PIPER AIRCRAFT PA-32-301 /301T MAINTENANCE MANUAL

H'illiarnsport. Pa. 1770 1 Parts Catalog = AVCO LYCOMIVG - P S PC-I02 Abco Lycorning Di\ ision Williarnsport. Pa. 17701 Operators Handbook = AVCO LYCOMIVG 10-540 and TIO-540 SERIES AIRCRAFT ESGISES - P V 60297-10 A \ r o Lycoming Di\.ision Williamsport. Pa. 1770 1 PROPEL1 E R : O\erhaul Instructions = HARTZELL COMPACT COSST.\\T SPEED and FEATHERISG PROPELLER - P S 11'-D Hartzell Propeller Inc. Piqua. Ohio 45356 \1.4GVETOS: I nqtallation. Operation and Maintenance l nst ruct ions = D-2000 and D-2200 SERIES M.4G\ETO IGSITIOS SYSTEM - P S L-928 Bendix Electrical Components Di~lslon Sidne!.. S ~ H York 13838 .41'TO FLIGHT: CEVTURY 41 A C T 0 PILOT EDO-41 RE Mitchell P.O. Box 610 31ineral H'ells. Texas 76067 Introduction Page - 4 Revised: August 9. 1984 PIPER AIRCRAFT PA-32-301 /301 T MAINTENANCE MANUAL PIPER PL'BLICATIOSS. C O \ I \ I C \ I C A T I O S S : Rrmo\ al. Installation and Maintenance Instructions = 761 502 Autocontrol Ill B S e n ice V a n u a l 761 481 AutoFlite I 1 S e n ice Manual 753 771 Pitch Trim S e n i c e Manual Radio S e n i c e and Maintenance Manual = 761 7 13 Avionics Wiring Diagram Ser\ ice Manual Vol. I and Vol. 11 ( 1979) REPAIRS: A.B.S. Thermoplastic Landing Gear Wheel and S t r u t Fairing Repair Instructions = 761 708V A.B.S. Thermoplastic Landlng Gear Wheel a n d Strut Fairing Repair lnstructlon Manual P A R T S C A T A L O G = 761 720 PA-32-30] 3OlT P E R I O D I C I S S P E C T I O N R E P O R T F O R M = 230 1046 PA-32-301 3OIT P R O G R A M M E D I S S P E C - TIOY M A S U A L = 761 747 PA-32-301 3OIT l ntroduction Page - 5 Revised: August 9, 1984 PIPER AIRCRAFT PA-32-301 /301T MAINTENANCE MANUAL S Y S T C H A P C A M A S Y S T E M I C H A P T E R I N D E X G U I D E S U B - S Y S T S E C T I O S T I T L E A I R W O R T H I N E S S T I M E L I M I T S M A l N T C H E C K S D I M E N S I O N S A N D A R E A S L I F T I K G A N D SHORllVG L E V E L I S G A N D W E I G H I N G T O W I N G A K D T A X I I N G P A R K I S G A N D M O O R I N G R E Q U I R E D P L A C A R D S S E R V I C I S G - L U B R I C A T I O K S T A S D A R D P R A C T - A I R F R A M E E N V I R O N M E N T A L S Y S T E M A U T O F L I G H T C O M M U S I C A T I O N S E L E C T R I C A L P O W E R E Q U I P M E N T : F U R K I S H I N G S F L I G H T C O N T R O L S F U E L L A S D I N G G E A R L I G H T S N A V I G A T I O N & P I T O T , S T A T I C O X Y G E N A E R O F l C H E G R I D \O. I A'O l B l l 1C15 1 D ' O Introduction Page - 6 1A7 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-30 1/30 1T MAINTENANCE MANUAL G A M A SYSTEM/CHAPTER INDEX G L I D E (cont) SYST SUB-SYST C H A P S E C T I O S T I T L E 3 7 V A C U U M 39 E L E C T R I C A L S T R U C T U R E S D O O R S S T A B I L I Z E R S W I S D O W S W l S G S P R O P E L L E R S S T A S D A R D P R A C T I C E S - E N G I K E S P O W E R P L A N T E N G I K E F U E L S Y S T E M I G S I T I O S E S G I N E I K D I C A T I S G E X H A U S T O I L S Y S T E M S T A R T I N G T U R B I N E S C H A R T S A N D W I R I N G D I A G R A M S S P E C I A L P U R P O S E E Q U I P M E N T A E R O F I C H E G R I D KO. 'I' 21 15 21 18 Introduction Page - 7 Revised: August 9. 1984 PIPER AIRCRAFT PA-32-301 /301T MAINTENANCE MANUAL FIGURE S O LIST OF ILLUSTRATIONS SUBJECT GRID \ O Three View of PA-32-301 Three View of PA-32-301T Station Reference Lines (PA-32-30 1 ) Station Reference Lines (PA-32-30 IT) Access Plates and Panels Jacking Lekeling Airplane Weighing Placards and Decals Fuel Filter Bowl and Screen Servicing Points Main Gear Oleo Struts (Cut-Away View) Lubrication Chart (Landing Gear. Main) Lubrication Chart (Landing Gear, Nose) Lubrication Chart (Control System) Lubrication Chart (Air Conditioning Condenser) Lubrication Chart (Cabin Door. Baggage ~ o o r and Seat) Lubrication Chart (Power Plant. Propeller and Control Pivot Points) Lubrication Chart (Back-Up Extender and Fuel Selector) Torque Wrench Formula Method of Installing Rod End Bearings Cherrylock Rivet Removal Hose Line Markings Flareless-Tube Fittings Maximum Distance Between Supports for Fluid Tubing Cabin Heater. Defrosters and Fresh Air System ( PA-32-30 1 ) Cabin Heater. Defroster and Fresh Air System ( PA-32-30 1 T) Air Conditioning System lnstallation (Typical) Service Valves Test Gauge and Manifold Set Manifold Set Operation Leak Test Hookup E\acuation Hookup Charging Stand Charging Hookup Compressor and Fabricated Oil Dipstick Compressor and Alternator Belt Installation Magnetic Clutch Condenser Air Scoop Installation Expansion Valve Components Installation Air Conditioning Wiring Schematic (Early Models) Air Conditioning Wiring Schematic (Later Models) IE15 I E23 I F4 I F5 I F6 I F7 I F9 IF11 I FI? I F17 IF18 l F2O I F24 1GI 1G3 I G4 1G5 Introduction Page - 8 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301/301T MAINTENANCE M A N U A L LISTOF ILLUSTRATIONS (cont) SUBJECT Emergency Locator Transmitter Schematic (Narco) E LT.Portable Folding Antenna (Narco) ELT Using Fixed Aircraft Antenna (Sarco) Avionics Master and Emergency Switch Circuit Exploded View of Alternator - Prestolite Lamp-Bank Load Removal of Slip Ring End Bearing Removal of Rectifier Removal of Drive End Head Remo\al of End Head Bearing Testing Rotor for Ground Testing Rotor for Shorts Installation of Bearing Installation of Rectifier Terminal Assembly - Prestolite Slip Ring End Bearing Assembly Testing Alternator Brush Installation Internal Wiring Diagram Alternator Exploded View - Ford Rear View Terminal Identification Stator Core and Windings Rectifier Assembly Internal Relationship of Alternator Components Rectifier Ground and Positive Diode Test Stator Ground and Negative Diode Test Field Circuit Open or Ground Test Alternator Housing Disassembly Rear Housing Components Front Housing Disassembly Front Housing Components Rotor Continuity Test Rotor Ground Test Stator Continuity Test Stator Ground Test GRID \ O Introduction Page - 9 Revised: August 1 1, 1983 PIPER A I R C R A F T PA-32-301 /301T MAINTENANCE MANL'AL L I S T O F I L L U S T R A T I O N S (cont) SUBJECT Diode Testing Front Housing Assembl! Rear Housing Bearing and Brush Assembly l nstallation Rear Housing Components H ousing Assembly Alternator Installation - Ford Seat Back Lock Rod End Installation Method Control Column Assembl) Aileron Controls Aileron Rigging Bellcrank Rigging Tool Aileron Rigging Tool Aileron Rudder Interconnect Rudder Controls Rudder Rigging Tool Rudder Tratel Adjustments Rudder Rigging Clamping Rudder Pedals Rudder Trim Control Rudder Steering Pedal Assembly Stabilator Controls Stabilator Rigging Stabilator Tra\ el Adjustments Methods of Securing Trim Cables Stabilator Trim Controls H'rapp~ngTrim Barrels Stabilator Rigging Tool Manually Operated Flap System Flap Step Adjustment Electrically Operated Flap System Flap Rigging Tool Fuel System (PA-32-301) Fuel System (PA-32-f01T) Fuel Cell Installation 1 nstallation of Locking Fuel Cap Fuel Filter Fuel Gauge Main Gear Oleo Strut Assembly Main Gear Installation Nose Gear Oleo Strut Assembly G R I D YO 1113 i115 1115 1116 112.1 15 12 lJ 13 1.1 I6 1j20 1j20 1j21 1j23 1 K 2 I K 1 I K 1 I K 1 I K J 1k5 1 K ' I K9 I K I ! 1k15 1k15 I K I ' I K 2 O I K20 I K 2 1 I K 2 1 I L2 I LJ 2,422 2 423 2 B3 2Bl l 2812 2B16 2824 2c2 2C4 I nttoduction Page - 10 Revised: August 9, 1984 PIPER AIRCRAFT PA-32-301 1301 T MAINTENANCE M A N L A L FIGURE \O. LIST OF ILLUSTRATIONS (cont) SUBJECT Sose Gear lnstallation Clamping Rudder Pedals in Neutral Position Rudder Pedals at Seutral Angle Main Wheel Assembly Sose Wheel Assembly Brake Assembly - Removal and lnstallation of Anchor Bolts Brake Disc Minimum Thickness Brake System lnstallation Brake Master Cylinder ( H a n d . Parking Brake) Toe Brake lnstallation Brake Cylinder ( 10-30) (Toe Brake) Brake Cylinder ( 17000) (Toe Brake) Landing Gear Fairing lnstallation Strobe Light Connections Pitot-Static System lnstallation Fixed Oxygen System lnstallation Test Apparatus for Testing Oxygen S!fstem Oxygen Tubing Installation lnstallation of Sn.agelock Fittings Oxygen Cylinder and Regulator Assembly Oxygen System Recharge Valve lnstallation Ox!,gen Pressure Gauge lnstallation Oxygen lnstallation (Portable) Skin Material and Thickness Surface Scratches. Abrasions or Ground-in-Dirt Deep Scratches. Shallow Sicks and Small Holes Mixing of Epoxy Patching Compound Welding Repair Method Repairing of Cracks Various Repairs Repair of Stress Lines Repair of Impacted Damage Snubber lnstallation Empennage Group Stabilator Balancing Rudder Balancing Windshield Installation (Typical) G R I D S O 2C8 2c10 2C lo 2Cl l 2C I? 2C15 2C16 2C16 2c11 2C18 2C20 2C2 1 2C2 1 'Dl ' D l ? 2d20 2et1 'El l 2E 13 SE 16 2E 19 2E 19 2e21 2F2 zf21 2G I SG' 2G 2 2G3 2G3 2G 4 2G6 2G 6 2G I4 2G 23 ZH I 2H3 2H8 Introduction Page - 11 Revised: August 1 1. 1983 PIPER AIRCRAFT PA-32-301130 1T MAINTENANCE MANUAL FIGURE S O . LIST OF ILLUSTRATIONS (cont) SUBJECT Side Windou Installation. Single Pane (Typical) Wing lnstallation Aileron and Flap Installation Aileron Balance Configuration Typical Nicks and Removal Method Propeller lnstallation (PA-32-301) Three Blade Propeller lnstallation (PA-32-301) Propeller Installation (PA-32-30 IT) Three Blade Propeller lnstallation (PA-32-301 T) Propeller Governor Engine Installation (PA-32-30 1 ) E ngine Mount lnstallation (PA-32-301T)(Dynafocal) Engine Mount Installation (PA-32-30 1 T) (Lord Mounts) Fuel injector Schematic Diagram of RSA Fuel Injection System Fuel-Air Bleed Sozzle Adjustment of Engine Controls Height of Spring in Distributor Block Tower Contact Points Engine Timing Marks Timing Light Connected to Magneto Timing Marks on Magneto Rotor Painted Tooth Centered in Timing Window Timing Mark on Rotor Aligned with Pointer Timing Light Connected to Magento and Breakers Cam End View of Magneto Removing Impulse Coupling Checking Flyweight to Stop Pin Clearance Stop Pin lnstallation Dimension Checking Flyweight Axial Wear with Drill Shank Checking Flyweight Radial Wear with Gauge Points of Coupling Body Wear Acceptable and Deformed Coupling Springs Checking impulse Coupling for Magnetization Orientation of Spring in Coupling Body Lifting Inner End of Spring Checking Harness Lead Continuity Checking Harness Lead Insulation Resistance Modified Pliers Removing Spring From Lead Assembly Assembly Tool Using Assembly Tool Ferrule Postioned Under Braid Ferrule Seating Tool Position of 11-8627 Kit and Contact Spring at Start of lnstallation GRID \ O . Introduction Page - 12 Revised: August 1 1, 1983 PIPER AIRCRAFT PA-32-301 /301T MAINTENANCE MANUAL LIST OF ILLCSTRATIONS (cont) FIGURE K O . SUBJECT Position of 11-8627 Kit and Contact Spring After Installation Lubricating Sleeve Lubricating Ferrule Shoulder Removing Spark Plug Frozen to Bushing Ignition Switch Wire Positions Exhaust System Inspection Points Exploded View of Gear Reduction Starting Motor Turning Starting Motor Commutator Testing Motor Armature for Shorts Testing Motor Fields for Grounds So-Load Test Hook-Up Stall-Torque Hook-Up Turbocharger Installation Tire Balancer Fixture Orifice Replacement Tool Fabricated Tool for Baggage Door Lock Retainer Ring Tool Fabricated Aileron Bellcrank Rigging Tool Fabricated Rudder Rigging Tool Fabricated Aileron and Flap Rigging Tool Fabricated Stabilator Rigging Tool Control Surface Balancing Tool G R I D 5 0 Refer to Card 3, Grid No. 3011 for Electrical Schemaric Index. lntroduct ion Page - 13 Revised: August 9. 1984 PIPER AIRCRAFT PA-32-30] /301T MAINTENANCE MANUAL LIST OF CHARTS SUBJECT Leading Particulars and Principal Dimensions Thread Lubricants Type of Lubricants Hose Clamp Tightening (Initial Installation) Blower System Wire Color Codes Troubleshooting (Air Conditioner) Troubleshooting (Air Conditioning System) Temperature Pressure Aluminum Tubing Torque System Vacuum Chart Compressor Oil Charge Troubleshooting (Alternator) Troubleshooting (Battery) Alternator Specifications (Prestolite) Alternator Belt Tension (Prestolite) Hydrometer Reading and Battery Charge Percent Electrical System Component Loads Troubleshooting (Surface Controls) Cable Tension Vs. Ambient Temperature Troubleshooting Chart (Fuel System) Fuel Cell Repair Equipment Lists Sender, Fuel Quantity Gauge Tolerances Troubleshooting Chart (Landing Gear) Sose Gear Alignment Tolerances Electrical System Troubleshooting Troubleshooting (Rate of Climb Indicator) Troubleshooting (Altimeter) Troubleshooting (Airspeed Tubes and Indicator) Troubleshooting (Gyro Horizon Indicator) Troubleshooting (Directional Gyro Indicator) Troubleshooting (Magnetic Compass) Troubleshooting (Turn and Bank Indicator) Troubleshooting (Oxygen System) Oxygen System Component Limits (Fixed) Filling Pressures for Certain Ambient Temperatures Oxygen System Component Limits (Portable) Troubleshooting (Vacuum System) List of Materials (Thermoplastic Repair) Propeller Specifications (PA-32-301) Propeller Specifications (PA-32-301T) Engine Troubleshooting Chart Troubleshooting (Magneto) Coupling Torques GRID SO. introduction Page - 14 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301 /301T MAINTENANCE MANUAL CHART YO. LIST O F CHARTS (cont) SUBJECT Troubleshooting (Manifold Pressure Indicator) Troubleshooting (Tachometer) Troubleshooting (Engine Oil Pressure Gauge) Troubleshooting (Oil Temperature Indicators) Troubleshooting (Exhaust Gas Temperature Gauge) (Alcor) Troubleshooting (Cylinder Head Temperature Gauge) Troubleshooting (Starter) Starting Motor Specifications Troubleshooting (Turbocharger) Tube and Hose Assembly Torque Recommended Nut Torques Decimal Conversions Conversion Charts List of Consumable Materials Electrical Wire Coding Electrical Symbols GRID \ O Introduction Page - I S Revised: August 9, 1984 CHAPTER AIRWORTHINESS LIMITATIONS PIPER A I R C R A F T PA-32-301 /3@I T M A I N T E N A N C E MANUAL CHAPTER SECTIOL S t BJECT S L BJECT GRID 10. EFFECTIi IT) 4-00-00 .AlR\I'ORTHISESS LIM ITATIO\S 4-0 1-00 General 4 - Cont./Effec. ! Page - 1 Revised: August 11. 1983 iI PIPER AIRCRAFT PA-32-301 /301T SIAINTENANCE MANUAL T h e airworthiness limitations are F A A approved and specif!. inspections and maintenance req~ilrcd under Part 91.163 of the Federal A\iation Regulations. The following limitationsrelated t o fatigue life of the airplane and its components h a l e been c\tahl~.hr.J with respect t o the PA-32-301 3OIT airplane: I . T h e safe life of the airframe structure will be released when the information become\ a\allahle 2 . T h e safe life limit of the propeller blades is unlimited. Rejer to the LIMITATIONS in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual for a detailed delineation of the flight limitations ofthe airplane. The mandatory replacement time and or inspection intervals of life Iimitedparts are contained in Chapter 5 of this manual. - END - 4-0 1-00 Page 4-01 Revised: August 11. 1982 CHAPTER TIME LIMITS/MAlNT CHECKS PIPER AIRCRAFT PA-32-301 /301T MAIlVTENANCE MANUAL CH.4PTER SECTIOK SI'BJECT - CH.4PTER 5 - TIME L I M I T S / M A I N T E S A S C E CHECKS TABLE O F COSTEYTS/EFFECTII'ITY SUBJECT G R I D 5 0 . EFFECTI\'IT\t TIME LIMITS lnspection Requirements Preflight Checks O\erlimits lnspection SCHEDULED MAIYTENASCE Periodic Inspections Programmed lnspection \:\SCHEDULED MAIYTEVASCE CHECKS Spec~alInspections as Required. Upon Condit~on 1.423 I A23 3R h - $ 4 l BlO l BlO l B l O 5 - Cont./Effec. Page - 1 Revised: August 9. 1981 1 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL This chapter p r o ~ i d e sinstructions for conducting inspections. Repair o r replacement instructions for those components found t o be unserviceable at inspection may be found in the chapters c o ~ e r i n gthe applicable aircraft system. U hen working on engines. ground the magneto primary circuit before performing an? operation. TIME LIMITS. INSPECTION REQUIREMENTS. The required inspection procedures are listed in Periodic Inspections. T h e inspection procedure is broken d o w n into major groups which include Propeller. Engine. Turbocharger. Cabin. Fuselage and Empennage. Wing. Landing Gear. Operational Inspection a n d General. T h e first column in each group lists the inspection o r procedure to be performed. T h e second column is divided into four columns indicating the required inspection i n t e r ~ a l sof 50 hours. 100 hours. 500 hours. a n d 1000 hours. Each inspection o r operation 1 5 required a t each of the inspection i n t e n a l s as indicated by a circle ( 0 ) . If a n item is not entirel! accessible o r must be r e m o ~ e d .refer t o the applicable chapter of this manual for instructions on h o ~ to gain access to remoLe the item. b hen performing inspections, use inspection forms furnished by the Piper Factory S e n Ice Department. a t ailable through Piper Dealers o r Distributors. - NOTE - In addition to inspection intervals required in Periodic Inspections, preflight inspections must be performed. PREFLIGHT CHECKS. This check is for the pilot a n d ' o r mechanic and should become part of the airplane operational routine a n d o r preflight check before each flight. Refer t o Section 1V of the Pilot's Operating Manual for a I~stingof items that must be checked. OVERLI3IITS INSPECTION. I f the airplane has been operated s o that any of its components have exceeded their maximum operational limits. check u i t h the appropriate manufacturer. 5-1 3-00 Page 5-01 Revised: August 1 I , 1983 PIPER AIRCRAFT PA-32-301/301 T *MAINTENANCE MANUAL , SCHEDULED MAINTENANCE CHECKS. PERIODIC INSPECTIONS. Perjorm all inspections or operations at each inspection interval as indicated by a circle (0). (See Notes 1, 2, 3 and 4.) Nature of Inspection A . PROPELLER GROUP I . Inspect spinner and back plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2. lnspect blades for nicks and cracks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3. Check for grease and oil leaks.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4. Lubricate propeller per lubrication chart in maintenance manual. . . . . . . . . 5. Inspect spinner mounting brackets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6. lnspect propeller mounting bolts and safety (check torque if safet! is broken) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7. Inspect hub parts for cracks and corrosion.. . . . . . . . . . . . . . . . . . . . . . . . . . . 8. Rotate blades and check for tightness in hub pilot t u b e . . . . . . . . . . . . . . . . . 9. Remove propeller: remove sludge from propeller and crankshaft . . . . . . . . . 10. lnspect complete propeller and spinner assembly for security, chafing. cracks, deterioration, wear. and correct installation . . . . . . . . . . . . . . . . . . . . I I. Overhaul propeller (per latest revision Hanzell Service ......................................................... Letter 61) B. ENGINE CROUP WARNING: Ground magneto primary circuit before working on engine. NOTE: Read notes 5 . 23, and 24 prior to completing this inspection group. I . Remove engine cowl and inspect for damage .......................... 2. Clean and inspect cowling for cracks, distortion. and loose o r .................................................. missing fasteners 3. Drain oil sump (see note 6) ......................................... 4. Clean suction oil strainer a t oil change (inspect for foreign ......................................................... panicles) 5. Change full flow (cartridge type) oil filter element (Inspect element for foreign panicles) ........................................ Inspection Time (hrs) 5-21 -00 Pone 5-02 Interim Revision: September 26, 1986 PIPER AIRCRAFT PA-32-301 1301 T *MAINTENANCE MANUAL -- PERIODIC INSPECTIONS. (cont) Perform all inspections or operations at each of the inspection intervals as indicated by a circk (0). {See Notes 1, 2, 3 and 4.1 5-21 -00 Page 5-03 Revised: August 11. 1983 Nature of Inspection B. ESCINE CROUP (cont) 6. Inspect oil temperature sender unit for leaks and security ............... 7. Inspect oil lines and fitting for leaks, security, chafing, dents and . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . cracks (See Sote 8 ) ........................... 8. Clean and inspect oil radiator cooling fins.. . . . . . . . . . . . . . . . . . . . . . . . . . . 9. Remove and flush oil radiator (See Note 16) 10. Fill engine with oil per information on cowl or lubrication chart ............................................ in Maintenance Manual 11. Clean engine ...................................................... CAUTIOS: Use caution not to contaminate vacuum pump with 1 cleaning fluid. (Refer to latest revision Lycoming 1 Service Letter No. 1221) I 12. lnspect condition of spark plugs (Clean and adjust gap as 1 required; adjust per latest revision Lycoming Service / Instruction S o . 1042). .............................................. I SOTE: If fouling of spark plugs has been apparent, rotate ! bottom plugs to upper plugs. i 13. lnspect spark plug cable leads and ceramics for corrosion I , and deposits ...................................................... . 14. Check cylinder compression (Ref: AC 43.13-lA) . . . . . . . . . . . . . . . . . . . . . . . : 15. Inspect cylinders for cracked or broken fins . . . . . . . . . . . . . . . . . . . . . . . . . . . i 16. lnspect rocker box covers for evidence of oil leaks. If found. 1 replace gasket; torque cover screws 50 inch-poundsi 1 ( S e e N o t e 1 2 ) ...................................................... j NOTE: Lycoming requires a Valve Inspection be made after every 400 hours of operation. (See Note I I ) ; 17. lnspect ignition harness and insulators for high tension leakage ..................................................... andcontinuity 18. Check magneto points for proper clearance (Maintain clearance ........................................................... at.016) .................................. . 19. Inspect magneto for oil seal leakage 1 20. Inspect breaker felts for proper lubrication ............................ 21. lnspect distributor block for cracks, burned areas or corrosion. and height of contact springs ........................................ 22. Inspect magnetos to engine timing ................................... 23. Overhaul or replace magnetos (See Note 7 ) . ........................... 24. Remove air filter and clean per Chapter 12 (Replace as required) .......................................................... . 50 0 0 0 0 0 Inspection 100 0 0 0 0 0 0 0 0 0 Time 500 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 (hrs) 1000 0 0 0 0 0 0 0 0 0 0 0 PIPER A I R C R A F T PA-32-301/301T *MAINTENANCE MANUAL PERIODIC INSPECTIONS. (cont) Perform all inspections or operations at each of the inspection intervals as indicated by a circle ( 0 ) . (See Notes 1, 2, 3 and 4.) Nature of Inspection B. ENGINE GROUP (cont) 5-21-00 Page 5-04 Revised: August 11. 1983 25. Clean fuel injector inlet line screen (Clean injector nozzles ........................... as required) (Clean with acetone only) . . . . ; 26. Inspect condition of alternate air valve and housing ................................................. (Refer t o Note 13) 27. Inspect intake seals for leaks and clamps for tightness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . (Torque clamps 40-50 inch-pounds) . . . . . . . . . . . . . . . . . . . . 28. Inspect all air inlet duct hoses (Replace as required) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Time (hrs) 0 0 0 0 50 500 100 0 1 0 0 ; O o i o ! 0 1 0 1 i0 1 0 1 0 1 ° 11;O i O 0 1 0 0 0 0 0 0 0 0 29. Inspect condition of flexible fuel lines I 1 0 30. Replace flexible fuel lines (See Note 7). I . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31. Inspect fuel system for leaks. 32. Inspect fuel pumps for operation (engine driven and electric) . . . . . . . . . . . .I 1 :33. Overhaul or replace fuel pumps (engine driven) (See Note 7 ) . I i . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34. Inspect and replace electric fuel pump on condition 1 1 1000 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35. Inspect vacuum pump and lines.. 36. Overhaul or replace vacuum pump (See Note 7) . . . . . . . . . . . . . . . . . . . . . . . 37. Inspect throttle. alternate air, mixture and propeller governor controls for security.'trat.el and operating condition . . . . . . . . . . . . . . . . . . . . 38. Inspect exhaust stacks. connections and gaskets (Refer . . . . . . . . . . . . . . . . . . . . . . . . . . to Chapter 78) (Replace gaskets a s required). 39. Inspect muffler. heat exchange and baffles (Refer to Chapter 78) ......... ..................... 40. Inspect breather tube for obstructions and security 41. Inspect crankcase for cracks. leaks. and security of seam bolts ............ ................. 42. Inspect enpne mounts for cracks and loose mounting.. 43. lnspect all engine baffles (also check engine baffle seals on 0 0 0 I ! I 1 0 j o 9 0 0 I 0 0 0 1 0 PA-32-301T) I l o ' 0...................................................... 44. lnspect rubber engine mount bushings for deterioration (Replace as required) i 1 O ............................................... ............................................. 45. Inspect fire wall seals.. 46. Inspect condition and tension of alternator drive belt (Refer to ............... Chapter 24 or Chapter 21 if air conditioning is installed). 47. Lubricate alternator idler pulley (if installed); remove front grease seal and add grease (Refer to lubrication chart Chapter 12). ............. 0 0 PIPER AIRCRAFT PA-32-301 /301T 'MAINTENANCE M A N U A L PERIODIC INSPECTIONS. (cont) -NOTE - Perjonn a11 inspections or operations at each o/ the inspection intervals as indicated by a cbcle (0).(See Notes 1, 2, 3 and 4,) Nature of Inspection B. ENGINE GROUP (cont) 48. Inspect condition of alternator and starter.. . .... . . . .. . . . . . . . . . . . . . . . . . 49. Inspect security of alternator mounting . . . . . . ... . . . . . . . . . . . . . . . . . . . . . . 50. Check air conditioning compressor oil level (See Note 9 ) . . . . . . . . . . . . . . . . 51. Inspect condition of compressor belt and tension (See Chapter 21) .. . . . . . 52. Inspect compressor clutch security and wiring (See Note 10). . . . . . . . . . . . . 1 53. Inspect security of compressor mounting . . . . . ... . . . . . . . . . . . . . . . . . . . . . . / 54. Check fluid in brake reservoir (Fill as required). . . . . . . . . . . . . . . . . . . . . . . . i 55. Inspect and lubricate all controls (Refer to Chapter 12) . . . . . . . . . . . . . . . . . : 56. Overhaul or replace propeller governor (Refer to latest revision i of Hartzell Service Letter No. 61) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . i 57. Complete overhaul of engine or replace with factory rebuilt (See Note 7) ....................................................... 58. Reinstall engine cowl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Time (hrs) C. TURBOCHARGER GROUP (PA-32-301T) I 5-11-00 Page 5-05 Revised: August 11, 1983 1. Visually inspect system for oil leaks, exhaust system leaks and general condition . . . . . .. . . . . . . . . .. . . . . . .. . . . . . . . . . . . . . . . . . . . . . . I 2. Inspect the turbo housing for cracks.. . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . 3. Inspect the compressor wheel for nicks, cracks or broken blades . . . . . . . . . 4. Inspect for excess bearing drag or wheel rubbing against housing.. . . . . . . . 5. Inspect turbine wheel for broken blades or signs of rubbing ... . . . . . . . . . . 6. Inspect turbocharger to tailpipe coupling clamp for proper seating and nut torque of 40-50 inch pounds and bypass coupling clamp for proper seating and nut torque to 80-90 inch pounds. Safety the clamp nuts. Refer to Maintenance Manual "Installation of Turbocharger.". .. .. . ... . .. . . ... ..... . . .... . ....... .... ... .. . .. . ... 7. Inspect the wastegate for freedom of operation . . . . . .. . . .. . ... . . . . . . . . . 8. Inspect operation of alternate air control.. ....... . ..... . . . . . . .. . . . . . ..I 9. Inspect oil inlet and outlet pons in center housing to include the inlet check valve for leaks.. .............. . .... . . ... . ... . . . . . . . . . . . . . 10. Inspect turbine heat blanket for condition and security.. ... . . . . . . . . . . . . . 11. Inspect interconnect linkage between wastegate valve and throttle . . . . . . . . 12. Inspect induction and exhaust components for worn or damaged areas, loose clamps, cracks and leaks.. .. . . .. . .... . .. . . . . . . . . . 13. Inspect fuel injection nozzle reference manifold for deteriorated hose, loose connections, leaks or obstructions.. . . . . .. . . .. . . . . . . . . . . . . . . 14. Inspect operation of compressor bypass door ........ .. . .. . . . . . . . . . . . . . 15. Reinstall engine cowl . . . . . . . ... . . ........... . .... . .. . .... . . . . . . . .. . . 0 0 0 0 0 PIPER AIRCRAFT PA-32-301 1301 T 'MAINTENANCE M A N U A L PERIODIC INSPECTIONS. (cont) Perform all inspections or operations at each of the inspection intervals as indicated by a cucle (0). (See .Notes 1, 2, 3 and 4.) 5-21-00 Page 5-06 Revised: August 9. 1984 . Nature of Inspection D. CABIN CROVP I . lnspect cabin entrance. doors and uindows for damage. operation and security . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2. Inspect upholstery for tears . . . . :. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 . Inspect seats. seat belts. security brackets and b o l t s . . . . . . . . . . . . . . . . . . . . . 4. Inspect trim operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5. Inspect rudder pedals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 . In$pect parking brake t a l t e and brake handle for operation and c!.linder leaks.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7. In\pect control u heels. column. pulleys and cables (See S o t e 18) . . . . . . . . . 8. Inspect flap control cable attachment bolt (Manually operated flaps only) . 9 . O n aircraft S \ 32-H5---- and up. inspect the electric flap sclecror handle cable attachment for an!. signs of cable f r a y i n g . . . . . . . . . . . 10. O n aircraft S V 12-85---- and up. inhpect the electric flap \creu jack and attachments for condition and lubrication . . . . . . . . . . . . . . . I I . Check landing. navigation. strobe. cabin and instrument lights . . . . . . . . . . . 12. lnspect instruments. lines and attachments . . . . . . . . . . . . . . . . . . . . . . . . . . . . I?. lnspect ro operated instruments and electric turn and bank t o t e r h a u l o r replace as required) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14. Rep1;ice central air filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.'Cle;in or replace t a c u u m regulator filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16. In\pect altimeter (Calibrate altimeter system in accordance ~ i t h F4R 91.170. if appropriate) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17. Inqprct operation of fuel selector valte. (See h'ote 22) . . . . . . . . . . . . . . . . . . I H. I n\pect fuel t alt e drain let er cot.er for security and door for proper operation.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19. Inspect condition of heater controls a n d ducts . . . . . . . . . . . . . . . . . . . . . . . . . 20. Inspect condition and operation of air t e n t s . . . . . . . . . . . . . . . . . . . . . . . . . . . 21. Inspect condition of air conditioning ducts . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12. Rernotr ;ind clean air conditioning etaporator f i l t e r . . . . . . . . . . . . . . . . . . . . Time 500 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 50 0 0 ( h r \ ) I000 0 , 0 1 In3pection I00 0 0 0 I 0 0 0 I I 0 PIPER AIRCRAFT PA-32-301/301 T 'MAINTENANCE MANUAL PERIODIC INSPECTIONS. (cont) - NOTE - Peuonn aU inspections or oprmtlons at each of the hptction intervah as indicated by a circk (0). (See Notes 1, 2, 3 and 4.) 5-21-00 Page 5-07 Revised: A u ~ u s t11, 1983 Nature of Inspection E. FUSELAGE AND EMPENNAGE CROUP 1. Remove inspection plates and panels ........................ . ... . ... . 2. Inspect baggage doors, latches and hinges for operation and security ....................................................... 3, Inspect battery, box and cables (Inspect at least every 30 days. Flush box as required and fill battery per instructions on box). .... . . .... 4. Inspect electronic installations . .... ................ ...... . .. . . . . . .. . . 5. Inspect bulkheads and stringers for damage ................ . .... . . . . . . 6. Inspect antenna mounts and electric wiring.. ...... .... .. . .... . .... . .. . 7. Inspect air conditioning system for freon leaks.. . ....... . ........ . .... . 8. Inspect freon level in sight gauge of receiverdehydrator (Refer to Chapter 21). ... .. ....................... .................. 9. Inspect air conditioner condenser air scoop rigging ... ... . .... ...... . . . . 10. Inspect fuel lines, valves, and gauges for damage and operation .. . ... ... . 11. Remove, drain, and clean fuel strainer bowl and screen located in bottom of selector valve. (Drain and clean a t least every 90 days) .... . ... 12. Inspect security of all lines ........................ ............ . . . . . . 13. Inspect vertical fin and rudder surfaces for damage.. .. ..... . .. . ... . . . . . 14. Inspect rudder hinges, sector and attachments for damage, security and operation . . .......... ................ ....... .... . ........... . . 15. Inspect vertical fin attachments for security.. ................... . . . . ... 16. Inspect rudder control stops to insure stops have not loosened and locknuts are tight .. ................ ......... . ....... . . . 17. Inspect rudder hinge bolts for excess wear (Replace as required) .. . . . ... . 18. Inspect stabilator surfaces for damage .............. ........ .......... 19. Inspect stabilator tab hinges, horn and attachments for damage, security and operation.. ............................. .......... . . . . . . . 20. Inspect stabilator attachments for security and condition (see latest Piper Service Bulletin 856) ...................... .......... ..... ..... 21. Inspect stabilator and tab hinge bolts and bearings for excess wear (Replace as required). ............................ ........ ...... . ... 22. Inspect stabilator control stops to insure stops have not loosened and locknuts are tight .. ............................ . ..... . . 23. Inspect stabilator trim mechanism.. ......................... .... . .. . . 24. Check all cable tensions (use tensiometer) (See Note 17) ......... . .... . . 25. Inspect aileron, rudder, stabilator, stabilator trim cables, turnbuckles, guides and pulleys for safety, damage and operation (See Note 19) ..... .. 26. Clean and lubricate stabilator trim drum s c ~ w (Refer to Lubrication Chart) ................................ .... ........ . .. .. 27. Clean and lubricate all exterior needle bearings ............ ... ......... Interim Revision: ~ l r c h16, 1987 (hrs) 1000 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 5 0 0 0 0 0 Inspection 100 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 Time 5 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 PIPER AIRCRAFT PA-32-301/301T 'MAINTENANCE MANUAL • PERIODIC INSPECTIONS. (cont) Perform all inspections or operations at each of the inspection intervah as indicated by a circle (0).(See Notes 1, 2, 3 and 4.) 5-11-00 Page 5 0 8 Revised: August 11, 1983 Nature of Inspection E. FUSELAGE AND EMPENNAGE GROUP (cont) ................... 28. Lubricate per lubrication chart (Refer to Chapter 12) ................... 29. Inspect anti-collision light for security and operation 30. Inspect security of Autopilot bridle cable clamps .............................................. (Refer to Chapter 22). 31. lnspect all control cables, aileronlrudder interconnect cables, air ducts. , electrical leads. lines, radio antenna leads and attaching parts for I security. routing. chafing, deterioration. wear and correct installation .... ' 32. Inspect emergency locator transmitter battery for replacement date ............... ' or time (See latest revision Piper Service Letter No. 820). ............................... 1 33. Reinstall inspection plates and panels.. !I F. WING GROLrP 1. Remove inspection plates and fairings ................................ 2. Inspect surfaces and tips for damage, loose rivets, and condition of walkway .......................................................... 3. Inspect aileron hinges and attachments ............................... I 4. Inspect aileron controls stops to insure stops have not ...................................... loosened and locknuts are tight I 5. Inspect aileron cables, pulleys and bellcranks for damage and ...................... i operation. Check stops for security (See Note 20) ................ 6. Inspect flaps and attachments for damage and operation 1 7. Inspect condition of bolts used with hinges (Replace as required). ........ ............... 8. Lubricate per lubrication chart in Maintenance Manual.. ........................... I 9. Inspect wing attachment bolts and brackets 10. lnspect fuel tanks and lines for leaks and water (See Note 14) ........... ...................................... I I. Fuel tanks marked for capacity ....................... 12. Fuel tanks marked for minimum octane rating.. .................................. 13. lnspect fuel cell vents (See Note 15) ' 14. Inspect all control cables, air ducts, electrical leads, lines, and attaching I parts for security. routing, chafing, deterioration, wear and correct installation a ........................................................ I .............................................. 15. Inspect security of Autopilot bridle cable clamps (Refer to Chapter 22). 16. Reinstall inspection plates and fairings. ............................... lnspect~onTime (hrs) 1000 50 0 100 500 0 0 0 0 ' I i i 1 0 1 0 0 ' 0 0 0 1 0 0 0 0 0 0 0 0 , O ! 0 j O ' 0 0 1 0I 0 0 0 I 0 0 0 0 1 0 0 1 0 O I 00 1 0 O 0 0 0 0 o 0 0 0 0 0 0 0 0 0 0 0 0 0 1 0 l o o o O I O0 0 0 PIPER AIRCRAFT PA-32-301 /301T *MAINTENANCE MANUAL PERIODIC INSPECTIONS. (cont) a Perform all inspections or operations at each of the inspection intervals as indicated by a circle (0). (See Notes I. 2. 3 and 4.) - -- - 5-2 1-00 Page 5-09 Revised: August 11. 1983 Nature of Inspection C . LANDING GEAR GROUP I . Check oleo struts for proper extension (Check for proper .............................................. fluid level as required) ........................... 2 . Inspect nose gear steering control and travel ............................................ 3. Inspect wheel alignment 4 . Put airplane on jacks ............................................... 5 . Inspect tires for cuts . uneven or excessive wear and slippage ............. 6 . Remove wheels . clean . inspect and repack bearings ..................... 7 . Inspect wheels for cracks. corrosion and broken bolts .................. 8 . C h e c k t i r e p r e s s u r e ................................................. 9 . Inspect brake lining and disc for wear ................................ 10. Inspect brake backing plates for cracks ............................... I I . Inspect condition of brake lines ...................................... I2 . Inspect shimmy dampener operation ................................. 13 . Inspect gear forks for damage ....................................... 14. Inspect oleo struts for fluid leaks and scoring .......................... I5 . lnspect gear struts . attachments . torque links . and bolts for condition and security .............................................. 16. Lubricate per lubrication chart (Refer t o Chapter 12) ................... 17 . Remove airplane from jacks ......................................... H . OPERATIONAL INSPECTION 1 . Check fuel pump and fuel tank selector ............................... 2 . Check fuel quantity . pressure and flow readings ........................ .................................. 3 . Check oil pressure and temperature ............................................ 4 . Check alternator output ............................................ 5 . Check manifold pressure ................................................. 6 . Check alternate air 50 0 0 0 0 0 0 0 0 0 lnspection 100 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 Time 500 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 (hrs) 1000 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 PIPER AIRCRAFT PA-32-3011301T 'MAINTENANCE MANUAL PERIODIC INSPECTIONS . (cont) Perjorm a11 inspections or operations at each oj the inspection intervals as indicated by a circle ( 0 ). (See Notes 1. 2. 3 and 4.) 5-21-00 Page 5-10 . Revised: August 11. 1983 Nature of Inspection H . OPERATIONAL INSPECTION (cont) ............................................... 7 . Check parking brake ............................................... 8 . Check vacuum gauge ................................. 9 . Check gyros for noise and roughness ........................................ 10. Check cabin heater operation ..................................... I I . Check magneto switch operation 12.CheckmagnetoRPMvariation ...................................... ................................. 13. Check throttle and mixture operation ......................................... 14. Check propeller smoothness ..................................... 15. Check propeller governor action .................................................. 16. Check engine idle ....................................... 17. Check annunciator light panel 18. Check electronic equipment operation (Avionics master and ............................................. emergency switch . etc.) ..................... 19. Check air conditioner compressor clutch operation...................... 20 . Check air conditioner condenser scoop operation 21 . Check operation of Autopilot and Automatic Trim (See Note 21) ........ I . GENERAL .............................. I . Aircraft conforms t o FAA Specification ................. 2 . All latest FAA Airworthiness Directives complied with 3. All latest Manufacturers Service Bulletins and Letters complied with ..................................................... ......................... 4 . Check for proper Pilot's Operating Handbook ...................................... 5 . Aircraft papers in proper order lnspection Time (hrs) - 1000 0 0 0 0 0 0 0 0 0 0 50 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 100 0 0 0 0 0 0 0 0 0 0 0 500 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 O 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 PIPER AIRCRAFT PA-32-301/3OlT *MAINTENANCE MANUAL PERIODIC INSPECTIONS (cont) NOTES: I . Refer to the last card of the Piper Parts Price List - Aerofiche, for a check list of current revision dates to Piper inspection reports and manuals. 2. All inspections or operations are required at each of the inspection intervals as indicated by a (0). Both the annual and 100hour inspcctionsarecomplete inspections of the airplane, identical in scope. while both the 500 and 1000 hour inspections are extensions of the annual or 100 hour inspection. which require a more detailed examination of the airplane, and overhaul or replacement of some major components. Inspections must be accomplished by persons authorized by the F A A . 3. Piper service bulletins are of special i m p o n a n a and Piper considers compliance mandatory. 4. Piper service letters are product improvements and service hints pertaining to servicing the airplane and should be given careful attention. 5 . Inspections given for the power plant are based on the engine manufacturer's operator's manual (Lycoming Pan No. 60297-10) for this airplane. Any changes issued to the engine manufacturer's operator's manual shall supersede or supplement the inspections outlined in this report. 6. lntervals between oil changes can be increased as much as 100% on engines equipped with full flow (cartridge type) oil filters. provided the element is replaced each 50 hours of operation. 7. Replace or overhaul as required or at engine overhaul. (For engine overhaul, refer to latest revision Lycoming Service Letter L201.) 8. Replace flexible oil lines at engine TBO per latest revision Lycoming Service Bulletin 240. 9. The compressor oil level should not be checked unless a Freon leak has occurred, requiring an addition of Freon to the system. 10. Clean any traces of oil from the clutch surface. I I. At every 400 hours of engine operation, remove the rocker box covers and check for freedom of valve rockers when valves are closed. Look for evidence of abnormal wear or broken parts in the area of the valve tips, valve keeper, springs and spring seat. If any indications arc found, the cylinder and all of its components should be removed (including the piston and connecting rod assembly) and inspected for further damage. Replace any pans that do not conform with limits shown in the latest revision for Lycoming Service Table of Limits SSP-1776. 12. Check cylinders for evidence of excessive heat indicated by burned paint on the cylinders. This condition is indicative of internal damage to the cylinder and its cause must be determined and corrected before the aircraft is returned to service. Heavy discoloration and appearance of seepage at the cylinder head and barrel attachment area is usually due to emission of thread lubricant used during assembly of the barrel at the factory, or by slight gas leakage which stops after the cylinder has been in service for awhile. This condition is neither harmful nor detrimental to engine performance and operation. If it can be proven that leakage exceeds these conditions, the cylinder should be replaced. I . Check throttle body attaching screws for tightness; the correct torque for these screws is 40 to 50 inch-pounds. 14. Replace flexible fuel supply hose and interconnect hose couplings at time of engine overhaul. 15. Replace fuel tank vent line flexible connections as required, but no later than 1000 hours of service. 5-21-00 Page 5-11 Interim Revision: September 20, 1986 PIPER AIRCRAFT PA-32-301 / 301 T MAINTENANCE MANUAL PERIODIC INSPECTIONS. (eont) NOTES (eont): 16. Refer to latest revision Piper Service Bulletin 586, inspection and replacement of engine oil coolers. 17. Maintain cable tensions specified in chapter 27. 18. Refer to latest revision Piper Service Bulletin 619. 19. Refer to latest revision Piper Service Bulletin 701. 20. Refer to latest revision Piper Service Bulletin 703. 21. Refer to index of vendor publications for appropriate manual p a n number. 22. Refer to and comply with latest Piper Service Bulletin 772. 23. Refer to Lycoming Service Bulletin 469. 24. Refer to VSP 69 100 Hour/Annud Inqection Report printed copies can be obtained jrom Piper Service Sales - under Piper Part Number 230 1046. 5-21-00 Page 5-12 Interim Revision: !September 20, 1986 1B9 PIPER AIRCRAFT PA-32-301 /301T *MAINTENANCE MANUAL PROGRAMMED INSPECTION. The programmed inspection was designed t o permit the best utilization of the aircraft, by scheduling inspections through the use of a planned inspection schedule. This programmed inspection schedule is pre- pared in a manual form which is available from Piper Service Sales - order Piper Part No. 761-747. UNSCHEDULED MAINTENANCE CHECKS. SPECIAL INSPECTIONS A S REQUIRED, UPON CONDITION. The special inspections given, supplement the scheduled inspections as outlined in Periodic Inspections, to include inspections which are required a t intervals not compatible with airframe operating time o r inspection intervals. Typical of this type are: 1. Inspections required because of special conditions o r incidents that arise, and because of these conditions o r incidents, a n immediate inspection would be required to insure funher safe flight. 2. Hard o r Overweight Landing. This inspection should be performed after a known rough landing is made o r when a landing is made while the aircraft is known to exceed the design landing weight. Check the following areas and items: 0 Wings - for wrinkled skins, loose o r missing rivets. Fuel leaks around the fuel tanks. and fuel fittings throughout the wings. 0 Wing spar webs, bulkheads. nacelle skins and attachments, wing and fuselage stringers and skins for any signs of overstress or damage. A possible alignment check to clarify any doubt of damage. 3. Severe Turbulence Inspection. The same items and locations should be checked as stated for Hard o r Overweight Landings along with the following: 0 Top and bottom fuselage skins for loose o r missing rivets and wrinkled skins. 0 Empennage skins and attachments. 4. Engine overspeed, sudden stoppage. loss of oil, ovenemperature and lightning strike. Refer t o Engine Manufacturer for necessary corrective action. 5. Component overlimits inspection. 0 Check with the appropriate manufacturer for the necessary corrective action. -END - 5-51-00 Page 5- 13 Revised: August 11, 1983 a CHAPTER I I DIMENSIONS AND AREAS PIPER AIRCRAFT PA-32-301 /301T MAINTENANCE MANUAL CHAPTER 6 - DIMENSIONS A N D AREAS TABLE OF CONTENTS/EFFECTIVITY CHAPTER SECTION SUBJECT SUBJECT GRID NO. EFFECTIVlTY 6-10-00 DIMENSIONS 6-20-00 STATION REFERENCE LINES 6-30-00 ACCESS A N D INSPECTION PROVISIONS 6-40-00 WEIGHT AND BALANCE DATA 6-50-00 SERIAL NUMBER PLATE 6 - Cont./Effec. Page - 1 Revised: August 23, 1982 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL DIMENSIONS. The principal airplane dimensions are shown in Figures 6-1 and 6-2 and are listed in Chart 601. CHART 601. LEADING PARTICULARS AND PRINCIPAL DIMEKSIOSS MODEL PA-32-30 I PA-32-30 I T ENGINE Manufacturer Avco-Lycoming Avco-Lycorning Model 10-540-K I G5D T10-540-S I AD Rated Horsepower and Speed 300 hp @ 2700 rpm Take-off power (5 minutes max.) 300 hp at 2700 rprn at 36 in. h e . max. Cont~nuous power 270 hp at 2575 rprn at 33 In. hg Oil Sump Capacity I2 U.S. quans 12 U.S. quarts Fuel, Aviation Grade (Minimum and Specified Octane) 100: 130 100' 130 Fuel Injector. Bendix RSA-IOEDI or RSA-IOED2 RSA-IOEDI or RSA-IOED2 Magnetos, Bendix D6LN-203 1 (Dual D6LN-203 I (Dual Mag with impulse Mag with ~mpulse coupling) coupling) Magneto Timing 20 degrees BTC 20 degrees BTC Magneto Point Clearance 0.016 in. 0.016 in. Spark Plugs Refer to latest revision of Lycoming Service Instruction No. 1042. Spark Plug Gap Setting Refer to latest revision of Lycoming Service Instruction No. 1042. Firing Order 1-4-5-2-3-6 1-4-5-2-3-6 Starter. Prestolite I2 volt M24222 M24222 Alternator: Prestolite. 12 volt. 60 amp ALY 64211, ALY 6422' ALY 6421'. ALY 6422: Ford, I2 volt. 90 amp EOFF- 10300-AA' Voltage Regulator, WlCO X 16300B X 16300B Overvoltage Relay, WlCO X 16799 X 16799 Fuel Pump AC Pump Lycoming Lear-Siegler RG9080J6A P a n No. 75247 I Without Alr C o n d l t ~ o n l n # W ~ t hAir C o n d ~ t ~ o n l n g O p t ~ o n a lE q u ~ p m c n to n P A - 3 2 - 3 0 l T O n l y * 6- 10-00 Page 6-01 Revised: August 23, 1982 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL CHART 601. LEADING PARTICULARS A N D PRINCIPAL DIMEKSIONS (cont) MODEL PA-32-30 I PA-32-30 IT PROPELLER Manufacturer Hanzell Hanzell Hub. Model Refer to Chart 6101 Refer to Chan 6102 Blade. Model Refer to Chan 6101 Refer to Chan 6102 Governor Control Hanzell Hanzell Governor. Model F4-I I BZ F4-I 1 BZ FUEL SYSTEM Fuel Tanks 4 (2 interconnected 4 ( 2 interconnected each wing) each w~ng) Capacity 53.5 U.S. gallons 53.5 U.S. gallons (each set) (each set) Unusable Fuel 2.5 U.S. gallons 2.5 U.S. gallons (each set) (each set) Total Capacity 107 U.S. gallons 107 U.S. gallons Total Unusable Fuel 5 U.S. gallons 5 U.S. gallons Electric Fuel Pump Airborne 1 B5-6 Weldon 10080-B 6- 10-00 Page 6-02 Revised: May 21, 1980 PIPER AIRCRAFT PA-32-301 1301T 'MAINTENANCE MANUAL CHART 601. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont) 6- 10-00 Page 6-03 Revised: August 23, 1982 r MODEL PA-32-30 1 i' 30 1 T LANDING GEAR TYpe Fixed Shock Strut Type Combination Air and Or1 Fluid Required (Struts and Brakes) MIL-H-5606 Strut Extension (Exposure under Static Load): Nose 3.50 2 .50 in. Main 4.50 t .SO in. Wheel Base 7 ft. 8 in. Nose Wheel Travel 30° Left & Right Turning Distance (Min.) 59 ft. 10.8 in. Wheel. Nose Cleveland 40-778 or McCauley D-30500 Wheel, Main Cleveland 40-90A Standard or Cleveland 417- 120C H e a ~ yDut! Brake Type Cleveland 30-65 Standard or Cleveland 30-83 Heav! Duty Tire. Nose 5.00 x 5, 6 ply, Type Ill. McCrear or B.F. Goodrich 6:00 x 6, ply, Type 111. McCrear! or B.F. Goodrich (Optronal) Tire, Main 6:00 x 6. 8 ply. McCreary or 6:00 x 6. 8 ply, B.F. Goodrrch (Heavy Duty) Tire Pressure, Nose, Standard 35 psi Tire Pressure. Main. Standard 55 psi Tire Pressure, Nose, Heavy Duty, 5 inch 33-35 psi Tire Pressure. Main. Heavy Duty, 6 inch (With 5 inch Nose Wheel) 35-37 psi Tire Pressure, Nose, Heavy Duty, 6 inch 34 psi Tire Pressure, Main, Heavy Duty, 6 inch 46 psi C PIPER AIRCRAFT PA-32-301/301T 'MAINTENANCE MANUAL Figure 6-1. Three View of PA-32301 6.1&00 Page 6-04 Revised: August 19, 1980 6-10-00 p 8 ~ 6-05 Revised: May 21,1980 PIPER AIRCRAFT PA-32=301/301T *MAINTENANCE M A N U A L 0 5n 1 Figure 6-2. Three View of PA32301T PIPER AIRCRAFT PA-3L-301/301T 'MAINTENANCE MANUAL STATION REFEREKCE LIKES. In order to facilitate the location of various components of the airplane which require maintenance and servicing. a method utilizing fuselage station (Sta.), wing station or buttock line (BL). and water line (WL) designations is frequently employed in this manual. (Refer to Figure 6-3 or 6-4.) Fuselage stations. buttock lines. and water lines are reference points measured by inches in the vertical or horizontal direction from a given reference line which indicates station locations of structural members of the airplane. Station 0 of the fuselage is 78.4 inches ahead of the wing leading edge or 44.5 inches ahead of the lower edge of the fireuall: station 0 (BL) of the wing and stabilator is the centerline of the airplane; and station 0 (WL) of the fuselage vertical stabilizer and rudder is 20.5 inches below the cabin floor as measured at the rear wing spar with the airplane level. The reference datum line is located 78.4 inchesahead of the wing leading edge at the intersection of the straight and tapered section. ACCESS A N D INSPECTION PROVISIONS. The access and inspection provisions for the airplane are shown in Figure 6-5. The component to be seniced or inspected through each opening is identified in the illustration. All access plates and panels are I secured by either metal fasteners or screws. T o enter the aft section of the fuselage, remove the rear close-out access door. - CAUTION - Before entering the aft section of the fuselage, be sure the airplane is supported at the tail skid. WEIGHT A N D 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. SERIAL NUMBER PLATE. The serial number plate is located on the left side of the fuselage near the leading edge of the stabilator. The serial number should always be used when referring to the airplane on service or warranty matters. 6-50-00 Page 6-06 Revised: May 21, 1980 PIPER AIRCRAFT PA-32-30 1 /30 1T *MAINTENANCE M A N U A L Figure 6-3. Station Reference Lines (PA-32-301) 6-5&00 Page 6 0 7 Revised: August 19, 1980 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL Figure 6-4. Station Reference Lines (PA-32-301T) 650-00 Page 6-08 Issued: January 2, 1980 6-50-00 Page 6-09 Revised: August 19. I 980 PIPER AIRCRAFT PA-32-301 1301T *MAINTENANCE MANUAL I I 2859 11 1 8 9 2 0 m n 22 23 1 TIP STABILATOR 13 COVER. FUEL SELECTOR FILTER 2 COWL. ENGINE ACCESS 14. TAIL CONE. CONTROL CABLES & TRIM SCREW 3 SPINNER PROPELLER 15 WlNG TIP 4 DOOR. OIL FILLER 16 COVER, E L T ACCESS 5 COVER AIR FILTER 17 COVER, AILERON BELLCRANK ACCESS 6 COVER. ACCESS (PA-32-3011) 18. COVER. GEAR ATTACHMENT FllTlNG 7 FAIRING. ACCESS 19. DOOR. BAGGAGE 8 FIN TIP 20. CAP, FUEL TANK 9 RUDDER TIP 21. COVER, FUEL FITTING 1 0 PANEL. BATTERY 22. COVER. FUEL AND BRAKE FITTINGS 11 PLATES. TUNNEL ACCESS 23. COVER. FUEL FITTINGS 12 PANEL. FLOOR Figure 6-5. Access Plates and Panels + a CHAPTER LIFTING AND SHORING PIPER AIRCRAFT PA-32-301 1301T MAINTENANCE MANUAL CHAPTER 7 - LIFTING A N D SHORING TABLE OF CONTESTS/EFFECTlVITY CHAPTER SECTIOK SL'BJECT SUBJECT G R I D NO. EFFECTII.ITY 7 - Cont./Effec. Page - 1 Revised: August 1 1 1983 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL Figure 7-1. Jacking J A C K I S G . Jack the airplane as specified to perform \arious service operations. Proceed as folloufs: I. Place the jacks under the jack pads on the wing front spar. - CAUTION - Be sure to apply sufficient support ballast; otherwise, the airplane will tip forward and fall on the fuselage nose section. 2. Attach a tail support t o the tail skid. Place approximately 300 pounds of ballast on the support to hold the tail d o n n. ( Refer to Figure 7-1 .) 3. Carefull! rake jacks until all three wheels are clear of the surface. -- END - 7- 10-00 Page 7-01 Revised: August 11. 1983 CHAPTER LEVELING AND WEIGHING PIPER AIRCRAFT PA-32-301/301T MAINTENANCE MANUAL • CHAPTER 8 - LEVELING A N D WEIGHING TABLE O F CONTENTSIEFFECTIVITY CHAPTER SECTIOS SUBJECT SUBJECT GRID NO. EFFECTIVITY 8-10-00 LEVELING 8-20-00 WEIGHING 8 - Cont./Effec. Page - 1 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301/30lT *MAINTENANCE MANUAL LEVELING. All configurations of the airplane are provided with a means for longitudinal and lateral l e ~ e l ~ n g . The airplane may be le\eled while on jacks. during the weighing procedure while the wheels are on scales. or w hile the wheels are on the ground. T o level the airplane for purposes of weighing or rigging. the following procedures may be used: I. T o longitudinally level the airplane. partially withdraw the two leveling screws located immediately below the left front side window. (Refer to Figure 8-1.) Place a spirit level on these screw heads and deflate the nose wheel tire o r adjust the jacks until the bubble of the level is centered. 2. T o laterally level the airplane. place a spirit level across the baggage compartment floor along the rear bulkhead (refer t o Figure 8- 1 ) and deflate the tire on the high side of the airplane or adjust eitherjack u n t ~ lthe bubble of the level is centered. Longitudinally Laterally Figure 8- 1 . Leveling Airplane 8-10-00 Page 8-01 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301 /301T .MAINTENANCE MANUAL W E I G H I S C . (Refer to Figure 8-2.) The airplane ma! be weighed b! the following procedure: I . Posit~ona scale and ramp in front of each of the three uheels. 2. Secure the scales from rolling forward and tow the airplane up onto the scales. (Refer to T o u ~ n g . Chapter 9.) 3. Remove the ramp so as not to interfere with the scales. 4. I f the airplane is to be weighed for weight and balance computations. lekel the airplane. 8-20-00 Page 8-02 Revised: August 11, 1983 CHAPTER TOWING AND TAXIING PIPER AIRCRAFT PA-32-.301/301T MAINTENANCE MANUAL CHAPTER 9 - TOWING A N D TAXIING TABLE OF CONTEh'TS/EFFECTIVITY CHAPTER SECTIOK SUBJECT SUBJECT G R I D NO. EFFECTIVITY - - TOWISG TAXIING 9 - Cont./Effec. Page - 1 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301/301 T *MAINTENANCE MANUAL TOWING. W'hen 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. Whenmoving the aircraft forward by hand, avoid pushing on the trailing edge of the ailerons as this will cause the aileron contour to change resulting in an out-of-trim condition. T h e airplane may be moked by using the nose wheel steering bar that is stowed below the foruard ledse of the rear baggage compartment o r power equipment that will not damage or cause excessstrain to the nose pear steering assembly. Before attempting t o taxi the airplane. ground personnel should be checked out by a qualified p ~ l o tor other responsible person. Engine starting a n d shutdown procedures should be covered as \\ell. \\ h e n 11 i\ ascerta~nedthat the propeller back blast and taxi areas are clear. apply power to start the taxi roll and pert'orm the follouing checks: 1 . Taxi forw.ard a few. feet and apply brakes t o determine their effectikeness. 2 . Taxi with propellers set in lou pitch. high R P M setting. - 3 . ii'hile taxiing. make slight turns t o ascertain the effecti\eness of steering. 4 . O b s e n e wing clearances w hen taxiing near buildings o r other stationary objects. If poss~ble4tat1onil guide outside the airplane to obser\.e. 5 , \'hen taxiing on uneven ground. look for and avoid holes and ruts. 6 . D o not operate the engines at high R P M u h e n running up o r taxiing o \ e r ground containing looye stones. gra\el. o r an!. loose material that ma?. cause damage t o the propeller blades. - END - 9- 20-00 Page 9-01 Revised: August 11. 1983 a CHAPTER PARKING AND MOORING PIPER A I R C R A F T P.4-32-301/301T MAINTENANCE M A S I ' A L • CH.-\PTER I0 - P A R K I S C , A S D XlOORIUC, CHAPTER SECTIO\ S\H.IECT S1'B.I ECT G R I D \ 0. EFFECTIi I T ) I 0- 10-00 PARKIKG 10-20-00 MOORIKG 10-30-00 1.OCKlSG AIRPLAKE 10 - Cont./Effec. Page - I Revised: August 1 1 . 1983 PIPER AIRCRAFT PA-32-301/301T 'MAINTENANCE MANUAL H'hen parking the airplane. insure that it is sufficiently protected against adt.erse weather conditions and presents no danger to other aircraft. When parking the airplane for any length of time or oternight. i t i 3 recommended that it be moored. 1 . To park the airplane. head it into the wind. if possible. 2. Set the parking brake by pulling back the brake lever and depressing the knob attached to the left side of the handle. Then release the handle. T o release the parking brakes. pull back on the brake leter to disengage the catch mechanism. Then allow the handle t o swing forward. - NOTE - Care should be taken when setting brakes that are overheated or during cold weather when accumulated moisture may freeze the brakes. 3 . The aileron and stabilator controls may be secured with the pilot's seat belt. M O O R I S G . The airplane is moored to insure its immovability. protection. and security under ~ a r i o u surather conditions. The following procedure gives the instructions for proper mooring of the airplane: I . Head the airplane into the wind. if possible. 1. Block the u heels. 3. Lock the aileron and stabilator controls by looping the pilot's seat belt around wheel. -- CAUTION - Use square or bowline knots. D o not use slip knots. Secure tie-down ropes t o the wing tie-down rings and the tail skid at approximatel!. 45 degree angles to the ground. N'hen using rope constructed of non-synthetic material. leave sufficient slack to a\.oid damage to the airplane when the ropes contract due to moisture. A dditional preparations for high winds include using tie-down ropes from the landing gear forks, securing the rudder, and securing the props to prevent windmilling. LOCKING AIRPLANE. For con\,enience. the PA-32-301J301T aircraft are provided with matching ignition and door locks. (Forward cabin door. forward baggage compartment door. and rear cabin door.) One key fits all locks. - END - 10-30-00 Page 10-01 Revised: May 21. 1980 CHAPTER REQUIRED PLACARDS P I P E R A I R C R A F T PA-32-301 1301T M A I N T E N A N C E M A N C ' A L • CH.4PTER I 1 - R E Q l ' I R E D P L A C . 4 R D S CHAPTER SECTIO\ SI'R.1ECT SI'RJ ECT GRID YO. EFFECTI\ IT1 ! I 1-00-00 G E Y E R A L ICI! .A 6-H-l I l - Cont. 1 Effec. Paze - 1 Revised: .August 9. 1984 PIPER A I R C R A F T PA-32-301 /301T MAINTENANCE .M.AVt'A L G E \ E R . \ I . *301TONLY \ I I Figurc I I- I . Placard, and Decal, 11-2&00 Page 11-01 Revised: .Augu\t 9. 1984 PIPER A I R C R A F T PA-32-301 1301 T !tlAISTENANCE M A N l ' A L 1. PLACARD - PIPER-AIRE 40. PLACARD - OXYGEN "PULL ON" 2 NAMEPLATE - SARATOGA 41. PLACARD - CONTROL QUADRANT 3. PLACARD - OXYGEN B O T L E INSTAWTION 42. PLACARD - FUEL GRADE 4. MEDALLION - PIPER LOGO 43. PLACARD - A/P INTR. 5. PLACARD - AIR CONDITIONING DOOR OPEN 44. PLACARD - MIKE 6 . PLACARD - FLAP WARNING 45. PLACARD - CIRCUIT BREAKER PANEL 7. PLACARD - COMPASS 46. PLACARD - CIRCUIT BREAKER PANEL 8. PLACARD - OPEN 47. PLACARD - PITCH TRIM 9. PLACARD - LATCH 48. PLACARD - AUTOFLITE II 10. PLACARD - LIGHT SWITCH 49. PLACARD - OMNl COUPLER SWITCH 1 1. PLACARD - STORM WINDOW 50. PLACARD - CONDUCT TRIM CHECK (13A660-1) 12. PLACARD - OLEO SERVICE INSTAUATIONS 51. PLACARD - RADAR ALTIMETER "ON-OFF" 13. PLACARD - TURN LIMIT 52. PLACARD - RADAR ALTIMETER "OFF FOR TAKEOFF" 14. PLACARD - TURN LIMIT CENTER MARK 53. PLACARD - RADAR ALTIMETER 15. PLACARD - OLEO SERVICE INSTRUCTIONS 54. PLACARD - WARNING 16. PLACARD - SOFT WEAR ONLY 55. PLACARD - ALTITUDE REPORTER INSTALLED 17. PLACARD - RUDDER TRIM 56. PLACARD - FUEL CHECK B O l l L E 18. PLACARD - LANDING CHECKLIST, KNOTS 57. PLACARD - SUMP DRAIN 19 PLACARD - RADIO POWER. "ON-OFF" 58. PLACARD - FLAP LEVER 20. PLACARD - WARNING 59. PLACARD - ALTITUDE LEANING LIMITATIONS 21. PLACARD - STABllATOR TRIM 60.PLACARD - TABLE STOWAGE 22. PLACARD - EMERGENCY BUS SWITCH 61. PLACARD - ELT LOCATION 23 PLACARD - FUEL SELECTOR 62. PLACARD - EXTERNAL POWER 24. PLACARD - OPERATING LIMITATIONS 63. PLACARD - GLIDE SLOPE COUPLER 25. PLACARD - BAGGAGE LIMITATIONS. FORWARD 64 PLACARD - WARNING. EL1 26. PLACARD - BAGGAGE LIMITATIONS. A n 65. PLACARD - RADAR 27. PLACARD - CABIN AIR 6 6 PLACARD . DO NOT PUSH 28. PLACARD - AIR CONDITIONING CONTROL PANEL 6 7 PLACARD - LEVEL POINT 29. PLACARD - VENT FAN CONTROL 68 PLACARD hi0 STEP 30. PLACARD - REDUCE POWER 69 PLACARD - DOOR RELEASE I 31. PLACARD - HEATER AND DEFROST f L l n TO ACTUATE) 7 0 PLACARD . DOOR RELEASE I 32. PLACARD - PlTOT DRAIN 7 1 PLACARD . OIL SPEC 33. PLACARD - ALTERNATE AIR 72 PLACARD . NAV 1 OFF NAV 2 34. PLACARD - DEMONSTRATED CROSSWIND 73 PLACARD - TRANSPONDER IDENTIFIER PITCL( S Y k C 35. PLACARD - NAVIGATION AND INSTRUMENT LIGHTS 7 4 PLACARD . GO-AROUND 36 PLACARD - PRESS TO TEST 75 PLACARD - GEAR 37 MEDALLION - PIPER. CONTROL WHEEL 76 PLACARD . ON.OFF 38. PLACARD - WARNING 77 DECAL - AVGAS ONLY 1000002' 39. PLACARD - OXYGEN GAUGE LIGHT 7 8 PLACARD . AUTOPILOT 79 PLACARD - COMPASS SYSTEM i Figurc I 1-1. Placards and Decals (cont) 1 1-20-00 Page 1 1 -02 Re\ ised: Augurt 9. 19X4 CHAPTER SERVICING PIPER AIRCRAFT PA-32-301 /301T MAINTENANCE MANUAL • CHAPTER I2 - SERVICING TABLE OF COh'TEh'TS/EFFECTIVITY CHAPTER SECTIOS SLBJECT SUBJECT GRID NO. EFFECTI\'ITY REPLENISHING Fuel System Filling Fuel Tanks Draining Moisture From Fuel System Draining Fuel System Oil S!,stem Sen icing Oil System Draining Oil Sump Filling Oil Sump Oil Screen (Suction) Recommendations for Changing Oil Oil Filter (Full Flou) SCHEDULED SERVlClSG Sen icing Fuel System Sen icing Landing Gear Set\ icing Oleo Struts Filling Sose Gear Oleo Strut Filling Main Gear Oleo Strut Inflating Oleo Struts Brake System Sen lclng Brake System Filling Brake Cylinder Resenoir Draining Brake System Tires Senicing Tires Tire Balance Poner Plant Senicing Poner Plant Eng~neAir Filter S e n icing Propeller Electrical System Senicing Electrical System Battery Servicing Battery Box Corrosion Prevention Lubrication Instructions Application of Oil Application of Grease Lubrication Chart Winterization Plate 12 - Cont./Effec. Page - 1 Revised: August 11. 1983 PIPER AIRCRAFT PA-32-301 1301T 'MAINTENANCE MANUAL GENERAL. This chapter contains routine handling and servicing procedures that are most frequently encountered. Frequent reference to this chapter will aid the individual by providing information such as the location of various components. ground handling procedures. routing service procedures and lubrication. When any system or component requires service other than the routine procedures as outlined in this section. refer to the appropriate section for that codponent. REPLENISHING. FUEL SYSTEM. FILLING FUEL TANKS. The fuel tanks of each wing are filled through filler necks located on the forward slope of the wings. Each wing tank holds a capacity of 53.5 U.S. gallons. Obsente all required safety precautions for handling gasoline. Fill the tanks with fuel as specified on the placard adjacent to the filler neck. DRAINING MOISTURE FROM FUEL SYSTEM. The fuel system should be drained daily prior to first flight and after refueling to avoid the accumulation of water sediment. Each fuel tank is equipped with an individual quick drain located at the lower inboard rear corner of the tank. The fuel selector valve is provided with a quick drain valve (refer to Figure 12- I ) and is located aft of the spar box. Drain fuel tanks and fuel selector valve per the following: I . Drain each tank through its individual quick drain located at the lower inboard rear corner of the tank. making sure that enough fuel has been drained to insure that all water and sediment is removed. To minimize the possibility of &unagihg the jhrsh type fuel tank dram, use only the fuel sampler specified in Piper Parts Catalog (Fud Tank Assemblies). 2. Place a container under the fuel selector valve drain. Drain the fuel selector valve by pushing down on the quick drain handle located on the forward face of the spar box. 3. Examine the contents of the container placed under the fuel strainer drain for water and sediment and dispose of the contents. - CAUTION - When draining m y amount of fuel, care should be taken to insure that no fire hazard exists k j o r e darting m g k . After each use of the quick drain w o k , check thefuel selector valve dram to ensure that the quick drain valve has properly seated and that there is no loss of fuel from the drain. 12-11-02 Page 12-01 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301/301T +MAINTENANCE M A N U A L 1 . FILTER 2. SPRING 3. RETAINER WASHER 4. BOWL \-/' NYLON FILTER ASSEMBLY Figure 12- 1 . Fuel Filter Bowl and Screen 1 D R A I N I N G FVEL SYSTEM. Fuel ma!. be drained from the system by opening the valve at the inboard end of each fuel tank. The t l u 3 h type drain \she requires the drain cup pin t o hold the v a l ~ eopen. T h e remaining fuel in the s!stem ma! be drained through the filter bowl. Any individual tank may be drained by closing the selector \ al\ e and then draining as desired. 12-1 1-03 Page 12-02 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301 /301T *MAINTENANCE MANUAL SERVICING OIL SYSTEM. I The engine oil level should be checked before each flight and changed after each 50 hours of engine operation. During oil change. the oilscreen(s)should be removed and cleaned. and when installed. the oil filter cartridge replaced. Inter\.als between oil changes can be increased as much as 1005 on engines equipped u ith full flow (cartridge t!.pe) oil filters provided the element is replaced each 50 hours of operation. Should fuel other than the specified octane rating for the power plant be used. refer to latest re\.ision Lycoming S e n ice Letter S o . L 185 for additional information and recommended service procedures. The engine manuf;lcturer does not recommend oils by brand names. Use a quality brand Aviation Grade Oil of the proper season viscosity. F o r information on the use of detergent oil. refer to Recommendations for Changing Oil and or the latest re\-ision of Lycoming Service Instruction No. 1014. D o not introduce any trade additive to the basic lubricant unliss recommended by the engine manujacturer. To drain the oil sump. provide a suitable container with a minimum capacity of that required to f i l l the sump. Remo\.e the engine cowl and open the oil drain valve located on the underside of the engine b! pushins the arms of the drain up and turning counterclockwise. This will hold the drain in the open pos~tion.I t is recommended the engine be warmed to operating temperature to insure complete draining of the old oil. 1FILLING OIL SLMP. I The oil sump should normally be filled with oil to the mark on the engine dipstick. The quantit! of oil required for the engine may be found in Chapter 6. The specified grade of oil may be found in Chart 1202. the Lubrication Chart. or on the right cowl panel or each engine oil filler access door. To senice the engine 11 irh oil. open the quick release access door on top of the cowl and remove the oil filler cap with dipstick. OIL SCREEN (SVCTION). The oil suction screen. located on the bottom aft end of the engine sump is installed horizon tall^. T o remo\e. cut the safety wire and remove the hex head plug. The screen should be cleaned at each oil change to remove any accumulation of sludge and t o examine for metal filings or chips. I f 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 t o 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-C4 1 safety u ire. 12- 12-04 Page 12-03 Revised: August 11. 1983 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL RECOMMESDATIONS FOR CHANGING OIL. (Refer to the latest re\ision of Lycoming S e r \ ~ c e Instruction S o . 1014 and Lycoming S e n i c e Letter No. L185.) I . In engines that have been operating on straight mineral oil for several hundred hours. a change to additive oil should be made with a degree of caution. since thecleaningaction of some additive oils will tend to loosen sludge deposits and cause plugged oil passages. When an engine has been operating on straight mineral oil and is known, to be in excessively dirty condition. the switch t o additive or compounded oil should be deferred until after the engine is overhauled. 2. When changing from straight mineral oil to compounded oil. the following precautionary steps should be taken: A. D o not add additive oil to straight mineral oil. Drain the straight mineral oil from the engine and fill with additive oil. B. D o not operate the engine longer than five hours before the first oil change. C. Check all oil screens for evidence of sludge o r plugging and change oil ever); ten hours i f sludge conditions are evident. Resume normal oil drain periods after sludge conditions improve. OIL FILTER (FULL FLOW). I . The oil filter should be replaced after each 50 hours of engine operation: this is accomplished b! removing the lockwire from the bolthead at the end of the filter housing. loosening the bolt. and r e m o ~Ing the filter assembly from the adapter. 2 . Before discarding the throwaway filter. remove the element for inspection by using a Champion cutter tool. CT-470. available from Champion Spark Plug Co.. Toledo. Ohio 43601. I t hill cut open a n \ spin on t!,pe oil filter for inspection. Examine the material trapped in the filter for evidence of internal englne damage. such as chips or panicles from bearings. In new or newly overhauled engines. some small particles of metallic shavings might be found: these are generally of no consequence and should not be confused u ~ t h panicles produced by impacting. abrasion or pressure. Evidence of internal engine damage found in the oil filter justifies further examination t o determine the cause. 3. After the filter has been replaced. tighten the cartridge within 18 to 20 foot-pounds of torque. Lockwire the bolt through the loops on the side of the housing t o the drilled head of the thermostatic \ she. Be sure the lockwire is replaced at both the attaching bolthead and the thermostatic oil cooler bypass \ a h e. L'se MS-20995-C41 safety wire. 12-12-06 Page 12-04 Revised: August 11,1983 PIPER AIRCRAFT PA-32-301 /301T *MAINTENANCE MANUAL SCHEDULED SERVICING. SERVICING FUEL SYSTEM. 1 . At intervals of 50 hours or 90 days. whichever comes first. clean the fuel screen in the inlet side of the injector and the fuel selector valve screen. 2. T o flush the fuel tanks and selector valve. disconnect the fuel line at the injector. 3. Select a fuel tank. turn o n the electric fuel pump and flush fuel through the system until i t i s determined there is no d i n and foreign matter in the fuel valve or tank. During this operation. agitation of the fuel within the tank will help pick up and remove any din. 4. Repeat this procedure for each tank. 5 . When all tanks are flushed. clean all filters. The PA-32-301/301 T aucrajt are wproved for operation with an anti-icing addilive in thejuel. When an anti-icing additive is used it must meet the specgication MIL-I-27686, must be uniformly blended with the juel while rqfueling, must not exceed .IS% by volume of the refueled quantity, and to insure its effectiveness should be blended at not less than .1 0%by volume (oneand one-half liquid 02s. per ten gallon of fuel would be within the range). A blender supplied by the additive manufacturer should be used. Except for the information contained in this section, the manufacturer's mixing or blending instructions should be carefully followed. -- CAUTION - Assure that the additive is dbected into flowing fuel stream. The additiveflow should start after andstop before thefueljlow. Do not permit the concentrated additive to mme in contact with the aircraft painted surfaces or the interior suqfaces of the juel tanks. Some fuels have anti-icing additives pre-blended in the fuel at the refinery, so no further blending should be performed. Fuel additive cannot be used as a substitutefor a prejlight draining of the juel system drains. Page 12-05 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301 /301T *MAINTENANCE MANUAL SERVICING L A S D I S C GEAR. The landing gear consists of tires. brakes. oleo strut assemblies and. on some models. u heel fairings. 'These should be inspected for scored piston tubes. possible hydraulic fluid leakage. security and condition of all connection points. and the fairings for cracks. Check the brake linings for wear and frayed edges and brake discs for scoring. Replace if found necessap. Minor senicing is described in the following paragraphs. For detailed serLices and o ~ e r h a u linstructions. refer to Chapter 32. 1. FILLER. MAlN FUEL TANK, RIGHT 2. DRAIN. MAIN FUEL TANK. RIGHT 3. FILTER. FUEL PUMP. ELECTRIC 4 . CARTRIDGE FILTER, ENGINE OIL 5. FILLER/INDICATOR, OIL, ENGINE 6. PROPELLER 7. LINK ASSEMBLY. NOSE 8. TIRE. NOSE 9. FILLER. OLEO SHOCK STRUT. NOSE 10. SCREEN. OIL SUCTION. ENGINE 11. BATTERY (PA-32-301) 12. RESERVOIR. BRAKE SYSTEM 13. DRAIN. FUEL 14. DRAIN. MAlN FUEL TANK. LEFT 15. FILLER. OLEO SHOCK STRUT, MAlN 16. TIRE. MAlN 17. FILLER. MAlN FUEL TANK. LEFT 18. FILTER, VACUUM REGULATOR AND CENTRAL AIR 19. BAlTERY (PA-32-3011) Figure 11-2. Senicing Points 12-22-00 Page 12-06 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301 /301T *MAINTENANCE MANUAL SERVICING OLEO STRCTS. Air-oil struts are incorporated in each landing gear oleo to absorb the shock resulting from the impact of the wheels on the runway during landing. T o obtain proper oleo action. the nose gear oleo strut must h a \ e approximately 3.25 t .25 inches of piston tube exposed. while the main pear struts require approximately 4.5 2 .5O inches of tube exposure. - CAUTION - D o not exceed these t u k exposures. These measurements are taken with theairplane setting on a level surface under normal static load (empty weight of airplane plus full fuel and oil). If the strut has less tube exposed than that prescribed. determine whether it needs air or oil by raising theairplane o n jacks. With thestrut extended. remove the cap from the air valve at the top of the housing and depress the valve core to allow air t o escape from the strut piston until it is fully compressed. Allow the foam from the air-oil mixture to settle and then determine if oil is visible up to the bottom of the filler plug hole. If oil is visible at the bottom of the hole. then all that is required is the \.al\e be checked for unsatisfactory conditions and air added as described in Inflating Oleo Struts. Should fluid be at any level below the bottom of the filler plug hole. the oleo should be checked for leaks. etc.. and oil added as described in Filling Nose Gear Oleo Strut for the nose gear or Filling Main Gear Oleo Strut for the main gear. For repair procedures of the landing gear a n d / o r oleo struts. refer to Chapter 32. - WARNING - Do not release air by removing the strut vabe core or filler plug. Depress the vahe core pin until strut chamber pressure has diminished. - C A UTION - Dirt andloreign particles/orm around thefiller plugs of the landing gear struts, therefore, before attempting to remove theseplugs, the tops of the struts should be cleaned with compressed 4C and/or with a dry solvent. FILLING NOSE GEAR OLEO STRUT. . T o f i l l 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: I . Raise the airplane on jacks until the nose wheel is completely clear of the ground. (Refer to Chapter 7.) 2. Place a pan under the p a r t o catch spillage. 3. I f not previously accomplished. remove the engine cowl and relieve air from the strut housing chamber by removing the cap from the air valve and depressing the valve core. Page 12-07 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL 4. There are two methods by which the strut chamber may be filled and these are as follows: Method 1. A. Remove the valve core from the filler plug at the top of the strut housing. Allow the plug to remain installed. B. Attach one end of a clear plastic hose to the valve stem of the filler plug and submerge the other end in a container of hydraulic fluid. Ascertain that the end of the hose on the valve stem is tight and the f l u ~ d container is approximately equal in height t o the top of the strut housing. C. Fully compress and extend the strut thusdrawing fluid from the fluid container and expelling air from the strut chamber. By watching the fluid pass through the plastic hose. it can be determined when the strut is full and no air is present in the chamber. D. When air bubbles cease to flow through the hose. compress the strut fully and remove the hose from the valve stem. E. With strut compressed. remove the filler plug to determine that the fluid level is visible up to the bottom of the filler plug hole. F. Reinstall the core in the filler plug and apply thread lubricated (Parker #6PB) to the threads of the filler plug and install the plug in the top of the strut housing. Torque the plug to 45 foot-pounds. Method 11. A. Remove the filler plug from the top of the strut housing. B. Raise the strut piston until it is fully compressed. C. Pour fluid from a clean container through the filler opening until it reaches the bottom of the filler plug hole. D. Install the filler plug finger tight. and extend and compress the strut two or three times to mobe any air that may be trapped in the housing. E. Remove the filler plug. raise the strut to full compression and fill with fluid if needed. F. Apply thread lubricant (Parker #6PB) to the threads of the filler plug. Reinstall the filler plug and torque to 45-foot pounds. 5. With the airplane raised. compress 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. 6. Clean off overflow of fluid. and inflate the strut as described in Inflating Oleo Struts. 7. Check that fluid is not leaking from around the strut piston at the bottom of the housing. FILLING MAIN GEAR OLEO STRUT. A main gear oleo strut that is partly full or one that has been completely emptied may be filled with MIL- H-5606fluid as follows: I . Raise the airplane on jacks until the landing gear torque link assembly has almost reached its full travel. (Refer to Chapter 7.) 2. Place a pan under the gear t o catch spillage. 3. I f not previously accomplished. remove a cap on top of the wing to gain access to the top of the strut housing. and relieve air from the strut housing chamber by removing the cap from the air valve and depressing the valve core. 12-22-03 Page 12-08 Revised: August 11. 1983 PIPER AIRCRAFT PA-32-301 1301T *MAINTENANCE MANUAL 4. Remove any one of the three torque link bolts. and again raise the airplane until a minimum of ten inches ( d o not exceed twelve inches of tube exposure) of strut tube is exposed with the wheel remaining on the ground. With this amount of tube exposed. fluid will flow from the middlechamber to the bottom chamber of the strut housing. insuring that the bottom chamber is filled with fluid. -- NOTE - With the torque links disconnected, the piston tube is free to slidc from the strut housing. 5. Fill the main gear housing by one of two methods which are as follows: Method I. A. Remove the valve core from the filler plug at the top of the strut housing. Allow the plug to remain installed. B. Attach one end of a clear plastic hose t o the valve stem of the filler plug and submerge the other end in a container of hydraulic fluid. C. Fully compress and extend (10 + 2-0 inches of strut tube exposed) the strut thus drawing fluid from the strut chambers. By watching the fluid pass through the plastic hose. it can be determined u hen the strut is full and no air is present in the chambers. The strut must be extended to full ten inches to allou fluid to enter the bottom chamber of strut housing. D. When air bubbles cease t o flow through the hose. compress the strut fully and remo\e the hose from the valve stem. E. With the strut fully compressed. remove the filler plug to determine that the fluid \e\ells \ lsible up to the bottom of the filler plug hole. F. Reinstall the core in the filler plug and apply thread lubricant (Parker #6PB) to the threads of the filler plug and install the plug in the top of the strut housing. Torque the plug to 45 foot-pounds. Method 11. A. Remove the filler plug from the top of the strut housing. B. Raise the strut t o full compression. C. Pour fluid from a clean container through the filler opening until it is visible at the top of the strut chamber. I f the housing has been completely emptied or nearly so. allow sufficient time for the fluid to drain through the orifice from the upper chamber into the middle chamber. D. Lower the gear until the wheel touches the ground ( 10 + 2-0 inches of strut exposure) and then fully compress and extend the strut three o r four times to removeany air that may be trapped and to allou fluid t o enter the bottom chamber of the housing. E. Raise the strut t o full compression and if needed. fill with fluid t o the bottom of the filler plug. F. Apply thread lubricant (Parker #6PB) to the threads of the filler plug. Reinstall the filler plug and torque to 45 foot-pounds. 6. Replace the torque link bolt. Tighten bolt only tight enough t o allow no side play in the connection. 7. 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. 8. Clean off overflow of fluid and inflate the strut a s described in Inflating Oleo Struts. 9. Check that fluid is not leaking around the strut piston at the bottom of the housing. 12-22-03 Page 12-09 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301 1301T MAINTENANCE MANUAL Figure 12-3. Main Gear Oleo Struts (Cut-Away View) 12-22-03 Page 12-10 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-301/301T *MAINTENANCE MANUAL INFLATING OLEO STRUTS. After making certain that the oleo strut has sufficient fluid. attach a strut pump to the air valve and inflate the oleo strut. The strut should be inflated until the correct inches of piston is exposed with normal static load (empty weight of airplane plus full fuel and oil) on the gears. (Refer to Servicing Oleo Struts.) Rock the airplane several times to ascertain that the gear settles back to the correct strut position. (Ifa 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 from the valve to bring thestrut down to the proper extension.) Before capping the valve. check for valve core leakage. BRAKE SYSTEM. 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 Filling Brake Cylinder Reservoir. When found necessary to accomplish repairs to any of the brake system components, or to bleed the system. these instructions may be found in Chapter 32. FILLING BRAKE CYLINDER RESERVOIR. aThe brake cylinder reservoir should be filled to the level marked on reservoir. with MIL-H-5606 fluid. The reservoir. located on the left side of the firewall in the engine 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 Chapter 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 clean the brake system. flush with denatured alcohol. TIRES. SERVICING TIRES. The tires should be maintained at the pressure specified in Chapter 6. When checking tire pressure. examine the tires for wear. cuts. bruises and slippage on the wheel. The tire, tube, and wheel should be properly balanced when installed with the index mark on the tire aligned with the index mark on the tube. 12-24-01 Page 12-11 Revised: August 11, 1983 PIPER AIRCRAFT PA-32-3C1/301T MAINTENANCE MANUAL TIRE BALANCE. Proper balancing is critical for the life of aircraft tires. If a new tire is balanced upon installation it will usually remain balanced for the life of the tire without having any shimmy or flat spots. and an inexpensne balancer can be made that will balance almost any tire for light aircraft. Refer to Chapter 91 for balancer details. Balance the tire as follows: I. Mount the tire and tube (if one is used) on the wheel. but d o not install the securing bolts. Install the wheel bearings in the wheel: then. using the bushings, spacers. and nuts. install the wheel-tire assembly on the pipe. Secure the nuts finger-tight so that the wheel halves touch each other. Be sure the bolt holes are aligned. Insert the axle through the pipe and place the wheel in the center of the balancer. Make sure the axle is only on the chamfered edges of the balancer and that it is at 90° to the sides of the balancer. 2.