Piper Comanche Service Manual

Lubrication Chart - Flap Track - PA-24180,250,260 and 400 Lubrication Chart - Nose Landing Gear - PA-24-400 Lubrication Chart - Nose Landing Gear - PA-24- 180,250 and 260 Lubrication Chart - Stabilator - PA-24180,250,260 and 400 Lubrication Chart - Rudder Control - PA-24-180,250,260 and 400 Lubrication Chart - Bellcrank - PA-24-180,250,260 and 400 Lubrication Chart - Propeller - PA-24-180,250,260 and 400 Lubrication Chart - Main Landing Gear - PA-24-180.250.260 and 400 vpical Muffler Fatigue Areas Exhaust System Inspection Points - PA-24-180,250 and 400 Exhaust System Inspection Points - PA-24-260 Landing Light Installation Wing Attachment Fittings Flap Roller Installation (Eleceically Operated) Rc PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (continued) fiewe No. wf&st 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 24-4246.24-4248 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. 24-4247,244300 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.) Nose Gear Oleo Strut Assembly - PA-24-180. PA-24-250 (Serial Nos. 24-215 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 6-9. Main Landing Gear Installation (Left) Revised: 8/15/98 1F9 lFlO 1f11 1f12 1f19 1f23 1G2 1G4 1G4 1G6 1G15 1G15 1G16 1G18 1G21 1H1 1H4 1H16 1H24 and up; 1I5 1110 1113 1113 1114 1116 1I20 1I22 1122 1I23 1J2 PREFACE PREFACE PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (continued) Adjushnent of Main Landing Gear Drag Link 1J6 Aligning Main Gear 1J7 Landing Gear Retraction System 1110- Landing Gear Retraction Transmission Assembly 1J12 Landing Gear Retraction System Installation 1J17 Nose Gear Drag Link Clevis 1J18 Landing Gear Up L i t Switch 1J19 Torque Wrench and Adapter Installation, (Serial Nos. 24-1 to 24-4782 incl.; 24-4784 to 24-4803 incl.) 1J24 Torque Wrench and Adapter Installation, (Serial Nos. 24-4783; 24-4804 and up) 1K1 Landing Gear Down Safety Lock Installation 1K2 Landing Gear Waming Switch Installation 1K3 Landing Gear Waming Indicator 1K5 Nose Wheel Assembly 1K6 Main Wheel Assembly (Cleveland) - PA-24-180 and PA-24-250 1K8 Main Wheel Assembly (Cleveland) - PA-24-260 and PA-24-400 1K9 Main Wheel Assembly (Goodrich) - PA-24-400 lKlO Brake Assembly (Cleveland) - PA-24-180 and PA-24-250 (Serial Nos. 24-1 to 24-3295) 1K12 Brake Assembly (Cleveland) - PA-24-180 and PA-24-250 (Serial Nos. 24-3296 & up); PA-24-260 and PA-24433 1K14 Brake Assembly (Goodrich) - PA-24-400 1K15 Replacing Brake Disc 1K16 Bleeding Brakes 1K17 Brake System Installation - PA-24-1 80 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 Installation 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 1L4 Fabricated Plumbbob Tool 1L7 Fabricated Nose Wheel Alignment Jig 1L8 Fabricated Spanner Wrench 1L9 Inspection of Rod End Bearing l L l l Main Gear Wear Limits 1L14 Nose Gear Wear L i t s 1L16 Propeller Installation (McCauley) 2A14 Qpical Nicks and Removal Method 2A15 Propeller Installation (Ha~tzell) 2A18 Woodward Propeller Governor Adjustment Points 2A21 Revised: 8/15/98 PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (continued) 7-5. Hartzell PropeUer 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. Tuning Pointer 7-13. Timing Plate Installed on Breaker Compamnent 7-14. Breaker Compartment With Cast liming Marks 7-15. Engine xming M a k s 7-16. Ignition System Retard Breaker Magneto Installation 7-17. Removing Seized Spark Plug 7A-1. Propeller Installation (McCauley) - PA-24-250 7A-2. Typical Nicks and Removal Method 7A-3. Propeller Installation (Hartzell) - PA-24-250 7A-4. Propeller Instahtion (Hartzell) - PA-24-260 7A-5. Woodward Propeller Governor Adjustment Points 7A-6. Hartzell Propeller Governor Adjustment Points 7A-7. Engine Installation - PA-24-250 1 7A-8. Engine Installation - PA-24-260 (Serial Nos. 2443X thm 244803, less 24-4783) 7A-9. Engine Installation - PA-24-260 (Serial Nos. 244783 and 244804 and up) 7A-10. Carburetor 7A-11. Schematic Diagram of RSA Fuel Injector System - PA-24-250 & PA-24-260 7A-12. Idle and Mixture Adjustment (Fuel Injector) 7A-13. Fuel Air Bleed Nozzle 7A-14. Magneto Inspection 7A-15. Lead Positioning 7A-16. Impulse Coupling 7A-17. Magneto Timing Marks 7A-18. liming Pointer 7A-19 liming Plate Installed on Breaker Compartment 7A-20. Breaker Compartment with Cast Timing Marks 7A-21. Engine Timing Marks 7A-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. Idle Speed and Mixture Adjustment (Fuel Injector) 7B-7. Fuel Air Bleed Nozzle 7B-8. Magneto Timing Marks Revised: 8/15/98 !2l!aa 2.422 2B 1 - 2B5 2B6 2B8 2B9 2B9 2B10 2b10 2B11 2b11 2B12 2B15 2B17 2C7 2C8 2C10 2C12 2C16 2C17 2C21 2di 2D7 2d11 2D14 2D16 2D17 2D19 2D20 2D20 2D21 2D21 2D22 2D22 2D24 2E2 2E4 2E22 2E23 2FZ 2F3 2F8 2F10 2F12 2F14 PREFACE PIPER COMANCHE SERVICE MANUAL -7B-9. 7B-10. 7B-11. 7B-12. 7B-13. 7B-14. 7B- 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. 1 8-1. 8-2. 8-3. 8-4. 8-5. 8-6. 1 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) Reworked Plain Washer Filed Notch on Cam Installation of Rotor Holding Tool and Timing Pointer Alignment of Cam in Inspection Hole Engine T h i n g Marks Ignition System Retard Breaker Magneto Installation Removal of Seized Spark Plug Propeller Installation Typical Nicks and Removal Methods Propeller Governor Engine Installation - PA-24-260 Turbo Schematic Diagram of Turbocharger System Lockwiring V-Band Couplings Indicator Robe Installation Schematic Diagram of RSA Fuel Injector System - PA-24-260 Turbo Fuel Injector Fuel Air Bleed Nozzle Contact Points Rotor Holding Tool Installed Tuning Kit Installed Aligning Tuning Marks Single Contact Assembly Magneto Forming Leads in Breaker Compartment Engine T h i n g Marks Magneto liming Marlrs Removing Frozen Spark Plug Turbo Oil Flow Check Fuel Cell Installation (Mainflnboard) Fuel System Schematic - PA-24- 180 Fuel System Schematic - PA-24-250 (Serial Nos. 24-105 to 24-2298) Fuel System Schematic - PA-24-250 (Serial Nos. 24-2299 & up) and PA-24-260 Fuel System Schematic - PA-24-260 Turbo Fuel System Schematic - PA-24-400 Bayonet Fasteners Bunon Fasteners Checking Sender Unit Checking Fuel Gauge Three Position Fuel Valve - PA-24-180 and PA-24-250 Five Position Fuel Valve - PA-24250 and PA-24-260 Fuel Valve and Filter - PA-24-400 Fuel Strainer Disassembled - PA-24-400 Bendix Plunger Fuel Pump (Early) Bendix Plunger Fuel Pump (Late) Exploded View Bendix Rotary Fuel Pump Primer Pump (Carburetor Induction System) Fabricated Fuel Quantity Transmitter Checking Jig Re1 PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (continued) 9-1. Generator and Starter Wiring System 9-2. Sectional View of Generator 9-3. W ~ n g 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 9-9. 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 Voltage 9-13. Checking Current Regulator, Load Method 9-14. Checking Current Lead Method. Jumper 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 Output 9-24. Volt-Ohmmeter Test 9-25. Jumper Connection 9-26. Regulator Checks 9-27. Relay Test 9-27a. Exploded Mew 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 9-278. Testing Rotor for Grounds 9-27h. Testing Rotor for Shorts 9-27i. Installation of Bearing 9-27j. 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 'am!& 3A13 3A16 - 3A22 3 ~ 2 4 3A24 3B 1 3B 1 3B1 3B3 3B3 3B4 3B4 3B5 3B5 3B8 3B10 3b11 3b11 3b11 3B12 3B14 3B14 3B15 3B17 3B17 3B18 3B19 3B20 3B22 3B23 3B23 3B24 3B24 3C 1 3C 1 3C2 3C2 3C3 3C3 3C3 3C4 3C4 3C7 3C8 3C9 PREFACE PIPER COMANCHE SERVICE MANUAL LIST OF ILLUSTRATIONS (continued) Testing Overvoltage Control NeLoad 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 NeLoad 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) --CabinHeater, 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. 244247,244300 to 24-4782 incl.; 24-4784 to 244803 incl.) Cabin Heater. Defroster and Fresh Air System - PA-24400 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 Control Cable Inspection Technique External Cable Wear Patterns Internal Cable Wear Pulley Wear Patterns PREFACE PIPER COMANCHE SERVICE MANUAL LIST OF TABLES I h ! k w subkt I 1-1 Engine and Propeller II-I Leadiig Particulars and Principal Dimensions U-U Recommended Nut Torques (Inch Pounds) II-IIA Flare Fitting Torques n-m Indicated Oxygen Cylinder F'ressures for Given Ambient Temperatures U-IV Inspection Report - Overhaul Tune Limits (Oxygen Syst. Components) II-V Troubleshooting Chart (Oxygen System) U-VI Recommended Lubricating Oils I U-VII Decimal Equivalents of Drill Sizes U - w I Lubrication (Special Instructions) m-I Inspection Report V-I Control Surface Travel and Tension V-U Troubleshooting Chart (Surface Controls) VI-I Toque For Effective Wrench Length VI-II Troubleshooting Chan (Landing Gear and Brake System) W-III Main Gear Wear L i u VI-IV Nose Gear Wear Limits W - I Propeller Specifications - PA-24-180 W-n T h i n g Data W - I I I Troubleshooting Chart (Engine) - PA-24-180 VIIA-I Propeller Specifications - PA-24-250/260 VIIA-II T~rningData VIIA-III Troubleshooting Chart (Engine) - PA-24-2501260 VIIB-I Propeller Specifications - PA-24-400 VIIB-II Troubleshooting Chan (Engine) - PA-24-400 W C - I Propeller Specifications - PA-24-260 lhrbo W C - I A Troubleshooting Chart @4iixtureControl Indicator) VIIC-II Troubleshooting Chart (Engine) - PA-24-260 Turbo MU-I Specifications, Duke Model 4140-00-218 Electric Fuel Pump mu-n Flow Versus Pressure Chart at 14 V.D.C. VUI-III Pump Pressures (Fuel Injection) Vm-Iv Fuel System Troubleshooting M-I Alternator Checks M-II Circuit Load Chart (Models Prior To 1970) M-IIA Circuit Load Chart (Models 1970 And Later) M-m Lamp Replacement Guide IX-IV Index Electrical System Schematics M-V Electrical Wire Coding M-VI Electrical Symbols IX-VII Troubleshooting XI-I Vacuum System XI-I1 Duectional Gyro Indicator XI-In Gyro Horizon Indicator XI-IV Rate Of Climb Indicator XI-V Altimeter Revised: 8/15/98 !aLm 1A17 1B6 - 1B19 1822 1C13 1C15 1C18 1C19 1C23 1C24 1D20 1f15 1H5 1J23 1L5 1113 1115 2A19 2b11 2B21 2C14 2D23 2E8 2F1 2G2 2G16 2H2 211 2113 2J14 2115 2117 3B16 3D3 3D5 3D6 3D7 3d11 3D12 3E22 3F23 3G6 3G7 3G8 3G9 PREFACE PIPER COMANCHE SERVICE MANUAL I I LIST OF TABLES (continued) i XI-VI XI-W xr-WI XI-M XI-X XI-XI XI-XI1 XI-xm XI-XN I XI-XV 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 PREFACE Reviud: 8/15/98 • SECTION I INTRODUCTION Paragraph Aerofiche Grid No 1.1 . General .................................................................. 1.3 . S c o p e 0 1 Manual .......................................................... 1-7 Description ............................................................... 1.9 . Wing ............................................................ 1.10 . Empennage ...................................................... 1 . 1 1 . Fuselage ......................................................... 1.12. Landing Gear .................................................... 1.13 . Hydraulic Systems ................................................ 1.14 . Engine And Propellers ............................................. 1.15 . Fuel System ...................................................... 1.16 . Flight Controls ................................................... 1-17 Radio ........................................................... ...................... 1.18 . Cabin Heater . Defroster . And Fresh Air System 1.19 . Instrument And Autopilot Systems .................................. . ISSUED: 8/18/72 PIPER COMANCHE SERVICE MANUAL SECTION I 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 Il and III comprise the service part of this manual, whereas Sections N through XII 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 should 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 11-Il 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 laminx flow wing is of all-metal stressed-skim, 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 ~ d d e rand 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 PIPER COMANCHE SERVICE MANUAL 1-14. Engine and Propeller. T a l e I-I. Engine and Propeller. Model Engines PropeUers Horsepower Octane PA-24- I80 0-360-A 1A HartzeU HC-92ZK-8D, 01 180 91/96 0-360-AID McCauley 2D36C14 PA-24-250 0-540-A1A5 HartzeU HC-82XK-1 D 250 91/96 0 - 5 a A l B 5 or HC-A2VK-1, or 0-540-A1C5 McCauley 2D36C28 0-540-AID5 10-540-C1B5 HartzeU HC-A2VK-I PA-24-260 0-540E4A5 HartzeU HC-C2YK-I A 260 91/96 10-540-D4A5 or HC-C2YK-I B 10-540-N1 A5 Hartzell HC-E2YR-IB PA-24-260 Turbo 10-540-RIA5 HartzeU HC-E2YR-1B 260 1001130 or HC-E2YR-IBF PA-24-400 10-720-A1 A HartzeU HC-A3VK-4 400 1001130 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 pans: a modified directional gyro, a modified gyro horizon, a motor-driven actuator, ind an amplifier. Revised: 8/15/98 INTRODUCTION THIS PAGE INTENTIONALLY LEFT BLANK THIS PAGE INTENTIONALLY LEFT BLANK Paragraph SECTION I1 HANDLING A N D SERVICING Acrofiche Grid No Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . lA22 Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . lA22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Weight and Balance Data lA22 ....................................................... Serial Number Plate . . lA22 Access and Inspection Prov~sions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..... lA22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tools and Test Equipment IAZ? ...................................................... Torque Requirements IA23 Torque Wrenches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IA23 ................................................... Handhold and Walkways IA23 Ground Handling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IA23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10 Introduction to Ground Handling IA23 ................................................. 2.lOa . Torque Wrenches 1818 2-1 1 Jacking .......................................................... 1823 . . 2.12 . We~ghing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IB23 2-13 Leveling ......................................................... 1824 2.14 . Mooring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC2 2.15 . Parking . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ...... IC2 2-16 Locking Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC3 2-17 Towing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 . Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C3 2-20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I C 3 External Power Receptacle IC3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operation of External Power Receptacle IC3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cleaning IC4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22. Cleaning Engine Compartment IC4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23. Cleaning Landing Gear IC4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24 Cleaning Exterior Surfaces IC4 .................................. 2-25 . Cleaning Windshield and Windows IC5 . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.26 . Cleaning Headliner . Side Panels and Seats ICS ................................................. 2-27 Cleaning Carpets IC5 Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC5 .......................................... 2-29 introduction to Senicing IC5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Landing Gear System IC6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-31 Servicing Landing Gear IC6 Oleo Struts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .IC6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 3. Servicing Oleo Struts Ic5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-34 . Filling Oleo Struts ICY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35 Inflating Oleo Struts IC8 Brake System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-37 Servicing Brake System IC8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-38 . Filling . . Brake System Reservoir IC8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39 Dralning Brake System IC8 Tires . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . lC9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-41 . S e r v ~ c ~ n g Tires IC9 Power Plant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-43. Servicing Power Plant IC9 P r o ~ e l l e r. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . lClO REVISED: 11/1/82 PIPER COMANCHE SERVICE MANUAL 2 4 5 . S&cily h p d k . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 0 2 4. In&cdonAj~;Uta . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 0 2 7 . knicing Iduaiom Air FSta . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 0 2 4 8. FudSymcm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 0 2 4 9. F i b # F n d f u h . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . lClO 2.50 . Dnimng F d V.hc d Scnincn . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l l 2.51 . D u b b g F u d S y n e m . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC12 2 4 2. ElccaLJSymrm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C12 2.53 . Sapiciug E l t C P i a l S y s m ~ ~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 2 2.54 . OxrpnSyncm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l l 2 4 % D&pwn of O y p System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C12 2.56 . T d c l h m ~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 2 2 5 7 . O y p Syaem s.fCrg- . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 2 2 4 8. FJlinsOrylca Cyiirda . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C13 2.59 . Lnspectiao d Olcrh.ul Timr Limbr . . . . . . . . . . . . . . . . . . . . . . . . . 1C14 264 TsrLgfor L a h . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C15 2-61. Mbcmance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C15 2-62 . ClaninsOpntionr . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1Cl5. 2 4 3 . R u n o n l of O x y p CylLder d R q d m r . . . . . . . . . . . . . . . . . . . . . 1C16 2 6 1. Iniullrdon of O x y p C y l i n k a d Rqmhor . . . . . . . . . . . . . . . . . . . 1C16 2-65 . R a D m l o f Facr Vd~rc . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 7 2-66 . I ~ ~ n o f fikrV.hc . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . l C l 7 2 4 7 . R e m a d o f ReravcCol(c . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C17 2-6 8. I&don of P- Gage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C17 2-69 . Removalof Oudcu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C17 2.70 . Iraull.don of Ouderr . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C17 2.71. RypneOxypen lyacm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1Cl8 2.72 . Waningof FueMnlu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C18 2.73 . Lubriation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C19 2.74 . Oil Syncma ( E w ) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C19 2.75 . S a v i a q Oil Sy-mm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IC19 2.76. DnillingOJ Sump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C19 2.77 . FUqOilSump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C19 2.78 . Oil Screen (Suction) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C20 2.79 . Oil Screen (Ronuc) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C20 2.80 . 011 Film (Full Flow) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C21 2.81 . Raommadaiom for Ch.n&g Oil . . . . . . . . . . . . . . . . . . . . . . . . . . 1C21 2.82 . Lubriauon l m a u d o m . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1C21 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.83 . Appliadon of OJ 1C22 2.84 . Appliaaon of C r u v . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1Cf2 2.85 . Lubrication Gun . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1C22 PIPER COMANCHE SERVICE MANUAL SECTION I1 HANDLING AND SERVICING 2-1 1nlroduction. 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. referto 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 11-1 2-3. Weight nnd 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 Number 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 9 2-5 Access and Inspection Provisions. The access and inspection provisions for the airplane are shown I 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 thecarpet edges from under its retainer strips. lifting the edges and removing the carpet attaching screws. Remove thc.carpet. thus exposing the floor panel attaching screws. T o 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 theairplane 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 G HANDLING AND SERVICIN PIPER COMANCHE SERVICE MANUAL 2-7. Torque Requirements. The torque values given in Table 11-11 arc 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. I VIIB and VllC of this manual. Table 11-IIA lists the torque values for flared fittings of various sizes and materials. 2-70. Torque Wrenches. Torque wrenches should be checked daily and calibrated by means of weightsanda 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. I CAUTION I D o not overtorque fittings. I NOTE When flared fittings are being installed, ascertain that the male threads are properly lubricated. Torque fittings in accordance with Table 11-1IA. When it is necessary t o use a special extension or adapter wrench together with a torque wrench a simple mathematical equation must be worked out t o 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 pans Devoe non-skid compound and one part black enamel are painted on the 1e right wing and flap. CAUTION Avoid damage t o the wings by stepping only on the walkway. 2-9. Ground Handling. 2-10. Introduction t o 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: 4110181 PIPER COMANCHE SERVICE MANUAL 1 FIGURE 2-1. THREE-VIEW OF COMANCHE P A - 2 4 - 1 M ) d PA-24-a0 I HANDLING AND SERVICINQ REVISED: 4 m PIPER COMANCHE SERVICE MANUAL FIGURE 2.2 THREE v l m OF COMANCHE PA-24-~BO Ssid Nm. 244000 m 2 U Z 4 0 . 2 4 4 2 4 8 to 244199 HANDLING AND SERVICING REVISED: 4/3/78 PIPER COMANCHE SERVICE MANUAL FIGURE 2-3, THREE-VIEW OF COMANCHE PA-24-280 Send Nor 244247.244300 to 244782 144784 m 24-4803 ind. HANDLING AND SERVICING REVISED: 4/jr)8 PIPER COMANCHE SERVICE MANUAL FIGURE 24. THREE-VIEW OF W M A N M E PA-- HANDLING AND SERVICING REVISED: 4i3/7$ PIPER COMANCHE SERVICE MANUAL FIGURE 2.5. THREE-VIEW Of COMANCHE PA-lrCaO SOWN a wm.1 ~ 4 8 ( ~ md UP HANDLING AND SERVICING REVISED: 4/3/78 PIPER COMANCHE SERVICE MANUAL 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 A N D SERVICING REVISED: 4/3/78 PIPER COMANCHE SERVICE MANUAL MODEL ENGINE Manufacturer Model TABLE 11-1. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS 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: 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 PA-24- 180 PA-24-250 Carburetor Induction Avco-Lycoming 0-360-AI A or 0-360-A ID 180 H P @ 2700 RPM See Table 11-V1 8 qts. 91/96 MA-4-5 - S4LN-21 I S4LN-20' S4LN-2002 S4LN-204' 25 degrees BTC 0.0 18 A 0.006 in. (6) 1 1 18704 1 1 19224 Plunger I 0-360-AIA 2 0 - 3 W A I D 3 0-S4C-AIAS 4 0-YO-AIBS. OS4C-AICS 5 0-540-AIDS 6 Refer to I a m l revision of Lyeorning Service Instruclian No 1042 HANDLING AND SERVICING I REVISED: 4/10/81 Avco-Lycoming 0-540-A IA5; 0-540-A I BS, 0-540-A IC5 or 0-540-A I D5 295 250 H P @ 2575 RPM See Table 11-VI I2 qts. 91/96 MA-4-5 - S6LN2 I), S6LN-21' S6LN-203, S6LN-21' S6LN-200' S6LN-2049 25 degrees BTC 0.018 L 0.006 in. (6) (6) 1-4-5-2-3-6 0.5: 1 1 1 18704 1 1 19224 Plunger PIPER COMANCHE SERVICE MANUAL a TABLE 11-1. 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-Scheblcr Fuel injector. Bendix Magnetos (2). Scintilla: Left Right Magneto timing Magneto point clearance Soark ~ l u a s(shielded): . - . s p a r k plug gap setting Firing Order Tachometer drive. ratio to crankshaft Starter: Delco-Remy 12 volt Prestolite, I2 volt Generator, Delco-Remy: 12 volt (35 amp) I2 volt (50 amp) Generator voltage regulator. Delco-Remy ' I2 volt (35 amp) I2 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-24-250 PA-24-260 Fuel Injected Carburetor Induction Avco-Lycoming Avco-Lycoming 10-540-C I B5 0-540-E4A5 250 HP @ 2575 RPM See Table 11-IV I2 qts. 91/96 - RSA-SAD1 S6LN-200 S6LN-204 25 degrees BTC 0.018 2 0.006 in. (6) (6) 1-4-5-2-3-6 0.5: 1 - Plunger 260 HP @ 2700 RPM See Table Il-IV 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 - Plunger HANDLING AND SERVICING REVISED: 4110181 PIPER COMANCHE SERVICE MANUAL MODEL ENGINE Manufacturer Model FAA type certificate Rated horsepower, R P M : Full throttle Oil, S A E 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-Rerny, 12 volt Prestolite, 12 volt Generator, Delco-Remy: 12 volt (35 amp) 12 volt (SO amp) Generator voltage regulator, Delco-Remy: 12 volt (35 amp) 12 volt (50 amp) Alternator, Delco-Remy I2 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 PA-24-260 Fuel Injected - Serial Nos. Fuel Injected - Serial Nos. 24-4783. 24-4804 and u p 24-4000 t o 24-4782. 24-4784 t o 24-4803 inclusive Avco-Lycoming Avco-Lycoming 10-540-NIAS 10-540-D4A5 260 H P @ 2700 R P M See Table 11-IV 12 qts S6LN-200 S6LN-204 25 degrees BTC 0.018 f 0.006 in. (6) (6) 1-4-5-2-3-6 0.5: 1 - ALX842I VSF7203 XI7621 Plunger 260 H P @ 2700 R P M See Table 11-IV I2 qts. S6LN-200 S6LN-204 25 degrees BTC 0.018 i 0.006 in. (6) (6) 1-4-5-2-3-6 0.5: 1 - Plunger HANDLING A N D SERVICING REVISED: 41 10/81 PIPER COMANCHE SERVICE MANUAL TABLE 11-1. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont.) MODEL PA-24-260 Turbo PA-24-400 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, I2 volt Generator, Delco-Remy: I2 volt (35 amp) 12 volt (50 amp) Generator voltage regulator, Delco-Remy 12 volt (35 amp) I2 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 Avco-Lycoming 10-540-R IA5 I E4 260 HP @ 2700 RPM See Table 11-VI I2 qts S6LN- 1209 S6LN-1208 25 degrees BTC 0.0 16 i006 in. (6) (6) 1-4-5-2-3-6 0.5: 1 - ALX842I VSF 7203 XI7621 Lear Seigler RG- 17980 6 Rcler ro larcrr revaion of Lycoming Service lnrrrvction No 1041 Avco-Lycoming 10-720-A IA I E l 5 400 HP @ 2650 RPM See Table 11-VI 17 qts 1001 I30 - RSA-IOADI S8LN-701 S8LN-705 20 degrees BTC 0.019 L 0.001 in. (6) (6) 1-5-8-S2-6-7-4 0.5: 1 - Lear Seigler RG- 17980 HANDLING AND SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE 11-1. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont.) MODEL PA-24- I80 PA-24-250 FUEL SYSTEM Inboard (main) fuel cells Two Capacity (each) 30 U.S. gal Unusable fuel (each) 2 U.S. gal 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 b a r 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 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 600 x 6.4 ply rating 27 psi 27 psi 2550 lbs. 2550 lbs Two 30 U.S. gal 2 U.S. gal Two I5 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 600 x 6, 4 ply rating 6:00 x 6, 6 ply rating 27 psi 42 psi 2800 lbs 9 or 2900 lbs lo 2800 lbs 9 or 2900 lbs lo 9 Serial Nor 24-1. 24-103 to 24-2002 incl 24-XX)4 l o 242298 incl 10 Senal Nor 24-2001. 24-2299 and up HANDLING AND SERVICING REVISED: 41 10181 P I P E R C O M A N C H E SERVICE M A N U A L MODEL FUEL SYSTEM TABLE 11-1 PARTICULARS A N D PRINCIPAL DIMENSIONS (cont.) PA-24-260 PA-24-260 Serial Nos. 24-2400 to Serial Nos 24-4783. 24-4804 24-4782. 24-4784 to 24-4803 and up inclusive Inboard (main) fuel cells Two Capacity (each) 30 U.S gal Unusable fuel (each) 2 U S gal Outboard (auxiliary) fuel cells Two Capacity (each) 15 U S. gal Unusable fuel (each) - LANDING GEAR Type Shock strut type Fluid required (struts and brakes) Strut exposure I (exposure under static load) Wheel tread Wheel base C 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 Electrically operated Combination air and oil 2.75 in. 9 ft. 8 in 6 it. 6.62 in. Left 20'. Right 20" Cleveland 38501 Cleveland 40-84 Cleveland 30-4 1 6.00 x 6. 4 ply rating 6.00 x 6. 6 ply rating 77 psi 42 psi Two 30 U.S gal 2 U S . gal Two 15 U S. gal - Electrically operated Combination air and oil 2.75 in. Nose. 2.50 in Main 9 ft 8 in. 6 it 6.62 in Left 20'. Right 20" Cleveland 38501 Cleveland 40-84 6.00 x 6. 4 ply rating 6.00 x 6. 6 ply rating 27 psi 42 psi 2900 lbs 1 ' or 3100 lbs 3200 ibs 2900 lbs 1 1 or 2945 lbs 12 3040 lbs I I Scr8.tl \ o , !4->h42 24.U)oO lo 24-4?4h ~ C I ?A-424X l o 21.4299 i n r l I? Ser8sl \o. 2 4 4 4 7 . 24-JlllU 1 0 4 - 4 7 8 ? 8ncl 24.4784 l o .'4-4801 lncl HANDLING A N D SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL TABLE 11-1 LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont ) MODEL PA-24-400 FUEL SYSTEM Inboard (main) fuel cells Two Capacity (each) 30 U S. gal Unusable fuel (each) 3 U S. gal Outboard (auxiliary) fuel cells Two Capacity (each) 35 U S gal 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, \I ose Wheel, Main Brake type Tire. Nose Tires. Main Tire pressure. Nose Tire pressure. Main OVERALL Gross weight Gross landing weight Electrically operated Combination air and oil 2.50 in. 9 it. 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 6 00 x 6. 6 ply rating 6 00 x 6. 6 ply rating 42 psi 42 psi 3600 lbs. 3600 lbs. HANDLING AND SERVICING REVISED: 4110181 P I P E R C O M A N C H E SERVICE M A N U A L MODEL TABLE 11-1. LEADING P A R T I C U L A R S A N D PRINCIPLE D I M E N S I O N S (cont.) P R O P E L L E R Manufacturer T Ype H u b model. McCauley Hartzell Blade model. McCauley Hartzell Diameter. McCauley Hanzell Diameter, min , McCauley Hartzell PA-24- 180 PA-24-250 Carburetor Induction McCauley o r Hartzell Constant speed (two blades) 2D 36C14 HC-92ZK8D D-2IOI178KM-4 8447A- I2A 74 in. 72 in. 72 in. 70.5 in. Blade Angle (low pitch)'. McCauley 12.7O 2 O.ZO Hartzell 13' McCauley o r Hanzell Constant speed (two blades) 2 D 36C28 HC-82XKID or HC-A2VK-I D-2286i 80M M-6 V8433N-7 74 in. 77 in. 73 in. 76 in. ~ - . ~ ~ . Blade Angle (high pitch)'. McCauley 27 50 32' f 0.5' Hartzell 27' 31' to 33' Control governor Woodward o r Hartzell Woodward o r Hanzell Governor model, Woodward 210305 A210305 Hartzell D 1-5 8 - 4 2 HANDLING A N D SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE M A N U A L MODEL PROPELLER Manufacturer Type Hub model. McCauley Hanzell Blade model. McCauley Hartzell Diameter. McCauley Hanzell Diameter, min.. McCauley Hartzell Blade Angle (low pitch)l, McCauley Hanzell Blade Angle (high pitch)l. McCauley Hanzell Control governor Governor model. Woodward Hartzell PA-24-250 Fuel Injected Hanzell Constant speed (two blades) HC-A2VK-I - 77 in. - 76 in. - 14.5' 2 0.15' - 31' to 33' Hanzell A210305 8-4-2 PA-24-260 Carburetor Induction and Fuel Injected - Serial Nos 24-4000 to 24-4782, 24-4784 to 24-4803 incl. Hanzell Constant speed (two blades) - HC-C2Y K- I A or HC-C2YK-I B - 8467-7R - 75 in. - 15" - 32O to 34' Hartzell 7 Bladc angle at 30 in radlu, 8 111%becomes nccrrbar! ~orcdurcthcpropcllcrdiamctcrbelow 77 ~ n c h c r . f o rmnin1cnanccrcbalancingpurporcr.a placardrtaung"A\otd ranl~nuour opcrallon brlween 2500 and 2600 rpm abobc 25 inches manifold prcrrurc" must be dtrplayrd near Ihr mannlold pressure gauge HANDLING A N D SERVICING REVISED: 4/10/81 PIPER COMANCHE SERVICE MANUAL MODEL TABLE 11-1. LEADING PARTICULARS AND PRINCIPLE DIMENSIONS (cont) 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 PA-24-260 Turbo PA-24-40 Fuel Injected - Serial Nos. 24-4783, 24-4804 and up Hartzell Constant speed (two blades) - HC-E2YR- I B - 8467-7R - 77 in. - 75 in. - 32O to 34" Hartzell - F-4-4A CONTROL SURFACE TRAVELS CONTROL SURFACE CABLE TENSIONS Hartzell Constant speed (two blades) - - 8467-7R - 77 in. - 75 in. - 32' to 34O Hartzell - F-4-4A Refer to Section V. Hartzell Constant speed (three blades) - HC-A3VK-4 - V8433-7 - 77.25 in. - 75.25 in. - 36O Hartzell - F-4- I HANDLING AND SERVICING REVISED: 4110181 PIPER COMANCHE SERVICE M A N U A L O E ~un mrr ~uu un farmrmsr r r a mum m s m AKWmn lrnlltr P R ~mo! mm fmm A ~ S r u n l1d hIII.~A142WI PURUIIL*91YCED?ra I U I ullLlulmTlmitEIrr~n ISWI OEPaREWmIcll UILSSmnIn YI RIL T l m RLU IU O U m l m r r r r a Figure 2-7. Access Panels and Plates PA-24-260, Serial Nos. 24-4247, 24-4300 and up HANDLING A N D SERVlClN REVISED: 4/3/78 PIPER COMANCHE SERVICE M A N U A L znm ruauu rrr r r c ~ m mr~crssrun ICI UIIICCIS~PIDI~ 1- CW1rnI1YCI ? L l l I -LLII ronrm uc~rsPIHI ll"l1lll ? 1 1 ~ 1S l l 1 l I LmUU CWIIRIII D I D 1 6111 II11S161101C C I S S PIKL IS1111 I l I l Y l I In1 1m U I S S Pull In111 I~IUTI6111 [rnlsm 811 ICUU UIt lull nucum .YICIm Nn ICW IW1 ICCtSf ? l l I L Figure 2-8. Access Panels and Plates PA-24-400 HANDLING A N D SERVICING REVISED: 4/3/78 PIPER COMANCHE SERVICE M A N U A L 2-lOa. TORQUE WRENCHES. Torque wrenches should be checked daily and calibrated by means o eweights and a measured lever arm to makesure that inaccuracies are not present Checking one torque wrench against another is not sufficient and is not recommended. Some wrenchesarequiv sensitiveas to the way they are supported during a tightening operation Any instructions furnished by the manufacturer must be followed explicitly. When it is necessary t o 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 theformula to be used: (Refer t o 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 =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 7 EXAMPLE A bolt requires 30 loot-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 t o obtain the 30 foot-pounds at the bolt 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 Figure 2-8a Torque Wrench Formula REVISED: 11/1/82 1B18 HANDLING A N D SERVICING PIPER COMANCHE SERVICE M A N U A L TABLE 11-11 RECOMMEKDED NUT TORQUES (INCH-POUlriDS) 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 Undertorquecan 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-lockingfasteners)- Add the friction torque from Chart A Tor sizes 8through 7j 16to the recommended torque from Chart B to get the final torque. This would be the actual reading on the torque wrench. b Torque (castellated and non-self-locking nuts) - Use only the torque given in Chart B. Unless other- wise specified. when castellated nuts are used with a cotter pin on movingjoints, d o not torque the nut. Turn the nut onto the bolt until proper grip isestablished and alignment with thecotter pin hole is achieved. Then install the cotter pin GENERAL REQUIREMENTS: a Calibrate the torque wrench periodically t o assure accuracy: recheck frequently. b 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. c. Use a bolt length long enough to prevent bearing loads on the threads. The complete chamfer or end radius of the bolt or screw must extend through the nut. ,... . d. Unique torques specified in the text of this manual supersede the torques given in Charts A and B. e. Refer to the latest revision of Lycoming SSP 1776for torques on pans used on Lycoming engines. f A maximum of two AN960 washers may be added under the bolt heads or nuts t o correct for variations in material thickness within the tolerances permitted g. 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 t o run them up. providing there is no obvious damage to the self-locking device prior to installation. 2 Bolts 51 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 bolts are free from burrs around the cotter pin hole. 3 Do not use self-locking nuts at joints which subject either the nut or the bolt to rotation. 4 Never tap or rethread self-locking fasteners. Do not use nuts, bolls or screws with damaged threads or rough ends. HANDLING A N D SERVICING a REVISED: 11/1/82 PIPER COMANCHE SERVICE M A N U A L BOLT SIZE -8' TABLE 11-11 RECOMMENDED KUT TORQUES (INCH-POUNDS) (cont.) rmml CHART A CHART B FRICTION DRAG 100 ABLE TO COARSE THREADS ONLY REVISED: 11/1/82 HANDLING A N D SERVICING COARSE THREADSERIES A N 3 t h r u A N m AN 42 thru AN 49 AN 73 Ihru AN 81 AN 173 mru AN 186 MS 20033 l h ~ MS 2QY6 AN 509 NK9 AN 515 NK525 10 -24 114-M 5H6-18 3 l S 1 6 7/16-14 112-13 911S12 518- 11 314-10 718- 9 1 -8 1.118-8 1.114-8 20 40 8 0 160 235 400 500 700 1.150 2 . m 3.700 5.500 6.500 25 M 90 185 255 400 700 900 1.800 3.000 5.000 6.500 8.000 12 25 40 95 140 240 34) 4 m 700 1.300 2.200 3.300 4.000 15 P 55 110 155 290 420 540 950 1.800 3.000 4.000 5.000 PIPER COMANCHE SERVICE M A N U A L TABLE 11-11 RECOMMENDED NUT TORQUES (INCH-POUNDS) (cont ) ; HANDLING A N D SERVICING REVISED: 11/1/82 Nut-bolt size 8 -36 10 -32 1/4-20 5/16-24 318- 24 7/16-20 112-M 9/16-18 5/8-18 3 l C 1 6 7/8-14 1 -14 1.1/8-12 1.114-12 - FINE THREAD SERIES BOLTS Steal TmYOn M5 m004 thru MS 20024 NAS 144 thru NAS 158 NAS 333 thru NAS 340 NAS 583 thru NAS 590 NAS 824 thru NAS 644 NAS 1303 mru NAS 1320 NAS 172 NAS 174 BOLTS S m l Terdon AN 3 thru AN 20 AN 42 mru AN 49 AN 73 thru AN 81 AN 173 thru AN 186 MS 20033 lhru M5 ?O(Y6 MS 20073 MS 20074 AN HE) NK9 MS 24694 AN 525 NK525 MS 27039 NAS 517 BOLTS Aluminum AN ~ D Dmru AN 2 0 0 ~ AN 173DD thru AN lB6DD AN W D D AN 525D MS 270390 MS 24694DD SD.1 * r r bolt NAS 464 N S m I T n i o n AN 310 AN 315 AN 363 AN 365 NAS 1021 MS 17825 MS 21065 MS 2W65 MS 2mOO NAS 679 Toque L i m i n in.lbs Min 12 20 50 100 160 450 480 800 1.100 2 . m 2.500 3.700 5.000 9.000 LITS Sb.l S h u AN 310 AN 364 NAS 1022 MS 17826 MS?0364 Torque Limits in-lbr Min. Mar Alum T m w n AN 36613 AN 3100 NAS 102lD Toque L i m i n on-lbs Min Mar Max 15 25 70 140 190 500 890 1.QX) 1.300 2.500 3.000 4.500 7.000 11.000 7 12 30 60 95 270 290 480 660 1.300 l.5W 2.200 3.000 5.403 5 10 30 40 75 180 280 380 550 950 1.250 1.600 2.100 3.900 NUTS Alum She- AN 3200 AN 3640 N S 1022D Torque Limnts in-lbr Min. Max NUTS Stad T e n w n AN 310 AN 315 AN 363 AN 365 MS 17825 MS ~ 3 1 5 MS 21M5 NAS 1021 NAS 679 NAS 1291 Twgue L i m i n irrlbs 9 15 40 85 110 300 410 600 780 1.500 1.800 3.300 4.200 6.- 10 15 45 65 110 280 410 580 870 1.250 1.900 2.403 3.~10 5,- 3 5 15 25 45 110 160 230 270 560 750 950 1.250 2.300 Min 25 80 1 M 200 520 770 1.100 1.250 2.660 3.550 4,500 6 . a 1l.mO SDI S h u AN 320 AN 364 NAS 1022 MS 17826 MS 20364 Toque Limltr 8n.lbs . 6 10 30 40 70 170 260 560 410 BBO 1.200 1.500 2.000 3.850 M u 30 100 145 250 630 950 1 . m 1.550 3.200 4.350 5.500 7.- 1 3 . W Min 15 50 70 120 300 450 650 750 1.600 2.lm 2.700 3.600 6.600 Max 20 60 90 150 400 550 800 950 1.9W 2.690 3.300 4.400 8.000 PIPER COMANCHE SERVICE MANUAL TABLE 11-ILA. FLARE FITlTNG TORQUES 1 HANDLING AND SERVICING TORQUE - INCH-POUND Added: 411M1 TUBING OD INCHES 118 3 16 1I4 5116 W8 1 I2 518 W4 1 1-114 1-112 1 -34 2 - - - - STEEL TUBING FLARE AND 10061 MINIMUM MAXIMUM - 90 100 135 150 180 200 270 300 450 500 650 700 900 1000 1200 1400 - - ALUMINUM - ALLOY TUBING FLARE - AND 10061 OR AND 10078 MINIMUM MAXIMUM - - - 40 65 60 80 75 125 150 250 200 350 300 500 500 700 600 900 600 900 HOSE END FllTlNG AND HOSE ASSEMBLIES MINIMUM MAXIMUM - 70 100 70 120 85 180 100 250 210 420 300 480 500 850 700 1150 PIPER COMANCHE SERVICE MANUAL FIGURE 2-0. JACKING ARRANGEMENTS 2-11. Juldm& The jrplvle u provided wirh a jack p d on ach nuin spar jun a d ~ o a r dof the rmin lrndiig gear and suppon pairion by rn.kmgur of the d skid. ( R e f a ro Firc 2-9.) To jack the airplane. p n m d +r follow: a Place the julu u n d a the jack pdr b. Ameh the uil luppon to the ail skid. Place a p p r o x k t d y 400 pounds of b.llur on the suppon to hold the uil down. Be sure 10 apply sufficient d NPPOK ballast: 0th- the airplane w i l l up forward and fall on rbe fun- nose sccdon. r ILiK the jukr evenly u n d all r h r e wheh clear the floor, 2-12 W W i q . (Refer to Figure 2-10.) r Block the m i n gear oleo m c r in there fully extended posidon and the nose g a r at 2.50 inch- urcruion. Inflate all drcr to the r q u k d prrrarrcr. (Refer to Table 11-1.) b. Place the tiredc on three individual tuln by posidoning a r m p of the same h%ht u the d o being used in front of each landing g a r wheel. Poririon the s d a in front of rhc nmpr and tow the aircraft onto the xrlea. (Refer to P a n p p h 2 - l i for rowing p r o d l u a . ) Remove the ramp so they will nor interfere with the r u l s . Levti the aircrnfr per i n m c r i o n s given in Paragraph 2-1 3. c Rocecd to wash the aircnft in accordance with i n m a i o n s given in m u d AC 43.13-1A. I HANDLING AND SERVICING REVISED: 4l3178 PIPER COMANCHE SERVICE MANUAL 2-13. (Rcfa t o P&urc 2-11 and 2-12.) The rLEnfr nuy bc levdcd while on ja& or duMg the w c i g b g pmccdurc. (Refa to F'mgcqh 2-12 for weighing) r To l o ~ r u d i a d yI d the air& p d y wirbdnw the two INeliql screws on the s d c of the m e . Rcfa m F i 2-11 or 2-12 for t h e l c d i q loadon on the p.rdculu airmft being &mi. Use r levd long enough m e n m d lorran che two wrer h d b. To pur the aircnfI on jnckr. refa to P u a p p h 2.11. c. To pur the aircnfI in a l o n @ r u d d y I d poridon for w-ing or ~iggiq,f i m block rhc mlin g a r oleo m u m w their full a t a d o n and the n m gcrr to 2.50 i n c h a . NOTE AU drcr should be u n o m d i d a d o n pressure Dmoce the nose whed drr und the l e d paidon u obtained d To l u d y levd the a h a f t . place a levd m a the bulkhead ro which the b.gkge door ~~JIF b n c k m arc atuched or on the h u w d o n ch.nocl of che fiswrll bulkhead. (Refa to Figures 2-1 1 or 2-12 for the p.rd& loation of rhe air& being urviccd) Should equipment or o t h a o b d e s hinda p h a q the level direcdy on the chumd, urc two spcm of equal length betwan the level and the c h w d ro bring the 1 4 above my o b d a r To put the lkFnft into a l a d y level position, rrire or l o w r one wing by adjusring the jack or if the aircraft is on the ground or on xalo by deflating the appmpriare tire und an accunre level roding u obuined. HANDUNG AND SERVICING I REVlSED:VU)I PIPER COMANCHE SERVICE MANUAL Longitudinally Laterally FIOURE 2-11. LEVELINQ AIRPLANE P&aCl80, m,260. Lrbl N o r aCUlQl m 2444s. 244M a aCUBg md P A - 2 U I O Longitudinally Latarally FIGURE 2-12 LEVELING AIRPLANE PA-24-ZSO, *id N a . 244247.244300 and up HANDLING AND SERVICING ADDED: 44M8 PIPER COMANCHE SERVICE MANUAL 2-14. Mooriq. The a i r p h e should be m o o d m insure im immovabdky, pmtecrion and s a n i t y urrda vuiour w a r h a condmom. The followiq procedure giva the inanretiom for pmpcr mooring of tbe * h e . r H a d the a i r p b e into the wind if p d k . b. Lock tbc d a v n and snbdamr c o ~ ~ o l r uiag the b n t uu b d t or conrml h e blocks r BlocL the w h o h L S- d c d o m r o w to wiq dcdom riqp and d e ui~skid at approxima.tdy 4~-&grec @a to the p u n d . Lerse nrfbdent d u k to amid dam* to the aircraft vbm tbe roper coumcr due to moknrre. U x quare or borline b o a Do not u x slip knots. M d i d o d prcplndom for brgh am& include ndng dedown r o p r fmm the h d i n g gerr fork, and rcculing the mdder. 2-15. P d i u & Whm p u k q the iirplne. irrrufc that it ia snfficiendy pnxmcd .pinn advcm w a r b u conditiom a d pracnm no d q u m o t h s rircnfr When puking chc r L p h for m y 1- of time a ovemighr, it is recommended thu it k w o r c d u in Pul(p.pb 2-14. a To park rhc r i r p h c . h a d it into the rind. if po3ibk. b. Set Qe padung bmke by applying row pressure against rhe top of the bmkc pedals or pull b.& on ehc brake l c m m d at Ehe m e time pull out on the bnke 7"b d l c , located at the left of the control p a n d To m l a u Qe p d c i q bnke. apply toc p- on tbc pedals and pvrh in on tbe p a r k q bnkc handle. N O R To prevent damage to bnke drum. an should be taken when b n k a thor ae a v e r h a d or dudng cold warber when accurnulrtcd moLNfc rnry f r s n c rbe bnkc. HANDLING AND SERVICING ( R M S E D : YUn PIPER COMANCHE SERVICE MANUAL 2-16. Lackins Alrpl.ac The d m md b w q c doom arc provided wirb a key lock The p m e key CM be uud to o p c n ~ cb o d door lo& 2-17. Torins 'Ibe airplane may be m d by vdng rhe nou whed t o w i u g l ~ t up1widc4 or p o r a equipment that will not dunyc or clluc aces sniu to the oat gerr assembly. On PA-24-180. 250 ad 260 .L& wich Said bmba# 2 4 4 3 3 0 to 2 M 2 4 6 . 2 W 2 4 . 9 to 2 4 4 2 9 9 a d PA-2-0 the maily b u i nowed on che undcnide of chc haahelf in the b y l y comprrmer On PA-24260 Serial Numbm 24-4247. 2 4 4 9 9 and up it E lprChdm the f o d vcdon of the nuin Ipr cmr. When taming w& power equipmar do not nun che lrov g a r beyond i n 2 0 d q r ~in eirha W o n fmm carer, u thb hL d t in dam* to the n a c g a r md nee* mechanism. 2-18. T s d q Before lmmpring m taxi the airplne. gra~ndpnromd should be checked our by r qwlified $or or o r h a nponrible pcnon. Engine smting and a h u d o m proccdura dould be covered rc d L Whm it u uceruincd thot the p m p d l a b d blast +od uri MI are clor. apply powa ro sun the taxi mll md perform rbe foIloriag chalrr: a T u i f o n r d r few f c a .Idapply b n k a to deemmine rhdr dfcmkn5s. b. T d wid pmpelkr ur in low pst& high RPM scUiq. c. while uxiing. makc digbt turns to ascaain the d f e c r i w a # of ncoir(. d Obrcnc wing dcmncea wben axiiag n e u b u i l d i q ~or h c r n r d o a r y objscn if possible, stxion a guide ourride che rirplrne m obsemc c. When axing on uncrm ground. look for hola md m a f. Do not o p o u . che engine u lugh RPM when rnnnirq up or uxiing aver ground concaking loose a o n a , gram1or any loose material that nuy cwr damage to pmpdlcr blades. 2-19. E x d Power Reapode. 2-20. Opuuion of Ex& P w a IIeap&~.blrTbc cncmal p w e r n r c p u d e on PA-24180.250 and 260 airplsna with S a d Numben 24-2299 m 244246 inclusive. 2 4 4 2 4 8 to 2 4 4 2 9 9 inclusive a d PA-24400 Scrd Numben 26-2 md up. b l o a d on the nght side of rhe fuvkge aft of d o n 157. On PA-24-260 airplane wi& Sairl Numben 244247. 2 H 3 W to 2 4 4 8 0 4 and up. it u locared on rhc right side of the engine n d e just forward of the 6rcwalL When us@ the c d powa rrccpocle for rrudng or opendon of any + h e quip- place the mum witch in rhe OFF position before imemng or rcmoving the powa plug. The powa comrnor plug assembly is stored in the b q q e complmnenr HANDLING AND SERVICING I RMsED:YM PIPER COMANCHE SERVICE MANUAL 2-22 aaaiq Oaqmmmst Bcfm danin# che engine wmpumvnc place a lpip of 9pc on the mapem w o to p-t any s o l w r from m m i q cheu unio. r PkeaLrppnuadcrrh.cagiocmat&-. b. W~chthe en@e c u d i q mood, spny o r brush the m*e rirh solmu a r m k m of sokcm mdd-, ~rdakcdl r m . y b c n c c s ~ r g r o b m r h u c u t h u ~ r p n y e d r b m h u v y ~ m d ~ depado hm c d l e m d in ordu to clan chon. Do nor spny solvent iam b e geneam or rlrmuror. -. or .ir intaka c AUow che solvent ro remain on the w e from fhe to an m i n u t s then rinw the engine dun with d d i w d solvent and dm m dry. Do not o p n a until e- solvent h n - p a d or orhawise becnrrmwed d Remwe the pm- c w e n fmm rhc -L r Lubdcroc c o d , bcniqh e * erc.. pa Lubriatim Q P ~ Fi@= 2-20thm 2-22 2-23. Qaaiq Lading Geu. Before c h n m g che lading gen. place r p b i c m e a similar mmlterLl over me whed and bnke .Pembly. a PLce r pan under tbe gnr to cauh w a r b. Spray or bnub che gear a u wizb roivtnt or a mixnve of solvent and dcgmwcr, r daLed I t may be nu- m bnuh ucu t b u vac sprayed w h m huvy p u e and dirt deposrr h.H collected in order to dcrn thcm c. AUm the s o l w t to mnab on the gnr form five to r m minuto. then rinv tbe g a r with a d d i d o d solvent and d m to dry. d. Reman the cover from the whel and remare the cuch pan. r Lubricuc rhc g a r per lubriauon Qa.F@= 2-21. 2-24. aaaiq Ex- S m . The airplane should be wuhed with r mild soap md water. hush abndve or a l l u h c soaps or dctwm used on painted or plaaic dlm could make ~ t c h o or aux corrosion of menl surface. Cover areas where cleaning d u d o n could aur damrgc to wmh the airplane. the following procedure m y be u r d : I CAUTION When hosing down aircraft avoid directing water in the fuel tank vents. drain tubes and around the sealed cover plates and filler cap access openin@. HANDUUQ AND SERVICING Revised: 9' 10: 79 PIPER COMANCHE SERVICE MANUAL a. Flush away loose dirt with water. b. Apply cleaning solution with a rag, sponge or soft bristle brush. c. T o remove stubborn oil and grease, use a cloth dampened with naptha. d. Where exhaust stains exist, allow solution t o remain on the surface longer. e. Any good automotive wax may be used t o preserve the painted surfaces. Soft cleaning cloths or chamois should be used t o 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. 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 plasticcleaner. Used a soft cloth or sponge using a straight rubbing motion. D o not harshly rub surfaces. c. Remove oil and grease with a cloth moistened with kerosene. NOTE D o 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. D o 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. T o improve visibility through windshield and windows during flight through rain, a rain repellent such as REPCON should be applied t o 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 Panek 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 din. For soiled spots. use a non-inflammable dry-cleaning fluid. 2-28. Servicing. 2-29. Introduction to Senicing. 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 SERVlClNG REVISED: 4110181 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 bc visually inspected to 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 serbice and overhaul instructions are listed in Section VI - ~- - FIGURE 2-13. LANDING GEAR STRUT (EXPOSIIRE) 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 ) I f 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 s h o n 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 I f the oleo strul oscillates with long strokes (approximately three inches) and the airplane continues to oscillate after the rocking force is remobed. 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 t o Section VI. Deflate rtrut air prersure before disassembly REVISED: 4/3/78 t HANDLING A N D SERVlClN PIPER COMANCHE SERVICE MANUAL 2-34. PUiq Olco S m a To 611 the nose or m.i. g a r d m suut airh fluid (MIL-H-5606). w k r h a it be only the addition of a small amarnt or if the unit h a been completely emptied md WUrrquirr a Lyec nmounr it should be filled rr fdlorr: Do not rdnr air by w o v i q the m t nln core ar 611a plug. D c p m the n l v c core pin uud sllt c h b a prrrrurc has diminidid Dtrr and foreign pvcider form around the 6 U a plup of the hdiq gar mum therefore. before attanp* to mnon t h e plug. the tops of the IOU- should be d c w d wirh compmred air d l o r with r dry type d v e n ~ . r P k e the airplane on jack (Refern, JdN.Pangraph 2-1 1.) b. P k c a p m u n d a the gear to u t c h rpdhge. c. At the fills plu& relieve air pracure from the s m ~ rh&g chmbcr by m o v i n g the up from the air slln and dcprcsiag the vlhn: core d T h m are r r o methods by which the xnrt c h m k may be filled and thoc are rr follow% F ' i Mahod: 1. Ranovc the valve core from the filler plug u the mp of rhc nose g a r mut houri- or at the m p inboud d e of the main g a r howin& A U a the fdcr plug to rrmdn kdld 2. Attach one end of a c l a n ptvdc hose to rhe vlln xem of the m a plug and submagc the 0th- end in a c o n m n a of hydraulic fluid. An airtight comemion b necevuy bcrvccn the pludc mbc and the d v c am. Without such a connection, a mull amount of air WUbe sucked into the deo m t during n c h u q u e n a , ieruldng in an i n o b e amount of air bubbla and a prolonged fwopendon. 3. Fully comprco and a u n d the mt thus dnwing tluid from the fluid container m d expelling air from the m r chamber. By watching the B u d ppu through the p k O c hox, it c m be deramined when the suut is full m d no air is preant in the chamber. 4. When air bubbler cease to flow through the how. comprcu the s m t fully and rcmwe the hox from the valve ncm. 5. With the s m t compressed. remove the fder plug ro damnine that rbe fluid l e d is visible up to the bottom of the fillex hdc. I HANDUNQ AND SERVlClNG PIPER COMANCHE SERVICE MANUAL 6. With the oleo strut fully compressed. reinstall the core in the filler plug and the plug in the str 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 battom 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 bringthestrut down to the properextension.) Beforecappingthevalve. 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 t o 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- IS.) The brake system reservoir should be filled t o the level marked on the reservoir. with the fluid specified in Table 11-1. 2-39. Draining Brake System. T o 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 SERVlCl@ PIPER COMANCHE SERMCE M A N U A L FIGURE 2-14. BRAKE RESERVOIR FIGURE 2-15. BRAKE RESERVOIR PA-24180 and PA-24-250. Serial PA-24180 and PA-24250, Nos. 24-1 t o 24-2298 inclusive Serial Nos. 242299 and up, PA-24-260 and PA-24400 2-40 Tires. 2-41. Servicing Tires. T h e tires should be maintained at the pressurespecified in Table 11-1 When checking tire pressure. examine the tire for wear. cuts. bruises a n d slippage. 2-42 Power Plant. 2-43 Servicing Power Plant. Regularly check the engine compartment lor 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 V I I thru VllC o f t h i s manual and in the appropriate manufacturer's manuals HANDLING A N D SERVICING PIPER COMANCHE SERVICE MANUAL 245. RopdLr. The p 1 0 p d k bhdCS. S P ~ M md Vbibk hub lurfvs thould bc md impmed frequady for bmy,endu d oil !m&e Nicks t h d d be w d fmm the-lading cd@ of cbe bhdm in acmdamc rirh appLiable QMreg&- or imamcdom f o u d in M o m Vl1 dm VllC The k c of a c h blade r h d d be prinocd when ~ a r r yrich a flat print to r m r d ghc. To p m t camdoe. rip rurf.co rirh a l@t oil or wax. The bLds rhoule be checked th Q q turn fredy on the hub pilot m k by rockins the bLdcr b.cL aod for& Qma$b Qe di#htfreedom allowed by tbc piuh ch.agc mech.nim. tukiclte the p m p d l a u. 100 b n u in- in accordance with rhc Lubricldon Qm,P i m 2-20 d m 2-22. Ascuain pmpcUa b chaqed m the pmpr cbrmber pramue. Addiriod &a informanon for dre p m p d l a m y be found in Seaions VII &m~VUC. 2-46. M u d o n Air mca. 247. Scrv*iq Induction Air PUra. Due to tbe puiy of p o w p h o uud on the &our PA-24 modd airpha, rcfcr to tbe Po- Plant W o n MI hVlIO for the p d & induction d t a beirq vniad 249. FSio(t QdT v l t r Obsavc dl rquirai prccaudoru for handlina gasoline FilLtbe fuel rrnlu with fud specified in Table 11-1. On the PA-24-180, to obtain che nvldud fuel quantity of 30 gallom toul, or 25 @OIU per tank. KIICcelh arc Wed only to tbe borrom of the filler n& which mad. into chc fud c d l about 1 incb. To obtain rhe sondud plw mavc qtundry of 60 @oos tbe cdh arc Qlcd m the top of tbe filler neck. On rhc PA-24-250 and PA-24-260. m o b a h the mDd.rd fuel quanury of 60 gallom toul. or 30 gallons p a tank, the fuel c c b are mrnplerely tilled. If ruxiIiuy fuel c,dh arc i d e d (15 gal. o.)the hd qvrndty b in-d to 90 galloar On che PA-24-4UJ. w obain sandud fuel quantity of approximnefy 100 gallom, fill both inboud ccb complacly and tbc ourboud ells until fuel a p p n n at the borrom of a h fud cell when apparing &mu@ tbe f9cr neck. To obuin d a d plw rcmve. 130 @low fdl the ourbovd cdlr mmplmfy. CAUTION Accumalation of water in the fuel tanks could cause rough engine operation or complete power loss if the water freezer during cold weather operation. Therefore. to keep condensation in fuel tanksat a minimum. refuel the aircraft after each flight. HANDUNG AND SERVICING Revised: 9 10: 79 PIPER COMANCHE SERVICE MANUAL FIGURE 2-16. FUEL STRAINER A N D DRAIN FIGURE 2-17. FUEL SELECTOR A N D DRAIN PA-24180 and PA-24250. Serial Nos. PA-24400 242299 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 a n easy drain valve is mounted under the right forward section of the fuselage. The fuel strainer drain (Figure 2- 16) on PA-24- I80 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 isdrained from the cockpit by lifting up the red knob located in the center of the fuel selector The fuelstrainer should bedrained 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 t o flow out t o 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 selectingtheright and I left auxiliary fuel tank 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 l and the aircraft should be hangered to thaw out. and drained thoroughly REVISED: 9110179 l C l l HANDLING A N D SERVICING P I P E R COMANCHE SERVICE MANUAL 2-51. Draining Fuel System. Drain the fuel from the system by opening the drain valve at the bottom of t fuel strainer bowl. or removing the bowl. 2-52. Electrical System. 2-53. Servicing Electrical System. Servicing the electrical system involves adding distilled water to the battery t o maintain correct electrolyte level. checking cable connections and checking for any spilled electrolyte that would lead t o 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 IX 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 1 O F F control mounted on the imtrument panel. The stationary cylinder is located aft of the baggage area o n the left side of the fuselage The cylinder used is a n ICC or D O T 3 A A 1800 classification with a 63 cubic foot capacity at a working pressure of 1800 psi. High pressure oxygen is routed from thecylinder and regulator t o the pressure gauge mounted in the upper portion of the aft cabin bulkhead. Low pressure oxygen is routed from the cylinder and regulator t o the outlets and masks whenever the control knob is oulled t o the ON oosition. Each outlet has a sorine loaded valve . . which prevents the flow of oxygen until a mask hose is engaged into the outlet. I 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 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 D o not allow foreign matter to enter the oxygen lines. The presence of foreign matter in the high pressure lines can cause an explosion. When coming i n contact with oxygen equipment keep hands. tools and clothing clean - hospital clean. c 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 oxygcn 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 SERVICIN9 PIPER C O M A N C H E SERVICE M A N U A L TABLE 11-Ill. INDICATED OXYGEN CYLIKDER P R E S S U R E S FOR GIVEN AMBIENT T E M P E R A T U R E S 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. T o fill thc oxygen cylinder. open the access door. remove the cap from the filler halve 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 T E M P E R A T U R E OF l I0 100 90 80 70 60 50 40 KOTE IKDICATED CYLINDER PRESS PSI 1980 1935 1890 1845 1800 1755 1710 1665 I f the airplane's oxygen cylinder pressure is below 50 psi. thesystem should be purged a s described in Paragraph 2-71. b To obtain the correct filling pressure for the oxygen cylinder at various ambient temperatures a *. chan has been includtd for your convenience The pressures given are not exact. but sufficiently accurate for practical purposes of working pressure between 1800 and 2400 psig cylinders The cylinder should be allowed to cool to a stabilized temperature after filling before checking against the figures given in Table 11-Ill 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 SERVICI%G 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 bas 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 retill 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 twc-cylinder systems, use to approximately 600 psi, then return for filling. e. 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. Inspeetion and Overhaul Time Limits. It is recommended that inspection and overhaul be conducted I 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 I 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 1116 diameter vent hole in the side of the upper regulator housing is 10 ccl 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 PIPER COMANCHE SERVICE MANUAL TABLE Il-IV INSPECTION - OVERHAUL TIME LIMITS 2-60. Testing for Leaks. Apply detector fluid type CD-I solution or its equivalent The solution should be shaken to obtain suds or loam. The suds or foam should be applied sparingly to thejoints of a closed system Look for traces of bubbles No visible leakage should be found. Repair or replace any defective pans and retest system With the system pressurized to service pressure. further tests can be made. The rate of any leak should not exceed one percent of the total supply per 24 hour period All traces ofthedetector fluid should be wiped off at the conclusion of the examination PARTS Regulator Pressure Gauge High Pressure Lines Low Pressure Lines Outlets (Cabin) External Recharge Valve Masks 2-61. Maintenance. a. Check that all lines have sufficient clearance between all adjacent structures and are secured in place Also, check the cylinder to be sure it is securely mounted. b. Check the cylinder for the ICC or DOT identification number and for the date of the last FAA inspection and test. c. If cylinder is completely empty. it must be completely disassembled and inspected in an FAA approved facility before recharging . . d. Any lines that are defective should be replaced with factory replacements. e Clean all lines and fittings as described in Paragraph 2-62 f Use Ribbon Dope Thread Sealant (Permacel 412) on male end. 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. g. Refer to FAA Manual AC 43 13-IA for more service details. 2-h2. Cleaning Operations. To remove oil and grease from tubing and fittings. one of the following cleaning methods may be used a First Method. I A vapor degreasing with stabilized trichlorethylene conforming to specification MIL-T-7703 shall be used INSPECTION 300 Flight Hrs 300 Flight Hrs. 300 Flight Hrs 300 Flight Hrs 300 Flight Hrs. Each Use Each Use a ADDED: 4/3/78 OVERHAUL 5 Yrs. 5 Yrs 5 Yrs. Replace Every 5 Yrs Replace as Piecessary HANDLING AND SERVICING 1 I P I E R COMANCHE SERVICE MANUAL 2. lor m b i i c*.n and dy with a sueam of c h . dried. 6 l w d air. Cafe rh.U be taken m insure h t the interior o f the a4and fiainp are thm-y d a n d b. Second Method: 1. Qlwb r*h uaptb:onfamhg to tpcci6cadon m-N-95. 2. B l w d ~ l o d d y o f f d m b t r i r h w ~ p u m p d a i r . 3. Flub Mand-icing fluid mnfonningto spc@adon MIL-Q-566or mhydrnu ethyl d c a o l . 4. Rinvrhmughly rirh fmIl.nra. 5. Dry F h ~ ~ I y rirh a scram of dan. dried. wrer pumped air or by ha* at a rempmrure of U O a m 300.Q for a m i n h k period 6. The s o h a m y be r e n d providd they do mt become a & c~maminntedvirb 05 This cordidon hdlbe deDcrmined aa foUow: (a) E n p o ~ 100 d t e n of rhe Liquid to dryno# in a wdgbd g L u dish Evrpondon may be accomplished by haw u 200 * F fm onehaif h a . (b) A h a mpomion. cod and ragb the raidue. The m l w t W not be uxd if the raidue amb 100 milliplmrinwcigh~ c T h i . Mcthod: 1. Flmb airh bot inhibited .Uuline d a n e r und kh m oil and gcur 2. RMc dlaoughly rid tidl mta. 3. Dry rhoroughly wirb a arolm of d a n , dried. water pumpd air or by h a t k g at a tcmpaunre of 250'm 300 'F for a minhk pmod. 2-63. Remod of Orya CyBDds a d Rcphmr. The cylinder and n(pkror are l o a d on the left side ofthefudagc+frof theb.llpec.ruatnrdon157. r R c m m the lccsr pmd from the mr rrtl of the mmpuuncnt to gain accar to the cylinder and rcgulwr. On akplana wirh vrhl rmmbar 244300 and up which h v e rbe 5th and 6Fh vrn h d l c d . it ia necmvy to tcmovc the m u and then the back a c c a pnd. Bc mrc the nlve o