Piper Aircraft Corporation MOJAVE PA-31 P-350 Maintenance Manual Download

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Summary of Contents for MOJAVE PA-31 P-350

Page 1: ...MOJAVE MAINTENANCE MANUAL CARD 1OF 5 PA 31 P 350MOJAVE PIPER AIRCRAFT CORPORATION PART NUMBER 761781 lAl Courtesy of Bomar Flying Service www bomar biz ...

Page 2: ...pters are then broken down into Sub System Sections These sections are identified by the second element of the standardized numbering system The number 40 of the basic number series 32 4 00 is for the Wheels and Brakes portion of the landing gear The individual unitswithin a Sub System Section may be identified by a third element of the standardized numbering system such as 32 40 01 This number co...

Page 3: ... of Charts is for all fiche in this set following list of Illustrations 4 A complete list of paragraph titles and appropriate Grid location numbers is given at the beginning of each Chapter relating to the information within that Chapter 5 Identification of Revised Material Revised text and illustrations are indicated by a black vertical line along the left hand margin of the frame opposite revise...

Page 4: ... 14 1983 April 30 1986 July 23 1986 September 25 1986 June 15 1988 March 13 1990 October 7 1994 1 2 3 4 and 5 1 3 4 and 5 1 23 4 and 5 1 2 1 and 4 3 2 1 and 4 INTERIM REVISION Revisions appear in chapter 5 of card 1 and chapter 71 of card 4 Please dispose of your current cards 2 and 4 and replace with the revised one DO NOT DISPOSE OF CARDS 2 3 5 Consult the Customer Service Information Aerofiche ...

Page 5: ...o 419 255 4068 Autopilot Avionics Edo Corporation Avionics Division P O Box 610 Municipal Airport Mineral Wells Texas 76067 817 325 2517 Bendix Avionics Division 2100 N W 62nd Street Fort Lauderdale Florida 33310 305 776 4100 Collins General Aviation Division Rockwell International Cedar Rapids Iowa 52406 319 395 3625 King Radio Corporation 400 N Rogers Road P O Box 106 Olathe Kansas 66061 913 782...

Page 6: ... Narco Avionics Inc 270 Commerce Drive Fort Washington Penna 19034 215 643 2900 Avco Lycoming Avco Lycoming Division Williamsport Penna 17701 Environmental Systems Heater and Air Conditioner Janitrol Aero Division 4200 Surface Road Columbus Ohio 43228 614 276 3561 Sanden International U S A Inc 10710 Sanden Drive Dallas Texas 75238 Fuel Pumps Lear Siegler Incorporated 17602 Broadway Avenue Maple H...

Page 7: ...o 44035 216 323 4676 Propellers Hartzell Propeller Incorporated 1025 Roosevelt Avenue Piqua Ohio 45356 513 773 7411 Propeller Synchrophaser Tools Air Conditioning Turbocharger Wheels and Brakes Hartzell Propeller Fan Company 910 South Downing Street Piqua Ohio 45356 513 773 7411 Kent Moore Corporation Service Tool Division 1501 South Jackson Street Jackson Michigan 49203 517 784 8561 Airesearch In...

Page 8: ...R PUBLICATIONS PA 31P 350 Parts Catalog Continuous Inspection 761776 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 761 786 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 1A8 Introduction Page 7 Issued April 25 1983 ...

Page 9: ...GHING TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACTICES AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS NAVIGATIONAND PITOT STATIC OXYGEN SYSTEM AEROFICHE GRID NO 1Bl 1B4 1D11 1El IE1 1E9 1E13 1E13 1E20 1G1 1H11 2B1 2B4 2B12 2C17 2D1 2H...

Page 10: ... PANELS AND MULTI PURPOSEPARTS STRUCTURES DOORS FUSELAGE NACELLES STABILIZERS WINDOWS WINGS PROPELLER STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM STARTING TURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT lA10 117 3J1 3J3 3K1 4B1 4C1 4C 4C7 4D3 4D16 4E10 4F5 4F8 4G7 4G17 4H18 411 4111 4121 4J1 5B1 5E1 Introduction...

Page 11: ...rylock Rivet Removal 1G6 20 4 Hose Line Markings 1G8 20 5 Flareless Tube Fittings 1G9 20 6 Spray Patterns 1G17 20 7 Improper Spray Technique 1G19 20 8 Spray Technique 1G20 20 9 Spraying Corners 1G20 21 1 Pressurization System Schematic Garrett 1H22 21 2 Cabin Pressure Control System Schematic Garrett 1H23 21 3 Safety and Outflow Valves 112 21 4 Cabin Air Pressure Outflow Valve Controller Schematic...

Page 12: ...Inspection Points Air Conditioning System Typical 1L15 23 1 Emergency Locator Transmitter Schematic Narco 2B9 23 2 Portable Folding Antenna Narco 2B9 23 3 ELT Using Fixed Aircraft Antenna Narco 2B120 23 4 Avionics Master and Emergency Switch Circuit 2B120 24 1 Kelvin Low Resistance Bridge 2B21 24 2 Electrical Power Distribution System Typical 2B22 24 3 Lamar Model B 00382 1 Typical System Applicat...

Page 13: ...2 27 27 Flap Transmission Exploded View 2G2 27 28 Flap Transmission Measurements 2G5 27 29 Checking for Wormier Wear 2G7 27 30 Flap Rigging Adjustments 2G11 28 1 Fuel System Schematic 2H8 28 2 Fuel Cell Installation Inboard 2H11 28 3 Fuel Cell Installation Outboard 2H12 28 4 Fuel Cell Installation Nacelle 2H13 28 5 Fuel Valve Drain Plate 2H11 28 6 Fuel Cell Tie Detail 2H17 28 7 Installation of Fue...

Page 14: ...uffed Area and Patch 3B22 30 10 Applying and Stitching Fabric 3B22 30 11 Placing and Stitching Gum 3B24 30 12 Removing Trapped Air 3B24 30 13 MaskingRepair 3B21 30 14 Applying Neoprene Putty 3B24 30 15 Windshield Wiper 3C8 30 16 Typical Use of Dial Indicator 3C12 30 17 Centering of Brushes on Slip Rings 3C12 30 18 Modular Brush Assembly Wear Check 3C13 30 19 Angle of Contact Brushes to Slip Rings ...

Page 15: ...2 24 Adjusting Main Gear Down Light Switch 3F23 32 25 Gear Warning Switches Installation 3F24 33 1 Landing Taxi Light Installation 3G21 33 2 Logo Light Assembly Adjustments 3H2 34 1 Instrument Air System Installation Typical 3H9 34 2 Pitot Static Installation 3H10 35 1 Oxygen System Installation 311 35 2 Oxygen System Installation for FAR 135 Certification 315 35 3 Oxygen Tubing Installations 3112...

Page 16: ... 5 Forward Baggage Door Assembly 4B 19 52 6 Nacelle Locker Door 4B21 52 7 Door Ajar Switch 4B24 54 1 Nacelle Assembly 4C6 55 1 Empennage Installation 4C 1 55 2 Elevator Balancing 4C18 55 3 Friction Measurement 4C20 55 4 Rudder Balancing 4C24 55 5 Rudder Balance Weight Location 4C24 56 1 Windshield Installation 4D8 56 2 Fabricated Sealant Tools 4D 1 56 3 Storm Window Installation 4D13 57 1 Wing Ins...

Page 17: ...0 Checking Harness Lead Continuity 4H7 74 11 Checking Harness Lead Insulation Resistance 4H7 74 12 Modified Pliers 4H7 74 13 Removing Spring From Lead Assembly 4H7 74 14 Assembly Tool 4H9 74 15 Using Assembly Tool 4H9 74 16 Ferrule Positioned Under Braid 4H10 74 17 Ferrule Seating Tool 4H10 74 18 Position of 11 8627Kit and Contact Spring at Start of Installation 4H11 74 19 Position of 11 8627 Kit ...

Page 18: ...E10 95 9 Fabricated Tool Checking Main Gear Toe In Adjustment 5El 1 95 10 Tire Balancer 5E12 95 11 Fabricated Tool Checking Nose Wheel Alignment 5E13 95 12 Suggested Design for Seal Plate Plugs and Caps for Combustion Leakage Test 5E14 95 13 Charging Stand 5E14 95 14 Fabricated Pressure Test Adapters 5E15 95 15 Cabin Pressure Test Unit Typical 5E15 95 16 Test Gauge Manifold Set 5E16 95 17 Torque W...

Page 19: ...Electrolyte Temperature Corrections 2C8 2406 Specific Gravity Temperature Correction 2C9 2407 Recommended Discharge Rate 2C9 2408 Electrolyte Freezing Points 2C10 2409 Capacity Ratings at Discharge Rate 2C12 2410 Electrolyte Freezing Points 2C12 2411 Circuit Load Chart 2C13 2701 Troubleshooting Surface Controls 2D6 2702 Control Cable Rigging Tension vs Temperature 2D19 2801 Troubleshooting Fuel Sy...

Page 20: ...m Oxygen System Component Limits Cabin Instruments Display List of Materials Thermoplastic Repairs Types of Metal Corrosion Elevator Balance Specifications Rudder Balance Specifications Aileron Balance Specifications Propeller Specifications Troubleshooting Actuator Chart Engine Synchrophaser Troubleshooting Engine Troubleshooting Fuel Pressure Gauge Troubleshooting Fuel Flow Gauge Troubleshooting...

Page 21: ...f Consumable Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Electrical Wiring Coding Electrical Symbols GRID NO 5B4 5B16 5B 17 5 10 5B20 5B21 5B22 5C2 5C3 5C4 1A21 Introduction Page 19 Issued April 25 1983 ...

Page 22: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 1A22 ...

Page 23: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL 1 THIS PAGE INTENTIONALLY LEFT BLANK 1A23 ...

Page 24: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 1A24 ...

Page 25: ...CHAPTER AIRWORTHINESS LIMITATIONS 1B1 ...

Page 26: ...ENANCE MANUAL CHAPTER 4 AIRWORTHINESS LIMITATIONS TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 4 00 00 4 00 01 AIR WORTHINESS LIMITATIONS General 1B3 1B3 1B2 4 Cont Effec Page Issued April 25 1983 ...

Page 27: ... Parts 91 163 and 135of the Federal Aviation Regulations NOTE Refer to the LIMITATIONS in the Pilot s Operating Handbook and FAA Approved Flight Manual for a detailed delineation of theflight limitations of the airplane The mandatory replacement time and or inspection intervals of life limited parts are contained in Chapter 5 of this manual END 1B3 4 00 01 Page 4 01 Issued April 25 1983 ...

Page 28: ...CHAPTER TIMELIMITS MAINTCHECKS 1B4 ...

Page 29: ...1B14 5 21 05 Revisions 1B 15 5 21 06 Away From Home Station Requirements B16 5 21 07 Event No 1 1B17 IR 12 85 5 21 08 Event No 2 1C4 2R 12 85 5 21 09 Special Inspections 1C13 2R 12 85 5 21 10 Special Inspections as Required Upon Condition 1C16 2R 12 85 5 21 11 Operational Inspection 1C17 5 21 12 Inspection Notes 1CI9 1R 12 85 5 21 13 Event Inspection Record and Sign Off Sheet 1C20 1R 12 85 5 21 14...

Page 30: ...rplane every 200 hours one complete cycle Also included are various special inspections required at specific service times other than the 100hour events This type of inspection was selected by Piper Aircraft Corporation to provide greater utilization of the aircraft through the use of this planned inspection program NOTE In addition to inspection intervals required in the Event Inspections thefoll...

Page 31: ...Service Bulletins are of special importance and should be complied with promptly These are sent to the latest registered owners Piper Service Centers and Dealers Service Letters deal with product improvements and service hints pertaining to the aircraft They are sent to registered owners so they can properly service the aircraft and keep it up to date with the latest changes Owners should give car...

Page 32: ... inspections will be entered on the Discrepancy Record The person conducting the inspection will advise the owner operator of the discrepancies found during the inspection and entered on the Discrepancy Record Discrepancies which affect the airworthiness of the airplane will require the necessary corrective action to be accomplished before the airplane is returned to service The Piper Programmed I...

Page 33: ...rent status of the aircraft inspections Each event will be recorded in the Event Inspection Record and Signoff Sheet a EVENT No 1 The following inspections are to be performed at odd hundred flying hour intervals i e every 100 300 500 etc hours 1 Left Propeller Detailed 2 Left Engine Detailed 3 Left Turbocharger Detailed 4 Right Propeller Detailed 5 Right Engine Detailed 6 Right Turbocharger Detai...

Page 34: ...has been given to the owner operator and appropriate entries have been made in the aircraft and engine logbooks 5 Programmed Cycle Inspection Record and Signoff Sheet is prepared upon completion of two event inspections 200 flying hours The cycle inspection consists of ten items which determine that the cycle paperwork and inspection records are in order before starting on the next cycle The cycle...

Page 35: ...AD Notes and contains the following a AD note number b Compliance date c Aircraft hours d Method of compliance e Work order number FAA approved repair stations only f Certificate number and signature of person accomplishing the compliance 9 Equipment Change Record ECR is a form to record equipment changes which allows the control of equipment times for inspection or overhaul replacement By use of ...

Page 36: ...t to a maintenance base defined as 10 percent of the Ell Any extension time used must be deducted from the next EII to maintain the inspection schedule 6 Test Operation of aircraft components appliances or systems to evaluate functional performance 7 Operational Test A powered system run with a system component installed in an aircraft to verify that the component is in operable condition Each ope...

Page 37: ...cheduled interval bench test The authorized person who reinstalls the component performs necessary operational tests to ensure that the system is functioning properly and enters test data in the permanent aircraft records Serviceable parts that were issued will be identified in the aircraft permanent records 10 Maintenance Inspection overhaul repair preservation and the replacement of parts exclud...

Page 38: ...office A duplicate copy should be maintained in this manual Name Address Street City State Zip Telephone Number Any change in personnel responsible for scheduling the inspection program will be added with the appropriate information on a separate sheet of paper and the original copy sent to the local FAA GADO office while a duplicate copy is attached behind this part The previous information sheet...

Page 39: ...ibility of the manufacturer No changes can be made to this Inspection Program unless prior notice is given to the responsible F A A District Office who in turn must approve of the change prior to its enactment A record of all revision will be maintained by the owner operator on the revision of this manual RECORD OF NORMALREVISIONS REV NO REV APPROVAL DATE PAGE NO INSERTED BY DATE 1B15 5 21 05 Page...

Page 40: ...ied on this type aircraft The results of the inspection will be noted on the proper Sign Off Sheets which are then brought back to the home base The pilot will be responsible for all inspection forms and work sheet entries with mechanics and or inspector s signature and identification Discrepancies affecting the airworthiness of the airplane when the airplane is away from the local station will be...

Page 41: ...scription information LEFT ENGINE DETAILED See Chapter 71 Refer to Lycoming Service Bulletin 469 CAUTION Ground magneto primary circuit before working on engine 1 Remove engine cowl 2 Clean and inspect cowling for cracks distortion and loose or missing fasteners 3 Drain oil sump Drain while engine is warm See Inspection Note 1 4 Clean suction oilstrainer at oil change Inspect strainer for foreign ...

Page 42: ...7 Inspect induction alternate air system for condition and operation 28 Inspect intake seals for leaks and flanges for tightness 29 Inspect condition of flexible fuel lines 30 Inspect fuel system for leaks 31 Inspect fuel pump for operation engine and electric 32 Replace hydraulic filter element check element for contamination 33 Inspect hydraulic pump and gasket for leaks See Inspection Note 1 34...

Page 43: ...nifoldfor deterioratedhose loose connections leaks or obstructions 15 Check overboost relief valve for security of mounting boss 16 Check intercooler condition and security 17 Check intercooler ducts for condition and security 18 Reinstall engine cowl See Inspection Note 10 RIGHT PROPELLER DETAILED See Chapter 61 1 Remove and inspect spinner and back plate 2 Inspect blades for nicks and cracks 3 C...

Page 44: ...es and clamps Inspect terminals for security and cleanliness 18 Inspect ignition harnesses and insulators high tension leakage and continuity 19 Inspect magneto main points for clearance Set at 0 016 in 20 Inspect magneto retard points for proper retard angle 15 maintain clearance at 0 016 0 004 in 21 Inspect magneto for oil leakage 22 Inspect breaker felts for proper lubrication 23 Inspect distri...

Page 45: ... compressor clutch security and wiring Clean any traces of oil from the clutch surface RIGHT TURBOCHARGER DETAILED See Chapter 81 1 Visually inspectsystem for oil leaks exhaust system leaksand generalcondition See InspectionNote 1 2 Inspect the compressor wheel for nicks cracks or broken blades 3 Inspect for excess bearing drag or wheel rubbing against housing 4 Inspect turbine wheel for broken bl...

Page 46: ...on 12 Inspect engine exhaust shield for cracks severe buckling or loose rivets at the flange area 13 Remove drain and clean fuel filter bowl and screen Drain and clean at least every 90 days 14 Inspect fuel cells and lines for leaks and water 15 Check to ascertain that the fuel tanks are marked for capacity and minimum octane rating 16 Check operation and pressure of electric fuel pumps 17 Inspect...

Page 47: ...and strobe lights for broken lenses and operation I LANDING GEAR ROUTINE See chapter 32 maintenance manual Refer to Piper Service Bulletin 845 LEFT RIGHT NOSE 1 2 3 4 5 l 6 7 8 9 10 Check oleo strut for proper extension Inspect tire for cuts uneven or excessive wear and slippage Check tire pressure psi Inspect brake and hydraulic lines for damage and security Check gear leg for damage Inspect gear...

Page 48: ...Within the radome inspect the radar and glide slope antenna wave guide and receiver transmitter for condition and security of mounting if installed 10 Inspect bulkheads and stringers for damage condition and corrosion 11 Inspect left and right pitot mast security of mounting 12 Inspect heater and heater fuel regulator and filter for fuel or fume leaks 13 Inspect heater fuel lines and valve for lea...

Page 49: ...trolled air leaks 15 Lubricate fuselage area per lubrication charts in Chapter 12 16 Replace inspection plates panels and floor panels CABIN COCKPIT DETAIL 1 Remove inspection panels and plates and floorpanels 2 Inspect upholstery for tears 3 Inspect pilot and copilot seats and seat belts for damage security and operation 4 Inspect trim operation and indication for full travel both mechanical and ...

Page 50: ...pilot roll servo for security and condition of bridle cables and wiring Refer to approved autopilot manual 30 Check all lights for operation replace bulbs as required 31 Check pilot s storm window for condition operation and seal 32 Perform operational test of microphones and cabin speaker 33 Check gear warning horn and lights while on jacks 34 Lubricate cabin and cockpit area per lubrication char...

Page 51: ...zontal stabilizer attachments 13 Inspect elevator and tab hinge bolts and bearings for excessive wear 14 Inspect elevator stop screws and nuts for damage looseness or evidence of movement check for proper torque of jam nuts 15 Inspect elevator balance spring tension 16 Inspect elevator trim mechanism condition and operation 17 Inspect rudder elevator cables and trim cables for correct tension and ...

Page 52: ...tin 469 CA UTION Ground Magneto Primary Circuit before working on engine 1 Remove engine cowl 2 Clean and inspect cowling for cracks distortion and loose or missing fasteners 3 Drain oil sump Drain while engine is warm See Inspection Note 9 4 Clean suction oil strainer at oil change Inspect strainer for foreign particles 5 Change full flow cartridge type oil filter element Inspect element for fore...

Page 53: ...ow check nozzles 27 Inspect induction alternate air system for condition and operation 28 Inspect intake seals for leaks and flanges for tightness 29 Inspect condition of flexible fuel lines 30 Inspect fuel system for leaks 31 Inspect fuel pump operation engine and electric 32 Replace hydraulic filter element Check element for contamination 33 Inspect hydraulic pump and gasket for leaks See Inspec...

Page 54: ...harger 14 Inspectfuel injectionnozzlereference manifoldfor deterioratedhose loose connections leaksor obstructions 15 Check overboost relief valve for security of mounting boss 16 Check intercooler condition and security 17 Check intercooler ducts for condition and security 18 Reinstall engine cowl See Inspection Note 10 RIGHT PROPELLER DETAILED See Chapter 61 1 Remove and inspect spinner and back...

Page 55: ...ounds See Inspection Notes 3 and 4 17 Inspect wiring to engine and accessories Replace damaged wires and clamps Inspect terminals for security and cleanliness 18 Inspect ignition harnesses and insulators high tension leakage and continuity 19 Inspect magneto main points for clearance Set at 0 016 in 20 Inspect magneto retard points for proper retard angle 15 maintain clearance at 0 016 0 004 in 21...

Page 56: ... air conditioner drive belt Refer to Chapter 21 53 Inspect compressor clutch security and wiring Clean any traces of oil from the clutch surface RIGHT TURBOCHARGER DETAILED See Chapter 81 1 Visually inspect system for oil leaks exhaust system leaks and general condition See Inspection Note 1 2 Inspect the compressor wheel for nicks cracks or broken blades 3 Inspect for excess bearing drag or wheel...

Page 57: ...ileron and trim cables pulleys and bellcrank for damage and operation 5 Inspect aileron balance weight and arm for security and condition 6 Inspect flaps and attachments for damage and operation 7 Inspect wing flap transmission 8 Inspect flap actuator cable 9 Inspect wing attachment bolts and brackets for security 10 Inspect engine mount attaching structure for security and condition 11 Inspect en...

Page 58: ...ty 14 Inspect downlock for operation and adjustment 15 Inspect main gear lock cable assemblies for corrosion and fraying 16 Inspect gear doors and attachments for security 17 Check warning horn and light for operation 18 Retract gear and inspect operation 19 Retract gear and inspect doors for clearance and operation 20 Inspect anti retraction system operation 21 Inspect actuating cylinder for leak...

Page 59: ...for proper extension Check for proper fluid level as required 2 Inspect nose gear steering control and travel 3 Inspect wheel for alignment 4 Inspect tire for cuts uneven or excessive wear and slippage 5 Remove wheel clean inspect and repack bearings per lubrication charts in Chapter 12 6 Inspect wheel for cracks corrosion and broken bolts 7 Check tire pressure 8 Inspect shimmy dampener operation ...

Page 60: ... security CABIN COCKPIT ROUTINE 1 Check pilot seat for operation and damage 2 Check copilot seat for operation and damage 3 Check condition of oxygen mask 4 Check instrument lights for operation 5 Check control wheel for operation See Special Inspection 6 Check pilot and copilot seat belts and shoulder harnesses for proper security operation and condition CABIN MAIN ROUTINE 1 Check upholstery for ...

Page 61: ...tober 1981 LANDING GEAR INSPECTION Refer to Piper Service Bulletin 845 400 HOUR LEFT AND RIGHT ENGINE Lycoming requires a valve inspection be made after every 400 hours of operation NOTES At every 400 hours of engine operation remove rocker box covers and check for freedom of valve rockers when valves are closed Look for evidence of abnormal wear or broken parts in area of valve tips valve keeper ...

Page 62: ...GHT WING Inspect condition of bolts used with flap and aileron hinges replace as required FUSELAGE FORWARD Overhaul or replace heater fuel valve as required NOSE GEAR refer to Piper Service Bulletin 845 Inspect drag and side brace link bolts for wear replace as required LEFT AND RIGHT PROPELLER Remove propeller remove sludge from propeller and crankshaft LEFT AND RIGHT WING 1 Inspect clean and lub...

Page 63: ... Overhaul or replace starter at engine T B O 7 Overhaul or replace fuel injector at engine T B O 8 Complete overhaul or replacement of turbocharger at engine T B O 9 Complete overhaul or replacement of engines per engine MFG recommendations see latest Lycoming Service Instruction No 1009 MISCELLANEOUS INSPECTIONS RIGHT ENGINE 1 Inspect air conditioner compressor oil level whenever system is charge...

Page 64: ...throughout wings 3 Wing spar webs bulkheads nacelle skins and attachments fire wall skin and wing and fuselage stringers for any signs of overstress or damage 4 An alignment check to clarify any doubt of damage SEVERE TURBULENCE INSPECTION Check same items and locations as stated in Hard or Overweight Landings along with following 1 Top and bottom fuselage skins for loose or missing rivets and wri...

Page 65: ...ration and indication 11 Checkheateroperation 12 Check air conditioner operation if installed 13 Check propeller deicer operation 14 Engine Run Up a Propeller and mixture levers full forward b Throttle 1500RPM c Propeller feathercheck maximum 500 RPM decrease d Throttle 2300 RPM e Magneto check 175RPM maximum drop 50 RPM decrease f Propeller governing check g Alternator output check h Check all en...

Page 66: ... ENGINE SERIAL NO Left Right PROPELLER SERIAL NO Left Right OPERATIONAL INSPECTION cont POST INSPECTION RUN UP 1 Return aircraft to maintenance area 2 Check engine for general condition fuel and oil leaks 3 Reinstall engine cowlings 1C18 5 21 11 Page 5 37 Revised December 16 1985 ...

Page 67: ...ve 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 are 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 parts that do not conform with limits shown in the latest revision f...

Page 68: ... responsibility of the individual performing the inspection and must be made in accordance with all applicable current Federal Aviation Regulations Always check for and use only current information 2 The signatures signify that this aircraft has been thoroughly inspected and found air worthy in accordance with all appropriate current Federal Aviation Regulations and that appropriate entries have b...

Page 69: ... 2 1 2 2 1 2 1 2 1 2 1 2 1 2 1 2 INSP 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 A C TIME DATE W O SIGNATURE CERTIFICATE I 1C21 5 21 13 Page 5 40 Revised December 16 1985 ...

Page 70: ...PER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL EVENT 1 2 1 2 1 2 1 2 1 INSP 4700 4800 4900 5003 5100 5200 5300 5400 5500 A C TIME DATE W O SIGNATURE CERTIFICATE 1C22 5 21 13 Page 5 41 Revised December 16 1985 ...

Page 71: ... STATIONF C C LICENSES IN AIRCRAFT AND PROPERLY DISPLAYED 6 AIRCRAFT EQUIPMENT LIST WEIGHT AND BALANCE FAA FORM 337 IF APPLICABLE ARE IN AIRCRAFT AND IN PROPER ORDER 7 APPLICABLE MANUFACTURER S SERVICE INFORMATION HAS BEEN COMPLIED WITH 8 APPLICABLE FAAAIRWORTHINESS DIRECTIVES ARE COMPLIED WITH 9 PIPER CONTINUOUS INSPECTION RECORDS IN ORDER AND PROPERLY SIGNED OFF 10 OUTSTANDING CONDITIONS HAVE BE...

Page 72: ...DISCREPANCY RECORD A C HOURS SIGNATURE AND CERTIFICATE NO DISCREPANCY SIGNATURE DATE CORRECTIVE ACTION W O DATE z z ...

Page 73: ...ERIAL NUMBER REGISTRATION NUMBER ENGINE SERIAL NO Left Right PROPELLER SERIAL NO Left Right DISCREPANCY RECORD A C HOURS DISCREPANCY SIGNATURE DATE CORRECTIVE ACTION W O SIGNATURE AND CERTIFICATE NO DATE ...

Page 74: ...ER REGISTRATION NUMBER ENGINE SERIALNO Left Right PROPELLER SERIALNO Left Right SERVICE PUBLICATION COMPLIANCE RECORD SIGNATURE AND CERTIFICATE MANUFACTURER PUBLICATION NUMBER COMPLIANCE DATE A C HOURS W O 2 0 i ...

Page 75: ...SERVICE PUBLICATION COMPLIANCE RECORD MANUFACTURER PUBLICATION NUMBER COMPLIANCE DATE A C HOURS W O SIGNATURE AND CERTIFICATE ...

Page 76: ...SERIALNUMBER REGISTRATION NUMBER ENGINE SERIALNO PROPELLER SERIALNO Left Left Right Right FAAAIRWORTHINESS DIRECTORIES COMPLIANCE RECORD z n ...

Page 77: ...RIAL NUMBER REGISTRATION NUMBER ENGINE SERIAL NO PROPELLER SERIAL NO Left Left Right Right ECR EQUIPMENT CHANGE RECORD RECORD DATE A CHRS REMOVED PART SERIAL INSTALL PART SERIAL SIGNATURE ANDDERTIFICATE z ...

Page 78: ...2 ELECTRICAL LEAD LINES TO ENGINE INSTRUMENTS 13 HYDRAULIC LINESAND CONTROL CABLES 2 10 11 12 21 16 14 ELECTRICAL SHELVES REARAND OVERHEAD HYDRAULIC POWER PACK OXYGEN BOTTLE RECEIVERDRYER 15 NOSE BAGGAGE DOOR BATTERY BUS RADIOS TOW BAR AIR CONDITIONING SERVICEVALVE HIGH NOSECONELATCHRELEASE ACCESS 16 AIR CONDITIONEREVAPORATOR COVER DRAIN 17 AUXILIARY POWER RECEPTACLE 18 OXYGEN CYUNDER RECHARGE 19 ...

Page 79: ...L LEADS HYDRAULICLINES PNEUMATIC LINES CONTROL CABLES 16 SPAR SPUCE 17 TRIM DRUMS AND CABLES 18 ELECTRICALLEADS PRESSURIZATION AIR CONTROL BOX 5 1 AUXILIARYPOWER RECEPTACLE 2 OXYGEN CYLINDERRECHARGE 3 ELECTRICALLEADS CONTROL CABLES NOSE GEAR STEERING CABLE MISCELLANEOUS AIR AND FLUID LINES 4 ELECTRICALFUELPUMP CROSSFEED VALVE LEFT ONLY EMERGENCYSHUTOFF VALVE FIREWALL SHUTOFF VALVE GASCOLATOR WING ...

Page 80: ...RANSMITTER 18 AILERON CABLE PULLEYS 19 AILERON BELLCRANK 20 FUEL CELL VENT LINE 21 AILERON CABLE FAIRLEADS 22 AILERON CABLES AND RUB BLOCKS FLAP TRANSMISSION 23 LANDING GEAR ATTACHMENTS 24 MAIN LANDING GEAR 25 FUEL CELL VENT 26 FUEL CELL DRAIN 27 LANDING GEAR SIDE BRACE ATTACHMENTS 28 AILERON TRIM DRUM 29 FUEL LINE 30 FUEL VENT FLOAT VALVE 31 AILERON CABLES 32 FLAP POTENTIOMETERS 33 FLAP POT FLAP ...

Page 81: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 1D9 ...

Page 82: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK ...

Page 83: ...CHAPTER DIMENSIONS AND AREAS 1D1l ...

Page 84: ...AREAS TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 6 00 00 6 00 01 6 00 02 6 00 03 GENERAL Dimensions and Areas Station Reference Lines Access and Inspection Provisions ID13 1D13 1D17 1D17 6 Cont Effec Page 1 Issued April 25 1983 1D12 ...

Page 85: ...n in Figure 6 1 and listed in Chart 601 The serial number plate for the airplane is located near the tail skid The MAA plate is located under the lower front corner of the entrance door The engine number plates are located on the right side of the oil sump THIS SPACE INTENTIONALLY LEFT BLANK 6 00 01 1D13 Page 6 01 Issued April 25 1983 ...

Page 86: ...R CUBIC CARGO CAPACITIES AND WEIGHTS REFER TO PILOT S OP ERATING HANDBOOK 1 4 5 PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL J 5 DIHEDRAL STA 00 Figure 6 1 Dimensions 1D14 6 00 01 Page 6 02 Revised July 28 1983 ...

Page 87: ...olt 100Amp Voltage Regulator Lamar Over Voltage Relay Lamar Fuel Pump Lear Siegler Ayco Lycoming T10 540 V2AD and LT10 540 V2AD 350 2600 Sea Level to 15 000 feet Refer to Pilot s Operating Manual See Lubrication Chart 13 qts THO8A69 100 100LL RSA I 0DB2 D6LN 3200 D6RN 3200 20 0 016 0 004 0 016 0 004 11 D6LN 3200 19 D6RN 3200 Refer to latest issue of Lycoming Service Instruction 1042 017 to 021 1 4...

Page 88: ...n Static Load Nose Wheel Travel Main Wheel Toe In Turning Radius Min Nose Wheel Turning Radius Min Wing Tip Wheel Nose Wheel Main Brake Type Tire Nose Tire Main Tire Pressure Nose Tire Pressure Main 243 gal 238 gal 121 5 gal Hydraulically retractable Combination air and oil MIL H 5606 3 25 in 40 1 Right 40 1 Left 5 degrees 25 ft 3 in 49 6 ft Cleveland Cleveland Cleveland 6 00 x 6 ply rating 6 50 x...

Page 89: ...IONS Refer to Figure 6 3 The access and inspection provisions for the airplane are shown in Figure 6 3 The components to be serviced or inspected through each opening is identified in the illustration by the use of an assigned index reference number All access plates and panels are secured by either metal fasteners or screws CAUTION Before entering the aft section of the fuselage be sure the airpl...

Page 90: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL FACE Figure 6 2 Station References cont 1D18 6 00 03 Page 6 06 Issued July 25 1983 ...

Page 91: ...C CARGO CAPACITIES AND WEIGHTS REFER TO PILOT S OP ERATING HANDBOOK 1 4 5 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 80 DIA 5 DIHEDRAL Figure 6 2 Station References cont 1D19 6 00 03 Page 6 07 Issued July 25 1983 ...

Page 92: ... 2 ELECTRICAL LEAD UNES TO ENGINE INSTRUMENTS 13 HYDRAULIC LINESAND CONTROL CABLES 12 21 16 14 ELECTRICAL SHELVES REAR AND OVERHEAD HYDRAULIC POWER PACK OXYGEN BOTTLE RECEIVERDRYER 15 NOSE BAGGAGE DOOR BATTERYBUS RADIOS TOW BAR AIR CONDITIONING SERVICEVALVE HIGH NOSE CONE LATCH RELEASEACCESS 16 AIR CONDITIONER EVAPORATOR COVER DRAIN 17 AUXILIARY POWER RECEPTACLE 18 OXYGEN CYUNDER RECHARGE 19 BATTE...

Page 93: ...FLAP AMPLIFIER 15 ELECTRICALLEADS HYDRAULIC LINES PNEUMATIC UNES CONTROLCABLES 16 SPAR SPLICE 17 TRIM DRUMS AND CABLES 18 ELECTRICALLEADS PRESSURIZATIONAIR CONTROL BOX 1 12 13 11 7 9 1 AUXILIARY POWERRECEPTACLE 2 OXYGEN CYLINDERRECHARGE 3 ELECTRICALLEADS CONTROLCABLES NOSE GEAR STEERINGCABLE MISCELLANEOUS AIR AND FLUID LINES 4 ELECTRICALFUELPUMP CROSSFEEDVALVE LEFT ONLY EMERGENCYSHUTOFF VALVE FIRE...

Page 94: ...TRANSMITTER 18 AILERON CABLE PULLEYS 19 AILERON BELLCRANK 20 FUEL CELL VENT LINE 21 AILERON CABLE FAIRLEADS 22 AILERON CABLES AND RUB BLOCKS FLAP TRANSMISSION 23 LANDING GEAR ATTACHMENTS 24 MAIN LANDING GEAR 25 FUEL CELL VENT 26 FUEL CELL DRAIN 27 LANDING GEAR SIDE BRACE ATTACHMENTS 28 AILERON TRIM DRUM 29 FUEL LINE 30 FUEL VENT FLOAT VALVE 31 AILERON CABLES 32 FLAP POTENTIOMETERS 33 FLAP POT FLAP...

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Page 97: ...CHAPTER LIFTINGAND SHORING 1E1 ...

Page 98: ...8 181 MAINTENANCEMANUAL CHAPTER 7 LIFTING AND SHORING TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 7 00 00 7 10 00 GENERAL IE3 JACKING 1E3 1E2 7 Cont Effec Page 1 Issued April 25 1983 ...

Page 99: ...g jack pads 2 Position the tail support stand under the tail skid and attach the stand to the tail skid 3 Position the nosejack and jack pad tool P N 71973 2 under the nose section between station 25 75 and 43 35 4 Raise all jacks evenly until all three wheels clear the floor CAUTION If the nose jack and jack pad tool are not used be sure to apply sufficient tail support ballast otherwise the airp...

Page 100: ...CHAPTER LEVELINGAND WEIGHING 1E4 ...

Page 101: ...F CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID SUBJECT TECTIVIITY 8 00 00 8 10 00 8 20 00 8 20 01 8 20 02 8 20 03 GENERAL LEVELING WEIGHT AND BALANCE DATA Weighing Preparation For Weighing Weighing The Aircraft 1E6 1E6 1E7 1E7 1E7 1E8 1E5 8 Cont Effec Page 1 Issued April 25 1983 ...

Page 102: ...lly level the airplane partially withdraw the two leveling screws located on the right side of the fuselage nose section at station 57 00 and 35 00 Place a spirit level on these screw heads and deflate the nose wheel tire or adjust the jack until the bubble of the level is centered 2 To laterally level the airplane place a spirit level across the two center seat rails of the cabin and deflate the ...

Page 103: ...is not recommended and care must be taken to verify all fuel tanks are exactly full and not partially under or over full fuel topped off to bottom of filler neck with airplane in level attitude See Chapter 12 for fuel capacities Temperature will have an effect when weighing the airplane especially if fuel tanks are full and therefore will affect the balance The airplane and scales should be allowe...

Page 104: ...es of all three wheels WARNING If wheels are not blocked the airplane could roll off scales and cause serious injury and damage 4 Release emergency brake 5 If the airplane is to be weighed for weight and balance computations level the airplane per instructions given in the paragraph titled Leveling 6 Record weights on Weight and Balance Report Insure TARE weight weight of chocks blocks or other we...

Page 105: ...CHAPTER TOWINGAND TAXIING 1E9 ...

Page 106: ...NCEMANUAL CHAPTER 9 TOWING AND TAXIING TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SECTION GRID NO SUBJECT EFFECTIVITY 9 00 00 9 10 00 9 20 00 GENERAL 1E11 TOWING 1E12 1R7 83 TAXIING 1E12 E100 9 Cont Effec Page 1 Revised July 28 1983 ...

Page 107: ... other responsible person on the tow turning limits of the nose gear engine starting and shutdown procedures and any other system functions which may be required to properly and safely move the airplane Refer to Figure 9 1 298 WHEEL BASE 8 FT 8 IN NOSE WHEEL TRAVEL 40 Right 40 Left Figure 9 1 Turning Radius and Limits 1Ell 9 00 00 Page 9 01 Revised July 28 1983 ...

Page 108: ...re closed 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 and nose wheel steering A collapsible towbar is located in the nose baggage compartment fastened to the rear bulkhead The towbar is removed by pulling it from the friction retainers TAXIING When it is certain that t...

Page 109: ...CHAPTER PARKINGAND MOORING E13 ...

Page 110: ...NCE MANUAL CHAPTER 10 PARKING AND MOORING TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 10 00 00 10 10 00 10 20 00 GENERAL PARKING MOORING 1E15 1E15 1E15 10 Cont Effec Page 1 Issued April 25 1983 1E14 ...

Page 111: ...used to block the wheels rather than setting brakes 3 Secure the control wheel with the seat belt MOORING The airplane is moored to insure its immovability protection and security under various weather conditions The following procedure gives the proper instructions for mooring this airplane 1 Head the airplane into the wind if possible 2 Block the wheelswith wheel chocks 3 Secure the control heel...

Page 112: ...CHAPTER REQUIREDPLACARDS 1E16 ...

Page 113: ...NTENANCEMANUAL CHAPTER 11 REQUIRED PLACARDS TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 11 00 00 GENERAL 1E18 11 20 00 PLACARDS AND MARKINGS IE 8 11 Cont Effec Page 1 Issued April 25 1983 1E17 ...

Page 114: ...J32g PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL GENERAL PLACARDS AND MARKINGS Figure 11 1 Placards and Decals 1E18 11 20 00 Page 11 01 Revised December 14 1983 ...

Page 115: ...STRUCTION 31 DECAL MOJAVE 32 PLACARD BAGGAGE CAPACITY 33 PLACARD CABINPRESSURE TESTSWITCH 34 PLACARD MIKE PHONEJACKS 35 PLACARD MASTERCAUTION 36 PLACARD ANNUNCIATOR TEST 37 PLACARD ANNUNCIATOR HI LO 38 PLACARD COMPASS ERRATIC 39 PLACARD LUBRICATION 40 PLACARD FUELCONTROL LEFT 41 PLACARD FUELCONTROL RIGHT 42 PLACARD FUELCROSSFEED 43 PLACARD OFF 44 PLACARD ON 45 PLACARD THROTTLE CONTROL 46 PLACARD P...

Page 116: ...CHAPTER SERVICING 1E20 ...

Page 117: ...o Struts 1 F3 12 23 03 Filling Oleo Struts 1F3 12 23 04 Inflating Oleo Struts 1F3 12 23 05 Tires 1 F4 12 23 06 Tire Balancing 1F4 12 24 00 Hydraulic System 1F4 12 24 01 Filling Hydraulic System Reservoir 1F5 12 25 00 Propellers 1F5 12 24 00 Engine Lubrication 1F5 12 24 01 Filling Oil Sump 1F6 12 24 02 Draining Oil Sump 1F6 12 24 03 Oil Filter Full Flow 1F6 12 24 04 Oil Screens Suction 1F6 12 24 05...

Page 118: ...ID NO SUBJECT EFFECTIVITY UNSCHEDULED SERVICING Servicing Air Conditioning System Servicing Electrical System Operation Of External Power Receptacle Servicing Battery Removal Of Induction Air Filter Installation Of Induction Air Filter Alternate Air Door Oxygen System Oxygen System Safety Precautions Filling Oxygen Cylinder 1F17 1F17 1F17 1F17 1F17 1F17 1F17 1F18 1F18 1F18 1F19 1E22 12 Cont Effec ...

Page 119: ...plete refueling through the nacelle tank only CAUTION Never remove wing filler caps when there is fuel in the nacelle tanks DRAINING MOISTURE FROM FUEL SYSTEM To facilitate draining the fuel system filter bowls lines and fuel cells of moisture and foreign matter drains are incorporated in the bottom of each filter bowl in the system crossfeed line and the inboard end of each fuel cell 1 To flush e...

Page 120: ...PROPELLER 15 OIL SUMP DRAIN RIGHT ENGINE 16 BATTERY 17 EXTERNALPOWER SUPPLY 18 AIR CONDITIONING RECEIVER DRYER 19 FILLER NOSE OLEO SHOCK STRUT 20 FILLER OXYGEN 21 TIRE NOSE 22 HEATER 23 RESERVOIR POWER PACK 24 RESERVOIR BRAKESYSTEM 25 AIR VALVE LEFTPROPELLER 26 OIL FILLER LEFTENGINE 27 FUEL FILTERAND DRAIN LEFT 28 FILTER LEFT ENGINE INDUCTION 29 OIL SUMP DRAIN LEFT ENGINE 30 FILTER LEFT HYDRAULIC ...

Page 121: ...wing procedure 1 Gain access to the brake reservoir scupper open the nose baggage door remove the tow bar and screened radio access panel 2 Clean surface around scupper and adjacent aircraft skin with a suitable solvent to remove any foreign matter 3 Apply a bead of sealant 3M EC 750 or equivalent around the scupper Particular attention should be paid to sealing the forward edge of the scupper at ...

Page 122: ...irplane plus full fuel and oil If a strut has less than the required inches exposed determine whether it needs air or oil by rocking the airplane If the airplane settles to its normal position within one cycle after the rocking force is removed the oleo strut requires inflating air If the airplane continues to oscillate after the rocking force is removed the oleo strut requires filling oil WARNING...

Page 123: ...her end of the tube in a conntainer of hydraulic fluid as specified NOTE An air tight connection is necessary between the plastic tube and valve stem Without such a connection a small amount of air will be sucked into the oleo strut during each sequence resulting in an inordinate amount of air bubbles and a prolonged filling operation 5 Extend the oleo strut by pulling down on the wheel Fluid will...

Page 124: ...p center of the tire Rotate the tire 45 and 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 3 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 op...

Page 125: ... disconnecting the supply line from the service valve fitting 5 Reinstall the protective cap on the fitting and install the access panel PROPELLERS The blades should be checked periodically for damage Minor nicks in the leading edge of blades should be filed out and all edges rounded Daily inspection should include examination of blades and spinner for visible damage and grease leakage For further...

Page 126: ...l cut open any spin on type filter for inspection Examine the material trapped in the filter for evidence of internal engine damage such as chips or particles from bearings In new or newly overhauled engines some small particle of metallic shavings might be found these are generally of no consequence and should not be confused with particles produced by impacting abrasion or pressure Evidence of i...

Page 127: ...drain periods after sludge conditions improve SPECTROMETRIC OIL ANALYSIS The use of Spectrometric oil analysis is becoming widespread in the general aviation field It is another useful procedure in the maintenance of moder reciprocating aircraft engines The spectrometric method requires complete understanding of the procedures schedules and interpretation by the maintenance personnel using this sy...

Page 128: ...sed may be found in Lubrication Charts To insure the best possible results from the application of lubricants the following precautions should be observed 1 Use recommended lubricants Where general purpose lubricating oil is specified but unavailable clean engine oil may be used as a satisfactory substitute 2 Check the components to be lubricated for evidence of excessive wear and replace them as ...

Page 129: ...f oil appears on fingers do not add oil If the felt is dry moisten with light oil CA UTION Be careful not to add too much oil because the excess will be thrown off during operation and will cause pitting and burning of the magneto points LUBRICATION CHARTS The lubrication charts consist of individual illustrations for the various aircraft systems and each component to be lubricated is indicated by...

Page 130: ...S WIPE ALL LUBRICATION POINTSCLEAN OF OLD GREASE OIL DIRT ETC BEFORE RELUBRICATING 7 LUBRICATINGOILINTERVALSBETWEENOIL CHANGESAS CAN BE INCREASEDAS MUCHAS 100 ON ENGINES EQUIPPEDWITHFULLFLOW CARTRIDGETYPE OIL FILTERS PROVIDEDTHE ELEMENTIS REPLACEDEACH50 HOURSOFOPERATION SEELYCOMING SERVICEINSTRUCTION NO 1014FORUSEOF DETERGENT OIL NOTES 1 PILOT LUBRICATE TRACK ROLLERSANDSTOPPINSASREQUIRED 2 WHEEL B...

Page 131: ...INTENANCEMANUAL COMPONENT CLOTH AND HYDRAULIC FLUID MIL H 5606 2 CLEAN AND LUBRICATE WHEN EVER LANDINGGEAR AND WHEEL AREA HAS BEENWASHED Figure 12 3 Lubrication Chart Landing Gear Main 1F11 12 28 03 Page 12 13 Revised July 28 1983 ...

Page 132: ...7870 100 HRS 6 DRAG LINK ASSEMBLY AND IDLER LINK MIL G 23827 100 HRS 7 WHEEL BEARINGS SEE SPECIAL INSTRUCTION 3 MOBILGREASE 77 OR AND NOTE 21 MOBILUS EP2 100 HRS 8 UPPER AND LOWER TORQUE LINK MIL G 23827 100 MRS 9 UPPER AND LOWER TORQUE LINKCONNECTING BOLT AND SHIMMY DAMPENER MIL L 7870 100 HRS 10 GEAR HOUSING BUSHINGS MIL G 23827 100 HRS 11 UPLOCK BUSHING MIL L 7870 100 HRS C807 NOTES 1 WIPE EXPO...

Page 133: ...ROD ENDS MIL L 7870 100 HRS 6 AILERON HINGES RIGHT AND LEFT MIL L 7870 100 HRS 7 FLAP TRANSMISSION PIVOT BOLTS AND SENDER ARM MIL L 7870 100 HRS 8 FLAP TRANSMISSION AND SCREW RIGHT AND LEFT ISEE SPECIAL INSTRUCTION 3 MIL G 23827 500 HRS 9 FLAP TRACK RIGHT AND LEFT ALL PURPOSE SUP SPRAY DUPONT NO 5511 50 HRS 10 FLAP TRACK ROLLERS RIGHT AND LEFT MIL L 7870 00 HRS 11 AILERON BELLCRANK CABLE ENDS PIVO...

Page 134: ...CK CONTROL CABLEENDS AND BRAKE CYLINCERENDS MILL 7870 S ELEVATORBELLCRANK PIVOTBOLTS AND CABLE ENDS MIL L 7870 6 RUDDER HORN CABLE ENDS MIL L 7870 7 ELEVATORTRIM ISEE SPECIALINSTRUCTIONS31 MIL G 23827 8 ELEVATORTRIM TAB CONTROLROD ENDS MIL L 7870 MIL L 7870 9 ELEVATORCONTROLROO PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL FREQUENCY 290 1344 5 4 SKETCH B SKETCH C Figure 12 5 Lubrication Chart Contro...

Page 135: ...9 SKETCH A call PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL Page 12 17 Issued April 25 1983 ...

Page 136: ...COMPONENT PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL 12 28 03 Page 12 18 Issued April 25 1983 ...

Page 137: ...servicing and repair of the various components refer to Chapter 39 OPERATION OF EXTERNAL POWER RECEPTACLE The external power receptacle is located on the under side of the nose section below the forward side of the baggage compartment door To avoid any damage to the airplane s electrical system follow the instructions on the access door of the power receptacle SERVICING BATTERY Access to the batte...

Page 138: ... cu ft or 50 cu ft capacities also available for compliance with FAR 135 certification is a 50 cu ft cylinder with an altitude compensated regulator Service and maintenance instructions for the oxygen system may be found in Chapter 35 Safety Precautions and Filling Procedures follow OXYGEN SYSTEM SAFETY PRECAUTIONS The utmost care must be exercised in servicing handling and inspection of the oxyge...

Page 139: ...s cylinder has a pressure lower than the oxygen cylinder in the aircraft do not attempt using it for filling use the storage cylinder that has a pressure higher than the aircraft s cylinder but lower than the others B Open the valve on only the one storage cylinder with the lowest pressure When the pressure indicated on the aircraft s oxygen gauge and charging gauge has become equal close the valv...

Page 140: ...1609 9 1633 9 1658 0 1682 0 1706 0 1730 0 1754 1 1778 1 1802 1 1826 1 1850 1 1874 2 1898 2 1922 2 1946 2 1970 3 1994 3 2018 3 2042 3 2066 4 2090 4 2114 4 Filling Pressure Foi 1850 PSI At NTP 1537 8 1561 9 1585 9 1609 9 1633 9 1658 0 1682 0 1706 0 1730 0 1754 1 1778 1 1802 1 1826 1 1850 1 1874 2 1898 2 1922 2 1946 2 1970 3 1994 3 2018 3 2042 3 2066 4 2090 4 2114 4 2138 4 3162 4 2186 5 2210 5 2234 5...

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Page 145: ...CHAPTER STANDARDPRACTICES AIR FRAME 1G1 ...

Page 146: ... Surfaces 1G12 20 22 03 Carpets 1G12 20 23 00 Cleaning Exterior Surfaces 1G13 20 23 01 Windshield And Windows 1G13 20 23 02 Landing Gear 1G14 20 23 03 Engine Compartment 1G14 1R7 83 20 24 00 PAINTING 1G15 20 24 01 Painting Safety 1G15 20 24 02 Sanding 1G15 20 24 03 Painting Application 1G16 20 24 04 Spray Patterns 1G17 20 24 05 Cleaning Spray Gun IG18 20 24 06 Spray Techniques 1G18 20 24 07 Aircra...

Page 147: ...RACTICES AIRFRAME cont TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 20 24 00 20 24 17 20 24 18 20 25 00 20 26 00 PAINTING cont Storage Painting Facilities Waxing Decals 1H7 1H7 1H7 1H8 1G3 20 Cont Effec Page 2 Issued April 25 1983 ...

Page 148: ...pported during a tightening operation Any instructions furnished by the manufacturer must be followed explicitly When it is necessary to use a special extension or adapter wrench together with a torque wrench a simple mathematical equation must be worked out to arrive at the correct torque reading Following is the formula to be used Refer to Figure 20 T Torque desired at the part A Basic lever len...

Page 149: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL C A Figure 20 1 Torque Wrench Extension ONLY CORRECTMETHOD Figure 20 2 Method of Installing Rod End Bearings 1G5 20 10 01 Page 20 02 Issued April 25 1983 ...

Page 150: ...mage the sheets It is recommended that a small center drill be use 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 See Views 2 and 3 3 Pry the remainder of the locking collar out of the rivet head with the drift pin See View 3 4 Drill nearly through the head of the rivet using a drill the same size as the rivet ...

Page 151: ...f flareless tube fittings eliminates all tube flaring another operation referred to as presetting is necessary prior to installation of a new flareless tube assembly which is performed as follows 1 Cut the tube to the correct length with the ends perfectly square Deburr the inside and outside of the tube Slip the nut then the sleeve over the tube Step 1 2 Lubricate the threads of the fitting and n...

Page 152: ...TWO COTTON BRAIDS IMPREGNATED WITH SYNTHETICCOMPOUND ...

Page 153: ... CAUTION DO NOT USE OIL OR GREASE SLEEVE ...

Page 154: ... Gasoline and Oil Resistant Oxygen Ribbon Dope Thread Sealant Permacel 412 Pitot and Static TT A 580 JAN A 669 Anti Seize Compound White Lead Base NOTE Lubricate engine fittings only with the fluid contained in the particular lines TUBE IN 1 3 1 5 3 1 5 3 1 CHART 2002 MAXIMUM DISTANCE BETWEEN SUPPORTS FOR FLUID TUBING EOD DISTANCE BETWEEN SUPPORTS IN N ALUMINUM ALLOY STEEL 8 9 1 2 11 1 2 16 12 14 ...

Page 155: ...able to use a mild soap and water solution Loose dirt should be flushed away with clean water Harsh abrasive or alkaline soaps or detergents could cause corrosion or make scratches in the finish Use naphtha and a soft cloth to remove stubborn oil and grease Any good automotive wax can be used to preserve the painted surfaces Soft cleaning cloth or chamois should be used to prevent scratches when c...

Page 156: ...ent cleaners require adequate ventilation 2 Clean side panels and seats with a stiff bristle brush and vacuum where necessary 3 Leather material should be cleaned with saddle soap or a mild soap and water WOOD SURFACES Wood surfaces may be cleaned with any good household liquid or spray cleaner and polish manufactured for this purpose CARPETS Use a small whisk broom or vacuum to remove dirt For so...

Page 157: ...soap and water or a 50 50 solution of isopropanol and water Do not use plastic cleaners on glass windshields Do not use any abrasive materials strong acids or bases methanol or Methyl Ethyl Ketone Use a soft cloth or sponge in a straight rubbing motion Do not rub harshly CAUTION Do not use gasoline alcohol benzene carbon tetrachloride thinner or window cleaning sprays 3 Rinse thoroughly and dry 4 ...

Page 158: ...ion Chart ENGINE COMPARTMENT Before cleaning the engine compartment place a plastic cover or similar material around the pressure pump inlet filter to prevent any solvent from entering these units 1 Place a large pan under the engine to catch waste 2 With the engine cowling removed spray or brush the engine with solvent or a mixture of solvent and degreaser as desired It may be necessary to brush ...

Page 159: ...whatever is handy Almost any kind of cover will either smother the fire or at least contain it until a fire extinguisher can be brought to the can Another safety factor is the importance of proper air movement in the spray area A properly designed spray booth has an air movement system that not only keeps the air circulating but removes all of the solids and solvents Since all the materials used i...

Page 160: ...o Cleaning General A large majority of paint strippers metal brighteners and solvents will either attack the exposed sealant the anti static coatings on the glass or the exposed plastic Contact with these materials may damage the windshield to the point of replacement being necessary WARNING Aircraft should be grounded before painting to insure that no static electricity charges could build up and...

Page 161: ...NS Be sure the paint is thinned sufficiently Do not exceed paint manufacturer s specifications The use of a Zahn cup and stop watch is recommended to check the viscosity Malfunctions Spitting can be caused by a dried out packing around the material needle valve lubricate with a few drops of light oil dirt between the body of the gun and the fluid nozzle seat or a loose or defective nut attaching t...

Page 162: ... the gun until the thinner appears clear NOTE Remove pressure from equipment before beginning cleanup Then soak only the nozzle in thinner to further clean the head Lubricate the air valve stem and all the packings with light oil Tighten packing nuts finger tight only CA UTION Do not allow material to remain in gun after use However if the passages should become plugged up with acrylic lacquer dis...

Page 163: ... one pass of the gun will be typicall about 10 to 12 inches wide thicker in the middle and tapering off at each end In order to get a good even build up of finish spray on the first pass then come back with the gun on the return pass overlapping all but about two or three inches of this first pass The third pass will overlap all but about two or three inches of the second pass Continue this overla...

Page 164: ...RRECT THE PAINT SPRAY GUN MUST BE MOVED PARALLEL TO THE SURFACE IF THE GUN IS MOVED IN AN ARC THE SPRAY PATTERNWILL BE THICKIN SOME SPOTSAND THIN IN OTHERS Figure 20 8 Spray Technique Figure 20 9 Spraying Comers 1G20 20 24 06 Page 20 17 Issued April 25 1983 ...

Page 165: ...er across the fuselage and spanwise on the vertical and horizontal tail surfaces andthe wing After the primer has cured for the proper time and is ready to receive the top coats the same sequence is used to spray on the finish Spray the tack coat on the bottom surfaces starting at the center of the fuselage spraying across it then out the horizontal surfaces spanwise Spray the tack coat on the top...

Page 166: ...ent has been loosened from the bottom 4 After being certain that every bit of the pigment is in suspension box the material by pouring it back and forth between the two containers until it is THOROUGHLY mixed If unable to get a color match using standard methods there are three components which may be varied A The spray pressure B The amount of thinner C The number of coats If metallic material is...

Page 167: ... this second coat will probably run or sag The same will happen if the paint is applied to a cold skin when the air is warm The pressure pot should have a slow moving agitator to keep the pigments from settling out during spraying A fast agitation creates tiny air bubbles which are carried to the surface being sprayed High temperatures cause polyurethane to cure rapidly while low temperatures allo...

Page 168: ...ly metallic colors use 65 PSI Apply a light medium tack coat Allow to set up for 20 minutes Repeat for a second coat Then reduce 15 with 8485S 17 18 seconds in 2 Zahn cup and apply a third light medium coat Another light medium coat of the reduced paint may be added After drying this may be clear coated with 500S clear NOTE Drying time with 1895 accelerator is 2 4 hours tape free Without accelerat...

Page 169: ...n 48 hours NOTE Use primer within 6 hours of mixing Discard any remaining mixture E Mix Ranthane color according to manufacturer s directions and apply within 48 hours of priming Spray one very thin mist coat Let dry 15 minutes then apply a full wet coat and allow to dry May be taped after curing for 5 hours NOTE Use mixed colors within 4 hours Discard any remaining mixture F Trim and lettering ma...

Page 170: ... If cratering is encountered during application anti crater solution may be added to the primer solution not to exceed one ounce per gallon of catalyzed thinned primer solution Allow catalyzed primer to stand for a minimum of thirty minutes before application C Urethane Enamel Thoroughly mix equal parts of urethane enamel and enamel catalyst Thin as required with enamel thinner Recommended viscosi...

Page 171: ... catalyst 1 2 part enamel reducer except when using flat black then increase enamel reducer to 2 parts and 4 parts urethane enamel Allow to stand for 15 minutes then remix before use Thin as required with enamel reducer Recommended viscosity is 38 to 40 seconds using number 1 Zahn Cup D Refinish Installation of pressure sensitive decals placards and tapes on Titanine Polyurethane finish Affix all ...

Page 172: ...cessive air pressure must be used If the acrylic film is sprayed on too thick it may produce a glassy surface but it may appear hazy if viewed from the side instead of directly This is due to tiny air bubbles being introduced into the paint by excessive air pressure To prevent this thin the acrylic lacquer at least in a ratio of four parts of color to five parts of thinner This may seem too thin b...

Page 173: ...t dries When the top of the fuselage is to be painted white with a dark color adjoining it apply the light color and feather it into the area to be painted with the dark color When the light color has dried place masking tape and paper along the line of separation and spray the dark color on Allow the paint to dry for several hours before removing the masking tape Remove the tape by pulling slowly...

Page 174: ...over fresh successive coatings of wash primer and modified zinc chromate They will also adhere to freshly applied epoxy coatings dried less than 6 hrs 5 Epoxy topcoats will adhere to all paint systems that are in good condition Epoxy may be used for general touchup including touchup of defects in baked enamel coatings 6 Old wash primer coats may be overcoated directly with epoxy finishes A new sec...

Page 175: ...s will not have as much of an opportunity to pack at the bottom of the can Empty containers should be disposed of properly Because the useful life of some finishes is limited use the older materials first Temperatures in the storage area should be approximately 50 90 If finishes are stored in temperature extremes allow them tocome to room temperature before using PAINTING FACILITY Painting facilit...

Page 176: ...of masking tape Apply cyclohexanone or equivalent to adhesive side of film Position decal while adhesive is still tacky and apply to surface Work a roller across the decal until all air bubbles are removed To remove a vinyl decal place a cloth saturated with cyclohexanone or methyl ethyl ketone on the decals Scrape with a Micarta scraper Remove remaining adhesive with a cloth dampened with dry cle...

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Page 179: ...CHAPTER ENVIRONMENTAL SYSTEM 1H1l ...

Page 180: ...y Valve Cleaning 1110 21 30 10 Removal Of Controller 1111 21 30 11 Installation Of Controller 1111 21 30 12 Controller Filter Replacement 1111 21 31 00 Cabin Door Seal 1112 21 31 01 Description Of Door Seal 1112 21 40 00 HEATING 1114 21 40 01 Description And Principles Of Operation 1114 21 40 02 Troubleshooting 1114 21 40 03 Operating Controls 1120 21 40 04 Operating Procedure 1120 21 41 00 Inspec...

Page 181: ...Of Combustion Air Blower 111 21 42 22 Replacing Motor Brushes J 11 21 42 23 Installation Of Combustion Air Blower 1J12 21 42 24 Disassembly Of Combustion Air Blower Assembly 1J12 21 42 25 Cleaning 1J13 21 42 26 Cleaning And Inspecting The Combustion Tube Assembly 1J13 21 42 27 Repair Of Combustion Tube Assembly J 14 21 42 28 Reassembly Of Combustion Air Blower Assembly J 14 21 42 29 Recirculating ...

Page 182: ...gulator And Shutoff Valve IKI 21 42 51 Installation Of Fuel Regulator And Shutoff Valve 1K2 21 43 00 Test Procedure 1K2 21 43 01 General 1K2 21 50 00 COOLING 1K3 21 50 01 Description And Principles Of Operation 1K3 21 50 02 Troubleshooting 1K3 21 50 03 Malfunction Detection 1K13 21 51 00 Special Servicing Procedures 1K14 21 51 01 Service Valves 1K16 21 51 02 Test Gauge And Manifold Set 1K17 21 52 ...

Page 183: ... IL8 21 56 12 Receiver Dehydrator Installation 1L8 21 56 13 Condenser 1L8 21 56 14 Condenser Removal 1L8 21 56 15 Condenser Installation 1L9 21 56 16 Expansion Valve 1L9 21 56 17 Removal Of Expansion Valve 1L9 21 56 18 Installation Of Expansion Valve L11 21 56 19 Evaporator Control Valve 1L11 21 56 20 Removal Of Evaporator Control Valve IL11 21 56 21 Installation Of Evaporator Control Valve L11 I ...

Page 184: ... the air is directed through the environmental control system and through the air distribution ducts along both sides of the cabin walls All controls needed for operation and regulation of cabin pressurization are mounted on the lower left side of the instrument panel along with instruments to simplify the setting and checking of system operation Both the cabin altitude and rate of climb adjustmen...

Page 185: ...on ducts Excessive cabin leakage Solenoid valve malfunctions in the open position Valve on pressurized air control box won t close Valve on outside air control box won t close Vacuum tube not connected to controller Replace filter and check orifice Clean filter and check orifice on controller Remove and replace Remove and replace Remove and replace controller Remove and replace switch Replace swit...

Page 186: ... tube or volume tank Remove and replace tube or isobaric valve Remove and replace con troller Minimum rates unbalanced down rate faster than up rate Minor leak in tube between controller and volume tank or in volume tank Remove and replace tube or volume tank Minor leak in the controller Remove and replace con troller Higher unpressurized opera tion before takeoff and after landing Solenoid valve ...

Page 187: ...lfunction in controller Remove and replace con troller Remove and replace con troller Defective cabin rate of climb indicator Remove and replace indicator Cabin pressure rapidly increases or decreases with reselection of cabin altitude Cabin altitude exceeds selected value Malfunction in controller Loss of airflow into cabin Remove and replace con troller Repair or replace air supply Internal malf...

Page 188: ... and repair leak Remove and replace gauge Clean valve seats Locate leak and tighten connection Cabin pressure excessively high Isobaric static line clogged Clean static line Defective cabin over pressure switch Defective cabin altitude pressure gauge Safety valve static vent clogged Defective safety valve Remove and replace switch Remove and replace gauge Clean vent line Remove and replace valve C...

Page 189: ...ROUBLE CAUSE REMEDY Cabin door light wiii not come on Circuit breaker open Reset circuit breaker Broken wire or loose connection Check wiring and repair No pressure to door seal Leak in door seal pressure system Check and repair door seal pressure system 1H21 21 00 02 Page 21 06 Issued April 25 1983 ...

Page 190: ...CIRCULATION FAN 10 HEAT DUCT 11 PRESSURIZED AIR CONTROL BOX 12 STATIC VENT LINE 13 OUTFLOW VALVE 14 STATIC VENT LINE 15 SAFETY VALVE 16 VACUUM EJECTOR 17 SOLENOID VALVE 18 SONIC NOZZLE 19 HEATER 20 EVAPORATOR Figure 21 1 Pressurization System Schematic Garrett PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL OUTSIDE AIR SOURCE 20 19 16 1H22 21 00 02 Page 21 07 Revised December 14 1983 ...

Page 191: ...E STATIC RESSURE FILTER PORT PORT 2 CABIN DISCHARGE SAFETY VALVE DISCHARGE OUTFLOW VALVE SAFETY VALVE TRUE STATIC ATMOSPHERE Figure 21 2 Cabin Pressure Control System Schematic Garrett 1H23 PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL TEE FITTING CABIN RATE CONTROL ER SELECTOR KNOB CABIN ALTITUDE SELECTORKNOB SOLENOID AIR VALVE OUTFLOW VALVE CONTROLL FACE VIEW OF CONTROLLER 21 00 02 Page 21 08 Revi...

Page 192: ...the instrument panel and the auxiliary volume tank and filter are located behind the instrument panel The volume tank provides additional volume for the rate pressure chamber in the controller thus providing greater accuracy of the cabin rate of change control The air filter eliminates entry of tobacco tar and dust particles greater than 3 microns into the pneumatic control elements of the control...

Page 193: ...ate pressure chamber which houses the rate spring The upper element when assembled to the rate diaphragm and other two elements forms a reference pressure chamber which houses the reference pressure metering valve and metering valve follower spring This element also contains the various air connections for installation of the controller into the cabin pressure control system 4 Auxiliary VolumeTank...

Page 194: ......

Page 195: ...AIRCRAFT VACUUM CONNECTION 21 30 01 113 Page 21 12 Revised July 28 1983 ...

Page 196: ...own in referenced figures will be required to perform the pressurization test 1 Aircraft Preparation A Remove the access panel on the right side of the nose section to permit access to the pressure bulkhead at fuselage station 81 00 B Remove the access panels on the right and left side of the fuselage tail section at station 275 00 C Remove the trim panel at fuselage station 274 00 in front of the...

Page 197: ...ge C D P NOTE If no personnel are inside the pressurized cabin the rate of change can be as high as 6000 feet per minute E When 4 5 psi is indicated on the C D P gauge rotate the flow control valve and decrease the air flow rate until the cabin rate of climb gauge indicates zero F Maintain 4 5 psi cabin differential pressure and zero rate of change G Observe the leak rate on the test unit flow met...

Page 198: ... METERPRESSUREINDICATOR 2 RATEOF CLIMB INDICATOR 3 RATEOF FLOW INDICATOR 4 CABIN DIFFERENTIAL PRESSUREINDICATOR 5 INSTRUMENTAIR PRESSURE INDICATOR 6 FLOW RATEVALVE 7 CIRCUITBREAKER 8 STARTBUTTON 9 STOP BUTTON 10 AIR REGULATORVALVE 11 ELECTRICALCONNECTION 12 FILLPORT 13 14 15 16 17 BACK VIEW SIGHTGAUGE INSTRUMENTAIR CABIN REFERENCE PNEUMATICAIR OR PRESS AIR SHOP AIR Figure 21 6 Cabin Pressure Test ...

Page 199: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL I TO TEST BOARD REMOVE ...

Page 200: ...systematically check the function of each element of the cabin pressure control system so that any single or combination of component malfunctions may be safely detected and corrected Should a malfunction be detected it is imperative that the malfunction be corrected before continuing to the next step GROUND OPERATIONAL CHECK 1 Select outside air source and the normal position of the dump switch p...

Page 201: ...ect the sea level position on the cabin altitude selector knob and rotate the cabin rate control knob counterclockwise to its stop and note a cabin rate of climb between 50 and 300 feet per minute 5 To assure for differential control perform the following steps A When the cabin altitude reaches sea level climb to but do not exceed 11 000 feet note the cabin altitude at approximately 1 000 feet and...

Page 202: ...on of nut B Install nuts and tighten C Apply a drop of locking compound MIL S 22473 EV to the top of nuts between nuts and studs 3 Working through the tail section access opening install the three locknuts which hold the valve in place and tighten to metal contact and then backing off 1 4 turn 4 Install the access plate removed from the side of the tail section 5 Connect the lines removed from the...

Page 203: ...ER 1 Position the controller into the instrument panel cutout from the forward side of the panel 2 Secure the controller to the instrument panel with three screws 3 Position the electroluminescent panel to the instrument panel and secure with screws previously removed 4 Remove the protective caps from the lines and fittings of the selector and connect the lines to the fittings on the rear of the c...

Page 204: ...ts the 18 psig air charge from flowing back into the system when the system pressure returns to 5 5 psig The purpose of the accumulator tank is to store air for the door seal and to smooth out its operation There is a pressure switch located in the nose of the accumulator tank just aft of the check valve The switch monitors pressure in the tank The use of high pneumatic pressure only when required...

Page 205: ... 31P 350 MAINTENANCEMANUAL 1 3 1 ACCUMULATOR TANK 2 SWITCH 14 PSI TANK MONITOR 3 VALVE CHECK 4 VALVE SOLENOID 5 SEAL DOOR Figure 21 8 Cabin Door Inflation System Installation 1113 21 30 14 Page 21 22 Revised July 28 1983 ...

Page 206: ...controlled eyeball outlets next to each seat Controls for the gasoline combustion heater are located on the lower right instrument panel The system is normally operated in the AUTO mode position and when the thermostat calls for heat the controller turns the heater on and will operate at maximum efficiency until the desired temperature is obtained When the automatic position is selected the pilot ...

Page 207: ...tch open Remove the nozzle and clean or replace it Remove and check sole noid Replace if faulty Inspect all lines and con nections It mav be nec essary to disconnect lines at various points to determine where the restriction is located Replace vibrator Check for defective radio noise filter Press reset button firmly and recheck to de termine reason for switch opening Combustion air pressure switch...

Page 208: ...heater switch Check and repair wiring Close circuit breaker Replace motor brushes Remove and check the ventilating air blower wheel and realign it necessary Remove blower assembly and replace motor Replace filter Combustion air blower fails to run Fault wiring to motor Poor ground connection Worn motor brushes Blower wheel jammed Usually indicated by hot motor housing Defective radio noise filter ...

Page 209: ...ak in lead between ignition assembly and spark plug Inoperative ignition assembly Restriction in fuel nozzle orifice Nozzle loose in retainer or improper spray angle Replace spark plug Tighten the connection Replace the vibrator Remove and overhaul the combustion air blower assembly as re quired or correct low voltage condition Replace ignition assembly If vibrator is in good condition replace ign...

Page 210: ...ressure switch Adjust or replace switch Inoperative overheat switch Inoperative cycling switch Replace switch Adjust or replace the switch Heater fails to shut off Fuel solenoid valve in heater stuck open Remove and replace solenoid assembly Inoperative duct and heater switch Defective heater switch 1I18 Check and repair Replace the heater switch 21 40 02 Page 21 27 Issued April 25 1983 ...

Page 211: ...OMBUSTION AIR BLOWER 5 EVAPORATOR CONTROLVALVE 6 AIR CONTROL VALVE 7 RECEIVER DRYER 8 RECIRCULATING FAN 9 EXPANSION VALVE 10 EVAPORATOR AND SHROUD 11 CHECKVALVE 12 FUEL REGULATOR AND SHUTOFF VALVE 13 HEATER FUEL FILTER 14 HOUR METER 15 CYCLING SWITCH Figure 21 9 Environmental Components 1119 21 40 02 Page 21 28 Issued July 28 1983 ...

Page 212: ...cabin temperature for desired comfort level If this switch is set for ground operating comfort it may be necessary to reposition it after being airborne since ram air will increase the ventilator airflow and the heater output An override micro switch is incorporated on the duct switch to override the duct stat at the very last movement of the duct stat arm toward the high position 4 To stop heater...

Page 213: ...pect ventilating air and combustion air inlets and exhaust outlet for restrictions and security at the airplane skin line 2 Inspect the drain line to make sure it is free of obstructions Run a wire through it if necessary to clear an obstruction 3 Check all fuel lines for security at joints and shrouds making sure that no evidence of leaks exists Also check for security of attachment of fuel lines...

Page 214: ...rs and lockwashers Replace damaged parts 4 The combustion air pressure switch installed on the system must respond to delicate pressure changes and should always be checked and or replaced at overhaul Refer to Step 3 testing and Figure 21 11 5 Replace the vibrator in the ignition unit only when it no longer functions CAUTION Ignition assembly will be damaged if ignition lead is arced to ground oth...

Page 215: ...hey must be replaced Inspect the commutater for grooved brush track pitting or burning The commutater surface should be smooth and medium brown in color Replace the motor if the commutater or other parts show damage 13 Inspect the combustion air blower motor as described in the preceding step 14 Inspect the blower wheel for broken or bent vanes and replace it for either condition TESTING The follo...

Page 216: ...ch opening with a water manometer and needle valve in the line ahead of switch Switch must be tested in 45 degree position or as installed in the airplane B Connect an ohmmeter across the switch terminals to determine the exact instant of switch closing C Apply air pressure allowing it to build up very slowly from zero The switch contacts should close at 0 5 0 1 inches of water which will be indic...

Page 217: ...PER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL WINGNUT FLAT WASHER RUBBER STOPPER DRILL FOR BOLT FLAT WASHER BOLT EXPANSION PLUG Figure 21 10 Suggested Design for Seal Plate Plugs and Caps for Combustion Tube Leakage Test 2 3 4 AIR SUPPLY 7 Figure 21 11 Test Set up Combustion Air Pressure Switch 1J1 21 41 06 Page 21 34 Issued April 25 1983 ...

Page 218: ...is not closing properly and the fuel feed and nozzle holder assembly must be replaced MAINTENANCE JANITROL HEATER The heater is a gasoline operated 24 Vdc electrically controlled unit installed in the nose section just forward of bulkhead Sta 81 00 REMOVAL OF HEATER 1 Ascertain that the heater switches are off 2 Remove the access panel located on the right side of the airplane s nose section 3 Rem...

Page 219: ...n install the V band clamps at the ends of the heater NOTE Do not tighten the clamps at this time as it may be necessary to move the heater or evaporator assembly to make other hookups 4 Install the four screws which hold the evaporator shroud in place and secure the shroud 5 Connect the fuel drain fitting below the heater 6 Connect the fuel line and fuel shroud drain line at the heater and instal...

Page 220: ... removed 6 Remove the two screws and lift out the overheat limit switch and spacer gaskets 7 Remove the four screws to release the terminal strip and insulator from thejacket 8 Disconnect the fitting at the combustion air pressure switch Unscrew and remove the combustion air pressure switch from the combustion air inlet tube 9 Remove the cover screws and upper cover from solenoid assembly 10 Disco...

Page 221: ... TENSION LEAD 12 MACHINE SCREW 13 ADAPTER 14 TUBE COMBUSTION AIR SWITCH 15 SPARK PLUG 16 ELBOW 17 COMBUSTION AIR PRESSURE SWITCH 18 SCREW 19 COVER UPPER 20 SOLENOID 21 ELBOW 22 NUT 23 COVER LOWER 24 GASKET ANDWASHER 25 COMBUSTION TUBE AND JACKET ASSEMBLY 26 FUEL FEEDAND NOZZLE HOLDER ASSEMBLY 27 GASKET 28 SPRAY NOZZLE 29 MACHINE SCREW 30 COMBUSTION HEAD ASSEMBLY 31 HEAD GASKET 32 MACHINE SCREW Fig...

Page 222: ...ed remove the original nozzle from the polyethylene bag Screw the nozzle into nozzle holder and tighten to 75 100 inch pounds It is very important to torque the nozzle to this value as incorrect tightening could cause improper heater operation and drool CAUTION The spray nozzle is susceptible to damage if theface is contacted by any object which would alter the original contour of the face If this...

Page 223: ...ctrode on the plug NOTE The spark plug can be checked visually for sparking across the gap prior to installing the plug Disconnect the wirefrom the No 3 terminal on the heater wiring side of the terminal strip to de energize the fuel solenoid valve Connect the high voltage lead temporarily and lay the spark plug on the heater jacket Energize heater system and check for spark between spark plug and...

Page 224: ...ning under all flight conditions Heat is produced by burning a fuel air mixture in the combustion chamber of the heater Fuel is injected into the combustion chamber through the spray nozzle The resulting cone shaped fuel spray mixture with combustion air and is ignited by a spark from the spark plug Electric current for ignition is supplied by an ignition unit which converts 24 volts to high volta...

Page 225: ...IR FUEL INLET FRESH AIR FROM BLOWER Figure 21 13 Diagramatic Cutaway of Heater to Show Whirling Flame Action 4 3 2 1 COVER ASSEMBLY 2 IGNITION BOX 3 CLAMP 4 IGNITION COIL 5 VIBRATOR 6 FILTER 7 CONDENSER Figure 21 14 Ignition Unit Assembly 1J9 21 42 11 Page 2142 Issued April 25 1983 ...

Page 226: ...hten the screws securely 3 Carefully connect the high voltage lead to the spark plug Properly route high voltage cable so as to avoid grounding to power input connection and or any other sheet metal parts of heater 4 Connect the primary lead to the primary terminal on the ignition assembly and tighten the nut securely 5 Check for proper heater operation TESTING IGNITION UNIT The ignition unit does...

Page 227: ... 2 Replace the clamp COMBUSTION AIR BLOWER This centrifugal type blower supplies air to the combustion chamber of the heater Performance of the combustion air blower is assisted by the use of outside air during flight REMOVAL OF COMBUSTION AIR BLOWER Refer to Figure 21 15 1 Disconnect wireat quick disconnect terminal 2 Disconnect the inlet tubing from the inlet air adapter 3 Loosen the clamps that...

Page 228: ...t should have just enough clearance to rotate at full speed without binding against the outer housing Blower performance is based upon this close tolerance clearance It is recommended that correct voltage be applied for this clearance check 2 Install the blower inlet adapter in the same orientation as before removal 3 Place the combustion air blower assembly in position in the attaching clamp so t...

Page 229: ...ustion tube assembly is a normal condition for units that have been in service up to 500 hours The slight scaling condition will appear to be mottled and a small accumulation of blue gray powder may be present on the surface in certain areas This condition does not require replacement of combustion tube assembly unless severe overheating has produced soft spots in the metal NOTE This assembly shou...

Page 230: ...openings uncovered direct a stream of compressed air into the combustion tube assembly from first one opening then the other Make sure all loose material is removed REPAIR OF COMBUSTION TUBE ASSEMBLY No weld or braze repairs of the combustion tube assembly are authorized REASSEMBLY OF COMBUSTION AIR BLOWER ASSEMBLY Refer to Figure 21 15 1 Place the spacer over the end of the motor shaft and attach...

Page 231: ...LY 10 CAP BRUSH ASSEMBLY 11 TERMINAL PREINSULATED 12 WASHER LOCK 13 SCREW 14 SCREW 15 NUT 16 SCREW 17 WASHER LOCK 18 NUT 19 WASHER 20 STRAP CABLE 21 SET SCREW 22 SCREW 23 SCREW 24 HOUSING BLOWER OUTER 25 HOUSING BLOWER INNER Figure 21 15 Exploded View of Combustion Air Blower and Motor Assembly 89D23 1 21 42 28 1J15 Page2148 Revised July 28 1983 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1 I 13 ...

Page 232: ...d shroud and slide the upper edge of the fan housing into the cuff on the airbox 4 Secure the fan cuff and air control box together with two clamps 5 Slide the lower cuff over the lower end of the fan and secure it to the shroud and fan housing with the two other clamps NOTE Ascertain that the fan does not come in contact with any part of the air control box or evaporator shroud The cuffs act to s...

Page 233: ... 13 LOCK WASHER 14 PLAINWASHER 15 TERMINAL LUG 16 NUT 17 WASHER 18 NUT 19 WASHER 20 BRUSHES 21 FAN HOUSING 22 WASHERS FLAT 23 MACHINE SCREWS 24 END BELL 25 COTTER PIN 26 PROPELLER 27 FLATSPRING 28 BEARING 29 MOTOR ASSEMBLY 30 END BELL 31 BEARING SHIELD 32 BEARING 33 SLINGER 34 ARMATURE Figure 21 16 Recirculation Fan and Motor Assembly Dynamic Air 21 42 32 1J17 Page 21 50 Issued April 25 1983 ...

Page 234: ... armature shaft and align the reference marks 5 Secure the end bells to the stator with the two machine screws and washers Install safety wire MS20995 C32 to both screws 6 Install brushes into the brush holders of the motor assembly 7 Install the cap onto the terminal lug and secure with washer and nut 8 Install the sleeve spacer over the terminal lugs and position the radio noise filter onto the ...

Page 235: ...ing electro mechanical devices such as starters generators etc Refer to Chart2103 Leading Particulars REPAIR OF RECIRCULATING FAN MOTOR 1 Replace damaged leads and insulation on all parts 2 If commutator or armature is worn it should be turned down enough to eliminate evidence of wear and the mica between the bars undercut approximately 0 031 of an inch deep and 0 030 of an inch wide Remove all pa...

Page 236: ...0 cycles AC for one minute and insulation resistance shall measure 200 megohms or more If the test cannot be met replace the stator PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL CHART 2103 LEADING PARTICULARS AXIAL FLOW FAN DYNAMIC AIR Electrical Current 27 VoltsD C Service Continuous Sea Level to 40 000 feet R F Interference Filtered per Spec MIL 1 6181 Operating Temperature 54 C to 121 C 65 F to 2...

Page 237: ...ould not exceed 12 5 amperes and minimum speed should be 11 300 RPM CHART 2104 TROUBLESHOOTING RECIRCULATING FAN DYNAMIC AIR REMEDY TROUBLE CAUSE No rotation Power not supplied Turn on power supply Check for open in wiring Brushes not making contact to commutator Brushes worn need replacement Excessive current and low speed Bearings misaligned or preloaded Move armature back and forth to relieve p...

Page 238: ...ion air inlet tube and tighten it securely Exercise caution not to overtorque the switch as this could change the setting 2 Connect the tube assemblies to the switch using a suitable thread lubricant 3 Connect the electrical leads to the appropriate switch terminals If in doubt regarding proper connections refer to the wiring diagram Chapter 91 4 Check for proper heater operation OVERHEAT LIMIT SW...

Page 239: ...heat switch operates at 300 400 F CYCLING SWITCH This switch is installed in the ventilating air duct downstream from the heater to sense the ventilating air outlet temperature To select the desired cabin temperature the switch may be adjusted manually from a high of 250 F 10 downward through a range of 146 F The switch has a differential of 15 F 5 at any given setting REMOVAL OF CYCLING SWITCH 1 ...

Page 240: ...r to the wiring diagram Chapter 91 HEATER THERMOSTAT A manual reset thermostat has been attached to the outboard side of the hot air distribution box to prevent overheating of the heated air ducts If the thermostat should sense a temperature of 300 F 3 F electrical power will be interrupted to the heater control valve thereby precluding further heater operation until the thermostat is manually res...

Page 241: ... regulator and shutoff valve used in this system are adjustable but not repairable The following steps cover the proper adjustment of this unit 1 Install the regulator in a test stand similar to that shown in Figure 21 18 2 Install a 2 5 gph nozzle Janitrol Part No D08D09 Gasoline or Stoddard solvent can be used for testing 3 Apply a fluid pressure of 20 to 50 psi and energize the solenoid 4 Using...

Page 242: ...FUEL REGULATOR AND SHUTOFF VALVE 1 Install the fuel regulator and shutoff valve on its mounting with the attaching screws 2 Connect the fuel lines to the inlet and outlet openings and secure 3 Connect the electrical lead Be sure to slide an insulating sleeve or tape over the connection to avoid a short circuit and tie the sleeve in place 4 Check for proper heater operation TEST PROCEDURE GENERAL A...

Page 243: ...switch will control the operation of the air conditioner The system uses R 12 refrigerant which is drawn into the compressor and pumped to the condenser under high pressure The freon vapor is heated as a result of the compression process As it flows through the condenser the vapor is cooled which causes the vapor to condense into a liquid state This liquid refrigerant then passes from the condense...

Page 244: ... 350 MAINTENANCE MANUAL CHART 2105 TROUBLESHOOTING AIR CONDITIONER TROUBLE CAUSE REMEDY High discharge pressure indicated on gauge 1K4 Isolate compressor Repair or replace compressor 21 50 02 Page 21 61 Issued April 25 1983 ...

Page 245: ...ill show frost Expansion valve inlet screen clogged Inoperative ex pansion valve Valve stuck closed or capillary bulb has lost its charge Add Freon Install new dryer Evacuate and re charge system Remove screen Clean with sol vent and replace Warm capillary by holding in hand If suction pressure does not change replace expansion valve Restriction any where in liquid line Restric tion will show fros...

Page 246: ...lean with solvent and replace System produces no cooling Electrical Open circuit breaker Broken or dis connected elec trical wire Broken or dis connected ground wire Clutch coil burned out or disconnected Reset circuit breaker Check all termi nals for loose connections check wiring for hidden breaks Check ground wire to see if loose broken or dis connected Check current flow to clutch replace if i...

Page 247: ...etely frozen Expansion valve stuck in open position Replace drive belts and or tighten to specifications Remove compressor for service or re placement Replace expansion valve Refrigeration Broken refrigerant line Leak in system Clogged screen or screens in receiver dehydra tor or expansion valve plugged hose or coil 1K7 Examine all lines for evidence of breakage by external stress or rubbing wear ...

Page 248: ...sufficient cooling Electrical Circulating fan motor sluggish in operation Remove fan motor for service or replacement Mechanical Compressor clutch slipping Remove clutch assembly for ser vice or replace ment Obstructed blower passage Examine entire passage for ob struction Correct as necessary Insufficient air circulation over condenser coils fins clogged with dirt or bugs Clean condenser coils Ev...

Page 249: ...system and re place expansion valve Purge system replace expansion valve Purge system replace receiver dehydrator Purge system replace receiver dehydrator Purge evacuate and charge system Replace receiver NOTE When a unit must be removed from the system for service or replacement the system must have the receiver dehydrator replaced also and the system must be purged evacuated and recharged to rem...

Page 250: ...pressor for ser vice or replace ment Fill with correct amount of speci fied oil Circulating fan noisy excessive wear in blower motor Remove blower motor for ser vice or replace ment as necessary Refrigeration Excessive charge in system Low charge in system Excessive mois ture in system Discharge excess freon until high pressure gauge drops within specifications Check system for leaks charge sys te...

Page 251: ... 3 FREONPRESSURELINE 4 SERVICEVALVE LOW 5 CONDENSER 6 RECEIVERDEHYDRATOR 7 EVAPORATORCONTROL VALVE 8 EVAPORATOR 9 EXPANSION VALVE 10 LOW PRESSUREFREON SWITCH 11 SERVICEVALVE HIGH Figure 21 19 Air Conditioning System Installation 21 50 02 1K1l Page 21 68 Revised December 14 1983 ...

Page 252: ... Pressure Temperature Gague Reading F p s i 21 72 15 10 2 4 6 8 10 12 14 16 18 20 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 45 47 49 52 53 57 62 66 86 105 109 113 117 122 126 129 132 134 137 140 144 148 152 156 160 162 165 167 170 172 175 177 180 182 185 187 189 191 193 195 200 205 210 215 220 228 236 260 275 290 Ambient Temperature F 40 50 60 62 64 66 68 70 71 72 73 74 75 ...

Page 253: ...an the chart indicates It must be pointed out that the actual temperature of the air passing over the coils of the evaporator will be several degrees warmer allowing for a temperature rise caused by the loss in the fins and tubing of the evaporator The importance of a seasonal check up of the air conditioning system should be brought to the attention of the customer whenever possible A thorough ch...

Page 254: ... raise the temperature c Tape on an eye patch to avoid the possibility of dirt entering the eye d Rush to a physician or hospital for immediate professional aid e DO NOT ATTEMPT TO TREATIT YOURSELF 3 If liquid R 12 strikes the skin frost bite can occur Treat with cool water and protect with petroleum jelly 4 Do not discharge large quantities of R 12 into closed rooms It may displace most of the ai...

Page 255: ...tains 9 Replace O rings when a connection has been broken Dip new O rings in refrigeration oil before using NOTE A very strong acid HCL is formed when R 12 comes in contact with moisture A new receiver dehydrator should be opened and connected to the system only when ready to charge the system with refrigerant 10 Recommended torque values must be used on all flare fitting and O ring joints See Cha...

Page 256: ...performed at the evaporator assembly mounted valves NOTE Service valves are also located on the compressor However use of these valves in servicing is not recommended NOTE Whenever the air conditioning refrigerant lines or system is opened for any reason the lines and fittings should be capped and sealed immediately to prevent dirt and other contaminants from entering the system It is not advisabl...

Page 257: ...ures 21 21 and 21 22 The center port of the manifold set is used for charging or evacuation procedures or any other service that may be necessary Both the high and low side of the manifold have hand shut off valves When the hand valve is turned all the way in in a clockwise direction the manifold is closed The pressures on the side of the system will however be recorded on the gauge above the hose...

Page 258: ...DIAGRAM A DIAGRAM C PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL H H DIAGRAM B H DIAGRAM D Figure 21 22 Manifold Set Operation 1K18 21 51 02 Page 21 75 Issued April 25 1983 ...

Page 259: ...refrigerant to escape from the connections at the service valves Then tighten connections at the service valves 3 Close the low side manifold valve and open the high side manifold valve 4 Open the refrigerant container service valve and allow the pressure at the low side gauge to reach 50 psi at which time close the high side manifold valve 5 Close the refrigerant container service valve and remov...

Page 260: ...harging hose with a shut off valve arrangement to the fitting The charging hose must have a Schrader fitting or adapter to fit the valve 3 Connect the other end of the charging hose to a small cylinder of refrigerant and purge the hose by allowing a slight amount of refrigerant gas to escape from the Schrader valve fitting 4 The cylinder of refrigerant should be placed upright in a container of wa...

Page 261: ...losed if nofurther work is planned EVACUATING THE SYSTEM If the system has been operated in a discharged condition or anytime the system has been open to atmospheric pressure the receiver dehydrator must be replaced and the system evacuated to remove any trapped air and moisture which has entered it A vacuum pump capable of pulling 29 inches of mercury or better should be used As we lower the pres...

Page 262: ...the inlet of the vacuum pump VOTE Make sure the exhaust port on the vacuum pump is open to avoid damage to the vacuum pump 5 Start the vacuum pump and open the low side manifold hand valve Observe the compound low pressure gauge needle it should show a slight vacuum 6 Continue to operate the vacuum pump until 26 to 28 inches of vacuum is attained on the low pressure gauge then extend the operation...

Page 263: ... to charge the system USING A CHARGING STAND This is the preferred method of charging the system NOTE The following instructions apply to Kent Moore J23500 charging stand Refer to Figure 21 25 1 With the system discharged and evacuated proceed to hook up the charging stand Refer to Figure 21 26 2 Fill the charging cylinder by opening the valve at the base of the charging cylinder and filling the s...

Page 264: ...t control and valve 2 high pressure control 9 After completion of charging close all valves on the charging stand Disconnect the high and low pressure charging lines from the aircraft system A small amount of refrigerant remaining in the lines will escape Replace lines on holder of charging stand to keep air and dirt out of lines Open the valve at the top of cylinder to relieve any remaining press...

Page 265: ...This sight glass can be safely viewed with a mirror through the removable panel at the rear of the nose baggage compartment 6 With a low refrigerant charge in the system bubbles will be seen passing thru the sight glass when the system is operating 7 Open the valve on the refrigerant cylinder 8 Allow refrigerant to flow into the system until the bubbles disappear from the sight glass 9 Close the r...

Page 266: ...ly Any lubrication required in the assembly of the components should be refrigerant oil of the type used in the compressor COMPRESSOR REMOVAL The system must be discharged per paragraph Discharging before removing compressor The removal instructions for the Sankyo compressor are as follows 1 Ascertain that air conditioning circuit protector is in the off position 2 Removetheenginecowling 3 Disconn...

Page 267: ...s with engine at idle RPM 2 Discharge the system as previously instructed be careful not to lose any oil 3 Loosen the bolts securing the compressor in the mounting brackets Rotate the compressor in the bracket slots to disconnect drive belt 4 Rotate compressor so that oil filler plug is in a top dead center position 5 Remove the oil filler plug 6 Position the rotor to top dead center refer to Figu...

Page 268: ...G MARK SHOWING ROTOR AT TOP DEAD CENTER Figure 21 27 Top Dead Center Casting Mark Sankyo Compressor TURN CLUTCH FRONT PLATE CLOCKWISEUNTIL DIPSTICK DIPSTICKCANBE INSERTED FRONT PLATE BENCHSURFACE Figure 21 28 Rotation of Clutch Front Plate Sankyo Compressor Oil Check 1L4 21 56 04 Page 21 85 Revised July 28 1983 ...

Page 269: ...ain tension of 6 32 pounds 4 0 pounds for used belts Deflection should be 16 of an inch if less belt is too tight WARNING If the air conditioner is to be operated during ground servicing the test area should be clean and free of any loose objects lying on the ramp Only the service valve located on the evaporator assembly should be used for testing 2 Run the engine for a 15 minute period at engine ...

Page 270: ...ad wire from the compressor front housing INSTALLATION OF CLUTCH PULLEY AND COIL Refer to Figure 21 30 1 Place coil into position over flange protrusion and secure in this position with snap ring previously removed Also connect coil lead wire to compressor front housing 2 Support compressor on mounting ears at compressor rear If a vice is used clamp only on mounting ears never on compressor body 3...

Page 271: ...ng a new clutch assembly try the original shims first When installing a new clutch onto a compressor that previously had no clutch use 040 020 and 005 shims from clutch accessory sack If the air gap does not meet the specification in Step 9 add or subtract shims by repeating Step 8 C and D 6 7 5 9 12 10 1 HEX NUT 2 FRONT PLATE 3 SHAFT KEY 4 SHIMS 5 SNAP RINGS 6 ROTOR PULLEY 7 BEARING 8 CLIP 9 COIL...

Page 272: ...ALLATION 1 Slip the mounting bracket around the receiver and align the fittings to the proper line before securing the mounting bracket 2 Uncap and connect refrigerant lines to the receiver with new O rings installed on the fittings Lubricate the O rinsgs with refrigeration oil before using NOTE Torque thefittings See Chart 2107 3 Evacuate and recharge the system in accordance with previous instru...

Page 273: ...onnections 4 Connect electrical wiring 5 With the condenser secured proceed to evacuate and recharge the system 6 When the system is completely charged check it for any leaks 7 Replace and secure the right access panel on the nose section of airplane EXPANSION VALVE Refer to Figure 21 32 The expansion valve is located next to the evaporator between the receiver drier and the evaporator inlet The c...

Page 274: ...DSLOTS 3 ORIFICE 4 PISTONBLEEDVALVE 5 PISTONRING 6 NEEDLE VALVE 7 VALVESEAT 9 10 11 12 13 1 8 EVAPORATOR PRESS 9 PISTON 10 SCREEN 11 PISTON SPRING 12 BELLOWSCHAMBER 13 BELLOWS 14 VALVE SPRING Figure 21 31 Evaporator Control Valve FROM RECEIVER DEHYDRATOR VALVE Figure 21 32 Expansion Valve 1L10 21 56 17 Page 2 91 Issued April 25 1983 ...

Page 275: ...round the evaporator control valve 4 Disconnect the lines from the evaporator control valve and cap the open ends 5 Disconnect the clamp which holds the evaporator control valve to the evaporator shroud and remove the valve from the airplane INSTALLATION OF EVAPORATOR CONTROL VALVE 1 Install the evaporator control valve into the airplane as shown in Figure 21 33 and secure it to the evaporator wit...

Page 276: ...Remove the air conditioning duct extending over the heater from the evaportator shroud 3 Disconnect the forward V band clamp between the heater and evaporator shroud 4 Remove the four screws which hold the evaporator in place 5 Disconnect the refrigerant lines from the receiver dryer and loosen the clamps and remove the dryer 6 Remove the insulation on the evaporator contol valve and disconnect th...

Page 277: ...2 Install the expansion valve and evaporator control valve to the evaporator shroud as shown in Figure 21 33 3 Install the complete shroud evaporator evaporator control valve and expansion valve into the airplane 4 Connect the pressurized air line to the lower end of the evaporator shroud and secure with clamp Also route the drain hose through the grommet in the fuselage 5 Install the recirculatio...

Page 278: ...n Figure 21 35 Inspect this line for twist or kinks An alternate method of tightening B nuts in lieu Qftorque values is as follows A Hand tighten B nut while moving the tube from side to side This will aid in the seating of the nut and flare to the nipple B With the proper wrench tighten the nut 1 4 turn C Loosen the B nut and repeat Steps I and 2 3 Flared fittings are sometimes difficult to seal ...

Page 279: ...UAL CONICAL SE Figure 21 34 Installation of Seco 7 Seals EXTENDED OVER HERE AL TOOL MARKS CRACKS INSPECT THIS LINE FOR TWIST OR KINKS Figure 21 35 Inspection Points Air Conditioning System Typical 21 57 00 1L15 Page 21 96 Issued April 25 1983 ...

Page 280: ...the nacelle is observed to be clean and free of particles 9 Purge liquid from system by same method using Refrigerant 12 gas until all liquid is removed and only gas flows from pressure and suction lines 10 Replace the receiver dryer and reconnect pressure and suction lines 11 Due to loss of lubricant from the system during flushing the compressor oil level must be checked 12 Evacuate and recharge...

Page 281: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL GRIDS IL17 THRU LL24 INTENTIONALLY LEFT BLANK 1L17 ...

Page 282: ...PIPER AIRCRAFT CORPORATION PART NUMBER 761781 2A1 ...

Page 283: ...n broken down into Sub System Sections These sections are identifiedby the secondelement of the standardizednumbering system The number 40 of thebasicnumber series32 40 00is for the Wheelsand Brakes portion of the landing gear The individual units within a Sub System Section may be identified by a third element of the standardized numberingsystem such as 32 40 01 This number could beassignedby the...

Page 284: ...etelist of Charts is for all fiche in this set followinglist of Illustrations 4 Acompletelistof paragraph titlesand appropriateGrid locationnumbersis givenatthebeginningof each Chapter relating to the information within that Chapter 5 Identificationof RevisedMaterial Revisedtext and illustrationsare indicatedbya blackverticallinealongtheleft handmarginof the frame oppositerevised added or deletedm...

Page 285: ... 1983 July28 983 December14 1983 April30 1986 July 23 1986 September25 1986 June 15 1988 March13 1990 1 2 3 4 and5 1 2 3 4 and5 1 2 3 4 and5 1 2 1and4 3 2 INTERIM REVISION Revisions appear in chapter 27 of card 2 Please dispose of your current card 2 and replace with the revised one DO NOT DISPOSE OF CARDS 1 3 4 or 5 Consultthe CustomerServiceInformationAeroficheforcurrentrevisiondatesfor thismanu...

Page 286: ...hio 419 255 4068 Autopilot Avionics EdoCorporation Avionics Division P O Box 610 Municipal Airport Mineral Wells Texas 76067 817 325 2517 Bendix Avionics Division 2100N W 62ndStreet Fort Lauderdale Florida 33310 305 776 4100 Collins General Aviation Division Rockwell International Cedar Rapids Iowa 52406 319 395 3625 King Radio Corporation 400 N RogersRoad P O Box 106 Olathe Kansas 66061 913 782 0...

Page 287: ...00 Narco Avionics Inc 270 CommerceDrive Fort Washington Penna 19034 215 643 2900 Avco Lycoming Avco Lycoming Division Williamsport Penna 17701 Environmental Systems Heater and Air Conditioner Janitrol Aero Division 4200SurfaceRoad Columbus Ohio 43228 614 276 3561 Sanden International U S A Inc 10710 Sanden Drive Dallas Texas 75238 Fuel Pumps Lear Siegler Incorporated 17602Broadway Avenue Maple Hei...

Page 288: ...r Street Elvria Ohio 44035 216 323 4676 Propellers Hartzell Propeller Incorporated 1025 Roosevelt Avenue Piqua Ohio 45356 513 773 7411 Propeller Synchrophaser Tools Air Conditioning Turbocharger Hartzell Propeller Fan Company 910 South Downing Street Piqua Ohio 45356 513 773 7411 Kent Moore Corporation Service Tool Division 1501 South Jackson Street Jackson Michigan 49203 517 784 8561 Airesearch I...

Page 289: ...R PUBLICATIONS PA 31P 350 Parts Catalog Continuous Inspection 761 776 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 761 786 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 Introduction Page 7 Issued April 25 1983 2A8 ...

Page 290: ...G AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACTICES AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COM M UNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS NAVIGATION AND PITOT STATIC OXYGEN SYSTEM AEROFICHE GRID NO IBI 1B4 IDII IE1 IE4 IE9 1E13 1E16 1E20 1GI IHI1 2BI 2B4 2B12 2C17 2DI 2HI 2 18 3...

Page 291: ...RPOSE PARTS STRUCTURES DOORS FUSELAGE NACELLES STABILIZERS WINDOWS WINGS PROPELLER STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM STARTING TURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 3117 3JI 3J3 3KI 4B1 4CI 4C4 4C7 4D3 4D16 4E10 4F5 4F8 4G7 4G17 4H 18 411 4111 4121 4J1 5B1 5E1 Introductin Pag...

Page 292: ...rrylock Rivet Removal 1G6 20 4 Hose Line Markings IG8 20 5 Flareless Tube Fittings 1G9 20 6 Spray Patterns 1G17 20 7 Improper Spray Technique 1G19 20 8 Spray Technique IG20 20 9 Spraying Corners IG20 21 1 Pressurization System Schematic Garrett IH22 21 2 Cabin Pressure Control System Schematic Garrett IH23 21 3 Safety and Outflow Valves 112 21 4 Cabin Air Pressure Outflow Valve Controller Schemati...

Page 293: ... 7 Seals IL15 21 35 Inspection Points Air Conditioning System Typical IL15 23 1 EmergencyLocator Transmitter Schematic Narco 2B9 23 2 Portable Folding Antenna Narco 2B9 23 3 ELT Using Fixed Aircraft Antenna Narco 2BI0 23 4 Avionics Master and EmergencySwitch Circuit 2B10 24 1 Kelvin Low ResistanceBridge 2B21 24 2 Electrical Power Distribution System Typical 2B22 24 3 Lamar Model B 00382 1 Typical ...

Page 294: ...ploded View 2G2 27 28 Flap Transmission Measurements 2G5 27 29 Checkingfor Wormgear Wear 2G7 27 30 Flap RiggingAdjustments 2G11 28 1 Fuel SystemSchematic 2H8 28 2 Fuel Cell Installation Inboard 2HII 28 3 Fuel Cell Installation Outboard 2H12 28 4 Fuel Cell Installation Nacelle 2H13 28 5 Fuel ValveDrain Plate 2H14 28 6 Fuel Cell Tie Detail 2H17 28 7 Installation of Fuel ValveDrain Plate 2H17 28 8 Fu...

Page 295: ...3B20 30 7 Routing to Tube Fabric 3B22 30 8 Cutting Surface of Tube 3B22 30 9 Cementing BuffedArea and Patch 3B22 30 10 Applyingand Stitching Fabric 3B22 30 11 Placing and Stitching Gum 3B24 30 12 Removing Trapped Air 3B24 30 13 Masking Repair 3B24 30 14 ApplyingNeoprene Putty 3B24 30 15 WindshieldWiper 3C8 30 16 Typical Use of Dial Indicator 3C12 30 17 Centeringof Brusheson Slip Rings 3C12 30 18 M...

Page 296: ...2 24 Adjusting Main Gear Down Light Switch 3F23 32 25 Gear Warning Switches Installation 3F24 33 1 Landing Taxi Light Installation 3G21 33 2 Logo Light Assembly Adjustments 3H2 34 1 Instrument Air System Installation Typical 3H9 34 2 Pitot Static Installation 3H 10 35 1 Oxygen System Installation 314 35 2 Oxygen System Installation for FAR 135 Certification 315 35 3 Oxygen Tubing Installations 311...

Page 297: ...Lines 3K 17 51 10 Repairof Impacted Damage 3K 17 51 11 FuselageSealing Forward 311 51 12 FuselageSealing Aft 3L2 51 13 Faying Surface Seal 31 4 51 14 Joggle Seal 3114 51 15 Stringers Holes and Voids Seals 31 6 51 16 Fillet Seal 3L6 51 17 Bolts and Rivets Seals 31 7 51 18 Floor Board Seals 31 8 51 19 Wire HarnessSeals 3L9 Introduct ion O Page 15 Revised December14 1983 2A16 ...

Page 298: ...0 Checking HarnessLead Continuity 4H7 74 11 Checking HarnessLead Insulation Resistance 4H7 74 12 Modified Pliers 4H7 74 13 RemovingSpring From Lead Assembly 4H7 74 14 AssemblyTool 4H9 74 15 Using AssemblyTool 4H9 74 16 Ferrule Positioned Under Braid 4H10 74 17 Ferrule SeatingTool 4H10 74 18 Position of 11 8627Kit and Contact Spring at Start of Installation 4H11 74 19 Position of 11 8627Kit and Con...

Page 299: ...l 5E10 95 9 Fabricated Tool Checking Main Gear Toe In Adjustment 5E I 95 10 Tire Balancer 5E12 95 1 Fabricated Tool Checking NoseWheel Alignment 5E13 95 12 Suggested Design for Seal Plate Plugs and Caps for Combustion Leakage Test 5E 14 95 13 Charging Stand 5E14 95 14 Fabricated Pressure Test Adapters 5E15 95 15 Cabin Pressure Test Unit Typical 5E15 95 16 Test Gauge Manifold Set 5E16 95 17 Torque ...

Page 300: ...mperature Corrections 2C8 2406 SpecificGravity Temperature Correction 2C9 2407 Recommended Discharge Rate 2C9 2408 Electrolyte Freezing Points 2C10 2409 Capacity Ratings at Discharge Rate 2C12 2410 ElectrolyteFreezing Points 2C12 2411 Circuit Load Chart 2C13 2701 Troubleshooting Surface Controls 2D6 2702 Control Cable RiggingTension vs Temperature 2D19 2801 Troubleshooting Fuel System 2H5 2802 Tro...

Page 301: ...318 3901 Cabin Instruments Display 3J12 5101 List of Materials Thermoplastic Repairs 3K10 5102 Typesof Metal Corrosion 3K21 5501 Elevator BalanceSpecifications 4C17 5502 Rudder BalanceSpecifications 4C23 5701 Aileron BalanceSpecifications 4E5 6101 Propeller Specifications 4E15 6102 Troubleshooting Actuator Chart Engine Synchrophaser 4E22 7101 Troubleshooting Engine 4F I 7301 Troubleshooting Fuel P...

Page 302: ...f Consumable Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Electrical Wiring Coding Electrical Symbols GRID NO 5B4 5B16 5B17 5B19 5B20 5B21 5B22 5C2 5C3 5C4 Introduction Page 19 Issued April 25 1983 2A21 ...

Page 303: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 2A22 ...

Page 304: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 2A23 ...

Page 305: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 2A24 ...

Page 306: ...CHAPTER AUTO FLIGHT 2B1 ...

Page 307: ...ENANCE MANUAL CHAPTER22 AUTOFLIGHT TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION S UBJECT GRID NO SUBJECT EFFECTIVITY 22 00 00 GENERAL 2B3 22 10 00 NON PIPER A F C S EQUIPMENT CONTACTS 2B3 22 Cont Effec Page I Issued April 25 1983 2B2 ...

Page 308: ...facturers to obtain service direction parts support and ser ice literature Bendix Avionics Division 2100N W 62nd Street Fort Lauderdale Fla 33310 305 776 4100TWX 5109559884 Collins General Axiation Division Rockwell International Cedar Rapids Iowa 52406 319 395 3625Telex 464 421 Edo Corporation Avionics Division Box 610 Municipal Airport Mineral Wells Texas 76067 817 325 2517 Telex 76067 King Radi...

Page 309: ...CHAPTER COMMUNICATIONS 2B4 ...

Page 310: ...NO SUBJECT EFFECTIVITY 23 00 00 23 10 00 23 10 01 23 10 02 23 10 03 23 10 04 GENERAL EMERGENCY LOCATOR TRANSMITTER NARCO Description Battery Removal And Installation Description Operation And Testing Of Pilot s Remote Switch Testing Emergency Locator Transmitter 2B6 2B6 2B6 2B6 2B7 2B7 23 Cont Effec Page 1 Issued April 25 1983 2B5 ...

Page 311: ...unting bracket by releasing the latch on the strap and sliding the ELT off the bracket 5 Extend the portable antenna See Figure 23 2 6 Unscrew the four screws that hold the control head to the battery casing and slide apart 7 Disconnect the battery terminals from the bottom of the circuit board 8 Discard old battery pack DO NOT EXPOSE TO FLAME CA UTION The battery pack is shipped with a sealant on...

Page 312: ...itored b the various FAA installations Before performing any operational test of the ELT the following precautions should be observed CA UTION Testingof an EL T shouldbe conducted in a screen roomor metal enclosureto ensurethat electromagneticenergyis not radiated duringtesting If a shielded enclosure isnot available testingmay beperformedin accordance with thefollowingprocedures 1 Testshouldbeno ...

Page 313: ...nwardswepttone 6 Whenthe testis completed ascertainthe transmitterON ARM OFF switchis in the ARM position WARNING Whenever the unit is checked by moving the transmitter ON A RM OFF switchfrom the ARM tothe ONposition it must then be moved to the OFF position if there is one before reverting to the ARM position again CA UTION Under normal conditions the transmitter switch must be set to arm 7 Repla...

Page 314: ...ENANCE MANUAL Figure 23 1 Emergency Locator Transmitter Schematic Narco 8965 NOTCH PIN PORTABLE STOP ANTENNA OPERATIVE I BUT STORED ANTENNA EXTENSION TAB ANTENNA EXTENSION TAB VIEW A ANTENNA POPS OUT OF CHANNEL AND DOWN SET ON OFF ARM SWITCH TO ON PIN STOP VIEW C TO EXTEND TO FULL LENGTH Figure 23 2 Portable Folding Antenna Narco 23 10 04 Page 23 04 Issued April 25 1983 2B9 ...

Page 315: ...DE NOT MAKING CONTACT Figure 23 3 ELT Using Fixed Aircraft Antenna Narco EL1919 AVIONICS MASTER SWITCH AVIONICS ACCESSORY C B 35A RIGHT DISTRIBUTION BUS I AVIONICS BUS 2 AVIONICS BUS 2 AVIONICS BUS 25A BUS TIE Figure 23 4 Avionics Master and Emergency Switch Circuit 23 10 04 Page 23 05 2B10 Issued April 25 1983 ...

Page 316: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLYLEFT BLANK 2B11 ...

Page 317: ...CHAPTER ELECTRICAL POWER 2B12 ...

Page 318: ... Description Lamar B 00382 1 Alternator Control Unit 2C3 24 40 00 ADJUSTING LAMAR ALTERNATOR CONTROL UNITS B 00382 1 2C3 24 40 01 Adjustments 2C3 24 40 02 Alternator Control Units Test Specifications LAMAR B 00382 1 2C4 24 50 00 BATTERY LEAD ACID 2C4 24 50 01 Service Of Battery System 2C4 24 50 02 Removal Of Battery And Acid Recovery Jar 2C5 24 50 03 Installation Of Battery System 2C6 24 50 04 Cle...

Page 319: ...ng operational flexibilities during single alternator or single engine operation External Power facilities have been designed into the system to satisfy ground operational requirements Further a shelf mounted relay accessory panel assembly in the nose of the aircraft centralizes main accessory components for efficient service All circuit breakers and switches are within easy reach of the pilot wit...

Page 320: ...nit Brushes should be a free fit in the brush boxes with out excessive side play Binding brushes and brush boxes should be wiped clean with a gasoline undoped moistened cloth A new brush should be run in until at least 50 seated howeer if facilities are not available for running in brushes then the brush should be properly seated by inserting a strip of No 0000 sandpaper between the brush and comm...

Page 321: ...re known to be in good condition Test and then replace with new part Starter motor operates at proper speed but fails to crank engine Low starter motor and cranking speed Faulty Bendix drive Worn rough or im properly lubricated starter motor Remove Bendix drive as sembly Clean and check replace Disassemble clean in spect and relubricate replacing ball bearings if worn Same electrical causes listed...

Page 322: ...ont Remedy Remove and turn commu tator down on a lathe Reface commutator Replace battery Reset Reduce use of starter on the ground use external power wherever possible Remove and recharge battery if left in unused airplane Remove and recharge Replace battery Check wiring Replace battery and re charge acid recovery jar Maintain electrolyte level Replace Replace Replace battery Replace battery and t...

Page 323: ...eplace Water added and battery not chargedimmediately Leaking cell Alwa s recharge battery at least 1 2 hour when add ing water in freezing weather Replace Battery polarity reversed Battery consumes ex cessive water Connected backwards on airplane or charger Charging rate too high if in all cells Battery should be slowly dischargedcompletelyand thenchargedcorrectly and tested Check acid reco ery j...

Page 324: ...polarize the alternator No polarization is required Any attempt to do so may result in damage to the alternator regulator or circuits 4 Grounding of the alternator output terminal may damage the alternator and or circuit and components 5 Reversed battery connections may damage the rectifiers wiring or other components of the charg ing system Battery polarity should be checked with a voltmeter befo...

Page 325: ...ugh a small fuse the 10amp test current would blow smaller fuses It is practical to turn down the test current to 5 amp and then double the measured voltage to safely measure a 10 amp fused circuit 6 Nearly every normal resistance over 3 m will be due to the resistance of wire as shown on the chart Determine the wire gauge usually shown on Piper electrical schematics and estimate the length of eac...

Page 326: ... 350 MAINTENANCEMANUAL CHART 2402 WIRE RESISTANCE TABLE Copper Wire I Diameter Sol Wire 020 025 032 040 051 064 080 102 129 162 204 258 289 325 365 ft per 100 m 39 62 10 16 25 37 63 100 159 253 403 640 807 1018 1283 Gauge No 24 22 20 18 16 14 12 10 8 6 4 2 1 0 00 Resistance in Milliohms per Foot ft 68 F 20C 32F 0 C 122 F 50 C 167 F 75 C 25 67 m 23 65 28 70 31 22 16 14 14 87 1805 19 63 10 6 4 4 0 2...

Page 327: ...ANCE MANUAL EXTERNAL POWER CONTACTOR BATTERY MASTER CONTACTOR LEFT AMMETER 72 Bs 13 4 LEFT ALTERNATOR CONTROLUNIT I I RIGHT ALTER RIGHT AMMETER 121711 RNATOR CONTROLUNIT ALTERNATOR PARALLELING SYSTEM Figure 24 2 Electrical Power Distribution System TYPICAL 24 00 01 Page 24 09 Revised July 28 1983 2B22 ...

Page 328: ...Each alternator switch manually removes or applies field voltage to its system The Main Bus Tie is connected to the left and right Distribution Buses through 70AM P circuit breakers NOTE Figure 24 2 is a typical system schematic for reference refer to Chapter 91 Electrical Schematics for troubleshooting the system ALTERNATOR SERVICE TEST SPECIFICATIONS PRESTOLITE 100 AMP ALV 8402 L Prestolite spec...

Page 329: ...emperature varnish and cement to provide high temperature and vibration protection High temperature solder is used to secure the winding leads to the slip rings 5 The Drive End Head supports a sealed pre lubricated bearing in which the rotor shaft rotates METHODS OF CHECKING ALTERNATOR BELT TENSION 1 If properly installed tensioned and checked periodically the alternator drive belt will give very ...

Page 330: ...pounds is obtained 10 pounds for used belts 3 Measure the distance the belt has moved with the 10 to 14 pound load applied The distance deflection should be 5 16 inch If less than 5 16 inch the belt is too tight C Note that the belt tension of the belt is adjusted by means of an idler pulley NOTE Thealternator pulley and starter ring gear support pulley must be alignedfor maximum belt life A ltern...

Page 331: ...ng that bus to the Right Distribution bus is shorted and must be replaced 10 ResetLeft Main and 1 Avionics bus circuit breakersand pull OFF Right Main bus circuit breaker 1 Observe Right Main bus loses power If poweris not lost diode connecting Right Main bus to Right Distribution bus is shorted and must be replaced 12 Reset Right Main bus circuit breaker Right Distribution bus circuit breaker 35A...

Page 332: ...to ground or to bus v oltage no damage will result how eer load sharing will be lost and overvoltage protection will be affected hy an increase ot approximately 2 0 volts above the normal D V trip calibration point To reset from an overv oltagecondition momentary remov al of 28 V D C is required Should a short develop between alternator A and Field A an uncontrolled overvoltage condition will occu...

Page 333: ...NCE CIRCUIT REGULATOR SET TO O V TRIP CAL 0 V TRIPTIME 0 V SELECTIVIY ALT INOP INDICATOR ALT INOP SENSING POINT Figure 24 4 Lamar B 00382 1 A C U Test Specifications ALTERNATOR CONTROL UNITS TEST SPECIFICATIONS LAMAR B 00382 1 The temporary lamp or relay indicator called out below is not critical as long as the device represents a load and current flow A voltmeter is not sufficient BATTERY LEAD AC...

Page 334: ...ternator or regulator 6 Do not attempt to polarize the alternator REMOVAL OF BATTERY AND ACID RECOVERY JAR 1 Open the forward baggage compartment door and unlatch the nose cone locking handle located to the left inside the baggage door opening and swing open the nose cone 2 Pull back the rubber battery terminal boots loosen the wing nuts and remove battery cables CA UTION Remove NEGA TI VE battery...

Page 335: ... Wipe exterior of battery and interior of manifold with a cloth saturated with a solution of bicarbonate of soda mixed one part soda to twenty parts water Check cell plugs are tight do not allow any soda solution to enter any cells 2 Wash entire battery with clear water and dry thoroughly 3 Wash down with soda solution followed by clear water the floor area floor support angle battery hold down su...

Page 336: ...nd rinsewith clear water Then apply a fresh coating of high quality aircraft wax to this entire area CLEANING ACID RECOVERY JAR 1 Unscrew the bottom of the recovery jar and separate from the top 2 Remove the jar pad and empty jar contents into suitable container for proper disposal 3 Thoroughly washand neutralize jar pad and jar top including short vent hose previously re moved with the soda solut...

Page 337: ... false reading Temperatures different from the established normw ill also effect the hydrometer readings Refer to Chart 2406 for the temperature corrections Specific gravity values for a fully charged battery are as follows CHART 2405 ELECTROLYTE TEMPERATURE CORRECTIONS Electrolyte Temperature Specific Gravity 47 F 1 280to 1 300 77 F 1 280to 1 290 107 F 1 260to 1 280 Temperature change of 30 F cha...

Page 338: ... be obtained from a battery are greater for a long low rate or intermittent rate discharge than for a short high rate discharge because the oltage will drop faster at the higher discharge rate The maximum permissible rate of discharge is limited only by the current carrying ability of the wiring motor or other apparatus to which the battery is connected or by the current carrying ability of the ce...

Page 339: ...l action CHART 2408 ELECTROLYTE FREEZING POINTS Freezing Point Specific Gravity C F 1 300 70 95 1 275 62 80 1 250 52 62 1 225 37 35 1 200 26 16 1 175 20 4 1 150 15 5 1 125 10 13 1 100 8 19 BATTERY REPAIRS STORAGE AND SERVICE TIPS The internal parts of the battery have been designed to wear at approximately the same rate making it uneconomical to replace any of the parts with new ones Replacing the...

Page 340: ...supplying electrical power to all aircraft electrical buses Refer to Figure 24 2 2 With Battery Master Switch left in OFF position turn OFF all unnecessary electrical loads as in a normal start 3 Also pull Circuit Breaker Co er and PULL OFF 70 AMP Left and Right Distribution bus tie circuit breakers 4 Start right engine and move ground power unit well away from aircraft before starting left engine...

Page 341: ... divided by one hour is the rate of discharge to 1 5 volts per cell The ampere hours shown divided by five hours is the rate of discharge to 1 75 volts per cell The amperes shown is the rate of discharge for 25 minutes to a cut off voltage of 1 75 volts per cell The amperes shown in discharge current used to crank an engine for 30 seconds at 0 F to 1 2 volts per cell I CHART 2410 ELECTROLYTE FREEZ...

Page 342: ...5 MOTOR 5 IGNITION MOTOR FUEL VALVE HOUR METER SHUT OFF VALVE 5 DOOR SOLENOID VACUUM SOLENOID INDICATOR 7 5 HEATING ELEMENT 7 5 HEATING ELEMENT 5 SOLID STATE INDUCTIVE 5 SOLID STATE COMPUT R READOUT 5 METER INDUCTIVE 5 SOLID STATE INDUCTIVE 5 LAMP AND HORN 48 INDICATOR LAMPS SOLID STATE UNIT 10 INDUCTIVE 10 INDUCTIVE 2 INDUCTIVE 2 INDUCTIVE 2 INDUCTIVE 2 INDUCTIVE DUTY CYCLE INT INT INT INT INT IN...

Page 343: ...CYCI E CONT CURRENT FLOW IN AMPERES 28 D C 1 00 5 INDUCTIVE 5 INDUCTIVE 5 INDUCTIVE 5 INDUCTIVE 5 INDUCTIVE 10 HEATING ELEMENT 10 HEATING ELEMENT 5 METERS INDUCTIVE LAMPS 3 4 LANDING LIGHT SOLENOID LOCK SOLENOID RELAY LAMP IN TRANSIT 5 TIME DELAY UNIT HORN 10 VANE PLATE HTG ELEMENTS CORE HIG ELEMENTS RELAY 5 TIMER WING BOOT VALVE INBR D AND TAIL VALVE GYRO SHUT OFF VALVE LEFT REGULATOR VALVE RIGHT...

Page 344: ...R LEFT HEATING ELEMENTS RIGHT HEATING ELEMENTS 35 MOTOR 3 SOLENOID AMPLIFIER METER RHEOSTAT 3 5 MOTOR 5 MOTOR 5 SOLID STATE N A SOLENOID 5 VIBRA OR SOLENOID MOTOR 5 VIBRATOR SOLENOID MOT OR 10 SOLID STATE 10 SOLID STATE 5 MOTOR 5 MOTOR 10 MOTOR 10 MOTOR 7 5 LEFT WING LAMP RIGHT WING LAMP TAIL LAMP DUTY CYCLE INT INT INT INT INT INT INT INT INT INT INT INT CONT CONT INT INT INT INT IN T INT CONT NO...

Page 345: ...0 SOLENOID LAMPS 2 7 5 LAMPS 2 5 LAMP 10 SOLENOID LAMP 10 SOLENOID LAMP 75 MAP LAMPS 2 SIGN LAMPS 5 READING LAMPS 5 CABINET LAMPS 2 CHIMES SOLID STATE 5 BAGGAGE DELAY UNIT AISLE LAMPS 2 REAR EXIT LAMPS 2 EXIT STEPS 5 LAMPS 2 5 LAMPS 36 MAG SWITCH LAMPS 4 5 LAMPS 21 5 LAMPS 13 INVERTER 10 MOTOR DUTY CYCLE CONT CONT CONT CONT INT INT INT INT INT INT INT INT INT INT INT INT INT INT INT INT INT INT CO...

Page 346: ...CHAPTER EQUIPMENT FURNISHINGS 2C17 ...

Page 347: ...25 00 00 25 10 00 25 10 00 25 10 01 25 10 02 25 10 03 GENERAL 2C19 FLIGHT AND PASSENGER COMPARTMENTS SEATS Removaland Installation of Seats Removaland Installation of Folding Table Removaland Installation of Cabinetry and Divider EFFECTIV IT Y A 12 83 A 12 83 A 12 83 A 12 83 A 12 83 2C19 2C19 2C19 2C22 25 Cont Effec Page I Added December 14 1983 2C18 ...

Page 348: ...alog for part no This chapter providesinstructions for removal and installation of the equipment listed above FLIGHT AND PASSENGER COMPARTMENTS SEATS REMOVAL AND INSTALLATION OF SEATS Refer to Figures 25 1 25 2 and 25 3 1 To removethe crew and passenger seats the following proceduresare suggested A Removethe seattrack end coversor seatstops B Move the seatforward or aft to slots in seattracks and ...

Page 349: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL Figure 25 1 Crew and Passenger Seat Installation 25 10 02 Page 25 02 Added December 14 1983 2C20 ...

Page 350: ...CRAFT PA 31P 350 MAINTENANCE MANUAL TOILET FORWARD FACING STEP MOUNTED TOILET SIDE FACING TOILET FORWARD FACING FLOOR MOUNTED Figure 25 2 Toilet Seat Installation 25 10 02 Page 25 03 Added December 14 1983 2C21 ...

Page 351: ...ctrical wiring 4 Remove attaching hardware securing divider panels cabinetry remove divider panels and cabinet r 5 Removethe heating elementsby disconnectingwires and screwthem out of the unit 6 Removethe razor invertor razor outlet and razor or heating unit switchesby disconnectingthe electricalwires and removing the attaching hardware 7 Removethe armrest by removing two nuts that secureit to the...

Page 352: ...AIRCRAFT PA 31P 350 MAINTENANCE MANUAL LEFT REFRESHMENT AND STORAGE CABINET RIGHT JEPP CASE AND STORAGE CABINET Figure 25 4 Forward Cabinetry and Divider Panel 25 10 03 Page 25 05 Added December 14 1983 2C23 ...

Page 353: ...NANCE MANUAL REAR DIVIDER PANEL REFRESHMENT CABINET WITH DIVIDER PANEL REFRESHMENT CABINET REFRESHMENT CABINET WITH DIVIDER PANEL Figure 25 5 Aft Refreshment Cabinets and Divider Panels 25 10 03 Page 25 06 Added December 14 1983 2C24 ...

Page 354: ...CHAPTER FLIGHT CONTROLS 2D1 ...

Page 355: ...stallation of Aileron Bellcrank 2E11 27 13 00 Rigging and Adjustment of Aileron Controls 2E12 27 14 00 Aileron Trim Control Pedestal 2E 13 27 14 01 Removal of Aileron Trim Control Pedestal 2E13 27 14 02 Installation of Aileron Trim Control Pedestal 2E14 27 15 00 Aileron Trim Wing 2E17 27 15 01 Removal of Aileron Trim Wing 2E17 27 15 02 Installation of Aileron Trim Wing 2E17 27 16 00 Rigging and Ad...

Page 356: ...2F7 27 32 02 Installation of Elevator Bellcrank 2F11 27 33 00 Rigging and Adjustment of Elevator Controls 2F11 IR 7 83 27 34 00 Elevator Trim Control Pedestal 2F12 27 34 01 Removal of Elevator Trim Control Pedestal 2F13 27 34 02 Installation of Elevator Trim Control Pedestal 2F14 27 35 00 Elevator Trim Elevator 2F14 27 35 01 Removal of Elevator Trim Elevator 2F14 27 35 02 Installation of Elevator ...

Page 357: ...ission 2G8 IR 7 83 27 54 00 Rigging and Adjustment of Flaps 2G8 IR 7 73 27 55 00 Flap Position Sender 2G12 27 55 01 Removal of Flap Position Sender 2G12 27 55 02 Installation of Flap Position Sender 2G12 27 55 03 Rigging and Adiustment of Flap Position Sender 2G13 27 56 00 Flap Control Bo 2G13 27 56 01 Removal of Flap Control Box 2G13 27 56 02 Installation of Flap Control Bo 2G14 27 57 00 Flap Con...

Page 358: ...particular control surface As the trim control wheels are rotated they in turn rotate the mating drums at the control surfaces to actuate the particular trim tab A sender unit is installed at each trim tab and will transmit a signal to the indicator at the control pedestal indicating the position of the trim tab The wing flap system consists of a flap selector switch located on the instrument pane...

Page 359: ...ri zontal chain improperly adjusted Pulleys binding or rubbing Cables not in place on pulleys Bent aileron and or hinge Cables crossed or routed incorrectly Lubricate system Adjust cable tension Adjust chain tension Replace binding pulleys and or provide clearance between pulleys and brackets Install cables correctl Check cable guards Repair or replace aileron and or hinge Check routing of control...

Page 360: ...rol wheel and control rod Rig control wheel and control cables AILERON TRIM CONTROL SYSTEM Lost motion between trim control wheel and trim tab Cable tension too low Adjust cable tension Cablesnot in place on pulleys Broken pulley Linkage loose or worn Install cables Replacepulley Check linkage and tighten or replace Trim control wheel moves with excessive resistance Systemnot lubricated properly L...

Page 361: ...ELEVATOR CONTROL SYSTEM Lost motion between control wheel and ele vator Cable tension too low Adjust cable tension Linkage loose or worn Broken pulley Cables not in place on pulleys Check linkage and tighten or replace Replacepulley Install cablescorrectl Resistance to elevaor control movement System not lubricated properly Lubricate system Cable tension too high Binding control column Pulleys bin...

Page 362: ...avel cannot he obtained by adjusting elevator arm stops Elevator cables incor rectly rigged Rig cables ELEVATOR TRIM CONTROL SYSTEM I ost motion between trim control heel and trim tab Cable tension too low Adjust cables Cables not in place on pulle s Broken pulley l inkage loose or worn Install cables Replace pulley Check linkage and tighten or replace Trim control wheel moves with excessive resis...

Page 363: ... adjust rigging Either or both trim drums incorrectly wrapped Check and or adjust rigging T rim indicator fails to in dicate correct trim posi tion Trim indicator unit not adjusted properly Adjust unit RUDDER CONTROL SYSTEM L ost motion between rudder pedals and rudder Cable tension too low Adjust cable tension Linkage loose or worn Broken pulley Bolts attaching rudder to bellcrank are loose Check...

Page 364: ...ncorrectly adjusted Rig rudder cables Rig rudder bellcrank stop Nose wheel contacts stops before rudder Rig wheel contacts stops RUDDER TRIM CONTROL SYSTEM Lost motion between trim control wheel and trim tab Cable tension too low Adjust cable tension Cables not in place on pulleys Broken pulley linkage loose or worn Install cables Replace pulley Check linkage and tighten or replace Trim control wh...

Page 365: ...0 MAINTENANCE MANUAL CH RT 2701 TROUBLESHOOTING SURFACE CONTROL cont Trim indicator unit not adjusted properly Adjust indicator unit FLAP CONTROL SYSTEM Flaps fail to extend or re 2D12 27 00 02 Page 27 08 Issued April 25 1983 ...

Page 366: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL ...

Page 367: ... Sender unit not adjusted properlv Defecti e iring Battery switch off Circuit breaker open Sender unit ground open Amplifier component failure Flap motor circuit breaker off Flaps symmetrical Potentiometer failure Motor and or relay failure Power lost to amplifier Determine cause and replace or repair Replaceindicator unit Replace sender unit Adjust sender unit Check and repair wiring Turn switch ...

Page 368: ......

Page 369: ...ometers Remove and service actuator Perform rigging test and procedure Wracked flap Screwjack housing failure Remo e applicable screw jack and repair Ball screw fracture Flap connection failure Outboard flexshaft and or coupling failure Remove applicable screw jack and repair Replace shaft or con nection Replace the required item Frozen screwjack actuator Drag Brake Failure Malfunctioning amplifie...

Page 370: ...re Service the control box No flap moveme Flap control box Leer shaft failure L ocking pin failure Gearing failure Service the control box Flexhaft or coupling fa il ure Open circuit Replace worn part Check circuitry refer to schematic in this chapter Slowsystem cycle Excessive motor brush wear Remove and service flap motor Motor open circuit Check circuit per rigging and test procedures Check cir...

Page 371: ...RCRAFT PA 31 P 350 MAINTENANCE MANUAL Flap motor circuit breaker pulled or tripped Flaps asymmetric Potentiometer failure Reset circuit breaker Check and rerig flaps Replace potentiometer Replace component 2D18 ...

Page 372: ...ing to marking cable end etc before disconnecting a felt marker may be used 6 When turnbuckles have been set to correct cable tension no more than three threads should be exposed from either end of the turnbuckle barrel 7 Cable tension should be taken with the appropriate surfacecontrol in its neutral positionand ten sion specifiedcorrected to ambient temperature in the area wheretension is beingc...

Page 373: ...TENANCE MANUAL 901 DAMAGE HERE IMPROPER TOOL RESULTINGIN LOCKEDBALL A SPECIAL WRENCH MAY BE REQUIRED WITH A LONG THROAT ONLY CORRECT METHOD Figure 27 1 Correct Method of Installing Rod End Bearings 27 01 00 Page 27 16 Issued April 25 1983 2D20 ...

Page 374: ...e lockpin C Hold the drum with its base down Wrap the cable that leads from the base end of the drum nine and one quarter turns in a counterclockwise direction up towards the center of the drum Wrap the cable that leads from the upper end of the drum nine and one quarter turns in a clockwise direction down towards the center of the drum 7A To install and wrap the trim cable on the rudder trim drum...

Page 375: ...6 1 2 TURNS 18 1 2 TURNS OF CABLE ON DRUM I 18 1 2 TURNS OF CABLE ON DRUM 9 1 4 TURNS ON EACH END WITH DRUM CENTEREDBETWEENSTOPS C821 ELEVATOR TRIM SCREW 12 TURNS 6 1 2 TURNS 18 1 2 TURNS ON DRUM 6 1 2 TURNS ON UPPEREND AND 12 TURNS ON LOWER END 27 02 00 Page 27 18 Revised July 28 1983 Figure 27 2 Trim ScrewAssemblie 2D22 ...

Page 376: ...10 PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL A n C602 2D23 ...

Page 377: ...ntpanel C The squaretube assemblymay be disassembled by first removing the collar from the tube Draw the tube from the roller fitting D Cut the wire that safetiesthe cap bolts that securethe collar to the roller fitting Removethe bearinghousing from the fitting E Disassemblethe rollers from the fitting Note the numberand location of the spacer washers 3 The sprocket assemblymay be removedfrom the ...

Page 378: ...the panel INSTALLATION OF CONTROL COLUMN Refer to Figure 27 3 1 Installation of the control column torque assembly may be accomplished by the following procedure A Position but do not attach control arms on uninstalled torque tube assembly B Lubricate bearings and attach bearings to their mounting locations C Slide the tube extensions inside torque tube and install the torque tube Pull the tube ex...

Page 379: ...36 UNIVERSAL ASSY 37 HOUSING SPROCKET 38 SCREW 39 CAP BOLT 40 CHAIN RIGHT 41 TURNBUCKLE 42 CHAIN LEFT 43 CONTROLWHEEL 44 CONTROLTUBE LEFT 45 SCREW ADJUSTMENT 46 BLOCK 47 HOUSING GUIDE ASSY 48 SCREW 49 COVER 50 SPROCKET 51 LINK ASSY 52 CONTROLCABLE AILERON 53 CONTROLCABLE AILERON 54 CHAIN AILERON 55 PLATE CABLE ATTACH 56 BUSHING 57 COLLAR 58 NUT 59 CAP BOLT 60 WASHER 61 ROLLER 62 BLOCK 63 BEARING 6...

Page 380: ... PA 31P 350 MAINTENANCE MANUAL 175 174 69 70 68 70 71 SKETCH A 349 SKETCH B 360 79 80 72 81 73 74 75 79 73 75 81 80 SKETCHC SKETCHD Figure 27 3 Control Column Installation cont 27 03 02 Page 27 23 Issued April 25 1983 2E3 ...

Page 381: ...s C Install the bearing housing with bearings on the roller housing Install collar and cap bolts Rotate the collar tight against the bearing housing tighten cap bolts and safety D Ascertain that the four nylon guides are installed and safetied E Slide the collar on the forward end of the square tube F Place the square tube assembly in position and connect it to the flexible joint of the sprocket a...

Page 382: ...oint and rotate the tube 180 Reinstall bolts torque and safety 7 Adjust the control w heeltube slides at the instrument panel by tightening the adjustment screw to remove any play in the tube without restricting normal tube movement 8 Adjust the horizontal roller chain so that when the leftcontrol wheel is held solid incenter position the right wheel will also be centered with no play Safety turnb...

Page 383: ... Loosenthe turnbuckle separating theendsat theforwardendof theaileronbellcrank C Remove thecable guardpinsatwingstation29 00 and 150 00 andwithinthefuselage atstation 164 50 and 168 50 Remove the fairleadsat thefuselage D Drawthecablebackthroughthefuselage throughthewingandoutthroughtheaccess hole theaileronbellcrank 5 Remoxalof the rightbalancecablemaybeaccomplished by thefollowingprocedure A Loo...

Page 384: ...the forward control cable turnbuckle within the tuselage at station 100 00 D If balance cable is installed install the cable guard pins at wing stations 29 00 and 150 00and fuselage stations 164 50 and 168 50 Install the fairleads at fuselage station 137 00 2 The right balance cable may be installed by the following procedure A Ascertain that the right and left balance cables are connected if the ...

Page 385: ...NTERCONNECTING CABLE L 22 CABLE BALANCE L 23 CABLE CONTROL L 24 BELLCRANK LEFT 25 ROD CONTROL 26 TURNBUCKLE 27 SPRING 28 SPRING 29SPRING 30CABLE 31CONNECTOR 32 BOLT GUARD 33 DRUM 34 HOUSING 35 BOLT CAP 36 STOP SCREW 37 SCREW 38 BOLT ASSY 39 JAMNUT 40 CLEVIS 41 BOLT ASSY 42 BRACKET 43 BRACKET 44 RODEND 45JAMNUT 46BOLTASSY 47 END TURNBUCKLE 48 END TURNBUCKLE 49 BOLTASSY 50 RODEND 51 NUT JAM 52 STOPB...

Page 386: ...ELAGESTATION 125 21 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL NOTE BE SURETHE CABLE IS ROUTED BE TWEENTHE CABLE GUARD AND THE PULLEY A 57 VIEW A A 181 SUPPORT CABLE SKETCHC Figure 27 7 Aileron and Aileron Trim Controls cont 27 11 02 Page 27 29 Issued April 25 1983 2E9 ...

Page 387: ...ANE MAINTENANCE MANUAL C322 WING STATION 30 LEFT WING WING STATION 30 RIGHTWING SKETCHE WING STATION 147 5 SKETCHF C43 42 SKETCHG SKETCHH Figure27 7 AileronandAileronTrimControls cont 27 11 02 Page 27 30 Interim Revision March 13 1990 2E10 ...

Page 388: ...ess plate to the bellcrank assembly 2 Relieve cable tension from the control system by rotating one of the turnbuckles attached to the bellcrank 3 Disconnect the turnbuckle ends from the forward and aft ends of the bellcrank 4 Disconnect the aileron control rod at the bellcrank 5 Remove the pivot bolt securing the bellcrank and remove bellcrank from wing 6 The stop block may be removed by unboltin...

Page 389: ...t the tool between the bellcrank mounting brackets and over the end of the bolt from w hich the nut was removed It may be necessaryto loosen one of the primary control cables or the balance cable D Position the tool so that it fits tight against the outboard side of the bellcrank stop block E Clamp the tool to the lower support bracket with a small C clamp Place a small block of wood or similiar m...

Page 390: ... aileron and establish neutral or zeroon the protractor Remove the tools holding the aileron bellcranks in neutral replace nuts and safety Adjust the bellcrank stop bolts to the specific aileron travel from neutral as given in Figure 27 11 Stops of both bellcranks should contact their stop blocks at the same time and before the control wheel contacts its stop 6 Simulate flight load by dropping bot...

Page 391: ...7 I Ascertain that the cable is evenly wrapped on the trim drum centered and blocked to prevent unwrapping Refer to Wrapping Trim Drum 2 Lubricate the screw assembly shaft bearing on the face of the control pedestal 3 Position the screw assembly in the pedestal on its mounting bracket and secure 4 Draw the cables from the pedestal through the fuselage and into the wing 5 Install the cable pulleys ...

Page 392: ...OSITION INDICATOR 4 AILERON TRIM CONTROL S RUDDER TRIM SCREW 6 AILERON TRIM SCREW 7 MOUNTING BRACKET ELEVATOR TRIM SCREW 9 PIN AND COTTER PIN 10 SLEEVE 11 BUSHING AND PLATE 12 SHAFT Figure 27 10 Trim Controls Installation 13 ELEVATOR TRIM CONTROL 14 GEAR BOX 27 14 02 Page 27 35 Issued April 25 1983 2E15 ...

Page 393: ...LES Figure 27 11 Aileron Control Travels and CableTension C574 ASSY SEENOTE 1 2 ASSY NOTE 1 NOTES 1 AFTER STARTING WIRE THRU HEAD OF SCREW MAKE ONE COMPLETE WRAP AROUND SHANK OF SCREW NEXTTOJAM NUT FINISH WIRING THRU HOLES PRO VIDED IN FORGING INSTALL SAFETY WIRE THRU HEAD OF SCREW WITH WET ZINC CHROMATE 2 THE LOCK WIRE SHOULD ALWAYS BE INSTALLED AND TWISTED SO THAT THE LOOP AROUND THE HEAD STAYS ...

Page 394: ...m from unwrapping 2 Position the screw assembly in the wing install the attachment cap bolts and torque 3 Drawnthe cables through the wing and connect them at the turnbuckles at wing station 90 00 If the cables from the fuselage are not installed block the cables at the rib at wing station 87 50 by reaching through the accessopening at wing station 92 50 4 Remove the cable blocks from next to the ...

Page 395: ...2 Remove the left row of floor panels and the floor panel lateral to the entrance door 3 Remove the interior access panel to the aft section of the fuselage 4 Remove the tail cone and the access plate under the rudder on the top aft section of the fu elage 5 Loosen the aileron and rudder interconnecting cables at the turnbuckles at station 283 0 in the aft section of the fuselage enough to allow t...

Page 396: ...LE AFT 17 RUDDER SECTOR 18 TURNBUCKLE 19 RUB BLOCK 20 TRIM CABLE FWD 21 FAIRLEAD 22 SCREW ASS Y TRIM FWD 23 SCREW ASS Y TRIM AFT 24 STOP TRIM SCREW 25 SCREW TRIM 26 SAFETY WIRE 27 DRUM TRIM 28 CONTROL ROD 29 STOP TRIM SCREW 30 BOLT ASSEMBLY 31 RUDDER TUBE 32 BOLT ASSEMBLY 33 BOLT ASSEMBLY 34 CABLE END 35 BRACKET 36 BOLT ASSEMBLY 37 SECTOR STOPS 38 STEERING SECTOR 39 PULLEY 40 STEERING CABLE 41 TUR...

Page 397: ...PULLEY FWD SKETCHA FUSELAGESTATION 83 34 SKETCHB FUSELAGE STATION 274 92 c826 INTERCONNECTION CABLE ELEVATOR RUDDER CABLE CABLE 44 VIEW A A 194 INTERCONNECTION CABLE RUDDERCABLE SKETCH D FUSELAGE STATION 242 50 SKETCHC FUSELAGESTATION 125 21 Figure 27 13 Rudder and Rudder Trim Controls cont 27 21 02 Page 27 40 Issued April 25 1983 2E20 ...

Page 398: ...31P 350 MAINTENANCE MANUAL c29 RUDDER CABLE 31 10 9 ELEVATOR CABLE DOWN INTERCONNECTION CABLE SKETCH E SKETCHF C827 C828 42 39 SKETCHG SKETCHH Figure 27 13 Rudder and Rudder Trim Controls cont 27 21 02 Page 27 41 Issued April 25 1983 2E21 ...

Page 399: ...ure 27 13 1 Position the rudder sector under the rudder torque tube and hinge Install bolts and torque 2 Connect the rudder cables to the sector and secure Allow the cable ends to rotate freel 3 Set cable tension per Figure 27 14 and rigging and check adjustment 4 Install access plate panel and seat C805 RUDDER AND RUDDER TRIM TAB NOTE Trim Tab Travel with CABLE TENSIONS RUDDER RUDDER TRIM TAB 25 ...

Page 400: ...e turnbuckles 3 Disconnect the rudder control cables from the pedal assembly 4 Disconnect the brake master cylinder from the pedal assembly 5 Disconnect the balance cable from the two inboard pedals by removing the flat head pins at rudder pedals 6 Remove the rudder torque tube guards by removing the machine screws nuts and clamps positioning the guards to the torque tube and remove the attaching ...

Page 401: ...ss of 012 02 P N 1102 35 018 02 P N 81102 36 and 032 P N 81102 37 5 Lubricate and slide the torque tube through side of the fuselage and right bearing far enough to slide the right retainer collar on the tube 6 Slide the tube through the outer torque tube assembly installing the left pedals and left retainer collar 7 Insert the bolts through bolt retainer collars and tube do not install nut and de...

Page 402: ...R NUT BOLT 2 MOUNTING BRACKET 11 BOLT 23 PLATE 35 TORQUETUBE GUARD 3 BEARING BLOCK 12 BEARING BLOCK 24 ROD 36 MACHINE SCREWS 4 BOLT 13 SPACER 25 CONTROLCABLE AND NUTS 5 RETAINER 14 OUTERTORQUETUBE 26 BRAKE CYLINDER 37 SCREWS NUTS AND 6 TORQUETUBE 15 BOLT 27 PEDAL RIGHTOUTER CLAMPS 7 BOLT 16 ROLL PIN BOLT 28 PEDAL RIGHT INNER 38 PULLEY 8 ROLL PIN BOLT 17 BOLT 29 JAM NUT 39 FLAT HEAD PINS 15 SKETCHA...

Page 403: ...the elevator torque tube and slide it to the left until the centerline on thejig plate aligns with the centerline of the airplane D Set a bubble protractor to 29 28 and position it on the centerline of the jig plate This angle assures rudder travel measurement perpendicular to the rudder hinge centerline E With protractor still set to 29 28 center the bubble by adjusting the screwsat the aft end o...

Page 404: ...the cable ends to pass through 9 Cut safety wire and remove the roll pin that secures the flexible joint to the control shaft of the trim screw assembly 10 Remove the bolts that attach the screw assembly to its mounting bracket Draw the assembly with cables from the control pedestal INSTALLATION OF RUDDER TRIM CONTROL PEDESTAL Refer to Figure 27 13 1 Ascertain that the cable is evenly wrapped on t...

Page 405: ...between stops on the trim screw and the cables blocked to prevent them from unwrapping 2 Position the screw assembly in the vertical fin install the attachment bolts and secure 3 Draw the cables through the fin into fuselageand connectthem atthe turnbuckles at station 287 5 If the cables from the control pedestal are not installed draw the cables tight and block them at the bulkhead at station 317...

Page 406: ...maintenance repair rigging and adjustment of the elevator control system ELEVATOR CONTROL CABLES REMOVAL OF ELEVATOR CONTROL CABLES Refer to Figure 27 18 CA UTION Exercise care that the elevator control tube does not incur nicks dents or deep scratches during installation removal or rigging operations Visually reinspect the elevator control tube each time it is removed or reinstalled in the aircra...

Page 407: ...uard pins at stations 121 38 153 35 193 73 242 00and 276 00 H To removecablethat leadsto the lower end of the elevator bellcrank left cable removethe cable guard pins at stations 121 38 160 20 200 98 242 00and 276 00 I Removethe fairleads at fuselagestation 137 00 J Draw the cable aft through the fuselage INSTALLATION OF ELEVATOR CONTROL CABLES Refer to Figure 27 18 CAUTION Exercise care that the ...

Page 408: ...00 3 Set cabletension per Figure 27 19 check riggingand adjustment 4 Install access plates panels and seats ELEVATORBELLCRANK CAUTION Exercise care that the elevator control tube does not incur nicks dents or deep scratches during installation removal or rigging operations Visually reinspect the elevator control tube each time it is removed or reinstalledin the aircraft 1 Remove the left pilot s s...

Page 409: ...E 13 TRIM CABLE 14 BELLCRANK 15 ROD CONTROL 16 SPRING 17 LINK 18 ARM ELEVATOR 19 TRIM SCREWASSY 20 CABLE END 21 BOLT ASSEMBLY 22 BOLT ASSEMBLY 23 BOLT PIVOT 24 ROD END 25 BOLT ASSEMBLY 26 JAM NUT 27 TRIM SCREW ASSY 28 PULLEY 29 TRIM CABLE 30 GUIDE BRACKET 31 TRIM SCREW CLEVIS 32 BUSHING 33 TRIM TAB ROD 34 BOLTASSEMBLY 35 ROD END 36 ROD CABLE GUARD Figure 27 18 Elevator and Elevator Trim Controls 2...

Page 410: ...T PA 31P 350 MAINTENANCE MANUAL AILERON RUDDER CABLE CABLE C425 NOTE SURE THE CABLE IS ROUTED BE EEN THE CABLE GUARD AND THE FWD SKETCHA FUSELAGESTATION 83 34 C830 36 VIEW A A 186 ELEVATOR SKETCHC FUSELAGE STATION 125 21 SKETCHD FUSELAGE Figure 27 18 Elevator and Elevator Trim Controls cont 27 32 01 Page 27 53 Issued April 25 1983 2F9 ...

Page 411: ...EVATOR CABLE DOWN 1 CAUTION EXERCISECARETHAT THE ELEVATOR CONTROL TUBE DOES NOT INCUR NICKS DENTS OR DEEP SCRATCHES DURING INSTALLATION REMOVAL OR RIGGING OPERATIONS SKETCH E C832 Figure 27 18 Elevator and Elevator Trim Controls cont 27 32 01 Page 27 54 Issued April 25 1983 2F10 ...

Page 412: ...t the elevator in neutral position by placing a modified straightedge as shown in Figure 27 20 against the underside of the horizontal stabilizer next to and outboard of the row of ri ets at station 38 00 with the aft end of the tool even with trailing edge of the elevator This tool may befabricated from dimensions given in Chapter 95 3 With the elevator in neutral position check or adjust the ele...

Page 413: ...spring adjusted to 45 I pounds tension with elevator in neutral position 7 Check control operation and direction of travel bolts and turnbuckles for safety and installation of cable guards 8 Check the complete elevator control system including autopilot if installed to determine the friction in the system 9 Install access plates and panels tail cone and seats ELEVATOR TRIM CONTROL PEDESTAL The ele...

Page 414: ...e 6 Block the forward trim cablesat the trim screwassemblywithin the control pedestaland the alt cablesat bulkhead 317 75 to preventthe cablesfrom unwrapping from their drums byone ol the methods shown in Figure 27 6 If the aft screwassemblyis also to be removed then removethe access plateattached to the undersideof the horizontal stabilizer and block the cablesat the screw assemblyinsteadof in th...

Page 415: ...to Figure 27 18 I Remove the access plates located on each side of the fuselage and on the bottom side of the elevator and also remove the tail cone assembly 2 Block the forward trim cables at bulkhead station 274 00 by one of the methods shown in Figure 27 6 to prevent the cables from unwrapping If the forward trim assembly is also being remove block the cables at the forward trim screw below the...

Page 416: ...ve of the idlerpulley to the capstan and around the top groove of the idlerpulley to the aft section of the airplane completing a figure eight Refer to Figure 27 22 4 It the forward trim cables are not installed draw the rear cables tight and block the cables at bulkhead station 317 75 Install the forward trim assembly 5 Install the cable guard pins in the pulley at station 352 00 6 Connect the ro...

Page 417: ... is in specifieddown position per Figure 27 19with the elevators neutral 4 Check the rod ends for adequate thread engagement 5 Rotate the trim control wheelin the cockpitto the fullnose downpositionand checktab position per Figure 27 19with the elevators neutral Adjust the screw stops to obtain proper travel 6 Coordinate the trim wheel indicator with the tab position DETERMININGFRICTIONIN THEELEVA...

Page 418: ...310 SPRINGSCALE PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL TRAILING EDGL I I I I I OUTBOARD TAB DOW N Figure 27 23 Elevator Friction Measurement 27 37 00 Page 27 61 Issued April 25 1983 2F17 ...

Page 419: ... of flap position and condition over its full range In addition to the limiting of both up and down overtravel the system will shut the driving mechanism off in the event of 5 or more differential between right and left flap position and it will self monitor and automatically react appropriately in the event of critical component failure in the control circuitry Preselection of any desired flap po...

Page 420: ... 15 BUSHING AND SCREW ASSY 16 FLAP HORN 17 BOLT ASSEMBLY 18 TUBE TRANSMISSION BOLT AN3 4A WASHER AN960 10L GROMMET MS35489 33 13 NUT MS20365 1032C PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL SKETCHC FLEXIBLESHAFT IN 120 19 SWITCH DOWN LIMIT 20 SHAFT SENDER 21 ARM SENDER 22 SENDER FLAP POSITION 23 SWITCH UP LIMIT 24 ADJUSTMENT BOLT UP LIMIT 25 ADJUSTMENT BOLT DOWN LIMIT 26 ATTACHMENT BOLTASSY 27 G...

Page 421: ...AFT PA 31P 350 MAINTENANCE MANUAL A497 RT2 RT3 RC RL RR GND AMPLIFIER GND AMPLIFIER ADJUSTMENT RHEOSTATLINKAGE LEFTCONTROL RHEOSTAT RL Figure 27 25 Flap System Diagram 27 50 O Page 27 64 Revised July 28 1983 2F20 ...

Page 422: ...cated on the forward side of the fuselage bulkhead at station 174 00 Disconnect the electrical leads from the motor 3 Cut the safety wire and disconnect the flexible drive shaft ends from the motor 4 Remove the clamp that holds the motor on its mounting bracket Remove the motor 5 If desired to replace the shock grommets in the bulkhead the motor with itsmounting brackets may be removed together by...

Page 423: ...IRCRAFT PA 31P 350 MAINTENANCE MANUAL A489 SKETCH A 15 3 15 18 2 1 19 16 6 7 SKETCH A 9 SCREW 10 STUD CONTACT 11 NUT HEX 12 WASHER LOCK 13 SHOULDER WASHER 14 ENDBELL 15 BEARING BALL 16 WASHER SPRING 17 ARMATUREASSY 18 SLEEVEAND MAGNETASSY 19 PLATE IDENTIFICATION Figure 27 26 Motor Assembly Exploded View 2F22 27 51 02 Page 27 66 Revised July28 1983 ...

Page 424: ...ars as measurement is stepped around commutator B Insulation resistance between commutator and shaft should be 10megohm minimum at 85 ASSEMBLY OF FLAP ACTUATOR MOTOR Refer to Figure 27 26 1 Assemble shoulder washers contact studs lockwashers and nuts to front end bell Position flat on contact studs parallel to the side of the brush holder Torque outer nut to 30to 35 inch pounds See Sketch A of Fig...

Page 425: ... Checkflapriggingandadjustments perinstructionsgivenin thischapter 6 Installaccess platesand panels FLEXIBLEACTUATORSHAFT Refer to Figure 27 24 REMOVALOF FLEXIBLEACTUATORSHAFT Refer to Figure 27 24 1 Remove the centerfloor panellocatedin themaincabinarea 2 Remove the rightand or left rowof seats and floor panelsaft of themainspar 3 Remove theaftaccess plateonthefairinglocated ontheunderside betwee...

Page 426: ...ASSEMBLY OF FLAP TRANSMISION Refer to Figure 27 27 1 Remove safety wire bolts and rear housing 2 Remove O ring 3 Straighten tang on lockwasher so that locknut and lockwasher can be removed 4 Remove ball screw and tube assembly 5 Remove bearing assembly and shim 6 Remove worm gear key and shim 7 Remove front bearing assembly from housing 8 Remove protective cap if used 9 Remove screws and both outp...

Page 427: ...WIPER 10 SCREW MACHINE 11 WIPER 12 GEAR WORM 13 KEY 14 BEARING ASSY FRONT 15 CAP PROTECTOR 16 FLANGE OUTPUT 17 SCREW MACHINE 18 SHIM 19 BEARING BALL 20 SHAFT WORM 21 HOUSING ASSY FRONT 22 O RING 23 INSERT HELI COIL 24 INSERT HELI COIL 25 WASHER RUBBER BUMPER 26 HOUSING FRONT STEEL BALLS 67 69 OUTPUT TUBE SKETCH A Figure 27 27 Flap Transmission Exploded View 2G2 27 53 02 Page 27 70 Issued April 25 ...

Page 428: ... 4 Discard and replace all bearings O rings wiper and bumper washer 5 Inspect worm shaft and worm gear for excessive wear If worm gear is worn more than 0 015 inch Refer to Figure 27 29 the worm gear and worm shaft must be replaced as a set 6 All defective or worn parts must be replaced Do not attempt to repair defective parts ASSEMBLY OF FLAP TRANSMISSION Refer to Figure 27 27 1 Assemble ball scr...

Page 429: ...o housing 6 Insert both ball bearings into housing making sure bearings are seated 7 Attach one output flange and secure with four screws On opposite side attach output flange with two screws Using a dial indicator check end play of worm shaft and add shim as required to obtain 0 004 to 0 010 inch end play Secure with four screws 8 Insert tool 7801 T3 onto spline of worm shaft and check that shaft...

Page 430: ...MEASUREGEAR PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL PIN 27 53 04 Page 27 73 Issued April 25 1983 2G5 ...

Page 431: ...him previouslydetermined on top of worm gear 18 Place rear bearing flangeside up in housing 19 Place lockwasherover ball screw Thread locknut chamferedsidedown onto screw CAUTION Make sure ball nut and tube assembly is positioned awayfrom housingbefore tighteninglocknut 20 Torque locknut to 80 inchpounds minimum to align lockwashertang withslot in nut Bendtang into slot REARBEARING MEASUREREARBEAR...

Page 432: ...h 22 PlaceO ring into O ring groo ein housing Install rear housing and attach with bolts Torque bolts to 35 40 inch pounds FUNCTIONAL TEST OF FLAP TRANSMISSION 1 estequipment required A Tool 7801 T3 B Torque Wrench 2 Check no load torque as follows A Attach torque wrench to input pinion B Measure torque to rotate pinion with no load applied to screwja ack C No load torque to be 12 in 0z maximum 3 ...

Page 433: ...flap up position VCR Voltage differencebetween VC VR at flap up position VRL Voltage differencebetween RL RR RT2 AmplifierTrimmer Adjustment Left RT3 AmplifierTrimmer Adjustment Right The Control rheostat operated bythe Flap Selectorwillbereferredto throughout thisriggingprocedure as RC rheostat control The wing flap rheostats willbedesignatedas RL rheostat left and RR rheostat right The voltages ...

Page 434: ...P limit actuating bolt so that the switch is actuated witha 03inch maximum gap between the rollers and the end of the flap track slots See Figure 27 30 Sketch B NOTE It is the intent here that the electrical limits be reached just prior to the mechanical bottoming out of the rollers in the slot F Repeat the procedure of Step E preceding to adjust the DOWN limit switch See preceding NOTE G With the...

Page 435: ...XX X XX X XX U Thevaluesat the DOWN positionhavealreadybeenestablishedfor VC VLand VRinStep P preceding At this timeenter the readingsfor VC VL and VR at the UP position The work sheet might now resemblethe following example voltage values used in this example are for illustrativepurposes only They are NOT systemrequirements VC VL VR DOWN 9 15 8 95 8 95 UP 4 06 4 42 seestep3 4 4 36 see step3 4 CAU...

Page 436: ...PIPER AIRCRAFT PA31P 350 MAINTENANCE MANUAL A404 ACTUATOR ARM SKETCHA UP LIMIT DOWN LIMIT SKETCHB Figure 27 30 Flap Rigging Adjustments 27 54 00 Page 27 79 Issued April 25 1983 2G11 ...

Page 437: ...trokeand positionindication placethepositiveprobe of the digital voltmeterin RR at the amplifierand the negativelead inRL Selectthe flapsfull DOWN and monitor the voltagethroughout theextension Voltageisnot to exceed 15volts at any time NOTE The System should be allowedto warm upfor approximatelyfive minutes before making any electricaladjustments F It isconsidered to bea properflap position indic...

Page 438: ...ch switch arm 14 on the sender shaft so the arm will contact the roller on the switch actuator in the center Position the arm on the sender shaft as shown in Figure 27 24 Check that the approach flap switch is activated when the flaps are lowered to 15 1 lift flap trailing edge to obtain angle measurement 5 Install the access plates FLAP CONTROl BOX REMOVAL OF FLAP CONTROL BOX 1 Remove the knob fr...

Page 439: ...diagram of the system whenaccomplishingthis testprocedure To gain access to the system components refer to the appropriate Removal andInstallationInstructionsin thissectionofthemanual 1 Pull all circuit breakers to the OUT position 2 Actuate the flap motor and flap control circuit breakers 3 Turn ON battery master switch or connect external power to aircraft 4 Operate the flap selector handle in t...

Page 440: ... RL on the amplifier Use long enough meter leads so the person adjusting potentiometers can also read the voltmeter If this voltage exceeds 0 55 volts the shut down isdue to flap asymmetry Correct cause of asymmetry and rerigflap system 17 Connect the voltmeter between test jacks RR and GND on the amplifier Voltage should equal RC voltage within 0 3 volts 18 Connect the voltmeter between test RLan...

Page 441: ...ustedat the factory whenthe airplane istestflown and shouldnot require anyfurther adjustmentduring the normal servicelife of the airplane Should sometype of ser iceon the wing require removing the switch the following instructions will help in positioning the switch at the proper position I ooen the two Phillips head screws one on either side of the vane If the stall warning comes on too late move...

Page 442: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL GRIDS 2G17 THRU 2G24 INTENTIONALLY LEFT BLANK 2G17 ...

Page 443: ...CHAPTER FUEL 2H1 ...

Page 444: ...neral 2H21 28 5 02 Handling Of Repair Materials H21 28 5 03 Repair I imitations Of Fuel Cells 2H22 28 5 04 Repair Patch Heat Cure Method H22 28 15 05 Repair Patch Air Cure Method 211 28 15 06 Metal Fitting Sealing Surfaces 211 8 l 5 07 Accessor Replacement 211 28 15 08 Defect Repairs Of Fuel Cells 212 28 15 09 Testing Fuel Cells 212 28 16 00 Fuel Vent System 213 1R 7 28 20 00 DISTR UBTI ON 214 28 ...

Page 445: ...f Electric Fuel Pump BenchTest 2114 28 23 06 Adjustment Of Electric Fuel Pump In The Airplane 2114 1R 7 83 28 23 07 Installation Of Electric Fuel Pump 2116 1R 7 83 28 23 08 Removal Of Submerged Fuel Pump 2116 1R7 83 28 23 09 Installation Of Submerged Fuel Pump 2117 1R7 83 28 40 00 INDICATING 2118 IR 7 86 28 40 01 Descriptionand Operation 2118 IR 7 86 28 41 00 System Component Location 2118 IR 7 86...

Page 446: ...ed by a push pull control on the fuel control panel in the cockpit The valve is used as an ON OFF valve for the fuel system A manually operated shutoff val e is also pro ided at the tank outlet to shut the fuel off for filter cleaning The only other al e in the system is the crossfeed which is mechanically operated from the fuel control panel This valve should always remain OFF except under single...

Page 447: ...anks Filters dirty Fuel lines damaged or improperly installed O rings improperly installed Full fuel tanks and fuel expansion due to exposure to heat Float valve in wing tip sticking open or leaking YSTEM Remedy Check and reset Check and repair Replace Check ground connection at gauge and at fuel transmitters in the wings Clear vent holes Replace O rings or valve Trace lines and locate obstruction...

Page 448: ...roperly Inboard fuel transmit ter assembly grounded Shutoff valve off Fuel valve stuck Adjust filler caps to obtain tight seal Check inboard fuel transmitter installation and repair Turn on Check valve No fuel in tanks Filters dirty Defective fuel pump Defective gauge Check fuel fill Clean filters Check pump for pres sure build up Check diaphragm and relief valves in engine pump Check for obstruct...

Page 449: ...t does not appear to work Gauge appears to work properly on part of its range only Gauge appears to work properly but is not properly calibrated Gauge gets 24VDC but only reads on bench because system is shorted One or more bad Tank Sensor Units Tanks are partly or completely filled with other than Avgas fuel Replace Fuel Quantity Indicator Clear short or electrical leakage from wing tank sensors ...

Page 450: ...I PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 3306 18 Figure 28 1 Fuel System Schematic 28 00 02 Page 28 05 Revised July 28 1983 2H8 ...

Page 451: ...AIN VALVE 13 FILLERCAP 14 CHECKVALVE 15 SENDERUNIT NACELLE FUEL CELL 16 SUMP DRAIN VALVE 17 SUBMERGED FUEL BOOSTPUMP 18 SHUTOFF VALVE 19 NOZZLESAND NOZZLELINES 20 FUELFLOW GAUGE 21 FUEL PRESSUREGAUGE 22 INDICATOR LIGHT BOOSTPUMP FUELPRESSURE 23 FUELSELECTORPANEL 24 CROSSFEEDVALVE 25 CROSSFEEDDRAIN VALVE 26 TRANSDUCER PRESSURE 27 CHECKVALVE 28 PRESSUREREGULATORAND SHUTOFF VALVE 29 HEATER 30 CHECKVA...

Page 452: ...the electricalconnectionsand fuellinestothesubmerged fuelpump removetheshutoff valve and disconnect the fuel line that connects to the celljust aft of the pump by looseningthe clamp 9 Loosenthe mounting bolts that attach the submerged fuel pump to the wing rib reach through access hole above the pump and remove pump 10 Reach through the proper accessholesfor each fuelcelland untie the nylon cords ...

Page 453: ...L CELL GASKET 5 COVER FUEL CELL 6 ACCESS COVER 7 FUEL CELL ATTACHMENT PLATE 8 SCREW ASSEMBLY FLAPPERVALVE ATTACHMENT 9 FLAPPERVALVE 10 TIE KNOTS 11 WING SKIN 12 CORD 13 RIB ASSEMBLY 14 LOOP ATTACHMENT 15 LINER ASSEMBLY 16 SNAP BUSHING 17 FILLER CAP 18 O RING 19 ADAPTER FILLERCAP 20 BRACKET FUEL CELLFILLERNECK 21 KNOT AND WASHER 16 Figure 28 2 Fuel Cell Installation Inboard 2Hll 28 11 01 Page 28 08...

Page 454: ...SSEMBLY ACCESS 2 LINER ASSEMBLY 3 FUEL SENSOR 4 GASKET FUELSENSOR 5 FUEL CELL ATTACHMENT PLATE 6 FUEL SENSOR SUPPORT PLATE 7 FUEL CELL GASKET 8 WING SKIN 9 RIB ASSEMBLY 10 LOOP ATTACHMENT 11 TIE KNOTS 12 CORD 13 FUEL CELLCOVER 14 SNAP BUSHING 15 KNOT AND WASHER Figure 28 3 Fuel Cell Installation Outboard 28 11 01 Page 28 09 Revised July 28 1983 2H12 ...

Page 455: ...CESS 9 FUEL SENSOR 10 GASKET FUEL SENSOR 11 KNOT AND WASHER 12 LOOP ATTACHMENT 13 FUEL CELL PLATE 14 LINER ASSEMBLY 15 BUSHING PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 9 11 12 NOTE FUELSENSORSARE NOTINTERCHANGE ABLE CONSULT PARTS CATALOG FOR PROPERREPLACEMENTPART Figure 28 4 Fuel Cell Installation Nacelle 2H13 28 11 01 Page 28 10 Revised July 28 1983 ...

Page 456: ... cell into the shape and size which can be inserted through the access opening of the wing 6 After fitting the cell into the wing unroll the cell and establish correct relationship of the cell to the compartment 7 From each end of the cell compartment feed the cord through the cell hangers and rib bushings until the cords can be joined at the access openings Do not tie cord yet The cords are route...

Page 457: ...wn into the corresponding hole in the cell nut flange and pull the cell up against the bracket in the nacelle floor and install several cap bolts to hold the fuel cell until the rod is removed then install all cap bolts and torque to 35 5 inch pounds 15 Connect the fuel lines that attach to the outboard ends of the fuel cells and the drain line that runs from the inboard end of the main outboard f...

Page 458: ...gh to flex Do not use sharp tools such as screwdrivers files etc for installation purposes 4 Place tape or another protective material over the edges of the access opening to prevent damage to the cell 5 Roll the cell into the shape and size which can be inserted through the access opening of the cell compartment 6 Unroll the cell and establish correct relationship of the cell to the compartment I...

Page 459: ...STEP3 PIPER AIRCRAFT PA 31P 350 STEP 1 STEP2 STEP4 STEP5 STEP6 STEP 7 Figure 28 6 Fuel Cell Tie Detail 250 Figure 28 7 Installation of Fuel Vale Drain Plate 28 11 04 Page 28 14 Issued April 25 1983 2H17 ...

Page 460: ...y this action with MEK If fine cracks are evident the fuel cell is not repairable 2 Fuel cells may be inspected by the following procedure A New Cells Inspect the cell surface inside and outside for cuts abraded scuffed areas and accessory damage Also inspect the fitting seals for nicks scratches and foreign material B Used Cells Cells removed from the airframe cavity for inspection and repair or ...

Page 461: ...he cell compartment of all foreign material such astrimmings loosewashers bolts or nuts 2 Round off any sharp edgesin the fuel cell compartment 3 Inspect the fuel cell compartment just prior to fuel cell installation 4 Tape over all sharp edgesand all rough rivets MOLDED NIPPLE FITTINGS The molded nipple fitting is a lightweight fitting developedfor easein installation in certain location in the a...

Page 462: ...natural contours if possible while repairing Prevent contact with sharp edges corners dirty floors or other surfaces Repair area must be well ventilated Do not stack cells Inspect cavities and insure cleanliness prior to installing any cell WARNING Do not permit smoking or open flame near repair area or cells 2 When storing cells observe the following rules A Fold cells smoothly and lightly as pos...

Page 463: ...entatives or those who have re ceived their training from persons who have been certified and trained by Goodyear representatives To determine iffuel cell is repairable reach through the fuel cell access plate and take a section of cell between thumb andforefinger Wipe the ridge created by this action with MEK If fine cracks are evident the fuel cell is not repairable HANDLING OF REPAIR MATERIALS ...

Page 464: ...ed for 72 hours at roomtemperature of approximately 75 F CA UTION For each 10 drop in temperaturefrom 75 F add 20 hours cure time For example at 65 F curefor 92 hours 11 All heat cured patches are ready for use when cool 12 Fitting repairs are confined to loose flange edges seal surface rework and coat stock 13 The maximum number of heat cure repairs in the same area is four NOTE Any damage not co...

Page 465: ...t is necessary to perform the repair Group II equipment w ill be furnished at additional cost ifordered by customer Foam Rubber Cloth Back Sheet 14 x 12 x 12 Paint Bruh I inch wide Aluminum plates 1 4 x 6 x 6 4 Measuring cup 250 ml I Cellophane Sheet 12 x 24 2 NOTES Accessories order per individual cell requirements Phenol plates phenol plate assembliesand phenol test equipment can be ordered as r...

Page 466: ...may be moved by hand on wet surface to improve lap Do not lift repair patch slide it CAUTION Make sure cellophane inside cell over injury remains in place as any cement will stick cell wallstogether without it as a separator 10 Cover one smooth surface each of two aluminum plates plates must be larger than patch with fabric backed airfoam fabric side out Tape airfoam in place Foam must coveredgeso...

Page 467: ...one Moisten cleaned surface with clean cloth dipped in water Apply alodine 1200 solution undiluted to the affected area witha small nylon brush Allow solution to dry until a light golden color appears When coating has been formed remo e excess solution by wiping with a clean water moistened cloth Allowcoating to dry WARNING Do not allow solution to come in contact with hands eyes or clothing ACCES...

Page 468: ...ither method may be used See Repair Patch Loose seams may be trimmed if minimum lap remains 4 Loose Fitting Flange Inside Buff edge of flange and contact surface under flange Apply 80C27 mixed repair cement cellophane padded plates and clamp Followsprocedure as outlined for repair patch except for patch itself 5 Looseness Against Metal Prepare metal as per metal fitting sealing surfaces Appl 80C27...

Page 469: ...ate use should be stored in a closed rust proof container to prevent evaporation and deterioration After the test remove all plates and test equipment Allow the cell to air out In conducting either test outlined above the cell need not be confined by a cage or jig providing the 1 4 psi pressure is not exceeded NOTE The chemical test is the more sensitive and preferred test FUEL VENT SYSTEM The mai...

Page 470: ...fuel line from the aft end of the valve and control cable from the actuator arm on the valve 8 Disconnect the valve from the mounting bracket and unscrew and remove the valve from the cross fitting DISASSEMBLY OF CROSSFEED VALVE AND FUEL SHUTOFF VALVE Refer to Figures 28 9 and 28 10 1 Crossfeed Valve A Disconnect the control arm from the valve step by removing nut from the pin B Push the stem out ...

Page 471: ...s on the valve C Lubricate the O rings with DC 55 MIL G 4343 and insert the valve in the valve body Place the valve in the valve body so that the valve is allowed only 90 travel between stops D Lock the valve in the valve body by installing the snap ring on the valve E For the fuel shutoff valve install the two clamps For the crossfeed valve install one clamp 2 Crossfeed Valve A If seat valve was ...

Page 472: ...lueinits proper positionand secure it to its mounting bracket or with attachment clamps whichever value is being installed 2 Connect the proper fuel lines to the valve and also connect the control cable to the actuator arm with the attaching hardware 3 Put enough fuel in tank if not already there and check valve and end fittings for leaks 4 Install lower wing root fairing ADJUSTMENT OF FUEL SHUTOF...

Page 473: ...15 C833 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 3312 NOTE TORQUENUT60 TO80 INCH POUNDS SKETCH A 3312 SEE NOTE SKETCH C SKETCH B Figure 28 1 1 Fuel SystemInstallation 28 21 07 Page 28 28 Issued April 25 1983 217 ...

Page 474: ...P SCREW AND NUT 16 SCREW BUSHING AND WASHER 17 LOCK WASHER 18 PUMP ASSEMBLY 19 CABLE FUEL SHUTOFF VALVE 20 BALL JOINT AND NUT 21 NUT AND WASHER 22 VALVE ASSEMBLY FUEL SHUTOFF 23 PLATE ASSEMBLY 24 SCREW AND NUT 25 SCREW BUSHING AND WASHER 26 LOCK WASHER 27 HOSE ASSEMBLY 28 SAFETYWIRE 29 WING FILLET 30 ELBOW 31 LINE TO DRAIN 32 VALVE ASSEMBLY CROSSFEED 33 CROSSFEEDLINE 34 SCREW 35 CROSSFEEDVALVE 36 ...

Page 475: ... 1 Turn the fuel shutoff valve to the OFF position 2 Remove the access panel forward of the main spar between the underside of the wing and the fuselage 3 Disconnect the electrical leads to the fuel pump 4 Disconnectthe fuel lines to the filter and fuel pump Cover the lineends to prevent contaminatio 5 Remove the bolts that secure the filter and pump to their mounting brackets 6 Separate the filte...

Page 476: ...13 1 Wash the element in oil solvent such as mineral spirits It is not necessary to remove discs from element outlet tube for normal cleaning Plug open ends of element outlet tube while washing to keep out dirt 2 Inspect filter discs for damage and broken screens 3 Check condition of bowl gasket and washer 4 Check condition of bowl drain and drain O ring 5 Check for corrosion of filter parts 6 Che...

Page 477: ...nting brackets and secure 3 Connect the lines to the filter and pump tee 4 Connect the line from the pressure switch to the fitting on the filter 5 Connect the electrical leads to the fuel pump 6 Turn on the fuel valve and check for fuel leaks 7 Install the access plate CLEANING FUEL SYSTEM 1 To flush the fuel system disconnect fuel line at the injector 2 Turn on the electric fuel pump and flush f...

Page 478: ...aft Remove blade retaining spring and blades Also O ring seals 6 Using a light arbor press apply pressure to valve adjusting screw to release tension against the Tru Arc retaining spring and remove the spring with Tru Arc pliers Pull out adjustment guide containing O ring seal adjusting screwand locknut 7 Remove the valve spring and piston assembly CLEANING INSPECTION AND REPAIR OF ELECTRIC FUEL P...

Page 479: ...AR PLATE SPRING 5 WASHER SEAL 6 O RING 18 PISTON 9 SPRING VALVE 20 O RING 21 GUIDE ADJ 22 SCREWADJ 23 LOCKNUT VALVE 11 RING RET 12 ROTOR 13 WEAR PLATE 11 14 WEAR PLATE SPRING 15 PLUG INSER 16 O RING 17 INSERT BEARING RET 18 PISTON 20 O RING 21 GUIDE ADJ 22 SCREW ADJ 23 LOCKNUT VALVE 24 RING RET TRU ARC 15 25 ADAPTER 26 SCREWS 27 SCREWS Figure 28 14 Electric Fuel Pump 28 23 0 Page 28 34 Issued Apri...

Page 480: ...isable to have a full 28 volt DC current when running the pump in order to obtain the correct pressure of 401 psi maximum noflow 5 Run the pump with the bypass valve open until a steady flow of fuel is obtained Then close the bypass valveand check the pressure gauge for the proper reading of 40 psi maximum no flow If boost pump is operated in conjunction with electric fuel pump pressure reading sh...

Page 481: ...PIPER AIRCRAFT PA 31P 350 A WEAR NOTCH EXCEEDING 010 IN DEPTH IN THIS AREA INDICATES THAT BLADE SHOULD BE DISCARDED 28 23 06 Page 28 36 Issued April 25 1983 2115 ...

Page 482: ... fuel shutoff valve and secure Run the pump to check for any fuel leaks 9 Shut off the pump and replace and secure the access panels INSTALLATION OF ELECTRIC FUEL PUMP 1 Connect the fuel pump and fuel filter Tighten thejam nut on the fitting between the pump and filter to allow the O ring to seat on the non threaded portion of the fitting 2 Position the tuel pump and filter on the mounting bracket...

Page 483: ...outofthe fuel cell Either pump is removed in this manner INSTALLATIONOF SUBMERGEDFUEL PUMP Refer to Figure28 15 1 Installation of either fuel pump is accomplishedby first installinga new gasketon the fuel pump mounting boss then insertthe pump into the celland hold itinplacewhileanassistantattaches itto the wing butt rub with the four mounting bolts 2 Reconnect the electrical connections fuel and ...

Page 484: ...or the Lo Z electrical signal which is returned to the indicator Shielded wire is used for the Hi Z lead to the fuel sensor probes to minimize the effects of stray capacitance on system accuracy Termination continuity of the shields and wires must be maintained to ensure system accuracy Test equipment as specified in chart 2805 is required for system test and calibration See figure 28 16for system...

Page 485: ...k age or capaci tance and cali bration Lead Package 101 00431 or 2 coax BNC jumper cables Phone 305 871 3900 Telex 51 8808 or Test Set 89 108 2 Ragan Data Systems 3 Oval Drive P O Box 417 Central Islip NY 11722 Seeabove Phone 516 234 3800 Telex 685 2305 Probe Harness Comeswithtest set or Test Set Test Harness GTF 12 Field fabricated Gull Airborne 395 Oser Avenue Smithtown NY 11787 See above Phone ...

Page 486: ...INATION SHALL NOT EXCEED 3 8 INCH A 302 918 002 INDICATOR bUAL 014 943 013 NACELLE 014 943 012 OUTBD M 014 943 011 INBD MAI ULL PN NOMENCI AIBKCDGHJ IFE MS3126F12 IOS CONNECTOR TYP 3PLACES SPARES STRUCTURE GND D o DONOT USE D SHIELD C E F 28V DC G K POWER GND STRUCTURE GND 3583 TANKUNIT AIN TANK UNIT N TANK UNIT 2 2 2 2 5 4 3 2 LATURE OTYITEM HIZ HIZ LOZ SHIELD B C E 28VDC F K POWER GND STRUCTURE ...

Page 487: ...ION if used on TANK UNITSOR THEIR WIRINGHARNESS when in the presence of fuelor combustiblevapors Thespecial equipment listedin Chart 2805is soldcomplete withoperationinstructionsto beusedfor proper calibration of the fuel quantity indicating system components Thetestequipment listed inchart 2805canbeinsertedinbetweenan installedfuelquantity indicatorand its installed aircraft harness This allows a...

Page 488: ...AINTENANCE MANUAL 3583 TANK UNIT GTF 12 OR EQUIV INDICATOR AIRCRAFTTANK UNITS TEST HARNESS SEE FIG 28 18 TANK UNIT TO BE ON INSULATEDSURFACE Figure 28 17 Tank Unit Test Set Up 28 43 00 Page 28 43 InterimRevision July 23 1986 2122 ...

Page 489: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL D380 36 IN SPADE LUG FOR NO 6 SCREW COAX BNC MALE UNSH BNC FEMALE Figure 28 18 Test Harness Tank Units 2123 28 43 00 Page 28 44 InterimRevision July 23 1986 ...

Page 490: ...ckwise Pointer must not deviate from 400 pound increment by more than 0 010 ua 3 Scale error must comply with chart 2807 CHART 2807 DIAL x 100 0 3 4 6 9 MIN ma MAX ma 0 029 0 270 0 354 0 522 0 785 0 039 0 302 0 386 0 554 0 795 NOTE Abovereadings arevalid only whenlast dialgraduationis setto nom ma 0 794 NOTE Lightly tap indicatorbeforetakingreading 28 44 00 Page 28 45 2I24 Interim Revision July 23...

Page 491: ...INTENANCE MANUAL DRIVE FULL SET 302 918 002 METER TESTER TEST HARNESS SEE FIG 28 20 Figure 28 19 Indicator Test Set Up MS3126F12 IOS A B E F 24 IN Figure 28 20 Test Harness Indicator 28 44 00 Page 2846 InterimRevision July 23 1986 2J1 ...

Page 492: ...hing but one side is too high or too low One side will not properly calibrate or reads uneven fuel burn No D C power to gauge Shorted Lo Z wire or open meter circuit Dead Signal Conditioner Open probe or shorted probe wiring One Signal Conditioner is not calibrated Dirty or contaminated probe Correct loss of 24 VDC to gauge pin F or ground to pin G Remove Signal Conditioner check for short from pi...

Page 493: ...uld be at 0 034 ma If not adjust EMPTY pot on signal conditioner for 0 034 ma 5 Set probe simulator for 108 60pf normal value for full tanks 6 Digital multimeter should read 0 790 If not adjust FULL pot for 0 790 7 Repeat steps 2 through 6 until no further adjustment is necessary Figure 28 21 Signal Conditioner Test Set Up MS3126F 12 10 H A D J E C F K G INDICATOR INDICATOR 220 1 100 1 LO Z UNSH H...

Page 494: ...st be corrected and recheckedindividually 8 Remove Barfield unit Hook up ship system and add 2 gallons of fuel to each side Adjust quantity indicator to read zero needle lined up with the inside edge of the white zero line by adjusting the EMPTY screwon the signal conditioner referto figure 28 23 9 Reinstall test equipment Add 44 4 pf to the capacitance obtained from step 6 to simulate 120 2 gallo...

Page 495: ...st indicator if necessary to read zero by adjusting the EMPTY screw on the signalconditioner refer to figure 28 23 6 Addfuelin measuredincrementsof 225poundsto each side Waitten minutesbetweeneachaddition of fuel and check indicator for accuracy after each increment Systemaccuracy 5 of full scalefor each side 7 Adjust when full by adjusting the FULL screw on the signal conditioner see figure 28 23...

Page 496: ...A 31P 350 MAINTENANCE MANUAL D379 E403 LEFT E404 RIGHT FULL EMPTY CASE SEAL 7 WIRE HARNESS 302 918 002 P N 548 660 SIGNAL CONDITIONER Figure 28 23 Signal Conditioner 28 45 00 Page 28 51 InterimRevision July 23 1986 2J6 ...

Page 497: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 2J7 ...

Page 498: ...CHAPTER HYDRAULIC POWER 2J8 ...

Page 499: ...J24 29 12 07 Checking Priority Valve 2J24 29 12 08 Checking Main Relief Valve 2K2 29 12 09 Checking Hand Pump Relief Valve 2K2 29 12 10 Checking For Suction Air Leakage 2K2 29 13 00 Hydraulic Power Pack 2K4 29 13 01 Removal Of Power Pack 2K4 29 13 02 Installation Of Power Pack 2K5 29 14 00 Disassembly Cleaning Inspection And Repair Of Hydraulic Power Pack And Components 2K5 29 14 01 Power Pack 2K5...

Page 500: ...m 2K20 29 15 17 Adjustment Of Hand Pump Relief Valve 2K21 29 15 18 Adjustment Of Main Relief Valve 2K21 29 15 19 Adjustment Of Priority Valve 2K21 29 15 20 Adjustment Of Door Solenoid Valve 2K22 29 15 21 Adjustment Of Door Vent Valve 2K22 29 15 22 Assemblyof Power Pack 2K23 29 15 23 Testing Reservoir For Leakage 2K23 29 16 00 Hydraulic SystemComponent Servicing 2K23 29 16 01 Operation Of Gear Sele...

Page 501: ...ming Hydraulic Pump Hydraulic System Failure High Altitude Gear Operation 2L8 2L8 2L9 29 20 00 29 21 00 29 21 01 29 21 02 29 21 03 29 21 04 29 21 05 29 21 06 29 21 07 A UXILIARY Hand Pump Emergency Removal Of Hand Pump Disassembly Of Hand Pump Cleaning Inspection And Repair Of Hand Pump Assembly Of Hand Pump Installation Of Hand Pump Bleeding Hand Pump Hand Pump Test 2L9 2L9 2L9 2L9 2LII 2LII 2L11...

Page 502: ...tion The Power Pack works in conjunction with the engine driven pumps solenoid valves and hydraulic cylinders to perform the desired sequence of operation as selected by the control lever in the cockpit CAUTION To insure not having the landing gear moving to the up retracted position while the aircraft is on the ground the following check should be performed prior to applying hydraulic pressure to...

Page 503: ...within this Chapter CHART 2901 TROUBLESHOOTING HYDRAULIC SYSTEM Trouble Cause Remedy Landing gear system fails to operate Selector lever dis connected Connect lever Selector lever out of adjustment Selector lever jammed Note Se lector lever can not be moved to gear up while left main gear strut is compressed or when power is off Hydraulic fluid in reservoir below operating level Leak or obstructio...

Page 504: ...place line Repair or replace cylinder Check valve operation Check system opera tion Check system opera tion Replace damaged O rings Replace pump Selector handle returns to neutral before cycle is complete Cable line or other ob struction restricting the travel required to fully select gearup or down Check and remove obstruction Selector lever out of adjustment Time delay valve and or piston releas...

Page 505: ...With power off solenoid valve shuttles to door open and the doors may be opened without selecting gear up or down Check for loose wire or mounting or bent bracket Doors come open in flight NOTE Refer to Landing Gear Troubleshooting Chart 3201 Doors fail to close Improper rigging of door actuator Malfunction of actuator lock mechanism Faulty limit switch Check for proper rigging Check actuator oper...

Page 506: ... 5606 Examine seals and cylinder bores for damage 7 When the hydraulic system is completely flushed and there is no further indication of contamina tion reconnect the previously disconnected fittings and replenish the system with clean hydraulic fluid 8 Bleed the hydraulic system as described in the section on Bleeding the Hydraulic Systemand check for leaks 9 Replace the engine cowlings as explai...

Page 507: ...5 13 11 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 3314 C 11 12 12 Figure 29 1 Schematic Diagram of Hydraulic System 2J17 29 11 03 Page 29 06 Issued July 28 1983 ...

Page 508: ...TUATOR 10 RESTRICTORVALVE 11 MAIN GEAR ACTUATOR 12 MAIN GEAR DOOR ACTUATOR 13 POWER PACK ASSEMBLY A LOW PRESSURETHERMAL RELIEFVALVE B TIME DELAYVALVE C SIGHT GAUGE D HAND PUMP RELIEFVALVE E PISTON RELEASE LOCK F LANDING GEAR SELECTORVALVE G DOOR SOLENOID VALVE H PRIORITYVALVE I ENGINE PUMP CHECKVALVE J MAIN RELIEFVALVE Figure 29 1 Schematic Diagram of Hydraulic System cont 29 11 03 Page 29 07 Issu...

Page 509: ... 1 GEAR ISSHOWN DOWN AND LOCKED DOORS CLOSED AND SELECTOR HANDLE IN DOWN NEUTRAL POWER ON 2 POWER ON DOORS CLOSED POWEROFF DOORS OPEN GEAR WARNING HORN DOOR SOLENOID DOOR SOLENOID SWITCH ARLIMIT SWITCH RIGHT Figure 29 2 Schematic of Power Pack Electrical System 2J19 29 11 03 Page 29 08 Issued July 28 1983 ...

Page 510: ...e lower forward corner of the nose access panel opening and connect the pressure hose from the test unit Open the valve on the suction port and by placing the control lever in the up position proceed to fill the system per instructions with test unit Observe the fill lines to determine when the reservoir is full It the system must be operated during various ground checks overhaul or inspection of ...

Page 511: ...that the landing gear is down and locked 9 Check the indicator lights for proper operation 10 Remove the airplane from jacks CHECKING LANDING GEAR CYCLE TIME When the hydraulic system on the airplane is suspected of malfunction because gear cycle time is slow it could be caused by low fluid in airplane reser oir causing system to befull of air The following procedure will purge air from the system...

Page 512: ...SERVICEPORT 4 HYDRAULIC SERVICEPORT 5 GEAR ACTUATING CYLINDER LEFT 6 FILTER LEFTPUMP 7 HYDRAULICPUMP RIGHT 8 EMERGENCYHAND PUMP 9 HYDRAULICPUMP LEFT 10 POWER PACK ASSEMBLY 11 GEAR ACTUATINGCYLINDER NOSE 12 DRAIN TUBE i TO SKETCHA Figure 29 3 Hydraulic System Installation 29 12 04 Page29 11 Issued July 28 1983 2J22 ...

Page 513: ...csystem Check actuatorsfor internal leakage Repair or replaceactuators as required If actuators are not defective Power Pack internal leakageis indicated Repair or replacePower Pack CHECKING TIME DELAY VALVE 1 Place the airplane on jacks 2 Connect the hydraulic test unit as described in Connecting Test Unit 3 With test unit operating and airplane master switch ON move the landing gear selector han...

Page 514: ...7 Set hydraulic test unit bypass valve full open 8 Place landing gearselector handle in the full up position 9 Very slowly close the bypass valve until the handle trips back to neutral Read the gauge at the point of handle trip The pressure should be as indicated in Chart 2902 Be sure to allow time for the time delay valve to open 10 Refer to handle release adjustment should it be required 11 Asce...

Page 515: ...alve Open Low Pressure Thermal Relief Vent Valve Closed Priority valve Cracking Pressure Hand Pump Check Valve Cracking Pressure Landing Gear Position Release Time Delay Valve Hydraulic Fluid Required Weight Dr Power Pack Hydraulic Fluid Flow Rate Both Pumps Operating WTC 2135 1 1900P S I 1900 1950P S I 2025 2100 P S I 1900P S I 0 to 100 P S I 150P S I Max 600 650 P S I I to 3 P S I 800 1250P S I ...

Page 516: ...he pilot s seat under the floor and operate emergency hand pump to open landing gear doors 2 Disconnect door open line upper fitting from main gear door cylinder and connect hydraulic test unit pressure hose to door open line Cap actuator fitting 3 Close bypass valve on hydraulic test unit 4 Operate emergency hand pump in airplane observing hydraulic test unit pressure gauge for pressure at hich h...

Page 517: ...1 FITTING VENT 12 HOSE VENT 13 ACCESS OPENING 14 POWER PACK 12 14 9 15 16 18 19 20 21 22 23 24 15 BOLT 16 SAFETYWIRE 17 DRAIN 18 LINE GEAR UP 19 PANEL WHEEL WELL 20 BLOCK 21 LINE RETURNR ENGINE 22 LINE PRESSURER ENGINE 23 LINE DOOR CLOSE 24 LINE GEAR UP 25 LINE DOOR OPEN 26 LINE GEAR DOWN 27 LINE HAND PUMP PRESSURE 28 LINE HAND PUMP SUCTION 29 SUCTION FILLAND DRAIN LINE al 29 12 10 Page 29 16 Issu...

Page 518: ...d baggage compartment NOTE All disconnect and removal work can be accomplished from the upper baggage compartment access or right access panel 2 Drain the Power Pack by removing the drain cap from the end of the drain line on the right sideof the fuselage nose section Place a suitable container under the drain to catch the fluid Replacethe cap after the reservoir is empty 3 To gain access to Power...

Page 519: ... dirt Dry with filtered compressed air To disassemble the unit proceed as follows 1 Remove wire nut reservoircover and O ring Cover is a snug fit on reservoir Usea soft mallet and tap cover lightly to remove 2 Remove deflector plate and snap ring from center stud and remove baffle plate from resercoir Drain remaining hydraulic fluid from the reservoir 3 Remove the reservoir and O ring Reservoir is...

Page 520: ...NOTE THE SHADEDPARTS POPPET 6 AND POPPET SEAT 7 ARE MATCHED PARTS AND MUSTBE REPLACED AS ANASSEMBLY 11 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1323 29 14 01 Page 29 19 Issued July 28 1983 2K6 ...

Page 521: ...SUCTION 49 SNAP RING 50 FILTER HAND PUMP 51 HAND PUMP RELIEFVALVE 52 ADJUSTING SCREW 53 SPRING 54 STEM 55 BODY SECONDARYRELIEFVALVE 56 BALL 57 SEAT 58 O RING 59 CHECKVALVE TIME DELAY 60 SNAP RING 61 O RING 62 SEAT 63 BALL 64 PIN 65 BODY CHECKVALVE 66 O RING 67 BODY 68 O RING 69 BACK UP 70 NUT 71 FITTING 72 BOLT 73 WASHER 74 BRACKET 75 BOLT 76 WASHER 77 PLUG ELECTRICAL 78 SCREW 79 WASHER 80 TERMINA...

Page 522: ...AINTENANCE MANUAL 469 1 3 4 1 DRAIN FITTING 2 MAIN RELIEF VALVE 3 PRIORITY VALVE 4 HAND PUMP SUCTION FILTER 5 HAND PUMP RELIEF VALVE 6 TIME DELAY CHECK VALVE 7 DOOR VENT VALVE 8 STANDPIPE FILTER FWD 29 14 01 Page 29 21 Issued July 28 1983 2K8 ...

Page 523: ...valve sleeve NOTE Be sure that the end of the hook is not over 06 inches long and use the hook with care to prevent scratching the bore in the manifold The sleeve willbe hard to withdrawdue to O ring friction 4 Remove screw spring and the time delay plunger usinga small wooden do el inserted in the center of the plunger The plunger should slide out veryeasily 5 Remove the landing gear selector spo...

Page 524: ...CREW 6 TRANSFERVALVE 7 SLEEVE TRANSFERVALVE 8 0 RING SLEEVE 9 DOOR SELECTORSPOOL 10 SPOOL DOORSELECTOR 11 DOOR SOLENOIDVALVE ASSEMBLY 12 SOLENOID DOOR 13 O RING SOLENOID 14 SPRING PLUNGER RETURN 15 PLUNGER 16 PIN 17 LANDING GEAR SELECTORSPOOL 18 O RING 19 SPOOL LANDING GEAR SELECTOR 20 O RING 21 HANDLE DETENTASSEMBLY 22 O RING 23 PLUNGER 24 O RING 25 SPRING 26 RETAINER 27 O RING 28 FITTING 29 O RI...

Page 525: ...oppetseat 4 Usea brasshook not over 125incheslong and pull the poppetseatup andout of the body Hook throughthe holesin thesideof theseatandusecarenot to damage thebore in thebody 5 Reassemble thepoppetinto poppetseat Thepoppetand poppetseatarematchedparts PRIORITYVALVE Referto Figure29 5 1 Remove theadiustingscrewat the top of the priority alve 2 Remove priority valvebodywith spring buttonand popp...

Page 526: ...springs and plungers CA UTION Take care when removing snap rings cartridges are spring loaded POWER PACK HANDLE RELEASE MECHANISM Refer to Figure 29 8 1 Remove lockwire 2 Using a punch drive the roll pin out of the arm and remove arm 3 Using a punch drive the roll pin out of the return cam and remove return cam 4 Pull the input shaft assembly from Power Pack CLEANING INSPECTION AND REPAIR OF POWER...

Page 527: ...NUAL INDEXING OF PARTS 1 1 SWITCH CAM 2 PIN 3 GEAR 4 PIN 5 DETENTCAM 6 INPUTSHAFT 7 RETURNCAM 8 PIN 9 ARM 10 PIN 11 LOCKWIRE 12 INPUTASSEMBLY SHAFT Figure 29 8 Power Pack Handle ReleaseMechanism Wiebel 29 14 14 Page 29 26 Issued July 28 1983 2K13 ...

Page 528: ...ebody Torque to 45 inch pounds DOOR VENT VALVE Refer to Figure 29 5 1 Install the piston into the vent valve body 2 Lubricate and install the O ring on the retainer screw retainer into the valve body tighten and secure with safety ire 3 Install stem spring and adjusting screw into the retainer Install adjusting screw flush 4 Lubricate threads install O ring on the valve body and install assembly i...

Page 529: ...to the relief valve body and secure with adjusting screw The adiusting screw provides adjustment for the main relief valve Install flush at this time HAND PUMP RELIEF VALVE Refer to Figure 29 5 1 Lubricate and install O ring into the body 2 Inspect the seating surface of the seat Seating edge has to be sharp lap if necessary to obtain a clean sharp edge 3 Drop hall into the cavit of the hand pump ...

Page 530: ...mblyonly 5 Lubricate O rings and install on transfer valve sleeve 6 Install transfer valve sleeve into manifold 7 Attach the plunger to the door selector spool with a pin and install into the transfer valve sleeve 8 Lubricate O ring and install on solenoid 9 Lubricate the door solenoid threads insert the plunger return spring into the plunger cavity and screw assembly into the manifold Torque to 7...

Page 531: ... Do not over torque bolts asthis will causebinding of the landing gear selectorspool 5 Lubricate O rings and install on plunger 6 Install plunger and lubricated spring into manifold 7 Lubricate threads of retainer install into manifold Torqueto 25 inch poundsand safety wire retainer to manifold INSTALLATION AND ADJUSTMENT OF INBOARD GEAR DOOR SWITCH 1 Install switch assemblywith the insulating pla...

Page 532: ...IEW A VIEW A PIN Figure 29 9 Safetyin Control Arm Wiebel 473 3 4 1 RETURN CAM IN HORIZONTAL POSITION 1 MANIFOLD 2 LANDING GEAR SELECTOR SPOOL RACK 3 INPUT SHAFT GEAR 4 INPUT SHAFT RETURN CAM 5 LANDING GEAR SELECTOR SPOOL Figure 29 10 Indexing of Selector Spool Wieel 2K18 29 15 14 Page29 31 Issued July 28 1983 ...

Page 533: ...H 2 to 3 FT GEAR DOWN Figure 29 11 Power Pack Test Harness Schematic 474 1 STOP SCREW 2 INPUT SHAFT RETURN CAM 3 RETURN PLUNGER BALL 4 POWER PACK BODY 5 HANDLE RETURN CARTRIDGE 6 HANDLE RETURN CARTRIDGE 7 RETURN PLUNGER BALL 8 STOP SCREW RETURNCAM IN HORIZONTAL POSITION NEUTRAL Figure 29 12 Handle Release Adjustment 29 15 Page 29 32 Issued July 28 1983 2K19 ...

Page 534: ...cover DO NOT plug vent port 6 Cap all other fittings with high pressure caps NOTE For the control of the door valve solenoid it will be necessary to fabricatean electric harness as shown inFigure 29 11 This harness when connected to a 24 volt battery will allow control of the electrical current to the door valve solenoid permitting operation of the hydraulic door circuits ADJUSTMENT OF HANDLE RELE...

Page 535: ...ing 3 Adjust the adjusting screw at the top of the valve until the valve cracks at the maximum required pressure as given in Chart 2902 pumping slowly Bleed pressure by cracking the cap on the door open fitting after each adjustment ADJUSTMENT OF MAIN RELIEF VALVE Refer to Figure 29 5 1 With the input shaft in the gear up or gear down position apply pressure until fluid flows from the main relief ...

Page 536: ...at fluid flows from the door closed fitting 5 Disconnect the test equipment and cap all open fittings ADJUSTMENT OF DOOR VENT VALVE Refer to Figure 29 5 1 Remove the cap from the door open fitting on the power pack and attach the pressure hose from the hand pump with the 200 psi pressure gauge to the door open fitting 2 Slowly apply pressure to see that fluid seeps from the door vent valve 3 Adjus...

Page 537: ...voir and cap fittings 7 The hydraulic Power Pack is now ready to be installed in the airplane HYDRAULIC SYSTEM COMPONENT SERVICING OPERATION OF GEAR SELECTOR HANDLE MECHANISM Refer to Figure 29 13 Operation of the gear selector handle must give the feel of having made a positive engagement with a detent With theselectorhandle in the upordown positionand inadetent a force of 3 1 2to 6 pounds applie...

Page 538: ...3 3 STOP PIN 4 SAFETYWIRE 5 PLATE ASSY 6 LEVER ASSY 7 CABLE ASSY 8 BRACKETASSY 9 CLAMP 10 CONTROLARM 11 BRACKET ASSY 12 PIN WASHER AND COTTERPIN 13 SOLENOID 14 MOUNTING BLOCK 15 PANEL ASSY 16 LIGHT ASSY 17 CABLE ATTACHMENT PIN 18 TERMINAL 19 GROMMET 20 FIREWALL PLATE VIEW A A Figure 29 13 Landing Gear Selector Mechanism Installation 29 16 02 Page 29 37 Issued July 28 1983 2K24 ...

Page 539: ...lendscanbeadjustedtoobtaintheneutralpositioninboththecontrolarmandselector handle 7 Recheck that thehandlewill leave thedetentat 3 1 2 to 6 pounds REMOVALAND INSTALLATIONOF HYDRAULIC LINES Remove a damaged hydraulic line bydisconnecting thefittingsat each endandbydisconnecting where secured by brackets Providea smallcontainerfor drainingthe line Installa newor repairedlinein reverse order and refi...

Page 540: ...ENANCE MANUAL 13 4 1 ILTER SEAL SEAL 5 SPRING 6 BOWL 7 VALVE BYPASS 8 SPRING 9 SCREW PRESSURE 10 O RING SEAL Figure 29 14 Hydraulic Filter REPLACEMENT OF FILTER ELEMENTS Refer to Figure 29 14 29 17 01 Page 29 39 Issued July 28 1983 2L2 ...

Page 541: ...owls as required by releasing skin fasteners and separating the two halves 2 Place a drip pan under the engine to catch spillage 3 Disconnect the two hydraulic hoses from the end of the pump and cap them to prevent con tamination 4 Disconnect the drain hose from bottom of the pump 5 Remove the four nuts lockwashers and flat washers from the base of the pump 6 Remove the pump from the engine housin...

Page 542: ...E SIDE ASSEMBLY 8 LOCKNUT 9 O RING 10 CENTERPLATE ASSEMBLY 11 DOWELS 4 12 SCREW SQC HD CAP 13 REAR SIDE ASSEMBLY 14 STUD 15 O RING 16 DRIVEPIN 17 SECONDARYSHAFT 18 SECONDARYGEAR 19 DRIVEGEAR PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1072 Figure 29 15 Hydraulic Pump 29 17 04 Page29 41 Issued July 28 1983 2L4 ...

Page 543: ...t dipped in solvent Do not scrub any surface with a tool that willscratch surface WARNING Wear goggles rubber gloves andprovide adequate ventilation when using trichlorethylene or cleaning solvents Repeated contact of solvent with skin may produce irritation If vapors are inhaled serious damage may result 2 Dry all parts thoroughly with a clean lint free cloth or with dry filtered compressed air a...

Page 544: ...ENANCE MANUAL NOTE If possible run pump at rated speed while gradually increasing the pressure up to rated pressure by the end of a thirty minute period THIS SPACE INTENTIONALLY LEFT BLANK 29 17 06 Page 29 43 Issued July 28 1983 2L6 ...

Page 545: ...Gears PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL INSPECTION REPAIR Rear Side 29 17 0 Page 29 44 Issued July 28 1983 2L7 ...

Page 546: ...rewall to prevent the loss of fluid prior to the hookup of the hydraulic lines 3 Holding both lines at a levelhigher than the pump pour hydraulic fluid MIL H 5606 into the lines 4 Remove one cap at a time from the firewall fittings and connect the appropriate line to the fitting trying not to spill any of the hydraulic fluid previously put into the lines 5 After the engine has been operated check ...

Page 547: ...f the control pedestal 2 Disconnect the hydraulic pressure and suction lines from the forward end of the pump 3 Remove the pump from its mounting bracket by removing attachment bolts 4 Remove the pump from the airplane 5 Cover the pressure and suction lines to prevent contamination DISASSEMBLY OF HAND PUMP Refer to Figure 29 16 1 To remove the plunger and component parts remove quick click pin and...

Page 548: ...L 11 SPRING 12 GT RING 13 PLUNGER 14 QUICK CLICKPIN 15 O RING 16 GLAND 17 BACK UP 18 BACK UP 19 O RING 20 SCRAPER 21 BRACKET 22 QUICK CLICKPIN 23 LINK 24 QUICK CLICKPIN 25 SCREW 26 LEVER 27 GRIP 28 ROLL PIN 29 HANDLE 30 STOP 31 ROLL PIN 32 SPRING 33 DRIVE SCREW 34 HANDLEASSEMBLY o Figure 29 16 Hand Pump 29 21 02 Page 29 47 Issued July 28 1983 2L10 ...

Page 549: ...outside groove of gland 6 Lubricate the completegland and slide it onto the plungerwith the recessed end on the outside 7 Lubricate the bore of the pump body and slide the plunger with the gland into the pump body 8 Install the scraperinto the recess of the gland by sliding the scraperoverthe plunger Taperedlip of scraperto faceoutward 9 Attach the bracket to the pump body with the four screws Tor...

Page 550: ...he hand pump relief valve hasopened CAUTION It is very important that the handpump be operated veryslowly as pressureisbeingincreasedto bleedthehandpump relief valve If the handpumpisoperatedrapidly damage to the valvecanoccur asair permitspartsto slam against eachother Maximum indication of the gaugeshould beasindicated in Chart 2902 During the pumping operation the emergencyhand pump should not ...

Page 551: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL GRIDS 2L13 THRU 2L24 INTENTIONALLY LEFT BLANK 2L13 ...

Page 552: ...MOJAVE MAINTENANCE MANUAL CARD 3 OF5 PA 31P 350 MOJAVE PIPER AIRCRAFT CORPORATION PART NUMBER 761781 3A1 ...

Page 553: ...hen broken down into Sub System Sections These sections are identifiedby the secondelementof the standardized numberingsystem The number 40 of thebasicnumber series32 40 00is for the Wheels and Brakes portion of the landing gear The individual units within a Sub System Section may be identified by a third element of the standardized numbering system such as 32 40 01 This number could beassignedby ...

Page 554: ...e list of Charts is for all fiche in this set following list of Illustrations 4 A complete list of paragraph titles and appropriate Grid location numbers is givenat the beginning of each Chapter relating to the information within that Chapter 5 Identification of Revised Material Revised text and illustrations are indicated by a black vertical linealongthe left hand margin of the frame opposite rev...

Page 555: ... 1983 July28 1983 December14 1983 April30 1986 July 23 1986 September25 1986 June 15 1988 March13 1990 1 2 3 4 and5 1 2 3 4 and5 1 2 3 4 and5 1 2 1and4 3 2 INTERIM REVISION Revisions appear in chapter 27 of card 2 Please dispose of your current card 2 and replace with the revised one DO NOT DISPOSE OF CARDS 1 3 4 or 5 Consultthe CustomerServiceInformationAeroficheforcurrentrevisiondatesfor thisman...

Page 556: ...419 255 4068 Autopilot Avionics EdoCorporation Avionics Division P O Box 610 Municipal Airport Mineral Wells Texas 76067 817 325 2517 Bendix Avionics Division 2100N W 62ndStreet Fort Lauderdale Florida 33310 305 776 4100 Collins General Aviation Division Rockwell International Cedar Rapids Iowa 52406 319 395 3625 King Radio Corporation 400 N RogersRoad P O Box 106 Olathe Kansas 66061 913 782 0400 ...

Page 557: ... 5000 Narco Avionics Inc 270 CommerceDrive Fort Washington Penna 19034 215 643 2900 Avco Lycoming Avco Lycoming Division Williamsport Penna 17701 Environmental Systems Heater and Air Conditioner Janitrol Aero Division 4200Surface Road Columbus Ohio 43228 614 276 3561 SandenInternational U S A Inc 10710SandenDrive Dallas Texas 75238 Fuel Pumps Lear Siegler Incorporated 17602Broadway Avenue Maple He...

Page 558: ... Company 711 TTaylor Street Elyria Ohio 44035 216 323 4676 Hartzell Propeller Incorporated 1025RooseveltAvenue Piqua Ohio 45356 513 773 7411 Hartzell Propeller Fan Company 910 South Downing Street Piqua Ohio 45356 513 773 7411 Tools Air Conditioning Kent Moore Corporation ServiceTool Division 1501South Jackson Street Jackson Michigan 49203 517 784 8561 Turbocharger AiresearchIndustrial Division 32...

Page 559: ... PUBLICATIONS PA 31P 350 Parts Catalog Continuous Inspection 761 776 Piper Aircraft Corporation P O Rox 1328 Vero Beach FL 32961 1328 761 786 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 Introduction Page 7 Issued April 25 1983 3A8 ...

Page 560: ...GHING TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACTICES AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS NAVIGATION AND PITOT STATIC OXYGEN SYSTEM AEROFICHE GRID NO IB4 IDII IE1 1E4 IE9 1E13 1E16 IE20 IGI IHII 2B1 2B4 2B12 2C17 2DI 2HI 2...

Page 561: ...PURPOSE PARTS STRUCTURES DOORS FUSELAGE NACELLES STABILIZERS WINDOWS WINGS PROPELLER STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM STARTING TURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 3117 3J1 3J3 3KI 4B1 4C1 4C4 4C7 4D3 4D 16 4E10 4F5 4F8 4G7 4G17 4H 18 411 4111 4121 4J I 5B1 5EI Introducti ...

Page 562: ...3 Cherrylock Rivet Removal IG6 20 4 Hose Line Markings IG8 20 5 FlarelessTube Fittings 1G9 20 6 Spray Patterns IG17 20 7 Improper Spray Technique 1G 19 20 8 Spray Technique 1G20 20 9 SprayingCorners 1G20 21 1 PressurizationSystemSchematic Garrett 1H22 21 2 Cabin PressureControl SystemSchematic Garrett IH23 21 3 Safety and outflow Valves 112 21 4 Cabin Air PressureOutflow ValveController Schematic ...

Page 563: ...spection Points Air Conditioning System Typical 1L15 23 1 EmergencyLocator Transmitter Schematic Narco 2B9 23 2 Portable Folding Antenna Narco 2B9 23 3 ELT Using Fixed Aircraft Antenna Narco 2B10 23 4 Avionics Master and EmergencySwitch Circuit 2B10 24 1 Kelvin Low ResistanceBridge 2B21 24 2 Electrical Power Distribution System Typical 2B22 24 3 Lamar Model B 00382 1 Typical SystemApplication 2C3 ...

Page 564: ... 27 27 Flap Transmission Exploded View 2G2 27 28 Flap TransmissionMeasurements 2G5 27 29 Checking for Wormgear Wear 2G7 27 30 Flap Rigging Adjustments 2G1 _ 28 1 Fuel SystemSchematic 2H8 28 2 Fuel Cell Installation Inboard 2H 11 28 3 Fuel Cell Installation Outboard 2H12 28 4 Fuel Cell Installation Nacelle 2H13 28 5 Fuel Valve Drain Plate 2H 14 28 6 FuelCell Tie Detail 2H17 28 7 Installation of Fue...

Page 565: ...ffed Area and Patch 3B22 30 10 Applying and Stitching Fabric 3B22 30 11 Placing and Stitching Gum 3B24 30 12 Removing Trapped Air 3B24 30 13 Masking Repair 3B24 30 14 Applying Neoprene Putty 3B24 30 15 Windshield Wiper 3C8 30 16 Typical Use of Dial Indicator 3C12 30 17 Centering of Brushes on Slip Rings 3C12 30 18 Modular Brush Assembly Wear Check 3C13 30 19 Angle of Contact Brushes to Slip Rings ...

Page 566: ...2 24 Adjusting Main Gear Down Light Switch 3F23 32 25 Gear Warning Switches Installation 3F24 33 1 Landing Taxi Light Installation 3G21 33 2 Logo Light Assembly Adjustments 3H2 34 1 Instrument Air System Installation Typical 3H9 34 2 Pitot Static Installation 3H10 35 1 Oxygen System Installation 314 35 2 Oxygen System Installation for FAR 135 Certification 315 35 3 Oxygen Tubing Installations 3112...

Page 567: ... Forward BaggageDoor Assembly 4B19 52 6 NacelleLocker Door 4B21 52 7 Door Ajar Switch 4B24 54 1 NacelleAssembly 4C6 55 1 EmpennageInstallation 4C I 55 2 Elevator Balancing 4C18 55 3 Friction Measurement 4C20 55 4 Rudder Balancing 4C24 55 5 Rudder BalanceWeight Location 4C24 56 1 Windshield Installation 4D8 56 2 FabricatedSealant Tools 4D11 56 3 Storm Window Installation 4D13 57 1 Wing Installation...

Page 568: ...hecking Harness Lead Continuity 4H7 74 11 Checking Harness Lead Insulation Resistance 4H7 74 12 Modified Pliers 4H7 74 13 Removing Spring From Lead Assembly 4H7 74 14 Assembly Tool 4H9 74 15 Using Assembly Tool 4H9 74 16 Ferrule Positioned Under Braid 4H10 74 17 Ferrule Seating Tool 4H10 74 18 Position of 11 8627Kit and Contact Spring at Start of Installation 4H11 74 19 Position of 11 8627 Kit and...

Page 569: ...ravel 5E1O 95 9 FabricatedTool Checking Main Gear Toe In Adjustment 5E 1 95 10 Tire Balancer 5E12 95 11 FabricatedTool Checking NoseWheel Alignment 5E13 95 12 SuggestedDesignfor Seal Plate Plugsand Caps for Combustion LeakageTest 5E14 95 13 Charging Stand 5E14 95 14 Fabricated PressureTest Adapters 5E15 95 15 Cabin PressureTest Unit Typical 5E15 95 16 Test GaugeManifold Set 5E16 95 17 Torque Wrenc...

Page 570: ...ctrolyte Temperature Corrections 2C8 2406 Specific Gravity Temperature Correction 2C9 2407 Recommended Discharge Rate 2C9 2408 Electrolyte Freezing Points 2C10 2409 Capacity Ratings at Discharge Rate 2C12 2410 Electrolyte Freezing Points 2C12 2411 Circuit Load Chart 2C13 2701 Troubleshooting Surface Controls 2D6 2702 Control Cable Rigging Tension vs Temperature 2D19 2801 Troubleshooting Fuel Syste...

Page 571: ...s 318 3901 Cabin Instruments Display 3J12 5101 List of Materials Thermoplastic Repairs 3K10 5102 Types of Metal Corrosion 3K21 5501 Elevator Balance Specifications 4C17 5502 Rudder Balance Specifications 4C23 5701 Aileron Balance Specifications 4E5 6101 Propeller Specifications 4E15 6102 Troubleshooting Actuator Chart Engine Synchrophaser 4E22 7101 Troubleshooting Engine 4F 1 7301 Troubleshooting ...

Page 572: ...O List of Consumable Materials Flare Fitting Torque Valucs Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Electrical Wiring Coding Electrical Symbols 5B4 5B16 5B17 5B19 5B20 5B21 5B22 5C2 5C3 5C4 Introduction Page 19 Issued April 25 1983 3A21 ...

Page 573: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3A22 ...

Page 574: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3A23 ...

Page 575: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3A24 ...

Page 576: ...CHAPTER ICE AND RAIN PROTECTION 3B1 ...

Page 577: ...rfoil Deice Boots 3B12 30 15 00 Repair Of Airfoil DeiceBoots 3B13 30 15 01 Cold Repair 3B13 30 15 02 VulcanizedRepair 3B16 30 15 03 Materials For VulcanizedRepair 3B16 30 15 04 DefinitionOf Terms 3B17 30 15 05 General Procedure 3B18 30 15 06 Curing 3B18 30 15 07 Surface Scuffs 3B19 30 15 08 Deep ScuffThrough NeopreneSurface 3B19 30 15 09 Holes Or Tears Through SurfaceSide Of Tube Area 3B21 30 15 1...

Page 578: ...stallation 3C7 30 42 05 Wiper Blade And Arm Adjustment 3C9 30 60 00 PROPELLERS 3C9 30 60 01 Description And PrinciplesOf Operation 3C9 30 60 02 Troubleshooting 3C10 30 61 00 Maintenance Practices 3C1I 30 61 01 Propeller Deice System Operational Check 3C1 I 30 61 02 Recommended Overhaul Of Deice System Timer 3C I1 30 61 03 100 Hour Inspection 3C1I 30 62 00 Brush Modules Modular Brush Assemblies 3C1...

Page 579: ...cer Boots cont Installation Of DeicersAnd Required Materials PreparationAnd Application Of Sealer Wrinkled Deicers Electrical Check Final Electrical Check Of Propeller Deicers Installation Of Deicer LeadsAnd Wire Harness Balancing Propeller Ice Shield RemovalOf Propeller Ice Shield Installation Of Propeller Ice Shield 3C21 3C21 3C23 3C23 3C24 3C24 3D2 3D2 3D2 3D2 30 80 00 30 81 00 30 81 01 ICE DET...

Page 580: ...eicer boots at all times by means of the deicer ejector except when they are being inflated Deicer inflation is affected by the deicer systemcontrol switch When the switch is actuated the timer energizes the outboard wing deicer valve for six 5 seconds This valve shuts off the vacuum to the outboard wing boots and directs pressurized air to the deicers Upon automatic deenergization of the valveby ...

Page 581: ...ines and inspect connections Make air leakage test Deicer valve not functioning System pressure not being attained Deicer puncture Test or replace as required Check performance to manufacturers specifications Repair per specification or replace Deicers inflate indicator light does not function Ascertain that deicer boot switch is ON Indicator lamp burned out System pressure not being reached Repla...

Page 582: ...YSTEM cont Trouble Cause Remedy Deicers deflate slowly Lines partially Inspect and blow out lines cont blocked Overboard line from control valve partially blocked Leakage in system plumbing Inspect and blow out lines Leak check and correct leakage 30 00 02 Page 30 03 Issued April 25 1983 3B7 ...

Page 583: ...uate 6 5 seconds after the first and remain actuated for 6 5 seconds also If either valve does not function follow instructions below A Disconnect the wires at the particular valve Attach a test light or othersuitable test equipment to the connector and reactuate the system switch If the test equipment does not indicate a complete circuit make the following checks I Check the circuit from the time...

Page 584: ...TS 10 GYRO PRESSUREREGULATOR 11 PNEUMATICPRESSURESWITCH 12 INLINE FILTER 13 OUTBOARD DEICEBOOT 14 DUAL CHECKVALVE 15 DEICEINFLATION VALVE A 16 DEICEINFLATION VALVE B 17 EMPENNAGE DEICEBOOTS 18 CABIN DOOR SEAL 19 SOLENOID VALVE 20 ACCUMULATOR TANK 21 CABIN DOOR SEAL PRESSURESWITCH 22 CABIN DOOR SEAL CHECKVALVE 23 VACUUM EJECTOR 24 DEICEINFLATION SWITCHA 25 DEICEINFLATION SWITCH B 17 m Schematic 30 ...

Page 585: ...icsystem enginebleedair lineat the engine and connect a hose from shop air to the pneumatic line withair regulated to 22 psig The system operating pressureis 18 psig Beforecheckingthe system all deicersshould beinspectedfor damagedareas and repairedaccordingto the procedure in thissection outliningthe cold patch or vulcanizedrepairs In order to checkthe system a deicer piping diagram drawing is ne...

Page 586: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 421 ALL Figure 30 2 Pneumatic Deicer Boots Operation Typical 30 11 06 Page 30 07 Issued April 25 1983 3B11 ...

Page 587: ...CE BOOTS The removal of deicer boots should be done in a well ventilated area to avoid difficulty from the fumes of the solvents Materials required to remove the boots are Turco 388 or Kelite 21 to remove dried cement and MEK Methylethylketone in squirt can NOTE Disconnect linefittings from boot fittings 1 Starting at one corner of the upper trailing edge of the deicer apply a minimum amount of so...

Page 588: ... avoid trapping air pockets Thoroughly roll the patch with stitcher roller Part No 74 451 73 and allow to set for ten to fifteen minutes D Wipe the patch and surrounding area from the center outward with a cloth slightly dampened with solvent Apply one light coat of A 56B conductive cement to seal and feather edge E Satisfactory adhesion of patch to deicer will be reached in four hours Deicer ma b...

Page 589: ...6 B Conductive cement Small oval patch 1 1 4 x 2 1 2 in Medium oval patch 2 1 2 x 5 inch Large oval patch 5 x 10 in Patch 5 x 19 inch No 4 cement patching onl Cement brush I 2 in I 8 in Steel stitcher Emery Buffing sticks Buffing Shield 74 451 21 74 451 22 74 451 23 74 451 24 FS N8040 628 4199 and or FSN8040 514 1880 74 451 74 74 451 100 6 ft roll x 6 in wide 15ft roll x 2in wide 4 ft long x 8in w...

Page 590: ...1 2inch larger in length and width than the size of surface ply patch Apply one coat of cement Part No 74 451 20 to damaged area and one coat to patch Allow cement to set until tacky Roll the surface ply to the deicer with 2 inch rubber roller Part No 74 451 74 Roll edges with stitcher roller Part No 74 451 73 Applyjust enough tension on the surface ply when rolling to prevent wrinkling and be car...

Page 591: ... correct repair material Deicers are compounded to resist sunlight and weather and retain flexibility It is recommended that only materials as listed in Chart 3004 be used in making vulcanized repairs They are sufficient to supply a one or two man unit for a period of from four to six weeks repairing deicers with the average amount of miscellaneous types of repairs Select materials specified for m...

Page 592: ...6 B conductive cement NOTE Do not apply A 56 Bconductive cementin anyarea of any electrical transmitting or receiving equipment 8 Stitch to force fabrics or gum elements together with metal or rubber roller stitch from the center toward the edges to prevent trapping air between the elements CHART 3005 EQUIPMENT FOR VULCANIZED REPAIRS Part No Description Qty 74 451 B SUPPLY KIT High pressure Deicer...

Page 593: ...h work day 9 Use approved safety can for Toluol or MEK Take screen and spring out of solvent cans before filling so that all sediment may be removed 10 Cements should beof such aconsistency that they can beapplied in a thin smooth coating If the are partially set up or lumpy addition of the proper solvent may restore their usable characteristics Otherwise do not use 11 Do not attempt repairs in te...

Page 594: ...n carefully examine for soundness If in a tube inflate to 25 psig SURFACE SCUFFS Repair as follows I Wash surface to be restored and apply one coat of conductive cement Allowto dry thoroughly Add another coat and allow to dry Dip finger in conductive cement solvent Isopropyl Acetate and rub down with light circular movement Do not allow finger to become dry 2 Wipe surface lightly with cloth moiste...

Page 595: ...0 MAINTENANCE MANUAL 4678 467A Figure 30 3 Marking and Cutting Scuff 467C Figure 30 4 Routing Scuff 467D Figure 30 5 Buffing Edge of Repair Figure 30 6 Hole through Surface of Tube 30 15 08 Page 30 16 Issued April 25 1983 3B20 ...

Page 596: ...ch beyond repair Using mill knife or putty knife apply Neoprene putty filling cavitv flush with surface Make sure cavity is completely filled Remove masking tape and cure for 15 to 20 minutes 7 Restore conductive surface HOLES OR TEARS THROUGH BACKSIDE OF TUBE AREA Repair as follows 1 Route off coating down to fabric at least 3 4 inch beyond cut and wash thoroughly entire buffed area and cement 2 ...

Page 597: ...ANCE MANUAL 467F 467E Figure 30 7 Routing to Tube Fabric Figure 30 8 Cutting Surface of Tube 467G 467H Figure 30 9 Cementing Buffed Area and Patch Figure 30 10 Applying and Stitching Fabric 30 15 12 Page 30 18 Issued April 25 1983 3B22 ...

Page 598: ...ons for air connections etc PREPARATION OF LEADING EDGES If the leading edges are painted remove all paint including zinc chromate primer 1 With one inch I masking tape mask off leading edge boot area following I 2inch margin fornon recessed boots Take care to mask accurately thus eliminating the need for cleaning off excess cement later 2 Clean the metal surfaces thoroughly at least twice with ME...

Page 599: ...50 MAINTENANCE MANUAL 467K 467J Figure 30 11 Placing and Stitching Gum 467L Figure 30 12 Removing Trapped Air 467M Figure 30 13 Masking Repair Figure 30 14 Applying Neoprene Putty 30 16 01 Page 30 20 Issued April 25 1983 3B24 ...

Page 600: ...k hose to the corresponding air connection stem Tinnerman or other suitable non kink hose clamps should be used for this purpose Tighten each clamp with a pair of slip joint pliers but do not squeeze the clamp so tight that the hose is damaged NOTE If non kink hose clamps are not available wrap each hose connectionwith severalturnsof friction tape Overthe tape wrap two separatebindingsof safety wi...

Page 601: ...solvents used for installationareflammableand theirfumesslightly toxic Therefore all work should bedonein a well ventilatedareaawayfrom anysparksorflames Useof solvent resistant typeglovesis recommended In the event it becomes necessary to remove or loosen installed boots use MEK to soften the adhesion line A minimum of this solvent should be applied to the seam line while tension is applied to pe...

Page 602: ...eaned using a portable type ground heater As alternates use Benzol or non leaded gasoline Moisten the cleaning cloth in solvent scrub lightl and then with a clean dry cloth wipedry so that the cleaner does not have time to soak into the rubber Petroleum products such as these are injurious to rubber and therefore should be used sparingly AGEMASTER NO 1 AND ICEX APPLICATION Agemaster No I and Icex ...

Page 603: ...ur application methods mentioned above swabbing is the preferred method for installed deicer boots If the swabbing method is selected plastic or rubber gloves should be used to prevent the staining of the skin Apply Agemaster by moistening a two inch by four inch swab of lint free cloth and tub into the boot surface with smooth uniform strokes The swab should be kept wet but not dripping Cover the...

Page 604: ...x and the boot RESURFACING CONDUCTIVE CEMENT The following materials are required to remove and replace the old damaged coating 1 Fine grit sandpaper 2 Two inch paint brush 3 One inch masking tape 4 Conductive neoprene cement No A 56 B B F Goodrich Company 5 Isopropyl Acetate Federal Specification TT 1 721 as cleaning or thinning solvent 6 Alternate solvent Toluol or Toluene may be used as an alte...

Page 605: ...OWSAND WINDSHIELDS HEATED WINDSHIELD For servicingof pilot s heated windshield Referto Chapter 56 WINDSHIELDWIPERMECHANISM REMOVALOF WIPERMECHANISM Refer to Figure 30 15 1 Removethe accesspanel to the left side of the nose section 2 Cut the lockwireat the bolt whichsecuresthe arm to the serrated convertershaftand removethe bolt 3 Loosenthe adjustment nut and lift the wiperarm off the converter sha...

Page 606: ...d of sealer around the converter shaft where it extends through the fuselage and position and secure the seal cover in place with two remaining screws 7 Connect the electrical connector to the wiper motor and replace the access panels removed 8 Refer to wiper blade and arm installation and adjustment WIPER BLADE AND ARM REMOVAL 1 Cut the lockwire at the bolt which secures the arm to the serrated c...

Page 607: ...ER ARM 4 TENSION ADJUSTMENT NUT 5 LOCK WIRE 6 ADJUSTMENT SLEEVE 7 CONVERTER 8 MOTOR 9 FLEXIBLEDRIVE 10 BRACKET 4 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL C71 3 7 Figure 30 15 Windshield Wiper 30 42 04 Page 30 28 Revised December 14 1983 3C8 ...

Page 608: ...nt stud NOTE Ascertain that the base of the adjustment stud is in the recess provided in the wiper arm 5 After wiper has been adjusted and adjustment latch locked install lockwire PROPELLERS DESCRIPTION AND PRINCIPLES OF OPERATION The propeller deicer system consists of an electrically heated deicer bonded to each propeller blade slip ring assemblies to distribute electrical power to the propeller...

Page 609: ...an machine or replace slip ring assembly as required Check slip ring alignment Loose connection Switch faulty Wiring located within 8 inches of radio equipment wiring Locate and correct Try jumper wire across switch if radio noise disappears replace the switch Relocate at least 8 inches away from input wiring to radio equipment Rapid brush wear or frequent breakage Brush block out of alignment Che...

Page 610: ... seconds with no furtherannunciation if no failures are detected NOTE The malfunction annunciator will illuminate when the deice system is turned off in flight RECOMMENDED OVERHAUL OF DEICE SYSTEM TIMER International Avionics Incorporated has established a recommended overhaul period of 5 000 flight hours for contactor inspection and or replacement 100 HOUR INSPECTION 1 Remove cowling in accordanc...

Page 611: ...ANCE MANUAL SLIP RINGASSEMBLY Figure 30 16 Typical Useof Dial Indicator 394 BRUSH LOCATED INCORRECTLY ON SLIPRING NOTCH WORN IN BRUSH DUETOMISALIGNMENT Figure 30 17 Centering of Brushes on Slip Rings 30 61 03 Page 30 32 Issued April 25 1983 3C12 ...

Page 612: ...Figure30 18 D Visuallycheck brush blockfor approximately2 angle of attack Refer to Figure30 19 If not loosenmountingscrewsand twistblock but besure to holdclearancelimitsshownwhen tightening BRUSH MODULES MODULARBRUSHASSEMBLIES Each 3E2071modular brush assemblyconsists of one 3E2011 1brush module one 3E2011 2 brush module and a 4E2218 6spacer The brush modules whichconsistof a plastichousingwithan...

Page 613: ...t be checked NOTE New deicer brushes must be run in a minimum of two hours of engine operation prior to energizingthe deicer boots Brushes shouldbe checkedforproper seatingandalignmentaftertherunin period SLIP RINGS MACHINING OF SLIP RINGS Slip rings with roughened or damaged surfaces can be machined to restore to serviceability Remove the slip ring assembly from the aircraft to mount it in a lath...

Page 614: ...ct Brushes to Slip Rings C177 3 7 4 1 SPACER 4E2118 6 2 BRUSH MODULE ASSEMBLY 3E2011 1 3 BRUSH MODULE ASSEMBLY 3E2011 2 4 SCREW MS24693 S34 5 NUT MS35649 262 6 LOCKWASHER MS35333 37 7 WASHER AN960C6 Figure 30 20 Brush Module Assembly 3E2011 Figure 30 21 Modular Brush Assembly 3E2071 30 63 01 Page 30 35 Revised July 28 1983 3C15 ...

Page 615: ...short or open at the brush to slip ring contact disconnect harness at the timer and use low range ohmmeter to read resistance from each deicer circuit lead to ground it should read 1 58 to 1 64 If this reading is not obtained disconnect the deicer leads to measure heater resistances individually Individual heater should be4 74 to 4 90 If first check is off limits but second check is satisfactory t...

Page 616: ...visegrip pliers or similar tool 4 Apply a steady pull on the deicer to pull it off the propeller surface Continue using MEKor Toluol to soften the adhesion lines Unless the deicer being removed is damaged and is to be scrapped cushion the jaws of any pulling tool used to prevent damage to the deicer surface Remove very slowly and carefully If deicer has failed and is to be returned under request f...

Page 617: ...AN960C416 ADD AS REQUIREDTO ALIGN 1 SUPPORTBRACKET 2 MODULAR BRUSHASSEMBLY 3 MOUNTING BRACKET 4 SLIP RING STARTER RING GEAR 5 SLIP RINGWIRE HARNESSLEADS 6 PROPELLERASSEMBLY Figure 30 23 Modular Brush Assembly Installation 30 64 03 Page 30 38 Revised July 28 1983 3C18 ...

Page 618: ...e located the same distance from the hubfor rotational balance 3 Remove the pattern and remove any paint in the marked off area Clean down to bare metal Next clean the area thoroughly with MEK or acetone For final cleaning wipe the solvent off quickly with a clean dry lint free cloth to avoid leaving a film CA UTION Cleanliness of metal and rubber parts cannot be too highlystressed Only perfectly ...

Page 619: ...umidity is lessthan 75 If the humidity is 75 to 90 allow two hours drying time Do not apply cement ifthe relative humidity is higher than 90 After allowing the proper amount of drying time apply a second even brush coat of 1300Lcement NOTE If curlingof thedeiceredgesis aproblem applymaskingtapetothe edgesof theglazedsidebeforeapplingcementto theunglazedside Remove the tape before startingto instal...

Page 620: ...ng the sealer E Allow 24 hours cement curing time before turning up propeller Allow 72 hours curing time before operating the deicers Handle the propeller carefully to prevent damage to the deicers 2 Propeller deicers one for each propeller blade are supplied in B F Goodrich propeller deicing system kits Replacement deicers may be ordered from the B F Goodrich Company PREPARATION AND APPLICATION O...

Page 621: ...drich 1 2 pt per six blades Cleaning Solvent MEK Methyl Ethyl Ketone or Acetone Cleaning Cloth any clean lint free cloth I in Paint Brush 2 in Rubber Hand Roller 1 4 in Metal Hand Stitcher Scissors Turco 3 Turco Products Co Masking Tape 1 pt per six blades NOTE MEK can be used instead of Toluol to tackify cement however tests show that MEK causes rapid drying and provides only 10 seconds working t...

Page 622: ...ond the loose or wrinkled area Apply one coat of 1300Lcement to the deicer and propeller bonding surfaces and allow to air dry for one hour Then apply a second coat of 1300Lcement to both the deicer and bonding surface Allow to dry Retackify with MEK or Actone and press with fingers to work out wrinkles or to secure loose edges If material has stretched and will not cement flat replace thedeicer E...

Page 623: ...hims that might have been used for making the final electrical check INSTALLATION OF DEICER LEADS AND WIRE HARNESS 1 The deicer leads are fastened to the bulkhead in the same positions from which they were removed 2 The deicer leads are to be attached to the studs on the spinner bulkhead 3 The propeller deicer wiring harness is secured to the propeller counterweight as follows A Insert the deicer ...

Page 624: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL C838 A 2 TRANSFLUX TUBING Figure 30 26 Prop Deicer Wiring Harness Installation 30 64 11 Page 30 45 Issued April 25 1983 3D1 ...

Page 625: ...in from damage caused by ice shed from the propeller blades REMOVAL OF PROPELLER ICE SHIELD I Using a sharp plastic or hardwood sealant removal tool remove thesealant from around the shield 2 Remove the 14 screws MS35206 227 which secure the shield to the fuselage and remove shield 3 Remove all traces of sealant from the fuselage using sealant removal methods described in Chapter 51 INSTALLATION O...

Page 626: ...The light is mounted in the left outboard surface of the left nacellejust above the leading edge of the wing It is a sealed beam 24 volt unit which is controlled by a rocker type switch mounted on the overhead switch panel The light is positioned so as to illuminate the leading edge of the wing when the switch is activated SERVICING The only service required of this unit is the replacement of a bu...

Page 627: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3D4 ...

Page 628: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLYLEFT BLANK 3D5 ...

Page 629: ...CHAPTER LANDING GEAR 3D6 ...

Page 630: ...n Landing Gear Adjustment of Main Landing Gear Alignment of Main Landing Gear Main Gear Door Assembly Removal of Main Gear Door Assembly Cleaning Inspection and Repair of Main Gear Door Assembly Installation of Main Gear Door Assembly Adjustment of Main Gear Doors 3D17 3D17 3D17 3D20 3D20 3D20 3D20 EFFECTIVITY IR 7 83 IR 7 83 1 R 7 83 IR 7 83 IR 7 83 A 7 83 A 7 83 A 7 83 A 7 83 A 7 83 3D21 3D22 3D...

Page 631: ...tion of Gear Actuating Cylinder 3E22 32 32 00 GEAR DOOR ACTUATING CYLINDERS 3E22 A 7 83 32 32 01 Removal of Gear Door Actuating Cylinder 3E22 A 7 83 32 32 02 Disassembly of Gear Door Actuating Cylinder 3E22 A 7 83 32 32 03 Cleaning Inspection and Repair of Gear Door Actuating Cylinder 3E23 A 7 83 32 32 04 Assembly of Gear Door Actuating Cylinder 3E23 A 7 83 32 32 05 Installation of Gear Door Actua...

Page 632: ...tion and Repair of Wheel Brake Assembly 3F11 32 43 03 Brake Adjustment and Lining Tolerances 3F11 32 43 04 Assembly and Installation of Wheel Brake Assembly 3F12 32 44 00 Brake Master Cylinder 3F12 32 44 01 Removal of Brake Master Cylinder 3F12 32 44 02 Disassembly of Brake Master Cylinder 3F12 32 44 03 Cleaning Inspection and Repair of Brake Master Cylinder 3F14 32 44 04 Assembly of Brake Master ...

Page 633: ...ition Adjustment of NoseGear Up Limit Switch Adjustment of NoseGear Down Limit Switch Adjustment of Main Gear Up Limit Switch Adjustment of Main Gear Down Limit Switch Adjustment of Main Inboard Gear Door Ajar Sw itches Adjustment of Landing GearSafety Switch Warning Remo al of GearWarning Switches Installation of Gear Warning Switches Adjustment of Gear Warning Switches 3F20 3F20 3F20 3F21 3F21 3...

Page 634: ...ot impeded by the nose gear operation Located on the instrument panel to the right of the gear selector control are one red and three green indicator lights The red light will show an indication when the gear is not locked in either the up or down posi tion and the green lights will show when each individual gear is down and locked There is no indication light when the gear is up and locked The re...

Page 635: ...n that the LEFT main gear strut is ex tended and that the power is on Faulty safety switch on left main gear Adjust or replace safety switch Nose gear fails to lock up when handle returns to neutral Not enough actuator stroke Increase the actuator stroke Gear doors pinching Relieve door pinch by lengthening door oper ating rods Adjust cable Main gear fails to lock up Uplock cable out of adjustment...

Page 636: ...ctive Horn or light defective Defective wiring Internal wear in shimmy dampener Shimmy dampener or bracket loose at mounting Replace switches Adjust throttle switches Replace defective switch Adjust throttle switches Replace switch Replace defective part Check wiring Replace shimmy damp ener Replace necessary parts and bolts Tire out of balance Worn or loose wheel bearings Worn torque link bolts a...

Page 637: ...p of strut Determine cause and correct Replace defective roller Gear retracts or extends before the doors open Priority valve leaks in power pack Check priority valve cracking pressure Solenoid valve stuck in closed position Micro switch on power pack out of adjustment Turn off power and hand pump doors open Check for bent bracket or loose mounting or wire and adjust Doors come open in flight Door...

Page 638: ...anand inspectthe housingto determinethat no piecesremain in it 6 Wipe the piston tube and checkit for any abrasions whichmaydamage the newwiper Polish the tube to removeany abrasions found 7 A newwiperstrip shouldbecut witha30degreebevel a littlelongerthan needed tocirclethe piston tube 8 Insert the newwiperstrip up into the oleo housingwith the taperededge down Slidethe retainer washerand snap ri...

Page 639: ...RING ON PISTON SKETCH B INSTALLATIONOF NON EXTRUSION RINGS IN ROD END SKETCH C INSTALLATIONOF NON EXTRUSION RINGS ON PISTON SKETCH D B PROPERMATING OF SCARF CUTON NON EXTRUSIONRINGS SKETCH F CROSSSECTIONOF INSTALLED T RING ASSEMBLY SKETCH E Figure 32 1 Installation of T Rings 32 00 03 Page 32 06 Revised July 28 1983 3D16 ...

Page 640: ...an under the main gear to catch spillage 3 Remove the air and fluid from the oleo Refer to Oleo Struts Chapter 12 4 To remove the piston tube assembly from the oleo housing remove the upper and lower torque link connecting bolt assembly and separate the links Note the number and thickness of spacer washers between the two links 5 Compress the piston tube reach up along the tube and release the ret...

Page 641: ... OLEO 22 TUBE PISTON 23 BOLTASSEMBLY 24 FORK 25 PIN COTTER 26 NUT AXLE 27 BOLTASSEMBLY 28 PIN COTTER 29 BOLTASSEMBLY 30 BEARING UPLOCK 31 TORQUELINK LOWER 12 13 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 39 32 BOLT ASSEMBLY 33 TORQUE LINK UPPER 34 BOLT ASSEMBLY 35 WASHERS BUSHINGS 36 CONTACT SAFETYSWITCH 37 BUSHING 38 PLACARD SERVICE 39 SAFETYWIRE 40 SCREW 41 AXLE 1079 C235 10 25 41 VIEW A A Ref...

Page 642: ...21 3 4 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1080 5 6 8 I 17 24 22 7 Figure 32 2 Main Gear Oleo Strut Assembly cont 32 11 01 Page 32 09 Revised July 28 1983 3D19 ...

Page 643: ... ring can be installed in the annular slot at the lower end of the housing Install wiper strip slide washer into position and secure assembly with retainer ring At the top of the housing tighten the cap bolt 5 Install the upper and lower torque links Use same thickness spacer washers between the two links as those removed to maintain correct wheel alignment 6 Lubricate the gear assembly Refer to L...

Page 644: ...l joints for excesswear corrosion and damage WARNING Refer to latest revision of Piper Service Bulletin 845for specific inspection replacement instructionsfor the Main Landing Gear Forward Side Braces Piper considers compliance with service bulletinsas mandatory 3 Inspect the gear housing sidebrace links idler links rods and attachment plates for cracks bends or misalignment 4 Inspect lock hook fo...

Page 645: ...B Slide the pivot shaft through the attachment plate and into the attachment fitting Secure the pivot shaft to the attachment fitting C Ascertain that the forward upper arm is installed on the link Install the link on the pivot shaft and secure with washers and nut D The aft upper drag link may be installed by sliding the link on the aft attachment plate pivot bolt Tighten the nut to allow the lin...

Page 646: ... downlocked position with both stop surfaces of the side brace links touching B Ascertain that the linkage is 0 063 to 0 156 of an inch through center C If one side of the stop surfaces does not touch it can be filed to obtain the desired through travel D If filing brings the through travel beyond the 0 156 inch tolerance then a link or links must be replaced NOTE Afabricated tool maybeconstructed...

Page 647: ... DOWNLOCK 61 25 BRACKET SWITCH 62 26 HOOK DOWNLOCK 63 27 SIDE BRACELOWER 64 28 SIDE BRACE UPPERAFT 65 29 PLATE MOUNTING 66 30 BOLT WASHER NUT AND COTTERPIN67 VALVE ASSEMBLY HOUSING GEAR SAFETYSWITCH LINK TORQUE UPPER LINK TORQUE LOWER LINE BRAKE STRUTASSEMBLY BRAKEASSEMBLY BRACKETMOUNTING DISC BRAKE WHEEL AND TIRE HINGE OUTBOARD DOOR BEARING HINGE DOOR OUTBOARD BRACKET DOOR ROD RETRACTION HOSE BRA...

Page 648: ...i i II II 11 10 3321 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 3320 I 0 0 SKETCH A SKETCH B Figure 32 3 Main Landing Gear Installation Left cont 32 12 04 Page 32 15 Revised July 28 1983 3E1 ...

Page 649: ... maintain the new surface parallel with the original surface Replace pin if worn CA UTION Do not file pin 8 To replace pin cut the pin file off any burrs left by the cut and drive the pin out from either side Do not try to drill the pin out as this may damage the link Install new pin and flange 9 With the downlock hook engaged pull the retraction arm located at the top of the forward side brace to...

Page 650: ...ton travel at this point Repeat several times to determine that the stroke control is properly adjusted 15 Back off the stroke stop one half turn and tighten locknut on stop Place the key locks between the locknut and the keyway in the rod Screw the locknut on the rod and keep the key lock centered in the keyway while tightening the locknut With the locknut torqued install the lock wire from the k...

Page 651: ...er s square because of its especially long legs is rec ommended for checking main landing gear wheel alignment 3 If a gap appears at the rear between the block and square the wheel is toed out and must be re aligned If a gap appears at the forward end between the block and square the wheel has too much toe in and must be realigned to get 5 degree toe in 4 To rectifytoe in or toe out condition remo...

Page 652: ...to the door 2 The outboard geardoor is installed by aligning the hinge bracket holes with the bearings installing bolt assemblies and securing Attach the actuating rods between the door and landing gear housing ADJUSTMENT OF MAIN GEARDOORS 1 Ascertain that the main landing gear has been properly adjusted 2 Adjust outboard door rods to their maximum length and bolt them to the bosses on the gear ho...

Page 653: ...sembly from the cylinder separate upper and lower torque links by removing the connecting bolt with washer nut and cotter pin Note spacer washer between the two links 8 Compress the piston tube reach up along the tube and release the snap ring from annular slot at the bottom of the oleo housing 9 Pull the piston tube with component parts from the cylinder NOTE Prior to disassembling the upper bear...

Page 654: ...HER AND NUT 22 TORQUE LINK LOWER 23 WASHER SPACER 24 BOLTASSEMBLY 25 TORQUELINK UPPER 26 TUBE PISTON 27 SHIMMY DAMPENER 28 BOLT ASSEMBLY 29 BOLT ASSEMBLY 30 BOLTS AND SAFETYWIRE 31 BRACKET 32 BUSHING 33 STUD DOOR UPLOCK 34 PLACARD SERVICE 35 HOUSING OLEO 36 BUSHING 37 BOLT CAP 38 BOLT 39 PLUG FILLER 40 ALIGNER GUIDE BRACKET 41 VALVE AIR 42 ARM STEERING 43 PIN COTTER 44 SAFETYWIRE 45 PISTON RING 46...

Page 655: ...35 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1208 42 40 11 II 41 13 12 15 16 16 3 26 9 2 47 41 22 Figure 32 6 Nose Gear Oleo Strut Assembly cont 32 21 01 Page 32 22 Revised July 28 1983 3E8 ...

Page 656: ... the top of the cylinder install the piston ring 4 The fork tube assembly may be assembled by installing the tube components on the tube In order slide onto tube retainer ring washer lower bearing with outer and inner O rings spacer and upper bearing Align lock pin holes of the upper bearing and orifice tube and install pins 5 Lubricate the inner wall of the cylinder Carefully insert the piston tu...

Page 657: ...ing proced ure A Remove the downlock spring and the eye bolt which is attached to the idler link B Disconnect the gear actuating cylinder rod from the link C Remove the link pivot bolt by sliding the bolt out of the link allowing the head to enter the hole in the side of the limit switch bracket With the head through the bracket hole the threaded end of the bolt can continue out of the link D Remo...

Page 658: ...d spring and pulling steadilyagainst the hook and spring to get a reading 5 Inspect the uplock hook for wear and oversizedbearing surfaces 6 Inspect the uplock roller for freedom of movementand minimumwobble 7 Inspectthe uplock cable for corrosion 8 Check the generalcondition of limit switchesand wiringfor fraying poor connectionsor condi tions that may lead to failures 9 Attach the upper and lowe...

Page 659: ...ACTIONROD 37 DRAG LINK UPPERLEFT 38 PLATE ATTACHMENT 39 DRAG LINK UPPERRIGHT 40 ROD DOOR RETRACTION 41 DRAG LINK LOWER 42 STUD DOORACTUATOR 43 BOLTASSEMBLY 44 HOUSING GEAR OLEO 45 SHIMMY DAMPENER 46 TORQUELINK UPPER 47 TORQUELINK LOWER 48 FORKASSEMBLY 49 TIRE 53 50 WHEEL 54 51 BOLT EYE 55 52 STOP STROKE 56 15 SWITCH UP LIMIT 16 BRACKET SWITCH 17 TUBE SUPPORT 18 CABLE UPLOCK 19 BOLT ASSEMBLY 20 BOL...

Page 660: ...SKETCH C PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 3324 207 208 SKETCH A Figure 32 7 Nose Landing Gear Installation cont 32 22 03 Page 32 27 Revised July 28 1983 3E13 ...

Page 661: ...eaded end of the bolt to be inserted into the tube lug and link Tighten the nut on the bolt allowing the link to turn free with no side play C Attach the retraction rod and actuating cylinder rod end to the link Do not connect the re traction rod to the link until gear adjustment has been completed D The downlock spring may be attached after gear check and adjustment has been completed 7 To instal...

Page 662: ...ctuator attaching bolt is at the bottom of the slots in the attachment bracket F Rotate the drag links assembly by hand until the uplock hook engages the uplock bearing G With the uplock cable fully extended and the hook resting fully on the uplock roller adjust the cable end until the attaching bolt on the hook can be freely inserted Remove the bolt and extend the cable end one full turn and lock...

Page 663: ...right side of the wheel well so that the idler linkage is 22 to 28 inches through center 7 Connect the downlock spring to the idler link 8 Extend the actuator cylinder with hydraulic pressure and adjust the rod end until the attaching bolt can be freely inserted Release pressure and extend the rod end one full turn Reinstall the bolt and secure Tighten the rod end locknut NOTE The actuating cylind...

Page 664: ...lace the airplane on jacks Refer to Jacking Chapter 7 3 Level the airplane laterally and longitudinally Refer to Leveling Chapter 8 4 From the center of the tail skid extend a plumb bob and mark the contact point on the floor 5 Extend and attach a plumb bob from a point that is approximately 24 inches forward along the bottom center row of rivets as measured from the wheel well opening Mark the po...

Page 665: ...31P 350 MAINTENANCE MANUAL 1077 Figure 32 8 Clamping Rudder Pedals in Neutral Position Figure 32 9 Rudder Pedals Neutral Angle C621 PLUMB BOB LINE Figure 32 10 Aligning Nose Gear 32 22 05 Page 32 32 Revised July 28 1983 3E18 ...

Page 666: ...ull the piston rod of the shimmy damper to its full extension C Adjust the pushrod end bearing until the attachment bolt fits freely through the rod end and bracket D Remove bolt and turn the rod end bearing out one full turn E Bolt the rod end bearing to the bracket NOSE GEAR DOOR ASSEMBLY REMOVAL OF NOSE GEAR DOOR ASSEMBLY 1 To remove the gear door disconnect the retraction rod at the door and r...

Page 667: ...e following items until gear will lock up A Increase actuator stroke by turning out stroke control stop B Relieve door pinch by lengthening door operating rods C Delay the actuating of up limit switches EXTENSION AND RETRACTION GEAR ACTUATING CYLINDERS REMOVAL OF GEAR ACTUATING CYLINDER 1 Place the airplane on jacks Refer to Jacking Chapter 7 2 Disconnect the hydraulic lines from the actuating cyl...

Page 668: ...spect threaded areas for damage 4 Inspect the rod end fitting for wear and corrosion 5 Repairs to the cylinder are limited to polishing out small scratches burrs etc and replacing parts ASSEMBLY OF GEAR ACTUATING CYLINDER WTC 2115 1 Refer to Figure 32 11 Lubricate all parts with hydraulic fluid per MIL H 5606 prior to assembly 1 Install GT ring on the head of the piston 2 Install back up and O rin...

Page 669: ...m jacks GEAR DOOR ACTUATING CYLINDERS REMOVAL OF GEAR DOOR ACTUATING CYLINDER 1 With master switch off actuate the hand pump handle to bring the gear door down 2 Disconnect the hydraulic lines from the actuating cylinder and cover the open line ends to present contamination 3 Disconnect the cylinder from the door and its mounting bracket 4 Remove the cylinder from the wheel well DISASSEMBLY OF GEA...

Page 670: ...r 2 Install nut and nut on barrel 3 Install back up rings and O rings into grooves of barrel 4 Install spring plunger and race into clevis end and secure by screwing barrel into clevisend Tighten barrel down against the race and torque to 120to 140inch pounds Then tighten nut against the clexis end and torque to 120to 140 inch pounds 5 Install GT ring into groove of piston 6 Install GT ring into g...

Page 671: ...oval of Selector Handle Assembly A Remove stop pin and pull the control knob and sleeve from the lever assembly B Disconnect the wires leading from the panel assembly Remove four light assemblies securing the panel assembly to the plate assembly C Remove pin washer and cotter pin securing the terminal to the lever assembly D Remove the selector assembly from the instrument panel 3 Removal of Flexi...

Page 672: ...3 STOP PIN 4 SAFETYWIRE 5 PLATE ASSY 6 LEVERASSY 7 CABLE ASSY 8 BRACKETASSY 9 CLAMP 10 CONTROLARM 11 BRACKETASSY 12 PIN WASHER AND COTTERPIN 13 SOLENOID 14 MOUNTING BLOCK 15 PANEL ASSY 16 LIGHT ASSY 17 CABLE ATTACHMENT PIN 18 TERMINAL 19 GROMMET 20 FIREWALLPLATE VIEWA A Figure 32 13 Landing Gear Selector Mechanism 32 33 01 Page 32 39 Revised July 28 1983 3F1 ...

Page 673: ...and install nylomatic washer and lock nut and light cap Connect wires to their appropriate terminals D Insert the sleeve on the lever and install the control knob and stop pin 3 Installation of Solenoid Assembly A Position the solenoid on mounting block and secure in position with two lock nuts B Connect the solenoid wires to their appropriate terminals WHEELS AND BRAKES MAIN WHEEL ASSEMBLY REMOVA...

Page 674: ...age Remove rust and blend out nicks using fine 400 grit sandpaper Replace disc if cracked or when disc is worn below minimum thickness Refer to Figure 32 15 REPAIR OF MAIN WHEEL ASSEMBLY Repairs are limited to blending out small nicks scratches gouges and areas of slight corrosion plus replacement of parts which are cracked or badly corroded NOTE Remove rust and blend out small nicks using fine 40...

Page 675: ...al felt and snap ring into the proper wheel halves 2 Inflate the tube sufficiently to round it out Install tube into tire so that balance mark yellow or white band is radially aligned with the tire balance mark red dot 3 Place outer wheel half into tire and pull tube valvestem through valve hole Turn tire and outer wheel half over and place the spacer referto Figure 32 14 and inner wheel half into...

Page 676: ...rtion defects and excess wearand corrosion 3 Check tie bolts for looseness or failure 4 Check internal diameter of felt greaseseals Replacethe felt greaseseal ifsurfaceis hard or gritty 5 Check tire for cuts internal bruises and deterioration 6 Check bearing conesand cups for wearand pitting and relubricate per lubrication chart 7 Replaceany wheel casting having visiblecracks REPAIRAND REPLACEMENT...

Page 677: ...INNER 2 WHEEL HALF OUTER 3 BOLT 4 WASHER 5 NUT 6 BEARINGCUP 7 BEARINGCONE 8 GREASE SEAL RETAINER 9 GREASE SEAL FELT 10 SNAP RING PIPER AIRCRAFT PA 31 P 350 MAINTENANCE MANUAL 2589 B F GOODRICH 3 1076 6 1086 CLEVELAND 40 140 I Figure 32 16 Nose Wheel Assembly 32 42 04 Page 32 44 Revised July 28 1983 3F6 ...

Page 678: ...The wheelbearingandsealcan beremovedby tappingout evenlyfrom the insidewith abrassdrift Becareful not to damagethe bearingcage INSPECTION OF NOSE WHEEL ASSEMBLY B F GOODRICH 1 Clean metal parts in solvent and air dry thoroughly Cleanrubber parts bywiping withaclean lint free cloth 2 Magnaflux bolts for cracks breaks and surfaceblemisheson the bolt headradius or shank 3 With dyecheckor Zyglo inspec...

Page 679: ...ion between parts 2 Reinstall valve stem and balance weights if removed 3 Lubricate the packing with grease MIL G 3545C or equivalent and install in the packing groovc on the wheel hall 4 Install the tire and join the two wheel hales Apply a generous coat of thread compound MIL T5544 to threads of bolts faces of washers and bearing face of nuts Tigthen two nuts diametrically opposite to 100inch po...

Page 680: ...UBE FITTING 21 NUT 23 22 HOSE INLET 23 O RING 30 123 21 20 271 TORQUETO BOLT 2 WASHER 60 IN LBS 2WASHER 3 O RING 4 PISTON 5 INSULATOR 6 PLATE PRESSURE 7 FRICTION SPRING 8 LINING 30 95A 9 SHIM 10 PLATE BACK 11 PLATE TORQUE 2 12 NUT 13 CAP BLEEDER 14 SCREW BLEEDER 16 BOLT ANCHOR 048 MAX DISCTO LINING LININGSFULLYRETRACTED Figure 32 17 Wheel Brake Assembly Cleveland 30 95A and 30 123 32 42 08 Page32 ...

Page 681: ...NG HOLDING FIXTURE FIXTURE PRESS HOLDING FIXTURE PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 212 PRESS ANCHORBOLT STEP A STEPB STEP C CYLINDERBODY STEPD I Figure 32 18 Removal and Installation of Anchor Bolts 32 42 08 Page 32 48 Revised July 28 1983 3F10 ...

Page 682: ...ghly 2 Check the wallsof the cylinder housingand pistonsfor scratches burrs corrosion etc that may damageO rings 3 Check the generalcondition of the bleederscrewand lines 4 Check anchor bolts for wear 5 Lining mayberemo ed from a backingplateby insertinga sharptool betweenthe lining and plate Press new lining on the backing plate NOTE Replacement brake linings should be conditioned by performing t...

Page 683: ...inch pounds for 30 95A brake assemblies and 80 to 90 inch pounds for 30 123 brake assemblies 7 With brake line disconnected push the linings as far apart as possible In this position there should not be excessive drag or the tolerance between the disc and lining should not be greater than noted on Sketch A of Figure 32 17 Assemblies falling outside the limits noted should be removed and rechecked ...

Page 684: ... 2 VENTTUBE 3 RESERVOIR 4 MASTER CYLINDER RIGHT 5 MASTER CYLINDER LEFT 6 PARKINGBRAKE VALVE 7 PARKINGBRAKE HANDLE 8 FUSELAGE LINK 9 FLEXIBLEHOSE 10 GEAR LINK 11 BRAKEASSEMBLY I Figure 32 19 Brake Installation Typical 32 44 02 Page 32 51 Revised July 28 1983 3F13 ...

Page 685: ...hes burrs corrosion etc 5 Repairs to the cylinder are limited to polishing out small scratches burrs etc and replacing valve washer seal and O rings ASSEMBLY OF BRAKE MASTER CYLINDER Refer to Figure 32 20 I Install O ring on the cylinder piston Assemble onto the piston rod the piston spring washer seal and alve Allow the valve to extend into the baseof the piston Slide the O ring and washer in pla...

Page 686: ...e body A valve spring is held in place by the fittings Use caution not to loosen these when removing the fittings 2 From the valve body remove the valve spring and valve 3 To remove the valve cam remove the nut washer bushing and spring and pull the cam from the valve body CLEANING INSPECTION AND REPAIR OF PARKING BRAKE VALVE 1 Clean the valve parts with a suitable solvent and dry thoroughly 2 Ins...

Page 687: ...lines to the valve 3 Connect the control cable to valve lever and determine that whenvalve leverfits in the closed detent parking brake handle is 062 to 125 inch of being full in against stop 4 Bleed the brake system BLEEDING PROCEDURE If the brake line has been disconnected for any reason it will be necessaryto bleed the brake systemas described below 1 Place a suitable container at the brake res...

Page 688: ...RCYLINDER DUAL PARKING BRAKE VALVE OPEN CLEVELAND BRAKESYSTEM CAP BLEED PORT PRESSURE GAUGE REGUATOR SHUT OFF VALVE PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL C842 0 BRAKE BLEEDER FILL WITH MIL H 5606A SHOP AIR I Figure 32 22 Bleeding Brake Pressure Pot 32 45 06 Page 32 55 Revised July 28 1983 3F17 ...

Page 689: ...er cylinder from the pedal assembly 5 Disconnect the balance cable from the two inboard pedals by removing the flat head pins at rudder pedals 6 Remove the rudder torque tube guards by removing the machine screws nuts and clamps positioning the guards to the torque tube and remove the attaching hardware securing each guard to the brake line support channel 7 Remove the small round access plate loc...

Page 690: ...OLTASSEMBLY 18 RETAINER 19 BOLT ASSEMBLY 20 BOLT CAF 21 BLOCK BEARING 22 BRACKET MOUNTING 23 PLATE 24 ROD 25 CONTROLCABLE 26 BRAKE CYLINDER 27 PEDAL RIGHTOUTER 28 PEDAL RIGHTINNER 29 NUT JAM 30 BOLT ASSEMBLY 31 PEDAL LEFTINNER 32 PEDAL LEFT OUTER 33 BALANCE CABLE 34 BRAKE LINE SUPPORT CHANNEL 35 TORQUETUBE GUARD 36 MACHINE SCREWSAND NUTS 37 SCREWS NUTS AND CLAMPS 38 PULLEY 39 FLAT HEAD PINS 14 28 ...

Page 691: ...y The tube may be slid to either side when the collar bolts are removed to allow the spacer washers to bedivided and installed evenly between each set of retainers and bearings 8 With the spacer washers installed install the bolts through the retainers and both leftrudder pedals Install nuts with washers and secure 9 Wipe off excess lubricant from torque tube 10 Install the rudder torque tube guar...

Page 692: ... 4 Extend and retract gear to ascertain proper adjustment ADJUSTMENT OF MAIN GEAR DOWN LIMIT SWITCH Refer to Figure 32 24 1 Ascertain that the main landing gear downlock is properly adjusted 2 With the gear down and locked the green indicator light in the cockpit should come on when the downlock hook is lowered to within 030 to 069 of an inch of bottoming inthe hook slot of the lower side brace li...

Page 693: ...e airplane on jacks Refer to Jacking Chapter 7 2 Compress the strut until nine inches is obtained between the top of the gear fork and the bottom of the gear housing Hold the gear at this measurement 3 Adjust the switch down until it actuates at this point Secure the switch 4 Extend and then compress the strut to ascertain that the switch will actuate in the last 250 13 inch of oleo extension 5 Re...

Page 694: ... the frame I INSTALLATION OF GEAR WARNING SWITCHES Refer to Figure 32 25 1 The switch mounting brackets as part of the control lever assembly may be installed as follows A Assemble the mounting brackets switches and spacer blocks may be installed with mounting brackets tension springs and spacer washers in thecontrol frame and secure with keeper tube Secure keeper tube in frame B Install control l...

Page 695: ...tachment screws Install nuts on the screws and secure C Position the pedestal cover plates on the pedestal install screws and secure D Adjust the switches ADJUSTMENT OF GEAR WARNING SWITCHES The gear warning horn switches are installed in the control pedestal with each controlled by a throttle lever Each switch actuates the warning horn when either or both throttles are reduced below 10to 12inches...

Page 696: ... the gear up indicator horn sounds Checkthe location of the throttle to the adjusting mark The warning horn will operate when either or both throttles are retarded B Withthe warninghorn operating lowerthegearto insurethat the hornceasestooperate w hen the gear is down and locked C Remove the airplane from the jacks 3 Flight Adjustment A Flight test the airplane to insure operation of the warningsy...

Page 697: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL GRIDS 3G2 THRU 3G10 INTENTIONALLY LEFT BLANK 3G2 ...

Page 698: ...CHAPTER LIGHTS 3G11 ...

Page 699: ...n Of Operation 3G16 33 13 02 Removal Of Annunciator 3G 17 33 13 03 Installation Of Annunciator 3G17 33 13 04 Annunciator Panel Lamp Replacement 3G17 33 14 00 Trim Indicator Lighting 3G19 33 14 01 Replacement Of Trim Indicator Lamps 3G19 33 15 00 Cowl Flap Indicator Lighting 3G 19 33 15 011 Replacement Of Cowl Flap Indicator Lamps 3G19 33 20 00 PASSENGER COMPARTMENT 3G19 33 21 00 Speaker Panel Dome...

Page 700: ...41 06 Installation Of Wing Tip Strobe Power Supply 3G24 33 42 00 Recognition Lights 3G24 33 42 01 Removal Of Inflight Recognition Lights 3G24 33 42 02 Installation Of Inflight Recognition Lights 3G24 33 43 00 Landing Taxi Lights 3G24 33 43 01 Removal Of Landing Taxi Lamps 3G24 33 43 02 Installation Of Landing Taxi Lamps 3HI 33 44 00 Logo Lights 3HI 33 44 01 Logo Lamp Replacement 3HI 33 44 02 Logo ...

Page 701: ...ust be replaced and a point to point check must bemade within each lighting circuit before replacing Dimmer Control If only one E L Panel is OUT unplug the panel and check for 140 V A C 400 Hertz at panel connection then work back through the harness to the inverter Each E L panel can be bench tested at 117 V A C 60 Hertz If any E L Lighting is operating the inverter can be considered to be good I...

Page 702: ...y REMOVAL OF DIMMER SLIDE CONTROLS The slide controls are located together in the overhead switch panel 1 Remove the knobs from the slide controls 2 Remove the screws securing the placard panel to the switch panel and remove placard panel 3 Remove the screws securing the royalite trim panel containing the overhead switch panel and let hang 4 Remove wires from slide control making note of the place...

Page 703: ... 28 V D C is applied from battery bus No 2 via a 5 amp fuse Three redundant air frame ground pins are used and shall remain connected A loss of essential power or internal flasher is indicated on master caution channel 22 Fire extinguisher channels if extinguishers are not installed become alternate power channels and may be connected in parallel with annunciator power master caution channel 22 Di...

Page 704: ...he annunciator panel is located beneath the glareshield at the top of the instrument panel Replacement of a defective lamp does not require removal of the annunciator panel To replace a lamp simply push in on the appropriate light cover assembly until it clicks approximately I 16inch and release The cover assembly will be partially ejected from the base assembly Pull the cover assembly fromthe bas...

Page 705: ...ing Fasten Seat Belts Sign Reading Anti Collision Wing Tip Strobe Landing Taxi Logo Position Tail Position Wing Wing Inspection 472 058 472 028 472 028 758 15 472 027 472 057 472 028 472 028 472 028 472 028 472 769 472 057 472 027 472 029 453 886 387 327 MS 5584 15 1495 313 327 327 327 327 4596 313 1495 327 1309 EXTERNAL LIGHTING 762 472 761 761 753 472 003 769 207 208 769 049 A 610 4596 DA 27 A 5...

Page 706: ... by removing panel attachment screws Each bulb is rotated from itssocket The cowl flap switches are attached to the panel trim PASSENGER COMPARTMENT SPEAKER PANEL DOME LIGHTS REMOVAL OF SPEAKER PANEL DOME LIGHTS The lamp is located between speakers on the overhead speaker panel It is necessary to remove the complete panel assembly from the headliner before the lamp can be changed 1 Remove the 8 at...

Page 707: ... replace the lamp 1 Remove the machine screws holding the circular trim plate around light assembly and remove the trim panel 2 Using a flat tool carefully pry out the headliner panel from the trim extrusions 3 Remove the screws holding light assembly in place and remove assembly 4 Remove the snap cover over the lamp on the assembly and replace the lamp INSTALLATION OF ENTRANCE LAMP 1 Replace the ...

Page 708: ...screws holding the door step light assembly to the door trim panel 2 Slide off the rubber boot on the rear of the light assembly 3 Remove the snap bracket from the rear of the light assembly and remove the lamp INSTALLATION OF LAMP IN DOOR STEP LIGHTS 1 Replace the lamp using the proper number 2 Reinstall the snap bracket and rubber boot 3 Reinstall the light assembly and secure it to the panel wi...

Page 709: ...again develops a high voltage through transformer action After full voltage is again impressed on the capacitor the cycle repeats itself occuring at about 50flashes per minute Since each wing tip strobe is powered by its own power supply and if BOTH POWER SUPPLIES ARE EMITTING AUDIBLE TONES simply switch power supplies from each wing tip If the trouble follows the power supply replace it if the fa...

Page 710: ...to the strobe lamp at the bottom of the bracket assembly 5 Pull cut wires from wing tip and disconnect at three pin connector discard connector NOTE Secure wing harness connector outside of wing INSTALLATION OF WING TIP STROBE LIGHTS 1 Route wires from newlamp down through hole in the light bracket assembly 2 Insert the wire terminals into the plastic plug supplied with the new lamp Wire plug as f...

Page 711: ...ect electrical connection 5 Remove light assembly NOTE Bulb replacement can be accomplished by removing screw on re tainer ring and removing retainer and lens INSTALLATION OF INFLIGHT RECOGNITION LIGHTS 1 Reconnect the electrical connector to the light assembly 2 Secure light assembly with two screws previously removed 3 Place plexiglass cover in position on wing tip and secure with appropriate sc...

Page 712: ...amp place lens cover over light assemblyfor eye protection 3 When adjusting light assembly turn lamp switch off allow time for cooling reflector and lamp become extremely hot LOGO LAMP REPLACEMENT 1 Removelensscrewand lenscover 2 Removebulb 3 Install newbulb placelenscoveroverlight assembly applyelectricalpowerand turn on logo light switch and checkfor proper illumination of lamp 4 Placelogolight ...

Page 713: ...LIGHT The wing tip position lights are located on each wing tip inside a plexiglass cover 1 Remove the screws securing the plexiglass cover to the wing tip 2 Remove the screw securing the lens retainer to the light assembly 3 Remove the lens retainer and lens NOTE To remove the complete light assembly the wing tip must be removed 33 45 01 Page33 13 3H2 Issued April 25 1983 3H2 ...

Page 714: ...L POSITION LIGHT 1 Install the bulb 2 Install lens retaine and secure with the appropriate screws WING INSPECTION LIGHT DESCRIPTION AND OPERATION The light is mounted in the outboard side of the left nacellejust above leading edge of the wing It is a sealed beam 24 volt unit which is controlled from a rocker type switch mounted in the overhead switch panel The light is positioned in the nacelle to...

Page 715: ...p on the panel 2 Install the tour clips and securewith screwsand nuts 3 Connect the electricalleadsto the back of the lamp assembly 4 Position the entire panel on the nacelleside and securewith screws 5 Activate the switch in the cockpit to checktne lamp operation END 33 47 03 Page 33 15 Issued April 25 1983 3H4 ...

Page 716: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3H5 ...

Page 717: ...CHAPTER NAVIGATION AND PITOT STATIC 3H6 ...

Page 718: ... 34 23 02 34 24 00 GENERAL Description Troubleshooting Inspection and Checks of Instruments and System Removal of Instruments Installation of Instruments FLIGHT Rate of Climb Indicator Sensitive Altimeter Airspeed Indicator ATTITUDE AND DIRECTION Magnetic Compass Directional Gyro Gyro Horizon Gyro Installation Inspection Gyro Handling and Shipping Turn and Bank Indicator 3H8 3H8 3H8 3H11 3HII 3H12...

Page 719: ...gto the airspeed indicator on the instrumentpanel Static air systemconsists of two static ports one on each side of the fuselage Theseports are inter connected as shown in Figure 34 1and the tubing is then routed forward through the fuselageto the back of the instrumentpanel whereit isconnectedto the airspeedindicator altimeterand rate of climbindicator The purpose of the static system is to vent ...

Page 720: ...TATIC SYSTEM TEST FOR AIRCRAFTNOT OPERATEDIN CONTROLLED AIRSPACE UNDER IFR CONDITIONS SEE ADVISORY CIRCULAR AC 43 13 1A SEC TION 4 OF CHAPTER 16 REFERTO PARTS CATALOG FORTYPICAL SYSTEM ROUTING 1 STATICSOURCE FORPILOT SAND COPILOT S STATIC INSTRUMENTS 2 CIRCUIT BREAKER 3 AIRSPEED INDICATOR 4 ALTIMETER 5 RATE OFCLIMB INDICATOR 6 PITOTHEAD Figure 34 1 Instrument Air System Installation Typical 34 00 ...

Page 721: ...MBLY STATIC PRESSURE 4 VALVE STATICAIR PRESSURE 5 PLUG BUTTON 6 MANIFOLD ASSEMBLY STATIC AIR 7 CAP ASSEMBLY 8 GROMMET 9 INDICATOR AIRSPEED 10 ALTIMETER 11 INDICATOR RATEOF CLIMB 12 CABIN DIFF PRESSURE ALTITUDE 13 PNEUMATICPRESSURE Figure 34 2 Pitot Static Installation s 34 00 02 Page 34 03 Issued April 25 1982 3H10 ...

Page 722: ...curity and condition Check instrument lighting system for range of illumination burned out bulbs and defectivecontrols Check wiring for chafing excessivetension improper support or broken lacingand ties 8 Check instruments for evidenceof overheatingor contamination of equipmentby foreignmatter or water Dust dirt and lint contribute to overheatingof equipment poor ventilationand mal functioning Spe...

Page 723: ...and or electrical connector to back of instrument D Connect the electrical connector of the post light s Tighten connector finger tight E Check instrument and post light s operation 2 The shock mounted instruments may be installed by the following procedure A Place the instrument in its proper panel cutout and secure with screws B Install the post light s and secure Do not overtighten nut C Connec...

Page 724: ...d Pointer oscillates Leaks in static lines Disconnect all instru ments connected to the static line Check individual instruments for leaks Reconnect instruments to static line and test installa tion for leaks Defective mechanism Replace instrument Rate of climb indi cates when aircraft is banked Pointer has to be set before every flight Pointer cannot be reset to zero Instrument reads very low dur...

Page 725: ... higher altitude CHART 3402 TROUBLESHOOTING ALTIMETER Trouble Cause Remedy Excessive scale error Excessive pointer oscillation High or low reading Setting knob is hard to turn Inner reference marker fails to move when setting knob is rotated Setting knob set screw loose or missing Cracked or loose cover glass Improper calibration adjustment Defective mechanism Improper venting Wrong lubrication or...

Page 726: ...rspeed indication depends on the differential pressure between pitot air pressure and static air pressure This instrument has the diaphragm vented to the pitot air source and the case is vented to the static air system As the airplane increases speed the pitot air pressure increases causing the diaphragm to expand A mechanical linkage picks up this motion and moves the instrument pointer to the in...

Page 727: ...ch ON Circuit breaker popped Open circuit Reset Repair Excessive voltage drop between battery and pitot head Heating element burned out Check voltage at pitot head Replace pitot head NOTE When any connections in static system are opened for checking systemmust be checked per FAR 23 1325 ATTITUDE AND DIRECTION MAGNETIC COMPASS The magnetic compass is a self contained instrument This instrument has ...

Page 728: ...t Instrument too heavily compensated Excessive pivot fric tion or broken jewel Remove excess compensation Replace or repair instrument Liquid leakage Loose bezel screws Replace or repair instrument Replace or repair instrument Replace or repair instrument Replace or repair instrument Check lamp or conti nuity of wiring Discolored markings Defective light Age Burned out lamp or broken circuit Altit...

Page 729: ...en set for If the gyro is set on 270 for instance and the aircraft is turned to some other heading there can be a large error between the gyro and the magnetic compass due to the error in compass compensation this will appear as gyro precession The gyro should only bechecked on the heading on which it was first set also due to internal friction spin axis error air turbulence and airflow the gyro s...

Page 730: ...edegrees of bank CHART 3406 TROUBLESHOOTING GYRO HORIZON INDICATOR Trouble Cause Remedy Bar fails to respond Insufficient pressure Check pump and tubing Filter dirty Clean or replace filter Bar does not settle Insufficient pressure Check line and pump Adjust valve Excessive vibration Incorrect instrument Defective instrument Check shock mounts Replace if necessary Check part number Replace Bar osc...

Page 731: ...rect and does the pressure gauge give an accurate reading 7 Is the pressure regulator adjusted correctly and functioning properly 8 Is proper voltage available 9 Is electrical grounding in tact 10 Is circuit breaker correct or faulty 11 Are all electrical plugs and connections secure GYRO HANDLING AND SHIPPING The following information applies to all three inch directional gyros and attitude horiz...

Page 732: ...MAINTENANCE MANUAL Trouble Cause Remedy Instrument will not operate No power to instrument Reset circuit breaker Check circuit and repair Instrument malfunction Foreign matter lodged in instrument Repair instrument Replace instrument Incorrect sensitivity Pointer does not set on zero Misadjustment of sen sitivity spring Gimbal and rotor as sembly out of balance Adjust by means of sensitivity sprin...

Page 733: ...nd does not set on zero when stationary Oil has become too thick Insufficient bearing clearance Oil or dirt between damping pistons and cylinder Excessive clearance between rotor and rotor pivots Replace instrument Replace instrument Replace instrument Replace instrument Ball sticky Flat spot on ball Replace instrument Ball not in center when aircraft is correctly trimmed Instrument not level in p...

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Page 735: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLYLEFT BLANK 3H24 ...

Page 736: ...CHAPTER OXYGEN SYSTEM 311 ...

Page 737: ...ets 3110 35 14 03 Installation of Outlets 3110 35 14 04 Oxygen Cylinder 3111 35 14 05 Removalof Oxygen Cylinder and Regulator 3111 35 14 06 Installation of OxygenCylinder and Regulator 3111 35 14 07 Charging Valve 3113 35 14 08 Remoxalof Oxygen SystemCharging Val e 3113 35 14 09 Installation of Oxygen SystemCharging Valve 3113 35 14 10 PressureGauge 3113 35 14 11 Removalof PressureGauge 3113 35 14...

Page 738: ... Cylindersareavailablein the22cu It capacity or 50 cu ft capacity NOTE A so availablefor compliance to FAR 135certification is a50 cu ft cylinder with an altitude compensated regulator The storagecylinder is filled through the filler valveand supplieshigh pressureoxygento the regulator assembly High pressureoxygenis routed from the regulator to the pressuregaugewhile low pressureoxygenis routed fr...

Page 739: ...4 OXYGEN CYLINDER 5 HIGH PRESSURELINE 6 OXYGEN FLOW CONTROLKNOB 7 OXYGEN SUPPLYPRESSUREGAUGE 8 PILOTPLUG IN OXYGEN OUTLET 9 COPILOT PLUG IN OXYGENOUTLET 10 LOW PRESSURELINE 11 PASSENGEROXYGENOUTLETS 12 SEVENTHSEAT PASSENGEROXYGEN OUTLET Figure 35 1 Oxygen System Installation 35 00 02 Page 35 02 Revised July 28 1983 314 ...

Page 740: ...OR 6 HIGH PRESSURELINE 7 OXYGENSUPPLY PRESSUREGAUGE 8 OXYGEN FLOWCONTROLKNOB 9 PILOT PLUG IN OXYGENOUTLET 10 OXYGENSHUTOFFVALVE 11 COPILOTPLUG IN OXYGENOUTLET 12 LOW PRESSURELINE 13 PASSENGEROXYGEN OUTLETS 14 SEVENTHSEAT PASSENGEROXYGEN OUTLET Figure 35 2 Oxygen System Installation for FAR 135Certification 35 00 02 Page 35 03 3I5 Added July 28 1983 315 ...

Page 741: ...sure on pressure gauge Oxygen cylinder valve closed Open valve Pressure gauge defective Defective regulator Safety disc ruptured cylinder empty Replace gauge Replace regulator Replace cylinder and visual indicating disc Oxygen cylinder will not retain pressure Offensive odors in oxygen Leak in system Cylinder pressure below 50 psi Foreign matter has entered the system during previous servicing Loc...

Page 742: ...ygen systems Teflon tape and Krytox 240AC 4 All oxygen system components must be handled with care to avoid damage 5 Prior to working on the oxygen system personnel must clean hands and tools Cleanliness is essential 6 When removing regulator retain all adjustment washers which fit around the adjustment shaft These washers are safety stops for maximum regulated pressure and must be used with reins...

Page 743: ...hould be replacedwith factory replacements 5 Clean all linesand fittings in accordancewith Spec MIL 1 5585A PAR 331 Referto Cleaning Oxygen SystemComponents 6 Ribbon Dope Thread Sealant Permacel 412 should be applied to male pipe threads only Apply the sealantby startingat the second threadand wrapthreadsindirectionof threadspiralwith a 1 4 inch or more overlap after joint is made removeexcessive ...

Page 744: ...ry nitrogen 4 Flush with naphtha blow unit clean and dry with dry nitrogen Flush again using anti icing fluid or anhydrous ethyl alcohol Rinse thoroughly with fresh water and purge dry with dry nitrogen PURGING OXYGEN SYSTEM The oxygen system is purged to remove condensed moisture and offensive odors using dry nitrogen The system must also be purged if system pressure falls below 50 psi or ifany l...

Page 745: ...h the rest of the mask with a very mild solution of soap and water 4 Rinse the mask thoroughly to remove all traces of soap 5 Make sure the sides of the breathing bag do not stick together while drying as this may decrease the life of the rubber in the bag The mask can be sterilized with a solution of 70 percent ethyl alcohol COMPONENTS OUTLETS REMOVAL OF OUTLETS 1 Using a suitable spanner wrench ...

Page 746: ...cket assembly clamps that hold the cylinder in place 4 Remove the cylinder from the airplane using caution not to bump the neck of the cylinder regulator and compensator if installed CAUTION The cylindermust be completely dischargedof allpressureprior to removingthe regulatoror compensator if installed INSTALLATION OF OXYGEN CYLINDER AND REGULATOR 1 With the regulator and compensator if installed ...

Page 747: ...MS3367 CABLE TIES POSI TION SLIT AWAY FROM WIRES ETC SKETCHA PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL B871 1 8 MIN 1 8 MIN SKETCHB GROMMET CORRECT INCORRECT SKETCHD 2 IN SKETCHC I Figure 35 3 Oxygen Tubing Installations 35 14 06 Page 35 10 Revised July 28 1983 3112 ...

Page 748: ...ve is closed and there is no pressure in the system 1 Disconnect the connector from the back of the pressure gauge 2 Loosen and remove the retainer nut and clamp holding the gauge in place 3 Pull the gauge out from the front of the panel INSTALLATION OF PRESSURE GAUGE 1 Place the gauge into the panel from the front and replace the clamp and retainer nut on the back of the gauge Be sure the gauge i...

Page 749: ... whichever comes first The month and year of the last test is stamped on the cylinder beneath the ICC or DOT identification The light weight cylinder used with FAR 135 certification must be retired from service after 15 years 2 The outlets should be checked for leakage both in the non use condition and for leakage around an inserted connector 3 The high pressure gauge may be checked for accuracy b...

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Page 751: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLYLEFT BLANK 3116 ...

Page 752: ...CHAPTER PNEUMATIC SYSTEM 3117 ...

Page 753: ... Description DISTRIBUTION Pneumatic System Filter Replacement Dry Pneumatic Pump Removal of Dry Pneumatic Pump Installation of Dry Pneumatic Pump Regulating Valve Removal of Two Stage Regulating Valve Installation of Two Stage Regulating Valve Check Valve Removal of Check Valve Installation of Check Valve Pressure Switch Removal of Pressure Switch Installation of Pressure Switch 3119 3119 3119 311...

Page 754: ...neand two inlinefilterslocatedalongthe outlet sideof the pneumaticpumps The followinginstructionswillcoverthe removaland installationof the inline filtersalong with recommendedcleaningand replacementtime as required Refer to Chapter 71 for maintenance instructionsfor inductionair filters 1 Removalof inlinefilter located aft of the fire wall in both the left and right engine nacelle A Removethe app...

Page 755: ...PRESSUREREGULATOR 11 PNEUMATIC PRESSURESWITCH 12 INLINE FILTER 13 OUTBOARD DEICEBOOT 14 DUAL CHECKVALVE 15 DEICE INFLATIONVALVE A 16 DEICE INFLATIONVALVE B 17 EMPENNAGE DEICEBOOTS 18 CABIN DOORSEAL 19 SOLENOIDVALVE 20 ACCUMULATOR TANK 21 CABIN DOORSEAL PRESSURESWITCH 22 CABIN DOORSEAL CHECKVALVE 23 VACUUM EJECTOR 24 DEICEINFLATION SWITCH A 25 DEICEINFLATION SWITCH B 21 19 18 17 Figure 36 1 Pilot s...

Page 756: ...thuseliminating any need for thread lubricants If a thread lubricant is required use a powdered moly sulfide or graphite in dryform or in an evaporating vehicle or employ a silicone spray Apply sparingly to external threads of fittings only DO NOT use pipe tape thread dope hydrocarbon oil or grease as these can contaminate pump and cause malfunction With pump properly secured in vise insert fittin...

Page 757: ...ith hoseclamps 4 Reinstall accesspanel CHECK VALVE REMOVAL OF CHECK VALVE I Gain access to the checkvalveby removingthe centerfloorboard panelbetweenfuselagestations 140and 151 30 2 Removethree lines going to checkvalve 3 Cap lines 4 Removecheck valve INSTALLATION OF CHECK VALVE 1 Remove caps from lines 2 Attach lines to check valve Torque fittings 3 Reinstall previously removed floorboard panel P...

Page 758: ... 2 Disconnect electrical leads 3 Remove the switch by placing an open end wrench on the bottom of the switch and unscrew the switch from the line INSTALLATION OF PRESSURE SWITCH 1 Screwthe switch into the line and tighten 2 Connect the electrical leads 3 Reinstall floorboard panel END 36 15 02 Page 36 05 Issued April 25 1983 3123 ...

Page 759: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3124 ...

Page 760: ...CHAPTER VACUUM SYSTEM 3J1 ...

Page 761: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL NOTE The pneumatic and vacuum systems have been combined to form Chapter36 PneumaticSystem 3J2 ...

Page 762: ...CHAPTER ELECTRIC ELECTRONIC PANELS AND MULTI PURPOSE PARTS 3J3 ...

Page 763: ...del 2504 3J9 39 20 05 General Description 3J9 39 20 06 Service Guideline 3J10 39 20 07 Troubleshooting Digital Cabin Instruments Display 3J12 39 30 00 ANNUNCIATOR PANE 3 114 39 30 01 General 3 114 39 30 02 Troubleshooting 3J15 39 40 00 AVIONICS MASTER SWITCHING 3J15 39 40 01 General 3 15 39 40 02 Troubleshooting 3 15 39 50 00 ELECTRICAL SWITCHES AND CIRCUIT BREAKERS 3J15 39 50 01 Removal of Overhe...

Page 764: ... engine instruments and avionics equipment in the center A second set of flight instruments may be installed in the right panel for use by the copilot The flight instrument panels are shock mounted to minimize ibration and shock transmitted to the instruments Refer to Figure 39 5 INSTRUMENTS REMOVAL OF INSTRUMENTS The majority of instruments are mounted in a similar manner therefore a typical remo...

Page 765: ...l tube F Unscrew the electrical connector from the post light s G Disconnect the plumbing and or electrical connector from the back of the instrument and identify each line to facilitate reinstallation Attach a dust cap or plug to each fitting H Remove the post light s by turning off nut I Remove the screws that secure the instrument in the panel cutout J Remove the instrument from the panel and s...

Page 766: ...r tight E Ascertin that one end of the ground straps is placed over the panel side of the shock mount stud F Place the floating panel in position and allow the shock mount attachment studs to prov ide through the panel Install and tighten attachment nuts G Remove the padding and release the control wheel H Check the instrument and post light operation 3 Install front mounted instruments in the rev...

Page 767: ... timer which counts minutes and seconds for the first hour then hours and minutes to 24hours The desired display is selected by pressing the mode button the mode is then indicated by a decimal point annunciator in either the TIMER CLOCK position 1 TIMER operation A Press the MODE button to position the decimal point annunciator over the TIMER legend and to place the display in the TIMER mode B Pre...

Page 768: ...ther to display all characters C The display should return to the SET mode D Press the MODE button twice to get out of the SET mode CABIN INSTRUMENTS DISPLAY B D InstrumentsInc Model 2504 GENERAL DESCRIPTION The model 2504 is an independent passenger compartment digital display system annunciating True Airspeed Altitude Outside Air Temperature and Time The system is powered by the 2 Battery Bus Re...

Page 769: ...d and temperature for mach numbers up to 1 2mach The range of the Digital Cabin Display is from 0 999 knots M P H or Km hr are available 60 Celsius to 65 Celsius and altitudes from 1 900 feet to 65 000 feet SERVICE GUIDELINES Service of the Digital Cabin Display System is confined to a Black Box replacement Refer to Figure 39 3 CAUTION NOTE I Use only teflon tape on pitot static port threadedfitti...

Page 770: ...31P 350 MAINTENANCE MANUAL Temperature Probe PROGRAMINGDATA F OR DIGITAL CABIN DISPLAY TRUE AIRSPEED ALTITUDE TEMPERATURE TIME TRUEAIRSPEED INTERFACE TAS SCALE FCTOR ARINC 5G5 C D C ZEROREFERENCE X DUCER 2504 901 SerialNo St Use only Teflon Tape with these fittings ou DAMAGE DAMAGE Pat No 4163387 __ Figure 39 3 System Components Cabin Display THISSPACEINTENTIONALLY LEFTBLANK 39 20 06 Page 39 07 Is...

Page 771: ...e display ground Check wiring to display Red wire connected to 7 2 volts black wire ground Computer unit internal switching power supply Display unit Display lighted in correct altitude and or airspeed indica tion 63 400 feet displayed on altitude indicated a missing voltage or open wire If only slightly off check that the transducer assembly heater ground separate black wire on the connector is c...

Page 772: ...computer unit is faulty Transducer Assembly Check the altitude signal at Pin D of the con nector plug It should be approx 1 25 volts at 0 feet and increase with altitude to approx 2 3 volts at 10 000 feet Pin B ground If missing or incorrect the mal function is in the trans ducer assembly If good at Pin D check at P1 3 for wiring continuity Check the airspeed at Pin E of the connector plug It shou...

Page 773: ...6 volts If missing or incorrect check internal batteries for good connections proper polarity etc Computer Unit ANNUNCIATOR PANEL GENERAL The annunciator panel display presents visual information of various systems equipment functions The Master Caution Channels present alpha indications of malfunctions of selected priority systems equip ment and the Advisory Channels present alpha information of ...

Page 774: ...utilizingschematicsin Chapter 91 ELECTRICAL SWITCHESAND CIRCUITBREAKERS REMOVALOF OVERHEADROCKERSWITCHES 1 Make sure Battery Master Switch is in OFF position 2 Removeelectro luminescentpanel attachment screws 3 Pull electro luminescent E L panel away from the Rovalite trim panel The switchmounting clip can bereached from the rear of the E L panel 4 Insert a thin blade screwdriverbetweenthe clip an...

Page 775: ...in proper alignment any insulators that are called out are installedcorrectly and all electrical wiringand connectionsmeetaviation standards Do not deviate from the Parts Manual requirementswhen replacing circuit breakers DESCRIPTIONOF ENGINE STARTER SWITCHES The push button ALCO starter switch is a modular design The electricalcontactsof this switchare packaged in a switchcontact module several o...

Page 776: ...ex mounting ring on switch shaft from front of panel and tighten Ring may bottom on shaft NOTE To adjust for panel thickness two slot head rear panel mount screws are available at rear panel portion of switch Alternately tighten these two screws to ensure uniform pressure occurs CAUTION DO NOT OVERTIGHTEN REAR ADJUSTMENT SCREWS TO PREVENT DAMAGE TO THE E L PANEL 4 Reinstall E L panel into position...

Page 777: ...CLIMB 24 CLOCK 25 FUEL QUANTITY 26 OIL TEMP OIL PRESS CYL HD TEMP LEFT 27 FUELPRESSURE 28 OILTEMPERATURE OILPRESS CYL HD TEMP RIGHT 29 MIKE EARPHONE JACKS 30 ALTERNATESTATIC SOURCE 31 OXYGEN CONTROLKNOB 32 OXYGEN PRESS 33 CABINTEMP CONTROLS 34 WING FLAPTEST SWITCH 35 WING FLAP POSITIONINDICATOR 36 PROPDEICETEST SWITCH 37 WING FLAP CONTROL 38 MANUAL ALTERNATEAIR 39 PROPSYNC SWITCH 40 CABIN CALL CHI...

Page 778: ...TCH 20 COPILOTMAP LIGHT 21 ELECTROLUMINESCENT E L PANEL 22 ELECTROLUMINESCENT E L PANEL 23 ELECTROLUMINESCENT E L PANEL 24 ELECTROLUMINESCENT E L PANEL 25 EXIT LIGHTING SWITCH 26 WING INSPECTIONLIGHT SWITCH 27 LANDING LIGHTSSWITCH 28 TAXI LIGHT SWITCH 29 ANTI COLLISION LIGHTING SWITCH 30 POSITIONLIGHTS SWITCH 31 BATTERYMASTER SWITCH 32 LEFTWINDSHIELD HEAT SWITCH 33 PROPELLERDEICE SWITCH 34 LEFTPIT...

Page 779: ...RTER 2 19 ELECTRICALACCESSORYSHELF 20 ALTERNATORCONTROLUNITS 21 FUEL QUANTITYSIGNAL CONDITIONER 22 DIODE IN29848 23 VOLTAGE CLAMPERASSEMBLY COWL FLAP 24 STARTERVIBRATOR LEFT RIGHT 25 WINDSHIELD HEAT TIMER 26 FUEL QUANTITYSIGNAL CONDITIONER 27 ANNUNCIATOR CONTROLLERASSEMBLY 28 LANDING GEAR WARNING HORN 29 STALL WARNING HORN 30 LANDING GEAR WARNING RELAY 31 ANNUNCIATOR MASTER CAUTION WARNING 32 TAXI...

Page 780: ...AINTENANCE MANUAL NON ESSENTIAL BUS ICE BUS LEFT MAIN BUS Figure 39 8 Left Side Circuit Breaker Panel RIGHT MAIN BUS BUS DIODEAND HEATSINK TYPICAL Figure 39 9 Right Side Circuit Breaker Panel 39 60 04 Page 39 17 Issued April 25 1983 3J21 ...

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Page 784: ...CHAPTER STRUCTURES 3K1 ...

Page 785: ...s Prone to Corrosion 3K22 IR 12 83 51 30 00 SEALING PROCEDURES 3K23 51 30 01 Fuselage Sealing 3K23 51 30 02 Surface Preparation 3K23 IR 12 83 51 30 03 Material Preparation 3K24 51 30 04 List of Equipment 3K24 IR 12 83 51 30 05 List of Materials 3K24 51 30 06 Application of Sealants 3L3 51 30 07 SealingFaying Surfaces 3L3 51 30 08 Sealing Joggles 3L3 51 30 09 SealingHoles and Voids 3L5 51 30 10 Hol...

Page 786: ...minor dents and or materials used for filling the inside of surfaces is also prohibited on all movable tail surfaces NOTE Any time service is accomplished on the elevator control system a friction check must be made to insure that the system friction is within limits It mav be necessary to cut access holes to make skin repairs in some areas of the aircraft Refer to Figure 51 2 for typical access h...

Page 787: ...025 8 2024 0 9 2024 T3 10 2024 T3 040 051 064 015 4 2024 0 5 2024 T3 032 11 321 ST STL 6 2024 0 032 12 2024 T3 081 NOTE LEFTWING SHOWN RIGHTOPPOSITEAND NOTEDMATERIAL OUTLINED IN DOTS USED ON RIGHTWING ONLY CIRCLEDMATERIAL NUMBERS INDICATELEFTWING ONLY HEATTREATTO 2024 T4 AFTERFORMING Figure 51 1 Skin Thickness 51 00 01 Page 51 02 Revised July 28 1983 3K4 ...

Page 788: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL Figure 51 1 Skin Thickness cont 51 00 01 Page 51 03 Issued April 25 1983 3K5 ...

Page 789: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 3332 2 2 2 2 5 9 Figure 51 1 Skin Thickness cont 51 00 01 Page 51 04 Issued April 25 1983 3K6 ...

Page 790: ... ACCESSHOLE REINFORCEMENT PLATE 12 REQ 17317 ACCESSHOLE HOLE IN BOTTOM REINFORCEMENT WING SKIN PLATE DIAMETER 4 16 17315 ACCESSHOLE REINFORCEMENT PLATE B 1 17316 ACCESSHOLE COVER PLATE AN507 8 32R10 6 7 Figure 51 2 Typical Access Plates and Panels 51 00 01 Page 51 05 Issued April 25 1983 3K7 ...

Page 791: ...lass with the resin using a putty knife or stick Add catalyst according to kit instruction to the resin and mix thoroughly A hypodermic needle may be used to inject gel into small cavities not requiring fiberglass millings mixed with the gel 4 Work the mixture of resin fibers and catalyst into the damaged area using the sharp point of a putty knife or stick to press it into the bottom of the hole ...

Page 792: ...aybe wetout on cellophaneand appliedasa sandwich Enoughfiberglasscloth and mat reinforcementsshould be usedto at least replacethe amount of reinforcementsremovedin order to maintain the original strength If damage occured as a stresscrack an extra layer or two of cloth may be usedto strengthenarea 9 Lay patch over hole on inside of structure coverwith cellophane and squeegee from centerto edges to...

Page 793: ...ngfieldrepairsto itemsmadeofthermoplasticwhichareused throughout the airplane A list of material needed to perform these repairs is givenalong with suggested suppliersof thematerial Commonsafetyprecautionsshouldbeobservedwhenhandlingsomeofthe materials and tools used whilemaking these repairs CHART 5101 LIST OF MATERIALS THERMOPLASTIC REPAIRS DESCRIPTIONS SUPPLIERS Buffing and Rubbing Compounds Au...

Page 794: ... to 400 Solar Compounds Corp Linden N J 07036 Sears Roebuck Co or Most Hardware Stores Local Suppliers 1 1 Surface Preparation A Surface dirt and paint if applied must be removed from the item being repaired Household cleaners have proven most effective in removing surface dirt B Preliminary cleaning of the damaged area with perchlorethylene or VM P Naphtha will generally insure a good bond betwee...

Page 795: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 871 Figure 51 4 Deep Scratches Shallow Nicks and Small Holes 825 Figure 51 5 Mixing of Epoxy Patching Compound 51 12 00 Page 51 10 Issued April 25 1983 3K12 ...

Page 796: ...R AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 870 Figure 51 6 Welding Repair Method 827 STOP HOLES DOUBLERPLATE BONDED TO UNDERSIDEOF Figure 51 7 Repairing of Cracks 51 12 00 Page 51 11 Issued April 25 1983 3K13 ...

Page 797: ... holes greater than 1 4 inch in diameter D For larger damages an epoxy patching compound isrecommended This type material is a two part fast curing easy sanding commercially available compound E Adhesion can be increased by roughing the bonding surface with sandpaper and by utilizing as much surface area for the bond as possible F The patching compound is mixed in equal portions on a hard flat sur...

Page 798: ...th a pieceof similarmaterial C Whencuttingawaythe damagedarea undercut the perimeterand maintain a smoothedge The patch and or plug should also have a smooth edge to insure a good fit D Coat the patch with solventadhesive and firmly attach it over the damagedarea E Let the patch dry for approximately one hour before any additional work is performed F The hole etc isthen filledwiththe repair materi...

Page 799: ...831 830 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL PATCHING COMPOUND 828 DAMAGED AREA ABS ROD Figure 51 8 Various Repairs 51 12 00 Page 51 14 Issued April 25 1983 3K16 ...

Page 800: ...RCRAFT PA 31P 350 MAINTENANCE MANUAL STRESS LINES Figure 51 9 Repair of Stress Lines 829 832 PROFILEVIEW INDICATING DAMAGED AREA Figure 51 10 Repair of Impacted Damage 51 12 00 Page 51 15 Issued April 25 1983 3K17 ...

Page 801: ...ry acid and 2 electrochemical attack which requires a medium usually water The latter is the most common and is responsible for most forms of aircraft corrosion Since corrosion is a constant threat the only effective method to control it is a routine of regular inspection cleaning and surface refinishing FORMS OF CORROSION The following are the most common forms of corrosion 1 Surface Corrosion ap...

Page 802: ...e that no cleaning solution remains in any holes crevices or joints as it may lead to increased corrosion Also all exposed areas landing gear flap tracks control surface hinge parts etc should be lubricated after cleaning INSPECTION Corrosion should be inspected for at every inspection In trouble areas the inspection frequency should be increased In addition to routine inspections I Aircraft opera...

Page 803: ...normallyremovedbylighthandsandingor asmallamount of chemicaltreatment 2 ModerateCorrosion similarto lightcorrosionexcept there couldbesomeblisteringor evidenceof sealingand flaking removed by extensivehand sanding or mechanicalsanding 3 SevereCorrosion similar to moderate corrosionwith severeblistering exfoliation sealingand or flaking normally removedby extensivemechanicalsanding or grinding CAUT...

Page 804: ...admium has been depleted Promotes rusting of steel where pits occur in the coating Red rust generally shows on bolt heads hold down nuts and other aircraft hardware Its presence in these areas is generally not dangerous However it is indicative of a need formaintenanceand also of the possibility of corrosive attack in more critical areas Any corrosion on the surface of a highly stressed steel part...

Page 805: ...Engine frontal areas air inlet ducts and the leading edge of wings because they are constantly exposed to abrasion by dirt dust gravel and rain should bechecked frequently for the beginning of corrosion 8 Hinges piano hinges especially are extremely vulnerable to corrosion due to the wearing away of their protective coating and their being a natural trap for dirt salt and moisture 9 Control cables...

Page 806: ... and other foreign objects on the surfaces to be sealed by forced air or vacuum cleaning and brush 3 Clean all surfaces or voids to be sealed to remove all fingerprints oil or grease To clean wipe the affected areas with naphtha using a clean cotton cloth The cleaned surfaces should bewiped dry immediately and not allowed to air dry as to prevent redisposition of contaminants on the surface CAUTIO...

Page 807: ... 7502 or MIL S 8802 Class B sealants only 3 Half pint kits of MIL S 7502 or MIL S 8802 Class A sealants only 5 fluid ounces 4 Air powered sealant gun Semco No 250 6 with extra retainers for 2 1 2 ounce cartridges or equivalents 5 Assorted nozzles for sealant gun 6 Extension for sealant gun 7 Solvent dispensers polyethylene squirt bottles 8 Clean white cotton cloths 9 Stiff bristle brush not nylon ...

Page 808: ...1191 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1 FAYING SEAL 2 FILLET SEAL 3 OVERCOATW A TYPE SEALANT Figure 51 11 Fuselage Sealing Forward 51 30 05 Page 51 23 Issued April 25 1983 3L1 ...

Page 809: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1192 1 FAYING SEAL 2 FILLET SEAL 3 OVERCOATW A TYPE SEALANT n Figure 51 12 Fuselage Sealing Aft 51 30 05 Page 51 24 Issued April 25 1983 3L2 ...

Page 810: ...ach mating surface of the applicable parts Assemble and secure the components together before the sealant dries If the specific components require riveting the components should be riveted together while the sealant is still wet or if permanent fastening is not possible at the time temporary fasteners should be used inat least 50 of the holes to be riveted NOTE Sufficient sealantshould beapplied t...

Page 811: ...SPRIORTO ASSEMBLY B257 SKIN FAYING SEALBETWEEN SKINS AT SKIN LAP AREAS SKIN 315 A BEFOREASSEMBLY SECTION A A APPLICATION OF SEALANT SEALANT FILLETEDINTO SEAM AFTERASSEMBLY EXTRUDEDSEALANT AFTERASSEMBLY AFTERASSEMBLY Figure 51 13 Faving Surface Seal 316 INJECT UNTIL SEALANT EMERGES FROM THIS SIDE Figure 51 14 Joggle Seal 51 30 08 Page 51 26 Issued April 25 1983 3L4 ...

Page 812: ...ir noises and eliminate undesirable uncontrollable drafts Apply sealant to any holes and voids less than 125 inch wide and apply 3M 471 plastic tape on inside or outside surface of any holes and voids larger than 125 inch SEALING SEAMS AND JOINTS Refer to Figure 51 16 Fillet seals should be used along the edges of all structures riveted to the skin inthe pressurized area such as frames stringers d...

Page 813: ...LKHEAD ETC 14 LARGE HOLE GREATER THAN 125 15 NUT 16 WASHER WITH FAIRING PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL PRESSURE 6 7 SIDE 12 16 SEALINGHOLES PRESSURE SIDE SEALINGSTRINGERS Figure 51 15 Stringers Holes and Voids Seals APPLY SEALANT WITH FLOW GUN DETAIL A APPLICATION OF FILLET SEAL DETAIL C DIMENSIONS D 0 10 MIN W 0 20 MIN A B W EXCEPT A O WHEN B 0 20 OR MORE DETAIL B FORMING OF Figure ...

Page 814: ...t is being sealed it should be torqued before sealants set Tightening after sealant sets is not recommended SEALING AN STANDARD BULKHEAD FITTINGS Seal AN fittings passing through the pressure plain of the bulkhead by cleaning around the seal area and applying sealant to the inside surface around the hole and installing the fitting before the sealant sets 311 Figure 51 17 Bolts and Rivets Seals 51 ...

Page 815: ...ng halves around the wire harness on the pressure side of the bulkhead D Fill the groove inthe mounting flange of the fitting halves with sealant Refer to detail A of Figure 51 19 NOTE Use enough sealant to assure that sealant extrudes around the mounting flange after they are secured to the bulkhead E Secure the fitting to the bulkhead with fasteners F Fillet seal the extruded sealant around the ...

Page 816: ...APE 1 1 2 WIDTH PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL FILLET EXCESS SEALANT AFTER INSTALLATION OF FITTING HALVES DETAIL A DETAIL B DETAIL D Figure 51 19 Wire Harness Seals 51 30 14 Page 51 31 Issued April 25 1983 3L9 ...

Page 817: ...rs requiring a formed in place gasket shall receive an application of a releaseagent Sealant must beapplied to the prepared surface within two hours after the completion of surface preparation Surfaces not sealed within this time must be prepared again CA UTION Do not use Polyvinyl alcohol as a release agent near acrylic Plexiglas windows It will craze acrylic plastics SEALING FORMED IN PLACE GASK...

Page 818: ...T CUTTING TOOL NOTE THE ABOVE TOOLS SHOULD BE MADE OF HARDWOOD TO REDUCE THE POSSIBILITY OF STRUCTURAL DAMAGE 0 50 A 0 04 APPROX SEALANT FAIRING TOOL SMALL SEALANT FAIRING TOOL WITH SPOON TYPE HEAD LARGE SEALANT FAIRING TOOL NOTE THESE TOOLS MAY BE MADE OF 1 4 INCH DIAMETER BRONZE OR STEEL WELDING ROD AND MAY BE PLATED TO IMPROVE SMOOTHNESS Figure 51 20 Fabricated Tools 51 30 16 Page 51 33 Issued ...

Page 819: ...persmade of hardwood or plexiglas It isnecessaryto removeonlythe majorportion of the filletsor beads After rework the area should be cleaned resealedand tested for leaks EQUIPMENT CLEAN UP This must be accomplished within three hours after exposure to room temperature using naptha Methylethylketoneor Toluol as a cleaning material END 51 30 18 Page 51 34 Issued April 25 1983 3L12 ...

Page 820: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL GRIDS 3L13THRU 3L24 INTENTIONALLYLEFT BLANK 3L13 ...

Page 821: ...PIPER MOJAVE MAINTENANCE MANUAL CARD 4 OF5 PA 31P 350 MOJAVE PIPER AIRCRAFT CORPORATION PARTNUMBER 761781 4A1 ...

Page 822: ... then broken down into Sub System Sections These sections are identified by the second element of the standardized numbering system The number 40 of the basic number series 32 40 00 is for the Wheels and Brakes portion of the landing gear The individual units within a Sub System Section may be identified by a third element of the standardized numbering system such as 32 40 01 This number could be ...

Page 823: ...e list of Charts is for all fiche in this set following list of Illustrations 4 A complete list of paragraph titles and appropriate Grid location numbers is given at the beginning of each Chapter relating to the information within that Chapter 5 Identification of Revised Material Revised text and illustrations arc indicated by a black vertical line along the left hand margin of the frame opposite ...

Page 824: ... 1983 July 28 1983 December 14 1983 April 30 1986 July 23 1986 September 25 1986 June 15 1988 March 13 1990 October 7 1994 INTERIM REVISION Revisions appear in chapter 5 of card 1 and chapter 71 of card 4 Please dispose of your current cards 2 and 4 and replace with the revised one DO NOT DISPOSE OF CARDS 2 3 5 Consult the Customer Service Information Aerofiche for current revision dates for this ...

Page 825: ...o 419 255 4068 Autopilot Avionics Edo Corporation Avionics Division P O Box 610 Municipal Airport Mineral Wells Texas 76067 817 325 2517 Bendix Avionics Division 2100 N W 62nd Street Fort Lauderdale Florida 33310 305 776 4100 Collins General Aviation Division Rockwell International Cedar Rapids Iowa 52406 319 395 3625 King Radio Corporation 400 N Rogers Road P O Box 106 Olathe Kansas 66061 913 782...

Page 826: ...0 Narco Avionics Inc 270 Commerce Drive Fort Washington Penna 19034 215 643 2900 Avco Lycoming Avco Lycoming Division Williamsport Penna 17701 Environmental Systems Heater and Air Conditioner Janitrol Aero Division 4200 Surface Road Columbus Ohio 43228 614 276 3561 Sanden International U S A Inc 10710 Sanden Drive Dallas Texas 75238 Fuel Pumps Lear Siegler Incorporated 17602 Broadway Avenue Maple ...

Page 827: ...hio 44035 216 323 4676 Propellers Hartzell Propeller Incorporated 1025 Roosevelt Avenue Piqua Ohio 45356 513 773 7411 Propeller Synchrophaser Tools Air Conditioning Turbocharger Hartzell Propeller Fan Company 910 South Downing Street Piqua Ohio 45356 513 773 7411 Kent Moore Corporation Service Tool Division 1501South Jackson Street Jackson Michigan 49203 517 784 8561 Airesearch Industrial Division...

Page 828: ... PUBLICATIONS PA 31P 350 Parts Catalog 761 776 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 Continuous Inspection 761 786 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 4A8 Introduction Page 7 Issued April 25 1983 ...

Page 829: ...NG TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACTICES AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS NAVIGATIONAND PITOT STATIC OXYGEN SYSTEM AEROFICHE GRID NO IB1 1B4 1D11 1El IE4 1E9 IE13 IE16 1 E20 IG1 1HI1 2B1 2B4 2B12 2C17 2D1 2H1 ...

Page 830: ...ORS 4B 53 FUSELAGE 4C 54 NACELLES 4C4 55 STABILIZERS 4C7 56 WINDOWS 4D3 57 WINGS 4D16 61 PROPELLER 4E10 70 STANDARD PRACTICE ENGINES 4F5 71 POWER PLANT 4F8 73 ENGINE FUEL AND CONTROL 4G7 74 IGNITION 4G17 76 ENGINE CONTROLS 4H 77 ENGINE INDICATING 411 79 OIL SYSTEM 4111 80 STARTING 4121 81 TURBINES 4J1 91 CHARTSAND WIRING DIAGRAMS 5B1 95 SPECIAL PURPOSE EQUIPMENT 5E1 Introduction 4A10 Page 9 Revise...

Page 831: ... Cherrylock Rivet Removal G6 20 4 HoseLine Markings 1 G8 20 5 Flareless Tube Fittings 1G9 20 6 Spray Patterns 1G17 20 7 Improper Spray Technique 1G19 20 8 Spray Technique 1G20 20 9 Spraying Corners 1G20 21 1 Pressurization System Schematic Garrett 1H2 21 2 Cabin Pressure Control System Schematic Garrett 1H3 21 3 Safety and Outflow Valves 112 21 4 Cabin Air Pressure Outflow Valve Controller Schemat...

Page 832: ...nspection Points Air Conditioning System Typical 1L15 23 1 Emergency Locator Transmitter Schematic Narco 2B9 23 2 Portable Folding Antenna Narco 2B9 23 3 ELT Using Fixed Aircraft Antenna Narco 2B10 23 4 Avionics Master and Emergency Switch Circuit 2B10 24 1 Kelvin Low Resistance Bridge 2B21 24 2 Electrical Power Distribution System Typical 2B22 24 3 Lamar Model B 00382 1 Typical System Application...

Page 833: ...27 27 Flap Transmission Exploded View 2G2 27 28 Flap Transmission Measurements 2G5 27 29 Checking for Wormgear Wear 2G7 27 30 Flap Rigging Adjustments 2G1 28 1 Fuel System Schematic 2H8 28 2 Fuel Cell Installation Inboard 2H11 28 3 Fuel Cell Installation Outboard 2H 12 28 4 Fuel Cell Installation Nacelle 2H13 28 5 Fuel Valve Drain Plate 2H14 28 6 Fuel Cell Tie Detail 2H17 28 7 Installation of Fuel...

Page 834: ...fed Area and Patch 3B22 30 10 Applying and Stitching Fabric 3B22 30 11 Placing and Stitching Gum 3B24 30 12 Removing Trapped Air 3B24 30 13 Masking Repair 3B24 30 14 Applying Neoprene Putty 3B24 30 15 Windshield Wiper 3C8 30 16 Typical Use of Dial Indicator 3C12 30 17 Centering of Brushes on Slip Rings 3C12 30 18 Modular Brush Assembly Wear Check 3C13 30 19 Angle of Contact Brushes to Slip Rings 3...

Page 835: ...2 24 Adjusting Main Gear Down Light Switch 3F23 32 25 Gear Warning Switches Installation 3F24 33 1 Landing Taxi Light Installation 3G21 33 2 Logo Light Assembly Adjustments 3H2 34 1 Instrument Air System Installation Typical 3H9 34 2 Pitot Static Installation 3H10 35 1 Oxygen System Installation 314 35 2 Oxygen System Installation for FAR 135 Certification 315 35 3 Oxygen Tubing Installations 3112...

Page 836: ...Forward Baggage Door Assembly 4B19 52 6 Nacelle Locker Door 4B21 52 7 Door Ajar Switch 4B24 54 1 Nacelle Assembly 4C6 55 1 Empennage Installation 4C11 55 2 Elevator Balancing 4C18 55 3 Friction Measurement 4C20 55 3 Rudder Balancing 4C24 55 4 Rudder Balance WeightLocation 4C24 56 1 Windshield Installation 4D8 56 2 Fabricated Sealant Tools 4D11 56 3 Storm Window Installation 4D13 57 1 Wing Installa...

Page 837: ...0 Checking Harness Lead Continuity 4H7 74 11 Checking Harness Lead Insulation Resistance 4H7 74 12 Modified Pliers 4H7 74 13 Removing Spring From Lead Assembly 4H7 74 14 Assembly Tool 4H9 74 15 Using Assembly Tool 4H9 74 16 Ferrule Positioned Under Braid 4H10 74 17 Ferrule Seating Tool 4H10 74 18 Position of 11 8627Kit and Contact Spring at Startof Installation 4H11 74 19 Position of 11 8627Kit an...

Page 838: ...5E10 95 9 Fabricated Tool Checking Main Gear Toe In Adjustment 5E11 95 10 Tire Balancer 5E12 95 11 Fabricated Tool Checking Nose Wheel Alignment 5E 3 95 12 Suggested Design for Seal Plate Plugs and Caps for Combustion Leakage Test 5E14 95 13 Charging Stand 5E14 95 14 Fabricated Pressure Test Adapters 5E 5 95 15 Cabin Pressure Test Unit Typical 5E15 95 16 Test Gauge Manifold Set 5E16 95 17 Torque W...

Page 839: ...lectrolyte Temperature Corrections 2C8 2406 Specific Gravity Temperature Correction 2C9 2407 Recommended Discharge Rate 2C9 2408 Electrolyte Freezing Points 2C10 2409 Capacity Ratings at Discharge Rate 2C12 2410 Electrolyte Freezing Points 2C12 2411 Circuit Load Chart 2C13 2701 Troubleshooting Surface Controls 2D6 2702 Control Cable Rigging Tension vs Temperature 2D19 2801 Troubleshooting Fuel Sys...

Page 840: ...318 3901 Cabin Instruments Display 3J12 5101 List of Materials Thermoplastic Repairs 3K10 5102 Types of Metal Corrosion 3K21 5501 Elevator Balance Specifications 4C17 5502 Rudder Balance Specifications 4C23 5701 Aileron Balance Specifications 4E5 6101 Propeller Specifications 4E15 6102 Troubleshooting Actuator Chart Engine Synchrophaser 4E22 7101 Troubleshooting Engine 4F11 7301 Troubleshooting Fu...

Page 841: ... of Consumable Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Electrical Wiring Coding Electrical Symbols GRID NO 5B4 5B16 1 5B19 5B20 5B21 5B22 5C2 5C3 5C4 4A21 Introduction Page 19 Issued April 25 1983 ...

Page 842: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4A22 ...

Page 843: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4A23 ...

Page 844: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4A24 ...

Page 845: ...CHAPTER DOORS 4B1 ...

Page 846: ...oor Step Mechanism 4B12 52 15 01 Removal of Cabin Entrance Door Steps 4B12 52 15 02 Installation of Cabin Entrance Door Steps 4B12 52 16 00 Cabin Door Snubber 4B13 1R 12 83 52 16 01 Filling Snubber Assembly 4B13 A 7 83 52 16 02 Removal of Door Snubber 4B13 A 7 83 52 16 03 Installation of Door Snubber 4B13 A 7 83 52 20 00 EMERGENCY EXIT 4B15 52 20 01 Inspection and Servicing of Emergency Exit Windo...

Page 847: ... 52 30 19 Installation of Nacelle Locker Door 4B20 52 30 20 Nacelle Locker Door Latch Assembly 4B22 52 30 21 Removal of Nacelle Locker Door Latch Assembly 4B22 52 30 22 Installation of Nacelle locker Door Latch Assembly 4B22 52 40 00 SERVICE 4B22 52 41 00 Nose Cone 4B22 52 41 01 Removal of Nose Cone 4B22 52 41 02 Installation of Nose Cone 4B22 52 70 01 DOOR WARNING 4B22 52 71 00 Door Ajar Warning ...

Page 848: ... Operate the door latch mechanism and observe for proper functioning of all locking lugs and any sign of binding or looseness 3 Refer to Cabin Entrance Door Latch Mechanism for repair and service instructions of the latch mechanism 4 Refer to Chapter 12 for instructions on the proper lubrication of the door and related mechanisms REMOVAL OF CABIN ENTRANCE DOOR 1 Place a padded support under the do...

Page 849: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL Figure 52 1 Cabin Entrance Door 52 11 02 4B5 Page 52 02 Issued April 25 1983 ...

Page 850: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL SKETCH A Figure 52 1 Cabin Entrance Door cont 4B6 52 11 02 Page 52 03 Issued April 25 1983 ...

Page 851: ...RS DOOR CABLE SPRING AND BOOT ON MACHINE SCREW AS SHOWN APPLY LOOUIC PRIMER TO SCREWAND BRACKET APPLY LOCTITE GRADE E TO THREAD AND TIGHTEN SCREW WHILE HOLDING DOOR CABLE SPRING IN A VERTICALPOSITION 2 THE DOOR SUPPORT CABLES MUST BE ADJUSTED TO EQUAL TENSION 44 45 SKETCH C Figure 52 1 Cabin Entrance Door cont 4B7 52 11 02 Page 52 04 Issued July 28 1983 ...

Page 852: ...MOVAL OF LATCHING MECHANISM 1 Upper and lower latching mechanism A Remove the interior trim panels from the door B Remove the bellcrank coverplate C Remove the bolt connecting the vertical push rod to the bellcrank D Remove the bolts connecting the right or left push rod or both if necessary to remove complete assembly E If so desired the bellcrank or push rod and lugs can now be removed 2 Center ...

Page 853: ...and be sure to install the spacers between the vertical and horizontal pushrods as shown in Figure 52 1 Secure with bolts and locknuts E Install the coverplate and inside handle and adjust lugs ADJUSTMENT OF LATCHING MECHANISM 1 Remove the inside trim panels and access plates 2 With the door opened position the handle in the open position 3 Check all seven locking lugs to ascertain that all are ev...

Page 854: ...ertain that the O ring is installed in the bushing around the plunger 2 Place the assembly into the access opening and secure it in place with two screws and nuts 3 Install the lock rod into the slot in the bushing and through the hole in the plunger and secure in place with washer and cotter pin 4 Install the cover plate being sure the lock rod extends out through the bushing in the cover 5 Secur...

Page 855: ...nd seal Allow to dry and then apply a second coat and allow to dry CA UTION Take care to avoid getting cement on areas not to be cemented 3 Activate the cement by wiping the cemented surfaces lightly with Toluol Do approximately two feet at a time and immediately position and press the seal in place Start at the air inlet on the inflatable seal CAUTION Care must be taken to avoid stretching the in...

Page 856: ... the steps INSTALLATION OF CABIN ENTRANCE DOOR STEPS 1 Position the steps to the door and install the hinge pins 2 Position the step support tubes along the sides of the steps being certain to place the tube with the door support cable guide on the forward side of the door Be sure that the step stops on the step support tubes are pointing towards the center of the entrance door NOTE Ascertain that...

Page 857: ...n in and out to help remove any trapped air within the cylinder Collapse the piston into the cylinder and remove the plug add more fluid as required then reinsert the plug in the cylinder REMOVAL OF DOOR SNUBBER 1 With the door extended remove the screws which secure the boot over the lower end of the snubber 2 Remove the bolt and locknut which secures the lower end of the snubber to the cabin doo...

Page 858: ... SEAL SURFACES INDICATEDWITH PR1221 A2 2 APPLY T 18 TEFLON TAPE AROUND PERIMETER OF MATING SURFACE OF OPENING AND WINDOW RE MOVE EXCESS ADHESIVE FROM WINDOW ASSEMBLY C63 12 14 8 17 VIEW A A VIEW B B I Figure 52 3 Emergency Exit Window 4B14 52 16 03 Page 52 11 Revised July 28 1983 ...

Page 859: ...dow should be removed from the fuselage to ensure its operation Should the window stick or should the window be hard to remove perform the following 1 Inspect the rubber seal on the window frame for serviceability 2 Spray both the window frame and fuselage frame with silicone 3 Inspect the fuselage frame for excess skinlap sealant and remove any that may be present NOTE Excess sealant may cause th...

Page 860: ...ANEL DOOR 5 LATCH PIN AFT 6 CONTROL BELLCRANKSFOR AFT LATCHINGMECHANISM 7 PUSH ROD MAIN CONTROL FROM HANDLE BELLCRANKTO AFT BELLCRANK 8 BEARING SUPPORT OUTER 9 PUSH RODS LOWER LATCH PINS 10 LOWER LATCH PINS 11 HANDLEMECHANISM 12 HANDLE BELLCRANK 13 NYLONBEARING WASHER CARGO DOOR LATCH MECHANISM Figure 52 4 Cargo Door Installation 4B16 52 30 03 Page 52 13 Added December 14 1983 ...

Page 861: ...ed may now be removed INSTALLATION OF CARGO DOOR LATCH ASSEMBLY Refer to Figure 52 4 1 Install the upper door latch assembly push rods and secure with the appropriate hardware 2 Install the remaining push rods with locking pins attached 3 Install the bellcrank assemblies using new teflon washers where required 4 Secure with the push rod assemblies to the bellcrank assemblies using the appropriate ...

Page 862: ...cket assemblies and insert the hinge pins 2 Replace the washers and insert the cotter pins into the ends of the hinge pins 3 Reinstall baggage door holder link FORWARD BAGGAGE COMPARTMENT DOOR LATCH ASSEMBLY REMOVAL OF FORWARD BAGGAGE COMPARTMENT DOOR LATCH ASSEMBLY 1 With the door open remove the screws holding the inside cover and remove the cover from the door assembly 2 Remove the cotter pin a...

Page 863: ...OTTERPIN 3 DOOR ASSEMBLY 4 HINGE 5 BAGGAGE DOOR 6 DOOR LOCK 7 DOOR LOCK GUIDE 8 HANDLEASSEMBLY 9 DOOR SEAL 10 TUBE ASSEMBLY 11 INNER DOOR COVER 12 ARM ASSEMBLY 13 LOCK PLATE I Figure 52 5 Forward Baggage Door Assembly 4B19 52 30 14 Page 52 16 Revised December 14 1983 ...

Page 864: ...the tube assembly NACELLE LOCKER DOOR The nacelle locker is an integral part of the wing nacelle extending from a bulkhead at fuselage station 147 75 aft to a tapered fiberglass tip The lockable nacelle locker door provides security and protection from the elements for any cargo placed within the compartment Hinges are attached to the forward edge of the door assembly and a lock and latch assembly...

Page 865: ... 5 NACELLE OUTER SKIN 6 REINFORCEMENT 7 SCREW AND CAPNUT 8 NACELLE INNER SKIN 9 STRIKER 10 SEAL 11 TIP ASSEMBLY 12 SEALER EC750 13 CHANNEL 14 PLATE 15 COIL SPRING 16 BRACKET 17 HANDLE 18 DOOR LATCH 7 VIEW B B NACELLELOCKERDOOR LATCHASSEMBLY Figure 52 6 Nacelle Locker Door I 4B21 52 30 19 Page 52 18 Revised December 14 1983 ...

Page 866: ... a thin bead of PRC 5000 white sealant around the mating surface of the door latch cover place it in position on the locker door inner surface and secure with fourteen 14 washers and machine screws SERVICE NOSE CONE The nose cone provides access to the battery compartment and houses the radome when installed The radome is constructed principally of fiberglass and has an aluminum rear bulkhead Copp...

Page 867: ...r trim panel from around the door frame 2 Disconnect the electrical leads from the switch NOTE Make note of the place from which each wire was removed to facilitate reinstallation 3 Loosen the retainer nut and unscrew the switch from the receptacle INSTALLATION OF DOOR AJAR WARNING SWITCHES 1 Install new switch into latch receptacle located behind the door frame 2 With the door closed and locked a...

Page 868: ...n the retainer nut on the switch If several switches are being adjusted follow the same procedures for each switch 5 Install the interior trim panel around the door frame PERIODIC CHECK OF DOOR AJAR WARNING SWITCHES Periodically but not less than 100 flying hour intervals check the mechanical action of the cabin door ajar switches 1 Insert a long blunt object small enough to fit into the door lock...

Page 869: ...CHAPTER FUSELAGE 4C1 ...

Page 870: ...P 350 MAINTENANCEMANUAL CHAPTER 53 FUSELAGE TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT SUBJECT GRID NO EFFECTIVITY 4C3 4C3 53 00 00 53 00 01 GENERAL Description 53 Cont Effec Page 1 Revised December 14 1983 4C2 ...

Page 871: ...is removable upon pulling the release located above the window This window is sealed upon installation and should the window be removed it must be reinstalled with care in order to retain the pressure seal The cabin entrance door is located on the left side of the fuselage just aft of the wind This is a one piece door which swings down to open and provides cabin entrance steps All wiring plumbing ...

Page 872: ...CHAPTER NACELLES 4C4 ...

Page 873: ...AFT PA 31P 350 MAINTENANCEMANUAL CHAPTER 54 NACELLES TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT 54 00 00 GRID SUBJECT NO EFFECTIVITY GENERAL 4C6 IR 7 83 4C5 54 Cont Effec Page 1 Revised December 14 1983 ...

Page 874: ...tity dipstick for servicing The lower cowl priovides mounting for the cowl flap door and intercooler air inlet The nacelle fuel cell is located in a compartment directly aft the engine firewall The baggage locker is located aft of the nacelle fuel cell compartment The locker has a capacity of 9 cubic feet which allow 90 pounds of baggage to be carried The main nacelle structure excluding the engin...

Page 875: ...CHAPTER STABILIZERS 4C7 ...

Page 876: ...vator 4C16 55 20 03 Elevator Balancing Procedure 4C16 55 20 04 Elevator Control System Friction Measurement 4C17 R 7 83 55 25 00 Elevator Trim Tab 4C18 55 25 01 Remowal of Elevator Trim Tab 4C18 55 25 02 Installation of Elevator Trim Tab 4C19 55 25 03 Elevator Trim Tab Free Play 4C19 55 30 00 VERTICAL STABILIZER 4C19 55 30 01 Removal of Vertical Stabilizer 4C19 55 30 02 Installation of Vertical St...

Page 877: ... be accomplished in a draft free area and in a manner which allows unrestricted movement of the control surface BALANCLNG DEFINITIONS The following is a list of balancing definitions as used in this maintenance manual 1 Master Test Weight A fabricated tool temporarily attached to the control surface to determine when the surface is at its lower static balance limits 2 Balance Weight Weight attache...

Page 878: ...ion and align the front and rear spar mounting holes If installing a right stabilizer guide the elevator trim cables and sender wires into the fuselage 4 Position the elevator torque tube hinge bracket and temporarily install the rear spar mounting bolts 5 Install the front spar mounting bolts washers and nuts Do not torque at this time 6 Check to determine if the gap exists between the web area o...

Page 879: ...EQUIRED BETWEEN DOUBLER AND FRONT FACEOF REAR SPAR IT IS NOT PERMISSIBLE TO SHIM MORE THAN 091 THICKNESS OR TO USE ANY COMBINATION OF SHIMS REFERTO PARTS CATALOG FOR PROPER SHIM PART NUMBER 5 2 REQ 55 132 1 INSTALLWASHERSUNDERNUT WHENSHIM IS ADDED OMIT 1 WASHER 2 REFERTO CHAPTER91 FOR RECOMMENDED NUT TORQUES VIEWA A SKETCH A Figure 55 1 Empennage Installation 55 10 02 Page 55 03 Revised July 28 19...

Page 880: ...O CHAPTER 91 FOR RECOM MENDEDNUTTORQUES SHIM AS REQUIREDBETWEEN ELEVA TOR ASSEMBLY AND TORQUE TUBE ASSEMBLY MAXIMUM OF 3 PER TORQUETUBEASSEMBLY SIDE REFER TOPARTSCATALOG FOR PROPERSHIM PART NUMBER SKETCH B ELEVATOR TORQUE TUBE BRACKET ASSEMBLY ASSEMBLY BOLTAN173N 13 C C ...

Page 881: ...ASSY C G BOLTAN173 10 WASHER AN960 10 UNDER HEAD 2 REQ under NUT MS17825 3 ELEVATOR COTTERPINMS2466 5 1 7 2 BOLTAN174 10 WASHERAN960 41 6 2 REQ UNDER NUT 1 REQ UNDER HEAD NUT MS17825 4 COTTER PINMS24665 1 7 2 SY FWD INBD BOLT AN174 11 WASHER AN960 4 1 6 NUT MS17825 4 COTTER PIN MS24665 1 VIEW C C Figure 55 1 Empennage Installation cont 55 10 02 Page 55 05 Revised July 28 1983 4C13 ...

Page 882: ...IN MS24665 132 2 REQ SKETCH E RUDDER I RUDDERTRIM TAB SCREWASSY RUDDERASSY BOLTANI 73 7 NUT MS17825 3 COTTERPIN MS24665 13 2 BOLTAN3 5A WASHER AN960 BOLTAN173 10 WASHER AN960 10 NUT MS7825 WASHER AN960 IOL 4 REQ COTTERPIN MS24665 132 SKETCH G RUDDER TRIM SCREW INSTALLATION 136 RUDDER TAB ASSY RUDDERASSY SKETCH H RUDDER TRIM TAB INSTALLATION 138 NOTE 1 REFERTO CHAPTER91 FOR RECOMMENDED NUTTORQUES B...

Page 883: ...AR SPAR ASSY BULKHEADASSY SHIM AS REQUIRED BETWEEN SPAR AND BULKHEAD MAXI MUM OF 2 REFER TO PARTS CATALOG FOR PROPER SHIM PARTNUMBER FOR RECOM MENDED NUT TORQUES BOLT AN4 6A WASHER AN960 416 NUT MS20365 428C SKETCH M RUDDER HORN INSTALLATION Figure 55 1 Empennage Installation cont 4C15 55 10 02 Page 55 07 Revised July 28 1983 ...

Page 884: ... light wires and place the tail cone assembly in position Start all screws with washers and then tighten ELEVATOR BALANCING PROCEDURE Refer to Figure 55 2 1 Remove the complete both halves elevator assembly from the airplane The complete assembly including trim tab and actuating rod must be assembled and placed on a balancing jig 2 Fabricate a master test weight in accordance with specifications i...

Page 885: ...L SYSTEM FRICTION MEASUREMENT The complete control system including Autopilot if installed must be checked to determine the total friction The system must be rigged to its proper travels and cable tensions prior to determining the total friction The total friction in the elevator control system must not be in excess of ten pounds with 45 1pounds tension on elevator control spring with elevator in ...

Page 886: ...wering processes until average forces are obtained 6 The Total Friction is obtained by subtracting the two forces NOTES 1 Do not exceed 60pound force for any measurement 2 The elevator shall be rotated with a steady movement and the force reading taken when the elevator is passing through the neutral position Do not stop rotation when taking the reading ELEVATOR TRIM TAB REMOVAL OF ELEVATOR TRIM T...

Page 887: ...onnect the antenna wire from the top of the stabilizer 4 Remove the access plates located on each side of the fuselage under the horizontal stabilizer and the panel located on top of the fuselage aft of the vertical fin The tail cone may be removed if desired 5 Remove the access panel to the aft inside section of the fuselage 6 Remove therudder 7 Locate the rudder trim cable turnbuckles in the aft...

Page 888: ...I I PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL TRAILING EDGE UTBOA OUTBOARD I I SPRINGSCALE Figure 55 3 Friction Measurement 4C20 55 30 01 Page 55 12 Issued April 25 1983 ...

Page 889: ...nd bulkhead Use shim 032 P N 43998 00 as required Maximum of two 6 With the correct shims determined remove the forward and rear spar attaching bolts Move stabilizer up and aft to obtain enough room to place shim s between rear spar and bulkhead 7 Slide shim s into place and install rear mounting bolts washer and nuts 8 If removed position the lower rudder hinge bracket and install mounting bolts ...

Page 890: ...nels RUDDER BALANCING PROCEDURE Refer to Figure 55 4 1 Remove the rudder from the airplane 2 Place the rudder horizontally on the balance jig 3 Fabricate a master test weight per specifications given in Chart 5502 and hang it in the existing tool hole in the rudder tip support channel Ascertain that the tool hole is located to provide the proper master test weight arm as shown in Figure 55 4 and s...

Page 891: ...hts added to the master test weight to balance the rudder exceeds the maximum allowable per Chart 5502 the rudder balance exceeds the static limits and trim weights must be added to the rudder to produce a balanced condition Refer to Chart 5502 for the trim weight part number and the maximum amount allowed for the particular rudder assembly being balanced NOTE During this procedure the master test...

Page 892: ... AIRCRAFT PA 31P 350 MAINTENANCE MANUAL TAPE TRIM TAB LEVEL WITH RUDDER MASTER TEST WEIGHT ARM Figure 55 4 Rudder Balancing TRIMWEIGHT P N 53892 2 MAXIMUM OF 2 Figure 55 5 Rudder Balance Weight Location 4C24 55 40 03 Page 55 16 Issued April 25 1983 ...

Page 893: ...ect the control rod at the tab 2 Remove the hingebolts securing the tab INSTALLATION OF RUDDER TRIM TAB Refer to Figure 55 1 1 Place the trim tab in position and secure with bolts and bushings 2 Attach the tab control rod 3 Refer to Chapter 27 for adjustment and rigging END 4D1 57 41 00 Page 57 01 Issued April 25 1983 ...

Page 894: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4D2 ...

Page 895: ...CHAPTER WINDOWS 4D3 ...

Page 896: ...Window Sealant 4D6 56 10 00 FLIGHT COMPARTMENT 4D7 56 11 00 Windshield 4D7 56 11 01 Removal of Windshield Standard and Heated 4D7 56 11 02 Installation of Windshield Standard and Heated 4D7 56 11 03 Heated Windshield Functional Check 4D12 56 12 00 Pilot s Storm Window 4D12 56 12 01 Removal of Pilot s Storm Window 4D12 56 12 02 Installation of Pilot s Storm Window 4D14 56 20 00 CABIN 4D14 56 21 00 ...

Page 897: ...n the parting mediumarea is considerednormal A low degreeof adhesionisintendedinthisarea A delaminationareawhichis characterizedby an irregularorjagged boundaryindicatesthe separationof the vinyl and glass is not uniform Such a conditioncan cause the vinyl to pull chips from the inner glass surfacewhichcouldlead to failureof the glass ply If this situationoccurs it is recommendedthat a periodic in...

Page 898: ... that on the windshield D Applyfreshsealantupto theoriginalsealantlevel E Removemaskingafterthesealantstartsto cure F Allowthe sealantto curecompletely 2 It is verydifficultto effecta good repairon siliconesealants Therefore repairs shouldbe madewith extremecare NOTE All siliconebumpersshould beof the two componenttype Single component silicones that depend upon moisturefor their cure cannotbe cur...

Page 899: ...ct electrical leads 5 Remove the existing sealant from around the locknuts on the windshield 6 Remove the machine screws from around the collar moldings This will require the assistance of another person NOTE The machine screws which hold the windshield in position are installed in a particular order of sizes and when removed a note of their location should be made to insure the proper installatio...

Page 900: ...HT 5 48966 11 13 REQ LEFT 13 REQ RIGHT 6 48966 13 10 REQ LEFT 10 REQ RIGHT 16 COLLAR 17 WINDSHIELD CHANNEL 18 WINDOW 19 SKIN 20 CANTED BULKHEAD C862 NOTE TORQUE ALL SCREWS 15 20INCH POUNDS 15 SECTION B B PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL SECTION Figure 56 1 Windshield Installation 4D8 56 11 02 Page 56 04 Revised July 28 1983 ...

Page 901: ...PER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL WH4D VIEW C C NAL WIRE WH4E WINDSHIELD VIEWD D HEATED PILOT SWINDSHIELD WIRETERMINAL Figure 56 1 Windshield Installation cont 4D9 56 11 02 Page 56 05 Issued April 25 1983 ...

Page 902: ... defeated if it liftsfrom the structure after it has been applied 2 Mask the windshield optical surface and fuselage skin around the windshield collar area to minimize cleanup 3 Apply one inch wide 1 16inch thick vinyl foam tape Norton Co Tape No V542 Piper No 924 441 to the outer surface of the windshield even with the edge and covering the holes 4 Position the windshield into the eyebrow bulkhea...

Page 903: ...DGE BEVELED SURFACE SHARP EDGE LARGE SEALANT CUTTING TOOL BEVELED SURFACE SHARP EDGE SEALANT REMOVAL TOOL SMALL SEALANT CUTTING TOOL SEALANT FAIRING TOOL SMALL SEALANT FAIRING TOOL WITH SPOON TYPE HEAD LARGE SEALANT FAIRING TOOL NOTE THESE TOOLS MAY BE MADE OF 1 4 INCH DIAMETER BRONZE OR STEEL WELDING ROD AND MAY BE PLATED TO IMPROVE SMOOTHNESS Figure 56 2 Fabricated Sealant Tools 4D11 56 11 02 Pa...

Page 904: ... windshield becomes too hot to hold your hand against it This indicates that the temperature sensing element is operating properly and has passed through its thermostatic ON OFF cycle CAUTION Exercise caution during ground operation to prevent overheat andpossible damage to the windshield 5 When check is completed set the Windshield Heat to the OFF position and remove the test light PILOT S STORM ...

Page 905: ...IL S7502B RE MOVE EXCESSOR VISIBLE SEAL NT 3 SPLICE IN SEAL MUST BE AT TRAILING EDGE OF W NDCW CUT SEAL 75 IN LENGTH AT SPLICE AND CEMENTENDS TOGETHERWITH 3M EC 847 CEMENT 4 CEMENT SEAL TO RETAINERWITH 3M EC 847 CEMENT 8 6 NOTE 4 A 1 STORM WINDOW ASSEMBLY 2 SIDE WINDOW 3 SCREWS 6 EACH 4 SEAL 5 INNER RING 6 RETAINER 7 TRIM RING 8 SPACER 9 INNER WINDOW 2 VIEW A A Figure 56 3 Storm Window Installatio...

Page 906: ...ound its periphery The window pane is then mounted to the fuselage skin with machine screws washers and self locking nuts REMOVAL OF CABIN SIDE WINDOWS 1 Remove the trim moulding and inner window assembly from around the inside of the window 2 Remove the sealant from around the locknuts securing the window to the fuselage 3 Remove the locknuts and washers from the screws and remove the screws 4 Re...

Page 907: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4D15 ...

Page 908: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL CHAPTER WINGS 4D16 ...

Page 909: ...NG ATTACHFITTINGS 4D18 57 41 00 Removal of Wing 4D18 57 41 01 Installation of Wing 4D24 57 41 02 Hi Lok Pin Installation and Removal 4E2 57 50 00 FLIGHT SURFACES 4E4 57 51 00 Aileron 4E4 57 51 00 Removal of Aileron 4E4 57 51 02 Installation of Aileron 4E4 57 51 03 Aileron Balancing Procedure 4E4 57 52 00 Aileron Trim Tab 4E8 57 52 01 Removal of Aileron Trim Tab 4E8 57 52 02 Installation of Aileron...

Page 910: ...curing the ground wire to the wing structure 3 Remove the wing tip completely REPAIR OF WING TIP The wing tip may be repaired in accordance with fiberglass repair procedures in the Structural Repairs portion of Chapter 5 1 INSTALLATION OF WING TIP 1 Attach the ground wire terminal to the wing structure and connect the positive electrical leads together 2 Position the wing tip on the wing and start...

Page 911: ...0 IN LBS PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL BOLTAN4 16A WASHERAN960 416 NUTMS20365 428C TORQUE50 TO 70 IN LBS LONGITUDINAL LONGITUDINAL BEAM BOLTAN3 6A BEAM WASHER AN960 10 NUT MS20365 1032C SKETCH A SKETCH B Figure 57 1 Wing Installation 4D19 57 41 00 Page 57 02 Issued April 25 1983 ...

Page 912: ... MS20365 10 3 2 1 20 REQUIRED 1 32 INCH MAXIMUM GAP BETWEEN SPAR CAPS BOLTAN4 1OA NUT MS20365 428C 1 4 REQUIRED BOLT AN3 1OA WASHER ANS60 10L NUT MS20365 1032C 1 12 REQUIREDI I CALLOUTS FOR HI LOK PINS AND COLLARS 1 HL 18 5 12 HL 70 5 2 HL 18 6 10 HL 70 6 3 HL 18 6 12 HC 70 6 BOLT NAS464 P6LA20 WASHER AN960 616 NUT MS20364 624C 18 REQUIRED TORQUE 120 TO 150 IN LBS SKETCHC Figure 57 1 Wing Installa...

Page 913: ...55 2 44155 3 AS REQ BOLT AN5 14A WASHER AN960 516 NUT MS20365 524C TORQUE 100 TO 140 IN LBS FS 1740 BOLT AN5 12A WASHER AN960 516 2 REQ NUT MS20365 524C TORQUE 100 TO 140 IN LBS I BOLT AN9 13A WASHER AN960 916L UNDER BOLT HEAD AN960 916 UNDER NUT NUT MS20365 918C TORQUE800 TO 1000 IN LBS SPAR BULKHEAD FS 13500 SPAR SKETCHE SKETCHD Figure 57 1 WingInstallation cont 4D21 57 41 00 Page 57 04 Issued A...

Page 914: ...t wing remove the left forward floor panel between the fuselage side trim panel and control pedestal NOTE To help facilitate reinstallation of control cables and fuel or hydraulic lines before removing mark cable and line ends in some identifying manner and attach a line where applicable to cables before drawing them through thefuselage or wing CAUTION To prevent damage or contamination of fuel hy...

Page 915: ...w the cable end to pass through B Disconnect the aileron balance cable at station 171and draw the cable from the fuselage Remove the cable pulley to allow removal of the cable C Remove the access panels at the aft section of the fuselage Block the elevator and rudder trim cables ahead of the main spar and in the aft section of the fuselage to prevent the cables from unwrapping at the trim drums Re...

Page 916: ...lowing lines cables etc to follow INSTALLATION OF WING Refer to Figure 57 1 1 Ascertain that the fuselage is positioned solidly on a support cradle 2 Place the wing in position for installation with the spar end a few inches from the side of the fuselage and set on trestles Turn out the three adjusting screws that draw the bottom fairing against the wing butt 3 Prepare the various lines control ca...

Page 917: ...gging and Adjustment of Aileron Chapter 27 and safety turnbuckles 21 If the left wing is being installed the following items pertain to the installation of the left wing only A Draw the left balance cable into the wing and connect at the aileron bellcrank Install the cable guard pin at the cable pulley near the bellcrank and at the wing butt B Draw the primary control cables through the main spar ...

Page 918: ...the power driver into the pin hex recess and the socket over collar hex Press the power driver against the collar and operate until the collar s wrenching device has been torqued off D Check the protrusion of the threaded end for the limits given in Figure 57 4 Hi Lok protrusion Gauge part number 2 1522 offers a convenient method for checking pin protrusion limits 2 Remove Hi Lok pins and collars ...

Page 919: ... HL 18 6 SERIES HAS A 015 025 RADIUS TYPE OF HI LOK PIN R HL 18 5 SERIES 015 025 HL 18 6 SERIES HI LOK PROTRUSSION GAUGE HI SHEAR P N 2 1522 MAY BE USED WITH OR WITHOUT COL LAR INSTALLED EXAMPLE MINIMUM GRIP MAXIMUM GRIP Maximum Protrusion Minimum Protrusion MAXIMUM GRIP LENGTH OF STANDARD HI LOK PIN MINIMUM MAXIMUM 5 6 Figure 57 4 Hi Lok Fastener Installation 57 41 02 4E3 Page 57 10 Issued April ...

Page 920: ...master test weight on the forward attachment bolt of the balance weight 6 If the aileron balances with the master test weight installed it is at the minimum static balance limit and is satisfactory 7 If the aileron is leading edge heavy with the master test weight installed material must be removed from the surface balance weight until a balanced condition is obtained This would also result in the...

Page 921: ...r Maximum Number of Trim Weights Allowed Per Side Maximum Allowable Balance Weights and Trim Weights Pounds Per Side 0 0 to 0 50 lbs 6 00 in 0 0 3 in lbs Right Left 4 75 lbs 3 9 lbs 54395 3 2 Right Left 7 75 lbs 7 75 lbs NOTES 1 This data pertains to a control surface having final base and trim paint applied 2 Control surface must be removed from the aircraft for balancing THIS SPACE INTENTIONALLY...

Page 922: ...SY WASHER 40559 42 16 REQ INBD BUSHING 41413 5 CTR ASSYI BUSHING 86102 104 WASHER 3512 20 03 0544 4 REQ OUTBD ONLY 16 REQ OMITON CTR TRACK ASSY BUSHING 86102 105 OR 49982 43 SECTION A A 4 REQ CTR ONLY BUSHING 86102 106 4 REQ INBD ONLY SKETCH A Figure 57 5 Aileron and Flap Installation 57 51 03 4E6 Page 57 13 Issued April 25 1983 ...

Page 923: ...EQ L 1REO R BOLT 2 REQ BOLT AN4 15 WASHER AN960 416 NUT AN310 4 COTTERPIN MS24665 134 2 REQ PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL 1 REQ L 1 REQ R SKETCH B SKETCH C SKETCH E SKETCH D I Figure 57 5 Aileron and Flap Installation cont 4E7 57 51 03 Page 57 14 Issued April 25 1983 ...

Page 924: ... remove the outboard hinge pin from its bushing Remove the tab INSTALLATION OF AILERON TRIM TAB Refer to Figure 57 5 1 Insert the tab control rod through the aileron and insert the outboard hinge pin into its bushing 2 Position the inboard hinge brackets install hinge bolt and torque to 38 inch pounds includes 18 inch pounds average friction drag torque 3 Connect the tab control rod 4 Check tab fo...

Page 925: ...r roller assemblies and remove flap INSTALLATION OF FLAP Refer to Figure 57 5 1 Put the flap in position and install the lower roller assemblies on the flap brackets and torque bolts 2 Install the upper roller assemblies and torque bolts 3 Connect the control tube 4 If the left flap was removed connect the position sender rod 5 Check flap for proper operation Rigging and adjustment procedure may b...

Page 926: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL CHAPTER PROPELLER 4E10 ...

Page 927: ...LING 4E17 61 21 00 Propeller Governor 4E17 61 21 01 Removal of Propeller Governor 4E17 1R 7 83 61 21 02 Installation of Propeller Governor 4E17 1R7 83 61 21 03 Rigging and Adjustment of Propeller Goveror 4E18 61 22 00 Propeller Synchrophaser 4E19 61 22 01 Description 4E19 61 22 02 Flight Operating Instructions 4E19 61 22 03 Troubleshooting 4E20 61 22 04 Pulse Generator 4E21 61 22 05 Timing the Pul...

Page 928: ...to moue the blades into high pitch and feather in the absence of governor oil pressure PROPELLER ASSEMBLY MAINTENANCE REMOVAL OF PROPELLER Refer to Figure 61 1 WARNING Before performing any service functions on the propeller ascertain that the master switch is OFF the magneto switches are OFF grounded and the mixture control is in the IDLE CUT OFF position CAUTION Under no condition should blade a...

Page 929: ...Factory or Service Station 8 Check blades to determine whether they turn freely on the hub pivot tube This can be done by rocking the counterweights back and forth through the slight freedom allowed by the pitch change mechanism If they appear tight and are properly lubricated the pitch change mechanism should be checked further 9 Grease blade hub through zerk fittings Remove one of the two fittin...

Page 930: ...R 3 BOLT 4 COUNTERWEIGHT 5 PROPELLER DOME 6 SCREW CAP ATTACHMENT 7 CAP SPINNER 8 SAFETY WIRE 9 CHECK NUT SPINNER 10 CAP AIR VALVE 11 AIR VALVE 12 LOW PITCH ADJUSTMENT 13 GREASE FITTING 14 BALANCE WEIGHT Figure 61 1 Propeller Installation 4E14 61 11 03 Page 61 03 Issued April 25 1983 ...

Page 931: ...eller Mounting Bolts Spinner Bulkhead Check Nut Spinner Attachment Screws Low Stop Jamb Nut 2600 RPM Max Required Torque Dry 22 foot pounds 60 foot pounds 35 40 foot pounds 40 inch pounds 27 33 foot pounds CHAMBER PRESSURE REQUIREMENTS WITH TEMPERATURE With Feather Assist Spring Assembly Temp F 70 to 100 40 to 70 0 to 40 30 to 0 Press psi 41 1 lb 38 1lb 36 I lb 33 1lb 0 NOTE DO NOT CHECK PRESSURE ...

Page 932: ...ng by using a soap solution or equivalent and applying it around the valve and at the aft end of the tube Internal leakage will show up as flow of air through the tube 8 Install spinner cap and cowling ADJUSTMENT OF LOW PITCH BLADE ANGLE AND STOP Adjustment of the low pitch blade angle and stop should only be accomplished by an authorized repair station REFERTO AC 43 13 1A FORSPECIFICBLADE REPAIR ...

Page 933: ...ch have lodged between hub and crankshaft mounting faces Bent blades will require repair and overhaul of assembly CONTROLLING PROPELLER GOVERNOR REMOVAL OF PROPELLER GOVERNOR 1 Remove the upper engine cowl 2 Disconnect the control rod end from the governor control arm 3 Remove the governor mounting stud nuts washers and lock washers 4 Remove the mounting gasket If the governor is to be removed for...

Page 934: ...screw With the throttle full forward observe engine RPM which should be 2600 RPM withhigh RPM properly adjusted 3 Should engine RPM not be as required the high RPM setting should be adjusted as follows A Shut down the engine and remove the upper engine cowl B Adjust the governor by means of the fine adjustment screw for 2600 RPM To do this loosen the high RPM fine adjustment screw locknut and turn...

Page 935: ...he camshaft of the left MASTER engine One rotation of the camshaft constitutes one cycle of engine operation of a four stroke engine This permits the pulse generator to be timed to any relationship to the firing order of the engine This gives a latitude of selection permitting any selection of corresponding operation between master and slave engine The selector switch on the panel has two position...

Page 936: ...ive pad for possible damage G Check tachometer shaft core engine to pulse generator to assure that core has 7 16 inch minimum end play Tachometer shaft core may be cut as required at output square end Too much end play may cause cable core to bind in the housing 2 Perform a wiring harness check utilizing a Hartzell Test Box B 4467 to provide assurance that the synchrophaser is properly connected I...

Page 937: ...e respective pulse generator or the governor PULSE GENERATOR TIMING THE PULSE GENERATOR LEFT ENGINE AND RIGHT ENGINE CA UTION Be sure that the magneto switches are off 1 Loosen the hex nut securing the pulse generator to the tach generator 2 Turn the engine in the direction of rotation to locate the No 1piston at T D C on the ignition stroke Use the engine timing mark NOTE If this point is missed ...

Page 938: ...d glow lamp amplifier in computer not operating Glow lamp or lamps and or photo conductor of con ductors defective Faulty computer Electrical Mechanical Pilot Engines not set within range of system Replace fuse Check wiring and connections Replace computer Perform operational check Visually check Perform electrical test Replace glow lamp or photo conductor assemblies Perform electrical test Perfor...

Page 939: ...TER ENGINE LEFT 3 COMPUTER 4 SLAVED ENGINE RIGHT 5 PULSE GENERATOR 6 INSTRUMENT PANEL 7 WIRE HARNESS 8 FIREWALL 9 COCKPIT CONTROL SWITCH 10 CIRCUITPROTECTOR 11 GOVERNOR 12 SOLENOID Figure 61 4 Synchrophaser Installation 4E23 61 22 05 Page 61 12 Issued April 25 1983 ...

Page 940: ...USTMENT OF PULSE GENERATOR Refer to Figure 61 5 1 Attach the pulse generator to the dual tach drive by securing loosely with hex nut NOTE The front of the pulse generator can be defined by the square hole in the center of the unit to accept the square end of a tach shaft CAUTION Before proceeding further be certain the magneto switches are OFF 2 Time the pulse generator per instructions in Timing ...

Page 941: ...e the machine screws on the mounting flanges that hold the computer unit to the angle assemblies Remove the computer INSTALLATION OF COMPUTER ASSEMBLY Refer to Figure 61 4 1 Position the computer unit on the mounting angles 2 Secure the unit in place with the machine screws in the mounting flanges of the unit 3 Connect the electrical plug to the computer unit 4 Check the fuse to ascertain that it ...

Page 942: ...L RIGHT ENGINE PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL I LEFT ENGINE NOTE SWITCH SHOWN IN FLEX SHAFTS 4F2 61 22 10 Page 61 15 Issued April 25 1983 ...

Page 943: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4F3 ...

Page 944: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4F4 ...

Page 945: ...CHAPTER STANDARDPRACTICES STANDARD PRACTICES ENGINES 4F5 ...

Page 946: ...0 MAINTENANCEMANUAL CHAPTER 70 STANDARD PRACTICES ENGINES TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 70 00 00 STANDARD PRACTICES ENGINES 4F7 4F6 70 Cont Effec Page 1 Issued April 25 1983 ...

Page 947: ... clean before assembling 5 Never reuse any lockwire lock washers tablocks tabwashers or cotter pins All lockwire and cotter pins must fit snugly in holes drilled in studs and bolts for locking purposes Cotter pins should be installed so the head fits into the castellation of the nut and unless otherwise specified bend one end of the pin back over the stud or bolt and the other end down flat agains...

Page 948: ...CHAPTER POWERPLANT 4F8 ...

Page 949: ...1 12 00 Engine Cowl Flap 4F23 71 12 01 Rigging and Adjustment of Cowl Flap 4F23 71 12 02 Cowl Flap Position Sender 4G11 71 12 03 Removal of Cowl Flap Position Sender 4G11 71 12 04 Installation of Cowl Flap Position Sender 4G 71 12 05 Rigging and Adjustment of Cowl Flap Position Sender 4G 71 12 06 Rigging Cowl Flap Limit Switches 4G11 71 20 00 MOUNTS 4G2 71 21 00 Replacing Engine Shock Mounts 4G2 7...

Page 950: ...red to complete the installation The spark advance is 20 BTC In addition to the aforementioned components each engine is equipped with an alternator geared starter hydraulic pump and pneumatic pressure pump Engine mounts are steel tubing construction attached at the fire wall and incorporate vibration absorbing dynafocal mounts The two top exhaust stacks and extensions are positioned one for the l...

Page 951: ...n wire Defective battery Improper operation of magneto breaker Lack of sufficient fuel flow Water in fuel injector Internal failure 4F11 Leave ignition OFF and mix ture control in idle cut off open throttle and unload engine by cranking for a few seconds Turn ignition switch on and proceed to start in a normal manner Open throttle to one fourth of its range Clean and adjust or replace spark plugs ...

Page 952: ... is adequate listen for buzzingof vibratorduringstarting If no buzzing is heard either the vibrator is defective or the circuit from the Output terminal on the vibrator to the retard contact assembly is open Check both Switch and Retard circuits Also check for good electrical ground Retard points may not be closing due to wrong adjustment or may not beelectricallyconnected in circuit due to a poor...

Page 953: ...rouble check magneto for improper internal timing or improperly meshed distrib utor gears Magneto improperly timed to engine Advance contact assembly out of adjustment in ternal timing off Retard points opening too late Check magneto to engine timing Check magneto timing Check timing of retard points Failure of engine to idle properly Incorrect idle mixture Leak in the induction system Adjust mixt...

Page 954: ... indicated Mixture too lean indi cated by overheating or backfiring Leaks in induction system Defective spark plugs Improper fuel Magneto breaker points not working properly Defective ignition wire Defective spark plug terminal connectors Fuel injector nozzles clogged 4F14 Check fuel lines for dirt or other restrictions Check fuel injection nozzles Re adjustment of fuel injector by authorized pers...

Page 955: ... re move restrictions Drain and refill tank with recommended fuel Clean or replace nozzle Adjust prop Tighten all connections Check system with tester Check ignition timing Repair or replace mount Rough engine Cracked engine mount Defective mounting bushings Uneven compression Defective spark plugs Defective plug leads 4F15 Install new mounting bushings Check compression Try new spark plugs Check ...

Page 956: ...ressure gauge Stoppage in oil pump intake passage Remove and clean oil pres sure relief valve Check gasket between acces sory housing and crankcase Remove and clean oil strainers See High oil temperature in Trouble Column Replace gauge Check line for obstruction Clean suction strainer High oil temperature Insufficient air cooling Check air inlet and outlet for deformation or ob struction Insuffici...

Page 957: ...mption Low grade of oil Fill sump with oil conform ing to specifications Failing or failed bearings Piston rings worn Incorrect installation of piston rings Failure of rings to seat New nitrided cylinders Check sump for metal particles Install new rings Install new rings Use mineral base oil Climb to cruise altitude at full power and operate at 75 cruise power setting until oil consumption stabili...

Page 958: ...ect the pressure pump hose 13 Disconnect the tachometer drive cable at the engine accessory housing 14 Disconnect the throttle and mixture control cables at the injector the governor control cable at the governor and the alternate air door duct at the fire wall Disconnect the cables from their attachment clamps 15 Disconnect the hydraulic pressure line at the hydraulic oil filter on the fire wall ...

Page 959: ...ER 9 TURBINE ASSEMBLY 10 COMPRESSOR 11 TAIL PIPE BOTTOM 12 OIL COOLER 13 MAGNETO 14 DRAIN ENGINE SUMP 15 FREONCOMPRESSOR 16 FUELPUMP 17 HYDRAULIC PUMP 18 WASTE GATE 19 EGT PROBE 20 AIR FILTER 21 TUNNELASSEMBLY 22 TAIL PIPE UPPER 23 ALTERNATOR COOLING AIR INLET 24 ALTERNATE AIR BOX 25 ALTERNATE AIR DUCT Figure 71 1 Engine Installation 4F19 71 03 02 Page 71 10 Revised July 28 1983 ...

Page 960: ...ENANCEMANUAL 17 I 16 7 NOTE VIEW OF TURBOCHARGER INTERCOOLER BREATHER TUBE AIR INDUCTION SYSTEM TAILPIPE AND ENGINE CONTROL LINKAGE OMITTED FOR CLARITY Figure 71 1 Engine Installation cont 4F20 71 03 02 Page 71 11 Issued April 25 1983 ...

Page 961: ...ffle and attach the cable end to the starter Secure cable with clamps at the engine mount and the engine 15 Ascertain that the magneto switches are off and install the propeller per Chapter 61 16 Install the proper grade and amount of engine oil 17 Connect the battery ground wire at the battery 18 Turn on the fuel valve open the throttle full and turn on the electric fuel pump and check the fuel l...

Page 962: ...INTERCOOLER AIRINLETSCOOP PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL COWLING FASTENERLOCKED POSITIONSTRIPE 1PER FASTENER Figure 71 2 Cowling 71 11 01 Page 71 13 Interim Revision October 7 1994 4F22 ...

Page 963: ...es a have a dark line painted along the top half of the fastener and cowling This is done so a visual check can distinguish when the fasteners are open or closed In addition to the paint stripe each fastener has a pin in the center of the screw slot that will protrude into the slot if properly locked when screw driver is removed ENGINE COWL FLAP The engine cowl flap consists of an inner skin of 03...

Page 964: ...PAD ADJUSTABLE 8 COWL FLAP POSITION SENDER 9 COWL FLAP POSITION SENDER CONTROL ROD 10 COWL FLAP POSITIONSENDER ARM 11 PIVOT BOLT 12 SWITCH PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 3 SECUREWITH LOC ON ADJUSTMENT 12 12 Figure 71 3 Cowl Flap Installation 4F24 71 12 01 Page 71 15 Issued April 25 1983 ...

Page 965: ...t of the fire wall 2 Ascertain that there is approximately 4 75 inches between the center of the pivot bolt on the sender arm and the rod hole in the torque tube arm by adjusting pivot bolt on the rod that connects the two arms 3 Ascertain that the cowl nap is properly adjusted 4 With the sender arm free to rotate and the cowl flap door aligned with the bottom cowl rotate the sender shaft as viewe...

Page 966: ...be removed The bushing in each lower mount must be removed with the bolt 6 Raise the nose of the engine enough to remove the lower aft shock mounts and replace with new ones NOTE Care should be taken not to introduce adverse stresses on the control cables electrical cables hoses and other items attached to the engine while hoisting the engine 7 Lower the engine slide the attachment bolts with bush...

Page 967: ...e fuel injector to the individual engine cylinders When alternate air is selected air is drawn from the area behind the left hand side of the fire wall AIR INDUCTION FILTER REMOVAL OF AIR INDUCTION FILTER 1 Remove the upper cowling 2 Remove the four screws that secure the air filter between the forward and aft induction ducts 3 Move the aft duct slightly down to gain enough clearance to slide the ...

Page 968: ... air box to the fire wall 3 Slide the air box forward through the fire wall INSTALLATION OF ALTERNATE AIR BOX 1 Slide the air box aft into its hole in the fire wall 2 Rotate the air box until its magnetic catch is at itslowest position 3 Attach airbox to the fire wall with the screws 4 Connect the alternate air hose to the forward end of the air box END 4G4 71 62 02 Page 71 19 Issued April 25 1983...

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Page 970: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4G6 ...

Page 971: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL CHAPTER ENGINEFUEL ANDCONTROL 4G7 ...

Page 972: ...3 73 12 00 Fuel Air Bleed Nozzle 4G11 73 12 01 Removal of Fuel Air Blend Nozzle 4G11 73 12 02 Cleaning and Inspection of Fuel Air Bleed Nozzle 4G12 73 12 03 Installation of Fuel Air Bleed Nozzle 4G12 73 30 00 INDICATING 4G13 73 31 00 FuelPressure Gauge 4G13 IR 7 83 73 31 01 Troubleshooting 4G 13 I R 7 83 73 31 02 Removal and Installation of Fuel Pressure Gauge 4G14 IR 7 83 73 32 00 FuelFlow Gauge ...

Page 973: ...r tightness and lock D Remove and clean the injector fuel inlet strainer at the first 25 hour inspection and each 50 hour inspection thereafter Damaged strainer O rings should be replaced 2 Tests prove that gasoline which becomes stale due to prolonged storage absorbs oxygen rapidly This stale oxidized gasoline acquires a very distinctive odor similar to varnish cause rapid deterioration of synthe...

Page 974: ...y unit taken out of service or units being returned for overhaul must be flushed with preserving oil Specification MIL 0 6081 Grade 1010 using the following procedure 1 Remove plugs and drain all fuel from the injector If available apply 10to 15psi air pressure to the fuel inlet until all fuel is discharged from the injector 2 Replace plugs and apply flushing oil filtered through a 10 micron filte...

Page 975: ...the engine and air scoop servicing the airfilter surplus oil on the element or when injecting preservative into the engine prior to storing or shipping INSTALLATION OF FUEL INJECTOR 1 Attach the injector to the air box and induction duct 2 Connect the fuel inlet flow pressure and discharger lines to the injector 3 Connect the throttle and mixture control cables to the injector Attach the control r...

Page 976: ...sion of Lycoming Service Instruction No 1275 INSTALLATION OF FUEL AIR BLEED NOZZLE 1 Install the nozzles and torque to 60 inch pounds 2 Ascertain that the O rings are properly installed on the nozzle stem and install the nozzle shroud Refer to Figure 74 2 3 Connect the ventto the nozzle shroud 4 Install the springand spring retainer on the nozzle stem 5 Connect the fuel line to the nozzle and clam...

Page 977: ...s of each engine TROUBLESHOOTING CHART 7301 TROUBLESHOOTING FUEL PRESSURE GAUGE Trouble Cause Remedy No fuel pressure indication Fuel valve stuck Fuel valveoff No fuel in tanks Defective fuel pump Check valve Check valve Check fuel fill Check pump for pres sure build up Check diaphragm and relief valves in engine pump Check for obstruction in electric pump Check bypass valve Air leak in intake lin...

Page 978: ... The fuel flow gauge is mounted to the right of center in the upper section of the instrument panel and is electrically operated by the flow transducers located in the fuel lines at wing station 49 00 under the leading edge access covers of each wing TROUBLESHOOTING CHART 7302 TROUBLESHOOTING FUEL FLOW GAUGE Trouble Cause Remedy Pointer oscillates Air in fuel line Purge line REMOVAL OF FUEL FLOW G...

Page 979: ...s 2 Install the post light s and secure Do not overtighten the nut 3 Connect the electrical connector to the gauge FUEL PRESSURE LOW WARNING LIGHT Illumination of the warning lights located in the annunciator panel indicator impending fuel starvation due to insufficient fuel pressure to the engines END 4G15 73 33 00 Page 73 07 Revised July 28 1983 ...

Page 980: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4G16 ...

Page 981: ...CHAPTER IGNITION IGNITION 4G17 ...

Page 982: ...RAL Description and Operation Troubleshooting ELECTRICAL POWER SUPPLY Magneto Inspection of Magneto Installation and Timing Magneto to Engine Internal Timing of Magneto Overhaul DISTRIBUTION Ignition Harness Inspection of Harness Maintenance of Harness Spark Plugs Removal of Spark Plugs Inspection and Cleaning of Spark Plugs Installation of Spark Plugs SWITCHING Ignition Switch 4G19 4G19 4G19 4G21...

Page 983: ...retard breaker continues to function At the slow cranking speed of the engine the vibrator provides the high energy spark necessary to fire the spark plugs The vibrator provides interrupted battery current to the primary coil of the magneto The pulsating DC current is then stepped up by transformer action producing a shower of sparks at the plugs for improved starting When the engine fires and beg...

Page 984: ...s Failure of engine to idle properly Low power and uneven running Faulty ignition system Detective spark plugs Check entire ignition system Clean and gap or replace spark plugs Magneto breaker points not working properly Defective ignition wire Defective spark plug termi nal connectors Clean points Check in ternal timing of magnetos Check wire with electric tester Replace defective wire Replace co...

Page 985: ...rely riveted to its spring 6 Examine the contact points for excessive wear or burning see figure 74 2 for visual reference CAUTION Do not open point contacts more than 0 0625 1 16 inch for examination of contact surfaces Excessive spreading of breaker points will overstress and damage the contact spring Desired contact surfaces have a dull gray sand blasted almost rough or frosted appearance over ...

Page 986: ... GRAY SANDBLASTE APPEARANCE MINOR IRREGULARITIES SMOOTH ROLLING HILLS AND DALES WITHOUT ANY DEEP PITS OR HIGH PEAKS THIS IS A NORMAL CON DITION OF POINT WEAR MINOR IRREGULARITIES SMOOTH ROLLING HILLS AND DALES WITHOUT ANY DEEP PITS OR HIGH PEAKS THIS IS A NORMAL CON DITION OF POINT WEAR Figure 74 2 Contact Points 4G22 74 11 01 Page 74 04 Issued April 25 1983 ...

Page 987: ...ed with red paint Refer to Figure 74 6 3 When correctly timed internally a magneto will have the timing teeth of the large distributor gears approximately centered in the timing windows the R or L E gap mark on the rotor in alignment with the pointer and both main breaker points opening all at the same time These three references E gap painted teeth and point opening are all used when timing the m...

Page 988: ... PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL Figure 74 3 Engine Timing Marks BENDIX SWITCH TERMINAL KIT Figure 74 4 Timing Light connected to Magneto 4G24 74 11 02 Page 74 06 Issued April 25 1983 ...

Page 989: ...engine timing should be accomplished using the first main breaker to open as a reference point when the engine is in the firing position for No 1cylinder This will ensure that ignition created by either spark plug will not occur prior to the desired engine firing point 12 If both timing lights are ON indicating breaker contacts are closed proceed to Step 13 If either or both are OFF proceed as fol...

Page 990: ...ENANCE MANUAL RETARD ANGLES E GAP ANGLES Figure 74 5 Timing Marks on Magneto Rotor Figure 74 6 Painted Tooth Centered in Timing Window Figure 74 7 Timing Mark on Rotor Aligned with Pointer 4H2 74 11 02 Pae 74 08 Issued april 25 1983 ...

Page 991: ...st clearance If support is bent main breaker contact must be rechecked Torque breaker securing screws to 20 25 inch pounds NOTE Bend bracket carefully Do not correct by bending back if bent too much this weakens the bracket 7 Position rotor so keyway is at 12o clock position and red painted distributor teeth are visible in timing windows 8 Loosen drive shaft nut and position the Rotor Holding Tool...

Page 992: ... holding tool to turn rotating magnet back a few degrees then turn rotating magnet in normal direction of rotation Timing light should go out when timing pointer is aligned with R or L E gap mark Lock rotating magnet in position where points just open 15 Loosen right main breaker securing screws and position breaker so cam follower is pressed against cam with points closed Tighten contact assembly...

Page 993: ...Y I LEFT MAGNETO HIGH TENSION OUTLETS A LEFT MAIN BREAKER CONTACT ASSEMBLY RIGHT MAGNETO HIGH TENSION OUTLETS 1 RIGHT MAIN CONTACT ASSEMBLY 2 LEFT MAIN CONTACT ASSEMBLY 3 SCREW 4 LOCK WASHER 5 FLAT WASHER MAIN CAM VIEW A A 2 Figure 74 9 Cam End View of Magneto 4H5 74 11 03 Page 74 11 Issued April 25 1983 ...

Page 994: ... damage Inspect lead assemblies for abrasions mutilated braid or other physical damage 2 Inspect grommets for tears and eyelets for spark erosion 3 Disconnect harness coupling nuts from the spark plugs and extract the lead terminations Inspect contact springs and compression springs for any damage or distortion Inspect sleeves for cracks or carbon tracking 4 Inspect coupling nuts and elbow assembl...

Page 995: ...AIRCRAFT PA 31P 350 MAINTENANCE MANUAL Figure 74 10 Checking Harness Lead Continuity Figure 74 11 Checking Harness Lead Insulation Resistance Figure 74 12 Modified Pliers Figure 74 13 Removing Spring From Lead Assembly 4H7 74 21 01 Page 74 13 Issued April 25 1983 ...

Page 996: ... 11 4152 or a pair of diagonal pliers modified as shown in Figure 74 12 Work the wire back into the shielding so the grommet fits properly against the ferrules in the plate Slack in shielding or wire can beremoved by grasping the lead in one hand and sliding the other hand firmly along the lead towards the magneto cover To replace contact springs insulating sleeves compression spring or elbows pro...

Page 997: ... PA 31P 350 MAINTENANCE MANUAL DRILL NO 47 IN DEEP TAP 3 48 12 000 IN MAT NO 30 DRILL RODOR EQUIVALENT Figure 74 14 Assembly Tool SPRINGRETAINERASSY Figure 74 15 Using Assembly Tool 4H9 74 21 02 Page 74 15 Issued April 25 1983 ...

Page 998: ...NTENANCEMANUAL DRILL NO 47 IN DEEP TAP 3 48 12 000 IN MAT NO 30 DRILL ROD OR EQUIVALENT Figure 74 16 Ferrule Positioned Under Braid SPRINGRETAINERASSY Figure 74 17 Ferrule Seating Tool 4H10 74 21 02 Page 74 16 Issued April 25 1983 ...

Page 999: ...sition of 11 8627 Kit and Contact Spring at Start of Installation Figure 74 19 Position of 11 8627Kit and Contact Spring After Installation LUBRICATE USE FLUOROCARBON SPRAY MS 5122 USE GO JO NO LOK Figure 74 20 Lubricating Sleeve Figure 74 21 Lubricating Ferrule Shoulder 4H11 74 21 02 Page 74 17 Issued April 25 1983 ...

Page 1000: ...rommet Place a new eyelet on conductor and crimp per instructions given in second paragraph of Maintenance of Harness 6 When lead being replaced is of the elbow type salvage the used elbow and compression springs for installation on replacement lead Install these and new sleeve and contact spring refer to Figures 74 18 and 74 19 furnished with replacement lead per instructions given in Steps 1thru...

Page 1001: ...ue Coupling Threads lb in 5 8 24 90 95 3 4 20 110 120 SPARK PLUGS Refer to the latest revision of Avco Lycoming Service Instruction No 1042 for a list of approved spark plugs REMVOAL OF SPARK PLUGS 1 Loosen the coupling nut on the harness lead and remove the terminal insulator from the spark plug barrel well NOTE When withdrawing the ignition cable lead connection from the plug care must be taken ...

Page 1002: ...do not apply to plug removal and sufficient torque must be used to unscrew the plug The higher torque in removal is not as detrimental as in installation since it cannot stretch the threaded section It does however impose a shearing load on this section andmay if sufficiently severe produce a failure in this location NOTE A torque indicating handle should not be used for spark plug removal because...

Page 1003: ...verely damaged shell or shield threads nicked up stripped or cross threaded B Badly battered or rounded shell hexagons C Out of round or damaged shielding barrel D Chipped cracked or broken ceramic insulator portions E Badly eroded electrodes worn to approximately 50 of original size 2 Clean the spark plugs as required removing carbon and foreign deposits 3 Test the spark plug both electrically an...

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Page 1005: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4H17 ...

Page 1006: ...CHAPTER ENGINECONTROLS 4H18 ...

Page 1007: ... OF CONTENTS EFFECTIVITY SUBJECT GENERAL POWER CONTROL Adjustment of Throttle and Mixture Controls Adjustment of Idle Speed and Mixture Rigging Alternate Air Controls GRID NO EFFECTIVITY 76 00 00 76 10 00 76 11 00 76 12 00 76 13 00 4H20 4H20 4H20 4H20 4H21 4H19 76 Cont Effec Page 1 Issued April 25 1983 ...

Page 1008: ...he succeeding steps readjust the idle speed to 600 650 RPM NOTE The idle mixture must be adjusted with the fuel boost pump ON 4 When the idling speed has been stabilized move the cockpit mixture control lever with a smooth steady pull toward the Idle Cut Off position and observe the tachometer for any change during the leaning process Caution must be exercised to return the mixture control to the ...

Page 1009: ...ion duct 2 Pull alternate air control knob 12 to 25 inch from its full in position on the instrument panel 3 Place alternate air actuating arm all the way forward against its stop on the aft induction duct 4 Adjust the clevis on the end of the alternate air control cable to fit on the arm Tighten clevis jam nut END 0 4H21 76 13 00 Page 76 02 Issued April 25 1983 ...

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Page 1012: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4H24 ...

Page 1013: ...CHAPTER ENGINEINDICATING 411 ...

Page 1014: ...7 22 02 77 22 03 77 22 04 POWER Manifold Pressure Gauge Troubleshooting Removal and Replacement Manifold Pressure Gauge Filters Tachometer Indicator Troubleshooting Removal and Replacement TEMPERATURE Cylinder Head Temperature Gauge Troubleshooting Removal and Replacement Exhaust Gas Temperature Gauge Cleaning and Inspection Installation of EGT Probe Troubleshooting Removal and Replacement 412 413...

Page 1015: ...ine is transmitted to the instrument through a line A pointer indicates the manifold pressure available at the engine in inches of mercury TROUBLESHOOTING Refer to Chart 7701 CHART 7701 TROUBLESHOOTING MANIFOLD PRESSURE INDICATOR Cause Pointer shifted Line leaking Defective instrument Restricted filter element Remedy Replace instrument Tighten line connections Replace instrument Replace filter Dul...

Page 1016: ...ectrically interconnected with the tachometer secured to the instrument panel The system functions through the reaction of each engine operating its own tach generator As the generator is activated by the engine a pulse pattern is sent to the tachometer which reacts to the incoming signals to indicate the engine RPM TROUBLESHOOTING Refer to Chart 7702 CHART 7702 TROUBLESHOOTING TACHOMETER Trouble ...

Page 1017: ...LACEMENT Refer to Chapter 39 TEMPERATURE CYLINDER HEAD TEMPERATURE GAUGE The cylinder head temperature gauge is one of the functions of the oil temp oil press CHT gauges located on the right hand instrument panel These instruments measure the cylinder head temperature using senders located in a cylinder head in each engine These gauges are electrical instruments and are wired through the instrumen...

Page 1018: ...ve after checking with the troubleshooting chart it should be replaced If the leads to the gauge are defective in any way they must be replaced When replacing leads it is necessary to use the same type and length of wire because the resistance of the leads is critical for the proper operation of this gauge When troubleshooting this instrument be certain the system being checked coincides with the ...

Page 1019: ... Local instrument shops can replace broken glass in the bezel and check operation and calibration of the indicator It is recommended that the indicator be returned to the manufacturer for re calibration 4 If trouble still exists after making the above checks REMOVE the leads from the indicator and using an ohmmeter check the probe cables for the following Probe Resistance Probe 54353 0 98 20 ohms ...

Page 1020: ...r wiring Loose frayed or broken electrical leads or faulty connections Check probe and lead wires for chafing breaks or shorting between wires and or metal structure Clean and tighten connec tions Repair or replace defective leads REMOVAL AND REPLACEMENT Refer to Chapter 39 PRE INSTALLATION MEASUREMENT SSION FITTING MOUNT FITTING PACKING NUT Figure 77 1 EGT Probe Adjustable 418 77 22 04 Page 77 06...

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Page 1022: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4110 ...

Page 1023: ...CHAPTER OIL SYSTEM 4I11 ...

Page 1024: ...79 32 02 GENERAL Description and Operation Troubleshooting 4113 4113 4113 EFFECTIVITY 1R 7 83 1R 7 83 DISTRIBUTION Adjustment of Oil Pressure Relief Valve Oil Screen Oil Filter Element Installation of Oil Cooler 4116 4116 4116 4116 4117 INDICATING Engine Oil Pressure Gauge Troubleshooting Removal and Replacement Oil Temperature Indicator Troubleshooting Removal and Replacement 4117 4117 4118 4118 ...

Page 1025: ... valve is provided to pass the oil directly from theoil pump to the oil pressure filter The oil filter element located on the accessory housing provides a means of filtering from the oil any solid particles that may have passed through the suction screen in the sump After being filtered the oil is fed through a drilled passage to the oil pressure relief valve located in the upper right side of the...

Page 1026: ...ifications Remove and clean oil strainers Usually caused by worn or stuck rings Examine sump for metal particles If found over haul of engine is indicated Replace gauge Replace Excessive oil consumption Low grade of oil Fill tank with oil conform ing to specifications Failing or failed bearing Worn or cracked piston rings Incorrect installation of piston rings Failure of rings to seat New nitrided...

Page 1027: ...pressure line Dirty oil strainers High oil temperature Remove and clean oil pres sure relief valve Check gasket between access sory housing and crankcase Remove and clean oil strainers See High oil temperature in Trouble column Defective pressure gauge Stoppage in oil pump intake passage Replace gauge Check line for obstruction Clean suction strainer THIS SPACE INTENTIONALLY LEFT BLANK 4115 79 02 ...

Page 1028: ...de of the sump Clean and inspect the screen and gasket and replace the gasket if over compressed or damaged OIL FILTER ELEMENT 1 The oil filter should be replaced after each 50 hours of engine operation this is accomplished by removing the lockwire from the bolt head at the end of the filter housing loosening the bolt and removing the filter assembly from the adapter 2 Before discarding the throwa...

Page 1029: ...ler a backup wrench should be used 3 After installation inspect the cooler for distorted end cups 4 Run up engine After run up check for oil leaks INDICATING ENGINE OIL PRESSURE GAUGE The oil pressure gauges are one of the functions of the oil temp oil press CHT gauges on the right hand instrument panel These gauges will indicate the amount of oil pressure available at the pressurized engine oil p...

Page 1030: ...l with light oil Check for leaks If trouble persists clean and adjust relief valve Clean and check Line restriction to instrument Loss of oil in engine or other engine failure Clean and check Shut down engine refer to Chart 7901 NOTE Gauge will take longer to indicate in cold weather REMOVAL AND REPLACEMENT Refer to Chapter 39 OIL TEMPERATURE INDICATOR The oil temperature indicators are one of the...

Page 1031: ...any reading Excessive error Pointer fails to move as engine is warmed up Wiring open Improper calibration adjustment Open wiring Check engine unit and wiring to instrument Replace instrument Check engine unit and wiring Dull or discolored marking Age Replace instrument REMOVAL AND REPLACEMENT Refer to Chapter 39 END 4I19 79 32 02 Page 79 07 Issued April 25 1983 ...

Page 1032: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4120 ...

Page 1033: ...CHAPTER STARTING 4121 ...

Page 1034: ... EFFECTLVLTY CHAPTER SECTION SUBJECT GRID NO SUBJECT 80 00 00 80 00 01 80 10 00 80 20 00 80 30 00 GENERAL Description CRACKING TESTS REMOVAL OF STARTER MOTOR INSTALLATION OF STARTER MOTOR 4123 4123 4123 4124 4124 EFFECTIVITY 1R 12 83 4122 80 Cont Effec Page 1 Revised December 14 1983 ...

Page 1035: ...d be inspected at regular intervals 100 Hour Inspections The frequency should be determined by the type of starting conditions and the amount of starter usage In any case it is recommended the following tests be completed at least twice a year 1 Check the battery with a hydrometer to make sure it is fully charged and filled to the proper level A load test should be accomplished to verify the condi...

Page 1036: ...t off starter motor INSTALLATION OF STARTER MOTOR 1 Clean all traces of rust corrosion and dirt from all mounting surfaces and hardware All grounding points shall be clean and tight 2 Place starting motor in position with no stressing or binding forces present and reinstall mounting hardware 3 Reinstall starter cable to starter terminal post 4 Reconnect battery ground cable 5 Perform cranking test...

Page 1037: ...CHAPTER TURBINES 4J1 ...

Page 1038: ...1 23 03 81 24 00 TURBOCHARGER Turbocharger Nomenclature Turbocharger Maintenance Removal of Turbocharger Turbocharger Lubrication System Priming Installation of Turbocharger Adjustment of Turbocharger Rigging of Absolute Pressure Controller Exhaust Waste Gate Assembly Removal of Exhaust Waste Gate Assembly Exhaust Waste Gate Valve Setting Installation of Exhaust Waste Gate Assembly Turbocharger De...

Page 1039: ...r system requires little attention between turbo overhauls However it is recommended that the items outlined in the Inspection Report be checked during required inspection intervals Should trouble occur refer to the Troubleshooting Chart for assistance in determining the probable cause Do not break the clamp seal joining the turbine and compressor units TROUBLESHOOTING Troubles peculiar to the Tur...

Page 1040: ...ressor impeller or turbine Clear all ducting Disassemble and clean Excessive dirt build up in compressor Piston seal in actuator leaking Usually ac companied by oil leakage at drain line Waste gate controller malfunction Waste gate butterfly not closing Turbocharger impeller binding frozen or fouling housing Thoroughly clean compressor assembly Service air cleaner and check for leakage Remove and ...

Page 1041: ...esired pressure Remove inlet line at ac tuator and clean orifices Remove and clean lines Critical altitude lower than specified Controller not getting enough oil pressure to close the waste gate Check pump outlet pressure oil filters and external lines for leaks or ob structions Chips under metering valve in controller holding it open Metering jet in actuator plugged Actuator piston seal failed an...

Page 1042: ... has idled for a prolonged period High deck pressure Com pressor discharge pres sure Controller metering valve not opening Aneroid bellows leaking Replace controller assembly or replace aneroid bellows Waste gate sticking closed Shut off valve in return line not working Butterfly shaft binding Check bearings Replace bypass valve or correct linkage binding Controller return line restricted Oil pres...

Page 1043: ... packing or re place actuator assembly Oil in induction housing Oil leaking past seal in controllers Engine idles too slow turbo doesn t turn allow ing oil to leak from compressor seal Replace faulty controller Increase engine idle speed to a maximum of 700 RPM if turbo still smokes it must be replaced NOTE New turbos may smoke for a short period of time White exhaust Leaking oil seal in tur bine ...

Page 1044: ... Replace linkage and adjsut waste gate to open and close position to specifications in overhaul manual Replace controller Waste gate won t close completely Obstruction in oil inlet orifice Replace controller Leaking valves in con troller Piston seal in bypass valve worn or broken Broken linkage Replace controller Replace controller Repair linkage and adjsut waste gate to open or close position to ...

Page 1045: ...eaks Controller or waste gate malfunction Replace or overhaul turbo charger Repair leaks Replace controller NOTE When it has been determined that a controller is malfunctioning it should be removed and replaced The old unit should be sent to approved facilities for overhaul of turbochargers or repaired in accordance with current Avco Lycoming Overhaul Instructions THIS SPACE INTENTIONALLY LEFT BLA...

Page 1046: ...sor The actuator is operated by a hydraulic piston operated by engine oil and cylinder with the piston linked to an arm on the butterfly valve shaft Absolute Pressure Controller The absolute pressure controller senses deck pressure on an absolute scale and tries to maintain constant absolute deck pressure to provide sea level horse power at varying altitudes The controller aneroid bellows assembly...

Page 1047: ...e hesitate 1 to 3 seconds and continue advancing to full throttle slow and easy This will eliminate any owershoot due to turbocharger inertia This is a term used in conjunction wvith turbo machinery If you were to take all the air coming from a turbocharger compressor and duct it directly back into the turbine of the turbocharger it would be called a bootstrap system and if no losses were encounte...

Page 1048: ...emove the turbo from the airplane 3 The waste gate may be removed as follows A Remove the lower cowling B Disconnect the waste gate actuating mechanism from the waste gate actuating arm C Remove the two clamp that secure the waste gate between the right hand exhaust manifold pipe and the extension on the tail pipe Do not spread the clamps any more than is necessary to remove the waste gate 4 For s...

Page 1049: ...al run in 1 TEMPORARILY install a screen of 100 mesh or finer in the oil supply line to the turbocharger to trap metal particles from theengine during the initial run in CA UTION Since cleaning of the screen is not provided for in periodic maintenance procedures for the engine the screen must not be left in place after the initial run in period Operation of the turbocharger with a clogged screen w...

Page 1050: ...rdance with the latest revision of Avco Lycoming Service instruction No 11187 RIGGING OF ABSOLUTE PRESSURE CONTROLLER Refer to Figure 81 2 1 Disconnect controller link rod at injector throttle arm 2 Rotate throttle arm full open with throttle lever in cockpit and with 020 feeler gauge located between the throttle arm stop pin and the throttle arm hold the throttle in the full open position 3 Move ...

Page 1051: ...E BUILD UP OF OIL PRES SURE IN THE ACTUATOR CAUSES THE PISTONTOMOVE THEWASTEGATETOWARD THE CLOSED POSITION AS THE WASTEGATE CLOSES MORE EXHAUST GASES ARE DIVER TED INTO THE TURBINE CAUSING THE SHAFT TO IN CREASEINSPEED INCREASING THE COMRPESSOR DIS CHARGE PRESSURE 1 EXHAUST MANIFOLD 2 THROTTLE 3 ABSOLUTE PRESSURERELIEFVALVE 4 SONIC NOZZLE 5 RAM AIR OUTLET 6 EXHAUST BYPASSVALVE ASSEMBLY 7 FUEL 8 IN...

Page 1052: ...GS 1 COUPLING 2 WASTE GATE 3 GASKET 4 GUARD ASSEMBLY 5 TAIL PIPEASSEMBLY 6 SAFETYWIRE 7 BLANKET 8 ABSOLUTE PRESSURECONTROLLER 9 FUEL INJECTOR 10 INTERCOOLER 11 CONTROLLERLINK ROD 12 THROTTLE ARM Figure 81 2 Turbocharger Installation 4J16 81 23 01 Page 81 14 Revised December 14 1983 ...

Page 1053: ... gate valve must startfrom the closed positionfirst and then to the open position INSTALLATION OF EXHAUST WASTE GATE ASSEMBLY 1 Install waste gate assembly with gasket between exhaust transition and tail pipe 2 Secure waste gate with v band clamps and torque clamps 3 Connect oil lines and drain line to waste gate assembly NOTE It is recommended that the waste gate valve be lubricated with a decarb...

Page 1054: ... from the turbocharger and allow all oil to driving 2 Cap the oil outlet port on the turbocharger 3 Pour the Mouse Milk into the oil inlet port of the turbocharger and allow the unit to soak overnight 4 Drain all Mouse Milk from the turbocharger and flashthe unit with engine oil 5 Prime the turbocharger PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL END 4J18 81 24 00 Page 81 16 Issued April 25 1983 ...

Page 1055: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCEMANUAL GRIDS 4J19 THRU 4L24 INTENTIONALLY LEFT BLANK 4J19 ...

Page 1056: ...MOJAVE MAINTENANCE MANUAL CARD 5 OF5 PA 31P 350 MOJAVE PIPER AIRCRAFT CORPORATION PART NUMBER 761781 5A1 ...

Page 1057: ...n broken down into Sub System Sections These sections are identified by the second element of the standardized numbering system The number 40 of the basic number series 32 40 00 is for the Wheels and Brakes portion of the landing gear The individual units within a Sub System Section may be identified by a third element of the standardized numbering system such as 32 40 01 This number could be assi...

Page 1058: ...st of Charts is for all fiche in this set followinglist of Illustrations 4 Acompletelistof paragraph titlesandappropriateGrid locationnumbersisgivenat thebeginningof each Chapter relating to the information within that Chapter 5 Identificationof Revised Material Revisedtext and illustrationsare indicated bya blackverticallinealongthe left hand marginof the frame oppositerevised added or deletedmat...

Page 1059: ...1983 July 28 1983 December14 1983 April30 1986 July 23 1986 September25 1986 June 15 1988 March13 1990 1 2 3 4 and5 1 2 3 4 and5 1 2 3 4 and5 1 2 1and4 3 2 INTERIM REVISION Revisions appear in chapter 27 of card 2 Please dispose of your current card 2 and replace with the revised one DO NOT DISPOSE OF CARDS 1 3 4 or 5 ConsulttheCustomerServiceInformationAeroficheforcurrentrevisiondatesforthismanua...

Page 1060: ...o 419 255 4068 Autopilot Avionics Edo Corporation Avionics Division P O Box 610 Municipal Airport Mineral Wells Texas 76067 817 325 2517 Bendix Avionics Division 2100 N W 62nd Street Fort Lauderdale Florida 33310 305 776 4100 Collins General Aviation Division Rockwell International Cedar Rapids Iowa 52406 319 395 3625 King Radio Corporation 400 N Rogers Road P O Box 106 Olathe Kansas 66061 913 782...

Page 1061: ...ro Road Suite 102 Bethesda Maryland 20034 301 229 5000 Narco Avionics Inc 270 CommerceDrive Fort Washington Penna 19034 215 643 2900 Avco Lycoming Avco Lycoming Division Williamsport Penna 17701 Janitrol Aero Division 4200Surface Road Columbus Ohio 43228 614 276 3561 SandenInternational U S A Inc 10710Sanden Drive Dallas Texas 75238 Fuel Pumps Lear Siegler Incorporated 17602Broadway Avenue Maple H...

Page 1062: ...o 44035 216 323 4676 Propellers Hartzell Propeller Incorporated 1025RooseveltAvenue Piqua Ohio 45356 513 773 7411 Propeller Synchrophaser Tools Air Conditioning Turbocharger Hartzell Propeller Fan Company 910 South Downing Street Piqua Ohio 45356 513 773 7411 Kent Moore Corporation ServiceTool Division 1501South Jackson Street Jackson Michigan 49203 517 784 8561 AiresearchIndustrial Division 3201L...

Page 1063: ...R PUBLICATIONS PA 31P 350 Parts Catalog Continuous Inspection 761 776 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 761 786 Piper Aircraft Corporation P O Box 1328 Vero Beach FL 32961 1328 Introduction Page 7 Issued April25 1983 5A8 ...

Page 1064: ...WING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACTICES AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS NAVIGATION AND PITOT STATIC OXYGEN SYSTEM AEROFICHE GRID NO IBI 1B4 IDII IEI IE4 IE9 IE13 IE16 IE20 IGI IH I I IHII 2BI 2B4 2B12 2C17 2DI 2H...

Page 1065: ...RPOSE PARTS STRUCTURES DOORS FUSELAGE NACELLES STABII IZERS WINDOWS WINGS PROPELLER STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM STARTING TURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 3117 3JI 3J3 3K1 3KI 4B1 4CI 4C4 4C7 4D3 4D16 4E10 4F5 4F8 4G7 4G17 4H 18 411 4111 4121 4JI 5B1 5EI Introduct ...

Page 1066: ... 3 Cherrvlock Rivet Removal 1G6 20 4 Hose Line Markings IG8 20 5 FlarelessTube Fittings 1G9 20 6 Spray Patterns 1G17 20 7 Improper Spray Technique IG19 20 8 Spray Technique IG20 20 9 Spraying Corners IG20 21 1 PressurizationSystemSchematic Garrett IH22 21 2 Cabin PressureControl SystemSchematic Garrett 1H23 21 3 Safetyand Outflow Valves 1I2 21 4 Cabin Air PressureOutflow ValveController Schematic ...

Page 1067: ... 35 Inspection Points Air Conditioning System Typical 1L15 23 1 EmergencyLocator Transmitter Schematic Narco 2B9 23 2 Portable Folding Antenna Narco 2B9 23 3 ELT Using Fixed Aircraft Antenna Narco 2B10 23 4 Avionics Master and EmergencySwitch Circuit 2B10 24 1 Kelvin Low ResistanceBridge 2B21 24 2 Electrical Power Distribution System Typical 2B22 24 3 Lamar Model B 00382 1 Typical SystemApplicatio...

Page 1068: ...7 27 Flap Transmission Exploded View 2G2 27 28 Flap TransmissionMeasurements 2G5 27 29 Checkingfor Wormgear Wear 2G7 27 30 Flap Rigging Adjustments 2GII 28 1 Fuel SystemSchematic 2H8 28 2 Fuel Cell Installation Inboard 2HI I 28 3 Fuel Cell Installation Outboard 2H 12 28 4 Fuel Cell Installation Nacelle 2H13 28 5 Fuel Valve Drain Plate 2H14 28 6 Fuel Cell Tie Detail 2H17 28 7 Installation of Fuel V...

Page 1069: ...uffed Area and Patch 3B22 30 10 Applying and Stitching Fabric 3B22 30 11 Placing and Stitching Gum 3B24 30 12 Removing Trapped Air 3B24 30 13 Masking Repair 3B24 30 14 Applying Neoprene Putty 3B24 30 15 Windshield Wiper 3C8 30 16 Typical Use of Dial Indicator 3C12 30 17 Centering of Brushes on Slip Rings 3C12 30 18 Modular Brush Assembly Wear Check 3C13 30 19 Angle of Contact Brushes to Slip Rings...

Page 1070: ...24 Adjusting Main Gear Down Light Switch 3F23 32 25 Gear Warning Switches Installation 3F24 33 1 Landing Taxi Light Installation 3G21 33 2 Logo Light Assembly Adjustments 3H2 34 1 Instrument Air System Installation Typical 3H9 34 2 Pitot Static Installation 3H 10 35 1 Oxygen System Installation 314 35 2 Oxygen System Installation for FAR 135 Certification 315 35 3 Oxygen Tubing Installations 3112 ...

Page 1071: ... 5 Forward BaggageDoor Assembly 4B19 52 6 NacelleLocker Door 4B21 52 7 Door Ajar Switch 4B24 54 1 NacelleAssembly 4C6 55 1 EmpennageInstallation 4CII 55 2 Elevator Balancing 4C18 55 3 Friction Measurement 4C20 55 4 Rudder Balancing 4C24 55 5 Rudder BalanceWeight Location 4C24 56 1 Windshield Installation 4D8 56 2 Fabricated SealantTools 4DI I 56 3 Storm Window Installation 4D13 57 1 Wing Installat...

Page 1072: ... 10 Checking HarnessLead Continuity 4H7 74 11 Checking HarnessLead Insulation Resistance 4H7 74 12 Modified Pliers 4H7 74 13 RemovingSpring From Lead Assembly 4H7 74 14 AssemblyTool 4H9 74 15 Using AssemblyTool 4H9 74 16 Ferrule Positioned Under Braid 4H10 74 17 Ferrule Seating Tool 4H 10 74 18 Position of 11 8627Kit and Contact Spring at Start of Installation 4H11 74 19 Position of 11 8627Kit and...

Page 1073: ...ravel 5E10 95 9 Fabricated Tool Checking Main Gear Toe In Adjustment 5E11 95 10 Tire Balancer 5E12 95 11 Fabricated Tool Checking NoseWheel Alignment 5E13 95 12 SuggestedDesign for Seal Plate Plugsand Caps for Combustion LeakageTest 5E14 95 13 Charging Stand 5E14 95 14 Fabricated PressureTest Adapters 5E15 95 15 Cabin PressureTest Unit Typical 5E15 95 16 TestGauge Manifold Set 5E16 95 17 Torque Wr...

Page 1074: ...Electrolyte Temperature Corrections 2CS 2406 Specific Gravity Temperature Correction 2C9 2407 Recommended Discharge Rate 2C9 2408 Electrolyte Freezing Points 2C10 2409 Capacity Ratings at Discharge Rate 2CI2 2410 Electrolyte Freezing Points 2C12 2411 Circuit Load Chart 2C13 2701 Troubleshooting Surface Controls 2D6 2702 Control Cable Rigging Tension vs Temperature 2D19 2801 Troubleshooting Fuel Sy...

Page 1075: ...3901 Cabin Instruments Display 3J 12 5101 List of Materials Thermoplastic Repairs 3K10 5102 Types of Metal Corrosion 3K21 5501 Elevator Balance Specifications 4C17 5502 Rudder Balance Specifications 4C23 5701 Aileron Balance Specifications 4E5 6101 Propeller Specifications 4E15 6102 Troubleshooting Actuator Chart Engine Synchrophaser 4E22 7101 Troubleshooting Engine 4F 11 7301 Troubleshooting Fuel...

Page 1076: ...List of Consumable Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Electrical Wiring Coding Electrical Symbols 5B4 5B16 5B17 5B19 5B20 5B21 5B22 5C2 5C3 5C4 Introduction Page 19 Issued April 25 1983 5A21 ...

Page 1077: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5A22 ...

Page 1078: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5A23 ...

Page 1079: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5A24 ...

Page 1080: ...CHAPTER CHARTS AND WIRING DIAGRAMS 5B1 ...

Page 1081: ...01 91 00 02 91 00 03 91 00 04 91 00 05 91 00 06 91 00 07 GENERAL Consumable Materials Torque Requirements Lubrication of Threads Lubrication of Gaskets and Seals Conversion Charts Decimal Millimeter Equivalents of Drill Sizes Electrical Wire Coding and Symbols 5B3 5B3 5B16 5B19 5B19 5B19 5C2 5C3 91 10 00 ELECTRICAL SCHEMATIC INDEX 5C5 91 Cont Effec Page I Issued April 25 1983 5B2 ...

Page 1082: ...rts which are applicable to ariouschaptersand covered in this manual All electrical schematicsare also included in this chapter CONSUMABLE MATERIALS Refer to back of ConsumableMaterials List for Vendor Information THIS SPACE INTENTIONALLY LEFT BLANK 91 00 01 Page 91 01 Issued April 25 1983 5B3 ...

Page 1083: ...nd Graphite Petrolatum MIL T 5544 Armite Product Armite Laboratories Anti Seize Compound Rovco 44 Exxon Oil Company Royal Lubricants Co Anti Seize Compound White Lead Base TT A 580 JAN A 669 Armite Product Armite Laboratories Fel Pro C5 A Fel Pro Incorporated Buffing and Rubbing Compounds Automotive Type DuPont 7 DuPont Company Ram Chemical 69 Ram Chemicals Compound for Polishing Mirror Glaze Mirr...

Page 1084: ...2 Supermil Grease No A72832 Royco 27A Shell 6249 Grease RR 28 Castrolease A I Low Temp Grease E P 5114E P Grease AV55 AeroshellGrease7 Braycote627S Mobil Grease 27 B P Aero Grease 31B Unitemp E P RPM Aviation Grease 5 Supermil Grease No 8723 Permatex Companny inc Amoco Royal Lubricants Co Shell Oil Company Socony Mobil Oil Co Burmah Castrol LTD Texaco Incorp Standard Oil of Calif ShellOil Company ...

Page 1085: ...G 6152 Code 71 502 Alvania Grease2 XSG 6151 Code 71 012 Cyprina Grease3 XSG 6280 Code 71 003 MIL G 81322 Marfax All Purpose Texaco I Aeroshell No 6 Shell Oil Mobil Grease 77 Mobil Oi or Mobilux EP2 Shell Alvania EP2 ShellOil Roxco 22 Royal Lu ENDOR ncorporated Company bricants MIL G 3545 Mobil Grease 28 Aeroshell No 22 High Temp Grease Marfax All Purpose ShellaireGreaseHT Alvania E P Grease2 Aeros...

Page 1086: ...atine Plug Valve Gasoline and Oil Resistant MIL G 7711 MIL G 21164 MIL G 6032 MIL G 6032 Regal AFB2 Regal Starfak Premium PED 3040 Aeroshell Grease 6 Royco II Aeroshell Grease No 17 Royco 64C Castrolease MSA c Royco 32 Castrolease PV Parker Fuel Lube 44 B P Aero Grease 32 L 237 Rockwell 950 Standard Oil of Calif Shell Oil Company Royal Lubricants Company Shell Oil Company Royal Lubricants Co Burma...

Page 1087: ...RODUCT Aero Lubriplate VENDOR Fiske Brothers Refining Company Sears Roebuck and Company or most hardware stores Hot Melt Adhesive Polyamids and Hot Melt Gun Stick Form 2 in diameter 3 in long Hydraulic Fluid MIL H 5606 Univis 40 Bravco 756D Bray Oil Company TL 5874 PED 3565 Texaco Incorporated Standard Oil Company of California Texaco Incorporated StandardOil Company of California Exxon Compan U S...

Page 1088: ...e H and H Fed Spec TT M 261 MIL M 7866 Loctite 222 Oil Air Conditioner Molykote Type G Paste Molykote T pe 2 Powder Frigidaire 525 Suniso 5 Texaco Capilla E Caltex Low Temp Oil Local Supplier Dow Corning Corp Virginia Chemical Sun Oil Company of Pennsylvania Texaco Incorporated Caltex Oil Products Companhy Oil Lubricating General Purpose Low Temperature MIL L 7870 Sinclair Aircraft Orbit Lube 1692...

Page 1089: ...Sealant Fuel Tank Sealing RS 36b Stripper thin CEE BEE ChemicalCo RS 24b Stripper thick PR 1422A 2 Sealant Brushing Consistency Products Research Company PR 1422 B 2 Sealant Trowling Consistency PR 1431G Faving SurfaceSeal Type I PR 1321 B1 2 AccessPanel Sealant PA 1560MK Primer Anti Bacteriological Coating BJO 0930 Phenolic Balloons Products Research Company Union Carbide Plastics Division ERL 27...

Page 1090: ...lectric Co Silicone Products Department Solvents Methylethylketone Methylene Chloride Acetone Local Suppliers Y2900 Union Carbide Plastic Division Fed Spec PD 680 Type I Stoddard Solvent Local Supplier Type II High Temperature Local Supplier Propeller Slip Ring Cleaning Solvent CRC 2 26 Corrosion Reaction Consultants Inc Toluol TT M 261 Local Supplier Trichlorethvlene M I L T 7003 Perm A Clor Dext...

Page 1091: ...RIAL Teflon Tape 003 x 25 wide 2 Thread Sealant for High Pressure Oxygen System NOTE 1 Take precautions when using MIL G 23827 and engine oil These lubricants contain chemicals harmful to painted surfaces 91 00 01 Page 91 10 5B12 Issued April 25 1983 ...

Page 1092: ...ng Corporation Alpha Molykote Plant 64 Harvard Avenue Stanford Conn 06902 Dukes Astronautics Co 7866 Deering Avenue Canoga Park California 91304 DuPont Company Finishes Div Dupont Bldg Wilmington Delaware 19898 302 774 1000 E Exxon Oil Company 1251 Avenue of the Americas New York New York 10019 212 757 1200 F Fel Pro Incorporated 7450 N McCormick Blvd Box C1103 Skokie Illinois 60076 312 761 4500 F...

Page 1093: ...t 400 N Lexington Avenue Pittsburgh PA 15208 412 247 3000 Royal Lubricants Company River Road Hanover New Jersey07936 201 887 3100 S Shamban W S and Co 11543W Olympic Blvd Los Angeles CA 90064 213 879 2270 Shell Oil Company One Shell Plaza Houston Texas 77002 713 220 6697 Sinclair Refining Co 600 Fifth Avenue New York N Y 10020 Socony Mobil Oil Co Washington 5 D C 20005 Solar Compounds Corp 1201W ...

Page 1094: ...ALS cont VENDOR INFORMATION Union Cabide Plastic Di 270 ParkAvenue New York N Y 10017 212 3763 I Virginia Chemical 3340 W Norfolk Rd Portmouth a 23703 804 484 5000 ooster Products Inc 30 Spruce Street Wooster Ohio 44691 216 262 8065 91 00 01 Page 91 13 Issued April 25 1983 5B15 ...

Page 1095: ...S TORQUE INCHPOUND TUBING OD INCHES ALUMINUM ALLOY TUBINGFLARE AND 10061 OR AND 10078 STEELTUBING FLARE AND 10061 HOSEENDFITTING AND HOSEASSEMBLIES MINIMUM MAXIMUMMINIMUM MAXIMUMMINIMUM MAXIMUM 1 8 3 16 1 4 5 16 3 8 1 2 5 8 3 4 1 1 1 4 1 1 2 1 3 4 2 40 60 75 150 200 300 500 600 600 65 80 125 250 350 500 700 900 900 90 135 180 270 450 650 900 1200 100 150 200 300 500 700 1000 1400 70 70 85 100 210 ...

Page 1096: ... torque to the desiredtorque recommended by themanufacturer or obtaindesired torque asshowninChart9103 Thisis referred to asfinal torque whichshouldregister on the indicatoror thesettingfor a snapover typewrench NOTE Formoredetails on torquing referto FAAManual AC43 13 1 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL CHART 9103 RECOMMENDED NUT TORQUES NUTS Steel Tension BOLTS Steel Tension AN 3 thru...

Page 1097: ...AN 310D NAS 1021D AN 320D AN 364D NAS 10220 Nut bolt size Torque Limits Torque Limits in lbs in lbs Min Max Min Max Torque Limits Torque Limits in lbs in lbs Min Max Min Max Torque Limits Torque Limits in lbs in lbs Min Max Min Max 8 36 10 32 1 4 28 5 16 24 3 8 24 7 16 20 1 2 20 9 16 18 5 8 18 3 4 16 7 8 14 1 14 1 1 8 12 1 1 4 12 12 15 7 9 20 25 12 15 25 30 15 20 50 70 30 40 80 100 50 60 100 140 6...

Page 1098: ...y 6 Ascertain that lubricant does not enter fittings or flared areas 7 Any fittings going to the engine should be lubricated with the type of fluid going through the lines CHART 9104 THREAD LUBRICANTS TYPE OF LINE TYPE OF LUBRICANT Brakes Hydraulic Deicer Air Fuel Oil Ox ygen Pitot and Static MIL H 5606 TT A 580 JAN A 669 Anti Seize Compound White Lead Base MIL T 5544 Anti Seize Graphite Petrolatu...

Page 1099: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL CHART 9105 DECIMAL CONVERSION 91 00 05 Page 91 18 5B20 Issued April 25 1983 5B 20 ...

Page 1100: ... 6 in lbs 217 0 in lbs 300 cmkg 350 cmkg 400 cmkg 450 cmkg 500 cmkg 260 4 in lbs 303 8 in lbs 347 2 in lbs 390 6 in Ibs 434 0 in Ibs 550 cmkg 600 cmkg 650 cmkg 700 cmkg 477 4 in lbs 520 8 in lbs 564 2 in lbs 607 6 in lbs FOOT POUNDS TO METER KILOGRAMS mkg 32 491 mkg 33 182 mkg 33 873 mkg 34 565 mkg 35 256 mkg 35 947 mkg 36 639 mkg 37 330 mkg 38 021 mkg 38 713 mkg 39 404 mkg 40 095 mkg 40 786 mkg 4...

Page 1101: ...Procedure for Converting Inches to Millimeters Refer to Chart 9107 A Example Convert 1 5 inches to millimeters Read down inches column to I inches 2 Read across top inch column to 0 5 3 Read do n and across to find millimeters 1 5 inches is 38 10 millimeters 4 Procedure for Converting Fahrenheit F and Celsius C Centigrade Temperature Referto Chart 9107 A Read number in middle column if indegrees C...

Page 1102: ...FT I ITERS IMPERIAL GAL FLUID OZ CM FT MULTIPLY KILOGRAMS LITERS METERS METER KILOGRAM OUNCES AVDP OUNCES FLUID I B AVDP SQUARE INCH POUND PER SQUARE INCH PSI STATUTE MILE NAUTICAL MILE QUART MILLIMETER BY 2 205 35 27 1000 1000 61 03 0 03532 0 2642 0 22 1 057 39 37 3 281 1000 7 233 9 807 0 0625 28 35 437 5 29 57 1 805 453 6 7000 16 0 6 4516 0 0703 1 609 0 8684 1 151 9463 1000 0 00 1 0 000039 11 52...

Page 1103: ... 110 120 130 140 150 160 170 180 190 200 210 F 94 0 76 0 58 0 40 0 22 0 4 0 14 0 32 0 50 0 68 0 86 0 104 0 122 0 140 0 158 0 176 0 194 0 212 0 230 0 248 0 266 0 284 0 302 0 320 0 338 0 356 0 374 0 392 0 410 0 C 104 44 110 00 115 56 121 11 126 67 132 22 137 78 143 33 148 89 154 44 160 00 165 56 171 11 176 67 182 22 187 78 193 33 198 89 204 44 210 00 215 56 221 11 226 67 232 22 257 78 243 33 248 89 ...

Page 1104: ...5 1 828 1 854 1 879 2 082 2 108 2 133 2 336 2 362 2 387 0 005 0 006 0 007 0 127 0 381 0 635 0 889 1 143 1 397 1 651 1 905 2 159 2 413 0 152 0 406 0 660 0 914 1 168 1 422 1 676 1 930 2 184 2 438 0 177 0 431 0 685 0 939 1 193 1 447 1 701 1 955 2 209 2 463 0 203 0 457 0711 0965 1 219 1 473 1 727 1981 2 235 2 489 0 228 0482 0 736 0 990 1 244 1 498 1 752 2 006 2 260 2 514 0 01 0 254 2 794 5 334 7 874 1...

Page 1105: ...5 3086 52197 5 1816 5 1594 5 1054 5 0546 4 9784 49149 1 8 0125 31 0 120 32 0116 33 0113 34 0111 35 0110 7 64 01093 36 0 1065 37 0104 38 01015 31750 3 048 2 9464 2 8702 2 8194 2 794 2 7781 2 7051 26416 2 5781 59 0041 60 0 040 61 0039 62 0 038 63 0037 64 0 036 65 0 035 66 0033 1 32 00312 67 0032 1 0414 1 016 0 9906 09652 0 9398 09144 0 899 0 8382 0 7937 08128 Q 0332 21 64 03281 P 0323 0 0316 5 16 0 ...

Page 1106: ...OR NUMBER S AND LOCATIONS CIRCUITS A C F G H L P Q RP RZ J AUTOPILOT E 100 Series Left Wingand Nacelle CONTROL SURFACE FLIGHT INSTRUMENT LANDING GEAR HEATER VENTILATING DEICING E 200 Series Right Wingand Nacelle E 300 Series From Fuselage Station 57 0 Aft E 400 Series On Fuselage Station 57 0 and Forward LIGHTING POWER FUEL OIL ENGINE INSTRUMENT RADIO POWER RADIO AUDIO IGNITION 91 00 07 Page 91 25...

Page 1107: ...LS BATTERY CONNECTORS BUS BAR PNUEMATIC SWITCH TERMINALBLOCK 0 0 0 0 0 0 0 0 POTENTIOMETER DIODE FUSE RESISTOR GROUND CONNECTORS KNIFE DISCONNECT CONDUCTORS SWITCH PUSHBUTTON SWITCH INSULATED CONNECTOR CONDUCTORS CROSSINGS AND JUNCTIONS OFCONDUCTORS THE DOT AT THE INTERSECTION INDICATESA JOININGOF CONDUCTORS SOLENOID VALVE 91 00 0 Page 91 26 Issued April 25 1983 5C4 ...

Page 1108: ...14 Propeller Blade Deice Left Right 5D11 5 Stall Warning Heated Lift Detector 5C17 5 Surface Deice Pneumatic Pressure Switches 5C17 5 Windshield Heat Left Right 5C17 ELECTRICAL POWER SYSTEMS I Alternators 70 Amp Left Right 5C13 3 Alternators 100 Amp Left Right Optional 5C13 Bus Main Power Distribution Battery 70 Amp 100 Amp 5CI 2 External Power 5C11 6 Electronic Locator Transmitter E L T 5C19 ENGI...

Page 1109: ... Left Right 5C15 4 Fuel Transducers Left Right 5C15 4 Fuel Totalizer 5C15 4 Fuel Quantity 5C15 INDICATORS 10 Ammeter 5D3 I Cabin Instruments Display Computer 5C9 11 Cylinder Head Temperature Left Right 5D5 9 Fasten Seat Belts No Smoking 5DI 6 Gyro Attitude 5C19 6 Gyro Directional 5C19 6 Gyro Pictorial Rate Turn Bank Optional 5C19 11 Hour Recorder Flight 5D5 16 Hour Recorder Heater 5D15 11 Oil Pres...

Page 1110: ...iders 5D1 9 Dome Exit Door Steps and Map 5D1 9 Fasten Seat Belts No Smoking Chimes 5D1 9 Overhead Reading and Toilet 5DI 10 Panel Placard and Radio Electroluminescent 5D3 PROPELLERS 14 Propeller Blade Deice 5D11 II Propeller Synchrophaser 5D5 WARNING SYSTEMS 13 Annunciator 5D9 9 Baggage Door Nose Cone Ajar 5DI 5 Landing Gear Warning Horn Indicators 5C17 9 Fasten Seat Belts No Smoking Chimes 5DI 6 ...

Page 1111: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL INTENTIONALLY LEFT BLANK 5C8 ...

Page 1112: ... VOLTMETER VOLTMETER 6 30 7 PEDESTAL E402 INDEX I EATEDTHERMOS RAZOR INVERTERCIGAR LIGHTER CABIN INSTRUMENTS VOLTMETER 2 MAIN POWERDISTRIBUTION L RSTARTER 3 L R ALTERNA TOR 4 L R FUEL PUMPS FUEL QTY L RFUEL FLOW FUEL TOTALIZER L RFUEL PRESSURE 5 W SHLDWIPER L RP TOT EAT SURFACEDEICE STALL WARN HEAT PNEU PRESS SWI TCES 6 GYROS STALL WARNING ELT 7 POSITIONANTI COLLISON TAIL BEACONLOGO LIGHTS 8 RECOG...

Page 1113: ...ER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL MAG SWS L BATTERY MASTER SWITCH MAG 5WS 1 FUSE DISTRIBUTION BUS L R Z8 A H Sheet 2 Main Power Distribution Starters Left Right 5C11 5C12 91 10 00 Page 91 28 Revised July 28 1983 ...

Page 1114: ...PA 31P 350 MAINTENANCE MANUAL 1903 82187 DISTRIBUTION BUSES 5A 30 RFFILTER I I 181 0 1 ALTERNATOR CONTROL UNIT R ALTERNATOR CONTROL UNIT Sheet 3 Alternators Left Right 5C13 5C14 91 10 00 Page91 29 Revised July 28 1983 ...

Page 1115: ... MAINTENANCE MANUAL 11904 LEFT MAIN BUS L BOOSTFUEL PUMP SUBMERGED RIGHT FUEL PRESS TRANSDUCER A FUEL FLOW E104 403 LEFT FUEL TRANSDUCER GIHT FUEL Sheet 4 Fuel Systems Left Right 5C15 5C16 91 10 00 Page 91 30 Revised July 28 1983 ...

Page 1116: ... O PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL CE Sheet 5 Deice Systems Left Right 5C17 5C18 91 10 00 Page 91 31 Revised July 28 1983 ...

Page 1117: ...TURN f BANK INDICATOR OPT STALLWARNING OPT HEATED STALL WARNING VANE PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL LEFT MAIN BUS STALL WARNING Sheet 6 Gyro s Stall Warning E L T 5C19 5C20 91 1000 Page 91 32 Revised July 28 1983 ...

Page 1118: ...LEFTMAIN BUS RIGHT MAIN BUS Sheet 7 Anti Collision Position Logo Lights 5C21 5C22 91 10 00 Page 91 33 Revised July 28 1983 ...

Page 1119: ...Sheet 8 Recog Taxi Landing Wing Insp Lights 5C23 5C24 91 10 00 Page 91 34 Revised July 28 1983 ...

Page 1120: ...PA 31P 350 MAINTENANCE MANUAL Sheet 9 Chimes Map Cockpit Courtesy Lights 5D1 5D2 91 10 00 Page 91 35 Revised July 28 1983 ...

Page 1121: ...PA 31P 350 MAINTENANCE MANUAL Sheet 10 Placard Panel Radio Lighting 5D3 5D4 91 10 00 Page91 36 Revised July 28 1983 ...

Page 1122: ...PROP SYNC COMPUTER F11911 B7187 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL SheetII Tach Hour Meter Cabin Press Cont I Oil Cyl HeadTemp 5D5 5D6 91 10 00 Page91 37 Revised July 28 1983 ...

Page 1123: ...FLAP MOTOR NON ESSENTIAL BUS Sheet 12 Wing Flaps 91 10 00 5D8 Page91 38 Revised July 28 1983 5D7 ...

Page 1124: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL f 1913 82182 CABIN DOOR AJAR SWTCHES DOOR CLOSED Sheet 13 Annunciator Panel 5D9 5D10 91 10 00 Page 91 39 Revised July 28 1983 ...

Page 1125: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL Sheet 14 Heated Windshield Prop Deice Left Right Cowl Flaps Left Right 5Dll 5D12 91 10 00 Page 91 40 Revised July28 1983 ...

Page 1126: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL INSTALL OPT GEAR WARNMUTE A HERE Page 91 41 Revised July 28 1983 ...

Page 1127: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL I Sht 16 H r Air Conditioner Rcirc Fan Sheet 16 Heater Air Conditioner Recirc Fan 5D15 5D16 91 10 00 Page 91 42 Revised July 28 1983 ...

Page 1128: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL GRIDS 5D17THRU 5D24 INTENTIONALLYLEFT BLANK 5D17 ...

Page 1129: ...CHAPTER SPECIALPURPOSE EQUIPMENT 5E1 ...

Page 1130: ... SPECIAL PURPOSE EQUIPMENT TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 95 00 00 GENERAL 5E3 95 10 00 95 11 00 TOOLS AND TEST EQUIPMENT Construction of Tire Balancer 5E3 5EI2 95 Cont Effec Page 1 Issued April 25 1983 5E2 ...

Page 1131: ...ased special tools which may be required when performing various forms of maintenance on the PA 31P 350 TOOLS AND TEST EQUIPMENT 110 ALL WELDED CONSTRUCTION 2 0 X 6 0 X 200 X 9 0 9 00 MAY ADD WHEEL IF DESIRED Figure 95 1 Fabricated Jack Stand for Piper Jack Part No 18338 00 95 10 00 Page95 01 5E3 Issued April 25 1983 ...

Page 1132: ... PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1019 COWLING CL P BRAZE 2 50 1 00 50 BRAZE ROUND END 076 HOLE 37 D SASH CHAIN 8 00 L PIN 23 37 2 25 TYP PLATE 062 1 REQ 24 00 TYP ANGLE 2 00 X 2 00 X 187 X 24 00 45 4 REQ TYP ANGLE CORNER DETAIL ALL WELDED CONSTRUCTION Figure 95 2 Fabricated Tail Stand 95 10 00 Page 95 02 Issued April25 1983 5E4 ...

Page 1133: ... RI PIPER AIRCRAFT PA 31 P 350 MAINTENANCE MANUAL 198 MATERIAL 25 TO 50 ALUMINUM OR STEEL 6 50 2 39 50 50 50 R 3 39 Figure 95 3 Fabricated Bellcrank Rigging Tool 95 10 00 Page 95 03 Issued April 25 1983 5E5 ...

Page 1134: ... MAINTENANCE MANUAL DRILLANDTAP INCH BOLT FILETO LENGTH 25 50 to 1 0 14 625 DRILLANDTAP INCHBOLT FILETOLENGTH MATERIAL ALUMINUM PLATE SPAR MATERIAL MAYBEUSED Figure 95 4 Fabricated Aileron and Elevator Rigging Tool 95 10 00 Page 95 04 Issued April 25 1983 5E6 ...

Page 1135: ... PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL 1064 22125 MATERIALALUMINUM PLATE Figure 95 5 Fabricated Rudder Rigging Tool 95 10 00 Page 95 05 Issued April 25 1983 5E7 ...

Page 1136: ... PIPER AIRCRAFT PA 31 P 350 MAINTENANCE MANUAL 55 Figure 95 6 Fabricated Rudder Trim Tab Rigging Tool 95 10 00 Page 95 06 Issued April 25 1983 5E8 ...

Page 1137: ... ITIS IMPORTANT THAT CENTER LINE ACCURACY BEUSED WHEN LOCATING NOLES FOR INSTALLATION OF USHING SSITSLOT AND ELONGATD HOLE 175 015 625TIME SEE NOTE SCIE LINES ASSHOWN 2471 SEE NOTE SEENOTE 25 1 125 3 50 175HOLE 72 Figure 95 7 Fabricated Tool Checking Nose Gear Link Travel 95 10 00 Page 95 07 5E9 Issued April 25 1983 ...

Page 1138: ... TT CENTE LINE ACCURACY BEUSED WHEN LOCATING NOLES FOR INSTALLATION OFBUSHING SSWT SLOT AND ELOIGATED NOLE 125S I t 18 062 1 375 1 25 1 817 25 11 25 120 50 10 KOLE I 4 50 Figure 95 8 Fabricated Tool Checking Main Gear Side Brace Link Travel 95 10 00 Page 95 08 Issued April 25 1983 5E10 ...

Page 1139: ...31P 350 MAINTENANCE MANUAL 216 TOP 1 10 SIDE MATERIAL HARD WOOD 1 10x x11 56 NOTE MARK LARGE ENDFORWARD Figure 95 9 Fabricated Tool Checking Main Gear Toe In Adjustment 95 10 00 Page 95 09 5E11 Issued April 25 1983 5E11 ...

Page 1140: ...g Use AN426 AD5 rivets 2 center to center to secure 2 tee s to I base If tee extrusion is unavailable heavy angle extrusion could be used 3 sides must be paralleled and vertical 2 The 4 axle must slide through the 8 pipe The 5 nuts were made by reaming the existing threads in the AN365 624 nuts with an R drill then tapping with a 1 8 27 pipe tap 3 The 6 spacers were made from I 2 inch aluminum tub...

Page 1141: ...MANUAL 1094 SECTO1 NOTE THE PA23CHECKING TOOL MAY BE MODOFIED THESE DIMENSIONS BY EXTENDING THE DEGREE ANGLE ON THE TOOL PLATE AS SHOWN Figure 95 11 Fabricated Tool Checking Nose Wheel Alignment 95 11 00 Page 95 11 Issued April 25 1983 5E13 ...

Page 1142: ...UGE 2 VALVE LOW PRESSURE CONTROL 3 VALVE VACUUM CONTROL 4 CHARGING CYLINDER 5 BRACKET 6 SIGHT GLASS 7 HIGH PRESSURE GAUGE 8 HIGH PRESSURE CONTROL 9 REFRIG CONTROL 10 CHARGING LINE HOSE HOLDER 11 BRACKET 12 LOW PRESSURE CHARGING LINE 13 HIGH PRESSURE CHARGING LINE 14 VACUUM PUMP IS OIL FILL LOCATION 16 PLASTIC CAP 17 REFRIGERANT DRUM VALVE 18 VACUUM PUMP VALVE 19 VACUUM PUMP EXHAUST PORT 20 TOP CYL...

Page 1143: ...UMP BYPASS BEFORESTARTINGORSTOPPING UNIT 0 FRONT VIEW 17 1 FLOW METERPRESSUREINDICATOR 2 RATE OF CLIMB INDICATOR 3 RATEOF FLOW INDICATOR 4 CABIN DIFFERENTIAL PRESSUREINDICATOR 5 INSTRUMENTAIR PRESSURE INDICATOR 6 FLOW RATEVALVE 7 CIRCUITBREAKER 8 STARTBUTTON 9 STOP BUTTON 10 AIR REGULATORVALVE 11 ELECTRICALCONNECTION 12 FILL PORT BACK VIEW 13 SIGHT GAUGE 14 INSTRUMENTAIR 15 CABIN REFERENCE 16 PNEU...

Page 1144: ...MPOUND PRESSUREGAGE C TO SUCTION SERVICE VALVE HIGH PRESSURE GAGE TO DISCHARGE SERVICE VALVE TO VACUUM PUMP OR REFRIGERANTCYLINDER Figure 95 16 Test Gauge and Manifold Set A Figure 95 17 Torque Wrench Extension 95 11 00 Page 95 14 Issued April 25 1983 5E16 ...

Page 1145: ...T CUTTING TOOL SHARP EDGE LARGE SEALANT CUTTING TOOL BEVELED SURFACE SHARP EDGE SMALL SEALANT CUTTING TOOL SEALANT REMOVAL TOOL SEALANT FAIRING TOOL SMALL SEALANT FAIRING TOOL WITH SPOON TYPE HEAD LARGE SEALANT FAIRING TOOL NOTE THESE TOOLS MAY BE MADE OF 1 4 INCH DIAMETER BRONZE OR STEEL WELDING ROD AND MAY BE PLATED TO IMPROVE SMOOTHNESS Figure 95 18 Sealant Tools 95 11 00 Page 95 15 Issued Apri...

Page 1146: ...MANUAL C347 DRILL NO 47 IN DEEP TAP3 48 BLENDO D TO I D POLISHO D 12 000 IN MAT NO 30 DRILL RODOR EQUIVALENT 0 506 0 250 MATERIAL BRASS CUTNOTCH TO FIT SNUG ON NO 58 DRILL WITH JAWSCLOSED Figure 95 20 Modified Pliers for Igntion Harness Figure 95 21 Ferrule Seating Tool Ignition Harness 95 11 00 Page 95 16 Issued April 25 1983 5E18 ...

Page 1147: ...CONTACT SANKYO SANDEN INTERNATIONAL INC 10710 SANDEN DRIVE DALLAS TEXAS 75238 PHONE 214 349 3030 TELEX 73 0497 PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL C750 I 32446 JAWS 32435 CLUTCH ROTORINSTALLATIONSET 32416 FRONTPLATE PULLER Figure 95 22 Air Conditioning Compressor Tools 95 11 00 Page 95 17 Issued April 25 1983 5E19 ...

Page 1148: ...PIPER AIRCRAFT PA 31P 350 MAINTENANCE MANUAL GRIDS 5E20THRU 5L24 INTENTIONALLY LEFT BLANK 5E20 ...

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Piper Aircraft Corporation MOJAVE PA-31 P-350, Maintenance Manual

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