BEECH TURBO-BARON 56TC AND A56TC SHOP MANUAL

15 OVERHAUL E REPLACE SCHEDULE 16 PERIODIC INSPECTIONS 50 HOUR INSPECTION 100 HOUR INSPECTION 4 t3 ALPHABETICAL INDEX ALPHABETICAL INDEX A B Access Openings Balancing Control Surfaces Fuselage 3-6, illus. 3-7 Aileron .4-12A, illus. 4-13 Wing 3-8, illus. 3-9 Elevator 4-14, iUus. 4-15 Accumulator Removal, Propeller 7-3, illus. 7-3 Rudder 4-16, illus. 4-17 Actuator Battery, Nickel-Cadmium .13-1, illus. 13-3, 134 i\ileron Tab 4-1,i11us. 43 Servicing Elevator Tab 4-68.illus.4-6D Beechcraft ~ew:Matic i\utbpilot j,;~ mt. e7,s Flap 4-29, 1-30 Landing Gear 5-17, illus.5-1S Beechcraft Supplementary Publications 1-10 Rudder Tab 4-10, illus. 4-10A Belt Tension Aft Window Compressor, Air Conditioner 10-9 Installation 3-17 Belt Removal and Installation 10-11 Removal 3.17 Generator 13-9 Aileron Bleeding the Brakes 5-l,illus. 5-3 Balancing .4-12-4, iUus. 4-13 Blower Installation ´•CI Combustion Air 103 Removal .4-1 Condenser 10-9 Rigging Vent Air 104 Tab Actuator Assembly Boost Pump, Fuel (Eiectric) 8-28 Tab AcruatorDisassembly 43B. illus.i~-l Brake System TabRigging.. Bleeding Ar Conditioner System 10-5, iilus. 106, 10-8, 10-10 Installing Wheel and Brake .3.3 Compressor Belt R~moval and ~laster Cylinder installation IO-ll Linkage Adjustment .j.t Compressor Removal and Installation 10-10 Overhaul Condenser Blower Removal 10-9 Removal andlns;alla;ion Ri~ing the Ar Scoop and Ramp 10-9 Parking Brake Servicing Adjustment .3.1 the Frean System 107 Valve Overhaul Checking Compressor Oil Removing Wheel and Brake S-~X Level 1Q´•8, illus. 10-S Servicing Compressor Belt Tension 10-9 Wear Limits .5-1 Evaporator Air Filter Replacement 10-10 Breaker Point Adjustment, Ma~ne;o 6SB SpecialPrecautions 10-7 Brush Replacement System Operation 10-5 Electric ~Liotors .13 Troubleshooting 10-13 Generator 13-9 Aircraft Dimensions .1-’ ProDeller Deicer 11-9, illus. 11-9, 11-17- Aircraft Finishes 12-1 Box Section Fuel Cell Installation and Air Induction System, En~ne d?A Removal 5-6, illus. 8-6 illCal Calibration Unit .6-8 Bulb Replacement Guide Ij-1OA Alternator 13-5 Installation 13-6 Overhaul 13-6A C Removal 13-6 Aluminum Painting 17--1 Anchoring and Slooring Cabin Door Approved Oh Grades Adjustment 3-14 Approved Turbocharger Overhaul Facilities .6-7 Removal and Installation 3-14, illus. 3-14 Autopilot, Window 3-16 Beechcraft New-1Matic 4-27, illus. 4-28, 4-29,4-30 Cabin Heater 10-1 H-14 4~7, illus. 4-23, 4-24,1-25,4-26 Calibration Unit, t;Cal .6-8 Troubleshooting Guide 4-31 Capacity Check, Battery 13-3 Cell B Battery Equalizing 13´•7, Back Adjustment, Seat 3-;21 Replacement 134 84 ALPHABETICAL INDEX C D Cell (Continued) Deicer System Surface (Continued) Fuel Stall Strip installation 11´•8, illus. 11´•8 Box Section 8-6, illus. 86 System Checkout 11-3 Leading Edge 8-6, illus. 8-6 Troubleshooting 11-8A Nacelle 8.5, iUus. 8.5 Diagrams Outboard Leadin’g E;lg’ 8-6A, illus. S-6A Lubrication 3--13 Repairing .8-7 Stations .3-1 Center Seat Wiring 14-1 installation 3-12J Dimensions of Aircraft .1-3, Removal 3-12J Door, Cabin Center Window Adjustment 3-14 Installadon 3-1$ Znstallation and Removal 3-14, m~s. 3-14 Removal 3-17 Window 3-16 Charging, Battery 13-3 Drop-off Check, Magneto 6-2B Cleaning Dynamic Brake Relay Removaland Battery 13-1 Installation 5.19 Care of Airc;aft’Fini’sh .2-6 Deicer Boots 11-7 Plastic Windows .3,6 E Static System 11-19 Waxing the ~ircraft’Finish 126 Electrical System Combustion Air Blower, Heater 10~ Alternator 13-5 Compressor, Air Conditioner Installation 136 Belt Removaland Installation 10-11 Overhaul 13-6A Removal and installation 10-10 Overvoltage Relay; Ahju;unknt .13-5, 13-6 Consumable Materials Chart 2-10 Removal 13-6 Con~rolColumn illus. ~-7,, C24 Voltage Regulator Adju;lment 13J Control Column Arm Removal and Installation .4-1 Bulb Replacement Guide 13-!0A Control Column, Single .4-1 Elevator Trim Tab Control Column Chain, Riggin 4-l,illus. 4-2, LtZA Actuator Removal. ......4-68 Control System, Turbocharger Actuator Installation .....4-68 Controller, Turbocharger, Electric Trim Tab 4-60, illus. 4-60 Variable Pressure .6-6A illus. 6-5 Actuator R~moval 4-60 Correspondence 1-1 Cable installation 4-60 Cowl Flap Actuator .6-1 Magnetic Clutch Installation 4-60 Cowling, Removal and Installation .6-1 Magnetic Clutch Removal 4-60 Current Adjustment, Generator 13-8 Magnetic Clutch Torque Test Cylinder Electrical Equipment Location Brake Master Electrical Load Chart 13-13, Linkage Adjustment .S-1 Generator 136A Removal and Installation .54 Brush Replacement 13-9 Overhaul 5-4, illus. 5-4 Current Adjustment 13-8 Oxygen 11-1 Installation 13-9 Overhaul 13-9 D Overvoltage Relay 136A Dampener, Shimmy Parallehng Checks 13-8 Assembly 5-17, illus. 5-16 Removal 13-8 Overhaul .j-14A,illus.5-16 Stabilization of System lj=I Defueling .8-1 Voltage Adjustment 13-7 Decier System Voltage Regulator Adjustment Propeller 11-9,i1lus. 11-9, 11-12 and Generator Paralleling 13-7 Surface 11-3, illus. 114, 11-5 MckelCadmium Component ~aiXrenHnce 11-6 Battery .Ij-l,illus. 13-3, 133 Deicer Boot Removal& Installation 11-7 Capacity Check 13.3 Description 11-3 Cell Replacement 133 Operation Check 116 Charging 13-3 Resurfacing Deicet Boots 11-7 Cleaning 13-2 84 ALPHABETICAL INDEX E F Electrical System BatteN (Continue~ Filter Electrolyte Adjustment lj,l Autopilot "12 Equalizin,o Cells CentralInstrument 11-’3 Starter Deicer ll-j installation 13-9 Evawra~or 10-10 Maintenance 13-9 Hea;er Fuel 10-i Overhaul 13-9 Induction r~ir .Zb Removal lj-g Oil .25 Strobe Li~ht System .13-10B Finishes. 1~-1 Bullock 13-100 Fitring, Installation of Fuel Converter Tro;bikshooting lj-11 flared 84, iUus. 8-F Trigger Circuit Troubleshooting 13-11 naps Trouble Analysis 13-100 Actuator Overhaul 4-21,illus. ´•r-31 Troubleshooting Power Unit 13-10D indicator Adjusrmenr Hoskins .13-10B Installation 4-18 Power Cable Checks .13-10B 4lotor Gearbox Overhaul :4-;8r~iU;s. 4-70 Power Unit Removal and installation .Ij-IOB ~loror, installation and ~emoval 4-18 Troubleshooting Power Supply .ij.lOB Removal 4-18, iUus. 4-19 Troubleshooting Rigging ;Uternator 13-16 Track Rollers, Installation Battery 13-16 Ri´•Jrt Controls and Surfaces .4.1 Generator 13-18 Forward Left Hand Window Landing Lights 13-19 Installation i-!6 Lights 13-19 Removal j.tj Stall Warning Circuit’ Freon System, 10-7 Starter Front Seat Eiectrolyrz Xdjusrmenc, Barterv 13-1 Insralladon 3-12J 3leMcor R~moMi 3-12J Balancing Fuel Pump. Heater kemovai ad Down´•Soring Loads’ ´•L-ia Insralladon 10-i Insrallaton .?-6 Fuel 8-1, mt~. s? Removal .4-1 Adjustment of Tran;mi;ter~ Ri~ng Boost PumD, Recrric S-2B Elevator Skin Replacement Box Section Cell 8-6, lilus. S-j Elevator Tab Actuator iilus. siSc= Deiueling .8-1 Tab Actuator ~ssembiy Engine-Driven Pump Tab AcruatorDisassembly iilus. 1-6C Pressure Adjustment .8-1 Tab Rigging ´•66A. iilus. Removaland installation .8-1 Emoznna~e iiIus. 4-11 Fare Fitting Toraue Chart .8.i Emoennag and Fuselage S~cin Fuel Seiecror valves Flaring Control Cable RemoM1 Engine .6-1 Control Cable Ri~jng 8-i, illus. 8.7_ En~ineTroubleshoorink 6-I0 Removal and InstslIation .S-j Ea;ipmenr; Location, Electrical IIIus. 13-10 Installation of Flared Exterior F~nish !3-1 Firrings S~, illus. 54 External Power .3-3 ~Rsding Edge Cell 8-6, lilus. 8´•~ ~iacelle Fuel Cell 8-5. illus. 8-i F Ourboard Lsdin~ S-6A,lus. j´•6A Quantity Cage Resistance Readinos 8-7,8 Feathering Adjustment, Propeller .7-3 Repairing Fuel Cells .8-7 Fiberglass Component Repair 3-iT Schenatic 8-3, 9.7_~ Fifth and Sixth Seat Servicin,o .’I~ Installation 3-13 Testing Cells for Leaks 8-6;\ Removal 3-~u Testing Quantity 8-3B Stowaoe 3-13 Fuselage Access Openings 84 iii ALPHABETICAL INDEX F H Fuselage and Empennage Skin Heater System CContinued) Plating 3-’, illus. 3-3 Heater Fuel Noule 10-5 Fuselage (Wing Carry-Through Hearer Fuel Pump 10-5 ignition Unit Structure Inspection 3-12J, illus. 3-12N Vent Air Blower 10-F Pigging the Heater Controls 10-1 G Troubleshooting 10´•13, Gear Hoisting 3-1, iUus. 7-3 Main Landing 5-10, illus.Elr Nose Landing 5-13, ilius. 5-14 Gearbox, Flap Motor Overhaul 4-18A, illus. 4-20 General Information .1-3 Generator 13-6A Idle Speed and Brush Replacement 13-9 ,Uixrure Adjustment Current Adjustment 13-8 Ignitor, Heater Vibrator, 103 Installation 13-9 Ignitor Points, Heater 10.i Overhaul ;3-9 Ignition Unit. Hearer Removal and Paralleling Checks 13-8 Installation 10-i Removal 13-8 Indicator Calibration. TIT .6-i Stabilization of Svs;em’ 13-7 Indicator, Flap Position 5-IS, illus. C19 Voltage Xdjusrme~nt 13-7 Induction Air Filter, Servicing .7-5 Governor, Propeller induction Air System, Engine 6.7_X Adiustment 7-i, iUus. 7-1 Information, General .1-3 Removal and installation .I-i Insoefdon. Periodic 16-1 Grades,.L~pproved Oil .2-i Installation and Initial,Pun-~n: Gtaoh, Turjcs~arger Periormance Turboc~ar´•-er 6-M CroLnd Handling LigXring .1´•8 Xnchorine and ,Moorino .?-1 Interior Colors 126 External ~ower .2.3 Hoisting 2.IlillUS~ 2,7 lacking .2-1 J Lzveiing .2-i Tar~ing Brak; .1-1 Towino .1-1 Jac~dng Ground R~nning and Wsrm-uD .6-1 Guide, Bulb Replacement 13-IOA H-14 Autopilot 4-’,2. iUus. 4-’3,4-7,4, 4´•25,4-26 Landing Gear System ~iainrenanct and Repair 1-?2 Actuator Rigging Overhaul 5-17, illus. ~-18 Handling, Ground .2-1 Removal and installation Heater Svsrem I0-l,iflus. 10-3, Dvnamic Brake Relay Removal and Elgct;ical System 10-I installation.... ´•...´•5-19 Cleaning Spark Plug 10-3 Main Gear ignitor Points 10-3 ~ssemblv 5-13. illus. 5-11 Overheat Thermostat 10-1 Disassembly Replacing ignition Vibrator IO-j Inspec~ion 5-10A Spark Plug Gap 10-3 Lubrication and Reolac,omenr Fuel Filter 10-i of ~pIock Roiie:s 5-13 Fuel P~mcs 105 Pemoval and i´•10 Pressure ’l’est Tolerances 13 ’:m3vi.rr.j. :~stall;rion or Moror R~noMI and Insrailatlon j-19 2: ´•n HC3trT 105 ~iose Gear :´•;-r.ns :;ir Blower 10j Assembly iv Rr; ALPHABETICAL INDEX L O Landing Gear Nose (Continued) Oil Disassembiy AoDroved Grades .1--3 Inspection 5-13 Fii;er. Servicing ~7.5 Removal and Installation j,Ij Level, Air Conditioner Shimmy Dampener Assembly Compressor 10-8,i1lus 10-8 Shimmy Dampener Overhaul j-I4X. illi?s. 5-16 Pressure Adjustment, en~ne 6-~4,illus.6-1,A Shimmy Dampener Repair 5-I7 System Servicing .3_3 Tolerances 5-!3 Openings, Access Nose Wheel Steering Fuselage 36, ilIus. 3-7 Mechanism 5-19,iu~.S-7,0 Wing Travel Stop Adjustment ,-19 Ourboard Leading Ed~e Rigging 5-7, illus. j´•9 Fuel Cell 8dX,illus.SdA Safety System .~o Overhaul and Replacement Schedule IS-1 Micro Switch Adjustment .j,j Overvoltage Relay Adjustment 13dA Pressure Switch Adjustment .5a Oxygen System Safety Switch Check .Sd Cviinder Replacement 11-1 System Mainrenance an~ Adjudmenr L~ak Test ii-1 Troubleshoo tino, Purging 11-1 Warning Horn Switch .6.i Servicing .’,-6 Wheel And Tire ~laintenrtnce i-7,0 Leading Edge Fuel Cell Installation and Removal .5-6. 86A. illus. 8~j. 3´•-6A P Leveling Limits, Brake Wear .~-I Load Chart. aec:rical !3-13 Paint, FDoxy ~2´•2 Low RPM Ildiunmenr, Prdoelle: PainE, ~ethane 17-3 Lubrication Chart ~-ra Painting ~iluminum Lubrication Dia~am "´•ij Aodication !2-1 Surface Preparation 12´•1 M Painting Ma~ksium ~odicasion !3_.5 Sla~nesiun, Painting ll-j Paint Removal 12-5 Sun’ace Preparation 12J Breaker Point Adjustment 6-’18 P~ailelino Drop-off Check 6-1B Checks 13-8 ~-IB. mus. 6-3B Pzridn,o Brake Yam Lu~dinl i?r’ AdSuiunenr Maintenance and Repair, H-14 ;1´•-~2 Valve Overhaul ;Ciastet Cylinder, Bralce Pariornanc´• Graoh Turbochar´•e; .6-9 Linkage Adjustment Periodic Lnsoection 16-1 Overhaul 5J, iilus. j-~ Pitot and Static System .11-19, illus. 11.3_0 Removal and Installation Cleaning the Static System 11-19 Slarerials Chart, Consumable 2-10 inspecting Pirot Hose 11-19 ~rleasuring Rudder Travel in Inches :~-8, nlus. c10 InsDecting the Stade System 11-19 Mixture and idle Speed Adjustment 6-3X, illus. 6-7,X Leak Testing the Pitot System 11-19 Mooring and Anchoring .3´•! Stall Warning System Motor, Landing Gear Adjustment .Il-7-l,illus. 11-11 Removal and Installation 5-19 Troubleshooting 11-31 Points, Sla~neto Breaker 6-3,8 N Power Plant Air Induction System 6-’X ~acelle Fuel Cell installation Cowl Flap Actuator .6-1 and Removal 8-i, iilus. S-5 Cowling kzmoval ~iose Steerino ~echanism 5-19,illus.j-t0 Ground Running and w,~,, .6-1 Nose Wheel Travel Stop Adjustment 5-19 Idle Speed and Mixture 6-2A,illus.6-7-A Nozzle, Heater Fuel 10-6 InstaUBtion .6-1 84 ALPHABETICAL INDEX Power Plant (Continued) ~2Dair, Fuel 01l i~djusrmenr Rebair Minor Prooeller Blade 7.5, illus. 7-3 Ihronle L.G. warning Horn .~-I Reolacsaenr and i~vemaul Schedule lj-1 .6.i Deicer Boots 11-7 Pressure, Fuel Xdjusrment (EnginePU;n~ .8-1 Ri,o~ing Pressure System, AutoDilot 11-7,5 ~liieron 4-1, iilus. 4-i I1-?5 ~ileron ~ab 4-28, illus. 43 Plus Deicer II-27 ~ir Scoop and rlir Ramo 10-9 Plus Deiesr and Amdpilot Ii-7-7 Elevator 11-30 DeMtorTab .4´•8A, illus. 4-5 Plus Deicer and H-14 11-34 RaDs 3-18, illus. 4-19 Plus 11-14 Autopaot 11-37 Fuel Selector Valve .8-3, illus. 8-5, 83 Turn and Slio X~justable Oriiice I1-jg Ei-14 ~t33 Heater 1M Heater Conrrois 10-1 ~ccumuiaror Landing Gear Rudder LF-7, illus. 3~, 3-9 Removal Rudder Tab .3-8 Servicing 2-7 Tnrorde and Pressure Controller Air Dome Pressure, Servicing iUUS. 7_.8 Rollers, ~iolock Lubrication and Blade Bearing Lubrication 7.8, iUUS. 2-8 5-13, nectric Deicer 11-9, ~us. 11-9, 11-I?, Roton Locks, Servicing 2;7, iilus. 7´•7 Boot kwalIation ´•11-13, ~us. 11-i3, 11-14 Rudder ~o": .Il-lj,ilIus. 11-13, 11-14 Balancing cr-16, iUus. L~-1? las~allarion .I; Brush R;Dlacsmanr .4-7 11-11 Rig~ing I1-11 Tab Acmator Xssembty Rzsisranc- Cheek T1-lj .j Slip Ring.Macirining ll-10A Tab’Ri~ging Timer Check 11-I1 TravelinInches..... Troubleshooting .7-7- Governor ~djusting 7-1, iilus. 7-1 S Removal and installation .I-I Low RPM Xdjustmenr 7-~, illus. 7,3_ 1Minor Blade Repair Sar^try Synem, Gear .,o Maintenance and Xdjustmenr .~9 1-10 ~icro Switch Adjus~ment Vendor .1-a Pressure Switch Xdjusunent ~56 PumD Hkater Fuel Switch Check .ja Fuel (EnCe-Drivenj LO-j Schedule, Overiaui and Rznlac~menr’ 15-1 .8-1 Schematic, Fuel System 8-7,, Q-7A Vacuum Purging Oxygen System 11-3~ Sealing Chzr~ 11-1 Seats Back .3-13 Center Installation .3-13 Removal and Sixth .3-13 Readings, Fuel Quantity Resistance 8-1B Installarion .3-13 Re~ularor Adjustmene, Voltage Rr7moM1 .3-13 Ij.j 3-13 Relay, Landing Gtar Dynamic’Brake 13-7 Front 5-!9 Installation .3-13 Repair, Exterior Paint Touch-uD 12-1 Removal..... .3-13 85 ALPHABETICAL INDEX Servicing Battery Surhcco Deic-r System, Servicin´• .--o ´•7_-5 Surfaces, Connol .3-1 Brakes .7, Switch, Throttle Lpdin~ da; Warning Horn 8129 Charr Cleaning and’Care oT ~C Finish 2-10, System Cleaning Plas~ic Windows ~ir Conditioning !0-5, mus. 10-6, 10-8, 10-10 .2-6 BraLe 5-1, iUus. 5-7, Fuel Svsrem Induchon Air Filter’ .3l necmul lj-1 .7,-5 Fuel instrument Wedge Lighting .3_.5 Heatin,o .10-i, illus, 10-7,, 10-i Cil System .73 induction ;lit 6-2A Oxygen System .1-5 Landing Czar ~--5, illus. 5’-3 Preaurions, ~lir Ccnditioner !O-T Oxy~en ~ccumularoi 2´•a, illur.?-8 ALor and SLa~ic .1I-L9,lur. 11´•20 .3,-7 Deicer 11-9, ~lus. 11-9, 11-17, Roron Locks Stai~ P~nrino .11-31, ilius. 1!-7,1 7-7 Sudacl Deicrr Sur;Bc´• Deicsr System ´•2-3 Turboc~arger 64, ~us. 6-5 .7,6 Vacuum .11,7_3liilus, 11-7,3 Tires .7_.3 Snimmy Dampener .-\Jsembly 5-17,ii1us. 5-!6 Overhaul .5-i4A, illus, i-!6 T Servicing .2-1 Shock S’crut, Servicing Skin Pl.ating Tab Fuselage and Empennao´• j-2, iilus. =-j ~cruaEor, nevzror Wing 36, mcs. 3-5 Trim ~0, iilus. ~cru2rar RsmoMI cao En~ine Cable installation ~O Heater .1J 4la~Iletic autctr Insr~arion ~j0 10-i ~Masletic Clusci Removal ~to^O Soe~ai Tools .1-, iM~eric Clutch Toroue SrlnS ~ads, Elevator Stabiiiurion of Gnerlcor System’ ~aa ~ileron 13-7 Elevator 3-6, liluS. eL-~ StabBze: Insrallation, Horizontal ~udder 47, iilus, 49 3-_17, Table of Thread Lubricants .2-9 Insralladan, Vertical "-I? Table oiforques 1?, illus. 1-3 Removal, Horizontal 4-i3 Test, Turbocha~ner Critical .6-8 Removal, Vertical ".17_ Testing Fuel Cells rbr L=aks 81jA Stall StriD installation ii-a, iUus. 1!-8 Tnermostat, Overhear !0-1 Adjunmzne .Il-2l,iilus. 11-7I Thread Lubricants, Table 13-9 Tnrottle Landing Gear Warning Horn’ 6-3,B 6-2B, illus. 6-38 13-9 Timing, 13-9 Tip, Wing R~emoMi and installation j,!O Overhaul lj,g Tires Removal :3-9 Szrvicing Static and Pitot System .11-19, illus. 11-20 Wheel Maintenance 5-7,0 Stations Diagram ilIus. i-1 ?TT Indicator Calibration .6-7 Steering, Nose Wheel 5-19, illus. 5-7-0 Tolerances Ston Window RemoML 2nd Installation’ ~iain lan~ing Gear 5-17, Stowage, Fifth and Sixb Seat i-!3 Nose Landing Ge~ 5-13 Strobe Li´•Jlr ´•Ij-!OB Tools, Soec;,al .1´•7 Suction Relief Valve Xdjustment Torque Charr, Flared Suoolementary Publications B~echcraft I~orque Wrenches .l.j 1-10 Torquing Bolts in Snear .1-6 Vendor .1-8 ~Tauch-up, Exterior Paint 12-1 84 ALPHABETICAL 1NDEX Towing .2-I Voltage Regulator Adjustment Transmitter, Fuel Quantity With Alternators 13-5 Adjustment .8-3 With Generators 13-7 Testing 8-2B Troubleshooting Air Conditioner 10-13 Alternator 13-16 W Battery 13-16 Warm-up, Engine .6-1 Engine 6-10 Warning Horn, Landing Gear Throttle .6-3 Generator 13-18 Waste Gate Butterfly Lubrication .6-7 Heater Waste Gate Valve Adjustment, Landing Gea; .10-12 5-21 Turbocharger 6-6C, illus. 6-6C Landing Lights 13-19 Waxing and Cleaning the Airc;aft 126 Lights 13-19 Wear Limits, Brake .5-1 Pitot andsta;ic Sys;em .11-22 Wedge Lights, Insuument .2-8 Propeller Deicer 11-15 Wheel and Brake Stall Warning Circuit 13-19 Installation .5-3 Starter Removal 5-2A Surface Deicar 13-17 Il-gX Wheel and Tire 6later;anEe 5-70 Turbocharger 6-12 Windows Turbocharger Aft Control System .6-´•1 Installation 3-17 Critical;Utitude Test .6-8 Removal 3-17 Installation and Initial Run-in 6-6X Cabin I~oor Lubrication of Turbocharger Shafts 6-6i\ Installation 3-16 Lubrication, Waste Gate Butterfly .6-7 Removal 3-16 Overhaul Facilides .6-7 Center Performance Graph .6-9 Installation 3-17 Rigging Throttle and Pressure Conrr~ollet 66A Removal 3-17 Schematic illus. 6-5 Cleaning Plastic .26 Troubleshooting 6-12 Forward Left Hand Variable Pressure Controlle; 66X, illus. 6-5 Installation .........3-16 Waste Gate Valve Adjustment 6-6C, ilIus. 6-6C Removal 3-15 Storm Installation .........3-15 Removal 3-15 V Windshield Installation....... 3-15,illus. 3-13 Removal 3-13, illus. 3-1>’ Vacuum System Wing Suction Relie~ Adjustment’ 11-23 Access illus. 3-9 Suction ReiiefAdjustment,Au;opilot’ 1~-3,3 Vacuum Pump Removal Installation 11-23 Bolt, Nut and Fitting Inspection.........................,.,.,.3-1 2F Valve Magnetic Particle Inspection ...............................3-1 2H Fuel Selector .8-3, illus. 8-3, 8-4 Outboard Wing Spar Cap Suction Relief Variable Pressure Cont;oller, 11-23 Visual rnspection.............................~3-1 21, illus. 3-6G Installation .........................3-1 1, illus. 3-6, 3-6A thru 3-6E Turbocharger 6-6A, illus. 6-5 Removal O Vendor Publications .1-8 Skin illus. 3-5 Vent Air Blower, Cabin 104 Tip O Vertical Stabilizer Tip O Installation 4-12 Wing, Forward Spar Cany-ThroughRemoval 4-12 Structure Inspection 3-12K, illus 3-12N Vibrator, Replacing Heater Ignitor 10-3 Wiring Voltage Adjustment, Generator 13-7 Wrenches, viii B5 THE TURBO-BARON SHOP MAN~AL NOTICE Beech Aircraft Corporation expressly reserves the right to supersede, cancel andlor declare obsolete any part, part number, kit or publication that may be referenced in this manual without prior notice. The Model 56 TC Shop Manual presents the factory recomrfiended procedures for maintaining the Turbo-Baron in an easy to follow, easy to locate manner. Information in the Shop Manual is directed toward helping the experienced mechanic with specialized and more complex maintenance while simple and repetitive procedures are given less emphasis. When necessary, an illu’stration supplements the test for further clarification. The Shop Manual is divided into sixteen sections, with each section devoted to a specific system or major component. All the pertinent information will be found in one place. To quickly locate the information needed, an Alphabetical Index provides multiple entries for each subject. Troubleshooting guides may be found at the close of each major systems’ discussion. Serial effectivity is maintained throughout the manual to assure correct information for each airplane. MODEL j6TC TG-I through TG-83 MODEL Aj6TC TG-84 and after NOTICE WHEN A PROCEDURE APPLIES TO ONLY A CERTAIN SERIES OF THE AIRCRAFT MODEL, THE AIRCRAFT SERIAL EFFECTIVITY WILL BE DESIGNATED. PROCEDURES WITHOUT SERIAL EFFECTIVITY WILL APPLY TO ALL MODELS. NOTE This manual covets data on systems which are standard or standard options as of the publication of this manual, however, not ail standard options may be designatep as such. CORRESPONDENCE If a question should arise concerning the care of your airplane, it is important to include the airplane serial number in any correspondence. The serial number appears on the designation placard. On early serial airplanes, the model designation placard is attached to the bottom of the fuselage immediately forward of the tie down lug. On later serial airplanes, the placard is attached to the lower right hand side of the fuselage adjacent to the flap. 82 1-1 I------------ 15. 94’ _1 1 _ I 0 r! -~7 37, 82’ 6" DMEDRL~L, 1-----~1-----1 74" I)tA I ~3u c~ U 19. 221 I I IiO" i Fi~ure 1-1, L)imensions of Aircraft: r-2 WARNING Use only genuine BEECHCRAFT or BEECHCRAFT approved parts obtained from BEECHCRAF~ approved sources, in connection with the maintenance and repair of Beech airplanes. Genuine BEECHCRAFT parts are produced and inspected under rigorous procedures to insure airworthiness and suitability for use in Beech airplane applications. Pans purchased from sources other than BEECHCRAF~, even though outwardly identical in appearance, may not have had the required tests and inspection performed, may be different in fabrication techniques and materials, and may be dangerous when installed in an airplane. Salvaged airplane parts, reworked parts obtained from non-BEECHCRAFT approved sources, or parts, components, or structural assemblies, the service history of which is unknown or cannot be authenticated, may have been subjected to unacceptable stresses or temperatures or have other hidden damage, not discernible through routine visual or usual nondestructive testing techniques. This may render the part, component or structnral assembly, even though originally manufactured by BEECHCRAFf, unsuitable and unsafe for airplane use. BEECHCRAFf expressly disclaims any responsibility for malfunctions, failures, damage or injury caused by use of non-BEECHCI~FT approved parts. NOTE It shall be the responsibility of the owner/operator to ensure that the latest revision of publications referenced in this handbook are utilized during operation. servicing, and maintenance of the air- plane. 1,3_A 84 GENERAL INFORMATION POWER PLANT MISCELLANEOUS Lycoming TIO-541-E1B4, rated 380 horsepower Aircraft Dimensions at 2900 rpm. Overall Length 28. 98 Ft Spark Plugs Wing Span 37. 82 Ft TailHeight 9.22 Ft Champion RHB36P GAP:.015 to .022 Wheel Base 8. 108 Ft A. C. HSR87LP GAP: .015 to .022 Tread Width 9. 59 Ft Stabilizer Width 15. 94 Ft Firing Order Propeller Diameter 74 In Wing Dihedral 6" 145236 Propeller Ground Clearance 1.34 Ft NOTE Heater Spark Plug Number one cylinder is the forward cylinder CH-7S-06 GAP 0.312 to 0. 250 inch on the left hand side of the engine. Brake fluid Reservoir (Ftvd Baggage Compartment) Fillto 1 1/2 inch of top. Magneto Timing Maintain visible fluid level on dip stick 20" ETC (Before top center) of number 1 cylinder. Brake Wear Limits Oil Pressure Cleveland Minimum Abrasive surface .010 inch. 80 pounds at 150"F at 2600 rpm. Minimum Brake disc. thickness .325 inch. Oil Capacity Adjustment of Suction Relief Valve 13.0 quarts Gage reading 4.8 to 10. 5 quarts (usable) see Item 2 Consumable One Engine at 2200 rpm Materials Chart. 4.9 in. Hg. Two Engines at 2200 rpm Gage reading 5.0 to 5. 2 in. Hg. Propeller Hartzell HC-F3YR-2/C7479-2R With Autopilot Deice Brush Block Replacement One Engine at 2200 rpm Gage reading 8. 0 in. Hg. Goodrich, replace brushes when 15/32 inch maxi- ?tvo Engines at 2200 rpm Gage reading 8.4 mum distance is measured on wire inserted in. Hg. through inspection hole in brush support block. Oxygen Cylinder F.UEL SYSTEM Fill slowly to 1850 L- 50 psi at 70"F. Increase 3.5 psi for each degree increase. Fuel Grade and Capacity Decrease 3. 5 psi for each degree decrease. Gr~ade: 100/130, see Item 1 Consumable Materials Stall Warning Switch Chart. Capacity: Standard 142 Gallons (usable) Adjust 7 to 9 mph above a complete stall. TG-I and after Control Surface Travel Optional 178 Gallons (usable) TG-1 through TG-68 Flap O" Full Up Optional 204 Gallons (usable) 15" i´• 10 Approach TG-69 and after 300 i 00 -20 Full Down Fuel Pressure adjustment (Engine driven pump) With the engine running at 2100 rpm, adjust the fuel pressure to 23.0 psi. 1-3 Control Surface Travel (Continued) Engine Components Aileron 20" 1 Up 20" -e 1 Down Engine alternator Aileron Tab 10" -e 1 Up 10" -e 1 Down bracket bolts 500 in Ibs Rudder 33" -t 1" O" to Right; 25" -e 1 Left Engine alternator Rudder Tab 25" -e I Right 25" -t 1 Left adjusting arm bolt 190 in Ibs Elevator 30" -e 1 Up 15" -e I Down All generator mount- Elevator Tab r0"1 I Up 23" c I Down ing bracket bolts 160-190 in lbs Engind spark plugs 360-420 in Ibs Motor Brush Replacement Guide Engine oil filter retainer bolt 30-35 ft Ibs Flap Y16 inch min. required Propeller starter L. G. Retract 5/is inch min. required gearlslip ring to Heater Blower 3116 inch min. required crankshaft 60-70 ft Ibs Combustion Air Blower 3116 inch min. required Air Conditioning Compressor Air Conditioner j/ls drive shaft bolt 100-140 in Ibs Evaporator Blower inch min. required Horizontal and Vertical Stabi- Air Conditioner lizer Condenser inch min. required Front and rear spar Starter, Engine ~j inch min. required mounting bolts (ver- Generator 44_ inch min. required tical stabilizer) 160-190 in Ibs Alternator Slip Ring On Condition Front spar mounting bolts (horizontal stabilizer) 200-23,5 in Ibs DRY Service Rear spar mounting bolts (horizontal stabilizer) 85-100 in Ibs DRY Battery (Nickel Cad- Elevator horn hinge mium, 24 volt mounting bolts 50-70 in Ibs 13 amp/hour) 100 hours Wing Surface Controls Propeller Accumulator 125 -t 5 psig Pushrod to bell crank 30-60 in Ibs Main Gear Tires (6.50 Bellcrank to structure 50-100 in Ibs x 8 8 ply) 80 5 psig Aft Fuselage Controls Nose Gear Tire (5.00 Pushrod to bell crank 30-60 in Ibs x 5 6 ply) 47 t 50 psig Bell crank to structure 40-60 in Ibs Oil Filter 50 hours Rudder bell crank Oil Change 75 to 100 hourslor on linkage 50-70 in Ibs condition Wing Mounting Induction Air Filter Leading edge wing (replace) 500 hours mounting bolt 100-140 in Ibs. (dry torque) Suction Relief Valve Upper front wing Screen 100 hours mounting bolt 2480-2600 in Ibs (wet torque) Gyro Instrument Upper rear wing Central Air Filter mounting bolt 1180-1300 in Ibs (wet torque) (replace) 500 hours Lower rear wing Main Strut Extension 3 inches mounting bolt 2480-2600 in Ibs (wet torque) Nose Strut Extension 4.5 inches Lower forward wing Fuel System Screens 100 hours or sooner if mounting bolt 2880-3000 in Ibs (wet torque) and Strainers conditions warrant Landing Gear Wheel Bearings Main landing gear brace (repack) 100 hours bolts 290-410 in Ibs Cross arm to barrel TABLE OF TORQUES attach bolts 25-40 in Ibs Main landing gear Engine Mounting hinge bolts 250-800 in Ibs Fuel System Engine mount bracket bolts and nuts (at Attaching bolts for: firewall) 350 to 390 in Ibs Filler necks 45-55 in Ibs Engine shock mount Nacelle transmitter 45-55 in Ibs bolts and nuts 250 to 300 in Ibs Transmitter 25 in Ibs Engine mounting Access plates 45-55 in Ibs bracket bolts 270 in Ibs Fuel cell inter-connect clamps 25 -i- 5 in Ibs Rubber fuel nipple clamps 25 t 5 in Ibs Fuel vent valve assembly 20 in Ibs 1-4 B3 Courtesy of Bomar Flying Service www.bomar.biz When a torque wrench and adapter is used, (Figure 1-2) Example: D Desired reading compensation must be made for the extra leverage gained. L Length of torque wrench New indicator readings must be calculated before the wrench A Adapter length is used. To figure the desired lower readings which will T Torque actually give the torques specified, use the following formula: D=? L 33 inches Original wrench length x specified torque desired A 11 inches length of wrench adapter reading T 5,000 inch-pounds 33x5,000 165000 3750 inch-pounds 33 11 44 TOT~LLENGTH I i 5017-1 Figure 1-2. Torque Wrench and Adapter An acceptable method of checking the torque, if a torque in over torquing of the bolt. wrench is not available, (Figure 1-3) is to attach a spring scale to a conventional flex or "T" handle inserted in an adapter. When a torque wrench adapter is used, the length of the Force should be applied in a direction peIpendicular to an adapter must be added to the length of the flex or "T" handle imaginary line extending from the center of the bolt through wrench and a value calculated for that particular the spring scale attaching point. combination. The following is a typical example in finding a desired value. To calculate the force in pounds (scale reading) required to obtain the specified torque, divide the torque in inch-pounds Effective length of flex or "T" by the distance in inches between the center of the bolt and handle wrench: ......12 inches the scale attaching point. For example, if the specified Length of adapter 3 inches torque is 5,000 inch-pounds and the distance is 25 inches a Total length .15 inches specified as wet (lubricated), bolts to be torqued must be Desired torque on bolt 2000 inch-pounds pull of 200 pounds must be applied. Unless torque values are clean and free of all lubricants; otherwise loss of normal 2000 inch-pounds 133.3 pounds (scale reading) friction allowed for establishing the torque values may result 15 inches (LB) 900 TORQUE (IN. LB) 60´•1~´•2 Figure 1-3. Determining Torque by Spring Scale 83 1-5 TORQUING FINE THREAD SERIES BOLTS LOADED IN SMEAR NOTE The following torque values may be used as a guide when specific torques are not called out within this shop manual TORQUE LIMITS RECOMMENDED MAXIMUM ALLOWABLE (INCH-POUNDS) TORQUE (INCH-POUNDS) SIZE AN365 and AN310 AN364 and AN320 AN365 and AN310 AN364 and AN320 Nuts Nuts Nuts Nuts Column 1 Column 2 Column 3 Column 4 8-36 12-15 7-9 20 12 10-32 20-25 12-15 40 25 1/4-28 50-70 30-40 100 60 5/16 24 100-140 60-85 225 140 3/8-24 160-190 95-110 390 240 7/16 20 450-500 270-300 840 500 1/2- 20 480-690 290-410 1100 660 9/16 18 800-1000 480-600 1600 960 5/8-18 1100-1300 660-780 2400 1400 3/4-16 2300-2500 1300-1500 5000 3000 7/8-14 2500-3000 1500-1800 7000 4200 1-14 3700-5500 2200-3300 10000 6000 1-1/8- 12 5000-7000 3000-4200 15000 9000 1-1/4 12 9000-11000 5400-6600 25000 15000 NOTE: The above values apply to Class 3 threads, cadmium plated and nonlubricated. TORQUING COARSE THREAD SERIES BOLTS LOADED IN SMEAR TORQUE LIMITS RECOMMENDED MAXIMUM ALLX~WABLE (INCH-POUNDS) TORQUE (INCH-POUNDS) SIZE AN365 and AN310 AN364 and AN320 AN365 and AN310 AN364 and AN320 Nuts Nuts Nuts Nuts Column 1 Column 2 Column 3 Column 4 8-32 12-15 7-9 20 12 10-24 20-25 12-15 35 21 1/4-20 40-50 25-30 75 45 5/16 18 80-90 48-55 160 100 3/8-16 160-185 95-110 275 170 7/16 14 235-255 140-155 475 280 1/2 13 400-480 240-290 880 520 9/16 12 500-700 300-420 1100 650 5/8-11 700-900 420-540 1500 900 3/4-10 1150-1600 700-950 2500 1500 7/8-9 2200-3000 1300-1800 4600 2700 1 8 3700-5000 2200-3000 7600 4500 1-1/8-8 5500-6500 3300-4000 12000 7200 1-1/4-8 6500-8000 4000-5000 16000 10000 NOTE: The above values apply to Class 3 threads, cadmium plated and nonlubricated. 1-6 ADAPTER KIT 300-30 a SPECIAL TOOLS IS TO BE USED WITH THE MODEL 300 SERVICE JACK. O AILERON TAB TRAVEL GAGE 50-590090 ~i-- HOISTING SLING ADAPTER 95-590017 HOISTING SLING MODEL 300 95-590016-1 SERVICE JACK NOTE: IF AIRCRAFT IS TO BE HOISTED WITH WINGS REMOVED. 96-630000-1-810 USE THE 95-590017-1 SLING ADAPTER WITH A 95-590016-23 SPACER RUDDER iAB TRAVEL GAGE TS1222-3 UPPER FORWARD WING BOLT WRENCH KIT 35-4006 S TS1 171-2 UPPER FORWARD WING NUT TORQUE WRENCH ADAPTER TS1222-4 UPPER AFT WING BOLT WRENCH or I (j7 B FLAP TRAVEL GAGE TS1222-5 TS1171-1 UPPER AFI WING NUT TORQUE WRENCH ADAPTER 96-524000-810-2 50-590013 50-590014 LOWER FORWARD WING NUT TORQUE WRENCH ADAPTER -402 TS1222-3 LOWER FORWARD WING BOLT WRENCH TK1817-922-4 LOWER AFT WING BOLT WRENCH TS1171-2 LOWER AFT WING NUT TORQUE WRENCH ADAPTER ~-401 -403 -404 ADAPTERS FOR SERVICE JACK 932-7135-000001 96-524000-810 RUDDER TRAVEL GAGE 50-590013 60-960000/0922 35-135025-78-810-1 L.H. 95-524000-810-1 L.H. 8 R.H. TS1171-1 I TS1222-3 PROPELLER TORQUE 35-135025-79-810-1 R.H. ELEVATOR AND ELEVATOR TAB TS1171-2 TS1222-4 TS1222-5 TK1817-922-4 50-590014 1 WRENCH ADAPTER 1 AILERON TRAVEL GAGE I TRAVEL GAGE 56TC-17- 83 1´•7 SUPPLEMENTARY PUBLICATIONS Following is a List of publications providing servicing, overhaul and parts information on various components of the BEECHCRAFT Turbo Baron which you may obtain to supplement the BEECHCRAFT Turbo Bacon Shop Manual. In most instances, you should obtain the publi- cations directly from the manufacturer or his distributor. Only a few, such as eri~ine manuals and Beech supplementary publications, are available from the Parts and Service Operations, Beech Aircraft Cor- poration. Those which are available are Listed in the current Publications Price List. Since a wide variety of radio equipment is available and be- cause radio manufacturers normally supply parts and servicing man- uals with each set, radio publications have not been included in the list. As publications on additional components become available, they will be added to this List of publications. VENDOR PUBLICATIONS ENGINE Overhaul Manual 60294-6. Avco Lycoming Division, Williamsport, Pen- nsylvania, Parts Catalog PC-120. Avco Lycoming Division, Williamsport, Pennsylvania. FUEL INJECTION Operation and Service Manual, Form 15-338B. Bendix Corporation, South Bend, Indiana. PROPELLER Overhaul Instructions 117 for Hartzell Propeller. Hartzell Propeller Inc., Piqua, Ohio. ~tmer’s Manual 115 for Hartzell HC-FSYR-2/C 7479-2RPropeller. Hartzell Propeller Inc., Piqua, Ohio. Maintenance Handbook for Constant Speed Hydraulic Propeller Governor Type CSSA, Number 330014. Woodward Governor Company, Rockford, Illinois. Installation Manual for Woodward Electronic Synchronizer, Bulletin 33059. Woodward Governor Company, Rockford, Illinois. PROPELLER ACCUMULATOR Hydraulic Accumulator for Propeller Unfeathering, Bulletin 33058, Woodward Governor Company, Rockford, Illinois. MAGNETOS Maintenance Instructions for Bendix S-1200 Series M~anetos, Form L-609. Scintilla Division, Bendix Aviation Corporation, Sidney, New York. Service Parts List for Bendiu S-1200 Series Magnetos, Form L-608. Scintilla Division, Bendix Aviation Corporation, Sidney, New York. STARTING MOTOR Overhaul Instructions, Form~L Prestolite Company, Toledo, Ohio. 1-8 AUTOPILOT B-S Au~omatic Flight Control System Maintenance Manual 3950. Brittain Industries Torrance, California 90505. B-5 Flight Control System Ground Xnd Flight Check Procedures Manual 3952. Brittain Industries, Torrance, California 90505. B-7 Flight Procedures Manual 3959. Brittain Industies, Torrance, California, 90505. B-7 Maintenance iManual 3960. Brittain Industries, Torrance, California, 90505. 1-8A GENERATOR Overhaul and Parts Breakdown, File 30204. Lear Siegler Inc., Cleveland, Ohio. BATTERY Maintenance Manual and Parts List for Nickel-Cadmium Battery, GEJ-4344-2. GeneralElectric Company, Gainsville, Florida. STROBE LIGHT Installation/~laintenance Manual for Twilighter Mark mB High Intensity Aircraft Lighting System, Publication Number: 61-1006 and 61-1008, Hoskins Inc., Geneva, Illinois. Instruction and Se~ice Manual for Anti-collision Beacon, Publication ~umber: 50082, Bullock Magnetics Corp., Pomona, California. ELECTRIC PROPELLER DEICER Installation of Deicer Soots, Report 59-728. B. F. Goodrich Company, X~on, Ohio. Installation, Inspection and Tesdng or’ Prooeller Deicer System, Report 68-04-708. B. F. Goodrich Company, ,ud´•on, Ohio. SURFACE DE1CER Maintenance Instructions PublicationNumber: 63-200, B. F. Goodrich Company, A~on Ohio. HEATER VENT BLOWER Overhaul Instructions for Vane ,l_dal Blower Md861H-1A, with Motor iLI2916V. Dynamic Air En~ineering Inc., Santa Xna, California HEATER Maintenance Instructions for Janitrol F83A28 ,ilircraft Heater, a 30C57. Janitrol Aircraft-Automotive Division, Midland-Ross Corporation, Columbus, Ohio. Maintenance Instructions for Janitrol 11C30 Aircraft Heater Ignition Unit, 24C54. Janitrol Aircraft-Automotive Divi’sion, IMidland-Ross Corporation, ~Columbus, Ohio. AIR CONDITIONER COMPRESSOR Series 63 Compressor Manual, Form 180. JO-~TiM. York Corporation, York, Pennsylvania. Renewal Parts List, Form JN-E-RP. York Corporation, York, Pen- nsylvania. 1-9 BRAK~S Overhaul Information for Brake Shuttle Valve, Publication Ij 74d56. Hoof Products Co., Chicago, Illinois. Overhaul Information for Brake Shuttle Valve, Publication 23595. Paramount Machine Co., Stow, Ohio. SUPPLEMENTARY BEECHCRAFT PUBIICATIONS 98-35062 Wheel, Brake and Tire Servicing Maintenance Instructions, Illustrated Parts Breakdown. 98-33396 Overhaul Instructions for 60-389014 Alternator. 98-33857 Overhaul Instructions for 60-389017 and -1 Voltage Regulator. 98-35655 Operators Manual for B-5 and B-7 Autopilot. H-14 AUTOPIIOT 92-379A Operation Manual 130333B Adaptive Maintenance Manual 92-30103B Overhaul Instructions for BG274B2, CI, C2 Computer. 92-30105 Overhaul Instructions for CG136A1 Heading Selector. 92-30106B Overhaul Instructions for ~IG11SA1, MG113A2, 1LIG113A3, .MG113A4 Actuator and SG28A1, SG28A3 Pressure Switch. 92-30107A1 Overhaul Instructions for PC-S1X1 Altitude Control. 92-30229 Overhaul Instructions for GC205A3, GG205A4 (GG205B4) Turn and Bank Indicator Gyro. 92-30411B Overhaul Instructions for GG201A1, GG202B1 Vertical Gyro. 92-30412B Overhaul Instructions for GG202A1, GG202B1 Directional Gyro. 98-32523 Overhaul Instructions for 1MG11SAL and MG11BB1 Trim Actu- ator. 98-32839 Overhaul Instructions for CG417B1 and CG~d17B2 Flight Control- ler. 1-10 GROUND HANDLING ANCHORING AND MOORING PROVISIONS Exercise care in ground handling of the airplane to Three mooring eyes are provided; one in each wing avoid unnecessary damage. The following procedures and one in the tailbumper. To moor the airplane, are provided to reduce the possibility of ground dam- chock the wheels fore and aft, install the control age. lock and tie down the aircraft with a nylon line or chain of sufficient strength at each mooring eye. A- void overtightening the rear line, which pulls up the TOWING nose so that wind will create higher lift on the wings. If bad weather is anticipated, it is advisable to nose Attach the hand towbar to the tow lug on the nose the airplane into the wind. gear lower torque I~nee. PARKING BRAKE The brakes are set for parking by pulling out the parking brake control and depressing the pilot’s When towing with a tug, observe turn brake pedals to pressurize the system. Do not at- limits as placarded on the nose gear tempt to lock the parking brake by applying force to to prevent damage to the gear. the parking brake handle; it controls a valve only, and cannot apply pressure to the brake master cylin- ders. Icau´•rloal CAUTION Do not push on propeller or control Do not set the parking control when the surfaces. Do not place your weight brakes are hot from severe use or during on the horizontal stabilizers to raise low temperatures when an accumulation of the nose wheel off the groun& moisture may cause the brakes to freeze. HOISTING JACKING (Figure 2-1) A three-point jack is used to lift the aircraft off the The aircraft may be hoisted for maintenance or parts ground. Each jack pad is identified and located on replacement as follows: the under side of the fuselage. One jack pad is lo- cated on each lower wing-to-fuselage attachment a. Install one 95-590017 hoisting sling adapter on fitting along the front spar. The rear jack pad is lo- each forward wing attach bolt. cated under a protective cap in the middle of the fuselage at the rear fuselage carry thru spar. The rear jack fitting consists of an eye bolt that is NOTE screwed completely into the aircraft. When hoisting the aircraft with the wings IWARNINC) removed, replace the 95-590017 sling adapters with 95-590017-1 sling adapters and add a 95-590016-23 spacer between each sling adapter and the spar carry Be sure the rear jack point safety pin is thru fitting. Install with the upper rear in place to prevent the aircraft from nosing wing attach bolts, (see Figure 2-1). over. b. Attach the sling assembly, (P/N 95-590016-1), to the sling adapters. The Model 300 service jack with an adapter kit (P/N 300-30) is designed to be used with this aircraft, c. Install the sling strap around the nose, forward Facilities that have a 932-7 35-000001 service jack of the nose landing gear (see Figure 2-1). can convert it for use with the adapters listed in the Special Tools. d. Hoist the aircraft smoothly. When one engine or one wing is to be removed, a stand should be placed under the opposite ;ving and the tail to counteract the resu~ting unbalanced con´•- NOTE dition of the aircraft. Individual main wlseels mav be jacked by placing a floor jack under ~he ’5´•~i:: Adjust the sling strap to keep the aircraft located under each axle, in a level or slightly nose-down attitude. 2-1 a I// c ’I1Y’ 1! STRAP ADJUSTER ;NSTALL 95-590017-1 ADAPTE HERE WITH WING REMOVED. INSTALL 95-590017 ADAPTER HERE WITH WING INSTALLED. 95-590016-23 SPACER WING ATTACH BOLT SPAR CARRY 95-590017 ADAPTER THRU FITTING SPAF; CARRY THRIT FITTING WING SPAR FITTING 9 5- 59 0017- 1 ADAPTER WING ATTACH BOLT VIEW B _J VIEW A Figure 2-1. Hoisting the Aircraft 2-2 e. As an added precaution a stand may be installed TIRES under the tail of the aircraft. The main wheel tires are 6. 50 x 8, 8 ply tube type. The nose wheel tire is a 5. 00 x 5, 6 ply tube type. LEVELING Inflate the nose tire to 47 to 50 psi, and main wheel tires to 80 5 psi. Maintaining proper tire inflation To level the airplane longitudinally, first locate the will help to avoid damage from landing shock and con- phillips head screw labeled LEVEL POINT immedi- tact with sharp stones and ruts, and will minimize ately below the left side rear window. Loosen the tread wear. When inflating tires, inspect them visual- phillips head screw enough to attach and suspend a ly for cracks, breaks, or evidence of internal dam- cord and plumb bob. Inflate or deflate the nose gear age. shock strut as necessary to pass the cord through the center of a second phillips head screw at the bottom edge of the fuselage. Suspending the plumb bob in a can of light engine oil will assist in stabiliz- NOTE ing it. Beech Aircraft Corporation cannot recom- Lateral leveling is done by putting a bubble level on mend the use of recapped tires. Recapped the rear baggage compartment floorboard and deflat- tires have a tendency to swell as a result of ing the tire or strut on the high side of the airplane to the increased temperature generated during center the bubble, take-off. Increased tire size can jeopardize proper function of the landing gear retract EXTERNAL POWER system, with the possibility of damage to the landing gear doors and retract mechanism. An external power unit with a negative ground may be used to supply power for ground checks, starting and battery charging. A polarized external power recep- BRAKES tacle is located on the outboard side of the left engine nacelle. The receptacle is designed for a standard The brake fluid reservoir is located in the forward AN type plug. baggage compartment. The reservoir should be check- ed regularly and filled to within 1-1/2 inches of the The aircraft is equipped with a relay and diodes that top and a visible fluid level maintained on the dip protect the aircraft electrical system against damage stick at all times by adding hydraulic fluid (Item 13, from an external power source with reversed polarity. Consumable Materials Chart). Observe the following precautions when using an ex- ternal power source. SHOCK STRUTS a. Before connecting an external power unit, turn off the battery switch. The shock struts are filled with compressed air and hydraulic fluid (Item 13, Consumable Materials Chart). The same procedure is used for servicing b. To prevent arcing, make certain no power is be- both the main and nose gear shock struts. To service ing supplied when the connection is made, a strut proceed as follows: c. After the external power plug is connected, turn a. Remove the air valve cap and depress the valve on the battery switch before turning on any other core to release the air pressure. equipment. Leave the battery on during the entire external power operation. IWARNINCt IeAvr7i~ Do not unscrew the air valve assembly until the air pressure has been released or it may be blown off with considerable force, causing The battery may be damaged if exposed to injury to personnel or property damage. voltages higher than 30 volts. b. Remove the air valve assembly. SERVICING c. Compress the strut and fill through the air valve Proper and periodic servicing of the airplane will assembly hole with hydra~lic fluid (Item 13, Consum- prevent considerable wear and greatly lengthen the able Materials CharR until the Fluid overflows (ap- service life of parts and systems involved. For points prordmately one pint). of lubrication and the correct interval and materials, refer to the Lubrication and Servicing Charts in this d. Cycle the strut (iull e~tension to compressed) section. The following information gives instruction and refill. Repeat until filtld cclmot be added to the on the servicing of major systems, strut in the COm~I’eSSeC: T;t;iS:.’,l. 2-3 e. Install the air valve assembly. connect system, the filler cap must be removed from the main fuel cells unless the fuel level inthe f. With the aircraft resting on the ground and the fuel cells nacelle fuel cells is six inches or more below the full; Inflate the nose gear strut until 4-112 inches of the piston is full mark orfuel will drain out atfiller opening of the exposed and inflate the main gear strut until 3 inches of piston main fuel cell. is exposed. Rock the aircraft gently to prevent possible bin- ding of the piston in the banal while inflating. Most fuel injection system malfunctions can be attributed to contaminated fuel. Inspecting and cleaning the fuel strainers should be considered to be of the utmost importance as a NOTE regular part of preventive maintenance. k is recommended that the nose strut inflation Normally the fuel strainers should be inspected and cleaned dimension and the tire inflation pressure be care- every 100 hours. However, the strainers should be inspected fully adhered to. properly inflated tires and struts and cleaned at more frequent intervals depending on service reduce the possibility of ground damage occur- conditions, fuel handling equipment and when operating in ring to the propellers. Exercise caution when tax- localities where there is an excessive amount of sand or dust. ling over rough surfaces. Open each of the seven snap-type fuel drains daily to allow g. The shock strut piston must be clean. Remove foreign condensed moisture to drain ffom the system. material by wiping the strut with a cloth containing hydraulic fluid. NOTE FUEL SYSTEM If the cells are to remain unfilled for 10 days or more, apply a thin coating of light engine oil to the The standard fuel cell installation consists of 41 gallon fuel cell inside surface of the cell to prevent deterioration in each wing leading edge and 32 gallon fuel ceil in each wing and cracking. box section outboard of the nacelle. An optional 16 gallon fuel cell may be located in the ah section of the nacelle. Both standard cells located in each wing are interconnected and 01L SYSTEM filled through a common opening in the upper wing surface. The opening is covered by a Rush type cap. The optional Th,,,gines are equipped with a wet sump, pressure type oil nacelle tank is filled through an opening on the nacelle and is system. Each engine sump has a capacity of 13 quarts. The oil also covered by a Rush type filler cap. system may be checked through access doors in the engine cowling. A calibrated dip stick attached to the filler cap indi- When filling the aircraft fuel cells, always observe the foilow- cates the oil level. Due to the canted position of the engines, ing: the dip sticks are calibrated for either n’ght or left engines and a. Service the fuel calls with 100 octane Low Lead (blue) ,,,,ol interchangeable. 1 fuel, if not available, use 1001130 octane (green) or 115H45 octane (purple) fuel (ltem 1, Consumable Materials Chart.) The oil should be changed every 75 to 100 hours under normal operating conditions and the oil filter changed every 50 hours. b. Make sure the aircraft is statically grounded to the ser- Access to the oil drain is provided by removing the plate vidng unit, located on the bottom of the cowling just forward of the cowl flap. The engines should be warmed to operating temperature c. Do not fill fuel cells near open Rame or within 100 feet of t, assure complete draining of the oil. any open energized electrical equipment capable of produc- ing sparks. The oil grades listed in the Consumable Materials Chart are general recommendations only, and will vary with individual circumstances. The determining factor for choosing the cor- CAUT1ON rect grade of oil is the oil inlet temperature observed during flight; however, inlet temperatures consistently near the max- The wing fuel cells must be filled first on aircraft imum allowable indicate a heavier d~\ is needed. Lycoming equipped with optional nacelle fuel cells. Due to recommends use of the lightest weight oil that will give ade- the location of the nacelle fuel cells and the inter- quate cooling. 2-4 APPROVED OIL GRADES OPERATING AVERAGE OLL INLET AMBIENT AIR SINGLE MULTI- TEMPERATURE TEMPERATURE VISC~SITY VLSCOSITY FOR STARTING GRADES GRADES DESIRED MAXIMUM Above 600F SAE 50 SAE 40 or SAE 50 1800F 245"F 300 to 900F SAE 40 SAE 40 180"F 2450F 00 to 700F SAE 30 SAE 40 or 20W-30 1700F 2250F Below 10"F SAE 20 SAE 20W-30 1600F 210"F NOTE Dry Element The turbocharged engines are to be operated a. Remove the filter from the aircraft. with ashless dispersant oil conforming to specification MIL-L-22851 or a Lycoming b. Clean the filter according to the instructions on approved synthetic oil. the element frame and reinstall on the aircraft. An all climate synthetic aircraft engine lubricant, Anderol 456H or Anderol 4?1, is approved by Lycom- Ing. Owners desiring detailed information concerning the use of these oils should consult Lycoming Service Letter No. L147A. The provisions specified in this service letter must be followed when using this oil. BATTERY OIL FILTER The following List of battery servicing precautions and The oil filter should be replaced every 50 hours. Re- checks is meant to be a general guide. For specific place the filter as follows: details and complete procedures, see Section 13 of this manual a Cut safety wire and remove the filter housing. a. After each 100 hours of operation or every 30 b. Install new filter in the housing and secure to the days, whichever occurs first, check the electrolyte engine. Torque retainer bolt to 30 to 35 foot pounds, level and clean the battery and filler vent plugs. c. Safety retainer bolt. b. Any time the battery is subjected to more than 32 volts for as long as two minutes, the battery must be completely serviced. Clean the battery, charge it, INDUCTION AIR FILTER and adjust the electrolyte level The induction air filter should be cleaned every 50 c. Periodically check that the cell vents are clean hours and replaced every 500 hours of service. and open. Plugged vents may cause excessive internal Either a dry filter element or a wet filter element cell pressure and cause leaks. maybe installed. d. Never remove a cell from the battery case unless Wet Element: a replacement is immediately available; otherwise, the remaining cells may swell, making replacement of a. Remove the filter from the aircraft and wash the removed cells difficult. Loosen the vents before throughly, dirty side down, in solvent (Item 15, Con- cell replacement to eliminate the possibility of cells sumable Materials Chart). swelling from internal gas pressure. b. Allow to dry and apply a small amount of engine preservative oil (Item 28, Consumable Materials e. Check the torque of the terminal screws securing Chart) to the filter. the cross Links connecting the cells together. This torque should be from 48 to 60 inch-pounds (4 to 5 c. Allow any excess oil to drain off for approxim- foot-pounds). ately 2 to 4 hours before reinstalling on the aircraft. f. Check that no carbon deposit has built up on the cross links or between them and the battery case. If 2-5 such deposits are present, clean the affected areas gasoline; kerosene type distillates should be avoided. as indicated under "Battery Cleaning". Replacement filters, P/N H9W334-231, may be ob- tained from Beech Aircraft Corporation Torque g. When ttiere is any indication of oil in the battery, filter bolt to 40 to 60 inch pounds. The filters are remove all cells from the case and check all rubber located in the forward right hand side of the upper parts for deterioration. Remove the oil and replace nacelles. all damaged rubber parts. Do not use a solvent, use soap and water only. CLEAMNG DEICER BOOTS h Do not add electrolyte just because the level in the battery is low. if electrolyte is added instead of The boots should be checked for engine oil after ser- distilled water each time the level in the battery is vicing and at the end of each flight, and any oil found low, the high concentration of electrolyte may cause should be removed. This can be accomplished by the dissolution of the plates under high temperature con- use of a neutral soap and water solution. Care should ditions. This is indicated by the presence of black be exercised to avoid scrubbing the surface of the particles in the affected cells. boot as this will tend to remove the special conductive surfacing. i. Keep nickel-cadmium and lead-acid batteries stored separately to prevent mutual contamination Unless kept in closed storage containers, nickel- cadmium electrolyte @otassium hydroxlde) will ab- NOTE sorb enough carbon diordde from the air to render it ineffective. Since the deicer boots are made of soft, nercible stock, care must be exercised against dragging gasoline hoses over them or rest- OXYGEN SYSTEM ing ladders or platforms against the surface of the boots. To service the oxygen system, remove the protective cap from the filler valve located in the nose baggage compartment. CLEANING AND CARE Of AIRCRAFT FINISH Do not apply wax or polish for a period of 90 days ]WARNINOI after delivery to allow the paint to cure. Waxes and polish seal the paint from the air and prevent curing. For uncured painted surfaces, wash only with cold Keep fires, cigarettes and sparks away or lukewarm (never hot) water and a mild nondeter- when outlets are in use. Open and close all Pent soap. Any rubbing of the painted surface should oxygen valves slowly. Make sure the oxygen be done gently and held to a minimum tb avoid crack- shut-off valve is in the closed position In- ing the paint film. spect the filler connection for cleanliness be- fore attaching it to the filler valve. Keep After the paint cures, wash the airplane with a mild tools, hands and components clean, as fire soap and water. Flush loose dirt away first with or explosion may occur when pure oxygen clear water. Harsh, abrasive, or alkaline soap or comes in contact with organic material such detergents which could cause corrosion or make as grease or oil scratches should never be used. Use soft cleaning cloths or chamois to prevent scratches when cleaning Attach a hose from an oxygen recharging cart to the and polishing. Any good grade automobile wax may be filler valve. To prevent overheating, fill the oxygen used to preserve painted surfaces. To remove stub- system slowly by adjusting the recharging rate with born oil and grease, use a soft cloth dampened with the pressure regulating valve on the cart. The oxygen naphtha. However, after cleaning with naphtha, the cylinder should be filled to a pressure of 1850 -L 50 surface should be rewaxed and polished. psi at a temperature of 700F. This pressure may be increased an additional 3. 5 psi for each degree of increase in temperature; similarly, for each degree CLEANING PLASTIC WINDOWS of drop in temperature, reduce the pressure by 3. 5 psi. When the oxygen system is properly charged, A commercial cleaning compound made specificallv disconnect the filler hose from the filler valve and for acryllc plastic windows may be used. When using replace the protective cap, a commercial cleaner follow the instructions on the container. SURFACE DEICER SYSTEM It a commercial cleaner is not available, the follow- ing instructions should be followed Examine the filters after each 100 hours of engine ;,peration for dirt accumulation in the filter housing. Cleaning of the acrylic plastic windows should never r;or a cleaning agent use a commercial hydrocarbon be attempted when dry. The window should first be ~,rpe solvent such as naphtha, petroleum ether, or flushed with water or a mild soap solution, then rub- 2´•6 bed slightly with a grit-free soft cloth, chamois or When the shimmy dampener is full, the insertion sponge. Stubborn grease or oil deposits are readily depth is 2-3/16 inches. The emptyreading is 3-1/16 removed with aliphatic naphtha or hexane. Rinse inches. To add hydraulic fluid, (Item 13, Consum- with clear water. able Materials Chart), remove the shimmy dampener and proceed as follows: Icnu´•rlo#l the pistonrod.a. Remove the cotter key, washer and spring from Do not use thinner or aromatic abrasive cleaners to clean the windows; they will b. Remove the internal snap ring, scraper ring damage the surface of the plastic. ALiphatic and the end seal from the aft end of the barrel. (Op- naphtha and similar solvents are highly in- posite clevis end. flammable, and extreme care must be taken when using them. c. Insert a 6/32 threaded rod into the floating piston and remove the piston, using extreme care when moving the "0" ring seal of the floating piston past PROPELLER ACCUMULATOR the drilled holes in the piston rod, The propeller accumulators are located on the lower d. Push the piston rod to the clevis end and fill the rear section of each engine. The accumulators should barrel with hydraulic fluid. be inspected every 100 hours and charged with dry air or nitrogen to 125 psi 5 psi. e. Slowly actuate the piston rod, allowing the fluid to flow into the clevis end chamber, then return the AIR CONDITIONER piston to the clevis end of the barrel. See Section 10 of this manual for servicing instruc- f. Refill the displaced fluid and replace the end tions. seal, scraper ring and internal snap ring. SHIMMY DAMPENER g. Fill the piston rod with fluid. To check the fluid level in the shimmy dampener, in- k Reinstall the floating piston, spring, washer and sert a wire of appro~imately 1/18-inch diameter cotter pin. Spread the cotter pin to allow clearance through the hole in the disc at the end of the piston for the measuring wire. rod until it touches the bottom of the hole in the floating piston Mark the wire, remove and measure the depth of insertion Inserting the wire in the hole ROTON LOCKS of the floating piston, rather than letting it rest a- gainst the face of the piston, will give a more ac- (Figure 2-2) curate check Usually, Roton locks will need no set-vice. If there is a grinding and binding in the lock as the seat re- NOTE dines or the return action becomes jerky, a little grease properly applied as follows should improve the To determine if the wire is inserted in the operation. hole of the floating piston, insert the wire severaltimes, noting each insertion depth a. Use only (Item 30, Consumable Materials Chart) When the wire is correctly inserted the on the thread as shown in Figure 2-2. Too much length will be appro~dmately 1/4 inch great- grease or grease in the wrong place can cause im- er. proper operation. FULLY EXTENDED RETAINING SPRING GUIDE 3/4" (APPROX)- APPLY GREASE (LICJITLY HERE ONLY) ABSOLUTELY NO GREASE ~-SPRWG GUIDE TUBE IN THIS AREA MAIN ASSY COUNTERBALANCE SPRING Figure 2-2. Roton Lock :1 2-7 b. Compress the spring guide and counter-balance spring appro~dmately one inch AIR VALVE c. Remove the retaining ring. d. Relax pressure on the spring guide and counter- balance spring slowly ~mtil the spring is fully extend- ed. e. Remove the lock from the fixture and remove the ZERK spring guide, counter-balance spring, and spring GREASE ZERK guide tube. f. Apply a small quantity of grease to the completely extended thrust screw (see Figure 2-2). g. Reassemble the lock For service other than lubrications return the Roton lock to the manufacturer. PROPELLER The propeller should be serviced at 100 hour inter- o o o vals. Servicing consists of checking the air dome ~O O O pressure and lubricating the blade bearings. Service o as follows: a- ~b P PROPELLER BLADE BEARING LUBRICATION (Figure 2-3) a Remove the propeller spinner. Figure 2-3. Propeller Servicing Points b. Remove the safety wire and covers from the four grease "zerks". See Figure 2-3 for location. INSTRUMENT WEDGE LIGHTING c. Lubricate with Item 11, Consumable Materials (TG-84 and after) Chart by placing the grease gun fitting on one zerk of each blade and filling until the grease is visible Internal lighting of the instruments provides additional from the zerk on the opposite side of the blade. illumination across each instrument. A light tray mounted on the top side of the bezel of each instrument d. Clean excess grease from the propeller and re- holds two bulbs wired in parallel. If the light bulbs install the grease zerk covers and safety. are damaged or burned out, the light tray with bulbs must be replaced. e. Reinstallthe spinner, LIGHT TRAY REMOVAL a. Remove the screws that secure the instrument PROPELLER AIR DOME PRESSURE panel in place and tilt the instrument panel aft to gain access to the instruments. (Figure 2-3) NOTE a Remove the access cap from the propeller spin- ner to expose the filler valve. Instruments located at the lower edge of the panel may be removed if necessary to gain b. Charge the dome with dry air or nitrogen to a access to the light tray at the top of the pressure of 80 psi at 700F. Increase the pressure instruments. an additional 2 psi for every 10 degrees of increase in temperature; similarly, for every 10 of b. Remove the two screws that attach the light tray drop in temperature, reduce the pressure by 2 psi. to the instrument bezel. 2-8 LIGHT TRAY INSTALLATION ment panel and secure in place with the attaching screws. a. Install the new light tray and secure in place with the two attaching screws. c. Secure the instrument panel in place. b. Install the instrument, if removed, in the instru- 2-8A TABLE OF THREAD LUBRICANTS SYSTEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS Any product conform- ing to the referenced specification may be used. Fuel Anti-Seize, Graphite MDL-T-5544 Armite Product, Petrolatum Armite Laboratories Los Angeles, Calif. Anti-seize Compound I, Esso Standard. C~ Oil, Manifold Lubricating Grease (Gas- MIL-G-6~32 L-23’1. Lehigh Chem- Pressure, oline and Oil Resistant) ical Co., Chestertown, Anti-icer, Vacuum Maryland. Rockwell950 Rock- wellMfg. Co., New Yo~l;: N.Y. Royce 32, Royal Eng. Co., Whippany, N. J. Brake, Deicer, Anti-Size Compound Federal Specification Armite Product, Static and Pitot White Lead Base TT-A-580 (JAN-A-669) Armite Laboratories, Los Angeles, Calif. Oxygen Thread Compound, MIL-T-5542 No. 15 Rector Well Anti-Seize and Sealing, Equipment Co., Oxygen Systems Houston, Texas. D~ 217 Acheson Colloies Co., Port Huron, Michigan. Key Abso-Lute, Type St. Louis, nlinois. Oxygen, High Ribbon Dope Thread Sealant. MIL-T-27730 Permacel Tape Corp., Pressure Side Only. New Brunswick, N. J. Air Conditioner AntiSeize Compound Mn-T-5544 or TT-A-580 Turbocharger Anti-Seize Compound MIL-A-907C Anti-Seize Compound Inlet Temperature C5A Fel-Pro Inc., Probe 7450 McCormick, Skokie, Illinois 60076 2-9 CONSUMABLE MATERIALS CHART ITEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS The vendor products appearing in this chart have been selected at random to Avrey 10Vt 100, help field personnel determine products conforming to the Military Specifications Socony Mobil Oil Co.. listed in this publication. The brand names are listed for ready reference and are Inc., 150 East 42nd not specifically recommended by Seech Aircraft Corporation. Any product which Street, New York, conforms to the referenced specification may be used. N. Y. 10017. ITEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS Or any approved air- craft engine oil (graded 1. Fuel, Engine 100 octane Low Lead (blue, if at 1100 or 1065). not available, use 100/130 octane (green) or 115/130 7. Lubricating Oil (Gear) MIL-L-6086 Grade M Trojan Gear Oil fir6086 octane (purple): M. Cities Service Oil Co., 60 Wall Tower, 2. Oil, Engine MIL-L-22851 New York 5, N. Y. (See Oil Grades Chart) Aeroshell Fluid 5M, Shell Oil Co., 50 W 3. Corrosion Pre- MIL-C-6529 Cities Service Oil Co., 50th Street, New York. ventive Compound 60 Wall Tower, New N. Y. York 5, N. Y. L-1195, Sinclair Re- Rust Foil #652-2, lining Co., 600 Fifth Franklin Oil and Gas Avenue, New York, Co., Bedford, Ohio. N. Y. Kendex #7038, Kendall 8. Lubricating Grease MIL-G-7711 Regal AFB 2, Texaco Refining Co., Brad- (General Purpose) Inc., 135 East 42nd ford, Pa. Street, New York 17, N. Y. Aeroshell Grease t6. 4. Lubricating Oil MIL-0-6081 Gunlite Turbojet Oil Shell Oil Co., 50 West #1010, Gulf Oil Corp., 50th Street, New York Pittsburg, Pa. 20, N. Y. Aeroshell #3-1286, 22442, International Shell Oil Ca., 50 West Lubricants Co., New 50th Street, New York, Orleans, La. N. Y. 10020. 9. Lubricating Grease MIL-G-81322 Mobil Grease 28. Jet Engine Oil #1010, (High Temperature) Mobil Oil Corp.. Texaco Inc., 135 East Shoreham Bldg. 42nd Street, New York, Washington. D.C. 20005 N. Y. 10017. Aeroshell 65. Shell 5. Lubricating Oil SAE 20 Oil Co., 50 W 50th Street, New York, N. Y´• 6. Lubricating Oil, Aircraft M1L-L-6082 Conoco Aero Oil #1065, Reciprocating (Piston) Continental Oil Co., 10. Lubricating Grease (Gear) Mobile Compound~G. G. Engine Ponca City, Oklahoma. 11. Lubricating Grease MIL-G-23827 Supermil Grease Phillips 66 Aviation (Aircran and Instruments, RA72832, American Engine Oil, Grade 1065, Low and High Temperature) Oil Co., 910 South Phillips Petroleum Co., Michigan Avenue, Bartlesville, Oklahoma. Chicago, ill. Sl~eMite 100, Skelly Royco 27A. Royal Oil Co., El Dorado, Lubricants Co., River Kansas. Road, Hanover, N. J. 2-10 B1 ITEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS ITEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS Shell 6249 Grease, Shell Oil Co., 50 West 2.3. Paint Remover Turco #4260, Turco 5Mh St. New York 20, Products Inc., Los N. Y. Angeles, California 12. Lubricanl Mdybdenum MILM-7866 Molykote Z. Wilm Co.. 21. Epoxy Primer MIL-P-23377 Ameron Industrial Coatings Disulfide Powder Wichita, Kansas. P.O. Box 2153 Wichita, Kansas 67201 Molykote Z, Standard Oil of Kenluc*l. 2j~ Wash Primer Ameron Industrial Coatings Div. P.O. Box 2153 Molykote Z, HaRkel Wichita, Kansas 67201 Seals. Glendale, California. 2ij. Zinc Chromate Primer MIL-P-8585 Moly-Paul #4, K. S. 27. Rubber Hose Mn-H-5593 Paul Products Ltd., Nobel Road, London, 28. Oil, Engine Preservative MIL-L-21260 England. Graphite, Lubricating MIL-G-6711 GP-36, National Carbon 13. Hydraulic Fluid MIL-H-5606 Brayco 756D, Bray Co., New York, N.Y. Oil Co., 3344 Medford Street, Los Angeles 3(3. Lubricating Grease ENCO ANDOK-B Humble Oil Co., 63, California. Houston, Texas TL-5874, Texaco Inc., 31. Solvent CRC-2-26, Corrosion 135 East 42nd Street. Reaction Consultants, New York, N. Y. Inc., Philadelphia, Pa. FED 3565, Standard Oil Co. of California 32. Penetrating Oil Mouse Milk Worldwide Aircraft 225 Bush Street, San Filters Corp., 1685 Francisco 20, Calif. Abram Ct., San Leandro, California, 14. Oxygen-System Leak MIL-L-25567 94577 Testing Compound 33. Adhesive EC2216 Minnesota Mining Mfg. Co., 15. Solvent PD680 St. Paul, Minnesota 16. Lubricating Oil SAE-10 jj. Corrosion Preventive Mn-C-16173 Bray Oil Company, Compound Grade 2 1925 N. Marianna Ave. 17. Air Conditioner Refrigerant #12 Los Angeles, Refrigerant California 90032 18. Oil, (Air Conditioner Suniso Virginia 3:i. Coating Alodine 1200, Amchem Products Inc., Compressor) 500 Viscosity Chemical and Smelting 1200S or 1201 Spring Garden Street Co., West Norfolk, Ambler, Pennsylvania Virginia. 19002 Texaco Capella E., NOTES Texaco Inc., 135 East 42nd Street, New York i. If 100 octane Low Lead (blue) fuel is not available, 1001130 octane (green) or 17, N. Y. 115/145 octane (purple) fuel may be used as an alternate. 19. Aviator’s Breathing Oxygen MIL-0-27210 2. Precautions should be taken when using MIL-G-23827 and MIL-G-81322, since these greases contain chemicals harmful to painted surfaces. 20. Naphtha TT-N-95 21. Methyl Ethyl Ketone MIL-M-1 3999 22. Toluol TT-T-548 83 2-11 LUBRICATION CHART ITEM LOCATION LUBRICANT INTERVAL ITEM LOCATION LUBRICANT INTERVAL DETAIL A 1. Control column linkage (18) SAE-80 100 hrs, NOTE 2. Control column head (6) SAE-20 100 hrs. 3. Control column aileron link (3) SAE-20 100 hrs. See section 5 for instructions on periodic lubrication of up DETAIL B lock rollers. i. Door handle (1) SAE-80 100 hrs. 4. Main retract fittings (8) MIL-G-7711 100 hrs. 2. Door latch (2) SAE-80 100 hrs. DETAIL M DETAIL C 1. Flap motor gear box (1) MIL-C-23827 300 hrs. 1. Rudder pedals (8) SAE-80 100 hrs. DETAIL N DETAIL D 1. Nose wheel door hinges (4) SAE-20 100 hrs. 1. Landing gear motor gear box (1) MIL-G-7711 300 hrs. 2. Landing gear actuator gear box (l)t Mobile Compound GG 300 hrs. DETAIL O DETAIL E 1. Nose wheel bearings (2) MTL-G-81322 100 hrs. 2. Shimmy dampener (1) MIL-H-5606 100 hrs. 1. Main gear door hinges (10) SAE-20 100 hrs. 3. Nose shock strut (1) MIL-H-5606 100 hrs. 4. Nose retract fittings (4) MIL-G-7711 100 hrs. DETAIL F DETAIL P 1. Optional baggage door latch SAE-20 100 hrs. mechanism (3) i. Nose steering mechanism (5) Mn-C-7711 100 hrs. DETAIL G DETAIL 1. Rudder trim tab actuator (1) MIL-G-23827 AR i. Heater iris valve (1) MIL-M-7866 AR 2. ***Rudder trim tab hinge (1) MIL-G-6711 100 hrs. NOTES DETAIL H i. Elevator trim tab actuator (1) MTL-G-23827 AR Precaution should be taken when using MIL-G-23827 and MIL-G-7711, since these 2. +**Elevator trim tab hinge (1) MIL-G-6 711 100 hrs. greases contain chemicals harmful to painted surfaces. DETAIL I *Flap tr;~ck rollers O?re-lubed sealed bearings). Pressure lubricate at 1000 hours inspecti~n using MIL-G-23827 lubricating grease. 1. Aileron trim tab actuator (1) MIL-G-23827 AR 2. ***Aileron trim tab hinge (1) MIL-G-6711 100 hrs. **See prop~ller lubrication in this section for propeller blade bearing lubrication instructions. Lubricate at 100 hours,with MIL-G-23827 lubricating grease. DETAIL J ***Mix MIL-G-6711 with naphtha and apply with a brush. 1. Aileron bell cranks (6) SAE-20 100 hrs. tWhen properly filled, the oil level on a dipstick inserted through the filler hole DETAIL K will be approximately 1/4 inch. 1. Flap actuator (2) MIL-L-6086 300 hrs. Grade M DETAIL L 1. Main wheel bearings (4) MIL -G-3 545 100 hrs. 2. Main shock struts (2) MIL-H-5606 100 hrs. 3. Up lock rollers (2) SAE-80 50 hrs. 2-12 DETAIL A DETAIL B DETAIL C DETAIL D DETAIL E DETAIL F i~ ra 71 DETAIL Q DETAIL G DETAIL H LUBRICATION DIAGR dk M 111 A BCD E F \3DETAIL P T DETAIL I DETAIL J a P O N Valk M L K DETAIL O DETAIL N DETAIL M DETAIL L DETAIL K I B Figure 2-4. Lubrication Diagram 2-13 SERVICING CHART ITEM I LOCATION _I SERVICE WITH I INTERVAL Ce Engine Oil Level Access door on upper cowling (2) See oil grades chart Preflight. Battery Electrolyte Access plate on L.H. rear nacelle (1) See section 12 for detailed instructions. Every 10D hrs. Air Conditioner Compressor Oil Level See section 10 for location and special instructions Suniso m or Te.uaco Capella E, 500 Viscosity oil As Req. Air Conditioner Refrigerant See section 10 for location and special instructions Refrigerant ;f 12 As Req. Autopilot Servo Air Filter Aft of baggage compartnlent partition (1) Every 100 hrs. Propeller Air Dome Access cap on propeller spinner (2) Dry air or nitrogen Every 100 hrs. Propeller Accumulator Lower rear of engine (2) Dry air or nitrogen Every 100 hrs. Change Engine Oil Access plate on lower nacelle (2) See oil grades chart Every’75 to 100 hrs. Engine Oil Filter R.H. side of engine (2) Every 50 hrs. Clean Deicer Filter Housing Access plate on R.H. rear nacelle (2) Naphtha or petroleum ether Every 100 hrs. Induction Air Filters R.H. rear side of engine (2) Clean with solvent lubricate with MIL-L-21260 Every 50 hrs. Senro Fuel Filter Fuel injector (2) Clean with solvent and blow dry with air pressure Every 100 hrs. Fuel Strainers Main wheel well (2) Clean with solvent and blow dry with air pressure Every 100 hrs. Heater Fuel Pump Screens L.H. side of nose wheel well (2) Clean with solvent and blow dry with air pressure Every 100 hrs. Heater Fuel Strainers L.H. side of nose wheel well (1) Clean with solvent and blow dry with air pressure Eve ry 100 hrs. Engine Oil Screens Lower rear of engine (2) Clean with solvent and blow dry with air pressure Every 50 hrs. Suction Relief Valve Screens Forward of instrument panel (2) Clean with solvent and blow dry with air pressure Every 100 hrs. Air Pump Inlet Filter Top rear of engine (2) Clean with solvent and blow dry with air pressure Every 100 hrs. Drain Fuel Sump Drains Lower wing surface (2) Preflight Fuel Strainer Drains Lower wing surface (2) Prenight. Fuel Tank Drains Lower wing surface (2) Preflight. Heater Fuel Filter Drain L.H. side of nose wheel well (1) Prenight. Static Drain On upholstery panel below pilots sub panel (1) Every 100 hrs. Replace Central Air Filter Forward of instrument panel (1) Every 500 hrs. Deicer System Air Filter Access plate on R.H. rear of each nacelle (2) As Req. Autopilot Servo Air Filter Aft of baggage compartment partition (1) Every 1000 hrs. Induction Air Filter R.H. rear side of engine (2) Every 500 hrs. Gyro Instrument Air Filter In nacelle aft of firewall (2) Every 300 hrs. Service Brake Fluid Resenroir Forward baggage compartment (1) MIL -H-5606, hydraulic fluid As Req. Oxygen Cylinder Forward baggage compartment (1) MIL-O-27210, aviator’s breathing oxygen As Req. Main and Nose Landing Gear Struts Top of each strut (3) MLL-H-5606, hydraulic fluid and compressed air Every 100 hrs. Shimmy Dampener Nose landing gear (1) MIL-H-5606, hydraulic fluid Every 100 hrs. Numbers in parentheses indicate the number of points to be serviced. 2-14 SEALING CHART ITEM PRODUCT VENDOR 1. A-56-B Cement B. F. Goodrich Co., Akron, Ohio. 2. EC-870 Glue Minnesota Mining and Manufacturing Co., St. Paul, Minnesota. 3. Permatex Sealer No. 2 Permatex Co., Inc., Kansas City, Kansas. 4. Presstite Sealer No. 576 Presstite Engineering Co., St. Louis, Mo. 5. Silastic Sealer No. 140 Dow Coming, Midland, Michigan. 6. EP711 Coast Proseal and Manufacturing Co., Los Angeles, California 7. EC 1615 Minnesota Mining and Manufacturing Co., St. Paul, Minnesota 247.830 68.000 100.000 170.000 207.000 84.125 101.000 131.000 257.606 49.000r;116.700179.000 233.500 262.900 131.000 r272.000 ´•30.000 00.000 26.250 8.5 20.500 13´•250 37.000 i 1 -7-G~L i i WL 100.000 i.. I kc..T :I jl ,s, L,,.,, F5.58.125 82.960 118.500 FUSELAGE 60310 57.750 58.000 15.25 t 8.’25 67.850 3.885 46.500 79.450 56.250 35.150 00.000 34.750 46.000 25.5 1 as. AIRPLANE 22.250 i9.875 i ML FRONT SPAR IsTAa) WL 100.000 ML REAR SPAR i’ FOSELAGE STA. 273.750 VERrICAL STABILIZER IL36.150 jll 3.900 80.260 36.900 6.200 60.340 ---7~---59.000 HORIZONTAL STABILIZER 66.000--1 /11 55.500 70.3401 II 11 53´•000 47.000 73.000 39.375 228.000 205.500 175.831 80,340 191.000 162.563 94.09 34.37536.030 148.875 83.547 35.301 103.641 1 109,305 i I 113.1721( i (FS. 58.125) ~jjj II i iii FRONT SPAR (FS. 82.9601 i REAR SPAR (FS. 118.5001 222.000 136.188j 198.000 175.294 129,750 123182 80.047 122.750 94.86495.463 .,i.. i~L23.881 122.500 31.750 56TC´•ll-1 WING Figure 3-1, Stations Diagram 3-1 FUSELAGE AND EMPENNAGE SKIN INFORMATION The following fuselage and empennage skin information with the tab- ulation or" each individual skin and material description is furnished as general information for making skin repairs: INDEX NO. MATERIAL DESCRIPTION 1. .025 Clad 2024-’13 2. .032 Clad 2024-T3 3. .020 Clad 6061-T6 4. .020 Clad 2024-T3 S, .020 Clad 2024-’14 6. .016 Clad a024-~3 7. ,090 Royalite 8, .032 Clad 2024-T4 9. .020 3da~. Xl~oy, AZ31B-H24 10, .060 Clad 2024-T3 11. .040 Xlum. Xlloy, 6061-T6 12. ,050 Xlum. Allov. 6061-T6 13. .020 Alum. ~llo;; 6061-T6 14. ~o. 181Glass Cloth, 4 or 3 ply to obtain.050 wall thick- ness 3-2 2 4 1 J TOP I 11 I I \I 12-t´•\I I I\ U I I 1‘ Y’ 12 1 4 4 1 10 7 11 9 2 BOTTOM 2 9 CI a 2 11 II 12-C~III 1 2 3 14 I i9 i 2 13 2 9 2 2 2 2 t 2 J a O a (7 I~ 4 a 11 7 14 3 15 4 8 8 2 1 1 1 i 2 2 1 2 1 4 8 2 Figure 3-2. Fuselage and Empennage Skin Plating 3-3 WING SKIN INFORMATION The fo!bwi~g tvi~ skin iu~ormation with the tabulation of each individual skin and mare~ial descriurion is furnished as ge~erzl inform~ion for mak- in~ skin reairs: INDEX NO. MATERIAL DESCRIPTION .025 Clad 202~-T3 2. .032 Clad 2026-~3 3. .020 Clad 5024-T3 .020~um, ,-Uloy, 202~-T42 5. .040 Clad 2026,-’T3 .016 Clad 6061-T6 7. .032 Clad 202a-T1 8. .016 Clad 202s-T3 9. .03-0 Clad 6061-T6 10. .025.11um.,LUlov 6061-T5 11. No. 181GlaEs Cio~n. 3 Ply 12. .032 Xlufi,. Allov 6061-0 1 5 1~ 1P 5 2 .2 5 1? ~p 12 1 5 T n 3 5 6 3 k i ;6 111 I k k 3 2 6 RIGHT WTNG TOP VIEW LEFT WING TOP VTEW 1 2 3 s 12 Ip 1? 2 2 1~ Ip 112 5 7 2 1 3 3 3 3 8 7 3 3 7 2 6 1 -cf--c--1 ;3 (i RIGHT WMG BOTTOM VIEW i r I LETT WDI~G BOTTOM VIEW Figure 3-3. Wing Skin Plating 3-5 FUSELAGE ACCESS OPENINGS 1. Elevator trim tab actuator 9. Landing gear actuator 2. Elevator trim tab actuator sprocket 10. Control cable pulleys 3. Elevator tab cables 11. Ringe bolts for nose wheel strut ´•1. Horizontal stabilizer mounting bolts 12. Rudder tab actuator 5. Heater ignition, iris valve and blower assembly 13. Nose baggage door 6. Tailcone 14. Afl baggage compartment 7. Elevator bellcrank, elevator down spring, 15. Jack attach point and turnbuckles 16. Nose gear retract idler arm 8. Cable inspection 17. Rudder bellcrank 3-6 Zi ii2IO-1 i’ J ii c C~aj 6; 1; a Is s is 6 O C1I iI ,1 ii 51 Fi~ure 3-4~ Fusela~e Access Ooenings 3-7 WING ACCESS OPENINGS i. Leading edge and box section fuel filler neck 18. Air conditioning access 2. Landing light access 19. Battery, battery relays, voltage regulators, over- voltage relays, starter relays, paralleling rheostats, 3. Oil level indicator access paralleling relays, alternator out relays, fuel flow in- verter, radio inverter out relay, load meter shunt 4. Leading edge fuel cell. transmitter and fuel cell and fuse block installation access 20. Wing attach bolt access 5. Reverse current diode, external power relay and L. H. control relay 21. Cowlflap 6. External power receptacle 22. Wing leading edge cap 7. ~u?dliary fuel cell transmitter (Installed if nacel- 23. Flap hinge 501t access le fuel cell is not installed. 26. Xileron cable inspection 8. ~leron bellcrank 25. Xileron cable pulley 9. Nacelle fuel cell vent plumbing 26. Aileron tab actuator and pulley 10. Nacelle fuel cell filler neck 27. Wing tip access ii. Nacelle fuel cell and vent line plumbing 28. Wing tip spar fitting 12. Nacelle fuel cell plumbing, transmitter and in- stallation access 29. Pitot mast access 13. Nacelle fuel cell plumbing 30. Oil drain access 14. Reverse current diode 31. Engine exhaust 15. Leading edge fuel cell transmitter 32. Box section fuel cell installation access 16. Fuel pressure solenoid and deicer system filter 33. Fuel cell siphon valve 17. Fuel pressure solenoid, deicer system filter and 34. Fuelboostpump cabin door seal plumbing 3-8 D n 3 It---C~ II II n---H-- 3 5 6 19 11 II 11 1118174 15 20 20 15 14 2 1 4 ill Z r 1 7 8 8 7 9 10 11 12 20 10 13 9 11 10 12 LI~FT ~’ING IilGII’T \S’ING (UDPE;R) Ci_ n 21 30 31 ?2 22 30 21 31 29 ’j 29 33 71 28 27 33 C) 32 25 /4 26 23 24 25 32 23 20 13 14 13 I~rt;lr´•l´• WING (I,OW[~11) I i L,I-:F.I. W[N~ (I,OWEII) FiG"’e 3-5. Access Ol,ciiii,~s 3-9 WING wheel well and remove the roll pins from the inboard aileron cable pulley brackets. Disconnect the aileron tab cables and WING TIP REMOVAL aileron tab stops in the left wheel well. ~IOTE k. Disconnect the hydraulic brake line at the inboard connection in the wheel well. On aircraft equipped with pneumatic surface deicers, the deicer boot must be removed from i. Disconnect fuel lines between the wing root rib and the the wing tip before the wing tip can be removed. fuselagr. See Section 10 for deicer boot removal and installation instructions. m. Disconnect the flap drive shaft at the motor and remove the clamps attaching the shaft housing to the fuselage. a. Remove the screws attaching the wing tip to the wing. n. Remove the lower aft nacelle fairing assembly. b. Disconnect the electrical leads to the navigation light and to the landing light, o. Remove the inboard nacelle fairing. WING TIP INSTALLATION p. Remove the leading edge cover of the wing located between the fuselage and nacelle. a. Attach the electrical leads to the navigation light and landing light. q. Remove the clamps securing the wiring bundles to the wing inboard leading edge. Disconnect wiring bundles at b. Position the wing tip to the wing and install the attaching terminals located on the aft side of nacelle firewall. screws. r. Disconnect the wiring to the electrical components c. Reinstall deicer boot (If applicable), located in each side of the upper nacelle. s. Disconnect and cap the plumbing between the wing root WING REMOVAL rib and the fuselage. (Figure 3-6) a. Drain and purge all fuel cells. WARNING b. Remove the wing mounting bolt access plates from the The two air conditioner lines between the right top and bottom of the wing. wing root rib and the fuselage are high pressure lines. Before disconnecting the two lines, loosen c. Place the aircraft on a three point jack to prevent an the fitting just enough to bleed off the pressure unbalanced condition of the airplane after the wing is slowly. removed. d. Place a wing stand under the wing that is not being t. Disconnect the flap wire bundle and safety switch wiring removed and place a stand under the tail. Remove the engine in the left wheel well. Disconnect the plumbing and electrical according to the instructions given on engine removal in wirine (boost pump and fuel quantity transmitter) in each Section 6. wheel well. e. Open the brake cylinder bleed pens and pump all fluid u. Remove the clamps securing engine controls to the from the system. leading edge. f. Retract the landing gear until the inboard landing gear v. Disconnect the pitot line between the wing root rib and doors are fully open. the fuselage. g. Disconnect the inboard door actuating rod from the w. Outline the position of the wing on the fuselage as a guide control horn, to reinstallation. h. Disconnect the landing gear uplock cable at the inboard door idler arm in the cabin. CAUTION i. Disconnect the landing gear actuator rod from the There should be no bolt binding during removal. V-brace in the wheel well. Should binding occur, adjust the wing position until the bolts disen,oage freely. Do not screw or j. Disconnect the aileron cables at the turnbuckle in the drive a bolt into, or out of the fittings. 3-10 83 x. Remove the nuts and bolts from the fittings. CAUTION I fuselage.y. Remove the wing by pulling it straight away from the Bolts and nuts must be oriented as shown in the applicable illustration for each location (Figure 3-6, 3-6A, 3-6B, 3-6C and 3-6D). NOTE f. Start the nuts on the bolts. Rotate the wing trailing edge Discard the soft aluminum washers installed until the wing aligns with the outline drawn on the fuselage. between the upper wing attach fittings. Install After alignment is established, verify that the lower forward new washers when the wing is reinstalled. bolt is not binding in the bolt bore. If bolt binding is encountered, adjust the wing position until the bolt moves freely in the fittings. WING INSTALLATION g. Tighten the upper forward and aft nuts (Figure 3-6A and a. Using a nonmetallic brush and naphtha or methyl ethyl ketone 3-6B). (Item 3,0 Or 21, Consumable Materials Chart), clean the wine attach fittings and hardware (bolts, nuts, and washers). Inspect the wing attach F~ttings and hardware as instructed under WING BOLT NUT AND FITTING INSPECTION. CAUTION When torquing the nuts, assure that the wrenches do not bottom out on the wing fittings. Such an WARNING occurrence could cause false torque readings and damage to the fittings. After torquing the upper Wing bolts that have reached their life limit(l0 forward nut, remove the holding force from the years after the initial inspection) must not be wing cradle (if used) and torque the remaining reused. See Chart 3-1. three nuts. b. Coat the fitting bolt bores and bearing faces, bolts, h. Torque the nuts in the following order: upper forward, washers, and nuts with MIL-C-16173 Grade II corrosion upper aft, lower forward and lower aft (Figure 3-6A, 3-6B, preventive’compound (Item 34, Consumable Material 3-6C, and 3-6D). When a torque wrench adapter is used, the Chart). length of the adapter must be added to the length of the torque wrench and the proper torque value computed as shown in Figure 1-2. NOTE Do not lubricate the leading edge attach fitting or CAUTION hardware. Before the lower aft nut is torqued, a slight gap may be evident between the fittings. This gap c. Place the slide in the fuselage fitting at the leading edge should not exceed a width of.060 inch. No gap attach point (see Figure 3-6). should exist after the nut is torqued. Torque the wing attach bolts at the nut end. Do not rotate the d. Guide the flap shaft and landing gear retract rod into their bolt in the bolt bore. respective positions. CAUTION i. Torque the leading edge attach point to the dry torque value shown in Figure 3-6. There should be no bolt binding during installation. Should binding occur, adjust the j. Reinstall the engine, connect engine controls. wing position until the bolt moves freely through the fittings. k. Connect all electrical wiring to the engine, nacelle terminal, and the electrical components located in each side of the upper nacelle. e. Align the wing and fuselage fittings, install the soft aluminum washers between the upper wing attach fittings, i. Connect the plumbing between the wing root rib and the and insert the bolts into the fittings. fuselage. 83 3-11 60-i00011 AN960C516 BUSHING WASHER AN960D916L WASHER MS20365-524CNUT NAS 1305-21 FUSELAGE SMEAR TlE SUPPORT 60-100012 BOLT WING SMEAR TIE SLIDE 60-100011 AN960D916L WASHER BUSHING TORQUE TO 100 TO 140 INCH-POUNDS 56TC-31-22 O Figure 3-6. Leading Edge Attach Point Bolt Installation 3-12 83 t95-110025-1 WASHER 105090A032-12K WASHER ~t95-110021 WASHER (POSITION (POSITION WITH RADIUS7 I rWITH COUNTERSINK TOWARDS TOWARDS WING FITTING) I BOLT HEAD :i.´•:~::i 128126 NUT NAS152-37:M BOLT DRAIN HOLE 14~´•; s~;.;´•´•/--FUSELAGE FITTING :i:IV ~j-´• I’~ )’F´•’31 r: I WING FITTING WASHER BOLT TORQUE: 248010 2600 INCH-POUNDS. COAT THE COMPLETE 80LT. NUT. WASHERS. WING FITTING 80LT BORES. AND EXPOSED BOLT THREADS WITH MIL-C-16173. GRADE 2 CORROSION PREVENTIVE COMPOUND. ~CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS. WASHERS MAY 88 USED AS REQUIRED BETWEEN THE NUT AND 95-110025-1 WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT. NOTE Concunent with the scheduled torque ched(, inspect the upper wing attach fittings to assure that the drain hdes are clear. O REFER TO CHART 3-1 FOR THE WING BOLT \~O ~O O WRENCHES AND TORQUE ADAPTERS USED WITH THIS WING BOLT AND NUT. 56TC´•3(´•23 Figure 3-6A. Upper FoMrard Wing Bolt Installation 83 3-12A 105090A032-10J WASHER ~t35-105111 WASHER +95-110025-3 WASHER (POSITION WITH COUNTERSINK (POSITION WITH RADIUS TOWARDS BOLT HEAD] WING FITTING) 128108 NUT .~:C:r;14´•j.I i 150-35/M BOLT DRAIN HOLE r r:-i~:. WING FITTING ~r*NAS143-10 WASHER FITTING BOLT TORQUE: 1180 TO 1300 INCH-POUNDS. COAT THE COMPLETE BOLT. NUT. WASHERS. WING FITTING BOLT BORES. AND EXPOSED BOLT THREADS WITH MIL-C-16173. GRADE 2 CORROSION PREVENTIVE COMPOUND. *CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS. ++NAS143-10 WASHERS MAY BE USED AS REQUIRED BETWEEN THE NUT AND 95-110025-3 WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT. NOTE I REFER TO CHART 3´•1 FOR THE WING BOLT WRENCHES AND TORQUE ADAPTERS USED Concunent with the scheduled torque WITH THIS WING BOLT AND NUT. check, inspect the upper wing attach finings to assure that the drain holes are clear. O O O 56TC´•31-25 Figure 3-6B. Upper Af;Wing Bolt Installation 3-12B 83 3 FITTING rNAS495-1 4-26 80Li +50-105011 WASHERSL~88144 NUT FUSELAGE FITTING IPOSITION WITH RADIUS TOWARDS WING FITTING~ WET BOLT TORQUE~ 2880 TO 3000 INCH-POUNDS COAT THE COMPLETE BOLT. NUT. WASHER. WING FITTING BOLT BORES. AND EXPOSED THREADS WITH MIL-C-16173. GRADE 2 CORROSION PREVENTIVE COMPOUND. +CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS. 56TC´•31´•35 Figure 3-6C. Lower Forward Wing Bolt Installation 83 3-12C O o I, o 95-110021-1 WASHER (POSITION +~tMS20002-12 WASHER WITH COUNTERSINK TOWARDS BOLT HEAD) ´•3´•e :~4’’ iY:):i::~E’’’’.’ I´•.´•’ E3Uc~s 128-126 NVT~ 250-12-024/Mi BOLT +95-110025-1 WASHER (POSITION WITH RADIUS TOWARDS WING FITTING) BOLT TORQUE: 2480 10 2600 INCH-POUNDS. COAT THE COMPLETE BOLT. NUT. WASHERS. WING FITTING BOLT BORES. AND EXPOSED BOLT THREADS WITH MiL-C-16173. GRADE 2 CORROSION PREVENTIVE COMPOUND. +CHECK WASHER FOR A SMOOTH CONTINUOUS OUTER RADIUS. ++MS20002-12 WASHERS MAY BE USED AS REQUIRED BETWEEN THE NUT AND 95-110025-1 WASHER TO PROVIDE A PROPER BOLT GRIP ADJUSTMENT 56TC´•3(´•24 Figure 3-6D. Lower Aft Wing Bolt Installation 3-12D 83 Chart 3-1 Wing Bolt Wrenches And Torque Wrench Adapters TORQUE WRENCH POSITION BOLTPARTNO. WREIVCHPARTNO. NUTPARTNO. ADAPTER NO. UPPER FORWARD NAS 157-37/M1 TS 1/32-3 12B126 TS1171-2 UPPER AFT NAS 150-3511W TS11224 12B108 TS1171-1 or or TS1313-5 50-590013 LOWER FORWARD NAS395-13-26 TS1222-3 EB144 50-590014 LOWER AFT MS31150-12 TK1817-922-4 1213126 TS1171-2 -02411CV WING SMEAR FITTING LOOSEN THIS NUT UNTIL THE BUSHING CAN BE DISENGAGED FROM THE HOLES IN THE WING SMEAR FITTING SCRIBE MARK BUSHING FUSELAGE SMEAR TIE SUPPORT BUSHING NOTE SCRIBE MARK THE MARK SCRIBED ON THE SIDE OF EACH BUSHING AT THE TIME DETAIL A OF MANUFACTURE, MUST BE ALIGNED PRIOR TO RETORQUING LOOKING DOWN AT LEADING THE NUT. EDGE ATTACH POINT 56TC´•3r-34 Figure 3-6E. Leading Edge Attach Point 83 3-12E NOTE NOTE The air conditionin,o system must be purged and After torquing the upper wing attach nut, remove recharged after wing installation. See Section 10 the holding force from the wing cradle prior to for instructions on purging and recharging the torquing the remaining nuts. system. g. Rotate the bushings in the leading edge attach point until m. Connect the tlap wire bundle and plumbing in the aft they engage the shear fitting holes. The scribe mark on the wheel well, side of each bushing must be aligned before the nut is torqued. Torque the nut to the dry torque value shown in n. Replace all clamps securing wiring bundle and engine Figure 3-6. controls to the leading edge. h. After removing the wing and tail stands and thejack, test o. Reinstall the lower aft nacelle, wing leading edge cover, fly the airplane. nacelle fillets and inboard nacelle fairing. i. if adjustment will not remedy a heavy wing condition, rig the flap down on the heavy wing by screwing the actuator ADJUSTING THE WING out. Do this as a last resort, since rigging the flap down will create additional drag on the airplane. After the wing has been reinstalled or repaired, flight tests may show the wing to be chronically heavy or light. This condition may be corrected by rotating the wing to lower the trai