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Piper Navajo Chieftain PA-31-350, Maintenance Manual

The Piper Navajo Chieftain PA-31-350 Maintenance Manual is the ultimate guide for maintaining and repairing this exceptional aircraft. This comprehensive manual is available for free download at manualshive.com, providing aviation enthusiasts with a valuable resource to ensure the optimal performance and safety of their aircraft.

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Summary of Contents for Navajo Chieftain PA-31-350

Page 1: ...AIRLINE DIVISION MAINTENANCE MANUAL CARD 1OF5 PA 31 350 T1020 PIPER AIRCRAFT CORPORATION PART NUMBER 761768 lAl ...

Page 2: ...ers are thenbrokendownintoSub System Sections Thesesectionsare identified by the secondelementof thestandardizednumberingsystem Thenumber 40 of thebasicnumberseries32 40 00 isfor the WheelsandBrakes portionofthe landinggear The individualunitswithinaSub System Section maybeidentifiedby a thirdelementof thestandardized numberingsystem suchas 32 40 01 Thisnumbercouldbe assignedby the manufacturerto ...

Page 3: ...eferenceandrecordof materialrevisedis includedin eachchapter s Tableof Contents Effectivity The codesused in the effectivity columnsof eachchapteraredefinedas follows SAMPLEEFFECTIVITY CODES First Revision Second Revision Third Revision Fourth Revision Added Subject Month and Year 11 80 Revision Indication Month and Year 2R 12 80 Revision Indication Month and Year 3R 1 81 Revision Indication Month...

Page 4: ...1A4 INTENTIONALLYLEFT BLANK 1A4 ...

Page 5: ...0 SERIES AIRCRAFT ENGINES P N 60297 23 Avco Lycoming Division Williamsport PA 17701 HARTZELL CONSTANTSPEED AND FEATHERING PROPELLER P N 117D Hartzell Propeller Inc P O Box 1458 1800 Covington Avenue Piqua Ohio 45356 S 1200 SERIES MAGNETO IGNITION SYSTEM P N L 609 3 Bendix Electrical Components Division Sidney New York 13838 CLEVELAND WHEEL AND BRAKE Aircraft Wheel and Brake Division 1160 Center Ro...

Page 6: ...L AVIATION DIVISION Rockwell International Cedar Rapids Iowa 52406 319 395 3625 Telex 46 4421 KING RADIO CORPORATION 400 N Rodgers Rd Olathe Kansas 66061 813 782 0400 Telex 4 2299 Kingrad GLOBAL NAVIGATION 2144 Michelson Drive Irvine Ca 92715 714 851 0119 PIPER PUBLICATIONS PA 31 350T 1020 PartsCatalog CONTINUOUS INSPECTION 761 775 Piper Aircraft Corporation 2926 Piper Drive Vero Beach FL 32960 76...

Page 7: ...D SHORING LEVELING AND WEIGHING TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACT AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS AEROFICHE GRID NO IBI 1B4 1D23 1E13 1E16 1E21 1F1 1F4 1F8 1G12 II 2B1 2B4 2B12 2D1 2D10 2G19 2J1 3B1 3D9 3G19 ...

Page 8: ...37 VACUUM SYSTEM 3J4 39 ELECTRIC ELECTRONIC PANELS AND MULTI PURPOSEPARTS 3J6 51 STRUCTURES 3J22 52 DOORS 4B1 53 FUSELAGE 4B21 55 STABILIZERS 4CI 56 WINDOWS 4C17 57 WINGS 4D4 61 PROPELLERS 4EI 70 STANDARD PRACTICES ENGINES 4E22 71 POWER PLANT 4F1 73 ENGINE FUEL AND CONTROL 4G1 74 IGNITION 4G11 76 ENGINE CONTROLS 4H10 77 ENGINE INDICATING 4H14 79 OIL SYSTEM 411 Introduction 1A8 Page 7 Revised Febru...

Page 9: ...UAL GAMASYSTEM CHAPTERINDEXGUIDE cont SYST CHAP 80 81 91 95 SUB SYST SECTION TITLE STARTING TURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 4111 4121 5B1 5FI 1A9 Introduction Page 8 Revised November17 1983 ...

Page 10: ...r and Cowl Flap 1G3 12 7 LubricationChart DoorsandSeats 1G4 20 1 TorqueWrenchExtension 1G16 20 2 Methodof InstallingRod EndBearings 1G16 20 3 CherrylockRivetRemoval 1G17 20 4 Hose LineMarkings 1G19 20 5 FlarelessTubeFittings 1G20 20 6 SprayPatterns 1H8 20 7 ImproperSprayTechnique 1H10 20 8 SprayTechnique 1H11 20 9 SprayingCorners 1H11 21 1 HeatingandVentilatingSystem 1I10 21 2 HeaterAssemblyandCom...

Page 11: ...icated Oil Dipstick IL3 21 31 Magnetic Clutch Installation IL6 21 32 Expansion Valve Typical IL8 21 33 Air Conditioning Outlets 1L11 21 34 Positioning of Airflow Probe 1L13 21 35 Sealing of Ducts 1L14 21 36 Installation of VOI SHAN Seals 1L14 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...

Page 12: ...Tension 2E18 27 10 Safety Wiring Control Surface Stops 2E18 27 11 Rudder and Rudder Trim Controls 2E22 27 12 Rudder and Trim Tab Control Travels and Cable Tension 2F2 27 13 Clamping Rudder Pedals in Neutral Position 2F2 27 14 Installation of Rudder Rigging Tool 2F2 27 15 Rudder Pedal Installation 2F7 27 16 Elevator and Elevator Trim Controls 2F10 27 17 Elevator and Elevator Trim Travels and Cable ...

Page 13: ...ower Pack Handle Release Mechanism 2K8 29 9 Safetying Control Arms 2K9 29 10 Indexing of Selector Spool 2K10 29 11 Handle Release Adjustment 2K11 29 12 Landing Gear Selector Mechanism Installation 2K13 29 13 Power Pack Test Harness Schematic 2K18 29 14 Hydraulic Filter 2K20 29 15 Hydraulic Pump 2K22 29 16 Hand Pump 2L4 29 17 Shuttle Valves WTC 2216 WTC 2217 2L7 30 1 Pneumatic Deicer System Install...

Page 14: ...eLandingGearInstallation 3E16 32 8 ClampingRudderPedalsin NeutralPosition 3E22 32 9 RudderPedalsNeutralAngle 3E22 32 10 AligningNoseGear 3E22 32 11 EmergencyExtensionSystemInstallation 3F1 32 1 a TestEquipment Installation Emergency Gear ExtensionSystem 3F5 32 12 GearActuatingCylinder WiebelToolWTC2115 1 3F6 32 13 UnlockActuator WiebelToolWTC2215 3F7 32 14 GearDoorActuatingCylinder WiebelTool WTC2...

Page 15: ...7 51 4 Deep Scratches Shallow Nicks and Small Holes 3K7 51 5 Mixing of Epoxy Patching Compound 3K8 51 6 Welding Repair Method 3K8 51 7 Repairing of Cracks 3K9 51 8 Various Repairs 3K11 51 9 Repair of Stress Lines 3K12 51 10 Repair of Impacted Damage 3K 12 51 11 Installation of Radome Erosion Shield 3K18 52 1 Cabin Entrance Door Latch Assembly 4B6 52 2 Pilot s Door Latch Assembly 4B10 52 3 Cargo Do...

Page 16: ...oints 4G15 74 3 Rotor Holding Tool Installed 4G16 74 4 Timing Kit Installed 4G16 74 5 Aligning Timing Marks Single Contact Assembly Magneto 4G18 74 6 Forming Leads in Breaker Compartment 4G18 74 7 Engine Timing Marks 4G19 74 8 Magneto Timing Marks 4G19 74 9 Deleted 74 10 Checking Harness Lead Insulation Resistance 4G22 74 11 Modified Pliers 4G22 74 12 Removing Spring From Lead Assembly 4G23 74 13 ...

Page 17: ...cated Tool Checking Nose Gear Link Travel 5F7 95 5 Flight Control Rigging Tools 5F8 95 6 Fabricated Tool Checking Nose Wheel Alignment 5F9 95 7 Fabricated Jack Stand for Piper Jack Part No 18338 00 5F10 95 8 Fabricated Tail Stand 5F11 95 9 Fabricated Bellcrank Rigging Tool 5F 2 95 10 Fabricated Aileron and Elevator RiggingTool 5F13 95 11 Fabricated Rudder Rigging Tool 5F14 95 12 Suggested Design f...

Page 18: ...tanceTable 2B23 2402 AlternatorTestSpecifications 2C10 2403 AlternatorBeltTension 2C11 2404 HydrometerPercentageGuide 2C13 2701 Troubleshooting SurfaceControls 2D16 2702 ControlCableRiggingTensionVs Temperature 2E3 2801 Troubleshooting FuelSystem 2H1 2802 FuelCellRepairEquipmentLists 2H17 2803 WearLimitsForElectricFuelPump 218 2804 FuelQuantitySenderResistanceLimits 2112 2805 FuelQuantityIndicator...

Page 19: ...oplastic Repairs 3K6 5501 Elevator Balance Weight 4C9 5502 Rudder Balance Weight 4C15 5701 Aileron Balance Weights 4D14 6101 Propeller Specifications 4E6 6102 Troubleshooting Chart Engine Synchrophaser 4E13 7101 Troubleshooting Engine 4F4 7301 Troubleshooting Fuel Pressure Gauge 4G7 7302 Troubleshooting Fuel Flow Gauge 4G8 7401 Coupling Torques 4H5 7701 Troubleshooting Manifold Pressure Indicator ...

Page 20: ...umableMaterials FlareFittingTorqueValues Recommended NutTorques ThreadLubricants DecimalConversion TorqueConversion ConversionTables Decimal Millimeter Equivalents of DrillSizes CircuitLoadChart ElectricalWireCoding ElectricalSymbols GRIDNO 5B4 5B10 5B1I 5B13 5B14 5B15 5B17 5B22 5B23 5C3 5C4 Introduction Page 18 Revised February23 1982 1A20 ...

Page 21: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1A21 ...

Page 22: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1A22 ...

Page 23: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1A23 ...

Page 24: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1A24 ...

Page 25: ...CHAPTER AIRWORTHINESS LIMITATIONS lB1 ...

Page 26: ...ENANCEMANUAL CHAPTER4 AIRWORTHINESSLIMITATIONS TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT SUBJECT GRID NO EFFECTIVITY 1B3 1B3 4 00 00 4 00 01 AIRWORTHINESS LIMITATIONS General 1B2 4 Cont Effec Page 1 Issued September2 1981 ...

Page 27: ... Parts 91 163 and 135of the Federal AviationRegulations NOTE Refer to the LIMITATIONS in the Pilot s Operating Handbook and FAA Approved Flight Manual or a detailed delineation of the flight 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 4 00 01 1B3 Page4 01 Issued September2 1981 ...

Page 28: ...CHAPTER TIMELIMITS MAINT CHECKS 1B4 ...

Page 29: ...ns 1B16 1R2 82 5 21 07 Away From Home Station Requirements 1B17 1R2 82 5 21 08 Event 1 IB18 3R 7 84 5 21 09 Event 2 1C3 2R 11 83 5 21 10 Event 3 1C11 2R 11 83 5 21 11 Event 4 1C19 2R 11 83 5 21 12 Special Inspection 1D2 2R 11 83 5 21 13 Special Inspection as Required Upon Condition 1D4 1R 2 82 5 21 14 Operational Inspection 1D5 1 R 10 82 5 21 15 Event Inspection Record and Sign Off Sheet 1D7 1 R 2...

Page 30: ...eairplaneevery200hours onecompletecycle Also includedarevariousspecialinspections requiredatspecificservicetimesotherthanthosearrivingonthe 50hourevents This type of inspectionwas selectedby PiperAircraft Corporationto providegreaterutilizationof the aircraftthroughtheuse of thisplannedinspectionprogram NOTE In addition to inspection intervals required in Chart 501 a preflight check must beperform...

Page 31: ...rvice The owner should periodically check with his service representative or A P mechanic to see whether he has the latest issued AD against his airplane The owner is solely responsible for keeping up with ADs Piper Aircraft Corporation takes a continuing interest in having the owner get the most efficient use from his airplane and keeping it in the best mechanical condition Consequently Piper Air...

Page 32: ...sandService SparesLetters Thisserviceis offeredto interestedpersonssuchas owners pilotsandmechanicsat a nominal fee and may be obtainedthroughPiperAirline Division Ownersresidingoutsideof the United Statesare urged to subscribeto thisservice sincePipercan seldomotherwiseobtainthe addressesof foreignowners ServiceProductSupportManualsandrevisionsareavailablethrougha PiperServiceCenter THIS SPACEINT...

Page 33: ...duringinspectionswillbeenteredon the DiscrepancyRecord Thepersonconductingthe inspectionwill advisethe Ownerand orOperatorof thediscrepancies foundduringtheinspectionandentered on the DiscrepancyRecord Discrepancieswhichaffect the airworthinessof the airplanewill require the necessarycorrectiveactionto beaccomplished beforetheairplaneis returnedto service The PiperContinuousInspectionhas thefollow...

Page 34: ...s made in the Event Record and Cycle Inspection Record which are the running logs or current status of the aircraft inspections Each event will be recorded in the Event Inspection Record and Sign Off Sheet EVENT 1 To be performed at the 50 250 450 650 850 Flying Hour Intervals Consists of 1 Left Propeller Detailed 2 Left Engine Detailed 3 Left Turbocharger Detailed 4 Right Propeller Routine 5 Righ...

Page 35: ...ht Propeller Detailed 2 Right Engine Detailed 3 Right Turbocharger Detailed 4 5 6 7 8 9 10 11 Left Propeller Routine Left Engine Routine Left Turbocharger Routine Left Wing Routine Landing Gear Routine Fuselage Detailed Cockpit Routine Lubrication 3 Special Inspections inspections to be performed and recorded with the appropriate Event Inspection 4 Operational Inspection to be performed prior to e...

Page 36: ... or manufacturer s mandatory inspections may have to be accomplished beforefurtherflight in whichcase theircomplianceshouldbe recordedon theappropriate record 8 ServicePublicationComplianceRecord is usedto recordthe complianceof all manufacturer s service publications andcontainsthe followinginformation 1 Nameof Manufacturer 2 Publication Bulletin Letter etc 3 Number 4 ComplianceDate 5 AircraftHou...

Page 37: ...ection This ten l0 percent shall only be used to return the aircraft back to the maintenance base when inspection intervals fall due and the aircraft is away from home base 6 Tests Operation of aircraft components appliances or systems to evaluate functional performance 7 Operational Test This test is used to ascertain that a system component is in operable condition and can be performed with the ...

Page 38: ...ltest to ascertainthat thesystemis functioningproperly Thisperson willlogbenchtestandoperationaltestinthe permanentaircraftrecords Serviceable partsthatwere issuedto thecomponentwillbefiledintheaircraftpermanentrecords 10 Maintenance The word maintenance as defined by FAR I means inspection overhaul repair preservation andthereplacementof parts but excludespreventivemaintenance However where refer...

Page 39: ...licate 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 page The previous information sheet will be lef...

Page 40: ...onsibilityof the manufacturer No changescanbe madetothisInspectionProgramunlesspriornoticeis givento theresponsibleF A A District Office who in turn mustapproveof the changepriorto its enactment A record of all revisionswill be maintainedby theowner operator on therevisionof thismanual RECORDOF NORMAL REVISIONS REV NO REV APPROVALDATE PAGENO INSERTEDBY DATE 1B16 5 21 06 Page5 11 Revised February 2...

Page 41: ...craft The resultsof the inspectionwill be notedon the properSign Off Sheetswhichare thenbroughtbackto 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 corrected by either I or 2 a...

Page 42: ...ycircuitbeforeworkingon engine 1 Removeenginecowl 2 Cleanandcheckcowlingforcracks distortion andlooseor missingfasteners 3 Drainoilsump Drainwhileengineis warm 4 Cleansuctionoilstraineratoilchange checkstrainerforforeignparticles 5 Changefullflow cartridgetype oilfilterelement inspectelementfor foreignparticles 6 Inspectoil temperaturesenderunitforleaksandsecurity 7 Inspectoillinesandfittingsfor l...

Page 43: ...iblefuellines 30 Inspectfuelsystemforleaks 31 Inspectfuelpumpfor leakageunderpressure 32 Replacehydraulicfilterelement checkelementforcontamination 33 Inspecthydraulicpumpandgasketfor leaks ReplacepumpatengineT B O 34 Inspectconditionof pneumaticpumpandsecurityof lines 35 Inspectthrottle alternateair injector mixtureandpropellergovernorcontrolsfortraveland operatingcondition 36 Inspectexhauststack...

Page 44: ... Inspectconditionof deicerboots ifapplicable 5 Inspectpropellerairpressure atleastoncea month RIGHT ENGINE ROUTINE seechapter 71 maintenance manual refer toVSP 69 1 Removeenginecowl 2 Cleanandinspectcowlingforcracks distortion looseor missingfasteners 3 Drainoilsump Drainwhileengineis warm 4 Inspectsuctionoil strainerat oilchange Inspectstrainerforforeignparticles 5 Changefullflow cartridgetype oi...

Page 45: ...ctinductionandexhaustcomponentsfor wornor damagedareas looseclamps cracksandleaks 6 Inspectfluidpowerlinesforleaksandsecurity 7 Inspectfor oilleakagefromcontroller 8 Inspectconditionof cowlfastenerlockedindicatorstripes Touch upor restoreas necessary Referto MaintenanceManual Chapter71 9 Reinstallenginecowl RIGHT WING ROUTINE SeeChapter 57 Maintenance Manual 1 Checksurfaces skinsandtip fordamagean...

Page 46: ...on 20 Inspectanti retraction systemoperation 21 Inspectactuatingcylinderforleaksandsecurity 22 Inspectpositionindicatingswitchesandelectricalwiresforconditionandsecurity LEFT GEAR 1 Checkoleostrutsforproperextension Checkfor properfluidlevelas required 2 Inspectwheelfor alignment 3 Inspecttirefor cuts unevenor excessivewearandslippage 4 Removewheel clean inspectandrepackbearingsperlubricationchart...

Page 47: ...gear inspect operation 17 Retractgear inspectdoorsforclearanceandoperation 18 Inspectactuatingcylinderfor leaksandsecurity 19 Inspectpositionof indicatingswitchesandelectricalleadforsecurity 20 Removeairplanefromjacks EMPENNAGETAIL ROUTINE SeeChapter 27 Maintenance Manual 1 Inspectverticalfinandruddersurfacesfordamage andattachmentsforoperation 2 Inspecthorizontalstabilizerandelevatorsurfacesfor d...

Page 48: ...felectricfuelpumps 5 Checkinletair ductfor operation NOSE 1 Checkoperationof landingandtaxi lights 2 Checkoperationof pitotheat RIGHT WING 1 Checkinletairductfor operation 2 Checkoperationof electricfuelpumps 3 Checkpropdeicerboots 4 Checkheatedstallwarningindicator 5 Checkwingtipnavigationandstrobelights TAIL 1 Checkstrobelight recognitionlight andnavigationlightfor operation 2 Checklogolight for...

Page 49: ...rol rod ends 2 Rudder and rudder trim tab hinges and control rod ends 3 Rudder horn cable ends 4 Elevator bellcrank pivot bolts and cable ends FUSELAGE 1 Lower cabin door latch hinges and step mechanism 2 Upper cabin door hinges and latch 3 Cargo door hinges and latch If installed 4 Pilot door latch and hinges COCKPIT 1 Control wheel rollers link and flexiblejoint 2 Rudder pedals torque tube beari...

Page 50: ... EVENT 1 cont Cleanthe followingwithquickdryingsolventandlubricatewithMobilBearingGrease77or MobilusEP2 MAINWHEELBEARINGS NOSEWHEELBEARINGS REMOVETHE AIRCRAFTFROM JACKS 1 Replaceall inspectionplatesandcovers 2 Signofflubricationsectionof checkform THIS SPACEINTENTIONALLYLEFT BLANK 1C2 5 21 08 Page5 21 Revised February23 1982 ...

Page 51: ...e 1 Removeenginecowl 2 Clean and check cowling for cracks distortion and loose or missing fasteners 3 Drain oil sump Drain while engine is warm 4 Clean suction oil strainer at oil change check strainer for foreign particles 5 Change full flow cartridge type oil filterelement inspect element for foreign particles 6 Inspect oil temperature sender unit for leaks and security 7 Inspect oil lines and f...

Page 52: ...pfor leakageunderpressure 32 Replacehydraulicfilterelement checkelementfor contamination 33 Inspecthydraulicpumpandgasketfor leaks ReplacepumpatengineT B O 34 Inspectconditionof pneumaticpumpandsecurityof lines 35 Inspectthrottle alternateair injector mixtureandpropellergovernorcontrolsfor traveland operatingcondition 36 Inspectexhauststacksandgaskets Replacegasketsas required 37 Inspectbreathertu...

Page 53: ...ecowl LEFT PROPELLER ROUTINE See chapter 61 maintenance manual 1 Inspectspinnerandbackplate 2 Inspectbladesfor nicksandcracks 3 Checkforgreaseandoil leaks 4 Inspectconditionof deicerboots ifapplicable 5 Inspectpropellerairpressure atleastonceamonth LEFT ENGINE ROUTINE See chapter 71 maintenance manual Refer to VSP 69 1 Removeenginecowl 2 Cleanandinspectcowlingfor cracks distortion looseor missingf...

Page 54: ...inductionandexhaustcomponents for wornor damagedareas looseclamps cracksandleaks 6 Inspectfluidpowerlinesfor leaksandsecurity 7 Inspectoilleakagefromcontroller 8 Reinstallenginecowl LEFT WING DETAILED SeeChapter 57Maintenance Manual 1 Removeinspectionplatesandpanels CAUTION The accesspanel on the upper outboardsurface of the wing which coversthe Flux Detectoris secured with brass screws and must b...

Page 55: ...ctactuatingcylinderfor leaksandsecurity 8 Inspect condition of up and downlock springs 9 Wipe exposed strut with clean cloth and hydraulic fluid MIL H 5606 RIGHT GEAR 1 Check oleo strut for proper extension 2 Inspect tire for cuts uneven or excessive wearand slippage 3 Check tire pressure psi 4 Inspect brake and hydraulic lines for damage and security 5 Check gear legfor damage 6 Inspect gear door...

Page 56: ...eChapter32 Maintenance Manual 8 Inspectcontrolwheels column pulleysandcablesfordamage operationandfulltravel See Chapter27 MaintenanceManual 9 Inspectinstrumentsandattachmentsfor security propermarkingsandplacards Referto Pilot s OperatingManual 10 Inspectcompasscorrectioncardforcorrectdata Recalibrateasrequired 11 Inspectcommunications systemsfor conditionandsecurityofswitchesandknobs 12 Inspectp...

Page 57: ...ds 5 Uplockbushings NOSE GEAR 1 Steering arm rollers bellcrank retraction rod ends and steering rod ends 2 Nose gear door actuator retraction rod end and cylinder rod end 3 Uplockhookanduplockrod or cable 4 Doorhinges 5 Upperandlowertorquelinkconnectingboltandshimmydampener 6 Uplockbushing 7 Forwardbaggagedoorhingesandlatches FUSELAGE 1 Lower cabin door latch hinges and step mechanism 2 Uppercabin...

Page 58: ...t Left Right Right EVENT 2 cont NOSEGEAR O 1 Draglinkassemblyandidlerlink O 2 Upperandlowertorquelink O 3 Gearhousingbushings O 4 Cambearingsurface specialfittingrequired O 5 Centersteeringsupportbearing specialfittingrequired THIS SPACEINTENTIONALLYLEFT BLANK 1C10 5 21 09 Page5 29 Revised February23 1982 ...

Page 59: ...and loose or missing fasteners 3 Drain oil sump Drain while engine is warm 4 Clean suction oil strainer at oil change check strainer for foreign particles 5 Change full flow cartridge type oil filter element Inspectelement for foreign particles 6 Inspect oil temperature sender unit for leaks and security 7 Inspect oil lines and fittings for leaks security chafing dents and cracks 8 Inspect cylinde...

Page 60: ...ntforcontamination 33 Inspecthydraulicpumpandgasketfor leaks ReplacepumpatengineT B O 34 Inspectconditionof pneumaticpumpandsecurityof lines 35 Inspectthrottle alternateair injector mixtureandpropellergovernorcontrolsfortraveland operatingcondition 36 Inspectexhauststacksandgaskets Replacegasketsasrequired 37 Inspectbreathertubefor obstructions andsecurity 38 Inspectcrankcaseforcracks leaks andsec...

Page 61: ...ce a month RIGHT ENGINE ROUTINE Seechapter 71maintenance manual Referto VSP 69 1 Removeenginecowl 2 Cleanandinspectcowlingfor cracks distortion looseor missingfasteners 3 Drainoil sump Drainwhileengineis warm 4 Inspectsuctionoil strainerat oilchange Inspectstrainerfor foreignparticles 5 Changefullflow cartridgetype oil filterelement Inspectforforeignparticles 6 Fillenginewithoilperlubricationchart...

Page 62: ...allenginecowl RIGHT WING DETAILED SeeChapter 57 MaintenanceManual O 1 Removeinspectionplatesandpanels 2 Inspectsurfaces skinsandtipsfordamageandlooserivets 3 Inspectaileronandtab hingesforsecurityof attachment andoperation 4 Inspectaileronandtrimcables pulleysandbellcrankfordamageandoperation 5 Inspectall rod endbearingsfor freedomof ballmovement Usea 10Xmagnifyingglassto checkthread endof bearing...

Page 63: ...nd spring tension 16 Inspect gear doors and attachments for security 17 Check warning horn and light for operation 18 Retract gear inspect operation 19 Retract gear inspect doors for clearance and operation 20 Inspect anti retraction system operation 21 Inspect actuating cylinder for leaks and security 22 Inspect position indicating switches and electrical wires for condition and security LEFT GEA...

Page 64: ...ionandadjustment 0 13 Inspectnosegearlockrod or cableassemblyforcorrosion freedomofmovementandspring tension 0 14 Inspectgeardoorsandattachments 15 Checkgearwarninghornandlightfor operation 16 Retractgear inspectoperation 17 Retractgear inspectdoorsfor clearanceandoperation 18 Inspectactuatingcylinderfor leaksandsecurity 19 Inspectpositionof indicatingswitchesandelectricalleadfor security 20 Remov...

Page 65: ...ment dateor time 25 Reinstallinspectionplatesandpanels CABIN MAIN DETAILED 1 Checkthattheappropriate certificatesarein theairplaneandproperlydisplayed 2 Checkupholsteryfortears 3 Checkseats seatbeltsforsecurityof bracketsandbolts 4 Checkalllightsandair ventsfor damage 5 Inspectoxygenoutletsandmasksfordefectsandcorrosion ifinstalled 6 Checkoxygensystemforoperation ifinstalled 7 Checkportablefireext...

Page 66: ...es and latch 0 3 Cargo door hinges and latch if installed 4 Pilot door latch and hinges COCKPIT 1 Control wheel rollers link and flexible joint 0 2 Rudder pedals torque tube bearings and block control cable ends and brake cylinder ends 3 Fuel panel control levers With All Purpose Slip Spray DuPont No 6611 lubricate the following WINGS 0 0 1 Flap tracks With aircraft and instrument grease MIL G 238...

Page 67: ... Remove engine cowl 2 Clean and check cowling for cracks distortion and loose or missing fasteners 3 Drain oil sump Drain whileengine is warm 4 Clean suction oil strainer at oil change check strainer for foreign particles 5 Change full flow cartridge type oil filter element inspect element for foreign particles 6 Inspect oil temperature sender unit for leaks and security 7 Inspect oil lines and fi...

Page 68: ...pumpfor leakageunderpressure 32 Replacehydraulicfilterelement checkelementfor contamination 33 Inspecthydraulicpumpandgasketfor leaks Replacepumpat engineT B 0 34 Inspectconditionof pneumaticpumpandsecurityof lines 35 Inspectthrottle alternateair injector mixtureandpropellergovernorcontrolsfor traveland operatingcondition 36 Inspectexhauststacksandgaskets Replacegasketsas required 37 Inspectbreath...

Page 69: ...ecowl 14 Reinstallenginecowl LEFT PROPELLER ROUTINE Seechapter 61 maintenancemanual 1 Inspectspinnerandbackplate 2 Inspectbladesfornicksandcracks 3 Checkforgreaseandoilleaks 4 Inspectconditionof deicerboots ifapplicable 5 Inspectpropellerairpressure atleastoncea month LEFT ENGINE ROUTINE seechapter 71 maintenancemanual refer to VSP69 1 Removeenginecowl 2 Cleanandinspectcowlingfor cracks distortion...

Page 70: ...nandexhaustcomponentsforwornor damagedareas looseclamps cracksandleaks 6 Inspectfluidpowerlinesfor leaksandsecurity 7 Inspectoilleakagefromcontroller 8 Inspectconditionof cowl fastenerlockedindicatorstripes Touch upor restoreas necessary Referto MaintenanceManual Chapter71 9 Reinstallenginecowl LEFT WING ROUTINE SeeChapter 57 MaintenanceManual 1 Inspectsurfaces skinsandtip fordamageandlooserivets ...

Page 71: ...ttachmentsforcracksandcorrosion 6 Inspectactuatingcylinderfor leaksandsecurity 7 Inspectconditionof up anddownlocksprings 8 WipeexposedstrutwithcleanclothsoakedinhydraulicfluidMIL H 5606 FUSELAGEFORWARD DETAILED SeeChapter 53 Maintenance Manual 1 Removeinspectionplatesandpanels 2 Inspectbaggagedoor latch hinges doorajarswitchandcompartmentlightfor wear properrigging andoperation 3 Checkfluidinbrak...

Page 72: ...al 11 Inspect cabin door for damage condition of door seal and proper rig and operation 12 Replace inspection plates panels and floor panels 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 control wheel for operation See Special Inspection 5 Check pilot and copilot seat belts and shoulder harnesses f...

Page 73: ...nd latch if installed 4 Pilot door latch and hinges COCKPIT 1 Control wheel rollers link and flexiblejoint 2 Rudder pedals torque tube bearings and block control cable ends and brake cylinder ends 3 Fuel panel control levers With All Purpose Slip Spray DuPont No 6611 lubricate the following WINGS 1 Flap tracks With aircraft and instrument grease MIL G 23827 lubricate the following MAIN LANDINGGEAR...

Page 74: ...tem inline filters 3 Replace rubber engine mount bushings See Note 1 LEFT AND RIGHT MAIN GEAR 1 Inspect torque link assembly bolts and bushings rebush as required 2 Inspect drag and side brace link assembly and bolts replace as required NOSE GEAR 1 Inspect torque link assembly bolts and bushings rebush as required 2 Inspect drag link assembly and bolts replace as required EMPENNAGE 1 Cleanandlubri...

Page 75: ... at engine T B or 4 years per latest Bendix S B 586 2 Overhaul or replace fuel pumps engine driven and electric per latest revision of Lycoming Service Bulletin No 240 for engine driven O 3 Overhaulor replacehydraulicpumpat engineT B O O 4 Overhaulor replacepneumaticpumpatengineT B O 5 Overhaulor replacealternatorat engineT B O 6 Overhaulor replacestarteratengineT B O 7 Overhaulor replacefuelinjec...

Page 76: ...ings 3 Wingsparwebs bulkheads nacelleskinsandattachments firewallskinandwingandfuselage stringersfor anysignsof overstressor damage 4 Apossiblealignmentchecktoclarifyanydoubtof damage SEVERE TURBULENCEINSPECTION The same items and locationsshould be checkedas stated in Hard or OverweightLandingsalong withthe following 1 Topandbottomfuselageskinsfor looseor missingrivetsandwrinkledskins 2 Empennage...

Page 77: ...lapoperationandindication 11 Checkheateroperation 0 12 Checkairconditioneroperation ifinstalled 13 Checkpropellerdeiceroperation 14 EngineRunUp a Propellerandmixturelevers fullforward b Throttle 1500RPM c Propellerfeathercheck maximum500RPMdecrease d Throttle 2300 RPM e Magneto check 175 RPM maximum drop 50 RPM decrease f Propellergoverningcheck g Alternatoroutputcheck h Checkall enginetemperature...

Page 78: ...O PROPELLERSERIALNO Left Left Right Right OPERATIONAL INSPECTION cont POST INSPECTIONRUNUP O 1 Returnaircrafttomaintenance area O 2 Checkengineforgeneralcondition fuelandoil leaks O 3 Reinstallenginecowlings THIS SPACEINTENTIONALLYLEFT BLANK 1D6 5 21 14 Page5 49 Revised February23 1982 ...

Page 79: ...ice Manuals and Publications 2 Work order column is applicable only to FAA approved repair stations 3 Always check and use only current information 4 The signatures signify that this aircraft has been thoroughly inspected and found airworthy in accordance with all current Federal AviationRegulations Piper Service Manuals and Publications also that appropriate entries have been made in the aircraft...

Page 80: ...1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4 INSP 850 900 950 1000 1050 1100 1150 1200 1250 1300 1350 1400 1450 1500 1550 1600 1650 1700 1750 1800 1850 1900 1950 2000 2050 2100 2150 2200 2250 2300 2350 2400 A C TIME DATE W O SIGNATURE CERTIFICATE 1D8 5 21 15 Page5 51 Revised February 23 1982 ...

Page 81: ...TENANCEMANUAL EVENT INSP 1 2450 2 2500 3 2550 4 2600 1 2650 2 2700 3 2750 4 2800 1 2850 2 2900 3 2950 4 3000 A CTIME DATE W O SIGNATURE CERTIFICATE THIS SPACEINTENTIONALLYLEFT BLANK lD9 5 21 15 Page5 52 Revised February 23 1982 ...

Page 82: ...RADIOSTATION F C C LICENSESINAIRCRAFTANDPROPERLYDISPLAYED 6 AIRCRAFT EQUIPMENT LIST WEIGHT AND BALANCE FAA FORM 337 IF APPLICABLE AREINAIRCRAFTANDINPROPERORDER 7 APPLICABLE MANUFACTURER S SERVICE INFORMATIONHAS BEEN COMPLIED WITH 8 APPLICABLE FAAAIRWORTHINESS DIRECTIVES ARECOMPLIEDWITH 9 PIPERCONTINUOUS INSPECTION RECORDSINORDERANDPROPERLY SIGNEDOFF 10 OUTSTANDINGCONDITIONSHAVEBEEN CORRECTEDAS LIS...

Page 83: ...SERIALNUMBER REGISTRATION NUMBER ENGINESERIALNO Left Rignt PROPELLER SERIALNO Left Right DISCREPANCY RECORD DISCREPANCY AIC HOURS SIGNATURE DATE CORRECTIVEACTION SIGNATUREAND CERTIFICATENO DATE ...

Page 84: ...DISCREPANCY RECORD DISCREPANCY A C HOURS SIGNATURE DATE CORRECTIVE ACTION SIGNATURE AND W O CERTIFICATE NO DATE ...

Page 85: ...ER REGISTRATIONNUMBER ENGINE SERIAL NO Left Rtgnt PROPELLER SERIAL NO Left Right SERVICE PUBLICATION COMPLIANCE RECORD MANUFACTURE PUBLI CATION NUMBER COMPLI A C HOURS ANCE DATE WO NO SIGNATURE AND CERTIFICATE NO ...

Page 86: ...SERVICEPUBLICATION COMPLIANCE RECORD MANUFACTURE PUBLI CATION NUMBER COMPLI A CHOURS ANCEDATE WO NO SIGNATURE ANDCERTIFICATE NO ...

Page 87: ...SERIAL NUMBER REGISTRATION NUMBER ENGINE SERIAL NO PROPELLER SERIAL NO Left Left Rignl Right FAA AIRWORTHINESS DIRECTIVESCOMPLIANCE RECORD ...

Page 88: ...SERIALNUMBER REGISTRATION NUMBER ENGINESERIAL NO PROPELLER SERIALNO Left Left Rignt Right DATE A CHRS RECOVERED PART SERIAL INSTALLPART SERIAL SIGNATUREANDCERTIFICATE ...

Page 89: ...ERNAL POWER RECEPTACLE 14 NOSELANDING GEAR 15 HYDRAUUC LINES ELECTRICAL LEADS 16 ELECTRICAL CONNECTORS LINECONNECTORS FRONT SPARATTACHMENT 17 ELECTRICAL CONNECTORS LINES 18 FUELPUMP FUELFILTER CROSSFEED VALVE EMERGENCY SHUTOFF VALVE 19 FUELFILTER BOWL 20 SPARSPLCE DEICER PRESSURE SWITCH 21 MAIN SPARATTACHMENT 22 REARSPARATTACHMENT 23 CABINEXHAUST 24 SPARSPLICE 25 BRAKERESERVOIR 26 PULLEY ANDCABLEI...

Page 90: ...DENSER AIROUTLET PRESSURE SYSTEM AIRFILTER STROBE SENSOR IFPROP SYNCHROPHASER IS INSTALLED 15 WINGTIP 16 FREONCONDENSER IF INSTALLED 17 COWLFLAPTRANSMISSION PRESSURE SYSTEM RELIEF VALVE PRESSURE SYSTEM INUNE FILTER FREON CONDENSER IFAIR CONDITIONING IS INSTALLED 18 AILERON CABLEPULLEYS 19 AILERON BELLCRANK 20 FUELCELLCHECK VALVE 21 AILERON CABLEFAIRLEADS 22 AILERON TRIMCABLESRIGHT WINGONLY RUBBLOC...

Page 91: ... EXTERNAL POWER RECEPTACLE ATTACHMENTS 15 CONTROL CABLES PULLEYS AND TURNBUCKLES 16 ONTROLCABLES PULLEYS AND TURNBUCKLESENGINE CONTROL LINES WIRESANDCABLES 17 HYDRAUUC HANDPUMP PNEUMATIC B 18 CONTROL CABLES AND PULLEYS 19 TRIMWARNINGSYSTEM IFINSTALLED 20 AUTOPILOT UNITSROLL PITCH ANDPITCH TRIMSERVOS VOLTAGE DIVIDER ANDGYRO AMPLIFIER CONTROLCABLES WING FLAP MOTOR 21 PITCH SERVO IFINSTALLED 22 CABIN...

Page 92: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 1D20 ...

Page 93: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1D21 ...

Page 94: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1D22 ...

Page 95: ...CHAPTER DIMENSIONS ANDAREAS 1D23 ...

Page 96: ...DAREAS TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 6 00 00 6 00 01 6 00 02 6 00 03 GENERAL DIMENSIONS ANDAREAS StationReferenceLines AccessandInspectionProvisions IEI IE1 IE5 IE5 1D24 6 Cont Effec Page 1 Revised February23 1982 ...

Page 97: ... are showninFigure6 1andlistedinChart601 Theserialnumberplate for the airplaneis locatednearthe tail skid The MAAplate is locatedunderthe lowerfront corner of the entrancedoor Theenginenumberplatesarelocatedon therightsideof theoil sump THIS SPACEINTENTIONALLYLEFT BLANK 1E1 6 00 01 Page6 01 Issued September2 1981 ...

Page 98: ...NOTE Figure6 1 Dimensions 1E2 6 00 01 Page6 02 Revised November17 1983 ...

Page 99: ...4Volt Alternator Prestolite 24 Volt 70Amp VoltageRegulator Lamar Over VoltageRelay Lamar FuelPump LearSiegler PROPELLER Manufacturer Type Hub Blade Diameter GovernorModel Left Right 350 2575 13 000ft 260 2400 20 000ft 210 2200 RefertoPilot sOperatingManual SeeLubricationChart 12qts THO8A6Q 100 130 RSA IOEDI S6LN1209and 1208 S6RN1209and 1208 20 0 016 0 003 0 016 0 006 30a HSR 87LI RHB 36W Refertola...

Page 100: ...al LANDINGGEAR Type ShockStrutType FluidRequired Struts Brakes StrutExtension Staticload NoseWheelTravel MainWheelToe In TurningRadius Min NoseWheel TurningRadius Min WingTip Wheel Nose Wheel Main BrakeType Tire Nose Tire Main TirePressure Nose TirePressure Main Hydraulicallyretractable Combinationairandoil MIL H 5606 3 25 in 40 l Right 400 l Left 5 degrees 25 ft 3 in 49 6ft Cleveland Cleveland Cl...

Page 101: ...ECTIONPROVISIONS RefertoFigure6 3 The access and inspectionprovisionsfor the airplaneare shownin Figure 6 3 The componentsto be servicedor inspectedthrougheach openingis identifiedin the illustrationby the use of an assignedindex referencenumber Allaccessplatesandpanelsaresecuredby eithermetalfastenersor screws CAUTION Before entering the aft section of the fuselage be sure the airplaneis supporte...

Page 102: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL 137 0 22 02 FLAP SPAR 173 59 Figure6 2 StationReferences cont 1E6 6 00 03 Page6 06 Revised February 23 1982 ...

Page 103: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL I Figure6 2 StationReferences cont 1E7 6 00 03 Page6 07 Revised February 23 1982 ...

Page 104: ...YS AND TURNBUCKLES 16 CONTROL CA ES PULLEYS AND TURNBUCKLES ENGINECONTROL LINES WIRESAND CABLES 17 HYDRAUUC HANDPUMP PNEUMATIC BLOWDOWN 1 CONTROL CALES ANDPULLEYS 19 TRIMWARNINGSYTEM IF INSTALED 20 AUTOPILOT UNITS ROLL PTCHANDPITCH TRIMSERVOS VOLTAGE DIVIDERANDGYRO AMPIFIER CO L CABLE WING LRAP MOTOR 21 PITCH SERVO IFINSTALLED 22 CABINEXHAUST DOORMECHANISM 23 CONTROL ANDTRIMCABLESANDPULEYS SE6TATT...

Page 105: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL Figure6 3 AccessPlatesandPanels cont 1E9 600 03 Page 6 09 Issued September2 1981 ...

Page 106: ...NSER AIROUTLET PRESSURE SYSTEM AIR FILTER STROBE SENSOR IFPROP SYNCHROPHASER IS INSTALLED 16 WINGTIP 16 FREONCONDENSER IF INSTALLED 17 COWLFLAPTRANSMISSION PRESSURE SYSTEM REUEF VALVE PRESSURE SYSTEM INUNE FILTER FREON CONDENSER OFAIR CONDITIONING IS INSTALLED 18 AILERONCABLEPULLEYS 19 AILERONBELLCRANK 20 FUELCELLCHECK VALVE 21 AILERONCABLEFAIRLEADS 22 AILERONTRIMCABLESRIGHT WINGONLY RUB LOCKSANDF...

Page 107: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1E11 ...

Page 108: ...PIPERAIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLYLEFT BLANK 1E12 ...

Page 109: ...CHAPTER LIFTINGANDSHORING 1E13 ...

Page 110: ...NTENANCEMANUAL CHAPTER 7 LIFTING ANDSHORING TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT 7 00 00 7 10 00 GENERAL JACKING IE15 IE15 EFFECTIVITY 2R 11 83 1E14 17 ContJEffec Page 1 Revised November17 1983 ...

Page 111: ...oceedas follows 1 Placethewingjacksunderthewingjack pads 2 Positionthetailsupportstandunderthetailskidandattachthestandto thetailskid 3 Positionthenosejackandjack padtoolP N 71973 2underthenosesectionbetweenstations1 75and 19 35 4 Raisealljacksevenlyuntilallthree wheelsclearthefloor CAUTION If thenose jack andjack padtoolarenotusedbesureto apply sufficient tail support ballast otherwise the airpla...

Page 112: ...CHAPTER LEVELINGAND WEIGHING 1E16 ...

Page 113: ...NTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 8 00 00 8 10 00 8 20 00 8 20 01 8 20 02 8 20 03 GENERAL LEVELING WEIGHTANDBALANCEDATA Weighing PreparationForWeighing Weighing The Aircraft 1E18 1E18 1E19 1E19 1E19 1E20 1E17 8 Cont Effec Page Revised February23 1982 ...

Page 114: ...used 1 To longitudinallylevel the airplane partiallywithdrawthe two levelingscrewslocatedon the right sideof the fuselagenose sectionat station57 00and 35 00 Placea spirit levelon thesescrewheads anddeflatethe nosewheeltire or adjustthejacks untilthebubbleof theleveliscentered 2 To laterallylevel the airplane placea spiritlevel across the two center seat rails of the cabin and deflate the tire on ...

Page 115: ... tanks but it is notrecommended andcaremustbetaken toverifyall fueltanksare exactlyfull andnotpartiallyunderor overfull fueltoppedoff to bottomof filler neckwithairplanein levelattitude SeeChapter12for fuelcapacities Temperaturewillhaveaneffectwhenweighingtheairplane especiallyif fueltanksarefull andtherefore willaffectthebalance The airplaneandscalesshouldbeallowedapproximately two hourstostabili...

Page 116: ...desof allthree wheels WARNING If wheelsare not blocked the airplane could rolloff scalesand causeseriousinjury and damage 4 Releaseemergencybrake 5 If theairplaneis tobeweighedforweightandbalancecomputations levelthe airplaneperinstructions givenin theparagraphtitled Leveling 6 Recordweightson Weightand BalanceReport Insure TARE weight weightof chocks blocksor otherweighingaids is alsoenteredtoobt...

Page 117: ...CHAPTER TOWING ANDTAXIING 1E21 ...

Page 118: ...NANCEMANUAL CHAPTER9 TOWINGANDTAXIING TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 9 00 00 9 10 00 9 20 00 GENERAL TOWING TAXIING 1E23 IE24 1E24 1E22 9 Cont Effec Page Revised February 23 1982 ...

Page 119: ...ilot or otherresponsiblepersonon thetowturninglimitsof the nosegear enginestartingandshutdownprocedures and anyother systemfunctionswhich may be requiredto properlyand safelymovethe airplane Refer to Figure9 1 WHEEL BASE 10FT 8 IN NOSEWHEEL TRAVEL 40 Rght 40 Left Figure9 1 TurningRadiusandLimits 1E23 9 00 00 Page9 01 Revised November17 1983 ...

Page 120: ...doorsare closed Linesshouldbelongenoughtoclearthe nose and ortailby notlessthan 15feet anda qualifiedpersonto ridein thepilot sseat tomaintaincontrolby useof thebrakesandnosewheelsteering A collapsible towbar is located in the nose baggagecompartmentfastened to the rear bulkhead The towbaris removedbypullingitfromthefrictionretainers TAXIING When it is certain that the propellerback blast and taxi...

Page 121: ...CHAPTER PARKING ANDMOORING 1F1 ...

Page 122: ...NCEMANUAL CHAPTER 10 PARKINGANDMOORING TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 10 00 00 10 10 00 10 20 00 GENERAL PARKING MOORING 1F3 1F3 IF3 1F2 10 Cont Effec Page 1 Revised February 23 1982 ...

Page 123: ...above conditionsexist it is recommendedthat chocks be used to block the wheelsratherthansettingbrakes 3 Inserttheinternalcontrollock MOORING The airplane is moored to insure its immovability protection and security under various weather conditions Thefollowingproceduregivestheproperinstructionsformooringthisairplane 1 Headthe airplaneintothewind ifpossibleandcloseenginecowlflaps 2 Blockthewheelswi...

Page 124: ...CHAPTER REQUIRED PLACARDS 1F4 ...

Page 125: ... 1020 MAINTENANCEMANUAL CHAPTER 11 REQUIREDPLACARDS TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 11 20 00 PLACARDS ANDMARKINGS IF6 1F5 11 Cont Effec Page 1 Revised February 23 1982 ...

Page 126: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL I PLACARDSANDMARKINGS Figure 11 1 PlacardsandDecals 1F6 11 20 00 Page11 01 Revised February 23 1982 ...

Page 127: ...RESSURE PLACARD INSTRUMENT AIRDECKPRESSURE PLACARD FUELPRESSURE 37 PLACARD ASSEMBLY FUELCONTROL 38 PLACARD FUELVENTCHECKVALVE LEFT PLACARD FUELVENTCHECKVALVE RIGHT 39 DECAL FUELCELLQUANTITY MAIN 40 PLACARD FUELVENT CHECKVALVE AUXILIARY LEFT PLACARD FUELVENTCHECKVALVE AUXILIARY RIGHT 41 DECAL FUELCELLCAPACITY AUXILIARY 42 PLACARD THROTLE CONTROL 43 PLACARD PROPELLER CONTROL 44 PLACARD MIXTURE CONTR...

Page 128: ...CHAPTER SERVICING 1F8 ...

Page 129: ...15 Application of TireRubberProtectiveAgent 1F16 A 11 83 12 10 16 HydraulicSystem IF16 12 10 17 FillingHydraulicSystemReservoir IF17 12 10 18 Propellers IF17 12 10 19 EngineLubrication 1F17 12 10 20 FillingOilSump IF18 12 10 21 DrainingOilSump IF18 12 10 22 OilFilter FullFlow IFI8 12 10 23 OilScreens Suction IF18 12 10 24 Recommendations ForChangingOil IF19 12 10 25 Spectrometric OilAnalysis IF19 ...

Page 130: ... SUBJECT EFFECTIVITY 12 20 00 12 20 09 12 20 10 12 20 11 12 20 12 12 20 13 12 20 14 SCHEDULED SERVICING cont Removalof InductionAirFilter InstallationOfInductionAirFilter AlternateAir Door OxygenSystem OxygenSystemSafetyPrecautions FillingOxygenCylinder IG5 IG5 IG6 1G6 IG6 IG7 1F10 12 Cont Effec Page 2 Issued September2 1981 ...

Page 131: ...dfuelcellsof moistureandforeignmatter drains are incorporatedinthe bottomof each filterbowl inthesystemcrossfeedlineandtheinboardendof eachfuel cell 1 To flush either filterbowl open the accessdoor locatedon the panel betweenthe undersideof the wing and fuselage Pushup on the armsof the drain valvefor a few secondswiththe fuel selector valveon onecell thenchangethe selectorvalveto theothercellandr...

Page 132: ...HOCK STRUT LANDR 11 FILTER PRESSURE LINE LEFT 16 FUEL DRAIN LEFT OUTBOARD IFINSTALLED 17 FILLER INBOARD FUEL CELLLEFT 18 FILLER OUTBOARD FUEL CELL LEFT IF INSTALLED 19 AIR VALVE RIGHT PROPELLER 20 BATTERY 21 HEATER 22 EXTERNALPOWER SUPLY 23 POWER PACKALL FITTINGS 24 RESEVOIR BRAKE SYSTEM 25 TIRE NOSE 2 FILLER OXYGEN 27 FILLER OLEO SHOCK STRUT NOSE 2 RESERVOIR POWER PACK 29 GAUGE OXYGEN PRESSURE 0 ...

Page 133: ...edperthefollowing procedure 1 Gain access to the brake reservoirscupper open the nose baggagedoor remove the tow bar and screenedradioaccesspanel 2 Clean surfacearoundscupperand adjacentaircraftskin witha suitablesolventtoremoveanyforeign matter 3 Applya beadof sealant 3MEC 750 orequivalent aroundthescupper Particularattentionshould be paidto sealingtheforwardedgeof the scupperatthehingeattachingp...

Page 134: ...rplaneplus full fuel and oil If a strut has less than the requiredinchesexposed determinewhetherit needsair or oil by rockingthe airplane If the airplanesettles to itsnormalpositionwithinonecycleafterthe rockingforceis removed the oleo strut requiresinflating air If the airplanecontinuesto oscillateafter the rockingforce is removed the oleo strutrequiresfilling oil WARNING Do notreleaseair by remo...

Page 135: ...of the tube in a containerof hydraulicfluidas specified NOTE An air tightconnectionis necesary betweenthe plastictubeand valvestem Withoutsuch a connection a small amount ofair will be sucked into the oleostrut during each sequence resulting in an inordinate amount of air bubblesanda prolongedfilling operation 5 Extendtheoleostrutby pullingdownon the wheel Fluidwill besuckedintotheoleo strut Compr...

Page 136: ...kfor eachhalfounceof weightneeded Markthevalvestemlocationon thetire andtheoppositewheelhalf to assurereassemblyin the same position Removethe wheelfromthe balancestand breakit down andcleanthetire withtoluol Applya coatof patchcementto boththe patchandthe insidecenterof the tire in line withthe chalk marks Whenthe cementhas dried installthe patchesmakingcertain theyare on the centerline of the ti...

Page 137: ...thesupplylinefromtheservicevalvefitting 5 Reinstalltheprotectivecapon thefittingandinstalltheaccesspanel PROPELLERS The bladesshouldbe checkedperiodicallyfor damage Minornicksinthe leadingedgeof bladesshould be filed out andall edgesrounded Daily inspectionshould includeexaminationof blades and spinnerfor visibledamageandgreaseleakage Forfurtherinformation on propellerservicing refertoChapter61 EN...

Page 138: ...of the elementat bothends closeto the metalcaps Then carefullyunfoldthe pleatedelementandexaminethe materialtrappedin thefilterfor evidenceof internalenginedamage such as chipsor particlesfrom bearings In new or newlyoverhauledengines somesmallparticleof metallicshavingsmightbe found theseare generallyof no consequenceandshouldnot beconfused withparticlesproducedby impacting abrasionor pressure Ev...

Page 139: ...normaloildrainperiodsaftersludgeconditionsimprove SPECTROMETRIC OIL ANALYSIS The use of Spectrometricoil analysisis becomingwidespreadin the generalaviationfield It is another useful procedure in the maintenanceof modern reciprocatingaircraftengines The spectrometricmethod requirescompleteunderstandingof the procedures schedulesandinterpretation by the maintenance personnel using this system It mu...

Page 140: ...n regarding the locations time intervals and type of lubricantsusedmaybe foundinLubricationCharts Toinsurethe bestpossibleresultsfromthe applicationof lubricants thefollowingprecautionsshouldbeobserved 1 Use recommendedlubricants Where generalpurpose lubricating oil is specified but unavailable cleanengineoil maybeusedas a satisfactorysubstitute 2 Checkthecomponentstobelubricatedfor evidenceofexce...

Page 141: ...appearson fingers do not addoil If the feltisdry moistenwithlightoil CAUTION Be careful not to add too much oil because the excess will be thrown off during operationandwill causepitting and burning of the magnetopoints LUBRICATIONCHARTS The lubrication charts consist of individual illustrations for the various aircraft systems and each componentto be lubricatedis indicatedby anumberwhichreference...

Page 142: ...ONTAINER OR REFERTO SERVICEMANUAL CHAPTER 12 5 PROPELLER REMOVE ONEOFTHETWOGREASE FITTINGS FOREACHBLADE APPLYGREASE THROUGH FITTING UNTILFRESH GREASE APPEARS AT HOLEOF REMOVED FITTING 6 LUBRICATION POINTS WIPEALL LUBRICATION POINTS CLEANOF OLDGREASE OIL DIRT ETC BEFORE RELUBRICATING NOTES 1 PILOT LUBRICATE TRACKROLLERS ANDSTOP PINS AS REQUIRED 2 WHEELBEARING REQUIRE CLEANING ANDREPACKING AFTEREXPO...

Page 143: ...SEENOTES PIPER AIRCRAFT MA PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL Figure12 3 LubricationChart LandingGear Main 1F23 12 20 04 Page 12 13 Revised November17 1983 ...

Page 144: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL Figure12 4 LubricationChart LandingGear Nose 12 20 04 1F24 Page12 14 Revised November17 1983 ...

Page 145: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL SKETCH B Figure12 5 LubricationChart ControlSystem 1G1 12 20 04 Page 12 15 Issued September2 1981 ...

Page 146: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL COMPONENT SKETCHA SKETCHB SKETCHC Figure12 5 LubricationChart ControlSystem cont 1G2 12 20 04 Page12 16 Issued September2 1981 ...

Page 147: ... NOTE 3 7 FUEL PANEL AND CONTROL LEVERS SEE CAUTION 2 8 COW FLAP TRANSMISSION AND SCREW RIGHT AND LEFT SEESPECIAL INSTRUCTION 3 7 COWL FLAP BELLCRANK BEARINGS RIGHT AND LEFT 10 COWL FLAP CONTROL ROD ENDS RIGHT AND LEFT 11 COWL FLAP HINGE LUBRICANT FREOUENCY MIL G 23827 MIL L 7079 MIL L 7870 100 HRS 100 HRS 100 HRS 100 HRS 50 HRS 500 HRS 500 HRS 100 HRS 100 HRS MIL L 4082 MIL L 7870 MIL L 7870 MIL ...

Page 148: ...3 PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL Figure 12 7 LubricationChart DoorsandSeats 1G4 12 20 04 Page12 18 Issued September2 1981 ...

Page 149: ...hapter39 OPERATIONOF EXTERNALPOWER RECEPTACLE Theexternalpowerreceptacleis locatedon theunderside of the nose sectionbelowthe forwardsideof thebaggagecompartmentdoor Toavoidanydamagetotheairplane selectricalsystem followthe instructions on theaccessdoorof thepowerreceptacle SERVICINGBATTERY Accesstothe batteryis throughthenosebaggagecompartmentpanel Thestainlesssteelbox has a plastic draintubeloca...

Page 150: ...rnishedfroma stationarycylinderlocatedon theupperrightside of the fuselage aft of the rear baggage compartment At 1850psi of pressure the oxygencylinder has a capacityof 48 cubicfeet Serviceandmaintenanceinstructions for theoxygensystemmaybefoundinChapter 35 SafetyPrecautionsandFillingProceduresfollow OXYGENSYSTEMSAFETYPRECAUTIONS The utmostcare mustbe exercisedin servicing handlingand inspectiono...

Page 151: ...thiscylinderhas a pressurelowerthanthe oxygencylinderinthe aircraft do not attempt using it for filling use the storagecylinderthat has a pressurehigherthanthe aircraft scylinder butlowerthanthe others B Open the valve on only the one storagecylinderwith the lowestpressure When the pressure indicatedon the aircraft soxygengaugeandcharginggaugehas becomeequal closethe valveof the storagecylinder th...

Page 152: ...ICATED OXYGENPRESSURES FORGIVENAMBIENT TEMPERATURES AmbientTemperature F IndicatedCylinderPressure Psig 110 1980 100 1935 90 1890 80 1845 70 1800 60 1755 50 1710 40 1665 END THIS SPACEINTENTIONALLYLEFT BLANK 1G8 12 20 14 Page12 22 Issued September2 1981 ...

Page 153: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1G9 ...

Page 154: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLY LEFT BLANK 1G10 ...

Page 155: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1G11 ...

Page 156: ...CHAPTER STANDARD PRACTICES AIRFRAME 1G12 ...

Page 157: ...20 23 01 WindshieldandWindows 1G24 2 82 20 23 02 LandingGear 1H1 2 82 20 23 03 EngineCompartment 1H1 2 82 20 24 00 CORROSIONCONTROL 1H2A2 82 20 24 01 Formsof Corrosion 1H2 A 2 82 20 24 02 ConditionsAffectingCorrosion 1H2 A 2 82 20 24 03 Inspection 1H3 A 2 82 20 24 04 CorrosionRemovalandControl 1H3 A 2 82 20 24 05 AreasPronetoCorrosion 1H5 A 2 82 20 25 00 PAINTING 1H6 A 2 82 20 25 01 PaintingSafety...

Page 158: ...3 20 25 14 20 25 15 20 25 16 20 25 17 20 25 18 20 26 00 20 27 00 Application of Acrylics TrimandRegistrationNumbers PaintSystemCompatibility CommonPaintTroubles Storage PaintingFacilities Waxing Decals 1H19 1H20 IH20 1H21 1H22 1H22 IH22 IH23 EFFECTIVITY A 2 82 A 2 82 A 2 82 A 2 82 A 2 82 A 2 82 A 2 82 A 2 82 1G14 20 Cont Effec Page 2 Revised February23 1982 ...

Page 159: ...ortedduringa tightening operation Anyinstructionsfurnishedby themanufacturer mustbefollowedexplicitly Whenit is necessarytouse a specialextensionor adapterwrenchtogetherwitha torquewrench a simple mathematical equationmustbe workedout toarriveat thecorrecttorquereading Followingis theformulato beused Referto Figure20 1 T Torquedesiredat thepart A Basiclever length fromcenterof wrenchshank to cente...

Page 160: ...20 MAINTENANCEMANUAL T Figure20 1 TorqueWrenchExtension SURFACE CONTROLS IMPROPER TOOL RESULTING IN LOCKEDALL ONLY CORRECT METHOD Figure20 2 MethodofInstallingRod EndBearings 1G16 20 10 01 Page20 02 Issued September2 1981 ...

Page 161: ...ingoutthelockedstemmaydamagethesheets It is recommendedthat a small centerdrill be used toprovidea guidefor a largerdrill on top of therivet stem andthetaperedportionof the stembedrilledawaytodestroythelock SeeViews2 and3 3 Prytheremainderof thelockingcollaroutofthe rivetheadwiththedriftpin SeeView3 4 Drillnearlythroughtheheadof therivet usinga drillthesamesizeas therivetshank SeeView4 5 Breakoffr...

Page 162: ... Althoughthe use of flareless tube fittings eliminatesall tube flaring another operation referredto as presetting isnecessarypriortoinstallationof anew flarelesstubeassemblywhichis performedas follows 1 Cut thetube to thecorrectlength withtheends perfectlysquare Deburrthe insideandoutsideof the tube Slipthe nut thenthe sleeve overthetube Step1 2 Lubricatethe threadsof thefittingandnut SeeFigure20 ...

Page 163: ...TIC RESISTANT HOSE A FLAMEANDAROMATIC RESISTANT HOSE WHITENUMERALS LETTERS ANDSTRIPE RED VIEWSHOWSOPPOSITE SIDESOFHOSE C NON SELF SEALING AROMATIC ANDHEAT RESISTANT HOSE REDNUMERALS ANDLETTERS D FLAME AROMATIC ANDOIL RESISTANT HOSE REDNUMERALS LETTERS ANDSTRIPE E SELF SEALING AROMATIC RESISTANT HOSE HOSEIDENTIFICATION MARKINGS YELLOW GRAY HYDRAULIC DE ICING RED FUEL FUEL ORANGE BLUE PNEUMATIC YELL...

Page 164: ...L L 4343 MIL T 5542 TUBINGSYSTEM HYDRAULIC FUEL OIL PNEUMATIC OXYGEN CONEANGLE SLEEVE LEVEL SLEEVEPILOT TUBESHOULDER TUBE SLEEVE CUTTING EDGE NUT FLARELESS TUBEFITTING STEP 2 STEP3 SLIGHT DEFORMATION PERMISSIBLE 005 INCHMAXIMUM ALUMINUM ALLOYTUBING 015 INCHMAXIMUM CORROSION RESISTANT STEEL TUBING PRESETTING FLARELESS TUBEASSEMBLY Figure20 5 Flareless TubeFittings 1G20 20 10 04 Page20 06 Issued Sep...

Page 165: ...G 6032 LubricatingGrease GasolineandOilResistant RibbonDopeThreadSealant Permacel412 TT A 580 JAN A 669 Anti SeizeCompound WhiteLeadBase NOTE Lubricate engine fittings only with the fluid contained in the particularlines CHART2002 MAXIMUMDISTANCE BETWEENSUPPORTS FORFLUIDTUBING TUBEOD DISTANCE BETWEENSUPPORTS IN IN ALUMINUM ALLOY STEEL 1 8 9 1 2 11 1 2 3 16 12 14 1 4 13 1 2 16 5 16 15 18 3 8 16 1 2...

Page 166: ...eto use a mild soap andwater solution Loosedirt should be flushedawaywithcleanwater Harshabrasiveor alkalinesoaps or detergentscouldcausecorrosionor make scratchesinthefinish Usenaphthaanda softclothto removestubbornoil andgrease Anygoodautomotivewaxcan beusedto preserve the paintedsurfaces Soft cleaning cloth or chamois should be used to prevent scratches when cleaningor polishing Applya heavierc...

Page 167: ...kingor harshrubbing CAUTION Solvent cleaners requireadequate ventilation 2 Cleansidepanelsandseatswitha stiffbristlebrushandvacuumwherenecessary 3 Leathermaterialshouldbecleanedwithsaddlesoapor a mildsoapandwater WOODSURFACES Woodsurfacesmay becleanedwithanygood householdliquidor spraycleanerand polishmanufactured for thispurpose CARPETS Usea small whiskbroomor vacuumtoremovedirt For soiledspots u...

Page 168: ...ter or a 50 50 solutionof isopropanoland water Do not use plastic cleanerson glasswindshields Do not use anyabrasivematerials strongacidsor bases methanol or MethylEthylKetone Useasoftclothor spongeina straightrubbingmotion Donotrubharshly CAUTION Do not use gasoline alcohol benzene carbon tetrachloride thinner or windowcleaningsprays 3 Rinsethoroughlyanddry 4 Aftercleaning plasticsurfacesmay be p...

Page 169: ...ning the engine compartment place a plastic cover or similar material around the pressure pump inlet filter and a strip of tape on the magneto vents 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 tobrush ...

Page 170: ...oatsof zincchromateon eachsurface plus a 003thickpieceof vinyltape ifoneof the surfacesis magnesium 3 IntergranularCorrosionis difficultto detectin itsearly stages Whensevere it causesthe surfaceof themetalto exfoliate flakeor lift 4 StressCorrosionis the resultof sustainedtensilestressesandcorrosiveenvironment It usuallyoccurs in assembliessuch as aluminumalloy bellcrankswithpressed in bushings l...

Page 171: ...ycompartments fuel cell and all otherdrains and any bilge areasnot requiringextensive removalof inspectionaccesscovers B Detailedinspectionshouldincludethe abovereferencedareasalongwithareasrequiringremoval of screw attachedinspectionplates and panelsto thoroughlyinspect the internalcavitiesof the aircraft 4 Duringinspectionrememberthat painttendstohidecorrosionin itsinitialstages However the resu...

Page 172: ... same manneras the originalsurfacewas protected unlessthemanufacturerrecommends someotherprocedureor protectivecoating CHART2003 TYPESOFMETALCORROSION Type of Material Type of Corrosion Remedy Steel Rust Completeremovalof corrosion by mechanical means Aluminum Whitetogreypowderymaterial Mechanicalpolishingor brashingwithmaterialsofter thanaluminum Magnesium highlysusceptible Whitepowderysnow like ...

Page 173: ...efulsurveillanceis maintained 7 Enginefrontalareas air inletductsandtheleadingedgeof wings becausetheyareconstantlyexposed to abrasionby dirt dust gravelandrain shouldbecheckedfrequentlyfor thebeginningof corrosion 8 Hinges piano hingesespecially are extremelyvulnerableto corrosiondue to the wearingaway of theirprotectivecoatingandtheirbeinganaturaltrapfordirt saltandmoisture 9 Controlcablesmayhav...

Page 174: ...hateveris handy Almostanykindof coverwill eithersmotherthe fire or at leastcontainit untila fireextinguishercanbebroughttothecan Anothersafetyfactor is the importanceof proper air movementin the sprayarea A properlydesigned sprayboothhas anair movementsystemthat not only keepsthe air circulatingbutremovesall of the solids and solvents Sinceall the materialsused in paintingare heavierthan air the e...

Page 175: ...jorityof paint strippers metalbrightenersand solventswill either attack the exposedsealant the anti staticcoatingson the glass or the exposedplastic Contactwiththesematerialsmaydamagethewindshield to thepointof replacement beingnecessary WARNING Aircraft should be grounded before painting to insure that no static electricity charges could build up and discharge CAUTION Movable control surfaces sho...

Page 176: ...ATTERNS Be sure the paint is thinned sufficiently Do not exceed paint manufacturer s specifications The use of a Zahncupandstopwatchis recommendedtocheckthe viscosity Malfunctions Spittingmay becausedby a driedoutpackingaroundthe materialneedlevalve lubricate witha fewdropsof lightoil dirt betweenthe bodyof thegunandthe fluidnozzleseator a looseor defective nutattachingthegun tothesuctioncup Refer...

Page 177: ...through the gun until the thinner appears clear NOTE Remove pressurefrom 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 CAUTION Do not allow material to remain in gun after use However if the passages should become plugged up with acrylic lacque...

Page 178: ... portion Figure20 9 A singlelayerof materiallaidon thesurfacebyonepassof thegun willbe typicallyabout 10to 12inches wide thickerinthe middleandtaperingoff at each end In orderto get a good even build upof finish spray on the firstpass thencomebackwiththegun onthe returnpass overlappingall butabouttwoor threeinches of this first pass The thirdpass will overlapall but abouttwo or three inchesof the ...

Page 179: ...L INCORRECT THE PAINTSPRAYGUN MUST BE MOVEDPARALLEL TO THE SURFACE IFTHEGUNIS MOVED INANARC THESPRAY PATTERN WILLBETHICKINSOMESPOTS ANDTHININOTHERS Figure20 8 SprayTechnique Figure20 9 SprayingCorners 1H11 20 25 06 Page20 21 Added February 23 1982 ...

Page 180: ...the fuselage and spanwise on the vertical and horizontal tail surfaces and the 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 and spraying across it then out the horizontal surfaces spanwise Spray the tack coat on the top of t...

Page 181: ...be sure all pigment 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 THOROUGHLYmixed 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 metal...

Page 182: ...w flowing 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 agitationcreates tiny air bubbles which are carried to the surface being sprayed High temperatures cause polyurethane to cure rapidly while low temperatu...

Page 183: ...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 a 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 24 hours tape free Without accelerator...

Page 184: ...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 may be ...

Page 185: ...p NOTE If cratering is encountered during application anti crater solutionmay beaddedto the primersolution not to exceedone ounceper gallonof catalyzed thinnedprimersolution Allowcatalyzedprimertostandfor a minimumof thirtyminutesbeforeapplication C UrethaneEnamel Thoroughlymixequalpartsof urethaneenameland enamelcatalyst Thin as requiredwithenamelthinner Recommended viscosityis 18to22 secondsusin...

Page 186: ...el catalyst 1 2 part enamel reducer except when using flat black then increase enamel reducer to 2 pans 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 a number I Zahn Cup D Refinish Installation of pressure sensitive decals placards and tapes on Titanine Polyurethane finish Affix a...

Page 187: ...essure 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 but it is neces...

Page 188: ...color afterit dries Whenthe topof the fuselageis to bepaintedwhitewitha darkcolor adjoiningit applythe lightcolorand featherit intothe areato be paintedwiththedarkcolor Whenthe light colorhasdried placemaskingtapeandpaperalongtheline of separationandspraythedarkcoloron Allow the paint to dry for severalhoursbeforeremovingthe maskingtape Removethe tape by pulling slowlyparalleltothe surface Thiswil...

Page 189: ...rfresh successivecoatingsof wash primerandmodifiedzincchromate Theywillalsoadheretofreshlyappliedepoxycoatings driedless than6 hrs 5 Epoxytopcoatswill adhere to all paint systemsthat are in good condition Epoxymaybe used for generaltouchup includingtouchupof defectsinbakedenamelcoatings 6 Old washprimercoats may be overcoateddirectlywithepoxyfinishes A new secondcoat of wash primermustbeappliedifa...

Page 190: ...ventoryso that thepigmentswill nothaveas muchof anopportunitytopackat thebottomof the can Emptycontainersshouldbedisposedofproperly Becausetheusefullifeof somefinishesis limited usetheoldermaterialsfirst Temperaturesin the storagearea should be approximately50 90 If finishesare storedin temperature extremes allowthemtocometoroomtemperaturebeforeusing PAINTINGFACILITY Painting facilities should con...

Page 191: ...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 adhesivewith a cloth dampened with dry cleanin...

Page 192: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 1H24 ...

Page 193: ...CHAPTER ENVIRONMENTAL SYSTEM 111 ...

Page 194: ...42 00 HEATERELECTRICAL SYSTEM CHECKS 1119 21 42 01 Electrical Continuity Check 1119 10 82 21 42 02 Heater Power Circuit Check 1120 21 42 03 VentBlower Power Circuit Check 1120 21 43 00 MAINTENANCE 1120 21 43 01 Janitrol Heater 1120 21 43 02 Removal Of Heater 1122 2 82 21 43 03 Installation Of Heater 1122 21 43 04 Disassembly Of Heater 1 1 21 43 05 Reassembly Of Heater 1J2 21 43 06 Spark Plug 1J3 2...

Page 195: ...Air Pressure Switch J 15 21 43 31 Removal Of Combustion Air Pressure Switch J 15 21 43 32 Installation Of Combustion Air Pressure Switch 1J15 21 43 33 Heater Safety Limit Switch 1J15 21 43 34 Removal Of Cycling Switch And Limit Overheat Switch 1J15 21 43 35 InstallationOf Cycling Switch And Limit Overheat Switch IJ16 21 43 36 Duct Switch 1J16 10 82 21 43 37 Removal Of Duct Switch 1J16 2 82 21 43 3...

Page 196: ...1K24 21 50 19 Compressor Oil Level Check 1L2 2 82 21 50 20 Replacement Of Compressor Drive Belt 1L2 21 50 21 Adjustment Of Drive Belt Tension 1 L3 21 50 22 Magnetic Clutch Removal 1L4 21 50 23 Magnetic Clutch Installation 1L4 21 50 24 Condenser Removal 1L4 21 50 25 Condenser Installation 1L5 21 50 26 Adjustment Of Condenser Air Scoop and Safety Switch 1L5 21 50 27 Receiver Dehydrator Removal 1L7 2...

Page 197: ...me is allowed for the heater to cool By depressing the START RESET switch momentarily the heater can be restarted Heater restart is indicated by the HEATERFAILwarning light extinguishing after the START RESETswitch is released An additional scoop mounted on the bottom of the airplane draws fresh air into the cabin through individual vents at each seat Each vent is adjustable for the desired airflo...

Page 198: ...nsufficient fuel pressure Fuel lines clogged or broken Ignition vibrator inoperative Regulator not operating properly Manual reset limit overheat switch open 116 Applyexternal power supply Attempt to start heater Turn on manualshut off valve or master solenoid Remove the nozzleand clean or replace it Secure all fittings Remove and check sole noid Replaceif faulty Lower no current to fuel pump Chec...

Page 199: ...aceplug Resetgapsetting Ventilating air blower failstorun Heaterswitch OFF Brokenor loosewiring to motor Engergizetheheaterswitch Checkandrepairwiring Circuitbreakeropen Wornmotorbrushes Blowerwheeljammed Motorburnedout Defectiveradio noise filter Closecircuitbreaker Replacemotorbushes Removeandcheckthe ven tilatingairblowerwheel andrealignifnecessary Removeblowerassemblyand replacemotor Replacefi...

Page 200: ... fuel pump and fuel lines Make necessary repairs Spark plug partially fouled Replace spark plug CAUTION Do not create spark gap by holding lead to heaterjacket Damage to lead and ignition unit win result and operator may receive an electrical shock Loose primary connect tion at ignition assembly Faulty vibrator Combustion air blower speed fluctuates Can be caused by low volt age loose blower wheel...

Page 201: ... starts then goes out Lack of fuel at heater Check fuel supply through all components from thetank to the heater Make nec essary corrections Inoperative or chat tering combustion air pressureswitch Inoperative overheat switch Inoperative cycling switch Low voltage Adjust or replace switch Replace switch Adjust or replace the switch Attach external power I Heater fails to shut off Fuel solenoid val...

Page 202: ...ER AIROUTLET 4 HEATER EXHAUST TUBEPLATE 5 HEATER DUCT FWD 6 HEATER DUCT AFT 7 DUCTSWITCH 8 AIRDUCT VALVE 9 AIRDUCTCONTROL 10 HEATER INLETVALVECONTROL 11 DEFROSTER AIRCONTROL 12 COCKPIT HEATCONTROL 13 HOURMETER HEATER Figure21 1 HeatingandVentilatingSystem 1110 21 40 02 Page21 06 Revised Oetober15 1982 ...

Page 203: ...SS ASSEMBLY 6 COMBUSTION AIR PRESSURESWITCH 6 OMITTED 7 COMBUSTION AIR INTAKE TUBE 8 COMBUSTION AIR BLOWER 9 VENTILATING AIR BLOWER 10 VENTILATING AIR INTAKE VALVE 11 SPARKPLUG 12 TERMINAL STRIP 13 LIMIT SWITCH 14 CYCLING SWITCH 15 HEATER EXHAUST PIPE Figure21 2 HeaterAssemblyandCombination Air Blower l1l1 2140 02 Page21 07 Issued September 2 1981 ...

Page 204: ...e the 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 ventilating air flow 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 sto...

Page 205: ...usualcurrentdraw noiseor vibrations NOTE Toproceedwith the operationalcheck followparagraphentitled OperatingProcedures steps I through 5 Thisprocedureshould berepeatedoneor moretimes HEATER HEATER SOLENORO HEATER SWITCe STRIP HEATER 15 A VENT AIR 106 16 BLOWER BLOWYER 1 103 I SWITCH 101 16 HEATER FUEL REGULTOR OVERHEAT SW VALVE SWITCH L COMBUSTIONAIR HEATER CIRCUIT AIRCRAFT CONTROLCIRCUIT Figure ...

Page 206: ...points 5 Inspect the high voltage cable connection at the spark plug to make sure it is tight Also examine the cable sheath for any possible indications of arcing which would be evidenced by burning or discoloration of the sheath 6 Inspect the combustion air blower assembly for security of mounting and security of connecting tubing and wiring Tighten any loose electrical terminals and air tube con...

Page 207: ...embly Figure 21 8 for dented case loose or damaged primary terminal insulator and broken or obviously damaged high voltage lead Give particular attention to the condition of the spring connector at the end of the lead If the spring is burned off visibly eroded or carbon tracked the ignition assembly should bereplaced NOTE Do not attempt afield repair of the ignition unit as it is a sealed assembly...

Page 208: ...lationblowermotormanufacturedby HowardIndustries should turn9800 RPMand drawapproximately15 16amperesinano lead condition C If currentdrawis excessive or ifspeedis toolow replacethebrushes Recheckbothcurrentdraw andRPMafterbrushesareproperlyrun in D If afterreplacingbrushes operationisstill unsatisfactory replacethemotor NOTE The motor checks described above should be made without the blower housi...

Page 209: ...sing 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 indicated on the manometer NOTE The switch cover has a differential pressure tap and this opening must be left open to atmosphere during the test D Make several trials to insure switch reliability Be sure to increase and decrease the air pressure slowly ...

Page 210: ...P OPEN 6 ADJUSTING SCREW UNDER COVER 7 COMBUSTION AIRPRESSURE SWITCH PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL 2 3 4 AIR SUPPLY 7 Figure 21 5 Test Set up Combustion Air Pressure Switch THIS SPACEINTENTIONALLY LEFT BLANK 1118 21 41 06 Page21 14 Revised October15 1982 ...

Page 211: ...ne connected observe the fuel spray pattern It should be conical in shape with even dispersion in all directions WARNING Be sure tokeep theatomizedsprayawayfromfire D Energize and de energize the solenoid several times The spray should shut off permanently each time the solenoid is de energized There should be no sign of dribbling at the nozzle tip in excess of one or two drops E If the spray patt...

Page 212: ...of the heater terminal strip E From terminal No 3 of the heater terminal strip through the cycling switch to the fuel solenoid valve In the event that electrical continuity is not present at one or more of the above listed points the wiring must be traced back to the power source If components are still inoperative after the wiring inspection check the individual inoperative components for continu...

Page 213: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL Figure21 6 VentBlowerPowerCircuit AIRCRAFT CONTROLCIRCUIT Figure21 7 HeaterPowerCircuit 1121 21 43 01 Page21 17 Revised October 15 1982 ...

Page 214: ...teron itsmountingbracketandsecurewithclamp 2 Attachtheforwardendof theheaterto thefuselagebulkhead 3 Connecttheair inletvalvecabletothe forwardendof theheater 4 Connectthefuellineto theheaterandinstallshroudcover 5 Connectthefueldrainto theundersideof the heater 6 Positionthecombustionairblower connecttubesandsecuretheunittoitsmountingbracket 7 Connectthedefrosterandheatductstotheair heatdistribut...

Page 215: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL Figure21 8 Exploded Viewof HeaterAssembly 1123 21 43 03 Page21 19 Revised February 23 1982 ...

Page 216: ...BE 18 COMBUSTIONTUBE 19 GASKET 20 FUELSPRAYNOZZLE 21 VALVEASSEMBLYGASKET 22 BRUSHPLATEASSEMBLY 23 CAPACITOR 24 MOTORASSEMBLY VENTAIRBLOWER 25 BRACKET ASSEMBLY MOTOR 26 FAN VENTAIRBLOWER 27 SLOWER ASSEMBLY 28 GASKETCOMBUSTIONHEAD 29 COMBUSTIONHEADASSEMBLY 30 GROMMET 31 SCREW 32 FASTENERWASHERS 33 BLOWERHOUSING 34 FUELSHROUDGASKET 35 NIPPLE 36 ELBOW 37 FUELSHROUDBOX LOWER 38 FUELSHROUDBOX UPPER 39 F...

Page 217: ... and motor housing to disengage the notched end from the four screws in the end of the heater jacket Separate the electrical quick disconnect on motor lead wires Remove blower assembly Remove grommet from fuel shroud and carefully pull fuel solenoid wires through hole in shroud With open wrench remove fuel solenoid 11 Reach inside the inlet end of the jacket assembly with a 3 4 inch open wrench to...

Page 218: ...smadeduringdisassembly Makesuretheseamis ingoodconditionand atightfitis effected 7 Installcablestrapsat locationsnotedduringdisassembly 8 If new spray nozzle is not being installed removethe originalnozzlefrom the polyethylenebag Screwthe nozzleinto nozzleholderand tightento 75 100inch pounds It is veryimportantto torque thenozzletothisvalue as incorrecttighteningcouldcauseimproperheateroperationa...

Page 219: ...t it to the mating connectoron the wiring harness 20 Place the blower housing in position on thejacket assembly and secure it by installing the four screws if removed at disassembly This operation is easier if the screws are started into their threads and the blower housing rotated into place allowing the screws to enter the notched openings in edge of blower housing Tighten all screws securely 21...

Page 220: ...king the gap through the spark plug well when the heater is not disassembled Method I 1 Using a 5 32 inch drill 0 156 or a piece of 5 32 inch rod reach through the opening in the combustion head fuel nozzle location and find the ground electrode It is welded inside the head 2 Move the drill along the side of the electrode on the spark plug side Movement should be from the outer edge towards the ce...

Page 221: ...d 4 Check spark gap as noted in Methods I or 11 SPARK SPRAY IGNITION RefertoFigure21 14 The controlledatomizedspray from a speciallydesignedspray nozzle coupledwith high voltagespark plugignition insuresinstantfiringandcontinuousburningunderallflightconditions Heatis producedby burninga fuel airmixturein thecombustionchamberof the heater Aviationgasoline is injectedintothecombustionchamberthrought...

Page 222: ...SA E SPARK PLUGSTANDARD HOLES0 1285 DIA 30 DRILL 0 18 DEEP GAP 0 3126 DIA ROD 0 60 LONG 1010 1020 STEELROD DRILLANDTAPFOR4 40 SCREW LOCATED 1 4 IN EITHER END SCREW MACHINE RD HD ANOR MS 4 40 1 4 IN LONG NOTE ALL DIMENSIONS AREIN INCHES DENOTES SILVER SOLDER Figure 21 9 Spark Plug Fixture MOMENTARY SWITCH BATTERY AMMETER VOLTMETER VIBRATOR COIL TOTAL RESISTANCE A TO A MUST NOT EXCEED 0 3 OHMS Figur...

Page 223: ...UNDELECTRODE 5 JACKET ASSEMBLY 7 MEASURE 8 GASKET 6 4 SLIP FIT 255 DIA HOLE 18 MM THREAD 75 HEX STOCK UNDERCUT 010 MARKWITH BLACKPAINT I 3 444 3 317 MATERIAL CANBESAETYPE303 321OR347ST ST ORALUMINUM CASEHARDENED P N Figure21 12 SparkPlugGapAdjustmentandTool 1J7 21 43 11 Page21 27 Issued September2 1981 ...

Page 224: ...Y PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL INLET FRESHAIR FROM BLOWER Figure21 14 DiagramaticCutawayof Heaterto ShowWhirlingFlameAction HIS SPACEINTENTIONALLYLEFT BLANK 1J8 21 43 11 Page21 28 Revised February 23 1982 ...

Page 225: ...kplug 4 Connectthe primaryleadtotheprimaryterminalonthe ignitionassemblyandtightenthenutsecurely 5 Checkforproperheateroperation TESTING IGNITION UNIT The ignitionunitdoes not requirecompleteoverhaul The followingtest will indicatewhetheror not the unit is operational and whether the vibrator should be replaced before reinstallation in the aircraft The followingequipmentis requiredto testthecompon...

Page 226: ...om the housing brackets that secure the vibrator 2 Remove the vibrator from the ignition unit it may require a slight back and forth movement to remove it from the unit A piece of masking or friction tape around the exposed portion of the vibrator will help to grip the vibrator for removal INSTALLATIONOF VIBRATOR 1 Install the new vibrator with the index marks aligned The connector pins on the vib...

Page 227: ... for the first hour then gradually increase the speed until it is rotating at approximately normal speed Continue the run in operation for at least two hours to properly seat the brushes before installing the blower in the airplane INSTALLATION OF COMBUSTION AIR Blower Refer to Figure 21 15 1 Prior to installing the combustion air blower inspect all parts of the assembly for loose screws loose nut...

Page 228: ...randcleanallexteriorsurfacesthoroughly CLEANINGANDINSPECTINGTHE COMBUSTIONTUBEASSEMBLY Referto Figure21 8 1 Slightscalinganddiscolorationof thecombustiontube assemblyis a normalconditionfor unitsthat havebeen in serviceup to 500 airplanehours The slightscalingconditionwill appearto bemottled and a small accumulationof blue graypowdermay be presenton the surfacein certainareas This conditiondoes no...

Page 229: ...t 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 NOTE No weld or braze repairs 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 the motor assembly to the inner housing half with ...

Page 230: ...CKWASHER 13 FLATWASHER 14 NUT 16 BLOWER WHEEL 16 OUTER HOUSINGHALF 17 SCREW 18 BLOWER INLETADAPTER 19 DUCTSWITCH 20 SWITCH 21 BRACKET ASSEMBLY 22 LEVER SWITCH 23 PLATE SWITCHACTUATOR 24 MICROSWITCH PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL 1 Figure21 15 ExplodedViewof Combustion Air BlowerandMotorAssembly 2143 29 1J14 Page21 34 Issued September2 1981 ...

Page 231: ...orquethe switchas thiscouldchangethe setting 2 Connectthetubeassembliesto theswitchusinga suitablethreadlubricant 3 Connect the electrical leads to the appropriate switch terminals If in doubt regarding proper connections referto thewiringdiagram Figure21 3 4 Checkforproperheateroperation HEATERSAFETYLIMIT SWITCH Located in the heater is a heat limit switchwhichacts as a safety device to renderthe...

Page 232: ...3 NOTE The cycling switch shuts off the heater at 250 F It win then reset itself when the temperature falls below this point The overheat switch operates at 300 400 F DUCTSWITCH RefertoFigure21 16 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...

Page 233: ... the two wires from themicro switch to the duct switch terminals 3 Setthe temperatureselectorshaftat thehighstop thencarefullyplacethe temperaturecontrolin the aircraftcabintohighheatposition Reinstallcontrolwireintocontrolleverarmandtightenscrews 4 Set the microswitchto activateat the verylast movementof the controllever arm in the high heat position 5 Operatetheheaterwiththeductswitchsetaboveamb...

Page 234: ...ionsforcorrect installation 3 Removethescrewsattachingtheunittoitsmountingbracket ADJUSTMENTOF FUEL REGULATORANDSHUTOFFVALVE The fuel regulatorandshutoffvalve used in thissystemare adjustablebutnot repairable Thefollowing stepscovertheproperadjustmentof thisunit I Installtheregulatorina teststandsimilartothatshowninFigure21 17 2 Install a 2 5 gph nozzle Janitrol Part No D08D09 Gasolineor Stoddards...

Page 235: ...lows pressuredrops andotherfactorswhichwould be accomplishedina laboratory type test If such a testcannotbe made installtheheaterandcheckoperation on the groundand in the air to determineif operationis normal In shopswherecompletetest equipmentis availableanda completefunctionaltestcan be performed the testroutinedescribedin subsequentparagraphs shouldbemade EQUIPMENTREQUIRED RefertoFigure21 18 1 ...

Page 236: ...tchandreconnectthe terminalleaddisconnectedinprecedingstep5 10 Closethe powersupplyswitchandturnon thefuel supply Theheatershouldlightwithinfiveseconds mayrequireslightlylongerforairto bepurgedfromfuellineson the firsttrial 11 Observe operationof duct switch which should control heater operationaccordingto the switch setting 12 If the duct switchfails to controlthe temperatureaccordingto the setti...

Page 237: ...9 THERMOMETER 10 OVERHEAT LIMIT SWITCH 11 CYCLING SWITCH 12 EXHAUST OUTLET 13 DUCT 14 DUCT SWITCH 2 25 DIA ORIFICE Figure21 18 SuggestedSetupforHeaterOperationTest AIR I IGNITION UNIT 6 OVERHEATSW MANUAL RESET 102 16 COMBUSTION AIR HEATER CIRCUIT PRESSURE CYCLING SWITCH 202 16 FUEL VALVE EXTERNAL WIRING REQUIRED FOR ENCH TEST Figure21 19 WiringConnectionsforHeaterOperationTest 21 44 03 1J21 Page 2...

Page 238: ...odule from the compressor through flexible hoses and aluminum tubing routed from the compressor at the right front of the right engine down under and across the engine to a point on the left side of the fire wall From there through the condenser to the main spar into the wheel well into the cabin module evaporators The pressure and suction line running approximatelyparallel Thesuctionlinebeingthel...

Page 239: ...essor suctionservice valve Restrictionin liquidline fromcondenser Checkthatcapillary bulbis securely clampedtosuction line If capillary bulbOKreplace expansionvalve Checkfor kinked hosesandstopped up filter Lowdischarge pressure Undercharge of refrigerant Sightglassshows bubblesor foam Addrefrigerant untilbubbles disappear Check systemleaks Damagedcompressor valvesordirt undervalves Blowngasket Da...

Page 240: ...ll showfrost Expansionvalve inletscreen clogged Inoperativeex pansionvalve Valvestuck closedor capillary bulbhas lost itscharge AddFreon Installnewdryer Evacuateandre chargesystem Removescreen Cleanwithsol dicating ventandreplace Warmcapillaryby holdinginhand If suctionpressure doesnotcharge replaceexpansion valve Restrictionany wherein liquid line Restric tion willshow frost Highsuction pressure ...

Page 241: ...ithsolvent andreplace Replace valves with valve kit System produces no cooling Electrical Opencircuit breaker Brokenor dis connected elec trical wire Reset circuit breaker Checkall termi nalsforloose connections check wiringforhidden breaks Brokenor dis connectedground wire Clutchcoil or solenoid burnedoutor disconnected Thermostatsensing elementdefective 1K1 Checkgroundwire toseeifloose broken or...

Page 242: ...in open position Refrigeration Broken refrigerant line Leak insystem Compressorshaft seal leaking Replace drive belts and or tighten to specifications Remove compressor for service or re placement Replace expansion valve Examine all lines for evidence of breakage by external stress or rubbing wear Evacuate system apply static charge leak test system and repair leak as necessary Replace compressor ...

Page 243: ...h in operation Remove fan motor for service or replacement Mechanical Compressor clutch slipping Obstructed blower passage Insufficient air circulation over condenser coils fins clogged with dirt or bugs Evaporator clogged Insufficient air circulation over condenser coils fins clogged with din or bugs 1K3 Remove clutch assembly for ser vice or replace ment Examine entire passage for ob struction C...

Page 244: ...tem and re place expansion valve Purge system replace expansion valve Purge system replace receiver Purge system replace receiver 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 dehydrator replaced also and the system must be purged evacuated and recharged to remove excess moisture Excessively no...

Page 245: ...ear in blower motor Check mountings and repair remove compressor for ser vice or replace ment Fill with correct specified oil Remove blower motor for ser vice or replace ment as necessary Refrigeration Excessive charge in system Discharge excess freon until high pressure gauge drops within specifications Low charge in system Check system for leaks charge sys tem Excessive mois ture in system Repla...

Page 246: ... MAINTENANCEMANUAL CONDENSER FREON PRESSURE I FREON SUCTION SIGHT GLASS VENTILATING DUCT VENTILATING BLOWER RECEIVER CONTROL SWITCH Figure21 20 Air ConditioningSchematicDiagram 21 50 02 1K6 Page 21 50 Revised February23 1982 ...

Page 247: ...ETIC CLUTCH 5 SERVICE VALVES FREONPRESSURE LINE 7 CONDENSER 8 FREONSUCTION LINE RECEIVER DEHYDRATOR ANDSIGHTGLASS 10 VENTILATING DUCT 11 VENTILATING BLOWER 12 EVAPORATOR 13 EXPANSION VALVE 14 LOWPRESSURE SWITCH Figure21 21 AirConditioning SystemInstallation 1K7 21 50 02 Page21 51 Issued September2 1981 ...

Page 248: ...ture F 21 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 High Pressure Gauge Reading p s i 72 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 76 ...

Page 249: ... higher than the chart indicates It mustbepointedoutthat theactualtemperatureof theair passingoverthe coilsof theevaporatorwillbe several degrees warmer allowingfor a temperaturerise caused by the loss in the fins and tubing of the evaporator The importanceof a seasonalcheckup of the airconditioningsystemshouldbebroughtto theattentionof the customerwheneverpossible A thoroughcheck of the systemper...

Page 250: ...RMANCETEST IN COLDCLIMATES To run a performance test on the T 1020 air conditioning in cold climate below 70 F the following procedures will have to be used 1 Obtain an air blower with the following requirements A 300 cfm at 3 00 H20 static pressure with standard air density of 0765 1bs cu ft or a Piper recirculating air blower Piper Part No 460 003 2 Take the air blower and connect the exhaust si...

Page 251: ... cowlflap area to the Schrader valves on thefire wall being careful to miss the engine exhaust 1 The mostaccurateway to checkthe conditionof the systemis by attachinggaugesto the systemas showninFigure21 25 2 Alwayswearsafetygoggleswhenhandlingrefrigerant WARNING One of the most important precautions is protection of the eyes when handling refrigerant Any liquid refrigerant which may accidentally ...

Page 252: ...eration oil before using Do not over torque connections Refer to Chart 2104 9 To insure a consistent seal on all flared and pipe fittings used on the air conditioning system seal the fittings with Loctite refrigerant sealant Sealant should be applied only to the flare surfaces of the flare fittings 10 Torque all flare fittings in accordance with Chart 2104 CHART 2104 ALUMINUM TUBING TORQUE Metal T...

Page 253: ...o a manifold One gauge is a high pressure gauge used in the discharge side of the system The other is a low pressure gauge used in the suction side of the system The manifold is a device having fittings for both gauges and connection hoses with provisions controlling the flow of refrigerant through the manifold The center port of the manifold set is used for charging or evacuation procedures or an...

Page 254: ...of refrigerant gas to escape from the Schrader valve fitting 3 The cylinder of refrigerant should be placed upright in a container of warm 125 F max water on a small scale 5 Allow approximately 1 2 pound of refrigerant to enter the system by opening the valve on the charging hose and observing the weight change on the scale 5 Using an electronic leak detector check all joints and repair any leaks ...

Page 255: ...p NOTE Make sure the exhaust port on the vacuum pump is open to avoid damage to the vacuum pump 5 Operate 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 thenextendtheoperationfor another25minutes 7 If th...

Page 256: ...DIAGRAM A PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL H CLOSED CRACKED CRACKED CRACKED Figure21 23 ManifoldSetOperation H H DIAGRAM B DIAGRAM C DIAGRAM D 1K16 21 50 12 Page 21 60 Issued September2 1981 ...

Page 257: ... PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL HIGH PRESSURE GAGE D TO DISCHARGE SERVICEVALVE TO VACUUMPUMPOR REFRIGERANT CYLINDER Figure21 24 TestGaugeandManifoldSet SCHRADER VALVES Figure21 25 LeakTestHookup 1K17 21 50 12 Page21 61 Issued September2 1981 ...

Page 258: ...ntains refrigerant A Close all valves on charging station B Connect red high pressure charging line to high pressure Schrader valve at the fire wall fitting of the right nacelle Refer to Figures 21 27 and 21 29 C Open valve 2 high pressure control on charging station one turn D Hold end of blue low pressure charging line in a shop rag and slowly open valve 1 low pressure control on charging statio...

Page 259: ...CRAFT T 1020 MAINTENANCEMANUAL LINES TO COMPRESSOR RECEIVER DEHYDRATOR ANDSIGHT GLASSLOCATED IN RIGHT WHEELWELL Figure 21 27 Service Points Air Conditioning System THIS SPACE INTENTIONALLY LEFT BLANK I lK19 21 50 14 Page21 63 Added February23 1982 ...

Page 260: ...thechargingstation RefertoFigure21 28 D Operatepumpuntil26 to 28 inchesvacuumis attained Continuetooperatepumpfor 25 minutes after26 to28 inchesvacuumis reached NOTE Reduce vacuum reading one inch for each 1000feet altitude abovesea level E Whilesystemis evacuatingfill chargingcylinderas outlinedinstep3 F If 28 inchesof vacuumcannot beattained closevalve 3 vacuumcontrol stop pumpand check systemfo...

Page 261: ...highpressurecontrol fullyopen andvalve 1 low pressurecontrol closed openvalve 4 refrigerantcontrol and allowas much liquidrefrigerantto enter the high sideof the systemas possible It will be necessaryto slightly warmthe baseof the chargingcylinder If chargingstation does not havea cylinderheateruse heatfroma 75 to 100wattbulbandwatchthatsystempressuredoesnotexceed150psig inorder todrivethelastport...

Page 262: ...se the container valveafterthe sightglassclears F If meansare availableto weighthecontainer anadditional1 2poundof refrigerantcanbe added to increasethetimebetweensystemcharges G Turnoffthe airconditionerandstoptheengineaftercharging Removethecharginghosefromthe Schradervalveusinga clothtodirecttheescapingrefrigerant RecapSchradervalve REFRIGERANTDRUMMETHOD 1 DISCHARGING THESYSTEM A Closebothvalve...

Page 263: ...the gauge set hoses connectedper step I and systemevacuated connecta charginghose betweenthegaugesetmanifoldandarefrigerantcontainer B The refrigerant container should be placed in a container of warm 150 F max water The containershouldbe intheuprightpositionwiththe valveon top C Open the refrigerant container valve with the gauge set high pressure valve open and allow refrigerantgastoenterthe sys...

Page 264: ...r 5 Removebothservicevalvesfromthecompressorwiththerelatedpressureandsuctionlinesattached CAUTION Compressor pressure will bleed off at theflanges of these valves when the bolts are loosened 6 Loosenthecompressoradjustmentbolts releasethe belttensionandremovethedrivebelt 7 Supportthe compressorand remove the four bolts holdingthe compressormountingbracketto the engine COMPRESSORINSTALLATION When i...

Page 265: ...pen both the low pressure control valve and the vacuum control valve on the charging stand Continue to operate pump for 5 minutes after 26 to 28 inches of vacuum is reached 10 After evacuation close both the low pressure control valve and vacuum control valve Wait 5 minutes and observe the vacuum gauge no more than a 2 inch drop in vacuum is allowed If the 26 inch vacuum cannot be attained or if t...

Page 266: ...FREE The 16ounce oil level is requiredin compressorsinstalledon new systems Approximately 6 ouncesis distributedin thesystemduringoperation Replacement compressorsshouldbe chargedwith 10ouncesof oil unlessthe systemhas beenflushedclean of all oil Whena compressoris changedthe systemshouldbe run andstabilizedintemperatureprior torecheckingthe oil level The levelshouldbe toppedoff to 10ouncesif nece...

Page 267: ...EON COMPRESSOR INSTALLED BELT CONDITION GATES 150 TENSIOMETER BELT Alternator Refrigerant Compressor New Service New Service 99 lbs 66 lbs 104 lbs 69 lbs ACTUAL MEASUREMENT LOAD VS DEFLECTION 6 31 lbs 16 in 4 25 lbs 16 in 6 75 lbs 14 in 4 50 lbs 14 in Pertains to a belt that has been in use for longer than one hour HIGHPRESSURE DISCHARGE GAUGEPORT PROTECTIVE CAP INSTALLED 4 68 1 50 THIS ENDFOR HOR...

Page 268: ...E The compressorshaftmustbe cleanandfree from burrs 3 Slide the pulley assemblyonto the taperedshaft andsecure withwasherand self lockingcapscrew Torquethecapscrewto 180to240inch lbs NOTE If the clutch is not engagedwhile tighteningthe capscrew insert a spannerwrenchinto the holesprovidedinthe armatureface 4 Spin thepulleyby handto checkfor anyinterferencebetweenthefieldandrotor pulleyassemblies A...

Page 269: ...has been open to the atmosphere 4 Completethe hookupof the linestothecondenser Applya smallamountof Loctiterefrigerantsealant to theflareonlyto insureleak freeconnections Torquethefittings 5 Withthecondensersecured proceedtoevaluateandrecharge 6 When the systemis completelycharged check it for any leaks Referto Checkingthe Systemfor Leaks 7 Replaceairscoopandaccesspanels ADJUSTMENTOFCONDENSERAIR S...

Page 270: ...LLEY ASS 3 CAPSCREWS LOCK WASHERS 4 FIELD ASSY 5 COMPRESSOR PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL l I Figure21 31 MagneticClutchInstallation THISSPACEINTENTIONALLY LEFTBLANK 1L6 21 50 26 Page21 74 Revised February23 1982 ...

Page 271: ...ned between the top of the gear fork and the bottom of the gear housing Hold the gear at this measurement C Adjust the switch down until it actuatesat this point Secure the switch D Extend and then compress the strut to ascertain that the switch will actuate in the last 250 125 inch of oleo extension E Remove airplane fromjacks F Refer to Chapter 32 for left gear safety switch information RECEIVER...

Page 272: ...secondandthirdseats 1 Removetheseat s fromtheairplane 2 Removetheappropriatecabindividerpanel 3 Removetheseattracksandcarpetfromthefloorboardpanel 4 Removethescrewssecuringthe floorboardpanelovertheunitandremovethepanel 5 Dischargethesystempriortolooseninganyfittings 6 Removethetapecoveringthepressureline capillarytubeandclamp Removethe clamp Donotkink the capillarytube 7 Loosenandseparaterelatedt...

Page 273: ...tandremovethepanel 5 The airconditioningsystemmustbecompletelydischargedbeforedisassembly 6 Removethe inboardendpanelsof themodules threescrewseachpanel 7 Remove divider panels six screws each panel on right panel disconnect the related electrical connections 8 Loosenandseparatetubefittings thetubeflangesaresealedandmayrequireheattoseparate NOTE WhenLoctiterefrigerantsealanthas been usedon ajoint ...

Page 274: ...removedandsecure BLOWER ANDMOTORASSEMBLY Eachmoduleis equippedwitha blowerassembly theydifferinthat the leftonerotatescounterclockwise andtherightoneclockwise Locatedintheupperpartof the unitmodule BLOWER MOTORASSEMBLYREMOVAL 1 Removethedividerpanel 2 Disconnecttherelatedelectricalwires 3 Removethetwo screwsattachingtheairductbrackettoendpanelanddisengagethelockinglip 4 Removetheclampattachingtheb...

Page 275: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL Copilot 2 FWD Dividers 6 CabinArea Pilot 1 3 5 Figure21 33 Air ConditioningOutlets THISSPACEINTENTIONALLY LEFTBLANK 1L11 21 50 35 Page21 79 Issued September2 1981 ...

Page 276: ...incabin andpilotsdoorsclosed andremainingoutletsopen A simplewayto checkthe outlet is to recordthe outletnumberon a sheet of paper and recordthe air flows at each outlet workingfromthecockpitand movingaft CheckyourrecordedflowsagainstChart2108 3 Whencheckingair flows holdtheprobefromtheflow meterperpendicularto andinthe centerof the outlet Referto Figure21 34 4 Should the air flow at the various o...

Page 277: ...CRAFT T 1020 MAINTENANCEMANUAL SIDE VIEW I FRONTVIEW PROBE PILOTS COPILOTS OUTLETS GRILLE VANE PROBE CABINOUTLETS Figure21 34 Positioningof AirflowProbetoOutlets 21 50 38 1L13 Page21 81 Revised February23 1982 ...

Page 278: ...16ABX PiperCode486476 for di metertube VSF101 A8BX PiperCode488479 for diametertubes VSF1015A12BX PiperCode486 478 for diametertubes Figure21 36 Installation of VOI SHANSeals PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL SIDEOF DUCTS DUCT DUCT 1L14 21 50 38 Page21 82 Revised February 23 1982 ...

Page 279: ...imesdifficultto seal On the hard to get atfittings it may be necessaryto installVoi Shanseals Referto Figure21 36 To installthe seal placesealoverthe nippleend and placetube flare over seal andnipple Tightenper the proceduregiven in paragraphI excepttighten onlyonce CAUTION When installing Voi Shan seals check for cracks and scored flared endsand nippleends Replacepartsas necessary 3 Leaksaremostf...

Page 280: ...MAINTENANCE MANUAL CARD 2 OF5 PA 31 350 T1020 PIPER AIRCRAFT CORPORATIO PART NUMBER 761768 2A1 ...

Page 281: ...en broken down into Sub System Sections These sections are identifiedbythe secondelement ofthe standardizednumberingsystem Thenumber 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 Thisnumber could beassignedby the man...

Page 282: ...tepageadditionsarenotidentifiedbyrevisionlines A referenceandrecordofmaterialrevisedis includedineachchapter sTableof Contents Effectivity The codesusedintheeffectivitycolumnsof eachchapteraredefinedas follows SAMPLEEFFECTIVITY CODES FirstRevision SecondRevision ThirdRevision Fourth Revision AddedSubject Month and Year 11 80 RevisionIndication MonthandYear 2R12 80 RevisionIndication MonthandYear 3...

Page 283: ...INTENTIONALLY LEFT BLANK 2A4 ...

Page 284: ...R P N 117D Hartzell Propeller Inc P O Box 1458 1800 Covington Avenue Piqua Ohio 45356 MAGNETOS Installation Operation and Maintenance Instructions WHEELS AND BRAKES PARTS CATALOGS and Maintenance Instructions S 1200 SERIES MAGNETO IGNITION SYSTEM P N L 609 3 Bendix Electrical Components Division Sidney New York 13838 CLEVELAND WHEEL AND BRAKE Aircraft Wheel and Brake Division 1160 Center Road Avon...

Page 285: ...L AVIATION DIVISION Rockwell International Cedar Rapids Iowa 52406 319 395 3625 Telex 46 4421 KING RADIO CORPORATION 400 N Rodgers Rd Olathe Kansas 66061 813 782 0400 Telex 4 2299 Kingrad GLOBAL NAVIGATION 2144 Michelson Drive Irvine Ca 92715 714 851 0119 PIPER PUBLICATIONS PA 31 350 T 1020 Parts Catalog CONTINUOUS INSPECTION 761 775 Piper Aircraft Corporation 2926 Piper Drive Vero Beach FL 32960 ...

Page 286: ...D SHORING LEVELING AND WEIGHING TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACT AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS AEROFICHE GRID NO IBI 1B4 ID23 IE13 1E16 IE21 IFI 1F4 1F8 IG 12 III 2BI 2B4 2B12 2D1 2D10 2G19 2JI 3B1 3D9 3G1...

Page 287: ...C SYSTEM VACUUM SYSTEM ELECTRIC ELECTRONIC PANELS AND MULTI PURPOSE PARTS STRUCTURES DOORS FUSELAGE STABILIZERS WINDOWS WINGS PROPELLERS STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM AEROFICHE GRID NO 3HII 314 3116 3J4 3J6 3J22 4B1 4B21 4CI 4C17 4D4 4E1 4E22 4FI 4G1 4G II 4H10 4H 14 411 Intro Revised February 23 19 Revised Febr...

Page 288: ...UAL GAMA SYSTEM CHAPTERINDEX GUIDE cont SYST CHAP 80 81 91 95 SUB SYST SECTION TITLE STARTING TURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 4111 4121 5B1 5FI Introduction Page8 Revised November17 1983 2A9 ...

Page 289: ...Plant Propeller and Cowl Flap 1G3 12 7 Lubrication Chart Doors and Seats 1G4 20 1 Torque Wrench Extension IG16 20 2 Method of Installing Rod End Bearings 1G16 20 3 Cherrylock Rivet Removal 1G17 20 4 Hose Line Markings IG19 20 5 Flareless Tube Fittings IG20 20 6 Spray Patterns 1H8 20 7 Improper Spray Technique 1H 10 20 8 Spray Technique 1H 11 20 9 Spraying Corners 1H11 21 1 Heating and Ventilating ...

Page 290: ...ricated Oil Dipstick 1L3 21 31 Magnetic Clutch Installation 1L6 21 32 Expansion Valve Typical 1L8 21 33 Air Conditioning Outlets 1L1 1 21 34 Positioning of Airflow Probe 1L 13 21 35 Sealing of Ducts 1L14 21 36 Installation of VOI SHAN Seals 1L14 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 Avion...

Page 291: ...ension 2E 18 27 10 Safety Wiring Control Surface Stops 2E18 27 11 Rudder and Rudder Trim Controls 2E22 27 12 Rudder and Trim Tab Control Travels and Cable Tension 2F2 27 13 Clamping Rudder Pedals in Neutral Position 2F2 27 14 Installation of Rudder Rigging Tool 2F2 27 15 Rudder Pedal Installation 2F7 27 16 Elevator and Elevator Trim Controls 2F10 27 17 Elevator and Elevator Trim Travels and Cable ...

Page 292: ... 8 Power Pack Handle ReleaseMechanism 2K8 29 9 SafetyingControl Arms 2K9 29 10 Indexing of Selector Spool 2K10 29 11 Handle ReleaseAdjustment 2K11 29 12 Landing Gear Selector Mechanism Installation 2K13 29 13 Power Pack Test Harness Schematic 2K18 29 14 Hydraulic Filter 2K20 29 15 Hydraulic Pump 2K22 29 16 Hand Pump 2L4 29 17 Shuttle Valves WTC 2216 WTC 2217 2L7 30 1 Pneumatic Deicer System Instal...

Page 293: ...ing Gear Installation 3E16 32 8 Clamping Rudder Pedalsin Neutral Position 3E22 32 9 Rudder PedalsNeutral Angle 3E22 32 10 Aligning NoseGear 3E22 32 11 EmergencyExtension SystemInstallation 3F1 32 1la Test Equipment Installation EmergencyGear Extension System 3F5 32 12 Gear Actuating Cylinder Wiebel Tool WTC 2115 1 3F6 32 13 Unlock Actuator Wiebel Tool WTC 2215 3F7 32 1 Gear Door Actuating Cylinder...

Page 294: ...3K7 51 4 Deep Scratches Shallow Nicks and Small Holes 3K7 51 5 Mixing of Epoxy Patching Compound 3K8 51 6 Welding Repair Method 3K8 51 7 Repairing of Cracks 3K9 51 8 Various Repairs 3K11 51 9 Repair of Stress Lines 3K12 51 10 Repair of Impacted Damage 3K12 51 11 Installation of Radome Erosion Shield 3K18 52 1 Cabin Entrance Door Latch Assembly 4B6 52 2 Pilot s Door Latch Assembly 4B10 52 3 Cargo D...

Page 295: ...act Points 4G15 74 3 Rotor Holding Tool Installed 4G 16 74 4 Timing Kit Installed 4G16 74 5 Aligning Timing Marks Single Contact Assembly Magneto 4G18 74 6 Forming Leads in Breaker Compartment 4G 18 74 7 EngineTiming Marks 4G19 74 8 Magneto Timing Marks 4G19 74 9 Deleted 74 10 Checking Harness Lead Insulation Resistance 4G22 74 11 Modified Pliers 4G22 74 12 Removing Spring From Lead Assembly 4G23 ...

Page 296: ... Fabricated Tool Checking Nose Gear Link Travel 5F7 95 5 Flight Control RiggingTools 5F8 95 6 Fabricated Tool Checking Nose Wheel Alignment 5F9 95 7 Fabricated Jack Stand for Piper Jack Part No 18338 00 5F10 95 8 Fabricated Tail Stand 5F11 95 9 Fabricated Bellcrank RiggingTool 5F12 95 10 Fabricated Aileron and Elevator RiggingTool 5F13 95 11 Fabricated Rudder RiggingTool 5F14 95 12 SuggestedDesign...

Page 297: ...B23 2402 Alternator Test Specifications 2C10 2403 Alternator BeltTension 2C1I 2404 Hydrometer PercentageGuide 2C13 2701 Troubleshooting Surface Controls 2D16 2702 Control Cable RiggingTension Vs Temperature 2E3 2801 Troubleshooting Fuel System 2HI 2802 Fuel Cell Repair Equipment Lists 2H 17 2803 Wear Limits For ElectricFuel Pump 218 2804 Fuel Quantity Sender ResistanceLimits 2112 2805 Fuel Quantit...

Page 298: ...plasticRepairs 3K6 5501 Elevator Balance Weight 4C9 5502 Rudder BalanceWeight 4C15 5701 Aileron BalanceWeights 4D14 6101 Propeller Specifications 4E6 6102 Troubleshooting Chart Engine Synchrophaser 4E13 7101 Troubleshooting Engine 4F4 7301 Troubleshooting Fuel Pressure Gauge 4G7 7302 Troubleshooting Fuel Flow Gauge 4G8 7401 Coupling Torques 4H5 7701 Troubleshooting Manifold Pressure Indicator 4H16...

Page 299: ...Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents Circuit Load Chart Electrical Wire Coding Electrical Symbols GRID NO 5B4 5B10 5B11 5B13 5B14 5B15 5B17 5B22 5B23 5C3 5C4 of Drill Sizes Introduction Page 18 Revised February 23 1982 2A20 ...

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Page 302: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 2A23 ...

Page 303: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 2A24 ...

Page 304: ...CHAPTER AUTO FLIGHT 2B1 ...

Page 305: ...AL CHAPTER 22 AUTOFLIGHT TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY A 10 82 A 10 82 22 00 00 22 01 00 GENERAL Non Piper A F C S Equipment Contacts 2B3 2B3 22 Cont Effec Page 1 Added October 15 1982 2B2 ...

Page 306: ... obtain servicedirection parts support and serviceliterature Bendix AvionicsDivision 2100N W 62nd Street Fort Lauderdale Fla 33310 305 776 4100 TWX5109559884 CollinsGeneral Aviation Division Rockwell International Cedar Rapids Iowa 52406 319 395 3625Telex 464 421 Edo Corporation AvionicsDivision Box 610 Municipal Airport Mineral Wells Texas 76067 817 325 2517Telex 76067 King Radio Corporation 400 ...

Page 307: ...CHAPTER COMMUNICATIONS 2B4 ...

Page 308: ... 10 02 23 10 03 23 10 04 23 11 00 23 11 01 GENERAL EMERGENCY LOCATOR TRANSMITTER Description Battery Removal and Installation Description Operation and Testing Pilot s Remote Switch Testing Emergency Locator Transmitter AVIONICS MASTER AND EMERGENCY SWITCH CIRCUIT Description and Operation 2B6 2B6 2B6 2B6 2B7 2B7 2 82 2B11 2B11 23 Cont Effec Page 1 Revised October 15 1982 2B5 ...

Page 309: ...releasing the latch on the strap and sliding the ELT off the bracket 5 Extend the portable antenna See Figure 23 2 6 Unscrewthe four screwsthat hold the control head to the battery casing and slideapart 7 Disconnect the battery terminals from the bottom of the circuit board 8 Discard old battery pack DO NOT EXPOSE TO FLAME CAUTION The batterypack is shipped witha sealanton the insidelip so that a ...

Page 310: ...he various FAA installations Beforeperforming any operational test of the ELT the followingprecautions should be observed CAUTION Testingof an EL T should be conductedin a screenroom or metal enclosure to ensure that electromagneticenergy is not radiated during testing If a shieldedenclosure is not available testing may beperformed in accordancewith thefollowingprocedures 1 Test should be no longe...

Page 311: ...ic downward swept tone 6 When the test is completed ascertain the transmitter ON ARM OFF switch is in the ARM position WARNING Whenever the unit is checked by moving the transmitter ON ARM OFF switchfrom theARM to the ON position it must then be moved to the OFF position if there is one before revertingto the ARM position again CAUTION Under normal conditions the transmitter switch must be set to ...

Page 312: ...tor Transmitter Schematic Narco NOTCH PIN PORTABLE STOP ANTENNA OPERATIVE BUT STORED VIEW VIEW B PULL TAB ANTENNA EXTENSION TAB ANTENNA EXTENSION TAB SET ON OFF ARM SWITCH TO ON PIN STOP ANTENNA POPSOUT OF CHANNEL AND DOWN VIEW C TO EXTEND TO FULL LENG Figure 23 2 Portable Folding Antenna Narco 23 10 04 Page 23 04 Revised February23 1982 2B9 ...

Page 313: ...G CONTACT FIXED ANTENNA S CABLE CONNECTOR AND CONTACT SEPARATOR Figure 23 3 ELT Using Fixed Aircraft Antenna Narco 2180 MAIN ELECTRICAL BUS I 2 TO CABLES CONTROLPANEL AVIONICSBUS 2 Figure 23 4 Avionics Master and Emergency Switch Circuit 23 10 04 Page 23 05 Issued September 2 1981 2B10 ...

Page 314: ...protectedbytwo 50amp circuit breakers Radio Master 1and Radio Master 2 on the Main Electrical Bus In the event of a malfunction in the Avionics Master Switch circuit a 50 amp Emergency Switch circuit breaker is provided between the Main Electrical Bus and the AvionicsBus With this circuit breaker engaged power is supplied directly to the 1 Avionics Bus allowing the avionics components operatingoff...

Page 315: ...CHAPTER ELECTRICAL POWER 2B12 ...

Page 316: ...9 Assembly Of Alternator 2C6 24 30 10 Testing Of Alternator 2C8 24 30 11 Precautions 2C8 24 30 12 Alternator Nomenclature 2C8 24 30 13 Alternator Service Test Specifications 2C10 24 30 14 Methods Of Checking Alternator Belt Tension 2C10 24 31 00 BATTERY 2C 12 24 31 01 Removal Of Battery 2C12 24 31 02 Installation Of Battery 2C12 24 31 03 Charging Battery 2C12 24 31 04 Battery Box Corrosion Prevent...

Page 317: ...ON SUBJECT GRID NO SUBJECT EFFECTIVITY 24 33 00 24 33 01 24 33 02 24 33 03 24 34 00 24 34 01 24 34 02 OVERVOLTAGE CONTROL Purpose And Operation Test Procedure Overvoltage Relay Operational Check AMMETER General Removal And Replacement 2C20 2C20 2C20 2C21 2C21 2C21 2C21 24 Cont Effec Page 2 Revised July 3 1984 2B14 ...

Page 318: ...the fieldvoltageof each unit is controlledindependentlyby its own voltageregulator Theseregulatorsare interconnectedelectronicallyso as to provideparalleledoutputs from their associated alternators under normal operatingengine RPM ranges The systemincorporatesseparate overvoltagerelays The overvoltagerelay willopenand removefieldvoltageto the unregulatedalternator in the event of a failure of the ...

Page 319: ...ter solenoid or control switch Binding worn or im properly seated brush or brushes with excessive sideplay Referto wiringdiagram and check all wiring Replacefaulty unit Brushesshould be a free fit in the brush boxes with out excessiveside play Binding brushesand brush boxes should be wiped clean with a gasoline undoped moistenedcloth A new brush should be run in until at least 50 seated however if...

Page 320: ...g free from sand or metal particles Dirty commutator Shorted grounded or open armature Grounded or open field circuit If commutator is rough or dirty smooth and polish with No 000 sandpaper If too rough and pitted remove and turn down Blowout all particles Removeand replace with an armature known to be in good condition Test and then replace with new part Motor operates at proper speed but fails t...

Page 321: ...cuit Clean as outlined above Test and replace defective parts Excessive wear and arcing of motor brushes Rough or scored com mutator Remove and turn commu tator down on a lathe Armature assembly not concentric Reface commutator BATTERY 24 V Battery will not hold charge Battery worn out Replace battery Charging rate not set right Reset Discharge too great to replace Standing too long Equipment left...

Page 322: ...battery Cracked cell Hold down loose Replace battery and level Compound on top of battery melts Electrolyte runs out of vent plugs Excessive corrosion inside container Battery freezes Frozen battery Charging rate too high Too much water added to battery Spillage from over fillings Vent lines leaking or clogged Discharged battery Water added and battery not charged immediately Leaking jar tighten R...

Page 323: ... cell only Replace battery BATTERY DISCONNECTSOLENOID Does not operate Open circuit Repair wiring Dirty contacts on con nector plug Open circuited solenoid coil Plunger binding Clean contacts Replaceunit Removeand wash plunger and housing thoroughly with carbon tetrachloride Change spring compression only as a last resort Intermittent operation Short circuited coil Looseelectrical con nection Repl...

Page 324: ...er but show up bad when measured inthousandths of an ohm or milliohms Therefore the mechanicneedstwo things 1 Equipment to measure resistancein milliohms within 20 accuracy 2 An ability to judge how many milliohmsis too many to identifytrouble The averageshop already has or can get a digital volt meter that will read a 12volt battery in four significantfigures like 12 62 volts The only other thing...

Page 325: ...1 22 025 6 2 22 16 14 14 87 18 05 19 63 Ara Itn 032 040 051 064 080 102 129 162 204 258 289 325 365 10 16 25 37 63 100 159 253 403 640 807 1018 1283 18 16 14 12 10 8 6 4 2 1 0 00 6 4 4 0 2 5 1 6 1 0 63 40 25 16 12 098 078 Times Wire and CableCo brand RG 58A U Coax value Center conductor 12 6 milliohm foot Shield 4 11 milliohm foot 289 365 492 782 Aluminum Wire 1 20 00 13 m MS DIGITAL VOLTMETER SET...

Page 326: ... output current of eitheralternator may be checked by pressing the appropriate button LEFT or RIGHT located above the ammeter on the overhead switch panel A shunt is installed between aircraft electrical bus and the positive terminal of the battery to allow measuring of the battery charge and discharge current with its ammeter An alternator inoperative INOP warning light is provided for each alter...

Page 327: ...to the slip rings 6 The drive end head supports a sealed prelubricated ball bearing in which the drive end of the rotor shaft rotates CHECKING ALTERNATOR PARALLELING SYSTEM The alternator paralleling system incorporates an ammeter which provides for an independent check of each alternator as well as the charge discharge current of the battery In the event either ALTERNATOR INOPERATIVE light begins...

Page 328: ...ltageispresentat both theoutput andfieldleads thealternator should becheckedfor apossible malfunction ADJUSTMENTS The onlyadjustmentnecessaryto maintain the alternator systemisthe adjustmentof the voltagecontrol on the voltageregulator Avoltageof 28 5 voltsis maintained Allother controladjustmentsaremadeat time of installation and need not be reset IMPORTANT Since the alternatorandregulatorare des...

Page 329: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL FOR TROUBLESHOOTING SCHEMATICS REFER TO CHAPTER 91 Figure 24 2 Alternator Paralleling System 2C2 24 30 05 Page 24 12 Revised July 3 1984 ...

Page 330: ...ethe nuts lockwashers flat washersand insulatorsfromthe output and auxiliaryterminal studs Notecarefullythecorrectassemblyoftheinsulator washersand bushings Usingthe specialtoolsshown in Figure 24 3 support the end head and press out the three negativerectifiers The end head can now be separated from the stator assembly 5 To removethe slipringend bearingand greaseseal it willbe necessaryto havea h...

Page 331: ...ve End Head 361 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 364 363 Figure 24 4 Removalof End Head Bearing 362 Figure24 5 Removalof Rectifier Figure 24 6 Removal of Slip Ring End Bearing 24 30 07 Page 24 14 Revised July 3 1984 2C4 ...

Page 332: ...ld indicate an open winding 2 Rectifiers A diode rectifiertester willdetect and pinpoint openor shortedrectifierswithout going through the operation ofdisconnectingthe stator leads However ifa tester isnot available testprobesand a No 57 bulb connectedin serieswitha 12 voltbattery can be used in the followingmanner Touch onetest probe to a rectifierheatsink and the other test probeto a lead fromon...

Page 333: ...shaft useatool that fitsoverthe shaftandagainsttheinnerbearingrace and press until the inner bearing race is against the snap ring retainer cup Refer to Figure 24 9 2 Carefullyinstallthe rectifiersin the slipringend head or rectifiermounting plateby supportingthe unit and using the specialtools illustrated in Figure 24 10 CAUTION Usean arborpress do not hammer Reconnect thestator leadsto the recti...

Page 334: ...4 9 Installation of Bearing Figure 24 10 Installation of Rectifier NUT LOCKWASHER FLATWASHER FIBERWASHER INSULATOR RECTIFIER MOUNTINGPLATE AUXILIARY TERMINAL TERMINAL STUD OUTPUT TERMINAL Figure 24 11 Terminal Assembly 24 30 09 Page 24 17 Revised July 3 1984 2C7 ...

Page 335: ... If a booster battery or fast charger is used its polarity must be connectedcorrectly to preven damage to the electricalsystemcomponents ALTERNATOR NOMENCLATURE 1 Bearings Theseunitshavea sealedball bearingat thedriveendanda two piecerollerbearingat the slipringend Theinnerraceispressedontothe rotor shaftand therestofthe bearingisintheslipringend head Whenthe unit isassembled the inner race aligns...

Page 336: ...L 370 369 INNER RACE GREASE CAVITY SPACER BEARING Figure 24 12 Slip Ring End Bearing Assembly Figure 24 13 Testing Alternator 371 C451 ALTERNATOR END VIEW SIDE VIEW Figure 24 14 Brush Installation Figure 24 15 Internal Wiring Diagram 24 30 12 Page 24 19 2C9 Revised July 3 1984 2C9 ...

Page 337: ...lip and reduce alternator output Consequently a belt should be checked for proper tension at the time it is installed again after 25 hours operation and each 100hours thereafter or whenever any work is performed that would affect belt tension NOTE A minimum of 030ofaninch clearance isrequired between theback face of the ring gearandtheedge of thebeltatboth locationsof passage 2 There are two satis...

Page 338: ...tor 2 Pull on the scale until a reading of 14pounds is obtained 10 pounds for used belts 3 Measurethe distance the belt has moved with the 10to 14pound load applied The distance deflection should be 5 16 inch If less than 5 16inch the belt is too tight C Note that the belt tension of the belt is adjusted by means of an idler pulley NOTE Thealternatorpulley and starterring gearsupportpulley must be...

Page 339: ... the airplane 1 Remove cellcaps and check fluid level 2 Begincharging rate of 2 amperes and finishingwith 1 ampere 3 Should the battery boil over clean per Battery Box Corrosion Prevention 4 When battery is completelycharged reinstall in the airplane BATTERY BOX CORROSION PREVENTION The followingchecksagainstcorrosion withinthe batterybox shouldbeperformedat leastevery30days 1 Check terminals and ...

Page 340: ...y charging current 2 When starting with a power cart and the airplane s battery is nearly depleted the procedure in Step 1 neednot befollowed The capacityof a powercart is sufficientto start anaircraft witha low battery If a six voltbattery isavailable itcan beconnectedinserieswiththe 24 voltexternalbatterytosupply30 volts for starting In this case use the same starting procedure as used with a po...

Page 341: ...willpass current in onlyonedirection forward direction and in this respect it may be compared to a check valve 3 ZenerDiode Thezener diode Symbol Z inadditionto passingcurrent intheforwarddirection willalsopass current inthe reversedirectionwhen aparticular valueof reversevoltageisapplied Thisprop erty makes it usefulas a voltage referencedevicein the regulator 4 Capacitor Thecapacitor Symbol C is...

Page 342: ...s C1 and C2 function together with their related transistors ina way to smooth alter nator output ripple and voltage spikes so that the alternator field current is controlled at a steady value 7 The LAMAR solidstate regulatorcontrolsalternator fieldcurrent toa steadyvalueas required by the electricalloadconditionsand enginespeed It doesnot continuouslyswitchfieldcurrent betweenhighand low values a...

Page 343: ...ot recommended Fully insulatedbolted terminalconnec tions are best and these should be attached when all power is removed as previouslydescribed 3 When installinga battery inan aircraft be surethat the battery negativeterminal is ina positionso that this terminal can be connectedto the battery ground cable for negativeground systems 4 The regulator under test is to be mounted on a groundedmetallic...

Page 344: ...g in the charging system or on the test bench for at least five minutes at a charge rate of from1O to 15amperes 4 With the connections made as shown in Figure 24 17 start the engine and adjust itsspeed to obtain an RPM of 1500 Adjust the carbon pile or accessory load to establish the 10to 15ampere load value Note that the battery charge current is indicated by the ammeter Therefore the current val...

Page 345: ...esofdiscussion 2 Lift the wirefrom the PAR terminal of either regulator and insulatethe free end so it willnot contact other circuitsor ground duringthe adjustment procedure Breakingthe circuitdisablesthe balancing circuit in both regulators 3 Turn off the LEFT alternator field switch All the RIGHT alternator switchesare to be on 4 Operate the RIGHT engineand alternator systemwitha load of 15to 30...

Page 346: ... table A stable reading shouldnot beexpected A lowermeter rangesuchas 10 voltsmay beusedfor thisad justment Nowreconnectthe wiretojoin the PAR terminals ofthe tworegulatorsandobservethat thevolt meter drops to a verylowvalue 0 2to 0 5 volt and it willbestable Continue operationsin thismanner for 5to 10minutes to establishinitialwarmupof the LEFT regulatorand alternator system Afterthewarmup period...

Page 347: ...switchis turned off Figure24 19illustrates the overvoltagecontrol connected in a typical Prestolite insulated field alternator TEST PROCEDURE Connect the relayas shown in Figure24 20 Usea 100ohm potentiometer of 15watt rating or more to adjust the voltage The voltmeteris usedto readthe voltageuntil the relayopens at whichtimethe voltmeter reading willdrop to zero Seetabulation for voltagereading T...

Page 348: ...ethe output voltageofthevariableD C powersupplyuntilthe LEFTovervoltagerelaytrips out An audibleclickwillbe heardwhenthe relayoperatesandthe VOMneedlemustdrop tozero volts Re cord the power supply voltmeter reading whichwas indicatedjust prior to the overvoltagerelay operating Voltagelimits are Min 31 50 volts Max 32 50 volts 7 Reducethe powersupply to zero Turn OFF the leftalternator sectionof th...

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Page 351: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 2C24 ...

Page 352: ...CHAPTER EQUIPMENT FURNISHINGS 2D1 ...

Page 353: ...SSENGER COMPARTMENT Divider Curtain and Curtain Track Removal Installation Passenger Seats Removal Installation FIRE EXTINGUISHER HAND HELD Portable Fire Extinguisher Inspection and Maintenance Shoulder Harness Inertia Reel Adjustment CARGO Loading Limitations Installation of Cargo Furnishings 2D3 2D3 2D3 2D3 2D3 2D3 2D3 2D3 IR 10 82 A 2 82 A 2 82 IR 2 82 IR 2 82 A 2 82 IR 2 82 IR 2 82 A 10 82 A 1...

Page 354: ... CURTAIN AND CURTAIN TRACK REMOVAL 1 Removeone of the two stop screwslocated at either end of the forward or aft curtain tracks and slide the curtains off the curtain tracks 2 The forward and aft divider curtain tracks can be removed by releasingthe remainingthree and five attachment screwsrespectively INSTALLATION 1 Install the curtain tracks by means of attachment screws 2 Slide the curtain on t...

Page 355: ...LOT SEATS 2 FIREEXTINGUISHER PILOT ONLY 3 FLASHLIGHT 4 FORWARD CURTAIN 5 THIRDANDFOURTH PASSENGER SEATS 6 FIFTH THRUNINTHPASSENGER SEATS 7 TENTH AND ELEVENTH PASSENGER SEATS 8 INERTIA REELASSEMBLY 3 2 Figure 25 1 Interior Arrangement 25 23 00 Page 25 02 Added February 23 1982 2D4 ...

Page 356: ...tructions on the label attached to the fire extinguisher 2 When inspectingthe fire extinguisher check the followingitems A Check that the inspectiontag is present and has been updated B Check that the locking ring is firmly in placeand has not been tampered with C Checkfor cleanliness dents scratches damageandcorrosion Iffound take extinguisherto a qualified dealer or distributor for testing andio...

Page 357: ...ppropriate weight distribution A blanket issecuredto an extrusion above the windowsto protect the interior duringcargo operation There are roller assembliesavailablewhichfit on the seat tracks to make handling of bulkyitems easy The use of the barriers and protective devicescan bealtered in such a mannerthat the aircraftcould servea dual purpose by convertingfor mixed cargo and passengeruse in cer...

Page 358: ...ABLE LBS 100 200 200 200 100 10 200 400 1800 900 200 2000 TOTAL 150EACH MAXIMUM TIEDOWN CAPACITY PER FOOTOF TRACK PERTRACK PERTIE DOWNRING 200 LBS 900 LBS 200 LBS CARGO MUSTBELOADED WITHINTHEWEIGHT ANDBALANCE LIMITSOFTHISAIRCRAFT J Figure 25 2 Cargo Loading Placard 25 50 02 Page 25 05 Revised November 17 1983 2D7 ...

Page 359: ...BARRIER 6 ROLLPIN 7 CARGOBARRIER ATTACHMENT FITTING 8 BOLT 9 CARGOBARRIER TRIMCOVER 10 P N 11 CARGO BLANKETS 12 CARGO NET 13 CARGOROLLER ASSEMBLY 14 TIEDOWNRINGASSEMBLY 15 TIEDOWNRINGASSEMBLY 16 CARGO STRAP 17 PLACARD 18 BUSHING 19 HEADLINER Figure 25 3 Cargo Furnishing Installation 25 50 02 Page 25 06 Revised October 15 1982 I 2D8 ...

Page 360: ...d ring into the seat track lock holes 6 Install tie down rings in wedjit holes if required 7 Install cargo rollers in desired positions 8 Install cargo loading placard 9 When cargo is loaded secure cargo with cargo net and tie down straps WARNING When loadingcargo check cargo loadingplacard Figure 25 2 END 25 50 02 Page 25 07 Revised November 17 1983 2D9 ...

Page 361: ...CHAPTER FLIGHT CONTROLS 2D10 ...

Page 362: ...l 2E17 27 10 07 Installation Of Aileron Trim Assembly Control Pedestal 2E19 27 10 08 Removal Of Aileron Trim Assembly Wing 2E19 27 10 09 Installation Of Aileron Trim Assembly Wing 2E20 27 10 10 Removal Of Aileron Trim Sender Assembly 2E20 27 10 11 Installation Of Aileron Trim Sender Assembly 2E20 27 10 12 Rigging And Adjustment Of Aileron Trim 2E21 27 10 13 Rigging And Adjustment Of Aileron Trim S...

Page 363: ...rim Assembly Control Pedestal 2F14 27 30 08 Removal Of Elevator Trim Assembly Elevator 2F15 27 30 09 Installation Of Elevator Trim Assembly Elevator 2F15 27 30 10 Removal Of Elevator Trim Sender Assembly 2F15 27 30 11 Installation Of Elevator Trim Sender Assembly 2F16 27 30 12 Rigging And Adjustment Of Elevator Trim 2F16 IR 2 82 27 30 13 Rigging And Adjustment Of Elevator Trim Sender And Indicator...

Page 364: ...Of Flap Transmission Functional Test Of Flap Transmission Installation Of Flap Transmission Rigging And Adjustment Of Flap System Flap Control Box Removal Of Flap Control Box Installation Of Flap Control Box Flap Control Amplifier Removal Of Flap Control Amplifier Installation Of Flap Control Amplifier Electrical System Functional Test Procedure STALL WARNING Description Removal Of Lift Detector I...

Page 365: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGEINTENTIONALLY LEFTBLANK 2D14 ...

Page 366: ... particularcontrol surface Asthe trim control wheelsare rotated theyin turn rotate the matingdrums at the control surfaces to actuate the particular trim tab A senderunit is installedat each trim tab and willtransmit asignalto theindicatorat thecontrol pedestal indicating the position of the trim tab The wingflapsystemconsistsofa flapselectorswitchlocatedon the instrumentpanel areversibleelectric ...

Page 367: ...ble tension too high Control column hori zontal chain improperly adjusted Pulleysbinding or rubbing Cables not in place on pulleys Bent aileron and or hinge Cables crossed or routed incorrectly Adjust cable tension Adjust chain tension Replace binding pulleys and or provide clearance between pulleysand brackets Install cables correctly Check cable guards Repair or replaceaileron and or hinge Check...

Page 368: ...l 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 Cables not in place on pulleys Broken pulley Linkage loose or worn Install cables Replace pulley Check linkage and tighten or replace Trim control wheel moves with excessive resistance System not lubricated properly ...

Page 369: ...pointer movesto extreme right position Lost motion between control wheeland ele vator Low voltage in system Circuit breaker open Master switch not on Trim indicator ground open Trim sender unit defective Trim indicator unit de fective Defectivewiring in system Trim sender unit ground open ELEVATORCONTROL SYSTEM Cable tension too low Check power supply Resetcircuit breaker Turn on master switch Che...

Page 370: ...levator travel cannot be obtained by adjusting elevator arm stops Cables crossed or routed incorrectly Elevator arm stops in correctly adjusted Elevator control rod in correctly adjusted Elevator cables incor rectly rigged between pulleys and brackets Install cables correctly Repair or replace elevator or hinge Check routing of control cables Adjust stop screws Adjust control rod Rig cables ELEVAT...

Page 371: ...dicator fails to in dicate any movement Cables crossed or routed incorrectly System incorrectly rigged Either or both trim drums incorrectlywrapped Trim sender unit not ad justed properly Low voltage in system Circuit breaker open pulleysand brackets Install cables Lubricate hinge If nec essary replace Check routing of control cables Check and or adjust rigging Check and or adjust rigging Adjust u...

Page 372: ...rudder to bellcrank are loose Check linkageand tighten or replace Replace pulley Tighten bellcrank bolts Excessiveresistanceto rudder pedal movement Systemnot lubricated properly Lubricate system Rudder pedal torque tube bearing in need of lubri cation Cable tension too high Pulleysbinding or rubbing Cables not in place on pulleys Cables crossed or routed incorrectly Lubricate torque tube bearings...

Page 373: ... motion between trim control wheeland 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 linkageand tighten or replace Trim control wheelmoves with excessiveresistance Systemnot lubricated properly Lubricate system Pulleysbinding or rubbing Cables not in place on pulleys Trim tab hingebinding Ca...

Page 374: ... ad Adjust sender unit correct trim justed properly Low voltage in system Check power suppl indicator fails to in Circuit breaker open Reset circuit breake movement Master switchnot on Turn on master switch Trim indicator ground Check ground wire open Trim sender unit de Replacesender unit fective Trim indicator defective Replace indicator u Defectivewiring in Check wiring system ator pointer Trim...

Page 375: ...d Flap solenoidcircuit breaker open Defectiveflap selector switch Defectiveup or down limit switch Defectiveflap solenoid Ground open from flap solenoid Defectivecircuit wiring to retract Up limit switchincor rectlyadjusted Flaps fail t tract Flap not actuate circuit CONTROLS cont Remedy Turn switch on Reset circuit breaker Replace selectorswitch Replace relay Check ground connec tion Check ground...

Page 376: ...n Bindingbetweentrack Refer to Riggingan and rollers Adjustment Slippingor stripped Replacetransmissio transmission Loose electricalcon Check and repair elec nection trical connections Transmissionneeds lubri Lubricate transmiss cation oneside fails to Broken flexibleactuator Replaceflexiblesha shaft Defectivetransmission Determinecause an replaceor repair Faulty time delay switch Check operation ...

Page 377: ...ing flap position Batteryswitch off Circuit breaker open Sender unit ground open Amplifiercomponent failure Flap motor circuit breaker off Flaps symmetrical Potentiometer failure Motor and or relay failure Power lost to amplifier Annunciator failure Flap asymmetric con dition Flap motor circuit breaker off Turn switchon Reset circuit breaker Check ground connection Replace the amplifier Reset flap...

Page 378: ...ould be taken with the appropriate surfacecontrol inits neutral positionand ten sion specifiedcorrectedto ambient temperature in the area wheretension is beingchecked Referto Chart 2702 NOTE Whenever theelevator controlsystem isserviced africtioncheck of thesystemmustbeaccomplished in accordance withinstructions giveninElevatorControlSystemFriction Measurement 8 Ascertainthat all cableguardpins ar...

Page 379: ...ANCE MANUAL DAMAGE HERE IMPROPER TOOL RESULTINGIN LOCKEDBALL A SPECIAL WRENCH MAY BE REQUI RED WITH A LONG THROAT ONLYCORRECTMETHOD Figure 27 1 Correct Method of Installing Rod End Bearings 27 00 03 Page 27 14 Issued September2 1981 2E4 ...

Page 380: ...wrapthe trim cableandremovethecableand lockpinfromthedrum Ifoneendof thecablehas been marked to facilitatehook up of the cableends note this locationinrelation to thedrum wheninstalling a new cable on the drum 6 Check the condition of the bushingsin the housing bracket for excesswear 7 To installand wrap the trim cable locate the center of the cable measuringfrom end to end 8 Insert the center of ...

Page 381: ...ssembly Removethe square tube assembly from behind the instrument panel C The square tube assemblymay be disassembledby 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 rollerfitting Removethe bearing housing from the fitting E Disassemblethe rollers fromthe fitting Notethe numberand locationof the ...

Page 382: ...nstalled torque tube assembly B Lubricate bearingsand attach bearings to their mounting locations C Slide the tube extensions inside torque tube and install the torque tube Pull the tube ex tensions through the bearings D Install the control sector with the cables attached on the end of extension tube With the sector tube extensionsand arms in position installroll pins and bolts Tighten boltsto a ...

Page 383: ...P 35 BOLT ASSEMBLY 36 FLEXIBLE JOINT 37 HOUSING SPROCKET 38 SCREW 39 CAP BOLT 40 CHAIN RIGHT SKETCH A 41 TURNBUCKLE 42 CHAIN LEFT 43 CONTROL WHEEL 44 CONTROL TUBE LEFT 45 SCREW ADJUSTMENT 46 BLOCK 47 HOUSING GUIDE ASSEMBLY 48 SCREW ADJUSTMENT 49 COVER 5O SPROCKET 51 LINK ASSEMBLY 52 CONTROL CABLE ELEVATOR 53 CONTROL CABLE AILERON 54 CHAIN AILERON 55 PLATE CABLE ATTACH 56 GUARD CHAIN 57 BUSHING 58 ...

Page 384: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 177 58 SKETCHC Figure 27 3 Control Column Installation cont 2E9 SKETCHD 27 05 02 Page 27 19 Issued September 2 1981 ...

Page 385: ... and washerson the roller housingand adjust with the use of the eccentric bushingsineach rollerto allow 003of an inch betweenthe squaretubeand rollers Finish byinstallingangles shimmedwithspacerwashersasrequired andtightenboltassembliesto astandard torque Recheckclearance between rollers and square tube and lubricate the rollers C Install the bearing housing with bearings on the roller housing Ins...

Page 386: ...ERON AND TAB REMOVAL OF AILERON CONTROL CABLES Refer to Figure 27 6 1 Remove the two left floor panels located between the forward bulkhead of the fuselageand the main spar Remove the left floor panel behind the main spar 2 Ifthe right or leftbalancecableisto beremoved removethecenterfloorpanelaft ofthemain spar 3 Remove the accessplates located under the wing along the trailing edge at stations 1...

Page 387: ... to the balance cable E Draw the cable from the wing into the fuselage F Remove the cable guard pins at fuselagestations 244 00and 274 00 G Draw the interconnectingcables forward through the fuselage INSTALLATION OF AILERON CONTROL CABLES Refer to Figure 27 6 1 The right or left primary control cables may be installed by the followingprocedure A From the accessholeat the aileronbellcrank draw thec...

Page 388: ...RE THE CABLE IS ROUTED BETWEENTHE STOP PIN AND THE PULLEY PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL D 24 64 VIEWA A Figure 27 6 Aileron and Aileron Trim Controls 27 11 02 Page 27 23 Interim Revision March 13 1990 2E13 ...

Page 389: ...45 A I I PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 178 SKETCHB SKETCHC SKETCHD SKETCHE C43 SKETCHG Figure 27 6 Aileron and Aileron Trim Controls cont 27 11 02 Page 27 24 Interim Revision March 13 1990 2E14 ...

Page 390: ... 00 4 Setcabletensionper Figure27 9and checkcontrol cableriggingandadjustment Alsocheckcable clearance 5 Install accessplates and panels REMOVAL OF AILERON BELLCRANK ASSEMBLY Refer to Figure 27 6 1 Removethe access plate to the bellcrankassembly 2 Relievecable tension from the control systemby rotating one of the turnbucklesattached to the bellcrank 3 Disconnect the turnbuckle ends from the forwar...

Page 391: ...ot be removed C Insert the tool between the bellcrank mounting brackets and over the end of the bolt from whichthe nut was removed It may be necessaryto loosenone of the primary control cablesor 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 lowersupport bracket witha small C clamp Place a small block of woo...

Page 392: ...ivenin Figure27 9 Stopsofboth bellcranks should contact their stop blocks at the same time and before the control wheelcontacts its stop 6 Simulate flight load by dropping both aileron trailingedges down to a maximum of 1 4 from neutral Thisadjustment isaccomplishedby adjustingthe control rod connectingthe bellcrankto theaileron NOTE If provisions are providedfor safety wiringthe nut and screwon t...

Page 393: ...ntrol Travels and Cable Tension AILERON BELLCRANKASSY SEENOTE 1 2 ASSY 1 SEE NOTE 1 NOTES 1 AFTER STARTING WIRE THRU HEAD OF SCREW MAKE ONE COMPLETE WRAP AROUND SHANK OF SCREW NEXTTO JAM NUT FINISH WIRING THRU HOLES PRO VIDED IN FORGING INSTALL SAFETYWIRE 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 DOWN AND...

Page 394: ...letension per Figure 27 9and check riggingand adjustment 8 If the trim cablesfromthe screwassemblywithinthewingare installed connectthecableendsat the turnbucklesat wingstation 90 00 Ifthe trimassemblywithinthewingisnot installed pullthecablestight and block them reachingthrough the accessopening in the wing at station 92 50 9 With the cables connected install the cableguard pin in the fuselageat ...

Page 395: ...lesleadingfromthefuselage 5 Connect the control rod to the trim screw 6 Connect the electrical leads to the trim indicator sender 7 Install the cableguard pin at wing station 150 00 8 Closethe rub blocks at wingstation 117 50and secure 9 If the complete cable system is installed set cable tension with the turnbuckles at wing station 90 00per Figure 27 9and check riggingand adjustment 10 Install ac...

Page 396: ...lowableis one and one quarter turns 6 Check riggingand adjustment of trim senderand indicator per the followingparagraph RIGGING AND ADJUSTMENT OF AILERON TRIM SENDER AND INDICATOR Refer to Figure 27 6 1 Remove the accessplates on the underside of the right wing at station 171 00 2 Ascertain that the aileron trim is properly adjusted per the precedingparagraph 3 With the arm on the sender shaft fr...

Page 397: ...W ASSEMBLY TRIM 23 BOLT ASSEMBLY STOP 24 BOLT ASSEMBLY ARM PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1051 25 BRACKET MOUNTING 26 SENDER 27 SHAFT SENDER 28 ARM SENDER 29 STOP TRIM SCREW 30 SCREW TRIM 31 HOUSING BRACKET 32 DRUM TRIM 33 GUARD BOLT 34 GUIDE ANTI ROTATION 35 NUT JAM 36 ROD END 37 BOLT ASSEMBLY 38 ARM TRIM TAB 39 CONTROL ROD 40 STOP TRIM SCREW 41 BOLT ASSEMBLY 42 RUDDER TUBE 43 BOLT ASSE...

Page 398: ...ENANCE MANUAL 192 194 J75 NEUTRAL SKETCHD 180 1046C NOTE BE SURE THE CABLE IS ROUTED BETWEEN THE CABLE GUARD AND THE PULLEY VIEWA A SKETCHF Figure 27 11 Rudder and Rudder Trim Controls cont 27 20 01 Page27 33 Issued September2 1981 2E23 ...

Page 399: ... re moved install pins at stations 140 00and 162 60 4 Connect the aileron and rudder interconnectingcables to the rudder cables 5 Set cable tension per Figure 27 12and riggingand adjustment 6 Install accessplates panels and seats REMOVAL OF RUDDER HORN Refer to Figure 27 11 1 Remove the left pilot s seat and floor panel to the left of the control pedestal 2 Remove the access plate under the rudder...

Page 400: ...evelingis not mandatory if a propeller protractor is used for this adjustment B Allowthe elevator to remain in its down position C Positionthejig on the elevatortorque tube and slideit to the leftuntil the centerlineon thejig plate aligns with the centerlineof the airplane D Set a bubble protractor to 29 28 and positionit on the centerlineofthejig plate Thisangle assures rudder travel measurement ...

Page 401: ...NLYTO AIRPLANESWITHOUTAUTOPILOT BRIDLE CABLES ATTACHED REFER TOAPPROPRIATE AUTOPILOT SERVICE MANUALFORPROPER CABLE TENSIONS WHEN ATTACHING BRIDLE CABLES 40 1 Chord LineLevel Neutral Position Figure 27 12 Rudder and Trim Tab Control Travels and Cable Tensions 1052 1 STOP BOLT 2 RUDDER HORN 3 RIGGING TOOL 4 POINTER S RUDDER 6 ELEVATOR Figure 27 13 Clamping Rudder Pedals in Neutral Position Figure 27...

Page 402: ...m screwassembly 10 Removethe bolts that attach the screwassemblyto itsmounting bracket Draw theassemblywith cables from the control pedestal INSTALLATION OFRUDDER TRIMASSEMBLY CONTROL PEDESTAL Refer to Figure27 11 1 Ascertainthat the cableis evenlywrappedon the trim drum centered and blockedto prevent un wrapping Refer to Wrapping Trim Drum 2 Insertthe trim screwshaft inthe end of the swiveljoint ...

Page 403: ...ables through the fin into fuselage and connect them at the turnbuckles at station 287 50 If the cablesfrom the control pedestalare not installed draw the cables tight and blockthem at the bulkhead at station 317 75 Install the trim screwassembly in the control pedestal 4 Remove the cable blocks from next to the trim screwassemblyand from the cablesleading from the control pedestal 5 Install the a...

Page 404: ... this measurement 4 Withthe trim screwin neutral position thetrailingedgesofthetab and ruddershouldalign Should they not removetheattachment boltand loosenthejam nuton the rod endat theaftendofthe tab control rod Turn the rod end until the trailing edgesalign Secure attachment bolt and rod endjam nut 5 Turn the trim in each direction to screw stops to check tab angle or measureddistancefrom the ce...

Page 405: ... The left pedals are free to be removed 11 To removethe outer torque tube assemblywith right pedals unbolt and separatethe tube sbearing blocks located on top of the wheel housing Note number of spacer washersbetweenthe bearing blocks 12 Remove the outer tube assemblyand disassemble 13 The torque tube bearings may be removed by removing the cap bolts that securethe bearings to their mounting brack...

Page 406: ... PIN BOLT 17 BOLT ASSEMBLY 18 RETAINER 19 BOLT ASSEMBLY 20 BOLT CAP 21 BLOCK BEARING 22 BRACKET MOUNTING 23 PLATE 32 24 ROD 25 CONTROL CABLE 26 BRAKE CYLINDER 27 PEDAL RIGHT OUTER 28 PEDAL RIGHT INNER 29 ROD STEERING 30 NUT JAM 31 BOLT ASSEMBLY 32 PEDAL LEFT INNER 33 PEDAL LEFT OUTER 34 BRAKE LINE SUPPORT CHANNEL 35 TORQUE TUBE GUARD SKETCH A 36 MACHINE SCREWS AND NUTS 37 SCREWS NUTS AND CLAMPS Fi...

Page 407: ...ard pinsat the con trol sectionand pulley disconnectingit fromthe lowerend ofthesectorand drawingitaft around thepulleys E The outboard left cable may be removed by removing the cable guard pin at the control sector if not previouslyremoved when removingthe inboard cable disconnectingit fromthe upper end of the sector and drawing it aft around the pulley 2 To removethe control cables that route af...

Page 408: ...owerendoftheelevatorbellcrank left cable at stations 111 00 162 00 203 00 244 00and 274 00 3 Set cable tension per Figure 27 17and riggingand adjustment 4 Install accessplates panels and seats REMOVALOF ELEVATORBELLCRANKASSEMBLY Refer to Figure 27 16 1 Remove the left pilot s seat and the floor panel located to the left of the control pedestal 2 Relievecabletension from the control systemby loosen...

Page 409: ...LE END 22 BOLT ASSY 23 BOLT ASSY 24 BOLT PIVOT CABLE 25 BRACKET CABLE 26 ROD END KLE 27 BOLT ASSY LE 28 JAM NUT 29 TRIM SCREW ASSY TROL 30 HOUSING 31 TRIM DRUM 32 SCREW 33 FWD STOP SCREW 34 ARM SENDER 35 SENDER 36 SHAFT SENDER 37 BOLT ASSEMBLY 38 BRACKET SENDER 39 ROD END CLEVIS 40 JAM NUT 41 AFT STOP SCREW 42 NUT SENDER 43 WASHER SENDER 44 ROD CABLE GUARD 186 180 44 NOTE BE SURE THE CABLE IS ROUT...

Page 410: ...1046 SKETCHB 115 I PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 268 20 40 3120 140 SKETCHD 43 SKETCHE Figure 27 16 Elevator and Elevator Trim Controls cont 27 30 04 Page 27 45 Issued September2 1981 2Fll ...

Page 411: ...er tension of the elevatorbalancespring connecta spring scaleto the aft end of the spring and pull rearward until 37 lbs 1lb tension is obtained with the elevator inthe neutralposition At this point observewhichholein the link is inlinewith the hood at the endofthe springandconnectthe spring into this hole in the link If 37 lbs 1 lb cannot bereachedwithexistinglink holes referto latestrevisionof P...

Page 412: ... TOAPPROPRIATE AUTOPILOT SERVICEMANUAL FORPROPER CABLE TENSIONS WHEN ATTACHING BRIDLE CABLES 8 Chord Line Leve Neutral Position Figure 27 17 Elevator and Elevator Trim Travels and Cable Tensions 189 188 1 ELEVATOR 2 RIGGING TOOL 3 STABILIZER 1 STOP BOLT SAFETYWIRE 2 STOP PLATE 3 TORQUETUBE 4 RUDDER 5 ELEVATOR Figure 27 18 Installation of Elevator Rigging Tool 2F13 Figure 27 19 Elevator Travel Stop...

Page 413: ...0 9 Removeonescrewfromeach setof rub blocksat stations 162 50 174 00and 215 00and openthem far enough to allow the cable ends to pass through 10 Removethe screwthat securesthe elevator trimcontrol wheelon thesplineshaftand removewheel 11 Remove the screwsthat attach the screwassembly to the control pedestal INSTALLATIONOF ELEVATORTRIM ASSEMBLY CONTROLPEDESTAL Refer to Figure 27 16 1 Ascertain that...

Page 414: ...to prevent them from unwrapping 2 Allowthe senderarm to rotate freelyon the sendershaftuntil trim riggingand adjustment ismade 3 Positionthe screwassemblywithsenderunit attached inthe horizontalstabilizer installtheattach ment cap boltsandsecure Do notconnectthefork ofthe trim screwto thecontrol rod and armassemblyuntil trim riggingand adjustment is made 4 Drawthe trim cablesthrough the stabilizer...

Page 415: ...his measurement is not correct disconnect the fork of the trim screw from the trim control rod if not previously disconnected and turn the trim screw until 14of an inch is obtained Hold the trim drum neutral while turning the screw The trim screw neutral position is at this measurement Reconnect with screw stop nuts down 5 With the trim screw trim drum and elevator in neutral position the trailing...

Page 416: ...evator trailing edge down approximately 2 inches from the neutral position 3 Record the force seeNote 2 required to raisethe elevatorthrough the neutral positionuntil the trailing edge is approximately 2 inches above neutral 4 Record the restrainingforce loweringthe elevator from the 2 inchup positionthrough the neutral position to the original 2 inch down position 5 Repeat above raising and lower...

Page 417: ...ault light Releaseof the switchwillclear the simulated fault and allowthe systemto respond normallyto selectorposition command Alladjustmentsare made withthe motor circuitbreaker pulled OFF and theflapsinthedown position Adjustment procedureswillrequire somespecialequipmentsuch as a digitalvoltmeterand flap transmission tools FLAP ACTUATOR MOTOR REMOVAL OF FLAP ACTUATOR MOTOR Refer to Figure 27 23...

Page 418: ...adjacent bars as measurement is stepped around commutator B Insulation resistancebetweencommutator and shaft should be 10megohmminimumat 85 ASSEMBLYOF FLAP ACTUATORMOTOR Refer to Figure 27 22 1 Assembleshoulderwashers contact studs lockwashersand nuts to front endbell Positionflat on contact studs parallel to the side of the brush holder Torque outer nut to 30 35inch pounds 2 Install insulator ass...

Page 419: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL RT3 LEFT CONTROL RHEOSTAT RL Figure 27 21 Flap System Diagram 27 50 06 Page 27 54 Revised November 17 1983 2F20 ...

Page 420: ...RONT 6 BRUSH ASSY 7 SPRING BRUSH 8 INSULATOR ASSY 15 2 18 1 6 7 SEE SKETCH A 9 SCREW 10 STUD CONTACT 11 NUT HEX 12 WASHER LOCK 13 SHOULDER WASHER 14 END BELL 15 BEARING BALL 16 WASHER SPRING 17 ARMATURE ASSY 18 SLEEVE AND MAGNET ASSY 19 PLATE IDENTIFICATION Figure 27 22 Motor Assembly Exploded View 27 50 06 Page 27 55 Revised November17 1983 2F21 ...

Page 421: ...stall accessplates and panels FLEXIBLE ACTUATOR SHAFT Refer to Figure 27 23 REMOVAL OF FLEXIBLE ACTUATOR SHAFT Refer to Figure 27 23 1 Remove the center floor panel located in the main cabin area 2 Remove the right and or left row of seats and floor panels aft of the main spar 3 Removethe aft accessplate on the fairinglocatedon the undersidebetweenthe fuselageand wing 4 Removethe accessplates at t...

Page 422: ...TRAP MOTOR SUPPORT 10 NUT 11 SHAFT ASSEMBLY 12 WIRE SAFETY 040 13 MOUNTING BRACKET MOTOR 14 ROD LINKAGE 15 BUSHING AND SCREW ASSY 16 FLAP HORN 17 BOLT ASSEMBLY 18 TUBE TRANSMISSION 19 SWITCH DOWN LIMIT 20 SHAFT SENDER 21 ARM SENDER 22 SENDER FLAP POSITION 23 SWITCH UP LIMIT 24 ADJUSMENT BOLT UP LIMIT 25 ADJUSTMENT BOLT DOWN LIMIT 26 ATTACHMENT BOLT ASSY 27 GROMMET 28 BOLT ASSY SENDER ARM 19 28 10 ...

Page 423: ...ithout removal of the transmission by the followingprocedures 1 Position the flaps in the extended position Down 2 Remove the accesscovers on the lower wing surface to gain accessto the flap transmissions 3 With the use of visegrip pliersand exertinglight pressure grasp the exposed portion of the screk close to the transmission as shown Refer to Views A and B 4 With the pliers secured to the screw...

Page 424: ...rencebetween RL RR RT2 AmplifierTrimmer Adjustment Left RT3 AmplifierTrimmer Adjustment Right VCl VC 10 10 05 The Control rheostat operated bythe Flap Selectorwillbereferredto throughout thisriggingprocedure as RC rheostat control The wing flap rheostats willbe designatedas RL rheostat left and RR rheostat right The voltages present or read at the center taps will be referred to as VC VLand VR res...

Page 425: ...st the DOWN limit switch 40 degrees NOTE The following rigging limits UP 0 1 0 0 to1 down APPROACH 15 1 DO WN 40 1 H Support the leftflapinthe fullDOWNposition asindicatedbythe riggingtool Turnthe trans missionsleevefor the leftflap out from itsforward stop recordingthe number of turns until the attachment holein the sleevealignswiththe correspondinghole inthe flap horn Temporarilyinstalltheattach...

Page 426: ...sition Whenthe flaps stop moving actuating arm may not engagethe UP limit switch record systemvoltages on a work sheetas follows VC VL VR DOWN Position X XX X XX X XX UP Position X XX X XX X XX V Thevaluesat the DOWNpositionhavealreadybeenestablishedfor VC VLand VRinStep Q preceding At this time enter the reading for VC VL and VR at the UPposition The worksheetmight now resemblethe followingexampl...

Page 427: ... With the flaps extended adjust VR at the rheostat shaft so that the voltage is 2x VCR 40V in the example below the original VR reading in the DOWN position Tighten the actuator arm Now adjust RT3 so that VR reads 10 10 05 below VC in the DOWN position 6 Reinstate the flap motor circuit breaker and select flaps full UP Record voltages as per Step U and repeat the procedures if required No more tha...

Page 428: ...Voltage is not to exceed 15 volts at any time NOTE The System should be allowedto warmup for approximatelyfive minutes before making any electricaladjustments 9 Run the flapsthrough three complete UP DOWN cyclesto ensure proper operation of flaps 10 Check flapdeflectionangleswithriggingtoolsinstalledat DOWN APPROACH and UPsettings observing Note below NOTE When measuringflap deflectionangles lift ...

Page 429: ...stall the flap control box in the instrument panel 2 Install the two screwsthat secure the control box 3 Connect the electrical leads 4 Install the knob FLAP CONTROL AMPLIFIER REMOVAL OF FLAP CONTROL AMPLIFIER 1 Open accessdoor in nose of airplane to gain accessto amplifier at station 35 00 2 Disconnectthe electrical plug from the amplifier 3 Remove the attaching screwsand remove the amplifier fro...

Page 430: ...of the connectorto either wirelead F4E of relayKI or wirelead F4D of relay K2to actuate either the up or down relay and run the motor 11 Checkthe 27 5 voltpowerat the drive motorswhileanother person isenergizingrelaysKI and K2 If 27 5 voltsare not presentat the drivemotor thecontactsof relaysKI and or K2aredefective Replacede fectiverelay s Ifthe drivemotor operates byenergizingrelaysKI and or K2l...

Page 431: ...leftwing Atab willextendbeyondthe leadingedgeat the point wherethe lift detector is mounted With the master switchin the ON position gentlylift tab stall warning horn and or light should activate On airplaneswith a stall warningtime delay the delay unit is mounted to the channel abovethe access panel at station 64 5 This time delay unit assures a horn sound when the lift detector closesand for fou...

Page 432: ...B 27 5 TO SW I CONTROL BOX 13 TO UP LIMIT SW J 28 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL215 NOTE SWITCHES SHOWNAT 15 OR MID FLAPRANGE 2 Figure27 25 Amplifier Electrical Schematic Calco P N 8502M 1 27 90 02 Page 27 67 Revised July 3 1984 2G9 ...

Page 433: ... MAINTENANCE MANUAL NOTE CALCO AMPLIFIERP N 8502M1 CAN REPLACEAMPLIFIER P N 8482 BUTAMPLIFIER P N 8482 CANNOT REPLACEAMPLIFIER P N 8502M1 R V UP RELAY MOTOR DOWN RELAY FAULT AMP 27 90 02 Page 27 68 Revised July 3 1984 2G10 ...

Page 434: ...GFORFLAP RIGGING TOOLP N 71505 02 AND71505 03 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL SKETCH B ACTUATORARM LIMIT ROLLER Figure 27 26 Flap Rigging Adjustments Figure 27 27 Use of Flap Rigging Tool 27 90 02 Page 27 69 Revised July 3 1984 2G11 ...

Page 435: ...ll help in positioning the switch at the proper position Loosenthe two Phillipshead screws one on eithersideof thevane Ifthestallwarningcomeson too late movethe switchup If the stall warningcomeson too early movethe switchdown Retightenthe screwsafter making any adjustments CAUTION Never try to adjust the switch by bending the vane The onlyway to test the accuracyofthe setting isto flythe airplane...

Page 436: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL GRIDS 2G13THRU 2G18 INTENTIONALLY LEFT BLANK 2G13 ...

Page 437: ...CHAPTER FUEL 2G19 ...

Page 438: ... Fuel Cells 2H 15 28 11 04 Repair Patch Heat Cure Method 2H 15 28 11 05 Repair Patch Air Cure Method 2H 18 28 11 06 Metal Fitting Sealing Surfaces 2H 18 28 11 07 Low Fuel Warning Sender Sealing 2H 18 28 11 08 Accessory Replacement 2H 19 28 1 1 09 Defect Repairs Of Fuel Cells 2H20 28 12 00 TESTING FUEL CELLS 2H20 28 20 00 DISTRIBUTION 2H21 28 21 00 FUEL VALVES 2H21 28 21 01 Removal Of Fuel Valves 2...

Page 439: ... 05 Installation Of Fuel Filter 214 28 23 00 CLEANING FUEL SYSTEM 215 28 24 00 ELECTRIC FUEL PUMP 215 28 24 01 Removal Of Electric Fuel Pump 215 28 24 02 Disassembly Of Electric Fuel Pump 215 28 24 03 Cleaning Inspection And Repair Of Electric Fuel Pump 217 28 24 04 Assembly Of Electric Fuel Pump 217 28 24 05 Adjustment Of Electric Fuel Pump Bench Test 217 28 24 06 Adjustment Of Electric Fuel Pump...

Page 440: ...ion Gated Delay Relay Removal And Installation WARNING INDICATOR Removal And Installation Removal And Installation Housing Of Fuel Flow Warning Circuit Of The Fuel Flow Sensor Probe Of Warning Indicator Lamps Of Warning Indicator FUEL QUANTITY Checking Fuel Quantity Gauges Checking Fuel Quantity Senders Adjustment Of Fuel Gauges Fuel Quantity Indicator General Troubleshooting 2111 2111 2111 2111 2...

Page 441: ...the fuelfilter and the electricfuelpump Thesepumps are providedto maintain fuelunder pressureto the other fuel pumps improvingthe altitude performance of the fuel system Each pump is controlled by a separate circuitbreaker located inthe circuit breakercontrol panel Thesepumps are activatedwhenthe masterswitch is turned on and continue to operate until the master switchis turned off or the circuit ...

Page 442: ...elcontrol panelto indicatewheneithershutoffvalveisclosed Alockon the firewallfuel shutoffleverhas beendesignedas a safetyfeaturetopreventaninadvertentfuelshutoff Fuel gaugeswillindicate the quantity of fuel in each cell that fuel is being drawn from TROUBLESHOOTING Troubles peculiar to the fuel system are listed in Chart 2801 along with their probable causes and suggestedremedies Whentroubleshooti...

Page 443: ...in wingsand repair or replace Fuel gauge indi cating approximately 1 2 tank when tank is full but will function normally on other tank Inboard fuel transmit ter assembly grounded Float and arm assembly of fuel transmitter s in wing sticking Check inboard fuel transmitter installation and repair Check fuel transmitters in wingsand repair or replace No fuel pressure indication Emergencyshutoff valve...

Page 444: ...hten Fuel valve leaks Worn O rings Replace O ringsor valve FUEL WARNING SYSTEM Fuel flow warning light fails to illuminate Bulb s burned out No power from bus Replace Checkand reset the gear oil temperature and fuel quantity in dicator circuit breaker Trace through systemfor an open circuit or faulty component Fuel flow sensor probe malfunction Gated delay relay malfunction Check free movement of ...

Page 445: ... circuit Fuel boost pump warning light fails to illuminate Normal operation of the gated delay relay Bulb s burned out No power from bus Replace Check and reset the gear oil temperature and fuel quantity indicator circuit breaker If the breaker is popped the fuel flow warning lights have failed also Tracethrough system for an open circuit or faulty component Pressureswitch malfunction Replace Fuel...

Page 446: ...arning lights Ground in circuit No power from bus Checkcircuit for ground Check and reset the gear oil temperature and fuel quantity indicator circuit breaker Trace through system for an open circuit or faulty component Test switch mal function Check connectionsand replace if necessary Allthe warning lights fail to extinguish Test switch grounded Correct or replace if necessary 28 00 02 Page 28 06...

Page 447: ...FUELQUANTITY GAUGE 12 FUEL TANKVENTCHECK VALVE 13 INBOARD FUELTANK 14 FUEL FILTER QUICKDRAIN 15 FUEL FILTER 16 CROSSFEED QUICKDRAINVALVE 17 FUEL TANKQUICKDRAIN 18 FUEL TANKSTRAINER 19 SURGE TANK 20 FLAPPER VALVE 21 LOWFUEL WARNINGPROBE 22 FUEL SENDER SELECTOR SWITCHES OPTIONAL 23 FUEL TANKSELECTOR VALVE OPTIONAL 24 OUTBOARD FUELTANK OPTIONAL 25 FUELREGULATOR SHUTOFF VALVE Figure 28 1 Fuel System S...

Page 448: ...s 9 Remove the cap bolts that secure the adapter bracket to the fuel cell and draw the adapter bracket out through the elongated accesshole being careful not to damage the cell 10 Placetape or another protective material around the cellaccessopening to preventdamageto the cell when removing 11 Push the celldown and work the nyloncord back through the cellhangersand rib bushingto the outboard ends ...

Page 449: ...ple fitting If the rubber has not deteriorated the fingernailwill glide across the rubber If a degraded condition exists the fingernail will dig into the rubber Usually the deteriorated rubber will have changed from a light yellowish tanto a dark reddish brown 4 Check the tension and knots of the two nylon support cords 5 Inspectthe interior of the cell for security of baffle and the free operatio...

Page 450: ...sided adhesive transfer tape No 7322 Piper part number 189 704 to the fuel liner at a point directly beneath the location of the fuel indicator sender unit float in empty position Leave the backing on the tape to prevent adherence to the cell until the cell is properly positioned 3 Should the cell be in its shipping container do not remove until ready for installation 4 Check to be sure that the c...

Page 451: ...spect for cleanliness Install flapper valve 16 Install the fuel cap adapter bracket by wrapping the bracket with a protective coverso as not to damage the cell insert it through the elongated access opening and slide it in position Install the gaske between the bracket and cell and start the cap bolts that attach the bracket to the cell Align the holes in the adapter with the holes in the skin bra...

Page 452: ...EMBLY PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1111 27 24 2 247 NOTE INSTALL WITH ARROW TOWARD FUEL CELL AND HINGE UP SKETCH C SKETCH A SKETCH B SKETCH E 18 CORD 19 CLAMP 20 PLATE DRAIN 21 SCREW 22 CAPBOLT 23 GASKET 24 WASHER 25 STRAINER FINGER 26 NIPPLE 27 CELL 28 PROBE LOWFUEL 29 SCREW NYLON 30 ZINCCHROMATE TAPE 31 COVER FUELCELL 32 GASKET 33 NUT 21 2 3 2 SKETCH E SKETCH D Figure 28 2 Fuel Cell ...

Page 453: ...ATTACHMENT 12 KNOT AND WASHER 13 VALVE CHECK 14 BUSHING SNAP 15 LINER CELL 16 LOOP ATTACHMENT 17 RIB ASSEMBLY 18 CORD 19 CLAMP 20 PLATE DRAIN 21 SCREW 22 SCREW NYLON 23 GASKET 24 STRAINER 25 NIPPI E 26 CELL 27 GAP BOLT 28 WASHER NOTE INSTALL WITH ARROW TOWARD FUEL CLL AND HINGE UP SKETCHC 112 21127 7 SKETCH D SKETCH D Figure 28 3 Fuel Cell Installation Optional Outboard 28 10 05 Page 28 13 2H11 Is...

Page 454: ... Avoid stepping on folds or creases in cells Do not carry cells by fittings Maintain originalcellcontours or folds when refoldingfor boxing rollingto insert in airframecavitiesor handling in the repair area The cells to be repaired should be placed on a well lightedtable Maintain natural contours ifpossible whilerepairing Preventcontact withsharp edges corners dirty floors or other surfaces Repair...

Page 455: ...olds B Wrap cell in moisture proof paper and place it in a suitable container Do not crowd cell in container use wadding to prevent movement C Stack boxed cells to allow access to oldest cells first Do not allow stacks to crush bottom boxes Leave cells in boxes until used D Storage area must be dry 70 F and free of exposure to sunlight dirt and damage E Used cells must be cleaned with soap and war...

Page 456: ...ho have received their trainingfrom persons who have been certifiedand trainedby Goodyearrepresentatives NOTE To determineiffuel cell is repairable reachthroughthefuel cell access plate and take a section of cell between thumb and forefinger Wipetheridgecreatedby this actionwithMEK Iffine cracksare evident thefuel cellis not repairable HANDLING OF REPAIR MATERIALS 1 All materials are to be protect...

Page 457: ...cure repair patches are to remainclampedand undisturbed for 72 hours at roomtemperature of approximately 75 F CAUTION For each 10 drop in temperature from 75 F add20hourscure time For example at 65 F curefor 92 hours II 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 repai...

Page 458: ... without trapping air Hold the unrolled portion of repair patch off the cementedsurface until roller contact insuresan air freeunion At thistimerepair patch may be moved by hand on wet surfaceto improve lap Do not lift repair patch slideit CAUTION Make surecellophane inside celloverinjuryremains in placeas anycementwillstick cell walls together without it asaseparator 10 Cover one smooth surfaceea...

Page 459: ...11Materials The followingequipment is necessaryto perform the repair Group II equipmentwillbefurnishedat additional cost iforderedbycustomer Foam Rubber Cloth Back Sheet 1 4 x 12 x 12 Paint Brush I inch wide Aluminum plates 1 4 x 6 x 6 Measuringcup 250 ml 1 Cellophane Sheet 12 x 24 NOTES Accessories order per individual cellrequirements Phenol plates phenol plate assembliesand phenol test equipmen...

Page 460: ...ontactwith hands eyesor clothing LOW FUEL WARNING SENDER SEALING Referto Figure28 7 The followinginstructionsand illustrationexplainthe recommendedproceduresfor sealingthe lowfuel warning probe to prevent any possiblefuel leakage 1 Defuelthe aircraft to obtain a fuel levelwhichis belowthe warningprobe and removethe access cover plates on both wingsabove the probes Disconnect the electricalspliceat...

Page 461: ...ot to pull cell lap open while peelingaccessoryoff Pull from blind side of a cell lap toward the exposed edge 5 Buff the cell surface under accessory with emery cloth to smooth roughness and prepare for cement NOTE Removal ofoldaccessory willprobably leave anuneven cavityand surface 6 Prepare replacementaccessory by buffing and washing contact surface Also wash cell surface seerepair patch 7 Apply...

Page 462: ...r of the cell 2 ChemicalTest A Attach test plates to all fitting openingsexcept one B Make up a phenolphthaleinsolution as follows Add 40 grams phenolphthaleincrystalsin 1 2 gallon or Ethyl Alcohol mix then add 1 2 gallon of water C Pour ammonia on an absorbant cloth inthe ratio of 3 mlper cubicfootof cellcapacity Place the saturated cloth insidethe celland install remainingtest plate D Inflate th...

Page 463: ...n that the fuel tank shutoff valve is off 3 Disconnectthe control cablefrom the valve handle 4 Disconnectthe linesfrom the valve and cover the ends to prevent contamination 5 Removethe valve from its attachment fitting NOTE Repair to the crossfeed valve is limited to replacing O ring packings 252 253 1 WASHER 2 STEM VALVE 3 ODY VALVE 4 SEAT VALVE 5 O RING 6 O RING 7 PACKING 8 PIN 9 NUT 10 ARM CONT...

Page 464: ...ded 3 Repair to the valve is limited to reconditioning of parts such as smoothingout minor nicksand scratches and the replacingof O ring packings NOTE Fittingin valveis special Do not useAN fittings ASSEMBLY OF CROSSFEED VALVE Refer to Figure 28 8 1 If seat valve was removed install the O ring packing and assemble the seat fitting on the valve body 2 Lubricatethe O ring packingswith a thin coat of...

Page 465: ...econditioningof parts such as smoothing out minor nicksand scratches and replacingof O rings ASSEMBLYOF FIREWALL SHUTOFF VALVE Refer to Figure 28 9 1 Ascertain that the snap ring is installed on the upper portion of the valve 2 Place new O ringson the valve 3 Lubricate the O ringswith DC 55 MIL G 4343 and insert the valve in the valve body Place the valve so that the valve is allowed only 90 trave...

Page 466: ...er of the pin that goes through the valve and valve body Refer to Figure 28 11 5 Movethe crossfeedhandle to the ON positionand ascertainthat there isa minimumof one inch between the center of the shaft pin and the valve body 6 Install safetywire through roll pin and around crossfeedcontrol shaft 7 Reinstallthe accessand selectorpanels ADJUSTMENT OF FIREWALL SHUTOFF VALVE 1 Remove the fuel control ...

Page 467: ...NJECTOR RIGHT 13 FUEL PUMP LEFT 14 INJECTOR LEFT 15 GAUGE FUELPRESSURE 16 GAUGE FUELFLOW 17 BULKHEAD 18 LINE RT DECK PRESSURE 19 LINE RT FUELPRESSURE 20 LINE RT FUELFLOWPRESSURE 21 LINE LT DECK PRESSURE 22 LINE LT FUELPRESSURE 23 LINE LT FUELFLOWPRESSURE 24 RIBASSEMBLY 25 BRACKET MOUNTING 26 LINE TO LT ENGINE 27 VALVE EMERGENCY SHUTOFF 28 CONTROL EMERGENCY SHUTOFF 29 BRACKET MOUNTING 30 FUEL PUMP ...

Page 468: ...RE SWITCH 42 R PRESSURE SWITCH 43 FUELBOOSTPUMP 44 LOCKWIRE MS20995C41 45 LINETO L PRESSURE SWITCH 46 BRACKET LEFT 47 BRACKET RIGHT 48 BUSHING 49 CROSSFEED CONTROL CABLE PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL C371 282 2 VIEW A A 1164 SKETCHC A Figure 28 10 Fuel System Installation cont 28 21 15 Page 28 28 Issued September2 1981 212 ...

Page 469: ...dge subassembly 5 Slide the filter cartridge from the stud The filter discs and washers need not be separated from the element outer tube for normal cleaning 6 If necessary to disassemble the filter cartridge remove the retainer cup from the outer tube and slide discs and washersfrom the outer tube Do not use a screwdriveror sharp tool that maydamage the discs 7 The filter bypassassemblymay be rem...

Page 470: ... itself in the filter body 3 Secure the filter cartridge with nut Torque nut 10to 15inch pounds Torque check nut against nut 40 to 60 inch pounds 4 Place bowl gasket on housing and install bowl gasket and cap nut Torque cap nut 60 to 80 inch poundsand safety 5 Install the filter INSTALLATION OF FUEL FILTER Refer to Figure 28 10 1 Connect the filter and electric fuel pump Tighten the jam nut on the...

Page 471: ...mp by removing the two motor thru bolts located inside the cover at the commutator end of the motor The motor of the pump assembly may beseparatedfrom the pump by removingthe four motor attachment screws Care should be taken whenseparatingthepump fromthe motor to insurethat theshaftendbearing whichisa pressfiton the armature shaft slipsout of the pump body housing After separation of the pumpand m...

Page 472: ...10 INSERT 11 BLADE 12 RING BLADE RET 13 ROTOR 14 WEAR PLATE 15 WEAR PLATE SPRING Figure 28 13 Electric Fuel Pump 16 PLUG INSERT 17 O RING 18 CAN COVER 19 SCREWS 20 INSERT BEARING RET 21 PISTON 22 SPRING VALVE 23 O RING 24 GUIDE ADJ 25 SCREW ADJ 26 LOCKNUT VALVE 27 RING RET TRU ARC 28 ADAPTER 29 SCREWS 30 SCREWS 28 24 02 Page 28 32 Issued September 2 1981 216 ...

Page 473: ...ll the O ringseal on the insertplugand installpluginto pump body Newerpumpswithwear plate in plug be sure the wear platespring is betweenthe wearplateand the plug beforeinstallingpluginto pump body 9 Replacethe seal cage seal washerand sealspring on the rotor shaftbeforeinstallingthe motor to the pump body 10 Replacethe motor on the pump bodybeingsure the femaleend ofthemotor shaftfitsoverthemale ...

Page 474: ... WORNPART LIMIT A B C D E 2502 MAX 6252 MAX 6252 MAX 0455 MAX 2493 MIN C DIM F G H J K INSERT WORNPART LIMIT 6245 MIN 6244 MIN 6246 MIN 298 MIN 0448 MIN B _ F ROTOR K A WEAR NOTCH EXCEEDING 010 IN DEPTH IN THIS AREA INDICATES THAT BLADE SHOULD BE DISCARDED 28 24 05 Page28 34 Issued September2 1981 218 ...

Page 475: ...rveall safety precautionswhen engineis running 5 When a steady flow of fuel is obtained close the bypass valve and check the reading on the pressuregauge It should read47 I psiifboost pumpis not installedor 40 I psi ifboost pump isinstalled maximum no flow If boost pump is installedand operated in conjunctionwithelectricfuel pump pressure reading should be 47 to 54 psi maximum no flow Do not keept...

Page 476: ...ut Turn boost pumps off lightsshould come on If lightsdo not comeon openthrottle and mixture control to relievepressureand then close the lights should come on and stay on NOTE Do not runpumps at no flow for more than one minute Troubleshoot the electrical wiring and refer to the paragraphs on adjustment of fuel boost pumps and warning sensors ifthe operational test does not check out REMOVAL AND ...

Page 477: ...sor probe from cell 4 Installation is the reverseorder of steps I through 3 5 There is no adjustment of the switch replace ifdefective WARNING INDICATOR REMOVAL AND INSTALLATIONOF WARNING INDICATOR LAMPS Each individualwarningindicator hasa spring loadedmechanismwhichallowseasyaccesstothelamps A small releaselocatedon the inboard sideof the indiator whenpushed allowsthe indicatorto pop out and to ...

Page 478: ...wire 7 Continue to add fuel in incrementsof 10 0and 14 0U S gallons to the outboard and inboard cells respectivelyfor eachquarter capacity of the cells At eachquarter increment until full checkthat the quantity pointer alignswith anypart of the index wire with eitherfueltank shutoff valvein the ON position 8 Should the gaugeand the amount of fuel in the cell not correspond the gaugemay becalibrate...

Page 479: ...mall insulated screwdriver reach through the light receptaclehole and move the index ire to align with the quantity pointer Should the position of the pointer vary slightly hen the fuel selector lever is moved from one cell to another the wire may be adjusted to compensate for this difference by setting the wire at an average distance between the two selected positions of the needle The wire shoul...

Page 480: ...in series the outboard sendermust be insulated from airframe ground TROUBLESHOOTING CHART 2805 FUEL QUANTITY INDICATORS Trouble Cause Remedy Fuel gauge fails to indicate Broken wiring Check and repair Circuit breaker out Gauge not operating Check for possible short circuit then reset breaker Replace Fuel gauge indicates empty when tanks are full Loss of ground Check ground connections at outboard ...

Page 481: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL GRIDS 2I15 THRU 2124 INTENTIONALLY LEFT BLANK 2I15 ...

Page 482: ...CHAPTER HYDRAULIC POWER 2J1 ...

Page 483: ...e 2J 19 29 11 08 Checking Handle Release To Neutral 2J19 29 11 09 Checking Priority Valve 2J20 29 11 10 Checking Main Relief Valve 2J20 29 11 11 Checking Hand Pump Relief Valve 2J20 29 11 12 Checking For Suction Air Leakage 2J21 29 11 13 Disconnecting Test Unit 2J21 29 12 00 HYDRAULIC POWER PACK 2J21 29 12 01 Removal Of Power Pack 2J21 29 12 02 Installation Of Power Pack 2J23 29 12 03 Disassembly ...

Page 484: ...26 Priority Valve 2K14 29 12 27 DisassemblyOf Priority Valve 2K14 29 12 28 AssemblyOf Priority Valve 2K14 29 12 29 Adjustment Of Priority Valve 2K14 29 12 30 Time Delay Check Valve 2K14 29 12 31 DisassemblyOf Time Delay Check Valve 2K14 IR 11 83 29 12 32 Assembly Of Time Delay Check Valve 2K14 IR 11 83 29 12 33 Door Vent Valve 2K15 29 12 34 DisassemblyOf Door VentValve 2K15 29 12 35 AssemblyOf Doo...

Page 485: ...k BenchTest Adjustment 2K19 IR 2 82 29 13 00 BLEEDING THE HYDRAULIC SYSTEM 2K19 29 14 00 REMOVAL AND INSTALLATION OF HYDRAULIC LINES 2K20 IR 11 83 29 15 00 REMOVAL AND INSTALLATION OF HYDRAULIC FILTERS 2K20 29 15 01 ReplacementOf Filter Elements 2K21 29 16 00 HYDRAULIC PUMP 2K21 29 16 01 Hydraulic Pump Operational Check 2K21 29 16 02 ProcedureAfter Hydraulic Pump Failure 2K21 29 16 03 RemovalOf Hy...

Page 486: ...movalOf Hand Pump DisassemblyOf Hand Pump Cleaning InspectionAnd Repair Of Hand Pump AssemblyOf Hand Pump Installation Of Hand Pump BleedingHand Pump Hand Pump Test Removalof Shuttle Valves Disassemblyof Shuttle Valves Cleaning Inspection and Repairof Shuttle Valves Assemblyof Shuttle Valves Installation of Shuttle Valves 2L2 2L2 2L2 2L3 2L3 2L3 2L5 2L5 2L5 2L6 2L6 2L6 2L6 EFFECTIVITY IR 11 83 A 2...

Page 487: ...system operation The Power Pack works in conjunction with the engine driven pumps solenoid valvesand hydrauliccylindersto perform the desired sequenceof operation as selectedby the control lever in the cockpit CAUTION Toinsurenot havingthe landinggearmoving to theup retracted position whilethe aircraft is on the ground thefollowing check should be performed prior to applying hydraulicpressureto th...

Page 488: ...hinstructions givenwithinthis 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 ...

Page 489: ...ge at selector valve One engine pump inoperative Replaceline Repair or replace cylinder Check valve operation Check systemopera tion Check systemopera tion Replacedamaged O rings Replacepump Selector handle re turns to neutral be fore cycleis complete Cable line or other obstruction restrictingthe travel required to fully select gear up or down Check and remove obstruction Selectorleverand or push...

Page 490: ...ing pressure Solenoid valvestuck in closed position Micro switchon power pack out of adjustment Turn off power and hand pump doors open Note With power off solenoid valve shuttles to door open and the doors may be opened without selectinggear 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 clo...

Page 491: ...YSTEM cont Trouble Cause Remedy Doors fail to close cont Solenoid valve stuck in door open position Check wiring to solenoid valve Circuit breaker out Check breaker Note Without electric power the gear doors will open but not close 29 00 02 Page 29 05 Issued September 2 1981 2J10 ...

Page 492: ... Position Release Time Delay Valve Hydraulic Fluid Required Weight Dry Power Pack Hydraulic Fluid Flow Rate Both Pumps Operating Reservoir Operating Fluid Level Engine Pump Minimum Maximum Reservoir Fluid Level Emergency Stand Pipe Level WTC 2135 1 See Note Below 1900P S I 1900 1950 P S I 2025 2100 P S I 1900 1950 P S I 0 to 100 P S I 150P S I Max 600 650 P S I I to 3 P S I 1220 1250 P S I 5 to 9 ...

Page 493: ...aminated fluid The cause and type of contamination should be determined and corrected Use the following steps to perform this operation 1 Remove the engine cowlings as explained in Chapter 71 2 Disconnect the hydraulic lines at the engine driven pumps 3 Drain the hydraulic fluid from the Power Pack reservoir by using the suction fill and drain fitting on the bracket located at the lower aft corner...

Page 494: ...pplicationdescribed CONNECTING TEST UNIT 1 Remove the access panel on the right side of the nose section and open access in hydraulics components cover 2 If the systemrequiresfillingonly removethe protective cap from the suction fill and drain valve mounted on the bracket located at the loweraft corner of the nose access panel openingand connect the pressurehose from the test unit Openthe valveon ...

Page 495: ... be a leak in the suction plumbing in which air is being drawn into the system Check all ground service suction connections for leaks 4 With landing gear extended place gear handle in full up position and record time required for gear to retract and doors to close Time should not exceed 9 seconds 5 seconds plus the time required for the time delay valve to operate 5 With landing gear retracted pla...

Page 496: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 3140 Figure 29 1 Schematic Diagram of Hydraulic System 29 11 06 Page29 10 Revised November 17 1983 2J15 ...

Page 497: ... VALVE 13 NOSE GEAR ACTUATOR 14 EMERGENCYSHUTTLEVALVE NOSE GEAR 15 EMERGENCYNITROGENCYLINDER NOSE GEAR 16 EMERGENCYSERVICEPORTS 17 EMERGENCYUNLOCK ACTUATOR NOSE GEAR 18 EMERGENCYSHUTTLEVALVE MAIN GEAR 19 EMERGENCYMAIN GEAR ACTUATOR 20 EMERGENCYUNLOCK ACTUATOR MAIN GEAR 21 EMERGENCYSHUTTLEVALVE MAIN GEAR 22 EMERGENCYMAIN GEAR DOORACTUATOR 23 EMERGENCYNITROGENCYLINDER MAIN GEAR NOTES 1 GEAR IS SHOWN...

Page 498: ...C PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL I Figure 29 2 Schematic of Power Pack ElectricalSystem 29 11 06 Page 29 12 Issued September 2 1982 2J17 ...

Page 499: ...EAR ACTUATING CYLINDER RIGHT 2 GEAR ACTUATING CYLINDER LEFT 3 DOOR ACTUATING CYLINDER RIGHT 4 DOOR ACTUATING CYLINDER LEFT 5 EMERGENCY HAND PUMP 6 FILTER RIGHT PUMP 7 FILTER LEFT PUMP 8 HYDRAULIC PUMP RIGHT 9 HYDRAULIC PUMP LEFT 10 POWER PACK ASSEMBLY 11 FILLER ASSEMBLY Figure29 3 Hydraulic SystemInstallation 29 11 06 Page 29 13 Revised November 17 1983 2J18 ...

Page 500: ...assvalve full open 5 Place the landing gear selectorhandle in the full down position 6 Veryslowlyclosethe bypassvalveuntil the handle tripsbacktoneutral Readthegaugeat the point of the handle trip The pressureshould beas indicatedin Chart 2902 Besureto allowtimefor the timedelay valve to open NOTE Onerelease valve serves to release thehandle from boththegear downandgear up positions If the handler...

Page 501: ...bilizeson test unit gauge Stabilizationindicatesreliefvalvesetting The reliefvalvepressureand flowrate are 1900to 1950 psi and 1 6gallonsper minute respectively as listed in Chart 2902 5 The Power Packmain reliefvalveadjustmentcan beaccomplishedwiththe PowerPackinstalledin the airplane Removethe top cover and drain fluid to gain accessto adjusting screw 6 Disconnectthe hydraulictest unit CHECKING ...

Page 502: ...wnneutralposition and the landinggear isdown and locked 2 Shutdown the test unit per instruction supplied with the unit 3 Closethe suction fill drainvalveinthe airplanebyplacingthecontrol leverinthedownpositonand disconnectingthe test unit hose from the fitting Install the protective cap over the fitting Disconnectand removethe test unit pressurehosefrom the pressurefitting intheairplane ifpreviou...

Page 503: ...AM 15 CLEVIS 16 CHECK VALVE L ENGINE 17 CHECK VALVE R ENGINE 18 VALVE 19 LINE PRESSURE L ENGINE 20 LINE RETURN L ENGINE 21 LINE GEARDOWN 22 LINE GEARUP 23 PANEL WHEEL WELL 24 HOSE GEARUP 25 HOSE GEARDOWN 26 LINE RETURN R ENGINE 27 LINE PRESSURE R ENGINE 28 LINE DOORCLOSE 29 LINE GEARUP 30 LINE DOOROPEN 31 LINE GEARDOWN 32 LINE HANDPUMPPRESSURE 33 LINE HANDPUMPSUCTION 34 CYLINDER NOSEGEAR 35 BLOCK ...

Page 504: ... systemper instructions given in this chapter 6 Perform a systemoperational check and inspection 7 Closethe hydrauliccomponentscoverand replacethe accesspanel on the sideof theairplane nose section NOTE If cablewasremoved from support thegear selector will require readjustment Refer to Adjustment of Gear SelectorHandle Mechanism DISASSEMBLY OF POWER PACK Refer to Figure 29 6 Afterthe Power Packhas...

Page 505: ... 1 DRAIN FITTING 2 MAIN RELIEF VALVE 3 PRIORITY VALVE 4 FILTER HAND PUMP SUCTION 5 HAND PUMP RELIEF VALVE 6 TIME DELAY CHECK VALVE 7 DOOR VENT VALVE 8 STANDPIPE FILTER Figure 29 5 Location of Power Pack Components 29 12 03 Page 29 19 Issued September 2 1981 2J24 ...

Page 506: ...T T 1020 MAINTENANCE MANUAL 37 NOTE THE SHADED PARTS POPPET 6 AND POPPETSEAT 7 ARE MATCHED PARTS AND MUST BE REPLACEDAS AN ASSEMBLY 3 Figure 29 6 Hydraulic Power Pack 29 12 03 Page 29 20 Revised February23 1982 2K1 ...

Page 507: ...SUCTION 49 SNAP RING 50 FILTER HAND PUMP 51 HAND PUMP RELIEF VALVE 52 ADJUSTING SCREW 53 SPRING 54 STEM SS BODY SECONDARY RELIEF VALVE 55 BALL 57 SEAT 58 O RING 59 CHECK VALVE TIME DELAY 60 SNAP RING 61 O RING 62 SEAT 63 BALL 64 PIN 65 BODY CHECK VALVE 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 TE...

Page 508: ...ecaughtand the selectorspoolwill thenbe difficult to remove CLEANING INSPECTION AND REPAIR OF POWER PACK 1 Discardall old O ringsand gaskets 2 Remove the line fitting caps and wash all parts in dry cleaning solvent Federal Specification P S 661 or equivalent and dry with filtered compressedair NOTE Duringinspection anduntilthePowerPackistobereassembled be careful to keepthepartsascleanaspossible A...

Page 509: ...icates50 psi maximum 5 Checkfor leaks there should be no external leakage 6 Crackthe ventfittingto releasethe pressure removethetestequipment drain thereservoirandcap the fittings 7 The hydraulicPower Pack is now ready to be installed in the airplane MANIFOLD DISASSEMBLYOF MANIFOLD Refer to Figure 29 7 1 Removethe door solenoidbyunscrewingit fromthe manifold Usetheproperwrench Removethe plunger re...

Page 510: ...E 7 SLEEVE TRANSFER VALVE 8 O RING SLEEVE 9 DOORSELECTOR SPOOL 10 SPOOLDOOR SELECTOR 11 DOORSOLENOID VALVEASSEMBLY 12 SOLENOID DOOR 13 0 RINGSOLENOID 14 SPRING PLUNGER RETURN 15 PLUNGER 16 PIN 17 LANDING GEARSELECTOR SPOOL 18 0 RING 19 SPOOLLANDING GEARSELECTOR 20 O RING 21 HANDLEDETENT ASSEMBLY 22 0 RING 23 PLUNGER 24 O RING 25 SPRING 26 RETAINER 27 O RING 28 FITTING 29 0 RING 30 BACKUP 31 NUT 32...

Page 511: ...ecessary to replace asanassembly only 2 Inserttheselector spoolintothemanifoldfromthelandinggearhandle endof themanifold Insert only until thetaperof theselector spoolis protrudingout themanifoldend approximately 06inches NOTE If theselector spoolisnotprotruding 06inches outofthemanifold oppositetherackwheninstallinginto thebody see Figure29 10 thegearwillnotbeengaged initsproper position Also don...

Page 512: ...oltsand torque to 35 inchpounds Do not overtorque boltsas this willcause binding of the landing gear selectorspool 5 Lubricate an MS28775 010O ringand an MS28775 008O ringand installon the bottom and top of the plunger respectively 6 Install plunger and lubricated spring into manifold 7 Lubricate threads of retainer install into manifold torque to 25 inch poundsand safety wire retainer to manifold...

Page 513: ...NT OF POWER PACK HANDLE RELEASE MECHANISM Refer to Figure 29 11 The followingprocedure outlines the adjustments to set the handle releasecartridgesand stops inthe correct position before installingthe Power Pack into the airplane I Rotate the input shaft into the gear up detent positionand adjust the left stop screwto allowa slight overtravelpast the detent position 2 Rotatethe input shaft intothe...

Page 514: ...M OPERATION OF GEAR SELECTOR HANDLE MECHANISM Refer to Figure 29 12 Operation of the gear selector handle must give the feel of having made a positive engagement with a detent With the selector handle in the up or down position and ina detent a forceof 3 1 2to 6pounds applied perpendicular to the centerline of the handle at the centerline of the centerline of the knob will be required to move the ...

Page 515: ... security of control cable connections to the actuator arms both the power pack and selector handle ADJUSTMENT OF GEAR SELECTOR HANDLE MECHANISM Refer to Figure 29 11 1 Disconnect the landing gear selector control cable from the selector handle on one end and the Power Pack control arm on the other end 2 Connect a spring scale to the control arm and pull both fore and aft perpendicular to thecente...

Page 516: ...ol arm and the selector handle 8 Connect the terminal ends of the control cable to the Power Pack control arm and the selector handle 9 Remove the drill from the rigging hole in the Power Pack CAUTION REMOVE DRILL FROM RIGGING HOLE Hole A Figure 29 11 NOTE Whenever the cable assembly is removedfrom the airplane and then reinstalled be sure to seat the cable where it passes through the pressure bul...

Page 517: ...the bore in the hod 5 Reassemble poppet into poppet seat Thepoppet and poppet seatare matched parts ASSEMBLY OF MAIN RELIEF VALVE Refer to Figure 29 6 item 1 1 Inspectthe poppet and the poppet seatfrom pitting or scoremarks The two parts are matched parts If either or both are damaged replaceasan assemblyonly 2 Lubricate and install the O ring and back up ring on the poppetseat insert the poppetin...

Page 518: ... ASSY 12 PIN WASHER COTTER PIN 13 SOLENOID 14 MOUNTING BLOCK 15 PANEL ASSY 16 LIGHT ASSY 17 CABLE ATTACHMENT PIN II TERMINAL 19 CLAMP 20 LOCKNUT 21 FIREWALL PLATE 22 GROMMET 21 BUSHING PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 21 9 17 20 Figure 29 12 Landing Gear Selector Mechanism Installation 29 12 25 Page 29 32 2K13 Issued September2 1981 ...

Page 519: ...nstallthe button and springandsecurethem withtheadjustingscrew Theadjustingscrewprovides adjustment for the priority valve Install flush at this time ADJUSTMENT OF PRIORITYVALVE Refer to Figure 29 6 1 Place the input shaft in the gear up position and removecap from the gear up fitting 2 Applypressureand notethe priority valvecrackingpressureby observingthe pressuregauge when fluid first starts to ...

Page 520: ...secure with 032 safety wire 3 Install the stem spring and adjusting screw into the retaininer with the adjusting screw flush 4 Lubricate threads install O ring on the valve body and install assembly into Power Pack body Torque to 55 inch pounds ADJUSTMENT OF DOOR VENT VALVE Refer to Figure 29 6 item 26 I Remove the cap from the door open fitting on the Power Pack and attach the pressure hose from ...

Page 521: ...K VALVE Refer to Figure 29 6 item 88 1 Install poppet spring and guide into fitting and secure with snap ring 2 Lubricate the threads on the fitting valve and install the required O ring closest to the flangedend 3 Install the back up ring and O ring on the fitting 4 Install the valve assembly in the body using a torque of 55 inch pounds HAND PUMP RELIEF VALVE DISASSEMBLY OF HAND PUMP RELIEF VALVE...

Page 522: ... the door open fitting 3 Adjust the adjusting screw at the top of the valveuntil the valve cracks at 2025 2100psi as given in Chart 2902 pumping slowly Bleed pressure by cracking the cap on the door open fitting after each adjustment HAND PUMP SUCTION SCREEN DISASSEMBLY OF HAND PUMP SUCTION SCREEN Refer to Figure 29 6 item 48 1 Remove the suction screen by removing the snap ring ASSEMBLY OF HAND P...

Page 523: ...ear up and down position a couple of times to insure proper actuating of switch from on to off Torque switch screwsto 20 inchpounds 3 Safety wire solenoid to bracket seeFigure 29 7 using 032safety wire 4 Connect the electrical wiresfrom the switch to the terminal block seeFigure 29 6 and secureto solenoid using plastic strap GEARUP 106A 145 2S PLUG MS3057A6A CLAMP DOWN WIRE 1 GAUGE HARNESS LENGTH ...

Page 524: ... test pressurehoseto the pressureinletport of the Power Pack The 2500psigaugeisto operate off the pressure line 4 Connect the suction hose to the suction port of the Power Pack 5 If a vent hose ispart of the testunit connectit to the vent port at the port at the top ofthereservoir 1 cover Do not plug vent port 6 Cap all other fittings with high pressure caps NOTE For the control of the door valves...

Page 525: ... to be tightenedso that theO ringsealsareon the non threadedportionof thefitting NOTE Some hydraulic lines are not interchangeable Refer to Parts Catalogfor correct replacementpart numbers REMOVALAND INSTALLATIONOF HYDRAULICFILTERS The hydraulicfilters located on the lowerright forward sideof each enginefirewall are removedby the following procedure 1 Remove the turtle back skin aft of the cowling...

Page 526: ...n position The one pump should build up pressure withinthe hydraulicsystem and return the selector handle to neutral position withinthree to nineseconds Againselectthe down positionand checkthe handle return time 3 Shut down the engine and repeat the precedingsteps for the other engine 4 Should it befound that the selectorhandle willnot return to neutralduringthe operational check for one pump but...

Page 527: ... SPRING 5 SEAL WITH GARTER SPRING 6 GASKET 7 DRIVE SIDE ASSEMBLY 8 LOCKNUT 9 O RING 10 CENTER PLATE ASSEMBLY 11 DOWELS 4 12 SCREW SQC HD CAP 13 REAR SIDE ASSEMBLY 14 STUD 15 O RING 16 DRIVE PIN 17 SECONDARY SHAFT 18 SECONDARY GEAR 19 DRIVE GEAR Figure 29 15 Hydraulic Pump 29 16 03 Page 29 41 Issued September 2 1982 2K22 ...

Page 528: ...5 Removethe rear side by rockingit from sideto sideand slidingit fromthe four dowels In caseof sticking tap gently with a plastic or rubber hammer 6 Removethe four studs from the rear side Removeand discard the large O ringsealfromthe rear side Pull the drive and secondary shafts until drive pins clear gears Removedrive pins 7 Removedrive gear secondary gear and secondary shaft by pulling from cen...

Page 529: ... 2 Replace retainer ring into drive sideseal bore 3 Install new O ringseal on drive side 4 Mate centerplate assemblywith drive sideassembly and align dowel pins Install drive shaft from engine side of drive side assembly 6 Install secondaryshaftinto centerplate Installdrive and secondarygearsonto driveand secondary shafts Besure the drive pin counter bore on the drive gear faces the pump rear side...

Page 530: ...nspect the lapped surface for scratches or signs of scoring Lap the surface to remove any scratches If deep scratches are present replace part Secondary Shaft Inspect the shaft for deep scratches in the bearing area If deep scratches are present replace secondary shaft Gears Visually inspect gears for evidence of chipped teeth or cracks around the bore Measure the gear O D which should be 1 1646 1...

Page 531: ...uction and pressure linesfrom the firewallfittings 2 Install caps on suction and pressure fitting at the firewallto prevent the lossof fluid prior to the hookup of the hydraulic lines 3 Holdingboth linesat a levelhigherthan the pump pour hydraulicfluid MIL H 5606 into theline 4 Removeone cap at a time from the firewallfittings and connectthe appropriate lineto the fitting trying not to spill any o...

Page 532: ... are limitedto polishingout smallscratches burrs etc replacingO ringsand worn or damaged parts ASSEMBLYOF HAND PUMP Refer to Figure 29 16 Lubricate all parts with oil per MIL H 5606prior to assembly 1 Lubricate O ring and install on seat 2 Install the spring ball and lubricated seat into the plunger and retain with snap ring 3 Install GT ringon the plunger 4 Install O ring and back up into insideg...

Page 533: ... O RING 16 GLAND 17 BACK UP 18 BACK UP 19 O RING 20 SCRAPER 21 BRACKET 22 QUICK CLICK PIN 23 LINK 24 QUICK CLICK PIN 25 SCREW 26 LEVER 27 GRIP 28 ROLL PIN 29 HANDLE 30 STOP 31 ROLL PIN 32 SPRING 33 DRIVE SCREW 34 HANDLE ASSEMBLY PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1326 T Figure 29 16 Hand Pump 29 21 05 Page 29 47 Issued September 2 1981 2L4 ...

Page 534: ...It is very important that the hand pump be operated very slowly as pressureisbeingincreasedtobleedthehandpump reliefvalve Ifthe handpump is operatedrapidly damageto thevalvecanoccurasair permitsparts to slam againsteachother Maximum indication of the gauge should be as indicated in Chart 2902 During the pumping operation the emergency hand pump should not feel spongy in either the up or down strok...

Page 535: ...ited replacingdefectiveparts and minor scratchesand scoresmay be removedbypolishingwith fineabrasive crocuscloth providingtheir removaldoes notaffecttheoperationof the shuttle valve ASSEMBLY OF SHUTTLE VALVES Lubricate all parts with hydraulic fluid per MIL H 5606prior to assembly 1 Install O rings 2 Install piston being careful not to damage O rings INSTALLATION OF SHUTTLE VALVES 1 Position shutt...

Page 536: ...1020 MAINTENANCE MANUAL 1 VALVE ASSEMBLY 2 PLUG ASSEMBLY 3 O RING 4 SEAL DOUBLE DELTA PISTON 5 AIR 6 PORT 7 FITTING 7 WTC 2217 Figure 29 17 Shuttle Valves WTC 2216 WTC 2217 29 21 12 Page 29 50 Added February 23 1982 2L7 ...

Page 537: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL GRIDS 2L8 THRU 2L24 INTENTIONALLY LEFT BLANK 2L8 ...

Page 538: ...MAINTENANCE MANUAL CARD 3 OF5 PA 31 350 T1020 PIPER AIRCRAFT CORPORATION PART NUMBER 761768 3A1 ...

Page 539: ... broken down into Sub System Sections These sections are identified by the secondelementof the standardized numberingsystem Thenumber 40 of thebasicnumber series 32 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 numberingsystem such as 32 40 01 This number could beassignedby the...

Page 540: ...tepage additionsare notidentifiedby revisionlines A referenceandrecordof materialrevisedis includedineachchapter sTableof Contents Effectivity The codesused in theeffectivitycolumnsof each chapteraredefinedas follows SAMPLEEFFECTIVITY CODES FirstRevision SecondRevision ThirdRevision FourthRevision AddedSubject MonthandYear 11 80 RevisionIndication MonthandYear 2R12 80 RevisionIndication MonthandYe...

Page 541: ...INTENTIONALLY LEFT BLANK 3A4 ...

Page 542: ... P N 117D Hartzell Propeller Inc P O Box 1458 1800 Covington Avenue Piqua Ohio 45356 MAGNETOS Installation Operation and Maintenance Instructions S 1200 SERIES MAGNETO IGNITION SYSTEM P N L 609 3 Bendix Electrical Components Division Sidney New York 13838 WHEELS AND BRAKES PARTS CATALOGS and Maintenance Instructions CLEVELAND WHEEL AND BRAKE Aircraft Wheel and Brake Division 1160 Center Road Avon ...

Page 543: ... AVIATION DIVISION Rockwell International Cedar Rapids Iowa 52406 319 395 3625 Telex 46 4421 KING RADIO CORPORATION 400 N Rodgers Rd Olathe Kansas 66061 813 782 0400 Telex 4 2299 Kingrad GLOBAL NAVIGATION 2144 Michelson Drive Irvine Ca 92715 714 851 0119 PIPER PUBLICATIONS PA 31 350 T 1020 Parts Catalog CONTINUOUS INSPECTION 761 775 Piper Aircraft Corporation 2926 Piper Drive Vero Beach FL 32960 7...

Page 544: ...ND SHORING LEVELING AND WEIGHING TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACT AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS AEROFICHE GRID NO IBI 1B4 ID23 IE13 IE16 1E21 IFI 1F4 1F8 IG12 III 2BI 2B4 2B12 2DI 2D10 2G19 2JI 3B1 3D9 3G1...

Page 545: ...MATIC SYSTEM VACUUM SYSTEM ELECTRIC ELECTRONIC PANELS AND MULTI PURPOSE PARTS STRUCTURES DOORS FUSELAGE STABILIZERS WINDOWS WINGS PROPELLERS STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM AEROFICHE GRID NO 3H11 314 3116 3J4 3J6 3J22 4B1 4B21 4C1 4C17 4D4 4EI 4E22 4F1 4GI 4G11 4H10 4H 14 411 Introduction Page 7 Revised February 2...

Page 546: ...L GAMA SYSTEM CHAPTER INDEX GUIDE cont SYST CHAP 80 81 91 95 SUB SYST SECTION TITI E STARTIING TURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 4111 4121 5B1 5FI Introduction Page8 Revised November 17 1983 3A9 ...

Page 547: ...ant Propeller and Cowl Flap 1G3 12 7 Lubrication Chart Doors and Seats 1G4 20 1 Torque Wrench Extension G 16 20 2 Method of Installing Rod End Bearings 1G16 20 3 Cherrylock Rivet Removal 1G17 20 4 Hose Line Markings IG19 20 5 Flareless Tube Fittings 1G20 20 6 Spray Patterns I H8 20 7 Improper Spray Technique 1 H 10 20 8 Spray Technique 1H 1I 20 9 Spraying Corners IHI 1 21 1 Heating and Ventilatinp...

Page 548: ...icated Oil Dipstick 1L3 21 31 Magnetic Clutch Installation 1L6 21 32 Expansion Valve Typical 1L8 21 33 Air Conditioning Outlets 1L1 21 34 Positioning of Airflow Probe 1L13 21 35 Sealing of Ducts IL14 21 36 Installation of VOI SHAN Seals IL14 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 ...

Page 549: ...nsion 2E 18 27 10 Safety Wiring Control Surface Stops 2E18 27 11 Rudder and Rudder Trim Controls 2E22 27 12 Rudder and Trim Tab Control Travels and Cable Tension 2F2 27 13 Clamping Rudder Pedals in Neutral Position 2F2 27 14 Installation of Rudder Rigging Tool 2F2 27 15 Rudder Pedal Installation 2F7 27 16 Elevator and Elevator Trim Controls 2F10 27 17 Elevator and Elevator Trim Travels and Cable T...

Page 550: ...29 8 Power Pack Handle Release Mechanism 2K8 29 9 Safetying Control Arms 2K9 29 10 Indexing of Selector Spool 2K10 29 11 Handle ReleaseAdjustment 2K1 29 12 Landing Gear Selector Mechanism Installation 2K13 29 13 Power Pack Test Harness Schematic 2K18 29 14 Hydraulic Filter 2K20 29 15 Hydraulic Pump 2K22 29 16 Hand Pump 2L4 29 17 Shuttle Valves WTC 2216 WTC 2217 2L7 30 1 Pneumatic Deicer System Ins...

Page 551: ...ng Gear Installation 3E16 32 8 Clamping Rudder Pedalsin Neutral Position 3E22 32 9 Rudder PedalsNeutral Angle 3E22 32 10 Aligning Nose Gear 3E22 32 11 EmergencyExtension System Installation 3F1 32 11a Test Equipment Installation EmergencyGear Extension System 3F5 32 12 Gear Actuating Cylinder Wiebel Tool WTC 2115 1 3F6 32 13 Unlock Actuator Wiebel Tool WTC 2215 3F7 32 14 Gear Door Actuating Cylind...

Page 552: ...t 3K7 51 4 Deep Scratches Shallow Nicks and Small Holes 3K7 51 5 Mixing of Epoxy Patching Compound 3K8 51 6 Welding Repair Method 3K8 51 7 Repairingof Cracks 3K9 51 8 Various Repairs 3K11 51 9 Repair of Stress Lines 3K12 51 10 Repair of Impacted Damage 3K12 51 11 Installation of Radome Erosion Shield 3K18 52 1 Cabin Entrance Door Latch Assembly 4B6 52 2 Pilot s Door Latch Assembly 4B10 52 3 Cargo ...

Page 553: ...ints 4G 15 74 3 Rotor Holding Tool Installed 4G16 74 4 Timing Kit Installed 4G16 74 5 Aligning Timing Marks Single Contact Assembly Magneto 4G 18 74 6 Forming Leads in Breaker Compartment 4G 18 74 7 Engine Timing Marks 4G 19 74 8 Magneto Timing Marks 4G 19 74 9 Deleted 74 10 Checking Harness Lead Insulation Resistance 4G22 74 11 Modified Pliers 4G22 74 12 Removing Spring From Lead Assembly 4G23 74...

Page 554: ...abricated Tool Checking Nose Gear Link Travel 5F7 95 5 Flight Control Rigging Tools 5F8 95 6 Fabricated Tool Checking Nose Wheel Alignment 5F9 95 7 Fabricated Jack Stand for Piper Jack Part No 18338 00 5F10 95 8 Fabricated Tail Stand 5F11 95 9 Fabricated Bellcrank Rigging Tool 5F12 95 10 Fabricated Aileron and Elevator Rigging Tool 5F13 95 11 Fabricated Rudder Rigging Tool 5F14 95 12 Suggested Des...

Page 555: ...e 2B23 2402 Alternator Test Specifications 2C10 2403 Alternator Belt Tension 2C11 2404 Hydrometer Percentage Guide 2C13 2701 Troubleshooting Surface Controls 2D16 2702 Control Cable Rigging Tension Vs Temperature 2E3 2801 Troubleshooting Fuel System 2HI 2802 Fuel Cell Repair Equipment Lists 2H 17 2803 Wear Limits For Electric Fuel Pump 218 2804 Fuel Quantity Sender Resistance Limits 2112 2805 Fuel...

Page 556: ...oplastic Repairs 3K6 5501 Elevator Balance Weight 4C9 5502 Rudder Balance Weight 4C15 5701 Aileron Balance Weights 4D14 6101 Propeller Specifications 4E6 6102 Troubleshooting Chart Engine Synchrophaser 4E13 7101 Troubleshooting Engine 4F4 7301 Troubleshooting Fuel Pressure Gauge 4G7 7302 Troubleshooting Fuel Flow Gauge 4G8 7401 Coupling Torques 4H5 7701 Troubleshooting Manifold Pressure Indicator ...

Page 557: ...sumable Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Circuit Load Chart Electrical Wire Coding Electrical Symbols 5B4 5B10 5B11 5B13 5B14 5B15 5B17 5B22 5B23 5C3 5C4 Introduction Page 18 Revised February 23 1982 3A20 ...

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Page 559: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3A22 ...

Page 560: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3A23 ...

Page 561: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3A24 ...

Page 562: ...CHAPTER ICE AND RAIN PROTECTION 3B1 ...

Page 563: ...0 11 01 Filter Replacement 3B10 30 11 02 Control Valves 3B10 30 11 03 Timer Maintenance 2B11 30 12 00 INSPECTIONS 3B11 30 13 00 GROUND TEST PROCEDURE 3B11 30 14 00 100 HOUR INSPECTION 3B11 30 15 00 BOOTS 3B12 30 15 01 Removal Of Boots 3B12 30 15 02 Repair Of Boots 3B12 30 15 03 Cold Repair 3B13 30 15 04 Vulcanized Repair 3B14 30 15 05 Installation 3B16 30 15 06 Preparation Of Leading Edges 3B16 30...

Page 564: ...Using The Ammeter 3C8 30 61 03 Helpful Tips 3C8 30 61 04 50 Hour Inspection 3C8 30 61 05 100 Hour Inspection 3C9 30 61 06 Brushes Brush Block 3C13 30 61 07 Checking For Brush Wear 3C13 30 61 08 Replacement Of Brushes 3C13 30 61 09 Alignment Of New Brushes 3C14 30 61 10 Replacement Of Brush Block Modular Brush Assemblies 3C14 30 61 11 Brush Module Replacement 3C15 30 61 12 Slip Rings 3C15 30 61 13 ...

Page 565: ...30 61 26 30 61 27 30 62 00 30 63 00 30 64 00 MAINTENANCE PRACTICES cont Installation Of Deicers And Required Materials Preparation And Application Of Sealer Wrinkled Deicers Electrical Check Final Electrical Check Of Propeller Deicers Installation Of Deicer Straps And Wire Harness BALANCING TIMER TEST OTHER COMPONENTS 3C22 3C24 3C24 3C24 3D1 3D1 3D2 3D3 3D3 30 Cont Effec Page 3 Revised February23 ...

Page 566: ...system cycletimer which in turn shifts the two stage regulators to highpressure 18psi opens the A systemsolenoidvalvetosend air to the wingboots and cuts off air to the copilot s gyros wheninstalled After six seconds the A systemsolenoid is closedand the B systemsolenoid is openedto send air to the tail boots for six seconds At the completionof the tailcycle the B system solenoidcloses the two sta...

Page 567: ...locked or not connected securely Blow out linesand inspect connections Make air leakage test Deicer pump valve not functioning Low air pump capacity Deicer puncture Check fitting in deicer port for proper installation Check performanceto manufacturers specifications Repair per specification or replace Deicers inflate indicator light does not function Ascertain that deicer boot switch is ON Indicat...

Page 568: ... TROUBLESHOOTING PNEUMATIC DEICER SYSTEM cont Trouble Cause Remedy DEICER BOOTS INSTALLED cont Piping or lines partially Inspect and blow out lines blocked Control valve partially Inspect and clean blocked 30 10 02 Page 30 03 Issued September2 1981 3B7 ...

Page 569: ...Check circuit from power source through circuit breaker to switch to timer to ground C Replace timer 2 Solenoid Valves Check solenoid valves Activate system switch to ON position Solenoid valve should be actuated immediately for 6 seconds as evidenced by an audible click that can be felt if hand is placed on a solenoid PRESSURE LEAKAGE TEST 1 This test can be performed in either the left or right ...

Page 570: ...IRECTIONAL GYRO PILOT 10 ALTITUDE GYRO PILOT 11 DIRECTIONAL GYRO COPILOT 12 ALTITUDE GYRO COPILOT 13 A SYSTEM WING SOLENOIDVALVE 14 B SYSTEM TAIL SOLENOID VALVE 15 MANIFOLD CHECKVALVE 16 PRESSURESWITCH 17 EJECTOR 18 RELAYVALVE 19 EMPANNAGE DEICING BOOT i Figure 30 1 Pneumatic Deicer System Installation Typical 30 10 06 Page 30 05 3B9 Issued September 2 1981 ...

Page 571: ...er A Place the new filter in the engine nacelleaft of the fire wall and connectthe air linesto the filter and secure with hose clamps B Install and secure accesspanel previouslyremoved 3 Removal of Air Filter IJI 3 located in lower left and right engine nacelleaft of the firewall above the air inlet opening A Remove the appropriate access panel on the outboard sides of the engine nacelle aft of th...

Page 572: ...ck valvesinthe linesfromthe pneumaticpumps close automatically Thedeicersystemshould bewithinone psigof the recommendedoperatingpressurewitheach inflation cycle If deicersdo notreachthe operatingpressure checkthe inflationtimetoascertainthat the solenoidval es are open the specifiedlength of time six seconds If this is not the cause of trouble or if the boots deflate slowly the lines or valves may...

Page 573: ...lethylketone in squirt can NOTE Disconnectlinefittings from boot fittings 1 Starting at one corner of the upper trailing edge of the deicer apply a minimum amount of solvent to the seam line while tension is applied to peel back the corner of the deicer 2 Using a pressure handle squirt can filledwith solvent separate the deicer boot from the surface for a distance of 4 inches all the way along the...

Page 574: ...pe the buffed area with a clean cloth slightly dampened with solvent to remove all loose particles B Selecta patch of ample size to cover the area Apply one even thorough coat of cement Part No 74 451 20 to the patch and the corresponding damaged area Allow cement to set a couple of minutes until tacky C Apply the patch to the deicer with an edge or the center adhering first Work down the remainde...

Page 575: ...o 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 Apply just enough tension on the surface ply when rolling to prevent wrinkling and becareful to prevent trapping air If air blistersappear after surfaceply is applied remove them with a hypodermic needl...

Page 576: ...1 2 in 1 8 in Steel stitcher Emery Buffing sticks Buffing Shield This cement will give best results with the patches in this kit The following items may be procured from the B F Goodrich Co Akron Ohio or other manufacturer as required 74 451 21 74 451 22 74 451 23 74 451 24 FSN8040 628 4199 and or FSN8040 514 1880 74 451 74 74 451 100 6 ft roll x 6 in wide 15ft roll x 2 in wide 4 ft long x 8 in wi...

Page 577: ...ed remove all paint includingzinc chromate primer 1 With one inch 1 masking tape mask off leading edge boot area following1 2 inch margin for non recessed boots Take care to mask accurately thus eliminatingthe need for cleaningoff excesscement later 2 Clean the metal surfaces thoroughly at least twice with MEK or acetone For final cleaning wipethe solvent film off quickly with a clean dry cloth be...

Page 578: ...se is damaged NOTE If non kink hose clamps are not available wrap each hose connection with severalturns offriction tape Over the tape wrap two separatebindings of safety wire about 1 2 inchapart Each of these bindings should consist of several turns of wire Twist together the ends of each binding to tighten Press the twisted ends down against the hose Finally wrap the wire with several additional...

Page 579: ...ercutthe cement thus preventinginjury to the part Excessivequantities of solvent must be avoided ADHESION TEST Using excessboot material trimmed from the ends of any wing and empennagedeicers prepare one test specimenfor each deicer installed This specimen should be a 1 x 8 inch full thickness strip of boot material cemented to the wing skin adjacent to installed boot following the identical proce...

Page 580: ... minute 3 Checkthe pressureswitchoperation withthe deicersystemunder pressure whilethebatteryswitch is in the ON position the indicator light will glow 4 With the master switchON and the deicercontrol switchin the OFF position pressthe indicator light to check the circuit and light bulb If the indicator light does not function check and reset the circuit breakers a short may exist 5 Remove the tes...

Page 581: ...ticky surface which is veryundesirable because it will pick up runway dust and prevent best ice removingefficiency Due to the natural abrasive effects on leading edges of deicers during flight reapply Icex every 150 flight hours on wingsand empennage deicers RESURFACING CONDUCTIVE CEMENT The following materials are required to remove and replace the old damaged coating 1 Fine grit sandpaper 2 Two ...

Page 582: ...to onepart isopropylacetate WINDOWS AND WINDSHIELDS WINDSHIELD WIPER MECHANISM REMOVAL OF WIPER MECHANISM Refer to Figure 30 3 1 Remove the access panel on the left side of the nose section 2 Gain accessto the wiper motor by removingthe upper panel of the baggagecompartment 3 Cut the lockwire at the bolt which secures the arm to the serrated converter shaft and remove the bolt 4 Loosen the adjustm...

Page 583: ...NDS 5 LOCK WIRE 6 ADJUSTMENT SLEEVE 7 CONVERTER 8 MOTOR 9 MOTOR SHAFT 10 NIPPLE 11 COUPLING 12 CONVERTER SHAFT 13 BRACKET 14 BRACKET 149 3 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1 5 148 7 12 2 11 10 5 Figure 30 3 Windshield Wiper 30 41 01 Page 30 18 Issued September 2 1981 3B22 ...

Page 584: ...secure with four screws Do not install the seal cover at this time 6 Apply a bead 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 Install and secure the nose baggage compartment upper panel into position 9...

Page 585: ...a slip ring assemblywitha brush blockassemblyto transfer electricalpower to the rotating deicers a timer an ammeter acontrol switch circuitbreaker shunt togetherwithwiringharnessesto completethe circuit Power is drawn from the aircraft electrical system To conserve electrical power current is cycled to the deicer heaters at timed intervals rather than continuously Each deicer has two separate heat...

Page 586: ...otating deicers a brush block assemblyis mounted to the engine or similar stationary member and has brushes which are spring loaded to press against the revolvingslip rings The slipring assemblyis provided as a slipring gear assembly which replacesthe original starter ring gear of the engine 3 Timer The timeris a sealedunit If found inoperative it must bereplacedas an assembly no field repairs are...

Page 587: ... the switch If voltage is satisfactory at switch output go to next step Test for voltage up to and out of ammeter If low or zero output and input satisfactory re place ammeter If no voltage to ammeter lo cate and fix open between switch and ammeter Disconnect harness at timer and check voltage at Pin B of harness to ground If none lo cate and correct open Ammeter shows nor mal current part of cycl...

Page 588: ...ge is found at deicer leads locate and fix open from deicer to ground Ammeter shows nor mal current part of cycle low current rest of cycle Inner and outer deicers heating same phase Locate and repair incorrect connections Open in deicer or slip ring leads High resistance in circuit with low current Disconnect deicer straps to check heater resistance If satisfactory locate and fix open in slip rin...

Page 589: ...put and input satisfactory replace ammeter If no voltageto ammeter locate and fix open betweenswitchand ammeter Ground between ammeter and timer Disconnect harness at timer and with ohmmeter check from Pin B of harness to ground If ground is indicated locate and correct Ammeter shows nor mal current part of cycle excess current rest of cycle Ground between timer and brush block Disconnect leads at...

Page 590: ... If timer does not cyclewith voltageat Pin B replace timer but be sure short causing original failure has been located and corrected Ammeter flicks between 30 second phase periods Loose connection between aircraft power supply and timer input If trouble occurs over entire cycle trace wiring from power source to timer input to locate and tighten loose connection Loose or poor connection timer to de...

Page 591: ...ty Refer to Ammeter flicks between 30 second phase periods Try jumper wireacross switch if radio noise disappears replacethe switch Wiring located within 8 inches of radio equipment wiring Relocate at least 8 inches away from input wiringto radio equipment Cyclingsequence not correct Rapid brush wear or frequent breakage Crossed connections Brush block out of alignment Check systemwiring circuit d...

Page 592: ...ANUAL 392 4 1 DEICER 2 SLIP RING ASSEMBLY 3 BRUSH BLOCK ASSEMBLY 4 WIRING 5 AMMETER 6 SWITCH CIRCUIT BREAKER 7 POWER SOURCE 8 SHUNT 9 TIMER Figure 30 4 ElectricPropeller Deicer Installation 3C7 30 60 01 Page 30 27 Issued September 2 1981 ...

Page 593: ...f the systemas given in Principles of Operation NOTE When troubleshooting first use the ammeter test and heat test to determinewhich circuitsare involved Usecircuit diagram for assistanceto checkvoltages or continuity HELPFUL TIPS 1 If the ammeter reading drops to one third normal current this indicatesthat one heater circuit is open or possibleimproper connectionsare allowing both inboard and out...

Page 594: ...ner Look for abrasion or cuts especiallyalong the leadingedge and the flat or thrust face If heater wiresare exposedindamagedareas or ifrubber is found to be tacky swollenor deteriorated as from oil or solvent contact replace the damaged deicer NOTE Checkthat strap restrainersarecorrectlylocatedand secure Look for cracksor otherdamage Operatepropellerfrom full pitch to feathering andcheck that dei...

Page 595: ...20 MAINTENANCE MANUAL 1254A PHASE 1 Figure 30 5 Electrical Diagram Showing Cycle Sequence Phase I 1254 PHASE 2 Figure 30 6 Electrical Diagram ShowingCycle Sequence Phase II 30 61 05 Page 30 30 Issued September 2 1981 3C10 ...

Page 596: ...0 MAINTENANCE MANUAL 1254C PHASE 3 Figure30 7 Electrical Diagram ShowingCycle Sequence Phase III 1255D PHASE 4 Figure 30 8 Electrical diagram Showing Cycle Sequence Phase IV 30 61 05 Page 30 31 Issued September2 1981 3C11 ...

Page 597: ...CE MANUAL 393 ASSEMBLY Figure 30 9 Typical Use of Dial Indicator 394 BRUSH LOCATED INCORRECTLY ON SLIP RING NOTCH WORN IN BRUSH DUE TO MISALIGNMENT Figure 30 10 Centering of Brusheson Slip Rings 30 61 05 Page 30 32 Issued September2 1981 3C12 ...

Page 598: ...iringin the area under examination at that moment In such case check continuity through affected harness while flexing and prodding eachwirein thearea that gaveinitialindicationof trouble Usethe wiringdiagramin Figure30 11to trace circuitry BRUSHES BRUSH BLOCK CHECKINGFOR BRUSH WEAR Insert small diameter wire through hole in rear of brush retainer assembly Refer to Figure 30 12 Replace brushes if ...

Page 599: ...e lead is connected to proper stud 7 Checkfor free movementof brushes by pushing the brushes back into the block and allowingthe spring pressure to return them DO NOT SNAP If free movement is impaired correctthe restriction and recheck 8 Reinstall the brush block to the mounting bracket utilizing the hardware removed NOTE New deicerbrushesmustbe run in a minimumof two hoursof engineoperationprior ...

Page 600: ...emblyon the aircraft and check adjustments SLIP RINGS MACHINING OF SLIP RINGS Slip rings with roughened or damaged surfacescan be machined to restore to serviceability Remove the starter ringgear assemblyfrom the aircraft to mount it in a lathe locatedconcentricallyin the latheand withnot over0 002wobbleor run out over360 rotation withrespectto mountingsurfaceof starter gear slip ring assembly Tak...

Page 601: ...Y1 16 INCHOFBRUSHSHOULD BE ALLOWEDTO PROTRUDE FROM BRUSHBLOCK THISIS THENORMAL POSITION OF THE BRUSH WHEN INSTALLED ONTHEAIRCRAFT PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL BRUSH BLOCK ASSEMBLY X DIMENSION INCHES MUSTREPLACE 1 9 16 4E1311 2 3E204 1 BRUSHES WITH RODS BRUSHES WITHOUT RODS 17 64 1 7 64 Figure 30 12 Brush Block Assmelbyand Brush Wear Check 30 61 13 Page 30 36 3C16 Issued September 2 198...

Page 602: ...p Rings A446 1 BRUSHMODULEASSEMBLY 2 NYLONSPACER 3E2011 28 4 ONLY 3 WIREMARKER A 1 4 ASSEMBLY B 2 ASSEMBLY C 3 ASSEMBLY NOTE THEALTERNATE STACKING ARRANGEMENT IS USEDWHEN THEREIS INTERFERENCE BETWEEN ADJACENT MODULE RING TERMINALS Figure 30 14 Brush Module Assembly 3E2011 Figure 30 15 Alternate Module Stacking Arrangement 30 61 13 Page 30 37 Issued September2 1981 3C17 ...

Page 603: ...ICER BOOTS RESISTANCECHECKOF DEICERBOOTS To determine incorrect resistance 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 pins C D Eand F of harness plug to ground it should read 1 55to 1 78 If this reading is not obtained disconnect the deicer lead straps to measure heater resistances indi...

Page 604: ...ne The following steps apply wherever cementing is specifiedin the text 1 Clean the area to be bonded or patched with MEK or acetoneto removeall grease and dirt It is vital that surfacebe cleanfor good cementingjob After last wipewith cleaner quickly wipesurfacewith a clean dry lint free cloth to remove solvent film 2 Apply one evencoat of 1300Lcement Minnesota Miningand Mfg Co to area to be bonde...

Page 605: ... care should be exercisedso that no additional damage is incurred to the deicer during and after removal 5 Remove residual cement from blade UseTurco No 3 or equivalent to help withdried cements PREPARATION OF SURFACE PRIOR TO INSTALLATION OF DEICER 1 Mark and cut from maskingtape a pattern the sizeof the propellerdeicerincludingthe firstinch of the lead strap Refer to Figure 30 18 2 Place a mark ...

Page 606: ...CENTER LINE PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 436 MASKING TAPE Figure 30 18 Installation of Deicer Boots 400 Figure 30 19 Wrinkled Deicers 30 61 20 Page 30 41 Issued September 2 1981 3C21 ...

Page 607: ...ATERIALS It is imperativethat the followinginstructions be followedexactlyto insure maximumadhesion to the propeller blades 1 When the cement coats are tacky dry on both propeller surface and deicer surface proceed as follows A Position in the deiceron the propeller leadingedge using centerlinesstarting from the hub Referto Figure30 18 Makesure that the strap willfall inthe positionpreviouslymarke...

Page 608: ...hyl Ethyl Ketone or Acetone Cleaning Cloth any clean lint freecloth I in Paint Brush 2 in Rubber Hand Roller 1 4 in Metal Hand Stitcher Scissors Turco 3 Turco Products Co Masking Tape Amount I pt per six blades 1 2 pt per six blades I 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 time ...

Page 609: ...nd blade SeeFigure 30 21 Immediatelyremove masking tape and allow filler to dry for six hours 7 Apply newmasking tape approximately 125of an inch beyondfillerto allowapplicationof sealer directly to metal Apply one evenbrush coat of 82 076 1 2sealer or C19861 C 16176paint over 125ofan inch of bare metal filled area and 250of an inch of deicer See Figure 30 20 8 Insure that sealer completely covers...

Page 610: ...er is installedon an airplane the deicercircuits on the propeller must be electrically isolated from the rest of the airplane wiringwhen making the above resistancecheck The isolatingcan be done by any one of the following methods A Remove the brush block B Retract the brushes and slipa sheet of paper betweenthe brushes and the slip rings If this method is used make certain that the brushes are no...

Page 611: ...r that the propeller can be moved from full low pitch through the feathering position without placing the straps in tension NOTE Deicers should haveapieceof grayplasticbonded totheair side shiny side ofthedeicer strapasshown inFigure 30 22 Thestrap restrainers should bepositionedasshowninFigure 30 23whenthe propellerbladesarein thefull featherposition 4 If damage occursto slip ringwireharness rubb...

Page 612: ...uit Now use voltmeter from ground to the timer socket and check that timer is cyclingto deliversystemvoltageto C D E and F contacts in that order The starting point is not important but sequence must be as given Each of these four contacts must deliver voltage for approximately 30 seconds in turn and there must be zero voltage on the three contacts not energized 3 If the timer meets these requirme...

Page 613: ...T 1020 MAINTENANCE MANUAL 403 STRAP RESTRAINER STRAP GRAY PLASTIC BONDED TO SHINY SIDE OF DEICER STRAP IN THIS AREA Figure 30 23 Propeller Blade in Feather Position END 30 64 00 Page 30 48 Issued September 2 1981 3D4 ...

Page 614: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL GRIDS 3D5 THRU 3D8 INTENTIONALL LEFT BLANK 3D5 ...

Page 615: ...CHAPTER LANDING GEAR 3D9 ...

Page 616: ...in Landing Gear Adjustment Of Main Landing Gear Alignment Of Main Landing Gear Main Landing Gear 3D23 3D23 3D24 3E1 3E2 3E7 2R 11 83 1R 11 83 3R 7 84 2R 11 83 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 NOSE GEAR AND DOORS 3E7 3E7 3E8 3E8 3E9 3E9 32 21 00 3...

Page 617: ...sion System for Operation and Leaks 3F4 A 11 83 32 32 00 GEAR ACTUATING CYLINDERS 3F6 32 32 01 Removal Of Gear Actuating Cylinder 3F6 2 82 32 32 02 Disassembly Of Gear Actuating Cylinder 3F6 32 32 03 Cleaning Inspection And Repair Of Gear Actuating Cylinder 3F7 32 32 04 Assembly Of Gear Actuating Cylinder 3F7 32 32 05 Installation Of Gear Actuating Cylinder 3F8 2 82 32 33 00 EMERGENCY UPLOCK ACTUA...

Page 618: ...32 43 01 Removal And DisassemblyOf Wheel Brake Assembly 3F15 2 82 32 43 02 Cleaning Inspection And Repair Of Wheel Brake Assembly 3F18 32 43 03 Brake Adjustment And Lining Tolerances 3F18 32 43 04 AssemblyAnd Installation Of Wheel Brake Assembly 3F18 2 82 32 44 00 BRAKE MASTER CYLINDER 3F20 32 44 01 RemovalOf Brake Master Cylinder 3F20 32 44 02 DisassemblyOf Brake Master Cylinder 3F21 2 82 32 44 0...

Page 619: ...EDAL ASSEMBLY Removal Of Pedal Assembly Installation Of Pedal Assembly POSITION AND WARNING Adjustment Of Nose Gear Up Light Switch Adjustment Of Nose Gear Down Light Switch Adjustment Of Main Gear Up Light Switch Adjustment Of Main Gear Down Light Switch Adjustment Of Main Inboard Gear Door Ajar Switches Adjustment Of Landing Gear Safety Switch GEAR WARNING SWITCHES Removal Of Gear Warning Switch...

Page 620: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3D14 ...

Page 621: ...s are not completelyclosed A warninghorn in the cockpit willsound wheneverpower from one or both engines is reduced below 10to 12inches of manifold pressure whenthe gear isnot inthe down lockedposition This horn willalso sound wheneverthe landing gear selectorhandle is in the gear up position whilethe airplane is on the ground and the master switchis on Ifthe gearselectorhandle can be movedtothe u...

Page 622: ...up posi tion while the LEFT main gear strut is com pressed or with the power off Ascertain 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 Gear retracts or ex tends before the doors open Priority valve leaks in power pack Solenoid valve stuck in closed position Check priority valve cracking pressure Turn off...

Page 623: ...uator when handle returns to stroke stroke neutral Gear doors pinching Relievedoor pinch by oid ch Main gear fails to lock up No red light on panel when gear are in transit No green light on panel when gear are down Uplock rod out of adjustment Actuator out of adjust ment Circuit breaker out Indicator light burned out Circuit wirebroken Circuit breaker out Indicator light burned out Lock switchdef...

Page 624: ...hrottle switches Adjust doors Replace defective switch Adjust throttle switches Replace switch Replace defective part Defective wiring Check wiring Nose gear shimmies during fast taxi take off and landing Internal wear in shimmy dampener Shimmy dampener or bracket loose at mounting Replace shimmy damp ener Replace necessary parts and bolts Tire out of balance Worn or loose wheel bearings Worn torq...

Page 625: ...internal parts in strut Incorrect operating pressure Service strut with air and or fluid Replace defective parts Inflate tire to correct pressure Wheel out of alignment toe in or toe out Check wheel alignment Nose gear fails to steer properly Oleo cylinder binding in strut housing Lubricate strut housing One brake dragging Steering arm roller sheared at top of strut Determine cause and correct Rep...

Page 626: ...snap ring install it into the annular slot in the oleo housing 9 Inflate the oleostrut in accordance withinstructions giveninOleoStruts Chapter 12 and remove the airplane from the jack MAIN GEAR AND DOORS MAIN GEAR OLEO STRUT DISASSEMBLY OF MAIN GEAR OLEO Refer to Figure 32 1 The main gear oleoassemblymay beremovedand disassembledfromthegearoleo housingwiththegear removed from or installedon the a...

Page 627: ...BE PISTON 23 BOLT ASSEMBLY 24 FORK 25 PIN COTTER 26 NUT AXLE 27 BOLT ASSEMBLY 21 PIN COTTER 29 BOLT ASSEMBLY 40 30 BEARING UPLOCK 31 TORQUE LINK LOWER 32 BOLT ASSEMBLY 33 TORQUE LINK UPPER 34 BOLT ASSEMBLY 33 35 WASHER SPACER 36 CONTACT SAFETY SWITCH 37 BUSHING 38 PLACARD SERVICE 39 SAFETY WIRE 40 SCREW 41 AXLE 42 POLY PAKSEAL STRUT USEDWITH CLEVELANDSTRUT USED WITH GOODYEAR 31 WHEELANDBRAKES WHEE...

Page 628: ... 1020 MAINTENANCE MANUAL 1010 SPECIAL SHIM P N 54066 00 USED ONLY IF RETAINERRING GROOVE IN ORIFICE TUBE IS 105 a INCHES WIDE a Figure 32 1 Main Gear Oleo Strut Assembly cont 32 11 01 Page 32 08 3D22 Issued September 2 1981 ...

Page 629: ...er tight 3 The piston tube assembly may be assembled to the oleo housing by first installing the tube com ponents on the tube In order slide onto the tube the retainer ring washer lower bearing with inner and outer O rings spacer and upper bearing Align reference marks on the upper bearing and piston tube to insure proper indexing of the lock pin holes of the upper bearing and tube and install ret...

Page 630: ...ectingthe uplock rod or cable from the hook and then the hook pivot bolt Disconnect the emergencyactuator rod from the uplock hook 8 The uplock rod or cable may be removed by disconnectingthe rod or cable endat the lock crank 9 The landing gear and upper drag link attachment plates may be removedby reachingthrough the access holes to the nuts that secure the plates While holding the nuts wrench th...

Page 631: ...betweenattachments to allow a minimum amount ofend play Tightennut on each pivotbolt to asnugfit allowingthe gearto swingfree and safety 5 The upper and lower side brace link assembly may be installed by the following procedure A Install the forward upper link pivot tube attachment fitting to the spar and secure withcap bolts B Slidethe pivotshaft through the attachment plate and into the attachme...

Page 632: ...able from the downlock hook 4 The through center adjustment of the side brace links is accomplished as follows A Maintainthe gear in the downlockedposition with both stop surfacesof the sidebrace links touching B Ascertain that the linkage is 0 063to 0 156of an inch through center C If one side of the stop surfacesdoes not touch it can be filedto obtain the desired through travel D If filing bring...

Page 633: ...IVOT 67 BOLT AN178 33 68 SPRING DOWNLOCK 69 ACTUATOR ROD EMERGENCY GEAR EXTENSION 70 ANTI ROTATION CLIP 1 BRACKET LOCK CYLINDER 2 LOCK CYLINDER 3 BEARING HINGE 4 BRACKET INBOARD DOOR 5 HINGE INBOARD DOOR 6 BEARING HINGE 7 DOOR INBOARD 8 BRACKET UPLOCK HOOK 9 SPRING UPLOCK 10 BOLTASSY AND BUSHING 11 HOOK UPLOCK 12 BOLTASSY AND BUSHING 13 NUT LOCK 14 ROD UPLOCK OR CABLE SEE NOTE 15 CYLINDER 16 SWITC...

Page 634: ...NTENANCE MANUAL 9 12 TORQUE80 100 IN LBS AFTER RIGGING BEND FLANGE TO CONTACT SIDE OF FORK SEE NOTE2 NOTES 1 GEARDOWNANDLOCKED 2 ANTI ROTATION CUPS TO BE USEDWITHCABLES ONLY SKETCHB 063 TO 156 THROUGH CENTEP Figure 32 2 Main Landing Gear Installation Left cont 32 12 04 Page 32 14 Revised July 3 1984 3E4 ...

Page 635: ...riginalsurface Replace pin if worn CAUTION Do not file pin 9 To replace pin cut thepin file off anyburrsleft bythecut anddrivethe pinoutfrom eitherside Do not try to drill thepin out asthis maydamage the link Installnewpin and flange 10 With thedownlockhookengaged pull the retractionarm locatedat thetop of theforwardside bracetowardsthedo nlockhookto thelimitsof itstravel Alsopullthedownlockoperat...

Page 636: ...cause of deflection in the linkage CA UTION When installing the fork bolt in the actuator rod end be sure that the forked end is properly aligned with the downlock operating rod or cable 14 Extend gear and as side braces approach the locked position apply a side forceto the wheel so that the hydraulic actuator must force the linkage into the locked position 15 Adjust the stroke control stop on the...

Page 637: ... 4 Set a squareagainst the straightedgeand spacer blockand checktoseeifitsoutstandinglegbearsagainstthespacer block NOTE A carpenter s square because of its especially long legs is rec ommendedfor checkingmain landinggear wheel alignment 3 If a gap appears at the rear betweenthe block and square the wheelis toed out and must be re aligned If a gapappearsat the forward end betweenthe blockand squar...

Page 638: ...edto replacinghingebearing brackets or rivets minor skin repairs and painting INSTALLATION OF MAIN GEAR DOOR ASSEMBLY 1 The inboard gear door is installed by aligningthe hingebracket holeswiththe bearings installing bolt assembly and securing Install the actuating cylinder rod to the door 2 The outboard gear door is installed by aligning the hinge bracket holes with the bearings in stallingbolt as...

Page 639: ...oleo housing with the gear removed from or installed on the airplane 1 Place the airplane on jacks Refer to Jacking Chapter 7 2 Place a drip pan under the nose gear to catch spillage 3 Remove air and fluid from the oleo Refer to Oleo Struts Chapter 12 4 To remove the complete cylinder and fork assembly from the oleo housing as shown in Figure 32 6 cut safety wire and remove bolt washer nut washer ...

Page 640: ... BOLTASSEMBLY 25 TORQUE LINK UPPER 26 TUBE PISTON 27 SHIMMYDAMPENER 28 BOLTASSEMBLY 29 BOLTASSEMBLY 30 BOLTSANDSAFETY WIRE 31 BRACKET 32 BUSHING 33 STUD DOOR UPLOCK 34 PLACARD SERVICE 35 HOUSING OLEO 36 BUSHING 37 STEERING ARM STOPASSEMBLY 38 BRACKET ASSEMBLY 39 PLUG FILLER 40 NOSEGEARSTEERING PLATE 41 VALVE AIR 42 ARM STEERING 43 PIN COTTER 44 SAFETY WIRE 45 DELETED 46 CAM FOLLOWER 47 O RING PACK...

Page 641: ...57 5 5 53 47 48 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 3142 14 4 5 I 45 II 17 22 Figure 32 5 Nose Gear Oleo Strut Assembly cont 32 21 01 Page 32 21 Issued September 2 1981 3E11l ...

Page 642: ...nd damage C Lock rings for cracks burrs etc D Cylinder and orifice tube for corrosion scratches nicks and excesswear E Orifice plate for hole restriction F Fork tube for corrosion scratches nicks dents and misalignment G Air vale generalcondition 3 Repair of the oleo is limited to smoothing out minor scratches nicks and dentsand replacement of parts 4 Individual replacementof wiper strips may be a...

Page 643: ...EERINGARM 10 SAFETYWIRE 11 BOLT CAP AN4H 5A TORQUE50 55 IN LBS 12 PLATEASSEMBLY 13 BRACKET GUIDE 14 RING RETAINER 15 CLAMP HOSE LIGHTS 16 VALVE AIR 17 HOUSING OLEO 18 SLEEVE Figure 32 6 Nose Gear Oleo Strut Assembly THIS SPACE INTENTIONALLY LEFT BLANK 32 21 03 Page 32 23 3E13 Revised November17 1983 3E13 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL I ...

Page 644: ...r to Figures 32 6 and 32 7 1 Remove the right and left access panels sta 70 0 to the aft interior portion of the nose section Remove the access plates located on the nose baggage compartment floor panel to gain access to the landing gear attachment bolts Refer to Access Plates and Panels Chapter 6 2 Place the airplane on jacks Refer to Jacking Chapter 7 3 With the hand pump retract the nose gear s...

Page 645: ...rings bushingsand ball joints for excessivewear corrosion and damage B Gear housing drag links idler link rods and attachment plates for cracks bends or mis alignment C Downlock spring for wear corrosion and not returning to complete compression D Uplockhook for wear and oversized bearing surfaces E Uplockroller for freedom of movementand minimum wobble F Both uplock rods sliding surfacesfor corro...

Page 646: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 32 22 02 Page 32 26 Revised July 3 1984 ...

Page 647: ...10 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 3269 56 25 207 41 SKETCHA SKETCHB Figure 32 7 Nose Landing Gear Installation cont 32 22 02 Page 32 27 Revised November 17 1983 3E17 ...

Page 648: ...positionand ascertain that it rotates freelywithno sideplay then safetyit 5 Installthe uplockrod or cableand blowdownactuating rod byattaching and securingthe proper ends tothe uplockhook and the otherend on the gearactuatingcylindersupport boltandtheotherendof the blowdownactuating rod to its support bracket 6 The idler link may be installed by the followingprocedure A Alignthe bolt hole inthe li...

Page 649: ...ubrication Chart Chapter 12 11 Check the nose gear for alignment and operation ADJUSTMENT OF NOSE LANDING GEAR Refer to Figure 32 7 1 With the airplane on jacks and gear extended disconnect both gear door retraction rods and secure the doors in the open position 2 To facilitate adjustment of the uplock disconnect the lower drag link from the landing gear oleo housing 3 Disconnect the actuating cyl...

Page 650: ...over the nut of the bolt that connectsthe lower link to the gear housing E Look through the sight hole in the plate to ascertainthat the centerof the bolt is 063to 156 inch below the centerlineon the plate F Removethe tool and reinstall the cotter pins II Adjust the retraction rod to provide a distinct snap through action as the idler linkage passes through center 12 Adjust the idler link stopbolt...

Page 651: ...o align in a lateral position Refer to Figure 32 8 H Adjust the rod end bearings of each steering rod to align the nose wheel with the chalk lineand to bring the rudder pedals into neutral angle forward and aft To align the nose wheel straight forward stand in front of the nose gear and align the center rib of the tire with the chalk line or lay a straightedge along the side of the tire and parall...

Page 652: ...AL TO FWD 3 87 IN NEUTRALTO REAR 3 63 IN 3 87 3 63 STA 65 75 NEUTRAL POSITION Figure 32 8 Clamping Rudder Pedals in Neutral Position Figure 32 9 Rudder Pedals Neutral Angle REFERTO CHAPTER95 FORFABRICATED TOOL Figure 32 10 Aligning Nose Gear 32 22 05 Page 32 32 Revised October15 1982 3E22 ...

Page 653: ...e door retraction mechanism ascertain that the retraction rod is disconnected dis connect the downlock spring and remove the snap ring that holds the retraction mechanism on its support shaft Pull the retraction mechanism from the shaft CLEANING INSPECTION AND REPAIR OF NOSE GEAR DOOR ASSEMBLY 1 Clean all parts with a suitable cleaning solvent 2 Inspect the door for cracks or bent skin loose hinge...

Page 654: ...sis provided byfour sealed disposablegasstoragecylinders one for each main gearand two for the nose gear Thesecylindersare locatedbeneathanaccesscoveron the cabin floor between the pilot s and copilot s seats GAS STORAGE BOTTLES REMOVAL OF GAS STORAGE BOTTLES 1 To removethe gas storage bottles gain accessto the extenderinstallationcoverplate beneath the access plate betweenthe pilot s and copilot ...

Page 655: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 3140 NOTE REFER TO THEFOLLOWING PAGESFORCALLOUTS Figure 32 11 Emergency Extension System Installation 32 31 04 Page 32 35 Revised November 17 1983 3F1 ...

Page 656: ...D MAIN RELIEFVALVE E LOW PRESSURETHERMAL RELIEFVALVE F TIME DELAY VALVE 1 POWER PACK CONT G HAND PUMP RELIEFVALVE H PISTON RELEASE LOCK I LANDINGGEARSELECTOR VALVE 12 RESTRICTOR VALVE 13 NOSEGEARACTUATOR 14 SHUTTLE VALVE NOSEGEAR 15 NITROGEN CYLINDER NOSEGEAR 16 TESTPORTS 17 UNLOCK ACTUATOR NOSEGEAR 18 SHUTTLE VALVE MAINGEAR 19 MAIN GEARACTUATOR 20 UNLOCK ACTUATOR MAIN GEAR 21 SHUTTLE VALVE MAINGE...

Page 657: ...d leave the cap loose on the fitting 2 Once the damage has been corrected on the hydraulic system connect the hydraulic test cart to the hydraulic test ports 3 Utilizing the test cart cycle the gear to the down position and then at least six times more to insure the shuttle valve and system is in the hydraulic mode It may be necessary depending on the type of damage that may have occurred to the h...

Page 658: ... 1000 psig 7 Open the dischage valve on the test rig and insure that the particular landing gear extends properly and that there is no mechanical interference during the extension cycle NOTE The main gear will contact the inboard gear doors during the extension cycle however these doors should not significantly impede the main gear extension Themain gear must not hang up on the main gear doors Sho...

Page 659: ... REGULATOR N2 0 1500 PSI GAUGE FABRICATED TESTFITTING REFERTO CHAPTER95 INDUSTRIAL NITROGEN BOTTLE VENT VALVE BOTTLEDISCHARGER IN AIRCRAFT Figure 32 1la Test Equipment Installation Emergency Gear Extension System 32 31 07 Page 32 39 3F5 Added November 17 1983 3F5 ...

Page 660: ... wheel well DISASSEMBLY OF GEAR ACTUATING CYLINDER Refer to Figure 32 12 1 Before disassembly establish rod end engagement distance to aid in preliminary assembly of the actuating cylinder 2 Loosen nut to disengage key and remove rod end 3 Cut safety wire and remove Remove nut key and stop from piston 4 Remove safety wire and end cap from the cylinder body by unthreading end cap and pulling out th...

Page 661: ...Install GT ring on the head of the piston 2 Install back up and O ring into outside groove of end cap 3 Install GT ringand scraper into insidegrooves of end cap Taperedlip of scraperto face outward 4 Lubricate the piston assembly the end cap assemblyand the bore of the cylinder body 5 Slide the end cap assemblyonto the piston assembly 6 Slidethe pistonwiththeendcap intothe cylinder tightentheendca...

Page 662: ...nation 3 Removethe bolts the uplock rod ends and remove actuating assembly DISASSEMBLY OF ACTUATOR 1 Remove two spiral pins and remove end cap and spring from actuator body 2 Remove the piston CLEANING INSPECTION OF ACTUATOR 1 Clean the actuator parts with a suitable solvent and dry thoroughly 2 Inspect the actuator interior wallsand piston exterior surfacesfor scratches burrs corrosion etc 3 Insp...

Page 663: ...f the piston 6 Remove end cap from piston 7 Pull race plunger and spring out of the clevis end 8 Remove GT ring from end cap 9 Remove O rings and the back up rings from the barrel 10 Remove GT ring from piston 11 Remove O ring and back up ring from plunger CLEANING INSPECTION AND REPAIR OF GEAR DOOR ACTUATING CYLINDER Refer to Figure 32 14 1 Clean the cylinder parts with a suitable solvent and dry...

Page 664: ...into groove inside the end cap 7 Slidepistoninto the end cap installsix ballsinto holesin pistonheadand insertassemblyinto bore of barrel Screwendcap onto barrel and align port inend cap withport inclevisend Tightennut against end cap and torque to 120to 140inch pounds 8 Secure nut to end cap using safety wire 9 Secure nut to clevisend using safety wire 10 Install locknut and rod end on piston 11 ...

Page 665: ... retraction iftheselectorreturns to neutral and the gear unsafelight remainslit againselect the gear up positionand hold the handle up for 4 secondsafter the gear unsafelightextinguishes Besure that the light has extinguishedbefore exceedingthe maximum gear extended speed WHEELS AND BRAKES MAIN WHEEL ASSEMBLY REMOVAL AND DISASSEMBLY OF MAIN WHEEL Refer to Figure 32 15 1 Place the airplane on jacks...

Page 666: ...ow minimum thickness Refer to Figure 32 16 Ascertain that the latest revision of Piper Service Letter 766 is complied with if applicable In addition also perform the same inspection given for nose wheel REPAIR OF MAIN WHEEL ASSEMBLY Repairs are limited to blending out small nicks scratches gouges and areas of slight corrosion plus the replacement of parts which are cracked or badly corroded NOTE R...

Page 667: ...seal 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 valve stem through valve hole Turn tire and outer wheel half over and place the spacer refer to Figure 32 15 and inner wheel half ...

Page 668: ...he wheelbearingassembliesmay beremovedfromeach wheelhalfbyfirstremovingthe snap rings that securethe grease sealretainers and then the retainers greasesealsand bearing cones The bearingcups should be removed only for replacement INSPECTION OF NOSE WHEEL ASSEMBLY 1 Degreaseall parts and dry thoroughly 2 Visuallycheck all parts for cracks distortion defects and excess wear 3 Check tie bolts for loos...

Page 669: ...nded operating pressure per Chapter 12 5 Flexthe forkenough to allowfor the installationof thewheelandspacertubes Insertthe axletube fork caps and tie bolt Adjust the tie bolt nut to allow the wheelto turn free yet not fit looseon the axle BRAKE ASSEMBLY REMOVAL AND DISASSEMBLY OF WHEEL BRAKE ASSEMBLY Refer to Figure 32 18 1 To removethe brakeassembly firstdisconnectthe brake linefrom the brakecyl...

Page 670: ...E TO 80 90 IN LBS 1 BOLT 2 WASHER 3 O RING 4 PISTON 5 INSULATOR 6 PLATE PRESSURE 7 FRICTIONSPRING 8 LINING 9 SHIM 10 PLATE BACK 11 PLATE TORQUE 12 NUT 13 CAP BLEEDER 14 SCREW BLEEDER 15 CYLINDER 16 BOLT ANCHOR 17 SEAT BLEEDER 18 O RING 19 WASHER 20 TUBE FITTING 21 NUT 22 HOSE INLET 23 O RING 272 049 MAX DISC TO LINING LININGS FULLY RETRACTED Figure 32 18 Wheel Brake Assembly Cleveland 30 123 32 43...

Page 671: ...DING PRESS HOLDINGFIXTURE PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 212 PRESS ANCHOR BOLT STEP A HOLDING FIXTURE FIXTURE STEP C STEP B CYLINDERBODY STEP D Figure 32 19 Removal and Installation of Anchor Bolts 32 43 01 Page 32 51 Revised November 17 1983 3F17 ...

Page 672: ...eed not be replaceduntil the thicknessof any one segmentbecomesworn to 100of an inch or unevenly worn ASSEMBLY AND INSTALLATION OF WHEEL BRAKE ASSEMBLY Refer to Figure 32 18 1 If anchor bolts have been removed they should be reinstalled as follows A Support anchor bolt in a holding fixture Refer to Figure 32 19 Step B B Aligncylinder body over anchor bolt Refer to Figure 32 19 Step C C Using a sui...

Page 673: ...NT 3 RESERVOIR ASSEMBLY 4 MASTER CYLINDER RIGHT 5 MASTER CYLINDER LEFT 6 VALVE PARKING BRAKE 7 HANDLE PARKING BRAKE 6 LINK FUSELAGE 9 HOSE FLEXIBLE 10 LINK GEAR 11 BRAKE ASSEMBLY Figure 32 20 Brake Installation Typical 32 43 04 Page 32 53 Revised November 17 1983 3F19 ...

Page 674: ...ing occurs check axle nut to insure proper seating Ifrubbingoccurs checkback plateassemblyand pressureplateassemblyliningsto besure that linings are fully seated 8 Connect the brake line to the housing and bleed brakes BRAKE MASTER CYLINDER REMOVAL OF BRAKE MASTER CYLINDER 1 Disconnectthe brake lines from the cylinderand placea protectivecover overthe lineopeningsto prevent contamination of the sy...

Page 675: ...eason it will be necessary to bleed the brake system as described below 1 Place a suitable container at the brake reservoir to collect fluid overflow 2 Remove the rubber bleeder fitting cap located on the bottom of the brake unit housing on the landing gear 3 Slide a hose over the bleeder fitting loosen the fitting one turn and pressure fill the brake system with MIL H 5606 fluid Refer to Figure 3...

Page 676: ...tches burrs etc and replacingvalve washer seal and O rings ASSEMBLY OF BRAKE MASTER CYLINDER Refer to Figure 32 21 1 Install O ring on the cylinderpiston Assembleonto the piston rod the piston spring washerseal and valve Allowthe valveto extendinto the baseofthe piston Slidethe O ringand washerinplaceand secure with self lockingnut 2 Install O ring seal on the packing gland Slide spring washer O r...

Page 677: ...gs Usecaution not to loosenthese when removing the fittings 2 From the valve body remove the valve spring and valve 3 To remove the valvecam 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 solventand dry thoroughly 2 Inspect valveand seat surfaces of valve body for excessivew...

Page 678: ...URE GAUGE PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL CATCH TANK 5 GALLON AIRPLANE RESERVOIR LEFT PILOTSBRAKE MASTER CYLINDER CLEVELAND BRAKESYSTEM CAP BRAKE BLEEDER FILLWITH MIL H 5606A SF A REGULATOR Figure 32 23 Bleeding Brake Pressure Pot 32 46 00 Page 32 58 Revised November 17 1983 3F24 ...

Page 679: ...trol arm ofthe power pack Removethe locknut and terminal from the end of the cable assembly D Cut safetywireand removelock nut nearest the end of thecableassembly Carefullypullthe cable assemblythrough the hole in bracket assembly E Disassemblethe firewallplatesand grommets and pull cableassemblythrough the holein the bulkhead at station 57 0 INSTALLATION OF GEAR SELECTOR HANDLE MECHANISM Refer to...

Page 680: ... 11 BRACKET ASSY 12 PIN WASHER COTTER PIN 13 SOLENOID 14 MOUNTING BLOCK IS PANEL ASSY 16 LIGHT ASSY 17 CABLE ATTACHMENT PIN 1 TERMINAL It CLAMP 20 LOCKNUT 21 FIREWALL PLATE 22 GROMMET 23 BUSHING PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL Figure 32 24 Landing Gear Selector Mechanism 32 47 02 Page 32 60 Revised November 17 1983 3G2 ...

Page 681: ...ioning the guards to the torque tube and removethe attaching hardware securingeach guard to the brake line support channel 7 Remove the small round access plate located on the right side of the fuselage at station 63 25 8 Remove the bolts that secure the retainer collars and left pedals on the torque tube 9 Slidethe torque tube out through the right sideof the fuselage Notethe number ofspacerwashe...

Page 682: ...EMBLY 20 BOLT CAP 21 BLOCK BEARING 22 BRACKET MOUNTING 23 PLATE 24 ROD 25 CONTROL CABLE 26 BRAKE CYLINDER 27 PEDAL RIGHT OUTER 28 PEDAL RIGHT INNER 29 ROD STEERING 30 NUT JAM 31 BOLT ASSEMBLY 32 PEDAL LEFT INNER 33 PEDAL LEFT OUTER 34 BRAKE LINE SUPPORT CHANNEL 35 TORQUE TUBE GUARD 36 MACHINE SCREWS AND NUTS 37 SCREWS NUTS AND CLAMPS PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1049 14 27 SKETCH 1050 ...

Page 683: ...around the torque tube and fasten to the guards with machine screws and nuts 10 Connect the steering control rods at the pedals Pedal and nose wheel alignment may be checked by referring to the appropriate paragraphs in this section 11 Set cable tension per Chart 2702 and check rigging and adjustment 12 Install access plates panels and seats POSITIONAND WARNING ADJUSTMENT OF NOSE GEAR UP LIGHT SWI...

Page 684: ...ingcheck and adjustment may be accomplished A By hand raise the downlock hook until the downlock switchis heard to actuate click B With hook raised placea 070of an inchwirefeelergaugebetweenthe hook and bottom sur face of the slot in the side brace link Refer to Figure 32 26 C Lowerthe hook allowingit to rest on the feelergauge Theend of thegaugeshould beeven with the lock pin The switchshould not...

Page 685: ...he bottom of the gear housing Hold the gear at this measurement 3 Adjust the switchdown until it actuates at this point Secure the switch 4 Extend andthencompressthestrut to ascertainthat the switchwillactuate inthe last 250 125inch of oleo extension 5 Remove airplane from jacks GEAR WARNING SWITCHES REMOVAL OF GEAR WARNING SWITCHES Refer to Figure 32 27 The gear warningswitchesare located within ...

Page 686: ...EVER RIGHT THROTTLE 3 ACTUATOR LEFT THROTTLE 4 ACTUATOR RIGHT THROTTLE 5 SCREW ADJUSTMENT 6 BRACKET MOUNTING 7 SCREW ADJUSTMENT 6 BRACKET MOUNTING 9 SWITCH HORN 10 SPACER BLOCK 11 SWITCH HORN 12 SPACER BLOCK 13 SPRING TENSION Figure 32 27 Gear Warning Switches Installation 32 61 01 Page 32 66 3G8 Revised November 17 1983 3G8 ...

Page 687: ... Schematic Chapter 91 for wireinstallation B Place the switch and spacer block in its mounting bracket and install attachment screws It will be necessary to swing the bracket of the other switch and spacer block forward to install the attachment 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 ADJUSTME...

Page 688: ... when 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 warning system when the gear is up and power is reduced to the desired manifold pressure B If the horn fails to operate at the desired settings mark the throttles at the proper manifold pressure and repeat the preceding adjustment procedure as described i...

Page 689: ...NOSE GEAR PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL WEAR LIMITS Figure 32 28 Nose Gear Wear Limits 32 90 01 Page 32 69 Revised November 17 1983 3G1l ...

Page 690: ...g Link Applies to both ends of link Bolt Drag Link Joint Bushing Upper Drag Link L R Both ends Bolt Drag Link Top L R Bushing Drag Link Plate L R Bushing Nose Gear Idler Top Mfg Dimension 5625 0015 0000 5620 0000 0040 5625 0015 0000 4375 0015 0000 4367 0000 0005 4375 0015 0000 4367 0000 0005 4375 0015 0000 4367 0000 0005 4375 0015 0000 2500 0015 0000 Service Service Limit 5625 5570 5625 4375 4350 ...

Page 691: ...der Torque Link Attachment Unnotched Bushing Notched Bearing Oleo Strut Lower Bearing Oleo Strut Upper Mfg Dimension 2490 0000 0030 3745 0010 0000 2492 0000 0005 3117 0000 0005 3130 0020 0000 3125 0015 0000 2 002 001 000 2 3730 0000 0020 Min Service Limit 2455 2475 3105 3130 3125 Max Service Limit 2490 2492 3117 3160 3160 Chrome 2 3730 Plate Worn Thru 8 45314 05 24 TRA 2031 25 M34 14 Cylinder Asse...

Page 692: ...24 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL MAIN GEAR WEAR LIMITS Figure 32 29 Main Gear Wear Limits 32 90 02 Page 32 72 Revised November 17 1983 3G14 ...

Page 693: ...ace Lower Link Applies to both ends of link Bolt Side Brace Joint Bushing L R Side Brace Link Lower End Bushing Aft Side Brace Upper End Bolt Aft Side Brace Upper End AN178 may be used to reduce play Mfg Dimension 6245 0015 0000 6240 0000 0040 6250 0015 0000 4990 0010 0000 4991 0000 0005 5000 0015 0000 4991 0000 0005 5000 0015 0000 5000 0015 0000 4990 0000 0040 6245 6190 6250 4990 4981 5000 4981 5...

Page 694: ...using Bushing Torque Link Bushing Torque Link Center Bolt Torque Link Center AN177 may be used to reduce play Bushing Fork Torque Link Attachment Mfg Dimension 5000 0015 0000 1 1250 0015 0000 1 1245 0000 0010 3740 0020 0000 3742 0000 0005 3750 0015 0000 4375 0015 0000 4370 0000 0040 3740 0020 0000 Min Service Limit 5000 1 1250 1 1225 3745 Ream at install if req 3732 3750 4375 4330 3745 Ream at ins...

Page 695: ...olt Torque Link to Fork Bearing Oleo Strut Bottom Bearing Oleo Strut Top Unnotched Bearing Notched 3742 0000 0005 2 7500 0020 0000 3 2480 0000 0020 3732 2 7500 Chrome Plate Worn Thru 3742 2 7530 3 2480 3 40327 00 Housing Assembly Cylinder Bore 3 2500 0030 3 2500 0000 3 2545 Figure 32 29 Main Gear Wear Limits cont 32 90 02 Page 32 75 Revised November 17 1983 3G17 ...

Page 696: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 3G18 ...

Page 697: ...CHAPTER LIGHTS 3G19 ...

Page 698: ...e Lights In Speaker Panel Assemblies 3H 33 13 00 OVERHEAD READING LIGHT 3H1 33 13 01 Removal Of Lamp In Overhead Reading Light 3H1 33 13 02 Installation Of Lamp In Overhead Reading Light 3H1 33 14 00 REPLACEMENT OF COWL FLAP INDICATOR LIGHTS 3HI 33 15 00 REPLACEMENT OF TRIM INDICATOR LIGHTS 3HI 33 16 00 OVERHEAD ENTRANCE LIGHT 3HI 33 16 01 Removal Of Lamp In Overhead Entrance Light 3H2 33 16 02 In...

Page 699: ...wer Supply 3H5 33 42 11 Removal Of Tail Strobe Light 3H6 33 42 12 Installation Of Tail Strobe Light 3H6 33 42 13 Removal Of Tail Strobe Power Supply 3H6 33 42 14 Installation Of Tail Strobe Power Supply 3H6 33 43 00 TROUBLESHOOTING 3H7 33 44 00 RECOGNITION LIGHTS 3H8 33 44 01 Removal Of Inflight Recognition Lights 3H8 33 44 02 Installation Of Inflight Recognition Lights 3H8 33 45 00 GROUND RECOGNI...

Page 700: ...usly with the low voltage control circuit A switch inside the potentiometer controlsthis on off function Whenthe potentiometer scontrol knob isturned on the lighting intensityis verydim Lightingintensityincreaseswitha clockwiserotation ofthe potentiometer scontrol knob until it reachesitsbrightestintensity At thispoint theknob willno longerturn clockwise Reversalof the knob movementwill allow the ...

Page 701: ...ght Stall Warning Starter Energized Taillight Tail Strobe Tell Tail Lights Trim Indicator Voltmeter Wing Inspection Wing Tip Position Wing Tip Strobe 472 861 472 028 472 047 472 078 472 028 472 047 453 791 472 028 758 151 472 028 472 027 472 028 472 755 472 028 453 792 753 476 472 028 472 028 472 028 472 028 758 418 472 769 472 052 758 472 472 052 472 058 453 886 761 214 472 028 472 876 106S R F38...

Page 702: ...e of the bulkhead at Sta 57 00and W L 775 on the right side of the aircraft The followingprocedures apply to the panel lights dimmer only 1 Accessto the dimmer is through the forward baggage compartment 2 Locate dimmer assembly on upper forward bulkhead at Sta 57 00 and disconnect electrical connector E304 3 Remove the screwssecuringthe dimmer assemblyto the bulkhead 4 Remove the dimmer assemblyfr...

Page 703: ...the light assembly 2 Remove the lamp from the light assembly INSTALLATION OF LAMP IN OVERHEAD READING LIGHTS 1 Replacethe lamp using the proper number 2 Reinstall the lens cover REPLACEMENT OF COWL FLAP INDICATOR LIGHTS The cowlflap indicator lights are located betweenthe left and right cowlflap indicator The light bulbs may be replaced by removing the bottom trim panel from the face of the pedest...

Page 704: ...TS 1 Remove the screws holding the door step light assemblyto 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 Reinstallthe light assemblyand secure it to...

Page 705: ...on the assemblyagainst the strut housing with the bottom of the mounting bracket 5 63 inches up from the bottom of the housing Refer to Figure 33 1 Align the bracket longitudinally and secure with clamps The light beam angle may be adjusted by the adjustment screwsat the sideof the bracket and tilting as desired POSITION LIGHTS REMOVALOF WING NAVIGATION LIGHT 1 To removebulb remove the screwssecur...

Page 706: ...oved INSTALLATION OF WING TIP POSITION LIGHT 1 Install the bulb and lens 2 Secure lens retainer with appropriate screw 3 Place plexiglasscover in position on wing tip and secure with appropriate screws REMOVAL OF TAIL POSITION LIGHT The tail position light is located on the tip of the tail 1 Remove the screwssecuringthe lens retainer to the light assembly and remove lensretainer and lens 2 Remove ...

Page 707: ...ure with the appropriate screws 5 Install lensand lensretainer and securewith the appropriate screw 6 Install plexiglasscover on wingtip and secure with appropriate screws REMOVAL OF WING TIP STROBE POWER SUPPLY For each wingtipstrobe light there is onestrobe power supplymounted outboard on the outboard wing rib L or R 1 Remove screwsfrom wing tip L or R and movejust enough to gain accessinsidethe...

Page 708: ... 4 Secure the bottom fairing into place with the appropriate screws 5 Install navigation light previously removed 6 Replace lens and lens retainer and secure with the appropriate screws REMOVAL OF TAIL STROBE POWER SUPPLY The tail strobe power supply is mounted on the insideof the bottom tail fairing 1 Removescrewssecuring the bottom tail fairing and lower the fairingjust enough to gain access to ...

Page 709: ... diode in the power supply causing self destruction from overheatingof the power supply This damage is sometimesnot immediately apparent but will causefailureof the systemin time CAUTION Whendisconnectingthepower supply allowfive minutesof bleed down time before handling the unit 2 Check for malfunction in interconnectingcables A Ascertain pins I and 3 of interconnecting cableare not reversed B Us...

Page 710: ...ghts is pulled before attempting to remove the light 2 Remove the screwssecuring the plexiglasscover to the wing tip 3 Remove the two screwssecuring the light assembly to the bracket 4 Pull light assemblypartially out of bracket and disconnectelectrical connection 5 Remove light assembly NOTE Bulb replacementcan be accomplishedby removing screw on re tainer ring and removing retainerand lens INSTA...

Page 711: ...e of the aircraft 1 To gain accessto the flasher removethe screwssecuringthe accesspanelto the rear baggagecom partment and removepanel 2 Locate flasherand disconnect the electrical connector BLINK from the unit 3 Remove the two screwssecuring the flasher unit to the bulkhead 4 Remove the flasher unit INSTALLATION OF GROUND RECOGNITION BEACON FLASHER 1 Secure flasher unit to bulkhead with two scre...

Page 712: ...rand turn on logolight switch and check for proper illumination of lamp 4 Place logolight switchinoff position secureelectricalpowerto aircraft and securelenscoverwith appropriate screw LOGO LIGHTS ADJUSTMENT Refer to Figure 33 2 The logolightsare adjustablehorizontally and verticallyto illuminatethe vertical tailsection ofaircraft 1 Remove cover lensscrew and lens 2 Loosenlocking clamp retainer s...

Page 713: ...CHAPTER NAVIGATION AND PITOT STATIC 3H1 ...

Page 714: ...emoval Of Instruments Installation Of Instruments 3H13 3H13 3H13 3H15 3H15 3H16 34 10 00 34 10 01 34 10 02 34 10 03 34 20 00 34 20 01 34 20 02 34 20 03 34 20 04 34 20 05 34 20 06 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 3...

Page 715: ...sistsof two staticports oneon each sideof the fuselage locatedjust aft ofbulkhead station 296 0 Theseports are interconnectedas shown in Figure 34 1and the tubing is then routed forward along the top of the fuselageand downthe windshieldcenterpost to the backofthe instrumentpanel whereit is connected to the airspeed indicator altimeter and rate of climbindicator An alternate staticair sourceis loc...

Page 716: ...ORAIRCRAFT NOT OPERATED IN CONTROLLED AIRSPACEUNDERIFR CONDITIONS SEE ADVISORY CIRCULAR AC 43 13 1A SECTION4 OF CHAPTER 16 REFER TO PARTS CATALOG FORTYPICALSYSTEM ROUTING 1 PITOTHEAD 2 ALTERNATESTATICSOURCE 3 ALTIMETER 4 AIRSPEED INDICATOR 5 RATEOF CLIMBINDICATOR 6 SUCTIONGAUGE 7 STATICSOURCE FORPILOT SAND OPTIONAL COPILOT S STATICINSTRUMENTS Figure 34 1 Instrument Air SystemInstallation Typical 3...

Page 717: ...ort or broken lacing and ties 8 Check instruments for evidenceof overheatingor contamination of equipment by foreign matter or water Dust dirt and lint contribute to overheating of equipment poor ventilationand malfunctioning Specialattention should be giventhat ventilation openingsin equipment housingsare open and free from obstructing lint and dust REMOVAL OF INSTRUMENTS 1 The non shock mounted ...

Page 718: ...ost light s operation shock mounted instruments may be installed by the followingprocedure Place the instrument in its proper panel cutout and secure with screws Install the post light s and secure Do not overtighten nut Connect the plumbing and or electricalconnector to back of instrument Connect the electricalconnector of the post light s Tighten connector fingertight Ascertain that oneend of th...

Page 719: ...ointer 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 during...

Page 720: ...titude CHART 3402 TROUBLESHOOTING ALTIMETER Trouble Cause Remedy Excessivescale error Excessivepointer 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 Defectivemechanism Improper venting Wrong lubrication or lack of lubr...

Page 721: ...airplane CHART 3403 TROUBLESHOOTING AIRSPEED TUBES AND INDICATOR PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL CHART 3402 TROUBLESHOOTING ALTIMETER cont Trouble Cause Remedy Altimeter sticksat altitude or does not change with change of altitude Altimeter changes reading as aircraft is banked Altimeter requires resetting frequently Water or restriction in static line Water in static line Temperature com...

Page 722: ...h ON Circuit breaker popped Open circuit Reset Repair Excessivevoltage drop between battery and pitot head Heating element burned out Check voltageat pitot head Replacepitot head NOTE When any connections in static system are opened for checking systemmust be checked per FAR 23 1325 ATTITUDEAND DIRECTION MAGNETICCOMPASS The magnetic compass is a self containedinstrument This instrument has an indi...

Page 723: ...repair instrument Remove excess compensation Replace or repair instrument Liquid leakage Loose bezelscrews Replace or repair instrument Broken cover glass Defectivesealing gaskets Replace or repair instrument Replace or repair instrument Replace or repair instrument Discolored markings Age Defectivelight Card sticks Card does not move when compensating screwsare turned Burned out lamp or broken ci...

Page 724: ...as been setfor 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 Thegyro should onlybecheckedon theheading onwhichitwasfirst set alsodueto internal friction spin axiserror air turbulenceand airflow the gyro shouldbes...

Page 725: ...f bank CHART 3406 TROUBLESHOOTING GYRO HORIZON INDICATOR Trouble Cause Remedy Bar fails to respond Insufficientpressure Check pump and tubing Filter dirty Clean or replacefilter Bar does not settle Insufficientpressure Check line and pump Adjust valve Excessivevibration Incorrect instrument Defectiveinstrument Check shock mounts Replace ifnecessary Check part number Replace Bar oscillatesor shimmi...

Page 726: ... unused ports correctly sealed against air leaks 6 Is the systempressure correct and does the pressure gauge give an accurate reading 7 Is the pressure regulator adjusted correctlyand functioning properly GYRO HANDLING AND SHIPPING The followinginformation applies to all three inch directionalgyros and attitude horizon instruments installed by the factory or a Piper field servicefacility Gyro inst...

Page 727: ...ECTRICAL 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 spring screw If...

Page 728: ...nd does not set on zero when stationary Ball sticky Ball not in center when aircraft is correctly trimmed Oil has becometoo thick Insufficient bearing clearance Oil or dirt between damping pistons and cylinder Excessiveclearance between rotor and rotor pivots Flat spot on ball Instrument not level in panel Replace instrument Replace instrument Replace instrument Replace instrument Replace instrume...

Page 729: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 313 ...

Page 730: ...CHAPTER OXYGEN SYSTEM 314 ...

Page 731: ...tlets 3111 35 12 05 Purging Oxygen System 3111 35 12 06 Cleaning Of Face Masks 3112 35 13 00 COMPONENTS 3112 35 13 01 Oxygen Cylinder 3112 35 13 02 Removal Of Oxygen Cylinder And Regulator 3112 35 13 03 Installation Of Oxygen Cylinder And Regulator 3113 35 13 04 Charging Valve 3113 35 13 05 Removal Of Oxygen System Charging Valve 3113 35 13 06 Installation Of Oxygen System Charging Valve 3113 35 1...

Page 732: ... overboard through the dump outlet in the event of system over pressurization High pressure oxygen is routed from the regulator to the pressure gauge while low pressure oxygen is routed from the regulator to the outlets and masks whenever the control knob is pulled to the ON position Each outlet has a spring loaded valve which prevents the flow of oxygen until a mask hose is engaged in the outlet ...

Page 733: ...SURE LINE 2 OXYGEN PLUG IN RECEPTACLES 3 OXYGEN FLOW CONTROL KNOB 4 OXYGEN SUPPLY PRESSURE GAUGE 6 HIGH PRESSURE LINE 6 OXYGEN CYLINDER 7 PRESSURE REGULATOR 8 FILLER VALVE Figure 35 1 Oxygen SystemInstallation 317 35 00 02 Page 35 02 Issued September 2 1981 ...

Page 734: ...n and purge lines No indication of pressure on pressure gauge Pressure gaugedefective Safety disc ruptured cylinderempty Replacegauge Replacecylinderand visual indicating disc Oxygen cylinderwill not retain pressure Offensiveodors in oxygen Leak in system Cylinder pressure below 50 psi Foreign matter has entered the system during previous servicing Locate and repair leak Purge the oxygensystem 35 ...

Page 735: ...ich fit around the adjustment shaft These washers are safetystops for maximum regulated pressure and must be used with reinstallation 7 Avoid bendingtubing or damaging flareless fittings 8 All shut off valves must be opened slowly An explosion could result from rapid flowingoxygen generating heat against metal 9 Use only oxygen line leak detector fluid conforming to MIL L 25567 Type 1 After leak t...

Page 736: ...al 7 Referto FAA Manual AC43 13 1Afor more details WARNING Do not permit smoking or open flame near the airplane while oxygen is being used Keep all oils grease soap and solvent away from the oxygen system Hydrocarbons constitute a fire hazard and may burn or explode when contacted by oxygen under pressure CHART 3502 OXYGEN SYSTEM COMPONENT LIMITS PARTS INSPECTION OVERHAUL Regulator 300 Flight Hrs...

Page 737: ...outlet 2 Remove the screws holding the trim panel and remove the panel 3 The outlet can now be removed from the low pressure line INSTALLATION OF OUTLETS 1 Apply sealant Permacel 412 to the maleend of the fitting 2 Connect the outlet to the low pressure line 3 Position the trim panel and secure with screws 4 Position the outer half outlet and secure with a suitable spanner wrench 5 Torque the fitt...

Page 738: ... mask turrents Do not use soap to cleansponge rubber discs as this would deteriorate the rubber and giveoff unpleasant odors Clean in clear water and squeeze dry 3 Wash 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 sidesof the breathing bag do not stick together whiledrying as thismay decrease the life of t...

Page 739: ...to the regulator 5 Install aft panel rear baggagecompartment and secure with appropriate screws CHARGING VALVE REMOVAL OF OXYGEN SYSTEM CHARGING VALVE 1 Remove the screwssecuringthe rear panel inthe aft baggagecompartmentand removethe panel 2 Disconnect the tee fitting from the charging valve 3 Remove the three nuts and boltsholdingthe chargingvalvein placeand removethe valvethrough the access doo...

Page 740: ...POSITION SLIT AWAY FROM WIRES ETC CABLE WIRE BUNDLE EVERY TWO INCHES AT PASS OVERS PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1 8 Min 1 8 Min SKETCH A SKETCH B Grommet Correct Incorrect SKETCH D Figure 35 2 OxygenTubing Installations 35 14 08 Page 35 09 Issued September 2 1981 3114 ...

Page 741: ...fter 15 yearsor 4380 pressurizations whicheveroccursfirst The month and year of the last test is stamped on the cylinderbeneath the ICC identification 2 The outlets should be checkedfor leakageboth in the non use condition and for leakage around an inserted connector 3 The high pressure gauge may be checked for accuracy by comparing its indicated pressure with that of a gauge of knownaccuracy 4 In...

Page 742: ...CHAPTER PNEUMATIC SYSTEM 3I16 ...

Page 743: ...TION 3118 PNEUMATIC SYSTEM FILTER REPLACEMENT DRY PNEUMATIC PUMP Removal Of Dry Pneumatic Pump Installation Of Dry Pneumatic Pump PRESSURE RELIEF VALVE Removal Of Pressure Relief Valve Installation Of Pressure Relief Valve PNEUMATIC SYSTEM SET UP PROCEDURE Pilot s And Copilot s Gyro Installation With Deicer Boots Pilot s Gyros And Deicer Boots Pilot s Gyros And Copilot s Gyros Pilot s Gyros DEICER...

Page 744: ...s as required 1 Removal of inlet air filters located in the outboard sides of the left and right engine nacelles aft of the fire wall above the air inlet opening A Removethe appropriate accesspanel on the enginenacelle Theleft nacelleaccesspanel may have the ice detection light while the right access panel is a grill type panel B Disconnect the hose clamp and remove the hose from the filter C Remo...

Page 745: ...only enough vise pressure to hold pump firmly DO NOT apply vise pressure to outside diameter or overall length The ports of the AIRBORNE dry airpump have been treated with a dry film lubricantand the AIRBORNEfittingsarecadmiumplated thus eliminatinganyneed for thread lubricants If a thread lubricant is required use a powdered moly sulfideor graphiteindryform or inan evaporating vehicle or employ a...

Page 746: ...UMATIC SYSTEM SETUP PROCEDURE The pneumatic system setup procedures given in these instructions cover four combinations of instrument and accessory installations These are as follows Pilot s and Copilot s Gyro Installation with Deicer Boots Pilot s Gyros and Deicer Boots Pilot s Gyros and Copilot s Gyros and Pilot s Gyros only Beforeattempting any adjustments ascertain that all line connectionsare...

Page 747: ... DIRECTIONALGYRO PILOT 10 ALTITUDE GYRO PILOT 11 DIRECTIONALGYRO COPILOT 12 ALTITUDE GYRO COPILOT 13 A SYSTEM WING SOLENOIDVALVE 14 B SYSTEM TAIL SOLENOID VALVE 15 MANIFOLD CHECKVALVE 16 PRESSURESWITCH 17 EJECTOR 18 RELAYVALVE 19 EMPANNAGE DEICINGBOOT Figure 36 1 Pilot s and Copilot s Gyro Installation With Deicer 36 14 00 Page 36 04 3I21 Issued September 2 1981 ...

Page 748: ...cle NOTE Shouldthetest gaugereadingnot bewithintolerance firstascertain that the deicerboots have beenpressuretested 6 To adjust the deicer system operating pressure loosen the locknut on the nacelle mounted dual regulator The deicer system pressure regulator is the regulator without the electric solenoid 7 Repeat Steps 5 and 6 for the right engine left engine OFF 8 To adjust the gyro pressure set...

Page 749: ...uge for the pilot s gyros reads 5 5 4 in Hg 2 7 2 psi NOTE There will be a momentary fluctuation of pressure at the beginningof boot inflation Therefore the pilot s gyro pressure shouldbe readjust prior to completionof the boot inflationcycle Theair to the co pilot sgyros is shutoff duringboot inflation If this condition cannot be met the pneumatic relay valve may be defective PILOT SGYROSAND COPI...

Page 750: ...ANCE MANUAL 1267C 1 INLET FILTER 2 PUMP 3 REGULATOR 4 FILTER 5 MANIFOLD CHECK VALVE 6 INSTRUMENT PRESSURE GAUGE 7 REGULATOR GYROS Figure 36 2 Pilot s and Copilot s Gyro Installation 36 14 03 Page 36 07 Issued September 2 1981 3124 ...

Page 751: ...1020 MAINTENANCE MANUAL 1267D 7 1 I 1 INLET FILTER 2 PUMP 3 REGULATOR 4 FILTER 5 MANIFOLD CHECK VALVE 6 INSTRUMENT PRESSURE GAUGE 7 GYROS Figure 36 3 Pilot s Gyro Installation 36 14 03 Page 36 08 Issued September 2 1981 3J1 ...

Page 752: ...toff valvemust be connectedso as to trap airin the deicer system 2 Disconnectthe lineto the pressureregulator Attachthe testrigon the linetothe pressureregulator Bypass the one ejector valve and install temporary test line Apply 19 psi of air to the system and using the shutoff valve trap this air pressure in this portion of the system A soap solution may be used to check for leakage which should ...

Page 753: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLYLEFT BLANK 3J3 ...

Page 754: ...CHAPTER VACUUM SYSTEM 3J4 ...

Page 755: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL NOTE The pneumatic and vacuum systems have been combined toform Chapter36 Pneumatic System 3J5 ...

Page 756: ...CHAPTER ELECTRIC ELECTRONIC PANELS AND MULTI PURPOSE PARTS 3J6 ...

Page 757: ...Installation Of Overhead Switch Panel 3J9 39 10 07 Annunciator Panel 3J13 39 10 08 RemovalOf Annunciator Panel 3J13 39 10 09 Installation Of Annunciator Panel 3J14 39 10 10 RemovalOf Annunciator Controller 3J14 39 10 11 Installation Of Annunciator Controller 3J14 39 10 12 ElectroluminescentPanel Power Supply 3J14 39 10 13 RemovalOf ElectroluminescentPower Supply 3J14 39 10 14 Installation Of Elect...

Page 758: ... inthe center and the remainingengineand miscellaneous instruments to the right A secondset of flight instruments may be installedin the right sideof the panelfor use bythe copilot Additionalinstrumentsare mountedinasub panellocatedoverthe windshield Mostofthe instruments have been shock mounted to minimizevibration that is transmitted to the instrument panel INSTRUMENTS The instruments have been ...

Page 759: ...not to exceed torque requirements as noted on decal located on cover of gyro 4 Installation of instruments will be in the reversegivenfor removal Afterthe installationis com pletedand before replacingthe instrumentface panel checkall componentsfor securityandclearanceof the control column ELECTRICALSWITCHESAND CIRCUIT BREAKERS Electrical switchesand circuit breakers are located in a panel on the l...

Page 760: ...LOT 29 AUTOPILOT CONTROLS 30 ADF 31 WINDSHIELD WIPER CONTROL EMERGENCY BATTERY PACK 32 CIGAR LIGHTER 33 NAV 2 34 PARKING BRAKE 36 GEAR SELECTOR 36 GEAR INDICATOR LIGHTS 37 RADAR ALTIMETER 38 RADIO LIGHT SWITCH 39 AVIONICS MASTER SWITCH 40 PA VOLUME CONTROL ON OFF KNOB 41 AVIONICS 42 RADAR 43 MANUAL ALTERNATE AIR CONTROLS 44 HEATER CONTROL SWITCH 45 WING FLAP SELECTOR SWITCH 46 CABIN TEMP CONTROL 4...

Page 761: ...Figure 39 2 Switch and Circuit Breaker Control Panel PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL C460 39 10 06 Page 39 04 Issued September 2 1981 3J11 ...

Page 762: ...NGINE MAGNETO SWITCHES 12 LEFTFUELGAUGE 13 LEFTALTERNATOR PRESS TO TEST SWITCH 14 AMMETER 15 RIGHT ALTERNATOR PRESS TO TEST SWITCH 16 RIGHTFUEL GAUGE 17 FUELPUMPSWITCHES 18 ENGINE HOURMETER 19 RIGHTMAPLIGHTSWITCH 20 DIALLIGHT 1269 A LEFT SKETCHD PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 314 BOUND SEAT SKETCH SKETCHE SKETCH I I SKETCH G Figure 39 3 Overhead Switch Panel 39 10 06 Page 39 05 Issued Se...

Page 763: ...or panel Toreplaceadefectivebulb push inonappropriatelightcover assembly until it clicks then remove the light cover assembly Remove old bulb and replacewith newbulb Placethe lightcover assemblyinproper cut out andpush inuntilit clicks Thiswilllock the light coverassembly inplace 1 Remove screwssecuringcover to glare shield assemblyand remove cover 2 Remove screwssecuring center panel of instrumen...

Page 764: ... shelfwith the electrical connection facing aft 2 Secure the unit by installingappropriate screwsthrough the mounting bracket 3 Connect the electricalconnection to the unit 4 Install the accesspanel between Sta 35 00and Sta 57 00and securewith appropriate screws ELECTROLUMINESCENT PANEL POWER SUPPLY The inverterthat acts as a power supply for the electroluminescentpanelsis locatedbehindthe left si...

Page 765: ...ivated the relaywillthenclosethecircuitto the warninglight for a minimum of 10secondsand willremainclosedifthe causeis not corrected The lightsare provided witha press to test feature To test depress the annunciator test button for 3 seconds the lights should illuminate and remain on for 10 seconds During this test the fuel boost pump inoperative lights mounted belowthefuelflowwarninglightsshould ...

Page 766: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL FILTER Figure 39 4 Alternator Paralleling System 3J16 39 10 19 Page39 09 Issued September 2 1981 ...

Page 767: ...obe malfunction Gated delay relax malfunction Check free movement of probe tip replace if defective Replace relay after the cause for the white wire to ground has been iso lated and corrected Fuel flow warning light fails to extinguish Low fuel level in fuel cell Fill Fuel flow sensor probe malfunction Ground in circuit Pressure switch malfunction Check free movement of probe tip replace if defect...

Page 768: ...ated in the overhead panel Theseincludethe pilot s and copilot s optional lightsdimmerand the overheadpanel lightsdimmer A singlecircuitbreaker protects thesecircuits Eachrheostat isconnected to a transistor 2N6282 in the dimmercontrol assemblywhich is locatedforward of bulkhead 81 00on the right side Each transistor is protected by a 5 amp fuse Outage of any group of lightscould be causedby a blo...

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Page 772: ...CHAPTER STRUCTURES 3J22 ...

Page 773: ... 04 Surface Preparation For Pressure Sensitive Safety Walk 3K14 51 13 05 Application Of Pressure Sensitive Safety Walk 3K15 51 14 00 RADOME BOOT 3K15 51 14 01 List of Materials 3K15 A 10 82 51 14 02 Preparation and Installation of Radome Boot 3K15 A 10 82 51 14 03 Inspection of Radome Boot 3K16 A 10 82 51 15 00 RADOME EROSION SHIELD 3K16 A 11 83 51 15 01 List Of Materials 3K16 A 11 83 51 15 02 Pre...

Page 774: ...ymust be retained so that the surrounding areas will not receiveextra stress Major alterations or repairs require the approval of the Federal Aviation Administrationand can only be accomplishedwiththe approval of the administrator by personnelqualifiedin accordancewiththe regu lations If it becomesnecessaryto make modificationsor structural repairs it isrecommendedthat a properly qualified repair ...

Page 775: ...4 T3 2024 0 2024 T3 2024 0 020 025 025 032 032 NUMBER 7 9 10 11 12 MATERIAL 2024 T3 THICKNESS 040 040 051 064 015 032 NOTE LEFT WING SHOWN RIGHT OPPOSITE AND NOTED MATERIAL OUTLINED IN DOTS USED ON RIGHT WING ONLY HEAT TREAT TO 2024 T4 AFTER FORMING Figure 51 1 Skin Thickness and Material 51 10 00 Page 51 02 Issued September 2 1981 3K1 ...

Page 776: ...A PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1141 A Figure 51 1 Skin Thickness and Material cont 51 10 00 Page 51 03 Issued September 2 1981 3K2 ...

Page 777: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 165 17316 ACCESSHOLE COVER PLATE 7 Figure 51 2 Typical Access Plates and Panels 51 10 00 Page 51 04 Issued September 2 1981 3K3 ...

Page 778: ... 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 and to puncture any air bubbles which may be present Fill the scratch or hole above the surrounding undamaged area about 062 of an inch 5 Lay a piece of cellophane or waxed paper over the repair to cut off air and start the cure of gel mixture 6 Al...

Page 779: ...ubbles will show white in the patchand they should all beworked out to the edge Remove excess resin before it gels on the part Allow patch to cure completely 10 Remove cardboard or aluminum sheet from outside of hole and rough sand the patch and edge of hole Feather edge of hole about two inches into undamaged area 11 Mask area around hole with tape and paper to protect surface Cut a piece of fibe...

Page 780: ...Chemicals Gardena Cal 90248 Mirror Bright Polish Co Inc Irvin Cal 92713 Obtain From Local Suppliers Cleaners ABS Solvent Cements Solarite 11 Series Solar Compounds Corp Linden N J 07036 Solvents Methylethyl Ketone Methylene Chloride Acetone Obtain From Local Suppliers Epoxy Patching Compound Hot Melt Adhesives Polyamids and Hot Melt Gun Hot Air Gun Solarite 400 Stick Form 1 2 in dia 3 in long Temp...

Page 781: ... Surface Scratches Abrasions or Ground in Dirt PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 571 Hot Air Gun 871 Figure 51 4 Deep Scratches Shallow Nicks and Small Holes 51 12 00 Page 51 08 Issued September 2 1981 3K7 ...

Page 782: ...AIRCRAFT T 1020 MAINTENANCE MANUAL THOROUGHLY MIX USING FIGURE EIGHT MOTION 870 Figure 51 5 Mixing of Epoxy Patching Compound Figure 51 6 Welding Repair Method 51 12 00 Page 51 09 Issued September 2 1981 3K8 ...

Page 783: ...llow Nicks and Small Holes Less than I inch in diameter Refer to Fig ure 51 4 A Solvent cements will fit virtually any of these applications If the area to be repaired is very small it may be quicker to make a satisfactory cement by dissolving thermoplastic material of the same type being repaired in solvent until the desired paste like consistency is achieved B This mixture is then applied to the...

Page 784: ...ovide extra strength to the part D The crack should be V grooved and filled with repair material such as solvent cement hot melt adhesive epoxy patching compound or hot air welded whichever is preferred E After the repair has cured it may be sanded to match the surrounding finish 5 Repairing Major Damage Larger than I inch in diameter Refer to Figure 51 8 A If possible a patch should be made of th...

Page 785: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL PATCHING COMPOUND DAMAGED AREA Figure 51 8 Various Repairs 51 12 00 Page 51 12 Issued September 2 1981 3K11 ...

Page 786: ...INES 829 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL Figure 51 9 Repair of Stress Lines 132 PROFILE VIEW INDICATING DAMAGED AREA Figure 51 10 Repair of Impacted Damage 51 12 00 Page 51 13 Issued September 2 1981 3K12 ...

Page 787: ... to consider is that hard brittle coatings that are usuallybestfor abrasion resistanceshould not be used in areas whichincur highstress flexingor impact Suchcoating may crack thus creatinga weak area SAFETYWALKREPAIR SURFACEPREPARATIONFORLIQUID SAFETYWALKCOMPOUND 1 Clean all surfaceswith a suitable cleaningsolventto removedirt greaseand oils Solventsmay be applied by dipping spraying or mopping 2 ...

Page 788: ... After recoating or touch up if done allow the coating to dry for 15minutesto one hour before removing masking NOTE Thecoated surfaceshallnot be walkedonfor six hoursminimum afterapplicationof final coating SURFACE PREPARATION FOR PRESSURE SENSITIVE SAFETY WALK Theareasto whichthepressuresensitivesafetywalkisto beinstalledmust befreefromall contaminates and no moisture present If liquid safety wal...

Page 789: ... detergent Ivory Joy per gallon of solution 6 3M PA 1 plastic squeeze or equivalent 7 Masking tape wide 8 Industrial razor blade knife PREPARATION AND INSTALLATION OF RADOME BOOT 1 Thoroughly wash repair primed radome with isopropyl alcohol and wipe dry 2 Use a marking pen to place an orientation mark on the top center of radome surface 3 Position boot with protective liner still in place over rad...

Page 790: ... isopropyl alcohol wipe dry and paint with a suitable polyurethane paint INSPECTION OF RADOME BOOT 1 Inspect for cuts blisters perforations edge lifting etc every 100 hours 2 The boot should be replaced at the first sign of damage RADOME EROSION SHIELD LIST OF MATERIALS I Cement Minnesota Mining and Manufacturing Co EC 1403 or 1300 L Approximate coverage 80 sq ft per quart mixed 2 Scissors 2 blade...

Page 791: ...entified top surface of erosion shield on top surface of structure Then adjust each side to provide equal distance from structure attachment line Smooth out any wrinkles Apply 1 2 wide masking tape to the structure next to the shield s trailing edge Refer to Figure 51 11 View1 3 Establish a reference line at the top and draw a pencil mark on the masking tape to correspond with the center line mark...

Page 792: ...twisting or sharp creasingof shield Otherwise cement may be pulled loose from structure or shield Should it be necessary to remove or loosen an installed shield squirt alittle Toluolfrom clean oil can to soften the adhesion line Apply only minimum amount of solvent while slight tension is applied to the shield Allow solvent to do most of the work of separating cemented coats because if cement pull...

Page 793: ... CENTER PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL VIEW 3 VIEW 2 VIEW 1 VIEW 5 VIEW 4 POINTED SCISSORS VIEW 6 VIEW 7 Figure 51 11 Installation of Radome Erosion Shield 51 15 03 Page 51 20 Added November 17 1983 3K19 ...

Page 794: ... chemical or electrochemical attack At times this corrosion may spread under the surface coating and not recognized until the paint or plating is lifted off the surface in small blisters which result from the pressure of the underlying accumulation of corrosion products 2 Dissimilar Metal Corrosion This type of corrosion is also known as galvanic corrosion because of the electrochemical principle ...

Page 795: ...ralfactors suchas geographicallocation aircraft model and type of operation INSPECTION I Inspectionfor corrosionshould bedoneon adailybasisdueto thefactthat corrosionisacontinuing problem Except for special requirements in trouble areas inspection for corrosion should bea part of routine inspections such as daily and preflight 2 In addition to the routine inspections the following special requirem...

Page 796: ...type of corrosion damage is normally removed by extensivehand sanding or mechanicalsanding C SevereCorrosion The general appearance may be similar to moderate corrosion with severe blistering exfoliation scaling and or flaking Pitting depths will be deeper than 0 010 of an inch and is normally removed by extensivemechanicalsanding or grinding 4 Corrosion Removal There are severalstandard methodsfo...

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Page 798: ...MAINTENANCE MANUAL CARD 4 OF 5 PA 31 350 T1020 PIPER AIRCRAFT CORPORATION PART NUMBER 761768 4A1 ...

Page 799: ...roken 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 assigne...

Page 800: ...tified by revision lines A reference and record of material revised is included in each chapter s Table of Contents Effectivity The codes used in the effectivity columns of each chapter are defined as follows SAMPLE EFFECTIVITY CODES First Revision Month and Year 11 80 Second Revision Revision Indication Month and Year 2R 12 80 Third Revision Revision Indication Month and Year 3R 1 81 Fourth Revis...

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Page 802: ... AIRCRAFT ENGINES P N 60297 23 AvcoLycoming Division Williamsport PA 17701 HARTZELL CONSTANT SPEED AND FEATHERING PROPELLER P N 117D Hartzell Propeller Inc P O Box 1458 1800 Covington Avenue Piqua Ohio 45356 S 1200 SERIES MAGNETO IGNITION SYSTEM P N L 609 3 Bendix Electrical Components Division Sidney New York 13838 CLEVELAND WHEEL AND BRAKE Aircraft Wheel and Brake Division 1160Center Road Avon O...

Page 803: ...VIATION DIVISION Rockwell International Cedar Rapids Iowa 52406 319 395 3625 Telex 46 4421 KING RADIO CORPORATION 400 N Rodgers Rd Olathe Kansas 66061 813 782 0400 Telex 42299 Kingrad GLOBAL NAVIGATION 2144 Michelson Drive Irvine Ca 92715 714 851 0119 PIPERPUBLICATIONS PA 31 350 T 1020 Parts Catalog CONTINUOUS INSPECTION 761 775 Piper Aircraft Corporation 2926 Piper Drive Vero Beach FL 32960 761 7...

Page 804: ...D SHORING LEVELING AND WEIGHING TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACT AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS AEROFICHE GRID NO IB1 1B4 1D23 1E13 1E16 1E21 IF1 IF4 1F8 1G12 1I1 2BI 2B4 2B12 2D1 2D10 2G19 2J1 3B1 3D9 3G19...

Page 805: ...EUMATIC SYSTEM VACUUM SYSTEM ELECTRIC ELECTRONIC PANELSAND MULTI PURPOSE PARTS STRUCTURES DOORS FUSELAGE STABILIZERS WINDOWS WINGS PROPELLERS STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM AEROFICHE GRID NO 3H11 314 3116 3J4 3J6 3J22 4B1 4B21 4C1 4C17 4D4 4E1 4E22 4F1 4G1 4G11 4H10 4H14 411 4A8 Introduction Page 7 Revised Februa...

Page 806: ...NUAL GAMASYSTEM CHAPTERINDEXGUIDE cont SYST CHAP 80 81 91 95 SUB SYST SECTION TITLE STARTING TURBINES CHARTSAND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 4111 4121 5B1 5F1 4A9 Introduction Page 8 Revised November17 1983 ...

Page 807: ... Plant Propeller and Cowl Flap 1G3 12 7 Lubrication Chart Doors and Seats IG4 20 1 Torque Wrench Extension G 16 20 2 Method of Installing Rod End Bearings G16 20 3 Cherrylock Rivet Removal 1G17 20 4 Hose Line Markings 1G19 20 5 Flareless Tube Fittings 1G20 20 6 Spray Patterns 1H8 20 7 Improper Spray Technique 1H10 20 8 Spray Technique 1H11 20 9 Spraying Corners 1H11 21 1 Heating and Ventilating Sy...

Page 808: ...Fabricated Oil Dipstick 1L3 21 31 Magnetic Clutch Installation 1L6 21 32 Expansion Valve Typical 1L8 21 33 Air Conditioning Outlets IL11 21 34 Positioning of Airflow Probe 1L13 21 35 Sealing of Ducts IL14 21 36 Installation of VOI SHAN Seals 1L 14 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 Avi...

Page 809: ...e Tension 2E18 27 10 Safety Wiring Control Surface Stops 2E 18 27 11 Rudder and Rudder Trim Controls 2E22 27 12 Rudder and Trim Tab Control Travels and Cable Tension 2F2 27 13 Clamping Rudder Pedals in Neutral Position 2F2 27 14 Installation of Rudder Rigging Tool 2F2 27 15 Rudder Pedal Installation 2F7 27 16 Elevator and Elevator Trim Controls 2F10 27 17 Elevator and Elevator Trim Travels and Cab...

Page 810: ...Power Pack Handle Release Mechanism 2K8 29 9 Safetying Control Arms 2K9 29 10 Indexing of Selector Spool 2K10 29 11 Handle Release Adjustment 2K11 29 12 Landing Gear Selector Mechanism Installation 2K13 29 13 Power Pack Test Harness Schematic 2K18 29 14 Hydraulic Filter 2K20 29 15 Hydraulic Pump 2K22 29 16 Hand Pump 2L4 29 17 Shuttle Valves WTC 2216 WTC 2217 2L7 30 1 Pneumatic Deicer System Instal...

Page 811: ...ng Gear Installation 3E16 32 8 Clamping Rudder Pedals in Neutral Position 3E22 32 9 Rudder Pedals Neutral Angle 3E22 32 10 Aligning Nose Gear 3E22 32 11 Emergency Extension System Installation 3F1 32 11a Test Equipment Installation Emergency Gear Extension System 3F5 32 12 Gear Actuating Cylinder WiebelTool WTC 2115 1 3F6 32 13 Unlock Actuator Wiebel Tool WTC 2215 3F7 32 14 Gear Door Actuating Cyl...

Page 812: ...t 3K7 51 4 Deep Scratches Shallow Nicks and Small Holes 3K7 51 5 Mixing of Epoxy Patching Compound 3K8 51 6 WeldingRepair Method 3K8 51 7 Repairingof Cracks 3K9 51 VariousRepairs 3K11 51 9 Repair of Stress Lines 3K12 51 10 Repair of Impacted Damage 3K12 51 11 Installation of Radome Erosion Shield 3K18 52 1 Cabin Entrance Door Latch Assembly 4B6 52 2 Pilot s Door Latch Assembly 4B10 52 3 Cargo Door...

Page 813: ...ints 4G15 74 3 Rotor Holding Tool Installed 4G16 74 4 Timing Kit Installed 4G16 74 5 Aligning Timing Marks Single Contact Assembly Magneto 4G18 74 6 Forming Leads in Breaker Compartment 4G18 74 7 Engine Timing Marks 4G19 74 8 Magneto Timing Marks 4G19 74 9 Deleted 74 10 Checking Harness Lead Insulation Resistance 4G22 74 11 Modified Pliers 4G22 74 12 Removing Spring From Lead Assembly 4G23 74 13 L...

Page 814: ...icated Tool Checking Nose Gear Link Travel 5F7 95 5 Flight Control Rigging Tools 5F8 95 6 Fabricated Tool Checking Nose Wheel Alignment 5F9 95 7 Fabricated Jack Stand for Piper Jack Part No 18338 00 5F10 95 8 Fabricated Tail Stand 5F11 95 9 Fabricated Bellcrank Rigging Tool 5F12 95 10 Fabricated Aileron and Elevator Rigging Tool 5F13 95 11 Fabricated Rudder Rigging Tool 5F14 95 12 Suggested Design...

Page 815: ...B23 2402 Alternator Test Specifications 2C10 2403 Alternator Belt Tension 2C11 2404 Hydrometer Percentage Guide 2C13 2701 Troubleshooting Surface Controls 2D16 2702 Control Cable Rigging Tension Vs Temperature 2E3 2801 Troubleshooting Fuel System 2H 2802 Fuel Cell Repair Equipment Lists 2H17 2803 WearLimits For Electric Fuel Pump 218 2804 Fuel Quantity Sender Resistance Limits 2112 2805 Fuel Quant...

Page 816: ...oplastic Repairs 3K6 5501 Elevator Balance Weight 4C9 5502 Rudder Balance Weight 4C15 5701 Aileron Balance Weights 4D14 6101 Propeller Specifications 4E6 6102 Troubleshooting Chart Engine Synchrophaser 4E13 7101 Troubleshooting Engine 4F4 7301 Troubleshooting Fuel Pressure Gauge 4G7 7302 Troubleshooting Fuel Flow Gauge 4G8 7401 Coupling Torques 4H5 7701 Troubleshooting Manifold Pressure Indicator ...

Page 817: ... Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Circuit Load Chart Electrical Wire Coding Electrical Symbols GRIDNO 5B4 5B10 5B11 5B13 5B14 5B15 5B17 5B22 5B23 5C3 5C4 Introduction Page 18 Revised February23 1982 4A20 ...

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Page 822: ...CHAPTER DOORS 4B1 ...

Page 823: ... Latch Assembly 4B5 52 10 10 Installation of Door Latch Assembly 4B7 52 10 11 Adjustment of Door Latch Assembly 4B7 52 10 12 Pilot Door 4B8 52 10 13 Removal of Pilot Door 4B8 52 10 14 Installation of Pilot Door 4B8 52 10 15 Weatherstrip Installation and Sealing Instructions of Pilot Door 4B9 52 10 16 Adjustment of Pilot Door 4B11 52 20 00 EMERGENCY EXIT 4B11 52 20 01 Emergency Exit Window 4B11 52 ...

Page 824: ...ard Baggage Door Forward Baggage Door Latch Assembly Removal of Forward Baggage Door Latch Assembly Installation of Forward Baggage Door Latch Assembly Adjustment of Forward Baggage Door Latch 4B14 4B14 4B14 4B15 4B15 4B15 4B17 52 70 00 52 70 01 52 70 02 52 70 03 52 70 04 DOOR WARNING Door Ajar Switches Removal of Door Ajar Switch Cabin Door Installation of Door Ajar Switch Cabin Door Adjustment o...

Page 825: ... secure with retaining clip 3 Connect electrical wire and install the door trim panel REMOVAL OF CABIN ENTRANCE DOOR LOWER 1 Remove the snubber by removing the bolt and nut 2 Remove scuff plate and rubber cover from cabin floor 3 While supporting the door remove door support cable at each side of door 4 Remove door panel and disconnect electrical wire 5 Remove locking roll pins from hinges remove ...

Page 826: ...ving the bolt washer and eccentric bushing 3 The safety latch actuator rod can be removed from the safety latch stop bracket by removing the cotter pin and washer 4 Remove one roll pin from the tube assembly and bushing located to the rear of the steps 5 Remove two bolts and shim washers holding the inner handle to the actuator assembly Note the amount and thickness of shim washers for reference w...

Page 827: ... ACTUATOR ROD 8 SCREWS 9 HANDLE OUTER 10 SHIM WASHERS II ACTUATOR 12 LATCH MECHANISM 13 LATCH SPRINGS 14 PIN 15 ACTUATOR SPRING 16 ACTUATOR ASSEMBLY 17 SPRING 18 ADJUSTIN SCREW 19 HOOK SPRING ATTACHMENT 10 ROLL PIN 21 SHIM WASHERS 22 BOLTS 23 HANDLE INNER Figure52 1 CabinEntranceDoorLatchAssembly 4B6 52 10 09 Page52 03 Issued September2 1981 ...

Page 828: ...emove any excess travel in the outer handle and secure with locknut 11 Install the protector panel behind the stems and the door trim panel assemblies with theproper screws ADJUSTMENT OF DOOR LATCH ASSEMBLY Refer to Figure 52 1 1 Remove aft innerdoor panel 2 The safety latch mechanism can be adjusted by loosening the pivot bolt and rotating the eccentric bushing to position the safety latch into i...

Page 829: ...es out Fine trim the other switch in the same manner Open and close the door several times watching the operation and indicator to ascertain that all latch and indicator parts operate properly PILOT DOOR REMOVALOF PILOT DOOR RefertoFigure52 2 1 Remove the bolt securing the support assembly to the bottom of the door 2 Remove hinge pins from upper and lower hinges and carefully pull door away from t...

Page 830: ...ne of striker bead and all edges are smooth to prevent tearing of seal 10 Fill the empty space behind the forward and aft lower corner fillets of the door frame with sealant to prevent water passing behind these plates to the aircraft interior 11 Seal the area between the scuff plate bulkheads outer skin and bulkheads with PRC 1221B 2 or MIL S 7505C and smooth with a non metallic tool 12 Remove th...

Page 831: ...TCH ROD END 7 LATCH 8 THEFT LOCK 9 MAIN LATCH 10 TO OUTSIDE HANDLE 11 MAIN LATCH ROD 12 BELLCRANK ASSY 13 INNER HANDLE ROD END 14 INNER HANDLE 15 OUTIDE SKIN 16 CABLE FROM SKETCH A 17 CABLE FROM SKETCH 18 OTTOMLATCH 19 CLEVIS ROD END 20 HINGE PIN 21 BUSHING 22 SPRING Figure52 2 Pilot sDoorLatchAssembly 4B10 52 10 15 Page52 07 Issued September2 1981 ...

Page 832: ... C Connect therod end to the latch and tighten the locknut 3 With the handle in the fully bolted position adjust the bottom latch to obtain the maximum possible travel by adjusting the clevis rod end 4 The top latch should be adjusted to obtain the best fit between the top of the door and the fuselage skin when the door is closed and bolted This is accomplished by adjusting the top latch rod end 5...

Page 833: ...olding the upper and lower cable assemblies together on the right side of the cabin entrance door Position the clevis of the lower cable assembly onto the eye bolt located directly below the cargo door and insert the lock pin 2 Disconnect the door support from the door 3 Pull the door latch full out Cut and remove hinge pin and pull the door away from the fuselage INSTALLATION OF CARGO DOOR Refer ...

Page 834: ... EYE BOLT 1 MAIN CABIN DOOR LATCH PLATE 4 CARGO DOOR LATCH 5 LINK 6 LATCH PIN GUIDE LATCH PIN 8 ROD ASSEMBLY 9 SPACER l 122 3 AS REQ TO INSURE PROPER LATCHING 10 SPRING RETAINER PLATE 11 SPRING Figure52 3 CargoDoorLatchAssembly 4B13 52 30 05 Page 52 10 Revised November 17 1983 ...

Page 835: ...osition with retainer plate 6 With installation complete operate the door latch to determine the latch pins move in and out of the pin guides smoothly WING LOCKER DOORS Referto Figure52 4 The only service required is maintaining a tight fit between the door and door frame This is accomplished by adjusting the catch assembly Loosen the attaching screws and move the catch to obtain the desired fit t...

Page 836: ...ed from the bracket by removing the cotter pin washers and pin 3 Removal procedure for forward baggage door key lock assembly is as follows A Remove two screws from the outside of the door to disconnect the lock guide plate assembly located on the inside of door B The key lock assembly can now be removed by removing the retaining nut and washer from the back of the key lock assembly INSTALLATION O...

Page 837: ...NCEMANUAL 1 NACELLE LOCKER 2 CATCH ASSEMBLY 3 BUCKLE ASSEMBLY 4 BAGGAGE STRAP 5 DOOR SUPPORT 6 LOCKER DOOR 7 DOOR LATCH 8 LOCK ASSEMBLY Figure 52 4 Nacelle Wing Locker Latch Assembly 4B16 52 30 13 Page 52 13 Issued September 2 1981 ...

Page 838: ...tment is done through the removal of the cover and adjustment of two clevis fittings located at the ends of the tube assembly 1 Remove the cotter pin washer and pin from the clevis and arm assemblies and loosen the locknuts between clevis and tube 2 With handle in the closed position turn the clevis in or out to get the arms of the arm assemblies to extend out at a 90 degree angle to the edge of t...

Page 839: ...er and lower halves of the cabin entrance door and lock 2 Apply pressure from inside the door and press the safety latch button Pull the inner handle to unlock the door The ajar switch should activate before the doors are completely unlatched Make certain that the switch activates before the handle has reached a 90 degree position to the door 3 Remove the trim cover over the end of the strap handl...

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Page 842: ...CHAPTER FUSELAGE 4B21 ...

Page 843: ...20 MAINTENANCEMANUAL CHAPTER 53 FUSELAGE TABLEOF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 53 00 00 53 00 01 GENERAL Description 4B23 4B23 4B22 53 Cont Effec Page 1 Revised February 23 1982 ...

Page 844: ...d when the latch at the lower side is released the window will swing in and forward A 23 by 30 inch emergency exit is an integral part of the second right window and is jettisonable when the release just aft of the exit is pulled The cabin entrance door is located on the left side of the fuselage just aft of the wing The door separates at the middle with the upper half swinging upward and the lowe...

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Page 846: ...CHAPTER STABILIZERS 4C1 ...

Page 847: ...EVATOR 4C8 55 20 01 Removal of Elevator 4C8 55 20 02 Installation of Elevator 4C8 55 20 03 Removal of Elevator Trim Tab 4C8 55 20 04 Installation of Elevator Trim Tab 4C8 55 20 05 Elevator Balancing Procedure 4C9 55 20 06 Elevator Control System Friction Measurement 4C10 55 30 00 VERTICAL STABILIZER 4C13 55 30 01 Removal of VerticalStabilizer 4C13 55 30 02 Installation of VerticalStabilizer 4C13 5...

Page 848: ...ncing must be accomplished in a draft free area and in a manner which allows unrestricted movement of the control surface BALANCING 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 Weig...

Page 849: ...t the stabilizer in position 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 washersand nuts Do not torque at this time 6 Check to determine if a gap exists ...

Page 850: ...FETY WIRE SHIM AS REQUIRE SKETCH A SKETCHA BOLT AN73 13A PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL BOLT AN3 4 A WASHERA N 0 0L 4 REQ BOLT AN174 22A WASHER AN960 416 2 REQ NUT MS10311 42lC REQ SKETCH B SKETCHB BOLT ANS IIA WASHER ANS0416 NUT MS20136424C REQ SKETCHC Figure55 1 EmpennageInstallation 4C5 55 10 02 Page55 03 Issued September2 1981 ...

Page 851: ...T MS20365 1032C SKETCHD PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL BOLT AN3 5A BOLT AN4 12 WASHER AN960 415 NUT AN310 4 SKETCHE SKETCHF SKETCHG SKETCHH Figure55 1 Empennage Installation cont 4C6 55 10 02 Page55 04 Issued September 2 1981 ...

Page 852: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL SKETCH J SHIM SKETCHM Figure55 1 EmpennageInstallation cont 4C7 55 10 02 Page55 05 Issued September2 1981 ...

Page 853: ...The elevator push pull rod may be connected to the arm of the torque tube assembly 4 Place the elevator in position install bolt assembly and torque 5 Install bolts attaching the torque tube bracket and elevator Ascertain that the elevator halves align and tighten bolts use a protractor to check the angle between elevators 6 Insert the elevator trim tab control rod through the right elevator and s...

Page 854: ... position chord line level Ascertain that the assembly rotates freely with no binding at knife edges 4 Hang the fabricated master test weight in the tool hole of the elevator counterbalance rib assembly part number 43745 Check the master test weight arm location as shown on Figure 55 2 and specified in Chart 5501 5 If the elevator is balanced trailing edge aligns with reference mark with just the ...

Page 855: ... not be in excess of six pounds with the bungee spring adjusted to 37 1 pounds The following procedure will let you determine the actual frictional value of the system 1 Attach a spring scale to the inboard trailing edge of the elevator as shown in Figure 55 3 2 With the spring scale attached position the elevator trailing edge down approximately 2 inches from the neutral position 3 Record the for...

Page 856: ...N ELEVATOR RIB Figure 55 2 Elevator Balancing THIS SPACEINTENTIONALLYLEFT BLANK PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL TAPE TRIM TAB LEVEL WITH ELEVATOR SEE CHART 5601 MASTER TEST WEIGHT ARM 4C11 55 20 06 Page55 09 Issued September2 1981 ...

Page 857: ...AILING EDGE AN3 3BBOLT FULLY INSERTED SPRING SCALE PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL OUTBOARD INBOARDEDGE LEFTELEVATOR Figure55 3 FrictionMeasurement 4C12 55 20 06 Page55 10 Issued September 2 1981 ...

Page 858: ...tain gap between stabilizer and fuselage skin is 187 of an inch Trim to obtain this gap 2 Ascertain thatthe sealer extrusion is attached to the lower side of the vertical stabilizer 3 Install the rear spar mounting bolts and nuts temporarily 4 Install the front spar mounting bolts washer and nuts Tighten but do not torque at this time 5 Check to determine if a gap exists between the web area of th...

Page 859: ...ven in Chapter 27 with the rudder and control wheels centered 5 Check rudder for proper operation Refer to Chapter 27 6 Install fuselage and cabin access panels REMOVAL OF RUDDER TRIM TAB Refer to Figure 55 1 1 Disconnect the control rod at the tab 2 Remove thehinge bolts securing the tab INSTALLATION OF RUDDER TRIM TAB Refer to Figure 55 1 1 Place the trim tab in position and secure with bolts an...

Page 860: ...edsthe staticlimitsand trim weights mustbe addedtothe rudderto producea balancedcondition RefertoChart5502 for the trimweight part numberandthe maximumamountallowedfortheparticularrudderassemblybeingbalanced NOTE During this procedure the master test weight must carry no more than the maximum number of 0 1 pound test weights as called out in Chart 5502 10 For rudderassembly partnumber40046 38 thet...

Page 861: ... PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL LEVEL RUDDER BALANCE JIG MASTER TEST WEIGHT ARM Figure55 4 RudderBalancing TRIM WEIGHT P N 53892 2 Figure55 5 RudderBalanceWeightLocation 4C16 55 40 05 Page55 14 Issued September2 1981 ...

Page 862: ...CHAPTER WINDOWS 4C17 ...

Page 863: ...emoval of Standard Windshield Installation of Standard Windshield Heated Windshield Removal of Heated Windshield Installation of Heated Windshield CABIN Removal of Side Windows Installation of Side Windows Pilot Door Storm Window Removal of Pilot Door Storm Window Installation of Pilot Door Storm Window Replacement of Pilot Door Storm Window Seal EFFECTIVITY 4C19 4C19 4C19 4C19 4C19 4C20 4C20 4C20...

Page 864: ...te Tape Number 163 or equivalent on each side of windshield Fold excess around edge No tape is needed between collar and windshield 3 Slide the windshield into place with the tape located under the fuselage skin 4 Install Prestite tape or equivalent on the bottom side of the center windshield trim strip Install strip machine screws and round nuts Do not tighten screws 5 Install retainer screws aro...

Page 865: ...plastic windshield Use only a non metallic window sealer 1 Apply Behr Manning Vinyl Sponge Tape 1x 1 16 inches P N 542 or equivalent on the outside surface of the windshield around the outer edges 2 Apply masking tape around windshield and along the edge of the collar skins and trim strip before applying SEMKIT SEALER PR 1221 B2 or PR1425 on the outside surface of the windshield around the edges o...

Page 866: ...3ORPR1425 ALUMINUM SEALER STRIP WINDSHIELD COLLAR PRESSTITE PRC 383 OR TAPE 163 PR1425 SEALER PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL PRC 383 R PR1425SEALER TAPE 163 SECTION B B PRC 383 OR PR1425 SEALER SECTIONC C SECTION D D NOTE APPLYRT V SILICONESEALER UNDERHEADSOF SCREWS AROUND WINDSHIELD OUTER PERI METER Figure56 1 WindshieldInstallation Standard 4C21 56 10 06 Page56 03 Revised November17 1983...

Page 867: ...ER PR 1221 OR PR1425 PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL SEMKITSEALER PR 1221 OR PR1425 VINYL SPONGE TAPE VINYL SPONGE TAPE SECTIONA A SECTIONB B VINYL SPONGE TAPE SECTION C C Figure56 2 WindshieldInstallation Heated 4C22 56 10 06 Page56 04 Revised November17 1983 ...

Page 868: ... When check is completed turn off the switch CABIN REMOVALOF SIDEWINDOWS 1 Remove the screws that hold the trim molding around inside of the window 2 Remove the nuts that secure the inner window retainer molding and remove window 3 Remove the rivets that secure the outer windowretainer molding and remove window 4 Remove old window sealer from surfaces INSTALLATION OF SIDE WINDOWS Refer to Figure 5...

Page 869: ...e storm window fastener and remove the storm window INSTALLATION OF PILOT DOOR STORM WINDOW 1 Align the storm window hinge halves and insert the hinge pin 2 Check storm window operation and sealing REPLACEMENT OF PILOT DOOR STORM WINDOW SEAL To replace the storm window seal apply a thin coat of Scotch Grip Industrial Adhesive EC 4475 3M 911 109 to outboard surface of the lip on the storm window an...

Page 870: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4D1 ...

Page 871: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4D2 ...

Page 872: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4D3 ...

Page 873: ...CHAPTER WINGS 4D4 ...

Page 874: ...TACHFITTINGS 4D6 57 40 01 Wing 4D6 57 40 02 Removal of Wing 4D6 10 82 57 40 03 Installation of Wing 4D11 10 82 57 50 00 FLIGHT SURFACES 4D13 57 50 01 Aileron 4D13 57 50 02 Removal of Aileron 4D13 57 50 03 Installation of Aileron 4D13 57 50 04 Aileron Balancing Procedure 4D13 57 50 05 Aileron Trim Tab 4D17 57 50 06 Removal of Aileron Trim Tab 4D17 57 50 07 Installation of Aileron Trim Tab 4D17 57 5...

Page 875: ...g 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 51 INSTALLATIONOF WINGTIP 1 Attach the ground wire terminal to the wing structure and connect the positive electrical leads together 2 Positionthewingtipon thewingandstartall screwswithwashers 3 With allscrewsinplace tighten ATTACHFITTINGS WI...

Page 876: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL Figure 57 1 WingInstallation 4D7 57 40 02 Page 57 02 Issued September2 1981 ...

Page 877: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL SKETCHD SKETCHE Figure57 1 WingInstallation cont 4D8 57 40 02 Page 57 03 Issued September2 1981 ...

Page 878: ...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 hydraulic...

Page 879: ...e end to pass through B Disconnect the aileron balance cable at station 171 and draw the cable from the fuselage Remove the cable pulley to allow cable to be removed C Remove the access panel to 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 Refer to Figu...

Page 880: ...NSTALLATION 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 cables etc for inserting into the win...

Page 881: ...Adjustment of Aileron Chapter 27 and safety turnbuckles 19 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 and connec...

Page 882: ...in Figure 57 5 Establish a horizontal reference mark which aligns with the trailing edge of the aileron when it is held in a horizontal level position chord line level 3 Ascertain that the surface rotates freely with no binding at the knife edges 4 Assemblies P N 40200 42 and P N 40200 43 A If the surface balances it is within the balance limits and is satisfactory B If the surface is leading edge...

Page 883: ...wed Trim Weight Part No Maximum No of Trim Weights Allowed Per Surface Allowable Balance Weights plus Trim Weight Balance Limits Inch Pounds Aileron Part No 40200 42 40200 43 0 00 to 0 50 6 00 None 54395 2 3 1 4 5 2 0 0 3 Maximum condition 3 54395 2 trim weights and 1 54395 3 trim weight THIS SPACE INTENTIONALLY LEFT BLANK 4D14 57 50 04 Page 57 09 Revised February 23 1982 ...

Page 884: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL SKETCH A Figure 57 4 Aileron and Flap Installation 4D15 57 50 04 Page 57 10 Issued September 2 1981 ...

Page 885: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL SKETCH B SKETCHC SKETCH E SKETCHD SKETCH F Figure57 4 AileronandFlapInstallation cont 4D16 57 50 04 Page 57 11 Issued September2 1981 ...

Page 886: ...ab backand inboardenoughto removethe outboardhingepin fromitsbushing Removethe tab INSTALLATIONOFAILERONTRIM TAB Referto Figure57 4 1 Insertthetabcontrolrodthroughtheaileronandinserttheoutboardhingepinintoitsbushing 2 Positionthe inboardhingebrackets installhinge bolt and torqueto 38 in lbs includes 18 in lbs averagefrictiontorque 3 Connectthe tabcontrolrod 4 Checktabforproperoperation Referto Cha...

Page 887: ...flap 4 Remove the upper roller assemblies from the flap brackets 5 Remove the lower roller assemblies and remove flap INSTALLATION OF FLAP Refer to Figure 57 4 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 s...

Page 888: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL GRIDS 4D19 THRU 4D24 INTENTIONALLY LEFT BLANK 4D19 ...

Page 889: ...CHAPTER PROPELLER 4E1 ...

Page 890: ...top 4E7 61 10 05 Blade Track 4E8 61 20 00 CONTROLLING 4E8 61 20 01 Propeller Governor 4E8 61 20 02 Removal Of Propeller Governor 4E8 61 20 03 Installation Of Propeller Governor 4E8 61 20 04 Rigging And Adjustment Of Propeller Governor 4E9 61 20 05 Propeller Synchrophaser 4E10 61 20 06 Description 4E10 61 20 07 System Operating Procedure 4E11 61 20 08 Troubleshooting 4E11 61 20 09 Removal Of Pulse ...

Page 891: ...the blades into high pitch in the absence of governor oil pressure Thus feathering is accomplished by compressed gas and springs PROPELLER ASSEMBLY 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 Und...

Page 892: ...e 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 fittings for each propeller blade alternate the next time Apply grease through the zerk fitting until fresh grease appears at the fitting hole of the removed fitting Care should be taken to avoid blowing out hub gaskets INS...

Page 893: ... 3 BOLT 4 COUNTERWEIGHT 5 PROPELLER DOME 6 SCREW CAPATTACHMENT 7 CAP SPINNER 8 SAFETY WIRE 9 CHECKNUT SPINNER 10 CAP AIRVALVE 11 AIRVALVE 12 LOWPITCHADJUSTMENT 13 GREASEFITTING 14 BALANCE WEIGHT Figure61 1 PropellerInstallation 4E5 61 10 03 Page61 03 Issued September 2 1981 ...

Page 894: ...opeller Mounting Bolts Spinner Bulkhead Check Nut Spinner Attachment Screws Low PitchCheck Nut 2575 RPM Max Required Torque Dry 22 foot pounds 60 foot pounds 35 40 foot pounds 40 inch pounds 35 40 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 Ib 38 1 lb 36 1 lb 33 1 lb NOTE DO NOT CHECK PRESSURE...

Page 895: ...CK IN FACE OF BLADE REMOVED BY FILE AND CROCUS CLOTH AS RECOM MENDED Figure 61 2 Typical Nicks and Removal Method 7 Test for leakage by using a soap solution or equivalent and applying it around the valve stop 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 ADJUSTMENTOF LOW PITCH BLADEANGLEANDSTOP Adjustment of the low ...

Page 896: ...k should be removed and inspected for bent blades or for pans of sheared O ring or foreign particles which 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 cable end from the governor control arm 3 Remove the governor mou...

Page 897: ...le of the control arm 6 Adjust governor control 7 Install engine cowl RIGGING AND ADJUSTMENTOF PROPELLER GOVERNOR RefertoFigure61 3 1 Startthe engineandwarmin thenormalmanner 2 To check high RPM low pitch setting move the propeller control all the way forward to the INCREASEPROPELLERposition At this positionthe governorspeedcontrolarmshouldbe against the highRPMfine adjustingscrew With thethrottle...

Page 898: ...lever clearance Reconnect the cable end and tighten jam nut 5 It is usually only necessary to adjust the high RPM setting of the governor control system as the action automatically takes care of the positive high pitch setting PROPELLER SYNCHROPHASER DESCRIPTION This system consists of two pulse generators a computer and an electrical control solenoid on the governor The signals from both generato...

Page 899: ...se When an audible beat is heard with the system operating it is undoubtedly not holding the slave engine in phase with the master engine Return the selector switch to its manual position for 45 seconds and readjust engine RPM manually to operating RPM Set selector switch to phase position for automatic operation If the phasing is not established after the above procedure it is possible that some ...

Page 900: ... diagram Checkfor shorts open circuit breaker broken wires and wires connected to the wrong pins C Rotate the right engine by hand and watchthe Right Engine light If the light is off rotate the engineuntil it comeson or viseversa Theenginemayneedto berotatedtworevolutionsto obtain achange Repeattheprocedurefor theleftengineobservingtheLeftEnginelight D Placethe phase manualswitchin the manualposit...

Page 901: ...orm operational check Tach shafts and or dual drive units faulty Pulse generator and glow lamp amplifier in computer not operating Glow lamp or lamps and or photo conductor or con ductors defective Faulty computer Visually check Perform electrical test Replace glow lamp or photo conductor assemblies Perform electrical test Perform electrical test System will not sync Electrical NOTE Unit will not ...

Page 902: ...EADAPTER RIGHT ENGINE 7 TACHOMETER SHAFT PULSEGENERATOR 9 INSTRUMENT PANEL 10 WIRE HARNESS 11 DUALDRIVEADAPTER LEFTENGINE 12 TACHOMETER SHAFT 13 FIREWALL 14 PULSEGENERATOR 16 COCKPIT CONTROL SWITCH 1 CIRCUIT PROTECTOR 17 GOVERNOR 18 SOLENOID Figure61 4 SynchrophaserInstallation 4E14 61 20 08 Page61 12 Issued September 2 1981 ...

Page 903: ...the front of the pulse generator that connects it to the dual tach drive and remove the generator INSTALLATION AND ADJUSTMENT 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 Be...

Page 904: ...eller position cylinder number 2 at T D C on the ignition stroke and rotate the engine an additional 22 teeth on the ring gear beyond the timing mark 6 Connect the electrical plug connector to the pulse generator and install the access panel on top of the nacelle REMOVALOF COMPUTER ASSEMBLY This unit is mounted on a bracket in the upper right rear corner of the nose baggage compartment Refer to Fi...

Page 905: ...ON SWITCH PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL PHOTO 7 5 10W OHMITE RES SOLENOIDLOAD SIMULATOR TEST A to F 0 to 12V B to F 0 to 12V C to F 12V D to F 6V E to F SV DISCONNECT STROBESENSOR C TEST A to F 0 DC to F 0 DC C to F 12to 14V DC AC to F 15V A C A C E to F 15V AC 9 V AT EVEREADY 266 2iu 15V ADJUST R4 FOR PULSE AMPLITUDE OF 1 5 VOLTS USE OSCILLOSCOPE FOR MEASUREMENTS Figure 61 7 Pulse Gener...

Page 906: ...SHOWN IN RIGHT I ENGINE I PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL I L LEFT ENGINE FLEX SHAFTS FLEX SHAFT INPUT TO TACHS ON INSTRT PANEL Figure61 8 SynchrophaserSchematic 4E18 61 20 12 Page61 16 Revised July 3 1984 ...

Page 907: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4E19 ...

Page 908: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 4E20 ...

Page 909: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4E21 ...

Page 910: ...CHAPTER STANDARD PRACTICES ENGINES 4E22 ...

Page 911: ...NUAL CHAPTER 70 STANDARD PRACTICES ENGINES TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT 70 00 00 70 00 01 SUBJECT GRID NO EFFECTIVITY 4E24 4E24 GENERAL Standard Practices Engine 4E23 70 Cont Effec Page 1 Revised February 23 1982 ...

Page 912: ...hly clean before assembling 5 Never reuse any lockwire lockwashers 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 agai...

Page 913: ...CHAPTER POWERPLANT 4F1 ...

Page 914: ... 4F15 71 10 03 Installation Of Engine Cowling 4F15 71 10 04 Engine Cowl Flap 4F16 71 10 05 Removal Of Cowl Flap Transmission 4F16 71 10 06 Cleaning Inspection And Repair Of Cowl Flap Transmission 4F16 71 10 07 Installation Of Cowl Flap Transmission 4F16 71 10 08 Rigging And Adjustment of Cowl Flap 4F17 71 10 09 Removal Of Cowl Flap Position Sender Assembly 4F17 71 10 10 Installation Of Cowl Flap P...

Page 915: ...hanical linkage and an electric motor Electric indicators are used to show the position of the cowl flap The induction systemconsists of a dry type air filter an alternate air door a Bendix RSA 1OED1type fuel injector and a Lear Siegler fuel supply pump as an integral part of the fuel injector system An AiResearch model TH08A60 turbocharger is mounted as an integral part of the engine Automatic wa...

Page 916: ...age to the oil pressure relief valve located in the upper right side of the crankcase in front of the accessory housing This relief valve regulates the engine oil pressure by allowing excessive oil to return to the sump while the balance of the pressure oil is fed to the main oil gallery in the right half of the crankcase Residual oil is returned by gravity to the sump where after passing through ...

Page 917: ...ts Inoperative or defective vibrator Retard contact assembly in magneto not operating electrically Engine may kick back during cranking due to advance timing of ignition 4F5 If voltage is adequate listen for buzzing of vi brator during starting If no buzzing is heard either the vibrator is defective or the circuit from the Out put terminal on the vi brator to the retard contact assembly is open Ch...

Page 918: ...ting the starter switch Plug lead should throw a 19 of an inch spark If spark is weak or missing try new vibrator If this does not correct trouble check magneto for improper internal timing or improperly meshed distri butor gears Check magneto to engine timing Check magneto timing Checktimingof retard points Failure of engine to idle properly Incorrect idle mixture Adjustmixture Leak intheinductio...

Page 919: ...ogged Check fuel lines for dirt or other restrictions Check fuel injectionnozzles Tighten all connections Re place defective parts Clean and gap or replace spark plugs Fill tank with fuel of recommended grade Clean points Check timing of magnetos Check wire with electric tester Replace defective wire Replace connectors on spark plug wire Clean or replace Failure of engine to develop full power Lea...

Page 920: ...eads for con tinuity and break don Check distributor block for moisture and carbon tracking Check contact springs in distributor block Check magneto contact assem blies for burning or dirt Main and Retard Check distributor timing Check magneto to engine timing Inspect contact assemblies for proper opening Blocked fuel injector nozzles Check plugs and leads Clean or replace nozzles Low oil pressure...

Page 921: ...ines or strainers Excessive blow by Failing or failed bearings Defectivetemperature gauge Defectivethermostatic bypassvalve Fill oil sump to proper level with specified oil Replace with oil conforming to specifications 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 Excessiveoilcon...

Page 922: ... Cause Trouble Remedy Excessive oil consumption cont Failure of rings to seat New nitrided cylinders Use mineral base oil Climb to cruise altitude at full power and operate at 75 cruise power setting until oil consumption stabilizes 4F10 71 00 02 Page71 08 Issued September2 1981 ...

Page 923: ...al equipment 12 Disconnect the pressure pump hose at the upper left side of the fire wall 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 control cable at the left side of the oil filter plenum Disconnect the cables from their attachme...

Page 924: ...st temperature probe at the aft side of the exhaust manifold 13 Connect the alternator primary cable to the filter box located on the lower right side engine mount Connect the field wire 14 Route the starter cable through the lower side of the left aft engine baffle and attach the cable end to the starter Secure cable with clamps at the engine mount and the engine 15 Ascertain that the magneto swi...

Page 925: ...RAFT T 1020 MAINTENANCEMANUAL 5 17 18 20 NOTE Torque nuts on AN6 41A bolt attatching the engine mount to the firewall 17to 20 foot pounds Figure71 1 EngineInstallation 4F13 71 10 01 Page 71 11 Issued September2 1981 ...

Page 926: ...SSEMBLY 16 EXHAUST TAIL PIPE UPPER 17 SHAFT TACHOMETER 18 THERMOCOUPLE 19 TAIL PIPE BOTTOM 20 HOSE INTAKE PRESSURE PUMP 21 EXHAUST PLENUM 22 EXHAUST STACK EXTENSION L 23 COOLER OIL 24 MAGNETO ASSEMBLY 25 TUBE BREATHER 26 TUBE MAGNETO COOLING 27 DRAIN ENGINE SUMP 28 EXHAUST STACK LEFT 29 PIPE INTAKE 30 SPARK PLUG 31 NOZZLE INJECTOR 32 TUBE AIR BLEED 33 BOLT 34 BUSHING 35 SHOCK MOUNT GOLDCOOING 36 S...

Page 927: ...urewithscrewfastenersalongthe aftsectionof the cowl WARNING Thecowlingfastenerlockedpositionstripemustbe maintained Refurbish orreplacestripeiffaded missingorcowlingisrepainted 2 Raise the lower half to join the upper half using caution so as not to damage the tubes which extend through the cowl bottom Secure the screw fasteners along the aft section of the cowl and lock the fasteners that join th...

Page 928: ...or excess wear within the transmission by turning the screw by hand and noting the end and side play in the transmission drive shaft End play should not be great enough to cause end pressure on the motor drive shaft 6 Should any of these checks show excess wear corrosion or damage the transmission or its components should be replaced 7 After the transmission screw and tube have been cleaned and dr...

Page 929: ...n measured vertically to the bottom of the cowl at the rear edge of the cowl flap 3 Secure all jam nuts after adjustments have been completed REMOVAL OF COWL FLAP POSITION SENDER ASSEMBLY Refer to Figure 71 3 1 Remove the access plate located on top of the engine nacelle aft of the fire wall 2 Disconnect theelectrical leads from the sender unit 3 Loosen the bolt assembly that locks the arm on the ...

Page 930: ...shaft end in a clockwise direction to its stop position 5 Turn on the master switch A minimum of 24 volts must be supplied to the electrical system when making this adjustment 6 Rotate the sender shaft slowly counterclockwise when viewed from the shaft end until the flap indicator on the instrument panel reads flap closed Tighten the arm on the sender shaft 7 Operate the flap to the open and close...

Page 931: ...esses 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 bushings into place and install the spacers forward shock mounts washers and nuts Start nuts only a few threads 8 Remove the upper mount attachment bolts nuts washers heat shield forward shock mounts and spacers 9 Lower the engine e...

Page 932: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL GRIDS 4F20 THRU 4F24 INTENTIONALLY LEFT BLANK 4F20 ...

Page 933: ...CHAPTER ENGINEFUELAND CONTROL 4G1 ...

Page 934: ...allation Of Fuel Injector 4G5 73 10 07 Fuel Air Bleed Nozzle 4G5 73 10 08 Removal Of Fuel Air Bleed Nozzle 4G5 73 10 09 Cleaning And Inspection Of Fuel Air Bleed Nozzle 4G6 73 10 10 Installation Of Fuel Air Bleed Nozzle 4G6 73 30 00 INDICATING 4G7 73 30 01 Fuel Pressure Gauge 4G7 73 30 02 Troubleshooting 4G7 73 30 03 Removal And Installation Of Fuel Pressure Gauge 4G8 73 30 04 Fuel Flow Gauge 4G8 ...

Page 935: ...ghtness 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 causes rapid deterioration of synthetic...

Page 936: ... allow the injector to be removed PREPARATION FOR STORAGE Any unit taken out of service or units being returned for overhaul must be flushed with preserving oil Specification MIL O 6081 Grade 1010 using the following procedure 1 Remove plugs and drain all fuel from the injector If available apply 10 to 15 psi air pressure to the fuel inlet until all fuel is discharged from the injector 2 Replace p...

Page 937: ...when injecting preservative into the engine prior to storing or shipping INSTALLATIONOF FUEL INJECTOR 1 Move the injector inlet plenum aft enough to allow the injector with gasket to be installed Install attachment bolts and torque refer to Lycoming Torque Specs 2 Install and secure the hose between the injector and turbocharger 3 Connect the hoses and linksthat were disconnected from the turbocha...

Page 938: ...on of Lycoming Service Instruction No 1275 INSTALLATIONOF 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 73 2 3 Connect the vent to the nozzle shroud 4 Install the spring and spring retainer on the nozzle stem 5 Connect the fuel line to the nozzle and clamp...

Page 939: ...Defective fuel pump Defective gauge 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 lines Replace gauge Pressure low or pressure surges Obstruction in inlet side of pump Trace lines and locate obstruction Faulty bypass valve Replace Faulty diaphragm Replace or rebuild pum...

Page 940: ...ssure gauge will be in the reverse of removal FUEL FLOW GAUGE The fuel flow gauge is a non electric differential pressure gauge mounted in the bottom of the instrument panel TROUBLESHOOTING CHART 7302 TROUBLESHOOTING FUEL FLOW GAUGE Trouble Cause Remedy Pointer oscillates Air in fuel line Purge line Gauge reads low at altitude Pointer does not return to zero Vent line restricted Fuel indiaphragm o...

Page 941: ...reads protrude beyond the teflon seal 4 Thread fittings a minimum of three threads engagement into port of fuel flow gauge 5 Using light to medium torque tighten down tru seal nut against port to complete leak proof assembly FUEL FLOW LOWWARNINGLIGHT Illumination of the Fuel Flow Low Warning Light located in the annunciator panel indicates impending fuel starvation due to insufficient fuel in the ...

Page 942: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4G10 ...

Page 943: ...CHAPTER IGNITION 4G11 ...

Page 944: ... 74 10 05 Installation And Timing Procedure Timing Magneto To Engine 4G17 74 10 06 Starting Vibrator 4G19 74 10 07 Starting Vibrator Checking Procedure 4G19 74 10 08 Removal Of Starting Vibrator 4G20 74 10 09 Installation Of Starting Vibrator 4G20 74 20 00 DISTRIBUTION 4G20 74 20 01 Ignition Harness 4G21 74 20 02 Inspection Of Harness 4G21 2 82 74 20 03 Maintenance Of Harness 4G22 74 20 04 Spark P...

Page 945: ...or excessively burned areas should be discarded Examine the cam follower felt for proper lubrication If necessary points can be cleaned by using any hard finished paper Clean breaker compartment with dry cloth 2 If engine operating troubles develop which appear to be caused by the ignition system it is advisable tocheckthesparkplugsandwiringfirstbeforeworkingon themagnetos 3 Should the troubleappe...

Page 946: ... the oil Blot off the excess with a clean cloth Too much oil may foul contact points and cause excessive burning 8 Check the capacitor mounting brackets for cracks or looseness Using the Scintilla 11 1767 1 2 or 3 Condenser Tester of equivalent check capacitor for capacitance series resistance and leakage Capaciance shall be at lease 0 30 microfarads 9 Check magneto to engine timing as follows A C...

Page 947: ...g the engine accidentally when the ground lead is removed from the magneto 2 Disconnect the ground lead and the retard spark lead on the left magneto at the magneto 3 Remove the nuts and washers and draw the magneto fromthe engine TIMING PROCEDURE INTERNAL TIMING 1 Remove the cover to the contact s distributor block etc 2 To internally time the main contact assembly of either the dual breaker magn...

Page 948: ...e respective E gap mark 15 2 Tighten adjusting knob of 11 8465Tool and remove the 11 8149 Pointer Assembly from magneto Using a timing light adjust main contact points to just open This adjustment shall be made by rotating cam in opposite direction of rotation a few degrees beyond point where contacts close Then rotate cam in normal direction of rotation until contacts just open While holding cam ...

Page 949: ...g Tighten adjusting knob of 11 8465Rotor Holding Tool Applya light coating of Bendix Grease P N 10 27165 to teeth of distributor gear if needed The large distributor gear incorporatesfour timing marks L and LB for left handrotation and R andRB for right handrotation B With distributor gear assembled to block turn gear until raised rib on block lines up between the L and LB marks Assemble block and...

Page 950: ...ectionhole Referto Figure74 8 Withoutallowingthegear toturnfromthisposition assemblegasketand magnetoto the engine Secureinplacewithwashersandnuts tightenonlyfingertight 4 Fasten groundwire of electric timing light to any unpaintedportionof the engine and one of the positive wires of the timing light to a suitable terminal connectedto the ground terminal of the magneto Thenturnthe enginecrankshaft...

Page 951: ...retogether If timingis correct both timinglights will go out simultaneouslywhen the timing marksare in alignment Tightennuts to specifiedtorque 7 Aftermagnetoshave beenproperlytimed replacebreakercoverandsecure 8 Installthegroundlead andtheretardsparkleadon theleft magneto 9 Place the harness terminalplate on the magnetoand tightennut aroundthe plate alternatelyto seat coversquarelyon magneto Torq...

Page 952: ...s should be seen when holding the lead approximately 19 of an inch from engine ground WARNING Grasp the spark plug lead far enough away from the connection so as not to produce any dangerous electrical shock 5 If the spark does not jump the gap check the applied voltage to the starting vibrator The voltage should be 24 volts 6 If voltage is correct check the contact points of the magneto Both sets...

Page 953: ...ugs and extract the lead terminations Inspect contactspringsand compressionspringsfor any damageor distortion Inspectsleeves for cracksor carbontracking 4 Inspectcouplingnutsandelbowassembliesfor damagedthreadsor otherdefects NOTE Replaceany damagedcomponents 5 Test continuity of each harness lead using a High Tension Lead Tester Part No 11 8888 1from Bendix as follows A Connectblacktestleadtocont...

Page 954: ...ss inaccessibility of installation or number of leads to be replaced makes it unreasonable To replace grommets or eyelets pull the conductor through the shielding sufficiently to make eyelet accessible Remove the eyelet being careful not to damage conductor wire Replace grommet and eyelet using the AB groove of Crimping Tool No 11 4152 or a pair of diagonal pliers modified as shown in Figure 74 11...

Page 955: ...FT T 1020 MAINTENANCEMANUAL LUBRICATE SEE NOTE NOTE USEGO JONO LOK MANUFACTURED BY USEFLUORCARBON SPRAY GOGER INC AKRON OHIO44309 USEFLUORCARBON SPRAY Figure 74 13 Lubricating Sleeve Figure 74 14 Lubricating Ferrule Shoulder 74 20 03 Page 74 11 Revised February 23 1982 4G23 ...

Page 956: ...ol Install contact spring on cable terminal NOTE It may be necessary to lubricate the cable and insulating sleeve with a thin film of DC 200 200 000 centistokes or commercial grade alcohol tofacilitate assembly 5 To replace one of the lead assemblies proceed as follows A Remove clamps and brackets from defective lead assembly Cut ties from assembly and discard B Cut the eyelet from the lead and re...

Page 957: ...ust be used and inserted under the braid exactly as stated in step F G Pulltheleadbackintothecovertowedgethebraidbetweenthetapersof thecoverandferrule H Providea backup supportfor the cover and seatthe ferrule usingthe 11 7074FerruleSeatingTool Referto Figure74 18anda mallet Ferrulemustbedrivenstraightintothecoverandfullyseated I Threadthe pre strippedend of the conductorthroughgrommet Place a new...

Page 958: ... LOK manufactured by Goger Inc Akron Ohio 44309 10 Check cam securing screw Screw must be torqued to 21 25 inch pounds 11 With all high tension terminal grommets seated against the ferrules in the cover attach the bottom capacitor lead to the right main breaker and then the top capacitor lead to the left main breaker Position the cover on the magneto and secure Torque cover screws to 30 35 inch po...

Page 959: ...RIAL BRASS BLUECOATING Figure 74 17 Ferrule Positioned Under Braid Figure 74 18 Ferrule Seating Tool 11 7074 111 3000 DISTRI UTOR BLOCK DISTRIBUTOR BLOCK Figure 74 19 Position of 11 8627 Kit and Contact Spring at Start of Installation Figure 74 20 Position of 11 8627Kit and Contact Spring after Installation 4H3 74 20 03 Page 74 15 Issued September2 1981 ...

Page 960: ...I PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL Figure 74 21 Ignition System Schematic 4H4 74 20 03 Page 74 16 Issued September2 1981 ...

Page 961: ...RCRAFT T 1020 MAINTENANCEMANUAL Figure74 22 RemovingFrozenSparkPlug CHART7401 COUPLING TORQUES Spark Plug Coupling Threads 5 8 24 3 4 20 Torque lb in 90 95 110 120 4H5 74 20 03 Page74 17 Issued September2 1981 ...

Page 962: ... torque must be used to unscrew the plug The higher torque in removal is not as detrimental as in installations since it cannot stretch the threaded section It does however impose a shearing load on this section and may if sufficiently severe produce a failure in this location NOTE Torque indicating handle should not be used for spark plug removal because of the greater torque requirement 3 Place ...

Page 963: ...and foreign deposits 3 Set the electrode gap at 015 to 018 inches 4 Test the spark plug both electrically and for resistance INSTALLATION OF SPARK PLUGS Before installing spark plugs ascertain that the threads within the cylinder are clean and not damaged 1 Apply anti seize compound sparingly on the threads and install gasket and spark plugs Torque 360 to 420 inch pounds CAUTION Make certain the d...

Page 964: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4H8 ...

Page 965: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 4H9 ...

Page 966: ...CHAPTER ENGINECONTROLS 4H10 ...

Page 967: ...NTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 76 00 00 76 10 00 76 10 01 76 10 02 GENERAL POWER CONTROL Adjustment Of Throttle And Mixture Controls Adjustment Of Idle Speed And Mixture 4H12 4H12 4H12 4H12 4H11 76 Cont Effec Page Revised February23 1982 ...

Page 968: ...ding steps readjust the idle speed to the desired 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 Full ...

Page 969: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLYLEFT BLANK 4H13 ...

Page 970: ...CHAPTER ENGINEINDICATING 4H14 ...

Page 971: ...R 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 4H16 4H16 4H16 4H16 4H17 4H17 4H17 4H...

Page 972: ...rcury TROUBLESHOOTING Refer to Chart 7701 CHART 7701 TROUBLESHOOTING MANIFOLD PRESSURE INDICATOR Trouble Cause Remedy Excessive error at existing barometric pressure Excessive error when engine is running Sluggish or jerky pointer movement Pointer shifted Line leaking Defective instrument Replace instrument Tighten lineconnections Replace instrument Restricted filter element Replace filter Replace...

Page 973: ... of crankshaft speed in revolutions per minute The right hand tachometer has a reversing drive to correct for the counter rotation of the right hand engine TROUBLESHOOTING Refer to Chart 7702 CHART 7702 TROUBLESHOOTING TACHOMETER Trouble Cause Remedy No reading on indicator either permanent or inter mittent Broken drive cable Springs weak Replace cable Replace instrument Loose cable connections Ti...

Page 974: ...engine to the tachometer will rotate properly REMOVAL AND REPLACEMENT Refer to Chapter 39 TEMPERATURE CYLINDER HEAD TEMPERATURE GAUGE The cylinder head temperature gauge is in the instrument cluster located on the instrument panel This instrument measures the cylinder head temperature using a sender located in a cylinder head This gauge is an electrical instrument and is wired through the instrume...

Page 975: ...oken glass bent or broken pointer broken case the following checks should be performed before removing the instrument 1 The thermocouple probe should be removed and cleaned as required The following procedure should be used A Detach thethermocoupleleadsfromthe extensionlead if necessary Donot detachif the probe canbe removedandcleanedwithleadsattached B Unscrewthenutand liftout thethermocoupleasse...

Page 976: ...cal 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 troublestill existsafter makingthe abovechecks REMOVEthe leadsfromthe indicatorand using anohmmeterchecktheextensioncablesandthermocouples forthe following PROBERESISTANCE 1 ohm EXT LEADRESISTANC...

Page 977: ... reading Defective gauge probe or 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 PACKINGNUT Figure 77 1 EGT Probe Adjustable 4H21 77 20 08 Page77 06 Issued September2 1981 ...

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Page 979: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4H23 ...

Page 980: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGEINTENTIONALLYLEFT BLANK 4H24 ...

Page 981: ...CHAPTER OIL SYSTEM 411 ...

Page 982: ... 30 03 79 30 04 79 30 05 79 30 06 GENERAL Description And Operation Troubleshooting DISTRIBUTION Adjustment Of Oil Pressure Relief Valve Oil Screen Oil Filter Element Installation Of Oil Cooler INDICATING Engine Oil Pressure Gauge Troubleshooting Removal And Replacement Oil Temperature Indicator Troubleshooting Removal And Replacement 413 413 413 416 416 416 416 417 417 417 418 418 418 419 419 412...

Page 983: ... to the cooler an oil cooler bypass valve is provided to pass the oil directly from the oil 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 lo...

Page 984: ...o specifications 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 bearings Worn or cracked piston rings Incorrect installation of piston rings Failure of rings to seat New n...

Page 985: ...essure line Remove and clean oil pres sure relief valve Check gasket between acces sory housing and crankcase Dirty oil strainers Remove and clean oil strainers High oil temperature Defective pressure gauge Stoppage in oil pump intake passage See High oil temperature in Trouble column Replace gauge Check line for obstruction Clean suction strainer THIS SPACEINTENTIONALLYLEFT BLANK 415 79 00 02 Pag...

Page 986: ...tthe screenandgasket and replacethegasketifovercompressedor damaged OIL FILTERELEMENT 1 The oil filter element should be replaced after each fifty hours of engine operation this is accomplishedby removingthe lockwirefromthe bolt headat the endof the filterhousing loosening thebolt andremovingthefilterassemblyfromtheadapter 2 Beforediscardingthefilterelement removethe outerperforatedpapercover andu...

Page 987: ...und fitting boss care should be taken not to permit excessive torque on the fittings 2 When attaching lines to the cooler 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 gauge is mounted in the cluster on the instrument panel This gauge will indicate ...

Page 988: ...r other engine failure Replace instrument Replace instrument Disconnect line and fill with light oil Check for leaks If trouble persists clean and adjust relief valve Clean and check Clean and check Shut down engine refer to Chart 7901 NOTE Gauge will take longer to indicate in cold weather REMOVALANDREPLACEMENT RefertoChapter39 OIL TEMPERATUREINDICATOR Theoil temperatureindicatoris mountedinthe i...

Page 989: ... 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 419 79 30 06 Page79 07 Issued September2 1981 ...

Page 990: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4110 ...

Page 991: ...STARTING CHAPTER 4I11 ...

Page 992: ...GENERAL Description And Operation CRANKING Maintenance Of Starting System Starting Motor Overhaul Of Starting Motor Removal Of Starting Motor Disassembly Of Starting Motor Brushes Brush Holders Armature Field Coils Gear And Pinion Housing Bendix Drive Assembly Of Starting Motor Bench Tests Starting Motor Control Circuit Starting Motor Service Test Specifications 4113 4113 4114 4114 4114 4114 4114 ...

Page 993: ...rough the gear housing where it is supported by a roller bearing The gear mates with the teeth of the reduction gear that drives the bendix shaft The shaft is keyed to the reduction gear The Bendix drive is held in position on the shaft by a spirol pin The shaft is supported in the gear housing by a closed end roller bearing and in the pinion housing by a graphitized bronze bearing When the armatu...

Page 994: ...l 0 3 volt maximum B Voltageloss from battery ground post to starter frame 0 1 volt maximum NOTE If voltage loss is greater than the limits outlined in steps A and B additional tests should be made over each part of the circuit to locate the high resistance connections 3 No lubrication is required on the starting motor except at the time of overhaul Then lubricate the entire shaft under Bendix Dri...

Page 995: ...shaft 3 Turn the Bendix pinion until it locks in the extended position Locate spirol pin and use a punch to remove Slide drive assembly off the shaft Do not attempt to disassemble the drive and do not dip it in cleaning solvent 4 To remove the roller bearings from the gear housing use an arbor press and the correct bearing arbor DO NOT HAMMER OUT Each part should be cleaned and inspected for exces...

Page 996: ...armatureshaft shouldbe inspectedfor roughbearingsurfacesandroughor damagedsplines 2 Totest the armatureforgrounds a setof testprobesconnectedin serieswitha 110voltlight shouldbe used Touchone probeto a commutatorsegmentand the other to the armaturecore If the test lamp lights the armatureis groundedandshouldbereplaced 3 To testfor shortedarmaturecoils a growleris used Referto Figure80 3 The armatu...

Page 997: ...or equivalent on the Bendix portion of the shaft End play should be 005 to 050 of an inch 2 New brushes should beproperly seated when installing by wrapping a strip of 00 sandpaper around the commutator with the sanding side out 1 1 4 to 1 1 2 times maximum Drop brushes on sandpaper covered commutator and turn the armature slowly in the direction of rotation Dust should be blown out of the motor a...

Page 998: ...e battery solenoid and manualstarting switchesfor breaks poor connectionsand faulty insulation Tighten all connectionsand make sure solenoid is firmlymountedandmakesa goodgroundconnection 2 Check the voltageloss across the switchcontactsduring normalstarting If loss is in excess of 0 2 voltsper 100amperes the solenoidshouldbereplaced 3 If solenoidfailstooperatewhenthe manualswitchis turnedon or if...

Page 999: ...on 32 oz 40 oz No Load Test 75 F Volt Max Amps Min R P M 20 35 1300 Stall Torque Amps Min Torque Ft Lbs Approx Volts Pinion Position Drive at rest Drive extended 260 27 0 14 0 1 748 2 388 1 855 2 496 This dimension is measured from the centerline of the mounting hole nearest the drive end head to the edge of the pinion END 4119 80 10 15 Page80 07 Issued September2 1981 ...

Page 1000: ...PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL THIS PAGE INTENTIONALLYLEFT BLANK 4120 ...

Page 1001: ...CHAPTER TURBINES 4I21 ...

Page 1002: ...Removal Of Density Controller 4J10 81 20 08 Inspection And Repair Of Density Controller 4J10 81 20 09 Installation Of Density Controller 4J10 81 20 10 Adjustment Of Density Controller 4J 10 81 20 11 Differential Pressure Controller 4J11 81 20 12 Removal Of Differential Pressure Controller 4J11 81 20 13 Inspection And Repair Of Differential Pressure Controller 4J11 81 20 14 Installation Of Differen...

Page 1003: ...stem 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 Turboch...

Page 1004: ...mpeller 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 Leakinengineintake or exhaust 4124 Thoroughly clean compressor assembly Service air cleaner and ch...

Page 1005: ...move inlet line at ac tuator and clean orifice 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 and leaking ex cessively Waste gate valve st...

Page 1006: ...deck pressure Com pressor discharge pres sure be normal if engine has idled for a prolonged Controller metering valve not opening Aneroid bellows leaking Replace controller assembly or replace aneroid bellows Waste gate sticking closed Controllerreturnline restricted Oilpressuretoohigh Wastegate controller malfunction 4J2 Shut off valve in return line not working Butterfly shaft binding Check bear...

Page 1007: ...is disconnected orpower to engine is increased Oil in induction housing Oil leaking past seal in controllers Replace faulty controller Engine idles too slow turbo doesn t turn allow ing oil to leak from compressor seal 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 Leakingoilsealin tur ...

Page 1008: ...st waste gate to open and close position to specifications in overhaul manual Controller malfunction Replace controller Wastegate 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 adjust waste gate to open or close position to spe...

Page 1009: ...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 SSP266 THIS SPACEINTENTIONALLYLEFT BLA...

Page 1010: ...on operated by engine oil and cylinder with the piston linked to an arm on the butterfly valve shaft The density controller is designed to allow the engine to develop full rated power no matter what ambient temperature and pressure conditions are This controller regulates waste gate bleed oil only at full throttle position to maintain a constant air density at the injector inlet The pressure and t...

Page 1011: ...ure measured downstream of the engine throttle valve and is almost directly proportioned to the engine power output If a turbocharger system is used only to regain power losses caused by decreased air pressure of high altitude it is considered that the engine has been normalized An overboost condition means that manifold pressure is exceeding the limits at which the engine was tested and FAA certi...

Page 1012: ... the preselected manifold pressure will start to drop and this is considered critical altitude REMOVALOF TURBOCHARGER 1 Remove the engine cowling 2 Remove the turbocharger compressor and turbine assembly by the following procedure A Disconnect the oil supply line from the center section of the turbo and the return line from the hose connection near the accessory housing CAUTION Do not spread the v...

Page 1013: ...l through oil drain 2 Turn rotating assembly by hand to coat bearings and thrust washer with oil 3 Coat threads of attaching bolts or studs with high temperature thread lubricant 4 After installing turbocharger flush oil through oil inlet line and ensure that line is clean and unobstructed 5 Fill engine and oil inlet line with new clean lubricating oil and connect line 6 Connect oil return line Re...

Page 1014: ... theturbo 4 Install the engine cowling ADJUSTMENT OFTURBOCHARGER It isrecommendedthatadjustmentsof the turbochargerbeconductedby an authorizedoverhaulfacility in accordancewiththelatestrevisionof Avco Lycoming ServiceInstructionNo 1187 DENSITYCONTROLLER REMOVALOF DENSITYCONTROLLER 1 Remove engine cowling 2 Disconnect oil lines at controller unit 3 Remove the screws securing the controller to the c...

Page 1015: ... controller unless the proper equipment is available Refer to the latest revisions of Garrett Airesearch Publication No TP21 0109 and Lycoming Service Letter No L184 INSTALLATIONOF DIFFERENTIAL PRESSURECONTROLLER 1 Ascertain that all oil inlet and outlet lines are clean 2 Position the controller on the compressor discharge housing and secure with mounting screws 3 Reconnect inlet and outlet oil li...

Page 1016: ...dclearance betweenthevalveandthesideof the housingwithbacklashtakenup towardstheopenposition NOTE All adjustments to the waste gate valve must start from the closed position first 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 tospec...

Page 1017: ...NUAL EXHAUSTMANIFOLD w AIR INLET ENGINEOIL AIR INDUCTION MANIFOLDPRESSURE COMPRESSOR DISCHARGE PRESSURE EXHAUST GAS DISCHARGE EXHAUST GAS Figure 81 1 Schematic Diagram of Turbocharger System 81 20 18 4J13 Page81 15 Issued September2 1981 ...

Page 1018: ...ST TRANSITION ASSY PIPERAIRCRAFT T 1020 MAINTENANCEMANUAL NH1000897 40 IN LBS 10 COUPLING V BAND BYPASS VALVE 11 TAIL PIPE WASTE GATE 12 COMPRESSORDISCHARGE HOUSING 13 HOSECLAMPS AND HOSE 14 FUEL INJECTOR 15 DIFFERENTIAL PRESS CONTROLLER 16 DENSITY CONTROLLER 17 EXHAUST BYPASSVALVE WASTE GATE ACTUATOR 18 HOSECLAMPS AND HOSE Figure81 2 Turbocharger Installation 4J14 81 20 18 Page 81 16 Issued Septe...

Page 1019: ...em in this position and proceed to install couplings around flange and engage latch Tighten coupling nut to 50 inchpounds initial torque Tap outer periphery of coupling with mallet to distribute band tension Check torque and continue tightening to a final torque of 70 80 inch pounds Tapping coupling until torque reading stabilizes 2 With the flanges together position the coupling over the flanges ...

Page 1020: ... Gate TURBOCHARGER DECOKING Mouse Milk penetrating oil or equivalent may be used for decoking the turbine and compressor drive shaft by the following procedure 1 Disconnect the oil inlet and outlet lines from the turbocharger and allow all oil to drain 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 overnigh...

Page 1021: ...PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL GRIDS 4J17 THRU 4L24 INTENTIONALLY LEFT BLANK 4J17 ...

Page 1022: ...MAINTENANCE MANUAL CARD 5OF5 PA 31 350 T1020 PIPER AIRCRAFT CORPORATION PART NUMBER 761768 5A1 ...

Page 1023: ...n broken down into Sub System Sections These sections are identified bythe secondelementof the standardizednumbering system Thenumber 40 ofthe basicnumber series 32 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 beassignedbythe...

Page 1024: ...pletepageadditionsarenotidentifiedby revisionlines A referenceandrecordof materialrevisedis includedineachchapter sTableof Contents Effectivity The codesusedin theeffectivitycolumnsof eachchapteraredefinedas follows SAMPLEEFFECTIVITY CODES INTERIM REVISION Revisionsappearinchapter 27 of card2 Pleasedisposeof yourcurrentcard2and replacewiththerevisedone DO NOT DISPOSEOFCARDS1 3 4 or 5 Introduction ...

Page 1025: ...INTENTIONALLY LEFT BLANK 5A4 ...

Page 1026: ...P N 117D Hartzell Propeller Inc P O Box 1458 1800 Covington Avenue Piqua Ohio 45356 MAGNETOS Installation Operation and Maintenance Instructions S 1200 SERIES MAGNETO IGNITION SYSTEM P N L 609 3 Bendix Electrical Components Division Sidney New York 13838 WHEELS AND BRAKES PARTS CATALOGS and Maintenance Instructions CLEVELAND WHEEL AND BRAKE Aircraft Wheel and Brake Division 1160 Center Road Avon O...

Page 1027: ...AVIATION DIVISION Rockwell International Cedar Rapids Iowa 52406 319 395 3625Telex 46 4421 KING RADIO CORPORATION 400 N Rodgers Rd Olathe Kansas 66061 813 782 0400Telex 4 2299 Kingrad GLOBAL NAVIGATION 2144 MichelsonDrive Irvine Ca 92715 714 851 0119 PIPER PUBLICATIONS PA 31 350 T 1020 Parts Catalog CONTINUOUS INSPECTION 761 775 Piper Aircraft Corporation 2926 Piper Drive Vero Beach FL 32960 761 7...

Page 1028: ...ND SHORING LEVELING AND WEIGHING TOWING AND TAXIING PARKING AND MOORING REQUIRED PLACARDS SERVICING STANDARD PRACT AIRFRAME ENVIRONMENTAL SYSTEM AUTOFLIGHT COMMUNICATIONS ELECTRICAL POWER EQUIPMENT FURNISHINGS FLIGHT CONTROLS FUEL HYDRAULIC POWER ICE AND RAIN PROTECTION LANDING GEAR LIGHTS AEROFICHE GRID NO IBI 1B4 1D23 1E13 1E16 1E21 IFI 1F4 1F8 IG12 III 2BI 2B4 2B12 2DI 2D10 2G19 2JI 3B12 3D9 3G...

Page 1029: ...EUMATIC SYSTEM VACUUM SYSTEM ELECTRIC ELECTRONIC PANELS AND MULTI PURPOSE PARTS STRUCTURES DOORS FUSELAGE STABILIZERS WINDOWS WINGS PROPELLERS STANDARD PRACTICES ENGINES POWER PLANT ENGINE FUEL AND CONTROL IGNITION ENGINE CONTROLS ENGINE INDICATING OIL SYSTEM AEROFICHE GRID NO 3HII 314 3116 3J4 3J6 3J22 4B1 4B21 4C1 4C17 4D4 4E1 4E22 4FI 4GI 4GII 4H10 4H14 411 Introduction Page Revised February 23...

Page 1030: ...L GAMA SYSTEM CHAPTER INDEX GUIDE cont SYST CHAP XO XO XI 91 95 SUB SYST SECTION TITI E STARTING FURBINES CHARTS AND WIRING DIAGRAMS SPECIAL PURPOSE EQUIPMENT AEROFICHE GRID NO 4111 4121 5B1 5F1 Introductiom Page Revised November 17 1981 5A9 ...

Page 1031: ...r Plant Propeller and Cowl Flap 1G3 12 7 Lubrication Chart Doors and Seats IG4 20 1 Torque Wrench Extension IG16 20 2 Method of Installing Rod End Bearings IG16 20 3 Cherrylock Rivet Removal IG17 20 4 Hose Line Markings IG19 20 5 Flareless Tube Fittings 1G20 20 6 Spray Patterns 1H8 20 7 Improper Spray Technique IH10 20 8 Spray Technique IH11 20 9 Spraying Corners IH11 21 1 Heating and Ventilating ...

Page 1032: ...Fabricated Oil Dipstick 1L3 21 31 MagneticClutch Installation 1L6 21 32 Expansion Valve Typical 1L8 21 33 Air Conditioning Outlets 1L11 21 34 Positioning of Airflow Probe 1L13 21 35 Sealingof Ducts IL14 21 36 Installation of VOI SHAN Seals 1L14 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 Avionic...

Page 1033: ...e Tension 2E18 27 10 Safety Wiring Control Surface Stops 2E18 27 11 Rudder and Rudder Trim Controls 2E22 27 12 Rudder and Trim Tab Control Travels and Cable Tension 2F2 27 13 Clamping Rudder Pedals in Neutral Position 2F2 27 14 Installation of Rudder Rigging Tool 2F2 27 15 Rudder Pedal Installation 2F7 27 16 Elevator and Elevator Trim Controls 2F10 27 17 Elevator and Elevator Trim Travels and Cabl...

Page 1034: ...29 8 Power Pack Handle Release Mechanism 2K8 29 9 Safetying Control Arms 2K9 29 10 Indexing of Selector Spool 2K10 29 11 Handle ReleaseAdjustment 2KII 29 12 Landing Gear Selector Mechanism Installation 2K13 29 13 Power Pack Test Harness Schematic 2K18 29 14 Hydraulic Filter 2K20 29 15 Hydraulic Pump 2K22 29 16 Hand Pump 2L4 29 17 Shuttle Valves WTC 2216 WTC 2217 2L7 30 1 Pneumatic Deicer System In...

Page 1035: ...ing Gear Installation 3E16 32 8 Clamping Rudder Pedalsin Neutral Position 3E22 32 9 Rudder PedalsNeutral Angle 3E22 32 10 Aligning NoseGear 3E22 32 11 EmergencyExtension SystemInstallation 3FI 32 1la Test Equipment Installation EmergencyGear Extension System 3F5 32 12 GearActuating Cylinder Wiebel Tool WTC 2115 1 3F6 32 13 Unlock Actuator Wiebel Tool WTC 2215 3F7 32 14 Gear Door Actuating Cylinder...

Page 1036: ...rt 3K7 51 4 DeepScratches ShallowNicksand SmallHoles 3K7 51 5 Mixing of EpoxyPatchingCompound 3K8 51 6 WeldingRepairMethod 3K8 51 7 Repairingof Cracks 3K9 51 8 VariousRepairs 3KII 51 9 Repairof StressLines 3K12 51 10 Repairof ImpactedDamage 3K12 51 11 Installationof RadomeErosionShield 3K18 52 1 CabinEntranceDoor LatchAssembly 4B6 52 2 Pilot sDoor Latch Assembly 4B10 52 3 CargoDoor LatchAssembly 4...

Page 1037: ...t Points 4G15 74 3 Rotor Holding Tool Installed 4G16 74 4 Timing Kit Installed 4G16 74 5 Aligning Timing Marks Single Contact Assembly Magneto 4G18 74 6 Forming Leadsin BreakerCompartment 4G18 74 7 Engine Timing Marks 4G19 74 8 MagnetoTiming Marks 4G19 74 9 Deleted 74 10 Checking HarnessLead Insulation Resistance 4G22 74 11 Modified Pliers 4G22 74 12 RemovingSpring From Lead Assembly 4G23 74 13 Lu...

Page 1038: ...ricated Tool Checking Nose Gear Link Travel 5F7 95 5 Flight Control Rigging Tools 5F8 95 6 Fabricated Tool Checking Nose Wheel Alignment 5F9 95 7 Fabricated Jack Stand for Piper Jack Part No 18338 00 5F10 95 8 Fabricated Tail Stand 5F11 95 9 Fabricated Bellcrank Rigging Tool 5F12 95 10 Fabricated Aileron and Elevator Rigging Tool 5F13 95 11 Fabricated Rudder Rigging Tool 5F14 95 12 Suggested Desig...

Page 1039: ...23 2402 Alternator Test Specifications 2C10 2403 Alternator Belt Tension 2C11 2404 Hydrometer Percentage Guide 2C13 2701 Troubleshooting Surface Controls 2D16 2702 Control Cable Rigging Tension Vs Temperature 2E3 2801 Troubleshooting Fuel System 2HI 2802 Fuel Cell Repair Equipment Lists 2H 17 2803 Wear Limits For Electric Fuel Pump 218 2804 Fuel Quantity Sender Resistance Limits 2112 2805 Fuel Qua...

Page 1040: ...oplastic Repairs 3K6 5501 Elevator Balance Weight 4C9 5502 Rudder Balance Weight 4C15 5701 Aileron Balance Weights 4D14 6101 Propeller Specifications 4E6 6102 Troubleshooting Chart Engine Synchrophaser 4E13 7101 Troubleshooting Engine 4F4 7301 Troubleshooting Fuel Pressure Gauge 4G7 7302 Troubleshooting Fuel Flow Gauge 4G8 7401 Coupling Torques 4H5 7701 Troubleshooting Manifold Pressure Indicator ...

Page 1041: ...nsumable Materials Flare Fitting Torque Values Recommended Nut Torques Thread Lubricants Decimal Conversion Torque Conversion Conversion Tables Decimal Millimeter Equivalents of Drill Sizes Circuit Load Chart Electrical Wire Coding Electrical Symbols 5B4 5B10 5B11 5B13 5B14 5B15 5B17 5B22 5B23 5C3 5C4 Introduction Page 18 Revised February23 1982 5A20 ...

Page 1042: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5A21 ...

Page 1043: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLYLEFT BLANK 5A22 ...

Page 1044: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5A23 ...

Page 1045: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5A24 ...

Page 1046: ...CHAPTER HARTS AND WIRING DIAGRAMS 5B1 ...

Page 1047: ...1 00 04 91 00 05 91 00 06 91 00 07 91 00 08 91 10 00 GENERAL Consumable Materials Torque Requirements Lubrication Of Threads Lubrication Of Gaskets And Seals Conversion Charts Decimal Millimeter Equivalents Of Drill Sizes Circuit Load Chart Electrical Wire Coding And Symbols ELECTRICAL SCHEMATIC INDEX 5B3 5B3 5B10 5B13 5B13 5B13 5B22 5B23 5C3 5C5 91 Cont Effec Page 1 Revised February 23 1982 5B2 ...

Page 1048: ...are applicable to various chapters and systems covered in this manual All electrical schematics are also included in this chapter CONSUMABLE MATERIALS Refer to back of Consumable Materials List for Vendor Information THIS SPACE INTENTIONALLY LEFT BLANK 91 00 01 Page 91 01 Issued September 2 1981 5B3 ...

Page 1049: ...s Co River Road Hanover New Jersey 07936 Sinclair Refining Co 600 Fifth Avenue New York New York 10020 Hydraulic Fluid MIL H 5606 QPL 5606 12 Aircraft Hydraulic Oil AA Texaco Inc 135 East 42nd New York New York 10017 RPM Aviation Oil No 2 Code PED 2585 PED 3337 3126 Hydraulic Oil Aeroshell Fluid 4 Aeroshell Fluid 4 SL 7694 Aero HF Royco 756 75A 756B Standard Oil of California 225 Bush St San Franc...

Page 1050: ...Aeroshell Grease 6 Royco II Shell Oil Co 50 West 50th Street New York New York 10020 Royal Lubricants Co River Road Hanover New Jersey 07936 MIL L 7870 QPL 7870 9 1692 Low Temp Oil Texaco Inc 135 East 42nd New York New York 10017 Aviation Instrument Oil Royco 363 Sinclair Aircraft Orbit Lube Standard Oil of California 225 Bush St San Francisco California 94120 Royal Lubricants Co River Road Hanove...

Page 1051: ...fornia 94120 Shell Oil Co 50 West 50th St New York New York 10020 Mobil Oil Corporation Shoreham Building Washington D C 20005 Royal Lubricants Co River Road Hanover New Jersey 07936 Castrol Oils Inc Newark New Jersey American Oil Company 165 N Canal Chicago Illinois 60606 BP Trading Limited Moore Lane Britannic House London E C 2 England Grease Aircraft General Purpose Wide Temperature Range MIL ...

Page 1052: ...lifornia 94120 Shell Oil Co 50 West 50th St New York New York 10020 Mobil Oil Corporation Shoreham Building Washington D C 20005 Royal Lubricants Co River Road Hanover New Jersey 07936 Sinclair Refining Co 600 Fifth Avenue New York New York 10020 California Texas Oil Corp 380 Madison Ave New York New York 10017 Lubricating Grease Molybdenum Disulfide MIL G 21164 QPL 21164 15 Aeroshell Grease 17 Sh...

Page 1053: ...ew York New York 10020 Lubricating Grease Plug Valve Gasoline and Oil Resistant MIL G 6032 QPL 6032 10 Royco 32 Royal Engineering Co Whippany New Jersey Castrolease PV Parker Fuel Lube 44 BP Aero Grease 32 Castrol Oils Inc Newark New Jersey Parker Seal Co BP Trading Limited Moore Lane Brittanic House London E C 2 England Anti Seize Compound Graphite Petroleum MIL T 5544 TT S 1732 TT A 580 Royco 44...

Page 1054: ...aterproof Grease High and Low Temperature Aero Lubriplate Fiske Brothers Refining Company 129 Lockwood Newark New Jersey 07105 Rain Repellent Repcon FSCM 50159 UNELKO Corporation 727 E 110th St Chicago Illinois 60628 Worldwide Aircraft Filter Corporation 1685 Abram St San Leandro CA 94577 Lubricant Decoke Agent for Turbo charger Mouse Milk Lubricant Ignition Harness Ferrule Shoulder GO JO NO LOK G...

Page 1055: ...sizesand material NOTE When flaredfittings are being installedascertainthat the male threads areproperly lubricated Torque thefittingsinaccordance with Chart 9102 CA UTION Do not overtorquefittings CHART 9102 FLARE FITTING TORQUE VALUES TORQUE INCH POUND TUBING OD INCHES ALUMINUM ALLOY TUBINGFLARE AND 10061 OR AND 10078 STEELTUBING FLARE AND 10061 HOSEENDFITTING AND HOSEASSEMBLIES MINIMUM MAXIMUMM...

Page 1056: ...specified torque to get the final torque PIPER AIRCRAFT T 1020 MAINTENANCEMANUAL CHART9103 RECOMMENDED NUT TORQUES COARSE THREAD SERIES BOLTS SteelTension AN 3 thru AN 20 AN 42 thru AN 49 AN 73 thru AN 81 AN 173 thru AN 186 MS 20033 thru MS 20046 MS 20073 MS 20074 AN 509 NK9 MS24694 AN 525 NK525 MS27039 NUTS Steel Tension SteelShear AN 310 AN 32 AN 315 AN 364 AN 363 NAS 1 AN 365 MS 17 320 1002 102...

Page 1057: ... bolt Torque Limits Torque Limits size in lbs in lbs Torque Limits Torque Limits in lbs in lbs Torque Limits Torque Limits in lbs in lbs 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 Min Max Min Max Min Max Min Max Min Mx Min Max NOTE BOLT AND NUT SIZES 10 THROUGH 7 16 INCLUDE FRICTIONDRAG TORQUE 12 15 7 9 5 10 3 6 38 43 30 33 43 48 33 38 28 33...

Page 1058: ...nt does not enter fittings or flared areas 7 Any fittingsgoingto the engine should be lubricatedwiththe type of fluidgoingthroughthe lines CHART 9104 THREAD LUBRICANTS TYPE OF LINE TYPE OF LUBRICANT Brakes Hydraulic Deicer Air Fuel Oil Oxygen Pitot and Static MIL H 5606 TT A 580 JAN A 669 Anti SeizeCompound White Lead Base MIL T 5544 Anti Seize Graphite Petrolatum MIL G 6032 Lubricating Grease Gas...

Page 1059: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL CHART 9105 DECIMAL CONVERSION 91 00 05 Page 91 12 Issued September2 1981 5B14 ...

Page 1060: ... 400 cmkg 450 cmkg 500 cmkg 260 4 in lbs 303 8 in lbs 347 2 in lbs 390 6 in lbs 434 0 in bs 550 cmkg 600 cmkg 650 cmkg 700 cmkg 4774 n lbs 520 8 in lbs 564 2 in lb 607 6 in lbs FOOT POUNDS TO METER KILOGRAMS mkg 346 mkg 691 mkg 1 037 mkg 1 383 mkg 1 728 mkg 2 074 mkg 2 419 mkg 2 765 mkg 3 111mkg 3 456 mkg 3 802 mkg 4 148mkg 4 493 mkg 4 839 mkg 5 185mkg 5 530 mkg 5 876 mkg 6 222 mkg 6 567 mkg 6913 ...

Page 1061: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5B16 ...

Page 1062: ... 3 Procedure for Converting Inchesto Millimeters Refer to Chart 9107 A Example Convert 1 5inches to millimeters 1 Read down inches column to 1 inches 2 Read across top inch column to 0 5 3 Read down and across to find millimeters 1 5 inchesis 38 10millimeters 4 Procedure for Converting Fahrenheit F and Celsius C Centigrade Temperature Referto Chart 9107 A Readnumber inmiddlecolumn ifindegreesCelsi...

Page 1063: ...U KW HR DRAM CU CM CU IN U S GAL LITERS CU IN CU FT U S GAL LIQ LITERS CU IN CU FT LITERS IMPERIAL GAL FLUID OZ CM FT KILOGRAMS LITERS METERS METER KILOGRAM OUNCES AVDP OUNCES FLUID LB AVDP SQUARE INCH POUND PER SQUARE INCH PSI STATUTE MILE NAUTICALMILE QUART MILLIMETER MICRON INCH POUNDS INCH OUNCES 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 43...

Page 1064: ...100 110 120 130 140 150 160 170 180 190 200 210 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 F 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 ...

Page 1065: ...0 0228 0 482 0 0736 0 0990 0 1244 0 1498 0 1752 0 2006 0 2260 0 2514 0 009 0 228 0 482 0 736 0 990 1 244 0 05 1 270 0 06 1 524 0 07 1 778 0 0 2 032 0 09 2 286 1 295 1 549 1 803 2 057 2 311 1 346 1 600 1 154 2 10 2 362 1 371 1 625 1 179 2 133 2 387 1 498 1 752 2 006 2 260 2 514 INCHES 0 00 0 01 0 02 0 0 0 254 0 508 0 1 2 340 2 794 3 048 0 2 3 080 5 334 3 358 0 3 7 620 7 874 1 128 0 4 10 160 10 414 ...

Page 1066: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5B21 ...

Page 1067: ...08 DECIMAL MILLIMETER EQUIVALENTSOF DRILL SIZES 7 16 27 64 DRILL SIZESAVAILABLE Drillmay be obtained inregular sizestoa 4 inchdiameter and increasein64thsof aninch The regular metric drills vary from 2 to 76mm and increase in 0 5mm variations 91 00 06 Page 91 18 5B22 Issued September2 1981 5B22 ...

Page 1068: ... STROBE WING TIP 10 STROBE STANDARD 2 WING TIP I TAIL 5 ALTERNATOR FIELD CIRCUIT 5 CABIN READING LIGHTS MAP LIGHTS DOME LIGHTS DOOR UNSAFE LIGHT NO SMOKING FASTEN SEAT BELT 15 FAN MOTOR 10 LEFT FLAP MOTOR RIGHT FLAP MOTOR 10 LEFT FUEL PUMP RIGHT FUEL PUMP 5 FUEL QUAN INDICATORS OIL TEMP INDICATORS CYL HD TEMP INDICATORS GEAR POSITION LIGHTS 5 SELECTOR LOCK SOLENOID MOTION LIGHT WARNING HORN LANDIN...

Page 1069: ...LIGHT 20 TIMER PROP HEATER ELEMENT 5 ARKORP PROP SYNC SYSTEM 5 LIGHT HORN FLASHER 10 STARTER SOLENOID FLAP MOTOR SOLENOID HOURMETER 5 TIMER LEFT RELIEF VALVE RIGHT RELIEF VALVE GYRO ENGAGE VALVE DISTRIBUTOR VALVE TIMER RELAY CONTROL RELAY INDICATOR LIGHT 5 TRIM INDICATOR SYSTEM PNEUMATIC SOURCE INDICATOR 5 TURN BANK INDICATOR 25 HEATED WINDSHIELD 10 WIPER MOTOR 25 MOTOR NO OF UNITS OPERATING SIMUL...

Page 1070: ... 43 KDM 700 TRACK MODE KING KDM 700A TRACK MODE KING KDM 705 KING ELECTRIC TRIM MARKER BEACON NAV COMM I 5 PITCH TRIM SERVO MITCHELL 5 MBT 24 NARCO KGM 690 KING PM I PIPER 10 KNI 500 OR KNI 500L KING KTR 900 OR KTR 900A KING KX 170A KING KX 175 KING COMM III NARCO COMM IIA NARCO MP 10 CONVERTER XMITT RCV XMITT RCV XMITT RCV XMITT RCV XMITT RCV XMITT RCV RCV 4 15 6 80 6 80 145 150 160 170 2 85 3 50...

Page 1071: ... SIMUL TANEOUSLY XMITT RCV XMITT RCV MAX CURRENT PER UNIT 28 5V 9 55 2 85 150 2 50 15 SA 14RA SUNAIR ASB 130 SUNAIR RADAR 10 AVQ 47 RCA RDR 110 BENDIX 6 00 9 17 RADAR ALTIMETER TRANSPONDER 5 TRN 71 BONZER 5 KXP 750 OR KXP 750A KING KT 76 KING 0 90 1 14 1 35 THIS SPACE INTENTIONALLY LEFT BLANK 91 00 07 Page 91 22 Issued September2 1981 5C2 ...

Page 1072: ...ESS CONNECTOR NUMBER S AND LOCATIONS CIRCUITS A C F G H L P Q RP RZ J AUTOPILOT CONTROL SURFACE FLIGHT INSTRUMENT LANDING GEAR E 100 Series Left Wing and Nacelle E 200 Series Right Wingand Nacelle E 300 Series Aft Fuselage E 400 Series Forward Fuselage HEATER VENTILATING DEICING LIGHTING POWER FUEL OIL ENGINE INSTRUMENT RADIO POWER RADIO AUDIO IGNITION 91 00 08 Page91 23 Issued September2 1981 5C3...

Page 1073: ...YPE TYPE ALTERNATOR CIGAR LIGHTER SO ET BEACON THERMAL SWITCH ELECTRICALCLUTCH PNUEMATIC SWITCH TERMINALBLOCK OR VACUUM N C POTENTIOMETER ZENER DIODE DIODE FUSE RESISTOR GROUND NOISE FILTER PUSH BUTTON SWITCH SWITCH CONDUCTORS SHIELDED CONNECTOR SOLENOID VALVE 91 00 08 Page 91 24 Revised February 23 1982 CONDUCTORS CROSSINGS AND JUNCTIONS OFCONDUCTORS THE DOT AT THE INTERSECTION INDICATESA JOINING...

Page 1074: ...Clearance Optional 5D2 91 4 Avionics Master and Emergency Switching Optional 5C13 ENGINE SYSTEMS 91 38 Magnetos Hour Meter 5D21 91 38 Starters 5D21 ENVIRONMENTAL SYSTEMS 91 1 Air Control Nacelle Scoop Blower Motor With or Without Air Conditioning 5C8 91 24 Heater and Combustion Blower With Hour Meter 5D4 91 5 Ground Vent Fan 5C13 FLAP SYSTEMS 91 16 Cowl Flap Motors Solenoid Also see Indicators 5C2...

Page 1075: ...5 Gear and Safety Solenoid 5D5 LIGHTING EXTERNAL 91 33 Anti Collision Strobe 5D16 91 21 Anti Collision Beacon 5D2 91 26 Landing Taxi 5D7 91 32 Position 5D15 91 22 Recognition 5D2 91 26 Wing Inspection 5D7 91 12 Logo Tail Flood 5C18 LIGHTING INTERNAL 91 11 Baggage 5C18 91 8 Door Ajar 5C16 91 9 Fasten Seat Belts No Smoking 5C17 91 10 Map 5C17 91 28 Panel 5D11 91 7 Reading Exit Steps 5C15 PROPELLER 9...

Page 1076: ...T REVISION INCORPORATED FOR PIPER INTER OFFICE USE ONLY DWG REV 42637 AD 44115 U 44741 BO 49501 C 49515 DWG REV 52616 A 59372 71047 71103 C 71110 D DWG REV DWG REV DWG REV 71131 E 71619 THIS SPACE INTENTIONALLY LEFT BLANK 91 Elec Sch Index Page 3 Issued September 2 1981 5C7 ...

Page 1077: ...CONN E 204 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL 236 71103 SCOOP L_ 20 SCOOP Figure 91 1 Air Control With or Without Air Conditioning 91 10 00 Page 91 25 5C8 Revised February 23 1982 5C8 ...

Page 1078: ...LTERNATOR 90 A RIGHT VOLTAGE REGULATOR TAPED a TIED BACK WHEN FLITE CLEARANCE SWITCH IS NOT INSTALLED LEFT IU PF4EE REGULATOR MASTER SWITCH ALTERNATORINOPERATIVE SWITCH RIGHT LEFT CONN E330 OVERVOLTAGE SEE NOTE 3 PANEL LIGHTS LEFT ALTERNATOR ROOT RIGHT ALTERNATOR CONN 430 ANNUNCIATOR CONTROLLER Figure 91 2 Alternators Master Contactor and Battery 5C9 5C10 91 10 00 Page 91 26 Issued September 2 198...

Page 1079: ...R AIRCRAFT T 1020 MAINTENANCE MANUAL EL232 44741 ANNUNCIATORCONTROLLER DOOR LOCK SWITCH Figure 91 3 Annunciator Controller and Annunciator Panel Lights 91 10 00 5Cll 5C12 Page 91 27 Issued September 2 1981 ...

Page 1080: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 9 Figure 91 5 Ground Vent Fan 91 10 00 Page 91 28 513 Revised February23 1982 5C913 ...

Page 1081: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL49 43947 SEE NOTE PROP DE ICE AMMETER HOLDER BRUSH LEFT ENGINE RIGHT ENGINE Figure 91 6 Propeller Deice 91 10 00 Page 91 29 Added February 23 1982 5C14 ...

Page 1082: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL I Figure 91 7 Reading and Exit Steps 91 10 00 Page 91 30 Revised October 15 1982 5C15 ...

Page 1083: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL240 44741 Figure 91 8 Door Ajar 91 10 00 Page 91 31 Revised February 23 1982 5C16 ...

Page 1084: ...R AIRCRAFT T 1020 MAINTENANCE MANUAL SEAT BELTS NO SMOKING NO SMOKING Figure 91 9 Fasten Seat Belts No Smoking EL239 44741 CONN E300 Figure 91 10 Map Lights 91 10 00 Page 91 32 Revised February 23 1982 5C17 ...

Page 1085: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL239 44741 BATTERY Figure 91 11 Baggage Lighting EL2 4 9 74201 E375 E302B Figure 91 12 Logo Light 5C18 91 10 00 Page 91 33 Added February 23 1982 ...

Page 1086: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5C19 ...

Page 1087: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5C20 ...

Page 1088: ...ANUAL EL233 71619 SEE CABIN LIGHTS a CHIMES CONN E 328 SEE CABIN LIGHTS SPEAKER Figure 91 14 Chimes E 3C3 CONN PEDESTAL CIGAR LIGHTER LEFT CIGAR LIGHTER RIGHT CIGAR LIGHTER Figure 91 15 Cigar Lighter Revised November 17 1983 5C21 91 10 00 Page91 34 ...

Page 1089: ...COWL FLAP PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL222 44741 CONN E204 CONN E103 CLOSE COWL FLAP Figure 91 16 Cowl Flap Motors 5C22 91 10 00 Page91 35 Revised November17 1983 ...

Page 1090: ... QUANTITY INDICATOR 5 AMP LEFT FUEL BOOST PUMP 5 AMP RIGHT FUEL BOOST PUMP 5 AMP LEFT LOW FUEL SENSOR LEFT FUEL BOOST PUMP SEE NOTE 20 RIGHT FUEL BOOST PUMP RIGHT LOW FUEL SENSOR NOTE SEE ANNUNCIATOR PANEL Figure 91 17 Fuel Boost Pumps and Fuel Flow Warning 5C23 5C24 91 10 00 Page 91 36 Revised November 17 1983 ...

Page 1091: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL204 Figure 91 18 Fuel Pump Left Figure 91 19 Fuel Pump Right 91 10 00 Page 91 37 Revised November 17 1983 5D1 ...

Page 1092: ...N PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL HOLDING COIL 28 V FROM COMM I C B FROM BATTERY FROM AUDIO C B FROM BATTERY SWITCH und Clearance Switch Optional EL229 49515 Figure 91 21 Anti Collision Beacon Figure 91 22 Recognition Lights 91 10 00 Page91 38 Revised November17 1983 5D2 ...

Page 1093: ...ER AIRCRAFT T 1020 MAINTENANCE MANUAL EL209 42637 HEATED WINDSHIELD SWITCH HEAT SENSOR 100F TO 95 F WILL OPEN SENSOR Figure 91 23 Heated Windshield THIS SPACE INTENTIONALLY LEFT BLANK 91 10 00 Page 91 39 5D3 Revised November 17 1983 ...

Page 1094: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL CONN E112 Figure 91 24 Heater and Blower 91 10 00 Page 91 40 Revised November 17 1983 5D4 ...

Page 1095: ...EFT WING ROOT EIOI SEE CONN NOTEI G22AE PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL237 44741 E 300 CONN SOLENOID GEAR DOWN INDICATOR LIGHTS E 314 CONN E 314 CONN Figurc 91 25 Landing Gear and Safety Solenoid 5D5 5D6 91 10 00 Page 91 41 Revised November 17 1983 ...

Page 1096: ...EL20 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL Figure 91 26 Landing Taxi and Wing Inspection Lights THIS SPACE INTENTIONALLY LEFT BLANK 91 10 00 Page91 42 Revised November 17 1983 5D7 ...

Page 1097: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 5D8 ...

Page 1098: ...AD TEMP INDICATORS LEFT TOAMMETER 0 12 INBOARD RIGHT 2 I I INBOARD I RIGHT AUXILIARY FUEL SENDERS L F SEE NOTE 3 Figure 91 27 Oil and Cylinder Head Temperature and Fuel Quantity Gauges 5D9 5D10 91 10 00 Page 91 43 Revised November 17 1983 ...

Page 1099: ...LIGHTS RIGHT MAP LIGHT E305 CONN COPILOT LIGHTS LEFT FUEL QUANTITY RIGHT FUEL QUANTITY GAUGE AIR CONDITIONING EL PANEL HHEO LIGHT WHT BLK AMMETER LIGHT SW S EL PANEL AMMETER LIGHT DIMMER CONTROL CONN RIOOA SEE NOTE CONN RIOIA SEE NOTE PILOTS INST LTS CONN CONN CONN COPILOTS INST LTS COMPASS LT GEAR PLACARD BLK WHT I FUEL CONTROL LIGHTS COWL FLAP LIGHTS L119EE 20 Figure 91 28 Panel Lights 5D11 5D12...

Page 1100: ...LEFT PITOT TUBE PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL201 44741 Figure 91 29 Pitot Heat Right and Left THIS SPACE INTENTIONALLY LEFT BLANK 91 10 00 Page 91 45 Revised November17 1983 SD13 ...

Page 1101: ...NCE MANUAL TIMER SURFACE DE ICE SW 20 WING DE ICE ENGAGE VALVES 2 STAGE R REGULATOR SOLENOID I WING PUSH TO TEST TAIL PUSH TO TEST 12 STAGE L REGULATOR SOLENOID 20 SDIS 20 TAIL PRESSURE SW 91 10 00 Page 91 46 Revised November17 1983 Figure 91 30 Surface Deicing System 5D14 ...

Page 1102: ...1 CONN 430 ANUNCIATOR PANELLIGHTS LEFT PNEUMATIC PRESSINDICATOR SWITCH Figure 91 31 Pneumatic Indicators CONN E312B POSITION LIGHT SWITCH CONN E302A NOTE 3 LEFT WING ROOT STROBE LT POSITION LT GREEN CONN E205 RIGHT WING ROOT Figure 91 32 Position Lights 91 10 00 Page 91 47 Revised November17 1983 5D15 ...

Page 1103: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS SPACE INTENTIONALLYLEFT BLANK EL207 ANTI COLLISION LIGHTS Figure 91 33 Strobe Lights 91 10 00 Page91 48 Revised November 17 1983 5D16 ...

Page 1104: ...M SENDER UNIT RIGHT WING ROOT COWL FLAP soon POSITION LEFT SENDER UNIT LEFT WING ROOT CONN E103 ELEVATOR TRIM SENDER UNIT RUDDERTRIM SENDER UNIT AILERON RUDDER INDICA TOR INDICATOR Figure 91 34 Trim and Cowl Flap Indicators Voltmeter 91 10 00 Page 91 49 Revised November17 1983 5D17 ...

Page 1105: ...EL 24 49694 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL THIS SPACE INTENTIONALLY LEFT BLANK 91 10 00 Page 91 50 Revised November 17 1983 5D18 ...

Page 1106: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL220 STALL WARNINGHORN LIFT SITCH Figure 91 36 Stall Warning 91 10 00 Page 91 51 Revised November 17 1983 5D19 ...

Page 1107: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL STALL Figure 91 37 Stall Warning With Time Delay 91 10 00 Page 91 52 Revised November 17 1983 5D20 ...

Page 1108: ...E 300 CONN PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL 302 44741 NOT USED ON S N PA 31 7952001 AND UP Figure 91 38 Starter and Hourmeter 5D21 5D22 91 10 00 Page 91 53 Revised November 17 1983 ...

Page 1109: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL Figure 91 39 Turn and Bank THIS SPACE INTENTIONALLY LEFT BLANK 91 10 00 Page 91 54 Revised November 17 1983 5D23 ...

Page 1110: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL PANEL Figure 91 40 Wing Flap Motor Calco 5D24 91 10 00 Page 91 55 Revised November 17 1983 ...

Page 1111: ...EL19 44115 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL EL210 Figure 91 41 Windshield Wiper END THIS SPACE INTENTIONALLY LEFT BLANK 91 10 00 Page 91 56 Revised November 17 1983 5E1 ...

Page 1112: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 5E2 THRU 5E24 INTENTIONALLY LEFT BLANK 5E2 ...

Page 1113: ...CHAPTER SPECIALPURPOSE EQUIPMENT 5F1 ...

Page 1114: ...CIAL PURPOSE EQUIPMENT TABLE OF CONTENTS EFFECTIVITY CHAPTER SECTION SUBJECT GRID NO SUBJECT EFFECTIVITY 95 00 00 95 10 00 95 10 01 GENERAL 5F3 TOOLS AND TEST EQUIPMENT Construction Of Tire Balancer 5F3 5F4 95 Cont Effec Page 1 Revised February 23 1982 5F2 ...

Page 1115: ...rmal shop toolswillberequiredto servicethe aircraft Anillustratedlist of tools required follows NOTE Tools with Part Numbersgivenare availablethroughthe Piper ServiceDepartment Specifications for fabricatedtools may be found byreferringto theappropriate illustrationFigurenumberin themaintenance manualfollowingthelist of tools THIS SPACE INTENTIONALLY LEFT BLANK 95 10 00 Page 95 01 Issued September...

Page 1116: ...hreads in the AN365 624 nuts with an R drill then tapping with a 1 8 27 pipe tap 3 The 6 spacers were made from1 2 inch aluminum tubing The two lengths of spacers are suitable for balancing most any aircraft wheel 4 The 7 bushing may be bench made from one inch phenolic or aluminum using a I 1 2 inch hole saw to cut out the smaller bushing and 1 3 4 inch hole saw to cut out the larger By inserting...

Page 1117: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL TOP SIDE Figure 95 2 Fabricated Tool Checking Main Gear Toe in Adjustment 95 10 01 Page 95 03 SF5 Issued September 2 1981 ...

Page 1118: ...06 II 862 8 375 2 25 12 863 NOTE ITISIMPORTANT THAT CENTER LINE ACCURACY BE USED WHENLOCATI HOLE FOR INSTALLATION OF BRU SIGHT SLOT AND ELONGATED HO Figure 95 3 Fabricated Tool Checking Main Gear Side Brace ILinkTravel 95 10 01 Page95 04 Issued September2 1981 5F6 ...

Page 1119: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1096 MATERIAL Figure 95 4 Fabricated Tool Checking Nose Gear Link Travel 95 10 01 Page95 05 5F7 Issued September2 1981 5F7 ...

Page 1120: ... TOOL P N 71695 2 AILERON RIGGING TOOL P N 72025 OR 72159 3 RUDDER P N 71694 FLAP RIGGINGTOOL PN 71505 2 P N 71505 3 RUDDERAND RUDDERTRIM RIGGING TOOL Figure 95 5 Flight Control Rigging Tools 95 10 01 Page 95 06 Revised February 23 1982 5F8 ...

Page 1121: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1094 SECTION A A NOTE Figure 95 6 Fabricated Tool Checking Nose Wheel Alignment 95 10 01 Page95 07 5F9 Issued September 2 1981 ...

Page 1122: ...00 X 9 0 STL CHANNEL 2 REQ PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 110 ALL WELDED CONSTRUCTION Figure 95 7 Fabricated Jack Stand for Piper Jack Part No 18338 00 95 10 01 Page95 08 5F10 Issued September 2 1981 5FI0 ...

Page 1123: ... 375 HOLE 7 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 1019 5 R TYP 75 BRAZE COWLING CLIP Figure95 8 Fabricated Tail Stand 95 10 01 Page 95 09 Issued September2 1981 5F11 ...

Page 1124: ... 125 PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL 198 MATERIAL 25 TO 50 ALUMINUM OR STEEL 6 50 50 3 39 Figure 95 9 Fabricated BellcrankRiggingTool 95 10 01 Page 95 10 Issued September 2 1981 5F12 ...

Page 1125: ...IDE NEXTTOELEVATOR DRILLANDTAP INCH BOLT FILETOLENGTH 25 50 to 1 0 14 625 DRILLANDTAP INCH BOLT FILETOLENGTH MATERIAL ALUMINUM PLATE SPAR MATERIAL MAY BE USED Figure95 10 Fabricated Aileron and Elevator RiggingTool 95 10 01 Page 95 11 Issued September 2 1981 5F13 ...

Page 1126: ...I 2 MATERIAL ALUMINUM PLATE Figure 95 11 Fabricated Rudder RiggingTool 5F14 95 10 01 Page 95 12 Issued September 2 1981 ...

Page 1127: ... CI7 NOTE DIMENSION A VARIES WITH LENGTH OF SPARK PLUG 1 IN HEX S A E 1112 SCREW STOCK 0 640 DIA DRILL CANFER45 x 1 16 NEAR END ONLY THREAD 18 M M 1 5 M M PITCHS A E SPARK PLUG STANDARD 0 06 3 00 INCH 0 125 DIA STEELROD 0 3125 DIA ROD 0 50 LONG 1010 1020 STEEL ROD DRILL AND TAP FOR4 40 SCREW LOCATED 1 4 IN EITHEREND SCREW MACHINE RD HD AN OR MS 4 40 1 4 IN LONG NOTE ALL DIMENSIONS ARE IN INCHES DE...

Page 1128: ...ENANCE MANUAL 6 00 1 50 38 UNDER CUT 010 MARK WITH 3387 BLACK PAINT I MATERIAL CAN BE SAE TYPE 303 321 OR 347 ST ST ORALUMINUM CASE HARDENED Figure 95 14 Spark Plug Gap Adjustment and Tool Janitrol Heater 95 10 01 Page 95 14 5F16 ...

Page 1129: ...95 16 Charging Stand Kent Moor J8393 02 4 68 1 50 THIS END FOR HORIZONTAL MOUNT 1 75 108 NOTE 12 NOTCHES 1 8 INCH APART STARTING AT EACH END 1 50 THIS END FOR VERTICAL MOUNT Figure 95 17 Fabricated Oil Dipstick 95 10 01 Page 95 15 5F17 Revised February 23 1982 5F17 ...

Page 1130: ...Harness Ferrule Seating Tool 11 7074 Figure 95 19 Modified Pliers For Ignition Harness Grommet And Eyelet Installation BRAZE 2 IN 12 000 IN DRILL NO 47 IN DEEP TAP 3 48 BLENDO D TO D POLISH O D MAT NO 30 DRILL RODOR EQUIVALENT Figure 95 20 Assembly Tool For Ignition Harness Insulating Sleeve Installation 95 10 01 Page95 16 Issued September 2 1981 5F18 ...

Page 1131: ...PIPER AIRCRAFT T 1020 MAINTENANCE MANUAL GRIDS 5F19 THRU 5L24 INTENTIONALLY LEFT BLANK 5F19 ...

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