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Piper Aircraft Corporation PA-28-161 CADET Maintenance Manual Download Page 258

Trouble

Cause

Remedy

Rough running engine.

Cracked engine mounts.

Repair or replace engine mount.

Unbalanced propeller.

Remove propeller and have it
checked for balance.

Bent propeller blades.

Check propeller for blade track.

Defective mounting.

Install new mounting bushings.

Lead deposit on spark plug.

Clean or replace plugs.

Malfunctioning engine.

Check entire engine.

Low oil pressure.

Insufficient oil.

Check oil supply.

Dirty oil screens.

Remove and clean oil screens.

Defective pressure gauge.

Replace gauge.

Air lock or dirt in relief

Remove and clean oil pressure

valve.

relief valve.

Leak in suction line or

Check gasket between

pressure line.

accessory housing crankcase.

High oil temperature.

See "High Oil Temperature"
in Trouble Column.

Stoppage in oil pump

Check line for obstruction.

intake passage.

Clean suction screen.

Worn or scored bearings.

Overhaul.

High oil temperature.

Insufficient air cooling.

Check air inlet and outlet for
deformation or obstruction.

Insufficient oil supply.

Fill oil sump to proper level.

Clogged oil lines or screens.

Remove and clean oil screens.

PIPER AIRCRAFT

PA-28-161 CADET

AIRPLANE MAINTENANCE MANUAL

Issued:  FEBRUARY. 28, 1989

POWER PLANT

1K18

TABLE Vlll-ll. ENGINE TROUBLESHOOTING CHART (cont)

Summary of Contents for PA-28-161 CADET

Page 1: ...CADET MAINTENANCE MANUAL CARD 1 OF 2 PA 28 161 CADET PIPER AIRCRAFT CORPORATION PART NUMBER 761 829 1A1 Courtesy of Bomar Flying Service www bomar biz...

Page 2: ...ru 2841289 Serial numbers 2841294 thru 2841300 Serial numbers 2841304 thru 2841314 PA 28 161 Cadet 1990 Serial numbers 2841290 thru 2841293 Serial numbers 2841301 thru 2841303 Serial numbers 2841315 t...

Page 3: ...of Illustrations is given and follows the Table of Contents 3 A complete list of Tables is given for all fiche in this set and follows the List of Illustrations 4 A complete list of paragraph titles a...

Page 4: ...CONTROLS 1F21 VI HYDRAULIC SYSTEM Not Applicable VII LANDING GEAR AND BRAKE SYSTEM 1H18 VIII POWER PLANT 1J3 AEROFICHE CARD NO 2 IX FUEL SYSTEM 2A9 X INSTRUMENTS 2B6 XI ELECTRICAL SYSTEM 2C16 XII ELE...

Page 5: ...mula 1C19 3 1 Inspection Areas of Exhaust System 1D17 3 2 Typical Muffler Fatigue Areas 1D17 4 1 Aileron and Flap Installation 1E12 4 2 Wing Installation 1E13 4 3 Methods of Securing Control Cables 1E...

Page 6: ...ated Stabilator Rigging Tool 1H12 5 20 Fabricated Flap Rigging Tool 1H13 7 1 Nose Gear Oleo Strut Assembly 1H21 7 2 Nose Gear Installation 1IH24 7 3 Clamping Rudder Pedals in Neutral Position 1I2 7 4...

Page 7: ...K7 8 22 Installation in Housing 1K8 8 23 Securing Wire in Housing 1K8 8 24 Installation of Electrical Screw 1K9 8 25 Installation of Insulation Sleeve 1K9 8 26 Installation of Spring 1K9 8 27 Removing...

Page 8: ...d View of Gear Reduction Starter Motor 2D15 11 20 Turning Motor Commutator 2D17 11 21 Testing Motor Armature for Shorts 2D17 11 22 Testing Motor Fields for Grounds 2D18 11 23 No Load Test Hookup 2D18...

Page 9: ...ument Panel and Switch Lights 2F14 11 48 Pitch Trim 2F15 11 49 Stall Warning 2F16 11 50 Optional Avionics 2F17 12 1 ELT Portable Folding Antenna 2F24 12 2 ELT Using Fixed Aircraft Antenna 2F24 12 3 EL...

Page 10: ...t Surface Controls 1H7 VII I Landing Gear Troubleshooting 1I22 VIII I Propeller Torque Limits 1J8 VIII II Engine Troubleshooting 1K15 IX I Transmitter Fuel Gauge Tolerances 2A16 IX II Fuel Quantity Tr...

Page 11: ...Specifications 2D20 XI VI Troubleshooting Chart Electrical System 2E6 XI VII Lamp Replacement Guide 2E15 XI VIII Electrical System Component Loads 2E16 XI IX Electrical Wire Coding 2E17 XI X Electrica...

Page 12: ...ding Gear 1A13 1 8 Brake System 1A13 1 9 Engines 1A13 1 10 Propeller 1A13 1 11 Fuel System 1A14 1 12 Flight Controls 1A14 1 13 Radio 1A14 1 14 Cabin heater Defroster and Fresh Air System 1A14 1 15 Ins...

Page 13: ...tions of the major components and systems 1 4 WING The laminar flow wing is of all metal stressed skin full cantilever tapered low wing design Each tapered wing panel is bolted to a spar box assembly...

Page 14: ...system muffler shroud Fresh air is picked up from air inlets in the leading edge of each wing The air passes through the wings to individually controlled outlets located just forward of each front se...

Page 15: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 INTRODUCTION 1A15...

Page 16: ...iing 1B11 2 20 External Power Receptacle Optional 1B12 2 21 Operation of External Power Receptacle 1B12 2 22 Cleaning 1B12 2 23 Cleaning Engine Compartment 1B12 2 24 Cleaning Landing Gear 1B12 2 25 Cl...

Page 17: ...57 Draining Fuel System 1B21 2 58 Electrical System 1B22 2 59 Servicing Electrical System 1B22 2 60 Lubrication 1B22 2 61 Oil System Engine 1B22 2 62 Servicing Oil System 1B22 2 63 Filling Oil Sump 1B...

Page 18: ...ane Enamel 1C16 2 84 Product Listing For Randolph Paint Finish 1C16 2 85 Preparation and Application of Zinc Chromate Primer 1C16 2 86 Finish Painting With Randolph Paint B5420 D7784 1C16 2 87 Repairs...

Page 19: ...nd rudder is 20 5 inches below the cabin floor as measured at the rear wing spar with the airplane level The reference datum line is located 78 4 inches ahead of the wing leading edge at the intersect...

Page 20: ...12 11 75 2 6 5 3 4 35 10 23 9 6 7 3 6 STATIC GROUND LINE 6 8 Figure 2 1 Three View PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 HANDLING AND SERVICING 1A20...

Page 21: ...BL 22 25 WS 208 05 STA 258 72 THERORETICAL TIP STA 278 40 WS 211 57 BL 00 00 STA 280 90 WL 100 10 STA 7 00 WS 57 00 WS 88 75 STA 108 63 WL 96 50 WL 53 35 WL 0 386 STA 108 17 WL 40 00 STA 108 64 STA 1...

Page 22: ...agnetos Slick Left 4051 4251 Right 4050 4250 Magneto Timing 25 BTC Spark Plugs Shielded and Spark Plug Gap Setting SEE NOTE Note Refer to the latest issue of Avco Lycoming Service Instruction No 1042...

Page 23: ...d Shock Strut Type Combination Air Oil Fluid Required Struts and Brakes MIL H 5606 Strut Exposure under static load Nose 3 25 25 in Main 4 50 50 in Wheel Tread 10 0 ft Wheel Base 6 ft 8 in Nose Wheel...

Page 24: ...DIMENSIONS cont MODEL PA 28 161 CADET CONTROL SURFACE TRAVELS REFER TO SECTION V TABLE V I CABLE TENSIONS REFER TO SECTION V TABLE V I PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued...

Page 25: ...nimum octane aviation grade fuel for the PA 28 l61 Cadet is 100 octane Low Lead When using alternate fuels refer to the latest revision of Lycoming Service Letter No L185 END PIPER AIRCRAFT PA 28 161...

Page 26: ...BLY ENGINE 15 SPINNER PROPELLER 16 SEAT TORQUE TUBE AND CONTROL CABLES 17 PLATE CONTROL CABLES MIDDLE 18 PLATE AILERON AND STABILATOR CONTROL CABLE FORWARD 19 COVERS AILERON AND STABILATOR CONTROL CAB...

Page 27: ...listed and not its mating fastener use the lower torque d When using self locking fasteners and hardware with thread sizes 10 through 7 16 add the specified friction drag torque to the designated torq...

Page 28: ...bolt or nut is specified to be lubricated prior to tightening the torque range should be reduced 50 percent 3 Use a bolt length long enough to prevent bearing loads on the threads The complete chamfe...

Page 29: ...THREAD SERIES NUT BOLT TORQUE LIMITS TORQUE LIMITS SIZE IN LBS IN LBS MIN MAX MIN MAX 8 32 12 15 7 9 10 24 20 25 12 15 1 4 20 40 50 25 30 5 16 18 80 90 48 55 3 8 16 160 185 95 110 7 16 14 235 255 140...

Page 30: ...que Limits Tonque Limits Torque Limits size in lbs in lbs in lbs in lbs in lbs in lbs Min Max Min Max Min Max Min Max Min Max Min Max 8 36 12 15 7 9 5 10 3 6 10 32 20 25 12 15 25 30 15 20 10 15 5 10 1...

Page 31: ...0 70 100 1 4 40 65 135 150 70 120 5 16 60 80 180 200 85 180 3 8 75 125 270 300 100 250 1 2 150 250 450 500 210 420 5 8 200 350 650 700 300 48O 3 4 300 500 900 1000 500 850 1 500 700 1200 1400 700 1150...

Page 32: ...ner described in the following paragraphs the chance of possible damage to the airplane and its equipment will be prevented 2 12 JACKING Jacking the airplane is necessary to service the landing gear a...

Page 33: ...ng The airplane may be leveled while on jacks during the weighing procedure while the wheels are on scales or while the wheels are on the ground To level the airplane for purposes of weighing or riggi...

Page 34: ...airplane a Head the airplane into the wind if possible b Block the wheels c Lock the aileron and stabilator controls using the front seat belt or control surface blocks d Secure tie down ropes to the...

Page 35: ...t of the nose gear fork CAUTION When towing with power equipment do not turn the nose gear in either direction beyond its steering radius limits as this will result in damage to the nose gear and stee...

Page 36: ...output 2 22 CLEANING 2 23 CLEANING ENGINE COMPARTMENT Before cleaning the engine compartment place strips of tape on the magneto vents to prevent any solvent from entering these units a Place a pan u...

Page 37: ...n Do not rub surfaces harshly c Remove oil and grease with a cloth moistened with kerosene NOTE Do not use gasoline alcohol benzene carbon tetrachloride thinner acetone or window cleaning sprays d Aft...

Page 38: ...ESSURE ENGINE 17 FILLER OLEO SHOCK STRUT L AND R 6 FILLER INDICATOR OIL ENGINE 18 DRAIN FUEL TANK RIGHT 7 FILTER FUEL PUMP ELECTRIC 19 TIRE MAIN WHEEL L AND R 8 SCREEN FUEL DRAIN 20 FILLER FUEL TANK R...

Page 39: ...h the airplane setting on a level surface under normal static load empty weight of airplane plus full fuel and oil If the strut has less tube exposed than that prescribed determine whether it needs ai...

Page 40: ...se from the valve stem 5 With the strut compressed remove the filler plug to determine that the fluid level is visible up to the bottom of the filler plug hole 6 Reinstall the core in the filler plug...

Page 41: ...ully and remove the hose from the valve stem 5 With the strut fully compressed remove the filler plug to determine that the fluid level is visible up to the bottom of the filler plug hole 6 Reinstall...

Page 42: ...RESERVOIR The brake cylinder reservoir should be filled to the level marked on reservoir with the fluid specified in Table II I The reservoir located on the left side of the fire wall in the engine c...

Page 43: ...PLATE 4 RETAINER 5 FILTER ELEMENT 6 RETAINER 7 HOUSING 8 AIR FILTER BOX SEAL 9 CARBURETOR AIR FILTER BOX ASSEMBLY 10 SPRING 11 WASHER 12 FASTENER 3076 1 2 3 4 5 6 7 8 9 10 11 12 PIPER AIRCRAFT PA 28...

Page 44: ...tall filter 2 49 INSTALLATION OF AIR FILTER After replacement and or inspection Install filter element in screen housing Ensure the two retainers are properly positioned around the filter element acco...

Page 45: ...fter and stop before the fuel flow Do not permit the concentrated additive to come in contact with the aircraft painted surfaces or the interior surfaces of the fuel tanks CAUTION Some fuels have anti...

Page 46: ...e the oil screen s should be removed and cleaned and when installed the oil filter cartridge replaced Intervals between oil changes can be increased as much as 100 on engines equipped with full flow c...

Page 47: ...accessory case of the engine between the magnetos should be cleaned at each oil change to remove any accumulation of sludge and to examine for metal filings or chips If metal particles are found in th...

Page 48: ...sible results from the application of lubricants the following precautions should be observed a Use recommended lubricants Where general purpose lubricating oil is specified but unavailable clean engi...

Page 49: ...MIL H 5606 GREASE AIRCRAFT AND INSTRUMENT GEAR MIL G 23827 AND ACTUATOR SCREW GREASE AIRCRAFT HIGH TEMPERATURE TEXACO MARFAX ALL PURPOSE GREASE MOBIL GREASE 77 OR MOBILUX EP2 SHELL ALVANIA EP GREASE 2...

Page 50: ...BRICATING 7 INTERVALS BETWEEN OIL CHANGES CAN BE INCREASED AS MUCH AS 100 ON ENGINES EQUIPPED WITH FULL FLOW CARTRIDGE TYPE OIL FILTERS PROVIDED THE ELEMENT IS REPLACED EACH 50 HOURS OF OPERATION AND...

Page 51: ...ALL PURPOSE GREASE OR MOBIL GREASE 77 OR MOBIL EP2 GREASE 100 HRS 6 EXPOSED OLEO STRUT MIL L 60326 100 HRS 7 BRAKE RESERVOIR MIL H 5606 100 HRS SPECIAL INSTRUCTIONS 1 Main Wheel Bearings Disassembly...

Page 52: ...TEERING ROD MIL L 7870 100 HRS END BEARINGS 7 EXPOSED OLEO STRUT MIL L 60326 100 HRS SPECIAL INSTRUCTIONS 1 Main Wheel Bearings Disassemble and clean with a dry type solvent Ascertain that grease is p...

Page 53: ...RING 2 LUBRICANT AS REQUIRED 8 TEE BAR PIVOT POINT MIL L 7870 100 HRS 9 CONTROL COLUMN CHAIN MIL L 7870 500 HRS 10 CONTROL COLUMN FLEX JOINTS AND MIL L 7870 100 HRS SPROCKET 11 STABILATOR CONTROL MIL...

Page 54: ...SM TURNBUCKLE END AND CABLE PULLEY MIL L 7870 100 HRS 4 FLAP RETURN AND TENSION CHAINS MIL L 7870 500 HRS 5 AILERON BELLCRANK PIVOT POINT MIL L 7870 100 HRS 6 AILERON CONTROL ROD END BEARINGS MIL L 78...

Page 55: ...MIL L 60326 100 HRS 2 TOE BRAKE CYLINDER ATTACHMENTS MIL L 7870 100 HRS 3 RUDDER TUBE CONNECTIONS MIL L 7870 100 HRS 4 BRAKE ROD ENDS MIL L 7870 100 HRS 5 NOSE GEAR STEERING ROD ENDS MIL L 7870 100 H...

Page 56: ...OR AERO LUBRIPLATE FISKE BROS REFINING CO OR AERO SHELL 7 100 HRS 3 STABILATOR SCREW TAB LINKS MIL L 7870 100 HRS 4 STABILATOR HINGE POINTS MIL L 7870 100 HRS 5 RUDDER TRIM ASSEMBLY MIL L 7870 100 HR...

Page 57: ...70 100 HRS 2 DOOR SEALS MIL L 60326 50 HRS 3 DOOR LATCH MECHANISMS MIL L 7870 500 HRS 4 SEAT TRACK ROLLERS STOP PINS MAG 1 OR AERO LUBRIPLATE FISKE BROS REFINING CO OR AERO SHELL 7 100 HRS 1 2 3 4 PIP...

Page 58: ...Air Filter To clean filter tap gently to remove dirt particles Do not blow out with compressed air or use oil Replace filter if punctured or damaged 2 Intervals between oil changes can be increased a...

Page 59: ...and corrosive environment It usually occurs in assemblies such as aluminum alloy bellcranks with pressed in bushings landing gear shock struts with pipe thread grease fittings clevis pin joints and s...

Page 60: ...control methods All corrosion products must be removed prior to refinishing If they are not removed corrosion will begin again even though the affected area is refinished Before beginning any rework...

Page 61: ...susceptible White powdery snow like to corrosion mounds and white spots Cadmium plating White to brown to black mottling Mechanical removal of of surface plating is still pro corrosion should be limit...

Page 62: ...ing edge of wings because they are constantly exposed to abrasion by dirt dust gravel and rain should be checked frequently for the beginning of corrosion h Hinges piano hinges especially are extremel...

Page 63: ...ry with clean rags or other suitable materials free of lint and silicones f Repair with desired color according to instructions 2 81 PRODUCT LISTING FOR URETHANE ENAMEL AIRCRAFT FINISH OPTIONAL FINISH...

Page 64: ...be used only on aluminum previously primed with MIL P 8585 zinc chromate or MIL C 8514 wash primer The use of this primer over MIL P 8585 is an exception and will result in a small reduction in gloss...

Page 65: ...VETS To remove cherrylock rivet a File head flat b Centerpunch rivet head c In thick material remove the lock by driving out the rivet stem using a tapered steel drift pin See view 1 NOTE Do not drill...

Page 66: ...N BREATHING OXYGEN BREATHING OXYGEN BREATHING FUEL FUEL FUEL PNEUMATIC PNEUMATIC PNEUMATIC LUBRICATION LUBRICATION LUBRICATION CONDITION AIR CONDITION AIR CONDITION AIR GAS COMPRESSED GAS COMPRESSED G...

Page 67: ...re 2 14 T Torque desired at the part A Basic lever length from center of wrench shank to center of handle or an area stamped on wrench or listed for that model wrench B Length of adapter extension cen...

Page 68: ...ing Co 600 Fifth Avenue New York New York 10020 Hydraulic Fluid MIL H 5606 Aircraft Hydraulic Texaco Inc 135 East QPL 5606 12 Oil AA 42nd New York New York 10017 RPM Aviation Oil Standard Oil of No 2...

Page 69: ...s Co River Road Hanover New Jersey 07936 Lubricating Oil MIL L 7870 1692 Low Temp Oil Texaco Inc 135 East General Purpose QPL 7870 9 42nd New York Low Temperature New York 10017 Aviation Instrument St...

Page 70: ...oyco 27A Royal Lubricants Co River Road Hanover New Jersey 07936 Castrolease A1 Castrol Oils Inc Newark New Jersey Supermil Grease No American Oil Company A72832 165 N Canal Chicago Illinois 60606 BP...

Page 71: ...Shoreham Building Washington DC 20005 Royco 78 Royal Lubricants Co River Road Hanover New Jersey 07936 L 1212 Sinclair Refining Co 600 Fifth Avenue New York New York 10020 1916 Uni Temp California Tex...

Page 72: ...32 Royco 32 Royal Engineering Plug Valve Gasoline QPL 6032 10 Co Whippany and Oil Resistant New Jersey Gastrolease PV Castrol Oils Inc Newark New Jersey Parker Fuel Lube 44 Parker Seal Co BP Aero Grea...

Page 73: ...otive Type DuPont Company Compounds DuPont 7 Wilmington DL 19898 Ram Chemical 69 Ram Chemicals x 6 Gardena CA 90248 Mirror Glaze 1 Mirror Bright Polish Co Inc Irvin CA 92713 Cleaners Fantastic Spray L...

Page 74: ...2 in x 9 mil Troy NY 12181 Vinyl Foam 1 in x 1 8 in 530 Series Type I Norton Tape Division Troy NY 12181 Teflon Tape 003 x 50 wide 1 Minnesota Mining and Mfg 3M Center St Paul MN 55101 Shamban W S and...

Page 75: ...Convert 1 5 inches 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 inches is 38 10 millimeters 4 Procedure for...

Page 76: ...57 CU CM 12 000 MILS 1 805 CU IN 304 8 MM 0 3333 YARDS LB AVDP 453 6 GRAMS 7000 GRAINS FT LB 0 1383 M KG 16 0 OUNCES 0 001285 BTU 0 000000376 KW HR SQUARE INCH 6 4516 SQ CM FLUID OZ 8 DRAM POUND PER...

Page 77: ...8 89 300 572 0 6 67 20 68 0 154 44 310 590 0 1 11 30 86 0 160 00 320 608 0 4 44 40 104 0 165 56 330 626 0 10 00 50 122 0 171 11 340 644 0 15 56 60 140 0 176 67 350 662 0 21 11 70 158 0 182 22 360 680...

Page 78: ...2 2 108 2 133 2 159 2 184 2 209 2 235 2 260 0 09 2 286 2 311 2 336 2 362 2 387 2 413 2 438 2 463 2 489 2 514 INCHES 0 00 0 01 0 02 0 03 0 04 0 05 0 06 0 07 0 08 0 09 MILLIMETER 0 0 0 254 0 508 0 762 0...

Page 79: ...Seize Compound White Lead Base NOTE Lubricate Engine Fittings Only With The Fluid Contained In The Particular Lines Types of clamps Types of hose Worm screw type All other types Self sealing finger ti...

Page 80: ...ORTS IN IN ALUMINUM ALLOY STEEL 1 8 9 1 3 11 1 2 3 16 12 14 1 4 13 1 2 16 5 16 15 18 3 8 16 1 2 20 1 2 19 23 5 8 22 25 1 2 3 4 24 27 1 2 1 26 1 2 30 THIS SPACE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT...

Page 81: ...2 794 64 0 036 0 9144 T 0 358 9 1281 7 0 201 5 1054 7 64 0 1093 2 7781 65 0 035 0 899 S 0 346 8 7884 8 0 199 5 0546 36 0 1065 2 7051 66 0 033 0 8382 11 32 0 3437 8 7300 9 0 196 4 9784 37 0 104 2 6416...

Page 82: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 HANDLING AND SERVICING 1D10...

Page 83: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 HANDLING AND SERVICING 1D11...

Page 84: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 HANDLING AND SERVICING 1D12...

Page 85: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 HANDLING AND SERVICING 1D13...

Page 86: ...Inspection Periods 1D15 3 4 Inspection Requirements 1D15 3 5 Preflight Check 1D15 3 6 Overlimits Inspection 1D16 3 7 Special Inspections 1D16 3 8 Inspection of Exhaust System 1D16 3 9 Programmed Inspe...

Page 87: ...med The second column is divided into four columns indicating the required inspection intervals of 50 hours 100 hours 500 hours and 1000 hours Each inspection or operation is required at each of the i...

Page 88: ...efully before winter operation when the cabin heat will be in use NOTE It is recommended that all PA 28 airplanes be fitted with a new muffler at or near the 1000 hour period of which the muffler has...

Page 89: ...INDICATED BY ARROWS 8938 REFER TO AC 43 13 1A FATIGUE AREAS INDICATED BY ARROWS Figure 3 2 Typical Muffler Fatigue Areas Figure 3 1 Inspection Areas of Exhaust System PIPER AIRCRAFT PA 28 161 CADET AI...

Page 90: ...ge full flow cartridge type oil filter element Inspect strainer or element for foreign particles 6 Inspect oil temperature sender unit for leaks and security 7 Inspect oil lines and fittings for leaks...

Page 91: ...or leaks 32 Inspect fuel pumps for operation engine driven and electric 33 Overhaul or replace fuel pumps engine driven and electric See Note 5 34 Inspect engine driven vacuum pump clamps and hoses 35...

Page 92: ...rudder pedals for operation and adjustment 6 Inspect parking brake and brake handle for operation and cylinder leaks 7 Inspect control column pulleys and cables 8 Check landing navigation cabin and in...

Page 93: ...bearings for excess wear replace as required 20 Inspect stabilator trim mechanism 21 Inspect fuselage wing attach fittings for corrosion general condition and security See latest revision of Piper Se...

Page 94: ...cts electrical leads lines and attaching parts for security routing chafing deterioration wear and correct installation See Note 19 16 Reinstall inspection plates and fairings F LANDING GEAR GROUP 1 I...

Page 95: ...at 10 Check magneto switch operation 11 Check magneto RPM variation 12 Check throttle and mixture operation 13 Check propeller smothness 14 Check engine idle speed 15 Check electronic equipment operat...

Page 96: ...r further damage Replace any parts that do not conform with limits shown in the latest revision of Lycoming Service Table of Limits No SSPl 776 8 Check cylinders for evidence of excessive heat which i...

Page 97: ...ned in Section XI Electrical System 18 Replacement of the auxiliary pump motor assembly is required every 500 hours of operating time or 10 years whichever occurs first 19 Examine cables for broken st...

Page 98: ...PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 INSPECTION 1E2 THIS PAGE INTENTIONALLY LEFT BLANK...

Page 99: ...PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 INSPECTION 1E3 THIS PAGE INTENTIONALLY LEFT BLANK...

Page 100: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 INSPECTION 1E4...

Page 101: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 INSPECTION 1E5...

Page 102: ...18 Removal of Stabilator 1E18 4 19 Installation of Stabilator 1E19 4 20 Stabilator Trim Tab 1E19 4 21 Removal of Stabilator Trim Tab 1E19 4 22 Installation of Stabilator Trim Tab 1E19 4 23 Rudder 1E2...

Page 103: ...nubber 1F3 4 49 Rigging Instructions Seat Back Lock and Release 1F6 4 50 Structural Repairs 1F7 4 51 Fiberglass Repairs 1F7 4 52 Fiberglass Touch Up and Surface Repairs 1F7 4 53 Fiberglass Fracture an...

Page 104: ...e Each wing panel is an all metal full cantilever semi monocoque type construction with a removable fiberglass tip Installed in each wing ahead of the main spar is a metal fuel tank with a capacity of...

Page 105: ...ound lead is free of dirt and film to insure a good connection b Insert the wing tip into position and install the screws around the tip Use caution to refrain from damaging the fiberglass tip or wing...

Page 106: ...efer to Draining Fuel System Section II b Drain the brake lines and reservoir Refer to Draining Brake System Section II c Remove the access plate at the wing butt rib and wing inspection panels Refer...

Page 107: ...eighteen main spar bolts in accordance with the bolt legend in Figure 4 2 NOTE When replacing a wing assembly ascertain that the wing butt clearance is maintained Refer to Sketch A of Figure 4 2 WARNI...

Page 108: ...10 8 WASHER AN960 10 NUT MS20365 1032C 13 REQ SKETCH A A337 AILERON SKETCH F BOLT AN 23 18 NUT AN 310 3 WASHER AN 960 10 COTTER PIN MS 24665 132 A313 BOLT AN3 12A WASHER AN 960 10 6 REQ NUT MS20365 10...

Page 109: ...16 UNDER NUT NUT MS21045 4 SEE NOTE 0 12 MIN 0 35 MAX TORQUE NUT 50 60 IN LBS A A NOTE MINIMUM OF 1 UNDER NUT THEN AN960 416 OR AN960 416L AS REQUIRED TO LEAVE A MAXIMUM OF 1 1 2 VISIBLE THREADS OR MI...

Page 110: ...CE OF WING FITTING AND AFT FACE OF FUSELAGE FITTING IS ONE AN960 616L AND ONE AN960 616 ALL 3 WASHERS ALWAYS REQUIRED WITH ONLY THE AN960 616L WASHER ALLOWED UNDER BOLT HEAD SECTION A A SEE NOTE TORQU...

Page 111: ...A MS20365 624C 1 AN960 616 1 AN960 616 C 2 AN176 13A MS20365 624C 1 96352 3 2 AN960 616 C 3 AN176 13A MS20365 624C 1 96352 3 2 AN960 616 C 4 AN176 13A MS20365 624C 1 96352 3 2 AN960 616 C 5 AN176 13A...

Page 112: ...ervice and refill the brake system with hydraulic fluid Refer to Section II Servicing Brake System Bleed the system per instructions given in Section VII and check the system for leaks s Service and f...

Page 113: ...ttach the stabilator control cables to the stabilator balance arm with clevis bolts bushings washers nuts and cotter pins d Connect the ends of the fore and aft trim cables at the turnbuckles within t...

Page 114: ...Pull the rudder up and aft from the vertical fin 4 25 INSTALLATION OF RUDDER Refer to Figure 4 4 a Place the rudder in position and install the hinge bolts washers nuts and cotter pins NOTE Use any w...

Page 115: ...e of the fin to the fuselage c Install the stabilator trim assembly and aft trim cable per instructions given in Installation of Stabilator Trim Assembly Section V d Install the rudder per Paragraph 4...

Page 116: ...10L BOLT AN3 4A WASHER AN960 10L 4REQ SKETCH A 908 868 SKETCH C A 116 BOLT AN3 3A WASHER AN960 10L 4 REQ SKETCH D 908 SKETCH B BOLT AN23 12 WASHER AN960 10 COTTER PIN AN380 2 2 BUSHING 63900 31 SKETCH...

Page 117: ...BOLT AN4 7A 2 REQ NUT MS20365 428 2 REQ WASHER AN960 416 4 REQ SEE CAUTION WASHER AN960 416L AS REQ TO CENTER STABILATOR AND LOCK BEARING INNER RACE A BOLT NAS464P3A4 WASHER AN960 10 UNDER NUT WASHER...

Page 118: ...may allow water to penetrate past the windshield j Remove excess exposed sealer and tape 4 33 SIDE WINDOWS 4 34 REMOVAL OF SIDE WINDOWS a Remove the retainer molding from around the window by removing...

Page 119: ...WHITE SEALANT C C VINAL FOAM TAPE BLACK VINAL TAPE A A B B C C D D E E F F 956 VINAL FOAM TAPE WHITE SEALANT BLACK VINAL TAPE F F WHITE SEALANT VINAL FOAM TAPE BLACK VINAL TAPE E E 898 D D FOAM TAPE...

Page 120: ...adjustments may be made by tapping out the serrated door hinge bushings and rotating them to obtain the hinge centerline location that will provide proper door fit 4 40 REMOVAL OF DOOR LATCH MECHANISM...

Page 121: ...for operation and be certain that it is not rubbing on the trim panels 4 47 ADJUSTMENT OF DOOR SAFETY LATCH a To adjust the door safety latch remove the screws from the latch plate found at the top of...

Page 122: ...d to the jamb NOTE Do not stretch the rubber especially in the corner areas as this can cause cracks 6 It takes approximately one day for the bond to cure It is recommended that the door be kept open...

Page 123: ...BE AT CENTER OF DOOR JAMB 2 01 INCHES 4 ORIENT SNUBBER FLAT WITH THIS SURFACE VIEW C C TAPE ADHESIVE VIEW D VIEW B B VIEW A A STRIKER PLATE OVER SNUBBER STRIKER PLATE UNDER SNUBBER NOTE 4 B968 NOTE 2...

Page 124: ...the push pull cable in this position by tightening screws l and 2 on clamps 3 and 4 The stop 7 should be lubricated and free to swivel without excessive play e Push on seat back with stop assembly 7 i...

Page 125: ...or equivalent and remove paint to gel coat b The damaged area may be scraped with a fine blade knife or a power drill with a burr attachment to roughen the bottom and sides of the damaged area Feather...

Page 126: ...resin and catalyst enough to be used for one step at a time according to kit instructions h Thoroughly wet mat and cloth with catalyzed resin Daub resin on mat first and then on cloth Mat should be ap...

Page 127: ...ith the airplane properly rigged per instructions given in Section V of this Service Manual and the trim indicator at its neutral position Obtain a straightedge long enough to extend from the ground u...

Page 128: ...apable of measuring unbalance in inch pounds from the centerline of the control surface hinge pin A suggested configuration is shown in Figure 4 11 To use this tool a Insure that the control surface i...

Page 129: ...T3 016 2 2024 0 020 3 2024 T3 020 4 2024 T3 025 5 2024 T3 032 6 2024 T3 040 7 2024 T3 051 8 FIBERGLASS 9 5052 H34 032 HEAT TREAT TO T3 CONDITION AFTER FORMING 7 7 7 6 6 6 6 8 8 8 8 8 8 3 3 3 3 3 3 3 3...

Page 130: ...CEMENT PLATE AN 507 8 32 R 10 HOLE IN BOTTOM WING SKIN DIAMETER 4 11 16 A356 1 4 R 7 6 62109 ACCESS HOLE COVER PLATE NAS 395 18 3 MS 20740 AD 4 16 REQ 35362 ACCESS HOLE REINFORCEMENT PLATE AN 507 8 32...

Page 131: ...ING THE TOOL ITSELF ONCE THE TRAILING EDGE SUPPORT BEEN SET BUBBLE LEVEL SET SCREW VERTICALLY AND HORIZONTALLY ADJUSTABLE TRAILING EDGE SUPPORT VERTICALLY ADJUSTABLE FOR SETTING BEAM PARALLEL TO CORD...

Page 132: ...ble IV I proceed as follows a Leading Edge Heavy This condition is highly improbable recheck measurements and calculations b Trailing Edge Heavy It will be necessary to determine the exact cause of th...

Page 133: ...the static balance limit If the static balance is not within the limits given in Table IV I proceed as follows a Nose Heavy This condition is highly improbable recheck calculations and measurements b...

Page 134: ...INTENTIONALLY LEFT BLANK Figure 4 14 Rudder Balance Weight PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL STRUCTURES 1F14 Issued FEBRUARY 28 1989 BALANCE WEIGHT A A SECTION A A...

Page 135: ...e when the bubble level has been centered by adjustment of the movable weight and determine the static balance limit If the static balance is not within the limits given in Table IV I proceed as follo...

Page 136: ...a Peel back the full width of the protective liner approximately 2 inches from the leading edge of the safety walk b Apply the safety walk to the wing area begin at the leading edge insure proper alig...

Page 137: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL STRUCTURES 1F17 Issued FEBRUARY 28 1989...

Page 138: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL STRUCTURES 1F18 Issued FEBRUARY 28 1989...

Page 139: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL STRUCTURES 1F19 Issued FEBRUARY 28 1989...

Page 140: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL STRUCTURES 1F20 Issued FEBRUARY 28 1989...

Page 141: ...1G17 5 19 Installation of Stabilator Trim Assembly Forward 1G17 5 20 Removal of Stabilator Trim Assembly Aft 1G18 5 21 Installation of Stabilator Trim Assembly Aft 1G20 5 22 Rigging and Adjustment of...

Page 142: ...are also connected to the control column From the connecting point cables are routed around a series of pulleys down under the floor and aft to the tail section of the airplane The aft end of the cabl...

Page 143: ...t is located on either side of the tee bar assembly 5 by removing the nut washer and bolt 3 Pull the tube from the flexible joint 2 If removing the left control tube slide the stop 6 from the tube 3 S...

Page 144: ...BILATOR TAB TRAILING EDGE DOWN TRAVEL FROM NEUTRAL 12 1 STABILATOR CHORD LINE NEUTRAL POSITION SEE NOTE 2 1 MAXIMUM FREE PLAY FOR CONTROL SURFACE TAB IS 0 15 OF AN INCH MEASURED AT TAB TRAILING EDGE 2...

Page 145: ...NOTE CABLE TENSION GIVEN APPLIES ONLY TO AIRPLANES WITHOUT AUTOPILOT BRIDLE CABLES ATTACHED REFER TO APPROPRIATE AUTOPILOT SERVICE MANUAL FOR PROPER CABLE TENSIONS WHEN ATTACHING BRIDLE CABLES SUBTRA...

Page 146: ...EYS AILERON 14 BOLT WASHER 4 NUT 15 BOLT WASHER 2 NUT 16 BOLT WASHER NUT COTTER PIN 17 SPROCKET RIGHT CONTROL WHEEL 18 SPROCKET LEFT CONTROL WHEEL 19 IDLER SPROCKET AFT 20 SPACER IDLER SPROCKETS 21 ID...

Page 147: ...ings A SPECIAL WRENCH MAY BE REQUIRED WITH A LONG THROAT ONLY CORRECT METHOD IMPROPER TOOL RESULTING IN LOCKED BALL 901 WRONG DAMAGE HERE DAMAGE HERE PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANC...

Page 148: ...ks should hit their stops before the control wheel hits its stop Maintain 030 to 040 clearance between sprocket pin and adjustable stop bolts 9 Set the stabilator cable tension with turnbuckles in the...

Page 149: ...4 CABLE RIGHT FUSELAGE PRIMARY 15 CABLE LEFT FUSELAGE PRIMARY 16 TURNBUCKLE LEFT PRIMARY 17 CABLE LEFT WING PRIMARY 18 CABLE RIGHT BALANCE 19 CABLE LEFT BALANCE 20 PULLEY 21 BOLT WASHER AND NUT 22 BOL...

Page 150: ...le 12 or 16 located in the area aft of the main spar 3 Disconnect the aileron centering springs from the plate on the bellcrank 4 Disconnect the cable from the forward end of the aileron bellcrank by...

Page 151: ...cess plate on the underside of the wing c Either balance cable 18 or 19 may be installed by the following procedure 1 Draw the cable into the wing 2 Connect the cable along with the aileron centering...

Page 152: ...accomplished by the following procedure 1 Remove the access plate to each aileron bellcrank located on the underside of the wing forward of the center aileron hinge by moving the plate attaching scre...

Page 153: ...both bellcranks are at their neutral position 4 Adjust the turnbuckles located in the access opening just aft of the main spar of the primary and balance cables to their proper cable tension and main...

Page 154: ...embly by removing the plate attaching screws 2 If the right upper stabilator control cable 2 is to be removed remove the cotter pin guards at the pulley 14 located in the forward area of the tunnel 3...

Page 155: ...lator 2 Connect the cable to the stabilator balance arm and secure with bolt washer nut and cotter pin 8 Ensure bushing is installed with bolt 3 Connect the cable to the forward cable at the turnbuckl...

Page 156: ...OLT WASHER NUT COTTER PIN 9 BOLT WASHER NUT 10 BLOCK CABLE RUB 11 BOLT WASHER 7 NUT 12 BOLT WASHER 11 NUT 13 PULLEY FORWARD 14 BOLT WASHER NUT COTTER PIN 15 TURNBUCKLE 16 WEIGHT BALANCE ARM 17 BALANCE...

Page 157: ...in the near forward position Set 25 0 12 0 03 between the column and the stop bumper 4 Check each control cable for the correct tension as given in Table V I 5 Should tension be incorrect loosen the t...

Page 158: ...may be removed from its mounting brackets by removing nut washer and bolt 8 that secures the wheel between the brackets Draw the wheel from the brackets Use caution not to damage trim indicator wire 2...

Page 159: ...eys in the aft lower section of the fuselage at station 156 5 forward of the cable turnbuckles 6 Install the cable guard at the underside of the pulleys located just aft of the flap torque tube at sta...

Page 160: ...LE RIGHT 11 TURNBUCKLE LEFT 12 CABLE AFT 13 PULLEY CLUSTER 14 BOLT BUSHING WASHER 3 AND NUT 15 GUARD BOLT BUSHING WASHER AND NUT 16 RIB HORIZONTAL SUPPORT 17 PLATE RIB 18 GUARD 19 BUSHING BARREL 20 BA...

Page 161: ...l bushings 19 and 29 are installed in the rib plate 17 and clip 21 d Lubricate the bushings and install the trim barrel 20 in the bushings between the two support ribs Attach the bottom diagonal rib 2...

Page 162: ...s as given in Table V I The degree of travel on the protractor is determined by taking the difference between the protractor reading at neutral and up and neutral and down The bubble must be centered...

Page 163: ...nting bracket d Align the bolt holes in the center area of the torque tube assembly install bolts washers and nuts 25 and 26 and tighten e Position the torque tube support bracket 35 on the floor tunn...

Page 164: ...0 RUDDER PEDAL R OUTER 8 SUPPORT BLOCK LOWER 20 BOLT WASHER NUT COTTER PIN 31 BRACKET TUBE SUPPORT 9 WASHER SPACER 21 BOLT WASHER AND NUT 10 ARM IDLER 22 BOLT WASHER AND NUT 11 ROD BRAKE CYLINDER 23 B...

Page 165: ...he tail cone fairing by removing its attaching screws 2 Disconnect the cable 14 or 15 from the rudder horn 17 by removing cotter pin nut washer and bolt 16 3 Draw the cable through the fuselage 5 28 I...

Page 166: ...HING WASHER AND NUT 9 PULLEY CLUSTER 10 CABLE RIGHT FORWARD 11 CABLE LEFT FORWARD 12 TURNBUCKLE LEFT 13 TURNBUCKLE RIGHT 14 CABLE RIGHT AFT 15 CABLE LEFT AFT 16 BOLT BUSHING WASHER AND NUT 17 HORN RUD...

Page 167: ...nected the rudder may be moved by hand Refer to Table V I for required rudder travel 2 A rigging tool may be fabricated from dimensions given in Figure 5 17 to aid in rudder rigging With the rudder ag...

Page 168: ...nter of the trim screw 5 Check the safetys on the turnbuckles c Check the adjustment of the rudder pedal stops by the following procedure 1 Remove the clamp securing the rudder pedals in their neutral...

Page 169: ...ll the clevis pin and cotter pin 5 Should two thru holes be located in the aft end of the mounting channel the pin must be installed through the hole that will give equal travel and hit rudder stops b...

Page 170: ...ct the flap tension spring 22 from the cable if not previously disconnected by extending the flaps to relieve spring tension 3 Retract the flaps Use caution as forward pressure will be on the handle w...

Page 171: ...ed against the bearing blocks 7 thus allowing no side play of the assembly Tighten the bolt assemblies 10 on the stop fittings 8 Install the tube support blocks 16 and 31 on their support brackets 19...

Page 172: ...Figure 5 15 Flap Control System PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Interim Revision February 28 1995 SURFACE CONTROLS 1H4...

Page 173: ...as possible to the outboard end of the flap without contacting any rivets The tool must be positioned parallel with the wing ribs with the aft end of the tool even with the trailing edge of the flap...

Page 174: ...E BUT SHOULD NOT MAKE CONTACT WITH ANY RIVETS UP NEUTRAL 0 OF FLAPS WILL OCCUR WHEN THESE POINTS MAKE CONTACT WITH WING AND FLAP SKIN A551 TOOL REFER TO FIGURE 5 19 1 Figure 5 17 Flap Rigging Tool PIP...

Page 175: ...between pulleys and brackets Cables not in place on Install cables correctly Check cable guards pulleys Bent aileron and or hinge Repair or replace aiIeron and or hinge Cables crossed or Check routin...

Page 176: ...Lubricate system control movement properly Cable tension too high Adjust cable tension per Paragraph 5 16 Binding control column Adjust and lubricate per Paragraph 5 6 Pulleys binding or rubbing Repl...

Page 177: ...inding pulleys Provide clearance between pulleys and brackets Cables not in place on Refer to Paragraphs 5 19 and 5 21 pulleys Trim tab hinge binding Lubricate hinge If necessary replace Cables crosse...

Page 178: ...dal movement Rudder pedal torque Lubricate torque tube bearings tube bearing in need of lubrication Cable tension too high Adjust cable tension FLAP CONTROL SYSTEM Flaps fail to extend Control cable b...

Page 179: ...Rigging Tool C 341 MATERIAL STEEL OR HARD ALLUMINUM PLATE 125 X 20 0 X 6 187 FWD 5 296 20 3 34 6 187 25 R TYP 8 2 4 6 8 10 12 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY...

Page 180: ...3 82 82 1 10 1 29 MATERIAL 1 0 X 23 19 X 3 82 ALUMINUM BAR SURFACE PARALLEL TO BASE LINE STABILATOR CONTOUR 25 SET BACK 15 03 1 60 20 00 18 03 21 03 22 19 24 03 2 00 1 39 1 12 803 PIPER AIRCRAFT PA 28...

Page 181: ...AN 3 BOLT WITH HEAD FILED TO REQUIRED LENGTH 2 SPAR STOCK MAY BE USED IN PLACE OF ALUMINUM BAR STOCK MATERIAL 750 X 31 50 X 4 00 ALUMINUM BAR OR 750 X 31 50 X 750 SQ ALUYMINUM BAR STOCK MIN 31 50 4 0...

Page 182: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 SURFACE CONTROLS 1H14...

Page 183: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 SURFACE CONTROLS 1H15...

Page 184: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 SURFACE CONTROLS 1H16...

Page 185: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 SURFACE CONTROLS 1H17...

Page 186: ...Gear 1I2 7 14 Main Landing Gear 1I3 7 15 Disassembly of Main Gear Oleo 1I3 7 16 Cleaning Inspection and Repair of Main Gear Oleo 1I3 7 17 Assembly of Main Gear Oleo 1I7 7 18 Removal of Main Landing G...

Page 187: ...r Cylinder II16 7 38 Assembly of Brake Master Cylinder II16 7 39 Installation of Brake Master Cylinder Hand Brake II17 7 40 Brake Cylinder Toe Brake II17 7 41 Removal of Brake Cylinder II17 7 42 Disas...

Page 188: ...edies When troubleshooting the landing gear system it may be found that it is necessary to place the airplane on jacks If so refer to Jacking Section 11 7 4 LANDING GEAR SYSTEM 7 5 NOSE LANDING GEAR 7...

Page 189: ...P 17 SNAP RING 18 SNAP RING 19 TUBE 20 O RING 21 PLUG 22 TOW BAR LINK 23 BLOCK ASSEMBLY 24 FORK 25 SPACER 2 REQ 26 AXLE 27 ROD 28 PLUG 2 REQ 29 BLOCK 30 LINK ASSEMBLY UPPER 31 LINK ASSEMBLY LOWER 31 3...

Page 190: ...aph 7 22 2 Loosen and remove the bolt washer and nut that extends through the piston tube and block assembly 3 Push the plug through the top of the piston tube by use of a rod inserted through the bot...

Page 191: ...ad pin through the side of the horn and top of the strut assembly When it protrudes through the other side of the steering horn install the washer and secure with a cotter pin k Install the steering h...

Page 192: ...AND NUT 14 BOLT WASHER AND NUT 15 NOSE GEAR STRUT ASSEMBLY 16 BOLT WASHER AND NUT 17 LINK ASSEMBLY 18 BUMPER BLOCK 19 PISTON TUBE ASSEMBLY 20 TOE BAR BRACKET 21 FORK ASSEMBLY 22 TIRE 23 AXLE ROD ASSE...

Page 193: ...t c The shimmy dampener requires no service other than routine inspection in case of damage or malfunction the dampener should be replaced rather the repaired d Repair to the landing gear is limited t...

Page 194: ...ly three feet forward of the nose wheel at the centerline of the tire Snap the chalk line f Ascertain that the rudder is properly rigged and the rudder cable tension is correct Refer to Rigging of Rud...

Page 195: ...move the filler plug insert a siphon hose and drain fluid from the upper area of the housing 2 Disconnect the flexible brake line at the elbow on the brake assembly 3 Disconnect the torque link assemb...

Page 196: ...2 3 4 5 6 7 9 11 12 13 14 15 16 17 18 19 20 21 Figure 7 5 main Gear Oleo Strut Assembly PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 LANDING GEAR AND BRAKE SYSTE...

Page 197: ...12 O RING OR QUAD RING 13 RING SCRAPER 14 RING SPACER 15 RING RETAINER 16 TUBE PISTON 17 AXLE STUB 18 SPACER 19 SPACER 20 NUT WHEEL RETAINER 21 PIN CLEVIS 11 10 9 8 7 5 4 3 2 1 Figure 7 5 main Gear O...

Page 198: ...8 BOLT WASHER NUT AND COTTER PIN 9 OLEO ASSEMBLY 10 TORQUE LINK ASSEMBLY 11 TORQUE LINK ASSEMBLY 12 STUB AXLE 12 11 10 9 8 7 6 5 4 3 2 1 Figure 7 6 Main Gear Installation PIPER AIRCRAFT PA 28 161 CAD...

Page 199: ...t operates freely NOTE Links should be loose enough to allow free action of the gear but also resist side play To eliminate side play shim washers 6331 1 03 005 may be used as required Maximum side pl...

Page 200: ...ear until wheel is removed c Remove wheel by the following procedure 1 Remove the nut and washer from one end of the axle rod and slide out the rod and axle plugs 2 Lightly tap the axle tube out from...

Page 201: ...hich use the Cleveland Wheel Assembly torque nuts to 90 inch pounds Those aircraft models which use the McCauley Wheel Assembly torque nuts to 140 150 inch pounds 1 SNAP RING 2 RING GREASE RETAINER 3...

Page 202: ...nes grease seals 4 or 13 felt rings 3 or 14 and seal retainer ring 2 or 15 Secure with snap ring l or 16 1693 1 SNAP RING 2 RING GREASE RETAINER 3 FELT RING 4 RING GREASE SEAL 5 BEARING CUP 6 BEARING...

Page 203: ...ASSEMBLY AND INSTALLATION OF MAIN WHEEL Refer to Figure 7 8 a Ascertain that the bearing cup 5 or 9 for each wheel is properly installed Install the tire with tube on the outer wheel half 7 and then j...

Page 204: ...g the piston from the housing f Check anchor bolt for wear g Remove anchor bolt by the following procedure 1 Position cylinder assembly on a holding fixture Refer to Figure 7 10 2 Use a suitable arbor...

Page 205: ...RESS A122 STEP C STEP B STEP A ANCHOR BOLT HOLDING FIXTURE HOLDING FIXTURE CYLINDER BODY HOLDING FIXTURE CYLINDER BODY PRESS Figure 7 11Installation of Anchor Bolt PIPER AIRCRAFT PA 28 161 CADET AIRPL...

Page 206: ...king applications from 25 to 40 MPH Allow the brake discs to partially cool between stops 7 33 ASSEMBLY AND INSTALLATION OF WHEEL BRAKE ASSEMBLY Refer to Figure 7 9 a Lubricate the piston O ring with...

Page 207: ...LET 9 CLEVIS PIN 10 MASTER CYLINDER ASSEMBLY 11 BOLT ASSEMBLY 12 TORQUE TUBE 13 RIGHT COPILOT S BRAKE AND RUDDER PEDAL 14 LEFT COPILOT S BRAKE AND RUDDER PEDAL 15 TO LEFT WHEEL BRAKE 16 TO HAND BRAKE...

Page 208: ...h a suitable solvent and dry thoroughly b Inspect the interior walls of the cylinder for scratches burrs corrosion etc c Inspect the general condition of the fitting threads of the cylinder d Check th...

Page 209: ...ke system per paragraph 746 7 40 BRAKE CYLINDER Toe Brake 7 41 REMOVAL OF BRAKE CYLINDER Refer to Figure 7 12 a Disconnect the upper and lower lines from the cylinder to be removed and cap the lines t...

Page 210: ...he roll pin 15 washer 14 spring 11 washer 9 packing gland 7 seal 5 piston assembly 3 spring 2 and roll pin 12 3 Insert the piston rod assembly in the cylinder 1 and secure with the retaining ring 10 4...

Page 211: ...ge air from the toe brake cylinder system Watch for any air forced through the clear plastic tube during this operation to insure air has been forced from the toe brake system f Pump the hand brake an...

Page 212: ...ECK Pull for a good firm hand brake and lock parking brake mechanism Allow system to stand for approximately 10 minutes then by gripping the park brake handle it should not be able to be pulled aft fu...

Page 213: ...15 16 9 O RING 10 O RING 11 WASHER WIPER 12 RETAINING RING 13 ROD 14 SPRING 15 WASHER 16 ROLL PIN C344 1700 NOTE ON NEWER VERSIONS THE ROLL PIN 14 IS DELETED AND ITEM 13 IS A PERMANENT SHOULDER RING 8...

Page 214: ...or uneven wear Incorrect operating pressure Inflate tire to correct pressure on nose tire Wear resulting from shimmy Refer to proceedings for correction Nose gear fails to steer Oleo cylinder binding...

Page 215: ...or landing Worn or loose wheel Replace and or adjust wheel bearings bearings Worn torque link bolts Replace bolts and or bushings and or bushings Excessive or uneven wear Incorrect operating pressure...

Page 216: ...lation Tool THIS SPACE INTENIONALLY LEFT BLANK 9904 150 1 25 1 40 7 50 3 50 7 50 125 30 WELD ROLL PIN 50 DIA HANDLE PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 L...

Page 217: ...THIS PAGE INTENIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 LANDING GEAR AND BRAKE SYSTEM 1J1...

Page 218: ...THIS PAGE INTENIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 LANDING GEAR AND BRAKE SYSTEM 1J2...

Page 219: ...J14 8 17 Carburetor 1J14 8 18 Carburetor Maintenance 1J14 8 19 Adjustment of Idle Mixture 1J15 8 20 Adjustment of Idle Speed 1J16 8 21 Magnetos Slick 4000 and 4200 Series 1J17 8 22 Removal of Magnetos...

Page 220: ...oval of Spark Plugs 1K10 8 39 Inspection and Cleaning of Spark Plugs 1K11 8 40 Installation of Spark Plugs 1K11 8 41 Lubrication System Engine 1K11 8 42 Oil Pressure Relief Valve 1K11 8 43 Carburetor...

Page 221: ...engine is furnished with a starter 60 ampere alternator 14 volt electrical system shielded ignition vacuum pump drive and fuel pump The exhaust system is stainless steel with two mufflers A shroud is...

Page 222: ...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 d...

Page 223: ...acks sometimes start from such places Use fine emery cloth for finishing Refer to Figure 8 1 for propeller blade care A propeller with several nicks scratches corrosion or cracks should be returned to...

Page 224: ...GAUGE MUST NOT BE OPERATED AT MAXIMUM POWER WITH COWLING REMOVED PROLONGED GROUND RUNNING WITH THE COWLING REMOVED COULD CAUSE LOCAL HOT SPOTS IN THE CYLINDERS AND IRREVERSIBLE ENGINE DAMAGE TABLE VII...

Page 225: ...ip to follow the other while rotating in almost the same plane Excessive difference in blade track more than 0 062 inch may be an indication of bent blades or improper propeller installation Check bla...

Page 226: ...MUM OF 2 5 THREADS EXPOSED ON THE BOLT TORQUE TO 240 270 INCH POUNDS 1 BAFFLE ASSEMBLY LEFT 2 STARTER RING GEAR 3 SHOCK MOUNT SEE FIGURE 8 4 4 LIFTING STRAP 5 BAFFLE ASSEMBLY RIGHT 6 VACUUM PUMP 7 SPA...

Page 227: ...for any attachments remaining to obstruct its removal t Drain the engine oil if desired and close the drain u Remove the four engine mount assemblies and swing the engine free being careful not to da...

Page 228: ...ER TORQUE 450 500 IN LBS ENGINE MOUNTING LUG SHOCK MOUNT ENGINE MOUNT SPACER SHOCK MOUNT WASHER BOLT C D D C B B A A Figure 8 4 Engine Shock Mount Installation PIPER AIRCRAFT PA 28 161 CADET AIRPLANE...

Page 229: ...etely Turn on the electric fuel pump and check the fuel line for leaks t Install the engine cowlings and remove the tail stand CAUTION To avoid possible high speed bearing failure resulting from a lac...

Page 230: ...of an inch spring back on instrument panel stop when in full throttle or full rich position a The throttle may be adjusted as follows 1 At the carburetor disconnect the rod end of the throttle control...

Page 231: ...e work area b Draw back on the cockpit throttle control lever to obtain a reading of approximately 550 RPM on the tachometer c Turn the idle mixture adjusting screw 1 located near the rear of the carb...

Page 232: ...from 55O to 650 RPM Rotate the screw clockwise to increase the speed of the engine counterclockwise to decrease the engine speed The screw is located on the throttle arm NOTE One complete revolution o...

Page 233: ...vision of Lycoming Service Letter No L 177 and Slick pro rata instruction form No 1001 At the time of engine inspection or when a magneto has been removed from the engine The 4200 series magnetos can...

Page 234: ...rmation If possible check continuity from block with tester or light j Check insulators for cracks breaks or evidence of old age Be sure they are clean k Check ventilator plugs Ventilator has drilled...

Page 235: ...e model 4050 magneto without impulse coupling Spark Out the magneto by the following method 1 Install the gear and hold the number one lead wire 0 062 of an inch away from the magneto frame 2 Turn the...

Page 236: ...loading spring and washer from the end frame Place the rotating magnet in a suitable keeper and press the ball bearings off the journals Discard the ball bearings and washer h Using coil wedge extract...

Page 237: ...ADAPTER PLASTE T 123 TIMING PLUG T 103 OIL SEAL ASSEMBLING PLUG T 101 BEARING ASSEMBLING PLUG T 102 ROTOR AND FRAME ASSEMBLING PLUG T 122 WEDGE EXTRACTOR T 118 TIMING PIN Figure 8 7 T 1000 Assembly a...

Page 238: ...HOOD 27 AIR VENT 28 CONDENSER C698 13 SCREW 14 THICK LOCK WASHER 15 ROTOR GEAR 16 COIL 17 COIL WEDGE 18 SCREW 19 CONTACT POINT KIT 20 SCREW 21 BEARING BAR 22 GEAR DISTRIBUTOR 1814 15 22 16 23 25 24 17...

Page 239: ...plate making sure it is square on the bearing i Using rotor and frame assembling plug T 102 turn the T screw down until the plate bottoms in the frame Refer to Figure 8 11 Install bearing plate clamp...

Page 240: ...ING 4 ROTOR SHAFT 5 T SCREW 6 BEARING PLATE 7 PLUG FRAME ASSY 8 FRAME 4 1 3 2 7 6 8 Figure 8 11 Installation of Bearings and Bearing Plate Figure 8 10 Index Plate and Timing Plug PIPER AIRCRAFT PA 28...

Page 241: ...ing with the cut away toward the condenser Use screws and lockwashers Torque to 18 20 in Ibs s Connect the condenser wire to the slip terminal on the point assembly Align the L or R depending on magne...

Page 242: ...the pin engages the gear c If the pin is binding and will not go in the hole in the gear you have hit the pointer on the gear Pull the pin out enough to continue opposite rotation until the pointer h...

Page 243: ...condenser terminal Switch must be ON d Rotate the complete magneto opposite normal rotation of the magneto on the engine mounting until the timing light indicates the contact breaker points are just...

Page 244: ...86 or 86A or an equivalent direct current high voltage tester capable of delivering a test potential of 10 000 volts Connect ground lead to high voltage tester to outer shielding braid of a single lea...

Page 245: ...red Do not stretch the wire when measuring it b On the magneto end make a final mark 0 75 inch for slick magnetos or 562 for Bendix magnetos from the end of the wire A 0 937 inch mark should be made f...

Page 246: ...Figure 8 14 Stripping Tool Figure 8 15 Inserting Stripping Tool Figure 8 16 Cutting Insulation Figure 8 17 Removing Silicone Rubber from Wire PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL...

Page 247: ...1 16 M 1671 M 1458 A385 Figure 820 Installation Figure 8 21 Driving Tool Figure 8 18 Installation of Plug Endpoint Figure 8 19 Flaring out the Shielding PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTEN...

Page 248: ...d under shielding as in step i then drive the ferrule into the M 1569 or M 1893 Housing using the M 1744 Drive Tool similar to step j Refer to figure 8 23 m Clamp the threaded end of the M 1498 Electr...

Page 249: ...UG END M 1738 BROWN OR M 1677 GREEN SEE NOTE Figure 8 24 Installation of Electrical Screw Figure 8 25 Installation of Insulator Sleeve Figure 8 26 Installation of Spring Figure 8 27 Removing Spark Plu...

Page 250: ...the barrel insulator will be broken by a rotary twisting of the collar Avoid undue distortion of the collar and possible side loading of the barrel insulator b Remove the spark plug from the engine In...

Page 251: ...the plugs must be serviced at more frequent intervals Fine wire platinum or iridium electrodes should be set at 015 to 018 of an inch only 8 40 INSTALLATION OF SPARK PLUGS Before installing spark plu...

Page 252: ...ht will be extinguished The probe has an expected service life of 50 000 hours A built in test circuit is activated such that each time the switch is turned on the light will come on momentarily 8 44...

Page 253: ...approximately 600 ohms with ordinary light on the probe sensor 4 Cover the ice detection probe sensor with the hand to eliminate most light The ohmmeter reading should be very high approximately 10 0...

Page 254: ...inoperative and should be returned to the manufacturer See Note c To test the probe and instrument s function 1 Turn power on 2 Turn sensitivity control up from its full counterclockwise position unt...

Page 255: ...ectric tester and replace any defective wires Improper operation of Check timing of magnetos magneto Internal failure Check oil sump screen for metal particles If found complete overhaul of the engine...

Page 256: ...place Low power and uneven Mixture too rich indicated Check primer Readjustment running engine by sluggish engine operation of carburetor indicated red exhaust flame and black smoke Mixture too lean i...

Page 257: ...Improper ignition timing Check magnetos for trimming and synchronization Failure of engine to Throttle lever out of Adjust throttle lever develop full power adjustment Leak in induction system Tighten...

Page 258: ...ock or dirt in relief Remove and clean oil pressure valve relief valve Leak in suction line or Check gasket between pressure line accessory housing crankcase High oil temperature See High Oil Temperat...

Page 259: ...e Replace fuel pump O ring fuel pump vent Engine breather or vacuum Check engine and over pump breather haul or replace pump Failing or failed bearing Check sump for metal particles and if found over...

Page 260: ...wise direction with throttle FULL OPEN and ignition switch OFF Inaccurate pressure Cold weather High or low pressure readings due to extremely cold weather are not necessarily a malfunction Small and...

Page 261: ...PAGES 1K21 THRU 1L24 INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 POWER PLANT 1K21...

Page 262: ...CADET MAINTENANCE MANUAL CARD 2 OF 2 PA 28 161 CADET PIPER AIRCRAFT CORPORATION PART NUMBER 761 829 2A1 Courtesy of Bomar Flying Service www bomar biz...

Page 263: ...SERIAL NUMBER INFORMATION PA 28 161 CADET 1988 Serial Numbers 28 41001 and up PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL 2A2...

Page 264: ...A complete manual table of Contents is for all fiche in this set 2 A complete list of Illustrations is given and follows the Table of Contents 3 A complete list of Tables is given for all fiche in th...

Page 265: ...CONTROLS 1F21 VI HYDRAULIC SYSTEM Not Applicable VII LANDING GEAR AND BRAKE SYSTEM 1H18 VIII POWER PLANT 1J3 AEROFICHE CARD NO 2 IX FUEL SYSTEM 2A9 X INSTRUMENTS 2B6 XI ELECTRICAL SYSTEM 2C16 XII ELE...

Page 266: ...ed View of Alternator 2C24 11 4 Removal of Rectifier 2D3 11 5 Removal of Slip Ring End Bearing 2D3 11 6 Removal of Drive End Head 2D3 11 7 Removal of End Head Bearing 2D3 11 8 Testing Rotor for Ground...

Page 267: ...4 11 38 Engine Gauges 2F5 11 39 Hourmeter Optional 2F6 11 40 Turn and Bank 2F7 11 41 Anti Collision Strobe Lights Wing 2F8 11 42 Anti Collision Strobe Lights Tail 2F9 11 43 Recognition Lights Optional...

Page 268: ...5 X X Fuel Pressure Gauge 2C7 X XI Turn and Bank Indicator 2C8 X XII Fuel Quantity Indicator 2C9 X XIII Oil Temperature Indicator 2C11 XI I Index Electrical System Schematics 2C19 XI II Alternator Spe...

Page 269: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL 2A8...

Page 270: ...nsmitter Unit 2A15 9 14 Fuel Quantity Transmitter Gauge Check 2A15 9 15 Fuel Quanity Gauge Calibration 2A15 9 16 Check and Adjustment of Fuel Quantity Transmitter Unit 2A16 9 17 Locking Fuel Cap 2A18...

Page 271: ...mp 2A22 9 34 Adjustment of Electric Fuel Pump Bench Test 2A22 9 35 Adjustment of Electric Fuel Pump In Airplane 2A22 9 36 Installation of Fuel Pumps 2A23 9 37 Engine Primer Pump 2A23 9 38 Removal of E...

Page 272: ...smitter unit installed in the fuel tanks 9 3 TROUBLESHOOTING Troubles peculiar to the fuel system are listed in Table IX III along with their probable causes and suggested remedies When troubleshootin...

Page 273: ...R ENGINE FUEL PUMP ELECTRIC FUEL PUMP FUEL STRAINER FUEL TANK SELECTOR VALVE FUEL QUANITY GAGES LEFT MAIN TANK RIGHT MAIN TANK Figure 9 1 Fuel System Diagram PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MA...

Page 274: ...ay Lubricant Dupont or Ferrulube Parker Hannifin and torque the nut to the proper values as listed in Step d If the union is unserviceable it must be replaced per instructions given in paragraph 9 10...

Page 275: ...nto the union and snug up the nut using a wrench 3 Then using the wrench tighten the nut one to two flats 1 6 to 1 3 of a turn d If a repair is being made using Parker Hannifin unions and tubes withou...

Page 276: ...ining Fuel System Section 11 c Level the airplane longitudinally and laterally NOTE The electrical system should apply 14 volts to the gauge 9 15 FUEL QUANTITY GAUGE CALIBRATION A calibration chart ha...

Page 277: ...an inch spacer block Should the float not be touching the spacer or the float arm is not against the bottom stop adjust the arm stop of float assembly by bending it where shown in Figure 9 3 The entir...

Page 278: ...S GAL 0 10 15 F RIGHT FUEL U S GAL CALIBRATION CHART GRADUATION OHMS DEGREES TOLERANCE DOT MECH ZERO 40 1 2 0 3 32 1 0 5 14 15 1 10 23 2 1 15 33 20 1 F 45 32 1 2 NOTE TOLERANCE IS IN POINTER WIDTHS U...

Page 279: ...9 ASSEMBLY OF LOCKING FUEL CAP Refer to Figure 9 5 a Insert the key lock through the cover making sure that the O ring is installed under the key lock b Slide the spring teflon gasket rubber gasket an...

Page 280: ...attaching screws 9 22 INSTALLATION OF SHUTOFF VALVE a Secure the valve to the bulkhead attachment plate with attaching screws b Connect the fuel lines to the valve c Install the fuel valve placard wi...

Page 281: ...Position the bowl and bail wire and tighten the bail nut f Safety the bail nut and the bail wire assembly 9 27 ELECTRIC FUEL PUMPS 9 28 PLUNGER FUEL PUMPS 9 29 REMOVAL OF FUEL PUMP The fuel pump may...

Page 282: ...Do not disassemble 3 Shake the plunger assembly and listen for clicks to indicate valve action 4 Check the condition of the O ring 5 Check the condition of the cover gasket and plunger spring cup gas...

Page 283: ...is obtained Then close the by pass valve and check the pressure gauge for the proper reading of 4 to 4 75 psi maximum no flow f Repeat steps b through e for the second fuel pump g If the proper press...

Page 284: ...he primer 9 39 DISASSEMBLY CLEANING AND ASSEMBLY OF ENGINE PRIMER Refer to Figure 9 8 a The primer may be further disassembled after removal by removing the screws 3 springs 2 and check balls 1 from t...

Page 285: ...ith air pressure Do not use sharp objects or wire brush to clean the jet tube c Install the jet finger tight to assure that the threads are not crossed and then torque 60 inch pounds Align and install...

Page 286: ...n wire Check and repair operate Gauge inoperative Replace Circuit breaker open or Check and reset or replace fuse blown Incomplete ground Check ground connections at fuel transmitter in wings Float an...

Page 287: ...fuel selector to Check position of selector be in proper position and adjust if required Pressure low or pressure Obstruction in inlet side Trace lines and locate surges of pump obstruction Faulty by...

Page 288: ...50 RICHLITE MASONITE OR HARDWOOD 1 2 50 X 6 25 X 50 RICHLITE MASONITE OR HARDWOOD 2 1 625 X 2 50 X 125 2024 T3 ALUM 26 WOOD SCREWS 4 6 WOOD SCREWS EVENLY SPACED 50 TWO WOOD SCREWS EVENLY SPACED 1 1 9...

Page 289: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 FUEL SYSTEM 2B4...

Page 290: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 FUEL SYSTEM 2B5...

Page 291: ...Adjustment and Functional Check 2B15 10 22 Vacuum Regulator Setting Auxiliary Pump Off 2B16 10 23 Auxiliary Air Pump Functional Check Engine Shut Down 2B16 10 24 Auxiliary System Functional Check Eng...

Page 292: ...ire Gauge Calibration 2C4 10 62 Troubleshooting 2C5 10 63 Removal and Replacement 2C5 10 64 Fuel Pressure Gauge 2C6 10 65 General 2C6 10 66 Fuel Pressure Gauge Calibration 2C6 10 67 Troubleshooting 2C...

Page 293: ...1 10 88 General 2C11 10 89 Removal and Replacement of Cluster Mounted Instruments 2C12 10 90 General 2C12 10 91 Piper Auto Control System 2C13 10 92 Annunciator Panel 2C13 10 93 General 2C13 10 94 Tro...

Page 294: ...uld be examined periodically and inspected carefully whenever engine maintenance activities cause hose disconnections to be made at the pump regulating valve gyros and or vacuum gauge 2 The ends of th...

Page 295: ...s below the recommended value The filters should be replaced when gauge reading declines below the recommended value do not adjust regulator d Vacuum Regulator 1 The vacuum regulating valve seldom nee...

Page 296: ...below the instrument panel 10 11 TROUBLESHOOTING For troubleshooting of the vacuum regulator refer to Table X I 10 12 ADJUSTMENTS OF VACUUM REGULATOR VALVE a Loosen the locking nut or remove the prot...

Page 297: ...4 DIRECTIONAL GYRO 8 NAV COM TRANSCEIVER 15 TURN COORDINATOR ELECTRIC 9 TRANSPONDER 16 INDICATOR VOR LOC 10 SUCTION GAUGE 17 GLARESHIELD ASSEMBLY 11 ENGINE HOUR METER 18 CIRCUIT BREAKER PANEL 12 EXHAU...

Page 298: ...r restricted Line from pump to gyros Check all lines and leaking fittings Normal pressure indication Faulty instrument Replace instrument but sluggish operation of instruments High system pressure Vac...

Page 299: ...e caution must be exercised to avoid pump damage The square mounting flange must be held between soft wood blocks and only at right angles to the vise jaws Use only enough vise pressure to hold the pu...

Page 300: ...nt backup source of pneumatic power to operate the gyro flight instruments in the event the engine driven air pump fails The system consists of a 14 VDC electrically driven dry air pump that connects...

Page 301: ...L CHECK ENGINE SHUT DOWN Note If it is required to run the auxiliary pump for more than a couple of minutes it is recommended that the aircraft have an APU connected a Turn aircraft master switch on b...

Page 302: ...ALTERNATE STATIC SOURCE NOTE BOTH THE PITOT AND STATIC LINES CAN BE DRAINED THROUGH SEPERATE DRAIN VALVES 6 LOCATED ON THE LEFT LOWER SIDE OF THE FUSELAGE INTERIOR 1 2 3 4 7 6 5 Figure 10 2 Pitot Sta...

Page 303: ...ime indicator ETI or at 10 years of installed time in the aircraft whichever occurs first The ETI P N F7 97 1 is matched to the pump motor assembly and must also be removed and replaced at the same ti...

Page 304: ...recommended b After running the pump continuously for approximately 20 minutes check the entire system for proper operation according to section 10 23 10 28 ANNUNCIATOR LIGHT REPLACEMENT The annuncia...

Page 305: ...eans of hose and tubing routed through the wing along with the pitot line An alternate static air source is located below the instrument panel in front of the pilot The alternate static source is part...

Page 306: ...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...

Page 307: ...UBLESHOOTING TABLE X III GYRO HORIZON INDICATOR Trouble Cause Remedy Bar fails to respond Insufficient vacuum Check pump and tubing Filter dirty Clean or replace filter Bar does not settle Insufficien...

Page 308: ...Pointer fails to Obstruction in static Disconnect all instruments connected respond line to the static line Clear line Pitot head frozen over Water in static line Check individual instruments for obs...

Page 309: ...the diaphragm expands causing the pointers to move through the mechanical linkage 10 45 TROUBLESHOOTING TABLE X V ALTIMETER Trouble Cause Remedy Excessive scale error Improper calibration Replace inst...

Page 310: ...ecking system must be rechecked per F A R 23 1325 10 46 REMOVAL AND REPLACEMENT Refer to Paragraph 10 87 of this section 10 47 AIRSPEED INDICATOR 10 48 GENERAL The airspeed indicator provides a means...

Page 311: ...elf contained instrument This instrument has an individual light which is connected to the instrument lighting circuit The compass correction card is located in the card holder mounted on the instrume...

Page 312: ...etic Locate magnetic interference interference and eliminate if possible Excessive card Insufficient liquid Replace instrument oscillation Card sluggish Weak card magnet Replace instrument Excessive p...

Page 313: ...he way to stop Excessive lubricant in Replace instruments more noticeable in cold weather instruments Pointer jumps at idle Speed cup hitting Replace instrument rotating magnet Tachometer cable breaks...

Page 314: ...lve oil Check for leaks If trouble persists clean and adjust relief valve Sluggish operation ofpointer Engine relief valve Clean and check or pressure fails to build up open 10 63 REMOVAL AND REPLACEM...

Page 315: ...hat the suspect faulty gauge is within tolerance Refer to Figure 10 5 Note Actual recalibration of the gauge must be preformed by the manufacturer or an approved instrument repair facility CALIBRATION...

Page 316: ...race lines and locate pressure surges side of pump obstruction Faulty bypass valve Replace Faulty diaphragm Replace or rebuild pump Needle fluctuation Surge dome or pump Remove and empty filled with f...

Page 317: ...er to Paragraph 10 87 of this section 10 74 FUEL QUANTITY INDICATOR Refer to paragraph 9 15 of Section IX 10 75 GENERAL The two fuel quantity gauges are mounted in the cluster on the instrument panel...

Page 318: ...ete ground Check ground connections empty when tanks are at fuel transmitter in full wings Fuel gauge indicates Incomplete ground Check ground at full with tanks empty instrument Float arm stuck Repla...

Page 319: ...on of the gauge must be preformed by the manufacturer or an approved instrument repair facility a With the instrument installed in the aircraft the aircraft power connected 14 VDC and the ground conne...

Page 320: ...ents Special care should be taken when any operation pertaining to the instruments is performed a Remove the face panel by removing the screws from around the perimeter of the panel b With the face pa...

Page 321: ...tape well into threads 5 Screw fitting into port being careful not to exceed torque requirements as noted on decal located on cover of gyro d Installation of the instruments will be in the reverse or...

Page 322: ...pressure and the vacuum system The ALT warning light will illuminate when alternator output is zero the VAC light when the pressure difference is below 3 5 in Hg and OIL light when the oil pressure i...

Page 323: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 INSTRUMENT 2C14...

Page 324: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 INSTRUMENT 2C15...

Page 325: ...2D8 11 18 Battery 2D10 11 19 Battery Description 2D10 11 20 Servicing Battery 2D10 11 21 Removal of Battery 2D10 11 22 Installation of Battery 2D11 11 23 Charging Battery 2D11 11 24 Starting Through...

Page 326: ...Navigation Light 2D21 11 61 Installation of Tail Navigation Light 2D22 11 62 Anti Collision Light Rotating Beacon 2D22 11 63 Removal 2D22 11 64 Installation 2D22 11 65 Anti Collision Strobe 2D22 11 66...

Page 327: ...E4 11 85 Installation of Circuit Breakers 2E4 11 86 Switching 2E4 11 87 Removal of Ignition Switch 2E4 11 88 Installation of Ignition Switch 2E4 11 89 Annunciator Panel 2E5 11 90 Description 2E5 11 91...

Page 328: ...ock Electric and Digital Optional 2F4 11 38 Engine Gauges 2F5 11 39 Hourmeter Optional 2F6 11 40 Turn and Bank 2F7 LIGHTING SYSTEMS 11 41 Anti Collision Strobe Lights Wing 2F8 11 42 Anti Collision Str...

Page 329: ...trument panel The master switch must be on before any electrical equipment will operate The master switch controls the battery relay and field circuit The switch is a double pole single throw type The...

Page 330: ...LIGHT STALL WARN A C AIR BLOWER ROTAT G BEACON PITOT HEAT TURN BANK AUTO PILOT START ACC BATTERY FEEDER INSTRUMENT LIGHTS PANEL OVERHEAD NAV LIGHTS ANTI COLL LIGHT LANDING LIGHT NAV COM 1 GS NAV COM...

Page 331: ...a one or two minute cool down period the breaker can be reset manually If tripping reoccurs this indicates a short in the alternator circuit The ammeter does not indicate battery discharge but display...

Page 332: ...e approximate current drawn by the light Therefore when the light is switched on there will be an increase of current from 10 to 18 amperes displayed on the ammeter As each unit of electrical equipmen...

Page 333: ...in the rectifier mounting plate while the three negative rectifiers are mounted in the slip ring end head Each pair of rectifiers is connected to a stator lead with high temperature solder The stator...

Page 334: ...e charging circuit Failure to observe these service procedures will result in serious damage to the electrical equipment a When installing a battery always make sure the ground polarity of the battery...

Page 335: ...r tester will detect and pinpoint open or shorted rectifiers without going through the operation of disconnecting the stator leads However if a tester is not available test probes and a No 57 bulb con...

Page 336: ...f Rectifer Figure 11 5 Removal of Slip Ring End Bearing Figure 11 6 Removal of Drive End Head Figure 11 7 Removal of End Head Bearing PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued...

Page 337: ...ted in Figure 11 11 CAUTION Use an arbor press do not hammer Reconnect the stator leads to the rectifier When soldering these connections use pliers as a heat sink on the lead between the solder joint...

Page 338: ...fier 368 NUT LOCK WASHER FLAT WASHER FIBER WASHER END HEAD INSULATOR RECTIFIER MOUNTING PLATE TERMINAL STUD OUTPUT TERMINAL AUXILIARY TERMINAL Figure 11 12 Terminal Assembly PIPER AIRCRAFT PA 28 161 C...

Page 339: ...rvice Test Specification paragraph for output test figures Adjust the carbon pile if necessary to obtain the specified voltage The alternator is not to be run more than 2 minutes for each test point b...

Page 340: ...ring When the bearing is replaced the new inner race must be installed on the rotor shaft b Lubrication The slip ring end bearing should be lubricated whenever the alternator is disassembled The beari...

Page 341: ...sion is given as follows a Apply a torque indicating wrench to the nut that attaches the pulley to the alternator and turn it in a clockwise direction Observe the torque shown on the wrench at the ins...

Page 342: ...stretch that takes place as soon as it is operated These higher tension values should not be applied to belts which have previously been used THIS SPACE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 1...

Page 343: ...ons must be clean and tight Refer to Table XI IV TABLE XI IV HYDROMETER READING AND BATTERY CHARGE PERCENT 11 21 REMOVAL OF BATTERY a To gain access to the battery lift the right engine cowl b Loosen...

Page 344: ...AIRPLANE S BATTERY NEARLY DEPLETED a When using a 12 volt battery for external power starting and the airplane s battery is nearly depleted the following procedure should be used 1 Disconnect the air...

Page 345: ...x 1 BATTERY BOX ASSEMBLY 2 BATTERY 3 VENT HOSES 4 COVER ASSEMBLY 5 CONTACTOR POWER RELAY 6 DIODE ASSEMBLY 6 5 4 3 2 1 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989...

Page 346: ...around the battery the battery should be removed and both the box and battery cleaned by the following procedure a Remove the box drain cap from the underside of the fuselage and drain off any electr...

Page 347: ...wire to the alternator f Slip the plastic sleeves over the connectors and tie in place g Tie off wires as necessary to keep them away from moving parts and sharp edges on the structure h Reconnect bat...

Page 348: ...t 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 b...

Page 349: ...ding or excessive noise Then the engine should be started two or three times to see that the pinion disengages properly when the engine is turned off I1 39 OVERHAUL If during the above inspection any...

Page 350: ...core If the test lamp lights the armature is grounded and should be replaced c To test for shorted armature coils a growler is used Refer to Figure 11 21 The armature is placed on the growler and slow...

Page 351: ...if the pinion teeth are excessively worn or damaged 11 48 ASSEMBLY a When assembling the starter motor always use an arbor press and the proper bearing arbor for installing graphitized bronze and rol...

Page 352: ...23 If current is too high check the bearing alignment and end play to make sure there is no binding or interference Two or three sharp raps on the frame with a rawhide hammer will often help to align...

Page 353: ...released it should be replaced 11 51 STARTING MOTOR SERVICE TEST SPECIFICATIONS Prestolite specifications for 12 volt starting motors installed as standard equipment on PA 28 161 CADET airplanes are...

Page 354: ...7 DESCRIPTION There are three navigation lights one on each wing tip and one on the tail The navigation lights are controlled by a single switch and a 10 amp circuit breaker 11 58 REMOVAL OF WING NAVI...

Page 355: ...er supply for all three lights 11 67 REMOVAL OF WING TIP STROBE LIGHT a Remove the screw securing the navigation light cover and remove cover b Remove the three screws securing navigation light bracke...

Page 356: ...ING OFF FIN BLACK WITH SHIELD WHITE VIEW A TO FIN TIP SEE VIEW A TO RIGHT WING TIP SEE VIEW A TO LEFT WING TIP SEE VIEW A TO SPLIT SWITCH BLACK BLACK RED RED L4A RED 4 3 2 1 2 3 2 3 PIPER AIRCRAFT PA...

Page 357: ...VIEW A TO LEFT WING SEE VIEW A L4F NOT USED JUMPER AN TI CO LL OFF OFF FIN WING L4B L4A L4E BLACK WITH SHIELD RED RED VIEW A SPLIT SWITCH SPLIT SWITCH 882 BLACK LS4 2 3 PIPER AIRCRAFT PA 28 161 CADET...

Page 358: ...ROUBLESHOOTING PROCEDURE The strobe light functions as a condenser discharge system A condenser in the power supply is charged to approximately 450 volts DC then discharged across the Xenon flash tube...

Page 359: ...cket assembly of the anti collision light from the interconnecting cable 2 The following continuity checks can be made with an ohmmeter a Check for continuity between Pin 1 of AMP connector to Pin 1 o...

Page 360: ...e sensor blade of the unit drops down freely and secure in position with the four screws previously removed 11 80 ELECTRICAL SWITCHES AND CIRCUIT BREAKERS 11 81 DESCRIPTION The switches are of the roc...

Page 361: ...n the forward side of the instrument panel and withdraw the switch from the panel d Mark the wires and note their position on the switch then disconnect the wires 11 88 INSTALLATION OF IGNITION SWITCH...

Page 362: ...5 amp fuse located aft of the diode heat sink to the resistor and diode creating a no flow condition which does not allow the warning light to light The test button is used to check the operation of...

Page 363: ...ntire output circuit Measure voltage from ground to the following points in sequence bus bar and ammeter Zero output indicated Open output circuit Interruption of voltagethrough any of on ammeter rega...

Page 364: ...on ammeter connections at voltage regulator circuit breaker etc Examine crimped terminal ends for signs of deterioration at crimp or strands of broken wire at crimp Tighten any loose binding posts or...

Page 365: ...for shorting against frame If there are no obvious signs of a physical short circuit at field terminal or brush holder replace alternator Note Intermittent short circuit Internal short circuiting of t...

Page 366: ...by inserting a strip of number 000 sandpaper between the brush and commutator with the sanded side next to the brush Pull sandpaper in the direction of rotation being careful to keep it in the same co...

Page 367: ...these troubles fails to operate Excessive arcing of Binding worn or im See information above motor brushes properly seated brush dealing with this or brushes with excessive trouble side play Dirty co...

Page 368: ...pment left on Remove and recharge accidentally Impurities in electrolyte Replace Short circuit ground Check wiring in wiring Broken cell partitions Replace Battery life is short Overcharge due to leve...

Page 369: ...dding inside container filling water Vent lines leaking or Repair or clean clogged Charging rate too high Adjust voltage regulator Battery freezes Discharged battery Replace Water added and battery Al...

Page 370: ...ck terminals and fail to extinguish out replace switch if after engine is running necessary OIL warning light Bulb burned out Replace fails to operate No current to sensor Check all wire segments and...

Page 371: ...emove material bridged between terminals Defective sensor Replace ALT warning light Bulb burned out Replace fails to operate No current from bus Check all wire segments to resistor and connections ALT...

Page 372: ...509 Landing Light 472 661 Magnetic Compass Light 472 665 330 Navigation Light Wing Tip 751 381 1512 Tail 753 431 1073 Panel Lights 472 056 Rotating Beacon 1940 Strobe Lights Wing Tip 761 156 A427 Fin...

Page 373: ...Light 5 0 5 X X Fuel Pump 10 5 0 X Instrument Cluster 5 0 7 X Instrument Lights 18 5 2 2 X X Landing Light 10 8 0 X X Master Contactor 0 6 X Pitot Heat 15 13 2 X X Position Lights 10 4 0 X X Stall War...

Page 374: ...TION CIRCUITS LETTER A AUTOPILOT C CONTROL SURFACE F FLIGHT INSTRUMENT G LANDING GEAR H HEATER VENTILATING DEICING L LIGHTING P POWER Q FUEL OIL ENGINE INSTRUMENT RP RADIO POWER RZ RADIO AUDIO J IGNIT...

Page 375: ...TCH BUTT CONNECTORS SHIELDED CONDUCTORS CONNECTORS CROSSINGS AND JUNCTIONS OF CONDUCTORS THE DOT AT THE INTERSECTION INDICATES A JOINING OF CONDUCTORS CONDUCTORS FUSE RESISTOR LAMP GROUND BEACON PNUEM...

Page 376: ...3AF P V VACUUM SENSOR SWITCH OIL PRESSURE SENSOR SWITCH W6B W4B W6A W4A TO AMMETER ALTERNATOR W2AA W2A 3 6 8 1 ANNUNCIATOR PANEL W18 5A 5A 20 20 20 20 20 20 20 W1A ANNUNCIATOR LIGHTS PIPER AIRCRAFT PA...

Page 377: ...TO ANNUNCIATOR SYSTEM WIRING DIAGRAM W1B W6A W4A W2A 79333 00 UNIT 6 6 8 8 1 1 3 3 6 5 W 50 ALT VAC OIL Figure 11 29 Annunciator Internal Wiring PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MAN...

Page 378: ...Figure 11 30 Pitot Static Heat PITOT AND STATIC HEAT PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2E21...

Page 379: ...11 31 Alternator ALTERNATOR SWITCH 6 6 18 18 18 18 5 8 8 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2E22...

Page 380: ...ELECTRICAL SYSTEM BUS 10 PR1A A3 A4 PR1B 10 AVIONICS BUS 20 PR2A X1 X2 AVIONICS MASTER RELAY 20 PR2B OFF ON AVIONICS MASTER SWITCH PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEB...

Page 381: ...D MAGNETO STARTER SWITCH S L R GND B 4 18 O K1B 18 4 18 18 18 K1C P1A J1A K1A K2A TO ENGINE MAGNETOS J2A STARTER AND ACC 15 AMP P1C K2B 4 STARTER S 4 15 a PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINT...

Page 382: ...PR2B20N BATTERY MASTER Figure 11 34 Battery Master Switch PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F1...

Page 383: ...Figure 11 35 Air Blower PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F2...

Page 384: ...Figure 11 36 Fuel Pump PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F3...

Page 385: ...igure 11 37 Clock Electric and Optional Digital GND T STRIP 1 2 M2B M2A M2C TO BATTERY CONTACTOR PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F...

Page 386: ...Figure 11 38 Engine Gauges 5 5 14 14 1 1 P6A 20 P5A 20 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F5...

Page 387: ...PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F6 11 39 Hourmeter Optional TO BATTERY CONTACTOR GND T STRIP M3B M3A R2 P2 7 7 M3C M1B...

Page 388: ...Figure 11 40 Turn and Bank F2A20N PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F7...

Page 389: ...Figure 11 41 Anti Collision Strobe Lights Wing 12 12 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F8...

Page 390: ...Figure 11 42 Anti Collision Strobe Lights Tail 12 L12C 10 10 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F9...

Page 391: ...Figure 11 43 Recognition Lights Optional 5 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F10...

Page 392: ...Figure 11 44 Instrument Flood Lights INSTR FLOOD LIGHT PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F11...

Page 393: ...Figure 11 45 Navigationa Lights NAV LIGHTS 2 2 G1P20N PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F12...

Page 394: ...11 46 Landing Light LANDING LIGHT PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F13...

Page 395: ...11 47 Instrument Panel and Switch Lights SWITCH L5D L7B PANEL LIGHTS SWITCH LIGHTS INSTR PANEL LIGHTS PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYST...

Page 396: ...Figure 11 48 Pitch Trim PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F15...

Page 397: ...11 49 Stall Warning 13 13 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F16...

Page 398: ...SEE TRANSPONDER INSTL 5 A 5 A AUDIO PANEL RP 2 18 RP 7 18 RP 1 18A RP 4 20 SEE RADIO SYSTEMS INSTL A D F AND MARKER D M E TRANSPONDER 10 A 10 A 10 A 10 A SEE GLIDE SLOPE INSTL SEE RADIO INSTL SEE RADI...

Page 399: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F18...

Page 400: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F19...

Page 401: ...THIS PAGE INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRICAL SYSTEM 2F20...

Page 402: ...3 12 5 Testing Emergency Locator Transmitter 2G2 12 6 Description Operation and Testing of Pilot s Remote Switch 2G3 12 7 Avionics Master and Emergency Switch Circuit 2G3 12 8 Description and Operatio...

Page 403: ...nance Manual CAUTION It is very important to never use a substitute trim system component part for an original design part because of the fail safe characteristics of the system might be compromised R...

Page 404: ...head to the battery casing and slide apart f Disconnect the battery by unsnapping the snap off battery pigtail terminals from the bottom of the transmitter printed circuit board g Discard old battery...

Page 405: ...M SWITCH TO ON ANTENNA EXTENSION TAB Figure 12 1 ELT Portable Folding Antenna Figure 12 2 ELT Using Fixed Aircraft Antenna B965 ANTENNA STOP PIN RESET HANDLE NOTCH FOR HANDLE RELEASE PORTABLE ANTENNA...

Page 406: ...d whip should be replaced Antenna damage may cause structural failure a of whip in flight THIS SPACE INTENTIONALLY LEFT BLANK ELT 2 ON RESET ARMED BLACK WHITE WHITE BLUE 1 WHITE Figure 12 3 ELT Schema...

Page 407: ...A Advisory Circular AC 20 81 for detailed information concerning above caution a Remove the access plate on the right side of the fuselage aft of sta 228 30 b Tune the aircraft communications receiver...

Page 408: ...lot s Operating Handbook 12 7 AVIONICS MASTER AND EMERGENCY SWITCH CIRCUIT Refer to Figure 12 4 12 8 DESCRIPTION AND OPERATION Electrical power for the various avionics components is controlled by the...

Page 409: ...of Auto Pilot Flight Director manufacturers to obtain service direction parts support and service literature Bendix Avionics Division 2100 N W 62nd Street Fort lauderdale Fla 33310 305 776 4100 TWX 5...

Page 410: ...he Kansas 66061 913 782 0400 Telex 4 2299 Kingrad Sperry Flight Systems Avionics Div 8500 Balboa Blvd P O Box 9028 Van Nuys CA 91409 213 894 8111 Telex 65 1367 Global Navigations 2144 Michelson Drive...

Page 411: ...THIS PAGE INTENTALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRONICS 2G6...

Page 412: ...THIS PAGE INTENTALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRONICS 2G7...

Page 413: ...THIS PAGE INTENTALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ELECTRONICS 2G8...

Page 414: ...ofiche Paragraph Grid No 13 1 Introduction 2G10 13 2 Description 2G10 13 3 Heater Maintenance 2G10 13 4 Overhead Vent System 2G10 PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBR...

Page 415: ...an inlet in the leading edge of each wing The air passes through the wings to individually controlled outlets located just forward of each seat An air vent is located in the bottom of the fuselage to...

Page 416: ...WITCH OUTLET 9 DEFROSTER OUTLET 10 HEATER CONTROL 11 CABIN HEAT DIVERSION CONTROL 12 FRESH AIR CONTROL 13 DUCT ASSEMBLY 10 12 7 9 1 12 1 3 FRESH AIR CABIN HEAT 5 4 2 3 13 6 8 11 Figure 13 1 Cabin Heat...

Page 417: ...THIS PAGE INTENTALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 HEATING AND VENTILATING 2G12...

Page 418: ...THIS PAGE INTENTALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 HEATING AND VENTILATING 2G13...

Page 419: ...Overhead Vent Blower 2G15 14 3 Description 2G15 14 4 Removal of Blower Assembly 2G15 14 5 Disassembly of Blower Assembly 2G15 14 6 Reassembly of Blower Assembly 2G15 14 7 Installation of Blower Assemb...

Page 420: ...he inlet and outlet hoses from the blower assembly by removing the clamps d Remove the screws washers and nuts that secure the blower assembly to the hangar braces e Remove the screws and washers whic...

Page 421: ...utlet hoses securing them with the clamps d With the master switch off connect the plug and receptacles at the blower e Check the blower for the proper operation f Install the access door to the aft w...

Page 422: ...2G17THRU 2L24 INTENTIONALLY LEFT BLANK PIPER AIRCRAFT PA 28 161 CADET AIRPLANE MAINTENANCE MANUAL Issued FEBRUARY 28 1989 ACCESSORIES AND UTILITIES 2G17...

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