18 Revised: 8/15/98 1A10 PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (continued) Figure No. Subject 9-1. Generator and Starter Wiring System 9-2. Sectional View of Generator 9-3. Wiring Circuit of Three Unit Regulator 9-4. Use of Riffle File to Clean Contact Points 9-5. Voltage Regulator Air Gap Check and Adjustment 9-6. Adjusting Voltage Regulator Settings 9-7. Checking Voltage Setting, Fixed Resistance Method 9-8. Checking Voltage Setting, Variable Resistance Method 99. Cutout Relay Air Gap Check and Adjustment 9-10. Cutout Relay Point Opening Check and Adjustment 9-11. Checking Cutout Relay Closing Voltage 9-12. Adjustment of Cutout Relay Closing Voitage 9-13. Checking Current Regulator, Load Method 9-14. Checking Current Lead Method, Jumnper Lead Method 9-15. Alternator and Starter Wiring System 9-16. Cross Sectional View of Alternator 9-17. Checking Rotor 9-18. Slip Ring End Frame 9-19. Checking Stator 9-20. Checking Diodes 9-21. Brush Holder Assembly 9-22. Exploded View of Heat Sink Assembly 9-23. Checking Alternator Qutput 9-24. Volt-Ohmmeter Test 9-25. Jumper Connection 9-26. Regulator Checks 9-27. Relay Test 9-27a. Exploded View of Alternator 9-27b. Alternator and Starter Wiring System Schematic (Prestolite) 9-27c. Removal of Rectifier 9-27d. Removal of Slip Ring End Bearing 9-27e. Removal of Drive End Head 9-27f. Removal of End Head Bearing 9-27g. Testing Rotor for Grounds 9-27h. Testing Rotor for Shorts 9-27i. Installation of Bearing 9-27]. Installation of Rectifier 9-27k. Terminal Assembly 9-271. Slip Ring End Bearing Assembly 9-27m. Testing Alternator 9-27n. Brush Installation 9-270. Internal Wiring Diagram 9-27p. Regulator Diagram 9-27q. Testing Regulator 9-27r. Application of Overvoltage Control Revised: 8/15/98 1A11 Grid No, 3A13 3A16 - 3A22 3A24 3A24 3B1 3B1 3B1 3B3 3B3 3B4 3B4 3BS 3BS 3B8 3B10 3BI11 3B11 3Bl 3BI12 3B14 3B14 3B15 3B17 3B17 3B18 3B19 3B20 3B22 3B23 3B23 3B24 3B24 3C1 3C1 3C2 3C2 3C3 3C3 3C3 3C4 3C4 3C7 3C8 3C9 PREFACE PIPER COMANCHE SERVICE MANUAL 9-27s. 9-27t. 9-27u. 9-28. 9-29. 9-29a. 9-29b. 9-29c. 9-29d. 9-29e. 9-29f. 10-1. 10-2. 10-3. 10-4. 10-5. 10-6. 10-7. 11-1. 12-1. Wb PREFACE LIST OF ILLUSTRATIONS (continued) Subject Testing Overvoltage Control No-Load Test Lock-Torque Test Not Used. Not Used. Exploded View of Gear Reduction Starting Motor Turning Starting Motor Commutator Testing Motor Armature for Shorts Testing Motor Fields for Grounds No-Load Test Hookup Stall-Torque Hookup Cabin Heater, Defroster and Fresh Air System - PA-24-180 and PA-24-250 (Serial Nos. 24-1 to 24-1251) Cabin Heater, Defroster and Fresh Air System - PA-24-180 and PA-24-250 (Serial Nos. 24-1252 to 24-2298) Cabin Heater, Defroster and Fresh Air System - PA-24-180 and PA-24-250 (Serial Nos. 24-2299 and up) - Cabin Heater, Defroster and Fresh Air System - PA-24-260 (Serial Nos. 24-4000 to 24-4246, 24-4248 to 24-4299) Cabin Heater, Defroster and Fresh Air System - PA-24-260 (Serial Nos. 24-4247, 24-4300 to 24-4782 incl.; 24-4784 to 24-4803 incl.) Cabin Heater, Defroster and Fresh Air System - PA-24-400 Cabin Heater, Defroster and Fresh Air System - PA-24-260 (Serial Nos. 24-4783, 24-4804 and up) Instrument Panel Avionics Antenna Locations NOTE Refer to Electrical Schematics Index at 3D7 ndi Control Cable Inspection Technique External Cable Wear Patterns Internal Cable Wear Pulley Wear Patterns 1A12 - @3C9 3C11 3C12 3C14 3C17 3C17 3C17 3Ci8 3C18 3F9 3F10 3F11 3F12 3F13 3F14 3F15 ‘ 3F24 3H5 1L18 1L18 iL19 1L20 PIPER COMANCHE SERVICE MANUAL Table No, LI II-1 - I-IA o-1 v o-v I-vI I-vin o-vi IH-I V-1 v-II VI VI-II VI-II VI-IV VI-I VII-IT VII-III VHA-I VIA-O VIA-I VIIB-1 VIIB-II VHC-1 VIC-IA VIIC-IT VHI-I VII-II VII-UI VII-IV IX-1 IX-1I IX-1IA X-III IX-1v X-v IX-vi IX-VII XI-1 XI-II X111 XI-IV XI-v Revised: 8/15/98 LIST OF TABLES Subject Engine and Propeller Leading Particulars and Principal Dimensions Recornmended Nut Torques (Inch Pounds) Flare Fitting Torques ’ Indicated Oxygen Cylinder Pressures for Given Ambient Temperatures Inspection Report - Overhaul Time Limits (Oxygen Syst. Components) Troubleshooting Chart (Oxygen Systemn) Recommended Lubricating Oils Decimal Equivalents of Drill Sizes Lubrication (Special Instructions) Inspection Report Control Surface Travel and Tension Troubleshooting Chart (Surface Controls) Torgue For Effective Wrench Length Troubleshooting Chart (Landing Gear and Brake System) Main Gear Wear Limits Nose Gear Wear Limits Propeller Specifications - PA-24-180 Timing Data Troubleshooting Chart (Engine) - PA-24-180 Propeller Specifications - PA-24-250/260 Timing Data Troubleshooting Chart (Engine) - PA-24-250/260 Propeller Specifications - PA-24-400 Troubleshooting Chart (Engine) - PA-24-400 Propeller Specifications - PA-24-260 Turbo . Troubleshooting Chart (Mixture Control Indicator) Troubleshooting Chart (Engine) - PA-24-260 Turbo Specifications, Duke Model 4140-00-218 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 System Schematics Electrical Wire Coding Electrical Symbols Troubleshooting Vacuum System Directional Gyro Indicator Gyro Horizon Indicator Rate Of Climb Indicator Altimeter 1A13 Grid No. 1A17 1B6 - 1B19 1B22 1C13 1C1S 1C18 1C19 1C23 1C24 1D20 1F15 1H5 1323 L5 1L13 1L15 2A19 2B11 2B21 2C14 2D23 2E8 2F1 2G2 2G16 2H2 211 2113 2j14 2J15 2J17 3B16 3D3 3D5 3D6 3D7 3D11 3D12 3E22 3F23 3G6 3G7 3G8 3G9 PREFACE PIPER COMANCHE SERVICE MANUAL Table No. XI-VI XI-VII XI-IX XI-X X1-XI XI-X1I XI-X1V XI-XvV PREFACE LIST OF TABLES (continued) Subject Airspeed Tubes And Indicator Magnetic Compass Manifold Pressure Indicator Tachometer * Engine Oil Pressure Gauge Fuel Pressure Gauge Turn and Bank Indicator Oil Temperature Indicators Fuel Quantity Indicators Fuel Quantity Indicator 1A14 Revised: 8/15/98 ‘ . SECTION 1 INTRODUCTION Paragraph "Aerofiche Grid No 1-1 GeneTal ... e e e IA16 1-3 Scope Of Manual. .. ...t e e et 1Al6 1-7 DIPl OM . ottt ittt e e i e e 1A L6 1-9. 2 1V 1A16 1-10. EmMPennage ..ot e e 1A16 I-11. Fuselage .. ... e 1A16 1-12. Landing Gear .......o.iiuiiiii it e iitn ettt tAl6 1-13. Hydraulic Systems ... ... .. .ottt 1A16 1-14. Engine And Propellers...... .. .. i it tA16 1-15. Fuel System. . .ot i i e e i et 1A17 1-16. Flight Controls ..... ..o i i i i 1A17 1-17 Radio ... .. i e e i e 1A17 I-18. Cabin Heater, Defroster, And Fresh Air System ...................... 1A17 1-19. Instrument And Autopilot Systems. . .........oveviiiiieiineeennnnn.s 1A17 ISSUED: 8/18/72 1A15 PIPER COMANCHE SERVICE MANUAL SECTION 1 INTRODUCTION . 1-1. General. 1-2. This manual contains service and maintenance instructions for the Piper PA-24 Comanche (Figure 1-1), designed and manufactured as a versatile aircraft in the personal and business aviation field, by the Piper Aircraft Corporation, Lock Haven, Pennsylvania. 1-3. Scope of Manual. 1-4. Sections II and ITI comprise the service part of this manual, whereas Sections IV through XTI comprise the maintenance instructions. The service instructions include ground handling, servicing, and inspection. The maintenance instructions for each system include troubleshooting, removal and installation of components, and corrective maintenance and testing; each major system of the aircraft is covered in a separate section 1-5. Only qualified personnel shouid perform the operations described in this manual. 1-6. The description of the aircraft included in this section is limited to general information; however, Figures 1-2 through 1-4 gives specific external dimensions. Table II-II lists the leading particulars and principal dimensions. 1-7. Description. 1-8. The Piper PA-24 Comanche is a four place, (optional 5th and 6th seats are available in the PA-24-260, Serial Nos. 24-4300 and up) single-engine, low-wing monoplane of all metal construction. Paragraphs 1-9 through 1-19 provide descriptions of the major components and systems. 1-9. Wing. The laminar flow wing is of all-metal stressed-skin, full-cantilever, low-wing design, consisting . of two wing panels bolted together at the center of the fuselage. The wing tips are removable. The ailerons are cable and push rod controlled and are statically and dynamically balanced. The trailing edge wing flaps are manually or electrically operated. . 1-10. Empennage. The empennage consists of the fin, stabilators, and stabilator trim tabs. The rudder and stabilators are dynamically and statically balanced. 1-11. Fuselage. The fuselage consists of three basic units: the engine section, the cabin section, and the sheet-metal tail cone. 1-12. Landing Gear. The landing gear is an electrically operated tricycle gear. consisting 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. INTRODUCTION Revised: 8/15/98 ‘ 1A16 PIPER COMANCHE SERVICE MANUAL 1-14. Engine and Propeller. Table I-1. Engine and Propeller. Model Engines Propellers Horsepower Octane PA-24-180 0-360-A1A Hartzell HC-92ZK-8D, or 180 91/96 0-360-A1D McCauley 2D36C14 PA-24-250 0-540-A1A5 Hartzell HC-82XK-1D 250 "91/96 0-540-A1B5 or HC-A2VK-1, or 0-540-A1C5 McCauley 2D36C28 0-540-A1D5 10-540-C1B5 Hartzelt HC-A2VK-1 PA-24-260 0O-540-E4AS Hartzell HC-C2YK-1A 260 91/96 10-540-D4AS or HC-C2YK-1B 10-540-N1A5 Hartzell HC-E2YR-1B PA-24-260 Tutbo 10-540-R1AS5 Hartzell HC-E2YR-1B 260 100/130 or HC-E2YR-1BF PA-24-400 10-720-A1A Hartzell HC-A3VK-4 400 100/130 1-15. Fuel System. The fuel system on the PA-24-180 consists of two rubber cells in the wings, one engine driven pump, and one electrical auxiliary pump. On the PA-24-250 the fuel system is similar, with the exception that there are two electrical auxiliary pumps in addition to the engine driven pump and two auxiliary fuel cells as optional equipment. The fuel system on the PA-24-260 has two fuel cells as standard equipment, two fuel cells as optional equipment, one engine driven pump and two electric auxiliary fuel pumps with carburetor equipped engines or one electric auxiliary pump with fuel injection engines. The PA- 24-400 system consists of four fuel cells, one engine driven pump and one electric auxiliary pump. 1-16. Flight Controls. The flight controls are conventional equipment, consisting of a control wheel which operates the ailerons and stabilators, and pedals which operate the rudder. Duplicate controls are provided for the copilot. 1-17. Radio. Provisions for radio installations consist of microphone and headset jacks and mounting brackets, a loudspeaker, necessary wiring, and panel space for at least four radios. 1-18. Cabin Heater, Defroster, and Fresh Air System. Heater air for the cabin and defroster is obtained directly from the exhaust system muffler shroud. On the PA-24-180 and PA-24-250 fresh air is obtained through intakes at the engine cowl, and an air intake at the top of the fuselage providing air to the individual seats through the air line type overhead vents. On the PA-24-260 and PA-24-400 fresh air is taken from the leading edge of each wing to the forward portion of the cabin and through an intake located on the dorsal fin directing air through overhead vents. 1-19. Instrument and AutoPilot Systems. Provisions for instrument installation include panels for engine instruments and advance flight instruments, as well, as for an AutoPilot system which consists of four principal parts: a modified directional gyro, a modified gyro horizon, a motor-driven actuator, ind an amplifier. Revised: 8/15/98 INTRODUCTION 1A17 THIS PAGE INTENTIONALLY LEFT BLANK 1A18 THIS PAGE INTENTIONALLY LEFT BLANK 1A19 SECTION II ‘ HANDLING AND SERVICING Paragraph Acrofiche Grid No 2-1 TR e 10 L 4T 1 1A22 2-2. DIMNEISTONS & & v vt eeeae e ettt i et et ite e et s aa e aasanean e rsanaas 1A22 2-3. Weight and Balance Data . ... ...t 1A22 2-4. Serial Number Plate . ...ooooriiin i it 1A22 2-5 Access and Inspection Provisions 1A22 2-6. Tools and Test EQuipment .......ooov i iiiineeens 1A22 2-7 Torque REQUITEMENIES ...ttt ean ettt e een e reacnaens 1A23 2-Ta Torque WIenCRES ... .v i\ttt ettt a e e 1A23 2-8 Handhold and WalkWays .. .co.eenerontr et eninteaanearanecaneanerannss 1A23 2-9 Ground Handling. ... cooirini i e e 1A23 2-10 Introduction to Ground Handling ............ ... i, 1A23 2-10a. Torque Wrenches 1BI18 2-1 JACKINE 1 e e ettt i e 1B23 2-12. Weighing . 1823 2-13 Leveling ............ooooit ... 1B24 2-14. MOOTING .« ettt ittt i e Lo Q2 2-15. S ) 1C2 2-16 Locking Airplane 1C3 2-17 T OWITIE £ o o vttt et et e et vt e e 1C3 2-18. TAKIIIZ .+ oot e et eee it et et e 1C3 2-19. External Power Receptacle 1C3 2-20 Operation of External Power Receptacle ...t 1C3 2-21 L1 11T PR RS 1C4 2-22. Cleaning Engine Compartment 1C4 2-23. Cleaning Landing Gear ..................... 1C4 2-24 Cleaning Exterior Surfaces . .......oo i 1C4 2-25. Cleaning Windshield and Windows ..., 1C5 2-26. Cleaning Headliner. Side Panels and Seats ......................0tn 1C5 2-27 Cleaning Carpets ........ovueerieeaneeerireaanrnesnsconnaeinannnas 1C5 2-28. Y o111 R EE 1CS 2-29 INtroduction tO SEMVICING « . v v v v iiii it aaaiicecen e eas 1CS 2-30. Landing Gear SYSIEM ... ovtntnt it e ittt 1C6 2-31 Servicing Landing Gear... 1C6 2-32. Oleo SIrUts oo ovvevvveiennannenns 1Cé 2-23. Servicing Oleo Struts ... vv i 1CA 2-34. FUing Oleo SITULS ...ttt es 105 2-35 Inflating Oleo SITULS ... .iut it e inans 1C8 2-36 Brake SyStem ... .e..iniieinee ettt 1C8 2-37 Servicing Brake SyStem ... ...uoiiut i 1C8 2-38. Filling Brake System Reservoir ........ ..ot 1C8 2-39 Draining Brake System .. ... ... viiiiet i 1C8 2-40 THEES o v et eeeecieri i 1C9 2-41. Servicing Tires .... .. 1C9 2-42, Power Plant . ... ..ottt 1C9 2-43. Servicing Power Plant 1C9 2-44 PrOPeller .ottt e IC10 REVISED: 11/1/82 PIPER COMANCHE SERVICE MANUAL 246. 248. 2-52. 2-54. 2-73. 2-74. 245. ServicingPropeller . . . .. .. ... ... ... .. e, 1C10 Inductiom Air Filger . ... ....... ... .. ... ... it 1C10 2-47. Servicing Induction AirFilter . .. ............ ... ... ... 1C10 Fud System .. ... .. ... ... e et et e e e, 1C10 249. FillingFud Tanks . .. ..........0 00ttt iinnnnnennn. 1C10 2-50. Draining Fuel Valveand Strainers . .. ... ......... ... ... ..., 1C11 2-51. Draining FueiSystem . ........ e e e 1C12 EBlectrical System . . .. .. ... ... i e e e e e 1C12 2-53. Savicing Electrical System . . . .. ...... ... .. i e e 1C12 Xy Pen SYsto . . . . .. ...t eeee 1C12 2-55. Description of OXygen System . . . .. ... .iti et i it i 1C12 256, TroubleshOOBRg . . . . ... e e 1C12 2-57. Oxygen System Safety Precamrions .. ... ..................... 1C12 2-58. Pilling Oxygen Cylinder .. .. ... .......ocnvmvmnnnnnnnannnn. 1c13 2-59. Inspection and Overhaul Time Limirs . .. ... ................... 1C14 2-60. TestingforLesks ... ........ .0 00ttt nnnnenns 1C18 2-61. MAINIERANCE . . . . i e e e e 1C15 2-62. Cleaning Operstions . . .. .. ... v ittt intnn it 1C15. 2-63. Removal of Oxygen Cylinderand Regualtor .. .. ... .. ............ 1C16 2-64. Installation of Oxygen Cylinderand Regulator .. .. ... ............ 1C16 2-68. Removalof FilleValve . . .................... . ... .0 ... 1C17 2-66. Installadonof filler Valve . . . . .. ........ ... ... ... ... ... ... 1C17 267. Removalof Pressure Gamge . . . .. .. ... .. i .ieinnnnnnnannnn 117 2-68. Installadon of Pressure Gauge . . . .. ......... ...t 1C17 2-69. RemovalofOudets . ................... ..o iuvinern.. 1C17 2-70. Installadonof Quders . . . ....... ... ... ... ... . .. 1C17 2-71. Purging OXygen sysem . . . . . .. .. ... e 1C18 2-72. Claningof FaceMasks . . ... .. ... ... ... ... ...t niennnn. 1C18 Lubfication . . .. ... . e e 1C19 Oil Systems (EBGIBE) . . . . v vt e et i e e e 1C19 275, Savicing Ol Systerm . . .. .. ... .. ... e e 1C19 2-76. Draining Ol Sump . .. .................. e 1C19 2-77. Filling Ol Sump . .. ............. it 1C19 2-78. OUSeen (SUCHON) . . .. . v oottt it i it e 1C20 2-79. OilScreen (Pressure) . .. .. ... ...... ... ..t iteninnenn. 1C20 2-80. Qi Flrer (FullFlow) . .. ... .... ... ..ttt 1C21 2-81. Recommendations for ChangingOil . .. ....................... 1C21 2-82. Lubrication Imstructions . . . . .. ... .. ... ... i 1C21 2-83. Applicadonof O . .. ..... ... ... .. ... ... . L L, 1€22 2-84. Applicationof Grease . .. .. ... . ... .. i 1C22 2-85. Lubricagion Chart . .. ... . .. ... .. e 1C22 1A21 PIPER COMANCHE SERVICE MANUAL SECTION I1 . HANDLING AND SERVICING 2.1 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. refertothe 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 11-1 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. 24. Serial Number Plate. (Referto Figure2-6.) Theserial number plate on the various PA-24 modelaircraft 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 Inspection Provisions. The access and inspection provisions for the airplane are shown, 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. CAUTION 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 HANDLING AND SERVICIN! 1A22 PIPER COMANCHE SERVICE MANUAL 2-7. Torque Requirements. The torque values given in Table II-1I are derived from oil-free cadmium-plated threads and are recommended for all airframe installation procedures where torquing is required, unless otherwise noted in sections where other values are stipulated. Engine torque values are found in the latest revision of Avco-Lycoming Service Bulletin No. 268. Propeller torque values are found in Sections VII, VIIA, VIIB and VIIC of this manual. Table [I-1I1A 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 weightsand 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 11-11A. 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 of the fuselage, above the rear 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 1A23 PIPER COMANCHE SERVICE MANUAL | L $° OIMEDRAL ek P8.24-250(24-1 TO 24 - 2298 INCL ) 298 174" PA-24.100 {24-) TO 24 - 2298 INCL.) 296 172" = PA-26 - 18608 250 {24 - 2299 AND UP) 298 5/16° @ CENTERDINE OF THRUS' FIGURE 2-1. THREE-VIEW OF COMANCHE PA-24-180 and PA-24-250 HANDLING AND SERVICING REVISED: 4/3/78 1A24 PIPER COMANCHE SERYICE MANUAL ¢ OIMEDRAL 3 e T Ffl STATIC GROUNDL INE CENTERLINE OF THRUST FIGURE 2-2. THREE VIEW OF COMANCHE PA-24-260 Serial Nos. 24-4000 to 24-4248, 24-4248 to 24-4299 HANDLING AND SERVICING REVISED: 4/3/78 1B1 PIPER COMANCHE SERVICE MANUAL p——— N0 ’/."T 751/4"——0 | — L L ] '—- — \ I ; —_— _‘ | 8 { 8 ‘!e i ; s m— §° OBEDRAL o B 33 178 FIGURE 2-1 THREE-VIEW OF COMANCHE PA-24-260 Serial Nos. 244247, 24-4300 to 24-4782, 24-4784 to 24-4803 incl HANDLING AND SERVICING REVISED: 4/3/78 1B2 PIPER COMANCHE SERYICE MANUAL 282 r—ISO' N mF—I_nJ‘.'__l L "0 ]0] 90[ 03 B STA 63.5° o o:fi 94" a; - ;.ni"_.l § ig 308 & 2 FIGURE 24. THREE-VIEW OF COMANCHE PA-24-400 HANDLING AND SERVICING REVISED: 4/3/78 1B3 PIPER COMANCHE SERVICE MANUAL 38 .8 % .2 FIGURE 2.5. THREE-VIEW OF COMANCHE PA-24-260 Serial Nos. 24-4783, 24-4804 and up HANDLING AND SERVICING REVISED: 4/3/78 1B4 PIPER COMANCHE SERVICE MANUAL FUSELAGE $0TTOM L CovER AT 3 FUEL LE ACLESS PLATE FUSELAGL FLDOR (SEAL) / T \ . ACLTSS PANELS 4 ) e L Q WIKG ACCESS NOLE COVER PATE { ] Z \& ONGNE LEFY ACCLSS PAREL ‘ !!h C it -“\\v“;/'\ 4 ARHT FORWARD ACCESS PANEL LBGEAGL CONPARTIENT 000E ‘\ A L \\v’ YUt puns GEAR TRANSISISSION ACCESS PANEL i ii OR FLLER TaR STHGER FUSELAGE AFT SECTION ACCESS PLATE LUGGAGE COMPARTICERT BACK PLATE 186U s ACCESS PLATE WA FUEL AR . * ABKAURY FOEL TARK ACTESS PLATE ACCESS PATE \\’ srosca 15EALL . 1581} AN FUEL TARE FILLER PUTE 18£41) EMERGENCY SEAR EXTENSHN 7 840 4CCESS PUTE ARERSH BELLCRARK WEPECTION MLATE ENGIRE RGNT ACCESS PAREL Figure 2-6. Access Panels and Plates PA-24-180, PA-24-250 and PA-24-260, Serial Nos. 24-4000 to 24-4246, 24-4248 to 24-4299 HANDLING AND SERVICING REVISED: 4/3/78 1B5 P31 PIPER COMANCHE SERVICE MANUAL TABLE 1I-I. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS . MODEL PA-24-180 PA-24-250 Carburetor Induction ENGINE Manufacturer Avco-Lycoming Avco-Lycoming Model 0-360-A1A or 0-360-A1D O-540-A1AS5; O-540-A1BS, FAA type certificate Rated horsepower, RPM: Full throttle Oil, 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: Deico-Remy, 12 voit Prestolite, 12 volt Generator, Delco-Remy: 12 Voit (35 Amp) 12 Volt (50 Amp) Generator voltage regulator, Delco-Remy 12 volt (35 amp) 12 volt (50 amp) Fuel pump drive 0-360-A1A 0-360-A1D 0-540-A1AS 0-540-A1BS, O-540-A1C5 0-540-A1DS o a N - HANDLING AND SERVICING REVISED: 4/10/81 286 180 HP @ 2700 RPM See Table 11-VI 8 qgts. 91/96 MA-4-5 S4LN-2]! S4LN-20! S4LN-2002 S41.N-2042 25 degrees BTC 0.018 £ 0.006 in. 6) (6) 1-3-2-4 0.5:1 1109689 1101900 1101915 1118704 1119224 Plunger Refer to latest revision of Lycoming Service Instruction No 1042 1B6 0-540-A1C5 or O-540-A1D5 295 250 HP @ 2575 RPM See Table 11-VI 12 qts. 91/96 MA-4-5 S6LN21%, S6LN-214 S6LN-20%, S6LN-214 S6LN-200% S6LN-2045 25 degrees BTC 0.018 £ 0.006 in. 6 (6) 1-4-5-2-3-6 0.5:1 1109511 1101900 1101915 1118704 1119224 Plunger PIPER COMANCHE SERVICE MANUAL TABLE 1I-1. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont.) MODEL ENGINE Manufacturer Model FAA type certificate Rated horsepower, RPM: Full throttle Oil, SAE number Oil sump capacity Fuel, aviation grade, min octane Carburetor, Marvel-Schebler Fuel injector, Bendix Magnetos (2), Scintilla: 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) Alternator, Delco-Remy 12 volt (70 amp) Alternator voltage regulator, Delco-Remy Alternator overvoliage relay, Delco-Remy Alternator, Prestolite 12 volt (70 amp) Alternator voltage regulator, Prestolite Alternator overvoltage relay, Prestolite Fuel pump drive PA-24-250 Fuel Injected Avco-Lycoming 10-540-C1B5 1E4 250 HP @ 2575 RPM See Table 1I-1V 12 qts. 91/96 RSA-5AD! S6LN-200 S6LN-204 25 degrees BTC 0.018 £ 0.006 in. (6) (6) 1-4-5-2-3-6 0.5:1 1109511 1101900 1101915 1118704 1119224 Plunger & Refer to latest revision of Lycoming Service Instruction No 1042 -1B7 PA-24-260 Carburetor Induction Avco-Lycoming 0-540-E4AS 295 260 HP @ 2700 RPM See Table I1-1V 12 qts. 91/96 MA-4-5 S6LN-200 S6LN-204 25 degrees BTC 0.018 £ 0.006 in. 6 (6) 1-4-5-2-3-6 0.5:1 1109511 MZ-4206 1100660 or 1100717 9000590 1115831 Plunger HANDLING AND SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE 1I-1. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont.) . MODEL PA-24-260 PA-24-260 Fuel Injected - Serial Nos. Fuel Injected - Serial Nos. 24-4783, 24-4804 and up 24-4000 to 24-4782, 24-4784 10 24-4803 inclusive ENGINE Manufacturer Avco-Lycoming Avco-Lycoming Model 10-540-N1AS 10-540-D4AS FAA type certificate 1E4 1E4 Rated horsepower, RPM: Full throttle Oil, SAE number Oil sump capacity Fuel aviation grade: Minimum octane Carburetor, Marvel-Schebler Fuel injector, Bendix Magnetos (2), Scintilla: Left Right Magneto timing Magneto point clearance Spark plug (shielded): Spark plug gap setting: Firing Order Tachometer drive, ratio to crankshaft Starter: Delco-Remy, 12 volit 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) Alternator, Delco-Remy 12 volt (70 amp) Alternator voltage regulator, Delco-Remy Alternator overvoltage relay, Delco-Remy Alternator, Prestolite 12 volt (70 amp) Alternator voltage regulator, Prestolite Alternator overvoltage relay, Prestolite Fuel pump drive 260 HP @ 2700 RPM See Table 11-1V 12 gts 91/96 RSA-5ADI S6LN-200 S6LN-204 25 degrees BTC 0.018 £ 0.006 in. (6) 6) 1-4-5-2-3-6 0.5:1 MZ-4206 ALX842] VSF7203 X17621 Plunger 6 Refer to latest revision of Lycoming Service Instructions No 1042 1B8 260 HP @ 2700 RPM See Table 1I-1V 12 qts. 91/96 RSA-5ADI S6LN-200 S6LN-204 25 degrees BTC 0.018 + 0.006 in. 6 (6) 1-4-5-2-3-6 0.5:1 1109511 MZ-4206 1100660 or 1100717 9000590 1115831 Plunger HANDLING AND SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE II-1. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont.) MODEL ENGINE Manufacturer Model FAA type certificate Rated horsepower, RPM: Full throttle Oil, SAE number Oil sump capacity Fuel aviation grade: Minimum octane Carburetor, Marvel-Schebler Fuel injector, Bendix Magnetos (2), Scintilla: 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 volts 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) Alternator, Delco-Remy 12 volt (70 amp) Alternator voltage regulator, Delco-Remy Alternator overvoltage relay, Delco-Remy Alternator, Prestolite 12 volt (70 amp) Alternator voltage regulator, Prestolite Alternator overvoltage relay, Prestolite Fuel pump drive PA-24-260 Turbo Avco-Lycdming 10-540-R1AS 1E4 260 HP @ 2700 RPM See Table 11-VI 12 qts 100/130 RSA-5ADI S6LN-1209 S6LN-1208 25 degrees BTC 0.016 + 006 in. (6) (6) 1-4-5-2-3-6 0.5:1 MZ-4206 ALX8421 VSF 7203 X17621 Lear Seigler RG-17980 6 Refer to latest revision of Lycoming Service [nstruction No 1041 1B9 PA-24-400 Avco-Lycoming 10-720-A 1A 1E15 400 HP @ 2650 RPM See Table 11-V1 17 qts 100/130 RSA-10AD! S8LN-701 S8LN-705 20 degrees BTC 0.019 £ 0.001 in. (6) (6) 1-5-8-3-2-6-7-4 0.5:1 1113471 1100660 or 1100717 9000590 1115831 Lear Seigler RG-17980 HANDLING AND SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont.) MODEL 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 PA-24-180 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 2550 1bs. 2550 1bs 9 Serial Nos 24-1. 24-103 10 24-2002 inc! 24-2004 to 24-2298 incl 10 Serial Nos 24-2003. 24-2299 and up PA-24-250 Two 30 U.S. gal 2 U.S. gal Two 15 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, 6 ply rating 27 psi 42 psi 2800 Ibs ? or 2900 1bs 10 2800 1bs % or 2900 lbs 10 HANDLING AND SERVICING REVISED: 4/10/81 1B10 PIPER COMANCHE SERVICE MANUAL TABLE 11-1 PARTICULARS AND PRINCIPAL DIMENSIONS (cont.) MODEL FUEL SYSTEM Inboard (main) fuel celis Capacity (each) Unusable fuel (each) Outboard (auxiliary) fuel cells Capacity (each) Unusable fuel (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 11 Serial Nos 23-3642 24-3000 10 24-4246 incl 12 Serial Nos 24-4247, 23-4300 to 24-47%2 incl PA-24-260 Serial Nos. 24-2400 to 24-4782, 24-4784 to 24-4803 inclusive Two 30 U.S gal 2US gal Two 15US. 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 40-84 Cleveland 30-41 6.00 x 6. 4 ply rating 6:00 x 6. 6 ply rating 27 psi 42 psi 2900 tbs ! or 3100 Ibs 2 2900 1bs '! or 2945 lbs 12 24-424K 1o 24-4299 incl 24-4744 1o 24-4803 inct PA-24-260 Serial Nos 24-4783, 24-4804 and up Two 30 U.S gal 2US. gal Two 15US. gal Electrically operated Combination air and oil MIL-H-5606 2.75 in. Nose. 2.50 in Main 9ft 8in. 6ft 6.62in Left 20°, Right 20° Cleveland 38501 Cleveland 40-84 600 x 6, 4 ply rating 600 x 6. 6 ply rating 27 psi 42 psi 3200 Ibs. 3040 lbs HANDLING AND SERVICING 1B11 REVISED: 4/106/81 PIPER COMANCHE SERVICE MANUAL TABLE [I-1 LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont ) MODEL FUEL SYSTEM Inboard (main) fuel cells " Capacity (each) Unusable fuel (each) Outboard (auxiliary) fuel cells Capacity (each) Unusable fuel (each) LANDING GEAR Type Shock strut type Fluid required (strust 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 P A-24-400 Two 30 US. gal 3 US. gal Two IS5US 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 Nos. 26-2 to 26-129 incl. Cleveland 30-23 Serial Nos. 26-130 and up 600 x 6, 6 ply rating 6 00 x 6, 6 ply rating 42 psi 42 psi 3600 1bs. 3600 Ibs. HANDLING AND SERVICING 1B12 REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE [I-1. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont.) MODEL PA-24-180 PA-24-250 Carburetor Induction PROPELLER Manufacturer McCauley or Hartzell McCauley or Hartzell Type Constant speed (two blades) Constant speed (two blades) Hub model, McCauley 2D 36C 14 2D 36C28 Hartzell HC-92ZK8D HC-82XK 1D or HC-A2VK-1 Blade model, McCauley D-2101;78KM-4 D-2286; 80MM-6 Hartzell 8447A-12A VB433N-7 Diameter. McCauley 74 in. 74 in, Hartzell 72 in. 77 in. Diameter, min , McCauley 72in. 73 in. Hartzell 70.5 in. 76 in. Blade Angle (low pitch)’, McCauley 12.7° £ 0.2° 15.7° £ 0.2° Hartzell 13° 14.5° £ 0.15° Blade Angle (high pitch)’, McCauley 27 5° 32° £0.5° Hartzell 27° 31° to 33° Control governor Woodward or Haruzell Woodward or Hartzell Governor model, Woodward 210305 A210305 Hartzell D (-5 B-4-2 7 Blade Angle at 30 in Radius HANDLING AND SERVICING REVISED: 4/10/81 I 1B13 PIPER COMANCHE SERVICE MANUAL TABLE 1I-I. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont) MODEL PROPELLER Manufacturer Type Hub model, McCauley Hartzell Blade model, McCauley Hartzell Diameter, McCauley Hartzell Diameter, min.. McCauley Hartzell Blade Angle (low pitch)’, McCauley Hartzell Blade Angle (high pitch)’, McCauley Hartzell Control governor Governor model, Woodward ' Hartzell 7 Blade angle at 30 in radius PA-24-250 Fuel Injected Hartzell Constant speed (two blades) HC-A2VK-t VB433N-7 77 in. 76 in. 14.5° £ 0.15° 31° to 33° Hartzell A210305 B-4-2 PA-24-260 Carburetor Induction and Fuel Injected - Serial Nos 24-4000 to 24-4782, 24-4784 to 24-4803 incl. Hartzell Constant speed (two blades) HC-C2YK-1A or HC-C2YK-IB 8467-7R 77int® 75 in. 15° 32° 10 34° ' Hartzell F-4-4 or F-4-4A ‘ 8 If it becomes necessary 1o reduce the propeller diameter beiow 77 inches. for maintenance rebalancing purposes. a placard stating "Avoid continuous operation between 2500 and 2600 rpm above 25 inches manifold pressure™ must be displayed near the manifold pressure gauge HANDLING AND SERVICING 1B14 REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE I1-1. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont) MODEL PROPELLER Manufacturer Type Hub model, McCauley Hartzell Blade model, McCauley Hartzell Diameter, McCauley Hartzell Diameter, min., McCauley Hartzell Blade angle (low pitch)’ McCauley Hartzell Blade angle (high pitch)’ McCauley Hartzell Control governor Governor model, Woodward Hartzell PA-24-260 Fuel Injected - Serial Nos. 24-4783, 24-4804 and up Hartzell Constant speed (two blades) HC-E2YR-1B 8467-7R 77 in. 75 in. 15° 32° to 34° Hartzell F-4-4A CONTROL SURFACE TRAVELS CONTROL SURFACE CABLE TENSIONS 7 Blade angle at 30 in radius 1B15 PA-24-260 Turbo Hartzell Constant speed (two blades) HC-E2YR-1B or HC-E2YR-1BF 8467-7R 77 in. 75 in. 13.5° +.3°/-.0° 32° to 34° Hartzell F-4-4A Refer to Section V. PA-24-400 Hartzell Constant speed (three blades) HC-A3VK-4 V8433-7 77.25 in. 75.25 in. 14° 36° Hartzell F-4-1 HANDLING AND SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL WG ACCESS HOLE COVER PLATE TAL STINGER: e EWGBIE LEFT ACCESS PAMEL > LEFT FORWARD ACCESS PANEL REAR BAGGAGE FLOORBOARD D ANimatie Pich Servo! CENTER FLOORROARD & ( ROGHT FORWARD ACCESS PANEL " G REAR B0 2N o P 2080 gAY PN N LEFT REAR BOX ‘ OR FILLER . ~ 1y ACTESS PLATE Z y S g ) FUSELAGE AFT SECTION ACCESS PLATE GEAR TRANSMISSION ACCESS PAMEL \-J 1SEAL} J ABXIIARY RUEL TAMK ACEESS PLATE . ISEAL . NAB FUEL TARK ACCESS PLATE DNERLINCY SEAR EXTENSION 7 ISEAL| </ MAM FUEL TAMK FILER PLATE ENGME BEAT ACCESS PAEL \\ {SEAL) ALERON BELCIA WSPECTION PLATE Figure 2-7. Access Panels and Plates PA-24-260, Serial Nos. 24-4247, 24-4300 and up HANDLING AND SERVlClNG. REVISED: 4/3/78 1B16 PIPER COMANCHE SERVICE MANUAL 2849 TAR STRGER FUSELAGE AFT SECTION ACCESS PLATE: LOGEAGE COMPARTMENT BACE PLATE LUSBAGE COMPARTMENT DBOR GEAR TRANSISISSION ACCESS PAREL ISEaL| AUKILIARY FUEL TASNR ACCESS PLATE ISEAL FOSELAGE DOTTON COvER PUATE FUEL {mE ACCESS PLATE FUSELAGE FLOOR ACCESS PARELS AR FUEL TAMR Q ACCESS PATE isea| AN FREL T FILLER MATE ISEAL| ALERON SELLCAML NSPECTION PLATE (SERL| = / = — WINE ACCESS NOLE COVER PLATE ENGRIE LEFT ACCESS PANEL —LEFT FORWARD ACCESS PAREL IAnmatic Piica Serva] RIGHT FORWARD ACCESS PAREL FutL Pop on Fifl ACCESS PLATE EMERGERCY GEAR EXTENSIOR OAR ACCESS PUATE ENGIE DIGHT ACCESS PAREL Figure 2-8. Access Panels and Plates PA-24-400 1B17 HANDLING AND SERVICING REVISED: 4/3/78 PIPER COMANCHE SERVICE MANUAL 2-10a. TORQUE WRENCHES. Torque wrenches should be checked daily and calibrated by means o. 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. 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. Followingis theformulato 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 wrench or listed for that model wrench. B =Llength of adapter extension. center of bolt to center of shank. C =Scale reading needed to obtain desired torque (T). The formula: C=AXxT EXAMPLE A bolt requires 30 foot-pounds and a 3 inch adapter (one-quarter of a foot or 257 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=1x300rC=30=24ft-lbs 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 A933 Figure 2-8a Torque Wrench Formula . REVISED: 11/1/82 HANDLING AND SERVICING 1B18 PIPER COMANCHE SERVICE MANUAL TABLE 1I-Il RECOMMENDED NUT TORQUES (INCH-POUNDS) TORQUE REQUIREMENTS: 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 nuts 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. Torque (self-locking fasteners) - Add the friction torque from Chart A for sizes 8 through 7/ 16 to 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 givenin Chart B. Unless other- wise specified. when casteilated 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 GENERAL REQUIREMENTS: -0 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 1o tightening, the torque range should be reduced 50 percent. Use 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. Unique 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 AN960 washers may be added under the bolt heads or nuts to correct for variations in material thickness within the tolerances permitted Limitations of the use of self-locking nuts. bolts and screws including fasteners with non-metallic inserts are as follows* 1. 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. 2 Bolts 5/16 inch diameter and over with cotter pin holes may be used with self-locking nuts. Nuts with non-metallic locking devices may be used in this application only if the boits are free from burrs around the cotter pin hole. Do not use self-locking nuts at joints which subject either the nut or the boit to rotation. 4 Never tap or rethread self-locking fasteners. Do not use nuts, bolts or screws with damaged threads or rough ends. ‘22 REVISED: 11/1/82 HANDLING AND SERVICING 1B19 PIPER COMANCHE SERVICE MANUAL TABLE 11-]l RECOMMENDED NUT TORQUES (INCH-POUNDS) (cont.) mu_u. CHART A BOLT FRICTION DRAG SIZE_ | TORQUE (INLBS ) 8 15 10 18 1/4 30 5/16 60 3/8 80 7716 100 *APPLICABLE TO COARSE THREADS ONLY REVISED: 11/1/82 1B20 CHART B COARSE THREAD SERIES BOLTS Steel Tension AN 3 thru AN 20 AN 42 thru AN 49 AN 73 thry AN 81 AN 173 thru AN 186 MS 20033 thru MS 20046 MS 20073 MS 20074 AN 508 NK9 MS 24694 AN 525 NK525 MS 27039 NUTS Steel Tension Steei Shear AN 310 AN 320 AN 316 AN 364 AN 363 NAS 1022 AN 365 MS 17826 NAS 1021 MS 20364 MS 17825 MS 21045 MS 20365 MS 20500 NAS 679 Nut-bolt Torgue Limits Torgue Limits size in-lbs in-lbs Min Max Min Max 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 9% 110 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 1,150 | 1,600 700 950 7/8- 9 2,200 | 3,000 | 1,300 | 1,800 1 -8 3,700 | 6,000 | 2200 | 3,000 1-1/8-8 5,500 | 6,500 | 3,300 | 4,000 1-1/4-8 6,500 | 8,000 | 4,000 | 5,000 HANDLING AND SERVICING PIPER COMANCHE SERVICE MANUAL . TABLE [I-Il RECOMMENDED NUT TORQUES (INCH-POUNDS) (cont) FINE THREAD SERIES BOLTS BOLTS BOLTS Steel Tension Steet Tension Aluminum AN 3 thru AN 20 MS 20004 thru MS 20024 AN 3DD thru AN 200D AN 42 thru AN 49 NAS 144 thru NAS 158 AN 173DD thru AN 186DD AN 73 thru AN 81 NAS 333 thru NAS 340 AN S080D AN 173 thru AN 186 NAS 583 thru NAS 530 AN 526D MS 20033 thru MS 20046 NAS 624 thru NAS 644 MS$ 270390 MS 20073 NAS 1303 thru NAS 1320 MS 2469400 MS 20074 NAS 172 AN 508 NK9 NAS 174 MS 24694 NAS 517 AN 525 NK525 Steel shesr bolt MS 27039 NAS 464 NUTS NUTS NUTS Steel Tension Steel Shear Steel Tension Steel Shear Alum Tension Alum Shear AN 310 AN 320 AN 310 AN 320 AN 365D AN 320D AN 315 AN 364 AN 315 AN 364 AN 3100 AN 364D AN 383 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 20365 . MS 21045 MS 21045 MS 20365 NAS 1021 MS 20500 NAS 679 NAS 679 NAS 1291 Nut-bolt Torque Limits Torque Limits Torque Limits Torque Limits Torque Limits Torque Limits size in-ibs in-lbs in-lbs in-lbs - in-ibs in-lbs Min Max Min, Max Min Max Min Max Min Max Min, Max 8 -36 12 15 7 9 5 10 3 6 10 -32 20 25 12 15 25 30 15 20 10 15 S 10 1/4-28 50 70 30 40 80 100 50 60 30 45 15 30 5/16—24 100 140 60 85 120 145 70 90 40 65 % 40 3/8-24 160 190 95 110 200 250 120 150 75 110 45 70 7/16-20 450 500 270 300 520 630 300 400 180 280 110 170 1/2-20 480 690 290 a0 770 950 450 550 280 410 160 260 9/16-18 800 | 1,000 480 600 1,100 [ 1.300 650 800 380 580 230 360 5/8—18 1,100 | 1,300 660 780 1,250 | 1,550 750 950 550 670 270 420 416 2,300 ( 2500 | 1.300 | 1,500 2,650 | 3.200 | 1,600 | 1900 950 | 1,250 560 880 7/8-14 2,500 | 3,000 [ 1,500 | 1.800 3,550 | 4,350 | 2,100 | 2,690 1,250 | 1,900 750 | 1,200 g 1 -14 3,700 | 4,500 | 2,200 | 3,300 4500 | 5500 | 2,700 [ 3,300 1,600 | 2,400 950 | 1,500 8 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 E 1-1/4-12 9,000 | 11,000 | 5400 | 6,600 | 11,000 | 13,400 | 6,600 | 8,000 3,900 | 5600 | 2,300 | 3,650 o REVISED: 11/1/82 HANDLING AND SERVICING 1B21 PIPER COMANCHE SERVICE MANUAL TABLE II-HA. FLARE FITTING TORQUES 1B22 TORQUE - INCH-POUND TUBING ALUMINUM - ALLOY STEEL TUBING HOSE END FITTING oD TUBING FLARE - AND FLARE AND INCHES 10061 OR AND 10078 AND 10061 HOSE ASSEMBLIES MINIMUM MAXIMUM | MINIMUM MAXIMUM | MINIMUM MAXIMUM 18 - - - - . - 3116 . - %0 100 70 100 1/4 40 65 135 150 70 120 5/16 60 80 180 200 85 180 /8 75 125 270 300 100 250 112 150 250 450 500 210 420 5/8 200 350 650 700 300 480 3/4 300 500 900 1000 500 850 1 500 700 1200 1400 700 1150 1-1/4 600 900 - - - . 11172 600 900 - - . . 1-3/4 - - - - . - 2 - - - - . - HANDLING AND SERVICING Added: 4/10/81 PIPER COMANCHE SERVICE MANUAL FIGURE 2-9. JACKING ARRANGEMENTS 2-11. Jacking. The airpiane is provided with a jack pad on each main spar just outbosrd of the main landing gear and support position by making use of the tail skid. (Refer to Figure 2-9.) To jack the airpiane, proceed as follows: 2 Place the jacks under the jack pads. b. Attach the il support to the il skid. Place approximately 400 pounds of ballast on the support 10 hold the tail down. - CAUTION Be sure 1o apply sufficient tail support bailast: otherwise the airplane will dp forward and fall on the fuselage nose secton. ¢ Raise the jacks evenly undl all three wheels ciear the floor. 2-12, Weighing. (Refer to Figure 2-10.) 2. Block the main gear oleo struts in there fully extended position and the nose gear at 2.50 inches extension. Inflate all tires to the required pressures, (Refer to Table i1-1.) b. Place the zircarft on three individyal scales by positioning 2 ramp of the same height as the scales being used in front of each landing gear wheel. Position the scales in front of the ramps and tow the aircraft onto the scales. (Refer to Paragraph 2-17 for towing procedures.) Remove the ramps so they will not interfere with the scales. Level the aircraft per instructions given in Paragraph 2-13. ¢ Proceed to weigh the aircraft in accordance with instructions given in manual AC 43.13-1A. HANDLING AND SERVICING REVISED: 4/3/78 1B23 PIPER COMANCHE SERVICE MANUAL FIGURE 2.10. WEIGHING 2-13. Leveling. (Refer to Figure 2-11 and 2-12.) The aircraft may be leveled while on jacks or during the weighing procedure. (Refer to Paragraph 2-12 for weighing.) i To longitudinally level the aircraft, partially withdraw the two leveling screws on the side of the fuselage. Refer to Figures 2-11 or 2-12 for the leveling location on the particular aircraft being serviced. Use a level long cnough to extend accross the two screw heads. b. To put the aircraft on jacks, refer to Paragraph 2-11. ¢ To put the aircraft in 2 longitudinaily level position for weighing or rigging, first block the main gear oleo struss to their full extension and the nose gear to 2.50 inches. NOTE All dres should be az normal infladon pressure. Deflate the nose wheel tire until the level position is obuained. d. To laterally level the aircraft, piace a level aver the bulkhead to which the baggage door hinge brackets are attached or on the hat section channel of the firewall bulkhead. (Refer w Figures 2-11 or 2-12 for the particular location of the aircraft being serviced.) Should equipment or other obstacles hinder placing the level directy on the channel, use two spacers of equal length between the level and the channel to bring the level above any obstacles. e To put the aircraft into a laterally level position, raise or lower one wing by adjusting the jacks or if the aircraft is on the ground or on scales by deflating the appropriste tire until an accurate level reading is obtained. HANDLING AND SERVICING REVISED: 4/3/78 1824 PIPER COMANCHE SERVICE MANUAL AlLTe AlT? Longitudinally Laterally FIQURE 2-11. LEVELING AIRPLANE PA-24-180, 250, 260, Serial Nos. 24-4000 to 24-4246, 24-4248 10 24-4299 and PA-24-400 Al29 AR Longitudinally Laterally FIGURE 2-12. LEVELING AIRPLANE PA-24-280, Serial Nos. 24-4247, 24-4300 and up HANDLING AND SERVICING ADDED: 4/3/78 1C1 PIPER COMANCHE SERVICE MANUAL 2-14. Mooring. The airplane should be moored to insure its immovabiliry, protection and security under various wether conditions. The following procedure gives the instructions for proper mooring of the airplane. 2. Head the airplane into the wind, if possibie. b. Lock the aieron and smbilator controls using the front seat belt or conerol surface blocks. ¢ Block the wheels. : o d. Secure tie-down ropes to the wing te-down rings and the tail skid at approximately 45-degree angies to the ground. Leave sufficient slack to avoid damage to the aircraft when the ropes conauct due to moisture. CAUTION Use square or bowline knots. Do not use slip knozs. NOTE Additional preparatons for high winds include using tiedown ropes from the landing gear forks, and securing the rudder. e. Install pitot tube cover, if possible. 2-15. Parking. When parking the airplane, insure that it is sufficiendy protected against adverse weather conditions and presents no danger to other aircraft. When parking the airplane for any length of dme or overnight, it is recommended that it be moored as in Paragraph 2-14. 2. To park the airplane, head it into the wind, if possibie. b. Set the parking brake by applying tow pressure against the top of the brake pedals or pull back on the brake lever and at the same dme pull ourt on the brake “T™ handle, locared at the left of the coatrol panel. To release the parking brake, apply toe pressure on the pedals and push in on the parking brake bandie. : NOTE To prevent damage to brake drum, care should be taken when serting brakes that are overheated or during cold weather when accumulated moisture may freeze the brake. HANDLING AND SERVICING REVISED: 4/3/78 162 PIPER COMANCHE SERVICE MANUAL 2-16. Locking Airplane. The cabin and baggage doors are provided with a key lock. The same key can be used to operare both door locks. 2-17. Towing. The airpiane may be moved by using the nosc wheel towing/steering bar provided, or power equipment char will not damage or cause excess strain to the nose gear assembly. On PA-24-180, 250 and 260 aircraft with Serial Numbers 244000 to 244246, 244248 to 244299 and PA-24-400 the steering bar is stowed on the underside of the hatshelf in the baggage compartment. On PA-24-260 Seriai Numbers 24-4247, 24-4299 and up it is axached to the forward section of the main spar cover. CAUTION When towing with power equipment, do not turn the nose gear beyond it 20 degrees in cither direction from center, as this will resultin damage to the nose gear and steering mechanism. 2-18. Taxiing Before arrempting to taxi the airplane, ground persoonel should be checked our by a qualified pilot or other responsible person. Engine starting and shut-down procedures should be covered as well. When it is scertained thae the propeller back blast and taxi areas are clear, apply power to start the taxi roll and perform the following checks: 3. Taxi forward a few feer and apply brakes to determine their effectiveness. b. Taxi with propeller set in low pitch, high RPM setxing. c. While taxiing, make slight turns to ascertain the effectiveness of steering. d. Observe wing clearances when taxiing near buildings or other stationary objects. If possible, station a guide ouwide the sirpiane w observe. e. When taxiing on uneven ground. look for holes and ruts. f Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel or any loose material that may cause damage to propeiler blades. 2-19. External Power Receptacie. 2-20. Operation of External Power Recepmbie. The external power receptacie on PA-24-180, 250 and 260 airplanes with Serial Numbers 24-2299 o 24-4246 inciusive, 244248 to 24-4299 inclusive and PA-24-400 Serial Numbers 26-2 and up, is located on the right side of the fuselage aft of station 157. On PA-24-260 airplane with Serial Numbers 244247, 244300 to 24-4804 and up, it is located on the right side of the engine nacelle just forward of the firewall. When using the external power recepracie for starting or operation of any airplane equipment, place the master switch in the OFF position before inserting or removing the power plug. The power connector piug assembly is stored in the baggage compartment. HANDLING AND SERVICING REVISED: 4/3/78 163 PIPER COMANCHE SERVICE MANUAL 2-21. Cleaning. 2-22. CGesning Eagine Compartment. Before cleaning the engine compartment, pisce & strip of tape on the Magneto vents to prevent any solvent from entering these units. o Place a large pan under the engine to catch waste. b. With the engine cowling removed, spray or brush the engine with solvent or a mixture of soivent and degreaser, as desired. It may be necessary to brush areas that were sprayed where heavy grease and dire deposits have collected in order to clean them. CAUTION Do not spray solvent into the generator or alternator, smrter, or air intakes. c. Allow the solvent to remain on the engine from five to ten minutes, then rinse the engine clean with additional solvent and allow to dry. CAUTION Do not operate engine until excess solvent has evaporated or otherwise been removed. d Remove the protective covers from the magnetos. e Lubricate controls, besring surfaces, etc., per Lubrication Chart, Figure 2-20 thru 2-22, 2-23. Qaning Landing Gear. Before cleaning the landing gear, place a plastic cover or similar material over the wheel and brake assembly. 2 Place a2 pan under the gear to catch waste, b. Spray or brush the gear area with solvent or a mixture of solvent and degreaser, as desired. It may be necessary to brush areas that were sprayed where heavy gresse and dirr deposics have coilected in order to clean them. ' ¢. Allow the solvent to remain on the gear form five to ten minutes, then rinse the gear with additional solvent and allow to dry. d Remove the cover from the wheel and remove the catch pan. e Lubricate the gear per lubrication Chart, Figure 2-21. 2-24. Cleaning Exwmrior Surfaces. The airplane should be washed with 2 mild soap and water. harsh abrasive or alkaline soaps or detergners used on painted or plastic surfaces could make scratches or cause corrosion of metal surfaces. Cover areas where cleaning soludon could cause damage. to wash the airplane, the following procedure may be used: CAUTION When hosing down aircraft avoid directing water in the fuel tank vents. drain tubes and around the sealed cover piates and filler cap access openings. HANDLING AND SERVICING Revised: 9/10:79 1C4 PIPER COMANCHE SERVICE MANUAL Flush away loose dirt with water. Apply cleaning solution with a rag, sponge or soft bristle brush. To remove stubborn oil and grease, use a cloth dampened with naptha. 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 cleamng or polishing. A heavier coating of wax on the leading surfaces will reduce the abrasion problems in these areas. acowm 2-25. Cleaning 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. Toimprove 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. Cleaning 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 Servicing. 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 1C5 PIPER COMANCHE SERVICE MANUAL 2-30 Landing Gear System. ‘ 2-31 Servicing Landing Gear. The landing gear consisting of tires. brakes. oleo strut assembly. drag links. down locks and gear doors should be visually inspected 1o determine proper strut extension. possible hydraulic fluid 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 *2.2% for PA24-100 . FIGURE 2-13. LANDING GEAR STRUT (EXPOSURE) 2-32. Oleo Struts. 2-33. 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 setties 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. WARNING Deflate strut air pressure before disassembly REVISED: 4/3/78 HANDLING AND SERVlCIN! 1Cé6 PIPER COMANCHE SERVICE MANUAL 2-34. Filling Oleo Struts. To fill the nose or main gear oleo sorut with fluid (MIL-H-5606), whether it be only the addition of a small amount or if the unit has been complietely emptied and will require a large amount, it should be filled as follows: WARNING Do not rclease air by removing the swut valve core or filler plug. Depress the valve core pin undl strut chamber pressure has diminished. CAUTION Dirt and foreign particles form around the fller piugs of the landing gear struts, therefore, before aremnpting to remove these plugs, the tops of the struts should be cleaned with compressed air and/or with a dry type solvent. a Place the airplane on jacks. (Refer to Jacking, Paragraph 2-11.) b. Plsce a pan under the gear to catch spillage. c. At the filler plug, relieve air pressure from the struc housing chamber by removing the cap from the air valve and depressing the valve core. d There are two methods by which the strut chamber may be filled and these are as follows: First Method: 1. Remove the valve core from the filler plug ar the cop of the nose gear strut housing or at the top inboard side of the main gear housing. Allow the filler plug to remain installed. 2. Atnach one end of a clean plastic hose to the valve stem of the filler plug and submerge the other end in a conmainer of hydraulic fluid. NOTE An air-dght connection is necessary between the plastic tube and the valve stem. Without such a connection, a small amoune of air will be sucked into the oleo strut during each sequence, resuiting in an inordinsre amount of air bubbles and a prolonged filling operation. 3. Fuily compress and extend the sgrut thus drawing fluid from the fluid conminer and expelling air from the strut chamber. By watching the fluid pass through the plastic 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 through the hose. compress the strut fully and remove the hose from the valve stem. 5. With the strut compressed, remove the filler plug to determine that the fluid level is visible up to the bottom of the filler hole. HANDLING AND SERVICING REVISED: 4/3/78 167 PIPER COMANCHE SERVICE MANUAL 6. With the oleo strut fully compressed. reinstall the core in the filler plug and the plugin the slr‘ | 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. 3 Pour fluid from a clean container through the filler opening until it reaches the bottom of the 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. Inflating 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 the strut down to the proper extension.) Before cappingthe valve. 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 V1. 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 11-1. 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 HANDLING AND SERVICHQ 1C8 PIPER COMANCHE SERVICE MANUAL FIGURE 2-14. BRAKE RESERVOIR FIGURE 2-15. BRAKE RESERVOIR PA-24-180 and PA-24-250, Serial PA-24-180 and PA-24-250, Nos. 24-1 to 24-2298 inclusive Serial Nos. 24-2299 and up, PA-24-260 and PA-24-400 2-40 Tires. 2-41. Servicing Tires. The tires should be maintained at the pressure specified in Table 11-1 When checking tire pressure. examine the tire for wear. cuts. bruises and slippage. 2-42 Power Plant. 2-43 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 VIIC of this manual and in the appropriate manufacturer's manuals REVISED: 4/3/78 HANDLING AND SERVICING 1C9 PIPER COMANCHE SERVICE MANUAL 2-44. Propeller. 2-45. Servicing Propeiler. The propeiler blades, spinner and visible bub surfaces should be cleaned and inspected frequenty for damage, cracks and oil leakage. Nicks thould be removed from the leading edgé of the blades in accordance with applicable FAA regulations or instructions found in Sections VIl thra VIIC. The face of each blade should be paineed when necessary with a flac paint to rewrd glare. To prevent corrosion, wipe surfaces with a light oil or wax. The blades shoule be checked that they turn freely on the hub pilot tube by rocking the biades back and forth through the slight freedom allowed by the pitch change mechanism. Lubricate the propeller at 100 hour intervals in accordance with the Lubrication Chart, Figures 2-20 thru 2-22. Ascertain propeller is charged w the proper chamber pressure. Additional service information for the propeller may be found in Sections VIl thru VIIC. 2446. Induction Air Filter. 247. Servicing Induction Air Filter. Due to the variety of power plant used on the various PA-24 model sirplanes, refer to the Power Plant Section (V1 thru VIIC) for the particular induction airfilter being serviced. 2-48. Fusel Systems 249. Filling Fuel Tanks. Observe all required precautions for handling gasoline. Fill the fuel tanks with fuel specified in Table [I-l. On the PA-24-180, to obuain the standard fuel quandry of 50 gallons total, or 25 gallons per tank, the cells are filled only 10 the bettom of the filler neck, which extends into the fuel cell about 1 inch. To obtain the standard plus reserve quantity of 60 gallons, the cells are filled to the top of the filler neck. On the PA-24-250 and PA-24-260, to obmin the standard fuel quantry of 60 gallons total, or 30 gallons per tank, the fucl cells are completely filled. If auxiliary fuel cells are installed (15 gal. ea.) the fuel quantdcy is increased to 90 gallons. On the PA-24-400, to obuin saandard fuel quantity of approximarely 100 gallons, fill both inboard cells complezely and the outboard cells until fuel appears at the bowtom of each fuel cell when appearing through the filler neck. To obrain standard pius reserve, 130 gallons, fill the outboard cells completely. CAUTION Accumalation of water in the fuel tanks could cause rough engine operation or compiete power loss if the water freezes during cold weather operation. Therefore. to keep condensation in fuel tanks ata minimum. refuel the aircraft after each flight. HANDLING AND SERVICING Revised: 9:10. 79 1610 PIPER COMANCHE SERVICE MANUAL FIGURE 2-16. FUEL STRAINER AND DRAIN FIGURE 2-17. FUEL SELECTOR AND DRAIN PA-24-180 and PA-24-250, Serial Nos. PA-24-400 24-2299 and up, and PA-24-260 '2-50 Draining Fuel Valve and Strainers. a. On PA-24-180 and PA-24-250 aircraft bearing Serial Nos. 24-1 to 24-2298 inclusive. the fuel strainer, equipped with an easy drain valve is mounted under the right fporward section of the fuselage. The fuel strainer drain (Figure 2-16) on PA-24-180 and PA-24-250 aircraft bearing Serial Nos 24-2299and up and PA-24-260 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 the center of the fuel selector The fuelstrainer 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 {ue! 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 NOTE 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 HANDLING AND SERVICING 1C11 PIPER COMANCHE SERVICE MANUAL 2-51. Draining Fuel System. Drain the fuel from the system by opening the drain valve at the bottom oflh‘ fuel strainer bowl, or removing the bowl. 2-52. Electrical System. 2-53. Servicing Electrical System. Servicing the electrical system involves adding distilied water to the battery to maintain correct electrolyte level. checking cable connections and checking for any spilled electrolyte that would lead to corrosion. The security of all electrical connections should be checked as 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 1X of this manual 2-54. Oxygen System. 2-55 Description of Oxygen System. The oxygen system for the PA-24 consists of an oxygen cylinder and regulator., filler valve. pressure gauge. outlets and masks and an ON; OFF control mounted on the instrument panel. The stationary cylinder is located aft of the baggage area on the left side of the fuselage The cylinder used is an ICC or DOT 3AA 1800 classification with a 63 cubic foot capacity at a working pressure of 1800 psi. High pressure oxygen is routed from the cylinder and regulator to the pressure gauge mounted in the upper portion of the aft cabin bulkhead. Low pressure oxygen is routed from the cylinder and regulator to the outlets and masks whenever the control knob is pulled to the ON position. Each outlet has a spring loaded valve which prevents the flow of oxygen until a mask hose is engaged into the outlet. ‘ 2-56 Troubleshooting. Troubles peculiar to the oxygen system are listed in Table 11-V along with probable causes and suggested remedies 2-57. Oxygen System Safety Precautions. The utmost care must be éxercised 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. WARNING The presence of foreign 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. ¢ Never 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. Use Ribbon Dope Thread Sealant (Permacel 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 into the lines, REVISED: 11/1/82 HANDLING AND SERVIClN!! 1C12 PIPER COMANCHE SERVICE MANUAL TABLE II-111. INDICATED OXYGEN CYLINDER PRESSURES FOR GIVEN AMBIENT TEMPERATURES INDICATED CYLINDER PRESS TEMPERATURE °F PS1 110 . 1980 100 1935 90 1890 80 1845 70 1800 60 1755 50 1710 40 1665 2-58 Filling Oxygen Cylinder. 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 the oxygen cylinder. open the access door. remove the cap from the filler valve and attach the filler hose from the oxygen recharge unit to the filler valve Ascertain that all fittings are free from oil. grease. dirt. etc NOTE If the airplane’s oxygen cylinder pressure is below 50 psi. thesystem should be purged as described in Paragraph 2-71. b To obtain the correct filling pressure for the oxygen cvlinder at various ambient temperatures a chart has been includz=d for your convenience The pressures given are not exact. but sufficiently accurate for practical purposes of working pressure between 1800 and 2400 psig cvlinders The cylinder should be allowed to cool to a stabilized temperature after filling before checking against the figures given in Table 1111 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 system). it is recommended that the following procedure be used. REVISED: 4/3/78 HANDLING AND SERVICING 1C13 PIPER COMANCHE SERVICE MANUAL 1. Before opening any valves, check the pressure remaining in the airplane’s oxygen cylinder. If it is still partly charged, note the pressure indicated on the cylinder gauge. Then open and close each valve on the cascade storage system 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 for filling. Use the storage cylinder that has a pressure higher than the airplane’s cylinder but lower than the others. 2. Open the valve on only the one storage cylinder with the lowest pressure. When the pressure indicated on the airplane’s oxygen gauge and charging gauge has become equal, close the valve of the storage cylinder, then go to the storage cylinder with the next higher pressure and repeat the procedure. 3. 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 cylinders, but such remaining oxygen will be at a pressure something less than the 1800 pounds, which is not sufficient pressure to completely refill another aircraft cylinder, although it will refill several smaller cylinders. 5. It is not economical, even on a three or four-cylinder cascade system, to begin recharging with oxygen at less than 300 psi pressure in the 300 cubic foot bank of cylinders. So, use 300 cubic foot cylinders down to approximately 300 psi, then return for refilling. In two-cylinder systems, use to approximately 600 psi, then return for filling. €. 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 stabilizes. 2-59. Inspection and Overhaul Time Limits. It is recommended that inspection and overhaul be conducted by an FAA Approved Station; or, the manufacturer, Scott Aviation. The following checks and chart gives recommended inspection and overhaul times for the various parts of the oxygen system. a. The oxygen cylinder can be identified by the ICC or DOT identification stamped on the cylinder. The standard weight cylinder (ICC or DOT 3AA 1800) must be hydrostatic tested at the end of each 5 year period. The month and year of the last test is stamped on the cylinder beneath the ICC or DOT identification. b. 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 gauge of known accuracy. d. Inspection 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 pressure shall be not less than 45 psig at sea level with 200 psig supply cylinder pressure. It should be noted that the permissible leakage through the 1/16 diameter vent hole in the side of the upper regulator housing is 10 cc/ min. maximum, when the regulator is turned on. There shall be no external leakage anywhere on the regulator when it is turned off. All fittings shall be leak free. HANDLING AND SERVICING Revised: 8/15/98 ‘ 1C14 PIPER COMANCHE SERVICE MANUAL TABLE 1I-1V INSPECTION - OVERHAUL TIME LIMITS PARTS INSPECTION OVERHAUL Regulator 300 Flight H