shop manual - AeroElectric

8-4 thru 8-6 B"1 Jun 1970 14-260 88 Jan 7/77 9-1 Orig Apr 1970 14-27 8/5 Dec 1972 10-1 thru 10-2 812 Jun 18/80 14-28 8/3 Sep 1971 I0-2A 810 Apr 19/79 14-28A 8/5 Dec 1972 10-3 Orig Apr 1970 14-288 81 Eiov 1/73 10-4 thru 10-4A 812 Jun 18/80 14-280 88 Jan 7/77 10-5 thru 10-6 812 Jun 18/80 14-288 81 Nov 1/73 10-7 89 May 12/78 14-28E thru 14-28F 88 Jan 7/77 10-8 thru 10-11 85 Apr 20/76 14-286 B1 Nov 1/73 1~-1 B11 Aug 24/79 14-29 88 Jan 7/77 11-2 thru 11-10 Orig Apr r970 14-30 B/3 Sep 1971 11-11 8/3 Sep 1971 14-30A 81 Nov 1/73 12-12 thru ll-12A 82 Dec31/73 14-308 88 Jan 7/77 11-13 thru 11-14 815 Aug 28/87 14-31 64 Oct 17/75 ll-14A 815 Aug 28/87 14-32 88 Jan 7/77 11-15 thru 11-22 Orig Apr 1970 14-32A thru 14-328 84 Oct 17/75 12-1 thru 12-28 8/3 Sep 1971 14-33 8/5 Dec 1972 12-3 Orig Apr 1970 14-34 thru 14-35 88 Jan 7/77 13-1 thru 13-2 89 May 12/78 14-36 Orig Apr 1970 13-3 thru 13-4 831 Aug 24/79 14-36A 8/3 Sep 1971 13-5 812 Jun 18/80 14-368 84 Oct 17/75 13-6 thru 13-7 89 May 12/79 14-37 88 Jan 7/77 13-8 thru 13-9 810 Apr 19/79 14-38 Orig Apr 1970 13-10 thru 13-23 B9 May 32/78 14-38A 8/3 Sep 1971 14-1 89 May 12/78 14-388 84 Oct 17/75 14-2 84 Oct 17/75 14-39 88 Jan 7/77 14-3 thru 14-5 Orig Apr 1970 14-40 Orig Apr 1970 14-6 8/3 Sep 1971 14-40A 84 Oct 17/75 14-6A 8/5 Dec 1972 14-41 88 Jan 7/77 14-68 88 Jan 7/77 14-42 Orig Apr 1970 14-7 Orig Apr 1970 14-42A thru 14-428 8/3 Sep 1971 14-8 8/3 Sep 1971 14-43 88 Jan 7/77 14-8A thru 14-80 8/5 Dec 1972 14;44 8/5 Dec 1972 14-80 thru 14-8E 88 Jan 7/77 14-44A 88 Jan 7/77 14-9 Orig Apr 1970 14-45 thru 14-468 8/5 Dec 1972 14-10 thru 14-10A 8/3 Sep 1971 14-47 thru 14-57 88 Jan 7/77 14-108 8/5 Dec 1972 14-58 812 Jun 18/80 14-11 thru 14-13 Orig Apr 1970 15-1 82 Dec 31/73 14-14 8/3 Sep 1971 15-2 thru 15-3 B11 Aug 24/79 9 14-14A 81 Nov 1/73 16-1 thru 16-7 B11 Aug 24/79 14-148 84 Oct 17/75 B15 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL ALPHABETICAL INDEX Access Openings 3-2,3-3 System Leak Detection. 10-7 Actuator Troubleshooting 10-10 Assembly, Landing Gear, Ventilation Blower Removing And Installing 5-16A Installation, Removal 10-9 Flap 4-148 Servicing 2-4A Disassembly 4-16,Illus.4-17 Charging 2-4A Elevator Trim Tab Overhaul 4-2A Checking Compressor Oil 2-48 Landing Gear Overhaul 5-16A,I71us.5-18 Airplane Defueling 8-2A Adjusting Airplane Dimensions 1-3,1-4,1-4A Brake Master Cylinder Linkage 5-2 Air Filter, Induction ...r........ 2-4A Cabin Door 3-19 Air Induction System. Engine 6-5 Flap Limit Switch 4-14,Il1us.4-15 Air Pressure Pump 6-8A Fuel Pressure 1-48 Air System, Static Fuel System Illus.6-3,6-4 Air System Static, Cleaning 11-11 Idle Speed and Mixture 6-2,Illus.6-3 Airplane Finish, Cleaning Care 2-6 Landi ng Gear System 5-6 Aluminum Finish, Cleaning Waxing 12-3 Magneto Breaker Point 6-6 Airplane Alum. Exterior Micro Switch 5-8 Preparation for Paint 12-1 Oil Pressure 6-4,Illus.6-5 AlcalCalibration Unit 6-19 Overvoltage Relay 13-3 Alignment, Slip Ring 11-5 Parking Brake 5-2 Alternator 13-1,13-2 Pressure Relief Valve 1-4A Overhaul 13-3 Pressure Switch 5-8 Removal 13-2 Pressure System 11-13 Installati~n 13-2 propeller Governor 7-1,Illus.7-1 System Troubleshooting 13-16 Seat Back Adjustment 3-16 Anchoring Mooring Provisions 2-2 Stall Warning 11-11 Application of Ext, Paint Throttle Warning Horn 6-5 on Aluminum Skins 12-1 Utility Door Approved Eng. Oils, Chart 2-5 Aft Half 3-19 Assembly of Landing Gear Forward Half 3-20 Shock Struts 5-11,5-13,Illus.5-14 Voltage Regulator 13-3 Autopilot Wings 3-9 Troubleshooting 11-18 Ai7eron Auxiliary Fuel Pump 8-28 Balancing 4-7,Illus.4-8 Control Trimmer 4-2 B Insta7lation 4-2 Removal 4-2 Baking Enamel 2-2A Rigging 4-2,Illus.4-3 Balancing System 4-2,I1lus.4-3 Aileron 4-7,I11us.4-8 Tabs 4-2 Control Surfaces 4-7 Air Conditioning Elevator 4-9,Illus.4-11 System 2-4A,10-5,11~us.10-6 Rudder 4-12,I7lus.4-13 Charging,System 2-4A Battery 2-4, 13-1 Compressor, Removaf,Installation 10-9 14 Volt System 2-4 Compressor Belt 28 Volt System 2-4A Removal, Installation 10-7 Charging 13-1 Tension Adjustment 10-7 Maintenance 2-4A Evaporator Troubleshooting 13-16 Filter Replacement 10-9 BEECHCRAFT New-Matic A/P 11-14A Removal, Installation 10-9 BEECHCRAFT Supplemental Functional Test 10-7 Publications 1-2A Maintenance 10-5 Blade Maintenance, Propeller 2-8 precautionary Service Measures 10-5 Blade Repair, Propeller 7-2,Illus.7-2 B75 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Bolts, Wing 3-10 Vinyl Paint 12-2A Brakes, Assembly Wheel Check Removal installation 5-1 Brush Block Resistance 11-5 Bleeding Deicer Resistance 11-5 Dual System 5-1,I11us.5-4 Deicer Timer 11-4 Gravity 5-1 Landing Gear System W/Safety Pressure 5-1,I~lus.5-3 Switch in Test Position 5-8 Fluid Reservoir ’2-28,1-40 Cleaning Master Cylinder Battery Maintenance Program 13-1 Linkage Adjustment 5-2 Engine 2-6 Overhaul 5-2,111us.5-4A,5-5 Interior Cab7n Trim 2-6A Removal Installation 5-2 Plastic Windows 2-6 Parking 2-2 Static Air System 11-11 Adjustment 5-4A Cleaning Care of Airplane Finish 2-6 Valve Overhaul 5-4A,Illus.5-5 Cleaning Waxing Airplane Finish 12-3 Valve Removal Instal~ation 5-2 Cleaning, Repair Parts Replacement Relining 5-2 Shimmy Dampener 5-16A Servicing 2-2B Coarse Thread Series Bolts, Torqu~ng 1-7 System 5-1,Il1us.5-3 Colors, Interior 12-2A Troubleshooting 5-20 Component Replacement Electrical 13-1 Wear Limits 1-4C,5-1 Component, Repair of ~iberglass 3-24 Breaker Point Adjustment, Magneto 6-6 Compressor Brush Block Replacement 1-4B Belt 10-7 Brush B7ock Resistance Check 11-5 Oil Level 2-48 Brush, Replacement, Removal,Installation 10-9 Deicer Servicing Illus.2-4B Brushes, Starter 13-5 Condenser Removal, Installat7on 10-7 Bu13ock Strobe Unit 13-6,111us.13-7 Console Light Bulb Replacement 13-5 ConsumableMaterials Chart 2-9 thru 2-1-1 C Continuity Test, Deicer 11-4 Control Column, Single 4-1 Cabin Cooling 10-2 Removal Installation 4-1 Cabin Door 3-16 Rigging 4-1 Adjustment 3-19 Control Lock 2-2 Lock 3-18 Controls, Surface Flight Removal Installation 3-17 Aileron 4-2 Teleflex Cable Removal Balancing 4-7,111us.4-8 and Installation 3-17 Control Trimmer 4-2 Window Removal Installation 3-20 Removal Installation 4-2 Cabin Heating 10-1,111us.10-2A Rigging 4-2,Illus.4-3 10-3,10-4,10-4A Tabs 4-2 Cabin Ventilation 10-1,1llus.10-2A Elevator 4-2A 10-3,10-4,10-4A Balancing 4-10,Illus.4-1l Capacity, Fuel Grade 1-48 Removal Installation 4-2A Capacity, Oil 1-4B Rigging 4-2A,Illus.4-4 Case Repair of Fuel Cells 8-4 Trim Tab 4-2A Cells, Fuel, Removal Actuator 4-2A Installation 8-2A Rigging 4-2A Charging Air Conditioning System 2-4A flaps 4-14,Illus.4-15 Chart Actuator 4-14B,I11us.4-17 Approved Engine Oi7s 2-5 Disassembly 4-16 Consumable Materials 2-9 thru 2-11 Installation cf Removal 4-14 Electrical Utilization Load Limit Switch 4-14,I11us.4-15 14 Volt 13-10, 13-11 Motor Removal Installation 4-14A 28 Volt 13-12, 13-13, 13-14, 13-15 Motor Gearbox Assembly Flare Fitting Torque 8-6,Il1us.8-6 and Disassembly 4-16 Lacquer Paint 12-2A Overhaul Replacement Schedule 15-2 Lubrication 2-12,2-13,Illus.2-14 Position Indicator Adjustment 4-14A Sealing 2-16 Shaft Removal Installation 4-148 Servicing 2-15 Track Wear Limits 4-14 ii B15 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Rudder Electric Wiring Diagrams 14-1 Balancina 4-12,Illus.4-13 Elevator 4-2A,Illus.4-4 Removal Insta7lation 4-5 Balancing 4-9,Illus.4-l1 Rigging 4-5 Check Tab Free Play 4-40 Control Surface Travel 1-40 Removal Installation 4-2A Cooler, Oil 6-8A Rigging 4-2A,Illus.4-4A Cooling, Cabin 10-1 Trim Tab 4-2 Cowl Flaps 6-1 Actuator 4-2B,4-2A,Illus.4-4 Cowling Removal 6-1 free Play 4-4C,Illus.4-4E Cylinder, Brake, Master Rigging 4-2A Overhaul 5-2,I71us.5-5 Electric 4-4B,Illus.4-4D Cylinder, Oxygen 1-40 Enamel Baking 12-2A Cylinder, Oxygen Replacement 11-1 Engine Cyl inder Head Temperature 1-48 Air Induction System 6-5 Baffles 6-1 D Cleaning 2-6 Fuel System 6-3 Dampener, Shimmy 2-6A,5-15 Fuel Pump Adjustment 8-5 Defueling Airplane 8-2A Instruments 3-23 Electric, Propeller 11-1,16-1 Oils, Approved 2-5 Boot Installation (EA-I aft) 6-2 Brush Block Replacement 1-48 Removal (EA-I Aft) 6-2 Brush Replacement Removal Installation 6-4 Heat Test 11-4 Troubleshooting 6-13 Resistance Check 11-5 Evaporator System Troubleshooting 11-7 Filter Replacement 10-9 Timer Check 11-4 Removal Installation 10-9 Diagram, Stations 3-1 Exhaust Temperature Indicator 6-18 Dimensions, Airplane 1-3,1-4,1-4A Exterior, Airplane Aluminum, Disassembly of the Main Preparation for Paint 12-1 Gear Shock Strut 5-10A,Zllus.5-12 Exterior Interior Finish 12-1 Door Exterior Interior Primer 12-2A Cabin Exterior Paint on Aluminum Adjustment 3-19 Skins, Application 12-1 Utility 3-19 Exterior Paint Touchup Repairs 12-28 Adjustment External Power 2-2A Aft Half 3-19 Forward Half 3-20 F Dual Brake System, Bleeding 5-1,1llus.5-3 Fiberglass Components, Repair of 3-24 Fifth Sixth Seat Removal E Installation 3-15 Fifth gr Sixth Seat Stowage 3-15 EGT Indicator 6-18 Filter, Air Induction 2-4A Electric Elevator Trim 4-48 Filters, Pressure System 1l-14A Electric Propeller Deicer Fine Thread Series Bolts, Torquing 1-7 50-Hour Inspection 16-6 Firing Order 1-48 Electric Propeller Deicer Flaps 4-14,Il~us.4-15 100-Hour Inspection 16-6 Actuator 4-148,Illus.4-17 Electric Propeller Deicing DisassembSy 4-16 Goodri~h 11-1 Installation Removal 4-14 Electric Symbols 14-3 Limit Switch 4-14,I17us.4-15 Electrical System 13-1 Motor Removal Battery 13-1 Installation 4-14A,4-148 Elevator Trim, Electric 4-48 Motor Gearbox Component Replacement 13-1 Assembly Disassembly 4-16 Overhaul Replacement Schedule 15-3 Overhaul Replacement Schedule 15-2 Electric Utilization Load Chart Position Indicator Adjustment 4-14A 14 Volt 13-10,13-11 Track Wear Limits 4-14 28 Volt 13-12,13-13,13-14,13-15 Flap Control &-Indicator 815 iii BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Circuit, Troubleshooting 13-20 Servicing 2-3 flap Fitting Torque Chart 8-6,I1ius.8-6 System 1-4A,8-1.Illus.8-2C Flared Fittings, Installation 8-5 System Adjustment 6-3 Flight Contro-ls Surfaces 4-1 Tank Vent Line Aileron 4-2,711us.4-3 Inspection 8-1.111us.8-3 Balancing 4-7,I~lus.4-8 Controller Trimmer 4-2 G Removal Instal7ation 4-2 Rigging 4-2,Il1us.4-3 Gear Landing, Electrical System, Trim Tabs 4-2 Troubleshooting 5-20 Elevator 4-2A,Illus.4-4 Gear, Landing, Overhaul Balancing 4-9,I17us.4-11 Replacement 15-2 Removal Installation 4-2A Gear, Landing, Rigging 5-8A Rigging 4-2A,Illus,4-4 Gear, Landing, Safety System 5-6 Trim Tab 4-2A Gear, Landing System 5-6,Illus.5-7 Actuator 4-2A Gear, Main, Removal Installation 5-13 Rigging 4-2A Gear, Main, Tolerances 5-11 Flaps 4-14,Il1us.4-15 Gear, Nose, Removal Installation 5-13 Actuator 4-148,I11us.4-17 Gear, Nose, Tolerances 5-11 Disassembly 4-16 Gear, Nose Shock Strut Assembly 5-13 Installation Removal 4-14A Gear, Nose Shimmy Limit Switch 4-14,111us.4-15 Dampener Assembly 5-15,Illus.5-16 MOtor Removal Installation 4-14A Gearbox, Flap Motor Motor Gearbox Assembly Overhaul 4-16,Illus.4-17 Disassembly 4-16 General Information 1-4A Overhaul Replacement Generator System, Standby 13-3 Schedule 15-2 Glareshield Removal Installation 3-23 Position Indicater Adjustment 4-14A Governor, Propeller Shaft Removal Installation 4-148 Adjustment 7-1,Illus.7-1 Track Wear Limits 4-14 Gravity Bleed Brakes 5-1 Rudder Grimes Strobe Unit 13-8 Balancing 4-12,1llus.4-13 Ground Cable Static Adjustment 2-8 Removal Installation 4-5 Ground Checks, Electric Rigging 4-5 Elevator Trim 4-48 Single Control Column 4-1 Ground Handling 2-1 Control Column Arm Installation 4-1 Ground Run Warm Up 6-1 control Column Arm Removal 4-1 Guide, Inspection 16-1 Effect of Temperature Upon Guide, Motor Brush Replacement 1-40 Cable Tension 4-2 Guide, Replacement, Rigging the Control Light Bulb 13-9 Column Chain 4-1 Forward LH Window Removal H and Installation 3-20,3-21 Front Seat Removal Installation 3-15 Handling, Ground 2-1 fuel Heat Test, Deicer 11-4 Boost Pump 8-20 Heater Muff, Removal Installation 10-1 Cells Heater Muff Pressure Testing 10-1 Care 8! Repair 8-4 Heating Vent System Inspection 10-2 teak Testing 8-4 Heating Cabin 10-1 Removal Installation 8-2A High Oii Temp 6-4 System Adjustment 6-3 Hoisting 2-2A Engine Driven Pump Adjustment 8-5 Horizontal Stabilizer Removal Grade Capacity 1-48 Installation 3-15 Inspect Flapper Valve 8-2 Overhaul Replacement 15-2 Pressure Adjustment 1-48 Sel ector Valve 8-5 Idle Speed Mixture Quantity Indicator Circuit Adjustment 6-2,1llus.6-3 Troubleshooting 13-21 Ignition Troubleshooting 13-17 Removal Installation 8-5 Index, Wiring Diagrams 14-2 iv B15 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Induction Air Filter 2-4A Troubleshooting 13-19 Information, General 1-4 Position Light Adjustment 5-8A Inside Patch, F~fel Cells 8-4 Pressure Switch Adjustment 5-8 Inspection Parts Replacement, Rigging 5-8A Main Gear 5-11 Safety System 5-6 Inspection Parts Replacement, System 5-6,I71us.5-7 Nose Gear Shock Strut 5-13 System Check. w/Safety Inspection of Fuel Tank Switch in Test Position 5-8 Vent Lines 8-1,Illus.8-3 System Maintenance Adjustment 5-8 Inspection Guide 16-1 Uplock Rollers, Lubricate 2-3 Inspection of Heat Vent System 10-2 Landing Light Circuit Installation, Aileron 4-2 Troubleshooting 13-21 Instal7ation, Front Seat 3-15 Latch Pin Adjustment, Utility Door 3-20 Instal~ation, Light Tray 2-7 L.E. Main Spar Installation 3-4 Instal7ation, Propeller Deice Boot 11-5 L.E. 6 Main spar Removal 3-4 Installation of Flared Fittings 8-5 Leather Panels 12-2A Installation of Velcro Tape Leveling 212A W/Replacement Cells 8-3 Light Bulb Replacement Guide 13-9 Installation of L.E. Main Spar 3-4 Light, Strobe 13-6 installation of Magnetos 6-7 Light Tray Installation, Wing 3-4 Installation 2-7 Instrument, Engine, Removal Removal 2-7 Installation 3-23 Limit Switch Adjustment 4-14,Illus.4-15 Instruments, Overhaul Replacement 15-3 Limit, Wear, Brake 1-40,5-1 Instrument Wedge Lighting 2-7 Limit, Wear, Track 4-14 Interior Exterior Finishes 12-1 Linkage, Brake Master Cylinder Interior Colors 12-1 Adjustment 5-2 Introduction 1-1 Load Chart, Electrical Utilization 14 Volt 13-10,13-13 J 28 Volt 13-12,13-13,13-14,13-15 Lock, Control 2-2 Jacking 2-1 Locks, Roton 2-7,Illus.2-7 Jacking, Main Wheel 2-2 Lubrication, Thread 2-8A Lubrication L Airplane 2-4A Chart 2-12,2-13,Illus.2-14 Lacquer 12-2A Uplock Rollers 2-3,5-13 Lacquer Paint Chart 12-2A Starter 13-5 Landing Gear Actuator Overhaul 5-10A,Illus.5-18 M Adjustment, System 5-8 Assembly of Main Shock Machining, Slip Ring 11-5 Strut 5-II,I~lus.5-12 Magnetos 6-5 Assembly of Nose Gear Point Gap Timing 6-6 Shock Strut 5-13,I~lus.5-14 Drop Off Check .1................ 6-5 Disassembly of Main Instal~ation 6-7 Shock Strut 5-10A,I11us.5-12 Preparation for Installation 6-6 Disassembly of Nose Gear Removal 6-6 Shock Strut 5-13 Timing 1-4B Electrical System Troubleshooting 5-20 Installation Timing 6-7 Main, Removal Installation ..I 5-10 Main Gear Removal Installation 5-10 Main, Retract Rod Main Gear Shock Strut Removal Insta77ation 5-19 Disassembly 5-10A,Illus,5-12 Maintenance, Systems 5-8 Main Gear Tolerances 5-11 Microswitch Adjustment 5-8 Main L.G. Retract Rod Motor Removal Installation 5-19 Removal Installation 5-19 Nose, Removal fnstallation 5-13 Main L.G. Shock Strut Assembly 5-11 Nose Wheel Steering Mechanism 5-19 Main Spar L.E. Installation 3-4 Overhaul Replacement 15-2 Main Spar L.E. Removal 3-4 L.G. Positionlndicator Circuit Main Wheel Jacking 2-1 B75 v BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Maintenance Overhaul Replacement Schedule 15-1 Battery 2-4 Overhaul of L.G. L.G. System 5-8 Actuator 5-16A,Illus.5-18 Prop. Blade 2-8 Overhaul. Parking Brake Wheel. Tire 5-19 Valve .......I........ 5-4A,Zllus.5-5 Master Cylinder, Brake Overhaul, Starter 13-5 Overhaul 5-2,Illus.5-4A,5-5 Overhaul Elevator Trim Tab Master Cylinder, Brake Actuator 4-2A Removal Installation 5-2 Overvoltage Relay, Adjusting 13-3 Microswitch Adjustment 5-8 Oxygen Minor Propeller Blade Cylinder 1-40 Repair 7-1,I77us.7-2 Replacement 11-1 Miscellaneous 1-40 System Miscellaneous Overhaul Purging 11-1 Replacement 15-3 Servicing 2-6 Mixture Idle Speed Adjustment 6-2,Zllus.6-3 P Mooring Anchoring Provisions 2-2 Motor Brush Replacement Guide 1-40 Painting, Aluminum 12-1 Motor, Flap, Removal Panels,Leather 12-2A Tnsta~lation 4-14A,4-148 Panels, Vinyl 12-2A Motes Gearbox, Flap, Assembly Parking Brake 2-2 Disassembly 4-16,1llus.4-17 Adjustment 5-4A Motor, L.G- Removal Installation 5-19 Parking Brake Valve Muff, Heater, Testing 10-1 Overhaul 5-4A,Illus.5-5 Muff, Heater, Removal Parking Brake Valve Installation 10-1 Removal Installation 5-2 Parts Replacement Inspection, N Main Gear 5-11 Parts Replacement Inspect~on, Navigation Light Circuit Nose Gear Shock Strut 5-13 Troubleshooting 13-21 Pitot System Nose Gear Plant, Power 1-48, 6-1 Removal Installation 5-13 Plant, Power, Overhaul Shimmy Dampener Replacement 15-2 Disassemb7y 5-15,171us.5-16 Plastic Windows, Cleaning 2-6 Table of Manufacturing Plugs, Spark 1-48 Tolerances 5-15 Position Indicator, Flap Shock Strut Adjustment 4-14A Assembly 5-13 Power, External 2-2A Disassembly 5-13,1llus.5-14 Power Plant 1-48,6-1 Tolerances 5-15 Power Plant, Overhaul Nose Wheel Travel Stop Replacement 15-2 Adjustment 5-19 Power Supply Unit, Strobe Light Removal Installation 13-8 O Preparation of Airplane Aluminum Exterior for Paint 12-1 Oil Pressure Approved, Engine 2-5 Bleed Brakes 5-1,Il7us.5-3 Capacity 1-48 Fuel Pressure Adjustment 1-48 Compressor, Level 2-48 Oil 1-48 Cooler 6-8A Adjustment 6-4,Illus.6-5 High Temperature 6-4 Relief Valve Adjust 1-40 Pressure 1-48 Switch Adjustment 5-8 Adjustment 6-4,171us.6-5 System System Servicing 2-3 Adjusting 11-13 Opening Access 1llus.3-2,3-3 Filters Order, ~iring 1-48 Primers, Exterior Interior 12-2A Outside Patch, Fuel Cells 8-4 Propeller 1-48,7-1 Overhaul, Alternator 13-3 Adjustment 7-1 vi B15 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Blade Maintenance 2-8 Rigging Elevator Blade Repair 7-1,Illus.7-1 Control System 4-2A,Illus.4-4 Deicer Rigging Elevator Trim Tab 4-2A Boot Removal Rigging Landing Gear 5-8A Installation Rigging Rudder Electric, Propeller 11-1 Control System 4-5,Illus.4-6 Governor Ring, Slip, Aligning 11-5 Adjusting 7-1,Illus.7-1 Ring, Slip, Machining 11-5 Removal Installation 7-1 Roton Locks 2-7,Illus.3-7 Inspection 16-6 Rubber Seals 2-6A Troubleshooting 11-7 Rudder Pedal Rig Tool 4-5 Publications, Supplementary Rudder Balancing 4-12,Illus.4-13 BEECHCRAFT 1-2A Rudder Control System, Rigging 4-5 Vendor 1-2 Rudder Installation ....11......... 4-5 Pump, Air Pressure 6-8A Rudder Removal 4-5 Pump, Engine Driven, Fuel 6-9 Rudder System 4-5,Illus.4-6 Purging, Oxygen System 11-1 Safety System, L.G. 5-6 Reassembly of Shimmy Schedule, Overhaul Dampener 5-16A,Illus.5-16 Replacement 15-1 Regulator, Voltage Adjustment 13-3 Sealing Chart 2-16 Relay, Overvoltage Adjusting 13-3 Seals, Rubber 2-6A Rel i n i ng Bra ke s 5-2 Seats 3-15 Removal, Aileron 4-2 Back Adjustment 3-16 Removal Installation of Third Fourth, Removal fuel Cells 8-2 Installation 3-16 Removal Installation of Fifth Sixth Removal Glareshield 3-23 Installation 3-15 Removal Installation of Front, Removal Installation 3-15 Horizontal Stabilizer 3-15 Second Window Removal Removal Installation of Installation 3-23 Utility Door 3_19 Selector Valve, Fuel, Removal Installation of Removal Installation 8-5 Vertical Instruments 3-23 Servicing 2-28 Removal Installation of Battery 2-4 Vertical Stabilizer 3-15 Brakes 2-28 Removal 8~ Installation L.G. Chart 2-15 Actuator Assembly 5-16A Fuel System 2-4 Removal, Cowling 6-1 Information 1-4C Removal, Front Seat 3-15 Oil System 2-4 Removal, Light Tray ......,...1-... 2-7 Shock Struts 2-28 Removal, Propeller Deicer Boot 11-15 Tires 2-28 Removal of L,E. Main Spar 3-4 Shaft, Flap, Removal Removal of Magnetos 6-6 Installation 4-148 Removal, Wing Tip 3-4 Shimmy Dampener 2-6 Repair of fiberglass Components 3-24 Shimmy Dampener Repairs, Exterior Paint Touch-up 12-28 Nose Gear, DiZassembly 5-15,Illus.5-16 Replacement, Brush Block, Deice 1-48 Shimmy Dampener, Replacement, Deicer Reassembly 5-16A,Illus.5-16 Brush Shock Strut, Main L.G. Replacement, Electrical Component 13-1 Assembly 5-11 Replacement Guide, Light Bulb 13-9 Disassembly 5-12,5-10 Replacement, Oxygen Cylinder 11-1 Shock Strut, Nose L.G, Reservoir, BrakeFluid 1-4C Assembly 5-13,111us.5-14 Resistance Check, Brush Block 11-5 Disassembly 5-13,171us.5-14 Resistance Check, Deicer Shock Strut Servi~ing 2-28 Rigging Aileron Single Control Column 4-1 Control System 4-2,171us.4-3 Removal Installation 4-1 B15 vii BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Rigging 4-1 Overhaul Replacement Slip Ring Alignment 11-5 Schedule 15-2 51ip Ring Machining 11-5 Position Indicator Adjustment 14-4A Spark Plugs 1-48 Shaft Removal Installation 4-14B Special Tools 1-8,1-9 Track Wear Limits 4-14 Stabilirers 3-15 Rudder 4-5,Illus.4-6 Stall Warning indicator Circuit Balancing 4-12,Illus.4-13 Troubleshooting 13-20 Removal Installation 4-5 Stall Warning Switch 1-40 Rigging 4-5,Illus.4-6 Sta71 Warning System Switch, Stall Warning 1-4C Standby Generator System 13-3 Symbols, Electrical 14-3 Starter 13-5 System, Fuel 1-4A,8-1,Illus.8-2A 8-2B Brush Replacement 13-5 System Maintenance Adjustment, Lubrication 13-5 Landing Gear 5-6 Overhaul 13-5 Removal 13-5 T Installation 13-5 System Troubleshooting 3-16 Tables Static Air System, Cleaning 11-11 Finishes 12-1 Static ir System, Testing For Leaks 11-11 Manufacturing Tolerances, Nose STatic Ground Cable Adjustment 2-8 Gear Shimmy Dampener 5-15 Stations Diagram 3-1 Thread Lubricants 2-8A Strobe Light 13-6 Torques 1-5 13-6 Tabs, Aileron 4-2 Grimes 13-8 femperature, High Oil 6-4 Strobe Light, Tail, Tests Removal Instal7ation 13-8 Deicer Continuity 11-4 Strobe Light Wing, Deicer Heat 11-4 Removal Installation 13-9 Fuel Cells Leaks 8-4 Storm Window, Static Air System Leaks 11-11 Removal Installation 3-20 Third Fourth Window Stowage, Fifth Sixth Seats 3-15 Removal Installation 3-23 Supplementary BEECHCRAFT Thread Lubricants, Table 2-8A publications 1-2A Three View 1-3,1-4,1-4A Supplementary Vendor publications 1-2 Throttle Warning Horn Publications 1-2 Switch Adjustment 6-5 Surfaces Flight Timer Check, Deicer 11-4 Controls 4-1 Timing Magneto 1-48 Aileron 4-2,111us.4-3 Timing the Magnetos to the Engine 6-7 Balancing 4-2,I71us.4-8 Tire Wheel Maintenance 5-19 Control Trimmer 4-2 Tires 2-28 Removal Installation 4-2 TIT Indicator 6-18 Rigging 4-2,I17us.4-3 Tolerances, Main Gear 5-11 Tabs 4-2 Tolerances, Nose Gear 5-15 Elevates 4-2A,Illus.4-4 Tools, Special 1-8,1-9 Balancing 4-9,1llus.4-11 Torque Wrenches 1-6 Removal Installation 4-2A Torques, Table Of 1-5 Rigging 4-2A,I71us.4-4 Torq~uing Coarse Thread Series Bolts 1-7 Trim Tabs 4-2A Torquing Fine Thread Series Bolts 1-7 Actuator 4-2A Towing 2-1 Disassemb’ly Track-Wear Limits 4-14 Assembly 4-2A,4-28,Il~us.4-4A Travel, Control Surface 1-46 flaps 4-14,1l1us.4-15 Travel Stop Adjustment, Nose Wheel 5-19 Actuator 4-148,111us.4-17 Trim Tab, Elevator Actuator Assembly Disassembly 4-16 Disassembly 4-2B,Illus.4-28,4-4A Installation Removal 4-148 Trim Tab, Elevator Limit Switch 4-14,Z1lus.4-15 Free Play 4-4C,Iilus.4-4E Motor Removal Br Installation 4-14A Rigging 4-2A Motor Gearbox Assembly Trim Tab, Elevator, Electric 4-48 Disassembly 4-16 Trimmer, Aileron Control 4-2 viii B15 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL Troubfeshooting Velcro Tape Installation with Alternator System 13-16 Replacement Cells 8-3 Autopilot 11-18 Vender Publications 1-2 Battery 13-16 Ventilation Blower 10-9 Brake System 5-20 Ventilation Heater System, Engine 6-13 Inspection 10-2 Flap Control h Indicator Circuit 13-20 Ventilation, Cabin 10-1,Illus.10-2A Fuel Quantity Indicator Circuit 13-21 Vertical Instruments 3-23 Ignition System 13-17 Vertical Stabilizer Removal L.G. Electrical System 5-20 Installation 3-15 L,G. Position Indicator Circuit 13-19 Vinyl Paint Chart 12-2 Landing Light Circuit 13-21 Vinyl Panels 12-2 Navigation Light Circuit 13-21 Voltage Regulator Adjustments 13-3 Propeller Electric Deicer System 11-7 StandbSt Generator 13-22 W Starter System 13-16 Stall Warning Indicator Circuit 13-20 Warm-up Ground Run 6-1 Warning Horn Circuit 13-19 Warning Horn, Circuit Turbocharger System 6-16 Troubleshooting 13-19 Turbine Inlet Warning Horn, Throttle Switch Temperature 1-4B,6-18,171us.6-19 Adjustment 6-5 Calibration 6-19 Warning Switch, Stall 1-40 Turbocharger 6-9,Illus.6-10 Warning System, Stall Adjustment Test 6-9 Wear Limits, Brake 1-40 5-1 Leak Test 6-10 Wear Limits, Track 4 14 Controller Illus.6-ll Wedge Lighting, ´•Installation 2-7 Freeing Turbocharger Shaft 6-12 Wheel Brake Assembly, Removal Removal 6-12 Installation 5-1 Installation 6-12 Wheel Tire Maintenance 5-19 Controller Removal 6-13 Wheel, Main, Jacking 2-1 Controller Installation 6-13 Wheel, Nose, Travel Stop Troubleshooting 6-13 Adjustment 5-19 Windows 3-20 U Cabin Door Removal Installation 3-16,3-17 L’plock Rollers, Lubricate 2-3,5-13 Forward Left Hand Utility Door 3-19 Removal Installation 3-20,3-21 Adjustment 3-19 Second Aft Half Adjustment 3-19 Removal Installation 3-23 Fwd. Ha7 f Adjustment 3-20 Storm Latch Pin Adjustment 3-20 Removal Installation 3-20 Removal Installation 3-19 Third h Fourth Utility Systems 11-1 Removal Installation 3-23 Utilization Load Chart, Electrical Windshield ~nstallation 3-21 14 Volt 13-10,13-11 Windshield Removal 3-21 28 Volt 13-12,13-13,13-14,13-15 Wings 3-4 Adjusting 3-9 V Bolts 3-10 Installation 3-4 Valve, Adjustment, Pressure Relief 1-4A Removal 3-4 Valve, Fuel Selector, Tip Removal 3-4 Removal Installation 8-5 Wiring Diagrams, Electrical 14-1 Valve, Parking Brake Wiring Diagram Index 14-2 Overhaul 5-4A,Illus.5-5 Wrenches, Torque 1-6 B15 ix not have had the required tests and inspections performed, may be different in fabrication The Bonanza 36 Shop Manual provides the factory techniques and materials, and may be recommended procedure for maintaining the Bonanza 36, dangerous when installed in an airplane. A36 and A36TC in an easy to follow, easy to locate manner. Information in the Shop Manual is directed toward Salvaged airplane parts, reworked parts helping the experienced mechanic with specialized and obtained from non-BEECHCRAFT approved more complex maintenance, while simple and repetitive sources, or parts, components, or structural procedures are given less emphasis. When necessary, an assemblies, the service history of which is illustration supplements the text for further clarification. unknown or cannot be authenticated, may have been subjected to unacceptable stresses or In all instances where no serial designations are made the temperatures or have other hidden damage; not information applies to the 36, A36, and A36TC. In areas discernible through routine visual or usual where E-r85 or later "E" serials appear, the information nondestructive testing techniques. This may will apply to both the A36 and A36TC, except when the render the part, component or structural same subject is also covered by "EA" serial designations. assembly, even though originally manufactured In the latter instance the serialized information applies only by BEECHCRAFT, unsuitable and unsafe for to its respective model. airplane use. The Shop Manual is divided into sixteen sections, with each BEECHCRAFT expressly disclaims any section devoted to a specific system or major component, responsibility for malfunctions, failures, AH pertinent information will be found in one place. damage or injury caused by use of non- BEECHCRAFT approved parts. As shop procedures and aircraft modifications warrant, revisions to the Shop Manual may be issued. Complete operating instructions for the BEECHCRAFT NOTICE Bonanza 36, A36 and A36TC may be found in the applicable Model Owner’s Manual. Beech Aircraft Corporation expressly reserves the right to supersede, cancel andlor declare To aid you in locating the information you need, an obsolete any part, part numbers, kits or alphabetical index contains multiple entries for each publication that may be referenced in this subject. manual without prior notice. The wiring diagrams for the Model 36 and A36, serials E-l thru E-709, and E-711 thru E-762 are contained within CORRESPONDENCE Section 14 of this Shop Manual. If a question should arise concerning the care Refer to the BEECHCRAFT Bonanza Wiring Diagram of your airplane, it is important to include the Manual P/N 35-590102-7 for the wiring diagrams pertaining airplane serial number in any correspondence. to the Bonanza Model A36 airplane serials E-710, E-763 The serial number appears on the model through E-1240 except E-ilrl. On Bonanza Model A36 designation placard, located inboard of the right serials E-l 111, E-1241 and after and Model A36TC serials nap on the fuselage. EA-I and after, refer to the BEECHCRAFT Wiring Diagram Manual P~N 35-590102-9. NOTE WARNING Service Publications reissues or revisions are not automatically provided to the holders of Use only genuine BEECHCRAFT or this manual. For information on how to obtain BEECHCRAFT approved parts obtained from reissues or revisions applicable to this manual, BEECHCRAFT approved sources, in refer to BEECHCRAFI~ Service Instructions connection with the maintenance and repair of No. 0250-010, Rev. IV or subsequent revisions. Beech airplanes. Genuine BEECHCRAFI~ parts are produced NOTE and inspected under rigorous procedures to insure airworthiness and suitability for use in This manual covers data on systems which are Beech airplane applications. Parts purchased standard or standard options as of the from sources other than BEECHCRA~, even publication of this manual, however not all though outwardly identical in appearance, may standard options may be designated as such. B13 1-1 SUPPLUIEHTARY PUBUCATIONS PROPELLER Following is a lisr of publications providing servicing, Overhaul Manual and Parts Catalog Manual No. 720415 overhaul and parts information on van~ous components of McCauley Industrial Corporation, Dayton, Ohio. I the BEECHCRAFT Bonanza 36, A36 and A361~C which you may obtain to supplement the Shop Manual. in most Hartteli Propeller Owner’s Manual, 1ISB. Hartzell instances, you should obtain the publications directlyfrom Propeller, Inc. Pigua, Ohio. the manufacturer or his distnbutor. Only a few, vendor manuals and Beech supplementary publications, are II availabie from Commercial Products Support, Beech Aircraft Corporation. Those which are available are listed in the current Publications Price List. Since a wide variety PROPELLER GOVERNOR of radio equipment is available and because radio manufacturers normally supply parts and servicing manual Overhaul Manual with Parts List Bulletin No. 33017 for the v;ith each set, radio publications have not been included in 35-380088 Propeller Governor. Woodward Governor the fist. Company, Rockford, Illinois. As publications on additional components become Overhaul Manual with Parts List Bulletin No. 33080 for the available, they will be added to this Iist of publications. 35-38008&1 PropelIer.Governor. Woodward Governor Company, Rockford, Illinois. YENDOR PUBLlCATIONS ENGINE MRGNET23S Service Parts Catalog Form X-30040. Teiedyne Continental Motors Aircraft Products Division, Post Office Box 90 Overhaul Instructions for Bendix S-1200 Series Magnetos Mobile, Alabama 36601. Form L-609. Scintilia Division, Bendix Aviation Corporation, Sidney, New York. Maintenance and Overhaul Manual Form X-30039. Teled~ne Continental Motors Aircraft Products Division, Service Parts List for Bendix S-1200 Series Magnetos, Post Office Box 90 Mobile, Alabama 36601, Form L-608. Scintilla Division, Bendix Aviation Corporation, Sidney, New York. Operaten Handbook Form X-30041, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90 Parts Catalog and Service Manual for Slick 400 and 600 Mobile, Alabama 36601. Series Magnetos, Form l(n0, Stick Elecuo Inc., 530 Blackhawk Park Ave., Rockford, r~ois 61101. Overhaul Manual for ISIa520 Series Aircraft Engines Form No. X-3001Z, Teledyne Continental Moron Aircraft Installation, Maintenance and Operation Instructions, Products Division, Post Office Box 90 Mobile, Alabama S6RN-201 and S6RN-205 Magnetos, Form L-526. Scintilla 36601. Division, Bendix Aviation Corporation, Sidney, New York. Operators Manual for TSIO-n0-U and -UB Engines Form Overhaul Instructions, S-600 Series Magnetos, Form L-551. No. X-M044, Teledyne Continental Motors Aircraft Scintilla Division, Bendix Aviation Corporation, Sidney, Products Division, Post Office Box 90 Mobile Alabama New York. 36601. Service Parts List, S-600 Series Magnetos, Form L-552-1. NRBOCHARGER Scintilla Division, Bendix Aviation Corporation, Sidney, New York. Overhaul Manual and Parts Catalog Form No. X-30055, Teledyne Continental Motors Aircraft Products Division, Post Office Box 90 Mobile, Alabama 36601. STARTING MOTOR FUEL IU/EC770N Maintenance Instructions Service Bulletin No. 1M-125 and Overhaul Manual and Parts Catalog Form No. X-30052. Service Test Specifications Bulletin No. rM-186, Delco- ?iledyne Continental Motors Corporation, Aircraft Remy, Anderson, Indiana Products Division, Post Office Box 90, Mobile, Alabama 36601. Parts List Group 55A. Delco-Remy, Anderson, Indiana. ~-2 B~O ALTBMrATOR A/R CONDITIONER COMPRESSOR Test and Maintenance Bulletin No. 3(3-262 and Service Model 508 Compressor, Abacus International, P.O. Box Test Specifican~ons B;Uctin No. IG-187, Deko-Remy, 3n Daltas, ~exas 75W1. Anderson, Indiana. Parts List Group 8S-J and Group 8&T(, Delco-Remy, FLIGKT CON~ROLS Anderson, Indiana ELECTRIC ELR~ATOR TRIM TAB Equipment List, Service Parts and Technical Dam OE-AI, Prestolite Service Department, Parts and Equipment Edo-Aire Mitchell, Automatic Flight Control Systems, Section, Toledo, Ohio 93601. AW63 Bulletin No. 686 or AK669 Bullerin No. 798 EDO-AIRE MITCHELL, P.O. Box 610 Mineral Wells, Service and Overhaul Instructions for Continental Texas 76067. 642056A1 Alternator. Publication No.X-30531, Teledyne Continental Motors, Aircraft Products Division, Post Office Box 90 Mobile, Alabama 36601. EATIERY ELECTRIC PROPELLER DE/CER Service Manual, Publication Number: GSM-12TI, Teledyne Battery Products. P.O. Box 431, 840 W. Brockton Ave., Installation of Deicer Boots, Report 6~707 (two blade Redlands, CA 92373. propeller), Report 6604-716A (three blade propeller). B~ E;. Goodrich Company, Akron, Ohio. AUTOPILOT B-5 Flight Control System Ground and Plight Check SUPPLEMENTARY BEECHCRAFT PUBU~ATIONS Procedures, Publication Number 3952, Brittain Industries, P.O. Box 51370 ~ulsa, Oklahoma 74151. 98-33690B Installation, Maintenance and Illustrated Pans Breakdown for the 35-?80093 and 35-380093-I Voltage B-S Automatic Plight Control System Maintenance Manual, Regulator. Pub~ication Number 3950. Brinain industries. P.O. Box 51370 Tulsa, Oklahoma 74151 9835012 Servicing Maintenance Instructions and Illustrated Parts Breakdown for the Main Wheel, Nose Wheel and B-7 Flight Control System Flight Procedures Manual, Publi- Brake Assembly. cation Number 3959, Brittain Industries, P.O. Box 51370 IfuIsa, Oklahoma 74151 9&35655 B-5 and B-7 Owners Manual Automatic Flight Control Systems. B-7 Troubleshooting Manual, Publication Number 3960, Brinain Indusln~es, PO. Box 51370 fulsa, Oklahoma 74151 9835776 Maintenance Information and Illustrated Pans Breakdown for 35-380094 Landing Gear Motor. STROEE UGH7 9835850 Electronics Components Maintenance Manual and Instruction and Senice Manual for Airguard Anti-collision Parts Breakdown B-5, B-5A, B-7, B1VII, B-VII1 Autopilot. Beacon, Publication: 50082, Bullock Magnetics Corp., Pomona. California 9836234 Installation, Maintenance and Illustrated Parts Breakdown for the 35-380093-2 Voltage Regulator. Overhaul Manual with illustrated Parts List (60-1750-3 Pow- er Supply), Publication Number: 33-40-58; Grimes Manufac- 98-36486 Overhaul Instructions for Vertical Display Engine turing Company, 515 North Russel Street. Urbana, Ohio Indicators used on BEECHCRAFT Bonanza Series 43078. ~irp]anes. Bll 1-2A 72 Ff. 27 )N. i I i kl 32 FT. 9.9 iN. W Ils41N.Dt* I ,-i-_ --------x,_ n FT. 6.6 IN. r IIjr~i5i) /8PT.51N. THRUST C~, ~7--ZC ~N.L.100 E FT. 6.4 IN. I i t 7.81..IMIN. WITn t 356" A36-H)7-(t TIRE AND SnOCK DEFLAfEDI Figure 1-1. Three View (E-l d~ru E-184) 1-3 82 12 TT. 21 IN. 33 FT. 5.5 IN, 841N. DIA. 9FT, 6.7 IN. nFf~ 5.6 IN. 8 FT. 5 IN. jCl~j THRUSf-%LL--- L~7 6 6.0 tN. 3~560 75 IN. (MIN. CLEARANCE 36607-10 WITH TIRE AND SHOCK DEFLATED) Figure I-1A. Three View (E-185 and after) 62 2.5" 33 FT. 6 IN. VERTICAL STABILIZER 12 FT. 2 IN. IN. DIA. 9 FT. 7 IN. 29.5 rrc~ i3 8 FT. 5 IN. 6 FT.: 6 IN. n~ce a --W.L. 100 ID -L___f 9.5 IN. (MIN. CLEARANCE WITH TIRE f AND SHOCK STRUT DEFLATED) 3"56 MIN. A36TC607-X) Figure 1-1B. Three View (EA-1 and atter) B10 19A GENERAL 1NFORMATION POWER PLANT OIL, SAE NUMBER Continental E-l through E-264 and Above 4.4"C (40"F) ...................................................SO IO-520-B ..............:.........,...,......~....E-266 through E-272 Below 4.4"C (400F)................,..................... 30 or 10W30 IO-520-BA E-265 and E-273 through E-1370 IO-5M´•BB E-1371 and after These 3 engines rated 285 horsepower at 2700 rpm. OUL CAPACITY Continental 12.0 qts. See item 2 of the Consumable Materials Chart. TSIO-SM-U ,........................,,...,.........................EA-1 TSIO-SM´•UB EA-2 and after CYLINDER HEAD TEMPERATURE These 2 engines rated 300 horsepower at 2700 rpm. Maximum ................................................238"C (460"F) TURBOCHARGER TURBINE INLET TEMPERATURE AiResearch TE0659 Maximum .,..............................~........................165O"F PROPELLER SPARK PLUGS E-l and after Champion RHB32N Gap: .018 to .022 RHB33E .018 to .Ou McCauiey 2A36C23/84B-0 or 3A32C76/82NB A.C. ACnl ,018 to .Ou McCauley 2A36C23-CP/84B-0 AC281 .018 to .022 McCauley 3A32C76S/84NB-2 AC273 ,018 to .022 Hartzell PHC-C3YF-1RF/F8468-6R or AC283 .018 to .022 PHC-C3YF1W84686R Hartzell BHC-C2YF-1BF/4868 or BHC-(32YF-1B14868 FIRING ORDER EA-I and after IQw MfCauIey 3A32C7~U1/82NB-2 I DEICER (GOODRICH) BRUSH BLOCK NOTE REPLACEMENT (14 Volt System) Number one cylinder is the rear cylinder on the right hand side of the engine. Replace brushes when 15/32 inch maximum distance is measured on wire inserted through inspection hole in brush support block. f6AGNETO TIMING I 22" 0" 2" (Before top center) of number 1 cylinder FUEL SYSTEM OIL PRESSURE FUEL GRADE AND CAPACITY Minimum fK~Ie) 10 psi. Operating range 30 to 60 psi. Grade: 100 LL (Blue) or 100 (Green) See Item 1 of the Maximum (cold).....................,.......................... 100 psi. Consumable Materials Chart. Capacity: OIL TEMPERATURE Standard 50 gallons (usable 44 gallons) Optional 80 gallons (usable 74 gallons) Minimum for C/5"n Recommended Minimum 38"C (tOO"F) FUEL PRESSURE ADJUSI~MENT Recommended crufse n"C (170"F) Maximum 1 15"C (240"F) See Fuel System, Section 8 or Power Plant Section 6. fdB B11 GENERAL INFOR~HATION (Cont’d) M/SCELLANEOUS (E-1371 and after) 0" full up AIRCRAFT DIMENSIONS 15"’ 1" approach 30" 0"-2" full down Overall Length 27’ 5.6" Wing Span (E-l thru E-1&l) 32’ 9.9" Aileron 20" a 2" full up (E-185 and after) 33’ 55" 20" -C 2" full down ran Height 8’5" Tread Width 9’ 6.7" Rudder 25" -C I" full left and right hopeller Diameter E-landafter 84" Elevator 23" a I" full up EA-I and after 80" 20" a 1" full down Propeller Ground Clearance E-landafter 7.5" minimum Elevator Tab Ill" a 1" full up EA-I and after 9.5" minimum 27" -C 1" fulldown BRAKE FLUID RESERVOIR tin engine accessory section) MOTOR BRUSH REPLACEMENT GUIDE Fill to I-lrr inch of top with MIL-H-5606 hydraulic fluid, 1 see Item 1~, Consumable Materials Chart. Maintain visible fluid level on dip stick. Landing Gear, Retract 5/16" minimum required Starter, Engine 3/8" minimum required BRAKE WEAR LIMITS Alternator 1/4" minimum Cleveland Replace Iinings when they are worn 3/32 inch above rivet. Minimum brake disc thickness 330 inch. SERVICE El thru E-1240 except E-llrl 100 hours100hours I AI~JUSTMENT OF PRESSURE RELIEF VALVE Battery (Lead acid) See Pressure System, Section 11. 12 volt (35 amplhour) OXYGEN CYLINDER 24 volt (11 amplhour) Fill slowly to 1850 psi at 70"F. Increase the system 3.5 psi E-llll, E-1241 and after for eve~ degree of temperature increase and decrease Main Gear Tires (7.00 x 6-6 ply) 33-40 psig 3.5 psi for every degree decrease. Nose Gear Tire (5.00 x 5-4 ply) 40 psig Oil Filter 100 hours STALL WARNING SWITCH Oil Change 100 hours Adjust 7 to 9 mph above a complete stall. Induction Air Filter 500 hours (replace) CONTROL SURFACE TRAVEL Gyro Instrument Air Filter 500 hours (replace) Main Strut Extension 3 inches Flap (E-l through E-1370) Nose Strut Extension 3-1/2 inches 0" full up Fuel System Screens 100 hours 30" 0" 2" full down WheelBearing (repack) 100 hours B11 1-4C Courtesy of Bomar Flying Service www.bomar.biz TABLE OF TORQUES ENGINE MOUNTING Engine shock mount bolts and nuts 300 to 340 in.flbs. ENGINE COMPONENTS Engine alternator 150 to 180 in./lbs. Engine starter 150 to 180 in.flbs. Engine spark plugs 300 to 360 in.flbs. Engine oil filter 18 to 30 ft.flbs. Prop spinner bulkhead bolts 85 to 90 in.nbs. Prop mounting nuts 660 to 720 in.nbs. RUDDER AND ELEVATOR Elevator horn hinge mounting bolts 50 to 70 in.nbs. Rudder mounting bolts 50 to 70 in.nbs. Rudder bell crank bolts 50 to 70 in.flbs. HORIZOMAL AND VERTICAL STABILIZER Attach bolts 50 to 70 in.nbs. WING MOUNTING (WET TORQUE ONLY) Lower forward wing attach bolt 2480 to 2600 in.nbs Upper forward wing attach bolt I 180 to 1300 in.flbs (E-~ thru E-379 except E-356) Upper forward wing attach bolt 2480 to 2600 in.nbs (E-356, E-380 and after, EA-] and after) Upper aft wing attach bolt 1180to 1300 in.nbs Lower aft wing attach bolt 1180 Ito 1300 in.nbs LANDING GEAR Main landing gear axle nut 15 to 20 ft.nbs. Nose landing gear axle nut 10 to 15 ft.nbs. Main landing gear brace bolts 180 to 200 in.flbs. Cross arm to barrel attach bolts 70 in.flbs. Main landing gear hinge bolts 250 to 800 in.nbs. Retract drag leg bolt 25 to 75 in.nbs. FUEL SYSTEM Attaching bolts for. Fuelfller 50 5 in.flbs. Fuel transmitter 25 in.nbs. BIS ´•~d TORQVE WRENCHES Example: D Desired reading Lw Length of torque wrench When a torque wrench and adapter is used, (Figure 1-2) La Adapter length compensation must be made for the extra leverage gained. T Torque New indicator readings must be calculated before the wrench is used. To figure the desired lower readings which D will actually give the torques specified, use the following Lw 33 inches formula: La II inches L 44 inches T 5, inch-pounds Original wrench length x specified torque Desired 33 x 5.000 165000 length of wrench adapter reading 33 11 44 3750 inch-pounds LSII Ln 64-17-1 Figure 1-2. Torque Wrench and Adapter An acceptable method of checking the torque if a torque When a torque wrench adapter is used, the length of the wrench is not available (Figure 1-3), is to attach a spring adapter must be added to the length of the flex or "T" scale to a conventional flex or ’T" handle inserted in an handle wrench and a value calculated for that particular adapter. Force should be applied in a direction perpcndicu- combination. The following is a typical example in finding a lar to an imaginary line extending from the center of the desired value. bolt through the spring scale attaching point. To calculate the force in pounds (scale reading) required to Effective length of flex or "T" obtain the specified torque, divide the torque in inch- handle wrench: 12 inches pounds by the distance in inches between the center of the Length of adapter............................~................3 inches bolt and the scale attaching point. For example, if the Total length.......,.............................. 15 inches specified torque is 5,000 inch-pounds and the distance is 25 Desired torque on bolt ........,..................2000 inch-pounds I inches, a pull of 200 pounds must be applied. Unless a bolt torque is specified as wet Oubricated), bolts to be torqued must be clean and free of all lubricants; otherwise, loss of normal friction allowed for establishing the torque values 2000 inch-pounds _ may result in overtorquing of the bolt. 15inches 133.3 pounds (scale reading) (LB) 90" TOE~UE (IN. LB) TOTAL LENGTH Figure 1-a. Computing Torque witk Spring Scale 60~7’2 8t3 TOROUING 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 andAN310 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 3~40 100 60 5/16-24 100-140 60-85 225 140 318- 24 160-190 95-110 390 240 7/16-20 450-500 27~300 840 500 1j2-20 480690 29(3~10 1100 660 9/16-18 800-1000 480600 1600 960 5]s-ls 1100-1300 66~780 2400 1400 3/4-16 2300-2500 1300-1500 5000 3000 7/a-14 2500-3000 1500-1800 7000 4200 1-14 3700-5500 2200-3300 10000 6000 1-1/8-12 5000-7000 30004200 15000 9000 1-114-12 900~11000 540~6600 25000 15000 hTOTE: The abore values apply to Class 3 threads, cadmium plated and nonlubricated. TOROUING COARSE THREAD SERIES BOLTS LOADED IN SMEAR TORQUE LIMITS RECOMMENDED MAXIMUM ALLOWABLE (1NCH-POUNDS) TORQUE (INCH-POUNDS) SIZE AN365 and AN310 AN364 and AN320 AN365 and AN310 AN3~ and AN320 Nuts Nuts Nuts Nuts Column 1 Column 2 Column 3 Column 4 a-32 12-15 7-9 20 12 10-24 20-25 12-15 35 21 1~-20 40-50 25-30 75 45 5/16-18 80-90 4&55 160 100 3/8-16 160-185 95-110 275 170 7/16-14 235-255 140-155 475 280 1]2- 13 400480 240-290 880 520 9/16- 12 500-700 300´•420 1100 650 sis-11 700-900 420-540 1500 900 314- ‘10 1150-1600 700-950 2500 1500 7~S-9 2200-3000 130~1800 4600 2700 I-S 3700-5000 2200-3000 7600 4500 1-ljs-s 55006500 3300´•4000 12000 7200 1-1/4-S 65008000 4000-5000 16000 10000 NOTE: The above values apply to Class 3 threads, cadmium plated and nonlubricated. 1-7 SPECIAL TOOLS i 45-590074-7 Landing Gear Tension Gage Assembly /3: 810´•3 35660040 LH. 810 33524000 8103 356600401 R.H. Rudder Check Fixture Elevator Check Fixture BLIE 81~1 50590091 81035660043-2 Aileron Travel Gage Elevator Trim Tab Jig 36590015 35590002 Tow Handle Tow Handle Replaces 34590002 35590021 fail Support Assembly ss-17´•ln 78 B5 SPECIAL TOOLS TS1253-1 (9116 inch) TSIm-4 (9116 inch) TS1222-5 (9/16 inch) 731171-2 (7/8 inch) TSlms (9116 inch) 50-590012 (9/16 inch) TS1176-2 (7/8 inch) TSlm-3 (518 inch) 50-590013 (3/4 inch) TSIm-s (In inch) Tslln-l (3/4 inch) Tslm-9 (1/2 inch) TS11761 (3/4 inch) LOWER FORWARD WING BOLT WRENCHES: UPPER AND LOWER AFT WING BOLT WRENCHES: TSlm-5 50-590012 TSlm-4 TS1222-5 TS12228 TS1222-4 TS1253-1 TSlm-8 50-590012 TS1253-1 LOWER FORWARD WING NUT TORQUE WRENCH ADAPTERS: TS1171-2 UPPER AND LOWER AFT WING NUT TS117~-2 TORQUE WRENCH ADAPTERS: 50-590013 TS1171-1 UPPER FORWARD WING BOLT WRENCHES: ITS1176-1 50-590012 (for 9/16 inch-hex) TSlm-5 (for 9116 inch-hex) TS12224 (for 9/16 inch-hex) TSlm8 (for 9/16 inch-hex) TS1253-1 (for 9/16 inch-hex) TSlm-6 (for 1R inch-hex) T51222-9 (for 1/2 inch-hex) TS1222-3 (for 518 inch-r~ex) UPPER FORWARD WING NUT TORQUE WRENCH ADAPTERS: TS1176-~ (for 3,4 inch-hex) TS1171-1 (for 3/4 inch-hex) 50-590013 (for 3,4 inch-hex) TS1‘17~-2 (for 7(8 inch-hex) TS1176-2 (for 7/8 inch-hex) 36-17-18 B13 1-9 SPECIAL TOOLS 35-590006 35-590067 ~U I Main Wheel Jack Adapter Fmings 35-590051-1 Hoisting Sling AssemMy Model 300 Service Jack 35-590009 ~hrottle Retaining Nut Wrench 3~17-19 813 BEECHCRAFT B,ONANZA 36 SERIES SHOP MANUAL GROUND HANDLING from the ground by applying his weight on the fuselage just forward of the Exercise care in ground handling of the stabilizers. Points where pushing is per- airplane to avoid unnecessary damage. The mitted are the leading edge of the wing, fol 7 owl ng procedures are provided to wing tip, and the fuselage forward of the reduce the possibility of ground damage, stabilizer leading edge. TOWING CAUTION WARNING Do not push on the propeller or the control surfaces. Do not place If the engine is warm and it is any weight on the horizontal necessary to move the propeller stabi 1 izers to rai se the nose to attach the tow bar, stand clear wheel off the ground. of the area of rotation and move the propeller against the normal To tow the airplane with a tractor or tug, direction of rotation. Make cer- attach the tow bar to the tow lugs on the tain the magneto switch is off, nose gear lower torque knee. Al way s While the engine is warm, residual observe the turn limits of the nose gear fuel in the intake ports and when making turns. Turns greater than injectors may ignite and cause the these limits can cause extensive damage engine to kick, to the nose gear. Also, exercise care when removing the tow bar from the nose gear CAUTION lower torque knee to prevent damage to the lubrication fittings on the landing gear. Never tow or taxi with a flat strut. Even brief towing or taxi- NOTE ing with a deflated strut can cause severe damage. Do not attempt to tow the airplane backward by the fitting in the NOTE tai 1 skid. This tail skid was designed only to protect the tail The top of the cabin door should in the tail-low landing and to not be used as a handhold while provide attachment for the tail entering or leaving the cabi n. ti e-down. Always open the storm window to relieve internal pressure when JACKING slamming the door. Never leave the cabi n door open on the ramp as CAUTION wing gusts may damage the door. Jacking the airplane for landing The two lugs on the nose gear lower torque gear operation should only be knee are used with the hand tow bar fur- accomplished within an enclosed nished with each airplane. One man can hangar. Should it become neces- move the airplane easily on a smooth and sary to jack the airplane in the 7eve7 surface with the tow bar. open, no more than one jack point should be utilized at a time. For CAUTION safety of personnel and the air- plane, wi nd veloci ty in any After moving the airplane, always direction must be considered pri- remove the tow bar. Never turn the or to jacking the airplane in the engine over with the tow bar open. attached to the fork, as the propeller will not clear the bar. CAUTION In a hangar and where movement is Prior to jacking the airplane, restricted, two men may pivot the airplane ensure that an unbalanced condi- on the main wheels. One man should push tion does not exist. Fuel should on the leading edge of the wing tip while be distributed evenly in both the other workman lifts the nose wheel wings to prevent an unbalanced 815 2-1 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL condition which could cause the shock strut is properly inflated to the airplane to be unstable while on correct height. If the strut is not the jacks. Make certain a suitable inflated to the recommended height, it weight is-available to anchor the will be impossible to insert the jack tail of the airplane to be jacked. adapter into the main wheel axle. A The use of a tail tiedown device scissor type jack is recommended for with suitable weight 500 pounds individual wheel jacking. such as P/N 35-590021 embedded in a movable concrete filled bar- When lowering the airplane, caution should rel or equivalent. be exercisedso that the shock strut does not become compressed and force the land- WARNING ing gear door against the jack adapter. The landing gear does not incor- CAUTION porate a rebound control assem- bfy, Do not attempt to remove the Do not walk on the wing walk with torque knees, the torque knee pins the airplane on the main wheel or the bolt connecting the torque jack. knees, when the airplane has been placed on jacks, without first ANCHORING AND MOORING PROVISIONS deflating the shock absorber assembly and supporting the gear. Three mooring eyes are provided: one in The torque knees provide the each wing and one in the tail bumper. To extension stop for the lower shock moor the airplane, chock the wheels fore absorber assembly. When they are and aft, install the control lock and tie disconnected the cylinder is free down the airplane with a nylon line or to slide out of the upper barrel chain of sufficient strength at each assembly, mooring eye. Avoid overtightening the rear fine, which pulls up the nose so that wind A three-point jack is used to lift the will create higher lift on the wings. If airplaneoff the ground. Each jack pad bad weather isanticipated, it is advis- is identified and located on the under able to nose the airplane into the wind. side of the fuselage. One jack pad is located on each 7 ower wing-to-fusel age PARKING BRAKE attachment fitting along the front spar. The rear jack pad is located under a pro- The brakes are set for parking by pulling tective cap in the middle of the fuselage out the parking brake control and at the rear fuselage carry-thru spar, The depressing the pilot’s brake pedals to rear jack fitting consists of an eye bolt pressurize the system. Do not attempt to that is screwed completely into the air- lock the parking brake by applying force plane. to the parking brake handle; it controls a valve only, and cannot apply pressure WARNING to the brake master cylinders. Be sure the rear jack point safety CAUTION pin is in place to prevent the airplane from nosing over. Do not set the parking control when the brakes are hot from When one wing is to be removed, a stand severe use or during low temper- should be placed under the opposite wing ature when a accumulation of and the tail to counteract the resulting moisture may cause the brakes to unbalanced condition of the airplane. freeze. MAIN WHEEL 3ACKING CONTROL LOCK A main wheel jack adapter is included with A control column lock pin is provided for each airplane prior to airplane serial the control column and the aileron control E-243. On serials E-244 and after, the wheel. The lock pin secures the aileron adapter is supplied as optional equipment, control wheel in neutral and the control Before raising the airplane, be sure the col umn in neutral elevator position, 2-2 B15 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL unless modification of the control gust shock strut as necessary to pass the cord lock as been accomplished per BEECHCRAFT through the center of a second phillips Service Instructions No. 0660-155 or sub- head screw directly below. Suspending the sequent issue, When this modification has plumb bob in a can or’ light engine oil been accomplished, the control wheel will will assist in stabilizing it. be rotated 120 clockwise and 2 inches forward. Existing holes in the control Late ra 1 7 evel i ng is accomp 7 i shed by column will be plugged. Ensure positive removing the front seat(s) and placing a retention of the lock pin by positioning bubble level on the spar carry-thru the attached red plate on top of the structure. Deflate the tire or strut on throttle and propeller controls. the high side of the airplane to center the bubble. HOISTING POWER The airplane may be hoisted for mainte- nance or parts replacement as follows: An external power unit with a negative ground may be used to supply power. for at Install (P/N 35-590067) hoisting ground checks, starti ng and battery sling fitting on each upper forward wing charging. The power unit may be connected attach bolt, directly to the battery or to an optional polarized external power receptacle b, Attach the sling assembly (P/N located on the lower engine cowling. The 35-590064-1) to the sling adapter. receptacle is designed for use with a standard AN type plug. c. Insta77 the strap assembly around the propeller blade shanks. The optional external power circuit is equipped with a relay and a diode to pro- d. Hoist the airplane smoothly. teet the ai rp7 ane electri cal system against damage from an external- power NOTE source with reversed polarity. Adjust the strap assembly to keep Observe the following precautions when the ai rpl ane in a 1 evel or using an external power source. slightly nose-down attitude. CAUTION e- As an added precaution, a stand may be installed under the tail of the Check whether the ai rpl ane is airplane. equipped with a 14-volt or 28-volt electrical system. If the airplane must be hoisted and the 35-590064-1 sling assembly is not avail- a. Before connecting an external able, remove the cabin door, the left power unit, turn off all radio equipment, front window and the front seats. Attach the alternator switch, and the battery a sling to the front wing spar in the switch. fuselage, and a 7ine to the hoist fitting on the engine, b. To prevent arcing, make certain no power is being applied when the con- CAUTION nection is made. A spreader must be used above the c. After the external power unit is cabin to prevent damaging the door connected, turn on the battery swi tch molding and window frame. before turning on any other equipment. Leave the battery on during the enti re LEVELING external power operation. To i evel the airplane 1 ongitudi nal ly, CAUTION attach a cord and plumb bob to the phillips head screw, located aft of the The battery may be damaged if rear window on the left side of the air- exposed to voltages higher than plane. Inflate or deflate the nose gear 15 volts (prior to E-1241 except B75 2-2A BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL E-llll) or higher than 30 volts nitrogen. The same procedure is used forl (E-llll, E-1241 and after). servicing both the main and nose gear shock struts. To service a strut proceed SERVICING as follows: Proper and periodic servicing of the air- a. Remove the air valve cap and plane will prevent considerable wear and depress the valve core to release the air greatly lengthen the service life of parts pressure. and systems involved. For points of lubrication and the correct interval and WARNING materials, refer to the Lubrication and Servi cing Charts in thi s secti on. The Do not unscrew the air valve following information gives instruction assembly until all air pressure on the servicing of major systems. has been released or it may be blown off with considerable TIRES force, causing injury to person- nel or property damage. The nose wheel tire is a 5.00-5 4-ply tire. The main wheel tires are 7.00-6 b. With the weight of the airplane 6-ply tires. Inflate the nose wheel tires on the gear, loosen the filler plug slowly to 40 pounds and the main wheel tires to to assure that all air has escaped, then 33 to 40 pounds. Maintaining proper tire remove the filler plug. inflation will minimize tread wear and aid in preventing tire rupture caused from c. With the shock strut fully sunning over sharp stones and ruts. When deflated, raise the strut barrel so that inflating tires, visually inspect them for it is 1/4 inch (nose gear strut) or 1 to cracks and breaks, 2 inches (main gear strut) from the fully compressed position. Beech Aircraft Corporation cannot recom- mend the use of recapped tires. The tires d. Fill the strut to the level of the may pass the retraction test when first filler plug with hydraulic fluid (Item 13, installed: however, recapped tires have Consummable Materials Chart). Lower the a tendency to swell after use and may strut barrel and with the strut in the cause malfunction of the retract system fully compressed position, allow the or damage to the landing gear doors. excess oil to drain out. Oil and other hydrocarbons spilled on e. Clean and install the filler plug tires not only weaken the rubber, but may and inflate the strut. The nose gear shock cause it to swell. Avoid spilling oil, strut should be inflated until 3-1/2 fuel or solvents on tires and clean off inches of piston is exposed. The main gear any accidental spillage as soon as possi- shock strut should be inflated until 3 ble. inches of the pistons are exposed. BRAKES CAUTION The brake fluid reservoir is located on If a compressed air bottle con- The reservoir should be checked pressure is used, care shouldhithe upper forward side of the firewal7. .taining air under extremely and filled to within 1-1/2 inches of the taken not to overinflate the top and visible fluid level should be strut. maintained on the dip stick at all times by adding hydraulic fluid (Item 13, Con- f. Rock the airplane gently to pre- sumable Materials Chart). vent sticking or binding the strut. SERVICING SHOCf( STRUTS g. Remove all foreign material from the exposed piston of the shock strut with The shock struts are filled with hydraulic a cloth moistened with hydraulic fluid. fluid (Item 13, Consumable Materials Chartj and inflated with dry air or 2-28 B15 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL OF LANDING GEAR UPLOCH a. Service the fuel cells with grade ROLLERS (E-283 AND AFTER,4ND PRIOR IOOLL or grade 100 or ii not available, ,4IRPLANE COMPLYING WITH SERVI CE use 115/145 octane fuel (Item I. Consum- IINSTRUCTION-S NO. 0448-211) able Materials Chart). b. Make sure the airplane is stat- The uplock roller bearing should be ically grounded to the servicing unit. lubricated with grease (Item 11, Consum- able Materials Chart), every 100 hours or c. Do not fill fuel cells near open any time that, while the wheel well is flame or within 100 feet of any open being cleaned, the bearings are subjected energized electrical equipment capable of to degreasing with solvent under pressure. producing sparks. Using a pressure gun, the uplock bearing is lubricated through a grease fitting Most fuel injection system malfunctions installed in the uplock bearing bolt. can be attributed to contaminated fuel. Inspecting and cleaning the fuel strainers NOTE should be considered to be of the utmost importance as a regular part of preventive The grease fitting on the drag maintenance. 1 eg, directly above the uplock roller bearing, does not supply Normally the fuel strainers should be lubrication for the uplock relier inspected and cleaned every 100 hours. bearing. However, the strainers should be inspected and cleaned at more frequent intervals, FUEL SYSTEM depending on service conditions, and fuel handling equipment or when operating in CAUTION localities where there is an excessive amount of sand or dust. Open the three Any time the fuel system is snap-type fuel drains daily to purge any drained or a fuel cell is empty condensed water vapor from the system. for any reason, air may enter the Each fuel cell drain is located on the system. If the possibility that bottom of the wing just outboard of the air has entered the system does root. The system low spot drain at the exist, start and operate the bottom of the fuel selector valve is engine on the ground until all air accessible through a door inboard of the is removed from the system. Oper- left wing root. ate the engine for several minutes on each tank until proper engine NOTE operation is assured. Refer to the app7 icabl e Pilot’s Operating Care should be exercised while Handbook and Airplane Flight Man- filling the fuel cell to prevent uaf before starting and operating scratching, denting, or otherwise the engine, damaging the surface or leading edge of the wing. The standard fuel cell insta~lation con- sists of a 25 gallon (22 gallon usable) OIL SYSTEM fuel cell andfiller cap in each wing leading edge. In the optional installation CAUTION a 40 gallon (37 gallon usable) fuel cell replaces each 25 gallon fuel cell. Each If metal contamination of the oil 40 gallon fuel cell contains a visual system is detected and the cause measuring tab below the filler neck to is corrected, the oil cooler permit partial filling, when desired. The should be replaced. In addition, tab bottom indicates 30 gallons of fuel flush out the system through the and the tab slot indicates 35 gallons. interconnected oil system plumb- ing and replace or clean any other When filling the airplane fuel cells, accessories that will remain with always observe the following: the engine. 815 2-3 BEECHCRAFT BONANZA 36 SERIES SHOP MANUAL The airplane is equipped with a wet sump ual circumstances. Check oil inlet oil sS’sten requiring 12 quarts of temperature during flight in determining j The oil filler cap is accessible by open- the use of the correct grade of oil. Inlet ing the left engine cowl. temperatures consistently near the maxi- mum allowable indicates a heavier oil is io drain the engine sump, remove the right needed. Use a detergent aviation grade oil hand access plate and unscrew the sump in the heaviest weight that will give drain plug in the lower right hand side satisfactory starting. Above 400F, SAE 50 of the engine crankcase. An oil drain viscosity should be used: below 400F, SAE trough, furnished with each airplane is 30 is recommended. Any detergent aviation used to conveSr the oil through the bottom grade engine oil which meets Continental of the engine cowl. Motors Corporation Specification MHS-24B is acceptable for use. ~nder normal operating conditions, the recommended number of operati ng hours BATTERP between oil changes is 100 hours. The oil filter should be removed and replaced at CAUTION each oil change. Check to confirm the voltage (14 NOTE or 28 volts) of the system. A torque of 18-20 foot-pounds 14-VOLT SYSTEM (12-VOLT BATTERY) (PRIOR should be applied to the nut of TO E-1241 EXCEPT E-llll) the oil filter when the oil filter is replaced. Ii no torque wrench The battery is located on the right side is available when the filter is of the engine comart~ment just forward of replaced, clean and lubricate the the firewall. The battery is accessible new gasket with engine oil. Then for servicing by raising the right engine turn the filter by hand to a light cowl door and removing the battery boX gasket contact. Tighten the iil- cover. Never add anything but distilled ter with a suitable wrench, three water to the battery. The water level in quarters to one full turn after the BEECHCRAFT or Gill battery should be gasket contact. maintained at 1/2 inch above the separa- tors. Never fill above this level. When operating under adverse weather con- ditions or continuous high power settings, NOTE the oil should be changed more frequently. Before draining the oil, run up the engine Do not overfill. When the battery until the oil reaches operating temper- cells are overfilled, water and ature to assure complete draining of the acid will spill on the lower oil: Oil grades 7isted in the Approved portions of the engine accessory Eng7ne Oils Chart are genera7 recommen- section and lower fuselage. dations only, and will vary with individ- 2-4 B15 28VOLI SYSTEM (24-Vo~t Battery) e. The log of battery service performed should be Mill, 8-1241 and after) evaluated to determine the need to service the battery at the above recommended intervals or to extend the intervals if A 24 volt, iiO ampere hour Teledq.ne battery is provided to justified. Accurate water consumption data is a valid baro- operate the electrical system. The battery is located on the meter to use for adjustment of the servicing intervals. right side of the engine compartment just forward of the firewall. The battery is accessible for servicing by raising the right engine cowl door and removing the battery box cover. INDUCTION A/R FILTER The battery should be maintained in a fully charged state at ail rimes and the electrolyte level checked at regular inter- The induction air filter should be cleaned periodically and vals. Never add anything but distilled water when adjusting replaced every 500 hours of service. Clean the filter as the electrolyte level in the battery. If electrolyte is added described in the manufacturer‘s instructions on the filter. each rime the level in the battery is low, a high concentration of sulfuric acid may cause dissolution of the plates. Under high temperature conditions, this may be indicated by the LUBR/CA TION presence of black particles in the electrolyte of the affected cells. A lubrication chart in this section and a lubrication diagram (Figure 2-2) contains information that ensures the proper operation and preservation of the airplane. Location, inter- NOTE val and lubricant required are given. Bearings used in pul- leys, bell cranks.hinge points, and rod-ends are of the Do not fill the battery over 318 inch above the sealed-type and do not require periodic lubrication. Avoid separators. Only lead-acid equipment should be excessive application of lubricants. used when servicing lead-acid type batteries. Do not use tools that are used on nickel-cadmium batteries. AIR CONDITIONING SYSTEM Servicing the air conditioning system consists of periodically BATTrRY MAINTENANCE PROGRAM checking the refrigerant level, checking compressor oil level. checking the compressor belt tension, and changing A systematic battery maintenance program should be estab- the system air filter. Recharge the system as outlined under Iished and carefully followed. CHARGING THE AIR CONDITIONING SYSTEM whe- never the refrigerant level is low, air has entered the system, a. The battery should be removed from the airplane or components carrying refrigerant are replaced. Refrigerant for service. leaks may be detected by inspection with a flameless leak b. A log of the services performed on the battery detector. should be maintained. c. The battery should be removed from the airplane and serviced after 100 flight hours or 30 days, whichever CHARG/NG THEAIR CONDITIONING SYSTEM occurs first. If the ambient temperatures are above ~O"F or the rime between engine starts averages less than 30 minutes, the time between servicing should be reduced. Dur- WARNING ing periods when the ambient temperature is below 32"F, the battery should be maintained in a fully charged state to A face shield should be worn when servicing the prevent freezing. When water is added, the battery should lines; refrigerant, coming in contact with the be charged sufficiently to thoroughly mix the water with the eyes, can Muse the loss of sight. electrolyte as a precaution against freezing. d. For peak performance, the battery must be kept clean and dry. If foreign materials are present in sufficient When working on a refrigerant air cooling system, observe quantities the resultant deposits may form conductive paths the following special servicing precautions. that permit a rapid self discharge of the battery. To prevent the collection of such deposits the battery should be cleaned a. Remember, this is a high pressure system. When after each 100 hours of service or every 30 days, whichever disconnecting a line, loosen the fittings just enough to bleed occurs first. off pressure slowly, then disconnect the fitting. b. Whenever a line is disconnected, purge the entire system with a vacuum pump operating at the 125 micron level. CAUT/ON c. Use only refrigerant R-12 (Item 30, Consumable Material Chart) other refrigerants, particularly those con- Excessive spewage may result if cell vents are taining methyl chloride, will cause rapid deterioration of the not kept clean and open. aluminum compressor components. 89 2-44 d. When servicing the system with refrigerant, avoid ENGINE COMPRESSOR smoking or working near an open flame. Refrigerant passing FIREWALL over an open flame will produce a highly toxic phosgene gas. e. Hook the service unit to the connections located under the copiiofs seat. When char~ing a compierely purged 5\ stem, charge with 2 pounds of refrigerant. After charging, i the sight glass should be observed for bubbles or a milky II appearance caused by an insufficient refrigerant level. if it is o served through the sight glass. COMPRESSOR i! necessar~ to add refrigerant to a partially charged system, add refrigerant slowly until a satisfactory condition is ob- FUSE OIL ENGINE F~LLER 3WZ~1 PLUG BAFFLE CHECKING COMPRESSOR O/L LEVEL r The air conditioner compressor oil level should be checked bq. a qualified air conditioner service man if the refrigerant Figure 2-1. Senricing Compressor charge is lost (evidenced by oil loss). The air conditioner s\stem requires 12-14 ounces of 500 viscosity oil (Item 31, Consumable Material Chart) to maintain 4 ounces in the compressor. bIe Pilot’s Operating Manual. Shut down engine in accord- ance with the applicable Pilot’s Operating Manual. Check the compressor oil level as follows: d. Relieve the air conditioner system pressure by loosening the compressor filler plug just enough to bleed off a. Fabricate a dipstick by bending a wire to a 90" pressure slowly. angle so that 1-Ii~ inches of the wire will insert into the e. After the system pressure is relieved, remove the compressor. oil filler plug. b. Paint the dipstick with a flat black paint. Allow f. Insert dipstick through oil filler pen. slowly rotate sufficient time for paint to dry. clutch shaft until the dipstick will insert to the bottom of the c. Start engine in accordance with the applicable Pi- compressor. lot’s Operating Manual and run the air conditioner. Run air g. Withdraw dipstick, oil should register on the dip- conditioning system for 15 minutes with the engine running stick 518 inch below filler port. Add oil as necessary to obtain a~ low rpm to allow oil to accumulate in the compressor. this measurement. Observe engine operating limitations as noted in the appiica- h. Install oil filler plug with O-ring and secure plug. 2-4B B9 APPROVED ENGINE OILS The marketers of the aviation lubricating oil listed below In listing the product names, TCM or Beech Aircraft have supplied data to Teledyne Continental Motors Corporation make no claim of verification of marketer’s indicating their products conform to all the requirements of statements or claims. Listing is made only for the TCM Specification MHS-74B, Lubricating Oil, Ashless convenience of the users. Dispersant. BRAND NAME APPROVED Phillips Petroleum Company Phillips 66 Aviation Oil, Type A Shell Oil Company Aeroshell OilW Continental Oil Conoco Aero S Texaco, Inc. Texaco Aircraft Engine Oil Premium AD Mobil Oil Company Mobil Aero Oil Castro Limited (Austraiia) Castrolaero AD Oil Pennzoil Company Pennzoil Aircraft Engine Oil Sinclair Oil Company Sinclair Avon Humble Oil g: Refining Company Esso Aviation Oil Enco Aviation Oil BP Oil Corporation BP Aero Oil Quaker State Oil Refining Co. Quaker State AD Aviation Engine Oil Delta Petroleum Company Delta Avoil Oil Union Oil Company of California Union Aircraft Engine Oil HD Gulf Oil Company Gulfpride Aviation AD B10 2-5 hTOTE CLEAIV/NG AND CARE OF AIRPLANE FINISH hlake sure that the O-ring is not twisted and that no dirt or particles are on the Oling or Do not apply wax or polish for a period of 90 days after seat. The plug should be snug. Do not deiiveIy to allow the paint to cure. Waxes and polish seal over-ti~hten plug. the paint from the air to prevent curing. For uncured painted surfaces, wash only with cold or i;kewarm (never hot) water and a mild nondetergent soap. Any rubbing of i. Charge the air conditioning system as noted in the painted surface should be done gently and held to a CHARGIhTG THE AIR CONDTTIONING SYSTEM. minimum to avoid cracking the paint film. j. Check area around filler plug for leaks. If leaks exist, do not over-ri~hten flier plug, remove plug as noted After the paint cures, wash the airplane with a mild soap in steps "c" and "d" and install a new O-ring. Secure plug and water. Flush loose dirt away first with clear water. and recharge system as noted in steps "h" and ’f". Harsh, abrasive, or alkaline soap or detergents which could cause corrosion or make scratches should never be used. OXYGEN SYSTEM Use soft cleaning cloths or chamois to prevent scratches when cleaning and polishing. Any good grade automobile To snice the o~en system, remove the protective cap wax may be used to preserve painted surfaces. To remove from the fTIler valve located below and forward of the stubborn oil and grease, use a soft cloth dampened with pilot’s and copilot’s seats. naptha. However, after cleaning with naphtha, the surface should be rewaxed and polished. NOTE Use only Aviator’s ~eathing Oxy~n, Otem 17, ENGINE CLEANING Consumable Materials Chart), when rechar_ging ´•theoxygenbottle. The engine may be cleaned with kerosene, Stoddard soivent, or any standard solvent recommended for cleaning engines. The cleaner may- be sprayed or brushed on the VYARNING engine. Wipe the engine dry; compressed air may be used to remove excessive on. I;eep fireS d~arettes, and sparks away when outlets are in use. Open and close all oxygen valves slowly. Make sure the oxygen shut-off CLEANING PLASTIC WINDOWS ~aive is in the closed position. Inspect the filier connection for cleanliness before attachingit to A commercial cleaning compound made specifically for the filler valve. I(eep tools, hands and acrylic plastic windows may be used. When using a components clean, as fire or explosion may commercial cleaner follow the instructions on the occur when pure oxygen comes in contact with container. organic material such as grease or oil. If a commercial cleaner is not available, the following instructions should be followed. Attach a hose from an oxygen recharging cart to the filler Cleaning of the acrylic plastic windows should never be valve. To prevent overheating, fin the oxygen system slowly attempted when dry. The window should first be flushed by adjusting the recharging rate with the pressure regulating with water or a mild soap solution, then rubbed slightly valve on the cart. The oxygen cylinder should be filled to a with a grit-free soft cloth, chamois or sponge. Stubbom pressure of 1850 1 50 psiat a temperature of 70"F. This grease or oil deposits are readily removed with aliphatic pressure ma~ be increased an additional 3.5 pd for each naphtha or hexane. Rinse with clear water. degree ofinaease in temperahlre; similarly, for each degree of drop in temperature, reduce the pressure by 35 psi. P;hen the oxygen system is properly charged, disconnect the filler hose from the finer valve and replace the protective cap. CA UTION Do not use thinner or aromatic abrasive NOTE cleaners to clean the windows; they will damage the surface of the plastic. Aliphatic naphtha The cylinder presnue is connected directly to and similar solvents are highly flammable, and the pressure gage on the console. extreme care must be taken when using them. 2-6 B5 CLEAN/NC INTERIOR CABIN TRIM RUBBER SEALS Proper care and cleaning of the interior cabin trim (Noryl plastics) is of primary importance to maintain a desirable Deterioration andlor sticking of rubber seals around doors. appearance. Washing the interioi cabin trim with a uindows and cowlin~s may be prevented by coating them detergent so~ and water, and brush scIubbing with a soft uith Oakite 6 compound, (product of Oakite Products. bristle brush ~in dislodge most dirt. Rinse with clean water Inc., 19 Rector St., New York 6, New York). No special and wipe dry. Alcohol mav be used to remove foreign care is required when applying the compound to keep it material that is alcohol soluable. from coming in contact with any painted surfaces. The compound is noninjurious to paint and may be removed by CA UTION employing normal cleaning methods. The interior cabin trim can be eas~y contaminated if cleaned with methyl ethyl ketone, naphtha, Mufti standard solvent, SHIMM Y DAMPENER gasoline, lacquer thinner and other types of thinnes. Sharp edges or cuts on the edge of the To check the fluid level in the shimmy dampener, insert a interior cabin trim material may cause it to wire of approximately 1/16-inch diameter througl~ the hole crack, in the disc at the end of the piston rod until it 85 2-6A touches the bottom of the hole in the floating piston. INSTRUMENT WEDGE L/GHTING Mark the uire, remove and measure the depth of insertion. (E-185 and after) Inserting the wire in the hole of the floating piston, rather than letting it Test against the face of the piston, will give a Internal lighting of the instruments provides additional more accurate check, illumination across each instrument. A light tray mounted on the top side of the bezel of each instrument holds two bulbs wired in parallel. If the light bulbs are damaged or NOTE burn out, the light tray with bulbs must be replaced. To determine if the wire is inserted in the LIGHT TRAY REMOVAL hole of the floating piston, insert the wire se~eral times, notingeach insertion depth. a. Remove the screws that secure the instrument panel H7hen the wire is correctly inserted the length in place and tilt the instrument panel aft to gain access to will be approximatel~ 1!4 inch greater than the instruments. when the wire is Testing a_gainst the face ofthe floating piston. NOTE ~hen the shimmy dampener is full, the insertion depth is Instruments located at the lower edge of the 2 3/16 inches The empty reading is 3 1/16 inches. panel may be removed if necessary to gain To add hydraulic fluid, (Item 13, Consumable Materials access to the light tray at the top of the Chart), remove the shimmy dampener and proceed as instruments. follows: a.Remove the cotter key, washer and spring from b. Remove the two screws that attach the light tray to the piston rod the instrument bezel. b. Remove the internal snap ring, scraper ring and the end seal from the aft end of the barrel. (Opposite clevis LIC;HT TRAY INSTALLATION end). c. Insert a 6/32 threaded rod into the floating piston Install the new light tray and secure in place with the and remove the piston, using extreme care when moving two attaching screws. the "0" ring seal of the floating piston past the drilled b. Install the instrument, if removed, in the instrument holes in the piston rod, panel and secure in place with the attaching screws. d. Push the piston rod to the clevis end and fll the Secure the instrument panel in place. barrel with hydraulic fluid. e. Slowly actuate the piston rod, allowing the fluid ROTON LOCKS to flow into the clevis end chamber, then return the Fgure 2-1A) I piston to the clevis end of the barrel. f. Refill the displaced fluid and replace the end seal, Usually, Roton locks will need no service. If there is a scraper ring and internal snap ring. grinding and binding in the lock as the seat reclines or g. Fill the piston rod with fluid, the return action becomes jerky, a small amount of h. Reinstall the floating piston, spring washer and cot- grease properl~i applied as follows should improve the ter pin. Spread the cotter pin to allow clearance for the operation. measuring wire. a. Use only (Item 28, Consumable Material Chart) on f-FUUYEXTENDED RETAINING SPRING GUIDE 3/4" (APPROX)- APPLY GREASE (LIGHTLY HERE ONLY) AB‘SOLUTELY NO GREASE ’SPRING GUIDE TUBE IN THIS AREA ~MAIN ASSY COUNTERBALANCE SPRING 60-314-1 Figure 2-1A. Roton Lock i 2-7 B5 1 the thread as in Figure 2-1A.Too much grease or STATIC GROUND CABLE AND ADJUSTMENT grease in the ~ilong place can cause improper operatioa (E-l through E-236) b. Compress the spring guide and counter-balance spring approximatel~vone inch. The static ground cable attached to the nose gear is de- c. Remove the retaining ring. signed to discharge static electricity on touchdown and d Relax pressure on the spring guide and counter- need not make contact with the runway as the charge will balance spring slowl~r until the spring is fully extended are from the cable. The cable should not drag on the e. Remove the lock from the fixture and remove the runway while taxiing as this may create considerable radio spring guide, counter-balance spring, and spring guide interference and lead to rapid wear of the ground cable. tube. f. Apply a small quantity of grease to the completely The following adjustment to the static ground cable is I extended thrustsnew recommended: g. Reassemble the lockFor service other than lubri- a Inflate tires to correct air pressure (see Servicing cations return the Roton lock to the manufacturer. Tires this section). b. Adjust the tip of the cable to provide 5.75 .12 PROPELLER BLADE MA/NTENANCE inches of free cable between the attaching bolt and the bottom of the cable. The cable should then be be- Due to the high stresses to which propeller blades are tween 114 to 1/2 inch from the ground. subjected, their careful maintenance is vitally import- ant, particularly on the leading edge of each blade from the tip inboard to just beyond the 33-ioch station. All nicks and scratches must be repaired before the WARNING airplane is flown. Nicks and scratches set up concentrations of stress which can exceed the strength of the blade Do not wrap or tie the static ground cable material; the result will be a crack and premature failure to the mud scraper, landing gear fork, axle of the blade. The method and limits for this type of or any other part of the landing gear. Inter- repair as outlined in the applicable Propeller Handbook ference between structure and wheel well may should be followed carefully. develop. 28 B5 TABLE OF THREAD LUBRICANTS SYSTEM MA TERIA L SPEC/FICA TIONS VENDOR PRODUCTS Any product conforming to the referenced specification may be used. Fuel Anti-Seize, Graphite hlIL-T-5544 Arrnite Product, Armite La- Petrolatum boratories, Los Angeles, Calif. Anti-seize Compound I, Esso Standard Co. Oil, hlanifold Lubricating Grease (Gas- MIL-Gd032 Zr237, Lehigh Chemical Co., Pressure oline and Oil Resistant) Chestertown, Maryland tlnti-icer, Vacuum Rockwell 950, Rockwell Mfg.. Co., New York, N.Y. Royce 32, Royal Eng. Co., Whippany, N.J. Brake, Deicer, Static Anti-Seize Compound Federal Specification Armite Product, Armite La- and Pitot White Lead Base TT-A-580 boratories, Los Angeles, Calif. Oxygen Thread Compound, MIGT-5542 No. 15 Rector Well Equip Anti-Seize and Sealing, ment Co., Houston, Texas oxygen Systems Dag 217 Acheson Colloies Co., Port Huron, Michigan Key Abso-Lute, Type B., Key Co., East St. Louis, Illinois Oxygen, High Ribbon Dope Thread MILcT-27730 Permacel Tape Corp., New Pressure Side Only Sealant Brunswick, NJ. 2-8A CONSUMABLE CHATERIALS CHART The vendor products appearing in this chart have been selected at random to help field personnel determine products conforming to the Military Specifications listed in this publication. The brand names are listed for ready reference and are not specifically recommended by Beech Aircraft Corporation. Any product which conforms to the referenced specification may be used. /TEM MATERIAL SPECIF/CATIONS VENDOR PRODUCTS i. Fuel, Engine Grade 100LL (blue) if not available use grade 100 (green) or 115/145 (purple) 2. Oil, Engine Continental Motors Corp., See Approved Engine Oils Specification No. MHS-24B Chart 3. Corrosion Pre- MIL-Cd529 Type II Anti-Corrode No. 205, Cities I venrive Compound Service Oil Co., 60 Wall Tow- (Engine Oil) er, New York 5, N.Y. Rust Foil No. 652-2, Franklin Oil and Gas Co., Bedford, Ohio Kendex No. 7038, Kendall Refining Co., Bradford, Pa. 4. Lubricating Oil MIL-La081 .Gulflite Turbojet Oil, No. 1010. Gulf Oil Corp., Pitts- burg, Pa. Aeroshell No. 3-1286, Shell Oil Co., 50 West 50th Street, New York, N.Y. 10020 Jet Engine Oil No. 1010, Texaco, Inc., 135 East 42nd Street, New York, N.Y. 10017 5 Lubricating Oil SAE 20 or SAE 10W30 6. Lubricating Oil, Aircraft MIL-L-6082 Conoco Aero Oil No. 1065, Reciprocating (Piston) Continental Oil Co., Ponca Engine (Frrst 20 City, Oklahoma to 30 hours of a new or remanufactured Phillips 66 Aviation Engine engine) Oil, Grade 1065, Phillips Petroleum Co., Bartlesville, Oklahoma Skelaite No. 100, Skelly Oil Co., El Dorado, Kansas Avrey 10V1100, Socony Mobil on Co., inc., 150 East 42nd Street, New York, N.Y. 10017 Or any approved aircraft en- gine oil [graded at 1100 (SAE 50) or 1065 (SAE 30)1. 1´•9 CONSUMABLE MATERIALS CHART (Cont~d) 17EM ~TERIAL SPECIF/CAT/ONS ~ENDOR PRODUCTS 7. Lubricating Oil (Gear) MIL-Ld086 Grade M Trojan Gear Oil No. 6086 M. Superseded by Cities Service Oil Co., 60 Wall MIL-L10324A Tower, New York 5, N.Y. Superseded by MIL-L-2105C Aeroshell Fluid 5M, Shell Oil Grade 75W or Co., 50 W. 50th Street, New 101-380016 York, N.Y. L-1195, Sinclair Refining Co., 600 Fifth Avenue, New York, N.Y. 8. Lubricating Grease MIL-G-TI;III (General Purpose) Superseded by MIL-G-813U 9. Lubricating Grease MIL-G-813U Mobilgrease 28, (Wide Temperature Mobil Oil Corporation Range) 150 E. 42nd Street New York, N.Y. 10017 Aeroshell Grease 22, Shell Oil Company One Shell´•Plaza P.O. Box 2463 Houston, TX 77001 10. Lubn’cating Grease (Gear) Mobn 636 II. Lubricating Grease MILG-238n Supermil Grease No. A72832, (Aircraft and Instruments, American Oil Co., 910 South Low and High Temperature) Michigan Avenue, Chicago, 111. 60680 Royco 27A, Roy~ Lubricants Co., P.O. Box 95,,River Road, Hanover, N.J. 07936 AerosheU. Grease 7, Shell Oil One Shell Plaza P.O. Box 2463 Houston, TX 77001 12. LubriEanr M~yWenum MIL-M-78~6B Moiykote Z. Witco Co;, Disuffide Powder Wichita, Kansas Molykote Z. Standard Oil of Kentucky Molykote Z. HaficeI Seals, Glendaie, California Moly-Paul No. 4, K.S. Paul Products Ltd., Nobel Road, London, England 3-~0 B~1 CONSUMABLE MATERIALS CHART (Cont’d) ITEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS 13. Hydraulic Fluid MIL-H-5606 Brayco 756D, Bray Oil Co., 3344 Medford Street, Los Angeles 63, California TL-5874, Texaco Inc., 135 East 42nd Street, New York, N.Y. FED 3565, Standard Oil Co. of California, 225 Bush Street, San Francisco 20, Calif. 14. Ox~gen-System Leak MIL-L-25567 Testing Compound 15. Solvent PD680 16. Lubricating Oil SAE10 17. Aviator’s Breathing Oxygen MIL-O-n210 18. Naphtha TT-N-95 19. Methyl Ethyl Ketone MIL-M-13999 20. Toluol TT-T-548 21. Paint Remover Turco No. 4260, Turco Pro- ducts Inc., Los Angeles, California 22. Epoxy Primer MIL-P-233n Ameron Industrial Coatings Division, P.O. Box 2153 Wichita, Kansas 67201 23. Wash Primer EX2016G, Ameron Industrial Coatings Division, P.O. Box 2153 Wichita, Kansas 67201 24. Zinc Chromate Primer M1L-P-8585 25. Rubber Hose MIL-H-5593 26. Oil, Engine Preservative (Refer to Item 3) 27. Graphite, Lubricating MIL-Ga;llI (Refer to Item 12) 28. Lubricating Grease ENCO ANDOK-B Humble Oil Co., Houston, Texas 29. Solvent CRC-2-26, Corrosion Reaction Consultants, Inc., Philadelphia, Pa. 2-~OA CONSUFdABLE MATERIALS CHART (Cont’d~ lTEM MATERIAL SPECIFICATIONS VENDOR PRODUCT 30. Refrigerant R-12 DuPont Inc., Freon Products Division, Wilmington, Delaware 19898 31. Oil (Air Conditioner Compres- 500 Viscosity Suniso No. 5, sor) Virginia Chemical and Smelting Co., West Norfolk, Virginia Texaco Capella E, Texaco inc., 135 East 4nd Street, New York, N. Y. 10017 32. Lubricant (Starter) Lubricant No. 1960954, Delco-Remy Division of General Motors Corp., Anderson, IN 33. Penetrating Oil Mouse Milk Worldwide Aircraft Filter Corporation, 1684 Abram Court, San Leandro, California 94571 WI)-40 Rocket Chemical Company, 9390 Napa Street, San Diego, California 34. Lubricating Grease (Wheel Aero Shell No. 5 Aero Shell No. 5, Bearing) Shell Oil Company, One Shell Plaza, P.O. Box 2463, Houston, Texas 77001 35. Anti-seize Compound MIL-A-907D 36. Coating Alodine 1200, 12008, 1201 Amchem Products Inc., Spn~ng Garden St., Ambler, Pennsylvania 19002 37. Corrosion preventive compound MIL-C-16173 Grade 2 Braycote 137, Bray Oil Co., 1925 Mar’anna St., Los Angeles, California 90032 Peuotech 1-4, Penreco, P.O. Box 671, Butler, Pennsylvania 16001 NOTES 1~ If IOOU (Blue) or 100 (Green) fuel is not available, 115 (Purple) fuel may be used as an alternate. Never use a lower grade fuel. 2. Precautions should be taken when using MiL-G-23827 and MIL-G-81322, since these greases contain chemicals harmful to painted surfaces. 3. Item 9, MIL-G-81322 grease and Item 34, Aero Shell No. 5 grease are not compatible, do not mix these greases. BtS LUBRICATION CHART ITEM NO. LOCATION LUBRICATION IMERVAL DETAIL A 1 Nose shock strut (1) M1L-H-5606 AR 2 Shimmy Dampener (1) MILH-5606 AR 3 Nose gear hinge points (2) MIL-G-813U 100 hrs. 4 Nose gear linkage (2) MIL-G-81322 100 hrs. 5 Nose gear torque knees (6) MIL-G-81322 100 hrs. "A" frame pivot points (2) MIL-G-81322 100 hrs. 7 Nose wheel bearings (2) tMIL-G-8I322, Aeroshell 5 preferred 100 hrs. 8 Nose gear swivel (2) M1L-G-81322 100 hrs. 9 Rod end fitting (1) MIL-G-813U 100 hrs. DETAIL B I Steering mechanism linkage (3) MILG-81322 100 hrs. 2 Steering mechanism (2) MIL-G-8T3U 100 hrs. DETAIL C 1 Control column linkage (18) SAE No. 20 or SAE 10W30 100 hrs. 2 Control column head (6) SAE No. 20 or SAE 10W30 100 hrs. 3 Control column aileron link (3) SAE No. 20 or SAE 10W30 100 hrs. DETAIL I) 1 Door handle (1) SAE No. 20 or SAE 10W30 100 hrs. 2 Door latch (3) SAE No. 20 or SAE 10W30 100 hrs. DETAIL E 1 Landing gear motor gearbox (1) MIL-G-81322 600 hrs. 2 Landing gear actuator gearbox (1) Mobil 636 or Compound GG* 300 hrs. 3 Rod ends (5) SAE No. 20 or SAE 10W30 100 hrs. DETAIL F I Door handle (1) SAE No. 20 or SAE 10W30 100 hrs. 2 Door latch O) SAE No. 20 or SAE 10W30 100 hrs. 3 ’*Hinge (2) MiL-M-7866B 100 hrs. DETAIL G I Flap motor gearbox (1) (Prior to E-953) MIL-G-238u 600 hrs. (E-954 and after are non serviceable) DETAIL H I Elevator bell crank (2) SAE No. 20 or SAE 10W30 100 hrs. 2 Elevator control push pull rods (2) SAE No. 20 or SAE 10W30 100 hrs. DETAIL I 1 Trim