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Raytheon BEECH BARON 58P, Maintenance Manual


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Summary of Contents for BEECH BARON 58P

Page 1: ...d After Maintenance Manual NOTE This manual was formerly called the Beechcraft Baron 58P 58PA Barcn 58TC 58TCA Maintenance Manual Copyright 0 Raytheon Aircraft Company 2002 P N 102 590000 5 P N 102 59...

Page 2: ...d Raytheon Aircraft Company EXPORT STATEMENT Exported under the authority of license exception TSU 7hese commodities technology or software were exported from the United States in accordance with Expo...

Page 3: ...Rev Date Inserted By Date Inserted By Date Inserted By No No No A23 11 17 97 A24 1 9 02 A25 8 21 02 ATP When a revision is inserted the revision number the date the revision is inserted into the manua...

Page 4: ...91 102 590000 5A8 March 23 1979 Introduction 21 28 61 71 81 102 590000 5A9 May 25 1979 28 61 NOTE A List of Effective pages will be in the front of each chapter ic publications are assigned a part nu...

Page 5: ...102 590000 5A13 November 12 1980 Introduction 24 61 102 590000 5A14 March 31 1981 5 11 57 91 102 590000 5A15 June 18 1981 23 32 102 590000 5A16 March 31 1982 5 25 102 590000 5A17 June 21 1982 5 30 102...

Page 6: ...ding gear and actuator ovemaul and replacement A24 schedule in Chapter 5 10 00 27 2 Nov 15 93 Revised FLAP DRIVE CABLE CONNECTION in Chapter A24 27 50 00 32 1 Jul 16 99 Add LANDING GEAR WARNING TEST t...

Page 7: ...ditional data and revised supplier publications data 5 10 00 Propeller overhaul data now refers to supplier data Added data on engine baffle seals and instrument air manifold check valve 5 20 00 Chang...

Page 8: ...A Page A25 B Page B Page A25 All INTRO EFF 1 INTRO EFF Jun 28 02 All INTRODUCTION 1 thru 14 INTRODUCTION Jun 28 02 All 5 EFF 1 and 2 5 EFF Jun 28 02 All 5 TOC 1 5 TOC Jun 28 02 All 5 10 00 201 thru 2...

Page 9: ...CHAPTE R SECTION SU BJ ECT PAGE DATE Introduction Effectivity 1 Jun 28 02 Introduction 1 Jun 28 02 2 Jun 28 02 3 Jun 28 02 4 Jun 28 02 5 Jun 28 02 6 Jun 28 02 7 Jun 28 02 8 Jun 28 02 9 Jun 28 02 10 J...

Page 10: ...102 590000 23 The Beech Baron 58TC Wiring Diagram Manual P N 106 590000 13 or 106 590000 23 The Beech Baron 58P Wiring Diagram Manual P N 102 590000 59 The Beech Baron 58P and Baron 58TC Beech Manufac...

Page 11: ...rganized into four levels The four levels are GROUP Identified by different colored divider tabs These are the primary divisions of the manual that enable broad separa tion of content Typical of this...

Page 12: ...s applicable to all serial numbers listed on the title page except where specifi cally stated LIST OF EFFECTIVE REVISIONS The List of Effective Revisions A page following the title page of the manual...

Page 13: ...nt revision There will not be a revision bar if text was deleted from the page REVISED ILLUSTRATIONS Revised art may be identified by a revision bar printed on the side of the page for major changes o...

Page 14: ...orm X 30042 Continental TS10520 Series Aircraft Engines Teledyne Continental Motors Air craft Products Mobile Alabama Parts Catalog Form X 30043A Continental TSIO 520 Series Aircraft Engines Teledyne...

Page 15: ...yal Handbook Recommended Handling and Storage Procedures for Bladder Type Fuel and Oil Cells P N FC1473 73 Uniroyal Inc Mishawaka Indiana Goodyear Manual Fuel Cell Repair P N AP 368 Goodyear Aerospace...

Page 16: ...a Mesa California Operating Instructions for Model CIR 11 Emergency Locator Transmitter System Transmitter P N TR70 13 Collins Communications Components Corporation Costa Mesa California Owners Manual...

Page 17: ...20 Scheduled Maintenance Checks 50 Unscheduled Maintenance Checks 6 DIMENSIONS AND AREAS 00 General 7 LIFTING AND SHORING 00 General 8 LEVELING AND WEIGHING 00 General 9 TOWING AND TAXIING 00 General...

Page 18: ...ral 21 AIR CONDITIONING 00 General 10 Compression TJ 3 and After 20 Distribution 30 Pressurization Control TJ 3 and After 31 Door Seal Pressurization TJ 3 and After 40 Heating 50 Cooling 22 AUTO FLIGH...

Page 19: ...neral 60 Emergency 27 FLIGHT CONTROLS 00 General 10 Aileron and Tab 20 Rudder and Tab 30 Elevator and Tab 31 Stall Warning 50 Flaps 70 Gust Lock and Damper 28 FUEL 00 General 10 Storage 20 Distributio...

Page 20: ...Nose Gear and Doors 30 Extension and Retraction 40 Wheels and Brakes 50 Steering 60 Position and Warning 33 LIGHTS 00 General 40 Exterior 34 NAVIGATION 00 General 10 Flight Environment Data 35 OXYGEN...

Page 21: ...STRUCTURES 00 General 52 DOORS 00 General 10 Passenger Crew 70 Door Warning 53 FUSELAGE 30 Plates Skins 54 NACELLES 00 General 55 STABILIZERS 10 Horizontal Stabilizer 20 Elevator 30 Vertical Stabilize...

Page 22: ...ITLE 50 Flight Surfaces 61 PROPELLERS 00 General 10 Propeller Assembly 20 Controlling 71 POWER PLANT 00 General 10 Cowling 72 ENGINE RECIPROCATING 73 ENGINE FUEL AND CONTROL 30 Indicating 74 IGNITION...

Page 23: ...8TC MAINTENANCE MANUAL CHAPTEWSYSTEM INDEX GUIDE CONTINUED SYSTEM CHAPTER SUBSYSTEM SECTION TITLE 80 STARTING 00 General 10 Cranking 81 TURBINES 00 General 91 CHARTS Jun 28 02Pagel4 INTRODUCTION A25 C...

Page 24: ...CHAPTE R TIME LIMITS MAINTENANCE CH EC KS...

Page 25: ...ionary Notice 201 Operational Inspection 203 Power Plant Nacelles Wings and Carry through Structure 207 Cabinand BaggageCompartment 209 Nose Section Rear Fuselage and Empennage 211 Main Gearand Brakes...

Page 26: ...1 Jun 28 02 202 Jun 28 02 203 Jun 28 02 204 Jun 28 02 205 Jun 28 02 206 Jun 28 02 5 20 00 201 Jun 28 02 202 Jun 28 02 203 Jun 28 02 204 Jun 28 02 205 Jun 28 02 206 Jun 28 02 207 Jun 28 02 208 Jun 28 0...

Page 27: ...NANCE MANUAL CHAPTER 5 TIME LIMITS MAINTENANCE CHECKS LIST OF PAGE EFFECTIVITY CONTINUED CHAPTER SECTION SUBJ ECT PAGE DATE 205 Jun 28 02 206 Jun 28 02 207 Jun 28 02 208 Jun 28 02 209 Jun 28 02 210 Ju...

Page 28: ...he starter con trol circuit breakers and the Landing Gear circuit breaker This will kill power to the starter control and Landing Gear Control relay Airplanes operated for Air Taxi or other than norma...

Page 29: ...n requirement Any pitting corrosion cracking distortion or visible wear noted during the replacement will also constitute the requirement for an overhaul Nose Gear On Condition Leaking orcollapsed str...

Page 30: ...system On Condition Oil cooler On Condition Replace when contaminated p peller Hprt2ell lafestrevision oitlartleilssrviee LenerS1 PiopeNer UcCauiwi of McC ulevselvicssuilefin Propeller controls On Co...

Page 31: ...On Condition Dry air pressure gage On Condition Cabin altitude controller On Condition Manifold pressure gage On Condition Airspeed indicator On Condition Cabin climb gage On Condition Cabin altitude...

Page 32: ...r UTILITY SYSTEM Cabin heater Every 1 000 heater hours or when pressure decay test requirements cannot be met Heater ignitor and plug On Condition On Condition Heater fuel pump Heater fuel spray noizl...

Page 33: ...00 hours FLAPS AND FLIGHT CONTROL Flight controls On Condition Aileron tab actuator On Condition Elevator tab actuator On Condition Rudder tab actuator On Condition Flap motor and drives Every 2 000 h...

Page 34: ...am in accordance with 14 CFR Parts 43 and 91 consist of but is not limited I to inspection items listed in the Inspection Guide any applicable Airworthiness Directives issued against the airframe or a...

Page 35: ...the Technical Manual Distribution Center TMDC at 1 800 796 2665 fax 316 676 4824 or E mail TMDC Raytheon com All electrical systems operational inspections are to be made using an extemal power sourc...

Page 36: ...formance of the magneto by performing the MAGNETO DROP OFF CHECK specified in the applicable Pilot s Operating Handbook 9 POWER CHECK Check as outlined in the applicable Pilot s Operating Handbook 10...

Page 37: ...er operation and feel for positive detent and proper placarding 24 ALL LIGHTS Check for condition attachment cracked or broken lenses Check switches knobs and circuit breakers for looseness and operat...

Page 38: ...Tighten spark plugs to proper torque and check ignition harness condition and for proper attachment 4 COMPRESSION Perform differential compression test 5 PLUMBING Inspect plumbing and associated acce...

Page 39: ...nt Check cylinders for broken cooling fins and loose or missing base nuts 21 EXHAUST SYSTEM Check for deformation security cracks leaks loose or missing nuts and clamps Check for thin wall condition w...

Page 40: ...RVICING in Chapter 36 00 00 of this Maintenance Manual 37 ELECTRIC PROPELLER DEICER Check for service damage to the deicer heaters brush rods springs and brushes Check the lead strap and all other cla...

Page 41: ...for leakage chafing condition and security 9 ELECTRICAL WIRING AND EQUIPMENT Inspect for chafing damage security and attachment 10 FLAP LIMIT SWITCHES Check for condition security and freedom of oper...

Page 42: ...ND PULLEYS Check the flight control components cables and pulleys Replace control system components push rods turnbuckles end fittings castings etc that have bulges splits bends or cracks Check contro...

Page 43: ...Maintenance Manual for detailed inspection procedures TJ 3 and After Check doors for condition and attachment Check latching mechanism for proper engagement and ease of operation On TJ 3 and After ch...

Page 44: ...ment and cracks 4 BATTERY Inspect for dean tight connections and correct fluid level Add distilled water as required Inspect vent hose at battery box for obstructions The battery box should be washed...

Page 45: ...intenance Manual 7 STATIC PORTS Check for obstruction and clean as necessary 8 PLUMBING Check for leakage cracks chafing condition and security 9 ELECTRICAL WIRING AND EQUIPMENT Inspect for chafing da...

Page 46: ...pect in accordance with the directions provided in Service Bulletin Number 2147 I NOSE GEAR MECH INSP 1 WHEEL AND TIRE Check wheel for cracks and tire for wear damage condition and proper inflation Ch...

Page 47: ...n apply a sharp load by hand in an aft direction against the nose gear strut If this causes the main gear wheels to move approximately 1 2 to 1 inch it is a good indication that the gear actuator asse...

Page 48: ...ce Manual Check for binding 14 SAFETY SWITCH Check for security proper rig and operation 15 NOSE GEAR UP TENSION Check the up tension on the nose gear per Chapter 32 30 00 of this Maintenance Manual 1...

Page 49: ...g b With the engine shut down turn the deicer switch ON and feel the deicer boots on the propeller for the proper sequence of the heating elements The presence of local hot spots indicates damage to t...

Page 50: ...inch or if over any 4 inch are it ex ceeds 0 002 inch refer to step h g Examine the brush mounting brackets and housing for cracks deformation or other indications of damage Check for tight connectio...

Page 51: ...pter 32 20 00 b Disassemble the nose landing gear as instructed in the Baron 58P Beech Manufactured Components Mainte nance Manual c Wash all existing corrosion preventive compound and grease from all...

Page 52: ...s to prevent damage to the barometric altitude sensor 3 Pitot and Static Lines Check for obstructions by applying reverse air 100 Hours or as required pressure not to exceed 20 psi to the ends of the...

Page 53: ...se deterioration Check strut inflation as annually noted in Chapter 12 Clean exposed surface of shock strut piston with clean cloth moistened with hydraulic fluid e Wheel Wells Clean foreign material...

Page 54: ...th a more detailed inspection of any damage areas which were indicated in the findings of the first level inspection If it is determined by the first level inspection that there is no damage to the ai...

Page 55: ...or missing rivets Check cowling attachment fittings for alignment or damage Inspect engine control cables for smooth operation and check plumbing and wiring for security and attachment Inspect engine...

Page 56: ...loose or missing rivets Inspect empennage and control surfaces for freedom of movement SECOND LEVEL NOTE Because shock loading may be transmitted along one structural member to another carefully inspe...

Page 57: ...r damage Inspect wheel well structure and surrounding areas for signs of structural failure Test avionics radar antenna plumbing and wiring for proper operation 14 Fuselage Center and Aft Examine stri...

Page 58: ...level inspection FIRST LEVEL I WARNING WARNING Even though wrinkles in the wing or fuselage skin surface may be slight enough to be considered as negligible a close inspection of the internal support...

Page 59: ...attachment 6 Fuselage Center Section Inspect external skin surface for cracks wrinkles After encountering turbulent air and loose or missing rivets 7 Fuselage Aft Section Inspect the entire length of...

Page 60: ...d equipment for loose broken or cracked mountings Operational test the avionics radar antenna plumbing and wiring 12 Fuselage Center and Aft Examine stringers frames and sidewalls for After encounteri...

Page 61: ...covering the extent of inspection the damage and the repair if applicable must be noted in the airplane permanent records INSPECTION AFTER LIGHTNING STRIKE 1 Propeller At times the difficulty is not...

Page 62: ...xit are found the structure between these points should be carefully inspected Attention should be given to hinges and hinge pins for possible pitting Cables pulleys bearings bolts and all bonding jum...

Page 63: ...CHAPTE R DIMENSIONS AND AREAS...

Page 64: ...N SUBJECT PAGE DATE 6 EFF ECTIVITY CONTENTS 1 Nov 30 76 6 00 00 1 Nov 30 76 2 Jan 9 76 CHAPTER 6 DIMENSIONS AND AREAS TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE Dimensions And Areas 6 00 0...

Page 65: ...USED ON TJ SERIALS ONLY tTK I AND AFTER ic leLANDING LIGHTS TJ 2 fHRU TJ 93 TK l THRU TK 28 te i I LANDING LIGHTS TJ 94 AND AFTER TK 29 AND AFTER 80 IN DIA 78 IN DIA e c 453 840 35s so 1N _ l 110 2011...

Page 66: ...1 1848 SP l WL 100 00Q FVsII OE Sri 611 FIONT Silll 161 tL iSr II 1141 800088 Sr I 212 750 VERTICAL STABILIZER 0 160 36 900 II 1 109 3051r108 201 36 150 3 900 113 172 11 r103 660 122 6 200 112 7 123 1...

Page 67: ...CHAPTE R LIFTING AND SHORING...

Page 68: ...CHAPTER PAGE 7 00 00 Lifting And Shoring Maintenance Practices 201 Jacking 201 Jacking W th Model 300 jack Itquippea w tn Ironair Kit 201 Jacking With Model 300 Jack Without a Tronair Extension it 202...

Page 69: ...P 58TC MAINTENANCE MANUAL CHAPTER 7 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 7 EFFECTIVITY 1 May 22 87 7 CONTENTS 1 May 22 87 7 00 00 201 May 22 87 202 May 22 87 END 7 EFFECTIVITY Pa...

Page 70: ...one jack should be on the jack extension to the tail utilized at a time For safety of of the airplane at this time personnel and the airplane wind Damage to the airplane and the velocity in any direc...

Page 71: ...ACKS TRONAIR tiedown device with suitable weight 500 MODEL 100 OR EQUIVALENT pounds such as P N 35 590021 embedded in a movable concrete filled barrel or a Attach a suitable weight to anchor equivalen...

Page 72: ...CHAPTE R LEVELING AND VVEIGHING...

Page 73: ...CHAPTER SECTION SUBJECT PAGE DATE 8 EFFECTIVITY CONTENTS 1 Apr 1 75 8 00 00 201 Apr 1 75 CHAPTER 8 LEVELING AND WEIGHING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 8 00 00 Mainten...

Page 74: ...om the upper Suspending the plumb bob in a can of light level point located just aft of the cabin door engine oil will assist in stabilizing it b Install a screw approximately three inches long in the...

Page 75: ...CHAPTER TOVVING AND TAXIING...

Page 76: ...55P 58TC MAINTENANCE MANUAL CHAPTER 9 TOWING AND TAXIING TABLE OF CONTENTS SUBJECT CHAPTER PAGE 9 00 00 Towing And Taxiing Maintenance Practices 201 Ground Handling 201 Towing 201 END 9 CONTENTS Page...

Page 77: ...ARON 55P 58TC MAINTENANCE MANUAL CHAPTER 9 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 9 EFFECTIVITY 1 May 22 87 9 CONTENTS 1 May 22 87 9 00 00 201 May 22 87 END 9 EFFECTIVITY Page 1 A2...

Page 78: ...void unnecessary damage The care to avoid damaging the grease fol i owl ng procedures are prov i ded to fittings DO NOT attempt to tow reduce the possibility of ground damage the airplane backward by...

Page 79: ...CHAPTER PA RKING MOORING STO RAG E RTN TO SVC...

Page 80: ...v 30 76 204 Nov 30176 CHAPTER 10 PARKING AND MOORING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 10 00 00 Maintenance Practices 201 Parking 201 Mooring 201 STORAGE 10 10 00 Flyabie...

Page 81: ...reate higher lift brake control and depressing the pilot s brake pedals to on the wings If bad weather is anticipated it is advisable to pressurize the system Do not attempt to lock the parking nose t...

Page 82: ...a hangar 3 Run the engine at least five minutes at a tie down securely at the three tiedown points provided on the speed between 1000 and 1200 rpm with the oil temperature airplane Do not use hemp or...

Page 83: ...blue in color when installed Protect and support the spark plug leads with 1 Remove airplane batteries and ELT battery AN4060 1 protectors from the airplane and store in accordance withstandard 7 Pla...

Page 84: ...attery cable terminals to neutralize any battery acid that may be present 1 Lubricate all flight control surfaces hinge pins bearings bell cranks chains control rods and quadrants and m Instrument Pan...

Page 85: ...rs by hand through all compressions of the engines to check drained after a ground warm up Install engine oil 2 Chart for liquid lock Reinstall cowling and start engines in the 207 91 00 00 before fli...

Page 86: ...CHAPTER PLACARDS AND MAR KI NGS...

Page 87: ...1 Nov 30 78 11 20 00 1 Nov 30 78 2 Aug 1 80 3 Mar 31 81 4 Mar 31 81 CHAPTER 11 PLACARDS MARKINGS TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL Description and Operation 11 00 00 FAA R...

Page 88: ...model designation placard is located on the RH side of attached the fuselage adjacent to the inboard end of the flap The placard identifies the airplane by its model number and serial number Should a...

Page 89: ...ap Located on the right side of the fuselage at FS 151 00 r c I I C n 2 places PC8 OIL USE SAE 50 ABOVE 400 F USE SAE 30 BELOW 40 F TIE DOWN Located adjacent to the t i e 3 Places Installed on the und...

Page 90: ...UNLICENSED OPERATION UNLAWFUL OPERATION IN VIOLATION OF FCC JACK PAD RuLES SUBJECT TO FINE OR LICENSE REVOCATION Located on the AH fuselage just JACK ATTACH POINT forward and below the RH elevator TJ...

Page 91: ...INCHES OF PISTON SHOWING WITH AIRPLANE EMPTY EXCEPT FOR FULL FUEL AND WARNING I I I OILKEEP STRUT INFLATED 703 TO J INCHES RELEASE III IN STRUT BEFORE DISASStMBLING I I I OF PISTON SHOWING WARNING RE...

Page 92: ...bin door CAUTION BE SURE ALL ELECTRICAL POWER IS OFF BEFORE REMOVAL OR INSTALLATION OF THIS ACCESS COVER Located on the top of the left nacelle EXTERNAL POWER 24 VOLT Located on the outboerd of the le...

Page 93: ...CHAPTER SERVICING...

Page 94: ...r Belt Tension Adjustment 204 Pressurization System TJ 3 and after 204 Cleaning The Outflow And Safety Valve Fi Iters And Seats 204 Heating System 204 Brake System 204 Oxygen System 204 12 20 00 Sched...

Page 95: ...lage Access Openings 224 Wing Access Openings 226 Special Tools 228 12 30 00 Unscheduled Servicing 201 Deicing And Anti Icing Airplanes On The Ground 201 Snow Removal Frost Removal 201 Ice Removal 201...

Page 96: ...01 May 22 87 202 May 22 87 203 May 22 87 204 May 22 87 204A May 22 87 204B May 22 87 205 Oct 6 83 206 Oct 6 83 207 Oct 6 83 208 Oct 6 83 209 May 22 87 210 Oct 6 83 211 Oct 6 83 212 Oct 6 83 212A Oct 6...

Page 97: ...AND 58TC MAINTENANCE MANUAL CHAPTER 12 LIST OF PAGE EFFECTIVITY C nt d CHAPTER SECTION SUBJECT PAGE DATE 230 Aug 1 80 231 Oct 6 83 12 30 00 201 May 22 87 202 May 22 87 203 May 22 87 END 12 EFFECTIVITY...

Page 98: ...n procedures and maintenance practices used when servicing 58PIBaron 58TC Wiring Diagram Manual P N 102 590000 the various systems of the airplane Detailed maintenance 23C1 or subsequent For airplane...

Page 99: ...d from single filler in each wing or the filler the airplane open the sump drains to com in each of the optional wet wing tips plete the defueling operation providing single point filling for each sid...

Page 100: ...ecommends the use of ashless dispersant oil In order to When working on a refrigerant air cooling promote faster ring seating and oil con system observe the following special ser trol a straight miner...

Page 101: ...if the refrigerant step c If the compressor will charge is lost evidenced by oil loss not hold the entire system as The air conditioner system requires 13 15 described in step h and charge ounces of...

Page 102: ...tool placed at a point midway between the idler pulley and the compressor will register a NOTE belt tension of 70 to 90 pounds If no gage is available adjust until the belt If the spark plug fails to...

Page 103: ...aft and replace the protective cap If at any fuselage On TK 1 thru TK 84 the cylinder time in the process of or is located in the nose baggage compart purging the system or replacing the oxygen ment o...

Page 104: ...ure gener operation place an external bat ated during takeoff Increased tery in parallel with the output tire size can jeopardize proper of the external power unit before function of the landing gear...

Page 105: ...n s i de rabl e above recommended intervals or to exceed force causing injury to personel the intervals if justified Accurate water or property damage consumption data is a valid barometer to use for...

Page 106: ...Mark the wire remove and cotter pin to allow clearance for the measure the depth of insertion Inserting measuring wire Reinstall the shimmy the wire in the hole of the floating pis damper ton rather...

Page 107: ...R propeller assemblies 100 5 psi at 700F Increase the pressure I charge propeller air dome cylinder ps for every 10 degrees with dry air or nitrogen to 100 2 psi at of increase in temperature similarl...

Page 108: ...l cause an electrostatic waxed for a period of 90 days to allow the charge which attracts dust paint to cure Wash uncured painted sur faces with only cold or lu kewa rn never Remove oil and grease wit...

Page 109: ...with one of mend that these materials be dry the three commercial cleaners mentioned cleaned previously it will not be necessary to apply wax Each of these cleaners con a Brush the upholstery along th...

Page 110: ...STEM MA TERIAL SPECIFICA TION t ENDOR P ODUCTS Fuel Petrolatum VV P 236 Oil Manifold Pressure Air Lubricating Grease Gasoline MIL G 6032 L 237 Lehigh Chemical Co Pressure and Oil Resistant Chestertown...

Page 111: ...e operator user to determine the current revision of the applicable Military Specification prior to usage of that item This determination may be made by contacting the vendor of a specific item ITEM M...

Page 112: ...York Compound N Y Rust Foil No 652 2 Franklin Oil and Gas Co Bedford Ohio Kendex No 7038 Kendall Refining Co Bradford Pa 4 Lubricating Oil MIL L 6081 Gulflite Turbojet Oil No 1010 Gulf Oil Corp Pitts...

Page 113: ...ing MlL G 23827 Supernill Grease No A72832 American Oil Co 910 Grease Aircraft South Michigan Ave and Instrument Chicago ill High and Low Temperature Royco 27A Royal Lubricants Co River Road P O Box 9...

Page 114: ...Oi 1 Air Condi 500 Vi scos i ty Suni so No Vi rg i n i a Chemi cal and tioner 5 Smelting Co West Norfolk Compressor VA Texaco Texaco Inc 135 East 42nd Capella E Street New York NY 19 Aviator s MIL 0...

Page 115: ...Center St Paul Minnesota 33 Sealer EC801 Minnesota Mining and Manufacturing Co 3M Center St Paul Minnesota 34 Lubricating Aeroshell 7A Shell Oil Co 50 West 50th Grease Street New York N Y 35 Urethane...

Page 116: ...Memorial Drive Cambridge Mass 45 Cement Bostic 1024 United Shoe Machinery Corp B B Division 748 Memorial Drive Cambridge Mass 46 Trichloroethane Mll T 81533 Vulcan Materials Co Chemicals Division 6200...

Page 117: ...over New Jersey 57 Adhesive Acrylic PS 30 Cadillac Plastic 8 Chemi cal Co Detroit Michigan 58 Adhesive Sealant RTV732 Dow Coming Corporation Midland Michigan 48640 59 0030 inch Thick No 474 Minnesota...

Page 118: ...ity Kansas P P 560 Anti Static Plastic Polish Park Chemical Company Detroit Michigan MGH 10 Mirror Bright Polish Com pany Irvine California 67 Lubricating Grease MIL L 10324 Gear Altemate for Superced...

Page 119: ...Oil Level Cowl access open T C M Spec Preflight ing 2 MHS 24B Battery Electrolyte Fwd baggage com Distilled water Every 25 hours partment 1 Air Conditioner See Chapter 21 Suniso No 5 or As Required Co...

Page 120: ...2 Clean per Every 50 hours instructions on filter Fuel Strainers Wheel wells 2 Clean with sol Every 100 hours vent and blow dry with air pressure Cabin Altitude Outflow Control console Clean with sol...

Page 121: ...System Inline Aft of engine firewall in Every 500 hrs Air Filter upper nacelle 2 Air Pump Intake Filter Fonnrard side of aft engine Every 300 to baffle 2 500 hrs Induction Air Filter UI cowl door 2 Ev...

Page 122: ...harmful to painted surfaces MIL G 23827 grease is recommended for use in lubricating the blade bearings in the Hartzell Propeller This grease will ensure against a possible freeze up of the pitch chan...

Page 123: ...er Aeroshell Grease No 5 preferred or MIL G 81322 3 Do not intermix as these 58P604 24 greases are not compatible NOTE POINTING HAND DENOTES CHANGE DETAIL B INDEX LOCATION LUBRICANT INTERVAL NOSE GEAR...

Page 124: ...TEM LOCATION LUBRICATION INTERVAL NOSE LANDING DOORS DETAILC Landing gear door hinges 4 SAE 20 or 100 hrs SAE 10W30 s O DETAIL C O C cSg DETAIL D ITEM LOCATION LUBRICANT INTERVAL RUDDER PEDALS DETA LD...

Page 125: ...or SAE 10W30 100 hrs 311 NOTE Forward cabin door hinges and latches TJ 3 and after do not require lubrication O 2 ji t T 3 NOTE O DETAIL E TK 1 AND AFTER a DETAIL F TJ 3 through TJ 435 TJ 437 through...

Page 126: ...and TK 151 and after INDEX LOCAT ON POINTS LUBRICANT INTERVAL CONTROL COLUMN SAE20 or O Control column chains 4 10W30 Oil tM hrs O Ball bearings 10 MIL L 7870 Oil 100 hrs O Torque shafts 2 MEK Solven...

Page 127: ...636 MIL L 2105 D Landing gear system SAE 1DW30 75W 100 hrs retract arms 15 SAE 10W30 2 TOP VIEW O NOTE SIDE VIEW POINT NG HAND DETAIL G DENOTES CHANGE Nose gear retract arm is located beneath the gear...

Page 128: ...with either Aeroshell Grease No 5 preferred or MIL G 81322 Do not intermix as these NOTE greases are not compatible POINTING HAND DENOTES CHANGE 4 b DETAIL I ha DETAIL J ITEM LOCATION LUBRICATION INT...

Page 129: ...AE 10W30 100 hrs Utility door latches 3 O Utility dmr hi s 2 Mll M 7866 100 hrs NOTE POINTING HAND DENOTES CHANGE O TK 1 AND AFTER DETAIL K rJ 3 AND AFTER e Mix MIL M 7866 with naphtha and apply with...

Page 130: ...27 900 hrs Inside cable housing r 7 I ICP 4 Prior to TJ 107 and TK 43 Later flap motor gearboxes are permanently lubricated and require no maintenance DETAIL 44 NOTE POINTING HAND DENOTES CHANGE DETAI...

Page 131: ...Rudder trim rabhinge li VV L800A 100 hrs O Rudder trim tab VV L 800A 100 hrs actuator rod O r3 DETAIL O NOTE POINTING HAND DENOTES CHANGE n DETAIL P INDEX LOCATION LUBRICANT INTERVAL ELEVATOR TRIM DE...

Page 132: ...NUAL CHART 204 Cont d LUBRICATION SCHEDULE INDU LOCATION LUBRICANT INTERVAL HEATER DETAIL Q fK l AND AFTER O Heater Iris Mix MIL M 7866 As Required Valve 1 lubricant with Naphtha and apply with a brus...

Page 133: ...BEECHCRAFT BARON 58P ANO BARON 58TC MAiNTENANCE MANUAL 2 3 1II 1 3 2 J 4 n4 5 O I d 14 P IS 10 13 5 14 11 58P 13 llA Fuselage Access Openings Sheet 1 of 2 Figure 202 2 20 00 Page 224 Aug 1180...

Page 134: ...5 Nose Cone 6 Tail Cone 7 Elevator Bell Crank Elevator Down Spring Turnbuckles and Cable Inspection 8 Wiring Inspection 9 Landing Gear Actuator 10 Control Cable Pulleys and Nose Gear Retract Idler Ar...

Page 135: ...I I t n7 _ o 34Jc 34 L FT WING TOP 9 8 7 6 6 7 8 R1GHf WING ITOP 7 17 14 14 31 31 16 11 1 16 13 12 1 10 33 33 10 11 12 30 13 30 28 28 bcalX Xlw 25 I I ITr tc I I I I I I C rT L I I 25 19 2122 24 35 1...

Page 136: ...Aileron Tab Actuator and Pulley 8 Aileron Bell Crank 25 Wing Tip Access 9 Fuel Cell Transmitter 26 Fuel Cell Access 10 Wing Tip Spar Fitting and Float Valve Assembly 27 Fuel Filler Opening 11 Fuel Ce...

Page 137: ...LERON TRAVEL GAGE AILERON TAB TRAVEL GAGE I 810 96524000 810 96 630000 1 RUDDER TRAVEL GAGE RUDDER TAB TRAVEL GAGE 810 1 95524000RH 810 195524000LH 810 2 96 524000 ELEVATOR AND ELEVATOR TAB TRAVEL CAG...

Page 138: ...BEECHCRAFT BARON 580 AND BARON 58fC MAINTENANCE MANUAL MODEL 300 100 SERVICE JACI 101 590020 1 FUEL SUMP DRA N WRENCH 58P1716e Special Tools Sheet 2 of 4 Figure 204 12 2MH Page 229 Aug 1180...

Page 139: ...ANCE MANUAL MAIN WHEEL JACK ADAPTER TOW HANDLE ASSEMBLY 35 590006 u 95 590033 25 d HOISTING SLING ADAPTER HOISTING SLING 95 590017 95 590016 1 95 590017 1 5BP 1716 Special Tools Sheet 3 of 4 Figure 20...

Page 140: ...222 5 9 16 inch hex TS1176 10 UPPER FORWARD WING NUf TORQUE WRENCH NOTE ADAPTER T1 817 922 4 LOWER AFT WING BOLT WRENCH POINTING HAND 731176 10 LOWER AFT WING NUT TORQUE WRENCH DENOTES CHANGE ADAPTER...

Page 141: ...rning devices etc Remove fluid No attempt should be made to remove loose snow from the fuselage before heat ice deposits or break an Ice bond by ing the airplane interior otherwise at force low temper...

Page 142: ...rfaces or plastics DEICING AND ANTI ICING FLUID APPLI Should have a high flash point CATION Should be nontoxic Aircraft deicing fluids may be used diluted or undiluted according to manufac Should have...

Page 143: ...ds should not be stored out fluids particularly when diluted by snow side and unheated during cold ice or water should cause little or no weather injury to most broadleaf plants grasses perennial grou...

Page 144: ...CHAPTER STANDARD PRACTICES AIRFRAME...

Page 145: ...rior Colors 202 202 Painting Aluminum 202 Enamel Paint Preparation of Airplane Aluminum Exterior for Paint 202 Application of Exterior Paint on Aluminum Skins 202 Exterior Paint Touch Up Repair Enamel...

Page 146: ...HAPTER 20 STANDARD PRACTICES AIRFRAME TABLE OF CONTENTS CONTINUED SUBJECT PAGE Nose Radome 205 Surfaces Susceptible to Mud and Spray 206 Rubber Seals 206 Enclosed Areas Subject to High Humidity 206 Ba...

Page 147: ...CTICES AIRFRAME LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE P0 Effectivity 1 Sep 3 01 20 Contents 1 Sep 3 01 2 Sep 3 01 20 00 00 1 Sep 3 01 2 Sep 3 01 3 Sep 3 01 201 Jan 9 76 202 Oct 26...

Page 148: ...ction of any component remove all identification tags Check all associated systems for correct function prior to returning the airplane to service TORQUE WRENCHES When a torque wrench and adapter is u...

Page 149: ...e if the specified torque is 5 000 inch pounds and the distance is 25 inches a pull of 200 pounds must be applied Bolts to be torqued must be clean and free of all lubricants otherwise loss of normal...

Page 150: ...Raythean Aircraft BEECH BARON 58P AND BARON 58TC MAINTENANCE MANUAL LB 900 TORQUE IN LB TOTAL LENGTH 5017 1 Computing Torque with Spring Scale Figure 2 A24 20 00 00 Sep 3 01Page 3...

Page 151: ...e Brown 118684 223 never be used Use soft cleaning cloth or chamois to Peacock Turquoise 118684 333 prevent scratches when cleaning and polishing Any good Sahara Tan 118684 337 grade automobile wax ma...

Page 152: ...p primer LACQUER exposed sealer and other shop soils d Lightly roughen all scratches with nylon pad to Interior Colors insure a satisfactory paint base e Reclean the roughened surface with solvents to...

Page 153: ...al paint stripper with solvent until all trace of discoloration is gone apply a If a urethane stripper is not available a good enamel thin coat of pretreatment primer to the damaged area stripper may...

Page 154: ...loose edges of paint by using a high a Mix the primer in accordance with the tack adhesive tape around the edge of the damaged area manufacturer s instructions c Using a coarse sandpaper fair the edge...

Page 155: ...in a well time between application of the primer and top ventilated area since prolonged exposure to coat high concentrates of vapor may irritate the eyes and lungs SPECIAL PAINT PROCEDURES c Allow t...

Page 156: ...ces Apply a thin coat of Dow Coming No 7 after the m Pitot mast and static button finish topcoat is dry n Cabin door sill and upper latch ENCLOSED AREAS SUB3ECT TO HIGH HUMIDITY The following items ar...

Page 157: ...CHAPTER Al R CONDITIONING...

Page 158: ...and after 1 Operational Characteristics 1 Cabin Altitude Controller 2 Outflow Valve and Safety ValvelDump Solenoid 2 Pressurization Test Switch 2 Ejector 2 Troubleshooting TJ 3 and after 101 Maintenan...

Page 159: ...210 TJ 229 and after 202 Pressure Tank Installation TJ 210 TJ 229 and after 202 Door Seal Automatic Deflate Switch Removal TJ 3 and after 202 Door Seal Automatic Deflate Switch Removal TJ 3 and after...

Page 160: ...t Installation 202 Condenser Blower Removal 202 Condenser Blower Installation 202 Condenser Removal 202 Condenser Installation 202 Condenser Control Rigging 202 Compressor Removal 203 Compressor Insta...

Page 161: ...6 Mar 23 79 21 10 00 Mar 21 80 201 Mar 21 80 21 20 00 201 Mar 21 80 21 30 00 1 Mar 21 80 2 Mar 21 80 3 Mar 21 80 101 Mar 21 80 102 Mar 21 80 103 Mar 21 80 201 Mar 21 80 202 Mar 21 80 203 Mar 21 80 20...

Page 162: ...tC MAINTENANCE ANUAL CHAPTER 21 LIST OF PAGE EFFECTIVIN Cont d CHAPTER SECTION SU IECT PACE DATE 21 50 00 1 Mar 21 80 101 Apr 1n5 102 Apr 1175 201 Mar 21 80 202 Mar21 80 203 Mar 21180 204 Mar 21 80 EN...

Page 163: ...eflate valve is located in the door indicator door seal inflate deflate switch the cabin altitude adjacent to the hook assembly When the door handle is in controller a PRESS TO TEST switch a PRES the...

Page 164: ...ually resettable overtemp switch located on the position On the ground the air scoops open to heater shuts off the system until reset in case the discharge approximately 3 1 2 inches In flight the air...

Page 165: ...II II nLI1 Excn uG I EV rOrA101 nl tl Il O IIOI ICOHr OL O C IIN nt 1 certrlo CIIICONDITIONII ODI IOS1 CON IOL ITIIUIIIIIIOW I I II O LH CIIIHIIISILII InUIO I O IH C SIN C1SSS t SnUrOrr OCOIIIOIlII C...

Page 166: ...LVI CnlCK VALVI TUsBO H PC I V LVI OSr II CONDlNSta i wr l IXC NCI Il fO R IV POI TO il HtATslPIII OP LOr III tONTaOL O C aIN nllT CO NTIIOL 11I CO YDITIONI O D rltOSr CONTaOL IlrlSUIIIZlnON Ig O LY...

Page 167: ...CONDITIONER OUTLETS 4 PLACES FRESH AIR HIPITIR AIR O CABIN PIIR CONTROL O CABIN HEAT CONTROL AIP COND TIONER O DEFROST CONTROL PILOT AIR CONTROL C EXHAUST AIR O COPILOT AIR CONTROL AFT BULKHEAD FS 19...

Page 168: ...TROL LOW PRESSURE SWITCH AIR CONDITIONER OUTLETS 4 PU CES FRESH AIR OUTLETS 6 PLACES HEATER IR O W BIN AIR CONTROL O CABIN HEAT CONTROL MR CONDITIONER O DEFROST CONTROL PILOT AIR CONTROL EXHAUST AIR O...

Page 169: ...lied by the turbocharger 153 and 3 8 10 psi on TJ 153 and TJ 169 and after by compressor In operation engine exhaust gas passing over control of the outflow and safety valve A pressurization air the t...

Page 170: ...operations the CABIN PRESS AIR SHUTOFF push pull control knobs are pushed against the HEA T EXCHANGER INSTALLA TION lower LH subpanel This will allow maximum airflow to enter the cabin In the event of...

Page 171: ...N Distribution Ducts Check cabin hot and cold air outlet The functional diagrams in Chapter 21 00 00 provide a valves for condition obstructions and proper operation detailed layout of distribution sy...

Page 172: ...w mae xe cabin prsssure will be affated and cabin pespurs hrtua6on ill P 1ESSUZIATION SYSTEM OPEFTA TIONAL be s paiancsd A fKhladon of 2000 fpm is mmul unda hsse mndt ns I Rmaeada a Ui nm Porn A mmun...

Page 173: ...n the pressure The outflow valve regulates cabin pressure up to maximum position and the firewall shut off valves in the open position I differential pressure of 3 75 psi on TJ 3 lhru TJ 168 except Se...

Page 174: ...ALVE NO 211 11 KNOB ALTITUDE OUTFLOW VALVE CONTR LER IWELECTOR KNOB AIRCRAn ELECTRICAL SYSTEM CABIN PRESSURE REFERENCE PRESSURE O DISCHARGE PRESSURE RATE PRESSURE AIRCRAFT VACUUM PRESSURE FACE VIEW OF...

Page 175: ...ats with a lint free cloth valve seats dirty moistened with isopropyl alcohol g Firewall shutoff valves pulled g Open valves closed h Hole in flex ducts from h Inspect and repair or replace as require...

Page 176: ...control e Inspect repair as line kinked or restricted necessary 6 Cabin altitude lower a Cabin pressurization a Replace controller than selected altitude controller out of FJot exceeding maximum adjus...

Page 177: ...d 7ROUBLE PROBABLE CAUSE REMARKS 9 Airplane pressurizes a Landing gear safety a Replace or adjust the RH landing on ground switch inoperative or gear safety switch improperly rigged b Open circuit in...

Page 178: ...and installation procedures of the outflow valve When reinstalling the existing valve or installing a new valve the existing mounting gaskets and SAF V VALVE GROUND CHECK seals must be discarded and t...

Page 179: ...ID INSTALLATION a Place ejector in position and secure with attaching a Remove caps from the pressurization plumbing screws and position the preselect solenoid so that the flow is indicated toward the...

Page 180: ...uipment hoses furnished with the forward of the LH and RH firewall test unit may be connected in only one eRher a Connect the PNEUMATIC AIR fitting on the test or both nacelles The TEST EQUIPMENT text...

Page 181: ...102 sealant in the notch of the seal fitting Apply EC1239B1 2 590020 939 or equivalent on the atmosphere ports of the sealant to all plumbing fittings at Be pressure vessel safety and outflow valves...

Page 182: ...FIREWALL FITTING SHUTOFF ALUMINUM TURBOCHAdGER B CnECKVAL VALVE FITTING SONIC NOmE SONIC SHUTOFF NOZZLE VALVE AIR TO AIR HEAT EXCHANGER AIR TO AIR HEAT NOTE ATT PRESSURE BULKHEAD FS 190 THE EXACT LOC...

Page 183: ...HCRA T BARON 580 AND BARON 58TC II AIMEWANCE MANUAL I DETAIL A Oi I CABIN SENSOR 00O DETAIL 8 a P hr I LILILY 1 r SBPg BQ Cabin Pressuritation Tgst Hookup Page 2 of 2 Figure 302 2r 3eor Pagtt 288 Mer2...

Page 184: ...e door seal system is regulator and door seal The forward cabin door seal standby repressurized Excessive cycling of the pump during normal pressure regulator incorporates a 12 psi pressure switch ope...

Page 185: ...cabin door seal replacement b Pressure pump s b Replace pump s malfunction c Loose or broken wires c Check electrical wires for condition See Wiring Diagram Manual 102 590000 23 d Defective forward c...

Page 186: ...J 123 and after compartment door On TJ 123 and after the door seal control valve is replaced by a door seal pressure switch and a check relief valve DOOR SEAL PUMP REMOVAL TJ 210 TJ and after a Gain a...

Page 187: ...r NOTE b Locate the pressure tank ah of FS 10 00 and remove floorboard panels ah of the pressure tank Ensure that the door is open so that the switch c Disconnect pressure tubing from the ah side of a...

Page 188: ...ngs to c Connect electrical wires to the regulator prevent contaminants from entering the system d Conduct the PRESSURIZATION TEST d Remove the attaching screws which hold the PROCEDURE as described i...

Page 189: ...b The BLOWER HTR switch controls the vent air assembly and back to the cabin as heated air blower circuits however when the CABIN HEAT switch is in the CABIN HEAT position the low vent air blower HEA...

Page 190: ...spect all lines and connections broken It may be necessary to disconnect lines at various points to determine where the restriction is located i Ignition vibrator i Replace vibrator check for inoperat...

Page 191: ...motor f Remove combustion air motor for overhaul or replacement of motor 4 Heater fires but burns a Insufficient fuel supply a Inspect fuel supply to heater unsteadily including solenoid valve fuel pu...

Page 192: ...om the tank to the heater Make necessary corrections b Inoperative or chattering b Check adjust or replace combustion air pressure switch switch c Inoperative overheat switch c Check or replace switch...

Page 193: ...ine and secure the clamps around the boot access to the heater d Install the wire harness to the heater b Loosen the clamp and disconnect the duct from e Connect the duct to the combustion air blower...

Page 194: ...i Attach cabin air control to iris valve Rig cabin air baggage webbing as necessary to gain access to the heater control to open the iris valve when the control knob is pulled b Remove the nose cone a...

Page 195: ...ggage door temperature between 190 to 210 F during the soak period Flush the heater thoroughly with clean water and wipe dry at CLEANING THE HEATEFI the end of the soak period a Cleaning the combustio...

Page 196: ...ensures instant firing and continuous buming under a To install a new vibrator carefully rotate the new all flight conditions Heat is produced by buming a fuel air vibrator until the index marks are a...

Page 197: ...heater regardless of fuel inlet adjusted the ground electrode may be bent up or down by pressure variations reaching through the spark plug hole with the appropriate shaped tool CLEANING THE HEATER BA...

Page 198: ...R switch thus when the PRESS AIR COOL pos ition On the ground the air scoops open to switch is in the A C position the forward and ah evaporator appSoximately 3 1 2 inches In Right the air intake scoo...

Page 199: ...functioning b Repair c Leak in system c Leak test and recharge d Compressor valves d Repair or replace inoperative 3 Excessive vibration of a Overcharged a Correct refrigerant charge unit b Air in sy...

Page 200: ...oose a Adjust b Overcharged b Correct refrigerant level c Air in system c Evacuate and recharge 8 Excessive belt wear a Pulleys not in line a Align pulleys b Belt too tight b Adjust or replace c Pulle...

Page 201: ...rdance with the applicable Pilot s Operating Manual passing over an open flame will produce a highly toxic d Relieve the air conditioner system pressure by phosgene gas loosening the compressor filler...

Page 202: ...tension las shown on a V belt tension gage is lines obtained After 36 to 48 hours operating time a new belt will c Remove attaching hardware and remove the con stretch to its normal operating length...

Page 203: ...LLA TION a Position compressor on the mounting bracket and AFT EVAPORATOR BLOWER MODULE F LTER install the attaching bolts and nuts CLEANING TJ 3 and after b Install compressor belt as noted in COMPRE...

Page 204: ...BLOWER MODULE the forward evaporator blower module INSTALLATION TK I and after e Tag and remove electrical wiring f Remove the attaching bolts and remove the a Place the forward evaporator module in...

Page 205: ...CHAPTE R AUTO FLIG HT...

Page 206: ...PAGE DATE 22 EFFECIIVITY CONTENTS 1 Nov 30 78 CHAPTER 22 AUTO FLIGHT TABLE OF CONTENTS SUBJECT GENERAL AUTOPILOT SPEED ALTITUDE CORRECTION AUTO THROTTLE SYSTEM MONITOR NOTE Refer to the Edo Aire Mitch...

Page 207: ...CHAPTER COMMUNICATIONS...

Page 208: ...TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE STATIC DISCHARGING 23 60 00 Description and Operation 1 201 Maintenance Practices Static Wick Removal Prior to TJ 388 Prior to TK 146 201 Static...

Page 209: ...io and avionics OPERATION equipment operation Therefore static wicks are installed on the trailing edges of the flight surfaces to aid in the A static electrical charge may build up in the surface of...

Page 210: ...wicks is riveted to the flight surface and need not be removed in normal service c Install the wick using the two screws and lock washers d Refinish the surface area around the wick STATIC WICK REMOVA...

Page 211: ...CHAPTE R ELECTRICAL POVVER...

Page 212: ...e Regulator Adjustment and Paralleling 201 Overvoltage Sensor Check 204 Left Overvoltage Sensor 204 Right Overvoltage Sensor 204 BATTERY 24 32 00 Troubleshooting 101 Maintenance Practices 201 Battery...

Page 213: ...1 Nov 30 78 24 30 00 1 Nov 30 78 101 Apr 1n5 102 Apr 1 75 201 Nov 30 78 202 Nov 30 78 24 31 00 101 Apr 1 75 201 Nov 30 78 202 Apr 1 75 203 Oct 3 75 204 Nov 30 78 205 Oct 3 75 24 32 00 101 Apr 1175 10...

Page 214: ...t 25 ampere hour lead acid baneries Aircraft Alterations Manual AC 43 13 2 Any and by two 24 volt 50 ampere 100 ampere optional components replaced and any wire cable or terminals used alternators Alt...

Page 215: ...TK 51 through TK 55 and confined to the fuel flow indicator and the electroluminescent TK 59 and after the fuel flow inverter is not installed The panel lights Each system includes an inverter which...

Page 216: ...electrical system during engine operation The airplane electrical system includes two 24 volt 50 ampere alternators two optional 28 volt 100 ampere An external power receptacle located on the outboard...

Page 217: ...shes not contact e Clean brushes and holders ing slip rings with a lint free dry cloth replace weak springs f Worn or broken f Check brushes and brushes replace if necessary g Open current limiter g C...

Page 218: ...r pointer or a Loose connections in a Check system tighten lights flicker charging system or or replace loose or damaged wiring harness damaged wiring or wiring connections b Worn brushes b Check brus...

Page 219: ...r voltage drops 1 5 to 3 0 volts below bus voltage The cotter pin must be installed and then trimmed The portion bent toward the alternator ALTERNATOR REMOVAL housing must NOT touch the thrust washer...

Page 220: ...ould be remembered that the c Connect all electrical wiring alternator is polarized everytime the master switch is turned on therefore any attempt to polarize the unit will only damage the voltage CAU...

Page 221: ...or no output voltage a Excessive load a Check load and reduce b Poor system con b Check system and tighten nections all connections c Voltage adjustment c Adjust the voltage set too low regulator 2 H...

Page 222: ...rol range under facilitate reinstallation c Remove screws securing the voltage regulator to operating conditions the bulkhead d Remove the voltage regulator Each regulator is capable of nearly 1 0 vol...

Page 223: ...al voltmeter is not purposes If this circuit touches any other recommended for the paralleling adjustment circuit or the airplane structure erroneous results will be obtained i Restart the left engine...

Page 224: ...ines according to the ENGINE START procedures in the applicable Pilot s The right engine is not operating The left Operating Manual loadmeter should indicate a load of r Check both loadmeters in the c...

Page 225: ...ls of the power a Remove left engine nacelle access door on top of supply the nacelle e Turn on the battery master switch b Disconnect the lead wire P59B16 at the diode heat f Press the PRESS TO TEST...

Page 226: ...EL ASSEMBLY I F2 OVERVOLTAGE I I L I OVERVOLTAGE RELAY I I f I SENSOR I I I TO VOLTAGE REGULATOR ALTERNATOR P1 V1 P1 VARIABLE POWER DIICONNECr LEAD WIILE AT SUPPLI O SOVd DIODE FOR OVERVOLTAGE SENSOR...

Page 227: ...Battery relay contacts b Check battery relay stuck for operation and replace if necessary c Battery master relay c Check circuit for coil circuit shorted short and repair to structure between as nece...

Page 228: ...lly particular ly if left standing a few days Replace battery 6 Compound on top of a Charging rate too a Adjust voltage battery melts high regulator on airplane 7 Cell connector melted in a Shorted or...

Page 229: ...verse BA TTE R Y MA INTENANCE PROGRAM polarity will destroy the diodes and other electronic components in the electrical systems A systematic battery maintenance program should be established and care...

Page 230: ...n using auxilairy power f Inspect the battery for cracks holes or bu m spots to recharge the battery Replace if necessary g Make sure that all batteries hardware is clean and a Place the battery maste...

Page 231: ...The low The airplane is equipped with a low voltage detector for each voltage detectors are checked each time the battery is turned alternator These detectors compare the alternator voltage to on with...

Page 232: ...witch is turned off for required Use of an inadequate ground power unit can cause extended ground power operation place an a voltage drop below the drop out voltage of the starter external battery in...

Page 233: ...PER LOAD PER LOAD PER AIRPLANE UNIT AIRPLANE IN IN AMPS AMPS Cowl Flap Actuator 2 1 00 2 00 Heater System 1 17 20 17 20 Fuel Vent Heaters 2 1 40 2 80 Fuel Flow System 1 85 85 Fuel Quantity Indicator 2...

Page 234: ...TRIM ICE LIGHT THROTTLE WARN LANDING GEAR RELAY jj PROPELLER ANTI ICESTROBE LIGHT FLAP IN DI CATOR WI NDSHIELD ANTI ICE FUEL QUANTITY LANDING GEAR MOTOR RIGHT HAND FUEL BOOST PUMP LEFT HAND ALTERNATO...

Page 235: ...0 Navigation Lights 3 85 2 55 Landing Gear Motor 1 20 00 20 00 Flap Motor 1 13 00 13 00 Fuel Boost Pump 2 5 00 10 00 Landing Lights 2 9 00 18 00 Avionics All 30 00 30 00 Starter Relay 2 3 60 7 20 Star...

Page 236: ...R PER LOAD PER LOAD PER AIRPLANE UNIT AIRPLANES IN AMPS IN AMPS Wing Ice Light 1 1 40 1 40 Windshield Anti ice System alcohol 1 65 65 Surface Deice 1 45 45 Starter Vibrator 2 2 00 4 00 Step Light 1 30...

Page 237: ...attery bus system use the h Coml following steps i Nav I or Nav II j Transponder a Remove the guard on the ALT BAT BUS switch by turning the cover as indicated b Place the ALT BAT BUS switch in the ON...

Page 238: ...CHAPTE R EQUIPMENT FURNISHINGS...

Page 239: ...th and Sixth Seats 202 Passenger Seats Storage Fifth and Sixth Seats 202 202 Vertical Position 202 Horizontal Position 202 Roton Locks Modification of Third and Fourth Passenger Seat Back Supports TJ...

Page 240: ...S CONTINUED SUBJECT PAGE Emergency Maintenance Practices 201 Emergency Locator Transmitter Maintenance 201 Narco Battery Replacement 201 Collins Communications Components Corporation Battery Replaceme...

Page 241: ...SUBJECT PAGE DATE 25 Effectivity 1 Sep 3 01 25 Contents 1 Sep 3 01 2 Sep 3 01 25 00 00 1 May 22 87 2 May 22 87 201 May 22 87 202 May 22 87 202A May 22 87 203 Mar 31 82 204 Mar31 82 205 Sep 3 01 206 Se...

Page 242: ...436 TJ 444 and after are equipped underneath the seat allowing the gas with vertically adjusting seats In the spring piston rods to extend or retract crew compartment c opilotl s seat is to raise or...

Page 243: ...T BARON 588 AND 58TC MAINTENANCE MANUAL r SECTOR GEAR GAS SPRING 7 Y Q RELEASE LEVER ACTUATOR loO ROD TORQUE TUBE ADJUSTING LEVER 36 313 51 Vertically Adjusting Seat Figure 1 END 25 00 00 Page 2 May 2...

Page 244: ...the mounting track Engage the fore and aft b pull up on the fore and aft lock and make certain the seat is securely adjustment lever and slide the seat onto in place the seat track Release the adjustm...

Page 245: ...FIFTH retract position and position the seat AND SIXTH SEAT bottom on the floorboard a Pos i ti on the seat and secure in b Fold the seat back forward and place with the attaching bolts position it on...

Page 246: ...ove the lock from the fixture The following steps are applica and remove the spring guide counter ble to both seats balance spring and spring guide tube b Remove the seat back assembly from f Apply a...

Page 247: ...main h Remove the screw washer and nut which was defroster duct tube at the clamp temporarily installed in step f f Remove the glareshield from the airplane i Drill or ream the upper hole in the fille...

Page 248: ...aggage leadliner panel to the airplane structure Pull the headliner compartment Remove the bolts attaching the inertial reels panel away from the overhead console and remove from the to the airplane s...

Page 249: ...aggage webbing h Replace the aft garment hangers located over the fifth and sixth seats and over the hat shelf on the headliner and secure with the attach screws i Reinstall the forward and aft should...

Page 250: ...from the console lights and tag and identify the wiring o Remove the console from the airplane p Gently pull down on the headliner to disconnect it from the velcro fasteners The velcro tape is spaced...

Page 251: ...olts then replace the snap on covers over the inertial reels r Install the flight compartment seat as outlined in FLIGHT COMPARTMENT SEAT INSTALLATION in this chapter FUSELAGE MAINTENANCE PRACTICES FO...

Page 252: ...tall carpet e On aft side of spar cover install screws to secure aft end of spar cover and install carpet f Check emergency landing gear hand crank to ensure handle will rotate without interference wi...

Page 253: ...operate installed on airplane serials TJ 272 and after and TK 22 automatically upon impact The REARM position resets the and after and earlier airplanes equipped with Kit No 101 transmitter in the eve...

Page 254: ...er one cumulative hour of use ing the portable antenna and the handling of the control head dur e After operation of unknown dura ng the battery replacement in tion order to avoid damage to the antenn...

Page 255: ...ttery pack around the area of the control head which CAUTION is joined with the battery case when reas sembled Exercise extreme care in order to avoid damage to the antenna or the NOTE plastic tab on...

Page 256: ...ery as defined by the battery manufacturer d Disconnect the remote switch COLLINS COMMUNICATIONS COMPONENTS CORPO e Remove the screws holding the ELT RATION BATTERY REPLACEMENT in place a Place the AR...

Page 257: ...d the ELT Is functi oning properly The ELT switch should not be If there was no audible tone turned ON unless the ELT is con assuming that the VHF nected to its associated antenna transceiver Is opera...

Page 258: ...CHAPTER FLIGHT CONTROLS...

Page 259: ...rol T Column Arm Chain Rigging 201 Dual Control Columns 202 Control Column Chain Removal 202 Control Column Chain Installation 202 Control Column Chain Rigging 206 Aileron Removal 206 Aileron Installa...

Page 260: ...07 Rudder Trim Tab Free Play Inspection 207 27 30 00 Elevator and Tab Maintenance Practices 201 Elevator Removal 201 Elevator Installation 201 Elevator Cable Removal 201 Elevator Cable Installation 20...

Page 261: ...7 31 00 Stall Warning Description and Operation 1 Stall Warning Troubleshooting 101 Stall Warning Maintenance Practices 201 Stall Warning Indicator Removal 201 Stall Warning Indicator Installation 201...

Page 262: ...NANCE MANUAL CHAPTER 27 1 FLIGHT CONTROLS TABLE OF CONTENTS CONTINUED SUBJECT PAGE Flap Drive Cable Connection 205 27 70 00 Qust Lock and Dampener Maintenance Practices 201 Control Lock Removal 201 Co...

Page 263: ...REVISIONS REVISION DATE DATE REASON PAGE NUMBER INSERTED REMOVED REMOVED NUMBER 27 1 Dec 11 92 Nov 15 93 Temporary 27 50 00 Revision Page 204 27 2 27 2 Nov 15 93 Jan 9 oz 27 50 00204 NOTE Insert this...

Page 264: ...1 Sep 3 01 2 Sep 3 01 3 Sep 3 01 4 Sep 3 01 27 00 00 1 Oct 6 83 27 10 00 201 Oct 6 83 202 Oct 6 83 203 Oct 6 83 204 Oct 6 83 205 Oct 6 83 206 Oct 6 83 207 Oct 6 83 208 Oct 6 83 209 Oct 6 83 210 Oct 6...

Page 265: ...0 00 201 Oct 6 83 202 Jun 14 85 203 Oct 6 83 204 Oct 6 83 205 Oct 6 83 206 Jun 14 85 207 Jun 14 85 208 Oct 6 83 209 Jun 14 85 210 Jun 14 85 210A Jun 14 85 211 Oct 6 83 212 Oct 6 83 27 31 00 1 Apr 1 75...

Page 266: ...Refer to the applicable rigging procedures for details regarding chain and cable tension control wheel movement and force down spring force and system friction Air lane serials TJ 3 through TJQ35 11...

Page 267: ...tate control wheels to the neutral position in Figure 201 prior to chain installation and rigging levei and slide the control column arm off the control b Position the sprocket at the base of the cont...

Page 268: ...that the a Disconnect the tumbuckles from the control distance between the edge of the chain terminal and the column chain edge of the turnbuckle nut does not exceed 15 inch f Remove the four connect...

Page 269: ...NTENANCE MANUAL YELLOW MARK ON I SPROCKET AND CHAIN I t r c I I CHAIN TURNBUCKLE CHAIN ACCESS OPENING YELLOW MARK ON SPROCKETANDCHAIN SLOT IN SPROCKET Single Control Thnmr O r Column Arm Chain Rigging...

Page 270: ...CKEI LONG CHAIN A s mnx i I is nn mar TIP CAL 4 PLACES ORT CHAIN DEfAIL A t Y B TCHAIN z LONG CHAIN SPROCI ET CENTER LINE OF TOOTH TO BE ON CENTER LINE OF SLOT WIIHIN D fAIL B sep lss lo Duel Control...

Page 271: ...ATOR TORQUE TUBE SUPPORT 8 BOB WEIGHT ASSEMBLY 9 COLLAR 10 COLLAR ASSEMBLY 11 ELEVATOR PUSH ROD 12 CONNECTOR 13 INNER COLUMN GUIDE 14 INNER COLUMN TORQUE TUBE 29 21 15 U JOINT 19 i 16 SPROCKET SUPPORT...

Page 272: ...aileron must move f Paint one tooth of the control column sprocket down and the conesponding link of the chain and cable assembly to ensure proper alignment at installation CONTROL COLUMN CHA N RIGG...

Page 273: ...ileron must align with the lead line and connect the balance cable and the aft contour of the wing within 1 16 inch 0625 inch on either or outboard cables to the tumbuckles in each wing both sides c R...

Page 274: ...p clearance provides a slight horizontal misalignment of 3 16 inch is allowed between movement of the control wheel a cushion the trailing edges of the aileron and wing If the aileron is not after the...

Page 275: ...LEFT WING DOWN CRANK SV3PS BALANCE CABLS AILERON TAB STOPS F S 68 00WING DOWN 7 CoMa l nbonr Boood on 59 F Ambi nt A ToloPom oro 40 L o 30 LEFT WING DOWN RIGHT WING DOWN W S 23 881 cI AILERON 20 BELL...

Page 276: ...ETAIL F BELL CRANK Cabk i nlions bard on 590F Ambi nt Air f np m uc 1 40 WING DOWN W S Sl nS o 30 d IO WING DC WN W 5 45 000 t Jp DETAIL A W S 6 000 trrrr F S 68 00 20 I t I_ Tob LHf WING DOWN to L j...

Page 277: ...move the fward left passenger seat and the floorboard NOTE d Remove the necessary access plates to gain access to the trim tab cables the actuator and the cable BEECHCRAFT recommends the use of the pu...

Page 278: ...linkage e Remove the bolts attaching the actuator to the 1 Multiply B by 2 and record as 28 wing structure Remove the actuator 2 Subtract A from 28 and record as X 3 Multiply D by 2 and record as 28 4...

Page 279: ...cator 5 1 3 4 X 21 2X 14 aluminum or equiv 6 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Dia xlcorrosion res stl 1 6 IN 8 1 1 4 28 nut 9 1 W x 5x10 rubber 31 IN 1 10 1 3 8 X 2 X 10 rubber 11 1 1 4 X 2 X 1...

Page 280: ...color bolts Torque the bolts to 50 70 inch pounds c Connect the rudder tab cables at the tumbuddes a Route the rudder cables forward in the tail section and install the cabe retainer pins and fairlead...

Page 281: ...830 B C A F S 233 50 RIGHT RUD CABLE TAB RIGHi 58P 15216 TAB LEFT o Cable Tensions Based on 590F Ambient Air Temperatute DEfAIL D 70 LEFT RUD CABLE S IRIGHT RUD CABLE g d 60 DETAIL A c in 50 RU j TAB...

Page 282: ...mperoture 7 70 I 8 RUD TAB LEFT 8 MIDI C d 60 r i TAB RIGHT s0 RIGHT RUD CABLE DETAIL A LEFf RUD CABLE 40 30 RUDDER RIGHT C FWDI RUD TAB LEFT RU TAB LEFT RUD fAB RIGHT RUD TAB RIGHT SURFACEtRAVU 5 118...

Page 283: ...e such as the lower trailing bcd and two 43 inch diamter steel pins The edge comer must be established before measuring rudder pins are parallel and located forward on the or rudder tab travel bcd at...

Page 284: ...154 5 BLOCK W x 3 LONG Rudder Pedal Rigging Tool Figure 203 SURFACE DIRECTION MAXIMUM MINIMUM MEASURING POINT Rudder R 8 L s so 260 8 88 24 Lower trailing edge corner Rudder Tab R L 4 50 260 4 16 240...

Page 285: ...e left hand side of I RUDDER TR M TAB CABLE NSTALLAT ON the fuselage just forward of the horizontal stabilizer Figures 201 and 202 a With me rudder trim tab in the neutral position RUDDER TRIM TAB RIG...

Page 286: ...the tail cone shown in Figure 205 a dial indicator and a push pull scale c Disconnect the rudder trim tab cables at the for applying accurate loading to the tab is required for tumbuckles located in...

Page 287: ...L t 5 1 3 4 X 21 2 X 14 aluminum or equiv 6 1 Va Cia x 2 corrosion res stl II 1 II 1 1 61 IN 7 1 1 4 Dia x 1 corrosion res stl 8 1 1 4 28 nut 31 IN 9 1 3 X 5 x 10 rubber 10 1 3 X 2 x 10 rubber 11 1 1...

Page 288: ...D 3 POUND READING READING 1 Multiply 8 by 2 and record as 28 2 Subtract A from 28 and record as X B 3 Multiply D by 2 and record as 20 28 A X 4 Subtract C from 20 and record as Y D 20 C Y NOTE X Y E T...

Page 289: ...r trim tab actuator rod to the control system components observe the color elevator trim tab coding on all parts DO NOT connect coded parts of one color to coded parts of a different color NOTE Check...

Page 290: ...uide the centerline of the bottom cable hook up hole in the assemblies on the pilot s and copilot s control column torque elevator bell crank is 80 inch from the ah bulkhead tube assemblies at the ful...

Page 291: ...I 185 00 ELEV OR DOWNICABLE B F S 170 000 I i DETAIL D L F S 151 00 ELEVAfOR I iili I F S 140 00 Cable Tensions Based on 590F Ambient Air Temperoture F S 18 50 CABLE DETAIL A ELEV UP 40 DOWF I Q NOSE...

Page 292: ...EMPERATURE CABLE TENSION GRAPH I H 14 AND SP 3 AUTOPILOT ELEVATOR AND ELEVATOR TAB CABLES j o z i F 5 1 8 50 7 g r i II I z LFS 262 90 C IMIN A w 1 5 II 30 40 50 60 70 80 90 100 110 I d S 257 506 TEMP...

Page 293: ...al the tab wheel shall tum smoothly with very little resistance Bearings not previously lubricated may be lubricated with NOTE MIL L 6086 oil 7 Chart 207 91 00 00 Lubricate shafts and thrust surfaces...

Page 294: ...em fully installed including Tensiometer readings must be taken on the autopilot and electric trim if required the load and load resist upper and lower elevator cables with the elevator in neutral anc...

Page 295: ...o 2 3 of its light wire and remove the tail cone total travel c Remove the access panel on the left hand side of f Set the elevator trim tab to 23 a i down and the fuselage just forward of the horizon...

Page 296: ...30 DETAIL A O IDLER PULLEY TIE AND SOLDER I II II INDICATOR DRUM SHEAVE 1Hr B IIN W r TRIM TAB CONTROL TRIM WRr JLL WHEEL SHAFT CONTROL ROTATED 90 WHEEL DETAIL B 35 15259 Elevator Trim Tab Indicator C...

Page 297: ...oves freely from one stop to the other After rigging the elevator and elevator trim tab i Check the tab travel and direction of movement to control system check for correct movement of the be sure tha...

Page 298: ...btained Record the dial reading as 8 h Apply a full Spound upward load at the masking CHART 201 tape on the bottom surface Record the dial reading as C ELEVATOR TAB FREE PLAY LIMITS i Release half the...

Page 299: ...III 1 6 IN 5 1 3 4 x 2 1 2 x 14 aluminum or equiv 31 IN 6 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Dia xl corrosion res stl 8 1 1 4 28 nut 10 1 3 8 x 2 x 10 rubber I 1 9 1 3 8 x 5 x 10 rubber 11 1 1 4...

Page 300: ...inch inside diameter OPTIONAL c Using a clean rag dampened with methyl ethyl ketone 21 Chart 207 91 00 00 thoroughly clean the hole a Position the actuator to the bracket and secure in the tab hem th...

Page 301: ...screws until there is no visible end play in the cable drum shaft Slide the 1 Find a metal plate of sufficient thickness for clutch rotor on the motor shah to obtain 010 to 015 inch rigidity and larg...

Page 302: ...low mounted forward of the instrument panel a lift transducer a lift transducer vane heater element a face plate heater CAUTION element on the leading edge of the left wing a landing gear switch a 5 a...

Page 303: ...ive a Warning circuit breaker a If circuit breaker tripped persists in tripping check for grounded circuit b Open circuit b Check for continuity c Defective warning horn c Replace switch switch d Defe...

Page 304: ...irplane into a stall noting the Locate the switch installation on the under surface of the speed at which the warning horn comes on and the speed at left wing leading edge and loosen the two phillips...

Page 305: ...indicated by three lights to connected to a jackscrew actuator at the flaps the left of the gap control switch The lights indicate down approach and in transit positions All lights are out when the Li...

Page 306: ...bolt connecting the actuator to the flap inch of the contour of the wing on either or both sides The gap between the lap and the fuselage must be 375 125 1875 The gap between the flap and ailemn must...

Page 307: ...e actuator until the flap synchronizes on the flap actuator in the left wing just forward of the rear with the opposite lap then connect the actuator to the flap spar e Check the rigging of the wing R...

Page 308: ...SING FUP ACTUATOR LIMIT SWITCHES FLAP TRANSMITTER AND INDICATOR CrJ s THROUGH TJ 435 TJ 437 THROUGH TJ 443 TK THROUGH TK 146 AND TK 143 THROUGH TK 150 FLAP ACTUATOR O INDICATOR O TRANSMITTER TC ADJUST...

Page 309: ...all the drive shaft retainers actuator should not be twisted when removed c Connect both flexible drive shaft housings to the support bracket e Remove the safety wire and four retaining bolts attachin...

Page 310: ...90 e Keep inboard pressure on the retainer and tighten both retainer set screws f Secure the flap drive cable to the mounting support by tightening the nuts Tighten the inboard nut to ensure that the...

Page 311: ...event the throttles from being opened NOTE A rudder control locking pin which joins and locks the pilot s rudder pedals is attached to the control column lock by a Prior to installing the control lock...

Page 312: ...CHAPTE R FUIEL...

Page 313: ...Removal 203 Outboard Leading Edge Fuel Cell Installation 203 Wet Wing Tip Removal 204 Wet Wing Tip Installation 204 Wet Wing Tip Leak Test 204 Fuel CellLeakage Check 204 Fuel Cell Repair 206 Goodyear...

Page 314: ...L CHAPTER 28 FUEL CELLS TABLE OF CONTENTS CONfD CHAPTER SECTION SU IECT SU IECT PAGE INDICATING 28 4090 Maintenance Practices 201 Fuel Quantity Indicators 201 Fuel Transmitter Removal 201 Fuel Transmi...

Page 315: ...DATE 28EFFECTIVITY 1 Oct 83 28CONTENTS 1 Mar23 79 2 Nov 30 78 2800 00 1 Jan K76 2 Oct 683 3 Oct 683 201 Oct 6 83 2810 00 201 Nov 30 78 202 Apr 1 75 203 Nov 30 78 204 Jan 9 76 205 Oct Y75 206 Mar 2Y79...

Page 316: ...erged cell mounted fuel boost pumps are provided order to make all of the usable fuel from each wing for each engine and are located in the inboard leading edge available to its engine when the fuel s...

Page 317: ...EFTWINGSYSTEMO LY 1 L FUELOWhlTITYTRUISlrlT TER CCIECKVALVE ARROW FUEL STRAINER O FUPPER VALVE INDICATES FLDW r3 B SELECTOR VALVE FUEL MANIFOLD DRAIN VALVE FIUERCAP FLAME ARRESTER TJ 229 THRU O FUELFL...

Page 318: ...L HEATED VENT LEFTWHGONLY I NELOUAMITYTRANSM TER OCnECKVALVEURROW FUEL STRAINER W FLAPPER VALVE INDICATES FLOW aD SELECTOR VALVE FUEL BOOST PUMP FUEL MANIFOLD DRAIN VALVE FILLERCAP FLAME RREGTER O FUE...

Page 319: ...ensure that all fuel is removed from the system the fuel b Make sure the airplane is statically grounded to should be drained through the boost pumps To expedite the servicing unit the defueling opera...

Page 320: ...of 10 days or longer coat the inside of the cell with light engine oil to prevent cracking or deterioration L ____ M INBOARD LEADING EDGE FUEL CELL INSTAL LATION BOTTOM VIEW CAUTION i Access Plate an...

Page 321: ...affled fuel cells The flapper valves should be inspected periodically for freedom of operation and proper seating Beech Aircraft recommends TOP VIEW that the inspection be accomplished at each annual...

Page 322: ...ure of at least 60 F for a sufficient OUTBOARD LEADING EDGE FUEL CELL NSTAL period of time to ensure flexibility during LAT7ON installation I CAUTION a Carefully insert the fuel cell into the wing cav...

Page 323: ...he 3 inch fuel pressure shall be maintained for 5 minutes interconnect and vent lines e If 3 73 0 25 psig is not maintained for 5 minutes f Disconnect the electrical connections maintain 3 73 0 25 and...

Page 324: ...capability EPAIR OF INACCESSIBLE AREAS 1 Door material 0 32 2024 T3 Aluminum ALCLAD Doubler material 051 2024 T3 Aluminum ALCLAD Nut Plates K1000 832 or equivalent Screws AN507 8R length to be determi...

Page 325: ...phenolphthalein crystals to 1 2 gallon the 114 psi pressure is not exceeded of ethyl alcohol mix then add 1 2 gallon of water 4 Inflate the cell with air to a pressure of 114 FUEL CELL REPAIR psi maxi...

Page 326: ...e of the pump aligned with the decal When the linkage is adjusted to a longer length located on the pump mounting bracket see Figure 201 a richer mixture is provided When the linkage is Torque the bol...

Page 327: ...well a Remove the cover plate not shown stop screw b The cable may be removed through the overtravel 1 and overtravel tube 2 from the fuel selector valve port by rotating the selector gear gearbox 3 l...

Page 328: ...per selection and operation b Connect the three vent lines to the check valve and i Install and safety the cover plate No lubricant is torque the hose clamps to 25 5 inch pounds used on the fuel selec...

Page 329: ...degree angle facing forward to ensure a positive vent pressure Any other configuration would create a negative The end of the fuel vent lines should extend 10 degrees pressure that would pull the air...

Page 330: ...or for each respective wing Two transmitters are located in each inboard leading edge wing cell one outboard and one inboard F UEL TRANSMITTER INSTALLA nON I One transmitter is located in each outboar...

Page 331: ...CHAPTER ICE AND RAIN PROTECTION...

Page 332: ...n Rubber Figure 201 202 Resurfacing Deicer Boots 203 Adjustment 204 Deice Controller Removal 204 Deice Controller Installation 204 TJ 3 and jJ14 jKLl and afterj 204 Deice Duplex Valve Removal ITJ 5 an...

Page 333: ...ectrothermal Propeller Deice System TK 139 and After TJ 349 and after 105 30 60 00 Propeller Maintenance Practices 201 Propeller Deicer Boot Removal 201 Propeller Deicer Boot Installation 201 Deicer T...

Page 334: ...ment McCauley TK i4j TK i5i and afCer jJL4jGI TJ 444 and after 211 Brush Blo k Removal cCa leyj iK1147j jK11Sl and aiterj iTj 436 Tj 444 and after 212 Brush Block Installation iMcCauie iK 147 iK11Sl a...

Page 335: ...Nov 9 84 103 Nov 9 84 201 May 22 87 202 May 22 87 203 May 22 87 204 May 22 87 205 May 22 87 206 Nov 9 84 30 20 00 1 Nov 9 84 30 30 00 1 May 22 87 30 40 00 1 May 22 87 2 Nov 9 84 101 Nov 9 84 102 Nov...

Page 336: ...OF PAGE EFFECTIVITY Cont d CHAPTER SECTION SUBJECT PAGE DATE 203 May 22 87 204 May 22 87 205 May 22 87 206 May 22 87 207 May 22 87 208 May 22 87 209 May 22 87 210 May 22 87 211 May 22 87 212 May 22 8...

Page 337: ...er icing equip ment offered includes pneumatically The airplane is equipped with heated operated surface deice boots elec p i tot heated stall warn ng and heated trically heated propellers wi ndsh i e...

Page 338: ...e and through this pressure relief valve reaches hold the boots flat against the surface 19 psi the pressure relief valve dumps Then when the deice system is operated the pressure from the system the...

Page 339: ...l Gyro 3 Dual Pressure Relief Valve 13 Pressure Relief Valve 4 Filter 14 Deice Duplex Valve 5 Pressure Mainfold 15 Pressure Switch 6 Instrument Air Pressure Regulator 16 Wing Deice Boot 7 Instrument A...

Page 340: ...ATIC DEICE CABINDOOR PRESSVREGAGE SEAL DOOR SEAL PRESSURE DEICE REGULATOR PRESSURE LINE PRESSURE VALVE RELIEF VENTLINE 7 VALVE EXHAUST DEICE DUPLEX VALVE TJ 2 TJg6 TJ SB AND AFTER AND THOSE CijNFORMIN...

Page 341: ...ller functioning d Pressure swi tch not d Replace pressure switch functioning e Deicer boot e Repair as described in this punctured chapter or replace f Deice duplex valve f See steps 4 and 5 not func...

Page 342: ...plugged NOTE The following items might aid in ascertaining whether or not the deSce duplex valve is functioning properly 4 One or more boots do a Defective wiring in a Check Wiring Diagram Manual not...

Page 343: ...ctive boots a Repair as described in this inflate but do not chapter or replace deflate readily with pressure gage at normal reading b Obstruction of lines b Ensure exhaust port of deice duplex valve...

Page 344: ...rface with a Because the deicer boots are made clean cloth and inspect the cloth for of soft flexible stock care must dirt If dirt is present reclean with be exerci sed against dragging methyl ethyl k...

Page 345: ...nally roll the boot tends to soften the first coat and roll trailing edge with a steel stitcher roll ing and balling up will result Allow er the coating to thoroughly dry a minimum of 30 minutes prefe...

Page 346: ...ND 2 If the surfacing has developed cracks 15 22 AT WING STATION 15 22 AT WING STATION 130 03 1 130 03 3 If the conductivity is low 58P 3412 The following procedures should be accom Stall Strip Instal...

Page 347: ...The deice with a clean white cloth saturated with duplex valve is located between FS 207 00 Icex Hand buff the boot with a clean soft and FS 223 00 to the right of the airplane cloth to obtain a smoo...

Page 348: ...ot however is c Loosen the hose cl amp s on the a temporary or emergency method of inlet and outlet hoses and remove hoses repair Therefore at the first opportu from the switch nity the boot should be...

Page 349: ...of No 4 cement to that surface of and apply a second light coat The air the patch plane may be flown as soon as the cement is dry however do not operate the deic f Allow the cement to set unti 1 ers...

Page 350: ...ty of induction system icing firewall will open automatically and the s reduced by the non icing character induction system wi 11 operate on alternate istics of fuel injection engines and the air When...

Page 351: ...ents is located to the right of the nose gear doors Left and right pitot heat A standard pitot tube for the pilot s switches supply heat to the left and right flight instruments is located immediately...

Page 352: ...he system energ zing windshield The discharge tube is equipped the relay allowing the temperature to with five orifices which are equally rise again Thus the temperature control spaced for diffusion o...

Page 353: ...ENANCE MANUAL ALCOHOL QUANTITY SENSOR INSTRUMENT PANEL n nANTI ICE TANK ANTI ICE PUMP ALCOHOL QUANTITY INDICATOR O I I I O n 58P 246 12 Windshieid Anti icer System TJ 9 thru TJ 85 TJ 87 thru TJ 97 Fig...

Page 354: ...nspect and repair or re kinked or not connected place as required g Clogged screen in g Clean screen drain and bottom of anti icing flush tank pump h Anti icing pump inop h See steps c and d erative i...

Page 355: ...pair b Defective WSHLD b Replace switch switch c Windshield heater c Replace relay relay stuck in the open position d Defective temperature d Replace controller controller e Sensing element e Check fo...

Page 356: ...ated on the pilots The resistance of the sensing element of subpanel The amount of wi ndshi eld the windshield varies with temperature anti icing fluid available in the supply changes The acceptable r...

Page 357: ...BARON 588 AND BARON 58TC MAINTENANCE MANUAL MAXIMUM MINIMUM B 310 240 ioo do 260 400 600 80 1009 1200 1400 160 1800 DEGREES FAHRENHEIT Sensing Element Tolerance Check Figure 201 30 40 00 Page 202 Nov...

Page 358: ...y masking tape along Using a sharp edged putty knife or each edge the entire height of the frame similiar tool scrape off the sealant and at least 6 inches out from the edge around the perimeter of th...

Page 359: ...he shield heater frame attachment strip windshield heater plate and the windshield heater frame attachment strip which is b Make sure all sealant is scraped bonded to the windshield This is neces off...

Page 360: ...Lay the new top retainer onto the of the top retainer that butt up against heater plate frame in the installed posi the ends of the side retainers tion Trim the ends of the retainer to obtain a good f...

Page 361: ...rs Besure that any n Apply sealant to the inside of the possible paths of moisture penetration wi re cover unti 1 it s approximately have been sealed Allow the sealant to three fourths full of sealant...

Page 362: ...er through the nose baggage compartment door and locate the controller b Tag and remove electrical wiring from the relay b Tag and remove electrical w r ng from the controller c Remove the screws nuts...

Page 363: ...o 18 amperes A small momentary nance of the modular brush blocks and slip deflection of the ammeter needle may be r ng assemblies are covered elsewhere in noticed approximately every 34 seconds this c...

Page 364: ...BARON 58TC MAINTENANCE MANUAL I i j I ENGINE SWITCH I ACCESS PLUG I ti ACCESSPLUG AMMEfER i snusH BLOCKi tAMMETER SHUNT TP J DEICER BOOT DEICER BOOT 58P 03 59 Propeller Deicer System Figure 1 END 30 6...

Page 365: ...located and corrected any new timer that two thirds the normal amount of current is installed may suffer the same internal is an indication that one of the circuits damage during the first use of the...

Page 366: ...cuit one c If voltage at deicer leads eng ne locate and fix open from deicer to ground 3 Ammete r shows no rma 1 a Inner and outer a locate and repair incorrect current part of cycle deicers heating s...

Page 367: ...ated locate and correct b Grou ld between brush b If no short exists at brush block and deicers slip ring contact check for Excluding ground brush ground from slip ring lead to circuit bare prop while...

Page 368: ...ough or di rty slip rings causing brush to skip If not this trace circuits to locate and fix loose or poor connection If all deicers on one prop are affected check the ground circuit c Timer cycles er...

Page 369: ...ANS AMPHENOL LEFT L1 I RECEPTICAL F MULTIMErrRd J1 L2 OFF J1 AND J2 TO BE COMPATIBLE WITH RIGHT J METER LEADS BEING USED D SW2 JACKS ALIGATOR CLIP GROUND TO STRUCTURE Electrothermal Propeller Deice Te...

Page 370: ...g sequence from one installation to another and will refer to notes found at the bottom of the be subject to the accuracy of the partic chart An electrothermal propeller deice ular resistance measur n...

Page 371: ...Do lamps L1 and L2 Omund conmctlon I No llluniM tw00rmnd aech through one 180 I Not rom C terminal ot Oebctlve timer aecond cycle buah Moat am and Coma bun aacum Vr v All awam am good bun 5 D kc hn r...

Page 372: ...milar tool propeller For other McCauley installation dimensions refer to CAUTION Figure 201A Unless the boot being removed is b Mask off an area approximately 1 2 to be scrapped cushion the jaws inch...

Page 373: ...M THE DE ICE BOOT LEAD STRAP AND WRAP AROUND PROP BLADE SO THAT A DOVBLE THICKNESS WILL COVER ME DE ICE BOOT LEAD STAR TRIM RETAINER STRAP SO THAT IT WIIIEND APPROX AS SHOWN A A SO YPICPL c 125 OMRLAP...

Page 374: ...er Rolling Figure 202 When solvent is used to moisten the cement methyl ethyl ketone MEK provides approximately 10 NOTE seconds for deicer installation while toluol will provide approx If the blade is...

Page 375: ...ap around the blade shank over minimum amount of MEK Remove slowly the inboard 1 4 inch of deicer enough to allow the solvent to soften the boot on B F Goodrich or 1 2 inch cement thus preventing remo...

Page 376: ...udged to be inoperable approximately 24 volts when the aircraft battery supply is being used Next check a With the timer harness plug dis the de voltage to ground from pins C D connected and the deice...

Page 377: ...r heating sequence of the eng ne propeller deicer areas If any irregular ities are detected a continuity check c Pin E of the plug to the outboard should be performed on the wiring from the terminal o...

Page 378: ...older then slide and must be replaced the springs off the brushes I BRUSH BLOCK RESISTANCE CHECK d Unsolder the wi res from the brushes being replaced noting which pin To check for an open circuit a s...

Page 379: ...gral brush and degrees of slip ring rotation install spring These modular units are stacked shims P N 1 E1157 between the brush with a spacer and held together by screws holder and the mount until the...

Page 380: ...modular unit terminals h Before installing the retai ning b Remove the sc rews nuts and nuts ensure that the brushes are aligned washers that secure the modular unit to with the slip rings so that the...

Page 381: ...r bulkhead Slip r ngs that may have roughened or b Torque the six slip r ng attach damaged surfaces but which are struc bolts to approximately 25 inch pounds turally sound can be machined and being ca...

Page 382: ...for wear by one BRUSH REPLACEMENT MCCAULEY of the following methods iTJ 436 TJ 444 AND AFTER TK 147 TK 151 AND AFTER Figure 211 ON THE AIRPLANE a Remove the brush block from the a Insert a stiff w7re...

Page 383: ...may be engine with the two screws but do not cleaned with a clean cloth dampened with tighten the screws methyl ethyl ketone MEK Do not soak the brush block assembly with MEK b Add or remove shims se...

Page 384: ...AINTENANCE MANUAL 094 MIN 1 FEELER GAGE O BRUSH BLOCK I BRUSH WEAR MEASUREMENT BRUSH AND 6 3 O IBEEMBCI I BUTTON HEAD SCREW TORQUE 20 24 LB IN 36 251 6 DISASSEMBLY Brush Block Assembly McCauley Figure...

Page 385: ...ring The resistance should e Ensure that the face surface of be a minimum of 50K ohms the slip rings are parallel and flat within 008 inch overall SLIP RING REMOVAL MCCAULEY f The slip ring holder fa...

Page 386: ...CHAPTER LAN DING G EAR...

Page 387: ...ce Practices 201 Main Gear Shock Absorbers 201 Lubrication 201 Main Gear Removal 201 Main Gear installation 201 100 Hour Inspection 201 Actuator and Motor 201 Landing Gear Strut 203 Strut Fluid Level...

Page 388: ...elay Installation 201 Landing Gear Rigging 203 100 Hour Inspection 207 Retract Mechanism 207 Doors and Linkage 207 Position Indicators 207 Warning Horn 207 Downlocks 207 Safety Switch 207 Actuator 207...

Page 389: ...ter Cylinder Removal 204 Brake Master Cylinder installation 204 Brake Master Cylinder Linkage Adjustment 204 Parking Brake Valve Removal 204 Parking Brake Valve Installation 204 Parking Brake Adjustme...

Page 390: ...AND BARON 58TC MAINTENANCE MANUAL CHAPTER 32 LANDING GEAR TABLE OF CONTENTS CONTINUED SUBJECT PAGE Landing Gear Position Lights Adjustment 202 Landing Gear Warning Horn System Throttle Switch Adjustm...

Page 391: ...No Chapter Page s By Date No 32 1 32 60 00 201 ATP I S 10 04 99 A24 1 9 02 When inserting or removing a temporary revision the applicable revision number and the initials of the person s inserting an...

Page 392: ...Raytheon Aircraft BEECH BARON 58P AND 58TC MAINTENANCE MANUAL RECORD OF TEMPORARY REVISIONS Temporary Affected Inserted Removed Revision By Revision No Chapter Page s By Date No Date...

Page 393: ...ep 3 01 2 Sep 3 01 3 Sep 3 01 4 Sep 3 01 32 00 00 i Oct 6 83 101 Apr 1n5 32 10 00 201 Nov 30 78 202 Apr 1 75 203 Apr 1 75 32 20 00 201 Nov 30 78 202 Apr 1 75 203 Apr 1 75 32 30 00 201 Apri 75 202 Apr...

Page 394: ...ND BARON 58TC MAINTENANCE MANUAL CHAPTER 32 1 LANDING GEAR LIST OF PA GE EFFECTI VITY CONTINUED CHAPTER SECTION SUBJEC T PAGE DATE 32 50 00 201 Apr 1 75 32 60 00 201 Sep 3 01 202 Sep 3 01 203 Sep 3 01...

Page 395: ...easons the airplane must be put on extension and retraction of the main and nose landing gear jacks and inspected before the gear controls are Rod assemblies attached to the smaller upper actuator arm...

Page 396: ...djust limit switch actuator is hitting internal stops b Dynamic brake switch defective b Replace switch 5 Warning horn in a Open or grounded circuit a Check continuity operative or malfunctioning b Th...

Page 397: ...hing 6 bolts 2 and With the aircraft resting on the ground and the fuel cells full 3 washers 4 5 and 7 and nuts 8 Torque to 250 to 400 inflate the main strut until 3 inches of the piston is exposed in...

Page 398: ...I i FRONT SPAR h 6 1JI USE ONE 100951SO1bXF WASHER BETWEEN MAIN GEAR AND ZPAR HAVING A MAXIMUM TOTAL GAP OF 016 TO 031INCH USE ONE 100951X032XF WASHER IF GAP IZ 032 70 04 4 7 INCH i ii 9 58P 201 4 Mai...

Page 399: ...ller valve and piston area bending and security STRUT FLUID LEVEL Inspect the strut for proper LANDING GEAR STRUT Inspect the strut and attaching inflation If leakage is detected deflate the strut and...

Page 400: ...ock the aircraft gently to prevent possible binding of the piston in the barrel when inflating c Install the nose baggage compartment flooring d Connect the landing light wire e Connect the drag leg o...

Page 401: ...E MAN UAL eo 6 2 i t Q 7 i USE 100951S016YP WASH ERS MAXIMUM OF 2 PER SIDE TO OBTAIN TOTAL END PLAY BETWEEN NOSE GEAR AND SUPPORTS OF 000 TO 015 INCH 8 3 iiI li 58P 2055 Nose Gear Installation Figure...

Page 402: ...acks security condition and leakage at c Swivel the nose wheel to check the turning radius the air filler valve and piston area of the strut and for freedom of movement without binding or rough spots...

Page 403: ...g gear motor and the dynamic brake relay g Remove the landing gear actuator access door on i Check rigging of the landing gear system When the bottom of the fuselage and remove the nose gear cycling t...

Page 404: ...NSION 9 a I II un III il II Illc GOWN LOCK IINSION CHECKING MAIN GEAR ADJUST r I LINKAGE HEREI ir D FI B o I O MAIN GEAR OUTBOARD DOOR ADJUSTMENT NOSE WHEEL SHIMMY DAMPENER A E C 2 4 c e H H 5 1 Y I 1...

Page 405: ...ent to properly cycle the position landing gear during rigging A 28 25 25 volt auxiliary c Disconnect the nose wheel door linkage Secure power unit capable of maintaining the initiai setting within th...

Page 406: ...wise movement before the Do not operate the hand crank with the power sector gear contacts the gearbox internal stop If proper on internal clearance is not obtained adjust the landing gear uplimit swi...

Page 407: ...ing bolt head from initial contact with no clearance T gMen the locknut securely n With the mJn landing gear fully extended and the i Install the inboard door retract rods at the downlock in the locke...

Page 408: ...tracted position spring feeler gage between the strut io apply a force of 52 62 pounds to the inboard portion of and bumper and the hook portion around nearby structure the uplock assembly Check for a...

Page 409: ...ing for breaks conditions of insulation and loose connections indicators for proper indication MAIN GEAR Adjust the downlock switch installed on the main gear so that the overtravel of the switch plun...

Page 410: ...SEMBL Y resulting from the movement of the master cylinder pistons is transmitted through flexible hoses and fixed aluminum The airplane is equipped with a Cleveland 5 00 x 5 nose tubing to the brake...

Page 411: ...systems 3 Unable to hold a Leak in brake system a Visually check entire pressure system for evidence of leaks b Check master cylinder seals replace if scored 4 Parking brake will a Air in system a Bl...

Page 412: ...otter pin location and install a new cotter pin NOTE I NOSE WHEEL INSPECTION Make sure that the brake disc lugs engage the slots of the inner wheel half Rotate the wheel a Inspect wheel half flanges f...

Page 413: ...the cylinders Remove the brake and bubbles are gone from the draining fluid Pumping the lay it on its side Add brake fluid as needed through the brake pedals is not necessary bleed port and tap the b...

Page 414: ...RS BRAKE RESERVOIR PRESSURE EOUALIZAT LINE FORWARDPRESSURE iJQ DETAIL B le TJ 2 AND AFTER BRAKE DISC PISTON HOUSING 250 WORN BRAKE j e 00 CARRIER LINING BRAKE BLEEDER a 0 INSULATOR CARRIER LINING PIST...

Page 415: ...to remove end play Using a PARKING BRAKE VA L VE REMO VAL wrench tighten the nut to the next available cotter pin position and install a new cotter pin a Bleed the brake system of all hydraulic fluid...

Page 416: ...s growth is the attach fitting balanced by tread wear so there is no increase e Test the parking brake adjustment by pulling the in tire diameter parking brake handle out and operating the brake pedal...

Page 417: ...d and the tape on the piston rod just contacts the scraper ring Tighten the lock nuts securely ADJUSTMENT e Turn the nose wheel to the extreme right place the tape on the forward end of the piston rod...

Page 418: ...ts 2 3 down position then stop and inch the gearthe remaining distance to the down limit switch by intermittent operation of the circuit breaker Check the emergency hand crank for 1 8 to 1 4 turn free...

Page 419: ...e on jacks c Pullthe LANDING GEAR MOTOR circuit breaker d Apply electrical power to the airplane e Disconnect the left safety switch operating arm at the torque link and position to simulate an on gro...

Page 420: ...correspond to gear position LANDING GEAR WARNING HORN SYSTEM THROTTLE SWITCH ADJUSTMENT The throttle warning horn micro switch is located in the pedestal console and is actuated by the movement of the...

Page 421: ...CHAPTE R LIGHTS...

Page 422: ...1 Landing Lights Taxi Lights and Tail Lights 101 Maintenance Practices 201 High Intensity Lights 201 Power Supply Unit Removal TJ 3 thru TJ 132 TK 1 thru TK 70 except TK 68 201 Power Supply Unit Insta...

Page 423: ...ntensity light system greatly increases the visibility The power supply unit steps up voltage of the airplane of the airplane to other airplanes during night flight by system to the level required to...

Page 424: ...ce bulb b Fixture not grounded b Check for good bonding between fixture and structure Tighten mounting screws c Loose connection c Check all connections in circuit d Defective fixture or switch d Repl...

Page 425: ...bles at the power supply or light the cables at the power supply or light assemblies and before handling or assemblies and before handling or disassembling either of these units in any way disassembli...

Page 426: ...it for at least 10 minutes to elapse before disconnecting CAUTION the cables at the power supply or light assemblies and before handling or Observe the precautions outlined under the disassembling eit...

Page 427: ...off resistor is incorporated in On airplanes TJ 80 and after and TK 41 and the power supply circuit tum the control switch after a harness wring out and high potential for the strobe lights OFF and a...

Page 428: ...ding Gear Position Lights 327 Engine Instrument Post Lights 327 Reading Lights 303 Cabin Lights 1864 step Lights 1495 Courtesy Light 30 0502 5 Nose Baggage Compartment Light 303 Cabin Altitude and Cab...

Page 429: ...678 TJ 185 and after TK 57 and after flashtube 31 1745 or 203415 nav bulb 678 or 203529 2 Strobe Light Wing TJ 3 thru TJ 132 flashtube 55 0221 1 TK 1 and after TK 133 and after flashtube 55 0221 1 or...

Page 430: ...CHAPTER NAVIGATION...

Page 431: ...VIGATION TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 34 00 00 Description and Operation 1 Instrument Access 1 Instrument Operation 1 FLIGHT ENVIRONMENT DATA 34 10 00 Descripfion and...

Page 432: ...een installed to enable you to pull the instrument out INSTRUMENT OPERA nON To gain access to the flight instruments remove the screws attaching the panel and pull it out far enough to disconnect The...

Page 433: ...The optional dual pitot system provides forward side of the front spar cover is placarded a second pitot tube located in the nose section to the right ALTERNATE NORMAL When it is required select the...

Page 434: ...unded or open circuit b Check for continuity c Defective heating element in pitot head 2 Circuit breaker keeps a Grounded wire tripping 3 Instruments inoperative or a Lines clogged a Drain static air...

Page 435: ...ith airspeed indicator reading a cleaning solvent to ensure that no film exists d If there is no decline in the reading after several on them minutes there is no leak in the pitot system e If a declin...

Page 436: ...T STATIC BUTTONS UPPER DRAIN VALVE CLIMB RH P1T0T CABIN DIFFPRs6SURL EMERGENCY CLIMB STATIC A1R SOURCE EMERGENCY ALT I I L l SOURCE UPPER AIR SPEED I TJ 2 AND I FTER r TK l AND AFTER APf ssaPlrclacn s...

Page 437: ...CHAPTE R OXYGEN...

Page 438: ...6 79 4 Oct 26 79 5 Oct 26179 201 Oct 26179 202 Oct 26 79 CHAPTER 35 OXYGEN TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 35 00 00 Description and Operation 1 Maintenance Practices 201...

Page 439: ...adjacent to the pilot s oxygen outlet oxygen outlet and also adjacent to the oxygen filler valve in indicates the pressure at the cylinder When the cylinder is the aft fuselage When the cylinder is fu...

Page 440: ...oXVGEN II W I E loooI oo OXYGEN W SUPPLY 3 ak O Wn DETAIL A DETAIL B A BU D orJ p ll PUSH PULL CONTROL KNOB DETAIL E FILLER VALVE TO OUTLETS I omoaru I I RECH ROEI TO PRESSURE GAGE OVERBOARD TO CONTR...

Page 441: ...tu A s D Ao c A oETnll A A i Q AI B Dr OXYGIN SUPPLI P ISIUII GIGI T1 2 m u TJ 132 C A oErniL B irl al IREC IIOEI CVICI PULL TO PUSII PULL CONI OL orrniL E To sarssvlr GIGE oETnllC OVII O ID IPLI SI...

Page 442: ...GEN OUTLET SoOXYGENII I I c OXYGEN SUPPLI O DETAIL A DETAIL B g L o Q pl PUSH PULL CONTROL KNOB DETAIL E TO PRESSURE GAGE fO PUSH PULL OX CEN RECnAROE CONTROL TO OUTLETS OVERBOARD TO FILLER PORT RELEA...

Page 443: ...ESSUIE O CiT OXIGEN OUTLET OXYGEN OXYGEN DETAIL A DETAIL B o ll c A A a DETAIL E O nrsrulr O GE TO OU1IITS TO llllr COIT I UXYOETll TO CONTIOL OXIGEN SUPILI Insn lsr I Qi rIIElrUIIEO oE 5 TO VENT LINE...

Page 444: ...test using the aft fuselage cylinder pressure Using the supply gage on the pilot s side wall note cylinder pressure There shall be no pressure loss after 30 minutes In case leakage exists apply MIL L...

Page 445: ...LAT ON i On TK 1 thru TK 84 install the supply cylinder cover and equipment screen Close the nose compartment a Place a new cylinder with regulator attached in baggage door On TK 85 and after close th...

Page 446: ...CHAPTER PNEUMATIC...

Page 447: ...essure Regulator And Dual Pressure Relief Valve Adjustments 201 Pressure Pump Removal 202 Pressure Pump Installation 202 Dual Pressure Relief Valve Remo ai 202 Dual Pressure Relief Valve Installation...

Page 448: ...T OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 36 EFFECTIVITY 1 May 22 87 36 CONTENTS 1 May 22 87 36 00 00 1 Nov 30 78 101 Nov 30 78 102 Nov 30 78 201 May 22 87 202 May 22 87 202A May 22 87 2...

Page 449: ...efective regulator d Replace regulator 2 Pump out recess button s a Defective pump s a Replace pump s extended b Filter or line plugged b Replace filter between pump and manifold Clean lines as necess...

Page 450: ...00 for cabin door seal replace ment b Pressure pump s malfunction b Replace pump s c Loose or broken wires c Check electri cal wires for condition See Vl ring Diagram Manual 102 590000 23 d Defective...

Page 451: ...the instrument air pressure indi great amount of dust or sand in the air cater to read in the green are with both the filters should be inspected and engines operating at 1500 rpm replaced at more fre...

Page 452: ...on top of the engine pump is accessible by removing the LH and RH engine cowling Never use an air pump which has been dropped or mishandled a Remove the air filter inlet and outlet hoses from the air...

Page 453: ...OR INSTALLATION b Install the inlet and outlet hoses on the valve and secure the hoses with a Install the adapters on the regu clamps later making certain the insides are clean and free of foreigh obj...

Page 454: ...DUAL PRESSURE RELIEF VALVE RELIEF VALVE PNEUMATIC DEICE J I I I I FORWARD PRESSURE GAGE I I CABIN DOOR SEAL DOOR SEAL DEICE PRESSURE PRESSURE LINE PRESSURE REGULATOR RELIEF VALVE VENT LINE VALVE EXHAU...

Page 455: ...f Valve 4 Filter 14 Deice Duplex Valve 5 Pressure Manifold 15 Pressure Switch 6 Instrument Air Pressure Regulator 16 Wing Deice Boot 7 Instrument Air Pressure Gage 17 Horizontal Stabilizer Deice Boot...

Page 456: ...CHAPTER...

Page 457: ...Panel 203 Removal of Engine Instruments 203 Installation of Engine Instruments 204 Upper Left Subpanel 204 Circuit Breaker Switches 204 Switches 204 Circuit Breaker Subpanel 206 E LECTR ICA L AN D E...

Page 458: ...00 00 1 Apr1 75 39 1 0 00 201 Apr 1 75 202 Apr1 75 203 Apr1 75 204 Jan 9 76 205 Apr1 75 206 Jan 9 76 207 Jan 9 76 39 20 00 201 Apr1 75 202 Jan 9 76 203 Jan 9 76 204 Jan 9 76 205 Jan 9 76 206 Jan 9 76...

Page 459: ...breakers for the avionics equipment located in the upper left corner of the instrument panel contains the flight instruments 3 The left panel located just below the floating panel contains the autopi...

Page 460: ...ps instrument panel and carefully lift the glareshield d Connect the plumbing and or electrical b Disconnect the air duct Remove the glareshield connections to the flight instruments c Disconnect the...

Page 461: ...ns Some units must be removed from the panel possible it will be necessary to inspect the installation to prior to removing the harness connector from determine the required procedure to follow for th...

Page 462: ...nect and remove any post lamps e Remove the mounting screws securing the Some units must be removed from the panel instrument to the center section prior to removing the harness connector from f Remov...

Page 463: ...ent SWITCHES panel When removing any of the components for maintenance purposes tag and identify any wires removed Air Conditioner Press Air Cool S59 to facilitate reinstallation of the components Air...

Page 464: ...HT LEtl COND C HTE CAIIN AUX FVBL PV OID ORD O O WE T I T B L T O 0 IS 8 R g Q 8 RH LH T XI LIO T ICE O E PILOP DE ICE suar N V DE ICE IUEL PITOI C I O LANDING LTS LIGHTS LIOHI LltnT LIGHI VENI EH LH...

Page 465: ...n Gyro Instruments CB91 TJ 2 thru TJ 45 TK 1 structure When removing any of the components for and after maintenance purposes tag and identify any wires removed Hour Meter CB103 to facilitate the rein...

Page 466: ...I 5A AIRCOND AIR OIL CYL TEMP COWL IGN ALTNR CABII INST GYROI TURN BLWRS OPT L RIGHT LEFT FLAPS START OVV LIGHTS LIGHTS I INST I SLIP a c a snsn SURFACE ALCOHOL PROP 6 8 es DE ICE II OTY HOUR LDG OR P...

Page 467: ...ts and the illustrations The circuit diagrams and the accompanying equipment lists showing their installation on the following pages identify in the Wiring Diagram Manual identify each electrical thes...

Page 468: ...e Accessible from Forward Side 533 633 Flap 231 232 Forward Cabin Bulkhead to Instrument Panel 541 641 Wing Outboard Leading Edge Accessible from within Fuselage 542 642 Wing Outboard Aft of Main Spar...

Page 469: ...191 00 WZ 108 281 730 II I 7io ws Ib8 281 195 lb1 00 351 11 11 352 361 nK 362 F5 10 00 F5 39 00 810 I 5 58 00 820 830 330 2 0 LS W 340 5 3 1 253 T r 320 1251 252 1 310 370 L_ _J 231 232 131 132 140 i...

Page 470: ...re mounted individually with screws and nut plates When Prop Deicer Shunt R11 removing any of the components for maintenance purposes Stall Warning Horn LS12 tag and identify any wires removed to faci...

Page 471: ...DEICER REGULATOR TIMER r ANNUNCIATOR i 1 DIMMING RELAY G k I e I t i WARNING I II HORN C LANDINGGEAR L jIjj I I I W INING RESISTOR LANDING GEAR i I wnaNINe L i ___ ___ FLASHER LANDING GEAR WARNING HO...

Page 472: ...onents for maintenance purposes tag and identify any wires removed to facilitate the reinstallation of the The following electrical components are located on the left components side of the airplane u...

Page 473: ...J 30 TK I AND AFTER 5 67 DETAIL B LIGHT DIMMER TRANSISTOR ASSEMBLY LEFT STRINGER LEFT STRINGER 18 55 5 625 MAIN SPAR FS 82 96 I I FS 84 50 ce 4 I L 4 t i G e e a i8 L 4 Q I I ga 4 TRANSISTOR ELECTROLU...

Page 474: ...re 204 Airplane serials TJ 31 and after the following equipment is Inverter Electroluminescent Lights MG 11 mounted on the left side of the fuselage at FS 50 00 Annunciator Terminal Board Assembly bet...

Page 475: ...ABIN BULKHEAD PANEL FS 39 00 DErnlL A FS 58 00 ELECTROLUMINESCENT INVERTER 550 11 MAIN SPAR FS 82 96 ANNUNCIATOR TERMINAL BOARD ASSEMBLY FORWARD CABIN BULKHEAD FS 39 00 SWITCH CABIN S ALTITUDE WARNING...

Page 476: ...d bolts When removing any of the components for maintenance purposes tag any wires removed to facilitate Above Floorboard the reinstallation of the components Fuse Baggage and Courtesy Lights F42 Fuse...

Page 477: ...FS lk 25 Ace a 5 30 SPARE FUSES I FUSE BAGGAGE d AGC S COURTESY LIGHTS AGC 5 5 43 FS lq 25 n FUSE STALL WARNING FS 27 00 AGC 5 5 44 BAGGAGE Oi COMPARTMENT FLOORBOARD FUSE ALTERNATE BUS RELAY AGC S F...

Page 478: ...av Lights F36 located on the forward baggage compartment below the Fuse Comm F37 floorboard All components are attached with screws bolts Fuse Nav F38 and nut plates When removing any of the component...

Page 479: ...G I TURN I CABIN I COM I AUDIOI SPARE LT SLIP I LTS 10A 56 56 5A 56 56 5A 5A 5A 5A SA 10A GYROS I INST NAV I NAV 1 XPNDR I SPARE LTS LTS BOX ASSEMBLY p DETAIL A 888888888888 1 I ALTERNATE SPARE LIMITE...

Page 480: ...207 LE FT NACELLE ZONE 521 Figure 207 The following electrical equipment is mounted in the right nacelle and is accessible through an access panel The following electrical equipment is mounted in the...

Page 481: ...LLE Risesaro O O PLTOVI o FUSE ALTERNATOR AGC I5 F 24 FVSE AIRCONDITIONING AGC 5 K 20 STARTER RELAY K 20 Co it VIEW LOOKING OUTBOARD Af RIGHT NACELLE DETAIL B u our Puss INVERTER FUEL FLOW MG 12 FUSE...

Page 482: ...the external power system are The following electrical equipment is mounted on the mounted on the outboard side of the left nacelle These outboard side of the left nacelle components are mounted indiv...

Page 483: ...MAINTENANCE RnANUAL EXTERNAL POWER BOX ASSEMBLY AND BATTERY RELAY REAR VIEW OF EXTERNAL POWER RECEPTALE DETAIL A EXTERNAL POWER RELAY K 21 EXTERNAL POWER RECEPTABLE J 32 58 354 17 External Power Figur...

Page 484: ...CHAPTER STANDARD PRACTICES STRUCTURES...

Page 485: ...CT 51 EFFECTIVITYICONTENTS 1 OctBgl 1 Jan K76 51 00 00 201 Oct 6 83 CHAPTER 51 STRUCTURES TABLE OF CONTENTS CHAPTER SECTION SUBJECT PAGE SUBJECT 51 00 00 GENERAL 1 Description and Operation 201 Mainte...

Page 486: ...stations 39 00 and 190 00 All skin bulkheads and The fuselage is of semimonocoque construction Although structure points plumbing and wiring connections passing the carry through structure is an integ...

Page 487: ...s are recommended in addition inch smaller than the first and the third patch 112 inch to AC 43 13 11 AIRCRAFT INSPECTION AND REPAIR smaller than the second MANUAL and AC 43 13 2 AIRCRAFT ALTERATIONS...

Page 488: ...CHAPTER DOORS...

Page 489: ...203 Aft Cabin Door Removal CTJ 2 and after 203 Aft Cabin Door Installation TJ 2 and after 203 Installing a New Aft Cabin Door TJ 2 and after 203 Aft Cabin Door Latch Adjustment TJ 2 and after 204 Aft...

Page 490: ...CHAPTER SECTION SUBJECT PAGE DATE BEFFECTIVITY 1 Oct 633 52 CONTENTS 1 Oct 83 52 00 00 1 Jan K76 2 Oct 6 83 52 10 00 201 Nov 30 76 202 Nov 30 76 203 Nov 30 76 204 Nov 30 76 205 Nov 30 76 206 Nov 30 76...

Page 491: ...k fittings in the edge of the door opening and bottom of the door The upper eccentric plate is rotated by inward toward the door to pull the door edges firmly the cabin door handles and drives the cen...

Page 492: ...ure structure The plastic is of the same type f the push pull tube and outside door handle connected material as the other windows and is installed in the same directly to the latch tongue manner Repa...

Page 493: ...the door sill as the door swings out to 06 inch is required around the edge of the door f Perform PRESSURIZATION TEST PROCEDURE as described in Chapter 21 30 00 NOTE FORWARD CABIN DOOR RIGGING TJ 2 a...

Page 494: ...7 Hook 4 8 Push Pull Rod 9 Locknut 10 Flexible Cable Assembly ADJUSTMENT 11 Barrel Nut 12 POINT 12 Eccentric Arm 13 Push Pull Rod 7 11 14 Locknut A DJU S T M EN T POINT ADJUSTMENT POINT ADJUSTMENT PO...

Page 495: ...d toward the door frame contour of the door when the seal is inflated Check for an expansion distance of 12 inch between the seal and the door frame d Perform PRESSURlfATlON TEST PROCEDURE c Clean the...

Page 496: ...remove the aft cabin door upholstery panels Refer to Figure 202 for pictorial coverage of the adjustment points AFT CABIN DOOR FLEX CABLE REPLACEMENT a Before closing door actuate the door handle to T...

Page 497: ...he upper door j Install the upholstery panels and door handle on the inside of the door CABIN DOOR RIE MOVAL TK I ANn AfTENI if the cable is broken inside the door making it impossible to Figures 203...

Page 498: ...EECHCRAFT BARON 58P AND BARON 58TC MAINTENANCE MANUAL ADJUSTMENT POINT ADJUSTMENT POINT ADJUSTMENT POINT ssP oczs Aft Cabin Door Latching Mechanism TJ 2 and after Figure 202 52 1 M O Page 206 Nov 30 7...

Page 499: ...the door to obtain a proper fit The shims Figure 204 1 should be retained and the same number of shims installed under each hinge when the door is reinstalled CABIN DOOR INSTALLA nON TK I and afterj...

Page 500: ...ttach the scissors door stop to each door sill b Support the doors and remove the hinge pins by a If the air leakage is around the forward half of the pulling straight up door the necessary adjustment...

Page 501: ...ndoor follows c Back the switch adjustment off until the switch is not actuated a Remove cabin upholstery panels beneath the door d Readjust the switch until it actuates at F S 73 9 and at the aft edg...

Page 502: ...CHAPTER FUSELAGE...

Page 503: ...PTER SECTION SUBJECT PAGE DATE 53 EFFECTIVITY CONTENTS 1 Jan 9 76 53 30 00 201 Jan 9 76 202 Jan 9 76 CHAPTER 53 FUSELAGE TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE P LATES SKIN 53 30 00 Ma...

Page 504: ...cables enclosed within the fuselage When installed FUSELAGEACCESS OPENINGS they continue the aerodynamic lines of the fuselage with little increase of drag The panels plates and doors as shown in Figu...

Page 505: ...Nose Cone 6 Tail Cone 7 Elevator Bell Crank Elevator Down Spring Turbuckles and Cable Inspection 8 Wiring Inspection 9 Landing Gear Actuator 10 Control Cable Pulleys and Nose Gear Retract idler Arm 1...

Page 506: ...CHAPTER NACELLES PYLONS...

Page 507: ...CT PAGE DATE 54 EFFECTIVITY CONrrNTS 1 Nov3W76 54 00 00 201 Nov30 76 CHAPTER 54 NACELLES PVLONS TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE NACELLES 54 00 00 Maintenance Practices 201 Inspe...

Page 508: ...be removed removing the engine cowling b Inspectthesteel rivetsin thefoMlardandaftsideof d Paint the rivet heads completely with epoxy the nacelle firewall for condition polyamide primer MIL P 23377C...

Page 509: ...CHAPTER STABILIZERS...

Page 510: ...heck Balance By Counter Balancing 201 Equipment Required to Perform Check Balancing By Counter Balancing 201 Balancing Procedure Counter Balancing Method 202 VERTICAL STABI LIZER 55 30 00 Maintenance...

Page 511: ...PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 5 EFFECTIVITY 1 Jan 9 76 55 CONTENTS 1 Jan 9 76 55 10 00 201 Apr 1 75 55 20 00 201 Jan 9 76 202 Jan 9 76 203 Jan 9 76 55 30 00 201 Apr1 75 55 40 00...

Page 512: ...left hand side of the aft fuselage Beeswax may be used on shanks of aft bolts to c Remove the elevator facilitate installation All threads should be dry d Loosen the elevator trim tab cables at the t...

Page 513: ...be and read the reaction on the beam balance completed The tab tab push rod static wicks and hinge e Calculate the static underbalance moment M bolts must be attached The chord line must be horizontal...

Page 514: ...is free to rotate about the hinge line 2 The over or underbalance moment is d To determine if weight should be added or designated by M removed use a short length of small dia meter string secured 3...

Page 515: ...ANCE CHECK PLACE NEAR ELEVATOR CONTAINER HINGE LINE VIEW A A TOP FORWARD SCREW A B MASKING TAPE DETAIL B CONTAINER MASKING TAPE TO SECURE TAB IN NEUTRAL ii 1 c ELEVATOR HINGE CLEVIS LC KNIFE EDGE D E...

Page 516: ...osition the vertical stabilizer and install the bolts a Remove the tail section access doors on the left at the forward and rear spars Install the elevator center hand side of the aft fuselage hinge b...

Page 517: ...pounds Tail heaviness indicates static underbalance while nose The spindle must be vertical throughout the heaviness indicates static overbalance balancing procedure Hold a spirit level against the ma...

Page 518: ...he trailing edge Mark the chord line 4 The following is a typical example of a with a suitable marker such as a grease pencil then remove balancing calculation Assume the rudder was slightly the strai...

Page 519: ...ER HINGE LINE MASK NCrlPT TO SECURE TAB IN NEUTRAL e KNIFE EDG E ACTUAL FORCE MEASUREMENT D iI c CONTAINER VIEW A A JIG MUST BE HORIZONTALLY LEVEL JIG MUST BE HORIZONTALLY LEVEL STATIC UNDERBALANCE TA...

Page 520: ...CHAPTER WIINDOVVS...

Page 521: ...er 203 LH Window Removal C K 1 and after 203 LH Window Installation C K I and after 203 Storm Window Removal CR l and after 204 Storm Window Installation Cn 1 and after 204 Door Window Removal CTK 1 a...

Page 522: ...PAGE DATE 56 EFFH TNIN 1 Oct J83 56CONTENTS 1 Oct 883 5 0Q 00 1 Oct 883 201 Oct 883 202 Oct 883 203 Oct 683 204 Oct 83 205 Oct 883 206 Oct 83 207 Oct 883 208 Oct 883 209 Oct 883 210 Oct 883 211 Oct 8...

Page 523: ...anufactured of clear The windows are secured with HFLok fasteners spaced or tinted acrylic plastic of 250 inch thickness The cabin evenly with a distance of 40 inch from the centerline of the windows...

Page 524: ...ion of the windshield against the frame will soften the plastic and may cause crazing squeeze the seater around the fasteners to the edge of the Afiphatic naphtha and similar solvents are highly metal...

Page 525: ...section b Remove We Hi Lok fasteners and remove We window Remove the old sealer with toluol 22 Chart 207 91 OM00 I NDSHIELD IEIS I ALLATION T K I and after LH WINDOW INSTALLATION TJ 3 and after a Cle...

Page 526: ...as the altar fasteners are secured a Position the hinge block and install the hinge pin A unifom pad of sealant 007 inch thick will b Secure the hinge pin and the set screws assure a good seal if the...

Page 527: ...ow replace g Place the window in position and cleco in place the storm window seal h Using MS20470AD4 rivets secure the window to the door S70RM WINDOW REMOVAL 7K I and after NOTE a Remove the two iot...

Page 528: ...he plastic to soften or craze All cabin windows are installed using HFLok fasteners ff the replacement window does not have fastener holes already drilled the window must be dn lled and installed acco...

Page 529: ...ow installation be vety careful with the window pane Do not allow tools rings h Clean the edge of the window with a dean soft rough cloths or any other objeds that might flannel doth sc tch the window...

Page 530: ...e window Using the No 40 pilot holes h On airpianes that did not have a spacer and strap as a center use the 102 5004 D701 1 dnll bit or a spea al installed on the upper and ah portion of the window i...

Page 531: ...ons indicated in Figure 203 s install Be strap with temporary fasteners t Using a washer under each nut install new HU8PB70 5 6 fasteners Draw the window down evenly all NOTE the way around After new...

Page 532: ...OK FASTENERS INTERIOR VIEW CT s X C F 5 4 S7RAP Y _ZC 1 r 0 DAIIITHESE LOCATIONS FORj 1 TEMPORARY INSTALLATION OFMNDOW I I i i DRILL THESE LOCATIONS FOR tt i OF SPACER sl I t 1 SPACER i I i I i AFT 1...

Page 533: ...206 illustrates an d Inspect the Hi Lok mounting fasteners for proper example of light placement installation Check specifically for 1 perpendicularity to the surface of the window with no gaps under...

Page 534: ...nd Fastener Positioning Figure WMIDOW REPAIR SCRATCH REMOVAL must be replaced Do not attempt to repair this type of damage Minor aau ng or scratches may be safely removed from the outer pane without w...

Page 535: ...NIANWL qIAMP tV MP VINV A A VIEW LOOKING DOWN A A IB VIEW VIEW I e 4 LAMP LAMP LAMP VIEW VIEW LOOKING INTO SIDE Ii OF FUSELAGE FUSELAGE SKIN VIEW B B Vkwing Angles and LfgM Placement for Window Inspe...

Page 536: ...BEECHCRAFT BARON 588 AND BARON 58n MCU CTt32PHCE NIANUAL C1 i z he ai 5 O k tLs 1 r edlyi iX a I Example of C19dng ngure 207 END S QOQO papa n3 A18 Oct 8 88...

Page 537: ...ove the hinge pin c Remove the window If blank windows are used for replacement windows the followiog procedures should be used for dn lliog holes SECOND WINDOW NSTALLA T ON TK I and after i Place the...

Page 538: ...as descn bed holes in the back section as a guide in step c of the window removal procedure f Remove the window bun all holes and apply sealer 51 Chart 207 91 00 00 to an area appro mately 1 2 inch w...

Page 539: ...CHAPTE R VVINGS...

Page 540: ...ng Assembly 210 Metal Stall Strip 211 Wing Bolt Nut and Fitting Inspection 211 Magnetic Particle Inspection 213 Ning Main Spar Cap Visual Inspection 215 PY TESISKIN 57 30 00 M ntenancePractices 201 Ni...

Page 541: ...1 Oct 83 57 00 00 1 Oct 883 201 Oct 883 202 Oct 83 203 Oct 83 204 Oct 6r83 205 Oct 683 206 Oct 883 207 Oct 883 208 Oct 83 209 Oct 883 210 Oct 883 211 Oct F 83 212 Oct 883 213 Oct FJ83 214 Oct 883 215...

Page 542: ...formed clad 2024 T3 and 2024 T4 aluminum alloy angles and dad 2024 T3 cap strips The tamped ribs are formed The carry through structure to which the wi g assemblies stringers used throughout the wing...

Page 543: ...located at trailing d g e b Position the wiilg tip to the wing and insM11 the WARNING e two air conditioner lines between the n ght NOTE wing root db and the fuselage are high pressure I haccessible...

Page 544: ...e wrench adapter is used the length of the adapter b Coat the fitting bolt bores and bean ng faces must be added to the length of the torque wrench and the bolts washers and nutwith M1LC16173 Grade II...

Page 545: ...ING DRAIN HOLE NAS143 12 WASHER WET BOLT TORQUE 2480 TO 2600 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHERS WING nmNG BOLT BORES AND D POSED 80LT THREADS WT MILC16173 GRADE 2 CORROSION PREVENTIVE COMP...

Page 546: ...143 10 WASHER WET BOLT MROUEr 1180 TO 1300 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHERS WING FITTING BOLT BORES AND D POSED BOLT THREADS WT H MIL C 1G1M GRADE 2 CORROSION PREVENTIVE COMPOUND tCHECK...

Page 547: ...AGE FTTnNG T6WARDS WING FITTING WET BOLT TOROUE 2880 TO 3000 INCH POUNDS COAT THE COMPLETE BOLT NUT WASHER WING FTT IING BOLT BORES AND MPOSED THREADS WT MIL C 16173 GRADE 2 CORROSION PREVENTIVE COMPO...

Page 548: ...NG FITTING WET BOLT TORQUE 2480 TO 2600 INCH WUNDS COAT THE COMPLETE BOLT NUf WASHERS WING FITTING BOLT 80RES AND EXPOSED BOLT THREADS WTTH MIL C 16173 GRADE 2 CORROSION PREVENTIVE COMPOUND CHECK WASH...

Page 549: ...100012 SLIDE FUSELAGE F NG WING FTTnNG AN960D916L WASHER AS REQUIRED t 66100011 BUSHING MS20002C5 WASHER LWB22 5 22 BOLT TORQUE BOLT TO 100 140 INCH POUND 1 O ca o o 60 100011 BUSHINGS TO HAVE 00TO A...

Page 550: ...ts washers and nuts into the n Replace all damps securing the wire bundle and fittings engine controls to the leacEng edge d Loosen the nut at the leading edge attach point o Reinstall the lower aft n...

Page 551: ...ding Edge Attach Point Figure 2018 I g Rotate the bushings at the leading edge attach jack test fly the airplane point ontn they engage the attach fitting holes The scn be i If after adjustment a heav...

Page 552: ...the hinge and support the pin with hinge pins Remove the pins from the box section first then the longest tubes against the hinge then drive the pin the leading edge Remove the tubes as necessary unti...

Page 553: ...ng to its original position Stall Strip fnstallation Figure 203 CAUTION There should be no wing bolt binding during NOTE removal or installation of the bolts Do not screw or drive a bolt in or out of...

Page 554: ...f eight bolts and nuts have been hardware that has been given an additional inspected Only the attach bolts at the forward and aft spar magnetic particle inspection since manufacture exduding leading...

Page 555: ...At the first scheduled inspection after the wing deterioration however any component that is cracked bolts have been inspected or replaced check for proper bolt cxroded or has mechanical damage must...

Page 556: ...by improper operation magnetization on a central conductor fusually a copper rod of the test equipment can result in eventual the approximate site of the nut inside diameter For proper failure of the...

Page 557: ...mosphen e wing attach fitting to the outboard end of the conditions are highly conducive to conosion THIS ILLUSTRATION REPRESENTS A TYPICAL SECTION OF THE SPAR CAP AREAS TO BE INSPECTED FOR INDICATORS...

Page 558: ...eas a thorough inspection areas to determine if any damage has occurred must be performed to determine if corrosion has occured Wax or paint trapped between the edge of the skin and the exposed sectio...

Page 559: ...little increase of drag The panels plates and doors as shown in Figure 201 32 32 3 rl 3 If 15 1 26 62 2 26 1 27 27 4 4 33 28b l 28 33 o OI I I r0 O 34x 34 LEFT WING TOP 9 a 7 6 6 j 8 RIGHT WING fOP 17...

Page 560: ...ir Filter 24 Aileron Tab Actuator and Pulley 8 AileronBellCrank 25 WingTipAccess 9 Fuel Cell Transmitter 26 Fuel Cell Access 10 WingTipSparFittingand Heat 27 Fuel Filler Opening Valve Assembly 28 Land...

Page 561: ...y The major fittings in each wing are the supporting aluminum alloy fittings attached to the main and rear spar structures adjacent to the attachment points for the flap The support brace is attached...

Page 562: ...h up must be from the formula completed The tab tab push rod static wicks and hinge bolts must be attached The chord line must be horizontally M D R T inch pounds where level and the hinge line must b...

Page 563: ...unt the aileron on the knife edge supports Ascertain nose heavy and the paper cup was suspended from the that the aileron is free to rotate about the hinge line trailing edge Assume that the aileron b...

Page 564: ...FORCE MEASURMENT METHOD i A MASKING TAPE ITo SECURE TAB O iN NEUTRAL KN1FE ED G E Y PLACE NEAR A1LERON HINGE LINE STEEL TUBE WITH PIG MASKING TAPE LEAD I 11 JIG MUST BE HORIZONTALLY LEVEL DETAIL B VIE...

Page 565: ...CHAPTE R PROPELLERSI PROPU LSORS...

Page 566: ...oubleshooting Propeller Synchronizer 101 Troubleshooting Dual Speed Governor 102A Controlling Maintenance Practices 201 Propeller Governor Removal 201 Propeller Governor Installation 201 Propeller Gov...

Page 567: ...r Accumulator Removal 202B propeller Accumulator Installation 202B Synchronizer Functional Test 203 Synchronizer Checks 203 Synchronizer Wiring Check 203 Flight Checks 204 Syncfirophaser Test 204 Sync...

Page 568: ...61 CONTENTS 1 May 22 87 2 May 22 87 61 00 00 1 May 22 87 S1 lO OD 201 May 22 87 202 May 22 87 203 May 22 87 204 May 22 87 61 20 00 1 Nov 12 80 2 May 25 79 101 May 25 79 102 May 25 79 102A May 25 79 10...

Page 569: ...on TJ 46 propel 7ers Spring force and TJ 55 15 83 TJ 85 through TJ 443 except couterweights are used to move the T3 436 and TK 1 through TK 150 except propeller toward high pitch or feather TK 147 eq...

Page 570: ...loose from the shaft a Remove the spinner dome cap retaining screws and remove the spinner CAUTION dome cap Do not damage the threads on the b Remove the spinner dome retaining mounting studs screws...

Page 571: ...e dei eer T3 436 and TK 1 through TK 150 Iexcept e Remove the rubber bands and thin T3 83 13 85 through T3 443 except brushes TK 147 with PHC 33YF 22 FCC66630 propeller assemblies fill to 80 2 psi f I...

Page 572: ...ove the nuts and pull the CAUTION propeller forward removing it from the engine The attaching nuts may be reused f the break away torque is at i Remove the propeller deice slip least 18 inch pounds ri...

Page 573: ...any nicks or gouges into the leading edge with smooth curves and generous e Pushing hard on the spinner radii as shown in Figure 202 Reanodize install rour equa l y spaced screws and reworked area by...

Page 574: ...er will always speed up the slower engine to propeller rpm of each engine win automatically adjust to match the rpm and fin ng order of the faster engine Nonal the same rpm To change rpm adjust both p...

Page 575: ...T LIGHT MICRO SWITCH PEDESTAL SATTERY MICRO SOLENOID 5A SWITCH PRESSURE Ijljl SWITCHES PROPELLER GOVERNORS FUSE MICRO SWITCH SOLENOID MANIFOLD 58 W 3 73 RESET LIGHT OPTIONAL DUAL SPEED PROPELLER GOVER...

Page 576: ...s I 8 3 governor e Left governor coil gives a Broken or grounded wire e Repair or replace an open or short reading in coil Coil defective broken wire or replace on pins 6 8 7 govemor f Rightgovemorcoi...

Page 577: ...put See Woodward Governor Bulletin No 33117 3 Oil leaks from magnetic pi up a Defective O n ng between pick a Replace connection in governor body up and lock nut b Defective gasket under lock b Replac...

Page 578: ...itch out of govemor mounted micro adjustment switch c Defective manifold pres c Replace gage sure gage d Propeller govemor high d Adjust propeller rpm out of adjustment governor high rpm adjustment e...

Page 579: ...and replace defective part g Defective propeller g Replace tachometers tachometers 5 Governor reset fights a Wiring shorted out be a Isolate short and come on and stay on tween propeller governor rep...

Page 580: ...ust the high rpm screw inward to reduce the redline figure The high rpm adjustment screw is located at the front f Disconnect the oil line from the govemor of the governor see Figure 201 One complete...

Page 581: ...micro switch on the lower left side of the c Remove tags and install electn cal win ng govemor See 201 b Hook a volt ohm meter across the micro switch PROPELLER GOVERNOR MOUNTED MICRO leads SWITCH REM...

Page 582: ...AL SECONDARY HIGH RPM STOP 2700 RPM SECONDARY SOLENOID GOV ARM PRIMARY HIGH RPM ADJUSTING SCRRN 2600 RPM SECONDARY GOV ARM bO SPRING O MICROSWITCH FEATHER ROD PRIMARY GOV ARM 58 254 20 OrmONALDUAL SPE...

Page 583: ...r to the applicable the rod manufacture s FAA Approved Propeller Manuals PROPELLER ACCUMULATOR REMOVAL For airplanes which are equipped with the unfeathering accumulator PROPELLER CONTRoL LEVERS B 11I...

Page 584: ...cilloscope are required to RECEPTACLENUMBERS READING ondoct the tests below I and airplane ground 0 ohms SYNCHRON ZER WIRING CHECK 2 and airplane ground I open circuit a To eliminate the most obvious...

Page 585: ...lloscope should indicate 3 0 volts peak to peak The voltage should not read less than 2 0 peak to These checks will help locate the source of trouble should peak at minimum cruise rpm nor more than 10...

Page 586: ...52 68 ohms 6 and airplane ground open circuit AIR DOME Check the propeller air dome for correct 7 and airplane ground open circuit pressure 8 and airplane ground open circuit 4 and 8 112 138 ohms DEIC...

Page 587: ...CHAPTE R POVVE RP LANT...

Page 588: ...SECT ON SUBJECT SUBJECT PAGE GENERAL 71 00 00 Description and Operation 1 TrooMeshooting Engine 101 Maintenance Practices 201 Engine Removal 201 Engine BuiM Up 201 Engine Instanation 201 Ground Runnin...

Page 589: ...aximum continuous power horsepower each at 2700 rpm and 38 in Hg An optional dual speed govemor is available that reduces engine The TSIO 520 L and LB engines are rated at 310 performance to 301 horse...

Page 590: ...rect malfunction e Induction system e Tighten or replace loose leak or damaged hose connections 2 Failure of Engine to a Mixture levers set a Use FULL RICH mixture Idle Properly for lean mixture lever...

Page 591: ...ge c Improper fuel flow c Check strainers and flow at fuel injector d Restriction in air d Check passages and remove B intake passages restrictions e improperfuel e Drain and refill cells with recomme...

Page 592: ...osity f Prolonged ground f Limit ground operation operation to a minimum g Malfunctioning gage g Check wiring Check bulb or bulb unit unit Check gage Replace defective parts 7 Excessive Oil a Low grad...

Page 593: ...Defective fuel manifold b Replace fuel manifold valve valve c Defective relief valve c Tighten fuel injector pump operation in fuel injector control line from tu ocharger connections Replace control l...

Page 594: ...cowling inch pounds Refer to Chapter 71 10 00 c Remove the propeller Refer to Chapter 61 10 00 d Disconnect all plumbing at the firewall Be sure to NOTE cap ail open lines and fittings If the engine...

Page 595: ...idle valve screw should be loosened and the idle valve assembly NOTE pulled out slightly This will prevent bending of the linkage stud by providing clearance between An oil pressure indication of 70...

Page 596: ...FLAP ACTUATOR in this Chapter a Place cowIing in position Support lowercowl until installation is completed b Secure upper and lower cowi with screws at the RIGG NG THE COWL FLAPACTUATOR nose bug and...

Page 597: ...CHAPTER ENGINES...

Page 598: ...ITY CONTENTS 1 Apr 1 75 CHAPTER 72 ENGINE TABLE OF CONTENTS SUBSECT GENERAL FRONTSECTION POWER SECTION CYUNDERSECTION IZIRBOCHARGER SECTION LUBRICATION NOTE Refer to the Continental Engine Overhaul an...

Page 599: ...CHAPTER ENGINE FUEL AND CONTROL...

Page 600: ...ONTENTS 1 Oct 833 73 30 00 201 Oct 883 CHAPTER 73 ENGINE FUEL AND CONTROL TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE FUEL FLOW IND CATING 73 30 00 Maintenance Practices 201 Fuel flow Indic...

Page 601: ...ives a readout in gallons of fuel per hour The the mounting bracket and secure with the two clamps indicator has dual pointers one for each engine and is Safety wire the damps located in the upper RH...

Page 602: ...CHAPTE R IGNITION...

Page 603: ...201 Nov 30 78 74 20 00 201 Nov 30 78 CHAPTER 74 IGNITION TABLE OF CONTENTS CHAPIER SECTION SUBJECT SUBJECT PAGE GENERAL 74 00 00 Description and Operation 1 ELECTRICAL POWER SUPPLY 74 10 00 TrouMeshoo...

Page 604: ...ding a retarded ignition for engine starting regardless current to flow through the retard breaker of the left of engine speed The retard breaker is actuated by the same magneto while the right magnet...

Page 605: ...e to elec ically connected in the circuit due advance timing of ignition to poor connection Inspect retard points to see if they close Check for proper contact at the switch and retard terminals of th...

Page 606: ...MARKS 2 Engine roughness a Install new spark plugs b Check plug leads for continuity and breakdown c Check magneto breakers main and retard for burning or dirt 3 Magneto rpm check is out a Check magne...

Page 607: ...nal timing MAGNETO BREAKER PO KTADJUSTMENT f Connect positive lead of a timing light to the switch terminal capacitor stud of the magneto and secure the Magneto contact assemblies should be checked af...

Page 608: ...locations of clamps and clips to be certain that the replacement is clamped at the correct locations For engine In the event that an ignition hamess oran individual lead is to fin ng order and magnet...

Page 609: ...CHAPTER ENGINE INDICATING...

Page 610: ...ION SUBJECT PAGE DATE n EFFH nVTTYICO TEMS 1 Nov 30 78 TI OM O 201 Nov 30 78 CHAPTER 77 ENGINE INDICATING TABLE OF CONTENTS CHAP ER SECTION SUBJECT SUBJECT PAGE GENERAL 77 00 00 Mai enance Practices 2...

Page 611: ...8 91 00 00 The following procedure may be used to check and calibrate the TTT indicator a Remove the TIT probe from the turbocharger APPLY TORQUE APPLY TORQUE intake manifold on the RH engine Do not d...

Page 612: ...CHAPTER OIL...

Page 613: ...00 00 1 Apr1 75 201 Apr1 75 202 Apr 1 75 203 Apr 1 75 CHAPTER 79 OIL TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 79 00 00 Description and Operation 1 Maintenance Practices 201 Recom...

Page 614: ...ts change thereafter it is recommended that only Servicing the oil system is provided through access doors in ashless oil be used The oil in the engine the engine cowiing Due to the canted position of...

Page 615: ...ng the drain valve on with ice the bottom inboard side of the oil sump and by disconnecting the oil line at The bottom of the turbocharger OIL NLTER REMOVAL air oil separator to completely drain the s...

Page 616: ...l Oil W tin 4 grades Grade 120 Nominal SAE SO Military Grade 1120 Grade 100 Nominal SAE 50 Military Grade 7100 Grade 80 Nominal SAE 40 Military Grade 1080 Grade 65 Nominal SAE 20 or 30 Military Grade...

Page 617: ...ILS Cont d COMPANY BRAND Quaker State Quaker State AD Aviation Engine Oil Grades 20W30 40 and 50 Union Oil Company of California Union Engine Oil HD Grades 80 and 100 Designates ash residue type oils...

Page 618: ...CHAPTER STARTING...

Page 619: ...00 1 Jan 9 76 101 Apr 1 75 80 1 0 00 201 Apr 1 75 CHAPTER 80 STARTING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 80 00 00 Description and Operation 1 Troubleshooting 101 CRANKING 8...

Page 620: ...end of each engine When the ignition switch is placed in the START position IThe airplanes are equipped with 24 volt starters which current is supplied by the battery bus which energizes the engages...

Page 621: ...en circuit d Check connections and continuity between battery positive relay and left starter relay 2 One starterinoperative a Starter relay inoperative a Check relay terminal connections and continui...

Page 622: ...Start the engine to check for oil seepage at the Do not clean the starter in any degreasing tank mounting fiange and check for proper operation or grease dissolving solvents Avoid excessive lubricati...

Page 623: ...CHAPTE R TURBINES...

Page 624: ...Mar 23 79 CWPTER 81 TURBINES TABLE OF CONREnTTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 81 00 00 Description and Operation 1 System 1 control System 1 Ove ost Control 1 Engine Air Induction Syste...

Page 625: ...normal the wastegate actuator and engine oil are the prindpal controller should be checked by an authon ted components of the control system The pressure controller facility senses compressor outlet p...

Page 626: ...PRESS AIR SHCITOFF i TURBINE CONTROL I ENGINE e c TO CABIN OMPRESSOR 7 itF1REWALL I VARIABLE PRESSURIZATION ALTERNATE AIR OIL SEPARATOR PRESSURE VENTURI AIR DOOR CONTROLLER THROTTLE CONTROL c AND ARE...

Page 627: ...haul turbine station for overhaul or repair c Excessive dirt buildup in c Service engine induction air compressor filter and check for leakage Remove turbocharger and return to approved overhaul stati...

Page 628: ...actuator c Remove actuator and clean plugged jet d Actuator piston seal leaking d Clean cylinder and replace excessively piston seal a Wastegate poppet valve sticking e Clean and free action 4 Engine...

Page 629: ...TURBOCHARGER Cont d TROUBLE PROBABLE CAUSE REMARKS 5 High deck pressure d Wastegate actuator piston d Disassemble actuator check compressor discharge locked in closed position condition of piston and...

Page 630: ...peller after unit is 84 or 39 5 in Hg manifold pressure 5 153 rotating and TJ 169 and after TK 85 and after As soon as oil appears at the end of the oil inlet line attach d if at the full throttle pos...

Page 631: ...f Repeat steps b through e until the manifold Do not exceed 38 in Hg manifold pressure CTJ pressure at full throttte is 38 in Hg CTJ 2 thru TJ 168 TK l 2 thru TJ 168 TK 1 thru n 84 or 39 5 in Hg thru...

Page 632: ...CHAPTER CHARTS...

Page 633: ...ing Gear 201 Fuel System tta h ng Bolts For 202 Heater System 202 Chart 202 Torquing Fine Thread Series Bolts Loaded In Shear 203 Chart 203 Torquing Coarse Thread Series Bolts Loaded In Shear 204 Char...

Page 634: ...ay 22 87 91 CONTENTS 1 May 22 87 91 00 00 201 Mar 31 81 202 Mar 31 81 203 Apr 1 75 204205 r 1 75r 1 75 206 Oct 6 83 207 Jan 9 76 208 Oct 6 83 209 Aug 1 80 210 Nov 30 78 211 Mar 21 80 212 Mar 21 80 213...

Page 635: ...and 100 hours after each wing reinstallation replacing a wing bolt s or adjusting the wing If it is necessary to retorque the wing bolts at this time the bolts should then be checked at the next 100 h...

Page 636: ...ecks 45 to 55 in Ibs Leading Edge Fuel Cell Outlet Plate 20 to 30 in Ibs Transmitter 5in Ibs Fuel Boost Pump to 55 in ibs Ac ess Plates to 55 in Ibs Fuel Cell Interconned Clamps 25 5in Ibs Rubber Fuel...

Page 637: ...LUMN 2 COLUMN 3 COLUMN 4 8 36 12 15 79 20 12 7032 70 25 12 15 40 25 1 4 28 50 70 30 40 100 60 5 16 24 700 140 60 85 225 140 318 24 7 60 7 90 95 1 73 390 240 7 16 20 450 500 270 300 840 500 1 2 20 480...

Page 638: ...12 7Q24 20 25 12 15 35 21 fN 2O 40 50 2530 75 45 5 16 18 80 90 4 55 160 100 3 8 16 160 185 95 170 275 170 7116 14 235 255 740 155 475 280 1 2 13 400 480 240 290 880 520 76 12 500 700 300 420 1100 650...

Page 639: ...16 90 100 70 100 1 4 40 65 135 150 70 120 5 16 60 80 180 200 85 180 3 8 75 125 270 300 100 250 112 150 250 450 500 210 420 5 8 200 350 650 700 300 480 3 4 300 500 900 1000 500 850 1 500 700 1200 1400...

Page 640: ...e optional wet wing tip on TJ 23 and after and TK I and after ITEM PRODUCT VENDOR 1 EC612 Minnesota Mining and Manufactun ng Co St Paul Minnesota 2 EC776 Minnesota Mining and Manufactun ng Co St Paul...

Page 641: ...thick Sealant is to be faired 5012398 1 2 into the joint or seam and is to over Pro Seal 8908 1 2 or lap adjoining structures 1 8 to 1 4 EC7675B 1 2 inch Coating Seal EC776 or 601 239 A 1 2 Apply sea...

Page 642: ...s are assembled EC1239B112 Pro Seal 8908 1 12 M EC1675B 1 2 W ndow Seal Pro Seal 890 4 Apply with a bead of approximately 3 16 inch in height or sufficient sealant to fill around fas teners and to eac...

Page 643: ...n al is applied between mating surfaces of two or more parts before assembly Paying Surface Pillet Seal refers to a seal where the sealant is applied on top of a faying surface seal at one of two edge...

Page 644: ...ade 40 Castrolaero AD Castrol Limited Grade 50 Castrolaero AD Australia Conoco Aero S Continental Oil Co Ponca City Okla Gulfpride Aviation AD Gun Oil Co Pittsburgh Pa Esso and Enco Aviation Humble Oi...

Page 645: ...il and Gas Co Bedford Ohio Kendex No 7038 Kendall Refining Co Bradford Pa 4 Lubricating Oil MiL L 6081 Gulflite Turboiet Oil No 1010 Gulf Oil Corp Pittsburgh Pa Aeroshell No 3 1286 Shell Oil Co 50 Wes...

Page 646: ...L G 23827 Supermill Grease No A72832 Amen can Oil Co Grease Aircraft 910 South Michigan Ave and Instrument Chicago ill High and Low Temperature Royco 27A Royal Lubn cants Co River Road P O Box 95 Hano...

Page 647: ...NJ Freon 12 Dupont Inc Freon Products Div Wilmington DE 18 011 Air Condi 500 Viscosity Suniso No 5 Virginia Chemical tioner Sme ti ng Co West Compressor Norfolk VA Texaco Capella E Texaco Inc 135 East...

Page 648: ...Pike Dresher Pa 32 Adhesive EC1300L Minnesota Mining and Manufactun ng Co 3M Center St Paul Minnesota 33 Sealer EC801 Minnesota Mining and Manufacturing Co 3M Center St Paul Minnesota 34 Lubricating...

Page 649: ...7 Bray Oil Co Preventative 1925 N Marianna Ave Compound Los Angeles California 90032 44 Cement Postic 1008 United Shoe Machinery Corp B B Division 748 Memon al Drive Cambilc e Mass 45 Cement Bostic 10...

Page 650: ...rd 10046 Ranco Laboratories Inc 3617 Brownsville Road Pittsburgh Pennsylvania 55 Grease MIL G 1 0924 56 PreseFmti tdIL H 6083 AMex 904 Mobil Oil Corporation 150 fydraulic nuid E 42nd St New York New Y...

Page 651: ...Minnesota 65 Ple ciglas Micro Mesh Cushioned Remover Abrasives Micro Surface Anishing Products Wilton iowa 52778 Polysand Cushioned Abrasives Fledn ck B Anthon Entelprizes U S Distributor Cope Plastic...

Page 652: ...643 Shell International Petroleum Company Limited Shell Centre Dept MKF 32 London S E 1 England g9 Coating MIL C 5541 Alodine 1200 Amchem Products Inc 1200S or 1201 300 Brookside Ave Ambler PA 19002 A...

Page 653: ...fold Pressure Air Lubricating Crease Gasoline MIL G 6032 L 237 Lehigh Chemical Co Pressure and Oil Resistant Chestertown Maryland Roc cwell 950 Rod well Mfg Pittsburgh Pa Royco 32 Royal Lubricants Co...

Page 654: ...Co on Type A Bartlesville Okla Aeroshen Oil W Grades Shell Oil Co One Shell 120 100 80 and 65 Plata Houston Texas Pennton Aircraft Engine Pennzoil Company Oil Heavy Dispersant Grades 30 40 50 d Mobn A...

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