761-590 - SENECA II SERVICE MANUAL - PA-34-200T

4-12. Mixing of Epoxy Patching Compound ....................................... 1F9 4-13. Welding Repair Method .................................................... 1F9 4-14. Repairing of Cracks ..................................................... . IF10 4-15. Various Repairs ........................................................... IF11 4-16. Repair of Stress Lines ...................................................... 1F12 4-17. Repair of Impacted Damage ................................................ IF12 4-18. Control Surface Balance Tool ................... ............................ 1F16 4-19. Aileron and Rudder Balance Configuration ................................... IF18 4-20. Stabilator Balance Configurations ........................................... IF19 5-1. Control Column Assembly .................................................. IG1 5-1a. Correct Method of Installing Rod End Bearing ................................ IG4 5-2. Aileron Controls .......................................................... IG5 Revised: 3/16/81 1A5 Island Enterprises PIPER SENECA II SERVICE MANUAL LIST OF ILLUSTRATIONS (cont.) Figure Aerofiche Grid No. 5-3. Bellcrank Rigging Tool ..................................................... 1G9 5-4. Aileron Rigging Tool ...................................................... IG10 5-5. Stabilator and Stabilator Trim Controls ...................................... 1G13 5-6. Stabilator Rigging Tool .................................................... IG16 5-7. Methods of Securing Trim Cables ........................................... IG16 5-8. Rudder and Brake Pedal Assembly ......................... ................. 1G22 5-9. Rudder and Rudder Trim Controls .......................................... H I 5-10. Rudder Rigging Tool ...................................................... 1H3 5-11. Clamping Rudder Pedals ................................................... 1H3 5-12. Rudder and Stabilator Travel Adjustment .................................... I H4 5-13. Flap Controls ............................................................. 1H9 5-14. Flap Step Adjustment .............. ........................................ 1 H II 5-15. Flap Rigging Tool ......................................................... 1HI1 5-16. Fabricated Aileron Bellcrank Rigging Tool ........................... ....... 1H 13 5-17. Fabricated Aileron and Flap Rigging Tool .................................... 1H14 5-18. Fabricated Stabilator Rigging Tool .......................................... H 15 5-19. Fabricated Rudder Rigging Tool ............................................ H 16 6-1. Schematic Diagram of Hydraulic System ..................... ................ 117 6-2. Hydraulic System Installation ............................................... 118 6-3. Hydraulic Pump/Reservoir, Exploded View ................................... 1111 6-4. Test and Adjustments of Hydraulic Pump .................................... 1114 6-5. Pump Mounting ....................................................... .... 1115 6-6. Free-Fall Valve Assembly ................................................... 1115 6-7. Gear Actuating Cylinder .................................................... 1116 6-7a. Installation of T-Rings .................................................... . . 1117 6-8. End Gland Locking Device ................................................. 1118 6-9. Nose Gear Actuating Cylinder Installation .................................... 1120 7-1. Nose Gear Oleo Strut Assembly .................... ......................... 1J9 7-1a. Nose Gear Service Tolerances ............................................... 1J 1 7-2. Nose Gear Installation ..................................................... IJ16 7-3. Clamping Rudder Pedals in Neutral Position .................................. 1 K2 7-4. Rudder Pedals at Neutral Angle ............................................. 1K2 7-5. Main Gear Oleo Strut Assembly ............................................. 1K4 7-5a. Main Gear Service Tolerances ............................................... 1K6 7-6. Main Gear Installation ..................................................... 1 7-7. Aligning Main Gear ........................................................ 1 K16 7-8. Toe-In/Toe-Out Adjustment ................................................ IK17 7-9. Adjust Nose Gear Down Limit Switch ........................................ 1K19 7-10. Adjust Main Gear Down Limit Switch ....................................... 1K19 7-11. Throttle Warning Switch ................................................... I K20 7-12. Nose Wheel Assembly ...................................................... 1L1 7-13. Main Wheel Assembly ..................................................... 1L3 7-14. Wheel Brake Assembly ..................................................... 1L4 Revised: 12/08/83 1A6Island Enterprises PIPER SENECA II SERVICE MANUAL LIST OF ILLUSTRATIONS (cont.) Figure Aerofiche Grid No. 7-15. Removal and Installation of Anchor Bolts .................................... IL5 7-16. Brake Master Cylinder (Hand, Parking Brake) ................................ 1L7 7-17. Brake System Installation ..................... .............................. L8 7-18. Brake Cylinder (17000) (Toe Brake) .......................................... 1L9 7-19. Brake Cylinder (10-27) (Toe Brake) .......................................... 1L9 7-20. Brake Cylinder (10-30) (Toe Brake) .......................................... IL10 7-21. Brake Reservoir ........................................................... IL14 7-22. Bleeding Brake ........................................................... 1L14 8-1. Engine Cowling Installation ..................... ............................ 2A14 8-2. Cowl Flap Installation ........................................ 2A14 8-3. Propeller Installation ....................................................... 2A 16 8-4. Typical Nicks and Removal Method ......................................... 2A17 8-5. Propeller Governor ........................................................ 2A20 8-6. Engine Installation ......................................................... 2A23 8-7. Schematic Diagram of Turbocharger System .................................. 2B5 8-8. Induction System Installation ............................................... 2B6 8-8a. Magneto Assembly ........................................ 2B9 8-9. Contact Spring Inspection ..................... ............................. 2B11 8-10. Contact Points ......................................................... ... 2B12 8-11. Impulse Coupling .......................................................... 2B12 8-12. Flyweight Clearance of Impulse Coupling ..................................... 2B13 8-13. Rotor Holding Tool Installed ............................................... 2B14 8-14. Timing Kit Installed ........................................ 2B14 8-15. Cast-In Timing Marks ...................................................... 2B15 8-16. Fabricated Pointer ......................................................... 2B 15 8-17. Engine Timing Marks ...................................................... 2B17 8-18. Removing Spring From Lead Assembly ...................................... 2B 19 8-19. Assembly Tool ........................................ 2B20 8-20. Assembly Tool Application ..................... ............................ 2B20 8-21. Measuring Lead Assembly Length ........................................... 2B20 8-22. Ferrule Seating Tool ....................................................... 2B22 8-23. Measuring Wire From Top of Ferrule ........... ............................. 2B22 8-24. Needle ...... ....................................... 2B22 8-25. Installing Grommet Over Lead Assemblies .................................... 2B22 8-26. Lead Assembly Installed in Grommet ........................................ 2B23 8-27. Wire Doubled Over For Installation of Eyelet ................................. 2B23 8-28. Ignition Schematic ......................................................... 2B24 8-29. Removing Frozen Spark Plug ........................................ 2C3 8-30. Lubrication System Maintenance Points ...................................... 2C6 8-31. Schematic Diagram of Fuel Injection System .................................. 2C8 8-32. Fuel Injector Nozzle Assembly .............................................. 2C9 8-33. Engine Controls ........................................................... 2C10 8-34. Idle Speed and Mixture Adjustment Points ................................... 2C 12 8-35. Sectional View of Altitude Compensating Fuel Pump Assembly ................. 2C16 8-36. Exhaust Bypass Valve Screw ................................................ 2C18 Revised: 3/16/81 1 1A7 Island Enterprises PIPER SENECA II SERVICE MANUAL LIST OF ILLUSTRATIONS (cont.) Figure Aerofiche Grid No. 9-1. Fuel System Schematic ..................................................... 2D7 9-2. Fuel Cell Installation ....................................................... 2D12 9-3. Fuel Gauges ............................................................... 2D20 9-4. Fuel Filter ........................................................... ..... 2D20 9-5. Fuel Selector Valve ........................................................ 2D23 9-6. Slider Resistor Terminal .................................................... 2EI 9-6a. Resistor Set-Up/Test for Fuel Quantity Gauge ................................ 2E3 9-6b. Maximum Deviation of Fuel Quantity Gauge Needle ........................... 2E4 10-1. Gyro Pressure System ...................................................... 2E14 10-2. Pitot-Static System, Serial Nos. 34-7570001 to 34-7670136 incl .................. 2E16 10-2a. Pitot-Static System, Serial Nos. 34-7670137 and up ............................ 2E17 10-3. Instrument Panel ................................................... ....... 2E18 11-1. Switch Panel - For Models Without Primer System ............................ 2F21 11-la. Switch Panel - For Models With Primer System ............................... 2F22 11-2. Removal of Slip Ring End Bearing .......................................... 2G 1 11-3. Removal of Rectifer . .................... .................................. 2G I 11-4. Testing Rotor for Ground .................................................. 2G4 11-5. Testing Rotor for Shorts ................................................... 2G4 11-6. Installation of Rectifier ..................................................... 2G5 11-7. Terminal Assembly ........................................................ 2G6 11-8. Slip Ring End Bearing Assembly ........................................... 2G7 11-9. Testing Alternator ........................................................ . 2G7 11-10. Regulator Diagram .................................................. ...... 2G 10 11-11. Testing Regulator .......................................................... 2G12 11-12. Adjusting Regulator ....................................................... 2G 13 11-13. Application of Overvoltage Control .......................................... 2G15 11-14. Testing Overvoltage Control ................................................ 2G15 11-15. Exploded View of Starting Motor ........................................... 2G17 11-16. Turning Motor Commutator ...................................... ...... .. 2G18 11-17. Testing Motor Armature for Shorts .......................................... 2G18 11-18. Testing Motor Fields for Grounds ........................................... 2G19 11-19. No-Load Test Hookup ............................................ ........ 2G19 11-20. Stall Torque Hookup ...................................................... 2G20 11-21. Landing Light Adjustment .................................................. 2H1 11-22. Adjusting Lift Detector Micro Switch ........................................ 2H2 NOTE Electrical Schematics for Section XI. see 2F18 12-1. Two Year, Magnesium Battery Connections ................................... 2122 12-2. Garrett ELT Schematic ................................. .................. 2123 12-3. Communications Components ELT Schematic ................................. 2J 1 12-4. Emergency Locator Transmitter Schematic (Narco) ............................ 2J I Revised:11/12/82 lA8 Island Enterprises PIPER SENECA II SERVICE MANUAL LIST OF ILLUSTRATIONS (cont.) Figure 12-5. ELT Portable Folding Antenna (Narco) ...................................... 12-6. ELT Using Fixed Aircraft Antenna (Narco) ................................... 13-1. Cabin Heater, Defroster and Fresh Air Installation ............................ 13-2. Heater and Combustion Air Blower Assembly (30,000 BTU) .................... 13-3. Heater and Combustion Air Blower Assembly (45,000 BTU) .................... 13-4. Diagramatic Cutaway of Heater to Show Whirling Flame Action ................ 13-5. Fuel Regulator and Shutoff Valve ........................................... 13-6. Top View - Duct Switch .................................................... 13-7. Wiring Diagram........................................................... 13-8. Primary Power Circuit ..................................................... 13-9. Starting Power Circuit ..................................................... 13-10. Spark Plug Fixture ........................................................ 13-11. Wiring - Test Setup ........................................................ 13-12. Spark Plug Gap Adjustment ................................................ 13-13. Ignition Unit Assembly ..................................................... 13-14. Test Setup for Fuel Regulator and Shutoff Valve .............................. 13-15. Heater Fuel Pump ......................................................... 13-16. Suggested Design for Seal Plates, Plugs, and Caps for Combustion Tube Leakage Test ........................................... 13-17. Test Setup for Combustion Air Pressure Switch ............................... 13-18. Exploded View of Heater Assembly (30,000 BTU) ............................. 13-19. Exploded View of Heater Assembly (45,000 BTU) ............................. 13-20. Exploded View - Combustion Air Blower and Motor Assembly (30,000 BTU) ........................................................... 13-21. Exploded View - Combustion Air Blower and Motor Assembly (45,000 BTU) ........................................................... 13-22. Suggested Setup of Heater Operation Test .................................... 13-23. Wiring Connections for Heater Operation Test ................................ 13-24. Spark Plug Gap Adjustment Tool .......................................... 14-1. Propeller Deicer Installation ................................................ 14-2. Electrical Diagram Showing Cycle Sequence - Phase 1.......................... 14-3. Electrical Diagram Showing Cycle Sequence - Phase II ......................... 14-4. Electrical Diagram Showing Cycle Sequence - Phase III ........................ 14-5. Electrical Diagram Showing Cycle Sequence - Phase IV ........................ 14-6. Typical Use of Dial Indicator ............................................... 14-7. Centering of Brushes on Slip Rings .......................................... 14-8. Wiring Schematic - Electric Propeller Deicing System .......................... 14-9. Brush Block Assembly ..................................................... 14-10. Brush Module Assembly 3E2011 ............................................. 14-1Oa. Alternate Module Stacking Arrangement ..................................... 14-1Ob. Modular Brush Assembly 3E2042-1 (2 Bladed Prop) ........................... 14-10c. Modular Brush Assembly 3E2062-2 (3 Bladed Prop) ........................... 14-10d. Angle of Contact Brushes to Slip Rings ...................................... Aerofiche Grid No. 2J3 2J3 2J9 2J12 2J13 2J14 2J16 2J16 2J20 2J21 2J22 2J24 2J24 2KI 2K5 2K8 2K9 2K17 2K17 2K21 2K22 2L3 2L4 2L6 2L6 2L9 3A12 3A13 3A13 3A14 3A14 3A16 3A17 3A19 3A20 3A22 3A22 3A23 3A23 3A24 Revised: 3/16/81 1A9 Island Enterprises Figure PIPER SENECA II SERVICE MANUAL LIST OF ILLUSTRATIONS (cont.) Aerofiche Grid No. 14-11. 14-12. 14-13. 14-14. 14-15. 14-15a. 14-16. 14-17. 14-18. 14-19. 14-20. 14-20a. 14-21. 14-22. 14-23. 14-24. 14-25. 14-26. 14-27. 14-28. 14-29. 14-30. 14-31. 14-32. 14-33. 14-34. 14-35. 14-36. 14-37. 14-37a. 14-38. 14-39. Propeller Deicer Installation ................................................ Installation of Deicer Boot.................................................. Wrinkled Deicers .......................................................... Sealer Application (Boot) .................................................. Pneumatic Diecer System Installation (S/N's to 34-8070144) .................... Pneumatic Deicer System Installation (S/N 34-8070144 and up) ................. Pneumatic Deicer Boots Operation ........................................... Pneumatic Deicer System Schematic ......................................... Ice Detection Light Schematic ............................................... Portable Oxygen Installation ................................................ Fixed Oxygen System Installation (Optional) .................................. Oxygen Tubing Installations ................................................ Oxygen System Filler Valve Installation ...................................... Oxygen Cylinder and Regulator Assembly .................................... Oxygen Pressure Gauge Installation .......................................... Air Conditioning System Installation ......................................... Test Gauge and Manifold Set ............................................... Manifold Set Operation .................................................... Leak Test Hookup......................................................... Evacuation Hookup........................................................ Charging Stand ........................................................... Charging Hookup ......................................................... Top Dead Center Casting Mark (Sankyo Compressor) ......................... Rotation of Clutch Front Plate (Sankyo Compressor) .......................... Condenser Air Scoop Installation ............................................ Expansion Valve .......................................................... Components Installation .................................................... Air Conditioning Wiring Schematic (Early Models) ............................ Synchrophaser Wiring Schematic Auto Synch/Manual Switch ................... Synchrophaser Wiring Schematic (Phase Adjustment Switch).................... Engine Synchrophaser Installation ........................................... Pulse Generator Installation ................................................. 3B1 3B3 3B6 3B7 3B15 3B16 3B18 3B18 3C9 3C15 3C16 3C17 3C.18 3C18 3C20 3C24 3D5 3D6 3D7 3D9 3D 11 3D12 3D15 3D15 3D19 3D20 3D22 3E1 3E11 3E12 3E13 3E15 Revised:3/16/81 1A10 Island Enterprises PIPER SENECA II SERVICE MANUAL LIST OF TABLES Table Aerofiche Grid No. 11-1. 11-11. II-11A. II-IIB. II-III. II-IV. III-1. IV-I. IV-II. IV-III. IV-IV. V-II. V-II. V-Ill.V-III. VI-l. VII-I. VI I-111. VII-l. VIII-ll. VII-IV. VIII-III. VIII-IV. VIII-VII. IX-I. IX-II. IX-ll. IX-IV. X-I. X-II. X-lll. X-IV. X-V. Leading Particulars and Principal Dimensions .............................. Recommended Torque Values ............................................ Flare Fitting Torque Chart ............................................... Thread Lubricants ....................................................... Conversion Tables ...................................................... Chart A. Inches to Millimeter ............................................ Chart B. Fraction; Decimal Conversions ................................... Chart C. Centigrade Fahrenheit Conversion Table .......................... Chart D. English Vs. Metric .............................................. Chart E. Decimal Millimeter Equivalents of Drill Sizes from 1 2" to No. 80 ................................................... List of Consumable Materials ............................................. Inspection Report ....................................................... Maximum Distances Between Fluid Tubing Supports ........................ Maximum Resistance Values Allowed for Electrical Bonding.................. List of Materials (Thermoplastic Repair) ......... .......................... Balance Specifications ................................................ Control Surface Travels and Cable Tensions ................................ Cable Tension Vs. Ambient Temperature ................................... Troubleshooting Chart (Surface Controls) .................................. Leading Particulars. Hydraulic Pump ...................................... Characteristics. Hydraulic Pump Motor Troubleshooting Chart (Hydraulic System) ................................. Nose Gear Service Tolerances ............................................. Main Gear Service Tolerances ............................................. Toe-In - Toe-Out Correction Chart ....................................... Troubleshooting Chart (Landing Gear) ..................................... Propeller Specifications .................................................. Propeller Chamber Pressure Requirements .................................. Engine Data ............................................................ Fuel Flow Vs. Engine Speed .............................................. Metered Fuel Assembly Calibration ........................................ Limits - Fuel Flow Vs. Brake H.P........................................ Troubleshooting Chart (Engine)........................................... Fuel Quantity Sender Gauge Tolerances .................................... Fuel Gauge Reading Tolerances ........................................... Gauge Readings' Resistance With Fuel in Tanks ............................. Troubleshooting Chart (Fuel System) ...................................... Gvro Pressure System .................................................... Directional Gyro Indicator ............................................... Gvro Horizon Indicator ................................................. Rate of Climb Indicator ......... ....................................... Altimeter .............................................................. IA21 IB2 1B4 1B4 1C8 1C9 1CII 1C12 1C13 1C14 1C15 1D2 1D19 1D19 1F7 1F17 1F23 1F24 1H17 1112 1112 1122 IJ12 1K7 IK15 1L15 2A18 2A18 2A21 2C17 2C18 2C19 2C20 2D20 2E4 2E5 2E6 2E12 2E20 2E21 2E22 2E23 Revised: 3/16/81 1All Island Enterprises PIPER SENECA II SERVICE MANUAL LIST OF TABLES (cont.) Table Aerofiche Grid No. X-VI. X-VII. X-VIII. X-IX. X-X. X-XI. X-XII. X-XIII. X-XIV. X-XV. X-XVI. X-XVII. XI-I. XI-1. XI-III. XI-IV. XI-V. XI-VI. XI-VII. XI-VIII. XI-IX. XIII-I. XIII-II XIV-I. XIV-II. XIV-III. XIV-IV. XIV-V. XIV-VI. XIV-VII. XIV-VIII. XIV-IX. XIV-X. XIV-XI. XIV-XII. XIV-XIII. Airspeed Tubes and Indicator ............................................. Magnetic Compass ...................................................... Manifold Pressure Indicator .............................................. Tachometer ............................................................. Engine Oil Pressure Gauge ............................................... Turn and Bank Indicator ................................................. Fuel Quantity Indicators ................................................. Oil Temperature Indicators ............................................... Exhaust Gas Temperature Gauge .......................................... Cylinder Head Temperature Gauge ........................................ Fuel Flow Gauge ....................................................... Instrument Markings .................................................... Index to Electrical Schematics ............................................ Alternator Specifications ................................................. Starting Motor Specifications ............................................. Hydrometer Reading and Battery Charge Percent ............................ Troubleshooting Chart (Electrical System) .................................. Lamp Replacement Guide................................................ Electrical Wire Coding ................................................... Electrical Symbols ....................................................... Electrical System Component Loads ....................................... Inspection ........ ' Inspection ......... ................................................................ Troubleshooting Chart (Janitrol Heater) ......... .......................... Required Materials for Repair of Propeller Deicer ........................... Mixing of Materials ..................................................... Electrical Resistance ..................................................... Troubleshooting Chart (Propeller Deicer System) ............................ Operating Pressures...................................................... Materials and Supplies for Cold Repair ......... ........................... Troubleshooting Chart (Pneumatic Deicer System) ........................... Oxygen System Components Limits........................................ Troubleshooting Chart (Oxygen System) ................................... Temperature Pressure Chart .............................................. Aluminum Tubing Torque ................................................ Blower System Wire Color Codes ......................................... Troubleshooting Chart (Air Conditioner) ................................... 2FI 2F2 2F5 2F6 2F7 2F8 2F9 2F10 2F13 2F14 2F14 2F15 2F18 2G8 2G21 2G23 2H8 2H20 2H21 2H22 2H23 2K5 2L10 3B3 3B5 3B7 3B9 3B21 3B24 3C7 3C13 3C21 3D1 3D4 3D24 3E2 I Revised:8/10/80 1A12 Island Enterprises SECTION I INTRODUCTION Paragraph Aerofiche Grid No. 1-1. General 1-2. Scope of 1-3. Descripti¢ 1-4. Wing .. 1-5. Empenna 1-6. Fuselage 1-7. Landing Gear 1-8. Brake System 1-9. Engines a 1-10. Fuel Syst 1-11. Flight Co 1-12. Radio 1-13. Cabin Heater, Defroster and fresh air sustem 1-14. Instrument and Autopilot System ............................................... . .... I1A14 Manual ................... ....................... 1A14 ................. .................. .......... 1 . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IA 14 1A14 ge ............................................. IA14 1A14 Gear ............................................ 1 system............................................ 1item ............................................ 1A14 nd Propeller ....................................... 1 em ............................................ IA15 ntrols ...................................... ..... 1A15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1A 15 ater, Defroster and Fresh Air System ......................... 1A15 and Autopilot System ................................ 1A15 Reissued: 10/11/79 1A13 Island Enterprises PIPERSENECAI SERVICEMANUAL SECTIONI INTRODUCTION 1-1. GENERAL. This manual contains service and maintenance instructions for the Piper PA-34-200T Seneca II, designedand manufactured as a versatile airplane in the personal and business aviation field, by the Piper Aircraft Corporation, Vero Beach, Florida. 1-2. SCOPE OF MANUAL. Sections II and III comprise the service part of this manual; whereas, Sections IV through XIV 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 airplane is covered in a separate section. Only qualified personnel should perform the operations described in this manual. The description of the airplane included in this section is limited to general information. Section II gives leading particulars and principal dimensions,along with ground handling, while each major system is described in its appropriate section of the manual For a more detailed description of the airplane, refer to the Owner's Handbook. 1-3. DESCRIPTION. The Seneca II is a six place (seventh seat optional), twin engine, low-wingmonoplane of all metal construction. The following paragraphs provide descriptions of the major components and systems. 1-4. WING. The laminar flow wing is of all metal stressed-skin,full cantilever, low-wingdesign, consisting of two wing panels bolted to a spar box assemblyin the fuselage.The wing tips are removable.The ailerons are cable and push rod controlled and are aero dynamically balanced. The trailing edge wing flaps are manually operated. 1-5. EMPENNAGE.The empennage consists of the fin, rudder, rudder trim tab, stabilator and stabilator trim tabs. The rudder and stabilator are statically balanced. 1-6. FUSELAGE. The fuselage consists of three basic units: the nose section, the cabin section and the sheet-metal tail cone. 1-7. LANDINGGEAR. The tricycle landing gear is of the retractable air-oil strut type, consistingof a nose wheel and two main wheels. 1-8. BRAKE SYSTEM. The standard brake system is operated hydraulically by dual toe brakes located on the rudder pedals or by a hand lever connected to a singlebrake cylinder below and behind the left center of the instrument panel. Reissued: 10/11/79 A14 INTRODUCTION A14 Island Enterprises PIPER SENECAI SERVICEMANUAL 1-9. ENGINES AND PROPELLER. The airplane is powered by two Teledyne Continental six cylinder, direct drive, wet sump, horizontally opposed turbocharged engines. The left engine rotation is in the right-hand direction while the right engine rotates in the left-hand direction. The propellersare Hartzell full feathering, constant speed units controlled by a governor mounted on each engine. 1-10. FUEL SYSTEM. The fuel system consists of two interconnected aluminum fuel tanks in each wing, having a combined capacity of 49 U.S. gallons, for a total capacity of 98 U.S. gallons. With optional fuel tanks, each wing will have a combined capacity of 64 U.S. gallons, for a total capacity of 128 U.S. gallons. Incorporated in the system are selector valves, gascolators, and electric priming fuel pumps and engine driven pumps. 1-11. FLIGHT CONTROLS. The flight controls are conventional equipment, consistingof a control wheel which operates the ailerons and stabilator, and pedals which operate the rudder. Duplicate controls are provided for the copilot. Trim controls are provided for the rudder and stabilator. 1-12. RADIO. Provisions are provided for the installations of microphone and headset jacks, loudspeaker, and panel space for radios and various avionic equipment. 1-13. CABINHEATER, DEFROSTERAND FRESH AIR SYSTEM. Heated air for the cabin and defroster is obtained from the combustion heater located in the tail cone. Fresh air is supplied to the heater from an intake located in the dorsal fin. The combustion heater has a blower which is used to circulate heated or unheated air through six adjustable outlets. There is a defroster blower, in the same distribution system to provide additional defrost capability when required. There are six overhead fresh air vents supplied by a separate inlet in the dorsal fin. This system can be supplemented by an optional blower. 1-14. INSTRUMENTAND AUTOPILOT SYSTEM. Provisions for instrument installation include panels for engine instruments and advanced instruments, as well as for an Autopilot system. Reissued: 10/11/79 INTRODUCTION 1A15 Island Enterprises SECTION II HANDLING AND SERVICING Aerofiche Paragraph Grid No. 2-1. Introduction ........................................... . 1A18 2-2. Dimensions ...................................... ....... 1A18 2-3. Station Reference Lines ...................................... A18 2-4. Weight and Balance Data ..................................... A18 2-5. Serial Number Plate ...................................... .. 1A18 2-6. Access and Inspection Provisions ................................ 1A18 2-7. Tools and Test Equipment .................................... IA18 2-8. Torque Requirements ...................................... . IA24 2-8a. Torque Wrenches ................. .................................... . IB 2-9. Step, Handhold and Walkways .................................. -1B7 2-10. Ground Handling ...................................... ... 1 2-11. Introduction to Ground Handling ............... ......... . 1 2-12. Jacking ...................................... ... B7 2-13. Weighing .......................................... . B8 2-14. Leveling ................... ................... .. . 1B8 2-15. Mooring ...................................... .. . 1B9 2-16. Locking Airplane .................................. . 1B9 2-17. Parking .. .... .................................. IBIO 2-18. Towing ................................... ... ... IBIO 2-19. Taxiing ...................................... .. . IBIO 2-20. External Power Receptacle .................................... IB I 2-21. Operation of External Power Receptacle ...................... IBII 2-22. Servicing ................. .................... ........ IBII 2-23. Introduction to Servicing ................... ............ B IB I 2-24. Fuel System .................... ........................ IBII 2-25. Servicing Fuel System ................................. IBII 2-26. Filling Fuel Tanks ................................... 1 2-27. Handling of Moisture in Fuel System ................................... B12 2-28. Draining Fuel System ................................. 1B12 2-29. Brake System ........................................... . 1B13 2-30. Servicing Brake System ................................ 1 2-31. Filling Brake Cylinder Reservoir ........................... B13 2-32. Draining Brake System ................................ B13 2-33. Oleo Struts ............................................. 1 2-34. Servicing Oleo Struts ................................. IB13 2-35. Filling Nose Gear Oleo Strut ............................. IB15 2-36. Filling Main Gear Oleo Struts ............................ B 17 2-37. Inflating Oleo Struts .............. .................... 1 2-38. Servicing Steering Bungees ................... B........... 119 Revised:8/10/80 1A16 Island Enterprises Aerofiche Paragraph Grids 2-39. Tires ... ................. ....... ........ .. ..... .... 1 B19 2-40. Servicing Tires ..................................... 1 B 19 2-41. Hydraulic System ........................................ . 1B 19 2-42. Servicing Hydraulic System ................... I.......... 1 2-43. Servicing Hydraulic Pump/Reservoir ........................ 1 244. Battery ............................................... 1 B20 2-45. Servicing Battery.................................... IB20 246. Cleaning ......... ...... ........ ... ... ...... ...... ... 1B20 2-47. Cleaning Engine Compartments ...... ............ .... . 1B20 2-48. Cleaning Landing Gear ................................ 1 249. Cleaning Exterior Surfaces .............................. IB21 2-50. Cleaning Windshield and Windows ......................... 1 B21 2-51. Cleaning Headliner, Side Panels and Seats ..................... 1 2-52. Cleaning Carpets ................... .................. 1 B22 2-53. Lubrication ....... .......... ............. . B22 2-54. Oil System (Engine) ................... ................... . . 1B22 2-55. Servicing Oil System ............................. 1 2-56. Filling Oil Sump ................... ...... .......... B.22 2-57. Draining Oil Sump .................................. . 1 2-58. Oil Screen (Suction) .................................. 1 2-59. Oil Filter (Full Flow) ................................ 1 2-60. Recommendations for Changing Oil ......................... 1 2-61. Lubrication Instructions ................... ....... 2-62. Application of Oil ........................ ........ 2-63. Application of Grease ..................... ........... . I B24 2-64. Lubrication Chart ................................... 1 B24 NOTE This chapter contains the Conversion Tables. For ease of use they are also indexed herein. CHART A. Inches to Millimeters ...................... IC9 CHART B. Fraction / Decimal Conversions .............. 1C II CHART C. Centigrade/Fahrenheit Conversions .......... IC 12 CHART D. English Vs. Metric ........................ IC13 CHART E. Decimal/Millimeter Equivalents of Drill Sizes from 1/2"to No.80 .......................... IC14 Revised:8/10/80 1 A17 Island Enterprises PIPERSENECAII SERVICEMANUAL SECTIONII HANDLINGAND SERVICING 2-1. INTRODUCTION.This section contains routine handling and servicing procedures that are most frequently encountered. Frequent reference to this section will aid the individualby providinginformation 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 routine proceduresas outlined in this section, refer to the appropriate section for that component. 2-2. DIMENSIONS.The principal airplane dimensions are shown in Figure 2-1 and are listed in.Table II-L 2-3. STATION REFERENCE LINES. In order to facilitate the location of various components of the airplane which require maintenance and servicing, a method utilizing fuselage station, wing station or buttock line (BL), and waterline (WL)designationsis frequently employed in this manual. (Refer to Figure 2-2.) Fuselage stations, buttock lines,and waterlines are reference points measured by inches in the vertical or horizontal direction from a givenreference line which indicates station locations of structural members of the airplane. 2-4. WEIGHT AND BALANCE DATA. When figuring various weight and balance computations, the empty, static and gross weight, and center of gravity of the airplane may be found in the Weight and Balance Form of the Airplane Flight Manual. 2-5. SERIAL NUMBERPLATE. The serial number plate is located on the left side of the fuselagenear the leading edge of the stabilator. The serial number should always be used when referring to the airplane on serviceor warranty matters. 2-6. ACCESSAND INSPECTIONPROVISIONS. The access and inspection provisionsfor the airplaneare shown in Figure 2-3. 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. To enter the aft section of the fuselage,remove the rear baggagecompartment upholstery panel by removingthe attachment screws. CAUTION Before entering the aft section of the fuselage, be sure the airplane is supported at the tail skid. 2-7. 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 givenin the back of the section that pertains to a particular component or are listed in the back of the PA-34-200TParts Catalog. Reissued: 10/11/79 HANDLINGAND SERVICING 1A18 Island Enterprises * PIPERSENECAII SERVICEMANUAL 13'6.7" 6'4"DIAMETER 7 DIHEDRAL t STATIC CLOUD LINE Figure 2-1. Three View Reissued: 10/11/79 HANDLINGAND SERVICING 1A19Island Enterprises 1 94 __ W.L - 19 75 *PIPER SENECAII SERVICEMANUAL 76.98 W 14 1444 78.0 W .S 221.49 Figure 2-2. Station References Reissued: 10/11/79 A20 1A20 HANDLING AND SERVICING Island Enterprises PIPERSENECAII SERVICEMANUAL TABLEII-I. LEADINGPARTICULARSAND PRINCIPALDIMENSIONS PA-34-200TSENECAII MODEL ENGINE Manufacturer Model - Left Model - Right FAA Type Certificate Rated Horsepower(Max. Continuous, Sea Level) Rated Speed Oil, SAE Number Oil Sump Capacity Fuel, Aviation Grade, MinimumOctane Fuel Injector Magnetos, Scintilla: "' Left (Left Engine) Right (Left Engine) Left (Right Engine) Right (Right Engine) MagnetoTiming MagnetoPoint Clearance Spark Plugs(Shielded): Spark Plug Gap Setting Firing Order: Left Engine Right Engine Starter - Prestolite (12-volt): Left Engine Right Engine Alternator - Prestolite (65 amp) Alternator Voltage Regulator, LAMAR Alternator OvervoltageRelay, WICO Continental TSIO-360E-1A(CW)or TSIO-360-EB LTSIO-360E-1A(CCW)or LTSIO-360-EB E9CE 200 2575 RPM See Lubrication Chart 8 U.S. quarts 100/130 Continental 10-79020-18L 10-79020-19R 10-79020-18L 10-79020-19R 20° BTC .018 Refer to latest revisionof Teledyne Continental Aircraft Engine ServiceBulletinM77-10 Refer to latest revision of Teledyne Continental Aircraft Engine Service Bulletin M77-10 1-6-3-2-5-4 1-4-5-2-3-6 MCL-6501 MCL-6501 ALX 9425 B-00288-1 X-16799B ( REPLACEMENT ENGINE ON AIRCRAFT MODELS WITH SERIAL NUMBERS PA-34-7570001AND UP. 10 MAY BE PRESSURIZED IF KIT NO 764921V IS INSTALLED Revised: 12/08/83 1A21 HANDLING AND SERVICING Island Enterprises PIPER SENECA II SERVICE MANUAL * TABLE II-I. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont) PROPELLER Manufacturer Hub, Model: Left Engine Right Engine Alternate Hub, Models: Blade, Model: Left Engine Right Engine Diameter Diameter, Minimum Blade Angle, Low Pitch (High RPM) Blade Angle, High Pitch (Low RPM) Governor Control Governor Model: Left Engine Right Engine Alternate Governor Model: Left Engine Right Engine Right Engine When Synchrophaser is installed Hartzell McCauley BHC-C2YF-2CKF(2) BHC-C2YF-2CLKF(2) BHC-C2YF-2CKUF(Left Eng.)(2 BHC-C2YF-2CLKUF (Right Eng.)(2) FC8459-8R& FC8459B-8R FJC8459-8R & FJC8459B-8R 76 in. 75 in. 14.4° + 0.2° 79.3°,+ 2.0 ° (4)or 80° to 81.5 ° (4)(5) Woodward 3AF34C502 3AF34C503 80HA-4 L80HA-4 76 in. 75 in. 12.2° + 0.2° or 11.5° + 0.2° Up to S/N 34-7870492 (inclusive) 12.0° + 0.2 ° S / N 34-7970001 (inclusive) and up (9) 81° to 83.5° C210659 210C58 Hartzell E-3 E-3L 49E-8L FUEL SYSTEM Fuel Tank Total Capacity (Both Wings) Total Usable Fuel 49 gal./ wing 98 gal. 93 gal. 64 gal./wing(3) 128 gal.(3) 123 gal. (3) (2) PROPELLERS TO BE MOUNTED IN PAIRS ONLY. DO NOT MIX WITH OTHER PROPELLERS (3) WITH OPTIONAL FUEL TANKS INSTALLED (4) ON PROPELLER HUBS WITH SERIAL NUMBERS PRIOR TO AN3943. EITHER SETTING IS APPROPRIATE AT OWNER'S DISCRETION. (5) ON PROPELLER HUBS WITH SERIAL NUMBERS AN3943 AND SUBSEQUENT ONLY THIS SETTING CAN BE USED. (7) LEFT ENGINE ONLY. (8) RIGHT ENGINE ONLY (9) BOTH ENGINES Revised: 12/08/83 HANDLING AND SERVICING 1A22 Island Enterprises PIPERSENECAII SERVICEMANUAL * TABLE II-I. LEADINGPARTICULARSANDPRINCIPALDIMENSIONS(cont.) LANDINGGEAR Type Shock Strut Type Fluid Required (Struts, Brakes & Hydraulic System) Strut Exposure (Exposure under Static load): Nose Main Wheel Tread Wheel Base Nose Wheel Travel Wheel, Nose Wheel, Main BrakeType Tires, Nose Tires, Main Tire Pressure,Nose Tire Pressure,Main Fully Retractable Air-OilOleo MIL-H-5606 2.60 + .25 in. 3.60 + .25 in. 11.1 ft. 7 ft. 27 ° left, 27 right Cleveland38501, 6:00 x 6 Cleveland 40-56B 6:00 x 6 Cleveland 40-90 6:00 x 6 Cleveland 40-120 6:00 x 6 Heavy Duty Cleveland 30-65 or 30-83 (6) 6:00 x 6 (6 ply) or Nylon-T.T.Type III (6) 6:00 x 6 (8 ply) or Nylon-T.T. Type III (6) 31 psi @Gross Weight,34 psi 6) 55 psi @ Gross Weight, 46 psi 6) CONTROLSURFACES Refer to Section V CABLETENSIONS Refer to Section V (6) PA-34-200T MODEL WITH HEAVY DUTY BRAKES. WHEELS AND EITHER B.F. GOODRICH NYLON.T.T. TYPE III TIRES OR McCREARY AIR HAWK TYPE III. (REFER TO PIPER KIT NO. 761 048 V.) Revised: 12/08/83 HANDLING AND SERVICING 1A23 Island Enterprises * PIPER SENECA II SERVICE MANUAL 2-8. TORQUE REQUIREMENTS. Proper torque application cannot be overemphasized. Undertorqued assemblies can result in premature failure due to fatigue from uneven loads, as well as causing unnecessary wear of nuts. bolts, and other parts. Overtorqued assemblies can be equally harmful by causing failure of a bolt or nut by overstressing the threaded areas. The torque values given in Table 11-11are 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 Teledyne Continental Overhaul Manual, and propeller torque values are found in Section VIII of this manual. Table Il-IIA lists the torque values for flared fittings of various sizes and material. Important procedures for torquing assemblies on Piper Aircraft are as follows: a. Frequently check and or calibrate the torque wrench. b. MAKE SURE bolt/screw and nut threads are clean and dry, unless otherwise required. If the threads are to be lubricated and no torque is specified, reduce recommended nut torque (plus the friction drag torque) by 50. c. Unless otherwise specified the charted torque values should be used. Should a bolt or nut be listed and not its mating fastener, use the lower torque. d. When using "self-locking fasteners" and hardware with thread sizes 8 through 7/ 16 add the specified friction drag torque to the designated torque. Assume a friction drag torque of zero for non self-locking fasteners. For other bolt sizes the friction drag torque is determined as follows: 1. Turn nut to "near contact" with the bearing surface (NOT IN CONTACT). 2. Attach a scale type torque wrench and determine the torque required to turn the nut on the bolt before it contacts the bearing surface. Add this value to the specified torque for the total torque value to be .applied. e. When torquing castellated nuts remember the following: 1. Determine total torque value (friction torque - if any - plus max. torque) and do not exceed when aligning slot and hole, change washers if necessary. 2. Tighten nuts only to remove looseness in the joint before installing cotter pin. f. Use the latest information from CONTINENTAL for torquing powerplant parts. g. On critical installations the nut should be permanently marked red after torquing and not be further tightened or disturbed. NOTE When flared fittings are being installed, ascertain that the male threads are properly lubricated. Torque the fittings in accordance with Table Il-IIA. For more details on torquing, refer to FAA Manual AC 43-13-1A. CAUTION Do not overtorque fittings. Revised: 3/16/81 HANDLING AND SERVICING 1A24 Island Enterprises PIPER SENECA II SERVICE MANUAL 2-8A. TORQUE WRENCHES. Torque wrenches should be checked daily and calibrated by means of weights and a measured lever arm to make sure that inaccuracies are not present. Checking one torque wrench against another is not sufficient and is not recommended. Some wrenches are quite sensitive as to the way they are supported during a tightening operation. Any instructions furnished by the manufacturer must be followed explicitly. When it is necessary to use a special extension or adapter wrench together with a torque wrench, a simple mathematical equation must be worked out to arrive at the correct torque reading. Following is the formula to be used: (Refer to Figure 20-5.) T =Torque desired at the part. A= Basic lever length from center of wrench shank to center of handle. This may be stamped on the wrench itself or it may be listed elsewhere. B = Length of adapter extension, center of bolt to center of shank. C = Scale reading needed to obtain desired torque (T). The formula: C = AA+B EXAMPLE A bolt requires 30 foot-pounds and a 3 inch adapter(one-quarter of a foot or .25) is needed to get at it. You want to know what scale reading it will take on a one-foot lever arm wrench to obtain the 30 foot-pounds at the bolt. C = x 30 or C = 30 = 24 ft.-lbs. +.25 1.25 Remember. the 3 inch adapter must be projecting 3 inches straight along the wrench axis. In general. avoid all complex assemblages or adapters and extensions of flex joints. A933 A T Figure 2-2a. Torque Wrench Formula Added: 8/10/80 HANDLING AND SERVICING 1B1 Island Enterprises PIPER SENECA II SERVICE MANUAL TABLE 11-11. RECOMMENDED TORQUE VALUES NOTE COARSE THREAD SERIES BOLTS Steel Tension AN 3 thru AN 20 AN 42 thru AN 49 AN 73 thru AN 81 AN 173 thru AN 186 MS 20033 thru MS 20046 MS 20073 MS 20074 AN 509 NK9 MS 24694 AN 525 NK525 MS 27039 NUTS WHERE NORMAL OPERATION REQUIRES MOVEMENT BETWEEN COMPONENTS BEING BOLTED OR CLAMPED TOGETHER, THE HARDWARE SHOULD BE TIGHTENED AS REQUIRED OR SPECIFIED. DISREGARDINGTHE TORQUE CHART(S) USE THE LOWER SIDE OF THE TORQUE RANGE WHERE THE BOLT IS FIXED AND THE NUT MOVEABLE USE THE HIGHER SIDE OF THE TORQUE RANGE WHERE THE NUT IS FIXED AND THE BOLT MOVEABLE Steel Tension Steel Shear AN 310 AN 315 AN 363 AN 365 NAS 1021 MS 17825 MS 21045 MS 20365 MS 20500 NAS 679 AN 320 AN 364 NAS 1022 MS 17826 MS 20364 FRICTION DRAG TORQUES COARSE AND FINE FRICTIONDRAG BOLT SIZE TORQUE (IN -LBS ) 8 (coarse) 10 1/4 15 18 30 Nut-bolt Torque Limits Torque Limits size in-lbs in-lbs Min Mx. Min Max. 5/16 60 80 0 a 8 -32 10 -24 1/4-20 5/16-18 3/8-16 7/16-14 1/2-13 9/16-12 5/8-11 3/4-10 7/8- 9 1 -8 1-1/8-8 1-1/4-8 12 20 40 80 160 235 400 500 700 1.150 2.200 3.700 5,500 6.500 15 25 50 90 185 255 480 700 900 1.600 3,000 5.000 6.500 8.000 7 12 25 48 95 140 240 300 420 700 1.300 2.200 3.300 4.000 9 15 30 55 110 155 290 420 540 950 1,800 3.000 4.000 5.000 Revised:3/16/81 1B2 HANDLING AND SERVICING Island Enterprises PIPER SENECA II SERVICE MANUAL TABLE II-11. RECOMMENDED TORQUE VALUES (cont.) FINE THREAD SERIES BOLTS Steel Tension BOLTS Steel Tension BOLTS Aluminum AN 3 thru AN 20 AN 42 thru AN 49 AN 73 thru AN 81 AN 173 thru AN 186 MS 20033 thru MS 20046 MS 20073 MS 20074 AN 509 NK9 MS 24694 AN 525 NK525 MS 27039 NUTS Steel Tension Steel Shear AN 310 AN 320 AN 315 AN 364 AN 363 NAS 1022 AN 365 MS 17826 NAS 1021 MS 20364 MS 17825 MS 21045 MS 20365 MS 20500 NAS 679 MS 20004 thru MS 20024 NAS 144 thru NAS 158 NAS 333 thru NAS 340 NAS 583 thru NAS 590 NAS 624 thru NAS 644 NAS 1303 thru NAS 1320 NAS 172 NAS 174 NAS 517 Steel sheerbolt NAS 464 NUTS AN 3DD thru AN 20DD AN 173DD thru AN 18600 AN 509DD AN525D MS 27039D MS 24694DD NUTS Steel Tension Steel Sheer Alum. Tension Alum. Shear AN 310 AN 315 AN 363 AN 365 MS 17825 MS 20365 MS 21045 NAS 1021 NAS 679 NAS 1291 AN 320 AN 364 NAS 1022 MS 17826 MS 20364 AN 3650 AN 3100 NAS 1021D AN 3200 AN 3640 NAS 10220 Nut-bolt size Torque Limits Torque Limits in-lbs in-lbs Min. Max. Min. Max. Torque Limits Torque Limits in-lbs in-lbs Min. Max. Min. Max. Torque Limits Torque Limits in-lbs in-lbs Min. Max. Min. Max. 8 -36 10 -32 1/4-28 5/16-24 3/8-24 7/16-20 1/2-20 9/16-18 5/8-18 3/4-16 7/8-14 1 -14 1-1/8-12 1-1/4-12 12 15 7 9 20 25 12 15 50 70 30 40 100 140 60 85 160 190 95 110 450 500 270 300 480 690 290 410 800 1,000 480 600 1,100 1,300 660 780 2,300 2,500 1,300 1,500 2.500 3,000 1,500 1,800 3,700 4,500 2,200 3,300 5,000 7,000 3,000 4,200 9,000 11,000 5,400 6,600 25 30 15 20 80 100 50 60 120 145 70 90 200 250 120 150 520 630 300 400 770 950 450 550 1.100 1.300 650 800 1.250 1,550 750 950 2.650 3,200 1,600 1,900 3,550 4,350 2,100 2,690 4,500 5,500 2,700 3,300 6,000 7,300 3,600 4,400 11,000 13,400 6,600 8,000 5 10 3 6 10 15 5 10 30 45 15 30 40 65 25 40 75 110 45 70 180 280 110 170 280 410 160 260 380 580 230 360 550 670 270 420 950 1,250 560 880 1,250 1,900 750 1,200 1,600 2,400 950 1,500 2,100 3,200 1,250 2,000 3,900 5,,00 2,300 3,650 Revised: 8/10/80 HANDLING AND SERVICING 1B3 Island Enterprises * PIPER SENECA II SERVICEMANUAL TABLE II-IIA. FLARE FITTING TORQUE CHART TORQUE - INCH POUND TUBING OD INCHES ALUMINUM - ALLOY TUBING FLARE-AND 10061 OR AND 10078 STEEL TUBING FLARE AND 10061 HOSE END FITTING AND HOSE ASSEMBLIES MINIMUMMAXIMUMMINIMUMMAXIMUMMINIMUMMAXIMUM 1/8 3/16 1/4 5/16 3/8 1/2 5/8 3/4 1-1/4 1-1/2 1-3/4 2 40 60 75 150 200 300 500 600 600 90 65 135 80 180 125 270 250 450 350 650 500 900 700 1200 900 900 100 150 200 300 500 700 1000 1400 70 70 85 100 210 300 500 700 100 120 180 250 420 480 850 1150 TABLE II-IIB. THREAD LUBRICANTS TYPE OF LINE TYPE OF LUBRICANT Brakes MIL-H-5606 Freon TT-A-580 or MIL-T-5544. Anti-Seize Compound MIL-T-5544. Anti-Seize. Graphite Petrolatum Fuel Landing Gear (Air Valve) 6PB Parker Oil MIL-G-6032. Lubricating Grease (Gasoline and Oil Resistant) Pitot and Static Lubricate engine fittings only Added: 8/10/80 TT-A-580 (JAN-A-669). Anti-Seize Compound (White Lead Base) NOTE with the fluid contained in the particular lines. HANDLING AND SERVICING 1B4 Island Enterprises 2010 A106 SKETCH C 1. VENTILATING AIR INTAKE 2. FAIRING FIN 3. BATTERY, BRAKE RESERVOIR, ELECTRONIC EQUIPMENT, HYDRAULIC POWER PACK j 4. RUDDER TRIM TAB SCREW 5. STABILATOR AND RUDDER STOPS. STABILATOR TRIM TAB SCREW A243 PIPER SENECA 11SERVICE MANUAL * SKETCH E 1. DOOR, NOSE GEAR, LANDING 2. HYDRAULIC PRESSURE SWITCH. NOSE GEAR ACTUATING CYLINDER AND LIMIT SWITCH, VOLTAGE REGULATORS 6 1. BATTERY 2. NOSE LANDING GEAR 3. MAIN SPAR 4. BRAKE RESERVOIR 5. EXTERNAL POWER PLUG 6. RADIO A106 1. FAIRING FIN 2. VENTILATING AIR INTAKE 3. STABILATOR AND RUDDER STOPS, STABILATOR TRIM TAB SCREW 4. COMBUSTION HEATER, COMBUSTION AIR INTAKE SKETCHF SKETCH D Figure 2-3. Access Plates and Panels Reissued: 10/11/79 1BS HANDLING AND SERVICING Island Enterprises 2 3 11 PIPER SENECA II SERVICE MANUAL 11 3 2 9 9 1. WING TIP 2. CAP, FUEL TANK ASSEMBLY 3. FAIRING 4. OIL FILLER DOOR 5. FAIRING 6. LINES, WIRES, CABLES 7. COWL, INBOARD 8. SPINNER, PROPELLER 9. PROPELLER RECHARGE VALVE 10. COWL, OUTBOARD 11. HATCH, NACELLE SKETCH A 1978 13 13 1. FUEL GAUGE SENDER 2. COWL FLAP 3. PROPELLER RECHARGE VALVE 4. SPINNER, PROPELLER 5. ENGINE OIL DRAIN 6. LINES, WIRES, CABLES 7. FAIRING 8. DOOR, MAIN GEAR, LANDING 9. COVER, GEAR ATTACHMENT FITTING 10. ELECTRIC WIRING 11. FUEL VALVE 12. COVER, BELLCRANK AND CONTROL CABLE 13. WING TIP 14. STALL WARNING & DEICER BOOTS 15. PITOT HEAT WIRING -AILERON CABLES DEICER LINES SKETCH B Figure 2-3. Access Plates and Panels (cont.) REISSUED: 10/11/79 HANDLING AND SERVICING 1B6 Island Enterprises 1976 Figure 2-4. Jacking 2-9. STEP, HANDHOLDAND WALKWAYS.A fixed handhold is located on the right side of the fuselage, above and aft of the second window. The walkway is made up of a non-skid material which is in turn bonded to the wingsurface. (Refer to Section IV for repair or replacement of wing walkwaymaterial.) CAUTION Walkon the walkwaysonly to avoid damage to the wings. 2-10. GROUNDHANDLING. 2-11. INTRODUCTIONTO GROUND HANDLING. Ground handling covers all essential information governing the 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 followingparagraphs,damageto the airplane and its equipment will be prevented. 2-12. JACKING. Jack the airplane as specified to perform various service operations. Proceed as follows: a. Place the jacks under the jack pads on the wing front spar. b. Attach a tail support to the tail skid. Place approximately 600 pounds of ballast on the support to hold the tail down. (Refer to Figure 2-4.) CAUTION Be sure to apply sufficient support ballast; otherwise, the airplane will tip forward and fall on the fuselagenose section: c. Carefullyraise jacks until all three wheels are clear of the surface. Revised: 8/10/80 HANDLNG AND SERVICING PIPER SENECAI SERVICEMANUAL . 1B7 Island Enterprises 1977 PIPERSENECAII SERVICEMANUAL Figure 2-5. Weighing CAUTION If the purpose for placing the airplane on jacks is to service the hydraulic system, the free-fallvalve knob should be pulled full out from the instrument panel. (Refer to Section VI, Paragraph 6-1.) 2-13. WEIGHING. (Refer to Figure 2-5.) The airplane may be weighedby the followingprocedure: a. Position a scale and ramp in front of each of the three wheels. b. Secure the scales from rolling forward and tow the airplane up onto the scales.(Refer to Towing, Paragraph 2-18.) c. Removethe ramp so as not to interfere with the scales. d. If the airplane is to be weighed for weight and balance computations, level the airplane per instructions givenin Paragraph 2-14. 2-14. LEVELING. All configurationsof the airplane are provided with a means for longitudinal and lateral leveling.The airplane may be leveledwhile on jacks, during the weighingprocedure while the wheels are on scales, or while the wheels are on the ground. To level the airplane for purposes of weighingor rigging,the following procedures may be used: a. To longitudinally level the airplane, partially withdraw the two leveling screws located immediately below the left front side window. (Refer to Figure 2-6.) Place a spirit level on these screw heads and deflate the nose wheel tire or adjust the jacks until the bubble of the level is centered. b. To laterally level the airplane, place a spirit level acrossthe baggagecompartment floor along the rear bulkhead (refer to Figure 2-6) and deflate the tire on the high side of the airplane or adjust either jack until the bubble of the level is centered. Reissued:10/11/79 HANDLINGAND SERVICING 1B8Island Enterprises * PIPER SENECA II SERVICE MANUAL A368 Longitudinally Laterally Figure 2-6. LevelingAirplane 2-15. MOORING. The airplane is moored to insure its immovability, protection, and security under various weather conditions. The following procedure, gives the instructions for proper mooring of the airplane: a. Head the airplane into the wind, if possible. b. Block the wheels. c. Lock the aileron and stabilator controls by looping the pilot's seat belt around wheel. d. Secure tie-down ropes to the wing tie-down rings and the tail skid at approximately 45 degree angles to the ground. When using rope constructed of non-synthetic material, leave sufficient slack to avoid damage to the airplane when the ropes contract due to moisture. CAUTION Use square or bowline knots. Do not use slip knots. NOTE Additional preparations for high winds include using tie-down ropes from the landing gear forks, securing the rudder, and securing the props to prevent windmilling. 2-16. LOCKINGAIRPLANE. The right cabin door is provided with a key lock on the outside. The cabin door lock and nose baggagecompartment door lock use the same key. Reissued: 10/11/79 HANDLING AND SERVICING 1 B9 Island Enterprises PIPER SENECAII SERVICEMANUAL 2-17. PARKING. When parking the airplane, insure that it is sufficientlyprotected against adverseweather conditions and presents no danger to other aircraft. When parking the airplane for any length of time or overnight, it is recommended that it be moored as in Paragraph 2-15. a. To park the airplane, head it into the wind, if possible. b. Set the parking brake by pulling back the brake lever and depressingthe knob attached to the left side of the handle. Then release the handle. To release the parking brakes, pull back on the brake lever to disengagethe catch mechanism.Then allow the handle to swing forward. NOTE Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze the brakes. c. The aileron and stabilator controls may be secured with the pilot's seat belt. 2-18. TOWING. The airplane may be moved by using the nose wheel steeringbar that is stowed below the forward ledge of the rear baggagecompartment or power equipment that will not damage or cause excess strain to the nose gear steering assembly.Tow bar engagesfront axle inside fork. CAUTION When towing with power equipment, do not turn the nose gear in either direction beyond its steering radius limits as this will result in damage to the nose gear and steering mechanism. CAUTION When moving the aircraft forward by hand, avoid pushing on the trailing edge of the ailerons as this will cause the aileron contour to changeresulting in an out-of-trim condition. In the event towing linesare necessary, lines (rope) should be attached to both main gear struts as high up on the tubes as possible. Lines should be long enough to clear the nose and/or tail by not less than 15 feet, and a qualified person to ride in the pilot's seat to maintain control by use of the brakes. 2-19. TAXIING. Before attempting to taxi the airplane, ground personnel should be checked out by a qualified pilot or other responsible person. Engine starting and shutdown procedures should be covered as well. When it is ascertained that the propeller back blast and taxi areas are clear, apply power to start the taxi roll and perform the followingchecks: a. Taxi forward a few feet and apply brakes to determine their effectiveness. b. Taxi with propellers set in low pitch, high RPMsetting. c. While taxiing, make slight turns to ascertain the effectivenessof steering. d. Observe wing clearances when taxiing near buildings or other stationary objects. If possible, station a guide outside the airplane to observe. e. When taxiing on uneven ground, look for and avoid holes and ruts. f. Do not operate the enginesat high RPM when running up or taxiing over ground containing loose stones, gravel, or any loose material that may cause damage to the propeller blades. Reissued:10/11/79 HANDLINGAND SERVICING lB10Island Enterprises PIPER SENECA II SERVICE MANUAL 2-20. EXTERNAL POWER RECEPTACLE. 2-21. OPERATION OF EXTERNAL POWER RECEPTACLE. The external power receptacle is located on the left side of the nose section. When using external power for starting or operation of any of the airplane's equipment. the master switch must be ON. CAUTION Turn master switch off before inserting or removing plug. NOTE When using a 12-volt battery for external power starting and the airplane's battery is nearly depleted, the instructions given in Section XI must be followed. 2-22. SERVICING. 2-23. INTRODUCTION TO SERVICING. Servicing the airplane includes the replenishment of fuel. oil. hydraulic fluid. tire pressures. lubrication requirements, and other items required to completely service the airplane. 2-24. FUEL SYSTEM. 2-25. SERVICING FUEL SYSTEM. At intervals of 50 hours or 90 days, whichever comes first, clean the fuel filter pack. Remove and clean the filters in accordance with the instructions outlined in Section IX. Additional service information may also be found in Section IX. Inspection intervals of the various fuel system components may be found in Section III. 2-26. FILLING FUEL TANKS. The fuel tanks of each wing are filled through a single filler located on the forward slope of the wing at the outboard tank. An anti-icing additive complying with MIL-I-27686 may be added if desired when filling the system (see paragraph 2-27). With each of the interconnected wing tanks having a capacity of 24.5 gallons, a total capacity of 49 gallons is available per wing. 64 gallons with optional tanks. CAUTION Observe all required safety precautions and use the fuel specified on the placard adjacent to the filler neck. Revised: 8/10/80 HANDLING AND SERVICING IBlI Island Enterprises PIPER SENECAII SERVICEMANUAL 2-27. HANDLING OF MOISTURE IN FUEL SYSTEM. Moisture and foreignmatter can be drained from drains incorporated in the bottom of the system's lowest point and the inboard end of each fuel tank. To prevent ice contamination an anti-icing additive per MIL-I-27686Bmay be used provided it is uniformly blended with the fuel whilerefueling. The additive must not exceed .15%by volume of the refueledquantity. To be effective the blend should not be less than .10% by volume. A good example would be 1-1/2 liquid ounces per 10gallonsof fuel. For best results, followthe manufacturer's mixingor blendinginstructions. Refer to list of consumable materials for purchasing information. If possiblea blender suppliedby the manufacturer should be used. CAUTION Make sure that when adding an anti-icing additive it is directedinto the flowing fuel stream, starting after and stopping before the fuel flow. DO NOT permit the additive to come in contact with painted surfaces or interior surfaces of the tank. Do not add further blending to pre-blended fuels. Fuel additive(s) do not substitute for preflight draining of fuel system drains. 2-28. DRAINING FUEL SYSTEM. The bulk of the fuel may be drained from the system by opening the valve at the inboard end of each fuel tank. Push up on the arms of the drain valveand turn counterclockwise to hold the drain in the open position. The remainingfuel in the system maybe drained through the fuel filters and the two drains located on the lower right side of the fuselage inboard to the flaps. INTENTIONALLYLEFT BLANK Revised: 8/10/80 HANDLINGAND SERVICING 1B12 Island Enterprises * PIPERSENECAII SERVICEMANUAL 2-29. BRAKESYSTEM. 2-30. SERVICING BRAKE SYSTEM. The brake system incorporates a hydraulic fluid reservoir through which the brake system is periodically serviced. Fluid is drawn from the reservoir by the brake cylinders to maintain the volume of fluid required for maximum braking efficiency. Spongy brake pedal action is often an indication that the brake fluid reservoir is running low on fluid. Instructions for filling the reservoir are given in Paragraph 2-31. When found necessary to accomplish repairs to any of the brake system components, or to bleed the system, these instructions may be found in Section VII. 2-31. FILLING BRAKE CYLINDER RESERVOIR. The brake cylinder reservoir should be filled to the level marked on reservoir with the fluid specified in Table II-I. The reservoir, located on the center of the bulkhead in the nose baggage compartment, should be checked at every 50 hour inspection and replenished as necessary. No adjustment of the brakes is necessary, though they should be checked periodically per instructions given in Section VII. 2-32. DRAINING BRAKE SYSTEM. To drain the brake system, connect a hose to the bleeder fitting on the bottom of the cylinder and place the other end of the line in a suitable container. Open the bleeder and slowly pump the hand brake lever and the desired brake pedal until fluid ceases to flow. To drain the wheel brake unit, disconnect the line at the bottom of the unit and allow fluid to flow into a suitable container. To clean the brake system, flush with denatured alcohol. 2-33. OLEO STRUTS. 2-34. SERVICING OLEO STRUTS. The air-oil type oleo strut should be maintained at proper strut piston tube exposures for best oleo action. The nose gear strut must have approximately 2.60 ± .25 inches of piston tube exposed, while the main gear strut requires approximately 3.60 ± .25 inches of tube exposure. These measurements are taken with the airplane sitting on a level surface under normal static load. NOTE Normal static load is the empty weight of the airplane plus full fuel and oil. CAUTION Do not exceed these tube exposures. If the strut has less tube exposure than prescribed, determine whether it needs air or oil by rocking the airplane. If the oleo strut oscillated with short strokes (approximately one inch) and the airplane settles to its normal position within one or two cycles after the rocking force is removed, the oleo strut requires inflating. Check the valve core and filler plug for air leaks, correct if required, and add air or nitrogen as described in Paragraph 2-37. If the oleo strut oscillates with long strokes (approximately three inches) and the airplane continues to oscillate after the rocking force is removed, the oleo struts require fluid. Check the oleo for indications of oil leaks, correct if required, and add fluid as described in Paragraph 2-35 or 2-36. For repair procedures of the landing gear and/or oleo struts, refer to Section VII of this manual. WARNING Do not release air by removing the strut valve core or filler plug. Depress the valve core pin until the strut chamber pressure has diminished. Revised: 3/16/81 HANDLING AND SERVICTNG 1B13 Island Enterprises PIPERSENECAII SERVICEMANUAL 840 M.T.D. MINIMUMTURNING DISTANCE(M.T.D.) 60.4 Ft. Figure 2-7. TurningDistance Reissued: 10/11/79 HANDLINGAND SERVICING 1B14Island Enterprises PIPERSENECAII SERVICEMANUAL CAUTION Dirt and foreign particles form around the filler plugs of the landing gear struts, therefore, before attempting to remove these plugs, the area around the filler plugs should be cleaned with compressed air and/or with a quick drying solvent. 2-35. FILLING NOSE GEAR OLEO STRUT. To fill the nose gear oleo strut with hydraulic fluid (MIL-H-5606), whether it be only the addition of a small amount or if the unit has been completely emptied and will require a large amount, it should be filled as follows: a. Raise the airplane on jacks. (Refer to Paragraph2-12.) b. Place a pan under the gear to catch spillage. c. Relieve air pressure from the strut housing chamber by removing the cap from the air valveand depressingthe valvecore. d. There are two methods by which the strut chamber may be filled and these are as follows: Method 1: Addition of small amounts of fluid. 1. Remove the valve core from the filler plug at the top of the nose gear strut housing. Allow the filler plug to remain installed. 2. Withthe piston tube extended, fill the strut with approved type fluid. 3. Attach one end of a clean plastic hose to the valvestem of the filler plug and submergethe other end of the hose in a container of clean hydraulic fluid; make sure the end of the hose is below the surface of the fluid. NOTE An air tight connection is necessary between the plastic tube and the valve stem. Without such a connection, a small amount of air will be sucked into the oleo strut during each sequence, resulting in an inordinate amount of air bubbles and prolonged filling operations. 4. Fully compress and extend the piston tube, thus expelling any air trapped within the strut chamber. By watching the fluid pass through the plastic hose, it can be determined when the strut is full and no air is present in the chamber. 5. When air bubbles cease to flow through the hose, compress the piston fully and remove the hose from the valvestem. Remove the filler plug to determine that fluid level is visibleup to the bottom of the filler plug hole. 6. Reinstallthe core in the filler plug and the plug in the strut housing and torque from 350to 400 inch-pounds. Method II - Filling completely empty struts. 1. Proceed with steps A through C. 2. Remove the filler plug at the top inboard side of the.gear housing. 3. Disconnectthe torque links by removing any one of the three torque link bolts. CAUTION With the torque link disconnected,the strut tube is free to slideout of the trunnion. 4. Extend the piston to a visible strut extension of 10 inches minimum - 12inches maximum. 5. Add one-half pint minimumof hydraulic fluid through the air valve hole and allow it to drain and fill the chamber below the top bearing hole. Revised: 12/08/83 HANDLING AND SERVICING 1B15 Island Enterprises 2 PIPER SENECA II SERVICE MANUAL 1970 12 5 4 12 4 16 1. FUEL FILLERS 2. FUEL INJECTORS 3. ENGINE OIL FILL 4. ENGINE OIL FILTERS 5. FUEL FILTERS 6. INSTRUMENT AIR FILTERS 7. FUEL SYSTEM DRAINS 8. FUEL METERING CONTROL UNIT 9. OIL DIPSTICK 10. MAIN GEAR STRUT 11. MAIN GEAR TIRES 12. INDUCTION AIR FILTERS 13. ENGINE OIL SUCTION SCREEN 14. PROPELLER AIR CHARGE 15. BRAKE RESERVOIR 16. NOSE GEAR STRUT 17. NOSE GEAR TIRE 18. EXTERNAL POWER RECEPTACLE 19. BATTERY 20. HYDRAULIC RESERVOIR Figure 2-8. ServicePoints HANDLING AND SERVICING HANDLING AND SERVICING Reissued: 10/11/79 lB16 Island Enterprises PIPER SENECA II SERVICE MANUAL * 6. Reconnect the torque links. 7. Add hydraulic fluid through the air valvehole until the fluid levelreachesthe bottom (or lower side) of the air valvehole with the piston fullycompressedand no air trapped in the assembly below the valve hole. NOTE Gear assemblies with the air valve hole on the side of the cylinder may be serviced in the horizontal position with the air valve hole vertical. 8. Install the air valve and torque it from 350 to 400 inch pounds. 2-36. FILLING MAIN GEAR OLEO STRUTS. To fill the main gear oleo struts with hydraulic fluid (MIL-H-5606) one of the followingmethods should be used, depending on the type of serviceperformed on the strut assembly: a. Method I: Addition of small amount of fluid. 1. Raise the airplane on jacks. (Refer to Paragraph 2-12.) 2. Place a pan under the gear to catch any spillage. 3. Relievethe air pressure from the strut housing chamber by removingthe capfrom the air valve and depressing the valve core. 4. Remove the valve core from the filler plug and allow the filler plug to remain installed. 5. With the piston tube extended, fill the strut with the approved type hydraulic fluid. 6. Attach one end of a clear plastichose to the valve stem of the filler plug and submergethe other end of the hose in a container of clean hydraulic fluid; make sure the end of the hose is belowthe surfaceof the fluid. NOTE An air tight connection is necessarybetween the plastic tube and the valve stem. Without such a connection, a small amount of air will be sucked into the oleo strut during each sequence, resulting in an inordinate amount of air bubbles and prolonged filling operations. 7. Fully compress and extend the piston tube, thus expelling any air trapped within the strut chamber. By watchingthe fluid pass through the plastic hose, it can be determined when the strut is full and no air is present in the chamber. 8. When air bubbles cease to flow through the hose, fully compress the piston and remove the hose from the valvestem. Remove the filler plug to determine that fluid is visible up to the bottom of the filler plug hole.9. Reinstall the air valve core in the filler plug and the plug in the strut housing and torque to 45 foot-pounds. 10. With the airplane still on jacks, compress and extend the gear piston tube several times to ascertain that the strut willoperate freely. The weight of the gear, wheel,and fork should allowthe piston tube to extend.11. Clean off any overflow of fluid and inflate the strut with air to 250 psi. 12. Remove the aircraft from jacks and check strut exposure per Paragraph 2-34. Revised: 3/16/81 HANDLING AND SERVICING 1B17 Island Enterprises *PIPER SENECA II SERVICE MANUAL Method II - Filling completely empty struts. 1. Proceed with steps I through 3 of Method I. 2. Remove the filler plug at the top inboard side of the main gear housing. 3. Disconnect the torque links by removing any one of the three torque link bolts. CAUTION With the torque link disconnected, the strut tube is free to slide out of the trunnion. 4. Extend the piston to a visible strut extension of 10 inches minimum - 12 inches maximum. 5. Add one-half pint minimum of hydraulic fluid through the air valve hole and allow it to drain and fill the chamber below the top bearing hole. 6. Reconnect the torque links. 7. Add hydraulic fluid through the air valve hole until the fluid level reaches the bottom (or lower side) of the air valve hole with the piston fully compressed and no air trapped in the assembly below the valve hole. NOTE Gear assemblies with the air valve hole on the side of the cylinder may be serviced in the horizontal position with the air valve hole vertical. 8. Reinstall the air valve core in the filler plug and the plug in the strut housing and torque the plug from 350 to 400 inch-pounds. Revised: 12/08/83 HANDLING AND SERVICING 1B18 Island Enterprises PIPER SENECA II SERVICE MANUAL * 2-37. INFLATING OLEO STRUTS. After making certain that an oleo strut has sufficient fluid, attach a strut pump to the air valve. With the airplane at empty weight (full fuel and oil only) fill the main strut to 250 psi and the nose gear to 150 psi. 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 with line pressure from a high pressure air system. Before capping the valve, check for valve core leakage. 2-38. SERVICING STEERING BUNGEES. At the specified frequencyaccording to the Lubrication Chart. the steering bungees must be serviced as follows: a. Remove the access panels located in the forward baggage compartment. b. Clamp the rudder pedals in the neutral position as shown in Figure 5-11. c. Remove the nut. washers, and bolt that secures the steering bungee and the steering arm. d. Remove the clamp that secures the boot, on the frame at station 49.50. to the bungee. e. Within the fuselage. disconnect the bungee from the rudder pedal arm by removing the nut. washer and bolt. f. Remove the steering bungee from the aircraft. g. Cut the safety wire from the bungee retainer. h. Carefully remove the retainer and release the spring. i. Apply Aero Lubriplate to the spring and mounting hardware as specified in the Lubrication Chart. j. Compress the spring into the bungee tube and install the retainer securing with M IL-W-6713 Type 316 safety wire. k. Ascertain that the measurement taken between the facing sides of the washers at the rod end is 13.71 inches. 1. With the nose gear in the neutral position, install the steering bungee into position. The web must be in the vertical position. (Refer to Figure 7-2.) m. Install the bolt. washers, and nut that secures the bungee to the steering arm. n. Install the bolt. washer. and nut that secures the bungee to the rudder pedal arm. o. Install the boot clamp. p. Repeat this procedure for the other steering bungee. q. Align the nose gear per Alignment of Nose Landing Gear. Section VII. r. Remove the rudder pedal clamps and check the operation of the steering bungees. s. Install the access panels in the forward baggage compartment with the attachment hardware. 2-39. TIRES. 2-40. SERVICING TIRES. The tires should be maintained at the pressure specified in Table I1-1. When checking tire pressure. examine the tires for wear. cuts. bruises and slippage. The tire. tube. and wheel should be balanced when installed. Align the index mark on the tire with the index mark on the tube. 2-41. HYDRAULIC SYSTEM. 2-42. SERVICING HYDRAULIC SYSTEM. The hydraulic pump and landing gear actuating cylinders should be checked for leaks, tightness of line fittings and general condition. The cylinder rods are to be free of all dirt and grit. To clean the rods. use an oil soaked rag and carefully wipe them. All the hydraulic lines should also be checked for leaks. kinks, corrosion and attachment fittings for tightness and security. Repair and check procedures for the hydraulic pump. cylinders, and various components may be found in Section VI of this manual. Revised: 8/10/80 HANDLING AND SERVICING 1B19 Island Enterprises PIPERSENECA SERVICEMANUAL 2-43. SERVICINGHYDRAULICPUMP/RESERVOIR.The fluid level of the reservoirof the combination pump and reservoir should be checked every 50 hours by viewing the fluid through the filler plug hole in the hydraulic pump. Access to the pump is through the panel at the right forward side of the nose baggage compartment. To check fluid level, remove the filter plug located on the forward side of the pump and ascertain that fluid is visible up to the bottom of the filler plug hole. Should fluid be below the hole, add fluid, MIL-H-5606,through the filler hole until full. Reinstallthe filler plug and tighten. NOTE A small vent hole is located under the vent screw head. Retain 1/64 inch clearance between the screw head and small vent hole. 2-44. BATTERY. 2-45. SERVICING BATTERY. Servicing of the battery which is located under the floor panel of the forward baggage compartment, involves adding distilled water to maintain electrolyte even with the horizontal baffles, checking cable connections, and checking for any spilled electrolyte that would lead to corrosion. A check for proper fluid level and presence of corrosion should be conducted at intervals of 50 hours or 30 days, whichever comes first. When corrosion is found, at each 100 hour inspection or every 90 days, the battery should be removed from the box and the battery and box should be cleaned. Removal, cleaning,and charginginstructions may be found in Section XI of this manual. 2-46. CLEANING. 247. CLEANINGENGINE COMPARTMENTS.Before cleaningthe engine compartments, place a strip of tape on the magneto vents to prevent any solvent from entering these units. a. Place a pan under the engines to catch waste. b. With the engine cowlings removed, spray or brush the engines with solvent or a mixture of solvent and degreaser as desired. It may be necessary to brush areas that were sprayed, where heavygrease and dirt deposits have collected in order to clean them. CAUTION Do not spray solvent into the alternator, starter, air intake, alternate air inlets and pressure pump drive area. c. Allow the solvent to remain on the engine from five to 10 minutes; then rinse the engine clean with additional solvent and allow to dry. CAUTION Do not operate engines until excess solvent has evaporated or otherwise been removed. d. Remove the protective coversfrom magnetos. e. Lubricate controls, bearingsurfaces, etc., per Lubrication Chart. Reissued:10/11/79 HANDLINGAND SERVICING lB20. Island Enterprises PIPER SENECA II SERVICE MANUAL 2-48. CLEANING LANDING GEAR. Before cleaning the landing gear. place a plastic cover or similar material over the wheel and brake assembly. a. Place a pan under the gear to catch waste. b. Spray or brush the gear area with solvent or a mixture of solvent and degreaser as desired. It may be necessary to brush areas that were sprayed where heavy grease and dirt deposits have collected in order to clean them. Do not brush micro switches. c. Allow the solvent to remain on the gear from 5 to 10 minutes: then rinse the gear with additional solvent and allow to dry. d. Remove the cover from the wheel and remove the catch pan. e. Lubricate the gear per Lubrication Chart. 2-49. CLEANING EXTERIOR SURFACES. The airplane should be washed with a mild soap and water. Harsh abrasive or alkaline soaps or detergents used on painted or plastic surfaces could make scratches or cause corrosion of metal surfaces. Cover areas where cleaning solution could cause damage. To wash the airplane. the following procedure may be used: a. Flush away loose dirt with water. b. Apply cleaning solution with a rag. sponge or soft bristle brush. c. To remove stubborn oil and grease, use a cloth dampened with naphtha. d. Where exhaust stains exist, allow solution to remain on the surface longer. e. Any good automotive wax may be used to preserve the painted surfaces. Soft cleaning cloths or a chamois should be used to prevent scratches when cleaning or polishing. A heavier coating of wax on the leading surfaces will reduce the abrasion problems in these areas. 2-50. CLEANING WINDSHIELD AND WINDOWS. a. Remove dirt. mud. etc.. from exterior surfaces with clean water. b. Wash with mild soap and warm water or an aircraft plastic cleaner. Use a soft cloth or sponge using a straight rubbing motion. Do not harshly rub surfaces. c. Remove oil and grease with a cloth moistened with kerosene. NOTE Do not use gasoline, alcohol. benzene. carbon tetrachloride. thinner. acetone. or window cleaning sprays. d. After cleaning plastic surfaces, apply a thin coat of hard polishing wax. Rub lightly with a soft cloth. Do not use a circular motion. e. A severe 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. Visibility through the windshield may be improved when flying through rain by using a water repellent on the windows such as Repcon. Refer to the List of Consumable Materials for purchasing information. 2-51. CLEANING HEADLINER. SIDE PANELS AND SEATS. a. Clean headliner. side panels. and seats with a stiff bristle brush and vacuum where necessary. b. Soiled upholstery. except leather. may be cleaned by using an approved air type cleaner or foam upholstery cleaner. Carefully follow the manufacturer's instructions. Avoid soaking or harsh rubbing. CAUTION Solvent cleaners require adequate ventilation. c. Leather material should be cleaned with saddle soap or mild soap and water. Revised: 8/10/80 HANDLING AND SERVICING 1B21 Island Enterprises PIPER SENECAII SERVICEMANUAL 2-52. CLEANING CARPETS. Use a small whisk broom or vacuum to remove dirt. For soiled spots, use a non-inflammable dry-cleaning fluid. Floor carpets may be removed and cleaned like any household carpet. 2-53. LUBRICATION. 2-54. OIL SYSTEM(ENGINE). 2-55. SERVICINGOIL SYSTEM. The engine oil level should be checked before each flight and changed after each 100 hours of engine operation. During oil change the oil screen(s) should be removed and cleaned, and the oil filter cartridge replaced. Replaceoil filter at 50 hour intervals. The engine manufacturer does not recommend oils by brand names. Use a quality brand Aviation Grade oil of the proper season viscosity. For information on the use of detergent oil, refer to Paragraph 2-60. CAUTION Do not introduce any trade additive to the basic lubricant unless recommended by the manufacturer. 2-56. FILLING OIL SUMP. The oil sump should normally be filled with oil to the mark on the engine dipstick. The quantity of oil required for the enginesmay be found in Table II-I. The specifiedgrade of oil may be found in Table II-III, the Lubrication Chart, or on the cowl panel access door of each engine.To service the engine with oil, open the accessdoor of the cowl and remove the oil filler cap. 2-57. DRAINING OIL SUMP. To drain the oil sump, provide a suitable container with a minimum capacity of that required to fill the sump. Remove the accesspanel in the lower cowl and remove oil drain plug located on the underside of the engine. It is recommended the engine be warmed to operating temperature to insure complete draining of the old oil. 2-58. OIL SCREEN (SUCTION). The oil suction screen is located on the bottom aft end of the engine sump, installed horizontally. To remove, cut the safety wire and remove the hex head plug. The screen should be cleaned at each oil change to remove any accumulationof sludge and to examine for metal filings or chips. If metal particles are found in the screen, the engine should be examined for internal damage. After cleaning and inspection, place the screen inside the recess in the hex head plug to eliminate possible damage to the screen. Insert the screen into the housing and when certain that the screen is properly seated, tighten and safety the plug with MS-20995-C41safety wire. 2-59. OIL FILTER (FULL FLOW). a. The oil filter should be replaced after each 50 hours of engine operation; this is accomplishedby removing the lockwire from the bolt head at the end of the filter, loosening and removing the filter assembly from the adapter. b. Before discarding the filter, remove the outer cover, and using a sharp knife, cut through the folds of the element at both ends. Then carefully unfold the pleated element and examine the material trapped in the filter for evidence of internal engine damage such as chips or particles from bearings. In new or newly overhauled engines,some small particle or metallic shavingsmight be found; these are generally of no consequence and should not be confused with particles produced by impacting, abrasion or pressure. Evidence of internal engine damage found in the oil filter justifies further examination to determine the cause. Reissued:10/11/79 HANDLINGAND SERVICING 1B22 Island Enterprises PIPER SENECA II SERVICE MANUAL NOTE Ascertain that oil filter completes with specifications of Continental Aircraft Engine Service Bulletin M75-7. c. Before installing the new filter, lubricate the gasket on the filter with engine oil, then install. Tighten slightly more than hand tight or 3 4 to I full turn after gasket makes contact. Do not over torque. d. Run the engine and check for oil leaks: then install lockwire between nut on filter and oil filter adapter assembly. 2-60. RECOMMENDATIONS FOR CHANGING OIL. The engine manufacturer recommends that the oil supply be drained and the entire sump filled with fresh oil after each 100 hours of engine operation. Always start and warm the engine to operating temperature before performing an oil change. While draining the oil, the screens should be removed from the crankcase cover and cleaned thoroughly. If sludge deposits are heavy. subsequent oil changes should be made at shorter intervals. Detergent oil that meets the latest revision of Continental Motors Corporation Specification MHS-24, is the only recommended lubricating oil. Use SAE-30 15W-50 or 20W-50 below 40° F and SAE-50 15W-50. 20W-50 or 25W-60 above 40° F. When the average ambient air temperature is approximately at the dividing line, use the lighter oil. 2-61. LUBRICATION INSTRUCTIONS. Proper lubrication procedures are of immeasurable value both as a means of prolonging the service life of the airplane and as a means of reducing the frequency of extensive and expensive repairs. The periodic application of recommended lubricants to their relevant bearing surfaces. as detailed in the following paragraphs, together with the observance of cleanliness will insure the maximum efficiency and utmost service of all moving parts. Lubrication instruction regarding the locations, time intervals, and type of lubricants used may be found in the Lubrication Chart. To insure the best possible results - from the application of lubricants, the following precautions should be observed: a. Use recommended lubricants. Where general purpose lubricating oil is specified, but unavailable. clean engine oil may be used as a satisfactory substitute. b. Check the components to be lubricated for evidence of excessive wear and replace them as necessary. c. Remove all excess lubricants from components in order to prevent the collection of dirt and sand in abrasive quantities capable of causing excessive wear or damage to bearing surfaces. NOTE If the airplane is inactive for long periods of time, it should be lubricated in accordance with Lubrication Chart every 90 days. 2-62. APPLICATION OF OIL. Whenever specific instructions for lubrication of mechanisms requiring lubrication are not available, observe the following precautions: a. Apply oil sparingly, never more than enough to coat the bearing surfaces. b. Since the control cables are sufficiently coated by the manufacturer, additional protection for the prevention of corrosion is unnecessary. c. Squeeze the magneto cam follower felts at regular inspection periods. If oil appears on fingers, do not add oil. If the felt is dry, moisten with light oil. Revised: 12/08/83 1B23 HANDLING AND SERVICING Island Enterprises PIPER SENECA SERVICEMANUAL CAUTION Be careful not to add too much oil, because the excess will be thrown off during operation and will cause pitting and burning of the magneto points. 2-63. APPLICATIONOF GREASE. Care must be taken when lubricating bearings and bearing surfaces with a grease gun, to insure that gun is filled with new clean greaseof the grade specified for the particular application before applying lubricant to the greasefittings. a. Where a reservoiris not provided around a bearing, apply the lubricant sparinglyand wipe off any excess. b. Remove wheel bearings from the wheel hub and clean thoroughly with a suitable solvent.When repacking with grease, be sure the lubricant enters the space between the rollers in the retainer ring. Do not pack the grease into the wheel hub. c. Use extra care when greasing the constant speed propeller hub to avoid blowing the clamp gaskets. Remove one grease fitting and apply grease to the other fitting until fresh greaseappears at the hole of the removed f