LANCE II SERVICE MANUAL

Skin Material and Thick'ness . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Surface Scratches. Abrasions or Ground-in-Dirt . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Deep Scratches. Shallow Nicks and Small Holes ............................... Mixing of Epoxy Patching Compound . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Welding Repair Method . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Repairing of Cracks Various Repairs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Repair of Stress Lines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Repair of Impacted Damage ................................................ Control Surface Balance Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aileron Balancing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Balancing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stabilator Balancing ....................................................... Control Column Assembly .................................................. Correct Method of Installing Rod End Bearings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aileron Controls (Typical) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bellcrank Rigging Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aileron Rigging Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stabilator Controls ........................................................ Stabilator Rigging Tool .................................................... Stabilator Travel Adjustments ............................................... Revised: 10/3/80 LIST O F ILLUSTRATIOXS (cont.) Figure Aerofiche Grid No . Methods of Securing Trim Cables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Stabilator Trim Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wrapping Stabilator Trim Barrel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder and Steering Pedal Assembly (Typical) ................................ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Controls Rudder Rigging Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Travel Adjustments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Trim Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flap Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flap Step Adjustment ...................................................... Flap RiggingTool ......................................................... Fabricated Aileron Bellcrank Rigging Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fabricated Aileron and Flap Rigging Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fabricated Stabilator Rigging Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fabricated Rudder Rigging Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Schematic Diagram of Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic System Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic Pump, Reservoir. Exploded View . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Test and Adjustment of Hydraulic Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Checking Aligning Brackets of Gear Back-up Extender Actuator . . . . . . . . . . . . . . . . Gear Back-up Extender Actuator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear Actuating Cylinder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . End Gland Locking Device (Main Gear) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Main Gear Actuating Cylinder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Gear Back-up Extender Actuator Aligning Tool . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear Oleo Strut Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear Service Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Adjustment of Eccentric Bushing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear Adjustment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Clamping Rudder Pedals in Neutral Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rudder Pedals at Neutral Angle ............................................. Nose Gear Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Main Gear Oleo Strut Assembly ............................................. Main Gear Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Main Gear Service Tolerances ................................................. Aligning Main Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Adjustment of Nose Gear Limit Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Adjustment of Main Gear Down Limit Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Throttle Warning Switches .................................................. Nose Wheel Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Main Wheel Assembly ..................................................... Removal of Anchor Bolt ................................................... Installation of Anchor Bolt ................................................. Revised: 9 / 2 / 7 8 Figure LIST OF ILLUSTRATIONS (cont.) Aerofiche Grid No . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wheel Brake Assembly IL5 . . . . . . . . . . . . . . . . . . . . . . . . . Brake System Installation 1L7 . . . . . . . . . . . . . Brake Master Cylinder (Handparking Brake) I L 8 . . . . . . . . . . . . . . . . . . . . . . . . . . Toe Brake Installation l L l O . . . . . . . . . . . . . . . . . . . Brake Cylinder ( 1700) (Toe Brake) l L l l . . . . . . . . . . . . . . . . . . . Brake Cylinder ( 10-27) (Toe Brake) l L l l . . . . . . . . . . . . . . . . . . . . Brake Cylinder (10-30) (Toe Brake) I L 1 3 Deleted . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Propeller Installation 2 A l l . . . . . . . . . . . . . . . . . . . . . . . Propeller Blade Minor Repair 2A12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Propeller Governor 2A15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Installation 2A18 . . . . . . . . . . . . . . . . . . . . . . Adjustment of Engine Controls 2A20 . . . . . . . . . . . Schematic Diagram of RSA Fuel Injection System 2A22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Injector 2A23 . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel- Air Bleed Nozzle 2B1 Height of Spring in Distributor Block Tower . . . . . . . . . . . . . . 2B2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Contact Points 2B3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Timing Marks 2B3 . . . . . . . . . . . . . . . . . . . Timing Light Connected to Magneto 2B5 . . . . . . . . . . . . . . . . . . . . . Timing Marks on Magneto Rotor 2B6 . . . . . . . . . . . . . . . Painted Tooth Centered in Timing Window 2B7 Timing Mark on Rotor Aligned With Pointer . . . . . . . . . . . . . . 2B7 . . . . . . . . . . . Timing Light Connected to Magneto and Breakers 2B8 . . . . . . . . . . . . . . . . . . . . . . . . . Cam End View of Magneto 2B10 . . . . . . . . . . . . . . . . . . . . . . . . Removing Impulse Coupling 2 B l l . . . . . . . . . . . . . . . . Checking Flyweight t o Stop Pin Clearance 2B11 . . . . . . . . . . . . . . . . . . . . . . Stop Pin Installation Dimension 2B12 Checking Flyweight Axial Wear with Drill Shank . . . . . . . . . . . . 2B13 Checking Flyweight Radial Wear with Gauge . . . . . . . . . . . . . . . 2B13 . . . . . . . . . . . . . . . . . . . . . . . Points of Coupling Body Wear 2B14 . . . . . . . . . . . . . . . Acceptable and Deformed Coupling Springs 2B14 Checking Impulse Coupling for Magnetization . . . . . . . . . . . . . . 3-B15 . . . . . . . . . . . . . . . . . Orientation of Spring in Coupling Body 2B15 . . . . . . . . . . . . . . . . . . . . . . . . Lifting Inner End of Spring 2B16 . . . . . . . . . . . . . . . . . . . . Checking Harness Lead Continuity 2B17 Checking Harness Lead Insulation Resistance . . . . . . . . . . . . . . 2B17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Modified Pliers 2B18 . . . . . . . . . . . . . . . . . Removing Spring From Lead Assembly 2B18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Assembly Tool 2B19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Using Assembly Tool 2B19 . . . . . . . . . . . . . . . . . . . . . . Ferrule Positioned Under Braid 2B19 Revised 6/ 15/79 Figure LIST O F ILLUSTRATIONS (cont.) Aerofiche Grid 50. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ferrule Seating Tool Position of 11-8627 Kit and Contact Spring at S t a n of Installation . . . . . . . . . . . . . . Position of 11-8627 Kit and Contact Spring after Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lubricating Sleeve . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lubricating Ferrule Shoulder ..................................... Removing Spark Plug Frozen t o Bushing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Propeller Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Propeller Blade Minor Repair . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Propeller Governor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Mount Installation ; . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Turbocharger Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Adjustment of Engine Controls Schema~icDiagram of RSA-Fuel Injection System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Injector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel-Air Bleed Sozzle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel System (PA-32RT-300) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Svstem r PA-32RT-300T) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Cell Installat~on Fuel Gauge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Filter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Instrument Panel (Typical) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Instrument Air System Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Lamp-Bank Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Checking Field Current . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Testing Field Circuit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Testing Rectifiers (Positive) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Testing Rectifiers (Negative) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C-3929 Fixtures and Adapters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Removing Rectifiers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installing Rectifiers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Soldering Rectifier Lead Testing Stator Coils . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Removing End Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installing End Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Removing Drive Pulley Removing Drive End Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Removing Slip Ring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installing Slip Ring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Solder Points . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installing Retainer Installing Driver End Shield and Bearing (Typical) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installing Pulley . . . . . . . . . . . . . . . . . . . . . . . . . . . Meter Connections for Alternator Performance Test ~ Revised: 11/ 1/83 LIST O F ILLUSTRATIONS (cont) Figure Aerofiche Grid No . Exploded View of Alternator ................................................ Removal of Slip Ring End Bearing .......................................... Removal of Rectifier ....................................................... Removal of Drive End Head ................................................ Removal of End Head Bearing .............................................. Testing Rotor for Ground .................................................. Testing Rotor for Shorts ................................................... Installation of Bearing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installation of Rectifier . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Terminal Assembly ........................................................ Slip Ring End Bearing Assembly ............................................ Testing Alternator ......................................................... Brush Installation .......................................................... Internal Wiring Schematic .................. ; . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . No-load Test ............................................................. Resistance Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Exploded View of Gear Reduction Starting Motor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Turning Starting Motor Commutator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Testing Motor Armature for Shorts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Testing Motor Fields for Grounds ........................................... No-Load Test Hook-up .................................................... Stall-Torque Hook-up . ! .................................................... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ignition S w ~ t c h Teqninal Block . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ELT Portable Folding Antenna (NARCO) .................................... ELT Using Fixed Aircraft Antenna (NARCO) ................................. NOTE: (Electrical Schematics Figures 11-44 to 11.63 . see Table XI-I.) ELT Schematics ........................................................... Cabin Heater . Defroster and Fresh Air System (PA-32RT-300) . . . . . . . . . . . . . . . . . . Cabin Heater . Defroster and Fresh Air System (PA.32RT.3001) ................. Air Conditioning System Installation (Typical) ................................ ............................................................. Service Valves Test Gauge and Manifold Set ............................................... Manifold Set Operation .................................................... Leak Test Hookup ......................................................... Evacuation 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 .......................................... Oxygen Installation ......................................................... l A 9 INTENTIONALLY LEFT BLANK Table LIST OF TABLES Ae rofiche Grid S o . 11.1 . 11.11 . II.Ila . 1I.IIb . 11.11~. II.IId . II.IIe . 11.111 . 111.1 . IV.1 . IV.11 . v.1 . v.11 . v-I I1. VI.1 . VI.11 . VI.111 . VI1.I . v11.11 . VII.111 . VII.IV . VIII.1 . VIII.11 . VlII.II1 . VIIIA.1 . VIIIA.11 . IX.1 . IX.11 . X.1 . X.11 . X.111 . X.IV . X.V . X.VI . X.VII . X.VIII . ' X.IX . X.X . X.XI . X.XII . X.XII1 . X.XIV . X.XV . X.XVI . X-XVII Leading Particulars and Principal Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .................................................. Recommended Torques Conversion Tables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Decimal, Millimeter Equivalents of Drill Sizes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum Distance Between Supports for Fluid Tubing . . . . . . . . . . . . . . . . . . . . . . Thread Lubricants ....................................................... Hose Clamp Tightening (Initial Installation) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Recommended Lubrication Oils . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inspection Report . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . List of Materials (Thermoplastic Repairs) ................................... Balance Specifications .................................................... Control Surface Travel and Cable Tension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cable Tension vs . Ambient Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Troubleshooting Chart (Surface Controls) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Leading Particulars . Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Characteristics. Hydraulic Pump Motor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic System Troubleshooting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Nose Gear Service Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Main Gear Service Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Toe-In - Toe-Out Correction Chart ........................................ Troubleshooting Chart (Landing Gear) ..................................... Propeller Specifications .................................................. Coupling Torques ....................................................... Engine Troubleshooting Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Propeller Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Troubleshooting Chart (Turbocharger) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sender! Fuel Quantity Gauge Tolerances . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Troubleshooting Chart (Fuel System) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Vacuum System ........................................................ Directional Gyro Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Gyro Horizon Indicator .................................................. Rate of Climb Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Altimeter ............................................................... Airspeed Tubes and Indicator ............................................. Magnetic Compass ...................................................... Manifold Pressure Indicator .............................................. Tachometer ............................................................. Engine Oil Pressure Gauge ............................................... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Pressure Gauge (PA-32RT-300) Turn and Bank Indicator ................................................. Fuel Quantity Indicators ................................................. Oil Temperature Indicators ............................................... Exhaust Gas Temperature Gauge (Alcor) ................................... Cylinder Head Temperature Gauge ........................................ ........................................................ Fuel Flow Gauge 1A22 1B3 1B9 1B15 1b16 1B17 1b17 1C15 1D12 1 EZO 1F7 1f13 1f15 1H6 1H24 1H24 1114 1516 1K7 1k14 Revised: 10/3/80 Table LIST OF TABLES (cont.1 Aerofiche Grid No . Index .Electrical System Schematics . . . . . . . . . . . . . . . . . . . Electrical System Component Loads . . . . . . . . . . . . . . . . . . . Electrical System Troubleshooting . . . . . . . . . . . . . . . . . . . . Electrical Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electrical Wire Coding . . . . . . . . . . . . . . . . . . . . . . . . . . . Temperature Pressure Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aluminum Tubing Torque Compressor Oil Charge . . . . . . . . . . . . . . . . . . . . . . . . . . . Troubleshooting Chart (Air Conditioner) . . . . . . . . . . . . . . . . Oxygen System Component Limits . . . . . . . . . . . . . . . . . . . Troubleshooting Chart (Oxygen System) . . . . . . . . . . . . . . . . Revised 6/ 15/79 SECTION I INTRODUCTION Paragraph Aero fiche Grid No . General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Scope of Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LandingGe ar . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Brake System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FlightContro ls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Cabin Heater, Defroster, and Fresh air System . . . . . . . . . . . . . . . . . Radio . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Instrument and Autopilot System . . . . . . . . . . . . . . . . . . . . . . . . Issued: 1/3/78 LANCE I1 SERVICE MANUAL SECTION I INTRODUCTION 1-1. GENERAL. This manual contains service and maintenance instructions for the Piper PA-32 RT-300 and PA-32 RT-300T Lance 11. designed and manufactured as a versatile airplane in the personal and business aviation field, by the Piper Aircraft Corporation, Vero Beach, Florida. 1-2. SCOPE OF MANUAL. Section I1 comprise the routine service part of this manual, Section 111 covers inspections, and Sections N through XlV comprise maintenance instructions. The routine service instructions include ground handling and routine servicing. The inspection section includes 50, 100, 500, and 1 0 0 hour inspections which the manufacture requires for this airplane. The maintenance instructions for the various systems of the airplane include system discription, troubleshooting, removal and installation of components, and corrective maintenance and testing as required. Each major system of the airplane is covered in a separate section. Only qualified personnel should perform the operations described in this manual. The description of the airplane included in this section is limited to general information. For more detailed description of the various systems refer to the appropriate section of t h s manual. For detailed operating instructions refer to the Pilot's Information Manual for the airplane. Section I1 of this manual also gives leading particulars and principal demensions, along with lubrication charts and other related routine service information. 1-3. DESCRIPTION. The Lance I1 PA-32RT-300 and PA-32RT-300T are singleengme, low-wing monoplanes of all metal construction, with seats available for six passengers (seventh seat optional). Paragraphs 1-4 through 1-16 provide descriptions of major components and systems. 1-4. WING. The lammar flow wing is of all metal stressed skin, full cantilever, low-wing design, consisting of two wing panels bolted to a spar box assembly in the fuselage. The wing tips are removalbe. The ailerons are statically balanced and cable and push rod controlled. The trailing edge wing flaps are manually operated. 1-5. EMPENNAGE. The empennage consists of the fin, rudder, stabilator and stabilator trim tabs. The stabilator is mounted above the fin and rudder in a "T" tail configuration. The rudder and stabilator are statically balanced. 1-6. FUSELAGE. The fuselage consists of three basic units: The engine section, the cabin section, and the tail cone section. 1-7. LANDING GEAR. The tricycle landing gear is hydraulically operated, fully retractable units consisting of shock absorbing air-oil oleo struts. b e d : 1/3/78 INTRODUCTION LANCE I1 SERVICE MANUAL 1-8. HYDRAULIC SYSTEM. The hydraulic system incorporates an electrically driven pump which is controlled by a selector lever on the instrument panel which in turn operates the retraction and extension of the landing gear. 1-9. BRAKE SYSTEM. The brake system is operated hydraulically and controlled by a hand lever connected to a single brake cylinder that operates both wheel brakes, plus individually operated toe brakes. 1-10. ENGINE. Engine models, rated horsepower and other related information may be found in Table 11-1 of Section 11. 1-1 1. PROPELLER. A constant speed propeller is installed and controlled by an engine mounted governor which is controlled by a lever on the power quadrant in the cockpit. Propeller specifications may be found in Table 11-1 of Section I1 and Table VIII A-I of Section VTII and VTIIA. 1-12. FUEL SYSTEM. The fuel system consists of two interconnected aluminum tanks in the leading edge of the wings, a strainer bowl with fuel screen, fuel selector valve, and electrical auxiliary fuel pump and an engine driven fuel pump. 1-13. FLIGHT CONTROLS. The flight controls are conventional equipment, consisting of a control wheel which operates the ailerons and stabilator and pedals which operate the rudder. Duplicate controls are provided for the copilot. 1-14. CABIN HEATER, DEFROSTER, AND FRESH AIR SYSTEM. Heated air for the cabin and defroster is obtained from the exhaust system shroud. Fresh air is picked up from an inlet in the leading edge of each wing and from an inlet in the leading edge of fin. The air is routed through the wings to individually controlled outlets located just forward and aft of the front seats. The fresh air from the fin is routed to overhead vents. 1-1 5. RADIO. Provisions are provided for the installations of various radio equipment along with microphone a n d headset jacks, loudspeaker and other radio navagationequipmen t. 1-16. INSTRUMENT AND AUTOPILOT SYSTEM. Provisions for instrument installation include panels for engine instruments and advanced flight instruments as well as for an Autopilot System. Issued: ,113178 SECTION I1 HANDLING A N D SERVICING Paragraph Introduction .............................................................. Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Station Reference Lines Weight and Balance Data ................................................... ....................................................... Serial Number Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Access and Inspection Provision . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Tools and Test Equipment ...................................................... Torque Requirements Torque Wrenches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Identification of Fluid Lines installation of Flexible Hose Assemblies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Support Clamps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Removal of Cherrylock Rivets Step . Handhold. and Walkways . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ground Handling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 . General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2- 12. Jacking 2.13 . Weighing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14 . Leveling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15 . Mooring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2- 16. Locking Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17 . Parking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18 . Towing 2-19 . Taxiing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . External Power Receptacle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21 . Operation of External Power Receptacle Servicing . . . . . . . . . . . . : . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23 . General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-25 . Servicing Fuel System 2-26 . Filling Fuel Tanks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-27 . Draining Moisture from Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-27a . Anti-lcing Fuel Additive 2-28 . Draining Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Brake System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-30 . Servicing Brake System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . - 3 I Filling Brake Cylinder Reservoir . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-32 . Draining Brake System Tires . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ................................................... 2-32b . Servicing Tires 2-32c . Tire Balance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-34 . Servicing Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-35 . Servicing Hydraulic Pump.. Reservoir . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Landing Gear System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-37 . Servicing Landing Gear Aerofiche Grid S o . ia17 ia17 1A17 1a17 \A17 1.417 IBI IBI 1 B 1 1B7 1B7 1B16 1b18 1b21 1 B? 1 1B2 I" 1b21 1B22 1B22 1B23 1B23 1B24 1B24 ICI 1C1 1C1 1C2 1C2 1C2 1c2 1C2 1C2 1C3 1C3 1c3 1C3 1C3 1C3 1C4 1C4 1C4 1C6 1C6 1C6 1C6 1C6 Revised: 10/3/80 Paragraph a Aerofiche Grid No . ............................................................... Oleo Struts 2.39 . Servicing Oleo Struts .............................................. . 2.40 Filling Oleo Struts ................................................ . 2.41 Inflating Oleo Struts .............................................. Tire ...................................................................... . 2.43 Servicing Tires ................................................... Induction Air Filter ........................................................ 2.45 . Servicing Induction Air Filter ...................................... ................................................................. Propeller 2.47 . Servicing Propeller ................................................ Battery .................................................................. 2-49 . Servicing Battery ................................................. Cleaning ................................................................. 2-5 1. Cleaning Engine Compartment ..................................... 2-52. Cleaning.Landing Gear .......... :................................. 2-53 . Cleaning Exterior Surfaces ......................................... 2-54 . Cleaning Windshield and Windows .................................. 2-55 . Cleaning Headliner, Side Panels and Seats ........................... 2-56 . Cleaning Carpets ................................................. Oil System (Engine) ........................................................ 2-58 . Servicing Oil System .............................................. 2-59 . Filling Oil Sump .................................................. 2-60 . Draining Oil Sump ................................................ 2-6 1. Oil Screen (Suction) ............................................... 2-62 . Oil Filter (Full Flow) .............................................. 2-63 . Recommendations for Changing Oil ................................. Lubrication ............................................................... 2-65 . Lubrication Instructions ........................................... 2-66 . Application of Oil ................................................ 2.67 . Application of Grease ............................................. 2-68 . Lubrication Charts ................................................ LANCE II SERVICE MANUAL SECTION I1 HANDLING AND SERVICING 2-1. INTRODUCTION. This section contains routine handling and servicing procedures that are most frequently encountered. Frequent reference to this section will aid the individual by providing information such as the location of various components, ground handling procedures, routine service procedures and lubrication. When any system or component requires service other than the routine procedures as outlined in this section, refer to the appropriate section for that component. 2-2. DIMENSIONS. The principal airplane dimensions are shown in Figures 2-1 or 2-2 and are listed in Table 11-1. 2-3. STATION REFERENCE LINES. In order to facilitate the location of various components of the airplane which require maintenance and servicing, a method utilizing fuselage station, wing station or buttock line (BL), and water line (WL) designations is frequently employed in this manual. (Refer to Figure 2-3 or Figure 2-4.) 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 33.4 inches ahead of the firewall; station 0 (BL) of the wing and stabilator is the centerline of the airplane; and station 0 (WL) of the vertical stabilizer and rudder is 20.5 inches below the cabin floor as measured at the rear wing spar with the airplane level. 2 4 . WEIGHT AND BALANCE DATA When figuring various weight and balance computations, the empty, static and gross weight, and center of gravity of the axplane may be found in the Weight and Balance Section of Pilot's Operating Handbook. 2-5. SERIAL NUMBER PLATE. The serial number plate is located on the aft left side of the fuselage. The serial number should always be used when referring t o the airplane on service or warranty matters. HANDLING AND SERVICING LANCE I1 SERVICE MANUAL Figure 2-1. Three View of PA-32RT-300 Issued: 1/3/78 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL Figure 2-2. Three View of PA-32RT-300T HANDLING AND SERVICING LANCE I1 SERVICE MANUAL Figure 2-3. Station Reference Lines (PA-32RT-300) HANDLING AND SERVICING LANCE II SERVICE MANUAL Figure 2 4 . Station Reference Lines (PA-32RT-30011 Issued : 113/78 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL TABLE 11-1. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS a Oil Sump Capacity Fuel, Aviation Grade (Minimum and Specified Octane Fuel Injector, Bendix Magnetos, Scintilla: L Magneto timing Magneto Point Clearance Spark Plug Spark Plug Gap Setting Firing Order Starter: Prestolite 12 volt Alternator, Chrysler, 12 volt, 60 amp: Alternator, Prestolite, 12 volt, 60 amp: Voltage Regulator, WICO Manufacturer Model Rated Horsepower and Speed AvceLycoming Avco-Ly coming 10-540-K 1 G5D TIO-540-S I AD 300 hp @ 2700 rpm Take-off power (5 minutes max.) 300 hp at 2700 rpm at 36 in. hg. max. Continuous power 270 hp at 2575 rpm at 33 in. hg. 12 U.S. quarts 12 U.S. quarts 100/130 100/130 RSA- \OED I RSA- 1OEDI D6LN-203 1 (Dual D6LN-23 1 (Dual Mag with impulse Mag with coupling) impulse coupling) 20 degrees BTC 20 degress BTC 0.016 in. 0.016 in. Refer to Lycoming Service Instruction No. 1042. Refer to Lycoming Service Instruction No. 1042. 145-2-3-6 145-2-3-6 MX4206 MX4206 C Revised 6/1 5/79 HANDLING AND SERVICING 1A22 LANCE 11 SERVICE MANUAL • Issued: 1/3/78 TABLE 11-1. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont.) HANDLING AND SERVICING B h MODEL PA-32RT-300 PA-32RT-300T Overvoltage Relay, WICO XI6799 X 16799 Fuel Pump Drive LearSiegler RG 17980-K AC Pump Lycoming Part No. 75247 PROPELLER Manufacturer Hartzell Hartzell Hub Model See Table VIII-I See Table VIIIA-I Blade Model See Table VIII-I See Table VIIIA-I Diameter 80.0 in. 80.0 in. Diameter, Minimum 78.5 in. 78.5 in. Blade Angle, Low Pitch (at 3 0 in. Radius) 13.5" h 0.2" 15.6" f 0.2" Blade Angle, High Pitch (at 3 0 in. Radius) . 34.0" + 1.0" 34.0' f 1.0" Governor Control Hartzell Hartzell Governor Model F4-11B F 4 1 l B FUEL SYSTEM Fuel Tanks: 4 (2 interconnected 4 (2 interconnected each wing) each wing) Capacity 4 9 U.S. gallons (each set) 49 U.S. gallons (each set) Unusable Fuel 2 U.S. gallons (each set) 2 U.S. gailons (each set) Total Capacity 9 8 U.S. gallons 98 U.S. gallons Total Unusable Fuel 4 U.S. gallons 4 U.S. gallons Electric Fuel Pump Airborne 1B5-6 , LANCE II SERVICE MANUAL TABLE 11-1. LEADING PARTICULARS AND PRINCIPAL DIMENSIONS (cont.) LANDING GEAR TYpe Shock Strut Type Fluid Required (Struts and Brakes) Strut Extension (exposure under static load) Nose Main Wheel Base Nose Wheel Travel Turning Distance (Min.) Wheel, Nose Wheel, Main Brake Type Tire, Nose Tire, Main Tire Pressure, Nose Tire Pressure, Main Hydraulically Retractable Cornbination Air and Oil MiL-H-5606 2.60 + .25 in. 4.00 + .25 in. 7 ft. 10.1 2 in. 22.5" f 2" left & Right 75 ft., 6 in. Cleveland 40-77B or McCauley D-30500 Cleveland 40-90A Standard or Cleveland 40-120 Heavy duty Cleveland 30-65 Standard or Cleveland 30-83 Heavy duty 5:00 x 5 , 6 ply, Type III 6: 00 x 6, 8 ply, McCreary or 6:00 x 6, 8 ply, B.F. Goodrich (heavy duty) 35 psi 38 psi CONTROL SURFACE TRAVELS REFER TO TABLE V-I, SECTION V Revised: 9/2/78 HANDLING AND SERVICING- LANCE II SERVICE MANUAL 2-6. ACCESS AND INSPECTION PROVISIONS. The access and inspection provisions for the airplane are shown in Figure 2-5. The component to be serviced or inspected through each opening is identified in the illustration. All access plates and panels are secured by either metal fasteners or screws. To enter the aft section of the fuselage, open the baggage compartment door and remove the access panel. CAUTION Before entering the aft section of the fuselage, be sure the airplane is supported at the tail skid. 2-7. TOOLS A N D TEST EQUIPMENT. Because of the simplicity and easy accessibility of components, few special tools outside normal shop tools will be required. Tools that are required may be fabricated from dimensions given in the back of the section that pertains to a particular component or are listed in the back of the PA-32RT-300 AND PA-32RT-300T Pans Catalog. 2-8. TORQUE REQUIREMENTS. The torque values given in Table 11-11 are derived from oil-free cadmium-plated threads and are recommended for all airframe installation procedures where torquing is required. unless othenvise noted in sections where other values are stipulated. Engine torque values are found in the latest revision of Avco-Lycoming Service Bulletin No. 268. and propeller torque values are found in Section VlII or VIIIA of this manual. a. Unless otherwise specified. torque all nuts to the applicable torque in the Recommended Torque Chart. I f the nut (or the bolt) is listed but not its mating fastener. use the lower torque specified for the listed nut (or bolt). NOTE If normal operation requires movement between any of the components being clamped together, tighten the nut (or bolt) without regard to the nut torque chart, to insure intended operation of the assembly. b. Bolt and nut threads should be clean and dry unless otherwise specified. If the threads are to be lubricated and no torque is specified, reduce the recommended nut torque (plus the friction drag torque) by 50%. c. For thread sizes 10 through 7 / 16, add the friction drag torque for all self-locking fasteners as specified in the friction drag torque table. For non self-locking fasteners, assume the friction drag torque to be zero. d. For other bolt sizes, determine the friction drag torque by turning the nut to near contact with the bearing surface. Attach a scale type torque wrench to the nut and determine the torque required to turn the nut on the bolt (before the nut makes contact with the bearing surface). Add this, the friction drag torque, to the specifred torque to get the final torque. I 1 NOTE If the bolt is stationary and the nut is torqued, use the lower side of the torque range. If the nut is stationary and the bolt is torqued, use the higher side of the torque range. HANDLING AND SERVICING Revised: 10/3/80 LANCE I1 SERVICE MANUAL e. When torquing castellated nuts, begin with minimum torque plus friction drag torque, but d o not exceed maximum torque plus friction drag torque when trying to align slot on nut with the hole in the bolt shank. If they d o not align, change washers and try again. When using castellated nuts on movable joints, d o not torque as described above. Tighten nuts only to remove looseness in the joint and then install the cotter pin. f. Unless otherwise specified, when parts are used on Lycoming engines, using Piper furnished or existing Lycoming threaded fasteners, use the torques specified in the latest applicable Lycoming specifications. g. After the final torque has been applied, the nut (or bolts or screws if no nut is used) should be permanently marked red and should not be further tightened or disturbed. Revised: 10/3/80 HANDLING A N D SERVICING LANCE I1 SERVICE MANUAL TABLE 11-11. RECOMMENDED N U T TORQUES TORQUES: The importance of correct application cannot be overemphasized. Undenorque can result in unnecessap wear of nuts and bolts as well as the parts they are holding t o g t h e r . When insufficient pressures are applied. uneven loads will be transmitted throughout the assembly which may result in excessive wear or premature failure due to fatigue. Ovenorque can be equally damaging because of failure of a bolt or nut from overstressing the thread areas. The following procedures should be followed to assure that the correct torque is applied: 1. Torque (self-locking fasteners) - Add the friction torque from C h a n A for sizes 8 through 7 16 to the recommended torque from C h a n B to get the final torque. This would be the actual reading on ! the torque wrench. 2. Torque (castellated and non-self-locking nuts) - Use only the torque given in Chart B. Unless otherwise specified. when castellated nuts are used with a cotter pin on moving joints. do not torque the nut. Turn the nut onto the bolt until proper grip is established and alignment with therotter pin hole is achieved. Then install the cotter pin. 1 GENERAL REQUIREMENTS: i I . Calibrate the torque wrench periodically to assure accuracy: recheck frequently. 2. Ascertain that the bolt and nut threads are clean and dry (unless otherwise specified by the I manufacturer). I f the bolt or nut is specified to be lubricated prior to tightening. the torque range I should be reduced 50 percent. 1 3. Use a bolt length long enough to prevent bearing loads on the threads. The complete chamfer or end radius of the bolt or screw must extend through the nut. .4. Unique torques specified in the text of this manual supersede the torques given in Charts A and B. 5. Refer to the larest revision of Lycoming SSP 1776 for torques on pans used on Lycoming engines. 6. A maximum of two AN960 washers may be added under the bolt heads or nuts to correct for variations in material thickness within the tolerances permitted. 7. Limitations of the use of self-locking nuts. bolts and screws including fasteners with non-metallic insens are as follows: A . Fasteners incorporating self-locking devices shall not be reused if they can be run up using on]! fingers. They may be reused if hand tools are required to run them up, providing there is no obvious damage to the self-locking device prior to installation. B. Bolts 5: 16 inch diameter and over with cotter pin holes may be used with self-locking nuts. Nuts with non-metallic locking devices may be used in this application only if the bolts are free from burrs around the cotter pin hole. C. Do not use self-locking nuts at joints which subject either the nut or the bolt to rotation. D. Never tap or rethread self-locking fasteners. D o not use nuts. bolts or screws with damaged threads or rough ends. Revised: 11/ 1183 HANDLING AND SERVICING LANCE 11 SERVICE MANUAL T A B L E 11-11. R E C O M M E N D E D S U T T O R Q U E S (cont.) TABLE A r BOLT FRICTION DRAG 1 SIZE TORQUE (IN.-LBS.) 8' 15 10 18 1/4 30 5/16 60 1 318 80 7/16 1 0 0 'APPLICABLE TO COARSE THREADS ONLY. Revised: 11/1/83 NutWt irr 8 -32 10 -24 1 1 6 2 0 Y 16-18 38-16 7/16-14 1/2-13 9/1*12 HANDLING AND SERVICING COARSE THREAD SERIES BOLTS S a t T w i o n AN 3 thru AN 20 AN 42 thm AN 49 AN 73 thru AN 81 A N 173 ckru AN 106 MS20033thruMS20(W6 MS 20073 MS 20074 AN 509 NK9 MS 24694 AN 525 NK525 MS 27039 NUTS S m l Tamion AN 310 AN 315 AN 363 AN 365 NAS 1021 MS 17825 MS 21045 MSzm65 MS 24500 NAS 679 Toqua L h i a in-lbr Min. 12 20 40 160 235 460 600 S a t Shur AN 330 AN 364 NAS 1022 MS 17826 MS 20364 T w r Limits in-lbs M u . 15 25 50 8 0 9 0 4 a 185 a 5 $80 700 Min. 7 12 25 95 140 240 300 M u . 9 15 30 55 110 155 290 420 LANCE I1 SERVICE MANUAL - -- T A B L E 11-11. RECOMMENDED TORQUES (Inch Pounds) (cont.) Issued: 1/3/78 HANDLING AND SERVICING Nut-bolt saze 8 -36 10 -32 1/4-26 5116-24 3/8-24 7/16-20 112-20 9/16-18 5/8-18 314--16 7/8-14 1 -14 1-118-12 1-114-12 BOLTS Alum~num AN 3DD thm AN 2000 AN 173DO thru AN 1860D AN 50900 AN 5250 MS 270390 MS 2469400 FINE THREAD SERIES 8 0 LTS Steel Tenscon MS 20004 thm MS 20024 NAS 144 thru NAS 158 NAS 333 thru NAS 340 NAS 583 thru NAS 590 NAS 624 thru NAS 644 NAS 1303 ttiru NAS 1320 NAS 172 NAS 174 NAS BOLTS S t w l Tenson AN 3 thm AN 20 AN 42 thru AN 49 AN 73 thru AN 81 AN 173 thru AN 186 MS 20033 thm MS 20046 MS 20073 MS 20074 AN 509 NK9 MS 24694 AN 525 NK525 MS 27039 Alum. Tens~on AN 3650 AN 3100 NAS 10210 Torque L ~ r n l n ~n-lbs Mln. Max Steel sheer bolt NAS 464 5 10 30 40 75 180 280 380 550 950 1.250 1.600 2.100 3,900 NUTS Alum. Shear AN 3200 AN 364D NAS 10220 Torque Llmrts an-lbs Mln. Max S m l Tenuon AN 310 AN 315 AN 363 AN 365 NAS 1021 MS 17825 MS 2 1045 MS 20365 MS 2 8 0 0 N AS 679 Torque L ~ r n ~ n ~n-lbs 10 15 45 65 110 280 410 580 670 1.250 1.900 2.400 3,200 5,600 3 5 15 25 45 110 160 230 270 560 750 950 1,250 2.300 Mln 12 20 50 100 160 450 480 800 1,100 2.300 2.500 3.700 5.000 9.000 6 10 30 40 70 170 260 360 420 880 1,200 1,500 2,000 3.650 - NUTS S t w l Shear AN 320 AN 364 NAS 1022 MS 17826 MS M364 Torque Llmtts ~n-lbs Mtn. Max. Max. 15 25 70 140 190 500 690 1.000 1.300 2.500 3,000 4.500 7,000 11,000 NUTS Steel Tenoon AN 310 AN 315 AN 363 AN 365 MS 17825 MS 20365 MS 21045 NAS 1021 NAS 679 NAS 1291 Torque L~rnlts ~n.lbs 7 12 30 60 95 270 290 480 660 1,300 1.500 2,200 3.000 5,400 Steal Shear AN 320 AN 364 NAS 1022 MS 17826 MS 20364 Torque Llrnlts ~n-lbs Mln. 25 80 120 200 520 770 1,100 1,250 2.650 3,550 4,500 6 . m 11,000 9 15 40 85 110 300 410 600 700 1,500 1.800 3.300 4.200 6.600 Mln. 15 50 70 120 300 450 650 750 1,600 2.100 2,700 3.600 6.600 Max. 30 100 145 250 630 950 1,300 1.550 3,200 4,350 5.500 7.300 13.400 Max. 20 60 90 150 400 550 800 950 1,900 2.690 3.300 4.400 8.000 LANCE I1 SERVICE MANUAL 28a. TORQUE WRENCHES. Torque wrenches should be checked daily and calibrated by means weights and a measured lever arm to make sure that inaccuracies are not present. Checking one torque wrench against another is not sufficient and is not recommended. Some wrenches are quite sensitive as to the way they are supported during a tightening operation. Any instructions furnished by the manufacturer must be followed explicitly. When it is necessary to use a special extension or adapter wrench together with a torque wrench, a simple mathematical equation must be worked out to arrive at the correct torque reading. Following is the formula to be used: (Refer to Figure 2 - 4 . ) T = Torque desired at the part. A = Basic lever length from center of wrench shank to center of handle or stamped on wrench or listed for that model wrench. B = Length of adapter extension, center of bolt to center of shank. C = Scale reading needed to obtain desired torque (T). The formula: A x T C = A + B EXAMPLE A bolt requires 30 foot-pounds and a 3 inch adapter (onequarter of a foot or 25') is needed to get at it. You want to know what scale reading it will take on a one-foot lever arm wrench to obtain the 30 foot-pounds at the bolt. Remember, the 3 inch adapter must be projecting 3 inches straight along the wrench axis. In general, avoid all complex assemblages or adapters and extensions of flex joints. Figure 2-4a. Torque Wrench Formula Added: 10/3/80 HANDLING AND SERVICIN lB6 LANCE I1 SERVICE MANUAL 2-8b. IDENTIFICATION O F FLUID LINES. (Refer to Figure 2-4b.) Fluid lines in aircraft are often identified by markers made up of color codes, words or geometric symbols. These markers identify each line's function, content and primary hazard as well as direction of fluid flow. In most instances fluid lines are marked with 1-inch tape or decals. Paint is used on lines in engine compartments where there is a possibility of tapes, decals, or tags being drawn into the engine induction system. Certain lines may be further identified as to specific function within a system. For example: DRAIN, VENT. PRESSURE or RETURN. Lines conveying fuel may be marked FLAM; lines containing toxic materials are marked TOXIC in place of FLAM. Lines containing physically dangerous materials such as oxygen, nitrogen or freon are marked PHDAN. The aircraft and engine manufacturers are responsible for the original installation of identification markers, but the aviation mechanic is responsible for their replacement when it becomes necessary. Generally, tapes and decals are placed on both ends of a line and at least once in each compartment through which the line runs. In addition. identification markers are placed immediately adjacent to each valve. regulator, filter or other accessory within a line. Where paint or tags are used, location requirements are the same as for tapes or decals. 2 - 8 ~ .INSTALLATION O F FLEXIBLE HOSE ASSEMBLIES. a. Flexible hose must not be twisted on installation. A flexible hose which is installed with a twist may have a reduced service life and may cause a loosening of the fittings to which it is attached. b. Never exceed the minimum bend radius and avoid tight bends in flexible hose assemblies (Refer to AC 43: 13-1, Chapter 10). c. Never stretch a hose tight between two fittings as this may result in overstressing and eventual failure. The length of the hose should be sufficiently long t o provide 5 to 8 percent slack. Added: 10/3/80 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL i Added: 10/3/80 .B362 TWO COllON BRAIDS - IMPREGNATED WITH SYNTHETIC COMPOUND A. FLAME AND AROMATIC RESISTAM HOSE Figure 2-4b. Hose and Line Markings YELLOW NUMERALS. LETTERS AND STRIPE r - u n - c a y s r B NON-SELF-SEALING AROMATIC RESISTANT HOSE - HANDLING A N D SERVICING 1BS C NON-SELF-SEALINGAROMATIC AND HEAT-RESISTANT HOSE D FLAME. AROMATIC AND OIL RESISTANT HOSE RED NUMERALS, LETTERS AND STRIPE E SELF-SEALING AROMATIC RESISTANT HOSE HOSE IDENTIFICATION MARKINGS BROWN ORANGE ORANGE ORANGE GRAY BLUE YELLOW GRAY I I I C I C.1 C W . ( Y I D 01 c1.2 r G . l IUC I(., C D - 0 ELECTRICAL COMPRESSED INSTRUMENT HYDRAULIC DE-ICING CONDUIT GAS AIR YELLOW BROWN GREY 'Ull BREATHING FUEL PNEUMATIC LUBRICATlON AIR OXGYEN CONDITION RED LANCE I1 SERVICE MANUAL TABLE 11-IIA. CONVERSION TABLES I . Thehe charts contain the ~ a r i o u sconversion data that may be useful when figuringcapacities. length>. temperatures. and various heights and mcasures from the English system values to the metricsystem u l u e s o r back again. 1. The English system is in uw b \ England and the United States. All other countries use the metrlc \!>tcm. 3. Proccdure for Converting Incheh to Millimeters. (Refer to Table 11-IIA.) A . Example: Convert 1.5 inches to millimeters. ( I ) Read down incheh column to I . inches. ( 1 ) Read across top inch column t o 0.5. ( 3 ) Read down and across to find millimeters (1.5 inches is 38.10 millimeters). 4. Procedure for Convert ing Fahrenheit ( O F) and Celsius (OC) (Centigrade) Temperature. ( Rel'er to Table 11-IIA.) A . Read nurnbcr in middle column. if in degrces Crlhius ('0.read Fahrenheit equi\alent in right-hand column. I f in degrees Fahrenheit (OF). read Celsiuh equivalent in left-hand column. Addtd: 1@,3/8OJ HANDLING AND SERVICING LANCE 11 SERVICE M A N U A L T A B L E 11-IIA. CONVERSION T A B L E S (cant) INCHES TO MILLIMETER INCHES 0 . m 0.0001 0.0002 0.0001 0 . m 0.0005 0.0006 0.0007 O.WO8 0.OW MILUMITER 0.000 a0025 0.009 0.0076 0.0101 0.0127 o.0152 0.0177 0.0203 0.0228 0.001 0.0254 0.0279 0.0304 0.0330 0.0355 0.0381 0.0406 0.0431' 0.0457 0.0482 0.002 0.0508 0.0533 0.0558 0.0584 0.0609 0.0635 0 . W 0.0605 0.071 1 0 0736 0.003 0.0762 0.0787 0.0812 0.0838 0.0863 0.0689 0.0914 0.0939 0.0965 0.0990 0.004 0.1016 0.1041 0.1066 0.1092 0.1117 0.1143 0.1168 0.1193 0.1219 0.1244 0.005 0.1270 0.1295 0.1320 0.124 0.1371 0.1397 0.1422 0.1447 0.1473 0.1498 0.006 0.1524 0.1549 0.1574 0.1600 0.1623 0.1651 0.1676 0.1701 0.1727 0.1752 0.007 0.1778 0.1803 0.1828 0.1854 0.1879 0.1905 0.1930 0.1955 0.1981 0.2006 0.008 0.2032 0.2057 0.2082 0.2108 0.2133 0.2159 0.2184 0 . m 0.=5 0.2260 0.009 0 2 8 6 0.2311 0.2336 0.2362 0.2387 0.2413 0.2438 0.2463 0.2489 0.2514 INCHES 0.000 0.001 0.002 0.003 0.004 0.005 0.036 0.007 0.008 0.009 MILLIMETER 0.00 0.025 O.OM 0.076 0.101 0.127 0.152 0.177 0 . ~ 0 3 0.:28 0.01 0 . m 0.279 0.304 0.330 0.355 0.381 0.406 0.431 0.457 0.482 0.01 0.338 0.531 0.558 0.584 0.609 0.635 0.660 0.685 0.711 0.736 0.03 0.762 0.787 0.812 0.838 0.863 0.889 0.914 0.939 0.965 0.990 0.04 1.016 1.041 1.066 1.092 1.117 1.143 1.168 1.193 1.219 1.244 0.05 1.270 1.295 1.320 1.24 1.371 1.I97 1.422 I .U7 1.473 1.498 0.06 1.524 1.549 I. 574 1.600 1.625 1.651 1.676 1.701 1.727 1.752 0.07 1.m 1.803 1.828 1.854 1.879 1.905 1.930 1.955 1.981 2.006 0.08 2032 2057 2082 2108 2133 1159 2184 2209 2235 2.260 0.09 L a 6 -2.31 1 2336 2362 2387 2413 2438 2.143 2189 2.514 INCHES 0.00 0.01 0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.09 M I L L l M m R 0.0 0.2% 0- 0.762 0.016 1.270 1.521 1.n8 2.012 2.36 0. I 254 2.794 3.044 3.302 3.5% 3.810 4.064 4.318 4.572 4.826 0.2 5.080 5.334 5 . 5.842 6 . M 6.350 6.- 6.858 7.112 7.366 0.3 7.620 7.874 8.121 8.12 8.636 8.1194 9.144 9.398 9.652 9.906 0.4 10.160 10.414 10.661 10.922 11.176 11.430 11.684 11.938 I2192 12.446 0.5 12700 12954 1 3 . m 13.a2 13.716 13.970 14.224 14.478 14.732 14.986 0.6 15.240 15.494 15.748 16.002 16.256 16.510 16.764 17.018 17.272 17.526 0.7 17.780 18.034 18.01 18.542 18.796 19.0% l 9 . B 19.558 19.812 20.066 0.8 20.320 70374 20.828 21.12 21.336 21.390 21.844 22.098 22.352 P.606 0.9 22.860 23.114 23.368 23.622 23.876 24.130 24.384 24.638 24.892 2S.146 MCHES 0.00 0. I 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 M I L U M m R 0. 2 54 5.08 7.62 10.16 1270 15.24 1 7 . 7 ~ 20.32 22.86 I . 23.40 27.94 30.48 33.02 35.56 38.10 40.64 43.18 45.72 48.26 2. 50.80 53.34 55.88 58.42 60.96 6 3 3 66.04 68.58 71.12 73.66 3. 76.20 78.74 81.21 83.82 &# 1.90 91.U 93.98 96.52 99.06 4. 101.60 104.14 106.6) 109.22 111.76 114.30 116.84 119.38 121.92 124.46 5. 127.00 129.54 13208 134.62 137.16 139.70 14224 144.78 147.32 149.86 6. I5240 154.94 157.48 160.02 16256 165.10 167.64 170.18 17272 175.26 7. 177.80 180.34 18288 185.42 187.96 190.W) 193.04 195.58 198.12 m.66 8. 103.20 20.74 IW.21 210.82 213.36 215.90 218.U 220.98 223.52 226.06 9. 228.60 231.14 233.M 23622 238.76 241.30 243.84 214.38 248.92 251.46 Added: 10/3/80 HANDLING AND SERVICING , LANCE 11 SERVICE MANUAL T A B L E 11-11A. C O N V E R S I O S T A B L E S (cont) I \ ( HE?, I 0 \ I l l I I \ I F I F R INCHES 0.W 0. I 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 M l L L I M m l 0. 2 % 5.08 7.62 10.16 I270 15.24 17.78 20.12 22.16 I. U.Y) 27.94 M.O 33.02 3 5 . ~ 4 U.IO 40.64 43.18 45.72 48.26 2 50.80 51.34 55.88. 51.42 60.96 63.50 66.W 5 71.12 73.66 3. 76.10 78.14 11.B 83.11 S6.Y 88.90 9 l . U 91.98 W.52 99.06 4. 101.60 104.14 106.6) 109.22 111.76 II4.B 116.84 119.38 121.92 124.46 5. 127.00 129.Y 13201 124.62 137.16 139.70 14224 144.78 147.12 149.116 6. 152.40 IS4.94 157.U 160.02 162% 165.10 167.64 170.18 17272 175.26 7. I77.W I8O.W 112.1) 185.42 187.96 1W.S 193.01 195.51 198.12 aD0.66 1. 2Q3.m P5.74 m.21 210.11 213.24 2IS.W 218.44 210.98 223.52 226.06 9. 228.60 U1.14 233.61 2M.P 238.76 241.M 243.84 246.38 248.92 731.46 T H I S S P A C E I N T E N T I O S A L L ) ' L E F T B L . \ S K Added: 10/3/80 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL - Added: 10/3/80 I HANDLING AND SERVICING TABLE 11-IIA. CONVERSION TABLES (cont) CENTIGRADE-FAHRENHEIT CONVERSION T A B L E Example: T o convert 20°C. to Fahrenheit. find 20 in the center column headed (F-C): then read 68.0° F. in the column (F) to the right. T o convert 20" F. to Centigrade; find 20 in the center column and read -6.67OC. In the ( C ) column C F-C F -56.7 -70 -94.0 -51 1 -60 -76.0 -45.6 -50 -58.0 -40.0 -40 -40.0 -34.0 -30 -22.0 -38.9 - 20 -4.0 -23.3 -10 14.0 -17.8 0 32.0 - 12.22 10 50.0 -6.67 20 68.0 - 1 . 1 1 30 86.0 4.44 40 104.0 10.00 50 122.0 15.56 60 140.0 21.1 1 70 158.0 26.67 80 176.0 32.22 90 194.0 27.78 100 2 12.0 43.33 l I0 230.0 38.89 I20 248.0 54.44 130 266.0 60.00 140 284.0 65.56 150 302.0 7 1 .OO 1 60 320.0 76.67 1 70 338.0 82.22 180 356.0 87.78 1 90 374.0 93.33 200 392.0 98.89 2 10 410.0 to the left. C F-C F 104.44 220 428.0 I 10.00 2 30 446.0 115.56 240 464.0 121.11 250 482.0 1 26.67 260 500.0 132.22 270 5 18.0 137.78 280 536.0 143.33 290 554.0 148.89 300 572.0 154.44 310 590.0 160.00 320 608.0 165.56 330 626.0 I 171.11 340 644.0 176.67 350 662.0 182.22 360 680.0 187.78 370 698.0 193.33 380 716.0 198.89 390 734.0 204.44 400 752.0 2 10.00 410 770.0 215.56 420 788.0 221.11 430 806.0 226.67 440 824.0 232.22 450 842.0 257.78 460 860.0 243.33 470 878.0 248.89 480 896.0 254.44 490 914.0 260.00 500 932.0 LANCE I1 SERVICE .MANUAL T A B L E 11-IIA.C O S V E R S I O N T A B L E S (cont) MULTIPLY CENTIMETERS CU. CENTIMETERS CU. FT. CU. IN. CU. METERS FEET FT.-LB. FLUID 02 GAL.. IMPERIAL GAL.. U.S. DRY GAL.. U.S. LlQ. Added: 10/3/80 MULTIPLY KILOGRAMS LITERS METERS METER-KILOGRAM OUNCES. AVDP OUNCES. FLUID LB.. AVDP SQUARE INCH POUND PER SQUARE INCH (PSI) STATUTE MILE NAUTICAL M I L E QUART MILLIMETER MICRON INCH POUNDS INCH OUNCES POUNDS HANDLING A N D SERVICING ,08333 JOULES 0.000948 0.7376 FT.-LB. BY 0.3937 0.0328 1 0.001 0.06102 0.0002642 28.320 1.728 7.48 1 28.32 16.39 0.0 1639 0.004329 0.0 1732 IOOOOOO 35.314 6 1 .OU 264.17 999.97 0 . M 12.000 304.8 0.3333 0.1383 0.001285 0.000000376 8 29.6 277.4 1.201 4 . 9 6 268.8 0. I556 1.164 4 405 23 1 .O 0.1337 3.785 0.8327 B Y 2.205 35.27 loo0 loo0 6 1.03 0.03532 0.26r2 0.22 1.057 39.37 3.281 1000 7.233 9.807 0.0625 28.35 417 5 29.57 1.805 . 453.6 7000 16.0 6.4516 0.0703 1.609 0.8684 1.151 .9461 I000 0.001 0.000039 11.521 0.72 0.451 TO OBTA IN IN. FT . LITERS CU. IN. U.S. GAL. CU. CM. CU. IN. U.S. GAL. LITERS CU. CM. LITERS U.S. GAL. QUARTS CU. CM. CU. FT. CU. IN. GAL. LITERS METERS MILS. MM. YARDS M-KG BTU KW-HR DRAM CU. CM. CU. IN. U.S. G A L LITERS CU. IN. CU. FT. U.S. GAL, LIQ. LITERS CU. IN. CU. Fl-. LITERS IMPERIAL GAL. FLUlD O Z TO OBTA I ti L B. 0 2 . GRAMS CU. Chi. CU. I N . CU. FT. U.S. GAL. IMPERIAL GAL. QUARTS IN. FT. MM. FT.-LB. JOULES LB.. AVDP GRAMS GRAISS CU. C h i . CU. IS. GRAMS I GRAISS OUSCES SQ. CM. KG-CM SQUARED KILOMETER NAUTICAL MILE STATUTE MlLE LlTE R MICROh' MII.LIMETER INCH METER GRAMS METER GRAMS KILOGRAMS LANCE II SERVICE MANUAL I I TABLE 11-IIA. CONVERSION TABLES DECIMAL CONVERSION CHART I i Revised: 10/3/80 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL TABLE 11-IIB. D E C I M A L I M I L L I M E T E R E Q U I V A L E N T S OF D R I L L S I Z E S Dec~mal/Mill~meterEquivalents of Drill Sizes From 1 /2" to No. 80 S~ze Dectmel M~llimem S~ze Dec~mal Millimeter S~ze Dec~mal Millimeter Size Dec~mal Milltmetw Equlv. Equ~v. Equiv. Equlv. Equlv I Equlv Equtv Equtv. 112 0.500 12.7000 G 0.261 6.6294 5/32 0.1562 3.9687 51 0.067 1.7018 31/64 0.4843 12.3031 F 0.257 6.5278 23 0.154 3.91 16 52 0.0635 1 6129 24 0.152 3.8608 25 0.1495 3.7973 26 0.147 3.7338 27 0.144 3.6576 55 0.052 1 3208 9/64 0.1406 3.5719 3/64 0.0468 1 1906 28 0.1405 3.5687 56 0.0465 1 181 1 . 29 0.136 3.4544 30 0.1285 / 3.2639 DRILL SIZES AVAILABLE Drill may be obtalned ~nregular slzes to a 4 ~ n c hd~arnefer,and Increase ~n64thsof an lncn The regular metrlc drllls vary from 2 to 76mm and increase ~n0 5mm varlatlons. 6 Added: 10/3/80 HANDLING A N D SERVICING 2-8d. S U P P O R T CLAMPS. Support clamps are used to secure the various lines to the airframe o r vowe plant assemblies. Several types of clamps ari used for this purpose. The rubber cushioned and plain are the most commonly used clamps. The rubber cushioned clamp is used to secure lines subject to vibration. The cushioning prevents chafing of the tubing. The plain clamp is used to secure lines in areas not subject to vibration. A teflon cushioned clamp is used in areas where the deteriorating effect of Skydrol 500 hydraulic fluid (MIL-H-5606) or fuel is expected. However, because it is less resilient, it does not provide as good a vibration damping effect as other cushion materials. Use bonded clamps to secure hydraulic, fuel and oil lines in place. Unbonded clamps should be used only for securing wiring. Remove any paint o r anodizing from the portion of the tube at the bonding clamp location. Make certain that clamps are of the correct size. Clamps or supporting clipssmaller than the outside diameter of the hose may restrict the flow of fluid through the hose. All plumbing lines must be secured at specified intervals. The maximum distance between supports for rigid fluid tubing is shown in Table 11-IIC. T A B L E 11-IIC. M A X I M U M DISTANCE BETWEEN S U P P O R T S F O R F L U I D TUBING • Added: 10j3/80 HANDLING A N D SERVICING TUBE OD (IN. ) DT ST.4NCE BEl7EEN SUPP0I:TS ( I N . ) .I\uIMImIALLOY STEEL 1/s !3-I/? 1 1 - 1 1 2 5/16 1 2 1 4 1/J 1 3 - 1 / 2 l b 5 / 1 6 1 5 1 8 3/ 5 1 6 - 1 / 2 3 0 1/ 7 19 ? - - 3 5/ 5 3 7 - & 2 5 - 1 / 2 3/4 24 2 7 - 1 / 2 1 26-1/? 50 < LANCE I1 SERVICE MANUAL - .- TABLE 11-IID. T H R E A D LUBRICANTS TYPE O F LINE T Y P E O F LUBRICANT Bra kts M I L-H-5606 Freon TT-A-580 o r MIL-T-5544. Anti-Seize Compound Fuel M 1L-T-5544. Anti-Seize. Graphite Petro!atum Landing Gear (Air Valce) 6 P B Parker 011 M I L-G-6032. Lubricating Grease (Gasoline and Oil Resistant) P ~ t o tand Static TT-A-580 (JAN-A-669). Anti-Seize Compound (White Lead Base) - ,VOTE - Lubricate engine fittings only with the fluid contained in the particular lines. b a 1. TABLE II-IIE. HOSE CLAMP T I G H T E X I Y G ( I S I T I A L I X S T A L L A T I O N Added: 10/3/80 Types of hose Se!f sealing .A11 orher hose HANDLING AND SERVICING If clamps do not seal at specified tightening. examine hose connection and replace p a n s as necessav. Types of clamps . Worm screw type Finger-tight-plus 2 complete turns Finger-tight-plus I I , 4 complete turns All other types Finger-tight-plus 3 1 : I ) complete turns Finger-tight-p~~s 2 complete turns LANCE I1 SERVICE MANUAL SMALL ENTER D R I L L -3 . Figure 2-4c. Removal of Cherrylock Rivet 2-8e. REMOVAL O F CHERRY LOCK RIVETS. (Refer to Figure 2 4 . ) Should it be necessary to remove a n installed cherrylock rivet, the following procedures are recommended. a. In thick material remove the lock by driving out the rivet stem using a tapered steel drift pin (Refer View 1). 8 NOTE Do not drill completely through the rivet sleeve to remove a rivet as this tends to enlarge the hole. b. If the rivets have been installed in thin sheets, drivingout the locked stem may damage the sheets. It is recommended that a small center drill be used to provide a guide for a larger drill on top of the rivet stem, and the tapered portion of the stem be drilled away to destroy the lock (Views 2 and 3). c. Pry the remainder of the locking collar out of the rivet head with the drift pin (See View 3). d. Drill nearly through the head of the rivet, using a drill the same size as the rivet shank (See View 4). e. Break off rivet head using a drift pin as a pry (See View 5). f. Drive out the remainingrivet shank with a pin having a diameter equal to the rivet shank (See View 6). Added: 10/3/80 HANDLING A N D SERVICING LANCE I1 SERVICE MANUAL Figure 2-5. Access Plates and Panels 820 FUSEUQE LEFT 2 3 1. FA1RING, ACCESS 2. FIN TIP 3. RUDDER TIP 4. T A I L CONE. CONTROL CABLES & TRIM SCREW 5 . DOOR. NOSE GEAR 6. COVER. AIR FILTER (32RT-300) 5 6 7 4 7. COVER, HYDRAULIC RESERVOIR & BATTERY SERVICE 820 3 2 1 FUSELAGE RIGHT 1. FAIRING, ACCESS 2. FIN TIP 3. RUDDER TIP - 7 -7 4. T A I L CONE. CONTROL C A B L 5 & T R I M !%CREW 5. DOOR. NOSE GEAR 6. DOOR. BAGGAGE 7. COVER. E - L T . A C C E S 4 6 5 821 FUSELAGE BOlTOM 1. PANEL, FLOOR 2. PLATES. TUNNEL ACCESS 3. COVER, FUEL SELECTOR n L T E R 1. PANEL, B A l T E R Y & HYDRAULIC EXTERNAL ACCESS 3 i Issued: 1/3/78 A HANDLING AND SERVICING LANCE 11 SERVICE MANUAL 022 UPPER WlNG SURFACE 1. WlNG TIP 2. PLUG. AILERON BELLCRANK ACCESt 3. M A l N FUELTANK 4 . CAP. FUEL TANK 822 ti i [ ~ L S R SURF- 1. WlNG TIP 2. COVER. FUEL F l l T l N G 3. MAlN FUEL TANK 4. COVER. FUEL& BRAKE FITTINGS AND GEAR AlTACHMENT F l l T l N G 5. FAIRING. FLAP TORQUE TUBE 1 AILERON CABLES 6. DOOR. MAlN G U R 7. COVER, FUEL F l l T l N G 8. COVER. AILERON BELLCRANK ACCESS 9. COVER. GEAR A-ACHMENT F l l T l N G Figure 2-5. Access Plates and Panels (cont.) HANDLING AND SERVICING LANCE II SERVICE MANUAL Figure 2-6. Jacking Arrangment 2-9. STEP, HANDHOLD, AND WALKWAYS. A fixed handhold is located on the right side of the fuselage, above and aft of the center seat window. The walkway is made up of a non-skid compound applied to the wing surface (Refer to Section IV for repair). A step is available as optional equipment and is installed just aft of the trailing edge of the right flap. - - 2- 1 0. GROUND HANDLING. 2- 1 1. GENERAL. Ground handling covers all essential information governing the handling of the airplane on the ground. This includes jacking, weighing, leveling, mooring, parking, towing 2nd taxiing When the airplane is handled in the manner described in the following paragraphs, damage to the airplane and its equipment will be prevented. 2-1 2. JACKING. Jack the airplane to service the landing gear and as specified to perform other service operations. Proceed as follows: a. Place the jacks under jack pads a the front wing spar. (Refer to Figure 2-6.) b. .Attach the tad support to the tail skid. PIace approximately 300 pounds of ballast on the base of the tail support .to hold down the tail. CAUTION Be sure to apply sufficient tail support ballast; otherwise the airplane will tip forward. c. Raise the jacks until all three wheels are clear of the surface. h u e d : 1/3/78 1B21 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL Figure 2-7. Weighing the Airplane 2-13. WEIGHING. (Refer to Figure 2-7.) The airplane may be weighed by the following procedure : a. Position a scale and ramp in front of each of the three wheels. b. Secure the scales from rolling forward and tow the airplane up onto the scales. (Refer to Towing, Paragraph 2-1 8.) c. Remove the ramp so as not to interfere with the scales. d. If the airplane is to be weighed for weight and balance computations, level the airplane per instructions given in Paragraph 2-1 4. 2-14. LEVELING. AU configurations of the airplane are provided with a means for longitudinal and lateral leveling. The airplane may be leveled while on jacks; during the weighing procedure while the wheels are on scales; or while the wheels are on the ground. To level the airplane for purposes of weighing or rigging, the following procedures may be used: a. To longitudinally level the airplane, partially withdraw the two leveling screws located immediately below the left front side window. (Refer to Figure 2-8.) Place a spirit level on these screw heads and deflate the nose wheel tire or adjust the jacks until the bubble of the level is centered. b. To laterally level the airplane, place a spirit level across the baggage compartment floor along the Izar bulkhead (Refer to Figure 2-9.) and deflate the tire on the high side of the airplane or adjust either jack until the bubble of the level is centered. Issued: 1/3/78 HANDLING AND SERVICING 1B22 LANCE II SERVICE MANUAL Figure 2-8. Leveling Longitudinally Figure 2-9. Leveling Laterally 2-15. MOORING. The airplane is moored to insure its immovability, protection and security under various weather conditions. The following procedure gives the instructions for proper mooring of the airplane. a Head the airplane into the wind, if possible. b. Block the wheels. c. Lock the aileron and stabilatar controls using the front seat belt. d. Secure tie-down ropes to the wing tiedown rings and the tail skid at approximately 45 degree angles to the ground. When using rope constructed of nonsynthetic material, leave sufficient slack to avoid damage to the airplane when the ropes contract due to moisture. CAUTION Use square or bowline knots. Do not use slip knots. NOTE Additional preparations for high winds include using tie-down ropes from the landing gear forks and securing the rudder. e. Install pitot tube cover if available. 2-16. LOCKING AIRPLANE. Matching key locks are provided on right cabin door, left cabin door, forward baggage door and ignition switch. Issued: 1/3/78 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL 2- 17. PARKING. When parking the airplane, insure that is is sufficiently protected against adverse weather conditions and presents no danger to other aircraft. When parking the airplane for any length of time or overnight, it is recommended that it be moored as in Paragraph 2- 15. a. To park the airplane, head it into the wind, if possible. b. Set the parking brake by pulling back the brake lever and depressing the knob attached to the left side of the handle. Then release the handle. To release the parking brakes, pull back on the brake lever to disengage the catch mechanism. Then allow the handle to swing forward. NOTE Care should be taken when .setting brakes that are overheated or during cold weather when accumulated moisture may freeze the brakes. c. The aileron and stabilator controls may be locked by using the front seat belt. When moving the aircraft forward by hand, avoid pushing on the trailing edge of the ailerons as this will cause the aileron contour to chang resulting in an outaf- trim condition. 2-18. TOWING. The airplane may be moved by using the nose wheel steering bar that is stowed below the forward ledge of the rear baggage compartment or power equipment that will not damage or cause excess strain to the nose gar steering assembly. The stem on the bar is inserted in the hollow of the nose wheel axle at its right side. CAUTION When towing with power equipment, do not turn the nose gear in either direction beyond its steering radius limits as this will result in damage to the nose gear and steering mechanism. In the event towing lines are necessary, lines (rope) should be attached to both main gear struts as high up on the tubes as possible. Lines should be long enough to clear the nose and/or tail by not less than 15 feet, and a qualified person to ride in the pilot's seat to maintain control by use of the brakes. CAUTION When moving the aircraft forward by hand, avoid pushing on the trailing edge of the ailerons as will cause the aileron contour to change resulting in an outof-trim condition. Issued: 1/3/78 HANDLING AND SERVICING 1B24 LANCE I1 SERVICE MANUAL 2-19. TAXIING. Before attempting to taxi the airplane, ground personnel should be checked out by a qualified pilot or other responsible person. Engine starting and shutdown procedures should be covered as well. When it is ascertained that the propeller back blast and taxi areas are clear, apply power to start the taxi roll and perform the following checks: a. Taxi forward a few feet and apply brakes to determine their effectiveness. b. Taxi with propeller set in low pitch, high RPM setting. c. While taxiing, make slight turns to ascertain the effectiveness of steering. d. Observe wing clearances when taxiing near building or other stationary objects. If possible, station a guide outside the airplane to observe. e. When taxiing on uneven ground, look for holes and ruts. f. Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones, gravel or any loose material that may cause damage to the propeller blades. 2-20. EXTERNAL POWER RECEPTACLE. 2-21. OPERATION OF EXTERNAL POWER RECEPTACLE. The external power receptacle is located on the left side of the nose section just aft of the engine cowling. When using external power for starting or operation of any of .the airplane's equipment, the following procedure should be followed: Turn the master switch OFF and turn all electrical equipment OFF. Connect the RED lead of the PEP kit jumper cable to the POSITIVE (+) terminal of an external 12-volt battery and the BLACK lead to the NEGATIVE (-) terminal. Insert the plug of the jumper cable into the socket located on the fuselage. Note that when the plug is inserted, the electrical system is ON. Proceed with the nonnal starting technique. After the engine has started, reduce power to the lowest possible RPM, to reduce sparking, and disconnect the jumper cable from theaircraft. Turn the master switch ON and check the alternator ammeter for an indication of output. DO NOT ATTEMPT FLIGHT IF THERE IS NO INDICATION OF ALTERNATOR OUTPUT. If aircraft battery is weak, charging current will be hi*. DO NOT TAKE OFF until charging current falls below 20 'amps. NOTE For a l l normal operations using the PEP jumper cables, the master switch should be OFF, but it is possible to use the ships battery in parallel by turning the master switch ON. This will give longer cranking capabilities, but will not increase the amperage. CAUTION: Care should be exercised because if the ships battery has been depleted, the external power supply can be reduced to the level of the ships battery. This can be tested by turning the master switch ON momentarily while the starter is engaged. If cranking speed increases, the ships battery is at a higher level than the external power supply. When the engine is firing evenly, advance the throttle to 800 RPM. If oil pressure is not indicated within thirty seconds, stop the engine and determine the trouble. In cold weather it will'take a few seconds longer to get an oil pressure indication. If the engine has failed to start, refer to the Lycoming Operating Handbook, Engine Troubles and Their Remedies. Starter manufacturers recommended that cranking periods be limited to thirty seconds with a two minute rest between cranking periods. Longer cranking periods will shorten the life of the starter. HANDLING AND SERVICING LANCE I1 SERVICE MANUAL 2-22. SERVICING. • 2-23. GENERAL. Servicing the airplane includes the replenishment of fuel, oil, hydraulic fluid, tire pressures, lubrication requirements and other items required to completely service the airplane. 2-24. FUEL SYSTEM. 2-25. SERVICING FUEL SYSTEM. At intervals of 50-hours or 90 days, whichever comes first, clean the screens and bowl in the fuel filter unit of the fuel selector. Remove and ckan the filters in accordance with instructions outlined in Section IX. Additional service information may also be found in Section IX. Inspection intervals of the various fuel system components may be found in Section 111. 2-26. FILLING FUEL TANKS. The fuel tanks of each wing are filled through filler necks. The fder neck s e ~ c e s - both inboard and outboard tanks. Each wing with interconnecting tanks has a capacity of 49 U.S. gallons. a. Observe all required safety precautions for handling gasoline. b. Fill the tanks with fuel as specified on the placard adjacent to the filler neck or refer to the latest issue of Lycoming Service Instruction No. 1070 for alternate fuels. 2-27. 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 or sediment. Each fuel tank is equipped with an individual quick drain located at the lower inboard rear comer of the tank. The fuel strainer and a system quick drain valve are located in the fuselage at the lowest point of the fuel system. It is important that the fuel system be drained in the following manner: a. Drain each tank through its individual quick drain located at the lower inboard rear comer of the tank, making sure that enough fuel has been drained to ensure that all water and sediment is removed. b. Place a container under the fuel sump drain outlet, which is located under the fuselage. c. Drain the fuel strainer by pressing down on the lever located on the nght-hand side of the cabin below the forward edge of the center seat. The fuel selector must be positioned in the following sequence: off position, left main and right main while draining the strainer to ensure that the fuel lines between each tank outlet and fuel strainer are drained as well as the strainer. When the fuel tanks are full, it will take approximately six seconds to drain all the fuel in one of the lines from a main tank to the fuel strainer. When the fuel tanks are less than full, it will take a few seconds longer. d. Examine the contents of the container placed under the fuel sump drain outlet for water and sediment and dispose of the contents. CAUTION When draining any amount of fuel, care should be taken to ensure that no fm hazard exists before starting engine. Issued: 1/3/78 HANDLING AND SERVICING LANCE I1 SERVICE MANUAL NOTE After using the underseat quick drain, it should be checked from outside to make sure it has closed completely and is not leaking. 2-27a. ANTI-ICING FUEL ADDITIVE. The PA-32RT-300/300T aircraft are approved for operation with a n anti-icing additive in the fuel. When an anti-icing additive is used i t must meet the specification MIL-L-27686. must be uniformly blended with the fuel while refueling, must not exceed .15% by volume of the refueled quantity. and toensure its effectiveness should be blended at not less than .lo%by volume (one and one half liquid 02s. per ten gallon of fuel would be within this 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. Assure that the additive is directed into flowing fuel stream. Theadditive flow should sran after and stop before the fuel flow. D o not permit the concentrated additive to come in contact with the aircraft painted surfaces or the interior surfaces of the fuel 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 substitute for a preflight draining of the fuel system drains. 2-28. DRAINING FUEL SYSTEM. Fuel may be drained from the system by opening the valve at the inboard end of each fuel tank. The flush type drain valve requires the drain cup pin to hold valve open. The remaining fuel in the system may be drained through the filter bowl. Either wing tank set may be drained by closing the selector valve and then drainingas desired. - 7 2-29. BRAKE SYSTEM. 2-30. SERVICING BRAKE SYSTEM. The brake system incorporates a hydraulic fluid reservoir through which the brake system is periodically serviced. Fluid is drawn from the reservoir by the brake cylinders to maintain the volume of fluid required for maximum braking efficiency. Spongy brake pedal action is often a n indication that the brake fluid reservoir is running low on fluid. Instructions for filling the reservoir are given in Paragraph 2-3 1. When found necessary t o accomplish repairs to any of the brake system components, or to bleed the system, these instructions may be found in Section VII. 2-3 1. FILLING BRAKE CYLINDER RESERVOIR. The brake cylinder reservoir should be filled to the level marked on reservoir, with the fluid specified in Table 11-1. 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 Section VII. 2-32. DRAINING BRAKE SYSTEM. To drain the brake system connect a hose to the bleeder fitting on the bottom of the wheel 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. T o drain the wheel brake unit, disconnect the' line at the bottom of the unit and allow fluid to flow into a suitable container. T o clean the brake system, flush with denatured alcohol. Revised: 10/3/80 HANDLING A N D SERVICING 1C3 2-32a. TIRES. 2-32b. SERVICING TIRES. The tires should be maintained at the pressure specified in Table 11-1. When checking tire pressure, examine the tires for wear, cuts, bruises and slippage- 2-32c. TIRE BALANCE.(Refer to Figure 2-9a.) Proper balancing is critical for the life of aircraft tires. If a new tire is balanced upon installation it wiU usually remain balanced for the life of the tire without having any shimmy or flat spots, and an inexpensive balancer can be made that will balance almost any tire for light aircraft. Balance the tire as follows: a. Mount the tire and tube (if one is used) on the wheel, but do not install the securing bolts. install the wheel bearings in the wheel; then, using the -7 bushing, -6 spacers, and -5 nuts, install the wheel-tire assembly on the -8 pipe. Secure the -5 nuts finger-tight so that the wheel halves touch each other. Be sure the bolt holes are aligned! Insert the -4 axle through the -8 pipe and place the wheel in the center of the b$ancer. 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. b. Release the tire. If it is out of balance it will rotate, coming to rest with the heaviest point on the bottom. Tape a 112 ounce patch across top center of the tire. Rotate the tire 4Soand release it again. If the tire returns to the same position, add a 1 ounce patch and again rotate the tire and release it. Continue this procedure until the tire is balanced. c. When balance is attained, put a chalk mark on the sidewall directly below the patch. Use one mark for each half ounce of weight needed. Mark the valve stem location on the tire and the opposite wheel half to assure reassembly in the same position. Remove the wheel from the balance stand, break it down and clean the inside of the tire with toluol. Apply a coat of patch cement to both the patch and the inside center of the tire in line with the chalk marks. When the cement has dried, install the patches making certain they are on the center line of the tire and aligned with the chalk marks on the sidewall. Burnish the patches to remove trapped air, etc. d. When reassembling the wheel, powder the inside of the tire. Mount the tire on the valve side of the wheel in the same position it was in when it was balanced. Install the other wheel half, aligning the chalk marks. Install the bolts and tighten to required torque, then air the tire and recheck balance. The wheel should not be more than 112 ounce out of balance.. e. The following instructions will help in building the balancer: (Refer to Figure 2-9a.) 1. Chamfer top edges of -3 sides leaving 1/16 inch flat on top inboard edge. Rivet -2 tee's to -3 sides using AN 470-ADS rivets 2" spacing. Use AN 426-AD5 rivets 2" center to center to secure -2 tee's to -1 base. If tee extrusion is unavailable, heavy angle extrusion could be used. -3 sides must be vertical. 2. The 4 axle must slide through the -8 pipe. The -5 nuts were made by reaming the existing threads in the AN 365624 nuts with an R drill, then tapping wi