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Raytheon Beech Baron A55, Shop Manual


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Summary of Contents for Beech Baron A55

Page 1: ...u TC 501 855 TC 371 TC 502 and After C55 TC 350 TE 1 thru TE 451 D55 TE 452 thru TE 767 E55 TE 768 and After 58 TH 1 and After Shop Manual Copyright 0 Raytheon Aircraft Company 2004 P N 55 590000 13E...

Page 2: ...ircraft Company The export of these commodities technology or software are subject to the US Export Administration Regulations Diversion contrary to U S law is prohibited For guidance on export contro...

Page 3: ...n y evlslon No Chapter Page s By Date No Date When inserting or removing a temporary revision the applicable revision number and the inltlafs of the person s inserting andlor removing these revisions...

Page 4: ...L ytkcol Aircraft BEEC BARON 55 AND 58 MAINTENANCE MANUAL RECORD OF TEMPORARY REVISIONS emporary Affected Inserted Removed Revision evlslon No Chapter Page s By Date No Date Page 2...

Page 5: ...ct Incorporated 4 1 Mar 8 96 Control Column Arm and Dual Control Arm Removal and Installation E16 4 2 Nov 15 93 Fla Drive CableConnection Procedures E16 15 1 Oct 31 97 Overhaul and Replacement Schedul...

Page 6: ...ervicing Air Conditioning System TE 1119 TE 1125 and After TH 873 TH 895 and After Break in Engine Oil Oil System Oxygen System Optional Vacuum System Pneumatic Pressure System TC 1 and After iE l and...

Page 7: ...RT PAGE SECTION PAGE SECTION DATED Title Page Title Page Dec 31 04 Logo Page Logo Page A Page A Page E23 B Page B Page E23 All 2 1 thru 62 2 Dec 31 04 All 3 1 thru 59 3 Dec 31 04 All 15 1 thru 6 15 De...

Page 8: ...thru 14 51 Onginal Section 2 1 thru 62 Dec 31 04 14 52 Jan 1 80 14 53 thru Section 3 1 thru 59 Dec 31 04 14 69 Onglnal Section 4 4 1 thru 4 85 Apr 2 99 14 70 thru 14 72 Aug 18195 Section 5 1 thru 78...

Page 9: ...November 10 2000 1 3 and 5 55 590000 13E19 June 28 2002 15 and 16 55 590000 13E20 June 27 2003 10 55 590000 13E21 December 31 2003 12 and 13 55 590000 13E22 June 30 2004 1 and 5 55 590000 13E23 Decem...

Page 10: ...trols and Surfaces SECTION 5 Landing Gear and Brake System SECTION 6 Poi ier Plan SECTION 7 Propeller SECTION 8 Fuel System SECTION 9 Pressurization SECTION 16 Heating and Cooling System SECTION 11 Ut...

Page 11: ...ALPHABETICAL INDEX...

Page 12: ...Overhaul Landing Gear Landing Gear and Brake System 5 78 Actuator Rudder Trim Tab Flight Controls and Surfaces 4 55 Aileron Balancing Flight Controls and Surfaces i 61 Aileron Control System Rigging F...

Page 13: ...ion 1 17 Air Conditioning Condenser Blower Installation Heating and Cooling System 10 17 Air Conditioning Condenser Blower Removal Heating and Cooling System 10 1 Air Conditioning Condenser Installati...

Page 14: ...ssure System Adjustment Utility Systems 11 15 Air Pressure System Inline Filter Inspection Utility Systems 11 13 Alternator and Generator Overhaul Electrical System 13 li D Alternator Belt Adjustment...

Page 15: ...pilot System H 14 Utility Systems 11 78 Autopilot Troubleshooting Utility Systems 11 t3 Autopilot Vendor Publications General Information 1 1 Avionics Compartment Door FoMlard Baggage and Airframe 3 5...

Page 16: ...g Compressor Heating and Cooling System 10 16 Blower Cabin Heater Heating and Cooling System 10 5 Blower Installation Air Conditioning Condenser Heating and Cooling System 10 16 Blower Module Aft Evap...

Page 17: ...ht Controls and Surfaces i 6 3 Cleaning Airplane Exterior Ground Handling and Servicing 2 If Cleaning Airplane Interior Ground Handling and Servicing 2 12k Cleaning Painted Surfaces Ground Handling an...

Page 18: ...1 Control Surfaces Aileron System Flight Controls and Surfaces 4 11 Control Surfaces Aileron Trim Tab Flight Controls and Surfaces 4 16 Control Surfaces Balancing Flight Controls and Surfaces 4 61 Co...

Page 19: ...ems 11 68 Deicer Brush Block Removal McCauley Utility Systems 11 68 Deicer Brush Block Replacement Goodrich Utility Systems 11 gj Deicer Brush Block Resistance Check Goodrich Utility Systems 11 59 Dei...

Page 20: ...ent Goodrich Utility Systems 11 53 Deicer Slip Ring Alignment McCauley Utility Systems 11 68 Deicer Slip Ring Installation Goodrich Utility Systems 11 59 Deicer Slip Ring Removal Goodrich Utility Syst...

Page 21: ...Window Cabin Airframe 3 5 Doors Adjustment Cabin Airframe 3 40 Doors Cabin Airframe 3 38 Dual Control Arm Installation Flight Controls and Surfaces 4 Dual Control Arm Removal Flight Controls and Surf...

Page 22: ...ng Ground Handling and Servicing 2 3 Electrical System Overhaul and Replacement Schedule Overhaul and Replacement 15 ii Schedule Electrical System Overvoltage Check Electrical System 13 12C Electrical...

Page 23: ...and Surfaces 4 35 Elevator Trim Tab Free Play Check Flight Controls and Surfaces 4 1 Elevator Trim Tab Horn Repair Flight Controls and Surfaces 4 3 Elevator Trim Tab Indicator Cable Replacing Flight C...

Page 24: ...tment Power Plant 6 5 Engine Idle Speed Adjustment Power Plant 6 5 Engine Induction Manifold Drain Ground Handling and Servicing 2 6B Engine Installation Power Plant 6 1 Engine Magneto Breaker Point A...

Page 25: ...erglass Repair Airframe 3 56 Filter Central Instrument Air Ground Handling and Servicing 2 9 Filter Cleaning Evaporator Blower Heating and Cooling System 10 19 Filter Gyro Air Utility Systems 11 Filte...

Page 26: ...ht Controls and Surfaces 4 78 Flap Motor and Gearbox Overhaul Flight Controls and Surfaces 4 7 Flap Motor and Gearbox Removal Flight Controls and Surfaces 4 77 Flap Motor Brush Replacement Guide Gener...

Page 27: ...and Surfaces 4 1 3 Flight Controls Rudder Rigging Flight Controls and Surfaces 3 dj Flight Controls Rudder Trim Tab Flight Controls and Surfaces 3 50 Flight Control Surface Travel General Information...

Page 28: ...tem Calibration Power Plant 6 12 Fuel Full Throttle Pressure Adjustment Power Plant 6 7 Fuel Injector Pump Installation Power Plant 6 8 Fuel Injector Pump Removal Power Plant 6 8 Fuel Level Transmitte...

Page 29: ...ry Through Structure Airframe C 2 Inspection Without Repair Kit Fuselage Wing Forward Spar Carry Through Structure Airframe 3 27 Inspection With Repair Kit Fuselage Wing Forward Spar Carry Through Str...

Page 30: ...System Utility Systems 11 i Gyro Instrument Air Filter Ground Handling and Servicing 2 9 Headliner Installation Airframe 3 37 Headliner Removal Airframe 3 37 Heater Blower Heating and Cooling System 1...

Page 31: ...ols and Surfaces 4 61 Horizontal Stabilizer Removal Flight Controls and Surfaces 4 6r Horn Elevator Trim Tab Flight Controls and Surfaces 4 43 Horn Switch Adjustment Throttle Warning Landing Gear and...

Page 32: ...3 47 Jacking Airplane Ground Handling and Servicing 2 1 Landing Gear Actuator Overhaul Landing Gear and Brake System 5 78 Landing Gear Actuator Removal and Installation Landing Gear and Brake System 5...

Page 33: ...ding Gear Nose Shimmy Damper Assembly Landing Gear and Brake System 5 Landing Gear Nose Shimmy Damper Servicing Ground Handling and Servicing 2 Landing Gear Nose Shimmy Damper Wear Tolerances Landing...

Page 34: ...ght Troubleshooting Navigation Electrical System 13 36 Lights Wedge Ground Handling and Servicing 2 4 Lock Control Ground Handling and Servicing 2C Lubricants Table of Thread Ground Handling and Servi...

Page 35: ...em 5 pS Main Landing Gear Overhaul Landing Gear and Brake System 5 25 3 Main Landing Gear Removal Landing Gear and Brake System 5 23 Main Landing Gear Strut Extension General Information 1 9 Main Land...

Page 36: ...Gear and Brake System 5 72 Nose Landing Gear Shimmy Damper Disassembly Landing Gear and Brake System 5 68 Nose Landing Gear Shimmy Damper Installation Landing Gear and Brake System 5 67 Nose Landing...

Page 37: ...m Pressure General Information 1 6 Oil System Pressure Fluctuation Adjustment Power Plant 6 5 Oil System Screen Cleaning Ground Handling and Servicing 2 Oil System Temperature Control Valve Power Plan...

Page 38: ...nishes 12 6 Painted Surfaces Cleaning Ground Handling and Servicing 2 11 Painting Aluminum Aircraft Finishes 12 1 Paints Enamel Topcoats Aircraft Finishes 12 1 Paints Epoxy Aircraft Finishes 12 2 Pain...

Page 39: ...Control Cables Power Plant 6 3 Power Plant Controls Adjusting Power Plant 6 2 Power Plant Cowl Flap Actuator Rigging Power Plant 6 3 Power Plant Cylinder Differential Compression Check Power Plant 6...

Page 40: ...essure Regulator Valve Removal Utility Systems 11 30 Pressure Relief Valve Adjustment General Information 1 9 Pressure Switch Adjustment Landing Gear Landing Gear and Brake System 5 13 Pressure System...

Page 41: ...ility Systems 11 63 Propeller Electric Deicer Boot Removal Goodrich Utility Systems 11 60 Propeller Electric Deicer Boot Removal McCauley Utility Systems If 62 Propeller Electric Deicer Brush Block In...

Page 42: ...Utility Systems 11 53 Propeller Electric Troubleshooting Utility Sysyem 11 69 Propeller Feathering Adjustment Propeller 7 4 Propeller Governor Propeller 7 3 Propeller Governor Adjustment Propeller 7 j...

Page 43: ...or Adjustment Alternator Electrical System 13 11 Regulator Adjustment Generator Electrical System 13 13 Regulator Fuel Transmitter or Transducer Troubleshooting Electrical System 13 30 Relay Adjustmen...

Page 44: ...faces 4 26 28 Rigging Flight Controls Rudder Flight Controls and Surfaces 4 43 Rigging Mechanical Cowl Flap Power Plant E Rigging Rudder Control System Flight Controls and Surfaces i39 Roller Bearing...

Page 45: ...Servicing 2 10 Seats Vertical Adjusting Airframe 3 33 Seats 5th and 6th Installation Airframe 3 Seats 5th and 6th Removal Airframe 3 3 Seats 5th and 6th Stowage Airframe 3 3j Se rvici ng Ground Handl...

Page 46: ...rning Switch General Information 1 Stall Warning Switch Heater Utility Systems 11 0 Stall Warning Switch Heater Test Utility Systems 11 1 Stall Warning System Adjustment Utility Systems 11 O Starter E...

Page 47: ...tems 11 26 30 Surface Deicer Cleaning Utility Systems 11 35 Surface Deicer Coating Utility Systems 11 35 Surface Deicer Installation Utility Systems 11 28 33 Surface Deicer Removal Utility Systems 11...

Page 48: ...Servicing 2 11 Throttle Warning Horn Switch Adjustment Landing Gear and Brake System 5 82 Throw Over Control Column Flight Controls and Surfaces 4 2 Time Limits Maintenance Practices Overhaul and Repl...

Page 49: ...Controls and Surfaces 4 20 Trim Tab Free Play Check Elevator Flight Controls and Surfaces 4 41 Trim Tab Free Play Check Rudder Flight Controls and Surfaces 4 58 Trim Tab Horn Elevator Flight Controls...

Page 50: ...Ground Handling and Servicing 2 Urethane Paints Colors List of Aircraft Finishes 12 6 Urethane Paints Pretreatment Primer Aircraft Finishes 12 Urethane Paints Primer Aircraft Finishes 12 5 Urethane Pa...

Page 51: ...el Cells Fuel System 8 la Vendor Publications General Information 1 15 Ventilation System Heating and Cooling System 10 1 Vent Line External Fuel Cell Fuel System 8 13 Vertical Stabilizer Flight Contr...

Page 52: ...indshield Anti icing Systems Utility Systems 11 41 42 Windshield Deice Check Utility Systems 11 47 Windshield Heater Functional Check Utility Systems 11 48 Windshield Heater Installation Utility Syste...

Page 53: ...moval Wet Airframe 3 a Wing Tip Wet Installation Fuel System 8 22 Wing Tip Wet Leak Check and Repair Fuel System 8 22 Wing Tip Wet Leak Test Fuel System 8 22 Wing Tip Wet Removal Fuel System 8 22 Wing...

Page 54: ...SECTION GENERAL INFORMATION...

Page 55: ...n quickly locating the information you need an alphabetical index contains multiple entres for each subject Additional information which should prove most helpful includes troubleshooting guides an ov...

Page 56: ...renced in this shop manual are utilized during operation service and maintenance of the airplane Raytheon Aircraft Company expressly reserves the right to supersede cancel anc or declare obsolete any...

Page 57: ...SPAN 55 A55 855 055 D55 E55 and 58 37 82 TAIL HEIGHT 55 A55 and 855 9 6 C55 9 37 055 E55 9 22 58 9 51 TREAD WIDTH 55 A55 855 055 D55 855 and 58 9 59 PROPELLER DIAMETER 55 A55 855 055 D55 E55 and 58 p...

Page 58: ...1 i Removed TC 1043 and aft 37 82 I Z r 78 DIA c I 1 0 5 2 I l i t l i t r s is a O 60 DIHEDRAL C9 59 jjl C 1043 and alter z r r i nl I j B g i i j j iFI I u 5 f 1 7 I to 42 1 C 7 0 1 TWHI 26 70 prior...

Page 59: ...i j i 97 83 I 1 s t x s j i i j i i i l li i i i i iijf i i i _1 s s I 5 x i I I 5 I SSfS r i j ii j j i l 1 i z r s i i 5 5 i i j jj ji f i i8i i i i i W i c DDIEDRAL I I i 5 i Z _ iji 2 _ g 37 r i 2...

Page 60: ...1 1II _ f r r 5 i I 1 5 r i j I j 1 iiiiB i i i i85ii i8i i i i i i8i ss X 2 5 5 i iiiiiijijijiijiiiiiiiial i i51 8 iS 3 60 DMEDEUL r I 51 zxo xlx r i li 51 B5 ii5 a zr M j j i j ii r li i 8 8 1 ii r...

Page 61: ...L LANOING LK HT TH B7 AND AFTrR I 37 82 1 DIAMETW PRBELLDI USED ON M 1389 TH 1396 AND AFTER 78 0 DIA 6 MHEORL L 969 t 10 43 PROPEUER GROUND CLEARANCE ON M 1389 TH 396 AND AF W 9 93 r0 45 C I 1 I _I s...

Page 62: ...the IO 520 C engines except the 1O 520 CB engine has a stronger crankshaft and other changes related to the stronger crankshaft I Model 58 TH 1389 TH 1396 and After two Continental 6 cylinder IO 550 C...

Page 63: ...L McCAULEY 2AF34C55n8FF 0 TC 371 TC 408 TC 473 STANDARD McCAULEY thru TC 1415 96 960006 608 1 TC 1416 and After OPTIONAL XARTZELL PCS465 6 08465 6 96 960022 601 TC 1416 and After OPTIONAL HARTZELL PC8...

Page 64: ...nd After OPTIONAL McCAULEY FC8475 6 96 960021 609 TE 849 and After OPTIONAL McCAULEY FC8475 6 BHCC2YF2CHFI TE 849 thru TE 942 STANDARD HARTZELL FC84756 except TE 938 96 960008 601 D3567 TE 1 thru TE 8...

Page 65: ...FC8475 6 exceptTH 1389 58 960010 607 TH 1 thru TH 1395 OPTIONAL HARTZELL FC8475 6 exceptTH 1389 PHCJ3YF2FI TH 1 thru TH 1395 OPTIONAL HARTZELL FC7663 2R except TH 1389 3AF32C512 82NEA 5 TH 1389 TH 139...

Page 66: ...t 6 FUEL CAPACITY AIRPLANE SERIAL FUEL SELECTOR POSITIONS CAPACITIES TC 1 thru TC 1607 TE 1 thru OFF AUX MAIN CROSSFEED 112 Gallon Capacity System TE 942 except TE 938 106 Gallon Usable TC 1 thru TC 1...

Page 67: ...F PRESSURE RELIEF VALVES Refer to Section 11 PRESSURE SYSTEM ADJUSTMENT CHART MOTOR BRUSH REPLACEMENT GUIDE NOTE On airplanes TC 2003 and After TE 1084 and After and TH 773 and After the flap motor sh...

Page 68: ...si TE 452 and After 52 to 56 psi TH 1 and After 52 to 56 psi TC 2092 and After TE 1114 and After and TH 873 and After That are equipped with Cleveland Heavy Duty Brakes 50 to 54 psi MAIN GEAR STRUT EX...

Page 69: ...System Screens and Strainers 100 hours or sooner if conditions warrant OIL SYSTEM Oil Filter 100 hours at oil change TE 1 and After TH 1 and After Oil Pressure Screen Clean in solvent every 25 hours...

Page 70: ...2 40 in lbs MAX 1 1 4 20 80 t 5 in lbs I 1 4 20 Rocker BoxCoverOnly 50 5 in lbs 11 4 28 100 10in lbs 1 3 8 24 370 to 390 in lbs REB3N OR F34 14M ROD END NUTS Used on throttle mixture and prop controls...

Page 71: ...lbs it necessary to align 1 cotter pin holes TC 2457 and After TE 1202 and After TH 1484 and After WING SURFACE CONTROLS Push Rod to Bellcrank 30 to 60 in lbs Bellcrank to Structure 50 to 100 in lbs...

Page 72: ...6 78 60 85 225 135 140 3750 24 3 8 24 160 1 90 72 108 95 110 390 200 240 4375 20 7 16 20 450 500 270 300 840 500 5000 20 1 2 20 480 690 290 410 210 230 1 100 660 1 415 5625 18 9 16 18 800 1 000 480 60...

Page 73: ...160 00 3 8 16 160 185 95 110 275 170 7 1 6 14 235 255 140 1 55 475 1 280 1 2 13 400 480 240 290 880 520 9 16 12 500 700 300 420 1 100 i 650 5 8 11 700 900 420 540 1 500 i 900 3 4 10 1 150 1 600 700 95...

Page 74: ...HOSE ASSEMBLIES INCHES AND10061 OR AND10078 MINIMUM MAXIMUM MINIMUM MAXIMUM MINIMUM MAXIMUM 1 8 3 16 90 100 70 100 1 4 40 65 135 150 70 120 5 16 60 80 180 200 85 80 3 8 75 125 270 300 100 250 1 2 150...

Page 75: ...enter of the bolt through the spring scale attaching point To calculate the force in pounds scale reading required to obtain the specified torque divide the torque In inch pounds by the distance in in...

Page 76: ...aft tompany BARON 55 AND 58 SHOP MANUAL TcrraL LENGTH L i THO1B Torque Wrench and Adapter Figure 5 LB 90 TOTAL LENGTH TO ZQUE HJ LB r ate Determining Torque by Spring Scale Figure 6 Page 2 2Ju n30 04...

Page 77: ...C 1 THRU TC 2358 TE 1 THRU TE 1182 TH 1 THRU iH l 192 T Y FLAP TRAVEL GAGE TS1176 2 UPPER FORWARD WING NUT TORQUE WRENCH ADAPTER FOR EXTERNAL WRENCHING NUT TC 2359 AND AFTER TE 1183 AND AFTER TH 1193...

Page 78: ...RBYtheOn Aircraft Company BARON 55 AND 58 SHOP MANUAL This Page Intentionally Left Blank SECTION 1 E22...

Page 79: ...Overhaul Manual Form No X 30022 10 470 Engine Series Teledyne Continental Motors Corporation Box 90 Mobile Alabama 36601 Parts Catalog Form No X 30023A 10 470 Engine Series Teledyne Continental Motors...

Page 80: ...n P O Box 114 Gainesville Florida 32601 Service Manual GSM 1277 for Gill Aircraft Batteries Teledyne Battery Products Redlands California Service Manual CB12 9 for the Concorde Aircraft Battery Concor...

Page 81: ...ney New York Catalog and Service Manual Form 1012 600 Series Slick Electro Inc 530 Btackhawk Park Avenue Rockford Illinois 61101 WHEELS BRAKES AND TIRES Maintenance Instructions for Goodyear 6 50 8 Br...

Page 82: ...ustries inc P O Box 51370 Tulsa Oklahoma 74151 STROBE LIGHT Instruction and Service Manual for Airguard Anti collision Beacon Publication Number 50082 Bullock Magnetics Corp Pomona California AIR COND...

Page 83: ...3A3 and MG113A4 Actuator and SG28A1 SG28A3 Switch 92 30107A1 Overhaul Instructions for P651A1 Altitude Control 98 32523 Overhaul Instructions for MG112A1 and MG112A2 Pitch Trim Actuator 92 30229 Overh...

Page 84: ...58 SHOP MANUAL RAYTHEON AIRCRAFT NEW MATIC AUTOPILOT 11807 8 4 and 8 4A Maintenance and Service Manual 92 402 New Matic Pilot Operating Instructions 130332 Dynertial Pitch Control Pilot Operating Inst...

Page 85: ...SECTION GROUND HANDLING AND SERVICING...

Page 86: ...ed with a Tronair Extension Kit P N 4013 are as follows WARNING Do not exceed the structural limitations of the Model 300 jack It is recommended that no airplane weighing over 5 000 pounds be jacked o...

Page 87: ...c Position the jack under the airplane up against the two forward jack points and position the rear clevis plate for attachment of the rear fitting eyebolt adapter d Install the safety pin in the rear...

Page 88: ...s obtained for normal gear operation of both the nose and main gears d Make sure the jack safety locks are engaged immediately after jacking e To lower the airplane disengage the jack safety locks and...

Page 89: ...Ray heon Aircraft Company BARON 55 AND 58 SHOP MANUAL SAFEP PIN PIN Tail Tie Down Support Figure 1 Page 4 D ec31 04 SECTION 2 E23...

Page 90: ...adapter c Install the sling strap around the nose forward of the nose landing gear d Hoistthe airplane smoothly NOTE Adjust the sling strap to keep the airplane in a level or slightly nose down attit...

Page 91: ...ING REMOVED INSTALL gg gg0017 ADAPTER HERE WITH WING INSTALLED 85 59001 a9 SPACER WING ATTACH BOLT SPAR CARRY 95 590017 ADAPTER THRU FrTTMC i r AR Y Cz itio THRU FITTING WING SPAR FITTING 95 590017 1...

Page 92: ...ll the sump to the full mark on the oil dipstick with corrosion preventive compound 3 Chart 3 This will mix 1 with normal oil is suitable as a lubricant and will provide protection against corrosion c...

Page 93: ...nst corrosion c Run the engine at least 5 minutes at a speed between 1 000 and 1 200 rpm with the oil temperature and cylinder head temperature in the normal operating range d Remove the top and botto...

Page 94: ...ded on the airplane Do not use hemp or manila rope It is recommended that a tail support be used to compress the nose strut which will reduce the wing angle of attack Attach a line to the nose gear En...

Page 95: ...earlier than 6 months Replace all desiccant and protex plugs Before spraying the engine shall be inspected for corrosion as follows Inspect the interior of at least one cylinder on each engine through...

Page 96: ...Check the air pressure periodically and inflate as necessary e It is advisable that unserviceable tires be used for prolonged storage CAUTION Do not apply corrosion preventative to the exposed surfac...

Page 97: ...on The elevator and aileron controls are locked by a locking pin which slides into matching holes in the elevator shaft aileron torque tube and control column hanger Another part of the lock slips ove...

Page 98: ...k by inserting the spring end of the lock into the left hand pilot s rudder pedal arm Neutralize the pedals and insert the opposite end of the locking pin in the other pedal arm by compressing the spr...

Page 99: ...efore rotation of the propeller blades ascertain that the magnetolstart switches are OFF the throttles are in the CLOSED position and the mixture controls are in the IDLE CUT OFF position Always stand...

Page 100: ...ed vents may cause excess internal cell pressure and cause leaks d Never remove a cell from the battery case unless a replacement is immediately available otherwise the remaining cells may swell makin...

Page 101: ...compartment should be checked regularly and a visible I fluid level maintained on the dipstick at all times by adding hydraulic fluid 13 Chart 3 LANDING GEAR The landing gear retract mechanism is a c...

Page 102: ...r the uplock roller bearing SHOCK STRUTS The shock struts are filled with compressed air and hydraulic fluid 13 Chart 3 The same procedure Is used for servicing both the main and nose gear shock strut...

Page 103: ...placed fluid and replace the end seal scraper ring and internal snap ring g Fill the piston rod with fluid h Reinstall the floating piston spring washer and cotter pin Spread the cotter pin to allow c...

Page 104: ...olvent 15 Chart 3 and blow dry with compressed air 1 HEATER FUEL FILTER NOTE Airplanes TC 1406 and After TE 847 and After and TH 176 and After do not have the heater fuel filter installed A fuel filte...

Page 105: ...s located under the copilot s seat WARNING Due to air quality control regulations being enacted in the United States R 12 and R 134a refrigerant cannot be vented into the atmosphere When performing ma...

Page 106: ...ut down the engine in accordance with the applicable Pilot s Operating Handbook d Relieve the system pressure by evacuating with a recycle servicing unit e Removethe oilfillerplug f Insert the dipstic...

Page 107: ...rrosion preventive compound 3 Chart 3 and should be changed after 20 to 25 hours of engine operation Replace with oil 6 Chart 3 which is used until oil consumption stabilizes The engines are equipped...

Page 108: ...tion and damage pnor to reinstalling Upon reinstallation the oil filter screen plug should be torqued to 500 to 520 inch pounds If slush deposits are heavy subsequent oil changes should be made at mor...

Page 109: ...GNETOS Ordinarily the magnetos will require only occasional adjustment lubrication and breaker point replacement CA UTION The internal automatic grounding devices used on the original S series magneto...

Page 110: ...nts c Remove the instrument wedge light TE 768 and After TH 1 and After by holding up and tilting the instrument then thru the instrument panel mounting opening remove the two screws that attach the f...

Page 111: ...conditions it may be necessary to inspect the filter daily A clogged filter reduces air flow and slows up the rotor causing improper gym indication due to a loss of gyroscopic inertia To replace the...

Page 112: ...located on the fonn ard side of each engine rear baffle The foam type filter shouM be removed each 100 hours washed in solvent and blown dry with low pressure shop air For TC 2003 and After TE 937 and...

Page 113: ...ment I Check the tank fluid level before each cold weather flight and refill with anti icer fluid 30 Chart 3 if necessary The tank should be drained and flushed twice a year NOTE The anti icer tank sh...

Page 114: ...the spring guide counter balance spring and spring gurde tube f Apply a small quantity of grease to the completely extended thrust screw I HYDROLOK If the hydrolok seat back adjusters need service the...

Page 115: ...ng thread lubricants the following rules should be observed a Clean threads before applying lubricant b Use only thin coats of selected thread lubricant c Apply lubricant to male threads only I On str...

Page 116: ...INTED SURFACES The materials for removing dirt grease and bug juice from the painted surface are easily obtainable such as a cellulose sponge or mild soap absolutely no synthetic detergents can be use...

Page 117: ...vision Cleveland Ohio For additional information concerning windshield cleaning refer to handbook A2 01335 included in the loose tool and equipment bag CAUTION Do not use gasoline benzene acetone carb...

Page 118: ...s AC Spark Ptugs IO 470 L REB37N HSR86L RHB37N HSR87LP RHB38E AC271 RHB36P AC281 RHB32N RHB33E IO 520 C IO 520 CB IO 550 C RHB32N AC271 RHB33E AC281 AC273 AC283 Indicates fine wire platinum electrodes...

Page 119: ...e and Oil I I Co Chestertown Md Anti icer Vacuum Resistant Rockwell 950 Rockwell Mfg Co New York NY Royce 32 Royal Eng Co Whippany NJ Brake Deicer Static Anti Seize Compound Federal Specification Armi...

Page 120: ...It is the responsibility of the operator user to determine the current revision of the applicable Military Specificat on prior to usage of that item This determination may be made by contacting the s...

Page 121: ...xxon Mobil L and S 3225 Gallows Rd Fairfax VA 22037 Aeroshell 22 Shell Oil Co One Shell Plaza P O Box 2463 Houston TX 77001 10 See Item 7 11 Grease MIL G 23827 A72832 Amoco Inc 2021 Spring Rd Oak Broo...

Page 122: ...lvent TT T 548 Toluol Toluene Obtain locally 21 Paint Remover Turco No 4260 Turco Products Inc Los Angeles CA 22 Epoxy Primer MIL P 23377 Obtain locally r I 23 Wash Primer IMIL C 8514 Obtain iocaliy I...

Page 123: ...Compressor No 5 Smelting Co West Norfolk VA Texaco Capella E Texaco Inc 135 East 42nd Street New York NY 36 Spray Adhesive No 77 Minnesota Mining and Manufacturing Co 3M Center St Paul MN 55101 37 Ad...

Page 124: ...stic 1008 B B Chemical Co 784 Memorial Drive Cambridge NE 69022 49 Corrosion Preventive MIL C 16173 Grade 2 Braycote 137 Castrol Inc Compound 16715 Von Karman Ave Suite 230 Irvine CA 92714 50 Water Di...

Page 125: ...Loctite 222 Loctite Corp 705 N Mountain Rd Newington CT 06111 1411 59 Retaining Compound Loctite 601 Loctite Corp 705 N Mountain Rd Newington CT 06111 1411 60 Cement EC1403 or 1300L Obtain locally 61...

Page 126: ...ce Highside Chemicals inc Detector Dye P O Box 3748 Gulfport MS 39505 71 Adhesive Sealant Loctite 209 Loctite Corp 705 N Mountain Rd Newlngton CT 06f11 1411 72 Locquic Primer Primer N Loctite Corp 705...

Page 127: ...macel Tape Corp New Brunswick NJ 85 Adhesive Mystic A103 Mystic Adhesive Products 2623 N Kildare Chicago IL 86 Cement EC2262 Manufacturing Company 3M Center St Paul MN 55144 87 Sealer MIL S 8802 Type...

Page 128: ...r gear box 1 Detail D MIL PRF 2105 Grade 75 300 hrs NOTE Check oil level by engaging and turning the emergency hand crank 1 2 turn to determine that oil is being picked up on the worm gear The oil lev...

Page 129: ...mtabhinge 1 Detail I VV L 800A Preferred 100 hrs LPS I CRC 3 36 WD 40 3 Aiieron trim tab clevis 1 Detail I VV L 800A Preferred 100 hrs LPS 1 CRC 3 36 WD 40 1 Aileron bellcranks 6 Detail J SAE 20 or SA...

Page 130: ...As Required 1 Heater iris valve 1 Detail Q MIL M 7866 As Required NOTES Any parts that rotate or slide metal to metal and have no other provision for lubricatton must be lubricated with SAE 20 or SAE...

Page 131: ...heel bearings is changed make certain that all affected areas are thoroughly cleaned before relubrication 12 Lubricate the aileron push pull rod ends in place at 10O hour intervals using SAE 20 or SAE...

Page 132: ...EVIEW o n LUBRICATION DIAGRAM TC 65B ANO AFTER bGI 5 F TE 959 TE 968 AND AFTER TCI THA1 TC 50 3 EXCEPT TC 371 DETAIL P i RIGHT AND LEFT SIDE 1 DETAIL I I DETAIL J p 121 2 I 3 On sun Iypa MrlCnIlnn li...

Page 133: ...Raytheon nircraft Company BARON 55 AND 58 SHOP MANUAL This Page Intentionally Left Blank Page SECTION 2 E23...

Page 134: ...ETAIL E I DETAIL F I 100188 s t 1 C N M L t i 3 I WCWTHDLEFT IW DETAIL P DETAIL Q O DETAIL C I DETAIL H I DETAIL I I DETAIL 1 TH lf HIUTH UBO SY 151 t TH41l AM AFTEA AljWT AM LEFT sn I I Rwurr AND LEF...

Page 135: ...Raytheon Aircraft Company BAR N 55 AND 58 SHOP MANUAL This Page intentionally Left Blank Page 50 31ro4 SECTION 2 E23...

Page 136: ...OF OIL REMOVE ONE OF THE NONADJUSTABLE ROLLERS SECTION 4 IF IT IS A SEALED ROLLER WITH THE SEALS INTACT REINSTALL THE ROLLER AND MAKE A MAINTENANCE RECORD THAT ME ROLLERS ARE SEALED AND DO NOT NEED L...

Page 137: ...ion and special Texaco Capella E instructions 500 Viscosity Oil Air Conditioner Refer to Section 10 for Refrigerant No 12 As required Refrigerant location and special instructions CHANGE Engine Oil Ac...

Page 138: ...tor Blower Filters Aft of FS 190 00 and fwd Backflow with Every 100 hrs of FS 49 00 E55 fwd of compressed air 39 00 58 DRAIN Main Fuel Cell Drains Lower side of nacelle Preflight Auxiliary Fuel Cell D...

Page 139: ...ng Too of each strut MIL H 5606 Hydraulic 100 hrs Gear Struts Fluid and Compressed Air Shimmy Damper Nose landing gear MIL H 5606 100 hrs Hydraulic Fluid Oxygen Cylinder Behind the cabin aft MIL 0 272...

Page 140: ...ircraft Engine Oil Sinclair Oil Company Sinclair Avoil Exxon Company U S A Exxon Aviation Oil E E BP Oil Corporation BP Aero Oil Quaker State Oil Refining Company Quaker State AD Aviation Engine Oil D...

Page 141: ...ch Co Akron OH 44318 I 2 EC870Glue St Paul MNMinnesota Mining and Manufacturing Co I 3 PermatexSealerNo 2 Kansas City KSPerm atexCo Inc 4 Presstite Sealer No 576 Presstite Keystone Engineering Co 3900...

Page 142: ...epth of ice Never attempt to chip or break frozen snow from the airplane If the a rplane has been hangared and snow is falling or there is active frost coat the airplane surfaces with an anti icing sO...

Page 143: ...reatment for anti icing must be completed prior to flight SAE TYPE I ANTI ICING FLUIDS UNTHICKENED TYPE FLUIDS SAE Type I fluids mainly provide protection against refreezing when there is no precipita...

Page 144: ...CKS FOR THE NEED TO DEICE The wings tail section and fuselage have to be checked far possible ice snow and frost accumulation If frost or ice has formed on the lower surface of the wing in the fuel ta...

Page 145: ...hen there is no precipitation These fluids are authorized for use on Baron 55 and 58 airplanes NOTE Raytheon Aircraft Company cannot accept responsibility for damage to the airplane finish windows rub...

Page 146: ...faces that are coated with glycol The mixture leaves a slippery film that is hazardous to walk upon h Take precautions to keep the solution from entering air ducts or cabin heater and ventilator ducts...

Page 147: ...af plants grasses perennial ground cover and woody plants Minor leaks or spills of deicing anti icing fluid in storage areas must be soaked up with an absorbent material such as sawdust vermiculite an...

Page 148: ...SECTION AIRFRAME...

Page 149: ...50 3 885 22 25S 66 550 9 875 00 000 _ ML FRONT 7 STAB ML REAR SPAR VERTICAL S PSIL Z_ FUSELAGE STA 273 750 55 i 6 206 60 340 59 330 3 960 66 000 1 66 800 36 150 AIRPLANE 70 340 73 000 36 s HORIZONTAL...

Page 150: ...llr_ 00 000 00 000 j ML FRONT SPAR L l l WL CSTAB 100 000 ML REAR SPAR VERTICAL STABILIZER FUSELAGE STA 273 750 59 000 7 55 500 60 340 53 000 80 26036 90036 150 IIAIRPLANE 66 000 1111 3 900 45 000 6 2...

Page 151: ...6 1009 9 875 j I 000 000 ML FRONT SPAR 7jl __ I fi ML REAR SPAR VERTICAL S SI_IZE STAB FUSELAGE S A 66 273 750 70 340 73 000 80 260 dl lr 80 34080 047 36 150 83 547 6 200 s Iv 94 094 108 281 III j I H...

Page 152: ...LER ARM 4 HORIZONTAL STABILIZER MOUNTING BOLTS 11 HINGE BOLTS FOR NOSE WHEEL STRUT 5 HEATER IGNITION IRIS VALVE AND 12 RUDDER TAB ACTUATOR BLOWER ASSEMBLY 13 NOSE BAGGAGE DOOR 6 TAIL CONE 14 AFT BAGGA...

Page 153: ...LEVATOR TAB CABLES GEAR RETRACT IDLER ARM 4 HORIZONTAL STABILIZER MOUNTING BOLTS 11 HINGE BOLTS FOR OSE k E__ 5 HEATER IGNITION IRIS VALVE AND 12 RUDDER TAB FICTU TDR BLOWER ASSEMBLY i NOSE BAGGAGE DO...

Page 154: ...UEL CELL TRANSMITTER 20 AILERON CABLE INSPECTION 6 NACELLE INSPECTION PLATE AND ACCESS 21 AILERON CABLE PULLEY TO ENGINE PLUMBING 22 AUXILIARY TANK ACCESS AUXILIARY FUEL CELL TRANSMITTER 23 AILERON CA...

Page 155: ...AIN FUEL CELL TRANSMITTER 20 AILERON CABLE INSpESilC 6 NACELLE INSPECTION PLATE AND ACCESS 21 AILERON CABLE PU _EV TO ENGINE PROPELLER ACCUMULATOR 22 AUXILIARY TANK ACCESS 7 PRESSURE REGULATOR 23 AILE...

Page 156: ...osition the wing tip to the wing and install the fasteners screws prior to TC 1916 TE 1071 and TH 680 rivets I TC 1916 and After TE 1071 and After and TH 680 and After WET WING TIP REMOVAL a Disconnec...

Page 157: ...connect aileron tab cables and aileron tab stops in left wheel well m Disconnect fuel lines between wing root rib and the fuselage n Disconnect the flap drive shaft at the motor and remove the clamps...

Page 158: ...rs on the hinge wire and using the pliers as both fulcrum and lever pull CAUTION Do not attempt to spin the hinge wire out with a drill motor the heating and expansion of the wire will cause it to sei...

Page 159: ...t the wing attach fittings and hardware as instructed under WING BOLT NUT AND FITTING INSPECTION WARNING Wing bolts that have reached their life limit 10 years after the initial inspection must not he...

Page 160: ...g in the wheel well Connect the aileron cables and install the roll pins in the inboard aileron cable pulley brackets Connect the aileron tab cables and aileron tab stops LH only j Connect the landing...

Page 161: ...TO 2 600 INCH POUNDS COAT THE COMPLETE BOLT L WASHERS WING FITTING BOLT BORES AND EXPOSED BOLT THREADS WITH MIL C161 GRADE 2 CORROSION PREVENTATIVE COMPOUND XCHECKWASHER FOR A SMOOTH CONTINUOUS OUTER...

Page 162: ...3 I il S II SJL 1111 1 1309098274 5 i S BOLT WING FITTING JVNAS143 10 WASHER J LFUSELAGE FITTING WET BOLT TORQUE 1 180 TO 1 300 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHERS WING FITTING BOLT BORES...

Page 163: ...50 05011 WASHER POSITION WITH RADIUS TOWARDS WING FITTING WET BOLT TORQUE 2 880 TO 3 000 INCH POUNDS COAT iHE COMLETE BCLT WASHER WING FITTING BOLT BORES AND EXPOSED BOLT THREADS WITH fi C Ei GRADE 2...

Page 164: ...ARDS WING FITTING WET BOLT TORQUE 2 480 TO 2 600 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHERS WING FITTING BOLT BORES AND EXPOSED BOLT THREADS WITH MIL C 16173 GRADE 2 CORROSION PREVENTATIVE COMPOUN...

Page 165: ...he wing attach nuts in the following order upper forward upper aft lower forward and lower aft There should be no gap between the fittings after the last nut Is torqued Torque each nut to the wet torq...

Page 166: ...ST REPEAT OR OLDER INSPECTION REPLACEMENT INSPECTION INITIAL INTERVAL AND INSPECTION REPLACEMENT CYCLE NOTE NOTE THE FIRST WING BOLT INSPECTION AT EACH REPLACEMENT INTERVAL FOR AIRPLANES FIVE YEARS OL...

Page 167: ...acking instructions Place a suitable cradle under each wing and a tail stand under the aft portion of the fuselage Defuel the wing loosen the remaining bolts and reposition the wing until the bolt mov...

Page 168: ...paint from this area Inspect the surface condition of each fitting focus special attention on the washer seat and bolt bore area If scoring corrosion pitting or washer impressions are discovered in th...

Page 169: ...ING LOCATIONS I ON THE SIDE OF THE FUSELAGE IMMEDIATELY ABOVE THE RH FORWARD AND AFT WING a3LT C VERS 2 ON THE WING IMMEDIATELY FORWARD OF THE LH FORWARD AND AFT WING BOLT COVERS 3 ON THE WING IMMEDIA...

Page 170: ...the following procedures are recommended for optimum detection of discontinuities in both bolts and nuts WARNING Improper operation of the magnetic particle inspection because of faulty equipment or...

Page 171: ...300 7 8 INCH 31 21NCH 7 900 718 INCH 3314 INCH 7 400 7 8 NCH 4 INCH 6 900 7 8 INCH 5 INCH 5 500 1 INCH 5 INCH 6 300 Amperage requirements is the ampere turns value divided by the number of turns on th...

Page 172: ...t be performed to determine if corrosion has occurred Wax or paint trapped between the edge of the skin and the exposed section of the spar cap should not be misinterpreted I as corrosion Ref Figure 1...

Page 173: ...EXcGGERATE3 CLARITY ANY ONE CF NY CCMaI INDICATORS ARE CAUSE 3R fi RirfS BOX SECTION SKIN SPAR CAP o L o RAISED AREPS CRACKS a a O i o 1P a a o a LEADING EDGE SKIN PAINT BUSTER e I THIS RIVET PAT ER...

Page 174: ...embly d On forward side of spar cover install screws to secure forward end of spar cover and install carpet e On aft side of soar cover install screws to secure aft end of spar cover and install carpe...

Page 175: ...y Chart 5 using the following inspection procedure a Remove the pilot s and copilot s seats and the carry through cover to obtain access to the front spar carry through structure b Thoroughly clean th...

Page 176: ...ROUND HUCKBOLTS CRACK g INSPECTION BETWEEN HUCKBOLTS LOCATIONS AREA AND ALONG THE RADIUS OF THE CARRY THROUGH WEB IN THE INSPEC TION AREAS INSPECIION AREA ooo a d80 o o O Z I 6 3i 1Ds ii o 0 a 80 8 8g...

Page 177: ...ted in Chart 6 within the next 25 flight hours or the next scheduled inspection whichever occurs first b A crack passing through two fasteners and extending beyond for less than 0 5 inch on both ends...

Page 178: ...E 1201 1 500 HOURS 500 HOURS TH 1 THRU TH 1475 1 500 HOURS 500 HOURS TH 1476 AND AFTER 3 000 HOURS 1 000 HOURS I Chart 5 Inspection Program For Repaired Structure INITIAL FREQUENCY OF SERIAL NO INSPEC...

Page 179: ...URE MODEL 855 TC 371 TC 502 THRU TC 1525 REINFORCEMENT EXCEPT TC 1471 AFT FRAME MODEL C55 TC 350 TE 1 THRU TE 451 EXCEPT TE 50 MODEL D55 TE 50 TE 452 THRU TE 767 MODEL 855 TE 768 THRU TE 896 MODEL 58...

Page 180: ...pin does not align with the holes in the center seat track it will be necessary to reposition the seat guides with shims Use shims as needed to center the locking pin with the holes in the seat track...

Page 181: ...in position and align the seat guides with the mounting track b Release the fore and aft adjustment lock and slide the seat onto the mounting track Engage the fore and ah lock and make certain the se...

Page 182: ...of the seat toward the front while the lever for the mechanical adjusters is at the base of the seat back Roton lock and Hydrolok servicing information may be found in Section 2 I VERTICAL ADJUSTING S...

Page 183: ...tteee Aircraft Company BARON 55 AND 58 SHOP MANUAL I SECTOR GEAR GAS SPRING RELEASE LEVER Jo ACTUATOR 1 j ROD TORQUE TUBE ADJUSTING LEVER Vertically Adjusting Seat Figure 18 E23 SECTION 3 Dec 51t04Pag...

Page 184: ...with clamps c Place the glareshield down in position making sure that it fits properly over the fasteners at the base of the windshield I d Secure the glareshield on both sides with the attach screws...

Page 185: ...the glareshield as outlined under GLARESHIELD REMOVAL I h Remove the attach screws securing the molding around the windshield and remove the molding i Remove the attach screws securing the trim above...

Page 186: ...e compartment h Replace the forward and aft coat hooks and secure with attach screws i Replace the trim above the flight compartment door and secure with the attach screws j Install the molding around...

Page 187: ...of the door Slowly close the door while applying a downward pressure on the doorstop until the stop is released from the door Ref Figure 20 g Remove the attaching bolts from each door hinge Ref Figur...

Page 188: ...in the open position operate the latching mechanism several times to ensure that the internal mechanism is operating smoothly and properly 2 With the door still in the open position rotate the inside...

Page 189: ...ided portion of the pin has extended through both the striker plate and the door opening frame to a minimum of 0 05 inch above the tapered area of the pin The latch pin must engage a minimum of 0 33 i...

Page 190: ...isconnect the lower aft latch pin mechanism from the operating tube c Rotate the tube to allow the bolt to protrude the proper distance NOTE When this is done the outside handle may protrude up to 0 2...

Page 191: ...E AFT PORTION OF THE HOOK WITHOUT RIDING ON IT FWD OVERCENTER ADJUSTABLE STOP SCREW UPPER OPERATING LINK O WHEN DOOR IS LATCHED THE FORWARD EDGE OF THE UPPER OPERATING LINK SHOULD BE LOWER OPERATING L...

Page 192: ...IL B GRIND OFF TOP OF PIN GUIDE IF REPUIRED TO A MAXIMUM OF 0 2 INCH AIRPLANES WITHOUT j KIT 36 4007 1 OA 36 4008 1 INSTALLED CUTOUT IN DOOR PAN STRIKER PLATE DOOROPENING FRAME PIN GUDE j 0 05 INCH MI...

Page 193: ...OOR POINT C CENTER OF PIN POINT B OF PIN 0 851N AFI i i od LOOKING OUTBOARD DETAIL t TH 1665 AND AFTER AND AIRPLANES M _UTELISIOI WITH KIT 36 4007 1 OR 36 4008 1 INSTALLED 0 03 TO 0 15 IN POINT C CENT...

Page 194: ...mechanism incorporates a bayonet type latching mechanism When the mechanism is actuated by turning the handle the bayonet points enter the door facing and hold the door securely in the closed positio...

Page 195: ...eral times A maximum pull of 40 inch pounds of torque should be required to actuate the door handle to the closed and latched position g Install the interior upholstery panel and install the door on t...

Page 196: ...ny BARON 55 AND 58 SHOP MANUAL ADJUSTMENT POINT I_ 1 LOCKING BFIR oo 20a 100 I to j LATCHING MECHANISM T BRACKET is L STOP BAYONET POINT LATCHING MECHANISM THOJB 991751AF Utility Door Figure 22 Page 4...

Page 197: ...to position the inside door shaft assembly to approximately 15 below honzontal when in locked position Ref Figure 24 TC 1608 and After TH 385 and After and TE 938 TE 943 and After Remove the necessar...

Page 198: ...WHEN IN LATCHED POSITTON DOOR EDGE COPILOT S DOOR HANDLE CORRECT AFT INCORRECT INSTALLATION II DOOR INSTALLATION II AFT EDGE II 000R EDGE UP II I UP BASE PLATE STEP FWD II ie II AFT DETAIL B B FREE PL...

Page 199: ...EMBLY AFTtl STOP DOWN TC 1 THRU TC 1607 TH 1 THRU TH 384 AND TE 1 THRU TE 942 EXCEPT TE 938 INSIDE DOOR SHAFT ASSEMBLY CLEVIS f _i 30 j TUBE ASSEMBLY AFT STOP DOWN TC 1608 AND AFTER TH 385 AND AFTER A...

Page 200: ...gthening the door latch connecting tube assembly NOTE By shortening the connecting tube assemblies the door will be pulled tighter against the door seal b To adjust the length of the connecting tube a...

Page 201: ...rocedure ADJUSTMENT OF THE FORWARD BAGGAGE DOOR Adjustment of the door is accomplished by readjusting the position of the latching mechanism striker plates at the bottom edge of the door frame Adjustm...

Page 202: ...the windshield in position and cleco in place using the pilot holes provided e Back drill the windshield frame using the existing holes in the canopy section as a guide f Remove the windshield clean a...

Page 203: ...ound the window d Remove the window FORWARD LH WINDOW INSTALLA TION TE 768 AND AFTER TH I AND AFTER a Clean the sealet from the canopy section where the old window was removed using toluol 20 Consuma...

Page 204: ...in Step b d Place the window in position and cleco in place using the pilot holes provided e Back drill the window frame using the existing holes in the canopy section as a guide f Remove the window...

Page 205: ...aching holes and riveting the window in place e Back drill the window frame using the existing holes in the door as a guide f Remove the window clean and deburr all holes and apply sealer 4 Sealing Ch...

Page 206: ...access to the window frame b Remove the trim strip from around the inside of the window c To facilitate installation mark the location of the trim strip clips d Removetherivetsfrom aroundthewindow e...

Page 207: ...001 or their equivalent for the patch in accordance with the manufacturer s instructions Make sure that your hands are free of oil grease or dirt when handling the resin d Apply an even coat of resin...

Page 208: ...SECTION FLIGHT CONTROLS AND SURFACES...

Page 209: ...lot s pedals the same lever can be used to place the copilot s pedals against the floor The wing flaps are operated by an electric motor driven gearbox on the forward side of the rear spar at the cent...

Page 210: ...ght rawhide or nylon mallet to set the pin The small end of the tapered shank must be flush with or extend no more than 0 06 inch above the surface I cnunon I CAUTION The taper pin can crack the torqu...

Page 211: ...ement d After the adjustments are complete check the location of the control wheel sprockets and turnbuckles Refer to Figure 4 1 e Safety wire the turnbuckles NOTE Airplane serials TC 1482 through TC...

Page 212: ...BARON 55 AND 58 SHOP MANUAL ii jr_C I u __ LONG CHAIN ACCESS OPENING TURNBUCKLE SHORT CHAIN SLOT IN SPROCKET C9201738 Single Throw Over Control Column TC 1 and After TH 1 thru TH 1388 TH 1390 thru TH...

Page 213: ...control arm control wheel and sprocket as shown in Figure 4 2 b Center the long and short chains on their sprockets within one link c The slot in the center sprocket must be approximately vertical Ref...

Page 214: ...OPPOSITE SLOT IN SPROCKET LONG CHATN I I riONS CHhT A TURNBUCKLES UST SHORT CHAIN BE OPPOSITE RIGHT LEFT VIEW LOOKING AFT RIGHT LEFT DETAIL A FWD C9201739 Dual Control Column Chains TC 1 and After TE...

Page 215: ...ed marks on the chain must align with the corre sponding marks on the sprockets b Install the link assembly Install the control column chain in the outboard holes of the link assembly c Install the ai...

Page 216: ...UPPORT 8 BOB WEIGHT ASSEMBLY 9 COLLAR 10 COLLAR ASSEMBLY 11 ELEVATOR PUSHROD 12 CONNECTOR 13 INNER COLUMN GUIDE 14 INNER COLUMN TORQUE TUBE 15 UJOINT 20 21 1G SPROCKEFSUPPORT 19 18 SPROCKET I 17 TAPER...

Page 217: ...control column chain near the airplane centerline e Rig the aileron control system as described in RIGGING THE AILERON CONTROL SYSTEM CONTROL COL UMN ROLLER ADJUSTMENT FORWARD OUTER TUBE ROLLERS ROLL...

Page 218: ...UMN SUPPORT ROLLER ADJUSTMENT ATTACHED TO THE INSTRUMENT SUBPANEL The top two rollers of each control column support are installed with eccentric bolts which may be used for adjust ment Check the roll...

Page 219: ...or CRC 3 36 LPS 1 or WD 40 50 Consumable Materials Chart Section 2 a Attach the bonding cable to the aileron b Place the aileron in position on the hinge brackets The hinge brackets must be in the co...

Page 220: ...change to the position of the control wheel using a spirit level protractor e Adjust the turnbuckles in the wheel wells to bring the right and left ailerons to neutral f Adjust the travel stops prima...

Page 221: ...AIL F r 40 O bD 70 8 90 1 Y 110 TEhBERATURE F CABLE NSIONS BASED ON 58 AMBIENT AR TE PERATUCIE W S 34 n5 TEMPERATURE CABLE TENSION GRAPH TEMPERATUPL CABLE TENSION GRAPH H 14 AND SP 3 AIIT OPLOT ALWON...

Page 222: ...Raytheon Aircraft BEECH BARON 55 AND 58 SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4 14 E16...

Page 223: ...be tween the trailing edges of the aileron and wing If the aileron is not in neutral adjust the length of the aileron push pull tube Loosen the locknuts on both ends and turn the tube to shorten or l...

Page 224: ...re both settings and return the trim tab actuator to the midpoint of the two extremes of travel This places the trim tab actuator in neutral e If the trim tab is not in neutral adjust the length of th...

Page 225: ...ERATU E_ B 40 BALANCE CABLE F r l 5TOP57 a DETAIL A 1 s 40 so 6070 cr 90 loo Ilo It G F W S 23 881 1 1 1 TEMPERATURE CABLE TENSK N CAAPH Ci AILERON IQC p0 AUTCPLOt A ERON CABLES TEMPERATURE CABLE TENS...

Page 226: ...Raytheon Aircraft BEECH BARON 55 AND 58 SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4 18 E16...

Page 227: ...ean all parts with solvent 15 Consumable Materials Chart Section 2 and inspect for cracks corrosion and distortion b Replace the bushings and any parts showing evidence of wear c Lubricate the actuato...

Page 228: ...tab free play Refer to Figure 4 9 a Securely lock the control surfaces to prevent movement of the ailerons Set the aileron trim tab in neutral b Use shot bags to hold the dial indicator check fixture...

Page 229: ...4 1 C81Q Indicator 1 6 IN 5 1 3 4 x 2 1 2 x 14 aluminum or equiv 6 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Die x 1 corrosion res stl 31 IN 8 1 1 4 28 nut 9 1 3 8 x S x 10 rubber 10 f 3 8 x 2 x 10 rub...

Page 230: ...e reading as D j Enter the recorded readings on a copy of Chart 4 1 and proceed as follows 1 Multiply B by 2 and record as 2B 2 Subtract A from 28 and record as X 3 Multiply D by 2 and record as 2D 4...

Page 231: ...cotter pin holes are not aligned continue tightening until the cotter pin may be inserted Do not tighten beyond 40 inch pounds d Torque the inboard hinge bolt to 30 to 40 inch pounds NOTE If cotter p...

Page 232: ...removed and the replacement skin installed on the elevator before the other skin is removed b Install the elevator in the holding fixture c Remove the forward outboard elevator tip cover d Remove the...

Page 233: ...levator structure and hold in place with Cleco fasteners p Rivet the skin to the elevator spar and ribs working from the center out to each end Leave the trailing edge loose NOTE 45 610005 14 channels...

Page 234: ...the elevator See BALANCING THE ELEVATOR ab Install the elevator on the airplane RIGGING THE ELEVA TOR CONTROL SYSTEM TC I AND AFTER TE I AND AFTER TH 1 THRU TH 1388 TH 1390 THRU TH 1395 FIGURE 4 11 NO...

Page 235: ...eel is moved forward the elevators must move down When the control wheel is moved aft the elevators must move up g Check the elevator downspring loads as described in the following procedure ELEVATOR...

Page 236: ...n 29 to 31 of up travel d Disconnect the elevator downsprings e Set the elevator controls in neutral To obtain neutral insert the short end of the fabricated tool in the control column hanger Refer to...

Page 237: ...0 NOSE DOWN F S 140 00 DETAIL E F S 11850 EY 20 Ajon CABLE 10 50 20 30 40 50 60 70 80 90 100 110 j ELEV UP cn 50 ELEV DOWN o u 40 NOSE DOWN 03 n 40 NOSE UP ELE i70R o r axi uC 20 E s U pER 30 O H i ss...

Page 238: ...Raytheon Aircraft BEECH BARON 55 AND 58 SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4 30 E16...

Page 239: ...70 so 90 tao NOSE DOWN S F S 118 50 s 112 000 TEMPERATURE CABLE TENSION GRAPH MODE 58 ELNATOR CABLES IENIPERATURE CABLE TENS1DN GRAPH vl40 H 14 AND SP 3 AUTOPILOT BRIATOR AND aRIAfOFI fAB CABLES DETAI...

Page 240: ...Raytheon Aircraft BEECH BARON 55 AND 58 SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4 32 E16...

Page 241: ...orque tube b Set the elevator trim tab control to 23 nose up c Adjust the tab actuator so that the actuator rod extends for two thirds of its total travel d Set the tab at 23 down and connect the push...

Page 242: ...equal in length d Wrap each end of the cable around the drum one full turn in opposite directions The end that wraps to the right wraps clockwise around the drum and the end that wraps to the left wr...

Page 243: ...ling edge of the horizontal stabilizer to gain access to the elevator trim tab actuator b Detach the tail cone disconnect the tail navigation light wire and remove the tail cone c Remove the access pa...

Page 244: ...OR SHEAVE ROTATED 90 DETAIL A O IDLER PULLEY TIE AND SOLDER I I II e A INDICATOR ORUM SHEA E r B I I Y1 TRIM TAB CONTROL WRAP 3 FULL TURNS WHEEL SHAFT TRIM ROTATED 90 CONTROL WHEEL DETAIL B 3 1YJD Ele...

Page 245: ...probability of unintentionally switching the actuators upon installation a Position the elevator trim tab actuator in the horizontal stabilizer and install the attaching hardware b Position the chain...

Page 246: ...ring 1 from the actuator housing 11 and pull the nut assembly 2 out of the housing b Remove the actuator screw 4 from the nut assembly c Drill out the rivets 12 and 13 and remove the spacer 5 and the...

Page 247: ...uator screw 4 that will rotate clockwise when screwed into the nut assembly 2 The trim tab actuator that will be installed on the right hand horizontal stabilizer shall have threads on the actuator sc...

Page 248: ...the nut assembly 6 IWARNINO WARNING The trim tab actuator to be installed on the left hand horizontal stabilizer shall have threads on its actuator screw 4 that rotate clockwise when screwed into the...

Page 249: ...hold the dial indicator check fixture so that the point of the dial indicator is 4 0 inches aft of the tab hinge line TE l and After TH 1 and After or 3 3 inches aft of the tab hinge line CTC 1 and Af...

Page 250: ...D 58 SHOP MANUAL 9W e CHECK NUT 2 BUSHING 8 3 NUT ASSEMBLY 4 HOUSING 5 ACTUATOR SCREW 6 COLLAR 7 i 7 RETAINER RING O ci 8 CAP DETAIL A C Elevator Trim Tab Actuator TC 1144 and After TE 618 and After T...

Page 251: ...ed FOR TAB HORNS WITH BRAZED IN BUSHINGS a Carefully grind or spot face the brazed in bushing flush with the sides of the tab horn NOTE Maintain the bushing centerline as nearly perpendicular as possi...

Page 252: ...C81Q Indicator 1 6 N 5 1 3 4 x 2 112 x 14 aluminum or equiv 6 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Die xl corrosion res stl 31 IN 8 1 1 4 28 nut 9 1 3 8 x 5 x 10 rubber 10 1 3 8 x 2 x 10 rubber 12...

Page 253: ...the trim tab tube centerline as possible a Drill and ream the existing hole in the tab horn to an inside diameter of 0 3745 0 3760 inch b Using a clean rag dampened with solvent 19 Consumable Material...

Page 254: ...the horn and bushing together use care not to squeeze out all of the adhesive g Remove the existing rod end and locknut from the tab pushrod assembly at the tab horn end and replace it with a P N 96 6...

Page 255: ...osition This will ensure adequate free cable on the drum in both directions to allow full travel on the cable stops MAGNETIC CLUTCH REMOVAL a Remove the lid from the clutch housing b Loosen the setscr...

Page 256: ...e the access plate from the clutch housing and blow the housing and clutch clean with clean dry air 6 Using a regulated power source set at 14 to 16 vdc connect the red electrical lead of the clutch t...

Page 257: ...ab cables at the turnbuckles Install the cable retainer pins and fairlead d Check the travel of the tab and rudder tab indicator to see that the tab and indicator agree e Install the tail cone and con...

Page 258: ...DER TRIM TAB RIGGING I FIGURES 4 19 AND 4 20 NOTE Seech recommends the use of the rudder trim tab travel gage shown in the GENERAL INFORMATION section of this manual a Set the rudder trim tab control...

Page 259: ...30 40 50 60 70 80 90 100 110 TENPERAfURE F SYSTEM CABLES ARE RIGGED RUDDER TAB CABLE STOPS 7 0 z RUDDERLEFT UDDER 3z60 TAB RIGHT P B DETAIL C 50 40 RUDDER CABLE rRIGHT RUDDER CABLE 30 DETAILA B RUDDER...

Page 260: ...Raytheon Aircraft BEECH BARON 55 AND 58 SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4 52 E16...

Page 261: ...M CABLES ARE RIGGED DETAIL D F S 233 50 RUDDER TAB LEFT g 3 I b RUDDER TAB RIGHT sO P RIGHT RUWIR CABLE FWDI 50 LEFT RUDDER CABLE RUDDER TAB RIGHT 40 ItFWDt TAB CABLE STOPS b 30 DETAIL A TAB LEFT DETA...

Page 262: ...Ray heon Aircraft BEECH BARON 55 AND 58 SHOP MANUAL THIS PAGE INTENTIONALLY LEFT BLANK 4 54 E16...

Page 263: ...rmly against the skin contour to fair the rudder to neutral O c Mark the point on the tail cone that corresponds to the bottom corner of the rudder trailing edge Refer to Figure 4 22 d The points used...

Page 264: ...olvent 15 Consumable Materials Chart Section 2 and inspect for cracks corrosion distor tion and excessive wear b Replace bushings and any other parts showing evidence of wear c Lubricate the actuator...

Page 265: ...stall the actuator rod end 2 on the actuator screw and tighten the check nut 1 Safety wire the check nut to the actuator rod end i Check that the end play between the actuator screw and the housing do...

Page 266: ...actuator This is the point of pressure against the tab by the push pull scale d Apply another piece of masking tape in the corresponding location on the other side of the tab e Set the dial indicator...

Page 267: ...NSTALLATION a Position the vertical stabilizer and install the bolts as follows 1 On airplanes TO 1 through TC 2456 TE 1 through TE 1201 and TH 1 through TH 1483 torque the bolts at the forward spar a...

Page 268: ...equiv 4 1 C81Q Indicator S 1 3 4 x 2 1 2 x 14 aluminum or equiv 1 6 IN 6 114 Dia x 2 corrosion res stl 31 IN 1 7 1 1 4 Die xl corrosion res stl 8 1 1 4 28 nut 9 1 3 8 x 5 x 10 rubber 10 1 3 8 x 2 x 10...

Page 269: ...ials priorto TC 2457 except TC 350 torque the bolts to 85 100 inch pounds On TE TH and TC serials TC 350 TC 2457 and After torque the fonnrard spar bolts to 200 225 inch pounds dry and torque the rear...

Page 270: ...Measurement A measurement of the force applied by the aileron surface on a single support at a known distance from the centerline of the hinge NOIE Counterbalancing is the simplest method of check ba...

Page 271: ...pounds The product of W X D In this instance M is within the required static balance range and is therefore acceptable The painted aileron assembly must be nose heavy by 0 2 to 1 5 inch pounds If the...

Page 272: ...IZONTAL LI LEV ACTUAL ORCE MEASURMENT METHOD A MASKING TAPE TO SECURE TAB A IN NEUTRAL KNIFE ED G E O MASKING TAPE STEEL TUBE WITH PIG PLACE NEAR AILERON HINGE LINE LEAD ONTAINER 10 MUST BE HORIZONTAL...

Page 273: ...tor assembly b Actual Force Measurement A measurement of the force applied by the elevator surface on a single support at a known distance from the centerline of the hinge FORCE MEASUREMENT METHOD I C...

Page 274: ...LANCING PROCEDURE COUNTERBALANCING M ETHOD I COUNTERBALANCING METHOD CHECK BALANCE BY COUNTERBALANCING I The equipment required to perform the check balance by counterbalancing is a follows a A stand...

Page 275: ...ntents and string then weigh them NOTE Since any weighing error is magnified by the distance D weighing is most important and must be done carefully on scales that are certified for accuracy h Calcula...

Page 276: ...R ELEVATOR HINGE LINE CONTAINER VIEW A A TOP FORWARD SCREW JIG MUST BE HORIZONTALLY LEVEL FOR UNDERBALANCE CHECK A B MASKING TAPE ZCONTAINER DETAIL B MASKING TAPE TO SECURE fAB II ELEVATOR HINGE CLEVI...

Page 277: ...Tail heaviness indicates static underbalance while nose heaviness indicates static overbalance CHECKING BALANCE The rudder balance must be checked in a draft free area with the rudder completely asse...

Page 278: ...point supported by the spindle g Ensure that the spirit level and rule are removed from the surface and read the reaction on the beam balance h Calculate the static underbalance moment M from the form...

Page 279: ...ust be perpendicular to the hinge line Measure D from the hinge line to the suspension point of the cup g Remove the cup contents and string then weigh them NOTE Since any weighing error is magnified...

Page 280: ...RUDD6RI CONTAINfR HINGE LINE TO SECURE TAB IN NEUTRAL o P KNIFE EDG E ACTUAL FORCE MEASUREMENT E CONTAINER VIEW A A JIO MUST BE HORIZONTALLY LEVEL JIO MUST BE HORIZONTALLY LEVEL STATIC UNDERBALANCE I...

Page 281: ...llers in the other track b Connect the bonding cable and install the bolt in the flap actuating arm FLAP TRACK WEAR LIMITS The allowable track wear on the bearing surfaces is 0 032 inch resulting in a...

Page 282: ...et and installed on the outboard side of the inboard flap track in the left wing They are accessible by lowering the flaps IcAuTlon i CAUTION Operation of the flap motor without adequate cooling can d...

Page 283: ...L INFORMATION section of this manual Place the travel gage on the flap just aft of the flap actuator Four limit switches tone for up position two for approach position and one for down position contro...

Page 284: ...e flaps to indicate intermediate positions Airplanes with serials after those noted above used lights to indicate all of the flap positions An adjustable transmitter for the flap position indicator is...

Page 285: ...g at the quick disconnect s j Remove the flap motor attaching bolts and remove the flap motor Airplane serials TC 1 through TC 2002 TE 1 through TE 1083 and TH 1 through TH 772 have a ground wire atta...

Page 286: ...ing bolts Install the ground wire b Connect the motor electrical wiring at the quick disconnect s NOTE A retainer has been added to the flap cables where they join the flap gear box This retainer may...

Page 287: ...nd secure with the set screw 11 d Fill the gearbox with lubricating grease 11 Consumable Materials Chart Section 2 e Install the gasket 7 and cover 8 on the gearbox and secure with the attaching screw...

Page 288: ...27 25 i o 8e r 3 9 10 f or i 11 BW 23 26 22 1 u fq 12 13 14 151b17 20 1 24 1 Flap Motor Housing 14 Worm and Gear 2 Armature Bearing 16 Counter Shaft Bearing ij 15 Thrust Washer 3 Oil Seal Collar 4 Oil...

Page 289: ...e landing gear and remove the airplane from the jacks h Installthe sparcover i Install the front seat assemblies FLAP INNER FLEX SHAFT REMOVAL FIGURE 4 32 a Place the airplane on jacks and retract the...

Page 290: ...n be noted at this time NOTE A retainer has been added to the flap cables where they join the flap gearbox This retainer may have been on production airplanes or added by Beech Service Bulletin No 246...

Page 291: ...piston 7 out of the housing 8 and unscrew the actuator screw 9 from the piston d Remove the O ring 16 from the housing NOTE The following step is necessary only if the piston plug 3 must be replaced...

Page 292: ...the piston plug and pin with primer 24 Consumable Materials Chart b Install the O ring 10 into the housing 8 c Pour 2 3 ounce of gear lube 7 Consumable Materials Chart into the threaded end on the pis...

Page 293: ...UATOR SCREW 6 PISTON 7 HOUSING PIVOT BOLT HOLES 8 HOUSING 9 HOUSING BARREL INSIDE DIMENSION 10 PISTON PLUG HOLE CONNECIS FLAP TO ACTUATOR II PISTON PLUG 12 O RING 13 HOUSING END HOLE 14 PIN 4 15 PISTO...

Page 294: ...SECTION LANDING GEAR AND BRAKE SYSTEM...

Page 295: ...AND AFTER TH l AND AFTER On serials noted above the brake linings should be replaced before the metal back plate is exposed through the abrasive surface Ref Figure 1 This can be checked visually witho...

Page 296: ...INING ON SOME AIRCRAFT DETAIL B ANVIL SIDE LINING BRAKE BLEEDING I _ PISTON SIDE LINING 8 1 I DISC BRAKE HOUSING AIRCRAFT SERIAL TC 423 THRU TC 662 SOURCE OF COMPRESSED AIR I TC 664 THRU TC 978 TC 960...

Page 297: ...tional dual brake system the copilot s brake system is bled by closing the valve on the pressure pot and pumping the copilot s brake pedal to change the shuttle valve position This causes hydraulic fl...

Page 298: ...THE WHEEL AND BRAKEASSEMBLY CLEVELAND TC 371 TC 6 3 TC 979 TC 984 TC 999 AND AFTER EXCEPT TC 1002 TE 1 AND AFTER a Clean the wheel bearings with solvent 15 Consumable Materials Chart Section 2 and re...

Page 299: ...ining apply a screwdriver or a similar prying tool between the retaining plate and the lining the lining should then pop off Replace the lining by fitting a new lining section over the locating pins i...

Page 300: ...by tread wear so there is no increase in tire diameter Raytheon Aircraft Company cannot recommend the use of recapped tires on the Baron models The tires may pass the retraction test when first instal...

Page 301: ...s with hydraulic fluid 13 Consumable Materials Chart Section 2 NOTE During assembly install new washers and seals b Install the valve assembly 13 and spring 17 into the housing 18 c Install the valve...

Page 302: ...Consumable Materials Chart Section 2 NOTE During assembly install new washers and seals b Install spring 16 into housing 17 c Install O ring 12 on piston 13 d Install piston 13 on shaft 3 e InstallO r...

Page 303: ...NG 12 COTTER PIN 3 SHAFT II O RIIUG 4 RETAINING MODIFIED 4 SNAP RING 12 O RIr jG WASHERS 13 VALVE ASSEMBLY 5 O RING 13 PISTON 5 ROD WIPER 14 VALVE STOP 6 CAP END 14 SPRING 6 GUIDE BUSHINGS 15 SPRING W...

Page 304: ...ve housing f Clean all parts in solvent 15 Consumable Materials Chart Section 2 and air dry all parts g Place a new O ring inside the brake valve housing h Check the valve seat for wear and distortion...

Page 305: ...t to the throttle position waming switch must also be in the open position This microswitch is actuated by the throttle control when the throttle is advanced sufficiently for the manifold pressure gag...

Page 306: ...normally require adjustment Because of the built in tolerance of these switches they should not be tampered with unless radically out of adjustment that is unless the switch in question fails to actua...

Page 307: ...ry the emergency landing gear actuator handcrank must always be disengaged when operating the gear electrically Before starting the rigging procedure place the airplane on jacks and start the retracti...

Page 308: ...p Inch the gear the remaining distance to the limit switch by the momentary operation of the circuit breaker Check the hand crank for 3 8 to 1 2 turn between retracted position and the internal stop f...

Page 309: ...adjust the nose gear tension at the aft retract rod shorten or lengthen to obtain deflection force of 55 Ibs or higher providing the retract spring does not stack at any point during the full travel o...

Page 310: ...ivates at I approximately 11 in of manifold pressure Refer to the procedure for adjustment of Throttle Warning Horn Switch contained in this section t Run gear up and check landing gear position indic...

Page 311: ...the retract system By lengthening the retract system By lengthening the retract rod c Insert the retract arm retract rod attach bolt pointing aft d Disconnect the up lock cables at the brackets leavin...

Page 312: ...ough to clear the inboard door in addition to maintaining the minimum of 1 16 in clearance To decrease the clearance between the knee and the top wing skin shorten the retract rod to increase clearanc...

Page 313: ...the main landing gear fully retracted and the uplock in the locked position rig the uplock cable to the tension of 52 10 0 Ibs Take the tensiometer reading on cable just inside of cabin w Connect the...

Page 314: ...the small jack from wheel Pull Landing Gear circuit breaker Disconnect the left safety switch operating arm at the I torque link and position to simulate an on ground position Select GEAR UP check fo...

Page 315: ...NUAL a rror M li GI l iNIO IO 0001 OIUIIUWI IH GL l WllOlsO 0001 IDIUIIYIWI NOlt WHIII IHIMMI e I rr r 5 w NOlt GI I DOOl DMIYrUr Y 010 CHIIlING M IN 0 I DOWN LOCI I MION MIIN 7 o i i ulm taut i vim r...

Page 316: ...o facilitate assembly a With the airplane on jacks retract the landing gear until the inboard door is in the fully open position b Disconnect the outboard landing gear door from the landing gear strut...

Page 317: ...ar may help align the lift leg c Install the access door in the lower wing leading edge d Install the stainless steel exhaust shield to the lower surface of the wing e Install the bolt attaching the l...

Page 318: ...ve assembly 1 1 Ref Figure 8 To prevent damage remove all hydraulic plumbing safety switch components and clamps d Remove the main wheel and brake assembly Refer to Section 5 REMOVING THE WHEEL AND BR...

Page 319: ...the allowable wear tolerances Refer to Chart 1 Damage which cannot be corrected or repaired Screws that are severely damaged or have stripped severely worn or scored threads Parts that are cracked chi...

Page 320: ...caused by corrosion or removal of corrosion must not reduce the material thickness of any component by more than 10 Refer to Chart 1 for MAIN LANDING GEAR WEAR TOLERANCES AND INSPECTION PROCEDURES on...

Page 321: ...1 is covered approximately 2 pints of hydraulic fluid h Assemble the piston ring 16 to orifice head 15 and install into the cylinder assembly 10 Slowly extend lower shock assembly 37 allowing the suct...

Page 322: ...35 Visually inspect for wear damage and 1 593 1 8600 corrosion Replace if wear tolerances are exceeded Axle 36 1 498 Visually inspect for wear damage and 1 497 corrosion Strip and cadmium plate axle a...

Page 323: ...are exceeded Orifice Tube 11 1 560 Visually inspect for wear damage and 1 557 corrosion Any sign of scratches or worn areas which can not be repaired is cause for rejection Check the orifice O D does...

Page 324: ...n purposes or replacement Welded Brace 9 Hinge Bore 7 0 6275 Visually inspect for wear damage and 0 6245 corrosion If wear tolerances are exceeded contact the Technical Support Department of Raytheon...

Page 325: ...NG 20 SNAP Rlhle 17 21 PISTON 22 UPPER TORQUE KNEE 25 18 BUSHING 26 23 UPPER TORQUE KNEE BORE 20 24 UPPER TORQUE KNEE 29 27 PIN 21 25 UPPER TORQUE KNEE 31 26 LOWER TOROUE KNEE BORE I I U 27 UPPER TROU...

Page 326: ...ressing the valve core 2 Ref Figure 9 To prevent damage remove all hydraulic plumbing safety switch components and clamps d Remove the main wheel and brake assembly Refer to Section 5 REMOVING THE WHE...

Page 327: ...rt 2 Damage which cannot be corrected or repaired Screws that are severely damaged or have stripped severely worn or scored threads Parts that are cracked chipped or broken Parts that have corrosion o...

Page 328: ...o determine the depth of penetration and cross sectional area change The damaged area must be thoroughly cleaned and the corrosion must be removed The deterioration caused by corrosion or removal of c...

Page 329: ...ce 1 1 and cylinder assembly 9 using main landing gear brace bolts 14 g Raise and block lower shock assembly 35 1 4 in from the fully compressed position and fill cylinder assembly I 9 with hydraulic...

Page 330: ...Visually inspect for wear damage and 1 593 1 8600 corrosion Replace if wear tolerances are exceeded Axle 37 1 498 Visually inspect for wear damage and 1 497 corrosion Strip and cadmium plate axle as n...

Page 331: ...4360 Visually inspect for wear damage and 0 3120 0 4330 corrosion Replace if wear tolerances are exceeded Bore Lower 33 0 3175 Visually inspect for wear damage and 0 3125 corrosion Replace if wear tol...

Page 332: ...required remove the bearing from the cylinder assembly 9 and measure the O D Select from the O D dimensions below to determine the correct replacement bearing 1 2 3225 2 3215 in P N 35 815246 13 Stan...

Page 333: ...ace the cylinder assembly 9 If additional information is required contact the Technical Support Department of Raytheon Aircraft Company P O Box 85 Wichita KS 67201 If replacement of bearing is require...

Page 334: ...10 Bore 0 2520 Visually inspect for wear damage and 0 2495 corrosion Replace if wear tolerances are exceeded Aft Bolt 14 Bore 0 4425 Visually inspect for wear damage and 0 4370 corrosion Replace if we...

Page 335: ...UE KNEE BORE 21 UPPER TORQUE KNEE PIN 22 STOP 23 UPPER TORQUE KNEE 24 CENTER TORQUE KNEE BUSHING 15 ij 25 UPPER TORQUE KNEE BORE 26 FELT PAD 27 RETAINER RING 11 SCRAPER SEAL 12 28 PISTON 10 CHROME POR...

Page 336: ...nspect the wheel bearing grease for contamination and solidification at each periodic maintenance inspection d Inspect wheel halves for cracks corrosion and other damage Cracked or badly corroded cast...

Page 337: ...t its fitting on the nose gear brace assembly c Disconnect the steering mechanism at the nose gear d Disconnectthe landing lightwiring e Remove the nuts washers bolts and bushings which connect the no...

Page 338: ...1 b Depress the valve core to deflate the strut and remove the air valve assembly 1 c Remove the nose wheel Refer to Section 5 NOSE WHEEL REMOVAL d Remove the snap ring 4 retaining the orifice tube 6...

Page 339: ...jection Wear which is greater than the allowable wear tolerances Refer to Chart 3 Damage which cannot be corrected or repaired Screws that are severely damaged or have stripped severely worn or scored...

Page 340: ...ne the depth of penetration and the cross sectional area change The damaged area must be thoroughly cleaned and the corrosion must be removed The deterioration caused by corrosion or removal of corros...

Page 341: ...3 i Position shimmy damper 20 and install the bushing 18 bolt 21 washers l7 and 19 and nut 16 j Install the bushing 28 bolt 26 washer 27 and 29 and nut 30 to connect the shimmy damper 20 k Slide the p...

Page 342: ...n the soapsuds from the top of the collar 2 and air valve assembly l with fresh water u Install the air valve cap on the air valve assembly 1 v Install the nose wheel onto the axle 52 Refer to Section...

Page 343: ...cause for rejection Replace bushing as needed Upper Torque Knee 37 Bore 0 4380 Visually inspect for wear damage and corrosion Replace if 0 4370 wear tolerances are exceeded Bushing 35 0 3775 Visually...

Page 344: ...rosion Any sign of P N36 820021 1 436 scratches or worn areas which can not be repaired is cause for TC 2434 and After rejection Conduct a magnetic particle inspection per MIL STD 1949 Any sign of cra...

Page 345: ...ause for rejection Remove all bearings and inspect for corrosion Conduct fluorescent or dye penetrant inspection per MIL STD 6866 Any crack is cause for rejection Coat interior of brace and hinge bear...

Page 346: ...2 PIN 6 17 WASHER 43 BOii 24 18 BUSHING 44 WASHER 19 WASHER 45 BUSHING 20 SHIMMY DAMPER 46 LOWER TORQUE KNEE 21 BOLT 47 PIN 22 LOWER BEARING 48 PISTON AND 23 BARREL FORK ASSEMGLY n _ 1 24 FELT PFIO 49...

Page 347: ...ase the air pressure in the nose gear cut the safety wire and remove the air valve assembly 14 c Invert the nose gear and drain out the hydraulic fluid d Cut the safety wire and remove the bolts attac...

Page 348: ...fluid 13 Consumable Materials Chart Section 2 prior to assembly REPLACEMENT PARTS a Inspect all parts and assemblies for damage or excessive wear The following conditions are cause for rejection Wear...

Page 349: ...er to Chart 4 for NOSE GEAR WEAR TOLERANCES AND 1 INSPECTION PROCEDURES on components For additional information contact the Technical Support Department of Raytheon Aircraft Company P O Box 85 Wichit...

Page 350: ...n Maximum clearance is 0 010 in between the strut housing 15 and the gear brace 6 j Place the gear brace 6 in the vertical position Assemble the laminated shims 3 and spacer 4 in the upper strut housi...

Page 351: ...ent conduct fluorescent or dye penetrant inspection per MIL STD 6866 Any crack is cause for rejection Corrosion proof as necessary per M1L C 5541 and touch up paint as required Upper Torque Knee 18 Bo...

Page 352: ...cause for rejection Conduct a fluorescent or dye penetrant inspection per MIL STD 1966 Any sign of cracking is cause for rejection Check the I D of bushing does not exceed wear tolerances Lower Strut...

Page 353: ...ection per MIL STO 6866 Any crack is cause for rejection Coat interior of brace and hinge bearing hdes with corrosion preventative compound per MIL C 18173 Grade 1 or 2 Replace all bearings when nose...

Page 354: ...WASHERS NUT 10 14 20 TORQUE KNEE BUSH NG 21 TORQUE KNEE BUSHING 22 LOWER TORQUE KNEE 23 LOWER TORQUE KNEE RO L PI 24 TORQUE KNEE BUSMIN S II 25 TORQUE KNEE BUSHINS 26 ORIFICE ROD ASSEMBiV 15 I 1 17 1...

Page 355: ...ASSEMBLY 1 a Remove cotter pin 1 washer 8 and compression spring 9 by holding the washer 8 down with a small rod or screw driver so that the parts will not spring out when the cotter pin 1 is removed...

Page 356: ...Replace the following parts when nose gear shimmy damper is overhauled Ref Figure 13 Cotter Pin 1 Retaining Pin 15 O Rings 4 11 13 16 20 21 Safety Wire Snap Ring 2 Springs 9 18 Piston Scrapers 3 22 I...

Page 357: ...and the floating piston into the piston rod 12 With a long 6 32 screw or threaded rod engage the floating piston 17 by pulling it toward the clevis 24 so that the retaining pin 15 can be inserted Inst...

Page 358: ...d corrosion Replace 0 3745 if wear tolerances are exceeded Damper Piston 14 0 857 Visually inspect for wear damage and corrosion Replace 0 850 if there is any noticeable ridges or grooves at 0 ring se...

Page 359: ...EL 7 ATTACHMENT HOLE 8 WASHER 9 COMPRESSION SPRING 10 FLOATING PISTON II O RING 12 PISTON ROD 7 13 O RINGS 19 14 DAMPER PISTON 20 15 RETAINING PIN 21 16 O RING 22 17 FLOATING PISTON 18 COMPRESSION SPR...

Page 360: ...m 20 inboard arm 21 attachment bolts 22 washers 23 and nuts 24 for security Ref Figure 14 Check retract rod rod ends 59 and 90 for indications of cracking and the mechanism assembly for shear stress w...

Page 361: ...NUT 19 BUMPER 33 SPRING 6 COTTER PIN 20 OUTBOFIRD ARM 34 SCREW 7 LUBE FITTING AND BUSHING 21 INBOARD ARM 35 NUT 8 BOLT 22 BOLT 36 ROD END 9 BUSHING 23 WASHER 37 DOOR ACTUATOR 10 BUSHING 24 NUT ROD AS...

Page 362: ...I 63 RETRACT IDLER ARM ASSEMBLY 64 80LT 65 WASHER 66 NUT 72 67 COTTER PIN 68 BRAG1 ET 8 69 COLLAR 71 FLATHEAD P I N O WASHER 74 75 ti 72 COTTER PIN 63 73 IDLER ARM 70 69 74 BUSHING 71 75 BEARING 6B 7...

Page 363: ...6 WASHER 87 COTTER PIN 88 NUT 89 WASHER 90 ROD END 91 92 WASHERWASHER 93 RETRACT ROD LINK DECAL t sO 90 78 r c 93 85 88 89 d 92 91 82 86 87 i 81 DETAIL A 83 e DETAIL 8 aB a 5 Nose Gear Retract Mechani...

Page 364: ...t switch actuators are installed when the retract rods are connected to the actuator k Install cotter pins and safety wire i After completing the landing gear actuator installation check the landing g...

Page 365: ...he actuator drive shaft through the sector gear make sure the scribe marks on each piece match The same applies when installing the nose gear actuator retract arm and the main actuator retract arm on...

Page 366: ...RM SECTOR 26 11 SCREW 12 ACTUATOR HAND CRANK 3 13 SPACER 14 0 RING SEAL 2 15 SCREW 16 HAND CRANK SHAFT HOUSING 17 RETAINER NUT 18 HALF RING 21 LOCK NUT 28 ACTUATOR RETRACT ARM 19 WORM GEAR 26 BEARING...

Page 367: ...oose at the back end and screw the end fitting either in or out to make the adjustment NOSE WHEEL TRA VEL STOP ADJUSTMENT The travel stop must be adjusted so the nose wheel travel is stopped when the...

Page 368: ...ADJUSTMENT TC I AND AFTER Adjustment of the throttle warning horn may be accomplished as follows a With the airplane in flight place the propeller controls in the low pitch position and slowly retard...

Page 369: ...he landing gear up circuit to prevent the landing gear from retracting when the throttles are retarded below 15 2 1 in of Hg in landing gear frcm renacting when the throttles are retarded below 1512 t...

Page 370: ...RIGHT RETRACT GEAR PREVENT RETRACT SWITCH PREVENT SWITCH RETRACT PREVENT I THROTTLE SWITCH CAMS II WARNING CAMS DETFIIL A LEFT THROTTLE e WARNING SWITCH LEFT THROTTLE WARNING SWITCH ACTUATOR ROD QSKAW...

Page 371: ...stem a Bleed brake system 3 Unable to hold pressure a Leak in brake system a Visually check entire system for evidence of leaks b Check master cylinder seals replace if scored 4 Parking brake will not...

Page 372: ...e switch 5 Warning horn or GR UP a Open or grounded circuit a Check continuity I annunciator light ton TH 1543 TH 1545 and After inoperative or malfunctioning b Throttle switches inoperative b Check a...

Page 373: ...SECTION POVVE RPLANT...

Page 374: ...g ring of capacitor and ground the wire to the the engine engine case If grounding is impractical remove the cable outlet plate on the rear b Hoist the engine into position on the airplane of the magn...

Page 375: ...after and TH 1 and after Be If the fuel injector line nuts at the nonle are removed careful to align the holes in the rubber from the 10 470 or the 10 520 engine they should be mount bushings plates w...

Page 376: ...M d Remove the nut and bolt securing the wires Figure 6 4 together The throttle warning horn cam and switch are iocated e Push in on the knurled knob and rotating it coun on the left side of the engin...

Page 377: ...ottle body butterfly valve in the fully shaft closed position It is spring loaded to the open posi tion consequently it will have to be held in the fully e Install the roll pin closed position NOTE b...

Page 378: ...d after and TH I and after The oil pressure indicator was a direct reading instru ment on TH 1 thru TH 1395 except TH 1389 An elec The oil radiator is located at the left rear of each eng tric oil pre...

Page 379: ...TE I metering valve assembly and remove angles two and after and TH 1 and after from mounting bolts a Install the air box to the flex duct and tighten the I g Remove the air box clamp b Install the an...

Page 380: ...rod end on the actuator shaft to obtain nut Do not let the rod end turn when tightening the 1 1 inch of clearance between the trailing edge of locknut the cowl flap and the nacelle h Connect the contr...

Page 381: ...ce for the cowl flap is correct that the bellcrank assem NOTE bly is contacting the crank stop in both positions and If the opening is not 2 6 1 inch relo that there is a slight cushion effect on the...

Page 382: ...fter adjusting the idle unmetered pressure at 9to 11 psi check the idle mixture Advance the throttle to e The Mixture controls should remain in the FULL approximately 2 000 rpm to clear the engine the...

Page 383: ...ixture is e Adjust the idle speed to 625 to 650 rpm with the obtained by backing off the nut to lengthen the link spring loaded screw located forward of the air throttle age lever Turn the screw clock...

Page 384: ...moved toward the idle cutoff position If the mixture is The pressure gage should be vented to too lean the rpm will drop If an idle mixture adjust the atmosphere ment is required turn the idle mixtur...

Page 385: ...rect metered fuel pressure If a fuel pressure adjustment is At 80 pph flow rate with the fuel temperature at 40 F required turn the fuel bypass adjustment screw as an airplane fuel flow indicator read...

Page 386: ...INGS COOLING SHROUD ETC OMITTED FOR CLARITY 36 283 2 IO 470L WITH ADJUSTABLE ORIFICE PUMP IO 520C AND IO 520CB ENGINES RELIEF VALVE ADJUSTME1 I VSED TO SET pUMP IDLE s CSSU9E ANEROID ADJUSTMENT SCREW...

Page 387: ...RPM DROP OFF CHECK side of peak margin is not obtained readjust the metered engine fuel pressure refer to step d of FULL The purpose of the drop off check is to determine that THROTTLE FUEL PRESSURE A...

Page 388: ...i FVALUE SHOWN 3 PSIG i i i i A i c i 13 0 22 0 23 0 24 0 25 0 26 0 27 0 28 0 29 0 MANIFOLD PRESSURE IN HG 58 282 8 LOCATE MANIFOLD PRESSURE ATTAINED DURING FULL THROTTLE STATIC RPM RUN UP POINT A AT...

Page 389: ...MANUAL ENGINE DISTRIBUTOR ENGINE FUEL FLOW TRANSDUCER VALVE AND NOZZLES AIRPLANE FUEL FILLER PORT FLOW RATOR MUSI BE IN A STRAIGHI VERTICAL POSITION ADJUSTABLE VALVE c AIRPLANE WING P36 181 43 Figure...

Page 390: ...ph in Flow 80 pph 13 3 1 13 5 13 8 14 0 in example example gph gph gph gph Flow 90 pph 15 0 15 3 15 5 15 8 gph gph gph gph Flow 110 pph 18 3 18 6 19 0 19 3 gph gph gph gph Flow 120 pph 20 0 20 3 20 7...

Page 391: ...crankshaft flange plugs d Turn the crankshaft to find the top dead center of g Shut down the engine to idle then off the number one cylinder on the compression stroke Align the zero degree mark on the...

Page 392: ...der with the before TDC The light should go out at 20 0 2 thumb and turning the crankshaft until pressure is felt before TDC on the thumb If the preceding procedure is used and the magnetos d Remove t...

Page 393: ...ING PREPARING THE SLICK MAGNETO FOR It is assumed that the magnetos have been internally timed properly with the points adjusted per the appli INSTALLATION ON THE ENGINE I cable Bendix or Slick vendor...

Page 394: ...lower spark plug hole of No 1 cylinder flange and engine crankcase parting surface or marks with thumb and turn the crankshaft until pressure is on the generator alternator drive pulley to position fe...

Page 395: ...until the timing marks are holding washers lock washers and nuts but tighten aligned At this point both timing lights should go out only enough to permit turning the magneto without at the same insta...

Page 396: ...a method for adjusting the magneto con to the oilite bearings tact points since a weak spark will result if the open ing of the contact points is not in time with the occur CYLINDER DIFFERENTIAL rence...

Page 397: ...fuel noule if no fuel shows replace fuel manifold valve 2 Engine starts but fails to keep a Inadequate fuel to fuel manifold a Set fuel control in FULL RICH I running valve position turn auxiliary pu...

Page 398: ...d electrodes improperly adjusted electrode gaps and cracked porcelains Test plugs for regular firing I under pressure Replace damaged or misfiring plugs Spark plug gap should be 0 018 to 0 022 inch c...

Page 399: ...use wire as probe Replace defective parts 10 Low oil pressure on engine a Insufficient oil in oil sump oil a Add oil or change oil to proper gage or high oil temperature dilution or using improper gr...

Page 400: ...SECTION PROPELLER...

Page 401: ...center of the engine crankshaft and propeller hub to prevent foreign material from contaminating the engine or propeller INSTALLING THE PROPELLER MCCAULEY a Make sure the propeller and engine flanges...

Page 402: ...rial from contaminating the engine or propeller INSTALLING THE PROPELLER HARTZELL a Clean the propeller and engine flanges removing any possible nicks which would prevent proper mating of the surfaces...

Page 403: ...governor h Covertheengine boss PROPELLER GOVERNOR INSTALLATION a Remove the cover from the engine boss wipe the engine pad clean and install a new governor mounting pad gasket I cnuTloN 1 CAUTION Mak...

Page 404: ...the propeller back to row rpm The point at which propeller feathering starts should be at 1850 rpm If adjustment is required turn the square head screw on the end of the governor control shaft inward...

Page 405: ...difference in pulse rates and changes the governor speed setting by varying the coil voltage of each governor until the rpm of each engine is equal The pro peller synchronizer may be turned ON by a t...

Page 406: ...eceptacle is properly mated with the plug in the airplane electrical system b Unplug the control box turn the airplane master switch OFF and pull the propeller synchronizer circuit breaker before proc...

Page 407: ...eak to peak at maximum cruise rpm NOTE These readings are based on a magnetic pickup toothed wheel clearance gap of approximately 0 005 inch If adjustment is required refer to the Woodward Test Specif...

Page 408: ...lator from the airplane Installation is the reverse of the removal procedures NOTE The pressure in the accumulators should be maintained at 100 5 psi When inflating the accumulators use commercial dry...

Page 409: ...overnor pins 1 3 e Left governor coil gives open e Broken or grounded wire in e Repair or replace broken wire or replace or short reading on pins 6 7 coil Coil defective governor f Right governor coil...

Page 410: ...SECTION FUEL SYSTEM...

Page 411: ...ons usable in each vlng fuel quantity indicators on the instrument panel indicate the system or a total of 16h gallons usable with left and right amount of fuel in either the main or auxiliary fuel ce...

Page 412: ...ition to The function for fuel management and the fuel selector the flush type filler cap in the outboard end of each outboard panel remote fuel controls fuel selector valves and fuel wing leading edg...

Page 413: ...J gallons usable with left and ri ht systems full One flu h 6 snap type drains 3 drains per wing are provided One type filler cap is in each wet wing tip rank in addition o rh drain in each wing is pr...

Page 414: ...airplane Goodyear fuel inspection and cleaning wiildepend upon service conditions cells manufactured prior to 1961 and fuel handling equipmenl cleanliness and local sand and dust fuel cells must be fi...

Page 415: ...u iC1607 FUEL S R INER TE I Ihru TE 942 80051 PUMP iEl ihru TEM2 irr iEe38 eice TE 938 I n3 V i LUI T1 Y13 ENGINE D IVth FUEL PUMP Y 1 1 i IM IN I ut i lu uii i 5528lP21 Figure 8 1 Fuel Synem TC 1 thr...

Page 416: ...INJLCTOI PUMP I I NlrC O OI LN OP IN i r I I T I I I caoss I XFUEL 1IR INER u irED I r I INES To C BIN HE TEI I I Y uxlllaar 1 PUMP s IMP I I I oq l I II I I 1 I TC 251 TC 371 TC 421 j 1 I THRU TC 60...

Page 417: ...PS AND HEATER Figure 8 3 Fuel System 142 Gallon Capacity 136 Gallons Vsable TC 1608 thru TC 2002 except TC t 970 TE 938 TE 9 3 thru TE f 083 except TE 1081 FUEL RETURN n FUEL LINE FUEL HEATER DISTRIBU...

Page 418: ...Capacity 136 Gallons Usable TC 1970 TC 2003 and after TE 1081 TE 084 and after TH 1 thru TH 384 TH 766 TH 773 and alter FUEL RETURN n FUEL I I HEATER FUEL LINE DISTRIBUTOR FUEL SUPPLY PUMP HEATER FUEL...

Page 419: ...n Capacity 166 Gallons Usable TH 385 thru TH 772 except TH 766 I FUEL RETURIJ n FUEL HEATER 9 FUEL LINE ENGINE DISTRIBUTOR FUEL SUPPLY DRIVEN PUMP ATER FUEL PUMP IVENT LINE WITH FUEL FI LTE R MECHANIC...

Page 420: ...ure 8 9 Fuel System 200 Gallon Capacity 194 Gallons Usable TH 669 thru TH 772 except TH 766 II FUEL RETURN n HEATER FUEL LINE FUEL SUPPLY EONRF1 NE DISTRIBUTOR CIYENT LINE PVMP HE TER FUEL PU P WITH F...

Page 421: ...NE strainer to prevent damage to the fuel cell he Long finger fuel strainer approximately 9 inches is used only in the aerobatic reservoir type fuel cell as provided in Kit No 35 901 All other inboard...

Page 422: ...e interconneas Torque the nipple clamps to II I inch pounds on Uniroyal cells and 7 5 inch pounds on Goodyear cells REMOVING INBOARD LEADING EDGE FUEL CELL g Install the access covers TC 1608 and alte...

Page 423: ...is note does not apply to airplane serials TH i in the box thru TH j84 Prior to installing a new inboard leading edge fuel cell particular attention should be paid to the removable yellow tag which is...

Page 424: ...ease of installation place the fuel ceil in an should be paid to the removable yellow tag area where the temperature is at least hOOF and which is attached to the cell near the nipple allow sufficien...

Page 425: ...ter TE 1081 TE 1084 and after INSTALLING THE FUEL SELECTOR VAL VES TC 1 I thru TC 2002 except TC 1970 TE I thru TE 1084 except TE 1OB1 a Position the fuel selector valve and make certain the selector...

Page 426: ...ire cover plate screws 141 TC 148 TC 164 TC 166 TC l68 through j Do not apply grease or oil to gear TC 1607 TE I through TE 942 except TE 938 and prior airplanes incorporating Service Letter No 4 have...

Page 427: ...INSTALLED ON ALL AIRCRAFT 55 364 265 Figure 14 Wiring Diagram Oliginal Transmit ers BUS 95 38001 2 13 95 38001 2 15 INBOARD TRANSMITTER OUTBOARD TRANS TER 42 STUD FULL EMPTY n STUD nz sTvD nl STUD DA...

Page 428: ...securing the transducer or transmitter to the mounting When adjusting the fuel quantity gages to bracket and remove the two clamps Remove the register a F full reading make sure that transducer or tr...

Page 429: ...G THE MAIN CELLS in this section for further instructions on installing the fuel cell c Cut the safety wire and I elno e the att3c hin b tlrs from the fuel cell access plate NOTE Installation of Kit 3...

Page 430: ...j amp circuit breaker in the left subpanei and th i c licr functioning properly thoroughly wipe the area in the vicinity wrapped around the exposed ponion of the rn The of the flapper valve with an o...

Page 431: ...intenance Manual for Vithane Fuel Cells inspection which is published by Goodyear Aerospace Corporation Engineering Fabrics Division Rockmart Georgia When synthetic rubber fuel cells are placed in ser...

Page 432: ...Doubler material 051 2024 T3 Aluminum ALCLAD Nut Plates K5000 832 or equivalent Screws AN507 8R length to be determined Rivets AN426AD3 for attaching nut plates Rivets AN426AD4 for attaching doubler R...

Page 433: ...he under minutes side of the wing loosen the clamps on the 3 inch fuel inter d Apply leak testing compound MIL L t5567 Item connect and vent lines 14 Consumable Materials Chart to the outside of the w...

Page 434: ...eak Test Sa up TH 669 and after RUNNING LEAK 1 3 I f 3 4 DIA I o 4 c5 DIA STAIN 1 11 2 DIA o i i 6 MAX SEEP 3 1 2 4 DIA O I J_i AREA WHERE FUEL APPEARS TO FLOW OR RUN FOLLOWING CONTOUR Or SKIN WHEN TH...

Page 435: ...the fuel out of the system The following steps must be accomplished before energizing the pump Scarf the ends of the existing fillet so that a new sealant can form a continuous and smooth tie in PR 89...

Page 436: ...SECTION PRESSURIZATION...

Page 437: ...THIS SECTION IS NOT APPLICABLE TO THE BEECHCRAFT BARONS...

Page 438: ...SECTION HEATING AND COOLING SYSTEM...

Page 439: ...1 the control wire to the iris valve actuator arm The safety switch is positioned on the underside of the heater shelf in adjustable slots Pull the CABIN AIR control to the half open position and set...

Page 440: ...955 thru TC 1657 and TE thru TE 451 wiring diagrams On serials TE 1 thru TE 451 the points are placed in service by adding a 20 gage jumper wire between terminals A and B on the heater ignition unit O...

Page 441: ...i 15 13 ii i 11 AIRPLANE SERIALS TC4 THRU TC601 1 12 HEATER OVERBOARD FUEL LINE 24 11 13 COMBUSTION FUEL INLET LINE 25r 15 HEATER SHROUD DRAIN 14 HEATER EXHAUST ir 16 HEATER SPARK PLUG AY ili j 19 IRI...

Page 442: ...Ray heon Aircraft Company BARON 55 AND 58 SHOP MANUAL This Page Intentionally Left Blank SECTION 10 E20...

Page 443: ...OM BUSTION FUEL INLET LINE 13 HEATER EXHAUST I i t 14 HEATER SHROUD DRAIN P Atii C B 15 HEATER SPARK PLUG jf j 16 HEATER IGNITION LEAD ASSEMBLY 17 COMBUSTION AIR INTAKE DUCT 18 IRIS VALVE 19 INTAKE BL...

Page 444: ...Raytheon Aircraft Company BARON 55 AND 58 SHOP MANUAL This Page Intentionally Left Blank JP n9 2f SECTION 10 E20...

Page 445: ...pointed piece of wood I CAUTION I CAUTION Do not use a metal tool for cleaning the parts as it will alter the flow characteristics of the nozzle 5 When reassembling the spray nozzle tighten the core w...

Page 446: ...the blower and iris valve from the plenum d Disconnect the heater ignition lead from the spark plug and heater ignitor e Disconnect the combustion air flexible tubing from the combustion air inlet at...

Page 447: ...IOVING AND INSTALLING THE CABIN HEATER FUEL DISCHARGE NOZZLE a Remove the nose cone b Disconnect the combustion air flexible tubing from the combustion air inlet at the heater c Disconnect the heater...

Page 448: ...el filter clogged f Clean filter g Spray nozzle clogged g Clean spray nozzle h Insufficient combustion air h Remove obstructions or repair leaks Check for combustion blower operation i Faulty differen...

Page 449: ...r to Figure 3 A thermostat in the heater duct controls the duct temperature according to its setting which is varied by the push pull control CABIN HEAT in the subpanel When the push pull control is a...

Page 450: ...the lug and tighten the screw Make sure the guide lug on the ductstat switch is in the straight downward position before I securing the control wire The pilot s and copilot s air vent doors above the...

Page 451: ...T THERMOSTAT 6 PILOT S OUTLET 20 HEATER AND OR BLOWER SWITCH i HEATER FUEL PUMP 21 DUCT TO REAR SEAT OUTLET 8 OVERHEAT THERMOSTAT 3000F 22 PILOT S AIR CONTROL 9 FUEL VALVE 23 GO PILOT S AIR CONTROL 10...

Page 452: ...Raytheon Aircraft Company BARON 55 AND 58 SHOP MANUAL This Page Intentionally Left Blank JPuan9 2 b SECTION 10 E20...

Page 453: ...AND 58 SHOP MANUAL A B VIEW A METER B55 E55 HEATER HOUR 58 BAG AGE DOOR ROD L SUPPORT HOLE REF VIEWB 03S6et n Heater Hour Meter Installation TC 2389 and After TE 1191 and After TH 1253 and After Figur...

Page 454: ...stripper solution 2 Use a stainless steel brush or sandblast to remove any accumulation of carbon or other foreign material from the inside of the combustion chamber Clean thoroughly with compressed a...

Page 455: ...n tapping on live metal These soft spots will usually have a dull gray appearance indicating considerable surface oxidation The presence of soft spots is reason for rejecting the combustion chamber an...

Page 456: ...t the hot air duct on the heater e Connect the two heater drain lines f Connect the fuel lines to the heater g Replace the combustion air flex duct to the heater h Connect the exhaust pipe with the at...

Page 457: ...zzle clogged g Clean spray nozzle h Insufficient combustion air h Remove obstructions or repair leaks Check for combustion blower operation i Faulty differential pressure switch i With heater ON check...

Page 458: ...a Thermostat not properly adjusted I a Adjust thermostat heat b Fuel filter in fuel pump partially b Clean filter clogged c Restriction in fuel lines c Clean line or otherwise remove restriction d Iri...

Page 459: ...ing system from operating any time the pressure within the air conditioning system falls outside the normal operating range Both pressure sensing switches are wired to a common 5 ampere fuse located o...

Page 460: ...R ORYER ktrk i L R C 1 iOW PRESSURE SWITCH Y I THE SERVICENOTEVALVES ON AREA I i COMPRESSOR AND IN THL OF BOTH EVAPORATORS WERE REMOVEO AT TH 17f15 AND AFTER jll I FRONT SPAR I S 2 i 90 i L IE FS 100...

Page 461: ...ydrated They are to remain sealed until just prior to making connections They should be at room temperature before uncapping This prevents condensation of moisture from the air that enters the system...

Page 462: ...the appearance of oily spots where oil has been carried out by escaping refrigerant Smaller leaks which are much more difficult to locate may be detected by detergent bubbles or an electronic detector...

Page 463: ...ant level restore the proper refrigerant level AIR CONDITIONING FUNCTIONAL TEST With the engine running at 1 000 rpm and the system on observe the sight glass If the refrigerant appears milky or bubbl...

Page 464: ...the compressor will register a belt tension of 75 to 90 Ibs c Tighten the lock bolts d Lockwire the adjustment bolt and the lock bolts CONDENSER BLOWER REMOVAL I a Gain access to the condenser blower...

Page 465: ...the inlet and outlet lines and secure d Charge the system Refer to the CHARGING THE AIR CONDITIONING SYSTEM procedure in Section 2 e Install the instrument air line f Install the three brackets g Pla...

Page 466: ...R 12 and R 134a I refrigerant cannot be vented into the atmosphere When performing maintenance on the air conditioning system where R 12 or R 134a can escape from the system evacuate the system with...

Page 467: ...uld be drained from the entire system and the system reserviced Refer to the REPLENISHING AIR CONDITIONING SYSTEM LUBRICATION procedure in Section 2 Drainage can be accomplished by cracking the freon...

Page 468: ...dded between compressor mount lugs and the compressor lugs to adjust the compressor alignment to the drive pulley c Install the compressor belt Refer to the COMPRESSOR BELT INSTALLATION procedure d Ad...

Page 469: ...Y 6 IDLER PULLEY ADJUSTMENT BOLTS 8 ENGINE CENTER LINE 9 SHIMS AS REQUIRED 10 7 16 COMPRESSOR MOUNT BOLTS II 5 16 COMPRESSOR MOUNT BOL1S 1 11 O O O 6 ij 9 O 11 I O 9 s _ 1 O 6 Iv u 1 4 ii ii no 7 ii i...

Page 470: ...because refrigerant coming in contact with the eyes can cause loss of sight Do not smoke when servicing the system with R 12 or R 134a because it converts to a highly toxic gas when exposed to an ope...

Page 471: ...the metal guard around the evaporator module and remove the guard from the airplane e Tag and remove the electrical wiring from the evaporator blower module IWARNINO WARNING Due to the air quality co...

Page 472: ...the baggage compartment door FORWARD EVAPORA TOR BLOWER MOTOR REMOVAL I a Gain access to the forward evaporator blower motor through the forward baggage compartment refer t o F i g u r e 8 b The modul...

Page 473: ...on the lines because refrigerant coming in contact with the eyes can cause loss of sight Do not smoke when servicing the system with R 12 or R 134a because it converts to a highly toxic gas when expo...

Page 474: ...conditioner operation whichever occurs first AFT EVAPORA TOR BLOWER MODULE FIL TER CLEANING a Locate the air outlet at the top of the bulkhead at FS 190 00 Remove the air outlet louvered molding plate...

Page 475: ...I i MODULE COVER WASHER NUT L EAL i EV P9RATOR WASHER NUT 8 WASHER FILTER FS 39 00 GROMMET II w RACKET DUCT VAPORATOI 5EAL MODULE NUT il TU iiirUeE WASHER ASHER f s Ido oo Y LAMP IUBE 1 DRAIN PA FLAN...

Page 476: ...essor valves inoperative d Repair or replace e Slipping or broken belt e Tighten or replace 3 Excessive vibration of unit a Overcharged a Correct refrigerant charge b Air in system b Purge and recharg...

Page 477: ...MOVAL a Remove the fifth and sixth seats if installed to gain access to the blower assembly mounted on the aft bulkhead b Remove the rear upholstery panel c Tag and disconnect the electrical wiring d...

Page 478: ...s are of the adjustable type it is impossible to properly adjust them on the airplane The expansion valves are adjusted at the factory to 38 0 05 psi Without proper equipment a satisfactory adjustment...

Page 479: ...RESH AIR FROM DORSEL FIN NACA INTAKE IN FLIGHT B i FLAPPER 4 JOI 2 INLET ELBOW 3 FAN MOTOR 3 4 INLET DUCT 5 SUPPORT BRACKET SIDE INTAKE FRESH AIR ON GROUND VIEW A x Fresh Air Vent Blower Optional TC 2...

Page 480: ...SECTION UTILITY SYSTEMS...

Page 481: ...d of the cylinder to the right Keep fire cigarettes and sparks awa from rhs of the airplane centerline An overboard vent is installed on vicinity of the oxygen cylinder Hands the right side of the air...

Page 482: ...Puritan Bennett Constant Flow Mask a Prepare a cleaning solution by mixing one ounce of The oxygen system m be rid of obnoxious and oif r sive antiseptic 64 Consumable Iaterials Chart Section 2I or o...

Page 483: ...ecrease suction a place the new cylinder in the brackets and close the c Stop the engine and repeat steps a and I b with cylinder clamps the opposite engine running b Tighten the bracket clamp wing nu...

Page 484: ...may be exception of control valve operation and air fiiterinS made as follows provisions which will be discussed separately a Locate the filter s mounted centrally behind the The principle components...

Page 485: ...P PUMP LT eJ ItS Q Ic CHECK CHECK VALVE I I VALVE VACUUM g I VACUUM REGULATOR I I REGULATOR VACUUM 3 4 GYRO DIEIECT ONAL GAGE GYRO HORIZON EFFECTIVE TC 191 THRU TC 909 EXCEPT TC 846 VACUUM VACUUM 4 7...

Page 486: ...UU I PU MP j tl Figure 11 2 Vacuum TC 910 through TC 1013 TE 1 through TE 207 VACUUM GAGE CHECX I I I I CHECK VALVE 1 1 I VALVE VACUUM VACUUM REGULATOR REGULATOR DIRECTIONAL I GYRO DIRECTIONAL CYRO GY...

Page 487: ...H r4 Autopilot installation R H Wing Boot 1Conttol Control L H WlnR Boot Valve I Valve Ilol rllor Overboard Vent f Vent Air Filter Alr Filter Oil Separator Li I 1 I Oil Separator 011 Separator II I U...

Page 488: ...l Valve Solenoid Air Filter n rl v I Itr Fllter i j Valve I Shuttle Vahe I I 1 Shuttle VaiveA _ ii I011Separator I I I I OL1 Separator R it Wing Boot I I I L H Wtng Boot Pressure Gage Vacuum Pump Vacu...

Page 489: ...the deicer boot intlatinp air The deicer system also The control valve solenoid shouid be actuarrcf contains a gage in the cockpit to register system pressure and immediately for seven seconds as evid...

Page 490: ...Vacuum System this Section if adjustment is the valve required CHECK 3 Thoroughly clean the control al s bore and poppet with a commercial hydrocarbon t ps olvrnr a With bath engines operating at cru...

Page 491: ...ng lines c Pressure regulator valve needs adjustment d Distributor valve is defective 2 Lack of adequate air pressure a Clogged lints to inflate boots b Leaking lines c Pressure regulator valve needs...

Page 492: ...ply valve is 2 Pressure Adjusting Screw open With the air supply valve in the open position observe the ra er ilthe gages do not correspond to the iollowing Figure 11 8 Air Pressure Regulator table re...

Page 493: ...ers to a pressure manifold The position completing the deicing cydle This is known as the pressure manifold is located aft of the front spar behind the pop off pressure The low pressure gage on the re...

Page 494: ...mechanical inrerfci ence b Piping lines blocked or not b Blow out lines and inspect c onncclion connected c Check valve malfunctions at c Observe chrck valve Unplug outlet rz cycling valve assembly pa...

Page 495: ...by the adjustment of the ori fice regulator the regulators in the nacelles should TC 2003 AND AFTER be readjusted to 5 0 t 5 psi Adjustment of the pressure system components in a f With both engines...

Page 496: ...OR REPLACEMENT ORDER P N 09 14 1 NAS43DD3 24 SPACER 58 910021 1 COVER AN315 3R NUT NUT t I I I i 1TERBASE I AN936A10 LOCK WASHER AN970 3 WASHED AN960P01716 WISHER L FILTER RETAINER NVT AND WASHER 570...

Page 497: ...il II ii II II II y OVERBOARD I IGYRO LDIRECT ON GYRO DIRECTION IIHORIZON GMO HORIZON GYRO IL 3 VENT LINE I II PRESSURE LINE GYRO PRESSURE INDICATOR t I A CHECK VALVE MANIFOLD L CHECK VALVE FILTER TE...

Page 498: ...NE Il GYRO nZRECTION I GYRO DIRECTION IIHORIZON GYRO UI HOR IZON GYRO L r il II II II I T TEST GAGE J I I II L TURN I AUTOPILOT GYRO C OOR DINAT OR L MA STE R PRESSURE VA LVE INDICATOR CHECK VALVE IIM...

Page 499: ...ting at 2300 rpm NOTE 2 Tighten the check nut and recheck the gyro Rotate the pressure regulator adjusting pressure indicator to read in the green are with both screw clockwise to increase pressure en...

Page 500: ...DJRECTION1 1 GYRO DIRECTION HORIZON GYRO IU HORIZ ON GYRO L LI r ii Lrrl 5 1 VENT LINE II PRESSURE LINE TO H 14 AUTOPILOT TEST GAGE CYRO JJ PRESSURE INDICATOR CHECK VALVE LMANIFOLD CHECK VALVE FILTER...

Page 501: ...out solenoid to obtain a reading of 16 to 19 psi on the deicer pressure gage with the deicer c Operate one engine at 2300 rpm and adjust the system ON A pressure of 17 to 20 psi on the test low pressu...

Page 502: ...TION J GYRO DIRECTION IIHORIZON GYRO GYRO L HORIZON I VENT LINE L l PRESSURE LINE DEICER PRESSURE GAGE r II I e TO DEICER SYSTEM GYRO L PRE SSURE INDICATOR CHECK VALVE LNLANIFOLD LCHECK VALVE FILTER T...

Page 503: ...YRO HORIZON GYRO TO B 5P 1 r 7 Ir II IIAUTOPILOT TEST CAGE B 5P L AUTOPILOT PRESSURE MASTER II REGULATOR TirRN VALVE I I COORDINATOR I I GYRO J TO DEICER SYSTEM PRESSURE INDICAT OR IJI A F DEICER PRES...

Page 504: ...he gyro instrument adjustable orifice TE operating individually at 2300 rpm If the pressure on 452 through TE 767 or the regulator valve CTC 2003 the test gage has been affected by the adjustment of t...

Page 505: ...O HORTZON GYRO i i 1 TO DEIC R SYSTEM AUTOPILOT VALVE WITH DEICER ON Il II II I IRE STRICTOR II II II Ii I I Ii TO H 14 It AUTOPILOT I II J l DEICER L AUTOPILOT VALVE PRESSURE WITH DEICER OFF GYRO IND...

Page 506: ...me time After 5 to 8 The following procedure should be followed when seconds the relay returns the distributor valve to the resurfacing deicer boots original or evacuate position In the evacuate posit...

Page 507: ...BILIZER VENTURI DISTRIBUTOR VALVE TO AUTOPILOT DEICE PRESSURE GAGE R H WING I L H WING MANIFOLD TO AIR PUMP I 1 TO AIR PUMP PRESSURE I I PRESSURE 60603 174 Figure 11 15 Pressure System with Surface De...

Page 508: ...t material in the clean supply of methyl ethyl ketone such as acetate steel etc formed into long strips and taped to the boot around b Reclean the metal surface with a clean cloth the perimeter of the...

Page 509: ...0 the boot is misaligned pull it free quickly with a quick motion and reposition it properly g Either of the two following methods may be used k Activate the cemented surfaces and roll on each to appl...

Page 510: ...oint On airplanes equipped with surface deicers the certain the inlet line to the pump is clean If the inlet line to the pump contains for nacelle regulator is actually an assembly with two eign mater...

Page 511: ...the occurs Always reinstall the filter cover with the open nacelle and secure ing facing down The in line filters are located between the pressure regulators and instruments The fre PRESSURE REGULATO...

Page 512: ...NDICATOR REGULATOR SOLENOID t SOLENOID CHECK CHECK FILTER DUAL PRESSURE VALVE VALVE UM RESSURE RELIEF VALVE RELIEF VALVE LOCATION TO TEE PNEUMATIC DEICE IN TEST GAGE PRESSURE GAGE PRESSURE LINE VENT L...

Page 513: ...urface dry k with a clean dry cloth Adjust the instrument pressure regulator located forward of the instrument panel on the left side to NOTE obtain a reading of 4 8 to 5 1 in Hg on the instrument pre...

Page 514: ...y aid in installation letting the cement dry for at least 30 minutes apply a second coat to both surfaces j Using a clean lint free cloth heavilly moistened not dripping with toluoil 20 Consumable Mat...

Page 515: ...polished film that evens out microscopic irregularities i Using a sharp knife trim the boots as required for on the rubber surfaces therefor ice formations have proper fit A 75 inch edge distance mus...

Page 516: ...YSTEM TC 2003 AND AFTER TE 452 AND AFTER THI1 AND AFTER Indication Probable Cause Remarks INSTRUMENT AIR SYSTEM 1 Zero indication on instrument gage a Hole in plumbing line line a Inspect plumbing rep...

Page 517: ...unctioning f Piping lines kinked blocked or f Inspect lines and connections not connected blow out lines g Leak in system g See System Checkout locate and repair 2 Deicer boots inflate too slowly a Pi...

Page 518: ...b Vacuum ejector on distributor b Overhaul or replace distributor valve plugged or partially blocked valve c Defective boots c Repair as prescribed in this section or replace d Obstruction of lines d...

Page 519: ...TC 350 123 25 to 132 25 TE I thru TE 45 B 14 38 in B 4 03 in Vacuum system TC 2003 and after 123 25 to 132 25 T TE 452 and after B 14 38 in B 14 03 in e TH I and after Pressure system TC 1 thru TC 160...

Page 520: ...contacts I Moving the vane with the Phillips screw loosened close full bus voltage is applied to the stall warning moves the entire unit up or down inside the wing caus switch heater The major compone...

Page 521: ...I ANTI ICING SYSTEMS plugged the system should be periodically checked to ensure that proper fluid flow is maintained The pro Figure 11 23 peiler anti icing system should be checked to ensure that 2...

Page 522: ...der is increased by the 7 Allow the second cement coat to dry about 30 amount of stretch minutes before placing the boot into position Do this by aligning the inboard end center with the propeller b P...

Page 523: ...STALL WARNING VANE PLATE STALL WARNING SWITCH GEAR SAFEPI SWITCH TO LANDING GEAR POSITION LIGHT C B 5A 71 ct 10 16 n 5ow 7 5A LANDING GEAR SAFETY SW TCH RELAY STALL WARNING HEAT ss M o 19 Figure 11 19...

Page 524: ...i u unohl Figure 11 20 CAUTION NOTE Ground operation of the windshield If it is desired to retain the existing wind heater is limited to 10 minutes shield heater plate for continued use make a putty...

Page 525: ...attachment strip of the windshield heater ith a clean white cloth frame which is bonded to the windshield This is nec c Cut a piece of masking paper to the width of the essary in order to break the bo...

Page 526: ...K electrical to isolate and correct the problem h Apply adhesive to the bottom surface of the new t Remove all tape from the windshield top windshield heater retainer Apply adhesive to the portion of...

Page 527: ...circuit between the black and the relay in place and remove the relay white black and red on later units leads of the heater WINDSHIELD HEATER RELAY NOTE INSTALLATION TE 1169 AND AFTER If both of the...

Page 528: ...limitations To prevent the As the sense element theater heats the copper from damaging the slip ring the brushes must resistance will become greater be replaced as soon as the copper plating becomes...

Page 529: ...Qeechcraft BARON 55 AND 58 SHOP MANUAL MAXIMUM MINIMUM 0 31 200 00 200 40 60 80 1000 120 140 100 180 DEGREES FAHRENHETT Figure 11 22 Temperature Resistance Chart E15 11 49...

Page 530: ...RON 55 AND 58 SHOP MANUAL j I i Fireu all Alcohol Qunntity r 7 Windshield I il J Quantity Anti ice Tank Sensor 7 Propeller Anti ice Boot Anti ice SlinSer Ri nS t Figure 11 23 Propeller Anti icer Syste...

Page 531: ...ND 58 SHOP MANUAL I i __ _ I PLIIGAMMETERPROP DEICER I r R H FIREWALL CIRC BREAKER T REWALL ANTI ICE I ANTI ICE PROP DEICER PLUG r _ I c 1 L DEICER DOOT 55 93 37 Figure 11 24 Electrical Propeller Deic...

Page 532: ...D sec outboard halves be aligned by adding shims between the slip ring and Pin 30 Right Engine prop its mounting surface To avoid error in the gage C sec inboard halves readings during such a check sl...

Page 533: ...tribute current to the deicer boot on the pro If the wire will insert more than 17 32 inch it is time to peller blades Heat from the boots reduces the grip of replace the brushes Refer to Figure 11 26...

Page 534: ...o prevent breakage during assembly and priate pins on the plug holding the wicking to 1 8 installation Refer to Figure 11 27 inch maximum i Check the amount of brush protrusion from the g Set the spri...

Page 535: ...rather than the timer If the ground connection is open m Connect and safety wire the cannon plug the timer step switch will not change position n To preclude arcing caused by the rough surfaces b Afte...

Page 536: ...st one e Pin G of the plug to ground in the cockpit to monitor the ammeter while the other f Ground terminal of one prop boot on the right eng checks the deicer boots The man in the cockpit turns ine...

Page 537: ...order to avoid damaging the brush part number The part number is etched into the sur modules face of the plastichousing e Restack the modules and spacer f Install the assembly screws so that the scre...

Page 538: ...probe on to the next present the timer is not defective check the power pin in the sequence Refer to Figure 11 40 After the supply However if system voltage is present at pin B correctness of the cyc...

Page 539: ...to ground face of 1 16 square inch BRUSH TO SLIP RING RESISTANCE b If this resistance measures over 0 013 ohms TEST GOODRICH locate and repair the cause of excessive resistance c If the resistance is...

Page 540: ...pply a slow steady pull on the boot to pull it off the propeller surface while continuing to use the sol a Remove the slip ring assembly from the airplane t t soften the adhesive and mount it in a lat...

Page 541: ...roller for sumable Materials Chart Section 2 and apply one cement to dry for at least one hour at 40 5 or above this purpose for they would damage the when the relative humidity is less than 75 or two...

Page 542: ...eller spinner overlap of the boot but extending to the masking tape i g bracket Remove the masking tape after applying the cement to obtain a neat border CAUTION m Install the clamp securing the lead...

Page 543: ...film INSTALLATION MCCAULEY3 i CRUTION f I CAUTION Figures 11 30 11 31 11 32 and 11 33 a Place the deice boot on the propeller so that its The metal and rubber parts must be centerline is on the leadin...

Page 544: ...HOP IVIANUAL so 11 BY AS SHOWNOVERLAP EDGE Of BOOT WITH SEALANT OE CE BOOT SEALANT i I ON INBOARD CONTINUE SEALANT DOWN TO I SHANK AS SHOWN li I SHARP CORNER OF BLADE 250 f 58251 28 Ngure 11 35 Boot L...

Page 545: ...o I pockets under the boot Refer to Figure 11 32 allow full propeller travel i Roll outwardly from the centerline to the edges of I the boot Refer to Figure 11 32 If excess material at CAUTION smoothl...

Page 546: ...in in sequence noted earlier After the correctness of The brushes may be checked for wear by one of the the cycling sequence has been established turn the following methods deicing system switch OFF a...

Page 547: ...ON 55 AND 58 SHOP MANUAL 094 M N 1 FEELER GAGE BRUSH WEAR MEASUREMENT BRUSH BLOCK DISASSEMBLY BRUSH AND HOLDER ASSEMBLY BUTTON HEAD as SCREW TORQUE 20 24 LB IN la 36 251 6 Figure 11 37 Brush Block Ass...

Page 548: ...s indicated in BRUSH ShOUld be corrected immediately If the chattering or BLOCK INSTALLATION screeching is heard above the idling engine noise the problem is severe Repositioning the brush block as in...

Page 549: ...mbly the power lead is shorted to ground It is possible that will be transferred when it is mounted on the propeller the excess current has welded the timer contacts in one phase Under these circunsta...

Page 550: ...YPICAL CURRENT BLOCKING DIODE UI 1 I I I I swl SINGLE POLE 5 POSITION ROTARY SWITCH OFF Swl I I 1 I I SW2 4 POLE DOUBLE THROW TOGGLE SWITCH D I I P1 ANS AMPHENOL PLUG or I I I I I R1 ANS AMPHENOL RECE...

Page 551: ...ropeller deice system must not be matic should be used for reference during system ground operated for extended periods of troubleshooting Refer to Figure 11 40 time as damage to the deice boots and p...

Page 552: ...iring between timer a Refer to paragraph on heat test to part of cycle zero current rest of and firewall connector find deicers not heating and test for cycle voltage on that pin of firewall connector...

Page 553: ...and deicers excluding ground contact check for ground from slip ring brush circuit lead to bare prop while Rexing slip ring and deicer leads If a ground is indicated locate and correct c Short between...

Page 554: ...circuit diagram for improper connections 11 Rapid brush wear or frequent a Brush block out of alignment a Check brush alignment as in step i breakage of 100 hour inspection Section 16 b Check slip rin...

Page 555: ...fter several minutes there is no leak in the pitot system NOTE e If a decline in the reading of the airspeed indicator Wax or polish applied to the static air is observed check the pitot system plumbi...

Page 556: ...AIR BUTTON PITOT LINE OPTIONAL PIMT INSTALLATION STATIC DRAIN STATIC AIR LINE TC I THRU TC 954 PITOT MAST PITOT MAST ASSEMBLY ASSEMBLY STATIC DRAIN TC 9 5 thru TC 1607 Figurs 11 41 P8ot and StaUc Air...

Page 557: ...aeechc ft BARON 55 AND 58 SHOP MANUAL STATIC AIR BUTTON STATIC AIR BUTTON STATIC AIR LINE PITOT LINE OPTIONAL PITOT LINE STATIC DRAIN E15 11 77...

Page 558: ...valve actuated by the ON OFF pedals and place rudder pedals in their original posi switch in the flight controller A pressure control valve tion up upstream from the solenoid valve maintains a pressur...

Page 559: ...rate of airspeed change and ing movement proportional to the voltage imposed inertial signals to control the elevator through the pitch upon it This unit also supplies an output voltage pro servos An...

Page 560: ...Suction Relief Volve Ch rL Vorve Servo Aileron Servo Flight Controller Solenoid Valve Pr llun pellet Valve Driven Vacuum Pump Y Elevator Trim Motor Elevator Oil kpomtor Computer lc t Ch r Vo ve Air O...

Page 561: ...ENSATION RUDDER SERVOS AIRCRAFT I GYRO DETECTS ROLL YAW BATTERY N I ILRL DDER SERVO _ i CON7ROLVALVE i AIRCRAFT MASTER SW PILOT DISPLAY 2 POSITION AUTOPILOT MASTER PNEUMATIC PITCH CONTROL VACUUM I I A...

Page 562: ...r BLACK I II II AMFHENOL I IJIJ1 YELLOW II II L YELLOY JIJ J PITCHIALT NO CONNECT H H NI N BROWN II II L BROWN J IN N 7PIN BLACK K K POWER K K RATE SUPPLY SENSOR DECAY RED INPUT POT L L BLACK L L GREE...

Page 563: ...ST NS HEMISPHERE SWITCH SENSOR COMPENSATION NAV CENTERING SENSOR COMPENSATION VOR GAIN S LOC GAIN a d9a0 sV v o T a ii ii i o I O FACTORY ADJUSTS INTERCEPT MAN CENTERING OUADRATURE SrD ie2 ADJUST SET...

Page 564: ...as outlined elsewhere in from turns in one direction adjusted this section b Loose airplane primaly cables or b Check security of attachment excessive friction in aileron and or binding etc and adjust...

Page 565: ...uum pressure b Check for foreign matter lines 11 Airplane fails to turn to and hold a Faulty magnetic heading sensor a Replace magnetic heading magnetic headings sensor b Faulty heading selector resol...

Page 566: ...plifier controller amplifier 22 Output voltage in CAP mode a Wrong nav input signals a Check wiring decays to 0 voltage b Defective switching console if b Repair or replace console installed c Dirty i...

Page 567: ...ressure not a Adjust as outlined in this section airspeed changes set properly b Pitot pressure inadequate b Check pitot plumbing c Decay rate improperly adjusted Adjust as required 10 System will not...

Page 568: ...nd should not be removed i CAU TION in normal service STATIC WICK REMOVAL Nectrical shock can resulty if the mego a Unscrew the static wick from the base hmmeter is improperly used Refer to the applic...

Page 569: ...SECTION AIRCRAFT FINISHES...

Page 570: ...om acid rain damage if exposure is unavoidable SEALING FUSELAGE SEALING Replacement of loose or missing sealer at skin joints prior to repainting is recommended General skin joints are sealed with eit...

Page 571: ...M CORROSION TREATMENT After corrosion removal and surface cleaning metals should be given protective treatment and painted Alodine treatment of aluminum alloys forms a protective a good surface for ad...

Page 572: ...Treatment Number 19 formula The chemical for Dow Treatment Number 19 formula may be purchased from a Raytheon Aircraft Company authorized outlet in powder form or may be procured focally and produced...

Page 573: ...5 AND 58 SHOP MANUAL RIGHT SIDE VIEW TOP VIEW LEFT SIDE VIEW rn128 03387YIFI Skin Diagram Fuselage Model 55 Figure 1 RIGHT SIDE VIEW TOP VIEW IHi28 LEFT SIDE VIEW Skin Diagram Fuselage Model 58 Figure...

Page 574: ...ate primer Item 24 Consumable Materials Chart Section 2 thinned one part primer and two parts toluol Item 20 Consumable Materials Chart Section 2 A heavy hiding coat of this primer is not desired and...

Page 575: ...metal is no longer visible i Spray on two thin topcoats of finish paint ENAMEL TOPCOATS I The following is a list of the Enamel paints available for the Baron airplanes BLUE COLOR PARTNUMBER Astro Bl...

Page 576: ...ilee Gold 118684 221 Klondike Yellow 118684 343 Lemon Yellow 118684 15 Mesa Gold 118684 511 Metallic Gold 118684 271 San Mateo Wheat 118684 13 Saturn Gold 118684 17 Sunburst Yellow 118684 357 Sunshine...

Page 577: ...27 Vendetta Red 118684 501 BROWN COLOR PARTNUMBER Beaver Brown 118684 21 CastleTan 1186 1 19 Sable Brown 118684 223 Sahara Tan 118684 337 BLACK COLOR PARTNUMBER Black 118684 33 GRAY COLOR PARTNUMBER...

Page 578: ...If an Epoxy stripper is not available use a good enamel stripper Removing the finish with such a substitute will require several applications and working the stripper with a stiff brush or wooden scra...

Page 579: ...at APPLYING EPOXY TOPCOAT a Mix the paint and catalyst as directed by the manufacturer b Apply the topcoat with a spray gun at 35 to 45 psi of air pressure Two coats are normally required to fully con...

Page 580: ...or 24 hours sand the area being repaired with a medium fine sandpaper Sand the edge of the repair area until the indentation where the metal and the old paint meet is gone If necessary apply additiona...

Page 581: ...ne Yellow 118684 233 WHITE COLOR PARTNUMBER Matterhorn White 118684 217 ORANGE COLOR PARTNUMBER Omaha Orange 118684 281 BROWN COLOR PARTNUMBER Beaver Brown 118684 207 Castle Tan 118684 205 Sable Brown...

Page 582: ...paints and primers require a special paint stripper If a urethane stripper is not available a good enamel stripper may be used Removing the finish with such a substitute will require several applicat...

Page 583: ...primer slightly to roughen the surface and assure adhesion Wipe off the surface with a cloth dampened with a solvent such as lacquer thinner then apply the topcoat APPLYING URETHANE TOPCOATS a Mix the...

Page 584: ...the area under repair with medium fine sandpaper Sand the edge of the repair area until the indentation where the metal and old paint meet is gone If necessary apply additional urethane primer until t...

Page 585: ...Brown 4143 Sahara Tan 4302 GRAY COLOR PARTNUMBER Gamma Gray 7014 Kingston Gray 7101 Whisper Gray 6311 GREEN COLOR PARTNUMBER Beechwood 8304 Citrus Green 8320 Jade Mist Green 8303 Olive Green 8316 Sham...

Page 586: ...ador Red 2153 Vendetta Red 2185 Venetian Red 2324 TURQUOISE COLOR PART NUMBER Peacock Turquoise 1312 Turquoise 8120 WHITE COLOR PART NUMBER Matterhorn White 6160 YELLOW COLOR PART NUMBER Antique Gold...

Page 587: ...Raytheon nircraft Company BARON 55 AND 58 SHOP MANUAL YELLOW Continued COLOR PART NUMBER Sunburst Yellow 5071 Sunshine Yellow 5182 Tender Yellow 6313 Yellow Jacket 5041 Dec 31 03Pagel8 SECTION 12 E21...

Page 588: ...572 575 Bristol Blue 572 585 Ethereal Blue 572 534 Marlin Blue 572 565 Pavonne Blue 572 580 BLACK COLOR PART NUMBER Black 571 520 BROWN COLOR PARTNUMBER Castle Tan 577 520 Regimental Brown 577 775 Sa...

Page 589: ...520 Shamrock Green 573 535 ORANGE COLOR PARTNUMBER Calypso Orange 575 585 Mandarin Orange 575 580 RED COLOR PART NU BER Burgundy Red 576 542 Really Red 576 601 Toreador Red 576 635 Vendetta Red 576 62...

Page 590: ...raft Company BARON 55 AND 58 SHOP MANUAL YELLOW COLOR PART NUMBER Antique Gold 574 830 Bright Gold 574 520 Champagne Gold 574 820 Mesa Gold 574 815 Tender Yellow 574 509 Yellow Jacket 574 825 E21 SECT...

Page 591: ...m surface d Remove the masking paper and wash the affected area thoroughly with water under high pressure Remove all remnants of paint with lacquer thinner I e Sand the repaired area lightly then appl...

Page 592: ...r openings Be particularly careful to mask off all static air buttons before washing or waxing Because the wax seals the paint from the outside air a new enamel or epoxy paint job should not be waxed...

Page 593: ...Blue 118684 63 Banff Blue 118684 241 Blue Antique 118884 494 Chairman Blue 118684 483 GREEN COLOR PART NUMBER Lakewood Green 246 55911 Olive 118684 485 BEIGE COLOR PART NUMBER Artic Beige 118684 235 D...

Page 594: ...Gray 118684 75 Autumn Smoke 246 55911 Driftwood 118684 183 RED COLOR PART NUMBER Chairman Red 118684 481 Red Antique 118684 491 YELLOW COLOR PARTNUMBER Chairman Gold 118684 471 WHITE COLOR PART NUMBER...

Page 595: ...Ray heon Aircraft Company BARON 55 AND 58 SHOP MANUAL INTERIOR ENAMEL COLOR PART NUMBER Black Baking Enamel 94 515 Driftwood 82A 23294 Insignia Red Baking Enamel 94 509 Page 26Dec31 03 SECTION 12 E21...

Page 596: ...S Apply one coat of a thoroughly dissolved solution of one part Oakite No 6 and two parts water to all rubber surfaces that are to come in contact with either metal or other rubber surfaces Apply a th...

Page 597: ...ds The following items are painted with Insignia Red Enmar 94 509 Baking Enamel on all Baron airplanes a Fuel selectorhandle b Landing gear emergency operation handle c Control lock assembly except th...

Page 598: ...SECTION ELECTRICAL SYSTEM...

Page 599: ...rvice or every 30 days whichever occurs first NICKEL CADMIUM BA TTERIES To obtain optimum service from the two 12 volt 25 ampere hour nickel cadmium batteries installed in some Barons proper and regul...

Page 600: ...rior to charging and installation b Inspect batteries shipped from the factory for shipping plugs in the vent holes of each of the battery cells The blunt aluminum screws that serve as shipping plugs...

Page 601: ...AND CONDITION CC CHARGE I I I I REMARKS REASON VOLTAGE RANGE M Maintenance Lowest Highest I Y Indicate c O F Failure m Reading Reading d Average water added P e o inimum Maximumlr O q burns or discolo...

Page 602: ...BATTERY MEASURE END OF CHARGE VOLTAGE REST BATTERY 2 TO 4 HOURS CHECK ELECTROLYTE LEVEL CLEAN AND CHECK AIRCRAFT S BATTERY CONNECTOR INSTALL BATTERY CHECK AIRCRAFT S BATTERY CHARGER SYSTEM PREVENTIVE...

Page 603: ...ore than 32 volts for 2 minutes Special Notes on Charging The following special comments are made with respect to charging nickel cadmium batteries a Charging is most efficient at battery temperatures...

Page 604: ...ries with respect to the discharging current capacity rating and amount of charge already in the battery If fully discharged the battery should be charged to 140 percent of its nominal ampere hour rat...

Page 605: ...TANT POTENTIAL CHARGING Nickel cadmium batteries can be charged much faster by the constant potential method but the charging time will depend on the current delivery capability 300 ampere generators...

Page 606: ...so o Constant Current Charge Charge At C 10 Rate Figure 1 NICKE L CADMIUM 19 CE LL 34 AH 200 I I AIRCRAFT BATTERY CONSTANT POTENTIAL CHARGE AT 28 5 180 d I 1 VOLTS ROOM TEMPERATURE FULLY DISCHARGED BA...

Page 607: ...is to restore a battery to its full capability and to prevent premature damage and failure Effective reconditioning requires specific procedures for certain periods of time No step in the procedure c...

Page 608: ...be used remove all possible acid contamination with a sodium bicarbonate solution and rinse Even minute traces of acid can damage a nickel cadmium battery a Remove the battery from the airplane b Wit...

Page 609: ...o the battery case Decrease the ammeter current range to obtain a readable value of current and record the value Perform the same measurement at the negative battery terminal by connecting it to the n...

Page 610: ...and bent or pitted terminals Defective receptacles can overheat cause arcing and decrease output voltage to result in premature battery failure i Scrap bent or torn battery cases and covers that are...

Page 611: ...it is possible that the battery is not sufficiently discharged to accept a charge This can be determined by turning the battery OFF while observing the loadmeter needle deflection A satisfactory load...

Page 612: ...e switch in the ammeter lead ON and turn the battery switch OFF in that order to prevent a current surge and possible damage to the ammeter f Note the charge current as indicated on the ammeter The ch...

Page 613: ...all external power should be disconnected j Disconnect all electrical wiring connections at the alternator Tag and identify all wires to facilitate reinstallation k Remove the pivot bolt and washers...

Page 614: ...TION GEAR DRIVEN I WARNING When working on a propeller always make certain that the ignition switch is in the OFF position and the engine has cooled completely To be safe treat all magnetos as hot To...

Page 615: ...44 TE 546 and if 548 or below the floorboard of the nose baggage compartment just foMlard of the battery box TC 1073 and After TE 541 I TE 543 TE 545 TE 547 TE 549 and After and TH I and After The vol...

Page 616: ...he engine for at least 20 minutes at minimum cruise rpm with approximately 15 to 20 percent electrical load as indicated on the respective loadmeter located in the center section of the instrument pan...

Page 617: ...On the airplanes which use one regulator to regulate the output of both of the alternators there are no provisions for paralleling the alternators Unbalanced outputs between the alternators can be cau...

Page 618: ...y I compartment on TH 1377 thru TH 1395 except TH 1389 On TC 2457 and After TE 1202 and After TH 1389 and TH 1396 and After the alternator control units are located on the forward side of the forward...

Page 619: ...ternator control unit located in the nose baggage compartment output to match the recorded voltage output of the right alternator h If the right alternator control unit requires adjustment shut down b...

Page 620: ...1 0 amp load indicated on the ammeter NOTE While performing the following step only one precision volt meter is required The input voltage does not need to be maintained at any precise value and the...

Page 621: ...4 SUPPLY 5A PRECISION 7 V VIM SHUNT 5 ii NOTE CONNECTIONS TO BE ARRANGED SO THAT ZERO CURRENT WILL FLOW IN THIS LEAD FIELD 4 A DUMMY 0 5 A RESISTANCE INDICATOR LOAD CONTACTOR 1 5 DEVICE 28 V EQUALIZE...

Page 622: ...he precision voltmeter d Wait 5 to 13 minutes to allow the alternator control unit to reach operating temperature e After the alternator control unit has warmed up increase the output of the power sup...

Page 623: ...positioned such that the hex flat is parallel with the alternator drive face belt thereby providing a minimum of 0 25 in clearance between the two AL TERNA TOR LUBRICA TION BELT DRIVEN Lubricate the...

Page 624: ...nd all external ground power should be disconnected j Disconnect all electrical connections at the generator Tag and identify the wires to facilitate reinstallation k Remove the pivot bolt and washers...

Page 625: ...ight they may be warmed up on the ground WARNING Exercise extreme caution to avoid personal injury from the moving propeller or prop wash while adjusting the voltage regulators The following procedure...

Page 626: ...lle h Place the right generator switch in the on position and the left generator switch in the off position i Bring the voltage regulator and generator up to operating temperature by running the engin...

Page 627: ...operation is adjusted by the shunt paralleling coil located on the voltage regulator unit STARTER STARTER ENERGIZE LIGHT TH 1389 TH 1396 AND AFTER AND AIRPLANES WITH KIT 55 3022 INSTALLED Whenever the...

Page 628: ...ushings and armature shaft should be coated with a small amount of Delco Remy Lubricant No 1960954 STARTER TROUBLESHOOTING Refer to Chart 29 TROUBLESHOOTING STARTER SYSTEM STARTER BRUSHES The starter...

Page 629: ...55 TC 350 TE 1 thru TE 451 MAXIMUM CONTINUOUS STANDARD EQUIPMENT 7 D55 TE 452 thru TE 767 INTERMITTENT STANDARD EQUIPMENT 8 E55 TE 768 thru TE 1142 INTERMITTENT OPTIONAL EQUIPMENT 9 58 TH 1 thru TH 67...

Page 630: ...or Trim Tab 1819 Lamp 2 0 04 0 08 indicator Flap 313 Lamp 1 0 17 0 17 Indicator Cowl Flap 313 Lamp 1 0 17 0 17 Heated Pitot 50 384040 1 3 30 3 30 Light Rheostat 327 Lamp 1 0 04 0 04 Light Wing Tip 152...

Page 631: ...ng 1 02 300 1 1 50 1 50 Cigarette Lighter LPA27630 1 7 50 7 50 Horn Landing Gear Warning 319 1 0 60 0 60 Flasher Landing Gear Warning 624 1 0 30 0 30 Motor Landing Gear 1814818 1 10 00 10 00 Landing G...

Page 632: ...s Post 327 Camp 35 0 04 1 40 Rotating Beacon Upper G7740 9 24 1 3 75 3 75 Rotating Beacon Lower 07740 9 24 1 3 75 3 75 Light Ice MS2531 8 1 1 2 14 2 14 Meter Engine Hour M1986 1 0 05 0 05 Pump Prop An...

Page 633: ...0 24 1 0 15 0 15 Indicator Trim Tab 1819 Lamp 2 0 04 0 08 Indicator Flap 50 384001 35 1 0 06 0 06 indicator Cowi Flap 327 Lamp 1 0 04 0 04 Heated Pitot 50 384040 1 3 40 3 40 Light Rheostat 327 Lamp 1...

Page 634: ...7630 1 7 50 7 50 Horn Landing Gear Warning 169 380021 9 1 1 50 1 50 Flasher Landing Gear Warning Horn R102 12V 1 0 40 0 40 Motor Landing Gear 96 380022 1 10 00 10 00 Landing Gear Dynamic Brake 6046H39...

Page 635: ...er D7080A1 24 1 3 75 3 75 Light Ice MS2531 8 1 2 3 75 3 75 Light Ice A7079B 24 1 2 14 4 28 Meter Engine Hour M1986 1 0 05 0 05 Pump Prop Anti ice 476439 1 0 40 0 40 Light De ice Post 327 Lamp 1 0 04 0...

Page 636: ...hru TE 1142 MODEL 58 TH 1 thru TH 679 No Per Amperes Amperes Equipment Part No Airplane Per Unit Total Alternator Out Light 2399A17 2 0 08 0 16 Alternator Out Relay 50 380048 3 2 0 40 0 80 Voltage Reg...

Page 637: ...476284 2 0 40 0 40 Heater Ignitor 11C30 1 1 90 1 90 Heater Solenoid Valve AV181473 1 0 39 0 39 Cabin Dome Light 303 1 0 30 0 30 Engine Instrument Light 327 8 0 04 0 32 Fuel Select Light 327 2 0 04 0 0...

Page 638: ...Horn Flasher R102 12V 1 0 40 0 40 Landing Gear Motor 96 380022 1 20 00 20 00 Landing Gear Relay 6046H39A 1 0 40 0 40 Compass Light 327 1 0 04 0 04 Landing Light LH 4596 1 8 90 8 90 Landing Light RH 45...

Page 639: ...D55 TE 452 thru TE 767 MODEL E55 TE 768 thru TE 1142 MODEL 58 TH 1 thru TH 679 No Per Amperes Amperes Equipment Part No Airplane Per Unit Total Magic Hand Switch 60 364011 1 2 50 2 50 Surface Deice R...

Page 640: ...s 327 39 0 04 1 56 Oxygen Light 327 1 0 04 0 04 Prop Deice Three Blade 7E1177 Goodrich 1 12 00 12 00 Prop Deice Two Blade Goodyear 1 8 00 8 00 RH Pitot Heat 50 384040 1 3 30 3 30 Rotating Beacon Lower...

Page 641: ...8 1 28 Indicator Cyl Head Oil Temp 96 380016 1 2 0 65 1 30 Indicator Fuel Qty 58 380050 1 2 0 02 0 04 Indicator Turn Bank 50 380024 1 0 15 0 15 Inverter Electroluminescent Panel X17512 1 0 60 0 60 Pot...

Page 642: ...nti ice Valve AV 1B 1473 1 0 35 0 35 Anti ice Prop 2 Blades Kit 65 060 1 12 00 12 00 Anti ice Prop 3 Blades Kit 65 065 1 18 00 18 00 Heater Pitot R H 50 384040 1 4 00 4 00 Indicator Engine Hours 15000...

Page 643: ...Stall Warning 169 380021 11 1 1 50 1 50 Motor Flap 35 364151 57 1 13 00 13 00 Motor Landing Gear 96 380022 1 20 00 20 00 Relay Dynamic Brake 6046H39A 1 0 40 0 40 Relay Starter 6041 E190 2 3 50 3 50 S...

Page 644: ...Total Actuator Pitch Trim 33 524033 15 1 1 60 1 60 Resistor Trim Shunt 4587 1 0 38 0 38 Surface Deice 96 970004 Relay 50 380048 1 1 0 10 0 10 Relay Delay GT4738 1 0 17 0 17 Valve Distributor 38E63 1 A...

Page 645: ...ply PS 243A 5 50 Transponder TRR 660 1 30 VHF Comm Transceiver RT 241A 0 80 VHF Comm Transceiver RT 241A 4 56 VOR ILS Indicator IN 245A 0 30 VOR IOC Indicator IN 244A 0 06 Radar Altimeter TRN 71 1 30...

Page 646: ...445 2 10 Autopilot H14 3 00 Comm Transceiver KTS SOOA Receive R 0 60 Transmit T 7 00 Comm Transceiver KX 195 R 0 65 T 4 50 Comrn Nav Transceiver KX 1708 R 1 30 T 5 10 Comm Nav Transceiver KX 1758 R 1...

Page 647: ...Converter KA 39 VOR Indicator KI 201C 0 16 VOR LOC Converter KN 77 0 10 Autopilot Century 1 2 00 Autopilot Century 11 1 50 Autopilot Century 111 4 50 Autopilot Century IV 4 00 Flight Director FD AP 28...

Page 648: ...25 H F Transceiver DXI O RA 6 25 ATC Transponder AVQ 95 1 40 Audio System AVQ 310 2 74 DME System AVQ 75 3 70 DME System AVQ 85 4 40 NAV System AVN 210A 0 30 NAV System AVNP 11A 0 19 RMI Converter AVI...

Page 649: ...Detector 04402 4 1 1 47 1 47 Indicator Cyl Head Oil Temp 96 380016 2 0 65 1 30 Indicator Electrical Load 58 380048 1 2 0 01 0 02 Indicator Electrical Load 58 380048 5 2 0 01 0 02 Indicator Flap Posit...

Page 650: ...ight 327 4 0 04 0 16 Flap Position Indicator Light 58 324065 5 1 0 03 0 03 Glareshield Flood 313 12 0 17 2 04 Map Light 1495 1 0 30 0 30 OAT Light 327 1 0 04 0 04 Rheostat Light 327 1 0 04 0 04 Switch...

Page 651: ...an 50 384001 1 0 01 0 01 Pump 476284 1 0 60 0 60 Valve Windshield AV 1 B l 473 1 0 29 0 29 Clock Digital CT 24 1 0 20 0 20 Electrothermal Prop De ice Ammeter 58 380086 1 0 01 0 01 Heater Prop 2 Blade...

Page 652: ...ument Wedge Single 58 380022 11 21 0 048 1 01 Instrument Wedge Dual 58 380022 11 23 0 048 1 10 Rotating Beacon Lower D7080A 5 24 1 3 22 3 22 Rotating Beacon Lower 40 0100 3 1 3 10 3 10 Rotating Beacon...

Page 653: ...20 Motor Flap D160 00 3 1 11 00 11 00 Motor Landing Gear 96 380022 1 40 00 40 00 Pump Fuel Boost 4404 00 1 2 4 00 8 00 Relay Dynamic Brake 6046H39A 1 1 25 1 25 Relay Starter 6041H190 2 3 30 3 30 Star...

Page 654: ...rt No Airplane Per Unit Total Actuator Elevator Trim 31 9A209 6 1 0 85 0 85 Resistor Trim Shunt 4587 1 0 38 0 38 Surface De ice Ejector Distributor Valve 2H59 4 1 0 22 0 22 Pressure Relief lalve 2H22...

Page 655: ...2 80 Comm Nav CN2O1 3A R 1 20 T 2 70 ADF Receiver DFA 73A 1 1 05 DME DME 203O 1 20 Autopilot FCS 81O A P 6 50 Autopilot FCS 81O W HSD 830 Compass 7 25 Compass System HSD 88O 2 10 RNAV Computer NCP 204...

Page 656: ...er Beacon Receiver MKR 350 0 255 Compass System PN 101 2 60 Power Converter PWC 150 0 02 Transponder TDR 90 1 90 Transponder TDR 950 1 74 Nav Receiver ViR 30M 0 80 Nav Receiver VIR 351 0 80 VHF Transc...

Page 657: ...Translator KA 43 0 10 Code Translator KA 58 0 03 Audio Ampl KA 134 1 30 Audio Ampl KAA 445 2 10 Compass System KCS 55A 1 73 ADF Receiver KDF 805 0 75 DME KDM 705A 3 00 Autopilot KFC 200 WNaw 11 05 W K...

Page 658: ...er KNR 660A 0 23 Nav Receiver KNR 661 0 50 RNAV System KNS 80 1 26 Radar Altimeter KRA 405 0 97 Marker Beacon Receiver KR 22 0 50 ADF Receiver KR 85 1 00 Transponder KT 76A 1 80 Radio Phone KT 96 R 0...

Page 659: ...66 Marker Beacon Receiver Audio Amplifier CP 136 2 11 DME DME 190 1 60 DME DME 195 2 80 Compass System HSI 100S 1 065 Compass System HSI 100 1 or 2 0 965 Marker Beacon Receiver MKR 101 0 29 Marker Bea...

Page 660: ...ipment Part Number Per Unit Radar PRIMUS30WXD 4 00 Radar PRIMUS 35WXD 6 00 Radar PRIMUS 40WXD 5 00 Encoding Altimeter 10 200 102 0 08 Lighted 0 09 Radar Altm AA 100 0 50 H F Transceiver ASB 60 R 2 50...

Page 661: ...0 30 Indicator Oil Temp Press 102 380014 2 0 15 0 30 Indicator Electrical Load Loadmeter 102 380018 2 0 03 0 06 Indicator Fuel Flow 102 380012 2 0 15 0 30 Inverter Electroluminescent 58 380101 1 0 50...

Page 662: ...er Amperes Amperes Equipment Part No Airplane Per Unit Total Map Light 1495 2 0 30 0 60 OAT Light 327 1 0 04 0 04 Compass Light 327 1 0 04 0 04 Flight Instrument Light Trays 58 380022 7 0 05 0 35 Wing...

Page 663: ...lay Windshield Heater MS24166D1 1 0 35 0 35 Electric Prop De ice Ammeter 50 380086 1 0 01 0 01 Power Supply Timer 845018 1 0 20 0 20 Heater 2 Blade 840245 51 1 12 50 12 50 Heater 3 Blade 840245 51 1 1...

Page 664: ...y Dynamic Brake 60406H39A 1 1 25 1 25 Motor Flap 160 00 3 1 11 00 11 00 Relay Flap 50 380048 1 2 0 10 0 10 Pump Fuel Boost 476284 2 4 00 8 00 Motor Fwd Blower 58 380072 1 3 85 3 85 Cigarette Lighter 3...

Page 665: ...Trim 33 524023 1 1 15 1 15 Air Conditioning Condenser Blower 58 380081 1 20 00 20 00 Relay Condenser Blower 6041 H200 1 0 35 0 35 Actuator Nacelle Scoop 50 380080 1 0 77 0 77 Surface De ice De ice Tim...

Page 666: ...DME 2O30 1 20 Autopilot FCS 810 6 50 Autopilot FCS 81O W HSD 830 Compass 7 25 RNAV Computer NCP 2O40 1 50 Radar RDR 150 3 50 Radar RDR 160 3 50 Radar RDS 82 5 00 Transponder TPR 2O60 1 30 Encoding Alt...

Page 667: ...dar WXR 1 50 3 00 Radar WXR 200 3 50 Amplifier 356F 3 1 30 Amplifier 356 4 0 185 Autopilot Century III W1 4 50 Trim Coupler 1 03 G S 0 20 Autopilot Century IV W 4 00 Trim 2 00 Yaw Damp 1 90 Compass Sy...

Page 668: ...5A Comp Sys W O Yawl 9 03 VOR LOC Converter Ind KI 203 0 10 VOR ILS Converter KI 204 0 10 VOR ILS Indicator KI 206 0 10 VOR LOC Converter KI 208 0 15 VOR ILS Converter Ind KI 209 0 15 RMI Kl 226 13 00...

Page 669: ...tormscope WX 8 0 50 ADF Receiver ADF 141 0 95 Transponder AT 50 R 1 25 T 1 86 VHF Transceiver COM 1208 R 1 26 T 5 10 VHF Transceiver COM 120 R 0 60 T 3 50 Audio Control Panel CP 135 0 66 DME DME 195 2...

Page 670: ...022 13 Engine Instrument Wedge Lights 13v 58 380022 9 Flight Instrument Post Lights 327 Flight Instrument Wedge Lights 58 380022 13 Deice Post Light 327 Clock Post Light 327 Clock Wedge Light 58 38002...

Page 671: ...ht 327 Courtesy Lights 2 1864 Cowl Flap Position Light Models 55 A55 B55 and C55 313 Console Lights Red D158 100 4T1 White 0158 100 5T1 Circuit Breaker and Switch Panel lights Red D158 100 4T1 White D...

Page 672: ...449 TC 1936 and After TE 856 thru TE 1200 TH 598 TH 684 thru TH 1362 632 Tail Navigation Light Whelen TE 1201 and After TH 1363 and After A508 Tail Strobe Light Flashtube Hoskins TE 768 thru TE 855 TH...

Page 673: ...u UCINUU dl GB t B c r f a L O YI c nruma rw s ol c OII LW UI yllll101 OI U 1 1 YN OC 1IDYIO 51 IE ZllI n r nr r 1 wwl nm nl I lo II rru BII r s B 9 L j u nr u oo au o ol uuur u um ucl mar rc Ic amo...

Page 674: ...RIES INDICATION PROBABLE CAUSE REMARKS 1 Apparent lossof capacity a Cells unbalanced a Equalize cell voltage by performing full capacity discharge cycle b Electrolyte level too low b Charge adjust ele...

Page 675: ...ter respond to charging They will show up as unbalanced cells and must be replaced 7 Frequent addition of water a Unbalanced cells a Equalize cell voltages b Leaky or defective cells damage b Replace...

Page 676: ...ative b Check continuity of starter system c Low batteries c Test batteries If low replace or start with external power d Loose connections or open circuit d Check connections and continuity between b...

Page 677: ...f worn to a I length of 5 16 in f Dirty commutator f With generator running clean commutator with No 0000 sandpaper Use air jet to remove grit g Defective voltage regulator g Replace regulator h Defec...

Page 678: ...oot connection at generator or regulator 2 Regulator too hot 3 Short in wiring between F and and negative leads between generator and regulator 4 Defective transistor 5 Shotted field in generator 4 No...

Page 679: ...10 No charge a Back bias diode open a Negative grounded systems 1 Severe ground at F terminal of generator 2 Severe ground in wiring between F terminals of generator and regulator 3 Generator field co...

Page 680: ...nal source 13 Poor switching may or may not a Filter capacitor open a Defective connection or defective fail output transistor capacitor 14 High system voltage a Feedback capacitor shotted a Defective...

Page 681: ...Wiring faulty or improperly c Perform wiring continuity check connected d Voltage regulator voltage setting d Adjust voltage setting Check improper or defective regulator regulator e Alternator defec...

Page 682: ...y connected in the during cranking due to advance circuit due to poor connection timing of ignition Inspect retard points to see if they close Check for proper contact at the SWITCH and RETARD termina...

Page 683: ...ne indicator light inoperative a Defective light bulb or indicator a Check bulb for proper contact and burned out filament b Defective switch b Check continuity of switch Replace if necessary c Open c...

Page 684: ...check on circuit Check for loose connections d Defective flap motor d Check brushes springs condition of commutators Replace if necessary 2 Flapswill not raise a Tripped circuit breaker a Check circu...

Page 685: ...a Check continuity of circuit Reset breaker circuit breaker I Chart 37 TROUBLESHOOTING STALL WARNING INDICATOR CIRCUIT INDICATION PROBABLE CAUSE REMARKS i Warning buzzerinoperative a Tripped circuit b...

Page 686: ...rt circuit Reset circuit breaker b Open circuit b Check continuity of entire circuit 2 Onenavigation lightinoperative a Defective light a Check bulb for proper contact and for burned filament b Open c...

Page 687: ...present the fault is probably located in the power unit TROUBLESHOOTING POWER UNIT Disassemble the power unit by removing the screws securing the end plates to the power unit Remove the end plate whic...

Page 688: ...check the capacitor 04 for shorts and leakage e If unijunction 03 is to be replaced it may be necessary to readjust the flash rate This can be done by changing R5 or by changing the value of 04 In ma...

Page 689: ...he red wire is connected to positive power and the black wire to ground Make sure that the red white I and black wires are connected to pins A B and C of the connector respectively and that the connec...

Page 690: ...ve these precautions may result in physical injury from electrical shock a Remove the screws from the lens and remove the lens b If the nav light needs to be replaced rotate the bulb counterclockwise...

Page 691: ...obe light assemblies Turn the control switch for the strobe lights OFF and allow at least 10 minutes to elapse prior to disconnecting the cables at the power supply or strobe light assemblies and befo...

Page 692: ...with a spring loaded cover is located in the right aft fuselage skin adjacent to the transmitter providing access for manual activation of the ELT The output frequencies are 121 5 and 243 0 MHz simul...

Page 693: ...unter batteries such as those sold for flashlights portable radios etc are usually unknown CAUTION The ELT switch should not be turned ON unless the ELT is connected to its associated antenna or a 50...

Page 694: ...g a stick apply a bead of sealant supplied with each battery pack around the area of the control head which is joined with the battery case when reassembled NOTE This sealant provides a water tight se...

Page 695: ...nnect the antenna d Disconnectthe remoteswitch e Remove the screws holding the ELT in place f Remove the ELT from the airplane 9 Remove the screws from the bottom of the ELT and remove the bottom h Di...

Page 696: ...or flight service station a Turn COMM 1 ON and tune to 121 5 MHz b Turn the COMM 1 audio switch to the SPEAKER position and place the volume control in the center of its range c Turn the ELT ARM OFF O...

Page 697: ...SECTION VVI RING DIAG RAMS...

Page 698: ...r and wire size Amer after and to the Baron 58 serials TH 598 TH 648 and after ical Wire Gage Frequently a suffix indicating a gound N phase A B etc or material alumel etc Is added The individual circ...

Page 699: ...nder Head and Oil FuelQuantjtv 11 38 Temperature lj 86 Vacuum Pressure Instrument Liehls 1 0 D Optional I i19 Optional Wedge lJ dl Deice Introduction J Three Bladed Prop Goodrich 14 107 L Two Bladed P...

Page 700: ...1 1 1 T l 1J i P Taxi Light ij 121 Temperature Pitot Heat 14 6 Cylinder Head and Oil l J 86 Power Distribution 14 6 Three Bladed Prop Deice Po wet External and S tarter I 4 1 5 Goodrich Ic 10 Pressure...

Page 701: ...he fol lowing type switches and relays 2 Position 3 Position O7 7 si 47f_ O 2 Pole Thermal Switch Pressure Switch o T o ANODE C ATE LC i O I CATHODESCR Low Current High Current Transistor MOTORS t t C...

Page 702: ...r Multiple Conductor Shielded Wire Twisted Wiring Cables Plug and Receptacle LIGHTS GROUND CONNECTORS 13 O I 77 R Color Case Ground I round Connection Connection I I Press to Test Light Light MISCELLA...

Page 703: ...G O LANDING GEAR O I LANDING GEAR O I CIGARETTE LIGHTER L1 H36A14 nlHEATER O PROP ANTI ICE PUMP o I PITOT HEAT o I PROPELLER ANTI ICE OPTIONAL O 1 FUEL BOOST PUMPSL COWL FLAPS O LANDING LIGHTS O I LAN...

Page 704: ...ICE ALTERNATOR IGNITION P2D10 QUAhTTITY P3A6 FIELD ENGINE HOUR wIh ns nELD LIGHTER AND IMSTRUMEhT METER ANTI ICE v TO DOOR WARNING LIGHTS PROPELLER ALTERNATOR TKROTTLE CABIN LIGHT P2E10 ANTI ICE I ARN...

Page 705: ...P15A RADIO REF P15B P17 P1 t P16 P18 I 1 i Battery Master Relay 2 Bus Bar 3 Key Switch Assembly 4 Battery TO STARTER RELAY Battery TC 1 thru TC 190 res...

Page 706: ...25B2 O i P23A18N i P26A2 I P27A2N I ONE 24 VOLT BATTERY STANDARD TWO 12 VOLT BATTERIES OPTIONAL i Battery Master Relay 2 Bus Bar TO 3 Battery Master Switch STARTER 4 Battery 24 V Standard RELAY Two 12...

Page 707: ...0X18 T P27A18N I PlsznlsN P151A18 I P150AI8 ONE 24 VOLT BATTERY STANDARD TWO 12 VOLT BATTERIES OPTIONAL I P23A18N 1_ I LP56A18 1 TO ALTERNATORS P55A18 i 55 36997 1 Battery Master Relay 2 S 550 Klipvol...

Page 708: ...I YELLOW COMPARTMENT LIGHT P25B2 TO NOSE BAGGAGE I P23A18N I T P26A2 I P55A18 i ALTERNATORS P56A18 TO P27A2N ONE 24 VOLT BATTERY STANDARD I TWO 12 VOLT BATTERIES OPTIONAL 553696 i Battery Master Relay...

Page 709: ...1B2 P25A18 P22A18 P25B2 b jlO I P23A18N I r P26A2 T P27A18N I I Battery Master Relay 2 L l k C 3 Battery Master Switch 4 Battery 24 V Standard TO Two 12 V Optional STARTER 5 Bus Bar RELAY 55 3592 1 Ba...

Page 710: ...GAGE RELAY P90A6 L LIGHTS 1 P22A2 TO RADIO P23A18 TH 3 AND AFTER ONE 24 VOLT BATTERY STANDARD jilji P25p18 TWO 12 VOLT BATTERIES OPTIONAL P22B2N I P24A1BN L 55 369 99 1 Battery Master Relay 2 Alternat...

Page 711: ...GAGE REL Y P90A6 L LIGHTSP22A2 TO RADIO ONE 24 VOLT BATTERY STANDARD P25A18 I P23A18 I TWO 12 VOLT BATTERIES OPTIONAL r t i P22B2N P24A18N jj i Battery Master Relay 2 Alternator Limiter 3 Subp nel Bus...

Page 712: ...K TO BATTERY K25 LH K27 C r K28 RH K26 ah P15B de L El j I I 0 K3 K2 v K5 K4 J L i Bus Bar 2 External Power Receptacle 3 Starter 4 Starter Relays 5 Starter Switches External Power and Starter TO 1 thr...

Page 713: ...GNITIO 5 Starter RH STARTER SU ITCH External Power C ptional and Starter TC 191 Thru TC 375 O TO O BATTERY O II RELAY P21B2 P21D4 P I 1 P21C2 K15A18N JUMPERBOSDI G MOP K1BAZ IOr K15B18N BONDING K13A18...

Page 714: ...ernal Power Optional and Starter TE 1 thru TE 196 r P8A20 P8B20 t 7 a i P21E4 C 1 01 TO TC 1 OPTIONA L P21D4 BATTERYRELAY MOT K18A2 aLP21C2 ii bP21B2 K16h2 iOT BO ISG BONDING JUMPER K15B18N JC IPER i...

Page 715: ...6 MOT U KllA2 P21B2 K10A2 i OT 8 K7A20N i K6A20N I K3A20 K5A20 TO IGNITION STARTER SWITCH TWO 6 GAGE 1 Receptacle WIRES MAY BE CSED 2 Starter LH 3 Starter Relay LH 4 Starter Relay RH 5 Starter RH 6 Re...

Page 716: ...FL C J2 h El s I FL O P E f FL O v i RightMagneto 2 Filter Units 3 Off On Switches 4 Left Magneto 5 Right Magneto 8 Left Magneto 7 Bus Bar Ignition TC 2 thru TC 23 14 19...

Page 717: ...Magneto 5 Ignition Starter Switch K19 18 INPUT BO K18 18 SW GN 55 16 L 36 16 ft tOLR RET LH r S Bi sw RO BAT TO STARTER t K17 16 RELAY K 22 18 K20 18 sw GND r Ja is L 59 is 30 LR RET RH yJ10 161 rVR...

Page 718: ...Starter and Cabin Lights Circuit Breaker J1818 16CA TC 191 THRC TC 33 INPUT EXCE PT 1C 201 18GA TC 201 TC 23 i Tl n J2A18 TC 319 Z0GA TC 320 xrn FTER SW 53A20 L L 7 I J4A20 I L LRGND LH J5A20 L R BO B...

Page 719: ...Left Magneto 4 Right Magneto 5 Ignition Starter Switch J1A18 I J3A20 OLRL GM LH S O BO BAT Q_ I J9A18N TO K13A18 STARTER J1B18 RELAY r I I J6A20 L r OLR GND 1 r rJ8A20 R Jsels r O BOSBAT K14A18 Ignit...

Page 720: ...ight Magneto 5 Ignition Starter Switch J1A20 0 J5A20 O LRL GND J3A20 R J9A20S O BO BAT K5A20 RE LAY JtB20 B r I II J6A20 L I I OLR GND I r r J8A20 if R J9 B20N t l S O BO BAT K3A20 Ignition TE 768 thr...

Page 721: ...5 I i PY PI 1 I se P37 P36 O C 3EI P 1 P23 I p2J P30 sl i I i 1 I B TC 6 thru TC 140 P33 P21 P35 P34 P22 P32 i Bus Bar 2 Ammeter I C 1 1 I 3 Circuit Breaker 4 Voltage Regulator Gen YA 5 Generator Swit...

Page 722: ...FP PF I G c I 3 6 I _I ii P14A16 I I IL I il I 1 I P4r 16 I P18A8 P8 8 I i Bus Bar P5A16 P15A16 2 Ammeter 3 Circuit Breaker 4 Voltage Regulator 5 Generator Switch FY YA 6 Generator Ay yr 7 Paralleling...

Page 723: ...8 I L _ J P3A8 P13A18 r r 1 i i I i i 1 r FP PF I I G c l r I 1 B I I B P14A16 P1A16 cY t P18 A8 P8j8 F f r L_ P15A16 i Bus Bar PSA16 2 Loadmeter 3 Circuit Breaker 4 Voltage Regulator ii 5 Generator S...

Page 724: ...ttl P47A18 BLUE I IF P38A18N P42A18 I I H C P47818 P48A18N BLACK Icfin j ll P4881BN I I U P55B18 P39A18 L P37AIO PSBA s IPI1A1B B B P40B18i l llHtP37818 RED P P 1 BLUE F llH P39818 P38A18N BLACK GRD...

Page 725: ...P 2A P47A18 I BLUE F P38A18N IH P42A18 P43A18N BLACK CRII U cj lt P48B18N P55B18 P39A18 L P37A10 P56A18 P41A18 I IH RED P QI P40B18 1P BLUE F 1___ 141 I IIH P38A1SN LACK CRD I t P38818N 1 Circuit Bre...

Page 726: ...0 IG I T P55A18 P44A8NP43A18 P44A18 d P37A14 I P78C18 I I Y I lp18B18 LP42A18 1 P56A18 2A 2A I r t F 1P78D18 P39A 18 Y Y l tP38BIBP t PJ P39A18 P40B 18 0 L Y P36Als i Bus Bar 7 Fuse 2 Circuit Breaker...

Page 727: ...2A Y 2A U P28A18 I P39 18 B NO 1 la 8 V R MI IM R VU 8 RH I I LH BLACK P39B18N C P46B1Bh I RH BLACK BLACK P36A18 P16C18 EG P46A18N r P P85A18 i Bus Bar P50B18 3 Throttle Warning Circuit Breaker o Z P...

Page 728: ...B18N II RH i L F P16B18 f 3 P16B18 BLACK 1 Bus Bar I 1 I t I I I I i I i PrSD1A 2 Circuit Breaker P53A1SN 1 11 P53A18N 7 1 I I J 3 Throttle Warning Circuit Breaker RH IZ 4 Ammeter 5 Alternator I P53 B...

Page 729: ...K P78B18 i Bus Bar 3 P16B18 2 Circuit Breaker P46B18E o a A 3 Throttle Warning Circuit Breaker 1 pj3A18N 4 Ammeter g D 5 Alternator P39A18 B 6 Capacitor 7 Fuse P53A18N P53B18N L j C B Alternator Out R...

Page 730: ...AIB CBLACK L J H 2 Circuit Breaker P51B1B I RED C P28B18 P78C18 i q sucK_1_ P16C18 L 1 3 P1GB18 f t BtACK K NO 1 1 Bus Bar RED P78D18 88 1 3 Throttle Warning Circuit B r e a k e r 6 Caplcitor BLACK1 r...

Page 731: ...1 I I il il M P43A16 P41A18P40B18 I P16B16 P78C18 pj0A16 I I I I I 1 2 I P78D18 1 Bus Bar IP P16B18 I I 1 3 1 I P2B A18 3 I J 2 Circuit Breaker 3 Throttle U arninc Circuit Breaker L O GREE N e P28 A 1...

Page 732: ...761EjlS L I I 4061E I DS P 1 T 2h T P BCI I I P1GA1E i i L i F 1 Bur Sar 2A i P16iiF jfiiEg 1 P ED1E LI rn Circui r 101 1 3 Throtti M zrninr Cir ui S r e a i r r 3 Lilterna or El I P39kIS 6 3 Loadm te...

Page 733: ..._I I I P78B18 r I I I P43A18 i PIOB18 878018 PSOA18 I I f IP P78D18 I BusB t 2A 5 P I I 4 5 7 LO GREEN f P28A18 I P39A18 B 6 Cse itor 8 Altan tor Out Sn oc PS1B1B RED O 9 AiOsnutor Switch I 1 P39818N...

Page 734: ...lA187 P74C20N lo P30A18 NO 1 P78C18P78D18 JF 2000n 1 P78B1 H BLACK r I I GREEN _I r L A I Of I I P79A18 P76B18 I P84A18 1B I 3A L C L P64A18N P75 418 I D i 3A v IE P66B20 2000 a L_ J 11 P66C20N I W6A2...

Page 735: ...NAL 39 GALLON MAIN TANK INSTALLATION THE WIRES E40 ELtl AND THE BOND STRAPS GROUNDING THE INBOILRD MAIN TRANSMITTERS ARE NOT OSED WHEN THE OPTIONAL 39 GALLON MAIN TANK IS INSTALLED i Bus Bar 6 Main Ta...

Page 736: ...ION THE WIRES E40 E41 AND THE BOND STRAPS GROUNDING THE INBOARD MAIN TRANSMITTERS ARE NOT USED WHEN THE OPTIONAL 39 GALLON MAIN TANK IS INSTALLED i Bus Bar 6 Main Tank Transmitter 2 Circuit Breaker 7...

Page 737: ...AND THE BOND STRAPS GROUNDING THE INBOARD MAIN TRANSMITTERS ARE NOT USED WHEN THE OPTIONAL 39 GALLON MAIN TANK IS INSTALLED 1 Bus Bar 6 Main Tank Transmitter 2 Circuit Breaker 7 Aux Inboard Transmitt...

Page 738: ...gzi is QllA18 Q2qA18 i B zY 1 2 2 IP 923A18 i r i Q22p18 rff 7fV I WIRING FOR OPTIONAL 39 GALLON MAIN TANKS E II L l l C l l l 1111 1 1 1 1 1 I i Bus Bar 2 Circuit Breaker 3 Resistor 4 FuelGage 5 Fuel...

Page 739: ...9A18 3P 1 4 yj Q16AI8 PI I I a22A18 Q23A18 2g27Ais Q24A18 3 4W n3 410A18 Q26A18 C Q25A18 4 Fuel G a g e 1 Bus Bar Q19A18 2 Circuit Breaker 3 Resistor 5 Fuel Gage Transfer Switch 6 Main Tank Transmitte...

Page 740: ...7A18 Q12A18 7 1 I i Q21A 8 gis is Q9A18 2 2P I Qls ls Id 2 3 41 11 3 Q10A18 Q26A18 1 4 g25A18 4 Fuel G a g e 1 Bus Barg19Aia 2 Circuit Breaker 3 Resistor 5 Fuel Gage Transfer Switch 6 Main Tank Transm...

Page 741: ...E41A18 I I_I I I E32Ala E 3Ala E42A18 ir0 2 2 4 11 E2 i 18 E31A18 E3iB18 E21 8 61 3 3 i Bus Bar 2 Circuit Breaker 3 Resistor 4 FuelCage 5 Fuel Gage Transfer Switch 6 Main Tank Transmitter 7 Aw Inboard...

Page 742: ...35A18 E34A18 E32Ai8 E47A18 E45A18 2B 4 E27i 18 E31A18 E21B18 E31 BL8 Cq 55 369 128 i Bus Bar 2 Circuit Breaker 3 Resistor 4 Fuel Gage 5 Fuel Gage Transfer Switch 6 Main Tank Transmitter 7 Aux Inboard...

Page 743: ...I MAIN AUX I _T E47H20 aE44A20Q 6 Fuel Sensor Inboard Xuxiliary 1 Bus Bar I E37A20 E34A20 2 Circuit Breaker 3 Fuel Circuit Board 4 Fuel Gage 5 Fuel Select Switch 7 Fuel Sensor Outboard Auxiliary E46A2...

Page 744: ...L E50A20 E58A20 E58B20 I L E54B20 I b MAIN AUX I _r E47H20 E43A20pjE44A20 6 Fuel Sensor Inboard Auxiliary 1 Bus Bar E37A20 2 Circuit Breaker E34A20 3 Fuel Circuit Board 4 Fuel Gage 5 Fuel Select Swit...

Page 745: ...5 T4 T3 72 T4 T3 000 an ooo T PI T5 T2 T1 T5 8 o 0 o o Ic E64A20 E63AM B PRIFITEO CIRCJIT 50P A3 E64B20 E63B O E64C20N E63C20N 1 i M 69 111 i Bus Bar 2 Circuit Breaker 3 Fuel Quantity Printed Circuit...

Page 746: ...TERM 4 TERM 4 TERM 3 7 TERM 3 TERM 3 I T TERM i PRINTED EblA20N PRINTED CIRCUIT E64A20 I E63A10 C1ICV1T C ii BOARD BOARD IHBOAID INBOARD FUEL FUEL SENSOR SENSOR E64B20 E63B20 OUTBOARD FUEL OVTBOARD S...

Page 747: ...B2 E48A20 E46A20 ct E47A20 E49A20 Q RH LH PRINTED CIRCUIT sOAfin PRINTED CIRCUIT BOARDS ARE E47B20 E49B20 E46820 E48B20 OE INDICATOR E63A20N E63A20N E62A20N E64A20N L L L L i Bus Bar 5 Transmitter Mai...

Page 748: ...INBOARDLEADING EDGE FUEL CELL E4820 E3BZO B UIRCS nND nRE USED WHEN OPTION I OUTBOAAD IEAOI G EDGE CELLISNOTINSTi CLEO E4C20N EjCZON II E47AZO OPTIONAL OUTBOARD LEADING EDGE CELL E48A20N E49AZON 1 i B...

Page 749: ...F EOAIlO I INa OAR D INIQ tO LEADING INIO 110 IEDGE FUEL ICELL MRES EJQCN PINO EoCZCN i 10 F4CtoN9 C QN ARE USED WHEN OPTIONAL DUT10 l0 OUTIOI O O BOAflD LEAOING EDGE FUEL PUL CELL IS NOT INSTILL DItN...

Page 750: ...NECTOR TERMINAL OF BATTERY REFER TO 6 POWER DISTRIBUTION KW33A20 P CURRENT OLIECTOP P55B2N TERMINAL ON I nSSIM8Lr POSITIVE SIDE 1 3 OF SHUNT CURRENT I 1 1 7 SENSOR KW36A20 4 SHUNT KW31A20 1 s KP8BA20N...

Page 751: ...cuit Breaker 2 Connector 3 Fuel Boost Pump H MOT El 11 Fuel Boost Pumr s LH TC 1 thru TC 335 except TC 251 Rf II 5A E56A18 E55A18 i Circuit Breaker 2 Fuel Boost Pump IciOT MOT Fuel Boost Pumps RH LH T...

Page 752: ...8 6129A18 1 1 I QSOAIP Q2 1 8 Q1A18 A T T i c I 1 c MOT lor i LH Fuel Boost Pump Switch B D 2 RH Fuel Boost Pump Switch R i 3 LH Fuel Boost Pump 4 RH Fuel Boost Pump LH RH 55 369 134 Fuel Boost Pump...

Page 753: ...4 RH Fuel Boost Pump LH RH Fuel Boost Pump TE 1 thru TE 451 prior to compliance with S 1 0584 285 TO C0 3 L FLAP CIRCUIT BREAIiER r g28Aie QzsDls 7 Q28C18 Q28t 18 Y_ _ _ LOU P o s Q2B18P Q1B18 Q24A18...

Page 754: ...I OF azsls 668 j 3A18 Q2A18 QSA18 Q6A18 ji I 1 T C A C I g r II B _I I 4i ii LH 811 E55 369 36 1 Bus Bar 2 Circuit Breaker 3 Fuel Pump Switch 4 Fuel Boost Pump Fuel Boost Pump 65 768 thru 65 856 and a...

Page 755: ...TA18 Q30Al8 RED C WHITE B RED C WH TE B RIGHT LEFT BLACK A BLACK A I_ 1 55 M9 755 i Bus Bar 2 Fuel Boost Circuit Breaker 3 Fuel Pump Switch 4 Boost Fuel Pump Fuel Boost Pump TC 1420 thru TC 1935 excep...

Page 756: ...Q3A18 gsA1e RE D C WHITE B RED L WHITE B Lo BLACK A BLACK A 1 I_ 55 369 137 1 Bus Bar 2 Fuel Boost Circuit Breaker 3 Fuel Pump Switch 4 Boost Fuel Pump Fuel Boost Pump TE 857 thru TE 063 and prior ai...

Page 757: ...IRCUIT SHOWN 10011 WITH AIRCRAFT ON GROUND 10W GEARS FULLY EXTENDED AND THROTTLE CLOSED C4AIBN 55389138A _L I Landing Gear Motor Circuit Breaker 9 Up Limit Switch 2 Throttle Warning Circuit Breaker 10...

Page 758: ...uit Breaker 40R10W rG4820 L AFTER i Landing Gear Motor Circuit Breaker P TH 1 ASD AFTER 2 Landing Warning Circuit Breaker 4 Control Switch 5 Down Limit Switch G8A18 6 Gear Down Indicator G4A20N 55369...

Page 759: ...ElY ITCH SWITCH WHITE tND 017A10N cI Il tK n ill YDt WHIN NI I 0EAR IS NOT DOWN AND LOCKED NOTE CIRCUIT SHOWN WITH PLANE ON GROUND GEAR TULLY EXTENDED 03A10 RED AND THROTTLE CLOSED LANDING WARNING GEA...

Page 760: ...101120 i LI WHITE OJ 30 017A10N S I BLACK n 18 voc WHIN NI GEAR IS NOT DOWN AND LOCKED 01 20 011 10 R n 5 itrr NOTE CIRCUIT SHOWN WITH PLANE SWITCH 021120 C1OI10 ON GROUND GEAR FULLY EXrEND1D RtD AND...

Page 761: ...fety System G9A18 t 1 19 RH Throttle Switch Gear Safety System 20 Test Switch Gear Safetsr System G27A18 I I 1 1 21 Pressure Switch 70 MPH P DN 18 G14B18 GlOA18 iG12A18 I G1B18 13 G23A18 2 G I 1 2 R 6...

Page 762: ...ar Safety System G27A20 19 RH Throttle Switch Gear Safety System 20 Test Switch Gear Safety System n t DN Ip I G1LG14B20 21 Pressure Switch 70 M PH G6A20 r13 G1B20 G10A20 G12A20 G23A20 2G 2R G10A20 Gl...

Page 763: ...i r ounzoh G61B20 LEFT G61A20 G55420 G58A23 G58820 NOSE DOWN I I I I 1 3 658820 658620 LH ANNUNCIATOR I I I I I I I I I I I I I 1 5 DIM RELAY 1 1 I I I 1 i GE 29 I I G52A20 652820 i I I VP M 652020 G5...

Page 764: ...D1AL I L L C8A 16 0 C 2A 1 6 UP DOWN C7A 16 C4h 16 ___C5C 16 C3C 16 MOT i Bus Bar C6A12N 2 Circuit Breaker L 3 Flap Position Switch 4 Up Limit Switch 5 Down Limit Switch 6 Flap Motor 7 Up Position Li...

Page 765: ..._ J iP II __ CIRCUIT BREAKER C10B18 Y C8B14 a cj 13 r ioT CGA14S Flaps TC 191 thru TC 1010 TO ttl I 8 15A CllB20 r INSTRUMENT 1P LIGHTS 1 2 CIRCUIT BREAKER C1A14 C12B20 C10A18 1 RED BLUE C13A20N WHIT...

Page 766: ...C4B18N G A JC4C18 R TO C4A18N L L L II INSTRUMENT II II CIRCUITLIGHT C1OA18 iP l_ i BREAKER 10B18 C10C18 MOT C6A 4N I 1 Bus Bar 2 Circuit Breaker 3 Flap Position Switch 4 Flap Up Limit Switch 5 15 Fla...

Page 767: ...IA14 C2A14 1 C12B20 CllB20 C7A14 15 IIjC d C14A14 LICIIT FLAP UP FLAP DOWN LIMIT SWITCH SWITCH 15 FLAP 15 FLAP POSITION POSITION C13A20N SWITCH SWITCH I 4 03 02 CBA14 C5A14 FLAP MOTOR L Y C8B14 C5814...

Page 768: ...RCUIT SWITCH PRINTED C7A 14 BOARD 4 03 02 C4A14 CIRCUIT SHOWN 14 IN 15 POSITION C7B14 FLAP DOWN C28 1 4 A LIMIT SWITCH q t FLAP UP 14 FLAP LIMIT LIMIT SWITCH t FLAP POSITION SWITCH INDICATOR C8A14 C5A...

Page 769: ...20NPRINTED 16 FLAP SWITCH C7A14 C9A14 CIRCUITBOARD 4 03 02 I C4A14 CIRCUIT SHOWN 14 IN I5 POSITION C7B14 FLAP DOWN C18B20 CISC20 q O C2B 1 4 b LIMIT SWITCH LO l t FLAP UP 14 FLAP LIMIT LIMIT SWITCH t...

Page 770: ...18 J I I I I L E16A18 IA E19A18 I I L E17A18 B E20D18N E20A18N E20B18N E20C18 C i Tachometer 2 Tachometer Generator LH 3 Tachometer Generator RH Tachometer TC 191 Thru TC 954 B A CI ICA B PI E18A18 C...

Page 771: ...Al U E51A20 f E52A20 LC i L_i IC T7 E53A20 E54A20 IU BI E56A20 A C E57A20N B L 1 i Tachometer Gage 2 Tachometer Gage Connector 3 Tachometer Generator Connector 4 Tachometer Generator Tachometer TE 768...

Page 772: ...liB 1ON I 6 2120 1 CONNECTOR CONNECTOR LH TACHOMETER LH TACHOMETER GENERATOR fi I I A 54A20 JHT OR RED OR B B t 1 E56A20 BLK OR BLU T T E56820 BLK OR BLU L l AC C 57A2o I CONNECTOR CONNECTOR Tachomete...

Page 773: ...ING H EAT F2 F2 L L LH RH STANDARD OPTIONAL Pitot Heat TC 1 thru TC 190 55369 119 1 Bus Bar 2 Circuit Breaker j10A 3 Pitot Heat F1A18 F1Als r TO OPTIONAL STALL WARNING H EAT B k F2A18N F2A18N L L LH R...

Page 774: ...WARNING 1_ TC 1608 and after TE 938 TE 943 and after TH 385 and after A B 1 Bus Bar 2 Circuit Breaker 3 Pitot Heat 55 369 150A Left Pitot Heat TC 1608 thru fC 1935 except TC 1913 75 938 TE 943 thru TE...

Page 775: ...943 TE 1063 F5A18N TH 385 TH 647 xTH 598 TC 1608 TC 1935 x TC 1913 F12A18N s A Bus Bar 2 Circuit Breaker 3 Pitot Heat PI ss sss lson Right Pltot Heat TC 1608 thru TC 1935 except TC 1913 TE 938 TE 943...

Page 776: ...H29A20N OFF I L El L 11 H30A20 MANUAL 20CA r n sazo WITH H 14 AUTOPILOT INSTALLATION H38P20 P iM7 M7 H39A20N H40A20N j i 1 Bus Bar 2 Circuit Breaker 3 Switch 4 Relay 5 Time Delay Relay 6 Deicer Valve...

Page 777: ...0 5A L PrO I H28A20 i H26A20 HZfjA20 H28B20 31 1 AUTOMATIC H29A20N i H28AZO H29A20N OFF L MANUAL H26B20 H30A WITH H 14 AC TOPILOT 1 Bus Bar 2 Circuit Breaker 3 Switch 4 Relay 5 Time Delay Relay 6 Deic...

Page 778: ...EJECTOR DISTRIBUTOR H25C20 VAL E 3 ikc H30D20 t H3 0D20 e BLUE WHITE 81 H33A21 N 62 H27A20N I 55369 53 H28A20 H29A20N I 31 12 H28B20 H26B20 I Circuit Breaker 2 Switch 3 Relay 4 Pressure Relief Valve L...

Page 779: ...Optional TC 1 thru TC 190 i __I ON H3D20 H3BZO OFF i Bus Rar L H3C20 MOM ON 2 Circuit Breaker H3Ar8 3 Propeller Anti ice Pump L H3E20Nj 4 Windshield Anti ice Switch 5 Windshield Anti ice Valve IP Pro...

Page 780: ...OFF H3E20 H3A20 _I H3F20N iT__ __ __1 51369155 i Bus Bar 2 Circuit Breaker 3 Pump 4 Windshield Anti ice Switch 5 Windshield Anti ice Valve Prop and Windshield Anti ice Pump Optional TE 768 thru 78 10...

Page 781: ...ICATOR D62 18 Dgq 18 D63 18 P se3 s lss Alcohol Ouantin Anti icer TC 1 thru TC 190 iP I i Bus Bar 2 Circuit Breaker 3 Resistor 4 Anti ice Indicator E13 B18 Fj Calibrating Rheostat E13A18 J 6 Anti ice...

Page 782: ...0A20 H62A20 H60B20 r H62B20 i Circuit Breaker 2 Resistor 3 AlcoholQuantity Gage 4 Resistor 5 Alcohol Quantity Transmitter Propeller Anti ice auantlty Alcohol TE 168 thru TE 1063 tH l thru TH 647 excep...

Page 783: ...12 E16 L Cylinder Head and Oil Temi ernture TC 1 tllru TC 190 1 Bus Bar pi p r 2 Circuit Breaker g A 3 Engine Gage LH 4 Engine Gage RH 5 Cylinder Head Temperature Bulb LH E7 18 6 Oil Temperature Bulb...

Page 784: ...7A20 E6A20 E13A20 rElla20N1 I I I rE7 20NI I I E14r 20 A B B A B Al IA B P i Bus Bar 2 Circuit Breaker 3 Engine Gage 4 Cylinder Head Temperature Bulb 5 Oil Temperature Bulb Cylinder Heed and Oil Tempe...

Page 785: ...Fuel Pump 14 Heater Blower Switch Heater TC 1 thru TC 190 PJ 31 10W HIOA18K H9A18 VVVV v 1 H5A12 bj c NC HllA12 rC H12A18 H13A18 COMB sn P i n14 BN 1 PP H6A12 H17AIB MOT H16A18 MOT H20A18 m H15A18 H1...

Page 786: ...954 I s a Jo ow a H36A14 H35A14 i Q 20A r 5H33A14 H9A20 I H5A14 m 1_ F I iH34814 H15AZO 34A14 jAZO H11A14 I TC 955 H17AZO H6A14 B 2 Circuit Breaker Switch H14A20N MOT I thru 1 BusBar TC 1042 C 3 Iris...

Page 787: ...2 Circuit Breaker H20A2 3 Air Valve Switch C H1BA20 4 Heater Blower Switch 6 Resistor tH19A20 IE 5 Fuse 7 HeaterIgnitor 8 Overtemp Thermostat 9 Ductstat Heat Control H7A14 10 Heater Fuel Pump H8A14N...

Page 788: ...1 H7A12 H19A20 H17A20 Q H16B20 MOT H8A12N H15B20 B A H14A20N L LF H17B20 MOT k m 55369 6 1 Bus Bar 8 Thermostat 2 Circuit Breaker 9 Heater Ignitor5witch 3 Air Valve Switch 10 Ignitor 4 Heater Switch 1...

Page 789: ...104 16 1 I IGNITION UNIT BLOWERI L HIJAIZ Y 3 C 101 16 I Utl O 1 1 rI ISOLtNOID OFF H5C12 HEATER I al2 IL nl 1211 1 sOl lb 7_ C 01 16 Y HI H TER IT LOWI BLOWER DOWN H7A12 6 106 16 SWITCH I LANDING GEA...

Page 790: ...Q RET O T EXT RET O O O EXT K15 K16 K11 K12 K10 2 1 Circuit Breaker Bus Bar Y 3 Cowl Flap Indicator Y 4 Cowl Flap Switch RED RED 5 Cowl Flap Actuator BLACK BLACK NIOT MOT WHITE WHITE KI lB K13 i I RH...

Page 791: ...K8A18 K9 18 7 FN KilOAiB K6A18 K5A18 I 2 Circuit Breaker i Bus Bar 3 Cowl Flap Indicator Y Y Y 4 Cowl Flap Switch RED RED Cowl Flap Actuator 5 BLACK BLACK MOT l lOT WHITE 1 1 Y K14X18 Y K13A18N I I R...

Page 792: ...R RED Is K5A18 I i KllA18 OR OR L RED 18 R RLACK I8 1 1 Bus Bar 2 Circuit Breaker Y 4 Cowl Flap Switch RED 3 Cowl Flap Indicator V RED OR 5 Cowl Flap Actuator OR C3 BLACK OR B2 C3 BLACK OR B2 MOT MOT...

Page 793: ...BLACK RED BLACK MOT MOT WHITE WHITE YELLOW I YELLOW I t K4Ar8 K9A18 K4B18 K9B18 TO ANNUNCIATOR 1 Bus Bar 2 Circuit Breaker 3 RH Cowl Flap Switch 4 RH Cowl Flap Motor 5 LH Cowl Flap Motor 6 LH Cowl Fla...

Page 794: ...r TO PITOT HEAT t W1A18 M3A18 W7A18 t M4A18 i i 1 W2A18 M5A18N INSTALLED WITH Is OPTIONAL SURFACE DEICE TC 1 608 and after W3A18 la 8 W4A 18 2 Circuit Breaker 3 Stall Warning Switch 4 Stall Warning Ho...

Page 795: ...HEAT W1B20 c 7 W7A20 W7A1S TE 938 TE 943 and after TH 385 and after I r l I I F 1 Circuit Breaker 2 Stall Detector 3 Stall Warning Horn 4 Stall Detector Heater W2A20 Stell Warning TE 768 thru Tf 1063...

Page 796: ...IP 5A B M3A20 M4A20 M5A20N 55 369 172 i Bus Bar 2 Circuit Breaker 3 Prejsure Switch 4 Engine Hour Meter Engine Hour Meter Optional TE 768 thru TE 1063 TH 1 thru TH 647 except TK598 14 99...

Page 797: ...IO _L 1 Bus Bar 2 Circuit nrenker 3 Indicator Turn and Slip TC I thru TC 190 5A F3AL8 El F4A18N I j 1 Bus Bar 2 Circuit Breaker 3 Indicator Turn and Slip TC 191 thru TC 1935 excapt TC 1913 fE l thru T...

Page 798: ...cept TH 598 IP 5n CAUTION WHITE WIRE OR WIRE COMMON TO CASE OF FUEL VENT HEATER MUST BE CONNECTED TO AIRCRAFT STRUCTURE H110A20 H112A20 1 H109A20N r T HIIIAZON WHITE RED RED WHITE 1 U U I But Bar 2 Ci...

Page 799: ...ck Terminal iv I 7 Ice Guard Boot I H177 20 8 slip Ring I H178A20 H176A14 E G B A C D F H184A145 I I I H181A14N H183 L 14 81 H179A14 1 1 s L H182A14 O 3 3 ICE UARI RESIST CIC TO nE 6 22 OH IS P I C CI...

Page 800: ...I I H184A14N 1 I I i t H1BII14N H183A14 H179A 4 ns n I x X B H180A14 H182A14 B v v 0 0 B HIS B14N HIB B14N _L ICE GUARD RES STANCE TO BE 6 22 OHMS PER EARLY AIRCRAFT DID NOT CIRC UrT USE SHIELDED WIRE...

Page 801: ...hTBOARD rH5QA 6 H45A12 I I I I I IEll n B H44A14 H41A14 A t c H43A14 B c H47A141 j1 r H46A14h C 1 Bus Bar 2 Circuit Breaker LH RH 3 Shunt 4 Ammeter 5 Timer C1 I 6 Brush Block Plu Ice Guard Boot El Sli...

Page 802: ...THE SHUNT ITEM 3 IS BEPASSED Oh THESE AIRCRAFT SERIALS H176A12 a A B D C F E4 IP O I H184A14h IP I I PI H180A14 I I A A H179A14 H182A14 B cC H18jA14hl H186A141 j C O I r LH I Bus Bar RH 2 Circuit Bre...

Page 803: ...A14 I A A H43A14 H42A14 B C H47A14hT1 _rH46A14N 1 C I LH 1 Bus Bar RH 2 Circuit Breaker 3 shunt 4 Ammeter j Timer 6 Brush Block Plug 7 Ice Guard Boot 8 Slip RlnF 55 369178 Hartzell Goodrich Prop Deice...

Page 804: ...r r 3 2 Ammeter 20 A 4 Timer I 5 Brush Block Plug H40A14 6 Brush Block 7 Ice Guard Boot 8 SlipRing H39A14 H46A14 B _L P P IIP i H3SA14H38A14 fii A H44A14 B H4jA14 B iC I H43A14 H42A14N LH r I I I RH i...

Page 805: ...Block Plug 6 Brush Block H40A14 7 Ice Guard Boot 8 SlipRing P K39A14 Ir O O 0 I 64 A H44A14 H38A14 A x Z B H45A14 H3 A14 6 C H43k14 H42 14N IP r L L RH LH CI 162 55 369 45 i I GOOdrich Three Bladed P...

Page 806: ...IP I I I I IP 4 H183A14 B H1BOA14 H182A14 A H179A14 C H185 414h 1_ r H186A14N C LH 1 Bus Bar RH 2 Circuit Breaker 3 Shunt 4 Amrmeter 5 Timer PI 6 Brush Block Plug 7 Ice Guard Boot 55369 277 8 Slip Ri...

Page 807: ...I i I 1_ B B C H44A14 J I I H41A14 A A t H43A14 H42A14 B C H47A14 i 1 rH46A14hT 1 C OI LH i Bus Bar RH 2 Circuit Breaker 3 Shunt IJ 4 4mmeter 5 Timer 6 Brush Block Plug 7 Ice Guard Boot 55369 196 8 S...

Page 808: ...er 3 Resistor 4 Cigarette Lighter Cigarette Lighter TC 1 thru Te 190 3A H21A16 2 1 50W n WHIE FURNISHED WITH LIGHTER O Bus Bar 2 Circuit Breaker 55 369 198 3 Resistor 4 Cigarette Lighter Cigarette Lig...

Page 809: ...igarette Lighter TE 768 thru TE 942 except TE 938 TH 1 thru TH 384 H21B16 L46A20 TO ANNUNCIATOR H21A16 1 Bus Bar 2 Circuit Breaker 2 OHMS 50 W 2 OHMS 50W 3 Resistor 4 Cigarette Lighter BLK WIRE FURNIS...

Page 810: ...Ej BLACK I YELLOW C 1 6 A 1 8 B R O W N D I 18 A I I C17A18 I _ 1 1 75 5tr j0i125 5 18GA C BLACK 1 Bus Bar 2 Circuit Breaker 3 CoiledCord 4 Switch 5 Resistor 6 Actuator Assembly Electric Trim Tab TE 6...

Page 811: ...o BLIIE 20GA BROWN YELLOW C17A20 75n 5W 50 25W c 16P20 C2 2A20 C23P20 i Circuit Breaker 2 CoiledCord 3 PitchTrim Su itch 4 Resistor 75 5H 5 Resistor 50 25W RED BLACK BLUE 6 Pitch Trim Actuator 7 Pane...

Page 812: ...20 75n 5W 50 n 25W c 16P 20 C22A20 C23A20 1 5I I Circuit Breaker 1 2 Coi edCord L L 3 Pitch Trim Switch i 4 Resistor 75 5W 5 Resistor 50 r 25M RED BLAC K BLUE 5 Pitch Trint Actuator 7 PanelSwitch 8 Em...

Page 813: ...12 i L11 L11D L11A LI1C R C G g El L11E Q L19 L11E C i Bus Bar 2 Circuit Breaker 3 Navigation Lights Flasher Optional 4 Left Wing Tip Lights 5 Right Wing Tip Lights 6 Tail Light Navigation Lights TC 1...

Page 814: ...2A18N I i L13A18 I 511TH FLASHER L13B 8iL13E18 L13D18 t G IP PI L13C18 L13F18 L14A18 i L15A18N I I Bus Bar 2 Circuit Breaker 3 Navigation Lights Flasher Optional 4 Left Wing Tip Lights 5 Right Wing Ti...

Page 815: ...L12A18NI L WIRE FURNISHED L13A18 WITH FLASKER L13B1Sdtr3E1S L1SD1S R C L13C18 L17C20 L13F18 L36A20N 1 Bus Bar 2 Circuit Breaker 3 Navigation Lights Flasher 4 Left Wing Tip Lights 5 Right Wing Tip Ligh...

Page 816: ...12A20N L13E20 L13G20 L13D20 L j r L13J20 P L L13C20 j L36A20N I Bus Bar I 2 Circuit Breaker 3 Navigation Lights Flasher 4 Wing Lights 5 Tail Light USED WITH OPTIO AL 3 LIGHT STROBE ONLY Naviaation Lig...

Page 817: ...L13JZO p NAV LIGHT 20 I L r L36AZON i 1 Bur Bar 2 C cuilBredLe 3 Navigation L19hlr Fiaj er 55 369 201n 4 Wing Lig l 5 Tail Li it USEOW1TH OPTIONnL 3 LIGHT STROBE ONLY Navigation Lights TC 1601 th o fC...

Page 818: ...r 3 Landing LighC Clear I Landing Light TC 191 thru TC 1935 except TC 1913 TE 1 thru TE 1063 TH 1 thru TH 647 except TH 598 10A L16 r i Bus Bar 3 Taxi Light Clear Taxi Light Optional TC 1 thru TC 190...

Page 819: ...ght RH Ice Light Optional TC 191 thru TC 1935 except TC 1913 18 1 thru TE 767 P g 5A J L17A20 L19A20 i Bus Bar L16A20N L1BA20N 2 Circuit Breaker 1_ 1 3 Ice Light LH 4 Ice Light RH WIRE FURNISHEDWITH L...

Page 820: ...Switch 4 Cabin Lights Clear L To WSTRUMENT LIGHTSt NhO 18 Cabin Lights TC 1 thru TC 190 Bi P I 5A I I TO INSTRUMENT LIGHTS L22A18 L21A18 i Bus Bar 2 Circuit Breaker r J 3 Cabin Lights Switch 4 Cabin L...

Page 821: ...o Q O o L42A18 rL4 A18N 1 L20D18NL20E18NL lo T ONAL J L20A18N L OVERHEAD INSTRU EST LIGMTS L20B18N TO L20C18N I 5 369 21 1 Bus Bar 2 Circuit Breaker 3 Cabin Lights Switch 4 Cabin Lights Clear Cabin Li...

Page 822: ...GHT L100A20 SW TCH iP L106A20 L101A20N L100BZ0 L 0IB10N El L107AZO 1100C20 3RD AND 4TH SEAT READING LIGHTS I101CZ0N LTOOD20 L101D20N L100EZO 5TH AND bTH SEAT READING LIGHTS L101E20N El 583 9 ZJBA Cabi...

Page 823: ...0N 1 L2ic20 gd L26B20N Et I I 0 O L40A20 L28A20N L20A20 i 1 Bus Bar 2 Circuit Breaker 3 Dome Light 4 Reading Light 5 Reading Light Switch 6 Dome Light Switch 7 0 A T Light 8 Compass Light 9 Glareshiel...

Page 824: ...LACK L100C1D 380 AND 41H SEAT READING LIGHTS LIOIC ON 1 IC t BLUE LIOBA20 L26820 LP1A20N 1 Llol07CN 1100020 L26A20 L90A OoPiioNAiL109 20 c k L104A20 6r Iro L100t20 5TH AND bTH SEAT READING LIGHTS IIOI...

Page 825: ...uit Breaker 3 Rotating Beacon IO A o i L14 R n jW lal P L15 GND 23 R R J L Rotating Beacon TC I thru TC 190 Le i Bus Bar 2 Circuit Breaker 3 Rotatillg Beacon 10 A n L7A18 L9A18 e Rotating Beacon TC 19...

Page 826: ...R Rotating Beacon TC 955 thru TC 1935 except TC 1913 TE 1 thru fC 767 IE 10A X L71A18 L73A18 I L72A18N I I L74A18N I i Bus Bar UPPER LOWER 2 Circuit Breaker 3 Rotating Beacon Lower Red 4 Rotating Beac...

Page 827: ...J I El L__ _____ m OXYGEN WIRE FURNISHED WITII LIGHT m MOVE L22A18 TO CA IS LIGf T CIRCUIT BREAKER WHEN POS7 1 Bus Bar LIGHTS ARE INSTALLED 2 Circuit Breaker 3 Rheostat 4 Landing Gear Visual Indicator...

Page 828: ...BAN hAP f IP iii HORIZON L2 NLI GI RO TAB POSITION INDICATOR L2H L2G L2F L2E ZL n IjI DIRECTIONXL L 7J P 4TE L i i2 cI I L2K L CLOCI LIGuTe fi3n 5 IRC I TT E3F EAhTF NT cn TCF i L2C n L D 10 P C rccir...

Page 829: ...This page intentionally left blank 14 132 E5...

Page 830: ...8 LIGHTS I WIRE FURNISHED WITH LIGHT IL23D19 3 1 BUS BAR 2 CIRCUIT BREAKER 3 RHEOSTAT r i i 4 LANDING GEAR VISUAL INDICATOR LIGHT CLEAR 5 RHEOSTAT LIGHT BLUEIWHITE 6 TRIM TAB INDICTOR LIGHT BLUEIWHITE...

Page 831: ...This page intentionally left blank 14 134 E5...

Page 832: ...5B20 LIGHTS L10 B20 CONNECTOR L26B20 TRANSISTOR L103j320N I OMNI DIMMING I I COMPASS L29C 18 L28A20 RIGHT ENGINE INSTRUMENT LIGHTS FUEL SELECTORL28B20 128 18 L28D18 LEFT L29R18 R OXYGEN PANEL LIGHTS I...

Page 833: ...4B20 L58A20 i ELEVATOR L32A20 TAB L39C2 L RED INDICATOR BLA I eP C L54D20 FLAP BI I I I POSITION rr FLIGHT L39D201 INSTRUMEh T AILEROh L331320 E DIMMING TAB I _ RED L54E20 7 INDICATOR PI LL69A20N BLAC...

Page 834: ...ZO ELEVATOR TAB L31jC20 RED L L43B20 L43C 20 7 INDICATOR lil L44f320 Lj8 20 C I L102D20 FLAP B POSITION IIr BLACK EI L39D20 FLIGHT INSTRUMENT I LH RH AILERO L33B20 E DIMMING I ENGINE ENGINE TAB I RED...

Page 835: ...GE RED L56A20 L90A20 L TO L64 20N A BLACK TO TO OPTIONAL CABIN RADIO A FLIGHT LIGHTS LIGHTS INSTRUMENT WIRE FURNISHED WITH LIGHT REF WHEEL CLOCK I L102FZO POST LIGHTS L39E20 CONNECTED TO BUS NO 2 WHEN...

Page 836: ...LIGHT I AQ HOUR METER SUCTION A D F INDICATOR GAGE DEICE PRESS J RE O CYGEN 2nd ALTIMETER OR AIRSPEED 1 LIGHT L29K18 L29L18L29M18 j L29N18L29 P18 L29QlP L29R16 L29S1B n B n BI IP TURN 6 DIRECTIO RATE...

Page 837: ...F GAGE IC3 DEIGE PRESSURE INDICATOR 2nd ALTIMETER OR AIRSPEED r LIGHT L29K18 13 PL291 118 L29N1 L29P18 L29 18 L29R18 IC11 El El nlcll L29L18 TCR 6 DIRECTIO RATE OF OMNI OMNI RH ENGINE LH ENGINE BA K...

Page 838: ...OmETEn i I SPEED WHITE I I L J I I wHlrt GYRO LOAD BLACK L69CZO METER HORIZON BLACK Y I VBLACK TO OPTIONAL WHITE BLACK L BLACK 7 WHllE ADF ALTITUDE BLACK BLACK LOAD METER BLACK BLACK WHITE I I WHITE T...

Page 839: ...R SPEED WHITE I I I I I GYIO LOAD BLACK L64C10 METER HORIZON BLACK Y Y BLACK TO OPTIONAL WHITE BLACK L BLACK WHITE ADF ALTITUDE BLACK LOAD METER BLACK BLACK I I Utl TURN COORDINATOR 70 OIIIONALADF OUA...

Page 840: ...E L56D10 r 56820 OmHI 1 THIPE LIOHTI IE CONNICTED TO THE D1MMINO TII NSI IOS WHEN OPTIONAL FLIGHT INSTRUMENT POST LIGHTS ARE NOT INSTALLED OMNI 3 1 BUS NO T 2 BUS NO 2 FLIGHT INSTR UMENT POST LIGHTS O...

Page 841: ...WHITE L 7 L81 20N 1 L IIIIOH _L BLACK WHITE TURN COORDINATOR L57C20 BLACK WHITE DIRECTIONAL GTRO BLACK 7 WHITE VER rlCAL SPEED L57520 e BLACI WHITE i AIR PRESSURE No 2 Bu L57D20 L79A20N i saji3153 r0...

Page 842: ...II ADF BLACK WHITE TURN COORDINATOR L57C2C BLACK WHITE OIIIECTIONAI GYRO BLACK WHITE VERTICAL SPEED L57520 e BLACK 7 WHITL i z AIR PRESSURE No 2 Bui 5or L57D20 L79A20H a 1 3 5a L57D20 1 TO INSTRUMENT...

Page 843: ...ltlON rLAP tl V 701 POSITION r I I 139I10 LH RH t39120 ENGINE ENGINE NOT USED GAGE GAGE I I MODELS 1 8ui No 3 I 555 a No IE55 I IG THESE LIGHTS ARE CONNECTED TO vIluIL DIMMING TRANSISTOR WHEN OPTIONAL...

Page 844: ...I AMMETER i L43B20 LI BLACK 7 WH17E LI 1 H TACHOMETER I BLACK WHITE MANIFOLD PRESSURE BLICK 7 WHITE FUEL PRESSURE BLACK L WHITE LH LOAD METER BCACK WHITE RH LOAD METER OUANTITY WHlrE _ BLACK WHITE LH...

Page 845: ...Light Switch 2 Nose Baggage Light and Switch Nose Baggage Compartment Light TE 1 thru TE 767 BAGGAGE LIGHT SWITCH ASSY ZL 0 LBZA D J COVRTESI LIGHT BLK T f BAGGAGE LIGHT SWITCH L_1_J s r JaP lol Nose...

Page 846: ...Light And Switch Assembly Nose Baggage Compartment Light TE 768 thru TE 848 TH 1 thru TH 185 To BATTERY C P12A20 P13A20 RE LAY TO L77A20 T COURTESY BLACK LIGHT 1 Fuse 2 Nose Baggage Light Switch 3 Lig...

Page 847: ...t31D20S 2 Switch3 Courtesy Light I 55 384 234 Courtesy Light TE 768 thru TE 848 TH 1 thru TH 185 TO NOSE BAGGAGE COMPARTMENT LIGHT LL77A20 c L 7B2o L77C20 C NC L34020N 1 Switch I 2 Courtesy Light Fa3...

Page 848: ...RTESY LIGHT SWITCH BPI P RY LBIAZ lele2o clalcloclsl 020 0 81E2__1 RELAY FUSE BLK BLK OCOURTESY CIG HT 5 BLK BLK Courtesy Light 00 1668 thru TC 1935 except TC 1913 To NOSE BAGGAGE COMPARTMENT LIGHT CO...

Page 849: ...93A18 C585E18 I C591A18N CjSjF18 C590B18 Q r C593 18 t t 2 h 3 C587A18S 1 Autopilot Circuit Breaker 5 Vacuum Failure Light 2 Vacuum Switch 6 Ram Air Solenoid N C 3 Vacuum Pressure Relay 7 Pressure Swi...

Page 850: ...96A18 C586A1 5 IP A i CSa5F16 C589A18N P C585H18 C595A18 NC n L f P C587i 18S II 1 Autopilot Circuit Breaker 2 Vacuum Switch 3 Pressure Switch 4 Ram Air Solenoid N C 5 Vacuum Failure Light 6 Pressure...

Page 851: ...585A18 J Cjg F18 C596AIB NO h C589A1SN L CI m No r C585H18 C595A18 v2 NC h L_1 C587A18S L i Autopilot Circuit Breaker 2 Vacuum Switch 3 Pressure witch 4 Ram Air Solenoid N C 5 Vacuum Failure Light 6 P...

Page 852: ...22 1 16 CE16A22 20 25 Cjj9A22 9 D J BACK 13 1 17 C51TA2Z 22 26 C560A22 9 E K COURSE Cj69A18 i 1 21j Cj21A22 t3 ii 27 t CS27A22 I I I I I SwITCH 1 35 C535A22 2 28 C561A22 9 Fl 25 29 C529A22 2 21 C 70A1...

Page 853: ...13 1 29 Cj29A2 21 26 C560A22 9 E IP COljRSE t C569A18 27 C327A22 7 Dj SWITCH 1 17j Cj17A22 j t2 28 Cj61A22 9 F 2 15 C600B22 29 Cj29A22 2 21j 2 CS2 2 23 L__Jm 1 33j C535X22 24 30 t Cj62A22 10 12 SA 25...

Page 854: ...35A22 24 31 Cj31A22 6 Fl e C533A22 A CS70A18N 25 32 Cj63A22 9 C II Cj04A22N B L E C604A22 26 1 15 C51jA22 0 C564A22 9 A 27 33 2 28 C605A22 i C C60jA22 2e w C534A22 9 B 1 27 C527A22 D 1 49 C580A22 29 3...

Page 855: ...K BLACK P BC ABC IF11 C1 RED X I RED D6 D IND UNINIUL 1 0 LlrD Olr Wilt WHIIE GROUND UNINSULAlED BLEED OFF WHITE WIRE TO CONNECTOR SHELL a qcr I I LSCK 1 Hor Slrob 2 3 Por r UniI I _ i B PIBC c 5 Winp...

Page 856: ...IND UN1NIUL TtD BLttD 01f WIRE Q GROUND UNINIULATtO IttD Olr WIRE TO CONHECIOI IHltt WHITE WHITE i I I I 1 Bui Bar Cir vii r oL r 3 Porr r Unic 4 Po r Uni Conn tor BLACK I IBLACW 5 Wing 6 Ligh Uni Con...

Page 857: ...RED X I RED DEAD END UNINSLILATED WIRE Q GROUND UNINSULATEO ILLED Orf W lt r0 CONNECTOR SHELL WHITE WHITE I I I I I 6u Oar 2 Cir ui I oL 3 Por Unil 4 Por r Uni BLACK I IBLACK 5 WinR 6 Lighl Unii Eonn...

Page 858: ...END VNIN ULIIID BLttDO r WIRE L g GROUND UNINIULaTED BLtlOClr Vllt 10 CONNLCTOLL IHILI WHITE WHITE I i I I I Bui Bar 2 Cirruii BI otcr 3 Poser Unit 4 Pox r Unit Conns tor 9rP CK I lslacK 5 Winp Conn t...

Page 859: ...61A20 2v L61C20 TC 1261 AND AFTER AND D55 SERWLS 3 TE 730 THRU TE 767 4 IC L62A20N L62B20N BLACK 1 8us Bar 2 Circuit Breaker WHITE 3 Power Unit RED 4 Strobe Light Unit 5 NavStrobe Switch I Bullock Str...

Page 860: ...3 4 Ot O I I I I 1 7i 0 14A20 CI a14D20 U 4G20 L25C20 iFL23B20 L23A2o 5 NAVIGATlOh LIGHTS I I el U L22A20Ej _L LH COM I FLAP OPZ i LIGHT SCOU L FLrlP 2 K4B1F 013 _L C 1 1 i 1 L25 420 CL76A20W _L a 4F2...

Page 861: ...S I f LH CO L FLAP P o L L22A20N i OPEhT LIGHT K4B18 fl 5 K4A18 CO L FLAP L P L25A20 C L76 211h j L B ZOh 1 a I 1 i II 1 W4F20 W4E20 I I II L25B20 RH COU L FLAP OPE LIGHT 1 Annunciator Lights IC9B18 C...

Page 862: ...E18 S LH COWL FLAP MOTOR O P L25A20 C a W4A20 5A 3 L71A20N W4J20 IF1 W4E OI I I I I L46A20 2 CIGARETTE LIGHTER L22A20N L25B20 RH COWL 1 L23A20 NAVIGATION LIGHTS FLAP OPEN 2 K9B18 RH COU L FLAP MOTOR L...

Page 863: ...G RETTE LIGHTER RH COWL FLAP YOTOR L15B20 I 9B15 KSA1S L13A20 iAVICAllOii LIGHTS _L RH CO L 1 WJT 0 FL P OPEN LIGHT r Xnnunciator Lights P nnunciator Press to Test Switch L76 20h 9 t L 61 30 I I 1 3 l...

Page 864: ...tF LANDING L L46010 6 L46820 IN DICITOI1 CiGARfTTf LIGHTER AND r DOOR DOOR ANNUNCIATOR L45820 j AJAR NC P D M Ptl T Li wii SWITCH L 45 10N 14CIZO _L 46 20 WlllP 20 41 ALTERNATOROUT 4 NOT USED 855 AND...

Page 865: ...Ram Air Boot Ram Air Anti ice Installed with Radar Prior to TC 1658 TE 959 and TE 968 TH 437 sAi RAM AIRCIRCUIT BREAKER H19A20 UP RAM AIR H20A20 ANTI ICE BOOT H17A20N LANDING GEAR UP LIMIT SWITCH 855...

Page 866: ...67A20 f 1 I I L E63A20 1 E69A20 1 L E70A20 7 1 E66B20N E72AZ coii llt E66A20N COll 66C20N 6602 WIRES WIRES Ixl T I II PICK UP WIRES PICK UP WIRES LH PROP GOVERNOR RH PROP GOVERNOR Prop Synchronizer 7...

Page 867: ...SECTION OVERHAUL AND REPLACEMENT SCHEDULE...

Page 868: ...nction as the aforementioned factors cannot be controlled by the manufacturer TABLE 201 I OVERHAUL AND REPLACEMENT SCHEDULE Item Overhaul or Replace NOTE All items not listed are to be overhauled or r...

Page 869: ...r 10 cleanings 300 hours or annually whichever occurs first Engine controls On condition Engine baffle seals On condition or every 10 years Engine vibration isolator mounts On condition Exhaust system...

Page 870: ...me Replacement Schedule SI 300 17 or subsequent See Supplier Data CAUTION at the end of this chapter Aero Accessories Pump Part Number AA442CW 12 or AA442CW 14 replace at 500 hours time in service Aer...

Page 871: ...l other hoses on condition Float valve On condition Fuel filler caps On condition INSTRUMENTS Turn coordinator On condition Altimeter Inspect and calibrate Every 24 months per FAA Directive Directiona...

Page 872: ...ace on condition Starter relay On condition Generator or Alternator On condition Landing gear selector switch Every 5 000 hours or on condition Battery At 50 of useful life las stated on the battery o...

Page 873: ...ostatically test every 3 years DOT Regulation Replace after 24 Light weight DOT 3HT 1850 years or 4 380 refills MISCELLANEOUS Seat belts or shoulder harnesses Inspect every 12 months Replace on condit...

Page 874: ...SECTION PERIODIC INSPECTIONS...

Page 875: ...e environmental conditions Airplanes operated in humid tropics or in cold damp climates etc may need more frequent inspections for wear corrosion lubrication and or lack of maintenance Under these adv...

Page 876: ...ended to be changed at five year periods regardless of airplane time I Additional publications are listed on the web at http pubs raytheonaircraft com For information on these publications contact the...

Page 877: ...ration temperature and fluctuations 5 ALTERNATOR GENERATOR Check for proper output and unusual noises 6 PROPELLER OPERATION Cycle propeller and check for proper rpm drop and smoothness of operation 7...

Page 878: ...tachment cracked or broken lenses Check switches knobs and circuit breakers for looseness and operation 23 STALL WARNING SYSTEM Check for proper operation and heating of the unit 24 RADIO OPERATION In...

Page 879: ...proper fluid level deformation and security 5 OIL DIPSTICK Check the dipstick for rust and general condition Inspect the dipstick tabs for security and that the tabs are not bent 6 OIL SUMP DRAINS AND...

Page 880: ...or missing nuts and clamps Check for thin wall condition which may occur due to normal internal erosion on stacks which have long service time 21 FIREWALL Check for wrinkles damage or cracks Check al...

Page 881: ...ter check for the security of attachment 36 ELECTRIC PROPELLER DEICER Check for service damage to the deicer heaters brush rods springs and brushes Check the lead strap and all other clamps connectors...

Page 882: ...ve flight loading 2 STRUCTURE Check for cracks deformation and concealed damage Check for loose or missing rivets Refer to Section 3 of this shop manual for inspections for fuselage web cracks at the...

Page 883: ...0 hour inspection and at the first 100 hour inspection after each installation of the wing attach bolts Refer to Section 3 for wing bolt nut and fitting inspection criterion and frequency 16 PITOT TUB...

Page 884: ...d crank 1 2 turn to determine that oil is being picked up on the worm gear The oil level should be maintained no more than necessary to cover 1 2 of the diameter of the worm gear Install oil filler pl...

Page 885: ...d shoulder harnesses for proper operation condition and security of attachment Inspect floorboards for condition and seat attachment Check for operation of the seat stops 15 OXYGEN SYSTEM Check condit...

Page 886: ...R FUEL SYSTEM Check lines for connection and chafing 8 HEATER DUCTING AND WIRING Check for security and chafing 9 AIR CONDITIONER EVAPORATOR Check for condition and secure attachment 10 HEATER IRIS VA...

Page 887: ...hinges Refer to Section 2 1 i I I 6 STATIC PORTS Check for obstruction and clean as necessary 7 PLUMBING Check for leakage cracks chafing condition and security 8 ELECTRICAL WIRING AND EQUIPMENT Inspe...

Page 888: ...AND TIRE Check wheel for cracks and tire for wear damage condition and proper inflation Check wheel bearings for condition and wear 2 LANDING GEAR STRUT Inspect the shock strut and components for crac...

Page 889: ...I j I extension and retraction cycles when performing the landing gear retraction inspection For more specific information which may be necessary to accomplish the following items refer to Section 5 1...

Page 890: ...tions 2 and 5 Check for binding 14 SAFETY SWITCH Check for security proper rigging and operation 15 NOSE GEAR UP TENSION Check the up tension on the nose gear Refer to Section 5 16 NOSE GEAR STEERING...

Page 891: ...em Turn the deicer switch ON and station an assistant in the airplane to observe the ammeter Flex all accessible wiring particularly the lead straps leads from the slip ring assembly and the fire wall...

Page 892: ...placed j Check for proper spacing between the brush block and slip rings as indicated in Figure 11 25 11 30 or 11 36 in Section 11 If this distance is not within the specified limits loosen the mounti...

Page 893: ...aces Instrument Air Filters Replace instrument line supply filters at or As noted before 100 hours under extremely dusty conditions CAUTION To avoid damaging the barometric sensor disconnect the autop...

Page 894: ...y 100 hours andlor annually damaged plating and evidence of overheating c Shock Absorber Check surfaces for cleanliness free from oil or Every 100 hours and or annually grease deterioration d Wheel We...

Page 895: ...red and looking for evidence of internal structural failure The second level Is concerned with a more detailed inspection of any damaged areas which were indicated in the findings of the first level i...

Page 896: ...Check area surrounding the landing gear attachment points Wing Center Section a Check wing attachment fittings for cracks Perform a Dye Penetrant inspection b Inspect plumbing wiring and actuator for...

Page 897: ...n any damaged area found in the first level inspection Landing Gear a Place airplane on jacks and check shock strut for free up and down movement b Remove tires and inspect internally for cuts or brok...

Page 898: ...ompartment floor boards and inspect the keel structure and supporting members for damage b Inspect wheel well structure and surrounding areas for signs of structural failure c Test avionics radar ante...

Page 899: ...necessary to proceed to the second level inspection F RST LEVEL INSPECTION Prior to next flight WARNING Even though wrinkles in the wing or fuselage skin surface may be alight enough to be considered...

Page 900: ...for cracks abnormal wrinkles and loose or missing rivets Fuselage Aft a Inspect the entire length of the external skin surface for cracks stress wrinkles and loose or missing rivets b Check the empenn...

Page 901: ...elage Nose a Remove floorboards and inspect the keel structure and supporting members for damage b Examine any fixed equipment for loose broken or cracked mountings c Operational test avionics radar a...

Page 902: ...theon Aircraft Company Wichita Kansas 67201 for assistance LOG BOOK ENTRY Following a turbulent air inspection an entry covering the extent of inspection the damage and the repair if applicable must b...

Page 903: ...s Normally two or more points will be found the entry and the exit points Antennas are frequently an entry point of lightning and should be carefully inspected for evidence of arcing sooting or pittin...

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