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Oeechcraft.DUKE

1. LANDING GEAR ACTUATOR ASSEMBLY With the airplane jacks and the retraction cycle started enough to break the downlock tension apply a sharp load by hand an aft direction against the nose gear strut If this causes the main gear wheels to move approximately 1 2 to 1 inch it is a good indication that the gear actuator assembly needs overhaul and or adjustment i LANDING GEAR GEARBOX AND ACTUATING LINKAGE Check for leakage wear condition and attachment Check for unu sual noise Check oil level by engaging and turning the emergency handcrank 1 2 turn to determine that oil is being picked up on the worm gear The oil level should be maintained no more than necessary to cover 1 2 of the diameter of the worm gear Check actuator gearbox motor and switches for leakage condition and security DOORS Check door operation fit and fair Check for unusual noise 5 20 00 Page 222 20 87 a 1 on 18 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL LANDING GEAR OPERATION Cont d GENERAL OPERATION Cycle the landing gear while check ing to ascertain that the position light switches oper ate jn conjunction with the landing gear position Check the condition and operation of the complete landing gear system as outlined in Chapter 32 30 00 POSITION LIGHTS Check for security adjustment wiring for breaks condition of insulation loose connection
2. PRACTICES z Adjust Up to 25 STALL WARNING INDICATOR REMOVAL a Remove the four screws attaching the doubler and indicator to the lower wing leading edge b Disconnect electrical wires at the indicator and heater switches STALL WARNING INDICATOR INSTALLATION a Connect the electrical wires to the indicator and heater switches b Position the indicator in the opening in the lower wing leading edge install the doubler and the four screws c Adjust the indicator See STALL WARNING INDICATION SYSTEM ADJUSTMENT STALL WARNING INDICATING SYSTEM ADJUSTMENT Figure 201 The stall warning switch is carefully adjusted when the airplane is test flown at the factory Should it require readjusting proceed as follows Locate the switch installation on the under surface of the left wing leading edge and loosen the two phillips head screws one on either side of the vane If the stall warning has been coming on too early puli the vane back and down If the stali warning has been coming on too late push the vane up and forward Moving the vane with the phillips head screws loosened moves the entire unit up or down inside the wing causing the switch to be closed earlier or later Retighten the screws after making each adjustment NEVER TRY TO ADJUST THE SWITCH BY BENDING THE VANE Actuate Sooner Adjust Down to Actuate Later 60 251 11 Stall Vane Adjustment Figure 201 As a rule of thumb moving the vane 7 4 in
3. 10 PARKING AND MOORING 00 General 11 PLACARDS AND MARKINGS 00 General 12 SERVICING 00 General 10 Replenishing 20 Scheduled Servicing AIRFRAME SYSTEMS 20 STANDARD PRACTICES AIRFRAME o Standard Practices Airframe INTRODUCTION Page 3 A14 K Nov 30 83 SYSTEM CHAPTER 21 23 24 25 26 INTRODUCTION Page 4 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SUB SYSTEM SECTION TITLE AIR CONDITIONING 00 General 10 Compression 20 Distribution 30 Pressurization Control 40 Heating 50 Cooling AUTO FLIGHT 00 10 Autopilot H14 1 Autopilot New Matic COMMUNICATIONS 60 Static Discharging ELECTRIC POWER 00 General 30 DC Generation 31 DC Generation Battery 32 DC Generation Charge Current Detector 40 External Power 50 Electrical Load Distribution EQUIPMENT FURNISHINGS 00 General 60 Emergency FIRE PROTECTION FLIGHT CONTROLS 00 General 10 Aileron and Tab 20 Rudder and Tab 30 Elevator and Tab 50 Flaps 60 Spoiler Drag Devices and Variable Aerodynamic Fairings 70 Gust Lock and Dampener FUEL 00 General 10 Storage 20 Distribution 40 Indicating 14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SYSTEM SUB SYSTEM CHAPTER SECTION TITLE 30 ICE AND RAIN PROTECTION 00 General 10 Airfoil 20 Air intakes 30 Pitot and Static 40 Windows and Windshields 60 Propellers Rotors 32 LANDING GEAR 00 General 10 Main G
4. SETSCREW CABLE DRUM SHAFT i CLUTCH ROTOR E pad m fJ 010 to 015 CLUTCH 2 ARMATURE COVER CABLE RETAINING PIN CABLE DRUM 60 364 1 Electric Trim Tab Actuator Figure 202 cable in the same position This will ensure adequate free cable on the drum in both directions to allow full travel of the cable stops Check cable travel as instructed step e of the ELECTRIC TRIM TAB ACTUATOR INSTALLATION ELECTRIC TRIM TAB ACTUATOR MAGNETIC CLUTCH REMOVAL Figure 202 a Remove the lid from the clutch housing b Loosen the set screw in the clutch rotor and armature hubs c Remove the motor from the clutch housing d Slide the cable drum and shaft assembly from the clutch housing e Remove the clutch from the clutch housing ELECTRIC TRIM TAB ACTUATOR MAGNETIC CLUTCH INSTALLATION Figure 202 a Install the clutch in the clutch housing b Slide the cable drum and shaft assembly into the clutch housing C Tighten the clutch armature set screws until there is no visible end play in the cable drum shaft Slide the clutch rotor on the motor shaft to obtain 010 to 015 inch clearance between the friction surfaces of the clutch before tightening the set screws Stake both set screws CAUTION With no visible end play in the cable drum shaft the clutch faces must not make contact while the clutch is de energized or damage t
5. CERT FUEL 80057 J G o TURN AND SLIP 5 FLAP AND LANDING GEAR INDICATORS ANNUNCIATOR j CABIN PRESSURE CONTROL SURFACE DEICE O RIGHT WINDSHIELD OEICE IF INSTALLED OVERVOLTAGE RELAYS LEFT FUEL VENT HEAT PO PITCH TRIM HOUR METER O ONCEONCBLONC C ICONE C EE Ee CO p 94 THROUG S iH 51 6 S S S S LANDING GEAR WARN LEFT WINDSHIELD DEICE CONTROL JS PROPELLER DEKE 5 RIGHT FFIGT WERT oP 62 AND AFL ER b DMSTALL WARNING D FLAF AND LANDING GEAR NOIEATURS AND is MOTOR prese STARTER AND IGNITION p PA THROUGH P 61 PILOT S INSTRUMENT LIGHTS 7 P 62 AND AFTER 1 O ROTATING BEACON P 62 ANO AFTER LANDING GEAR RIGHT LANDING LIGHT RIGHT CYLINDER HEAD TEMPERATU RIGHT FUEL VENT HEAT LANDING GEAR WARN D NAVIGATION LIGHTS ANNUNCIATOR D FUEL FLOW O HOUR METER O AUTOPILOT PITCH TRIM O PAOPELLER SYNCHRONIZER O CEFT WINDSHIELD ANTI ICE CONTROL O PROPELLER DEICE RIGHT PITOT HEAT 0 603 2 Power Distribution Schematic P 4 thru 445 Figure 202 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL BATTERY RELAY BATTERY SWITCH ON x LIMITER BATTERY CHARGE CURRENT SENSOR OFF 4 LEFT LEFT STARTER STAR
6. EXTERNAL POWER EXTERNAL POWER RFCFPTACLE RELAY CONTROL RIGHT STARTER RELAY RIGHT STAATER i LOADMETER e REVERSE RIGHT 1208 CURRENT GFNERATOR 9 900 t t VOLTAGE REGULATOR voci D OVER VOLTAGE RELAY UNLEFTNACELLE O t32 vuc AA 120A ALA WIN if LU LEFT WINDSHIELD ANTI ICE iNVEHTER ANTI I E AVIONS UF INSTALLED STANOBY INVEHTER LEFT AVIONICS ELECTRICAL POWER AVIONICS POWER CONTROL BUS RIGHT POWER O AVIONICS 2A 25 IST AND JRO ROW ZND ANO 4TH ROW BUS 25 5 o O O 2 AVICNICS CIRCUIT AVIONICS CIRCUIT O O O pare a BAEAKER BREAKERS 50 50 AVIONICS POWER CIRCUIT 9 Y 9 BREAKERS ARE ACCESSABLE sus aus BUS BUS TO PILOT ON ASU AIRCRAFT ONLY NOZ NO 1 NO 2 SERIALS P 243 THAU P 445 AVIONICS ANO THOSE PRIOR AIRCRAFT MASTER OFF WHICH HAVE INSTALLED SWITCH KIT PN GO 3005 4 THROUGH PG 34 oo CROTATING BEACON H S LEFT LANDING LIGHT TAXI LIGHT COPILOT S INSTRUMENT LIGHTS 17 P 62 AND AFTER CABIN TEMPERATURE CONTROL I LEFT CYLINDER HEAD TEMPERATURE LEFT COWL Fi AP LEFT FUEL VENT HEAT LEFT FUEL QUANTITY LEFT FUEL BOOST PILOT S INSTRUMENT LIGHTS INSTRUMENT FLOOD LIGHT ICE LIGHT 24 50 00 Page 202 May 12 78 4 THOUGH P 61 1 5
7. 8 PLUMBING Check for leakage chafing condition and security ELECTRICAL WIRING AND EQUIPMENT Inspect for chafing damage security and attachment FLAP LIMIT SWITCHES Check for condition security and freedom of operation FLAPS AND ACTUATORS Check for condition security binding or chafing of actuator cables Check flap skin and structure for cracks loose or missing rivets Check roller bearings and tracks for condition Check stop area for condition and damage FLAP POSITION TRANSMITTER Check for security and oper ation DRAIN HOLES Check the drain holes in the left and right upper wing attach fittings to assure that they are open and free of obstruction 5 20 00 Page 212 Nov 20 87 INSP Al BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL D WINGS AND CARRY THROUGH STRUCTURE Cont d MECH INSP WING SPAR CAP Inspect the wing spar cap for corrosion as outlined in Chapter 57 00 00 WING BOLTS Check wing bolts for proper torque at the first 100 hour inspection and at the first 100 hour inspection after each reinstallation of the wing attach bolts Refer to Chapter 57 00 00 for wing bolt nut and fitting inspection criterion and frequency STALL WARNING VANE Check for condition and obstructions 17 FUEL QUANTITY TRANSMITTER Check for attachment and electrical connection 18 NAVIGATION LIGHTS Check fo
8. 80 00 1 ES 1 oh BS W L 74 58 zn nw 1 136 51 114 155 25 00 57 40 67 00 109 50 19 00 127 50 128 00 148 00 113 50 WS NN 3 6 39 375 36 030 D 2n 129 150 3 123 182 e na 228 000 198 000 175 437 7 136 168 113 1 m 48 475 D 221 000 203 500 191 000 175 294 162 563 22 j FRONT SPAR FUS STA 138 00 pre SPAR FUS STA 113 50 12 000 0 000 W L 197 08 W L 185 04 105 578 90 760 W L 159 5 FUS STA 336 939 1 W L 128 00 Wek 022 00 P 1 s 020 12 250 Emm 329 00 60 602 10 6 00 00 2 Nov 2 73 Stations Diagram Figure 2 END f CHAPTER SECTION SUBJECT 7 EFFECTIVITY CONTENTS 7 00 00 SUBJECT LIFTING AND SHORING Description and Operation Jacking BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 7 LIST OF PAGE EFFECTIVITY PAGE CHAPTER 7 LIFTING AND SHORING TABLE OF CONTENTS END CHAPTER SECTION SUBJECT 7 00 00 DATE Oct 27 75 Oct 27 75 PAGE 7 EFFECTIVITY CONTENTS Page 1 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL LIFTING AND SHORING DESCRIPTION AND OPERATION JACKING CAUTION Prior to jacking the airplane ensure that an unbalanced condition does not exist Fuel should be distributed evenly in both wings to prevent an unbalanced condition which could cause the airplane to be unstable while on jacks A three point jack is used to lift the
9. 202 Cofisumable Materials Chart 203 Servicing Chart 204 Lubrication Schedule Fuselage Access Openings Wing Access Openings Special Tools END 14 201 201 201 201 201 202 202 202 202A 202A 203 203 203 212A 214 224 226 12 CONTENTS Page 1 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL DESCRIPTION AND OPERATION applicable following chapters For overhaut procedures for components of a system refer to the BEECHCRAFT Duke 60 The information in this chapter pertains to genera servicing Beech Manufactured Components Maintenance Manual P N procedures and maintenance practices used when servicing 60 590001 27 For electrical wiring diagrams refer to the the various systems of theairplane Detailed maintenance BEECHCRAFT Duke 60 Wiring Diagram Manual P N 60 information pertaining to these systems wili be found in the 590001 29 12 00 00 1 19 77 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL REPLENISHING MAINTENANCE PRACTICES FILLING THE FUEL CELLS NOTE Because the deice boots are made of soft flex ible material care must be exercised against dragging gasoline hoses over them or resting ladder or platforms against the surface of the boots The fuel system installation consists of an inboard main fuel and an outboard cell in the leading edge tank a wing pane fuel celi in each wing and a wet wing tip tank op
10. A60 604 8A 12 20 00 Page 215 Nov 2 73 IT ZN BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 Cont d LUBRICATION SCHEDULE LOCATION LUBRICANT INTERVAL LANDING GEAR ACTUATOR DETAIL C Landing gear motor gear box 1 MIL G 81322 t Landing gear actuator gear box 1 Mobile Compound GG DETAIL t When properly filled the oi level ona dip stick inserted through the filler hole will be approximately inch DETAIL D LOCATION LUBRICANT INTERVAL FLAP ACTUATOR DETAIL D Flap motor gear box 1 MIL G 23827 Flap actuator 2 MIL L 6086 Grade M 12 20 00 Page 216 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 Cont d LUBRICATION SCHEDULE INDEX LOCATION LUBRICANT INTERVAL RUDDER TRIM DETAIL E Rudder trim tab actuator 1 MIL G 23827 tRudder trim tab hinge 1 MIL M 7866 t Mix MIL M 7866 with naptha and apply with a brush DETAIL E DETAILF INDEX LOCATION LUBRICANT INTERVAL ELEVATOR TRIM DETAIL F Elevator trim tab actuator 1 MIL G 23827 tElevator trim tab hinge 1 MIL M 7866 tMix MIL M 7866 with Naphtha and apply with a brush A amp 0 604 108 12 20 00 Page 217 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 Cont d LUBRICATION SCHEDULE LUBRICANT INTERVAL INDEX LOCATION AILERON BELL CRANK DETAIL G bell crank 6 SAE10W 30 DETAIL G DETAIL H INDEX LOCATION LUBRICANT INTERVAL AILERON
11. DIFFERENTIAL CONTROL VALVE AND SAFETY VALVE PRIOR TO 308 A differential control valve and a safety valve are located on the forward side of the afi pressure bulkhead 4 On airplane serials P 247 and after the outflow valve and safety valve are mounted within a box structure which is a portion of the aft pressure bulkhead The differential control valve regulates cabin pressure up to maximum differential pressures of 4 6 to 4 7 psi A diaphragm in the valve controlled by the cabin altitude control closes but allows a preset amount of cabin air to bleed off into the tai section through an adjustable bleed valve This maintains the selected cabin altitudes up to maximum differential pressure The differential control 21 30 00 Page 4 May 30 75 feature of the valve maintains cabin pressure at maximum differential pressure 4 6 to 4 7 psi only The differential control utilizes a diaphragm that applies pressure against a spring loaded needie valve When cabin pressure reaches maximum differential pressure the diaphragm pushes against the needle valve allowing cabin air to bleed off into the section As cabin air bleeds off the diaphragm alows the needle valve to return to its normal position thus the diaphragm modulates the needle valve between the open and closed position to maintain the proper pressure Onsserials P 3 through P 126 except P 123 the safety valve incorporates a solenoid valve which
12. Obstruction in servo lines d Faulty turn coordinator gyro Low system pressure setting a Aircraft out of trim or a improperly rigged Loose primary cables or b excessive friction in cables and system Loose servo cable Defective turn coordinator gyro Leak in servo or servo d line REMARKS Check all lines and fittings for breaks looseness kinks etc Adjust regulator valve as outlined in Chapter 36 Adjust regulator as outlined in Chapter 36 Replace pump Clean or replace filter Check filters as outlined in Chapter 36 and replace if necessary Adjust regulator valve as in Chapter 36 Check security of attachment binding etc and adjust as outlined in Chapter 27 Check for leaks Check for foreign matter Replace turn coordinator Check system filters and adjust as outlined in Chapter 36 Trim aircraft or check controls for proper rig as outlined in Chapter 27 Check security of attach ment binding etc and adjust as outlined in Chapter 27 Replace turn coordinator gyro Check for servo or line ome 22 11 00 Page 101 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING TROUBLE ROLL AXIS Cont d NEW MATIC AUTOPILOT Cont d PROBABLE CAUSE REMARKS 5 Aircraft rate of turn Improper regulator Adjust regulator as outlined too fast or too slow adjustment in Chapter 36 Turn coordinator faulty Replace turn coordinato
13. j Stow the portable antenna CAUTION Exercise extreme care in order to avoid damage to the antenna or the plastic tab on the upper end k Install the transmitter in th airplane and secure the mounting strap 1 Connect the fixed antenna cabl to the ELT Ensure that the plastic contact separator is inserted between th portable antenna contact and the portabl antenna NOTE Without the contact separator in place a very weak signal may be transmitted This signal may be strong enough for a functional test but too weak for emergency use Al BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL m Connect the remote switch wiring if installed to the terminals on the ELT n Press the RESET button and place the ARM OFF ON switch on the ELT in the ARM position o The new replacement date should be marked on the ELT in a visible area This will aid in future inspections of the ELT This date is 50 of the useful life of the battery as defined by the battery manufacturer TESTING EMERGENCY LOCATOR TRANS MITTER Generally tests will be performed fol lowing maintenance or repair of ELTs other than battery replacement to deter mine their operational capability Test ing the ELT if improperly done could trigger false alerts and create frequency jamming and may interfere with the recep tion of a bonafide emergency transmission PORTABLE ANTENNA CONTACT FINGER Federal Communications Co
14. 11 12 12 20 00 Page 208 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 202 Cont d CONSUMABLE MATERIALS MATERIAL SPECIFICATIONS VENDOR PRODUCTS Lubricating Grease MIL G 7711 Superseded by MIL G 81322 see item 9 Lubricating Grease MIL G 8 322 Mobilgrease 28 Mobil Oil Corporation NOTE Shoreham Building MIL G 81322 is not compatible with Washington D C 20005 Aerosheli No 5 and contains chemi cals harmful to painted surfaces Aeroshell Grease 22 Shell Oil Co 50 West 50th Street New York N Y 10020 Lubricating Grease Gear Mobile Compound G G Lubricating Grease MiL G 23827 Supermil Grease Aircraft and Instruments No A72832 American Low and High Temperature Oil Co 910 South s Michigan Avenue NOTE Chicago Ill 60680 Precautions should be taken Royco 27A Royal Lubri when using MIL G 23827 and cants Co River Road MIL G 81322 since these greases P O Box 95 Hanover contain chemicals harmful to N J 07936 painted surfaces Shell 6249 Grease Shell Oil Co 50 West 50th Street New York 20 N Y Lubricant Molybdenum MIL M 7866 Molykote Z Wilco Co Disuifide Powder Wichita Kansas Molykote Z Standard Oil of Kentucky Molykote Z Haskell Engineering and Supply Company 100 East Graham Place Burbank California 91502 Moly Paul No 4 K S Paul Products Ltd Nobel Road London England A14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 2
15. 44 140 130 120 RESISTANCE OHMS no 100 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL nudi Soe 3 ILE ne 11 c Li MENE 1 SS E 40 404 TEMPERATURE F Temperature Resistance Curve for Outside Air Sensing Element The resistance on the ohmeter should increase 250 ohms If the resistance increase is higher or temperature control rheostat is defective f Reinstall all disconnected wires to their respective terminals Figure 205 FUEL PUMP lower the cabin An electric fuel pump located in the LH wing stub provides fuel to the heater at a pressure of 7 psi A solenoid operated fuel regulator regulates fuel pressure and acts as a remote shutoff for the heater regardless of fuel intet pressure variations END 21 40 00 Page 205 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL COOLING DESCRIPTION AND OPERATION The optional air conditioning system is a recirculating air cooling system containing a 16 000 BTU refrigerative type cooler The unit is controlled by an automatic temperature control and three sensing elements A six position mode switch controls the heater and air conditioner systems however each system operates independently of the other When placed in AUTO position the temperature is automatically controlled through the temperature controller located on the forward p
16. 57 00 00 38 30 00 21 40 00 21 40 00 21 10 00 21 50 00 21 50 00 21 50 00 12 10 00 21 50 00 12 10 00 21 50 00 21 50 00 21 50 00 21 50 00 91 00 00 12 20 00 27 00 00 21 00 00 27 00 00 27 00 00 21 30 00 21 30 00 21 50 00 71 10 00 71 10 00 71 10 00 71 10 00 71 10 00 24 00 00 28 00 00 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM OR SYSTEM NAME DEICER BOOTS DEICER BOOTS RESURFACING DEICER SYSTEM AIRFOIL OIF CONT amp SAFETY VALVE ADJUSTMENT OIF CONT amp SAFETY VALVE INSTALLATION DIF CONT amp SAFETY VALVE REMOVAL OIFFERENTIAL CONTROL VALVE OIMENSIONS AIRCRAFT DISTRIBUTION ELECT TRIM TAB ACT MAG CLUTCH INST ELECT TRIM MAG CLUTCH TEST ELECT TRIM TAB ACT MAG CLUTCH REMOVAL ELECTRIC TRIM TAB ACTUATOR INSTALLATION ELECTRIC TRIM TAB ACTUATOR REMOVAL ELECTRIC TRIM TAB CABLE INSTALLATION ELECTRICAL UTILIZATION LOAD CHART ELEVATOR BALANCING ELEVATOR CABLE INSTALLATION ELEVATOR CABLE REMOVAL ELEVATOR CONTROL SYSTEM RIGGING ELEVATOR INSTALLATION ELEVATOR REMOVAL ELEVATOR TRIM TAB ACTUATOR INSTALLATION ELEVATOR TRIM TAB ACTUATOR REMOVAL ELEVATOR TRIM TAB CABLE INSTALLATION ELEVATOR TRIM TAB CABLE REMOVAL ELEVATOR TRIM TAB RIGGING ELEVATOR TRIM TAB CHECKING FREE PLAY ELT COLLINS COMM COMP CORP ELT BATTERY REPLACEMENT NARCO EMERGENCY LOCATOR TRANSMITTER EMPENNAGE ENGINE AIR INDUCTION SYSTEM ENGINE 8UILO UP ENGINE GROUND
17. AUG 15 80 BEECHCRAFT OUKE 60 SERIES MAINTENANCE MANUAL ALPHABE TICAL INDEX COMPONENT ITEM CHAPTER CHAPTER 8 OR SYSTEM NAME NAME SUB CHAPTER STRUCTURAL REPAIR STRUCTURES 51 00 00 SURFACE DEICER BOOT INSTALLATION ICE AND RAIN PROTECTION 30 10 00 SURFACE DEICER BOOT REMOVAL ICE RAIN PROTECTION 30 10 00 SURFACE DEICER COMPONENT LOCATION ICE RAIN PROTECTION 30 10 00 SURFACE DEICER COMPONENT REPLACEMENT ICE RAIN PROTECTION 30 10 00 SURFACE DEICER SERVICING ICE AND RAIN PROTECTION 30 10 00 SYNCHRONIZER CHECKS PROPELLERS 61 00 00 SYNCHRONIZER FLIGHT CHECKS PROPELLERS 61 00 00 SYNCHRONIZER FUNCTIONAL TEST PROPELLERS 61 00 00 SYNCHRONIZER RIGGING PROPELLERS 61 00 00 SYNCHRONIZER WIRING CHECK PROPELLERS 61 00 00 TABLE OF TORQUES CHARTS 91 00 00 TEST EQUIPMENT AIR CONDITIONING 21 30 00 TEST OUTFLOW amp SAFETY VALVE AIR CONDITIONING 21 30 00 TEST PROCEDURE P 4 amp AFTER AIR CONOITIONING 21 30 00 5 PRESSURIZATION LEAKAGE AIR CONDITIONING 21 30 00 THREAD LUBRICANTS CHARTS 91 00 00 THREAD LUBRICANTS CHART SERVICING 12 20 00 TIRES LANDING GEAR 32 40 00 TIRES SERV ICING 12 20 00 TIT INDICATOR CALIBRATION ENGINE INDICATING 77 00 00 TOILET CHEMICAL CLEANING WATER WASTE 38 30 00 TORQUE WRENCHES STANDARD PRACTICES AIRFRAME20 00 00 TORQUING COARSE THREAD BOLTS CHARTS 91 00 00 TORQUING FINE THREAD BOLTS CHARTS 91 00 00 TOWING AIRCRAFT TOWING TAXING 09 00 00 TRIM TAB FREE PLAY CHECK AILERON FLIGH
18. BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL DC GENERATION MAINTENANCE PRACTICES GENERATOR REMOVAL a Remove the lower engine cowling b Remove the generator wiring c Remove the generator cooling air duct d Remove the bolt from the adjusting bracket and loosen the attaching bolts of the mounting bracket until the generator can be rotated to permit removal of the drive belts from the generator e Remove the attaching bolts and remove the generator from the airplane GENERATOR INSTALLATION a Secure the generator to the mounting brackets with the attaching bolts Leave the bolts loose enough to ailow the generator to rotate sufficiently to install the drive belts NOTE To equalize belt service life the belts must be replaced in pairs b install the and washer in the adjusting bracket c Position the generator in the mounting brackets so that a four pound pressure applied at the center of the belts will result in 1 4 inch deflection Tighten the attaching bolts to a torque of 160 to 190 inch pounds d Safety as necessary e Attach the generator cooling air duct Attach the electrical wiring and tighten securely GENERATOR BRUSH REPLACEMENT During periodic maintenance inspections the generator bru shes should be inspected for cracks chipped edges loose or frayed wire A lateral groove in the edge of the brush is an indication of the minimum wear length approximately 1 2 inch THe brush sho
19. Do not level electrolyte on new battery prior to charging CONNECT BATTERY CORRECTLY TO CHARGER CHARGE BATTERY Constant current recommended MEASURE END OF CHARGE VOLTAGE REST BATTERY 2 TO4 HOURS CHECK ELECTROLYTE LEVEL CLEAN AND CHECK AIRCRAFT S BATTERY CONNECTOR INSTALL BATTERY CHECK AIRCRAFT S BATTERY CHARGER SYSTEM Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PREVENTIVE MAINTENANCE CHECKLIST CLEAN BATTERY INSPECT FOR VISIBLE DAMAGE WASH VENT CAPS C RECONDITION DISCHARGE AND SHORT CONSTANT CURRENT CHARGE MEASURE END OF CHARGE VOLTAGE REST BATTERY 2 TO 4 HOURS LEVEL ELECTROLYTE MEASURE ELECTRICAL LEAKAGE V a A DISCHARGE MEASURING CAPACITY Aithough slower the constant current method is the recommended way of charging the battery Most shops are equipped with constant current chargers In cases where the chargers are limited to 6 ampere capability it will be necessary to start the charge of most batteries at a lower rate than recommended on the battery nameplate If a reduced rate is used a longer charging time is required The constant current method is much more effective in correcting cell imbalance and temporary loss of capacity and it permits easy computation of the charge capacity in ampere hours When using this method one must usually monitor and maintain the constant current by manually adjust
20. Nose Wheel zOlean with solvent and Well 1 zbtow dry with air pressure Lower wing surface 2 Lower wing surface 2 Lower wing surface 2 Aft bulkhead of nose wheel well On uphoistery panel below copilot s subpanel 1 AH rear side of nacelle 2 P 3 through P 159 except P 158 AH rear side of nacelle 2 P 158 P 160 and after Forward side of aft engine bafile P 247 and after AH rear side of each engine 2 Mounted on controller behind RH subpanel Aft fuselage INTERVAL Every 1000 hrs Every 100 hrs At Oil Change Every 100 hrs of heater operation Every 100 hrs of heater operation Every 100 hrs of heater operation Preflight Preflight Preflight Preflight Every 100 hrs Every 150 hrs Every 300 hrs Every 300 500 hrs Every 500 hrs Every 1000 hrs Every 1000 hrs 14 ITEM REPLACE Cont d Emergency Locator Transmitter ELT Battery SERVICE Brake Fluid Reservoir Oxygen Cylinder Main and Nose Landing Gear Struts BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 203 Cont d SERVICING LOCATION Aft fuselage Forward baggage compartment 1 Forward baggage compartment 1 Top of each strut 3 SERVICE WITH MIL H 5606 hydraulic fluid MIL O 27210 aviators breathing ox ygen MIL H 5606 hydraulic fluid and compressed air Indicates number of points to be serviced INTERVA One half of bat t
21. defective REMARKS Replace ignition assembly If vibrator is in good condition replace ignition assembly only Remove nozzle for cleaning or replacement Tighten or replace the nozzle as required Check fuel supply through ali components from the tank to the heater Make necessary corrections Check adjust or replace switch Check or replace switch Adjust or replace the switch Attach external power Remove and replace solenoid assembly Check and repair Replace the MASTER switch Repair Remove obstruction or repair Repair or adjust Replace Leak test and recharge Replace 21 00 00 Page 109 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING TROUBLE 2 No cooling 3 Air conditioner will not operate in AUTO mode but will function in the MAN COOL mode 4 Air conditioner runs constantly in either AUTO or MAN COOL 5 Excessive vibration of unit 6 Noisy unit 21 00 00 Page 110 May 30 75 AIR CONDITIONING SYSTEM Cont d PROBABLE CAUSE Loose connection Blower not functioning Leak in system Compressor reed valves inoperative Expansion valve stuck open Blown fuse Misadjustment of heater control box Malfunction of control box Malfunction of temperature sensing elements Malfunction of temperature sensing elements Overcharged Air in system Mount or compressor bolts
22. the SPEAKER position and place the volume control in the center of its range C Turn the ELT ARM OFF ON TEST AUTO XMIT XMIT ARM switch to ON and monitor the ELT signal 25 60 00 Page 204 Nov 20 87 tion present NOTE If there is no audible signal the battery is probably disconnected or dead assuming that the transceiver is operational Place the ARM OFF ON TEST Al XMIT XMIT ARM switch on the ELT to 1 OFF position The audio signal shot disappear completely e Place the switch in the ARM po There should be no audio sigr NOTE If a signal is heard the impact switch has probably been acti vated and should be reset f Firmly press the reset switch the front of the ELT and listen to ensi the audio signal disappears from COMM END Peechcraft DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 27 RECORD OF TEMPORARY REVISIONS NUMBER INSERTED REMOVED REMOVED NUMBER 27 1 Dec 11 92 Nov 15 93 Temporary 27 50 00 Revision Page 203 27 2 Page 203 ee as ee NOTE insert this Record of Temporary Revisions after the Chapter 27 divider tab Page 1 Nov 15 93 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 27 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 27 EFFECTIVITY 1 Sep 20 85 27 CONTENTS 1 Sep 20 85 2 Sep 20 85 27 00 00 1 Nov 2 73 201 Nov 2 73 202 Nov 2 73 27 10 00 201 2 73 202 2 73 203 Sep 14 79
23. AIR CONDITIONING EOUIPMENT AND FURNISHINGS IGNITION SERVICING ICE ANO RAIN PROTECTION TIME LIMITS MAINTENANCE CK TIME LIMITS MAINTENANCE CK ELECTRICAL POWER EQUIPMENT AND FURNISHING TIME LIMITS MAINTENANCE CK LANOING GEAR LANOING GEAR TIME LIMITS MAINTENANCE CK TIME LIMITS MAINTENANCE CK LANOING GEAR LANDING GEAR LANDING GEAR TIME LIMITS MAINTENANCE CK TIME LIMITS MAINTENANCE CK LANDING GEAR f TIME LIMITS MAINTENANCE CK LANDING GEAR LANDING GEAR TIME LIMITS MAINTENANCE CK NAVIGATION TIME LIMITS MAINTENANCE CK AIR CONDITIONING PROPELLERS TIME LIMITS MAINTENANCE CK TIME LIMITS MAINTENANCE CK PROPELLERS TIME LIMITS MAINTENANCE CK WINGS WINGS TIME LIMITS MAINTENANCE CK NAVIGATION NAVIGATION AIR CONDITIONING AIR CONDITIONING AIR CONDITIONING LIFTING AND SHORING LIGHTS LANDING GEAR LANDING GEAR LANOING GEAR LANDING GEAR LANOING GEAR LANDING GEAR LANDING GEAR LANOING GEAR LANOING GEAR LANDING GEAR LANOING GEAR LANOING GEAR 21 40 00 21 40 00 21 40 00 21 40 00 21 40 00 25 00 00 74 20 00 12 20 00 30 20 00 05 20 00 05 20 00 24 50 00 25 60 00 05 20 00 32 30 00 32 30 00 05 20 00 25 20 00 32 10 00 32 0 00 32 40 00 05 20 00 05 20 00 32 20 00 05 20 00 32 50 00 32 40 00 05 20 00 34 10 00 05 20 00 21 20 00 61 00 00 05 20 00 05 20 00 61 00 00 05 20 00 57 40 00 57 00 00 05 20 00 34 00 00 34 00 00 21 10 00 21 10 00 21 10 00 07 00 00 33 40 00 32 30 00 32 60 0
24. Acceptable range is 300 to 1 000 fpm h Place the airplane in a 1 000 fpm climb at normal climb power and record maximum cabin descent as the airplane begins to pressurize Maximum descent rate is 500 fpm i After climbing through an altitude 2 000 feet above the altitude selected on the cabin altitude controller adjust the bleed control valve if required as follows 1 If the cabin climbs as the airplane climbs close the bleed control valve to obtain a zero rate of climb on the cabin rate of climb indicator NOTE Because of the sensitivity of the pressurization control system the bleed control valve should be moved in increments of no more than 1 8 turn 2 If the cabin dives as the airplane climbs OPEN the bleed control valve to obtain a zero rate of climb on the cabin rate of climb indicator j Level the airplane at an altitude approximately 8 000 feet above the selected cabin altitude and compare the selected altitude on the controller with the indicated cabin altitude on the cabin altimeter If the difference in the two altitudes is in excess of 500 feet the contro head on the cabin altitude controller should be removed and adjusted to correspond with the altitude on the cabin altimeter NOTE The manual controller should be removed from the subpanel prior to take off if the need for adjustment is anticipated k After landing if lift off descent is excessive and isobaric descent is sail as recorded in steps
25. K GENERAL MECH 1 Airplane cleaned and serviced 2 Airplane lubricated after cleaning rutlined in Chapter 12 20 00 and BEECHCRAFT Safety Communique No 57 dated June 3 1981 Service Bulletins and previously issued Service Instructions are reviewed and complied with as required For a complete or annual inspection of the airplane all items on the airplane that are noted in this guide should be inspected Inspect all placards to assure that they are easily readable and securely attached 4 Assure that all Airworthiness Directives BEECHCRAFT 5 20 00 Page 224 Nov 20 87 18 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PILOT S DISCREPANCIES REMARKS 5 20 00 Page 225 A18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PILOT S DISCREPANCIES 5 20 00 Page 226 Nov 20 87 REMARKS Al BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PROPELLER SYSTEM INSPECTION DEICER The various components of the propeller deicer system should be inspected every 50 hours for the appearance of defects The following inspection may provide a means of detecting and correcting such defects before they render the deicer system inoperative ELECTRIC PROPELLER DEICER 50 HOUR GUIDE a Lock the brakes and operate the engines at near takeoff power Turn the deicer system switch ON and observe the ammeter for at least 2 minutes If the ammeter needle does not rest with
26. May 30 75 BEECHCRAFT OUKE 60 SERIES MAINTENANCE MANUAL COMPRESSION DESCRIPTION AND OPERATION Figure 1 Pressurized air for the cabin is supplied by the turbocharger compressor mounted on the same shaft as the turbocharger In operation engine exhaust gas passing over the turbine wheel causes the turbocharger compressor to rotate Ambient ram air supplied through the RH cow door is filtered and routed to the compressor where it is compressed and delivered to the cabin through a sonic nozzle When sonic velocity is reached by the air flowing through the throat of the nozzle each engine is producing the maximum flow rate of 4 to 5 pounds per minute Total air flow from both engines will deliver approximately 8 to THROTTLE BUTTERFLY 1 VALVE SONIC a VENTURI TURSO CHARGER FIREWALL SHUT OFF Li INTERCOOLER a NET DIFFERENTIAL CONTROL VALVE SAFETY V P 4 thru 246 9 247 and atter TUSAFETY VALVE CABIN CHECK VALVE Seed 10 pounds per minute and maintain a cabin pressure differential of 4 6 psi A pressurization air intercooler located in each wing root is used for temperature control of pressurization air before t enters the cabin Air flow through the intercoolers is controlled by a butterfly valve located in a ram air scoop under each wing root leading edge The butterfly valves are manually actuated by the intercooler temperature controls located on the RH subpanei F
27. Output voltage is inadequate 6 Pressure switch will not make contact when pressure is on 7 Output voltage one way only on pitch and altitude channels 22 11 00 Page 104 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING NEW MATIC AUTOPILOT Cont d PROBABLE CAUSE Dirty input signal AC volts Polarization pins reversed on heading sensor plug One of the components is shorted to ground Incorrect setting on controller amplifier Low or high voltage output on nav indicators Defective pitch altitude sensor or amplifier Defective pitch altitude sensor or amplifier Pressure switch on servo control valve out of circuit Defective solenoid valve Defective altitude switch on controller amplifier Improper pressure ad justment Sticky valve Pitch altitude amplifier sensor or harness shorted or improperly wired Defective pressure switch or not set at proper pressure Servo control valve shorted to ground REMARKS Check indicators Reverse pins See System Block Diagram Figure 2 Check for shorts Adjust intercept angle Check nav indicators to manufacturer s specs Check on Test Set TS 108 or replace one at a time Check on Test Set TS 108 or replace one at a time Check for faulty switch and replace if necessary Replace solenoid valve Check continuity See System Block Diagram Figure 2 Adjust pressure as outlined in Cha
28. Peechcraft DUKE MODEL 60 P 4 thru P 126 except 123 MODEL 60 P 123 P 127 thru 246 MODEL B60 P 247 and after MAINTENANCE MANUAL P N 60 590001 25 Issued November 2 1973 P N 60 590001 25A18 Supersedes 60 590001 5B Revised November 20 1987 PUBLISHED BY COMMERCIAL PUBLICATIONS BEECH AIRCRAFT CORPORATION WICHITA KANSAS 67201 U S A oum General Aviation A Raytheon Company Manulocturers Association 9 36416C LIST OF EFFECTIVE REVISIONS Always destroy superseded pages when you insert revised pages 4 44 4 4 4 41444 4 4 4 4 4 4 4 4 444 4144 4 4 4 4 4 4 4 LOG OF REVISIONS PART NUMBER 60 590001 25 60 590001 25A1 DATE November 2 1973 August 16 1974 CHAPTER AFFECTED Original 61 71 60 590001 25A2 May 30 1975 Intro 5 12 21 25 27 30 32 36 56 61 71 91 Insp Intro 7 12 22 28 30 32 53 57 9 12 24 25 28 30 32 33 61 73 79 Intro 5 11 12 20 23 24 30 Intro 5 27 Intro 5 12 21 57 91 intro 11 12 20 25 33 52 August 15 1980 Intro 25 38 November 28 1980 5 February 27 1981 55 57 April 2 1981 5 57 91 21 1982 5 30 gt 60 590001 25A3 October 27 1975 60 590001 25A4 October 19 1977 60 590001 2
29. Remove the control port tubing from both the outflow and safety vaives b Connect the 3 8 inch high pressure hose from the INSTRUMENT AIR or CABIN PRESSURE fitting on the test unit to the brake reservoir sense line at the forward pressure bulkhead located in the nose baggage compartment The air supply must be capable of maintaining 4 50 psi NOTE Ensure that all windows and doors are closed and securely latched am WARNING Personnel who work under pressurized conditions must be carefully chosen Pressurization may prove dangerous to personnel which are overweight have heart or respiratory disorders ear infection or are not emotionally stable 21 30 00 Page 208 Feb 22 80 Place high strength webbing P N 60 000000 D939 1 or equivalent in position over the pressure vessel doors and windows d Connect a 2 1 2 inch air supply hose between the test unit PRESSURIZING AIR fitting and the flexible dues forward of the LH and RH firewall e Connect the PNEUMATIC AIR fitting on the test mit to the pneumatic line in each nacelle forward of the pressure regulator NOTE Ensure that all connections are secure at the airplane and at the test unit Ensure that ail T and or Y fittings are secure f Slowly open the air valve to pressurize the cabin Monitor the RATE OF CLIMB and CABIN PRESSURE indicators The rate of climb should not exceed 1 000 feet per minute to a maximum of 25 000 feet The cabin
30. access panels which were removed during the test procedure 21 30 00 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 0o 106 SHOP AIR INLET PNEUMATIC AIR HOSE OUTLET o PRESSURIZATION AIR HOSE OUTLET L E E SN J INN f lt CABIN PRESSURE OR TEE OR Y CONNECTOR CTS INSTRUMENT AIR i FWD PRESSURE BULKHEAD F S 100 00 A PNEUMATIC LINE HOSE OUTLET CONNECT TO SHOP AIR BRAKE RESERVOIR SENSE LINE FLEXIBLE TURBOCHARGER DUCT PNEUMATIC LINE FIREWALL SHUTOFF AIR TO AIR VALVE HEAT EXCHANGER DUCT 2 FIREWALL SONIC SHUTOFF NOZZLE VALVE AIR TO AIR HEAT EXCHANGER NOTE AFT PRESSURE THE EXACT LOCATION OF THE INSTRUMENTS SHOWN THE PEE FS 242 00 KITCO TEST UNIT MAY NOT NECES SARILY CONFORM WITH THE ACTUAL ARRANGEMENT OF INSTRUMENTATION ON THE TEST UNIT BEING UTILIZED FOR THIS PROCEDURE SAFETY DUMP VALVE PRESSURIZATION OUTFLOW VALVE 60 603 39 Cabin Pressurization Test Hookup Page 1 of 2 Figure 201 21 30 00 Page 210 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL BRAKE RESERVOIR SENSE LINE FWO PRESSURE BULKHEAD 60 603 40 Cabin Pressurization Test Hookup Page 2 of 2 Figure 202 END 21 30 00 Page 211 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL HEATING DESCRIPTION AND OPERATION The heater system consists of a 45 000 BTU combust
31. installed on the right subpanel provide the operator with a visual indication of the wing flap position These lights are controlled by the flap limit switches a Adiust the flap limit switches to provide the correct travel Refer to FLAP CONTROL SYSTEM RIGGING b Select DN down position Observe that the red TRANSIT light illuminates and remains illuminated until the amber DN down light illuminates c Select the APH approach position Observe that the amber DN down light goes out and the red TRANSIT light illuminates and remains illuminated until the blue APH approach light is illuminated d Select the UP full up position Observe that the blue APH approach light goes out and the red TRANSIT light illuminates When the flaps are in UP full up position the red TRANSIT light will go out FLAP ACTUATOR REMOVAL a Fully extend the flaps and disconnect the actuator from the flap b Remove the access plate on the lower surface of the wing and uncouple the flexible drive shaft Remove the mounting bolts and actuator from the wing bracket Remove the bushings from the actuator FLAP ACTUATOR INSTALLATION a Position the actuator in the wing bracket and install the bushings and attaching bolts b Couple the flexible drive shaft to the actuator Install the access plate on the lower surface of the wing c Extend the actuator until the flap synchronizes with the opposite flap then connect the actuator
32. loose Drive pulley loose Compressor oil level low Defective belt Low refrigerant level Excessive moisture in system REMARKS Check connections continuity Repair Leak test and recharge Repair or replace Replace Service air conditioning system Check for over pressure purge and recharge if necessary Leak test and recharge if pressure is low Replace Replace Replace Replace Correct refrigerant charge Purge and recharge system Tighten Tighten Addoil Replace Add refrigerant Replace receiver dryer and recharge 10 11 TROUBLE Noisy unit Hissing in evaporator case Chatter or knock in evaporator case Beit slipping Excessive belt wear Broken belt BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING AIR CONDITIONING SYSTEM Cont d PROBABLE CAUSE Fan hitting shroud Defective compressor Low charge Defective expansion valve Loose Overcharged Air in system Pulleys not in line Belt too tight Pulley groove wrong size Belt width wrong Check all causes above END REMARKS Align and tighten shroud Replace Add refrigerant Replace Adjust Correct refrigerant level Evacuate and recharge Align pulleys Adiust or replace Replace Replace Replace 21 00 00 Page 111
33. set the elevator controls in neutral on airplane serials P 438 and after insert the short end of the fabricated tool see Figure 201A in the control column hanger Move the control aft and insert the other end of the tool into the contro shaft and torque tube Insert a 3 16 inch diameter rig pin in the aft elevator bell crank and adjacent structure g With the rig pins and elevator down springs installed rig the elevator cable tension as noted on the Elevator Rigging Illustration Figure 201 h Remove the rig pins securely tighten all lock nuts and safety wire the turnbuckles NOTE With the system fully installed including the autopilot when installed measure the force required to move the control column from the full forward position through neutral with a hand force gage This force should measure between 32 and 36 pounds The force required to restrain the control column when passing through neutral from a position not more than one inch aft of neutral should measure between 16 and 20 pounds when the system is properly rigged NOTE After rigging the elevator and elevator tab control system check for correct movement of the control surfaces with respect to the movement of the controls When the elevator trim tab control wheel is moved toward the NOSE DOWN position the elevator tab should move UP i Install the tail cone and the access plate on the side of the fuselage beneath the RH horizontal stabilizer ELEVATOR TR
34. 00 NOSE GEAR DOWNLOCK UPLOCK SWITCH ADJ LANDING GEAR 32 30 00 NOSE GEAR INSTALLATION s LANDING GEAR 32 20 00 NOSE GEAR LUSRICATION LANDING GEAR 32 20 00 NOSE GEAR REMOVAL LANDING GEAR 32 20 00 NOSE GEAR SHOCK ABSORBER SERVICING LAROING GEAR 32 20 00 NOSE STEERING ADJUSTMENT LANDING GEAR 32 50 00 NOSE WHEEL AND TIRE LANOING GEAR 32 40 00 NOSE WHEEL ASSEMBLY LANDING GEAR 32 40 00 OIL FILTER CHANGING SERVICING 12 10 00 OIL FILTER CHANGING s OIL i 79 00 00 OIL PRESSURE ADJUSTMENT POWER PLANT 71 00 00 OIL SYSTEM SERVICING 12 10 00 OUTBOARD WING WINGS 57 00 00 OUTFLOW VALVE FLIGHT CHECK AIR CONOITIONING 21 30 00 OVERHAUL AND REPLACEMENT SCHEDULE TIME LIMITS MAINTENANCE CK 05 10 00 OVERVOLTAGE RELAY CHECK ELECTR ICAL POWER 24 30 00 QVERVOLTAGE RELAYS ELECTRICAL POWER 24 30 00 OXYGEN CYLINOER REPLACEMENT OXYGEN 35 00 00 OXYGEN CYLINDER RETESTING OXYGEN 35 00 00 OXYGEN SYSTEM SERVICING 12 10 00 OXYGEN SYSTEM OXYGEN 35 00 00 OXYGEN SYSTEM PURGING OXYGEN 35 00 00 OXYGEN SYSTEM TEST PROCEDURES OXYGEN 35 00 00 PAINT FINISHES EXTERIOR amp INTERIOR STANDARO PRACTICES AIRFRAME20 00 00 PAINT PRIMERS EXTERIOR INTERIOR STANDARD PRACTICES AIRFRAME20 00 00 PAINT REMOVAL MAGNESIUM SURFACES STANDARD PRACTICES AIRFRAME20 00 00 PAINT REPAIR PROCEDURES URETHANE STANDARD PRACTICES AIRFRAME20 00 00 PAINT ENAMEL EXTERIOR COLORS STANDARD PRACTICES AIRFRAME20 00 00 INTERIOR COLORS STANDARD PRACTICES AIRFRAME20 00 0
35. 1 Fuel Engine 100 130 octane If not available use 115 145 Never use 91 96 octane fuel 2 Oil Engine MIL L 22851 Global Concentrate A Ashless Dispersant Delta Petroleum Company Inc P O Box 10397 New Orleans La 70121 Paranox 160 and 165 Enjay Chemicai Company 60 West 49th Street New York N Y 10020 451 RM 173E RM 180E Mobil Oil Corporation 150 East 42nd Street New York N Y 10017 12 20 00 Page 205 A14 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 202 Cont d CONSUMABLE MATERIALS ITEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS 2 Oil Engine Shell Concentrate A Code 60068 Ashless Dispersent Aeroshell W120 Aeroshell W80 Cont d Shell Company One Shell Plaza Houston Texas 77002 TX 6309 Aircraft Engine Oit Premium AD120 Premium AD80 Texaco Inc 135 East 42nd Street New York N Y 10017 PO Aviation Lubricant 753 American Oil and Supply Co 238 Wilson Avenue Newark N J 07105 Chevron Aero Oil Grade 120 Chevron Oil Co 1200 State Street Perth Amboy N J 08861 Esso Aviation Oil E 120 Enco Aviation E 120 Esso Aviation Oil A 100 Enco Aviation Oil A 100 Esso Aviation Oil E 80 Enco Aviation Cil E 80 Exxon Company U S A P O Box 2180 Houston Texas 77001 Chevron Aero Oil Grade 120 Standard Oil Co of Calif 225 Bush Street San Francisco Calif 94120 3 Corrosion Preventive MIL C 6529 Anti Corrode No 205 Compound Cities Ser
36. 10 00 51 50 00 24 10 00 36 00 00 27 10 00 27 10 00 21 10 00 27 10 00 27 10 00 27 10 00 12 10 00 21 50 00 21 00 00 12 10 00 21 50 00 21 50 00 STANDARD PRACTICES AIRFRAME20 00 00 SERVIC ING ENGINE INDICATING AIR CONDITIONING AIR CONDITIONING DOORS f DOORS DOORS DOORS DOORS DOORS DOORS DOORS DOORS DOORS DOORS AUTO FLIGHT PNEUMATIC AUTO FLIGHT AUTO FLIGHT EQUIPMENT FURNISHINGS ELECTRICAL POWER SERVICING ELECTRICAL ELECTRICAL ELECTRICAL ELECTRICAL ELECTRICAL ELECTRICAL ELECTRICAL ELECTRICAL ELECTRICAL POWER ELECTRICAL POWER EQUIPMENT AND FURNISHINGS ELECTRICAL POWER ELECTRICAL POWER ELECTRICAL POWER ELECTRICAL POWER ELECTRICAL POWER ELECTRICAL POWER ELECTRICAL POWER EQUIPMENT FURNISHINGS ELECTRICAL POWER POWER POWER POWER POWER POWER POWER POWER POWER 12 20 00 77 00 00 21 30 00 21 30 00 52 60 00 52 60 00 52 60 00 52 60 00 52 60 00 52 60 00 52 60 00 52 60 00 52 60 00 52 60 00 52 60 00 22 10 00 36 00 00 22 10 00 22 11 00 25 60 00 24 00 00 12 20 00 24 31 00 24 31 00 24 00 00 24 32 00 24 31 00 24 31 00 24 3 1 00 24 31 00 24 31 00 24 31 00 25 60 00 24 31 00 24 31 00 24 31 00 24 31 00 24 31 00 24 31 00 24 31 00 25 60 00 24 31 00 INTROOUCT ION PAGE 11 AUG 15 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM OR SYSTEM NAME BRAKE ASSEMBLY BRAKE ASSEMBLY INSTALLATION BRAKE ASSEMBLY REMOVAL BRAKE GRA
37. 12 78 203 12 78 204 _ May 12 78 24 31 00 101 May 12 78 102 May 12 78 103 12 78 104 12 78 201 12 78 202 2 73 203 Nov 2 73 204 Nov 2 73 205 Nov 2 73 206 Nov 2 73 207 Nov 2 73 208 May 12 78 209 May 12 78 24 32 00 201 May 12 78 24 50 00 201 Nov 2 73 202 May 12 78 202A May 12 78 203 Nov 2 73 204 Nov 2 73 205 Nov 2 73 206 Nov 2 73 END 24 EFFECTIVITY Page 1 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 24 ELECTRICAL POWER TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT GENERAL 24 00 00 Description and Operation AC Generation AC Voltage Frequency indicator DC Generation Generators Battery Battery Charge Current Detector System DC GENERATION 24 30 00 Troubleshooting Generator System Maintenance Practices Generator Removal Generator Installation Generator Brush Replacement Overvoltage Relays Overvoltage Relay Check Voltage Regulator Adjustment and Generator Paralleling Preliminary Potentiometer Check Preliminary Adjustment of Paralleling Rheostats Stabilization of Generator System Voltage Adjustment Minimum Load Current Adjustment Maximum Load Final Paralleling Checks DC GENERATION 24 31 00 Troubleshooting Battery System Nickel Cadmium Battery Lead Acid Battery Maintenance Practices Battery Maintenance Program Airplanes Prior to P 446 Maintenance Log Battery Removal Pre installation Instructions for Nickel Cadmium Batteries
38. 204 Sep 14 79 205 Sep 14 79 27 20 00 201 Nov 2 73 202 Nov 2 73 203 Nov 2 73 204 Sep 14 79 205 Sep 14 79 27 30 00 201 Sep 20 85 202 May 30 75 203 Sep 20 85 204 Sep 20 85 204A Sep 20 85 205 Sep 14 79 206 Sep 14 79 207 Sep 14 79 27 50 00 1 Nov 2 73 201 Nov 2 73 202 Nov 2 73 203 Nov 2 73 27 60 00 1 2 73 101 Nov 2 73 201 Nov 2 73 27 70 00 201 Nov 2 73 END 27 EFFECTIVITY Page 1 16 kai Sep 20 85 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 27 FLIGHT CONTROLS TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 27 00 00 Description and Operation 1 Effect of Temperature Upon Cable 1 Tension Maintenance Practices 1 Control Column 201 Bus Cable Removal 201 Bus Cable Installation 202 Bus Cable Rigging 202 202 AILERON AND TAB 27 10 00 201 Maintenance Practices 201 Aileron Removal 201 Aileron Installation 201 Control Cable Removal 201 Aileron Control Cable Installation 201 Aileron Control System Rigging 201 Trim Tab Cable Removal 201 Trim Tab Cable Installation 203 Trim Tab Rigging f 203 Trim Tab Actuator Removal 203 Trim Tab Actuator Installation 203 Checking Trim Tab Free Play 203 RUDDER AND TAB 27 20 00 201 Maintenance Practices 201 Rudder Removal 201 Rudder Installation 201 Rudder Cable Removal 201 Rudder Cable Installation 201 Rudder Control System Rigging 201 Trim Tab Cable Removal 203 Trim Tab Cable Installation 203 Trim Tab Rigging 203 T
39. 307 TROUBLE PROBABLE CAUSE REMARKS 1 Unable to pressurize a Cabin altitude control a Check by isolating control frorn system inoperative see PRESSURIZATION TEST PROCEDURE in this chapter b Differential control valve b Check by isolating control valve from inoperative system see PRESSURIZATION TEST PROCEDURE in this chapter c Dump solenoid stuck in c Cycle pressure circuit breaker listen for open position operation of dump solenoid replace if inoperative d Vacuum solenoid stuck in d Cycle pressure circuit breaker listen for open position operation of vacuum solenoid replace if inoperative e Cabin altitude control e Disconnect sense line at both ends and sense line restricted purge f Differential control valve f Clean the valve seats with seats dirty a lint free cloth moistened with alcohol For additional information relating to overhaul and cleaning procedures refer to Component Maintenance Manual P N 60 590001 27 g Firewall shutoff valves 9 Open valves pulled closed h Hole in flex ducts from h Inspect and repair or replace as required engine i Excessive pressure leaks i Check cabin for leaks repair as required in cabin door seal etc 2 No pressure indication a Press to test switch a Replace switch on ground s inoperative i b Rate of climb indicator b Replace indicator inoperative c Dump switch in dump c Place switch in pressure position position d Manifo
40. 50 00 Page 203 dated Nov 2 73 Reason Revise procedures for flap drive cable connection FLAP DRIVE CABLE CONNECTION Connect the LH and RH flap drive cables to the flap drive motor as follows using the illustration for component locations a Install the outboard nut and washer as far as it will go on the threaded portion of the flap cable b Insert the retainer through the mount support and onto the motor shaft as far as it will go Align the retainer keyway with the key slot in the flap motor drive shaft and tighten one set screw temporarily While inserting trie flap cable through the mount support install the inboard washer and nut Install the cable through the retainer arid into the motor drive shaft until the keyway is just past the key slot in the retainer d Loosen the set screw that was tightened in Step b Ensure that the retainer is still installed on the motor shaft as far as it will go and rotate the retainer 90 e Keep inboard pressure on the retainer and tighten both retainer set screws f re the flap drive cable to the mounting support by tightening the nuts Tighten the inboard nut to ensure that is sufficient clearance between the outboard edge of the retainer and the cable housing to allow the retai rotate without coming into contact with the cable housing if the threaded part of the cable housing is not I ough to install the two nuts and washers using a die add 5 8 24 UNEF threads until 88 inch thread
41. 7 32 SPARK PLUG GAP HEATER COMBUSTION HEAD GROUNO ELECTRODE 60 153 1 Heater Spark Plug Gap Figure 202 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL between the two measurements is the spark plug gap The gap should be 3 16 to 7 32 0 188 to 0 218 inches if the plug gap must be adjusted the ground electrode may be bent up or down by reaching through the spark plug hole with the appropriate shaped tool NOTE If the spark plug fails to clean up properly and or if the electrode is badly eroded it should be replaced If a new spark plug is being installed be sure to measure the gap Do not bend the positive electrode Torque the spark plug to 28 foot pounds NOTE The spark plug can be checked visually for sparking prior to installing the plug as follows Disconnect the wire from the terminal on the heater wiring side of the terminal strip to de energize the fuei solenoid valve Connect the high voltage lead temporarily and lay the spark plug on the heater jacket WARNING Be sure to plug the spark plug hole in the heater to prevent any possibility of residual fuel blowing out and igniting Do not touch the spark plug while energized because of dangerously high voltage TEMPERATURE SENSORS AND CONTROL RHEOSTAT TEST NOTE The aircraft must be in a location such as a hangar where temperatures inside and outside of the aircraft are equal and stable When making the tests slight variances may occu
42. As the airplane reaches and climbs through the pre set altitude the cabin rate of climb will slowly come to a zero point As the cabin altitude and the selected altitude begin to come together at the pre set altitude a pressure fluctuation may be noticed 1 000 fpm is normal Stabilization of the two altitudes within 500 feet of each other can be expected until maximum differential pressure is reached d Maximum Differential Pressure As the cabin leaves the isobaric altitude contro and goes on maximum differential pressure control it will make an adjustment and a fluctuation of 500 fpm may be noted before it stabilizes to the normal rate of climb of the airplane Again little or passenger discomfort should be experienced e Power Reductions A sudden power reduction or loss of power on one engine below 20 in Hg MP will cause a change in engine pressurization air flow Therefore cabin pressure will be affected and cabin pressure fluctuation will be experienced A fluctuation of 2 000 fpm is normal under these conditions f Pressurization at Minimum Power A maximum differential pressure 4 6 psi may be expected at any throttle setting of 20 in Hg MP or above on both engines or during single engine operation with the operating engine at 65 power or above at an altitude of 20 000 feet or above Once the isobaric altitude is set this is the altitude at which the cabin starts to pressurize it should be left there until
43. Battery Installation Battery Charging Special Notes on Charging Constant Current Charging Constant Potential Charging Battery Stand By Charging Capacity Reconditioning Frequency of Reconditioning Reconditioning Procedure Battery Electrolyte Level Adjustment Electrical Leakage Check Capacity Check Cleaning and Inspection PAGE o n n n a 101 101 101 201 201 201 201 201 201 202 202 202 203 203 204 204 101 101 101 101 103 201 201 201 201 201 201 203 203 203 205 205 205 206 206 206 207 207 207 24 CONTENTS Page 1 May 427 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 24 ELECTRICAL POWER TABLE OF CONTENTS Cont d CHAPTER SECTION SUBJECT SUBJECT DC GENERATION Cont d 24 31 00 Maintenance Practices Cont d Battery Maintenance Program P 446 and after Battery Removal Battery Installation Battery Cleaning Battery Box Cieaning Battery Servicing Recharging Batteries Using Auxiliary Power DC GENERATION 24 32 00 Maintenance Practices Batiery Charge Current Detector Functional Check EXTERNAL POWER 24 40 00 Maintenance Practices ELECTRICAL LOAD DISTRIBUTION 24 50 00 Maintenance Practices Periodic Inspection of Dual Bus Feeder Diodes Dual Bus Conformity Inspection Electrical Utilization Load Chart END 24 CONTENTS Page 2 May 12 78 PAGE 208 208 208 208 209 209 201 201 201 201 201 201 201 201 201 BEECHCRAF
44. ELECTRICAL POWER SERVICING STRUCTURES AIR CONDITIONING FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS CHAPTER amp SUB CHAPTER 12 20 00 30 10 00 30 10 00 21 30 00 21 30 00 21 30 00 21 30 00 06 00 00 21 20 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 24 50 00 55 20 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 27 30 00 25 60 00 25 60 00 25 60 00 55 00 00 81 00 00 71 00 00 71 00 00 71 00 00 71 00 00 91 00 00 79 00 00 81 00 00 72 00 00 71 00 00 21 30 00 21 50 00 12 10 00 24 40 00 12 20 00 51 00 00 21 10 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 27 50 00 INTROOUCTION PAGE 13 AUG 15 80 BEECHCRAFT OUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM CHAPTER CHAPTER 6 OR SYSTEM NAME NAME SUB CHAPTER FLARE FITTING TORQUE CHART CHARTS 91 00 00 FLARED FITTINGS FUEL 28 20 00 FLIGHT CONTROLS FLIGHT CONTROLS 27 00 00 FUEL BOOST PUMP INSTALLATION FUEL 28 20 00 FUEL BOOST PUMP REMOVAL FUEL 28 20 00 FUEL BOOST PUMPS FUEL 28 00 00 FUEL CELL DRAINS FUEL 26 00 00 FUEL CELL FLAPPER VALVE INSP BAFFLED FUEL 28 10 00 FUEL CELL 5 LEAOING EDGE FUEL 28 10 00 FUEL CELL INST OUTBOARO
45. Electric Nickel Cadmium Vented Cell Batteries P N GET 3593A which ever the airplane is equipped with Advisory Circular AC 00 33 printed by Department of Transporation Federal Aviation Administration is another good source of battery maintenance information MAINTENANCE LOG Customers are advised to keep a complete and up to date maintenance log on each battery This information will help determine the source of any battery problems and will assist ih substantiating warranty claims A sample format for maintenance log is illustrated on the following page BATTERY REMOVAL a Remove the upper access door to the electrical equipment compartment aft of LH nacelle firewall b Cut the safety wire and remove the battery quick disconnect c On serials P 226 through P 445 equipped with General Electric air cooled batteries disconnect the cooling ducts d Disconnect the battery vent tubing e Cut the safety wire remove the two nuts from the battery hold down bar and lift the battery out of the well PRE INSTALLATION CADMIUM BATTERIES INSTRUCTIONS FOR NICKEL Unless otherwise indicated by a red waming tag a nickel cadmium battery is shipped in fully discharged state and contains the proper amount of electrolyte Observe the following precautions to ensure maximum per formance and to protect the battery warranty a not remove the shorting strap until prepared to charge the battery Batteries from which th
46. LEADING EDGE FUEL 28 10 00 FUEL CELL INSTALLATION 80X SECTION FUEL 28 10 00 FUEL CELL INSTALLATION NACELLE FUEL 28 10 00 FUEL CELL LEAKAGE CHECK FUEL 28 10 00 FUEL CELL REMOVAL 80X SECTION FUEL 28 10 00 FUEL CELL REMOVAL INBO LEADING EOGE FUEL 28 10 00 FUEL CELL REMOVAL NACELLE FUEL 28 10 00 FUEL CELL REMOVAL OUTBD LEADING EDGE FUEL 28 10 00 FUEL CELL REPAIR GOOOYEAR FUEL 28 10 00 FUEL CELL REPAIR UNIROYAL FUEL 28 10 00 FUEL CELL VELCRO TAPE INST OF FUEL 28 10 00 FUEL CELL VENT FLOAT VALVE INSTALLATION FUEL 28 20 00 FUEL CELL VENT FLOAT VALVE REMOVAL FUEL 28 20 00 FUEL CELL VENT LINE EXTERNAL FUEL 28 20 00 FUEL CELLS FUEL 28 00 00 FUEL CELLS FILLING SERVIC ING 12 10 00 FUEL CROSSFEED FUEL 28 00 00 FUEL FILTERS SCREENS ENGINE SERVIC ING 12 10 00 FUEL FLOW INDICATOR ENGINE FUEL AND CONTROL 73 30 00 FUEL GAGING SYSTEM ADJUST AND TEST FUEL 1 28 40 00 FUEL HANDLING PRACTICES FUEL 28 00 00 FUEL PUMP ADJUSTMENT ENGINE DRIVEN FUEL 28 20 00 FUEL PUMP INSTALLATION ENGINE DRIVEN FUEL 28 20 00 FUEL PUMP REMOVAL ENGINE ORIVEN FUEL 28 20 00 FUEL QUANTITY INOICATORS FUEL 28 40 00 FUEL SELECT VALVE CONT CABLE REMOVAL FUEL 28 20 00 FUEL SELECT VALVE CONT CABLE RIGGING FUEL 28 20 00 FUEL SELECT VALVE CONT CABLE INSTALL FUEL 28 20 00 FUEL SELECTOR VALVE INSTALLATION FUEL 28 20 00 FUEL SELECTOR VALVE REMOVAL FUEL 28 20 00 FUEL SYSTEM DRAINING SERVICING 12 10 00 FUEL TRANSMITTER INSTALLATION FUEL 28 40 00 FUEL TRANSMITTER REMOVAL FUEL 28 40
47. Light Threshold Light Nose Baggage Compartment Light Fuel Boost Out Lights Cow Flap Motor Cigarette Lighter Fuel Boost Pumps Landing Gear Warning Horn Landing Gear Warning Flasher Landing Gear Dynamic Brake Relay Only one used at a time Number Per Aircraft N NR 4 m mi Load Per Unit in Amps 0 04 0 09 0 60 2 14 0 04 0 04 0 04 0 17 29 00 0 03 0 35 29 00 0 03 0 35 8 90 9 00 0 17 0 30 0 04 1 20 7 50 14 00 1 50 0 40 0 40 Load Per Aircraft in Amps 0 16 0 18 1 20 2 14 0 04 072 0 04 0 17 29 00 0 03 0 35 29 00 0 03 0 35 17 80 9 00 0 17 0 30 0 16 2 40 7 50 28 00 1 50 0 40 0 40 24 50 00 Page 20 Nov 2 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 201 ELECTRICAL UTILIZATION LOAD Cont d INTERMITTENT LOAD STANDARD EQUIPMENT Landing Motor Wing Flap Motor Starter Relay Starter Starting Vibrator Stall Warning Horn INTERMITTENT LOAD OPTIONAL EQUIPMENT Electric Trim System Elevator Trim Motor Trim Clutch Magic Hand Switch Surface Deice System Deice Relay Time Delay Relay Deice Valve Control Valve Nacelle Scoop Actuator Only one used at a time Maximum stall load only one used at a time END 24 50 00 Page 206 Nov 2 73 Number Per Aircraft ae N Load Per Unit In Amps 20 00 13 00 0 06 275 00 2 00 1 50 0 85 0 50 2 50 0 09 0 17 0 59 1 75 1 20 Load Pe
48. Mesa California Operating Instructions for Model CIR 11 Emergency Locator Transmitter System Transmitter P N TR 70 13 Collins Communication Components Corporation Costa Mesa California Owners Manual Installation and Pilot s Guide P N 03716 0602 for the Narco ELT 10 Emergency Locator Transmitter Narco H Avionics Division of Narco Scientific Industries Fort Washington Pennsylvania INTRODUCTION Page 10A A14 Nov 30 83 BEECHCRAFT OUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM OR SYSTEM NAME AC GENERATION AILERON BALANCING AILERON CONTROL CABLE INSTALLATION AILERON CONTROL CABLE REMOVAL AILERON CONTROL SYSTEM RIGGING AILERON INSTALLATION AILERON MAINTENANCE AILERON REMOVAL AILERON SERVO PRESSURE REGULATOR AILERON TRIM TAB ACTUATOR INSTALLATION AILERON TRIM TAB ACTUATOR REMOVAL AILERON TRIM TAB CABLE INSTALLATION AILERON TRIM TAB CABLE REMOVAL AILERON TRIM TAB RIGGING AILERON TRIM FREE PLAY AIR CONOITIONER CHARGING AIR CONOITIONING FUNCTIONAL TEST AIR CONOITIONING SYSTEM AIR CONDITIONING SYSTEM AIR CONDITIONING SYSTEM CHARGING AIR SCOOP RIGGING AIR CONDITIONING AIRPLANE FINISH CARE AIRPLANE FINISH CLEANING WAXING ALCAL CALIBRATION UNIT ALTITUDE CONTROLLER INSTALLATION CABIN ALTITUOE CONTROLLER REMOVAL CAB IN ASSIST STEP AOJUSTMENT FOLDEO ASSIST STEP BELL CRANK INSTALLATION ASSIST STEP BELL CRANK REMOVAL ASSIST STEP CABLE INST P 4 T
49. Meter Engine Hour Meter Generator Contro System Overvoltage Relay Maximum of three on at a time Only one used at a time 24 50 00 Page 204 Nov 2 73 Number Per Aircraft 163 N NN ob gt hf MH OS b 4 2 N Load Per Unit in Amps 0 04 0 04 0 04 0 09 0 04 0 04 0 04 0 04 0 04 0 17 0 17 0 04 0 04 0 04 0 17 0 30 0 75 0 65 3 10 3 10 2 90 15 00 0 35 0 17 0 25 0 09 0 75 0 06 2 00 0 35 17 00 0 35 18 00 3 30 2 50 0 02 0 02 0 03 Load Per Aircraft in Amps 6 52 0 08 0 08 0 09 0 08 0 04 0 12 0 04 0 40 1 17 1 36 0 04 0 04 0 72 0 17 1 80 3 00 0 65 3 10 3 10 2 90 15 00 0 35 0 17 0 25 0 09 0 75 0 06 0 35 17 00 0 35 18 00 3 30 2 50 0 02 0 02 0 03 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 201 ELECTRICAL UTILIZATION LOAD Cont d CONTINUOUS LOAD OPTIONAL EQUIPMENT Generator Control System Cont d Generator Out Light Paralleling Retay Generator Control Relay LH Wing Light Oxygen Panel Post Light Copilot s Instrument Post Lights Copilot s Clock Light Copilot s Map Light LH Heated Windshield System Inverter Windshield Temperature Control Box Windshieid Temperature Control Relay RH Heated Windshield System Inverter Windshield Temperature Control Box Windshield Temperature Control Relay INTERMITTENT LOAD STANDARD EQUIPMENT Lights Landing Lights Taxi
50. Operator s Manual 60297 13 Lycoming Division Williamsport Pennsylvania FUEL INJECTION Operation and Service Manual Form 15 468 Bendix Corporation South Bend Indiana PROPELLER Overhaul instructions 117B for Hartzell Propeller Hartzell Propeller Inc Piqua Ohio Owners Manual 115 for Hartzell 2 7479 2 and Hartzell HCF3YR2F FC7479B2R Propellers Hartzell Propeller Piqua Ohio Spinner Assembly Maintenance Instruction Guide Issued June 1974 Hartzell Propeller Inc Piqua Ohio Maintenance Handbook for Constant Speed Hydraulic Propeller Governor Type CSSA Number 33002 Woodward Governor Company Rockford Illinois MAGNETOS Overhaul Instructions for Bendix S 1200 Series Magnetos Form L 609 Scintilla Division Bendix Aviation Corporation Sidney New York Service Parts List for Bendix S 1200 Series Magnetos Form L 608 Scintilia Division Bendix Aviation Corporation Sidney New York STARTING MOTOR Overhaul Instructions Form OE A1 Prestolite Company Toledo Ohio DEICER DISTRIBUTOR VALVE Overhaul Instructions with Parts Breakdown Publication Number 38U 2 142 Fluid Power Division Bendix Aviation Corp Utica New York Operation and Service Instructions Publication Number 39U 1 810E Fluid Power Division Bendix Aviation Corp Utica New York ELECTRONIC SYNCHRONIZER Installation Manual Bulletin Number 33032A Woodward Governor Company Rockford Illinois Propeller
51. Overhaul and Replacement Schedule MP 201 Landing Geari wee w moe ds ue de heb ao sell Power plant ove eds ge UE de m qid Re TE oe Se Pula s Gogg ede Fuel system IC M qu ae um 1809 Instruments J Tda wie eL aD eS 2 4X 204 Electrical system AE NM ANE v AE MENE Ste dy a Tec cin 205 Utility system ities Sn oe aw qu NS ak eae 205 Flaps and flight controls Ere cue dede d ustedes 8 ie NGA chu ur ptt Us wo 2206 Miscellaneous vus Lever ud uu e os es a et io tutus cus ey sa Ye ZA ae iu ed 207 5 20 00 Scheduled Maintenance Checks Maintenance Practices guru Bad ok a 201 100 HOUR INSPECTION ke E Se x CAS Ah ee Mig 202 Operational inpsei ion PNE OE ME Ge Power Plant Deb de Nak he PaO Nacelles PEOPLE CER NE ur BELO Wings Carry Through Structure Ou eu sei ogogo hoe uk oom ue dll Cabin and Baggage Compartment RA Boh Gt aa UA BERS Sen So Pa Nose Section y Dee er E ool Rear Fuselage and Empennage EN V Na o a Gan NA eld Main Gear And Brakes 2 5 220 Nose Gear Rd wr oe wind Yi ine tee Mab wr Ae i 2020 Landi
52. PRESS CONT ADJUST TURBINES 81 00 00 TURBOCHARGER WASTEGATE SHAFT LUBE TURBINES 81 00 00 TURBOCHARGER WASTEGATE VALVE ADJUST TURBINES 81 00 00 TURBOCHARGER THROTTLE CONTROLLER RIG TURBINES 81 00 00 VALVE CHECK GROUND SAFETY AIR CONDITIONING 21 30 00 VALVE FLIGHT CHECK OUTFLOW AIR CONDITIONING 21 30 00 VALVE SAFETY OUTFLOW TEST AIR CONDITIONING 21 30 00 INTROOUC TION PAGE 19 AUG 15 80 W WASTE 0 WASTE D BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM OR SYSTEM NAME ISPOSAL OESC OPER ISPOSAL MAINT PRACTICES WET WING TIP INSTALLATION WET WIN WINDOW WINDOW WINDOW WINDOW WINDOW WINDOW WINDOW WINDOW WINDOWS WINDOWS WINDSHI WINDSHI WINDSHI WINDSHI WINDSHI WINDSHI G TIP REMOVAL HINGE INSTALLATION STORA HINGE REMOVAL STORM INSTALL FLIGHT COMPARTMENT SIDE INSTALLATION CABIN SIDE WINDOWS LATCH INSTALLATION STORM LATCH REMOVAL STORA REMOVAL CABIN SIDE REMOVAL FLIGHT COMPARTMENT SIDE CLEANING CLEANING ELO DEICER SYSTEM ELO FUNCTIONAL TEST HEATED ELO HEAT SENSOR ELEMENT RES CHK ELO INSTALLATION ELD REMOVAL ELO RESISTANCE CHECK HEATED WING ACCESS OPENINGS WING ADJUSTMENT WING ASSEMBLY WING ATTACH FITTINGS WING 80 WING DI WING IN LT REPLACEMENT 4 THRU P 61 SASSEMBLY STALLATION WING REMOVAL WING TI WING TI INTRODUCTION PAGE 20 AUG 15 80 P INSTALLATION P REMOVAL CHAPTER NAME WATER WASTE WATER WASTE FUEL FUEL
53. Page 1 Nov 2 73 CHAPTER SECTION SUBJECT 11 EFFECTIVITY CONTENTS 11 00 00 SUBJECT PLACARDS AND MARKINGS Description and Operation Modei Designation Placard BEECHCRAFT DUKE 60 SERIES _ MAINTENANCE MANUAL CHAPTER 11 LIST OF PAGE EFFECTIVITY PAGE DATE 1 Apr 18 80 1 Apr 18 80 CHAPTER 11 PLACARDS AND MARKINGS TABLE OF CONTENTS CHAPTER SECTION SUBJECT PAGE 11 00 00 1 1 END 41 EEFECTIVITY CONTENTS Page 1 Apr 18 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PLACARDS AND MARKINGS DESCRIPTION AND in any correspondence to Beech Aircraft Corporation OPERATION MODEL DESIGNATION PLACARD NOTE The mode designation placard is located on the left side of Ascertain that all placards are in place and the fuselage adjacent to the inboard end of the flap The legible whenever the airplane has been flaps must be lowered to observe the placard The placard repainted or touched up after repairs Replace identifies the airplane by its model number and serial any placards that have been inadvertently number Should a question arise concerning the care of the defaced after such repainting or repairs airplane it is important to include the airplane serial number END 11 00 00 Page 1 Apr 18 80 CHAPTER SECTION SUBJECT 12 EFFECTIVITY 12 CONTENTS 12 00 00 12 10 00 12 20 00 1 17 DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 12 LIST OF PAGE EFFECTIVITY PAGE 20
54. Practices 201 Heater Removal 201 Heater Installation 201 Combustion Air Blower Removal 201 Combustion Air Blower Installation 201 Heater Ignition 202 Vibrator Removal 202 Vibrator installation 202 Inspection and Servicing Spark Plug 202 Temperature Sensors and Control Rheostat Test 203 Fuel Pump 205 COOLING m m 21 50 00 1 Description and Operation 1 Refrigerative Air Cooling System 1 Maintenance Practices 201 Charging the Air Conditioning System 201 Air Conditioning Functional Test 201 Checking Compressor Oil Level 201 Evaporator Air Fitter Replacement 203 Rigging the Air Scoop 203 Condenser Blower Removal i 204 21 CONTENTS Page 2 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 21 AIR CONDITIONING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE COOLING Cont d 21 50 00 Maintenance Practices Cont d 201 Condenser Blower Installation Cont d 204 Compressor Belt Tension Adjustment 204 Compressor Belt Removal 204 Compressor Belt Installation 204 Compressor Removal 204 Compressor Installation 205 END 21 CONTENTS Page 3 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL DESCRIPTION AND OPERATION PRESSURIZATION SYSTEM Pressurized air for the cabin is taken downstream from the turbocharger compressor of each engine and reduced to a usable flow by a sonic nozzle or venturi When sonic velocity is reached by the air flowi
55. RH horizontal stabilizer The actuator A16 A SA OR RAI HE a is located on Fuselage Station 311 19 bulkhead adjacent to the trim tab cables b Disconnect the actuator wire harness at the disconnect splices c Disconnect the actuator cable at the turnbuckle then tape the cable to the actuator to prevent the cable from unwinding d Remove the three bolts securing the actuator to the bracket and remove the actuator from the airplane ELECTRIC TRIM TAB ACTUATOR INSTALLATION a Secure the actuator to the mounting bracket with the three attaching bolts b Connect the actuator cables at the tumbuckles in the aft fuselage c Connect the actuator wire harness at the splices d Rig the tab control system NOTE The tab rigging and cable tension are identical to the manuaily operated tab e Check that the elevator trim tab cable travels frorn stop to stop in 18 to 20 seconds with 28 5 VDC applied to the airplane electrical system if necessary adjust the resistor mounted adjacent to the actuator until cable travel is within the desired limit f Install the access plate beneath the RH horizontal stabilizer ELECTRIC TRIM TAB CABLE INSTALLATION Note the position of the old cable on the cable drum in relation to the forward cable end fittings Install the new 27 30 00 Page 204A Sep 20 85 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CLUTCH HOUSING SETSCREWS CLUTCH ASSEMBLY
56. SAE10W 30 MIL G 7118 MIL G 81322 A60 604 138 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 Cont d LUBRICATION SCHEDULE LOCATION LUBRICANT INTERVAL CABLE PRESSURE SEALS DETAIL K Control cable pressure seals 8 MIL G 23827 1000 hrs Trim tab cable pressure seals 3 MIL G 23827 1000 hrs DETAIL K A60 604 14A 12 20 00 Page 221 Nov 2 73 BEELNUNAr DUKE 60 SERIES MAINTENANCE MANUAL Fuselage Access openings Sheet 1 of 2 Figure 203 12 20 00 Page 222 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL Elevator Hinges 11 Uptock Cable Retract Rods Retract Rod Pressure Seals and Wing Stub Fue Fittings Tail Cone 12 Lower Pedestal Elevator Trim Tab Actuator 13 Landing Gear Gearbox and Actuator Rudder Trim Tab Actuator 14 Assist Step Mechanism Deicer Dump Valve Elevator Bell Crank Rudder Bell Crank and Control Cables 15 Autopilot Aileron Rudder and Elevator Servos Magnetic Navigation Sensing Element Vertical Stabilizer Deicer Hose B 5P Autopilot and Autopilot Computer H 14 Autopilot Emergency Exit 16 Oxygen Filler and Bottle Heater Ram Air Wing Bolts Plenum Brake Fluid Reservoir Avionics Equipment and Baggage Compartment Nose Cone 17 Cabin Door Hinges Intercooler Fuselage Access Openings Sheet 2 of 2 Figure 203 12 20 00 Page 223 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 31 12 10 1 9 87 621 1 29 6 52 3
57. SKIN Check for deformation and obvious damage or cracks Check for loose or missing rivets NACELLE STRUCTURE Check for cracks and deformation Check for loose or missing rivets and concealed damage PNEUMATIC PRESSURE REGULATORS Check for condition security and attachment INLINE FILTERS Clean or replace as required the fil ter in each nacelle as outlined under the heading SER VICING in Chapter 36 00 00 BATTERY Inspect for clean tight connections and cor FUEL QUANTITY TRANSMITTER Check for attachment electrical connection 5 20 00 Page 21 rect fluid level Add distilled water as required Inspect the vent hose at the battery box for obstructions The battery box should be washed out thor on dried each time the battery is removed and cleaned i 0 20 87 INSP INSP BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL FUEL CELLS AND VENTS Inspect fuel cells for leakage and vent lines for security as outlined in Chapter 28 10 00 PLUMBING Check for leakage chafing condition and security ELECTRICAL WIRING AND EQUIPMENT nee for chafing damage security and attachment AIR CONDITIONING Check for condition security and attachment D WINGS AND CARRY THROUGH STRUCTURE 1 SKIN Check for deformation and obvious damage Check for cracks loose or missing rivets If damage is foun
58. Series 67 Compressor Service Manual Form 180 33NM York Corporation York Pennsylvania Renewal Parts List Form 180 33RP York Corporation York Pennsylvania OUTFLOW AND SAFETY VALVE Operation and Maintenance Instructions Report No 4 268 15 April 1975 Garrett Airesearch Manufacturing Division Los Angeles CA aM FUEL CELLS Recommended Handling and Storage Procedures for Bladder Type Fuel and Oil Cells Publication Number FC1473 73 Uniroyal inc Mishawaka Indiana 46544 Repair Procedures for Heated Repairs to Bladder and Self sealing Fuel Cells Repair Procedure RK 72 February 3 1977 Uniroyal Inc Mishawaka Indiana 46544 INTRODUCTION Page 10 i Nov 30 83 14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NEWMATIC AUTOPILOT B 8 Ground and Flight Check Procedures Manual Number 3957 Brittain Industries Torrance California LANDING GEAR MOTOR Component Maintenance Manual with Illustrated Parts List for Landing Gear Motor P N 27 4 and 27 8 Electro Mech Inc Wichita Ks BRAKES Overhaul Information for A22 Brake Shuttle Valve Publication N mber 74456 Hoof Products Co Chicago Illinois Overhaul Information for Brake Shuttle Valve A SA404 Publication Number 23595 Paramount Machine Co Stow Ohio EMERGENCY LOCATOR TRANSMITTER Operating Instructions for Model CIR 10 Emergency Locator Transmitter System Transmitter P N TR 70 17 Collins Communications Components Corporation Costa
59. WINDOWS WINDOWS WINDOWS WINDOWS WINDOWS WINDOWS WINDOWS WINDOWS SERVICING WINDOWS ICE ANO RAIN PROTECTION ICE AND RAIN PROTECTION ICE AND RAIN PROTECTION WINDOWS WINDOWS ICE AND RAIN PROTECTION RINGS WINGS WINGS WENGS HINGS WINGS WINGS WINGS WINGS WINGS END CHAPTER SUB CHAPTER 38 30 00 38 30 00 28 10 00 28 10 00 56 10 00 56 10 00 56 10 00 56 20 00 56 10 00 56 10 00 56 20 00 56 10 00 12 20 00 56 00 00 30 40 00 30 40 00 30 40 00 56 10 00 56 10 00 30 40 00 57 30 00 57 00 00 57 00 00 57 40 00 57 00 00 57 00 00 57 00 00 57 00 00 57 00 00 57 00 00 CHAPTER SECTION SUBJECT 5 EFFECTIVITY 5 CONTENTS 5 10 00 5 20 00 A18 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 5 LIST OF PAGE EFFECTIVITY PAGE Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov Nov DATE 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 20 87 5 EFFECTIVITY Page 1 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 5 TIME LIMITS MAINTENANCE CHECKS TABLE OF CONTENTS SUBJECT CHAPTER PAGE 5 10 00
60. airplane off the ground Each jack pad is identified and located on the under side of the fuselage One jack pad is located on each lower wing to fuselage attachment fitting along the rear spar The forward jack pad is located in the middle of the fuselage just aft of the nose gear wheel well The Model 400 service jack and three adapters P N 60 590013 on P 3 through P 61 60 590013 1 P 62 and after are designed to be used with this airplane When one engine or one wing is to be removed a stand should be placed under the opposite wing and the tail to counteract the resulting unbalanced condition of the airplane Individual main wheels may be jacked by placing a floor jack under the jacking point located under each axle END 7 00 00 Page 1 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 8 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 8 EFFECTIVITY CONTENTS 1 Nov 2 73 8 00 00 201 Nov 2 73 CHAPTER 8 LEVELING AND WEIGHING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 8 00 00 201 Maintenance Practices 201 Leveling 201 ND 8 EFFECTIVITY CONTENTS Page 1 Nov 2 73 BEECHCRAFT OUKE 60 SERIES MAINTENANCE MANUAL GENERAL MAINTENANCE PRACTICES LEVELING The aircraft may be leveled longitudinally as follows Remove the phillips head screw from the upper level point located just aft of the cabin door b Install a screw approximately three inch
61. amperes should be connected in series with the battery and power source to monitor the charging current when the master generator panel meter indicates that the current has dropped sufficiently Charging should continue until the ammeter indicates a current flow of 1 ampere or less or until a maximum time of 4 hours has elapsed d Should a battery be severely discharged charging by the constant potential method may produce a slight imbalance in cell capacity The imbalance can be detected by a periodic check of the cell terminal voltages with a precision voltmeter after the charging current levels off to a few amperes while the battery is charging Should some cells differ from others by more than 05 volts connect the battery to a constant current source and charge for 14 hours at a rate of 1 4 amperes on a 13 5 ampere hour battery If the cells still fail to equalize perform an equalization charge BATTERY STAND BY CHARGING Since the self discharge rate of a nickel cadmium battery is approximately 1 2 percent per day at normal temperatures standby charging is required to maintain a battery at its full rated capacity For standby charging in the temperature range of 60 F to 90 F use a current equal to 003 ampere per each ampere hour of rated capacity Batteries on stand by charge must be regularly checked to ensure adequate electrolyte level CAPACITY RECONDITIONING The capacity of a nickel cadmium battery does not decrease app
62. automatically provided to the holders of this manual For information on how to obtain a revi sion service applicable to this manual refer to BEECHCRAFT Service Instructions No 0250 010 Rev or subsequent revisions CORRESPONDENCE If a question should arise concerning the care of your air plane it is important to include the airplane serial number in any correspondence The serial number appears on the mode designation placard refer to Chapter 11 for placard location ASSIGNMENT OF SUBJECT MATERIAL The content of this publication is organized at four levels Group System Chapter Sub System Section and Unit Sub ject Group Identified by different colored divider tabs These are primary divisions of the manual that enable broad separation of content Typical of this division is the sep aration between Airframe Systems and the Power Plant System Chapter The various groups are broken down into major systems such as Air Conditioning Electrical Power Landing Gear etc The systems are arranged more or less alphabetically rather than by precedence or importance They are assigned a number which becomes the first element of a standardized numbering system Thus the element 28 of the number 28 00 00 refers to 14 the chapter Fuel Everything concerning the fuel system will be covered in this chapter Sub System Section The major systems of an aircraft are broken down into sub systems These su
63. battery box b Coat the battery terminals and cable terminals with a lightzcoating of petroleum jelly CAUTION if the POSITIVE battery terminal is not marked 4 POS or painted red and the NEGATIVE bat tery terminal is not marked NEG or painted black use a voltmeter to determine the battery polarity before connecting the battery in air plane Reverse polarity will destroy the diodes and other electronic components in the electrical system c Position the POSITIVE cable terminal on the bat tery and secure d Position the NEGATIVE cable terminal on the bat tery and secure Instali the bus bar interconnect on both batteries f Remove any excess petroleum jelly from the termi nals g Position the battery box lid on the battery box and secure h Install the nuts on the hold down strap bolts i Install the access door BATTERY CLEANING For peak performance the batteries must be kept clean and dry tf foreign materials are present in sufficient quantities the resultant deposits may form conductive paths that permit a rapid discharge of the batteries To prevent the collection of such deposits use the following steps in cleaning the bat teries zafter each 100 hours of service or every 30 days whichever occurs first a Remove the batteries as described in the section BATEERY REMOVAL lt b Ensure that the battery ceil filler caps are tight in place Brush dirt off with a stiff
64. box should be washed out thoroughly and dried each time the battery is removed and cleaned BATTERY SERVICING The batteries should be maintained in a fully charged state at all times and the electrolyte level checked at regular inter vals Clean fully charged batteries will provide peak perform ance Never add anything but distilled water when adjusting the electrolyte level in the batteries If electrolyte is added each time the level in the batteries are low a high tion of electrolyte may cause dissolution of the plates Under high temperature conditions this may be indicated by the presence of black particles in the electrolyte of the affected celis NOTE Do not fill the batteries over one half inch above the separators Only lead acid equipment should be used when servicing lead acid type batteries RECHARGING BATTERIES USING AUXILIARY POWER The following steps should be used in using auxiliary power to recharge the battery a Place the battery master switch in the on position b Place both alternatcr switches and ai electrical and avionics equipment switches in the off positions c Connect the auxiliary power unit to the external power receptacle CAUTION Make certain that the battery switch is in the on position all avionics and electrical switches are in the off positions and batteries are in the sys tem before connecting an external power unit This protects the electrical voltage regul
65. cell that measured below 1 50 volts at 24 charge hours After removing the battery from charge measure the electrolyte temperatures If the electrolyte temperature of any cell is greater than 30 F above the ambient replace that cell BATTERY ELECTROLYTE LEVEL ADJUSTMENT Although the electrolyte level in the nickel cadmium battery varies with the state of charge it should be visible above the bottom of the baffle when the battery is fuily charged When the state of charge of the battery is low the plates absorb some of the electrolyte then release it as the battery is recharged The electrolyte level on any battery must be adjusted after a full charge and a two to four hour rest on open circuit Check the electrolyte level of the battery fully charged in the following manner CAUTION Never use acid or tools contaminated with acid during this adjustment for both bodily injury and equipment damage may result f possible use equipment reserved for nickel cadmium batteries If lead acid battery equipment must be used remove all possible acid contamination with a sodium bicarbonate solution and rinse Even minute traces of acid can damage a nickel cadmium battery a Remove the battery from the aircraft b With the battery removed from the aircraft remove the filler cap vent plug on each cell one cell at a time Insert a transparent tube approximately 6 inches long and 1 4 inch in diameter perpendicularily into
66. control head d Hold the outer ring of the control head and rotate the cabin altitude selection knob until the actual cabin altitude as indicated on the cabin altimeter aligns with the reference mark see step Align the guide pin and slide the control head back on the bellows shaft without turning the shaft f Secure the control head in place with the Allen screw and reinstali the controller in the subpanel For proper information relating to overhaul and cleaning procedures refer to Component Maintenance Manual P N 0 590001 27 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CABIN ALTITUDE CONTROLLER REMOVAL MOTORIZED a Remove the four attaching screws at the subpanel b Remove the screw washer and support clamp located behind the subpanel from the controller c Loosen and remove plumbing from the controller Cap open plumbing to keep shop soil dirt and foreign objects from entering d Remove the controller CABIN ALTITUDE CONTROLLER INSTALLATION MOTORIZED a Remove plumbing cap and install plumbing to controller b Position the controller in the subpanel c Install the support clamp on the controller and attach with the screw and washer d install the four attaching screws at the subpanel CABIN ALTITUDE CONTROLLER ADJUSTMENT MOTORIZED The controller does not need to be removed from the subpanel for this adjustment a Loosen the control head r
67. cure to 85 of its full hardness in 24 hours at temperatures of 80 F or higher Page 205 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL URETHANE TOUCH UP REPAIR a Mask around the skin containing the damaged area b Remove all loose edges of paint by using a high tack adhesive tape around the edge of the damaged area c Using a coarse sandpaper fair the edge of the damaged area d When the edge of the paint begins to fair into a smocth joint use a fine grade of sandpaper to eliminate the scratches left by the coarse paper Take care to avoid remov ing any more metal than is absolutely necessary e Wash the sanded area with a solvent such as lacquer thinner or toluene Do not use methyl ethyl ketone as it will soften urethane paint Change the wash cloths used for this purpose often so that all the sanding dirt will be picked up f After the area to be touched up has been cleaned with solvent until all traces of discoloration are gone apply thin coat of pretreatment primer to the damaged area NOTE metal conversion coating such as iridite or alodine is used the wash primer coating can be dispensed with If the metal has not been treated with a metal conversion coating and no wash primer is available carefully clean the surface to be touched up and apply urethane primer to the bare metal This should produce a satisfactory undercoat for the repair area g After the urethane primer has cur
68. either or both sides The inboard trailing edge of the flap must be within 20 inch above or below the trailing edge of the wing stub on either or both sides The gap between the flap and aileron must be between 13 and 50 inch FLAP TRACK ROLLER INSTALLATION install the rollers four per flap and two per track in the flap track brackets with the flanges to the outboard side of the inboard track and to the inboard side of the outboard track Install a 50 105000 3 washer between each of the aft rollers and its respective track Use only the wide flanged rollers in the aft locations The clearance between the roller and the front end of the forward slot in each track must be 03 to 12 inch FLAP CONTROL SYSTEM RIGGING Figure 201 The flap limit switches are mounted on a bracket and installed on the outboard side of the inboard track in the left wing panel The limit switches one for up two for the approach position and one for down travel control the travel of the flaps by breaking the circuit to the flap motor at the extreme limits of selected travel The switches are accessible by lowering the flaps NOTE An additional 16 limit switch is installed on serials P 247 and after The flap travel is adjusted by moving the limit switches The left flap is rigged first and then the right flap is synchronized with it Rig as follows NOTE Rig the flaps under a simulated flight load to reduce overtrave to a minimum af
69. engine nacelle The receptacle is designed for a standard AN type plug To supply power for ground checks and air conditioner operation a ground power source capable of delivering a continuous load of 300 amperes at 24 to 30 volts is required Use of an inadequate ground power unit can cause a voltage drop below the drop out voltage of the starter relay resulting in relay chatter and welded contacts By the same token a maximum continuous load in excess of 350 amperes will damage the external power relay and power cables of the aircraft Observe the following precautions when using an external power source a Use only an auxiliary power source that is negatively grounded If the polarity of the power source is unknown determine the polarity with a voltmeter before connecting the unit to the aircraft b Before connecting the external power unit turn off all radio equipment and generator switches but leave the battery on to protect transistorized equipment against transient voltage spikes CAUTION When the battery switch is turned OFF for extended ground power operation place an external battery in parallel with the output of the external power unit before operating any transistorized avionics equipment c f the unit does not have a standard AN plug check the polarity and connect the positive lead from the external power unit to the center post and the negative lead to the front post of the aircraft s external power recept
70. establish a steady flow of cabin air f Open the pressurization system circuit breaker Note that the safety valve on the aft pressure bulkhead closes and the airplane starts to pressurize g Selecta cabin altitude that is approximately 1 500 feet below the field elevation The cabin will pressurize at a rate of change rate to decrease the cabin altitude BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL h Rotate the rate contro selector knob counterclockwise and note a reduction in rate of change of cabin pressurization i Rotate the rate contro selector knob clockwise and note a reduction in the rate of change of cabin pressurization j Rotate the cabin altitude selector knob to the full counterclockwise stop and select a rate of change that is comfortable The cabin to atmosphere pressure differential will increase The value of the differential pressure attained will depend upon the field elevation at which the test is conducted k When the cabin pressure has stabilized disconnect and cap the plumbing from the cabin pressurization controller port labeled VACUUM Cap the plumbing and the controller port to prevent the entrance of foreign materials The cabin to atmosphere pressure differential will now increase to the normal positive differential pressure setting of the outflow valve and the safety valve NOTE Cabin pressure will increase to the maximum differential value at an uncontrolled rate when the vacuum line i
71. g and h adjust the dashpot clockwise approximately 1 2 turn for each 400 fpm Maximum clockwise adjustment is one turn l If lift off descent is small and isobaric descent is excessive as recorded in steps g and h adjust the dashpot counterclockwise approximately 1 2 turn for each 400 fpm m Reinstall the upholstery panels to the aft pressure bulkhead 21 30 00 Page 202 May 30 75 CABIN ALTITUDE CONTROLLER REMOVAL MANUAL a Remove the four attaching screws at the subpanel b Loosen and remove piumbing from the controller Cap open plumbing to keep shop soil dirt and foreign objects from entering c Remove the controller CABIN ALTITUDE CONTROLLER INSTALLATION MANUAL Remove plumbing and install plumbing to controller b Position the controller in the subpanel C Install the four attaching screws at the subpanel CABIN ALTITUDE CONTROLLER ADJUSTMENT MANUAL a Make a reference mark on the outer ring of the controller contro head to match the triangular mark on the edge light panel directly above the controi b Remove the controller from the subpanel NOTE The controller should be removed from the subpanel prior to take off if the need for adjustment is anticipated Loosen the contro head retention Allen screw and skide the control head off the bellows shaft without turning the shaft NOTE Do not loosen the slot head screw in the knob on the
72. heater system servicing after an over temperature condition has occured CAUTION Make certain any malfunction causing an overheat condition is corrected before attempting to operate the heater For additional heat the PRESSURIZATION AIR TEMI CONTROLS located on the copilot s RH subpane b pulled out to restrict cooling air flow through the cabin ai heat intercooler For maximum heat in the unpressurizec mode push the CABIN AIR control full forward to sto the flow of incoming cold air NOTE The intercooler doors should be closed during all heating operations to reduce the load on the heater Conversely the doors should be open to reduce load during all cooling operations END 21 40 00 Page 2 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL HEATING MAINTENANCE PRACTICES HEATER REMOVAL The heater should be removed from the aircraft and disassembled All parts should be thoroughly inspected and necessary repairs and parts replacements made every 500 hours of operation The heater is removed as follows a Remove the necessary nose baggage compartment floorboards to gain access to the heater b Loosen the clamp and disconnect the duct from the combustion air blower c Tag the wires and disconnect the wire harness from the heater d Loosen the clamps around the fuel inlet tine boot and slide the boot up the fuel fine Disconnect the fuel line from the heater e Remove the safety wi
73. intake duct and seal with EC 1792 sealant Chart 205 Chapter 91 00 00 INTERCOOLER CONTROL RIGGING Figure 201 The controls used on the intercooler installation are the Push pull type In the event the control needs minor adjustment a set pin with a hole provided for the control wire may be tightened if loose NOTE Make an operational check of the push puil control for correct adjustment and full travel INTERCOOLER CONTROLS FIREWALL SHUT OFF VALVE Intercooler and Firewall Shut off Valve Controls Figure 201 FIREWALL SHUT OFF VALVE Figure 201 During normal flight operations the FIREWALL SHUT OFF VALVE controls are pushed in against the lower RH subpanel This will allow maximurn airflow to enter the cabin In the event of a fire inside the engine cowl immediately pull the red handled control out to the stop This will shut off the air flow from the inoperable engine A check valve located just inside the pressurization airflow inlet will close and prevent complete loss of cabin pressurization This control is preset at the factory and should not need any further adjustment END 21 10 00 Page 201 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PRESSURIZATION CONTROL DESCRIPTION AND OPERATION P 3 THRU P 307 Cabin altitude is selected and controlled by the cabin altitude controller located on the RH subpanel standard manual controller is utilized by the various se
74. is replaced The compressor is serviced with oil 18 Chart 207 91 00 00 Only these or equivalent oils should be used when adding oil To check the compressor oil level use the following procedure CHART 201 AIR CONDITIONING FUNCTIONAL TEST 45 49 54 59 64 69 TEMPERATURE F AMBIENT OAT PLENUM MAX SUCTION DISCHARGE Measure temperature at outlet nearest plenum COMPRESSOR PRESSURE PSI 120 170 140 200 165 230 185 260 205 290 230 320 21 50 00 Page 201 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL FINGER RING 108 NOTCHES 1 10 IN APART OIL CHECK PLUG ALSO OTHER SIDE 60 451 1A Dipstick and Compressor Oil Check Plug Figure 201 a Operate the air conditioner for approximately 15 minutes in which the last 5 minutes should be at low engine rpm 1 000 to 1 100 This allows the oil to accumulate in the compressor for an accurate oil level reading b Attach service gages to compressor service valve ports c With air conditioner operating slowly close the suction service valve until the suction pressure gage reads 0 or slightly below d Stop the air conditioner and quickly close the suction service valve when the suction gage reads a littie above zero e Close the discharge service valve f With both service valves closed the suction pressure will slowly rise to about five pounds gage pressure g The remaining pr
75. leng ached Tighten the outboard nut against the mounting support M 60 AIRPLANES ARE EQUIPPED v A SPRING IN THIS LOCATION 2 THAT THE SPRING IS INSTALLED FORWARD RETAINER 50 361131 MOUNT ING SUPPORT ae gt OUTBOARD p NODE SET SCREW SET SCREW RETAINER MEE KEYWAY OUTBOARD WASHER KEY SLOT IN INBOARD INBOARD MOTOR SHAFT NUT WASHER ENSURE THAT THERE IS SUFFICIENT CLEAR ANCE BETWEEN THE OUTBOARD EDGE OF THE RETAINER AND THE CABLE HOUSING TO ALLOW THE RETAINER TO ROTATE WITHOUT COMING INBOARD END VIEW OF OUTBOARD END VIEW OF INTO CONTACT WITH THE HOUSING RETAINER 50 361131 RETAINER 50 361131 930 04 0116 27 50 00 Page 1 of 1 Temporary Revision No 27 2 Nov 15 93 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL on the flap actuator in the right wing just forward of the rear spar a Adjust the travel limit switches to provide the correct flap travel Refer to FLAP CONTROL SYSTEM RIGGING b Run the flaps down and check the pilot s compartment flap position indicator for 100 flaps tf full down flaps are not indicated loosen the transmitter attachment bolts and adjust fore and aft or rotate slightly until the reading is correct then tighten the transmitter attaching bolts c Run the flaps up and check the indicator for up flaps reading FLAP POSITION INDICATOR LIGHTS ADJUSTMENT AND FUNCTIONAL CHECK P 247 and After Figure 201 The flap position indicator lights
76. list of the various conditions which warrant battery replacement a Visual inspection shows signs of leakage corrosion or unsecured leads b Elapsed replacement date noted on the battery case this date represents 50 of the useful life of the battery NOTE The useful life of the battery is the length of time which the bat tery may be stored without losing its ability to continuously oper ate the ELT for 48 hours c After any emergency use d After one cumulative hour of use e After operation of unknown dura tion f If the transmitter is stored in an area where the temperature is normally above 38 C 100 F battery life will be shortened CAUTION Avoid storage of batteries at temperatures in excess of 55 C 130 F The information battery life and replacement is included in the data fur nished with each ELT and is usually placarded on the battery NOTE Replacement batteries should be obtained only from ELT and air plane manufacturers or other acceptable suppliers since the condition and useful life of over the counter batteries such A18 as those sold for flashlights portable radios etc are usual ly unknown CAUTION The ELT switch should not be turned ON unless the ELT is con nected to its associated antenna or a 50 ohm dummy load COLLINS COMMUNICATIONS COMPONENTS CORPORATION BATTERY REPLACEMENT NOTE The Narco ELT may be supplied by Kit No 101 3046 f
77. movement should be made with the toggle switch The inner scale shows the cabin altitude when read at the index mark 12 o clock position The outer scale under the window shows the selected airplane altitude The inner scale adjacent to the window shows what the cabin altitude will be when maximum differential pressure 4 6 psi is reached To ready the unit for operation place the rate rheostat knob in the mid range and insure that the directional toggle switch is in the off position CAUTION In event the directional toggle switch is positioned improperly the controller will drive to the end of the scale and damage to the slip clutch may result Manually set the cabin altitude controller inner scale to approximately 1 000 feet above the take off field elevation The red altitude selector ring will turn with the inner scale when this adjustment is made Now set the window on the red altitude selector ring to 1 000 feet above the planned airplane s cruise altitude This will avoid reaching maximum differential pressure in the cabin prior to achieving cruise altitude After take off and during the climb when the cabin rate of climb has returned to zero move the directional toggle switch to the up position This gradually climbs the cabin to the altitude which is opposite the altitude in the window on the red selector ring The controller should be driven at a rate to arrive at the cabin altitude shortly before the 21 30 00 Pag
78. outflow valve differential adjustment every 300 hours of airplane operation or annually On airplane serials P 308 and after perform a functional test of the outflow safety valves every 500 hours On airplane serials P 308 and after clean the cabin pressurization controller filter and orifice each 500 hours clean the safety valve filter and orifice each 1000 hours For checking cleaning and testing procedures refer to Chapter 21 30 00 FLAP MOTOR AND SHAFTS Check for condition security and wear at all points Check cable housing for securi ty and check jam nuts for tightness BRAKE MASTER CYLINDER AND PARKING BRAKE VALVE Check for condition security and leaks Check lines for signs of chafing or cracks 5 20 00 Page 214 Nov 20 87 1 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CABIN AND BAGGAGE COMPARTMENT Cont d MECH INSP 7 RUDDER PEDALS Check for freedom of movement Check cables push pull rods bell cranks pulleys turnbuckles fairleads for proper routing condition and security Check rudder pedal fore and aft positions for wear Check locks and pins to ensure positive lock NOTE On airplane serials 555 and after and ear lier airplanes with the noted replacement rudder pedal arms the following inspection is accomplished at 300 hour intervals 8 RUDDER PEDAL ARMS Check pedal arms for cracks and replace at 2000 hours or sooner if cracks are found Replace P N 50
79. pump Float valve Hoses carrying flammable liquids All other hoses A18 CORP TCR a hl JE V REN ANE NEVAR ET VAS Pos Lae OVERHAUL OR REPLACE On condition On condition replace when contaminated Every 2000 hours or 5 calendar years whichever occurs first On condition every 1600 hours Every 600 hours or on condition Every 1600 hours When condition warrants 5 years from date of deliv ery or at engine overhaul whichever occurs first On condition On condition On condition On condition On condition On condition Every 1000 hours Every 800 hours On condition When condition warrants 5 years from date of deliv ery or at engine overhaul whichever occurs first On condition 5 10 00 Page 203 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE Cont d ITEM FUEL SYSTEM Cont d Fuel pump engine driven INSTRUMENTS Turn and bank indicator Aitimeter Directional gyro Gyro horizon Dry air pressure gage Cabin altitude control Cabin altitude controller filter standard Cabin altitude controller filter motorized Manifold pressure gage Airspeed indicator Cabin differential pressure gage Cabin altitude and pressure differential indicator Rate of climb indicator Fuel pressure gage Fuel flow gage Tachometer Flap position fndicator Free air temperature indicator Gyro instrument filter Air
80. pump inlet filter A11 hoses 5 10 00 Page 204 Nov 20 87 OVERHAUL OR REPLACE Every 1200 hours On condition Every 24 months per FAA direc tive On condition On condtion On condition Cn condition On condition Every 100 hours On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition Every 500 hours On condition On condition A1 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE Cont d ITEM OVERHAUL OR REPLACE INSTRUMENTS Cont d Air pump inline filter 300 hours ELECTRICAL SYSTEM Landing gear dynamic brake relay On condition Battery master relay On condition Paralleling relay On condition All other relays On condition Voltage regulators On condition Heater vibrators Replace at heater overhaul Starter Inspect at engine overhaul and overhaul or replace on con dition Starter relay On condition Generator On condition Battery Emergency Locator Transmitter At 50 of useful life as stated on the battery or s any time transmitter is used more than one cumula tive hour or after inad vertent activation of unknown duration UTILITY SYSTEM Cabin heater Every 1000 hours or whenever ZAE pressure decay test reguirements cannot be met See appropriate manufactur er s manual Heater igniter and plug On condition Heater fuel pump On condition Heater fuel
81. purchased if service ther than lubrication is required HYDROLOK LOCKS Hydrotok locks will usually need no service but if service is reguiced return the unit to the manufacturer END Page 202 Apr 18 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL EMERGENCY DESCRIPTION AND OPER ATION EMERGENCY LOCATOR TRANSMITTER Airplane serials P 166 P 183 thru P 185 P 187 thru 244 and P 246 and after are equipped with an emergency locator trans mitter ELT to assist in the tracking and recovery of any airplane and crew in the event of a crash or if an emergency landing is necessitated Airplane serials P 166 P 183 thru P 185 P 187 thru P 244 and P 246 thru P 536 are equipped with Collins Communications Corporation ELT units Narco ELT units are installed on airplane serials P 537 and after and ear lier airplanes equipped with Kit No 101 3046 1 The ELT is mounted in the aft fuselage on the RH side at approximately F S 290 00 An antenna for the ELT is mounted on top of the fuselage under the vertical stabilizer at approximately F S 297 00 The output frequencies of the ELT are 121 5 and 243 0 MHz simultaneously Range is approximately line of sight The ARM OFF ON switch located on the trans mitter controls the operation of the set The ON position turns the set on for testing and the ARM position actuates the set to operate automatically upon impact A reset switch located on the forward end of the trans
82. ram air to the cabin is located on the copilots LH subpanel Pull the CABIN AIR control full aft for maximum air The CABIN AIR control is overridden when the cabin is pressurized e For windshield defrosting operate the heater in either the auto or manual mode and puil out the DEFROST control located on the pilot s LH subpanel f Heated air is normally directed onto the pilot s feet To shut off this air pull out the PILOT AIR control located on the pilot s LH subpanel g The COPILOT AIR control identical to the PILOT AIR control is located on the copilot s RH subpanel 21 40 00 Page 1 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NOTE The volume of air available for the pilot outlet and copilot outlet can be divided between the two outlets as desired by adjusting each control individually More heated air will be available for defrosting by reducing the flow of air from the pilot and or copilot outlets If malfunction resulting in dangerously high temperatures 300 F to 400 F should occur the heater over temperature switch will lock out and blow either the over temperature fuse manual mode or the over temperature fuse auto mode in the heater power circuit This renders the heater system except the blower inoperative The over temperature fuses are located behind the LH upper side panel The heater over temperature switch is located on the heater assembly The switch must be manually reset during
83. stones and ruts and will minimize tread wear When inflating tires inspect them visually for cracks breaks or evidence of external damage EXTERNAL POWER The airplane electrical system is protected against damage from reverse polarity by a relay and diodes in the extemal power circuit The extemal power receptacle is located just outboard of the left engine nacelle The receptacle is de signed for a standard AN type plug To supply power for ground checks and air conditioner operation a ground power source capable of delivering a continuous load of 300 am peres at 24 to 30 volts is required Use of an inadequate ground power unit can cause a voltage drop below the drop out voltage of the starter relay resulting in relay chatter and welded contacts By the same token a maximum continuous load in excess of 350 amperes will damage the extemal power relay and power cables of the airplane Observe the following precaution when using an extemal power source a Use only an auxiliary power source that is nega tively grounded If the polarity of the power source is un known determine the polarity with a voltmeter before con necting the unit to the airplane b Before connecting the external power unit tum off all radio equipment and generator switches but leave the battery on to protect transistorized equipment against trans ient voltage spikes CAUTION When the battery switch is tumed off for ex tended ground power oper
84. than 13 5 ma on 13 5 ampere hour batteries the battery should be cleaned This test should be made again after the battery has been completely cleaned and charged If the current measure is again more than 13 5 ma on 13 5 ampere hour batteries it may be assumed that one of the cells has a seal leak That cell may be found by measuring connector to battery case voltages The lowest voltages will occur at the connectors on each side of the defective cell A cell found leaking in this manner should be replaced CAPACITY CHECK a Discharge the battery at a rate of 6 0 amperes on 13 5 ampere hour batteries until an average voltage of one volt per cell is reached Measure the time required for the battery to reach that discharged state Any battery that discharges to one volt per cell in 84 minutes or less should be given another reconditioning deep cycle b After the second reconditioning cycle recheck the battery capacity by discharging at the rate used in step Measure the individual cell voltages after 84 minutes of discharge f any cell is below one voit replace it CLEANING AND INSPECTION a Scrub each cell with a 5 percent solution of boric acid in water but take great care to prevent the solution from entering the cell b Wash each ceil off under running water and dry with an air hose or clean absorbent towel c Inspect each cell for defects such as cracks holes or burn spots Replace defective cells with new or r
85. the ambient temperatures are above 90 F or the time between engine starts averages less than 30 minutes the duty cycle should be reduced d The log of battery services performed should be evaluated to determine the need to service the battery at the above recommended intervals or to extend the intervals if justified Accurate water consumption data is a valid baro meter to use for adjustment of the servicing intervais 12 20 00 Page 201 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CAUTION Methods of servicing lead acid batteries do not apply for the servicing of nickel cadmium bat teries Since the proper servicing of nickel cadmium batteries re quires two days an additional battery or batteries will be required where airplane utilization warrants For additional information on battery maintenance refer to Gulton Instruc tions for Use and Care of Sintered Plate Vented Nickel Cadmium Storage Batteries P N 1 100 or Marathon Battery Instruction Manual P N BA 89 or Operating and Service Manual for General Electric Nickel Cadmium Ven ted Cell Batteries P N GET 3593A which ever the airplane is equipped with Advisory Circular AC 00 33 printed by Department of Transportation Federal Aviation Administra tion is another good source of battery maintenance information DEICE BOOTS Because the deice boots and related components operate on clean air supplied from the pressure manifold li
86. thinner or an equivalent solvent NOTE Unprimed areas of magnesium castings are to be coated with MIL C 16173 corrosion preventa tive compound 43 Chart 207 91 00 00 unless these areas will come into contact with oil or grease after assembly Any holes in the castings which will receive bushings or bearings shail be coated with wet unreduced zinc chromate primer Or corrosive preventative compound at the time of installation b Prime the affected area and apply either the enamel or urethane topcoat if applicable NOTE Do not apply wash primer to magnesium sur faces Allow a minimum of four hours drying time between application of the primer and top coat BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SPECIAL PAINT PROCEDURES PROPELLER BLADES Paint the backs of the propeller blades with quick drying enamel per MIL E 5556 color No 37038 per Federal Stan dard 595 LANDING LIGHTS Paint the landing light wells excluding the ribs at the inboard and outboard ends the spar and attaching angles with quick drying enamel per MIL E 5556 color No 37038 per Federal Standard 595 AIR CONDITIONER EVAPORATOR COMPARTMENT Apply epoxy primer 24 Chart 207 91 00 00 to the entire surface area of the parts which make up the compartment NOSE RADOME Sanding surfacer or filler may be used to obtain a smooth surface Sand with 180 sandpaper just enough to remove the glaze After sanding the radome contour shali
87. thru P 307 Outflow and Safety Valve P 308 and After CHANGE Engine Oil Engine Oil Filter CLEAN Air Pump Intake Filter Induction Air Filter Servo Fuel Filter Manual Cabin Altitude Con trol Filter P 3 thru P 307 Cabin Pressurization Controller Filter and Orifice P 308 and after A14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 203 SERVICING LOCATION Access door on upper cowling 2 Access plate on LH rear nacelle 1 See Chapter 21 for location and special instructions See Chapter 21 for location and Special instructions Access cap on propeller spinner 2 2 Lower rear of engine 2 Aft pressure bulkhead Aft pressure bulkhead Access plate on lower naceile 2 RH side of engine 2 Forward side of aft engine baffle 2 P 3 through P 246 RH rear side of engine 2 Fuel injection 2 RH subpane 1 RH Subpanel 1 SERVICE WITH MIL L 22851 See Chapter 24 for detailed instruc tions Suniso No 5 or Texaco Capella E 500 Viscosity oil Refrigerant No 12 Dry air or nitrogen Dry air or nitrogen Refer to Chapter 21 30 00 Refer to Chapter 21 30 00 MIL L 22851 Wash with soap and water rinse l and dry Clean per instructions on filter Clean with solvent and blow dry with air pressure Clean with solvent and blow dry with air pressure Remove filter disassembie clean with solvent and air dry Ensure Orifice is open reassemble and rei
88. to the flap d Check rigging of the wing flap control system e If a new or overhauled actuator is installed lift lightly on the flap trailing edge while running the flap through a complete extend retract cycle There should be no roughness or evidence of binding in the actuator FLAP MOTOR GEARBOX REMOVAL a Gain access to the flap motor through the cabin floor panel at the rear spar carry through b Disconnect the electrical wiring at the motor c Remove the drive shaft retainers on each side of the gearbox and disconnect both flexible drive shafts from the support bracket d Remove the four bolts attaching the motor gearbox to the support bracket and remove the motor gearbox as a unit FLAP MOTOR GEARBOX INSTALLATION a Position the flap motor gearbox against the support bracket and install the four bolts Secure the bolts with safety wire b Connect the flexible drive shafts to the gearbox and install the drive shaft retainers c Connect both flexible drive shafts to the support bracket d Degrease the retainer threads with primer 40 Chart 207 91 00 00 Apply thread locking compound 36 Chart 207 91 00 00 to the retainers prior to installation e Connect electrical wiring at the motor f Install the cabin floor access panel g Perform a FLAP FUNCTIONAL GROUND TEST END 27 50 00 Page 203 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL STALL WARNING SYSTEM DESCRIPTION AND OPERA
89. water consumption data is a valid barometer to use for adjustment of the servicing intervals RECONDITIONING PROCEDURE a Discharge the battery at a current equal to or less than the one hour rate Short out each cell as it drops below 5 volts The cells may be shorted by clips or by wires having clips on each end Allow the shorts to remain on the ceils for a minimum of 16 hours and preferably for 24 hours b Remove the shorting clips and charge for 24 hours at 1 1 amperes for a 13 5 ampere hour battery After approximately 5 minutes of charge measure the individual cell voltages If any cell voltage is greater than 1 50 volts add distilled water The amount of water required is approximately 1 Cc per rated ampere hour capacity for example a 13 5 ampere hour ceil may require about 13 5 cc of water at this time c After approximately 10 minutes of charge rerneasure the cell voltages Replace any cell that measures below 1 20 volts or above 1 55 volts d Continue charging for 20 hours After 20 hours of charging measure and record the individual cel voltages tf necessary add distilled water to level the cell 1 8 to 1 4 24 31 00 Page 206 Nov 2 73 inch above the baffle Do not remove any electrolyte from the cells e Measure and record the voltage at 24 charge hours and compare with the 20 hour reading If the 24 hour voltage reading is below the 20 hour reading by more than 04 volts replace the cell Also replace any
90. 0 32 00 00 32 30 00 32 30 00 32 60 00 32 30 00 32 30 00 32 60 00 32 00 00 32 60 00 32 60 00 INTRODUCTION PAGE 15 AUG 15 80 BEECHCRAFT OUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM CHAPTER CHAPTER amp OR SYSTEM NAME NAME SUB CHAPTER LANOING GEAR SYSTEM LANDING GEAR 32 00 00 LOG GEAR SAFETY SYS MICROSWITCH ADJUST LANDING GEAR 32 60 00 LOG GEAR SAFETY SYS PRESS SWITCH AOJUST LANDING GEAR 32 60 00 LOG GEAR THROTTLE WARNING HORN SWITCH POWER PLANT 71 00 00 LEAK CHECKS 6 REPAIRS WING FUEL 28 10 00 LEAK TEST WET WING FUEL 28 10 00 LEAKAGE TEST CABIN PRESSURIZATION AIR CONDITIONING 21 30 00 LEVELING AIRCRAFT LEVELING AND WEIGHT ING 08 00 00 LOCKS sHYOROLOK EQUIPMENT FURNISHINGS 25 00 00 LOCKS ROTON SERVICING 12 20 00 LOCKS eROTON EQUIPMENT AND FURNISHINGS 25 00 00 LUBRICATION SCHEOULE CHART SERVIC ING 12 20 00 MAGNETO SREAKER POINT ADJUSTMENT IGNITION 74 10 00 MAGNETO OROP OFF CHECK IGNITION 74 10 00 MAGNETO TIMING IGNITION 74 10 00 MAIN GEAR DOWNLOCK UPLOCK SWITCH ADJUST LANDING GEAR 32 30 00 MAIN GEAR INSTALLAT ION LANOING GEAR 32 10 00 MAIN GEAR LUBRICATION LANOING GEAR 32 10 00 MAIN GEAR REMOVAL LANDING GEAR 32 10 00 MAIN GEAR SHOCK ABSORBERS SERVICING LANDING GEAR 32 10 00 MAIN WHEEL AND TIRE LANDING GEAR 32 40 00 MAIN WHEEL ASSEMBLIES LANOING GEAR 2 32 40 00 MODEL OESIGNATION PLACARD PLACARDS AND MARKINGS 11 00 00 MOORING A IRCRAFT PARKING AND MOORING 10 00
91. 0 PAINT ENAMEL TOP COAT APPLICATION STANDARD PRACTICES AIRFRAME20 00 00 PAINT ENAMEL TOUCH UP REPAIR STANDARD PRACTICES AIRFRAME20 00 00 INTRODUCTION PAGE 16 AUG 15 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM OR SYSTEM NAME P PAINT PREPARATION OF EXTERIOR FOR PAINT SPECIAL PROCEDURES PAINT URETHANE EXTERIOR COLORS PAINT URETHANE PRETREATMENT PRIMER PAINT URETHANE STRIPPING amp CLEANING PAINT URETHANE TOP COAT APPLICATION PAINT URETHANE TOUCH UP REPAIRS PAINTING MAGNESIUM SURFACES PARKING BRAKE ADJUSTMENT PARKING BRAKE VALVE INSTALLATION PARKING BRAKE VALVE REMOVAL PARKING AIRCRAFT PITOT AND STATIC PRESSURE SYSTEM PITOT AND STATIC SYSTEM PITOT SYSTEM LEAK TEST PNEUMATIC PRESS REGULAT ION TURN SLIP PNEUMATIC PRESSURE SYSTEM PNEUMATIC PRESSURE SYSTEM ADJUSTMENT PNEUMATIC PRESSURE SYSTEM SERVICING PNEUMATIC SUPPLY PRESSURE REGULATORS PRESSURIZATION CHARACTERISTICS PRESSURIZATION CONTROL PRESSURIZATION LEAKAGE 5 PRESSURIZATION SYSTEM PRESSURIZATION SYSTEM ADJUSTMENT PRESSURIZATION TEST PROCEDURE PRESSURIZATION TEST SwITCH PROP DEICER BRUSH BLOCK RESIST CHECK PROP DEICER BRUSH REPLACEMENT PROP OEICER BRUSH SLIP RING RESIST PROP DEICER SLIP RING MACHINING STANDARD STANDARD STANDARD STANDARD STANDARD HAPTER CHAPTER NAHE SUB CHAPTER PRACTICES AIRFRAME20 00 00 PRACTICES AIRFRAME20 00 00 PRACTICES AIRFRAME20 00 00 PRACTICES AIRF
92. 0 00 1 Jun 13 84 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL STATIC DISCHARGING MAINTENANCE PRACTICES Prior to serial P 581 static wicks two on each wing tip two on each elevator and two on the rudder are bolted to the flight surfaces Each of these ten static wicks are removed and installed in the same manner Starting at serial P 581 and after there are three static wicks on each wing tip each elevator and the rudder These fifteen static wicks are screwed into their bases which are riveted to the flight surfaces These bases should not need to be removed in normal service STATIC WICK REMOVAL Prior to P 581 a Remove the two screws and lock washers securing the wick to the surface b Remove the wick from the surface STATIC WICK INSTALLATION Prior to P 581 Ciean around the static wick area by a Removing ali anodic film grease oil paints lacquer metal finishes or other high resistance properties with Minnesota 3M No 600 grit sandpaper or equivalent and solvent 41 Chart 201 91 00 00 The mating surfaces must be smooth and contoured so that maximum surface area is in actual contact 15 Acceptable substitutes for the preceding used in accordance with MIL B 5087B or the surface may be prepared in accordance with MIL M 3171C NOTE Dissimilar materials are not to be used in intimate contact uniess suitably protected against electrolylic corrosion Whenev
93. 0 25 3 30 0 15 0 001 0 05 Load Per Aircraft in Amps 0 60 0 21 0 90 0 50 0 98 0 62 0 001 0 059 0 94 0 10 2 70 17 00 0 35 2 90 0 09 0 09 0 40 0 33 1 30 0 63 0 09 0 18 0 25 4 e 0 15 0 001 0 40 24 50 07 7 Nov BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 201 ELECTRICAL UTILIZATION LOAD Cont d CONTINUOUS LOAD STANDARD EQUIPMENT Lighting Cont d Edge Lights Cabin Altitude Warning Light Cabin Door Warning Light Annunciator Lights Dim Relay inverter Out Light Landing Gear Position Lights Landing Gear Uplock Light Landing Gear Down Lock Light Compass Light Engine Instrument Lights Instrument Flood Lights Red Instrument Flood Lights White Outside Air Temperature Post Light Pilot s Clock Light Pilot s Instrument Lights Post Light Pilot s Map Light Reading Lights Navigation Lights Wing Navigation Light Tail Rotating Beacon Lower Rotating Beacon Upper CONTINUOUS LOAD OPTIONAL EQUIPMENT Air Conditioner Combustion Blower Condenser Blower Condenser Blower Relay Cabin Temperature Control Box Cabin Air Sensing Element Heating or Cooling Temperature Control Relay Hot Gas By pass Solenoid Valve P 4 through P 126 except P 123 Solenoid Valve Timer Magnetic Clutch Nacelle Scoop Relay Vent Blower Vent Blower Relay Propeller Deice System Pitot Heater RH Cabin Air Inlet Deice Boot Flight Hour
94. 00 FUSELAGE ACCESS OPENINGS FUSELAGE 53 30 00 GENERATOR ELECTRICAL POWER 24 00 00 GENERATOR BRUSH REPLACEMENT ELECTRICAL POWER 24 30 00 GENERATOR CURRENT AOJ MAXIMUM LOAD ELECTRICAL POWER 24 30 00 GENERATOR INSTALLATION ELECTRICAL POWER 24 30 00 GENERATOR PARALLELING ELECTRICAL POWER 24 30 00 GENERATOR PARALLELING RHEOSTATS ADJUST ELECTRICAL POWER 24 30 00 GENERATOR PARALLELING FINAL CHECKS ELECTR ICAL POWER 24 30 00 GENERATOR REMOVAL ELECTRICAL POWER 24 30 00 GENERATOR SYSTEM STABILIZATION ELECTRICAL POWER 24 30 00 GENERATOR VOLTAGE ADJUST MINIMUM LOAD ELECTRICAL POWER 24 30 00 GENERATOR VOLTAGE REGULATOR ADJUST ELECTRICAL POWER 24 30 00 GUST LOCK FLIGHT CONTROLS 27 70 00 GYRG INSTRUMENT PRESSURE REGULATOR PNEUMATIC 36 00 00 HEATER CONTROL SYSTEM AIR CONDITIONING 21 40 00 HEATER FUEL PUMP AIR CONDITIONING 21 40 00 HEATER IGNITION AIR CONDITIONING 21 40 06 HEATER INSTALLATION AIR CONDITIONING 21 40 00 HEATER OPERATION AIR CONDITIONING 21 40 00 INTRODUCTION PAGE 14 AUG 15 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM OR SYSTEM NAME HEATER REMOVAL HEATER SYSTEM HEATER VIBRATOR INSTALLATION HEATER VIBRATOR REMOVAL HEATING HYOROLOK LOCKS IGNITION HARNESS INDUCTION AIR FILTER INDUCTION SYSTEM AIR INTAKES INSPECTION GUIDE 5 SECTION INSPECTION OUAL BUS FEEDER DIODES INSPECTION EMERGENCY LOCATOR INSPEC TION GENERAL INSPECTION LOG GEAR DYNAMI
95. 02 Cont d CONSUMABLE MATERIALS ITEM MATERIAL SPECIFICATION VENDOR PRODUCTS 13 Hydraulic Fluid MIL H 5606 Brayco 756D Bray Oil Co 3344 Medford Street Los Angeles 63 California PED 3656 Standard Oil Co of California 225 Bush Street San Francisco 20 California 14 Oyxgen System Leak MIL L 25567 Testing Compound 15 Solvent Dry Cleaning or PD680 or British White Spirit Specification 245 16 Lubricating Oil SAE 10 17 Air Conditioner R 12 Refrigerant 18 Oil Air Conditioner Suniso No 5 Virginia Compressor 500 Viscosity Chemical and Smelting Co West Norfolk Virginia Texaco Capella E Texaco Inc 135 East 42nd Street New York N Y 10017 19 Aviator s Breathing Oxygen MIL O 27210 20 Naphtha TT N 95 21 Methyl Ethyl Ketone MIL M 13999 22 Toluol Toluene TT T 548 23 Paint Remover Turco No 4260 Turco Products Inc Los Angeles California 24 Epoxy Primer Ameron industrial i Coatings Division P O Box 2153 Wichita Kansas 25 Wash Primer EX2016G Ameron Industrial Coatings Division P O Box 2153 Wichita Kansas 12 20 00 Page 209 A14 Nov 30 83 ITEM 26 27 28 29 30 31 32 35 12 20 00 Page 210 Nov 30 83 MATERIAL Zinc Chromate Primer Rubber Hose Oil Engine Preservative Graphite Lubricating NOTE BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 202 Cont d CONSUMABLE MATERIALS SPECIFICATIONS MIL P 8585 MIL H 5593 MIL H 5593 SS G 659 Supe
96. 1 202A 216 217 218 219 220 221 222 223 224 225 226 227 228 END DATE Jan 9 86 Nov 30 83 Oct 19 77 Jan 9 86 Jan 9 86 Jan 9 86 Nov 2 73 Nov 2 73 Nov 2 73 May 12 78 May 12 78 May 12 78 Apr 18 80 Nov 2 73 Nov 30 83 Nov 30 83 Nov 30 83 Nov 30 83 Nov 30 83 Nov 30 83 Nov 30 83 Nov 30 83 Nov 30 83 Nov 30 83 Feb 22 80 May 30 75 Nov 2 73 May 30 75 May 30 75 May 30 75 May 30 75 May 30 75 Nov 2 73 Nov 2 73 Nov 2 73 Oct 27 75 Oct 27 75 Nov 2 73 Nov 30 83 Oct 27 75 12 EFFECTIVITY Page 1 Jan 9 86 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 12 SERVICING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT GENERAL 12 00 00 Description and Operation REPLENISHING 12 10 00 Maintenance Practices Filling the Fuel Cells Draining the Fuel System Engine Fuel Fitters and Screens Ci System Changing the Oil Filter Brake System Air Conditioning System Charging the Air Conditioning System Checking Compressor Oil Level Evaporator Air Filter Replacement Compressor Belt Tension Adjustment Heating System Heater Spark Plug Oxygen System SCHEDULED SERVICING 12 20 00 Maintenance Practices Tires External Power Battery Deice Boots Shock Struts Propeller Blade Bearing Lubrication Propeller Servicing Points Propeller Accumulator Induction Air Filter Roton Locks Cleaning and Waxing the Airplane Finish Cleaning Plastic Windows Chart 201 Thread Lubricants
97. 1012 31 32 5 4 3 26 17 4 3 32 LEFT WING UPPER RIGHT WING UPPER 2322 20 15 19 RIGHT WING LOWER LEFT WING LOWER n 60 12 1A Wing Access Openings Figure 204 Sheet 1 of 2 12 20 00 Page 224 Oct 27 75 11 12 13 14 DUKE 60 SERIES MAINTENANCE MANUAL Leading Edge Fuel Cell Transmitter Alternate Air and Fuel Pressure Solenoid Nacelle Fuel Cell Transmitter and Plumbing Nacelle Fuel Cell and Vent Line Plumbing Fuel Vent Check Valve and Plumbing Battery Battery Relays Voltage Regulators Overvoltage Relays Starter Relays Paralleling Rheostat Fuel Flow Inverter Loadmeter Shunt Fuse Block Radio Inverter Radio Inverter Circuit Breaker and Relay External Power Diode and Current Limiter for Battery External Power Receptacle Reverse Current Diode External Power and LH Control Relay Leading Edge Fuel Cell Transmitter and Fuel Cell Installation Fuel Filler Remote Compass Landing Light Wing Wiring and Fuel Vent Float Valve Fuel Siphon Valve 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Aileron Tab Actuator Leading Edge Fuel Cell Nacelle Fuel Cell Plumbing Box Section Fuel Cell Aileron Actuator and Pulley Cable Fuel Vent and Battery Vent Box Section Fuel Cell Fuel Vent Line and Aileron Tab Cable Fuel Vent Line Landing Gear Attach Bolt Fuel Boost Pump Wing Attach Bol
98. 201 Maintenance Practices 5 201 Nacelle Fuel Cell Removal 201 Nacelle Fuel Cell Installation 201 Inboard Leading Edge Fuel Cell Removal 201 Inboard Leading Edge Fuel Cell Installation 202 Installation of Velcro Tape with Replacement Fuel Cells 202 Inboard Leading Edge Baffled Fuel Cell Flapper Valve Inspection 203 Box Section Fuel Cell Removal 204 Box Section Fuel Cell Installation 204 Outboard Leading Edge Fuel Ceil Removal 204 Outboard Leading Edge Fuel Cell Installation 205 Wet Wing Tip Removal 205 Wet Wing Tip Installation 205 Leak Test 207 Leakage Checks and Repairs Wet Wing gt 207 Fuel Cell Leakage Check 208 Fuel Cell Repair 209 Goodyear Fuel Cells 209 7Unireyal Fuel Cells 210 DISTRIBUTION 28 20 00 201 Maintenance Practices 201 Fuel Boost Pump Removal 201 Fuel Boost Pump Installation 201 Engine Driven Fuel Pump Removal 201 Engine Driven Fuel Pump Installation 201 Engine Driven Fuel Pump Adjustment 201 Fuel Selector Valve Removal 201 28 CONTENTS Page 1 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 28 FUEL TABLE OF CONTENTS Cont d CHAPTER SECTION SUBJECT SUBJECT PAGE DISTRIBUTION 28 20 00 Maintenance Practices Fuel Selector Valve Installation 201 Fuel Selector Valve Control Cabie Removal 201 Fuel Selector Valve Control Cable Installation 202 Fuel Selector Valve Control Cable Rigging 202 Vent Float Valve Removal 202 Vent Float Valve Installation 203 Flared Fittings 203 E
99. 30 00 AIR CONDITIGNING 21 30 00 AIR CONDITIONING 21 30 00 ICE AND RAIN PROTECTION 30 60 00 ICE ANO RAIN PROTECTION 30 60 00 ICE RAIN PROTECTION 30 60 00 ICE AND RAIN PROTECTION 30 60 00 PROPELLERS 61 00 00 SERVICING 12 20 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 SERVICING 61 00 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 ICE AND RAIN PROTECTION 30 60 00 ICE RAIN PROTECTION 30 60 00 ICE AND RAIN PROTECTION 30 60 00 ICE AND RAIN PROTECTION 30 60 00 ICE ANO RAIN PROTECTION 30 60 00 ICE AND RAIN PROTECTION 30 60 00 ICE AND RAIN PROTECTION 30 60 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 SERVICING 12 20 00 PROPELLERS 61 90 00 PROPELLERS 61 00 00 PROPELLERS 61 00 00 INTROOUCTION IN TR 00 INTROOUCTION IN TR OD INTRODUCTION IN TR OD AIR CONDITIONING 21 50 00 SERVICING 12 20 00 EQUIPMENT FURNISHS 25 00 00 STABILIZERS 55 40 00 INTROOUCTION PAGE 17 AUG 15 80 BEECHCRAFT OUKE 60 SERIES MAINTENANCE MANUAL ALPHABETICAL INDEX COMPONENT ITEM CHAPTER CHAPTER OR SYSTEM NAME NAME SUB CHAPTER RUDDER CABLE INSTALLATION FLIGHT CONTROLS 27 20 00 RUDDER CABLE REMOVAL FLIGHT CONTROLS 27 20 00 RUDDER CONTROL SYSTEM RIGGING FLIGHT CONTROLS 27 20 00 RUODER INSTALLATION FLIGHT CONTROLS 27 20 00 RUDDER REMOVAL FLIGHT CONTROLS 27 20 00 RUODER TRIM TAB ACTUATOR INST FLIGHT CONTROLS 27 20 00 RUDDER TRIM TAB
100. 4 403 118684 405 118684 407 118684 409 118684 411 118684 413 118684 415 118684 419 118684 421 118684 63 118684 75 118684 133 118684 155 118684 181 118684 183 118684 235 118684 237 118684 239 118684 241 118684 257 118684 275 118684 277 118684 279 118684 283 118684 285 118684 329 118684 423 118684 427 118684 429 118684 455 118684 457 118684 461 118684 471 118684 475 119694 477 Page 203 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ENAMEL interior Colors Insignia Red 94 509 Black 94 515 instrument Black Color No 514 per ANA Bulletin No 157 Short cut masking jobs for your paint department are possi bie when you use pre cut paint patterns and numbers Stripe and numeral patterns are available from Mid America Mark ing Inc 1720 S 151 W Wichita Kansas 67052 or any other equivalent product may be used Current listings in clude 4 12 20 inch Numbers and Letters Time can be saved when using these patterns and a much neater final paint job can be expected PAINTING ALUMINUM ENAMEL PAINT PREPARATION OF AIRPLANE ALUMINUM EXTERIOR FOR PAINT a Mask windows with a double thickness of paper Cover all openings where paint might enter airplane b Sand scratches and rough areas to improve smoothness c Clean surface of airplane with solvent lacquer thinner or methyl ethyl ketone to remove shop primer ex posed sealer and other shop soils Lightly r
101. 46 Chapter 24 31 00 Airplanes P 446 and after are equipped with two 12 volt lead acid batteries connected in series to provide 24 volts To obtain optimum service from the twin battery proper and regular maintenance of the batteries must be performed For maintenance procedures on the lead acid batteries refer to BATTERY MAINTENANCE PROGRAM P 446 and after Chapter 24 31 00 BATTERY CHARGE CURRENT DETECTOR SYSTEM The battery charge current detector system installed on air plane serials P 243 through P 445 and those prior airplanes which have complied with Service instructions No 0587 356 provides an indication of the amount of battery charge current The system consists of a shunt in the negative lead of the battery a current detector assembly located adjacent to the battery and a yellow caution light BATTERY CHARGE on the annunciator panel The detector assembly receives pow er through a 5 ampere circuit breaker The system senses the battery current through the shunt Any time the battery charge current exceeds approximately 3 amperes for a period longer than approximately 6 seconds the yellow light will be illuminated END 24 00 00 1 12 78 1 2 TROUBLE Zero or low charge indicated No generator output Low generator output Loadmeter reads off scale in wrong direction Loadmeter does not read BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING GENERATO
102. 50 Operation Manual for 3 Button Flight Controller 98 35636 Operation Manual for 4 Button Flight Controller With Heading Selector 98 32751 Maintenance Instructions for Goodyear Wheel Brake and Tire Assembly 98 34998 Maintenance Instructions for Goodrich Wheel Brake and Tire Assembly 98 36374 Overhaul and Cleaning Procedure for Pressurization Controllers Outflow and Safety Valves H 14 AUTOPILOT 130333C Maintenance Manual 98 30603 Maintenance Manual Supplement 92 30103B Overhaul instructions for BG274B2 C1 C2 Computer 92 30105 Overhaul Instructions for CG136A1 Heading Selector 92 30106B Overhadi instructions for MG113A1 MG113A2 MG113A3 MG114A4 Actuator and SG28A1 SG28A3 i Pressure Switch 92 30107A1 Overhaul Instructions for PG51A1 Altitude Control 92 30229 Overhaul Instructions for GG205A3 GG205A4 GG205B4 Turn and Bank Indicator Gyro 92 30411B Overhaul Instructions for GG201A1 GG201B1 Vertical Gyro 92 30412B Overhaul instructions for GG2021 GG202B1 Directional Gyro INTRODUCTION Page 8 30 83 f A14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL H 14 AUTOPILOT 98 32523 Overhaul Instructions for MG112A1 MG112B1 Trim Actuator 98 32839 Overhaul instructions for CG417B1 CG417B2 Flight Controller VENDOR PUBLICATIONS ENGINE Parts Catalog PC 120 Avco Lycoming Division Williamsport Pennsylvania Overhaul Manual 60294 6 Avco Lycoming Division Williamsport Pennsylvania
103. 524326 7 with P N 50 524326 17 amd P N 50 524326 8 with P N 50 524326 18 CONTROL COLUMN TRIM CONTROL AND INDICATOR Electric and Manual Check for freedom of movement Inspect pulleys sprockets bearings actuators chaiis and turnbuckles for condition security and operation Check trim indicator for proper indication 10 ELECTRICAL WIRING AND EQUIPMENT Check for condition security and signs of chafing 11 WINDSHIELD HEATER Check the voltge as outlined under the heading ELECTRiCALLY HEATED WINDSHIELD VOLTAGE CHECK Chapter 30 40 00 12 PLUMBING Check all plumbing and connections for secu rity leakage and general condition 13 WINDOWS AND DOORS Inspect windows for scratches crazing and general condition Check doors for condition and attachment Check latching mechanism for proper engagement and ease of operation Check that the CABIN DOOR warning light in the annunciator panel remains ee until the door is closed latched and ocked 5 20 00 215 18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL E CABIN AND BAGGAGE COMPARTMENT Cont d MECH INSP 14 INSTRUMENTS AND INSTRUMENT PANEL Inspect instrument panel subpanels placards and instruments for condition and attachment Check all knobs for security Inspect shock mounts ground straps for cracks and security SEATS SEAT BELTS AND SHOULDER HARNESSES Inspect cabin seats seat belts and
104. 5A5 May 12 1978 50 590001 25 6 60 590001 25 7 60 590001 25 8 September 14 1979 February 22 1980 April 18 1980 60 590001 9A9 60 590001 25A10 60 590001 25A11 60 590001 25A12 60 590001 25A13 NOTE A list of the effective pages will be found in the front of each chapter Basic publications are assigned a part number which appears on the title page with the date of the issue Subsequent revisions are identified by the addition of a revision code after the part number Al after a part number denotes the firsi revision to the basic publication A2 the second etc Occasionally it is necessary to completely reissue and reprint a publication for the purpose of obsoleting a previous issue and outstanding revisions thereto As these replacement reissues are made the code will also change to the next successive letter of the alphabet at each issue For example for the first reissue C for the second reissue etc z s When ordering a handbook give the basic number and the reissue code when applicable if a complete up to date publication is desired Should only revision pages be required give the basic number and revision code for the particular set of revision pages you desire i 998 39113 1 et RALI Bist OF EFFECT aoe 60 59050 25A14 0 S 90951 25A15 A 590091 25416 0 100002 2 Al cn 50 59067i 25A18 VE November 30 19
105. 83 June 13 1984 September 20 1985 January 9 1986 November 20 i987 Intro 5 12 20 57 23 325 57 Aiways destroy superseded pages when you insert ravised pages Intro 27 12 cu 25 32 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL INTRODUCTION LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE INTRODUCTION EFFECTIVITY 1 Sep 20 85 INTRODUCTION 1 Nov 30 83 2 Sep 20 85 3 Nov 30 83 4 Nov 30 83 5 Nov 30 83 6 Nov 30 83 7 Nov 30 83 8 Nov 30 83 9 30 83 10 30 83 10A Nov 30 83 11 Aug 15 80 12 Aug 15 80 13 Aug 15 80 14 Aug 15 80 15 Aug 15 80 16 Aug 15 80 17 Aug 15 80 18 Aug 15 80 19 Aug 15 80 20 Aug 15 80 END INTRODUCTION EFFECTIVITY bs Page 1 A16 Sep 20 85 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL INTRODUCTION This BEECHCRAFT Duke 60 Maintenance Manual is pre pared in accordance with the ATA Air Transport Association Specification No 100 format Additional airframe manuals which supplement this maintenance manual are the BEECHCRAFT Duke 60 Wiring Diagram Manual P N 60 590001 29 and the BEECHCRAFT Duke 60 Beech Manufac tured Component Maintenance Manual P N 60 590001 27 NOTICE Beech Aircraft Corporation expressly reserve the right to supersede cancel and or declare obso lete any part part numbers kits or publication that may be referenced in this manual without prior notice NOTE Service publication reissues or revisions are not
106. ACTUATOR REMOVAL FLIGHT CONTROLS 27 20 00 RUDDER TRIM TAB CABLE INSTALLATION FLIGHT CONTROLS 27 20 00 RUDDER TRIM TAB CABLE REMOVAL FLIGHT CONTROLS 21 20 00 RUDDER TRIM TAB RIGGING FLIGHT CONTROLS 27 20 00 RUDDER TRIM TAB CHECKING FREE PLAY FLIGHT CONTROLS 27 20 00 SAFETY 6 OUTFLOW VALVE TEST AIR CONDITIONING 21 30 00 SAFETY VALVE AIR CONDITIONING 21 30 00 SAFETY VALVE GROUNO CHECK AIR CONDITIONING 21 30 00 SCHEDULED MAINTENANCE CHECKS TIME LIMETS MAINTENANCE CK 05 20 00 SEALING MATERIALS CHARTS 91 00 00 SEALING MATERIALS APPLICATION OF CHARTS 91 00 00 SEAT BACK ADJUST FLIGHT COMPARTMENT EQUIPMENT FURNISHINGS 25 00 00 SEAT BACK ADJUST PASSENGER EGU IPMENT FURNI SHINGS 25 00 00 SEAT INSTALLATION FLIGHT COMPARTMENT EQUIPMENT FURNISHINGS 25 00 00 SEAT INSTALLATION PASSENGER EQUIPMENT FURNISHINGS 25 00 00 SEAT REMOVAL FLIGHT COMPARTMENT EQUIPMENT FURNISHINGS 25 00 00 SEAT REMOVAL PASSENGER EQUI PMENT FURNI SHINGS 25 00 00 SERVICING CHART SERVICING 12 20 00 SHIMMY OAMPENER INSTALLATION LANDING GEAR 32 20 00 SHIMMY OAMPENER REMOVAL LANOING GEAR 32 20 00 SHOCK STRUTS SERVICING 12 20 00 SPARK PLUG INSP AND SERV HEATER AIR CONDITIONING 21 40 00 SPARK PLUG HEATER SERVIC ING 12 10 00 SPECIAL TOOLS SERVICING 12 20 00 STABILIZER INSTALLATION HORIZONTAL STABILIZERS 55 10 00 STABILIZER INSTALLATION VERTICAL STABILIZERS 55 30 00 STABILIZER REMOVAL HORIZONTAL STABILIZERS 55 10 00 STABILIZER REMOVAL VERTICAL STABILIZERS 55 30 00 STALL STRIP INSTA
107. AFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 10 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 10 EFFECTIVITY CONTENTS 1 Nov 2 73 10 00 00 1 Nov 2 73 CHAPTER 10 PARKING AND MOORING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 10 00 00 1 Description and Operaton 1 Parking 1 Mooring 1 END 40 EFFECTIVITY CONTENTS Page 1 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL DESCRIPTION AND OPERATION PARKING The brakes are set for parking by pulling out the parking brake control and depressing the pilot s brake pedals to pressurize the system Do not attempt to lock the parking brake by applying force to the parking brake handle it controls a valve only and cannot apply pressure to the brake master cylinders MOORING Three mooring eyes are provided one in each wing and one on the lower aft fuselage To moor the airplane chock the wheels fore and aft install the control lock and tie down the aircraft with a nylon line or chain of sufficient strength at each mooring eye Avoid overtightening the rear line which pulls the nose up so that wind will create higher lift on the wings If bad weather is anticipated it is advisable to nose the airplane into the wind NOTE Do not set the parking brakes during low temperatures when accumulation of moisture may cause the brakes to freeze or when they are hot from severe use END 10 00 00
108. AGE AD JUSTMENT located behiad the copilot s seat on the righ side b airplanes prior to P 466 connect the negativ lead of a voltmeter to terminal the left voltage re gulator base and the positive lead to the airplane structure Terminal D carries a voltage that is negative with respec to the airplane structure On P 466 connect the negativ lead of a voltmeter to the terminal point of wire P113B18 0 the left paralleling rheostat and the positive lead to the term nal point of wire P113C18N on the same rheostat Th negative test point carries a voltage that is negative wit respect to the airplane structure C Operate the LH engine with the generator chargin and carrying a moderate to heavy electrical load BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CAUTION Monitor the bus voltage as soon as the generators are turned on Voltages in excess of 32 volts for two minutes will damage the battery d Monitor the voltmeter and turn the LH paralleling rheostat first clockwise then counterclockwise to determine which direction of rheostat rotation results in an increasing negative voltage e Turn the LH paralleling rheostat to a maximum negative voltage then decrease the voltage by turning the rheostat back 1 8 turn f Repeat steps d and e for the RH system STABILIZATION OF GENERATOR SYSTEM The generators and regulators must be stabilized for temper ature changes before any final adju
109. AINTENANCE MANUAL NOTE After the first 25 hours of engine operating time a new remanufactured or newly over hauled engine should be given a 100 hour including draining and renewing of oil COWLING Check for condition and security Remove the upper and lower cowling and clean Inspect for cracks COWL FLAPS Check for travel deformation and security Inspect for cracks SPARK PLUGS Clean inspect regap test and replace as necessary Tighten spark plugs to proper torque and check ignition harness condition and for proper attach ment COMPRESSION Perform differential compression test PLUMBING Inspect plumbing and associated accessories for condition such as cracks and attachment Check plumbing clearance and secure against possible chafing ENGINE OIL SUMP Check for cracks leaks deformation and security OIL DIPSTICK Check the dipstick for rust and general condition Inspect the dipstick tabs for security and that the tabs are not bent OIL SUMP DRAINS AND FILTERS Check for metal particles on filters Check for proper torque after installation Check drain plugs for leaks 5 20 00 Page 206 Nov 20 87 18 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL POWER PLANT Cont d MECH NOTE Change 011 and oil filter per Lycoming T10 541 Series Operating Manual 9 OIL COOLER Check oil cooler lines and fittings for condition security chafing and
110. AND EQUIPMENT Inspect for chafing damage security and attachment STATIC LINES Check condition of static lines and drain 12 ASSIST STEP Inspect for condition and attachment The step may be adjusted as outlined under the heading STEP ADJUSTMENT FOLDING POSITION in Chapter 52 60 00 ANTENNAS Check for condition and security 14 SCUPPER DRAINS Check that the drain guards are open facing aft and drain holes are free from obstruction 15 OXYGEN 1f applicable Inspect the oxygen cylinder and vatves for condition and security of attachment Check the valves for proper operation 5 20 00 219 A18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ASA ONA S IDN K MAIN GEAR AND BRAKES i MECH INSP ERA A ace ee d RBS LiR 1 BRAKES LINES LINING AND DISCS Check for condition wear and security Check lines for chafing and signs of leakage or cracks Check discs for wear or warping Check brake discs for cracks 2 WHEELS AND TIRES Check wheels for cracks and tires for wear damage condition and proper inflation Check wheel bearings for condition and wear 3 LANDING GEAR STRUTS Inspect the shock struts and com ponents for cracks attachment corrosion proper inflation and evidence of leakage 4 ACTUATING LINKAGE Check for wear and cracks at attach points Check for condition and security pin
111. C BRAKE RELAY INSPECTION LOG GEAR RETRACT MECH 100 HR INSPECTION MAIN GEAR BRAKE INSPECTION MAIN GEAR RETRACTION INSPECTION MAIN GEAR 100 HR INSPECTION MAIN WHEEL INSPECTION MAIN WHEEL TIRE amp BRAKE INSPECTION NACELLE INSPECTION NOSE GEAR RETRACTION INSPECTION NOSE GEAR 100 H0UR INSPECTION NOSE SECTION INSPECTION NOSE STEERING 100 HOUR INSPECTION NOSE WHEEL INSPECTION OPERATIONAL INSPECTION PITOT SYSTEM HOSE INSPECTION POWER PLANT INSPECTION PRESSURE OIST OUCTS 100 HOUR INSPECTION PROP CONTROLLING L00 HOUR INSPECTION PROPELLER OEICER 100 H0UR INSPECTION PROPELLER DEICER 50 H0UR INSPECTION PROPELLER 100 HOUR INSPECTION REAR FUSELAGE EMPENNAGE INSPECTION WING FRONT SPAR INSPECTION WING 100 HOUR INSPECTION WINGS INSTRUMENT ACCESS INSTRUMENT OPERATION INTERCOOLER CONTROL RIGGING INTERCOOLER INSTALLATION INTERCOOLER REMOVAL J JACKING AIRCRAFT L CLAMP BULB REPLACEMENT LANDING GEAR DYNAMIC BRAKE RELAY REMOVAL LANDING GEAR LIMIT SWITCHES AOJUST LANDING GEAR MANUAL EXTENSION SYSTEM LANDING GEAR MOTOR amp ACTUATOR INSTALL LANDING GEAR MOTOR amp ACTUATOR REMOVAL LANDING GEAR POSITION LIGHTS ADJUST LANDING GEAR RETRACT SYSTEM LUBRICATION LANDING GEAR RIGGING LANOING GEAR SAFETY SWITCH ADJUST LANDING GEAR SAFETY SYSTEM LANOING GEAR SAFETY SYSTEM LANOING GEAR SAFETY SYSTEM CHECK CHAPTER CHAPTER NAME SUB CHAPTER AIR CONDITIONING AIR CONOITIONING AIR CONDITIONING AIR CONDITIONING
112. CHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL DC GENERATION MAINTENANCE PRACTICES BATTERY MAINTENANCE PROGRAM Airplanes Prior to P 446 A Systematic Battery Maintenance Program should be estab lished and carefully followed CAUTION Methods of servicing lead acid batteries do not apply for the servicing of nickel cadmium bat teries a The battery should be removed from the airplane for service b A log of the services performed on each battery should be maintained c The battery should be removed from the airplane and serviced after 100 flight hours or 30 days whichever occurs first If the ambient temperatures are above 90 F or the time between engine starts averages less than 30 minutes the duty cycle should be reduced d log of battery services performed should be evaluated to determine the need to service the battery at the above recommended intervals or to extend the intervals if justified Accurate water consumption data is a valid baro meter to use for adjustment of the servicing intervals Since the proper battery servicing requires two days an additional battery or batteries will be required where air plane utilization warrants For additional information on bat tery maintenance refer to Gulton Instructions for Use and Care of Sintered Plate Vented Nickel Cadmium Storage Bat teries P N ABD 1100 or Marathon Battery Instruction Man ual P N BA 89 or Operating and Service Manual for Gener al
113. Cabin Pressurization Test Unit Manufactured by Kitco Tool and Die inc 21 Water Street Mill Hall PA 17751 1 Model 1200 for domestic use 2 Model 1300 for export use 21 30 00 Page 207 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NOTE The test equipment hoses furnished with the test unit may be connected in only one either or both nacelles The TEST EQUIPMENT text and Figure 201 illustrates the test equipment hoses connected in both nacelles b Use low pressure hose 2 1 2 inches in diameter to connect the PRESSURIZING AIR fitting of the test unit to the flexible ducts forward of the LH and RH firewall s Two pieces of 1 4 inch high pressure hose is used to connect the PNEUMATIC AIR fitting on the test unit to the pneumatic line in each nacelle forward of the pressure regulator d High pressure hose 3 8 inch in diameter connects the INSTRUMENT AIR or CABIN PRESSURE fitting on the test unit to the brake reservoir sense line at the forward pressure bulkhead located in the nose baggage compartment e Tee or Y shaped fittings and clamps to connect the hoses as described in steps b through d f High strength webbing or restraining straps to encompass fuselage doors and windows for safety of testing personnel during performance of test P N 60 000000 D939 1 or equivalent TEST PROCEDURE P 4 and after a Gain access to the outflow and safety valves at the aft pressure bulkhead
114. Communications Components Battery Replacement a ee wrist k 201 Narco Battery Replacement xus eral 202 Testing Emergency Locator Transmitter 6c es calc et bee ee 203 END 25 CONTENTS Page 1 18 20 81 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL MAINTENANCE PRACTICES FLIGHT COMPARTMENT SEAT REMOVAL a Remove the three seat stops at the forward end of the three seat tracks b Release the fore and aft seat adjustment lock Slide the seat forward and off the seat tracks d Unhook the seat spring on the bottom of the seat FLIGHT COMPARTMENT SEAT INSTALLATION a Hook the seat spring on the bottom of the seat b Position the seat and slide aft onto the seat track c Secure the fore and aft seat adjustment lock d Install the three seat stops at the forward end of Seat tracks and secure the thr FLIGHT COMPARTMENT SEAT BACK ADJUSTMENT On airplanes P 4 and after the pilot s seat back adjustments are controlled by a mechanical three position stop The adjustment selector is located at the base of the seat back on the inboard side airplanes P 4 thru P 510 and P 512 thru P 519 the copilot s seat back adjustments are controlled by a mechanical three position stop by a Roton lock for selected positioning On airplanes P 511 P 520 and after the copilot s seat back adjustments are controlled by a mechanical three position stop or by a Hydrolok lock for s
115. D VALVE 4 NC DUMP CABIN ALTITUDE CABIN RATE SELECTOR KNOB CONTROL SELECTOR KNOB RAM AIR DOOR OUTFLOW VALVE CONTROLLER MAGNETIC LATCH 2 se STATIC VACUUM 3 ELECTRICAL FACE VIEW OF CONTROLLER FILTER AND PORT 1 PORT T ORIFICE LT WR VALVE Ji POPPET POPPET FR vatve VALVE PORT 2 PORT 2 Pal NOISE NOISE TRUE STATIC SUPPRESSION TRUE STATIC DISCHARGE SUPRESSION 60 603 31 ATMOSPHERE SCREEN ATMOSPHERE SCREEN Cabin Pressure Control System Schematic P 308 and after Figure 4 END 21 30 00 7 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PRESSURIZATION CONTROLS MAINTENANCE PRACTICES P 3 THRU P 307 CABIN ALTITUDE CONTROLLER FILTER MOTORIZED A cabin altitude controller filter is utilized on Duke serials P 229 and after and those prior airplane s which have complied with Service Instructions 0528 453 that have the optional motorized cabin altitude controller installed The filter is designed to improve filtration and prevent the poppet valve from sticking due to tobacco tars and other contaminents Under normal operating conditions the average life of the filter is 1 000 hours This will vary according to extremes in cabin smoke density An indication of need for filter replacement would be a slow response to variations in altitude DIFFERENTIAL CONTROL VALVE AND SAFETY VALVE REMOVAL a Remove the upper and middl
116. ECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL highly corrosive elements Flush loose dirt away first with clear water then wash the airplane with a mild soap and water Harsh abrasive or alkaline soaps or detergents should never be used Use soft cleaning cloth or chamois to prevent scratches when cleaning and polishing Any good grade automobile wax may be used to preserve painted surfaces To remove stubborn oil and grease use a soft cloth dampened with naphtha After cleaning with naphtha the surface should be polished and rewaxed NOTE Frequently inspect the underside of the wing and flaps in the area covered by the engine turbocharger exhaust stream for fuel lead deposits If such deposits are discovered they should be removed immediately with a water and mild detergent solution and the surface rewaxed CLEANING PLASTIC WINDOWS A commercial cleaning compound made specifically for acrylic plastic windows may be used When using a commercial cleaner follow the instructions on the container If a commercial cleaner is not available the following instructions should be followed Cleaning of the acrylic plastic windows should never be attempted when dry The window should first be flushed with water or a mild soap solution then rubbed slightly with a grit free soft cloth chamois or sponge Stubborn grease or oil deposits are readily removed with aliphatic naphtha or hexane Rinse with clear water CAUTION Do n
117. EECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NOTE Check the trim tab system for correct movement of the control surface with respect to the movement of the trim tab control When the elevator tab control is moved toward the NOSE DOWN position the tab should move up ELEVATOR TRIM TAB ACTUATOR REMOVAL a Remove the access plate at the trim tab actuator b Remove the tail cone and the access plate beneath the RH horizontal stabilizer c Remove the access panel in the floorboard aft of the rear spar d Disconnect the tab control cables at the turnbuckles in the aft fuselage e Disconnect the tab actuator at the tab f Remove the bolt attaching the actuator to the elevator Remove the actuator and the chain and cable assembly from the actuator sprocket ELEVATOR TRIM TAB ACTUATOR INSTALLATION a Position the chain and cable assembly on the actuator sprocket so that the ends of the chain are equi distant at the sprocket centerline within 20 inch Install the boit attaching the actuator to the elevator b Connect the actuator to the tab c Connect the cables to the turnbuckles in the aft fuselage Rig the tab contro system d Install the access panel in the floorboard e instal the tail cone and the access plate beneath the RH horizontal stabilizer f Install the access plate at the trim tab actuator ELECTRIC TRIM TAB ACTUATOR REMOVAL a Remove the access plate on the side of the fuselage beneath the
118. Exterior Colors Lacquer Interior Colors Enamel Interior Colors Painting Magnesium Enamel Paint Urethane Paint Special Paint Procedures END PAGE 201 202 202 202 202 202 202 203 203 203 204 204 204 204 207 20 CONTENTS Page 1 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL STANDARD PRACTICES AIRFRAME TORQUE WRENCHES When a torque wrench and adapter is used Figure 201 compensation must be made for the extra leverage gained New indicator readings must be calculated before the wrench is used To figure the desired lower readings which will actu ally give the torques specified use the following formula Original wrench length x specifi ied torque Desired length of wrench adapter reading Example D Desired reading L Length of torque wrench Adapter length Torque D L 33 inches A 11 inches T 5 000 inch pounds 33 x 5 000 165 000 3 750 inch d pounds 33 11 22 L A TOTAL LENGTH ine Torque Wrench and Adapter Figure 201 An acceptable method of checking the torque if a torque wrench is not available Figure 202 is to attach a spring Scale to a conventional flex or T handle inserted in an adapter Force should be applied in a direction perpendicular to an imaginary line extending from the center of the bolt through the spring scale attaching point TORQUE IN LB TOTAL LENGTH 60 17 72 Computing Torque with
119. GROOVE TO BE A SNUG FIT TO THE SCREW BRACKET ON P N of Federal Products Corp Providence R I THE DIAL INDICATOR basse fae P N 45 135030 9 810 Check Fixture for Tab Deflection Figure 202 END 27 20 00 Page 205 Sep 14 79 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NOTE To position the elevator in neutral on airplane serials P 438 and after fabricate a tool from 5 16 inch diameter steel rod as shown in Figure 201A a Remove the tail cone and the access plate on the side of the fuselage beneath the RH horizontal stabilizer b Position the aft elevator bell crank in neutral by inserting 3 16 inch diameter rig pin through the beli crank and adjacent structure c Adjust the elevator push rods to place the elevator in neutral NOTE After the push rods are adjusted the threads on the rod ends must be visible in the inspection holes at each end of the push rods d Remove the rig pin from the aft elevator bell crank and adjust the elevator travel stops to obtain 17 1 up travel and 15 1 down travel FABRICATE FROM 5 16 DIAMETER STEEL ROD 1 35 95 60 17 15 Elevator Neutral Rigging P 438 and after Figure 201A 16 On airplane serials prior to P 438 insert 1 4 inch diameter rig pin in the control lock pin hole in the control column Insert 3 16 inch diameter rig in the aft elevator bell crank and adjacent structure f
120. HRU 509 ASSIST STEP CABLE INST P 510 amp AFTER ASSIST STEP CABLE REM 4 THRU 509 ASSIST STEP CABLE REM 510 amp AFTER ASSIST STEP INSTALLATION ASSIST STEP REMOVAL ASSIST STEP STRUT ASSY INSTALLATION ASSIST STEP STRUT ASSY REMOVAL AUTOPILOT PNEUMATIC SYSTEM AUTOPILOT REGULATOR H 14 AUTOPILOT H 14 AUTOPILOT NEW MATIC COLLINS COMM COMP CORP ELT BATTERY BATTERY BATTERY CAPACITY CHECK BATTERY CAPACITY RECONDITIONING BATTERY CHARGE CURRENT DETECTOR SYSTEM BATTERY CHARGE CURRENT DETECTOR SYSTEM BATTERY CHARGING BATTERY CLEANING INSPECTION BATTERY CONSTANT CURRENT CHARGING BATTERY CONSTANT POTENTIAL CHARGING BATTERY ELECTRICAL LEAKAGE CHECK BATTERY ELECTROLYTE LEVEL ADJUSTMENT BATTERY EMERGENCY LOCATOR BATTERY INSTALLATION BATTERY MAINTENANCE LOG BATTERY MAINTENANCE PROGRAM BATTERY PRE INSTALLATION INSTRUCT ION BATTERY RECONOITIONING FREQUENCY BATTERY RECONDITIONING PROCEDURE BATTERY REMOVAL BATTERY REPL NARCO ELT BATTERY STAND BY CHARGING CHAPTER NAME ELECTRICAL POWER WINGS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS WINGS FLIGHT CONTROLS PNEUMATIC FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS SERV IC ING AIR CONDITIONING AIR CONDITIONING SERVICING AIR CONOITIONING AIR CONDITIONING CHAPTER amp SUB CHAPTER 24 00 00 57 50 00 27 10 00 27 10 00 27 10 00 27
121. IAL INDICATOR S x eres P N 45 135030 9 810 Check Fixture for Tab Deflection Figure 202 END 27 10 00 Page 205 Sep 14 79 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL RH horizontal stabilizer and the access panel in the aft floorboard RUDDER TRIM TAB CABLE REMOVAL Figure 201 a Remove the tail cone the access plate beneath the RH horizontal stabilizer and the access plate at the trim tab actuator b Remove the pilot s seat and the left floorboard c Remove both upholstery panels on the left side of the pedestal d Remove the left passenger seat the floorboard between the main and rear spar and the access panel in the floorboard aft of the rear spar e Remove the cable retaining pins from the pulley brackets and the pressure seals from the rear pressure bulkhead f Disconnect the trim tab cables in the aft fuselage at the turnbuckles and connect lead lines to the forward cables Identify the lead line for tab left and tab right movement to ensure proper cable rerouting g Remove the taper pin from the forward universal and remove the attaching shaft and cable reel Note and record the number of cable revolutions on the reel h Remove the forward trim tab cable through the pilot s compartment i i Remove the tab cable stops and disconnect the chain and cable assembly at the trim tab actuator Remove the aft cable chain and cable assembly RUDDER TRIM TAB CABLE INSTALLATION Figure 201 a Wit
122. IES MAINTENANCE MANUAL COOLING MAINTENANCE PRACTICES Servicing the air conditioning system consists of Periodically checking the refrigerant level checking compressor oil level and changing the system air filter Recharge the system whenever the refrigerant level is low air has entered the system or components carrying refrigerant are replaced Refrigerant leaks may be detected by inspection with flameless leak detector The refrigerant level may be observed through the sight glass located in the RH wheel well P 4 through 144 or by removing a plug button from the forward section floorboard forward of the copilot s seat P 145 and after CHARGING THE AIR CONDITIONING SYSTEM When working on a refrigerative air cooling system observe the following specia servicing precautions a Remember this is a high pressure system When disconnecting a line toosen the fittings just enough to bleed off pressure slowly then disconnect the fitting s b Whenever a line is disconnected purge the entire system with a vacuum pump operating at the 125 micron level c Use only refrigerant 17 Chart 207 91 00 00 other refrigerants particularly those containing methyi chloride will cause rapid deterioration of the aluminum compressor components d When servicing the system with refrigerant avoid smoking or working near an open flame Refrigerant passing over an open flame will produce a highly toxic phosgene gas Hook the s
123. IM TAB CABLE REMOVAL Figure 201 a Remove the tail cone the access plate beneath the RH horizontal stabilizer and the access plate at the tnim tab actuator b Remove the pilot s seat and the left floorboard c Remove both upholstery paneis on the left side of the pedestal 27 30 00 Page 203 Sep 20 85 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL d Remove the left passenger seat the floorboard between the main and rear spar and the access panel in the floorboard aft of the rear spar e Remove the cable retaining pins from the pulley brackets and the pressure seals from the rear pressure bulkhead f Disconnect the trim tab cabies in the aft fuselage at the turnbuckles identify the cable for tab up movement and connect lead lines to the cables g Remove the pressure seals in the rear pressure buikhead h Remove the tab cable stops and disconnect the chain and cable assembly at the trim tab actuator Remove the aft cable and chain assembly i Remove the bolt attaching the cable drum and sprocket to the lower pedestal Note and record the number of cable revolutions on the reel j Remove the cable through the pilot s compartment ELEVATOR TRIM TAB CABLE INSTALLATION Figure 201 amp Place the elevator trim tab control wheel in neutrai position and wrap the cable around the drum the same number of revolutions noted during removal maintaining the cable ends equidistant b Position the cable drum an
124. LLATION ICE AND RAIN PROTECTION 30 10 00 STALL STRIPS METAL WINGS 57 00 00 STALL WARNING INDICATING SYSTEM ADJ FLIGHT CONTROLS 27 50 00 STALL WARNING INDICATOR INSTALLATION FLIGHT CONTROLS 27 60 00 STALL WARNING INDICATOR REMOVAL FLIGHT CONTROLS 27 60 00 STACL WARNING SYSTEM FLIGHT CONTROLS 27 60 00 STARTER STARTING 80 00 00 STARTER BRUSHES STARTING 80 10 00 STARTER CIRCUITT CHECKS STARTING 80 10 00 STARTER INSTALLATION STARTING 80 10 00 STARTER LUBRICATION STARTING 80 10 00 STARTER REMOVAL STARTING 80 10 00 STATIC OISCHARGING COMMUNICATIONS 23 60 00 STATIC SYSTEM CLEANING NAVIGATION 34 10 00 STATIC SYSTEM LEAK TEST NAVIGATION 34 10 00 STATIC WICK INSTALLATION COMMUNICATIONS 23 50 00 STATIC WICK REMOVAL COMMUNICATIONS 1 23 60 00 STATION DIAGRAM DIMENSIONS ANO AREAS 06 00 00 STRBOE LGT PWR SUP UNIT INST GRIMESESDI LIGHTS 33 40 00 STROBE LGT POWER CABLE CHECK HOSKINS LIGHTS 33 40 00 STROBE LGT PWR SUP UNIT CHKS HOSKINS LIGHTS 33 40 00 STROBE LGT PWR SUP UNIT INST HOSKINS LIGHTS 33 40 00 STROBE LGT PWR SUP UNIT REM GRIMES SOI LIGHTS 33 40 00 STROBE LGT PWR SUP UNIT REM HOSKINS LIGHTS 33 40 00 STROBE LGT TIMER MOOULE CHK HOSKINS LIGHTS 33 40 00 STROBE LIGHT REPLACEMENT GRIMES SDI LIGHTS 33 40 00 STROBE LIGHT WIRING GRIMES amp SOI LIGHTS 33 40 00 STROBE LIGHT SYS CHECK QUT HOSKINS LIGHTS 33 40 00 STROBE LIGHTS HIGH INTENSITY HOSKINS LIGHTS 33 00 00 STROBE LIGHTS HIGH INTENSITY GRIMES amp SOI LIGHTS 33 00 00 INTRODUCTION PAGE 18
125. LVE REMOVAL The safety vaive and the outflow vaive are nearly identical The safety valve is installed in the lower position and the outflow valve is installed in the upper position a Remove the upholstery pane from the aft pressure bulkhead b Remove the plate to gain access to the outflow and safety valves The plate is secured with two AN4 5A bolts and sixteen AN3 5A bolts C Loosen and remove the plumbing as necessary to permit removal of the valve Tag the plumbing as removed to facilitate reinstallation Cap all open plumbing and valve fittings to prevent shop soil and foreign objects from entering d Remove the access door on the lower LH fuselage just aft of the rear pressure bulkhead e Station a man inside the aft fuselage to remove the six attaching nuts and washers securing each valve f Remove the valve g Remove and discard the old gasket OUTFLOW VALVE AND SAFETY VALVE INSTALLATION a Remove all traces of the old gasket b Station a man inside the aft fuselage to install the attaching washers and nuts that secure each valve c Install the safety valve in the lower position and or the outflow valve in the upper position using a new gasket d Secure the valve to the pressure bulkhead structure by installing a washer and a nut at each of the six plates Tighten the nuts evenly to a torque of 4 1 inch pounds Earlier airplane serials have valves with flared fittings while later
126. May 30 75 201 Nov 2 73 202 Nov 2 73 203 Nov 2 73 204 Nov 2 73 205 Nov 2 73 END 21 EFFECTIVITY Page 2 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 21 AIR CONDITIONING TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT GENERAL 21 00 00 Description and Operation Pressurization System Air Conditioning System Heater System Troubleshooting Pressurization System Heater System Air Conditioning System COMPRESSION 21 10 00 Description and Operation Maintenance Practices Intercooler Removal Intercooler installation Intercooler Control Rigging Firewall Shut Off Valve DISTRIBUTION 21 20 00 Maintenance Practices 100 Hour Inspection PRESSURIZATION CONTROL F 21 30 00 Description and Operation P 3 thru P 307 Pressurization System Operational Characteristics Cabin Altitude Controller Manual Cabin Altitude Controller Motorized Differential Control Valve and Safety Valve Pressurization Test Switch Description Operation P 308 and after Maintenance Practices P 3 thru P 307 Cabin Altitude Controller Filter Motorized Differential Control Valve and Safety Valve Removal Differential Control Valve and Safety Valve Installation Differential Control Valve and Safety Valve Adjustment Pressurization System Adjustment Procedures Cabin Altitude Controller Removal Manual Cabin Altitude Controller Installation Manual Cabin Altitude Controller Adjustment Manual Cabin Altitude Controlle
127. NANCE MANUAL SUPPLEMENTAR Y PUBLICATIONS The following is a list of publications providing servicing overhaul and parts information on various components on the BEECHCRAFT Duke 60 Series airplanes which you may obtain to supplement the BEECHCRAFT Duke 60 Series Maintenance Manual in most instances you should obtain the publications directly from the manufacturer or his distributor Only a few such as Beech supplementary publications are available from Parts and Service Operations Beech Aircraft Corporation Those which are so available are listed in the current Publications Price List Since a wide variety of radio components and equipment is available and because radio manufacturers normally supply parts and servicing manuals with each set radio publications have not been included in the list As publications on additional components become available they will be added to the list of publications BEECH PUBLICATIONS 98 33857 Installation Maintenance and Illustrated Parts Breakdown for 60 389017 Voltage Regulator 98 36235 Installation Maintenance and Illustrated Parts Breakdown for 60 389017 1 Voltage Regulator 98 33702 Overhaul and Parts Breakdown for 50 921560 Engine Driven Fuel Pump 98 37031 Inspection Procedures and Maintenance Guide for the 20139 and 20051 inverter 98 35655 Brittain B 5 and B 7 Autopilot Operating Manual 98 35850 Brittain B 5 and B 7 Autopilot Maintenance Manua and lllustrated Parts Breakdown 98 343
128. NOTE Maintain temperature stabilization by operating the generators individually for only short periods f Make the necessary voltage adjustments by turn ing the voltage adjusting potentiometer on the voltage re gulator clockwise to increase the voltage and counterciock wise to decrease the voltage Make the adjustments smail increments only Allow ample time for the voltage to stabilize before making further adjustment g Repeat steps b through f until the minimum load voltage is satisfactory CAUTION Never adjust the core or carbon pile adjusting screw slotted heads in the ends of the regula tors The regulating characteristics of the regu lators will be altered as well as the voltage setting P 466 AND AFTER On airplanes P 466 and after the voltage regulators are adjusted to produce a voltage of 28 25 0 25 volts mea sured at the main bus with a minimum electrical load on the system as follows NOTE If the airplane is to be operated continuously where temperatures are 32 F or below the volt age should be adjusted to 28 50 0 25 volts a Connect the positive lead of a portable precision voltmeter to the positive red test jack located on the right circuit breaker panel Connect the negative lead to the nega tive black test jack The meter must be capable of measur ing 28 25 volts with an accuracy of 0 25 volts 24 30 00 Page 203 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MAN
129. NUT TOROUE TRISTA gt WRENCH ADAPTER UPPER AFT WING BOLT WRENCH UPPER AFT WING NUT TORQUE WRENCH ADAPTER LOWER AFT WING BOLT WRENCH LOWER AFT WING NUT TORQUE WRENCH ADAPTER for intemal wrenching nut LOWER AFT WING NUT TORQUE WRENCH ADAPTER for external wrenching nut 60 17 7 Special Tools Sheet 2 of 3 Figure 205 12 20 00 Page 227 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL P N 60 590013 P 3 thru P 61 P N 60 590013 1 P 62 and after 101 590020 1 FUEL SUMP DRAIN WRENCH SERVICE JACK ADAPTER 60 17 8A Special Tools Sheet 3 of 3 Figure 205 END 12 20 00 Page Oct 27 75 CHAPTER SECTION SUBJECT 20 EFFECTIVITY 20 CONTENTS 20 00 00 14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 20 LIST OF PAGE EFFECTIVITY PAGE 1 1 201 202 203 204 205 206 207 208 DATE Nov 30 83 May 12 78 Apr 18 80 Nov 30 83 May 12 78 May 12 78 May 12 78 May 12 78 May 12 78 May 12 78 20 EFFECTIVITY Page 1 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 20 STANDARD PRACTICES AIRFRAME TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT STANDARD PRACTICES 20 00 00 Torque Wrenches Airplane Finish Care Cleaning and Waxing Airplane Finish During Curing Period 90 days After Curing Period Exterior and Interior Finishes Exterior and interior Primers Enamei Exterior Colors Urethane
130. R PEDALS LOCKED c Position the throttle controi lock placarded THROTTLE CONTROLS STOP forward of the throttle levers in the closed position and secure it to the console with the Dzus fastener d The aileron control locking device placarded AILERON AND ELEVATOR CONTROLS LOCKED is installed by inserting the pin through a hole in a flange protruding from the subpanel and through a matching hole in the lower side of the control column tube To remove the control locks remove in the following order rudder aileron etevator and throttle END 27 70 00 Page 201 Nov 2 73 CHAPTER SECTION SUBJECT 28 EFFECTIVITY 28 CONTENTS 28 00 00 28 10 00 28 20 00 28 40 00 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 28 LIST OFPAGE EFFECTIVITY END PAGE 201 203 201 202 DATE Oct 19 77 Oct 27 75 Oct 19 77 Oct 27 75 Oct 27 75 Oct 27 75 Nov 2 73 Nov 2 73 Nov 2 73 Nov 2 73 Nov 2 73 Oct 27 75 Oct 27 75 Oct 19 77 Oct 27 75 Oct 27 75 Oct 27 75 Nov 2 73 Nov 2 73 Nov 2 73 Oct 19 77 Oct 19 77 28 EF FECTIVITY Page 1 Oct 19 77 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 28 FUEL TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 28 00 00 1 Description and Operation 1 Fuel Cells 1 Fuel Crossfeed 1 Fuel Boost Pumps 1 Fuel Cell Drains 1 Maintenance Practices 201 Fuel Handling Practices 201 Airplane Defueling 201 STORAGE 28 10 00
131. R SYSTEM PROBABLE CAUSE Engine speed too low Loose connections Open or shorted field circuit in generator detective armature Brushes not contacting com mutator Brushes worn out Dirty commutator Defective voltage regulator Defective loadmeter Current limiter blown Open circuit Defective generator control switches generator control re lay or reverse current diode Generator not tuming Generators not paralleled Generator field magnetized in wrong direction Loose connection or ground in airplane wiring Open fuse in loadmeter circuit END REMARKS increase speed Check connections throughout system Test resistance of field Check field circuit connections Replace generator if defec tive Clean brushes and holders with a clean lint free dry cloth Replace weak springs Replace brushes if worn to a length of 1 2 inch or less With generator running clean commutator with No 0000 sandpaper Use filtered air jet to remove grit Replace regulator Replace loadmeter Check for short circuit repiace Check continuity of circuit Test switches relay or diode Replace if defective Check generator drive belts Replace if necessary Readjust minimum load voltage Then readjust paralleling rheostats Flash fieid Do not flash field when generator is running Check entire system Check for short circuit replace 24 30 00 101 12 78
132. RAME20 00 00 PRACTICES AIRFRAME20 00 00 PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER PROPELLER ACCUMULATOR ACCUMULATOR ACCUMULATOR INSTALLATION ACCUMULATOR REMOVAL ADJUSTMENT BLADE BEARING LUBRICATION BLADE BEARING LUBRICATION BLADE REPAIR DEICER BOOT INSTALLATION DEICER BOOT REMOVAL DEICER BOOT REPAIR OEICER CONTINUITY TEST OEICER HEAT TEST DEICER TIMER CHECK DEICING SYSTEM FEATHERING ADJUSTMENT GOVERNOR ADJUSTMENT GOVERNOR INSTALLATION GOVERNOR REMOVAL INSTALLATION LOW RPM AOJUSTMENT REMOVAL SERVICING POINTS SYNCHRONIZER SYNCHROSCOPE PROPELLERS PUBLICATION VENDOR PUBLICATIONS BEECH PUBLICATIONS SUPPLEMENTARY REFRIGERATIVE AIR COOLING SYSTEM ROTON LOCKS ROTON LOCKS RUDDER BALANCING STANDARD PRACTICES A IRFRAME20 00 00 STANDARD PRACTICES AIRFRAME20 00 00 STANDARD PRACTICES AIRFRAME20 00 00 LANDING GEAR 32 40 00 LANDING GEAR 32 40 00 LANDING GEAR 32 40 00 PARKING ANO MOORING 10 00 00 NAVIGATION 34 10 00 ICE AND RAIN PROTECTION 30 30 00 NAVIGATION 34 10 00 PNEUMATIC 36 00 00 PNEUMATIC 36 00 00 PNEUMATIC 36 00 00 PNEUMATIC 36 00 00 PNEUMATIC 36 00 00 AIR CONDITIONING 21 30 00 AIR CONDITIONING 21 30 00 AIR CONDITIONING 21 30 00 AIR CONDITIONING 21 00 00 AIR CONDITIONING 21
133. RODUCTS Loctite Corp 705 N Mountain Road Newington Conn 06111 Worldwide Aircraft Filters Corp 1685 Abram Ct San Leandro Calif 94577 Kano Labratories Inc Nashville Tennessee Aeroshell Grease 5 Shell Oil Co 50 West 50th Street New York N Y Minnesota Mming and Manufacturing Company St Paul Minnesota Loctite Corp 705 N Mountain Road Newington Conn 06111 Turco Products nc 24600 S Main Los Angleis California 90746 Turco Products Inc 26400 S Main Los Angeles California 90746 Braycote 137 Bray Oil Co 1925 N Marianna Ave Los Angeles California 90032 Petrotech 1 4 Pamreco P O Box 671 Butler Pa 16001 Minnesota Mining and Manufacturing Co St Paul Minnesota 12 20 00 Page 211 Nov 30 83 ITEM 47 48 12 20 00 Page 212 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL MATERIAL SPECIFICATIONS Lubricating Silicone G 322L Anti Seize Compound Locatite 76764 Paste Form 1 ib Brush Top Can Coating Alodine 1200 1200S 1201 VENDOR PRODUCTS General Electric Waterford New York 12188 Loctite Corp 705 N Mountain Road Newington Conn 06111 Amchem Products Inc Spring Garden Street Ambler Pennsylvania ITEM CHECK Engine Oil Leve Battery Electrolyte Air Conditioner Compressor Level Air Conditioner Refrigerant Propeller Air Dome Propeller Accumulator Differential Control Valve and Safety Valve P 4
134. ROL a KNOBS DIFFERENTIAL CONTROL VALVE Z OUTFLOW s 4 VALVE SPRING FILT BLEED LTER INLET AIR SCREEN AND DIAPHRAGM 3 AD ON MM VALVE FLOW gt rx x 8262 VACUUM SOLENOID CABIN ALTITUDE CONTROL SENSE LINE CHECK VALVE Pressurization Control System Schematic P 3 thru P 307 Figure 2 21 30 00 Page 2 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL indicates that the cruise altitude and the cabin altitude are identical unpressurized 4 6 psi line indicates the maximum differential pressure obtainable in the cabin To determine the lowest cabin altitude which be maintained for a given cruise altitude enter the graph at the desired cruise altitude and read right to the 4 6 psi differential pressure line Then read down the graph to the altitude which can be maintained in the cabin DIFF PRESS PSI AA Vp Mee AIRPLANE ALTITUDE THOUSANDS OF FEET EH 15 20 25 30 CABIN ALTITUDE THOUSANDS OF FEET 60 501 33 Effectual Pressure Graph Figure 3 CABIN ALTITUDE CONTROLLER MANUAL PRIOR TO P 308 Cabin altitude is maintained by the cabin altitude controller with the control anywhere from zero pressure to the maximum differential of 4 6 psi The controller is rotated until the desired cabin altitude for flight is at the 12 o clock position under the index mark Any selected cabi
135. RUNNING AND WARM UP ENGINE IOLE SPEED amp MIXTURE ADJUSTMENT ENGINE INSTALLATION ENGINE OILS APPROVED ENGINE OILS APPROVED ENGINE OVERBOOST CONTROL ENGINE OVERHAUL ENGINE REMOVAL EQUIPMENT TEST PO4 AFTER EVAPORATOR AIR FILTER REPLACEMENT EVAPORATOR AIR FILTER REPLACEMENT EXTERNAL POWER EXTERNAL POWER FIBERGLASS COMPONENTS REPAIR OF FIREWALL SHUT OFF VALVE FLAP ACTUATOR INSTALLATION FLAP ACTUATOR REMOVAL FLAP CONTROL SYSTEM RIGGING FLAP FUNCTIONAL GROUND TEST FLAP INSTALLATION FLAP MOTOR GEARBOX INSTALLATION FLAP MOTOR GEARBOX REMOVAL FLAP POS IND LIGHTS ADJUST amp CHECK FLAP POSITION TRANSMITTER ADJUSTMENT FLAP REMOVAL FLAP TRACK ROLLER INSTALLATION FLAPS CHAPTER NAME SERVICING ICE AND RAIN PROTECTION ICE AND RAIN PROTECTION AIR CONDITIONING AIR CONDITIONING AIR CONDITIONING AIR CONDITIONING DIMENSIONS AND AREAS AIR CONDITIONING FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS ELECTRICAL POWER STABILIZERS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS FLIGHT CONTROLS EQUIPMENT FURNI SHINGS EQUIPMENT FURNISHINGS EQUIPMENT ANO FURNISHINGS STABILIZERS TURBINES POWER PLANT POWER PLANT POWER PLANT POWER PLANT CHARTS OIL TURBINES ENGINE POWER PLANT AIR CONDITIONING AIR CONDITIONING SERVICING
136. SYSTEM 308 AND AFTER PROBABLE CAUSE Cabin altitude con troller inoperative Outflow valve inop erative Dump valve solenoid stuck in open position Shutoff solenoid in cabin controller supply line stuck in closed Position Outflow valve control line restricted Outflow valve and safety valve seats dirty Firewall shutoff valves pulled closed Hole in flex ducts from engine i Excessive pressure leaks in cabin door seal etc REMARKS Check by performing PRESSURIZATION TEST Check by performing PRESSURIZATION TEST Cycle pressurization system Circuit breaker check for operation of solenoid replace if inoperative Cycle pressurization system circuit breaker check for operation of solenoid replace if inoperative Check for restrictions repair or replace Clean the valve seats with a lint free cloth moistened with isopropyl alcohol Open valves Inspect and repair or replace as required i Check cabin for leaks repair as required BEECHCRAFT amp DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PRESSURIZATION SYSTEM Cont d P 308 and after TROUBLE No pressure indication on ground Maximum cabin differ ertial pressure exceeds 4 6 psi Cabin pressure slow to respond to change in selected cabin altitude Cabin altitude higher than selected altitude Cabin altitude lower
137. Spring Scale Figure 202 20 00 00 Page 201 Apr 18 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL To calculate the force in pounds scale reading required to obtain the specified torque divide the torque in inch pounds by the distance in inches between the center of the bolt and the scale attaching point For example if the specified torque is 5 000 inch pounds and the distance is 25 inches a pull of 200 pounds must be applied Unless torque values are specified as wet lubricated bolts to be torqued must be clean and free of all lubricants otherwise loss of normal friction allowed for establishing the torque values may result in overtorquing of the boit When a torque wrench adapter is used the length of the adapter must be added to the length of the flex or T handle wrench and a value calculated for that particular combination The following is a typical example in finding a desired value Effective length of flex or T handle 2 2 22 2 4 12 inches Length of inches Totallengthi iiie onere eer ees eo er 15 inches Desired torque on bolt 2 000 inch pounds 15 inches 133 3 pounds scale reading AIRPLANE FINISH CARE CLEANING AND WAXING THE AIRPLANE FINISH NOTE Urethane finishes are fully cured at time of delivery may be cleaned with detergents and reguire no wax
138. Surf Green Shamrock Green Turquoise Lemon Yeliow Castle Tan BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL Huntsman Red Toreador Red Chianti Red Matterhom White 118684 1 Black 118684 3 Sable Brown 118684 5 Capri Blue 118684 7 Champagne Gold 118684 9 118684 11 Kingston Gray 118684 13 Marlin Blue 118684 15 Bahama Blue 118684 17 Pavonne Blue 118684 19 Matador Red 118684 21 Sunburst Yellow 118684 23 Jade Mist Green 118684 25 Astro Biue 118684 27 Peacock Turquoise 118684 29 Terrace Blue 118684 31 Sahara 118684 33 Prairie Beige 118684 39 Antique Gold 118684 221 Beechwood 118684 223 Embassy Red 118684 231 118684 265 LACQUER 118684 273 118684 299 Interior Colors 118684 333 118684 335 Alpine Blue 118684 337 Anchor Gray 118684 339 Duli Black 118684 341 Autumn Smoke 118684 345 Desert Beige 118684 347 Uriftwood 118684 349 Artic Beige 118684 351 Sandusky Gold 118684 353 Frontier Gold 118684 355 Banff Blue 118684 357 Sable Brown 118684 359 Turquoise 118684 361 Mist Green Pumpkin Broadway Blue Sun Beige Torch Red Spanish Gold 118684 302 Canyon Blue 118684 304 Gulf Blue 118684 305 Maize Gold 118684 306 Silver Gray 118684 307 Green 118684 308 New Blue 118684 310 New Bronze 118684 312 Varsity Blue 118684 315 118684 316 118684 317 118684 318 118684 319 118684 320 118684 322 118684 323 118684 324 118684 325 118684 393 118684 395 118684 397 118684 399 118684 401 11868
139. Synchronizer for Light Twin Engine Aircraft Bulletin Number 33049C Woodward Governor Company Rockford Illinois INTRODUCTION s Page 9 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL HYDRAULIC ACCUMULATOR Maintenance Manual Number 33058 Woodward Governor Company Rockford Illinois GENERATOR Overhaul and Parts Breakdown File 30204 Lear Siegler Inc Cleveland Ohio BATTERY Operator and Service Manual for Vented Celi Nickel Cadmium Battery GET3593A General Electric Company Gainesville Florida Maintenance Manual for Nickel Cadmium Battery ABD1100 Gulton Industries Inc Metuchen New Jersey Marathon Battery Installation Manua BA89 Marathon Battery Co Cold Springs N Y ELECTRIC PROPELLER DEICER installation of Deicer Boots Report 59 728 B F Goodrich Company Akron Ohio Installation Inspection and Testing of Propeller Deicer System Report 68 04 708 Goodrich Company Akron Ohio HEATER VENT BLOWER Overhaul Instructions for Vane Axial Blower Number M6921N6A with Motor M3416DA Dynamic Air Engineering inc Santa Ana California HEATER Maintenance instructions for Janitrol A34D51 Aircraft Heater Publication Number 57083 Janitrol Aero Division Midland Ross Corporation Columbus Ohio Maintenance Instructions for Janitrol 52070 Aircraft Heater Ignition Unit Publication Number 58D42 Janitrol Aero Division Midiand Ross Corporation Columbus Ohio AIR CONDITIONER COMPRESSOR
140. T DUKE 60 SERIES MAINTENANCE MANUAL GENERAL DESCRIPTION AND OPERATION AC GENERATION Since the major portion of the airplane instrumentation func tions on dc power the ac power requirements are confined to only the fuel flow indicator windshield heat and some avion ics The inverter for the fuel flow indicator is a small unit designed to supply power only to this instrument An inverter is installed for the operation of the left windshield heat and is activated by a switch on the pilots subpanel marked L WSHLD OFF This inverter is also used as a standby for the avionics inverter Avionics power is obtained by two switches mounted on the upper switch panel One is marked MASTER OFF and activates power to the avionics equipment For that equip ment requiring ac current a three position switch marked MN INV OFF STBY INV must be placed in the MN INV position Should a failure occur in the main inverter the switch can be placed in the STBY INV position This opens a relay to direct the current from the windshield heat inverter to the avionics provided the L WSHLD switch is on Because the STBY INV switch position is designed only to direct the current flow no power can be supplied to the avionics with the L WSHLD switch in the OFF position Power for the operation of both systems cannot be supplied by this inverter at the same time AC VOLTAGE FREQUENCY INDICATOR On airplanes that are equipped with the AC Voltage Freq
141. T DUKE 60 SERIES MAINTENANCE MANUAL under the hub clamp or on the edge of the spinner dome Manually operate the propeller from low pitch to high pitch while checking that the deicer lead straps do not come under tension e Check the slip rings for gouges roughened surfaces cracks burned or discolored areas and for deposits of oil grease or dirt Clean greasy or contam inated slip rings with PD680 solvent 15 Chart 207 91 00 00 After such cleaning a run in time of five hours of engine operation must be allowed before the deicer system is turned on f If uneven wear or wobble is detected check the alignment of the slip rings to the propeller shaft with a dial indicator While turning the propeller to check the slip ring alignment push in on the propeller to eliminate play in the propeller thrust bearing If the runout over 360 degrees of rotation is over 005 inch or if over any 4 arc it exceeds 002 inch refer to step h Examine the brush mounting brack ets and housing for cracks deformation or other indications of damage Check for tight connections and that the leads are not chafed or binding h Check to see that each brush rides on its slip ring over 360 degrees of rotation If the brush is not properly aligned raise or lower the brush block to the proper position If the brushes ride both high and low with respect to the slip rings in 360 degrees of rotation the slip ring is eccentrical
142. T CONTROLS 27 10 00 TRIM TAB FREE PLAY CHECK ELEVATOR FLIGHT CONTROLS 21 30 00 TRIM TAB FREE PLAY CHECK RUDDER FLIGHT CONTROLS 27 20 00 TROUBLESHOOTING ICE AND RAIN PROTECTION 30 40 00 TROUBLESHOOTING TURBINES 81 00 00 TROUBLESHOOTING AIR CONDITIONING SYS AIR CONDITIONING 21 00 00 TROUBLESHOOTING AIRFOIL DEICER SYST ICE AND RAIN PROTECTION 30 10 00 TROUBLESHOOTING 8ATTERY ELECTRICAL POWER 24 31 70 TROUBLESHOOTING BATTERY SYSTEM ELECTRICAL POWER 24 31 00 TROUSLESHOOTING BRAKE SYSTEM LANDING GEAR 32 00 00 TROUBL ESHOOTING ENG INE POWER PLANT 71 00 00 TROUBLESHOOTING GENERATOR SYSTEM ELECTRICAL POWER 24 30 00 TROUBLESHOOTING HEATER SYSTEM AIR CONDITIONING 21 00 00 TROUBLESHOOT ING LANODING LIGHTS LIGHTS 33 40 00 TROUBLESHOOTING LOG GEAR ELECT SYST LANDING GEAR 32 00 00 TROUBLESHOOT IING NEW MATIC AUTOPILOT AUTO FLIGHT 22 11 00 TROUBLESHOOTING PITOT STATIC SYST NAVIGATION 34 10 00 TROUBLESHOOT ING PRESSURIZATION SYST AIR CONDITIONING 21 00 00 TROUBLESHOOT ING PROP DEICING SYSTEM ICE ANO RAIN PROTECTION 30 60 00 TROUBLE SHOOTING PROP SYNCHRONIZER PROPELLERS 61 00 00 TROUBLESHOOTING STALL WARNING SYSTEM FLIGHT CONTROLS 27 60 00 TROUBLESHOOTING STARTER SYSTEM STARTING 80 10 00 TROUBLESHOOTING STROBE LIGHTS LIGHTS 33 40 00 TURBOCHARGER CONTROL SYSTEM TURBINES 81 00 00 TURBOCHARGER CRITICAL ALTITUOE TEST TURBINES 81 00 00 TURBOCHARGER INSTALLATION amp RUN IN TURBINES 81 00 00 TURBOCHARGER SYSTEM TURBINES 81 00 00 TURBOCHARGER VARIABLE
143. TER To RELAY 1 LOADMETFR 3 LEET REVERSE Et CURRENT NERATOR CE DIODE E VOLTAGE REGULATOR 128 VOC LEFT ISOLATION BUS LEFT NACELLE OVER VOLTAGE RELAY 432 RIGHT WINDSHIELO ANTI ICE INVERTER HE INSTALLEDI EXTERNAL POWER EXTERNAL VOLTAGE POWER RECEPTACLE TEST RELAY CONTROL RIGHT STARTER RELAY RIGHT STARTER lt i LOADMETER si REVERSE RIGHT CURRENT GENERATOR D DIODE VOLTAGE REGULATOR 28 VICI 1 J OVER VOLTAGE RELAY 32 pim RIGHT ISOLATION BUS IN LEFT NACELLE 45A WINDSHIELO ANTIICE AVIONICS STANDBY INVERTER LEFT AVIONICS RIGHT ELECTRICAL POWER LEFT AVIONICS ELECTRICAL POWER CONTROL BUS RIGHT POWER AVIONICS 1ST 3RD ROW 2ND AND 4TH ROW aus AVIONICS CIRCUIT AVIONICS CIRCUIT REAKER soe o SREAKE BREAKERS 50A aus Bus BUS BUS NO 1 NO NOT NO 2 AVIONICS MASTER SWITCH AiR CONOITIONER CABIN TEMPERATURE CONTROL LEFT CYLINDER HEAD TEMPERATURE LEFT COWL FLAP VOLT METER j RIGHT WINDSHIELD ANTI ICE UF INSTALLED OVERVOLIAGE RELAY FLAP MOTOR MOTOR STARTER ANO IGNITION LANOING GEAR RIGHT LANDING LIGHT COPILOT S INSTRUMENT LIGHTS SUSPANEL LIGHTS BATTERY CHARGE RIGHT CYLINDER HEAD TEMPERATURE RIGHT RIGHT FUEL
144. TION The stall warning system consists of a stall warning horn mounted forward of the instrument panel a lift transducer a lift transducer vane heater element a face plate heater element on the leading edge of the left wing a landing gear switch a circuit breaker and a stall and pitot switch located on the pilot s subpanel When aerodynamic pressure on the lift transducer vane indicates that a stall is imminent the transistor switch is actuated to complete the circuit to the stall warning horn The lift transducer senses the angle of attack and is triggered by reverse air flow CAUTION The heater element protects the lift transducer from ice however a buildup of ice on the wing may disrupt the airflow and prevent the system from accurately indicating an incipient stall END 27 60 00 Page 1 Nov 2 73 1 2 TROUBLE Warning system inoperative Horn continues to blow a BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING STALL WARNING SYSTEM PROBABLE CAUSE Warning circuit breaker tripped Open circuit Defective warning horn switch Defective warning horn Defective warning horn switch END REMARKS If circuit breaker persists tripping check for grounded circuit Check for continuity Replace switch Replace horn Replace switch 27 60 00 Page 101 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL STALL WARNING MAINTENANCE
145. TION SYSTEM Cont d P 308 and after TROUBLE 6 Cabin altitude lower than selected altitude not exceeding maximum differential pressure 7 Cabin pressure fluctuation 8 Cabin pressurization system circuit breaker tripped PROBABLE CAUSE Cabin altitude controller supply line or outflow valve control line leaks Cabin altitude indicator inoperative Valve seats dirty Dump valve solenoid shorted Shutoff solenoid in cabin pressurization controller shorted Pressurization system circuit shorted REMARKS Inspect repair or replace as required Replace indicator Clean the valve seats with a lint free cloth moistened with isopropyl alcohol Locate cause repair or replace defective component reset circuit breaker Locate cause repair or replace defective component reset circuit breaker Locate cause repair or replace defective component reset circuit breaker 9 Airplane pressurizes Landing gear safety Replace or adjust the RH landing on ground switch inoperative or gear safety switch improperly rigged Open circuit in cabin Locate cause repair or replace pressurization circuit defective component 21 00 00 Page 106 May 30 75 1 TROUBLE Heater fails to light BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING HEATER SYSTEM PROBABLE CAUSE REMARKS Master switch or circuit a Turn on master switch o
146. TRIM TAB DETAIL H MIL G 23827 trim tab actuator 1 tAileron trim tab hinge 1 MIL M 7866 TMix MIL M 7866 with naphtha and apply with a brush A60 604 118 12 20 00 Page 218 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 Cont d LUBRICATION SCHEDULE LOCATION LUBRICATION INTERVAL MAIN LANDING GEAR DETAIL 1 Main wheel bearings 4 MIL G 3545 Main shock struts 2 MIL H 5606 Uplock rollers 2 SAE10W 30 HAND PACK WITH MI L G 23827 MIL G 23827 P 3 THRU P 154 P 156 THRU P 162 P 167 THRU P 171 AND P 182 PRIOR TO COMPLIANCE WITH 5 1 0482 211 P 155 P 163 THRU P 166 P 172 THRU P 181 P 183 AND AFTER AND PREV IOUS AIRPLANE SERIALS IN COMPLIANCE WITH 5 1 0482 211 NOTE Refer to Chapter 32 of the Maintenance Manual for instructions on periodic lubrication of uplock rollers DETAIL I LOCATION LUBRICANT INTERVAL Main retract fittings 8 MIL G 81322 100 hrs Main gear door hinges 10 SAE10W 30 100 hrs 60 604 15 12 20 00 219 30 75 12 20 00 Page 220 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 Cont d LUBRICATION SCHEDULE LOCATION NOSE LANDING GEAR Nose wheel bearings 2 Nose shock strut 1 Nose gear door hinges 6 Nose gear forward retract rod 1 Nose gear brace bushings 4 P 297 and after DETAIL J AFT SIDE LUBRICANT INTERVAL DETAIL J MIL G 3545 MIL H 5606
147. UAL b Operate both engines at 1300 to 1500 rpm with both generators ON and the electrical load reduced to a minimum Adjustment of both voltage potentiometers in steps c and d will provide an increase in voltage when the potentiometers are turned clockwise Make the adjustment in smail increments only Allow ample time for the voltage to stabilize before making further adjustments c Turn the right generator CFF and adjust the left voltage potentiometer to 28 25 0 25 volts d Turn the right generator ON and the left generator OFF and adjust the right voltage potentiometer to 28 25 0 25 e Repeat steps c and d until the minimum load voltage is satisfactory CURRENT ADJUSTMENT MAXIMUM LOAD The paraileling rheostats are adjusted to produce equal out puts from the generators at heavy loads a Check the accuracy of the loadmeters on the in strument panel by alternately switching from one generator to the other while a normal load is turned on If equal readings are obtained as each generator supplies the current individu ally the loadmeters are satisfactory If excessive deviation in loadmeter readings exist the loadmeters should be replaced b Operate both engines at 1 300 to 1 500 rpm with both generators ON Tum on all feasible electrical loads using lights blowers radio equipment etc except pitot heat and heated windshieid c Read the loadmeters Each generator should take its share of the load w
148. UDE COOLING COWL FLAP ACTUATOR RIGGING COWL FLAP ACTUATOR INSTALLATION COWL FLAP AND ACTUATOR REMOVAL COWLING INSTALLATION COWLING REMOVAL OC GENERATION DEFUEL ING A IRCRAFT CHAPTER NAME LANDING GEAR LANDING GEAR LANDING GEAR LANDING GEAR LAROING GEAR LANDING GEAR LANOING GEAR LANOING GEAR LANDING GEAR SERVICING LANDING GEAR LANDING GEAR LARDING GEAR LANDING GEAR AIR CONDITIONING AIR CONDITIONING AIR CONDITIONING AIR CONDITIONING AIR CONDITIONING AIR CONDITIONING AIRCONDITIONING DOORS DOGRS DOGRS DOARS DOORS DOGRS DOORS AIR CONDITIONING FLEGHT CONTROLS WINGS WATER WASTE AIR CONDITIONING AIR CONDIT IONING AIR lt CONOI TIONING ATR CONDITIONING AIR CONDITIONING AIR CONDITIONING SERVICING ATR CONDITIONING SERVICING AIR CONDITIONING AIR CONOITIONING AIR CONDITIONING AIR CONOITIONING CHARTS SERVICING FLIGHT CONTROLS FLIGHT CONTROLS ELEGHT CONTROLS ELIGHT CONTROLS APR CONDIT IONING AIR CONOITIONING AER CONDITIONING POWER PLANT POWER PLANT POWER PLANT POWER PLANT POWER PLANT ELECTRICAL POWER FUEL INTRODUCTION PAGE 12 AUG 15 80 CHAPTER amp SUB CHAPTER 32 40 00 32 0 00 32 40 00 32 40 00 32 40 00 32 40 00 32 40 00 32 40 00 32 40 00 12 10 00 32 40 00 32 40 00 32 40 00 32 40 00 21 30 00 21 30 00 21 30 00 21 30 00 21 30 00 21 30 00 21 30 00 52 10 00 52 10 00 52 10 00 52 10 00 52 10 00 52 70 00 52 10 00 21 0 00 27 00 00
149. UL OR REPLACE FLAPS AND FLIGHT CONTROLS Cont d Flap motor and drives Every 2000 hours Flap gearbox Every 2000 hours Flap actuators Every 2000 hours Flap flexible shaft Every 2000 hours MISCELLANEOUS Wing bolts Replace 10 years after the initial inspection or on condition See Chapter 57 00 00 END 5 10 00 Page 207 A18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SCHEDULED MAINTENANCE CHECKS MAINTENANCE PRACTICES NOTE For listing of alternative inspection programs available for use with this airplane refer to the latest issue of the BEECHCRAFT Publications Price List P N 118556 The time periods for the inspections noted in this schedule are based on normal usage under average environmental conditions Airplanes operated in humid tropics or in cold damp climates etc may need more freguent inspections for wear cor rosion lubrication and or lack of main tenance Under these adverse conditions perform periodic inspections in compli ance with this guide at more frequent intervals until the owner or operator can set his own inspection periods based on the contingencies of field experience Airplanes operated less than 100 hours a year must have a 100 Hour Inspection per formed no later than 12 months following the date of the preceding 100 Hour Inspection The 100 hour interval between performance of the procedures specified herein should NEVER be exceeded by more tha
150. VENT HEAT J RIGHT FUEL QUANTITY RIGHT FUEL BOOST A ROTATING BEACON HOUR METER PROPELLER SYNCHRONIZER Power Distribution Schematic P 446 and after Figure 203 24 50 00 ELECTRICAL UTILIZATION LOAD BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 201 Number Per Aircraft CONTINUOUS LOAD STANDARD EQUIPMENT Battery Relay Cabin Pressure Control System Ram Air Magnetic Door Catch Isobaric Control Valve Cabin Pressure Differential Control Valve Cylinder Head and Oil Temperature System Cylinder Head Temperature Indicator Oil Temperature Indicator Flap Position System Flap Position Indicator Fiap Position Printed Circuit Board Fuel System Fuel Flow Indicator Inverter Fuel Quantity Indicator Fuel Vent Heater Heater System Vent Blower Vent Blower Relay Combustion Air Blower Manual or Automatic Select Relay Heater Cycle Control Relay Heater Fuel Pump Remote Heater Solenoid Valve Heater Assembly Combustion Air Select Valve Heater Safety Relay Cabin Temperature Control Box Cabin Air Sensing Element Pitot Heater LH Turn and Slip Indicator Voltmeter Lighting Dim Switches Only one used at a time Load Per Unit in Amps 0 60 0 21 0 90 0 50 0 49 0 31 0 001 0 059 0 94 0 05 1 35 17 00 0 35 2 90 0 09 0 09 0 40 0 33 1 30 0 63 0 09 0 18
151. VITY BLEEDING BRAKE HYDRAULIC SYSTEM BRAKE MASTER CYLINDER INSTALLATION BRAKE MASTER CYLINDER LINKAGE ADJUST BRAKE MASTER CYLINDER REMOVAL BRAKE PRESSURE BLEEDING BRAKE SYSTEM BRAKE SYSTEM BLEEDING BRAKE SYSTEM BLEEDING OUAL BRAKE WEAR LIMETS GOODRICH BRAKE WEAR LIMITS GOODYEAR CABIN ALTITUDE CONTROLLER ADJUSTMENT CABIN ALTITUDE CONTROLLER FILTER CABIN ALTITUDE CONTROLLER INSTALLATION CABIN ALTITUDE CONTROLLER INSTALLATION CABIN ALTITUDE CONTROLLER REMOVAL CABIN ALTITUOE CONTROLLER MANUAL CABIN ALTITUDE CONTROLLER MOTORIZED CABIN DOOR CABIN DOOR INSTALLATION CABIN DGOR LATCH ADJUSTMENT CABIN DOOR LATCH MECHANISM LUBE CABIN DOOR LATCH MECHANISM RIGGING CABIN DOOR LIGHT SWITCHES CABIN DOOR REMOVAL CABIN TEMP SENSORS CONT RHEO TEST CABLE TENSION EFFECT OF TEMP UPON CARRY THROUGH STRUCTURE CHEMICAL TOILET CLEANING COMBUSTION AIR BLOWER INSTALLATION COMBUSTION AIR SLOWER REMOVAL COMPRESSION COMPRESSOR BELT INSTALLATION COMPRESSOR BELT REMOVAL COMPRESSOR BELT TENSION ADJUSTMENT COMPRESSOR BELT TENSION ADJUSTMENT COMPRESSOR INSTALLATION COMPRESSOR OIL LEVEL CHECKING COMPRESSOR OIL LEVEL CHECKING COMPRESSOR REMOVAL CONDENSER BLOWER INSTALLATION CONDENSER BLOWER REMOVAL CONSUMABLE MATERIALS CONSUMABLE MATERIALS CHART CONTROL COLUMN CONTROL COLUMN BUS CABLE INSTALLATION CONTROL COLUMN BUS CABLE REMOVAL CONTROL COLUMN BUS CABLE RIGGING CONTROLLER INSTALLATIDNsCABIN ALTITUDE CONTROLLER REMOVAL CABIN ALTIT
152. YLINDER HEAD TEMPERATURE Check for proper operation temperature and fluctuations ALTERNATOR Check the output PROPELLER OPERATION Cycle propeller and check for proper rpm drop and smoothness of operation PROPELLER SYNCHRONIZER Check for proper operation PROPELLER DEICER Check for amperage drawn on ammeter proper operation and 5 20 00 Page 202 Nov 20 87 A1 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL A OPERATIONAL INSPECTION Cont d MECH INSP PRE 7 OIL PRESSURE AND TEMPERATURE Check for proper pres sure temperature limits and unusual fluctuations MAGNETOS Check the performance of the magneto by per forming the MAGNETO DROP OFF CHECK specified in the applicable Pilot s Operating Handbook POWER CHECK Check as outlined in the applicable Pilot s Operating Handbook ALL ENGINE CONTROLS With the engine running check for proper operational limits engine response and rigging Check friction locks for proper operation Check for proper lubrication of the connection bolts and excessive free play PROPELLER GOVERNORS Check for proper governor tion and feathering AIR CONDITIONER Operate the air conditioner and verify that the air scoop moves to the ground position when turned on and returns to the retracted position when turned off Check for proper operation unusual noise FLIGHT INSTRUMENTS Check for condition and prop
153. abin rate of descent not to exceed 1 000 feet per minute WARNING Increasing power rapidly could cause the cabin to pressurize to maximum differential within a short time to the subsequent discomfort of personnel in the airplane e tf the cabin rate of climb indicator shows a descent as power is increased above a minimum of 20 in Hg manifold pressure the cabin altitude control is defective f the cabin rate of climb does not show a descent as power is increased above a minimum of 20 in Hg manifold pressure the isobaric contro portion of the differential control valve is defective The differential contro portion of the valve may also be checked by allowing the cabin to pressurize to maximum differential pressure If cabin pressure stabilizes at 4 6 to 4 7 psi as monitored by the cabin differential pressure gage the differential control portion of the valve is functioning properly g SLOWLY decrease power until the cabin is depressurized then shut down both engines h If any components were found defective replace them and repeat the test i Reset the pressurization control circuit breaker j Reconnect the cabin altitude control sense line to the differential control valve then reinstall the upholstery panels on the aft pressure bulkhead 21 30 00 Page 203 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PRESSURIZATION CONTROL MAINTENANCE PRACTICES P 308 AND AFTER OUTFLOW VALVE AND SAFETY VA
154. aching screws COMPRESSOR BELT TENSION ADJUSTMENT After 36 to 48 hours operating time a new belt will stretch to its normal operating length The belt tension should be checked at this time and adjusted by moving the compressor up and down in its slotted mounts so that a belt tension gage placed at a point midway between the longest span will register a tension of 100 to 105 pounds After adjusting the tension on a new belt be sure the belt has ample clearance on all sides COMPRESSOR BELT REMOVAL a Remove the RH engine cowling to gain access tc the compressor belt b Loosen compressor attaching nuts and slide the compressor upward in its slotted mount to relieve tension on the belt Roli the belt off the compressor puliey c Remove the bolts attaching the compressor turbocharger mount support to the engine d Remove the belt from the engine crankshaft pulley and slip it out between the compressor turbocharger mount and the engine COMPRESSOR BELT INSTALLATION a Slip the compressor belt between the compressor turbocharger mount and the engine and position the belt on the crankshaft pulley b Secure the compressor turbocharger mount support to the engine with attaching screws c Roll the belt onto the compressor pulley Slide the compressor downward in its slotted mount to apply tension on the belt and secure the compressor attaching nuts d install the RH engine cowling COMPRESSOR REMOVAL a Remove the RH eng
155. achment Check refrigerant and oil levels Check belt for tension and worn or frayed condition INDUCTION AIR FILTER Check for condition cleanliness and security INDUCTION SYSTEM AND ALTERNATE AIR Check flexible air ducts for delamination of the inner lining Check the alternate air valve for blockage security cracks operation and wear FUEL INJECTION CONTROL VALVE Clean the screen and check for damage Install screen and check for leaks FUEL INJECTION SYSTEM Inspect all fuel injection com ponents lines and fittings for evidence of fuel leaks fraying and cracking TURBOCHARGERS Check the compressor wheel for nicks and cracks Check linkages for security and proper opera tion TURBINE INLET TEMPERATURE INDICATOR Check the indica tor for accuracy and calibrate as outlined under the heading TIT INDICATOR CALIBRATION in Chapter 77 00 00 L R 5 20 00 Page 209 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL B POWER PLANT Cont d 34 C N ELECTRIC PROPELLER DEICER Check for service damage to the deicer heaters brush rods springs and brushes Check the lead strap and all other clamps connectors and wiring for electrical soundness Check the slip rings for roughness cracks burned or discolored areas and for deposits of oil grease or dirt Check for security and attachment of all components Check deicer boots for wrinkles loose or torn areas ACELLES NACELLE
156. acle The smalt pin of the receptacle must be supplied with 24 VDC to close the external power relay that provides protection against damage by reverse polarity END 24 40 00 Page 201 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ELECTRICAL LOAD DISTRIBUTION MAINTENANCE PRACTICES The dual bus feeder diodes should be inspected at 600 flight hour intervals as instructed under PERIODIC INSPECTION OF DUAL BUS FEEDER DIODES Whenever the dual bus has been modified or extensive repairs have been made that could result in the dual bus loops being interconnected or open it is necessary to perform a DUAL BUS CONFORMITY INSPECTION This will ensure that the original design of the dual bus is maintained PERIODIC INSPECTION OF DUAL BUS FEEDER DIODES Figure 202 An open or shorted dual bus feeder diode cannot be detected during the normal operation of the aircraft electrical system Should a malfunction occur which would cause a bus isolation limiter to open such as a ground fault on a generator bus an open dual bus feeder diode could not supply power to its respective dual bus loop A shorted diode would not isolate its respective dual bus from a ground fault The inspection procedure outlined here will ensure the dual bus capability The inspection may be performed at a normal periodic inspection of the aircraft and either battery power or an auxiliary ground power unit connected to the external power receptacle may
157. ad until a 1 5 pound upward load is obtained Record the dial reading as D j Enter the recorded values on a copy of Chart 201 and proceed as follows 1 Multiply B by 2 and record as 2B 2 Subtract A from 2B and record as X 27 10 00 Page 204 Sep 14 79 3 Multiply D by 2 and record as 2D 4 Subtract C from 2D and record as Y NOTE The results of X and Y can be negative numbers 5 Add X and Y and record as E CHART 201 AILERON TAB FREE PLAY LIMITS 1 5 POUND 3 POUND READING READING Berl m c 28 SA NENNEN EMT X ullo SE E 0 032 inch maximum k If the aileron trim tab free play exceeds the 0 032 inch maximum noted above inspect all components of the tab actuation system to determine the cause All wom parts should be replaced BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ITEM QUANT DESCRIPTION NO 1 2 3 4 x 1 x 6 aluminum or equiv 2 2 1x1 3 8 x 1 3 4 aluminum or equiv 3 1 1 2 x 7 1 2 x 10 aluminum or equiv 4 1 C81Q Indicator 5 1 3 4 x 2 1 2 x 14 aluminum or equiv 6 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Dia x 1 corrosion res stl 8 1 1 4 28 nut 9 1 3 8 x 5 x 10 rubber 10 1 3 8 x 2 x 10 rubber 11 1 1 4 x 2 x 10 corrosion res sti 12 2 1 2 x 13 x 3 VLIER Torque screw 13 2 KN813 Keensert or tap 1 2 13 14 2 1 8 x 1 x 3 4 rubber SECTION A A THIS GROOVE TO BE A SNUG FIT P N of Federal Products Corp Providence R I IHE D
158. and the safety valve are to be tested for proper differential pressure operation proceed as follows 1 Remove the uphoistery panel from the aft pressure bulkhead Remove the access plate to gain access to the outflow valve and safety valves 2 Loosen and remove the plumbing from the true static air vent port 1 on the head section of each valve Tag each tube to facilitate reinstallation Add a section of tubing to each static air vent of sufficient length to reach through the holes in the access plate after it has been reinstalled since the airplane must not be pressurized prior to installation of the plate Provide a means of disconnecting and capping each true static air vent with the piate reinstalled Tag each tube for identification during the test 3 Reinstall the plate Secure the plate and tighten the boits evenly to a torque of 50 to 70 inch pounds for the AN4 5A bolts at the top and bottom of the plate and 20 to 25 inch pounds for the remaining bolts WARNING The airplane must not be pressurized prior to installation of the plate b Close and secure the cabin door c Rotate the cabin rate control selector knob to the 12 o clock position d Select a cabin altitude that is approximately 500 feet above the field elevation e Set the airplane brakes and start the engines as instructed in the applicable Duke Pilot s Operating Manual Operate both engines at a minimum power setting of 20 in Hg manifold pressure to
159. ape Chart 201 12 20 00 The system should then be checked for leaks with MIL L 25567 leak testing compound 14 Chart 202 12 20 00 After testing if no leaks are found wipe the system clean and dry END 12 10 00 Page 205 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SCHEDULED SERVICING MAINTENANCE PRAC TICES i TIRES NOTE Aero Seal is a tire additive which is very effec tive in stopping small leaks and weep hole leaks in tubeless tires The proper procedure for the use of this additive may be obtained by referring to Service Instructions No 0916 The nose gear is equipped with a 15 x 6 00 x 6 4 ply type VI tube type tire The main gear tires are either 6 50 x 8 8 ply tubeless rim inflated type P 4 through P 191 except P 190 or 19 5 x 6 75 x 8 10 ply tube type P 190 and after except P 191 and those airplanes prior to P 190 which have com plied with Service Instructions No 0536 202 Rev A max imum outside diameter of 15 inches on the nose gear tire is required to ensure proper clearance of the nose gear shock absorber assembly Inflate the nose gear tire to 47 50 psi Inflate the 8 ply main gear tires to 69 75 psi and the 10 ply main gear tires to 76 82 psi if necessary to comply with landing restrictions main gear tire inflation may be reduced to 65 psi for 8 ply tires Maintaining recommended tire infia tion will heip to avoid damage from landing shock and contact with sharp
160. ar the evaporator The fuse located in the right nacelle is thus opened preventing further operation of the compressor magnetic clutch and the compressor until the air conditioner system has been serviced NOTE The low pressure switch which was originally installed on airplane serials P 275 through 292 and P 294 prior to compliance with Service Instructions 0599 427 actuated at a pressure of 18 t 2 psi HEATER SYSTEM The heater system consists of a 45 000 BTU combustion air heater located under the nose baggage compartment floor a six position mode switch vent air blower combustion air blower heater fuel pump five outlets an automatic temperature control and three sensing elements In flight when pressurized the vent blower obtains air through the cabin air check vaive forces it through the heater and to the cabin outlets In the unpressurized mode in flight and for ground operations the vent blower obtains air from the cabin and the ram air plenum chamber and forces it through the heater and to the cabin outlets On serials P 3 through P 126 except P 123 a vent air distribution bypass valve located on the forward pressure bulkhead allows air to be directed into the pilot s compartment area and is regulated by a control knob on the pilot s left subpanel END 21 00 00 Page 2 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PRESSURIZATION SYSTEM P 3 THRU P
161. are enclosed and subject to high humidity should be pro tected against corrosion by coating with either epoxy primer MIL C 16173 corrosion preventative compound light grease or heavy oil LOWER WING AND FLAP SKINS If inspection of the lower wing and flap area aft of the exhaust stacks disclose corrosion from fuel lead deposits remove with a mild soap and water solution Use a stainless steel wire brush to remove deeper more resistive corrosion If Corrosion is so deep that 1596 or more of the skin thickness is removed the surface should be replaced if skin thickness has been reduced by less than 15 after the corrosion has been removed the area should be treated with cleaner 41 Chart 207 91 00 00 or an equivalent corrosion removing compound conforming to MIL C 38334 The skin should be treated both externally and where accessible intemally and given a protective coating as described below then primed and painted Inspection door nut plates should be removed prior to treating the skins with corrosion removing compound if corroded the nut plates should be replaced CAUTION The corrosion removing compound should be applied in accordance with the manufacturers instructions and cautions In addition to the above noted treated skins new flaps new skin splices should be treated externally with a protec tive coating as described below primed and painted and all accessible interior aluminum wing parts on the lower
162. asking tape on the opposite surface Record the dial reading as C i Release half the toad until a 1 5 pound load is obtained Record the dial reading as D col Enter the recorded values on a copy of Chart 201 and proceed as follows 1 Multiply B by 2 and record as 2B 2 Subtract A from 2B and record as X 3 Multiply D by 2 and record as 2D 4 Subtract C from 2D and record as Y NOTE The results of X and Y can be negas numbers 5 Add X and Y and record as E CHART 201 RUDDER TAB FREE PLAY LIMITS 1 5 POUND 3 POUND READING READING luu DB mA nan D 2D LL CC zY gt cd Y E 0 061 inch maximum k If the rudder trim tab free play exceeds the 0 061 _ ioch maximum noted above inspect all components of the tab actuation system to determine the cause All wom parts should be replaced BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 678 ITEM QUANT DESCRIPTION NO 1 2 3 4 x 1 x 6 aluminum or equiv 2 2 1x1 3 8 x 1 3 4 aluminum or equiv 3 1 1 2 x 7 1 2 x 10 aluminum or equiv 4 1 C810 Indicator 5 1 3 4 x 2 1 2 x 14 aluminum or equiv 6 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Dia x 1 corrosion res stl 8 1 1 4 28 nut 9 1 3 8 x 5 x 10 rubber 10 1 3 8 x 2 x 10 rubber 11 1 1 4 x 2 x 10 corrosion res stl 12 2 1 2 x 13 x 3 VLIER Torque screw 13 2 KN813 Keensert or tap 1 2 13 14 2 1 8 x 1 x 3 4 rubber SECTION A THIS
163. ating the desired information The alphabetical index provides the chapter and sub chapter in which any given information may be found Reference to the Table of Contents in the front of the indicated chapter will provide the exact page on which the information can be found MICROFICHE AEROFICHE The General Aircraft Manufacturers Association has developed a specification for microfiche and registered the name Aerofiche for use by all GAMA Members Consult the current issue of the Publications Price List for a enumeration of the maintenance information available i Aerofiche form for order from Beech Aircraft Corporation ATA 100 INDEX GUIDE The following is an ATA 100 System Chapter Sub System Section Index Guide for use with Maintenanci Manuais Parts Catalogs Wiring Diagram Manuals an Component Maintenance Manuals as required WARNING Use only genuine BEECHCRAFT or BEECHCRAFT approved parts obtained from BEECHCRAFT approved sources in connection with the maintenance and repair of Beech airplanes Genuine BEECHCRAFT parts are produced and inspected under rigorous procedures to insure airworthiness and suitability for use in Beech airplane applications Parts purchased from sources other than BEECHCRAFT even though outwardly identical in appearance may not have had the required tests and inspections performed may be different in fabrication techniques and materials and may be dangerous when installed in a
164. ation place an exter battery in parallel with the output of the exter nal power unit before operating any transis torized avionics equipment C If the unit does not have a standard AN plug check the polarity and connect the positive lead from the external power unit to the center post and the negative lead to the front post of the airplane s external power receptacle The small pin of the receptacle must be supplied with 24 vdc to close the extemal power relay that provides protection against damage by reverse polarity BATTERY Airplanes prior to P 446 are equipped with 24 volt 13 5 ampere hour batteries To obtain optimum service from the nickel cadmium battery proper and reguiar maintenance of the battery must be performed Serials P 4 through P 225 are equipped with either General Electric or Gulton batteries Serials P 226 through P 445 are equipped with General Electric air cooled batteries Airplanes P 446 and after are equipped with two 25 am pere hour 12 volt lead acid batteries connected in series and supplying a total system capacity of 24 volts A Systernatic Battery Maintenance Program should be estab lished and carefully followed a The battery should be removed from the airplane for service b log of the services performed on each battery should be maintained battery should be removed from the airplane and serviced after 100 Flight Hours or 30 days whichever occurs first if
165. ator This will be the point of pressure against the tab by the push pull scale 27 30 00 Page 206 Sep 14 79 d Apply another piece of masking tape in the corresponding position on the bottom surface of the tab for the same purpose e Zero the dial indicator at no load initially Do not reset during the checking procedure i f With the push pull scale at the point of the masking tape apply a full 3 pound downward load Record the dial reading as A g Release half the load until a 1 5 pound downward load is obtained Record the dial reading as h Apply a full 3 pound upward load at the masking tape on the bottom surface Record the dial reading as C i Release half the load until a 1 5 pound upward load is obtained Record the dial reading as D j Enter the recorded values copy of Chart 201 and proceed as follows 1 Multiply B by 2 and record as 2B 2 Subtract A from 2B and record as X 3 Multiply D by 2 and record as 2D 4 Subtract C from 2D and The results of X and Y be negative numbers 5 Add X and Y and record as E CHART 201 ELEVATOR TAB FREE PLAY LIMITS 1 5 POUND 3 POUND READING READING B 2B Doi Le 2D Mi a 5 et 2 0 020 inch maximum k If the elevator trim tab free play exceeds the 0 020 inch maximum noted above inspect all components of the tab actuation system to determine
166. ators and associated electrical equipment from volt age transients power fluctuations d Settheoutput of the auxiliary power unit at 27 0 to 28 5 vdc e Place the auxiliary power unit in the on position if the battery master relay will not close the batteries must be removed from the airplane for recharging Check the battery master relay control circuit for a malfunction END 24 31 00 Page 209 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL DC GENERATION MAINTENANCE PRACTICES BATTERY CHARGE CURRENT DETECTOR SYS 7EM FUNCTIONAL CHECK Prior to P 446 NOTE Satisfactory load change as used herein is de fined as deflection of the loadmeter needle equal to or less than a 025 load change approximate ly 3 amperes for airplanes with a 13 5 ampere hour battery A load change of 025 or 050 is barely perceptible The system may be checked in the airpiane with either en gine running After the engine is started turn the applicable generator ON After a time delay of approximately 6 seconds provided the battery is sufficiently discharged and will accept a charge the amber caution light BATTERY CHARGE located on the instrument panel should illuminate The light should remain illuminated until the battery is recharged Un der normal circumstances the battery should be recharged and the light should go out within 5 minutes However if the battery has had unusually low or high drain the recharge t
167. b systems are identified by the second element of a standard num bering system The number 40 of the number 28 40 00 is for the indicating portion of the fuel system Unit Subject The individual units within a sub system may be identified by the third element of the standard numbering system such as 28 40 01 This number is assigned by the manufacturer and may or may not be used and will vary in usage APPLICATION Any publication conforming to the ATA format will use the same basic numbering system Thus whether the manual be a BEECHCRAFT Duke 60 Maintenance Manual or Wiring Diagram Manual for a Beech Duke 60 the person wishing information conceming the indicating portion of the fuel system would refer to the Tab System Chapter 28 Fuel The table of contents in the front of the chapter will provide a list of sub systems covered in the chapter For example 28 00 General 28 10 Storage Tanks cells necks caps instruments etc 28 20 Distribution Fuel tines pumps valves controls etc 28 30 Dump If in flight durnping system is installed it would appear here 28 40 Indicating Quantity temperature pressure etc does not include engine fuel flow or pressure Carrying this example further Fuel indication Left Indicator Panel could be assigned the number 28 41 01 The table of contents in front of each chapter will list the items covered and the numbers assigned All publications will use the s
168. be free of pits holes or irregularities which may reduce radar transmissivity and range If glass laminate fibers are exposed hot resin wipe should be applied to seal the laminate and followed with a light sanding with No 400 sandpaper to remove the glaze Do not repair with Devcon body putty or any other plastics which have a different expansion coefficient than the original resin Apply three thin cross coats of white elastromeric polyurethane product of Hughson Chemical Co Erie Penn consisting of CD 857 40A two parts by volume and CD 857 40B one part by volume to the forward 15 to 17 inches of the nose cone The accelerator and base are available in the kit form P N CD857 40 1 1 2 pint through the BEECHCRAFT Dealer Organization Allow one hour drying time between coats and 48 hours drying time before applica tion of urethane topcoat SURFACES SUSCEPTIBLE TO MUD AND SPRAY Apply one coat of white epoxy paint to the following areas 1 Main and nose landing gear wheel wells 2 Interior surface of landing gear doors 3 Main and nose landing gear assemblies RUBBER SEALS Apply one coat of a thoroughly dissolved solution of one part Oakite No 6 and two parts water to all rubber surfaces that are to come into contact with metal or other rubber surfaces Apply a thin coat of Dow Corning No 7 after the finish top coat is dry ENCLOSED AREAS SUBJECT TO HIGH HUMIDITY Steel aluminum or magnesium parts and assemblies which
169. be used A suggested inspection procedure follows a Remove all power from the aircraft b Open the four 50 ampere bus feeder circuit breakers labeled ELECTRICAL POWER on the right circuit breaker subpanel c Turn the battery and or auxiliary ground power unit ON d Confirm the continuity of each dual bus feeder diode This may be accomplished by closing a single ELECTRICAL POWER feeder diode circuit breaker and confirming the presence of voltage on the corresponding dual bus loop The presence of voltage may be determined by the operation of circuits which receive power from the dual bus loop Refer to the Power Distribution Schematic Figure 202 or to the applicable wiring diagram for the appropriate aircraft serial in the Wiring Diagram Manual 60 590001 29 to determine which circuits receive power from each dual bus loop Repeat for each circuit breaker e Confirm that each dual bus is not shorted This may be accomplished by closing a single ELECTRICAL POWER feeder circuit breaker and determining that no voitage is present at the load side of each of the three remaining ELECTRICAL POWER feeder circuit breakers Repeat for each circuit breaker Should any diode prove to be either shorted or open this diode must be replaced and the inspection repeated After completion of the inspection reset all circuit breakers and tighten all connections securely Ensure that all wires and terminals are not chafing against the aircraft struc
170. bleed off from the condenser Cycling back through the compressor 21 00 00 Page 1 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NOTE Beginning with airplane serials P 123 P 127 and after and prior airplanes having installed Kit Number 60 5006 the hot gas bypass valve line and suction accumulator were removed from the system overpressure switch a pressure relief valve are incorporated into the system to regulate system compressor discharge pressure The overpressure switch is located in the condenser compartment of the right nacelle and is set to actuate at 375 10 psi When this switch is actuated power is removed from the compressor magnetic clutch and the 3 amp fuse is shorted through a resistor to the airplane structure The fuse is thus opened preventing further operation of the compressor magnetic clutch and the compressor until the system has been serviced A pressure relief valve located on the compressor discharge line immediately before it enters the condenser is set to bleed off pressure at 450 psi On airplane serials P 275 and after and on those prior airplanes which are in compliance with the Service Instructions 0599 427 a low pressure switch is installed on the evaporator This switch is designed to actuate when the refrigerant pressure drops to 7 1 psi The actuation of the low pressure switch shorts the 3 ampere fuse to airplane structure through the resistor located ne
171. bristle brush BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CAUTION Never use a wire brush or brush with a metal construction for this purpose as short circuiting or other damage may result c Scrub the batteries with a solution of ammonia or bicarbonate of soda one part of soda to a gallon of water This will neutralize any electrolyte sprayed or spilled out CAUTION Entrance of ammonia or soda solution into a battery cell will neutralize the cell electrolyte Never use solvents to clean the batteries for these may damage the battery case d Rinse the batteries with clear water then sponge off the excess water Allow the batteries to air dry e Wash the battery filler caps with ciean hot water and no soap then examine the vent holes in the battery filler caps to make sure they are clear f Inspect the battery for cracks holes or burn spots Replace if necessary g Make sure that all batteries hardware is clean and in good mechanical condition NOTE If additional cleaning of the battery terminals and cable terminal is required use a wire brush and brighten up the terminals to ensure a good elec trical connection BATTERY BOX CLEANING The battery box is vented overboard to dispose of electrolyte and hydrogen gas fumes discharged during normal charging operation To ensure the disposal of these fumes the vent hose connections at the battery box should be checked fre quently for obstructions The battery
172. c that have bulges splits bends or cracks Check con trol cables pulleys and associated equipment for con dition attachment alignment clearance and proper operation Replace cables that have broken strands or evidence of corrosion Check cables for proper tension at the first inspection and every 100 hours thereafter CONTROL SURFACES Check for deformation cracks and security Check for loose or missing rivets Check for freedom of movement and travel limits Check for securi ty of hinges and bond cable STRUCTURE Check for cracks deformation and concealed damage TRIM TABS AND ACTUATORS Check for security and wear Check allowable free play as outlined in Chapter 27 20 00 and 27 30 00 Check hinges and trim tab actuator for security and wear Check trim tabs for cracks and control rods for attachment Lubricate the trim tab hinges as outlined in Chapter 12 20 00 5 20 00 Page 218 Nov 20 87 i Alt BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL G REAR FUSELAGE AND EMPENNAGE Cont d MECH INSP 7 RUDDER TORQUE TUBE 4 thru P 533 of S I 1115 has not been complied with Inspect the rudder torque tube for possible elongated taper pin holes and corrosion as out lined in BEECHCRAFT Service Instructions No 1115 8 STATIC PORTS Check for obstruction and clean as neces sary PLUMBING Check for leakage cracks chafing condition and security ELECTRICAL WIRING
173. ccumulator were removed from the system An overpressure switch and a pressure relief valve are incorporated into the system to regulate system compressor discharge pressure The overpressure switch is located in the condenser compartment of the right nacelle and is set to actuate at 375 10 psi When this switch is actuated power is removed from the compressor magnetic clutch and the 3 amp fuse is shorted through a resistor to ground A pressure relief valve located on the compressor discharge line immediately before it enters the condenser is set to bleed off pressure at 450 psi On airplane serials P 275 and after and on those prior airplanes which have complied with Service Instructions 0599 427 a low pressure switch is installed on the evaporator This switch is designed to actuate when the refrigerant pressure drops to 7 1 psi The actuation of the low pressure switch shorts the 3 ampere fuse to the airplane structure through the resistor located near the evaporator The fuse located in the right nacelle is thus opened preventing further operation of the compressor magnetic clutch and the compressor until the air conditioner system has been serviced NOTE The low pressure switch which was originally installed on airplane serials P 275 through P 292 and P 294 prior to compliance with Service Instructions 0599 427 actuated at a pressure of 18 2 psi END 21 50 00 Page 1 May 30 75 BEECHCRAFT DUKE 60 SER
174. ce Let the clutch cool for approximately one minute before reattaching the lead for another fifteen second interval Repeat the foregoing sequence until the clutch will hold 30 inch pounds of torque as indicated in step a then blow the clutch and housing clean with compressed air CAUTION Exceeding the fifteen second bum in periods may overheat and damage the magnetic clutch CHECKING ELEVATOR TAB FREE PLAY Visually inspect the elevator tabs for damage security of hinge attach points and for tightness of the actuating system inconsistancies should be corrected prior to checking the free play of the tabs The elevator tab free play check should be performed at least once a year to ensure that the trim tab free play falls within the prescribed limits A check fixture P N 45 135030 9 810 or the equivalent as shown in Figure 203 a dial indicator and a push pull scale for applying accurate loading to the tab is required for making the inspection for free play of the tab a Securely lock the control surfaces to prevent movement of the elevators Set the elevator tabs in the neutral position gt b Using shot bags affix the indicator check fixture so that the dial indicator point is positioned 2 90 inches aft of the tab hinge line and on the outboard edge of the elevator tab Apply a small piece of masking tape for paint protection 4 50 inches aft of the tab hinge line and along the centerline of the tab actu
175. ch system operates i ndependently of the other When placed in AUTO position the temperature is automaticaliy controlled through th temperature controller located on the forward pressure buikhead above the pilot pedals It also regulates the cabin temperature variations monitored at the sensing units The sensing units are located in the ram air inlet heater outlet duct and forward of the two pressure control valves on the rear pressure bulkhead When placed in the MANUAL COOL Hi position the switch bypasses the automatic controls and allows maximum air conditioning output The maximum output is limited by an evaporator thermal switch and an overpressure switch The MANUAL COOL LO position allows a hot gas bypass valve if installed to be cycled on and off by a timer The bypass valve regulates the flow of the refrigerant to the condenser allowing partial cooling of the cabin On serials P 123 P 127 and after and prior airplanes which have complied with Service Instructions 0320 426 a MANUAL COOL position replaces the MANUAL COOL HI and LO positions on the mode selector switch Two BLOWER positions are placed on the mode switch to allow the blower to be selected without cycling through the opposite mode The air scoop and ramp assembly located in the upper RH nacelle controls the air circulation through the condenser compartment and is completely automatic The air scoop and ramp assembly has three positions closed when the ai
176. ch will change the time the stall warning actuates by about 4 4 knots of indicated air speed The only way to test the accuracy of the setting is to fly the airplane into a stall noting the speed at which the warning horn comes on and the speed at which the full stall occurs The stall should be made with the flaps and gear up and power off Prior to stalling decelerate no faster than one knot per second It may be Necessary to make several alternate adjustments and test flights before the desired setting can be reached The stall warning should actuate at 5 to 7 knots ahead of the complete stall The switch setting should be checked and adjusted as necessary whenever a wing or wing leading edge is replaced or extensively repaired or if a new switch is installed The switch should require no adjustment in normal service END Ihi 27 60 00 Page 201 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GUST LOCK AND DAMPENER MAINTENANCE PRACTICES If it is necessary to park the airplane outside for extended periods install the control locks and tie down the airplane Installing control locks may be done as follows a Insert the spring end of the rudder control locking pin into the hole at the top of the pilot s left rudder pedal arm b Neutralize the pedals with the locking pin spring compressed and insert the opposite end of the locking pin into the right pedal arm The rudder pedals locking pin is placarded RUDDE
177. circuit that must be located and corrected d To extend the life of the lead strap between the hub clamp and clip reposition the bend at least 1 2 inch from the existing location of the bend e Check for damaged springs and worn or damaged brushes ELECTRIC PROPELLER 100 HOUR GUIDE DEICER a Check for radio noise or compass interference by operating the engines at near takeoff power with the radio gear turned ON If under these conditions noise or interference occurs when the deicer systems switch is turned ON and disappears when the switch is OFF refer to the troubleshooting chart for the probable source of trouble b Check all clamps clips mountings electrical connections and connectors for tightness and electrical soundness Check also for loose broken or missing safety wire c Closely check deicer boots for wrinkles loose or torn areas partic ularly around the outboard end and at the point where the strap passes under the hub clamp Look for abrasions or cuts along the leading edge of the flat or thrust face If the heater element wires are exposed in the damaged areas or if the rubber is found to be tacky swollen or deteriorated as from contact with oil or solvent fluids replace the boot d Check that the hub clamps are tight Inspect for cracks or other damage Check to see that the cushioning material is not missing or damaged in the area 5 20 00 Page 227 Nov 20 87 BEECHCRAF
178. circuit breakers and return the aircraft to normal BUS 2 1 2 FEEDER a S Dual Bus Conformity Inspection Figure 201 ELECTRICAL UTILIZATION LOAD CHART The following chart provides information pertaining to the capacity of the generator for supplying the electrical load on the aircraft while maintaining a full charge on the battery To determine the total electrical load of the aircraft add the continuous load for standard equipment to the load of the optional equipment installed in the aircraft accessories and radio Since the aircraft is equipped with two 28 volt 125 ampere generators the total load shall not exceed 80 percent of the total generating capacity When an item of equipment functions at various times in different systems the ioad per unit value listed in the chart represents the highest value required to operate that particular unit in the various systems in which it functions 2450 00 Page 201 Nov 2 73 THHESHOLD LIGHT __ _ NOSE BAGGAGE LIGHT LIMITER BATTERY CHARGE CURRENT SENSOR BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL BATTERY BATTERY SWITCH ON LEFT STAATER RELAY sl LOADMETFR D 5 REVERSE 5 FT gt GENERATOR CURRENT 20 DIODE o 4 140A 7 1 LEFT ISOLATION BUS e VOCI RESULATOM UN LEFT NACELLE a 3 D OVER VOLTAGE RELAY 32 VOC RIGHT ISOLATION BUS
179. ck for condition attachment cracked or broken lenses Check switches knobs and circuit break ers for looseness and operation 24 STALL WARNING SYSTEM Check for proper operation 5 20 00 Page 204 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL A OPERATIONAL INSPECTION Cont d MECH INSP 29 26 A18 RADIO OPERATION Check for proper operation security of switches and knobs FLAPS Check for noisy operation full travel and prop er indication PITOT HEAT Check for proper heating of the unit BRAKES Check for condition and wear ease of operation and proper release of the parking brake Check for unu sual brake chatter EMERGENCY LOCATOR TRANSMITTER Check for proper tion Tune radio to 121 5 MHz on VHF or 243 MHz on UHF then turn ELT switch to ON and monitor for signal Turn ELT switch OFF then place in ARM position OXYGEN SYSTEM Functionally check the oxygen system for proper operation Check the oxygen bottle shutoff valve for proper operation SWITCHES CIRCUIT BREAKERS Check for proper operation FLIGHT CONTROLS TRIM CONTROLS AND TRIM INDICATOR Check freedom of movement and proper operation through full travel with and without flaps extended Check electric trim controls for operation IDLE CUT OFF Check for proper operation and freedom of movement TR O 5 20 00 Page 205 Nov 20 87 BEECHCRAFT DUKE 60 SERIES M
180. cked as outlined under CHECKING COMPRESSOR OIL LEVEL 12 10 00 Page 202A Jan 9 86 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL _CHECKING COMPRESSOR OIL LEVEL Figure 202 The compressor oil level should be checked by a qualified air conditioner man at the following times a After the air conditioner has operated for the first time b At the beginning of each season s operation c When oil is emitted from the compressor during servicing operation d After the air conditioning system has been recharged Ifa component is replaced The compressor is charged with Texaco Capella E or Suniso No 5 oil 18 Chart 202 12 20 00 Only th se or equivalent oils should be used when adding oil To check the compressor oil level use the following procedure a Operate the air conditioner for approximately 15 minutes in which the last 5 minutes should be at low engine rpm 1 000 to 1 100 This allows the oil to accumulate the compressor for an accurate oil level reading b Attach service gages to compressor service valve ports With air conditioner operating slowly close the suction service valve until the suction pressure gage reads zero or slightly below d Stop the air conditioner and quickly close the suction service valve when the suction gage reads a little above zero FINGER RING NOTCHES 1 10 IN APART e Close the discharge service valve f With both service valves closed the s
181. coarse paper so that the finish will be perfectly smooth Take care to avoid removing any more metal then is absolutely necessary e Wash the sanded area with a solvent such as naphtha or toluol Change the wash cloths used for this purpose frequently so that all the sanding dust will be picked up f After the area to be touched up has been cleaned with solvent until all trace of discoloration is gone apply a thin coat of pretreatment primer to the damaged area g Spray two or three coats of the zinc chromate primer for a heavier than normal build up h After the primer has dried sand the area being repaired with a medium fine sandpaper Sand the edge of the repair area until the indentation where the metal and the old paint meet is gone If it is necessary apply additional primer until the junction of the paint and metat is no longer visible i Spray on two thin topcoats of finish paint URETHANE PAINT The need for an extremely hard finish for protection against sandblast during takeoff and landings led to the development of urethane coatings for airplanes Urethane paint dries into a high gloss and retains color much better than standard fin ishes It is unaffected by the chemicals in hydraulic fluids deicer fluids and fuels and requires less care and mainte nance than other finishes URETHANE PAINT REPAIR PROCEDURES NOTE The time normally required for urethane paint to cure must be extended at temperature
182. contro wheels should be in neutral position SECURE CHAIN TO SPROCKET WITH 4 TURNS OF MS20995 C32 LOCKWIRE AS SHOWN POINT AT WHICH DEFLECTION MEASUREMENT IS TO BE MADE ADJUST TURN BUCKLES TO OBTAIN A 25 05 INCH LATERAL DEFLECT ION WITH A LOAD OF 2 5 POUNDS APPLIED AT A POINT 4 TO 5 INCHES LEFT LINE 60 155 1 Control Column Bus Cable Adjustment Figure 202 END 27 00 00 Page 202 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL left side of the pedestal Remove the forward left passenger seat and the floorboard d Remove the necessary access plates to gain access to the trim tab cables the actuator and the cable puliey brackets e Remove the cable retaining pins at the pulley brackets f Disconnect the tab cables at the turnbuckles in the left wing Identify and connect lead lines on the cable ends g Remove the cable stops and the pressure seals h Remove the outboard cable from the actuator sprocket Remove the cable through the actuator access opening i Remove one chain link at the sprocket on the pedestal Remove the cable through the pilot s compartment AILERON TRIM TAB CABLE INSTALLATION a Position the chain of the forward tab cable around the pedestal sprocket and install the chain link b Route the cable ends aft in the fuselage and outboard into the left wing c Position the chain of the outboard cable around the actuator sprocket and rout
183. ct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 23 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 23 EFFECTIVITY CONTENTS 1 Jun 13 84 23 60 00 1 Jun 13 84 7201 Jun 13 84 202 Jun 13 84 CHAPTER 23 COMMUNICATIONS TABLE OF CONTENTS CHAPTER li SECTION SUBJECT SUBJECT PAGE STATIC DISCHARGING 23 60 00 Description and Operation 1 Maintenance Practices 201 Static Wick Removal Prior to P 581 201 Static Wick installation Prior to P 581 201 Static Wick Removal P 581 and after 201 Static Wick Installation P 581 and after 201 END 23 EFFECTIVITY CONTENTS Page 1 A15 Jun 13 84 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL STATIC DISCHARGING DESCRIPTION AND OPERATION A static electrical charge may build up in the surface of the airplane while it is in flight This electrical charge if retained can cause interference in radio and avionics equipment operation is also dangerous to personnel disembarking after landing and to personnel servicing the airplane Therefore static wicks are installed on the trailing edges of the flight surfaces and wing tips to aid in the dissipation of the electrical charge Prior to serial P 581 two static wicks are installed on each wing tip two on each elevator and two on the rudder At serial P 581 and after three static wicks are installed on each wing tip three on each elevator and three on the rudder END 15 23 6
184. d check adjacent structure Check for indications of hard landing or excessive flight loading 2 STRUCTURE Check for cracks deformation and concealed damage Check for loose or missing rivets 3 ACCESS DOORS AND PANELS Inspect for cracks proper fit and attachment 4 CABLES PULLEYS AND TURNBUCKLES Check the wing flight control components cables and pulleys Replace control system components push rods turnbuckles end fittings castings etc that have bulges splits bends or cracks Check control cables pulleys and associated equipment for condition attachment alignment clear ance and proper operation Replace cables that have broken strands or evidence of corrosion Check cables for proper tension at the first inspection and every 100 hours thereafter 5 20 00 Page 211 18 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL D WINGS AND CARRY THROUGH STRUCTURE Cont d MECH AILERONS Check for condition and security Check for cracks loose or missing rivets and freedom of movement Check hinge bearings and brackets for condition push pull rods for security and rod ends for corrosion AILERON TRIM TAB Check for attachment and freedom of movement Check free play as outlined under the heading CHECKING AILERON TAB FREE PLAY IN Chapter 27 00 00 FUEL CELLS AND VENTS Inspect fuel cells for leakage and vent lines for security as outlined in Chapter 28 10 00
185. d can be neutralized afterwards by rinsing the affected area with water CAUTION Urethane strippers usually contain acids that irri tate or burn the skin Wear rubber gloves and eye protection when using the stripper c Rinse the area with water and dry d Wash the stripped area carefully with a solvent such as methy ethy ketone or lacquer thinner This will Prevefit tiny particles of loose paint from adhering to the stripped area e Using a nylon scratch pad or aluminum wool dip ped in water clean the surface with a cleanser such as Bon Ami Ajax Comet cleaner etc A good scouring will leave the surface completely clean f Thoroughly rinse with clean water and carefully dry the affected area if the stripped area includes several joints or skin laps let the airplane sit unti all moisture has dried This may be accelerated by blowing the skin laps and seams with compressed air Wet masking should be replaced PRETREATMENT WASH PRIMER FOR URETHANE PAINT An acid etching primer that conforms to MIL C 8514 should be applied to improve adhesion of the finishing coats EX2016G base and T6070 catalyst products of Enmar Paint Company Wichita Kansas are used in equal parts as a pretreatment wash primer at the factory a Mix the primer in accordance with the manufactur ers instructions b Apply a thin coat of primer it should be permitted to dry for at least an hour but not over six hours before the next coat of ur
186. d sprocket in the lower pedestal with the chain and sprocket teeth engaged and install the attaching bolt Route the forward cable aft to the LH trim cabie pulley located in the lower fuselage area Route the aft cable aft to the RH trim cabie pulley located in the lower fuselage area NOTE When the trim tab control cable is disconnected at the pedestal the tab wheel shall turn smoothly with very little resistance Bearings not previously lubricated may be lubricated with MIL L 6086 oil 7 Chart 207 91 00 00 Lubricate shafts and thrust surfaces with MIL G 23827 grease 11 Chart 207 91 00 00 for friction reduction With the elevator tab in neutral position the aft cable and chain assembly on the trim tab actuator sprocket So that the ends cf the chain are equidistant at the sprocket centerline within 20 inch d Route the chain and cable assembly inboard and forward the aft fuselage instali all cable retaining pins in the pulley brackets 27 30 00 Page 204 Sep 20 85 f Using 680 solvent 15 Chart 207 91 00 00 clean the cables for the length of trave through the pressure seals Lubricate to one inch beyond the cleaned area with MiL G 23827 grease 11 Chart 207 91 00 00 g Fill the pressure seals with MIL G 23827 grease 11 Chart 207 91 00 00 Install the seals h Install the cable stops and connect the cables to the turnbuckles in the aft fuselage Rig the elevator trim tab control
187. d the surface rewaxed JEXTERIOR AND INTERIOR FINISHES NOTE Any time an airplane is repainted or touched up inspect all placards to ensure that they are not Covered with paint are legible and are securely attached following list is included to be used as refere should it become necessary to touch up or match an inte or exterior paint Each paint is listed according to spe type and whether an exterior or interior paint EXTERIOR AND INTERIOR PRIMERS Anterior Aluminum MIL P 8585 anterior Magnesium Enmar EX1479 Exterior Aluminum Enmar EX2016G or MIL P 8585 Exterior Magnesium Enmar Epoxy Primer Urethane Acid Etch Wash Enmar EX2016G Ba Exterior Surface Enmar T6070 Cataly Urethane Intermediate Coat U S Paint 6165 Ba Exterior Surface U S Paint AA 92 C Catalyst ENAMEL Exterior Colors Pacific Blue Morning Glory Blue Blueberry Biue Surf Green Shamrock Green Turquoise San Mateo Wheat Lemon Yellow Saturn Gold Castle Tan Beaver Brown Flamingo Huntsman Red Toreador Red Chianti Red Matterhorn White Biack Champagne Gold Jubilee Gold Sable Brown Sunshine Yellow Capri Blue Omaha Orange Kingston Gray Peacock Turquoise Terrace Blue Sahara Tan Prairie Beige Antique Gold Beachwood Embassy Red Marlin Blue Bahama Blue Pavonne Blue Matador Red Sunburst Yellow Jade Mist Green Astro Biue URETHANE Exterior Golors Jubilee Gold Morning Glory Blue Blueberry Blue
188. differential pressure shall not exceed 4 6 1 psi as observed on the CABIN PRESSURE indicator 9 Pressurize the cabin to a differential pressure of 4 00 50 Allow five minutes for the cabin pressure to stabilize After stabilization is established check the cabin for excessive leakage A 38 cubic feet per minute leakage is permissible f the leakage is indicated at more than 38 cubic feet per minute isolate the cause and repair as described in the following paragraphs 1 Check all connections to the pressure vessel test unit and the T and or Y fittings in the test hoses to ensure that no leaks exist Repair all leaks anu repeat steps f through g 2 If leaks through the outflow or safety valves are suspected a slight adjustment of the outflow and safety valve mounting screws may reduce the leakage rate considerably If the outflow and or safety valves determined to be defective replace as necessary Perform the leak test described in steps f through g 3 Check around the windows for iud remove and replace windows found to be defective NOTE Ensure that the test unit is working properly and all gages are accurate 4 Gain access to the points where the contrc cables electrical wire bundles plumbing and landing gea BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL retract rods enter the pressure vessel by removing the seats floorboards and upholstery Fill the control cable pressure seals
189. e 3 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL airplane arrives at the cruise altitude This can be accomplished by increasing or decreasing the rate rheostat knob A few seconds lag time must be allowed for the pressurization controls to respond and stabilize before reading the cabin altitude rate of climb indicator The controller will automatically turn off when the window in the red selector ring reaches the 12 o ciock position However the directional switch should be placed in the OFF position CAUTION In the event the directional toggle switch is positioned improperiy the controller will drive to the end of the scale and damage to the slip clutch may result For normal descent turn the red selector ring until the window is opposite the altitude which is 1 000 feet above the landing altitude After departing the original aititude place the directional toggle switch in the down position In the event that a rapid descent rate is required set the rate rheostat for an increased rate of descent so as to maintain higher airplane altitude than cabin altitude throughout the descent if the cruise altitude selected is less than 11 000 feet or corresponding cabin altitude below the window is 1655 than the take off field elevation then the controller need not be moved However if the landing altitude is less than the take off field elevation then the controller can be driven down to the selected cruise altitude
190. e plate d Install the access door on the lower LH fuselage e Reinstall the upholstery panel DIFFERENTIAL CONTROL VALVE AND SAFETY VALVE ADJUSTMENT NOTE Check the differential control valve and safety valve for adjustment every 300 hours or annually The differential control valve and safety valve adjustments may be made in accordance with PRESSURIZATION SYSTEM ADJUSTMENT PROCEDURES For information relating to overhaul and cleaning procedures refer to Component Maintenance Manual P N 60 590001 27 PRESSURIZATION SYSTEM ADJUSTMENT PROCEDURES a Remove the middle upholstery panels from the aft pressure bulkhead to provide access to the differential contro valve and safety valve b Open the bleed control valve 1 1 4 turns counterclockwise Preset the cabin altitude controller to the nearest index mark above field altitude Minimum of 1 000 feet d Adjust the dashpot spring to position the diaphragm approximately 0 45 inch from valve mounting face surface e Check ram air door for resistance to opening by 21 30 00 Page 201 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL pushing with a long stiff rod with pressurization switch in pressurization mode and power on f Cabin bleed off rate at 4 6 psi should not exceed 6 000 fpm Required only if excessive leak rate is suspected g Execute a normal take off and record maximum cabin descent which occurs approximately 20 seconds after lift off
191. e shorting strap has been removed for even a short period of time must be considered in an unknown state of charge condition and must be completely discharged prior to charging and installation b Inspect batteries shipped from the factory for ship ping plugs in the vent holes of each of the battery cells The biunt aluminum screws that serve as shipping plugs must be removed prior to operation of the battery The Bunson vaives included with the battery in a separate plastic bag should then be screwed into the vent cap assembly in place of the screw plugs The Bunson valves will release excessive pres sure from gas accumulation to prevent cell rupture NOTE On batteries not equipped with the screw type plugs and Bunson valves remove the shipping plugs and clean the filler cap vent plugs as noted under CLEANING AND INSPECTION Retighten the cell vents with the vent plug wrench included with the battery c Check for a torque of 6 foot pounds on the terminal screws securing the cross links connecting the cells together d Before charging determine that ail cells are pro perly installed by making a cumulative voltage check e After determining the battery is in good physical condition and is properly assembled it should be charged as outlined under BATTERY CHARGING and the electroiyte level adjusted BATTERY INSTALLATION a Place the battery in the weil install tne battery hold down bar and the two nuts Safety wire the nu
192. e taper pins used to install the torque arms and the bob weight assembly c When installing the torque tube guide apply thread locking compound 36 Chart 207 91 00 00 t threads prior to installation CONTROL COLUMN BUS CABLE REMOVAL a Disconnect the aileron cables from the itrol column at the turnbuckles b Paint one tooth of each of the contro column sprockets and its corresponding chain link to ensure proper alignment of the contro wheels at installation Loosen the cable turnbuckle in the center of the control coiumn horizontal cross member Remove safety wire from the chains and sprockets Remove the cable and chain assembly CONTROL COLUMN BUS CABLE INSTALLATION a Instal the control column bus cable and chain assembly on the cross member of the control column with the painted links of the chains engaging the corresponding painted sprocket teeth b Rig the control column bus cable and safety wire the chain to the sprockets as shown in Figure 202 c Rig the aileron contro cable Refer to 27 10 00 CONTROL COLUMN BUS CABLE RIGGING Figure 202 Rigging of the control column bus cab e can be accomplished by adjusting the bus cable turnbuckles to Obtain a 25 05 inch deflection with a load of 2 5 pounds applied at a right angle 4 to 5 inches to the left of the aircraft center line as shown in Figure 202 NOTE When final adjustment of the bus cable is established the pilot and copilot
193. e the cable ends inboard d install the cable stops and connect the cables at the turnbuckles in the wing e Install all cable retaining pins in the pulley brackets f Using PD680 solvent 15 Chart 207 91 00 00 clean the cabies for the length of travel through the pressure Seals Lubricate to one inch beyond the cleaned area with MiL G 23827 grease 11 Chart 207 91 00 00 g Fill the pressure seals with MIL G 23827 grease 11 Chart 207 91 00 00 install the seais h Rig the aileron trim tab control system i Install all access plates in the left wing ji install the floorboard and the left forward passenger seat k install the floorboard and the pilot s seat i Install the upholstery panel on the left side of the pedestal AILERON TRIM TAB RIGGING Figure 201 a Place cockpit aileron trim tab contro in neutral position b Place aileron in neutral position and connect trim tab to tab actuator turning the sprocket on the actuator adjust the trim tab to both extremes of travel measure both settings and return the tab to the mid point of the two extremes of travel This will place the actuator in the neutral position d f the trim tab is not in the neutral position upon completion of step adjust push rod to place tab in neutral position e Center the chain on the sprocket and tighten the cable Rig cable tension and adjust travel as noted on the Aileron Tab Rigging Illustration F
194. e to modulate toward the closed position thus restricting the outflow of cabin air The outflow valve poppet valve will modulate to restrict the outflow of cabin air as required to maintain the selected altitude If the flight plan requires an airplane altitude greater than the altitude indicated on the inner scale of the visual display of selected cabin altitude the airplane cabin will be pressurized at the maximum differential pressure At this time the differential pressure across the differential pressure control diaphragm assemblies of the safety valve and the outflow valve will cause these valves to modulate open maintaining the maximum differential pressure of the airplane As the airplane continues to climb the cabin altitude will climb at the same rate of climb as the airplane climbs NOTE During a rapid rate of airplane assent if the cabin rate selector is set at a low rate the maximum differential pressure could be achieved prior to reaching the selected airplane altitude If the cabin altitude is greater than the selected cabin altitude and the airplane decends the cabin altitude will decend at the selected cabin rate until the selected cabin altitude is achieved Should there be a loss of cabin airflow from the turbochargers and the airplane decends to an altitude where the atmospheric pressure exceeds the cabin pressure a 21 30 00 Page 5 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL negative pre
195. e upholstery panels from the forward side of the aft lower pressure bulkhead making the valve accessible On airplane serials P 247 and after remove the plate which is attached by two AN4 5A bolts and sixteen AN3 5A bolts to gain access to the differentia control valve and the safety valve b Loosen and remove all necessary plumbing from the valve Cap open plumbing to keep shop soil dirt and foreign objects from entering c Remove the access door on the lower LH fuselage just aft of the rear pressure bulkhead d Station a man inside the aft fuselage to remove the six attaching bolts and remove the valve DIFFERENTIAL CONTROL VALVE AND SAFETY VALVE INSTALLATION a Station a man inside the aft fuselage to position the valve and install the six attaching bolts NOTE Tighten the attaching bolts to a torque of 15 inch pounds b Remove the caps and install all plumbing to the valves i NOTE Tighten the differential control vaive ELBOW or the safety valve TEE fitting to 50 10 inch pounds and secure with safety wire On airplane serials P 247 and after install the plate over the differential control valve and the safety valve Secure it with the two AN4 5A bolts top and bottom and sixteen AN3 5A bolts Tighten the bolts evenly to a torque of 50 to 70 inch pounds for the AN4 5A bolts and 20 to 25 inch pounds for the AN3 5A bolts WARNING The airplane must not be pressurized prior to installation of th
196. e zerk was removed e Reinstall the zerk on each blade f Clean excess grease from the propeller reinstall the grease zerk covers and safety 9 Reinstall the spinner PROPELLER SERVICING POINTS Figure 201 a Remove the access cap from the propeller spinner to expose the filler valve b Charge the dome with dry air or nitrogen to a pressure of 80 psi at 70 F Increase the pressure an addition al 2 psi for every 10 degrees of increase in temperature similarly for every 10 degrees of drop in temperature reduce the pressure by 2 psi PROPELLER ACCUMULATOR The propeller accumulators are located on the lower rear section of each engine The accumulators should be in spected every 100 hours and charged with dry air or nitrogen to 125 psi If a unit will not hold 70 of its normal charge from inspection to the next it should be replaced 12 20 00 Page 202A May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL AIR VALVE GREASE ZERK Bae ZERK E v Propeller Servicing Points Figure 201 INDUCTION AIR FILTER Wet or Dry Element The induction air filter should be cleaned every 50 hours and replaced every 500 hours of service Clean the filter as IN THIS AREA FULLY EXTENDED 3 4 APPROX APPLY GREASE LIGHTLY HERE ONLY ABSOLUTELY NO GREASE specified by the manufacturer s instructions stamped on the filter ROTON LOCKS Figure 202 Usually Roton locks will need n
197. eak detector i Unseat both the suction service valve and the discharge service valve and turn to the full aft position m Remove the service gages and install the caps on the service ports BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL The aircraft may now be returned to service EVAPORATOR AIR FILTER REPLACEMENT The evaporator air filter should normally be replaced annually Actual replacement may be required more often due to extremely dusty operating conditions a Remove the necessary equipment in the nose compartment to gain access to the floorboards forward of the pressure bulkhead b Remove the screws securing the top of the evaporator filter access plate Cut the cord securing the filter to the evaporator plumbing d Remove the old fitter e When instailing the new filter be sure the reinforced backing of the filter is placed against the evaporator coil AIR SCOOP AIR SCOOP ACTUATOR X RETRACT LIMIT SWITCH EXTEND SWITCH ON OPPOSITE SIDE AIR PRESSURE 7 RELIEF DOOR RIGGING THE AIR SCOOP Figure 202 Two limit switches control the air scoop actuator travel for the flight and ground positions The extend limit switch limits the air scoop travel from the closed position to the flight position The retract switch limits the air scoop travel from the ground position to the flight position The air scoop and limit switches may be adjusted as follows a Disconnect the air scoo
198. ear and Doors 20 Nose Gear and Doors 30 Extension and Retraction 40 Wheels and Brakes 50 Steering 60 Position and Warning 33 LIGHTS 00 General 40 Exterior 34 NAVIGATION 10 Flight Environment Data 35 OXYGEN 00 General 36 PNEUMATIC 00 General AIRFRAME SYSTEMS 33 WATER WASTE 230 Waste Disposal STRUCTURES 51 STRUCTURES 00 General INTRODUCTION Page 5 Nov 30 83 SYSTEM CHAPTER 52 53 55 56 57 PROPELLERS 61 POWER PLANT 71 73 INTRODUCTION Page 6 Nov 30 83 SUB SYSTEM SECTION DOORS 00 10 60 70 FUSELAGE 30 STABILIZERS 00 10 PROPELLERS 00 POWER PLANT 00 10 ENGINE RECIPROCATING BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TITLE General Passenger Crew Entrance Stairs Door Warning Plates Skin General Horizontal Stabilizers Elevator Vertical Stabilizer Rudder Generai Flight Compartment Cabin General Plates Skin Attach Fittings Flight Surfaces General General Cowling ENGINE FUEL AND CONTROL 30 Indicating 14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SYSTEM SUB SYSTEW CHAPTER SECTION TITLE 74 IGNITION 00 General 10 Electrical Power Supply 20 Distribution 77 00 General 79 OIL 00 General 80 STARTING 00 General 10 Cranking 81 TURBINES 00 91 CHARTS 00 Charts 14 INTRODUCTIO Page Nov 30 8 BEECHCRAFT DUKE 60 SERIES MAINTE
199. ebuilt cells d Make sure that battery hardware is clean and in good mechanical condition Wash the hardware liners case cover and other associated parts in a warm soapy solution to remove accumulated dirt and carbonate deposits Use a stiff brush to remove heavy deposits After washing rinse the parts free of soap and spread them out to dry e Remove corrosion preventive from connectors screws nuts and washers with alcohol or by degreasing f Wash vent caps thoroughly with hot water and no soap g After the parts are dry sort out damaged or heavily corroded pieces Scrap any links having burns bends or defective nickel plating If a link is tarnished at the terminal connection it should be polished with a wire 24 31 00 Page 207 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL brush It is recommended that new terminal screws and nuts be used to ensure proper electrical connection h Check the battery receptacle for burns cracks and bent or pitted terminals Defective receptacles can overheat cause arcing and decrease output voltage to result in prema ture battery failure i Scrap bent or torn battery cases and covers that are beyond repair i Replace or repair loose or damaged cover gaskets and cell holddown bars NOTE Refer to the maintenance manual of the battery manufacturer for additional details on battery dis assembly and assembly BATTERY MAINTENANCE PROGRAM P 446 and after A sy
200. ecurity cracks leaks loose or missing nuts and clamps Check for thin wall condition which may occur due to normal internal erosion on stacks which have long service time FIREWALL Check for wrinkles damage or cracks Check all electrical and control access holes for proper seal ing KOSE AND DUCTS Check all fuel oil and air hose or duct for leakage cracks deterioration and damage Check fittings for security ENGINE ACCESSORIES Check for condition security and leaks Check wiring hoses and tubes for chafing secu rity and leaks GENERATOR Check for condition attachment and chafed or loose wires ENGINE MOUNTS Check for cracks corrosion and securi ty Inspect rubber cushions mount bolts and nuts and grounding straps for condition and security PROPELLER GOVERNOR Check for leaks and control arm for security 5 20 00 Page 208 Nov 20 87 1 26 27 28 29 30 31 18 35 33 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL POWER PLANT Cont d B MECH INSP ENGINE CONTROLS Check controls and associated equip ment for condition attachment alignment and rigging Each 300 hours remove the throttle cable connection bolts and check for wear ELECTRICAL WIRING AND EQUIPMENT Inspect electrical wiring and associated equipment and accessories for fraying and attachment AIR CONDITIONER COMPRESSOR Check for security and att
201. ed for 24 hours sand the area under repair with medium fine sandpaper Sand the edge of the repair area until the indentation where the metal and old paint meet is gone If necessary apply additional urethane primer until the juncture of old paint and metal is no longer visible h Spray on two topcoats PAINTING MAGNESIUM PAINT REMOVAL FR M MAGNESIUM SURFACES a Mask around the edge of the damaged area with a double thickness of heavy paper to prevent accidental splashes of paint stripper from penetrating the masking b Apply paint stripper 42 Chart 207 91 00 00 to the skin under repair with a brush or non atomizing gun Page 206 May 12 78 CAUTION Stripping should be accomplished in a well venti lated area since prolonged exposure to high con centrates of vapor may irritate the eyes and lungs Allow the paint stripper to work for 20 to 30 minutes then work the remaining paint loose with a bristle brash CAUTION Never use a wire brush for it will damage the magnesium surface zd Remove the masking paper and wash the affected area thoroughly with water under high pressure Remove all reraanents of paint with lacquer thinner ze Sand the repaired area lightly then apply Dow No 1940 aid in the prevention of corrosion PAINTING MAGNESIUM SURFACES Prepare the surface to be repainted as indicated under PAINT REMOVAL FROM MAGNESIUM SURFACES Clean the affected area thoroughly with tacquer
202. elected positioning The mechanical adjustment selectors are located at the base of the seat backs on the inboard IN THIS AREA FULLY EXTENDED 3 4 APPROX APPLY GREASE LIGHTLY HERE ONLY ABSOLUTELY NO GREASE side The Roton of Hydrolok adjustment lever is located on the inboard side of the seat For information concerning Roton or Hydrolok servicing refer to ROTON LOCKS or HYDROLOK LOCKS in this chapter PASSENGER SEAT REMOVAL a Remove the seat stop from the middle seat track b Release the fore and aft seat adjustment lock c Slide the seat forward and off of the seat tracks PASSENGER SEAT INSTALLATION a Position the seat and slide aft onto the seat tracks b Secure the fore and aft seat adjustment lock c Install the seat stop at the forward end of the middie seat track and secure PASSENGER SEAT BACK ADJUSTMENT On airplanes P 4 thru P 510 and P 512 thru P 519 adjustment for the passenger seat backs is controlled by a mechanical three position stop or by a Roton lock for selected positioning On airplanes P 511 P 520 and after adjustment for the passenger seat backs is controlled by a mechanical three position stop or by a Hydrolok lock for selected positioning The adjustment selector for the mechanical stop is located at the base of the seat back on the inboard side The adjustment lever for the Roton or Hydrolok lock is located on the inboard side of the seat On airplanes P 511 P 520 and af
203. er operation Check gages for proper reading 14 GYRO INSTRUMENTS Check for erratic or noisy operation 15 DEICER Surface Check for proper operation and 1 ing 5 20 00 Page 203 18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL A OPERATIONAL INSPECTION Cont d INSP i NE R LM 16 IDLE RPM AND MIXTURE SETTINGS Check for both proper rpm and mixture settings Check controls for freedom of operation 17 IGNITION SWITCH Rotate the ignition switch through the OFF position to the extreme limit of switch travel if the engine stops firing the switch is normal If the engine continues to run with the switch held in the past OFF position it is an indication that one magneto is still hot or ungrounded When the switch is released from the past OFF position it shou d automatically return to normal OFF and the engine should stop running However any ignition switch exhibiting this abnormal condition should be replaced 18 HEATING AND VENTILATING SYSTEM Cneck for proper opera tion heat and airflow output Check controls for free dom of operation ae 19 PRESSURIZATION SYSTEM Check for proper operation FUEL QUANTITY AND FUEL FLOW GAGES Check for proper operation and unusual fluctuations FUEL BOOST PUMPS Check for proper operation FUEL TANK SELECTOR Check for proper operation and feel for positive detent and proper placarding ALL LIGHTS Che
204. er improperly set Decay rate improperly a Adjust as required adjusted Pitch altitude gain improperly b Adjust as required adjusted Friction in elevator or servo Check for friction and system 4 correct Decay rate too tight a Adjust as required Pitch gain too high b Adjust as required Primary pressure too high Readjust pressure as outlined in Chapter 36 Altitude gain too high a Adjust as required Decay rate improperly b Adjust as required adjusted Altitude hold solenoid a Replace solenoid inoperative 22 11 00 Page 105 Oct 27 75 TROUBLE PITCH AXIS Cont d 15 Aircraft does not return to altitude when dis placed Cont d 16 Aircraft descends or ascends continually when system engaged 22 11 00 Page 106 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING NEW MATIC AUTOPILOT Cont d PROBABLE CAUSE REMARKS Leak in altitude system b Check for leaks Altitude limiter improperly Adjust as required adjusted Servo control valve not Apply positive 6 0 volts phased correctly max to blue lead and verify nose up response EN BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL MAINTENANCE PRACTICES to the procedures described in the BEECHCRAFT New Matic Autopilot B 8 Ground and Flight Check NEW MATIC AUTOPILOT Procedures Manual P N 3957 For maintenance repair troubleshooting and testing refer EN D 22 11 00 Page 201 O
205. er it is necessary that any combination of such metals be assembled an interposing material compatible to each should be used b Install the wick using the two screws and lock washers c Refinish the surface area around the wick attachment point with the original finish or a clear laquer conforming to MIL L 6806 STATIC WICK REMOVAL P 581 and after a Unscrew the static wick from the base b Remove the static wick and lock washer STATIC WICK INSTALLATION P 581 and after The threads must be clean and free of grease oil and paint a install the static wick and lock washer b Torque the static wick to 4 7 inch pounds 23 60 00 Page 201 Jun 13 84 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL DETAIL DETAIL A DETAIL A NOTE The static wick installation shown is for airplanes prior to P 581 with static wicks installed in groups of two ten per vs airplane On later serials the static wicks are installed in the Ki same general location in groups of three fifteen airplane Detail is only for the earlier installation B60 363 2 DETAIL A Static Wicks Figure 201 END 23 60 00 Page 202 Jun 13 84 A15 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 24 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 24 EFFECTIVITY 1 May 12 78 24 CONTENTS 1 12 78 12 78 24 00 00 1 12 78 24 30 00 101 12 78 201 12 78 202
206. ervice unit to the connections the compressor The abbreviation DISCH or the letter D on the compressor cylinder head designates the discharge service valve word SUCTION or the letter 5 on the compressor cylinder designates the suction service valve When charging a completely purged system charge with 5 pounds of refrigerant After charging the sight glass should be observed for bubbles or a milky appearance caused by an insufficient refrigerant level if it is necessary to add refrigerant to a partially charged system add refrigerant slowly until a satisfactory condition is observed through the sight glass then add an additional 1 4 to 1 2 pound of refrigerant NOTE After the system has been charged the compressor oil level should be checked as outlined under CHECKING COMPRESSOR OIL LEVEL AIR CONDITIONING FUNCTIONAL TEST With the compressor running at 1 100 rpm a functional check may be made in accordance with Chart 201 Charge the system as outlined in CHARGING THE AIR CONDITIONING SYSTEM g CHECKING COMPRESSOR OIL LEVEL Figure 201 The compressor oil level should be checked by a qualified air conditioner man at the following times a After the air conditioner has operated for the first time b At the beginning of each season s operation c When oil is emitted from the compressor during servicing operation E d After the air conditioning system has been recharged e If a component
207. ery service life or when in use for one cumulative hour or after in advertant activa tion of unknown duration As Required As Required Every 100 hrs 12 20 00 Page 213 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 LUBRICATION SCHEDULE NOTE Apply MIL G 81322 lubricating grease at all points of friction in the cabin door except where Oilite bearings are installed The time interval for lubrication is as required Precaution should be taken when using MIL G 23827 and MIL G 81322 since these greases contain chemicals harmful to painted surfaces Flaps track rollers pre lubed sealed bearings Pressure lubricate at 1000 hours inspection using MIL G 23827 lubricating grease MIL G 23827 grease is recommended for use in lubricating the blade bearings in the Hartzell Propeller This grease will insure against a possible freeze up of the pitch change mechanism when prolonged flights Jhade 41 altitudes where the ambient temperature is below 20 C Lubricate at 100 hours inspection 6 Indicates the number of points to be lubricated 12 20 00 Page 214 May 30 75 A60 604 7B BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 204 Cont d LUBRICATION SCHEDULE INDEX LOCATION LUBRICANT INTERVAL CONTROL COLUMN DETAIL A Control column chain 3 SAE 20 100 hrs DETAIL A INDEX LOCATION LUBRICANT INTERVAL RUDDER PEDALS DETAIL 8 Pedals linkage 6 SAE 20 100 hrs
208. es long in the upper level point nutplate c Attach a cord and plumb bob to the outboard end of the screw installed in step b d Inflate or deflate the nose gear shock strut as necessary to pass the cord through the center of a second level point directly below NOTE Suspending the plumb bob in a can of light engine oil will assist in stabilizing it Lateral leveling is accomplished by placing a bubble level on the rear spar and deflating the tire or shock strut on the high side of the aircraft to center the bubble 8 00 00 201 Nov 2 73 CHAPTER SECTION SUBJECT 9 EFFECTIVITY CONTENTS 9 00 00 SUBJECT GENERAL Maintenance Practices BEECHCRAFT DUKE 60 SERIES _ MAINTENANCE MANUAL CHAPTER 9 LIST OF PAGE EFFECTIVITY PAGE 201 CHAPTER 9 TOWING AND TAXIING TABLE OF CONTENTS END CHAPTER SECTION SUBJECT 9 00 00 DATE Nov 2 73 Nov 2 73 PAGE 201 201 9 EFFECTIVITY CONTENTS Page 1 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL MAINTENANCE PRACTICES placarded on the nose gear to prevent damage to the gear Attach the hand towbar to the tow lug on the nose gear lower torque knee CAUTION Do not push on propeller or control surfaces CAUTION Do not piace your weight on the horizontal stabilizers to raise the nose wheel off the When towing with a tug observe turn limits as ground s EN D Page 201 Nov 2 73 BEECHCR
209. essure is relieved by unscrewing the plug for 5 full turns and bled to zero pressure h Remove the oil plug and O ring i To place the crank throw in the best position for dip stick insertion point the keyway on the compressor shaft up toward the cylinder head j Insert an dipstick until the end contacts the bottom of the Remove and measure the oil depth NOTE A compressor oil level depth of 1 5 to 1 8 inches is satisfactory 1f the oil level is below 1 5 inches add oil 18 Chart 207 91 00 00 then remeasure 21 50 00 Page 202 Nov 2 73 Dip Stick to Depth in be Added Oz CHART 202 CHECKING COMPRESSOR OIL LEVEL Oil should be removed when depths greater than 1 8 inch are observed Compressor oi level reduces 4 to 7 inches during operation at maximum rpm and also drops slightly with reduced evaporator loads Approximately 7 2 of oil is required to initially wet the system and circulate with the refrigerant When an evaporator or condenser coil is changed add approximately 2 oz of oil on installation then check and adjust the oi level as recommended locally manufactured dip stick see Figure 201 may be fabricated from 1 8 inch diameter rod a nonferrous material which is not subject to corrosion is preferred Notches cut 1 10 inch apart will aid in visually detecting oil depth k install the oil plug and O ring and check for leaks using a flameless l
210. etention Allen screws and slide the control head off the bellows shaft without turning the shaft NOTE Do not loosen the slot head screw in the knob on the control head b Rotate the control head until the altitude in the 12 o clock position the selection knob is the same as the actual cabin altitude as indicated on the cabin altimeter c Align the guide pin and slide the control head back on the bellows shaft without turning the shaft CAUTION Incorrect positioning of the control head on the bellows shaft may cause improper travel clearances and result in damage to the slip clutch d Tighten the Allen screws to secure the contro head on the bellows shaft For proper information relating to overhaul and cleaning procedures refer to Component Maintenance Manual P N 60 590001 27 PRESSURIZATION TEST PROCEDURE Refer to 1 a and 1 b under TROUBLESHOOTING PRESSURIZATION SYSTEM This test provides a means of isolating the cabin altitude control to determine if it or the differential control valve is defective when the system cannot be properly pressurized a Remove the upholstery panels providing access to the differential control valve at the aft pressure bulkhead b Disconnect the cabin altitude control sense line from the differential control valve c Pull the pressurization control circuit breaker d Start both engines and VERY SLOWLY increase power to a minimum of 20 in Hg manifold pressure c
211. ethane paint is applied URETHANE PRIMER a Mix two parts of the 6165 primer base to one part AA 92 C 4A catalyst products of U S Paint Company Wichita Kansas for intermediate primer NOTE For the best results these directions must be followed carefully for some manufacturers re quire that the primer be allowed to set for 1 2 hour after the catalyst and base have been mix ed while others recommend immediate use after mixing b Apply a coat of urethane primer with a spray gun using 35 to 40 psi of air pressure A dappled appearance indicates that the coat is thin c The primer shouid be permitted to dry approxi mately two hours at a temperature of 85 to 90 F at low humidity When the primer can not be scratched with a finger nail or will not ballup with sandpapering it is ready for the topcoat application d ifthe initial primer coat is allowed to cure for more than 24 hours before the topcoat is applied sand the primer coat slightly to roughen the surface and ensure adhesion Wipe off the sanding dust with a cloth dampened with a solvent such as lacquer thinner then apply the topcoat URETHANE TOPCOAT APPLICATION a the paint and catalyst as directed by the manu facturer b Apply the topcoat with a spray gun at 35 to 45 psi of air pressure Two coats are normaily required to fully conceal the primer and build up the topcoat film for adequate service life and beauty The urethane finish will normally
212. etract motor Retract motor brushes Shimmy damper Wheels and tires Brake assembly Brake lining Master cylinder Shuttle valve assembly Parking brake valve A11 hose POWER PLANT Engine Engine controls Engine vibration isolator mounts Exhaust system 5 10 00 Page 202 Nov 20 87 Every 2000 hours Every 4000 hours or on condi tion Every 2000 hours Every 500 hours or on condition Every 2000 hours or 3 years On On On On On On On Every condition condition condition condition condition condition condition 1600 hours for engines with serial numbers L 804 59 and up and remanu factured engines shipped after March 1 1976 and remanufactured over hauled engines which incor porate improved cylinder assemblies as described in the latest edition of Aven Lycoming Service Bulletin No 334 every 1200 hours for all other engines On condition On condition On Condition BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE Cont d ITEM POWER PLANT Cont d Turbocharger and waste gate 011 cooler Propeller Hartzell Propeller controls Propeller governor Dry air pressure pump Propeller Accumulator Hoses carrying flammable liquids All other hoses FUEL SYSTEM Fuel cells Nacelle fuel quantity transmitter Wing fuel quantity transmitter Fuel cell drain valve Fuel system check valves Fue selector valve Fuel boost
213. flows d Cycle the strut fuli extension to compressed and refill Repeat until fluid can not be added to the strut in the compressed position NOTE Cycling of shock strut is necessary to expel any trapped air within the strut housing ze Install the air valve assembly f Withthe airplane resting on the ground and the fuel celis full inflate the nose gear strut until 4 1 16 to 4 5 16 inches of the piston is exposed and inflate the gear strut until 3 inches of pistion is exposed Rock the airplane gently to prevent possible binding of the pistion in the barrel while infating NOTE is recommended that the nose strut inflation dimension and the tire inflation pressure be carefully adheared to Properly inflated tires and struts reduce the possibility of ground damage occurring to the propellers Exercise caution when taxiing over rough surfaces g shock strut pistion must be clean Remove foreign material by wiping the strut with a cloth dampened in hydraulic fluid PROPELLER BLADE BEARING LUBRICATIO Figure 201 a Remove the propeller spinner b Remove the safety wire and covers from the six zerks See Figure 201 for location c Remove one zerk from each blade d Lubricate the blade bearings with Hartzell DG Grease by placing the grease gun fitting on the remaining BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL zerk of each blade Fill until the grease is visible in the hole where the opposit
214. g bus provided the charging equipment has the proper current producing capability c Do not charge batteries in parallel using the constant current method d Do not charge individua cells unless the plastic case is supported on each side A special frarne may be built to fit the cell or two boards or plates may be placed on each side of the cell and held together by a C clamp The sides of the cell must be kept flat during charging e Perform necessary inspection cleaning and repairs before charging f Do not energize charging equipment until after the battery has been connected to the charging circuit g When charging a battery in the shop a thermometer should be placed so that the buib is below and between the top of the cells Do not place on charge any battery that has a temperature of 100 F or higher h The foam sometimes seen in cells during charging does not indicate a defect Foarning usually occurs after water is added and will disappear after a few cycles of operation The various charging procedures for the nickel cadmium battery are outlined in the following paragraphs CONSTANT CURRENT CHARGING CAUTION Monitor the battery closely during charging especially during the latter stages to prevent an overcharge that wil heat up and damage or destroy the battery AIRCRAFT BATTERY INSTALLATION CHECKLIST INSPECT FOR VISIBLE DAMAGE REMOVE SHIPPING HARDWARE ENSURE THAT ALL CONNECTORS ARE PROPERLY TIGHTENED
215. g is free of foreign material f install one screen the housing of the fitter assembly Instail the copper ribbon in the filter assembly housing Do not over compress the ribbon Install the remaining screen and secure the filter in the housing using the retaining ring g Install the filter assembly in the safety valve using the packing removed with the filter assembly Tighten to a torque of 15 to 20 inch pounds h Reinstall the plate over the outflow and safety valves Secure it with the two AN4 5A bolts at top and bottom and the sixteen AN3 5A bolts around the perimeter of the plate Tighten the bolts evenly to a torque of 50 to 70 inch pounds for the AN4 5A bolts and 20 to 25 inch pounds for the AN3 5A bolts WARNING The airplane must not be pressurized prior to installation of the plate i Reinstall the upholstery panel FUNCTIONAL TEST OUTFLOW VALVE AND SAFETY VALVE P 308 and after OUTFLOW VALVE FLIGHT CHECK Ttie following check must be accomplished with the airplane in flight a if the cabin pressure can be controlled at 1 2 psid pounds per square inch differential less than maximum differential of 4 6 1 psi the outflow valve is operating satisfactorily b If the cabin pressure goes to maximum differential and cannot be controlled at 1 2 psid below maximum differential the outflow valve must be replaced outflow valve is removed and installed as described in this Chapter under the headi
216. ge rate cf a vented nickel cad mium battery cell is in the order of C 1000 when fully charged C in this formula represents capacity in ampere hours This is about 13 5 ma for 13 5 ampere hour batteries The only pertinent measure of external leakage is the rate of discharge caused by the leakage The rate is significant only when it approaches the rate of internal leakage Therefore external leakage need be considered excessive oniy when an ammeter shorting the battery positive os negative terminal to the battery case indicates 13 5 ma or more on 13 5 ampere hour batteries Any current less than the preceding limits indicates a magnitude of leakage that has a negligible effect on battery performance Perform the following test to determine if external leakage is sufficient to necessitate cleaning the battery Set the range selector of a multi range ammeter to the 500 ma scale or higher a low cost meter is recommended to preclude possible damage to an expensive precision meter Connect the positive terminal of the ammeter to the positive battery terminal and the negative ammeter terminal to the battery case Decrease the ammeter current range to obtain a readable value of current and record the value Perform the same measurement at the negative battery terminal by connecting it to the negative terminal of the ammeter and connecting the positive terminal of the ammeter to the battery case if the current reading at either terminal is more
217. gle rate constant current charging voltage A battery is charged at the START rate until the battery temperature takes a sharp rise or until the terminal voltage while battery is charging reaches 29 5 volts for a 24 volt 19 cell battery When the 29 5 volt point is reached or the temperature takes a sharp rise the charging current is reduced to the FINISH rate and continued unti one third of the initial charge in ampere hours is added When the voltage rises to 29 5 volts the charge received by the battery is approximately equal to that removed when it was previously discharged The addition of ampere hours at the FINISH rate equal to one third of the ampere hour input at the START rate will usually ensure that the battery is fully charged NICKEL CADMIUM 19 CELL 34 AH 200 AIRCRAFT BATTERY CONSTANT POTENTIAL CHARGE AT 28 5 i 180 VOLTS ROOM TEMPERATURE 160 FULLY DISCHARGED BATTERY 140 120 ul ac a 100 t a lt 80 60 40 20 0 2 4 6 8 10 1 2 3 4 5 6 TIME HOURS 90 601 231 Constant Potential Charging Figure 202 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL The time required for completing the charge at the FINISH rate may be computed by the following formula Tp lex Te 3x Ip Te Time in hours required for finishing charge lg 7 Starting charge rate in amperes Ts Time in hours of charge at the starting rate until 29 5 volts or temperature rise occurs Ip Finish rate i
218. gth The belt tension should be checked at this time and adjusted by moving the compressor up and down in its slotted mounts so that a belt tension gage placed at a point midway between the longest span will register a tension of 100 to 105 pounds After adjusting tension on a new belt be sure the belt has ample clearance on sides HEATING SYSTEM HEATER SPARK PENO Figure 203 If the spark plug appears to be in good condition except for a mild coating of oxide on the procelain and electrodes it may be cleaned and reused Cleaning is accomplished on a conventional aircraft type spark plug cleaner except that it will be necessary to use two or more adapters in order to raise the long extension of the plug far enough out of the cleaner nozzle opening to provide an effective job Plug the ceramic insert cavity at the terminal end of the plug with a piece paper or cloth to keep out any of the cleaning sand Wipe this cavity out thoroughly with a cloth wet with carbon tetrachloride If after cleaning the spark plug porcelain is white and the electrode is not eroded the sparkplug gap may be set as follows Insert a six inch scale with a sliding clip into the spark plug well until it touches the ground electrode welded inside the combustion head Withdraw the scale and note the dimension between the sliding clip and the end of the scale Place the scale against the bottom of the spark plug gasket and determine the lengt
219. h of the spark plug positive electrode The difference between the two measurements is the spark plug gap The gap should be 3 16 to 7 32 188 to 218 inches if the plug must be adjusted the ground electrode may be bent up or down by reaching through the spark plug hole with the appropriate shaped tool NOTE if the spark plug fails to clean up properly and or if the electrode is badly eroded it should be replaced BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL If a new spark plug is being installed be sure to measure the gap Do not bend the positive electrode Torque the spark plug to 28 foot pounds NOTE The spark plug can be checked visually for sparking prior to installing the plug as follows Disconnect the wire from the terminal on the heater wiring side of the terminal strip to de energize the fuel solenoid valve Connect the high voltage lead temporarily and lay the spark plug on the heater jacket WARNING Be sure to plug the spark plug hole in the heater to prevent any possibility of residual fuel blowing out and igniting Do not touch the spark plug while energized because of dangerously high voltage OXYGEN SYSTEM CAUTION persons handling and servicing oxygen systems should review proper precautions to be observed during servicing FAA Advisory Circular 43 13 1 contains the necessary information The oxygen system consists of an oxygen regulator six outlets a nose or rear mounted cy
220. h the rudder tab in neutral position the aft chain and cable assembly on the trim tab actuator sprocket so that the ends of the chain are equi distant at the sprocket centerline within 20 inch b Route the aft chain and cable assembly forward in the aft fuselage c Place the rudder trim tab control wheel in neutral position and wrap the forward cable around the reel the same number of revolutions noted during removal maintaining the cable ends equi distant d Install the attaching shaft washer and reel align the shaft with the forward universal and install the taper pin NOTE When the trim tab control cable 15 disconnected at the pedestal the tab whee shall turn smoothly with very little resistance Bearings not previously lubricated may be lubricated with MIL L 6086 lubricating oil 7 Chart 207 91 00 00 Lubricate shafts and thrust surfaces in all trim tab systems with MIL G 23827 grease 11 Chart 207 91 00 00 for friction reduction e Route the forward cable end aft and instali all cable retaining pins in the pulley brackets f Using PD680 solvent 15 Chart 207 91 00 00 clean the cables for the length of travel through the pressure seals Lubricate to one inch beyond the cleaned area with MIL G 23827 grease 11 chart 207 91 00 00 g Fill the pressure seals with MIL G 23827 grease 11 Chart 207 91 00 00 Install the seals h Install the cable stops and connect the cables to the turnbuckles i
221. he terminal strip until all tests are complete b Using the graphs in Figures 204 and 205 determine the correct resistance for the heater discharge 21 40 00 Page 204 Nov 2 73 sensing element and the outside air sensing element respectively then add these resistance values Remove wire number H73F18 from terminal 8 of the temperature contro box terminal strip Measure the resistance between the terminal on wire number 73 18 and the terminal on wire H75A18 on terminal 5 of the temperature control box terminal strip This resistance should equal the added resistance of the two sensing elements not measure the resistance of the two sensing elements If the resistance does not equal the determined amount it is defective If the resistance is correct the heater discharge sensing element is defective c Rotate the cabin temperature control to the full increase position Using the graph in Figure 204 determine the resistance for heater discharge sensing element d Disconnect wire number H77B18 from terminal 24 of the temperature control box terminal strip Measure the resistance between the terminal on wire 77818 and terminal 1 of the temperature control box terminal strip If the resistance does not equal the determined value the heater discharge sensing element is defective e With the test probes still attached as noted in step rotate the cabin temperature control to the full decrease position
222. iation Regulations Beech Aircraft Corporation has prepared this inspection guide to assist the owner or operator in meeting the foregoing responsibilities This inspection guide is not intended to be all inclusive for no such guide can replace the good judgment of a certified airframe and power plant mechanic in the performance of his duties As the one primarily responsible for the airworthiness of the airplane the owner or operator should select only qualified personnel to maintain the airplane While this guide may be used as an out line detailed information of the many systems and components in the airplane will be found in the various sections chapters of the shop maintenance manual and the pertinent vendor publica tions It is also recommended that refer ence be made to the applicable Maintenance Handbooks previously issued Service Instructions Beechcraft Service Bulle tins applicable FAA Regulations and Pub lications Vendors Bulletins and Specifications for torque values clear ances settings tolerances and other requirements It is the responsibility of the owner or operator to ensure that the airframe and power plant mechanic inspecting the airplane has access to the previously noted documents as well as to this inspection guide 5 20 00 Page 201 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL Beech Aircraft Corporation issues service Service Bulletin to his particular set o information f
223. icing precautions a Remember this is a high pressure system When disconnecting a line loosen the fittings just enough to bleed 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 Use only R 12 refrigerant 17 Chart 202 12 20 00 in this system Other refrigerants particularly those containing methyl chloride will cause rapid deterioration of the aluminum compressor components d When servicing the system with refrigerant avoid smoking or working near an open flame Refrigerant passing over an open flame will produce a highly toxic phosgene gas Hook the service unit to the connections on the 17 compressor The abbreviation DISCH or the letter D on the compressor cylinder head designates the discharge service valve The word SUCTION or the letter S on the compressor cylinder designates the suction service valve When charging a completely purged system charge with 5 pounds of refrigerant After charging the sight glass should be observed for bubbles or a milky appearance caused by an insufficient refrigerant level If it is necessary to add refrigerant to a partially charged system add refrigerant slowly until a satisfactory condition is observed through the sight glass then add an additional to pound of refrigerant NOTE After the system has been charged the compressor oil level should be che
224. ide of the battery relay and the positive side of the ammeter to the generator side of the battery relay d With the switch in the ammeter lead turned off start either engine Allow the battery to charge until the loadmeter appears to stabilize e Turn the switch in the ammeter lead on and turn the battery switch OFF in that order to prevent a current surge and possible damage to the ammeter f Note the charge current as indicated on the ammeter The charge current should decrease until the light goes out at approximately 3 or 7 amperes and may continue to decrease to a lower level Repair or replace any parts found to be defective and repeat the functional check 3 Battery is charged and is not being excessive ly overcharged If the light is on and the charge current has dropped to a satisfactory level the detector assembly is malfunctioning and should be replaced a Light is erratic or does not operate in unison with suitable charge current values as previously out lined Check the wiring and detector assembly for proper operation Repair or replace defective parts and repeat the functional check 24 32 00 Page 201 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL EXTERNAL POWER MAINTENANCE PRACTICES The aircraft electrical system is protected against damage from reverse polarity by a relay and diodes in the external power circuit The external power receptacle is located just outboard of the left
225. ight chromic acid stains f Remove excess solution with cold running water a cheesecloth pad wetted with clean water Never use a high pressure hose rinse since the freshly formed chemical film will be removed or damaged Ali treated parts should be kept clean before priming and painting which should follow the chemical film application as soon as practical END Page 208 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 21 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 21 EFFECTIVITY 1 Feb 22 80 2 Feb 22 80 21 CONTENTS 1 May 30 75 2 Feb 22 80 3 Feb 22 80 21 00 00 1 30 75 2 30 75 101 30 75 102 May 30 75 103 May 30 75 104 i 30 75 105 30 75 106 30 75 107 30 75 108 May 30 75 21 10 00 1 Nov 2 73 201 Nov 2 73 21 20 00 201 Nov 2 73 202 May 30 75 203 30 75 21 30 00 1 May 30 75 2 May 30 75 3 May 30 75 4 May 30 75 5 May 30 75 6 May 30 75 7 30 75 201 30 75 202 May 30 75 203 May 30 75 204 Feb 22 80 205 Feb 22 80 206 Feb 22 80 207 Feb 22 80 208 Feb 22 80 209 Feb 22 80 210 Feb 22 80 211 Feb 22 80 21 EFFECTIVITY Page 1 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 21 LIST OF PAGE EFFECTIVITY Cont d CHAPTER SECTION SUBJECT PAGE DATE 21 40 00 1 Nov 2 73 2 May 30 75 201 Nov 2 73 202 Nov 2 73 203 Nov 2 73 204 Nov 2 73 205 Nov 2 73 21 50 00 1
226. igure 201 f Check trim tab travel adjust cable stops and safety tumbuckles NOTE After rigging the aileron and aileron tab control system check for correct movement of the control surfaces with respect to the movement of the controls Since the aileron tab is an anti servo tab every time the aileron moves up the tab should move up AILERON TRIM TAB ACTUATOR REMOVAL a Remove the access plates at the actuator and tab cable turnbuckles b Disconnect the outboard cable at the turnbuckles in the wing c Remove the outboard cable from the actuator sprocket d Disconnect the actuator from the trim tab linkage e Remove the bolts attaching the actuator to the wing structure Remove the actuator AILERON TRIM TAB ACTUATOR INSTALLATION a Position the actuator against the wing structure and install the attaching bolts b Connect the actuator to the tab linkage c Install the outboard cable on the actuator Sprocket d Connect the cables at the tumbuckles in the wing e Rig the aileron trim tab control system f install the access plates at the actuator and the tab cable turnbuckies CHECKING AILERON TAB FREE PLAY Visually inspect the left aileron tab for damage security of hinge attach points and for tightness of the actuating system Inconsistancies should be corrected prior to checking the free play of the tab The aileron tab free play check should be performed at least once a year to ensure that the tr
227. im tab free play falls within the prescribed limits 27 10 00 Page 203 Sep 14 79 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL A check fixture P N 45 135030 9 810 or the equivalent as shown in Figure 202 a dial indicator and a push pull scale for applying accurate loading to the tab is required for making the inspection for free play of the tab a Securely lock the control surfaces to prevent movement of the ailerons Set the aileron tab in the neutral position 2 b Using shot bags affix the dial indicator check fixture so that the dial indicator point is 2 30 inches aft of the tab hinge line and on the outboard edge of the aileron tab c Apply a small piece of masking tape for paint protection 4 00 inches aft of the tab hinge line and along the centerline of the tab actuator This will be the point of pressure against the tab by the push pull scale d Apply another piece of masking tape in the corresponding position on the bottom surface of the tab for ine same purpose e Zero the dial indicator at no load initially Do not reset during the checking procedure f With the push pull scale at the point of masking tape apply a full 3 pound downward load Record the dial reading as A g Release haif the load until a 1 5 pound downward load is obtained Record the dial reading as B h Apply a 3 pound upward load at the masking tape on the bottom surface Record the dial reading as C i Release half the lo
228. ime could be considerably shorter or longer When the light does go out turn the battery switch OFF while observing the affected loadmeter the loadmeter should indicate a satisfac tory load change Listed below are possible situations that could be experi enced and corresponding action that is recommended a Light does not illuminate If the bulb is operational but the light does not come on within approximately 6 sec onds after the operating generator is turned ON itis possible that the battery is not sufficiently discharged to accept a charge This can be determined by turning the battery OFF while observing the loadmeter needle deflection A satisfac tory load change indicates the battery is charged and the light should not be on An unsatisfactory load change indicates the light should be on and that there is a malfunction in the detector system Repair or replace the defective parts and repeat the functional check If the battery was not discharged enough to accept a charge turn the generator OFF and Partially discharge the battery by operating electrical equip ment Repeat the functional check b Light stays on Check the following possibilities 1 Battery is partially discharged and is charg ing If the light stays on after charging for approximately 5 minutes careful attention should be given the airplane load meter With a constant load on the airplane electrical system continue to charge the battery The loadmeter sh
229. in the shaded band except for a flicker that may occur when the step switch of the timer cycles refer to the troubleshooting chart in Chapter 30 60 00 for the probable sources of xrouble NOTE Timers with electronic stepping circuits may not flick notice ably between cycles b With the engine shut down turn the deicer switch ON and feel the deicer boots on the propeller for the proper sequence of the heating elements The presence of local hot spots indicates damage to the heating elements which should be repaired before more serious damage develops CAUTION When following the instructions of step b move the propeller back and forth to prevent arcing between the brushes and the slip ring WARNING Before moving the propeller make certain that the ignition switch is OFF and that the engine has cooled completely There is always some danger of a cylinder firing when a propeller is moved 18 Remove the spinner dome and open all access doors pertaining to the wiring and components of the deicer system Turn the deicer switch ON and station an assistant in the pilot s compartment to observe the system ammeter Flex all accessible wiring particularly the lead straps leads from the slip ring assembly and the firewall electrical connectors and their wiring Any movement of the ammeter other than the cycling flicker that may occur when the step switch of the timer cycles indicates a short or open
230. indicates dirty outfk and safety valves The seats of these valves should cleaned at 100 hour inspections or more frequently needed The inspection and cleaning of the valve seat bellows may be accomplished by the following suggest procedure a Remove the aft fuselage access panel from ti lower LH fuselage aft of the aft pressure bulkhead b Compress the bellows to permit inspection ai cleaning C Clean the bellows and the inner rim of the vat housing where the bellows contacts the housing when ti bellows is extended using a clean rag dampened wi isopropy aicohol 45 Chart 207 91 00 00 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SAFETY VALVE FILTER AND ORIFICE CLEANING The filter and orifice in the head section of the safety valve should be removed cleaned and inspected every 1 000 hours The filter may be cleaned by the following suggested procedure a Remove the upholstery panel b Remove the plate to gain access to the safety valve The plate is secured with two AN4 5A bolts and sixteen AN3 5A bolts Remove the filter from the head section of the safety valve Do not lose the packing d Remove the retaining ring from the filter assembly housing Remove one screen the copper ribbon and the remaining screen from the housing of the filter assembly e Wash both screens the copper ribbon and the filter assembly housing in solvent 15 Chart 207 91 00 00 _Ensure that the orifice of the filter housin
231. ine cowling to gain access to the air conditioner compressor b Disconnect electrical leads to the magnetic clutch c Disconnect refrigerant lines at compressor service valves WARNING The lines connected to the compressor are under high pressure Refer to CHARGING THE AIR CONDITIONING SYSTEM in this chapter before disconnecting any fitting in the refrigerant system BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL d Loosen the compressor mounting nuts e Slide the compressor up in its slotted mounting to relieve tension on the drive belt Roll belt off the compressor pulley f Remove mounting nuts and washers and remove compressor COMPRESSOR INSTALLATION a Position the compressor in its slotted mounting brackets Position washers on the compressor studs and loosely install the attaching nuts b Roll the compressor drive belt onto the compressor pulley For adjustment of the belt refer to COMPRESSOR BELT TENSION ADJUSTMENT c Torque the compressor mounting nuts to 160 190 inch pounds d Install the refrigerant lines to the compressor service valves e Install the electrical leads to the magnetic clutch f Install the RH engine cowling END 21 50 00 Page 205 Nov 2 73 CHAPTER SECTION SUBJECT 22 EFFECTIVITY CONTENTS 22 10 00 22 11 00 SUBJECT GENERAL Description and Operation H 14 Autopilot Maintenance Practices H 14 Autopilot GENERAL Description and Operation New Matic Autopilo
232. ing Enamel finishes will maintain the original beauty for many years if a few timely suggestions are followed To preserve this finish the following care is recommended DURING CURING PERIOD 90 days airplane should be cleaned with cold or lukewarm water and a mild nondetergent soap Any rubbing of the painted surfaces should be done gently and held to a minimum to avoid cracking of the paint film Rinse with cold water and dry with cloths or chamois b Avoid use of waxes or polish They seal the paint from the air and delay the curing process c Do not rub or buff the finish d Flights through rain hail or sleet should be avoided e Avoid fluids containing dyes such as fuel and hydraulic being accidentally spilled on the painted surfaces 20 00 00 Page 202 Nov 30 83 AFTER CURING PERIOD a Always wash the airplane with a mild soap water Rinse thoroughly b Remove oil and grease with naphtha c Wax with any good grade of automobile wax i shaded area A heavier coating of wax on the leading edi will help to reduce abrasions in those areas Urethane p requires no waxing d Never use strong detergents to clean the airpla NOTE Frequently inspect the underside of the wing and flaps in the area covered by the engine turbocharger exhaust stream for fuel tead deposits If such deposits are discovered they should be removed immediately with a water and mild detergent solution an
233. ing the charger The following procedures for constant current charging are generally applicable to all aircraft nickel cadmium storage batteries a time required to charge a nickel cadmium storage battery varies with respect to the discharging current capacity rating and amount of charge already in the battery If fully discharged the battery should be charged to 140 percent of its nominal ampere hour rating b When Using the constant current method of charging the battery may be charged in two steps by using the START rate of current and the FINISH rate of current Lower starting rates may be used if required by such factors as equipment limitations These rates are usually given on the battery nameplate The two step method is commonly used by the military Single rates slow or fast are usually preferred by commercial service shops because of their simplicity The single fast charging rate is 2 7 24 31 00 Page 204 Nov 2 73 NICKEL CADMIUM 19 CELL AIRCRAFT BATTER Y CONSTANT CURRENT CHARGE ROOM TEMPERATURE AT 10 RATE 30 28 26 24 22 BATTERY VOLTAGE 20 gt 1 2 3 4 5 6 7 8 9 10 N 12 13 14 15 16 TIME HOURS Constant Current Charge at C 10 Rate Figure 201 amperes per hour for the 13 5 ampere hour battery for seven hours The slow charging rate is 1 4 amperes per hour for the 13 5 ampere hour battery for 14 hours See Figure 201 for slow capacity 10 sin
234. ing too long Equipment left on acci dentally Short circuit or ground in wiring Broken cell partition Charging rate too high Shorted or grounded cable causing direct full discharge of battery Discharged Water added in cold weather without charging the battery sufficiently afterward to thoroughly mix the water with electrolyte before letting stand Too low specific gravity of the electrolyte caused by impro per filling S e p REMARKS Replace battery Adjust voltage regulator on airplane Replace battery Adjust voltage regulator on airplane Remove excess electrolyte down to specified level Adjust voltage regulator on airplane Replace or tighten vent caps Remove battery and recharge Remove battery and recharge Check wiring and correct malfunction then remove battery and recharge This is usually indicated by two or more adjacent cells running down continually particularly if left standing a few days Re place battery Adjust voltage regulator on airplane Check cables and repair malfunction Re place battery Replace battery Replace battery Replace battery 24 31 00 Page 103 May 12 78 TROUBLE 9 Cracked cell jars 24 31 00 Page 104 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING LEAD ACID BATTERY PROBABLE CAUSE REMARKS Hold down loose a Frozen battery END Replace battery b Replace battery BEE
235. ingle viscosity grade SAE 50 oil conforming with MIL L 6082 6 Chart 202 12 20 00 The oil drain is accessible through the cowl flap opening The engines should be warmed to operating temperature to as sure complete drainage NOTE The engine oil must be of the proper viscosity and meet the reguirements of the current Avco Lycoming specification 301 and Avco Lycoming Service instruction 1014K or subseguent The determining factor for choosing the correct grade of oil is the oil inlet temperature observed furing flight however inlet temperatures consistently near the maximum allowable indi cate a heavier oil is needed Lycoming recommends use of the lightest weight oil that will give adequate cooling CHANGING THE OIL FILTER The oil filter should be replaced every 50 hours Replace the filter as follows a Disconnect the fuel line to the inlet side of the engine driven fuel pump Cap the fuel line P 3 through P 20 and push the line down to allow clearance for oil filter removal b Cut the safety wire and remove the filter housing C After making sure ail traces of gasket material and cement are removed from the oil filter adapter recess install 12 10 00 Page 202 Jan 9 86 Brake Fluid Reservoir Figure 201 new aluminum ring and O ring seal which replace th existing rubber gasket Refer to Lycoming Service Bulleti 337 d Torque the retainer bolt to 30 35 foot pounds an safe
236. ion air heater located under the nose baggage compartment floor a six position mode switch vent air blower combustion air blower heater fuel pump five outlets an automatic temperature control and three sensing elements In flight when pressurized the vent blower obtains air through the cabin air check valve forces it through the heater and to the cabin outlets In the unpressurized mode in flight and for ground operations the vent blower obtains air from the cabin and the ram air plenum chamber and forces it through the heater and to the cabin outlets On serials P 4 through P 126 except P 123 a vent air distribution bypass valve located on the forward pressure bulkhead allows air to be directed into the pilot s compartment area and is regulated by a control knob on the pilot s left subpanel Exchanging the cabin air is accomplished by exhausting a controlled amount of air through the isobaric control valve on the aft pressure bulkhead HEATER CONTROL SYSTEM Figure 1 The heater controls are located on the copilot s LH subpanel Serials P 4 through P 126 except P 123 incorporates a six position switch placarded AUTO HEAT MANUAL HEAT BLOWER AUTO COOL MANUAL COOL Hi MANUAL COOL LO and OFF On serials P 123 P 127 and after the mode selector switch differs slightly in that a MANUAL COOL position replaces the MANUAL COOL and MANUAL COOL LO positions In addition two blower positions are placed on the select
237. is wired to the landing gear safety switch When the airplane touches down the safety valve will energize and dump the cabin pressure overboard A manual dump switch located on the RH subpanel will also energize the solenoid and dump pressure overboard while in flight On serials P 123 P 127 and after the dump solenoid is actuated by the dump switch only while the vacuum solenoid is actuated by the landing gear safety switch The safety valve functions the same as the lt ifferential control section of the differential control valve exeept that the pressure setting is slightly higher A solenoid valve is also located on the differential control valve The primary function of this solenoid is to eliminate pressurization fluctuation during ground run up and flight in the unpressurized mode When energized the solenoid valve allows vacuum to be applied to the control diaphragm which holds it in the open position allowing cabin pressure to freely dump overboard The solenoid valve is energized wtren the manual dump switch is in the dump position or any time the airplane is on the ground The vacuum source is an ejector located in the aft fuselage which obtains its air supply from the instrument air or deicer system PRESSURIZATION TEST SWITCH Arpressurization press to test switch is located on the RH subpanel The press to test switch de energizes the solenoid valves on the differential control valve and the safety valve sotthe pressuri
238. ithin 1096 of the loadmeter full scale reading d Adjust the paralleling rheostats until the load is equally shared by increasing the output from the low generator and decreasing the output from the high generator NOTE To maintain sensitivity keep both rheostats as near the maximum voltage end of the rheostat as possible There is a possibility of excessive sen Sitivity resulting in a hunting condition Should Such a condition be enccuntered sensitivity may be reduced by turning both paralleling rheostats away from the high voltage end e Check both minimum current voltage and me imum current paralleling at cruise engine rpm 2 750 rpm FINAL PARALLELING CHECKS PRIOR TO P 466 a Secure the access cover in place using sufficie fasteners to hold the cover securely in place during engi operation f b Stabilize the regulator and generator temperatur _ as outlined in STABILIZATION OF GENERATOR SYSTEI c Check both minimum load voltage and maximt current paralleling at cruise engine rpm 2 750 rpm d Remove the cover and make any necessary justments Replace the access cover and repeat the e After determining that the adjustmenis are sai factory secure the access cover in place using all fastene P 466 AND AFTER a Stabilize the regulator and generator temperatur as outlined in STABILIZATION OF GENERATOR SYSTE b Check both minimum load voltage and maximi current paralleling at cruise engine rpm 2750 r
239. itude control sense line leaks REMARKS Clean valve as described in the Component Maintenance Manual P N 60 590001 27 or replace valve Replace indicator Inspect lines and fittings tighten or replace as required Clean valve as described in the Component Maintenance Manual P N 60 590001 27 or replace valve Inspect lines and fittings tighten or replace as required Inspect and repair or replace as required Replace filter Adjust controller Replace indicator Inspect and repair or replace as required Replace control Clean filter Adjust controller Inspect and repair or replace as required 10 11 12 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PRESSURIZATION SYSTEM Cont d P 3 THRU P 307 TROUBLE Cabin altitude lower than selected altitude Not exceeding maximum cabin differential PROBABLE CAUSE REMARKS Cabin altitude indicator c Replace indicator pressure inoperative Cabin pressure Valve seats dirty a Clean the valve seats with fluctuation Cabin pressure fluc a lint free cloth moistened with alcohol For additional information relating to over haul and cleaning procedures refer to Components Maintenance Manual P N 60 590001 27 The check valve in the a Install check valve properly tuates when deice system differential contri valve is cycled with dump vacuum fine is instal
240. l Connect the negative lead of the voltmeter to the airplane structure e Adjust the 150 ohm rheostat to its minimum resist ance setting CAUTION To prevent excessive overvoltage check the sistance with an ohrnmeter to ensure the rheo stat is set for minimum resistance prior to initiat ing this test Do not operate the systern above 29 volts for more than two minutes during the test If the battery is subjected to voltages in excess of 32 volts for more than two minutes the battery must be removed from the airplane and com pletely serviced f Start the engines and advance the throttles as required to obtain desired voltage output g Turn off all switches and circuit breakers except the battery master switch and the generator protection circuit breakers CAUTION Should the test equipment be improperly instal led the airplane electrical equipment may be damaged unless all switches and circuit break ers except those noted above are turned off h After the airplane s loadmeters stabilize at a point 24 30 00 Page 202 May 12 78 below 10 percent of full scale observe the precision ter while slowly increasing the resistance setting of the 15C ohm rheostat A sharp drop in voltage will indicate the opera tion of the voltage relay This should occur when the preci sion voltmeter registers a reading of 32 to 34 volts The GENERATOR OUT light on the annunciator panel shoulc iluminate at the same ti
241. lap position transmitter is installed on the flap actuator in the right wing An indicator on the right subpanel provides a visual indication of the flap position On serials P 247 and after the position of the flaps are indicated by three indicator lights located on the righi subpanel The illumination of these lights are controlled by the flap limit switches When the flaps are UP ati lights are out A red TRANSIT light illuminates to indicate that the flaps are not in the selected position The red TRANSIT light goes out and either the blue APH approach or the amber down light illuminates to indicate the flaps are in the position selected The intensity of iflumination is reduced for night operations when the NAV lights are turned on The lights may be checked by pressing the PRESS TO TEST switch on the annunciator panel E ND 727 50 00 Page 1 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL FLAPS MAINTENANCE PRACTICES FLAP REMOVAL a Fully extend the flaps and remove the bolt from the flap actuating arm b Remove the bonding cable from the flap tracks c Remove the bolts from the flap track brackets and remove the flap FLAP INSTALLATION a Hold flap in position and install the rollers and the bolts in the flap track bracket b Connect the bonding cable and instali the bolt in the flap actuating arm NOTE The contour of the flap must be within 0625 inch of the contour of the wing on
242. ld pressure too d Increase manifold pressure to a minimum low during check of 20 in Hg 21 00 00 Page 101 May 30 75 BEECHCRAFT EE DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PRESSURIZATION SYSTEM Cont d P 3 THRU P 307 TROUBLE 3 Maximum cabin differ ential pressure exceeds 4 6 psi 4 Maximum cabin differ ential pressure exceeds 4 9 psi 5 Cabin pressure slow to respond to change in selected cabin altitude 6 Cabin altitude higher than selected altitude Ui 7 Cabin altitude lower than selected altitude not exceeding maximum cabin differential pressure 21 00 00 Page 102 May 30 75 PROBABLE CAUSE Differential control valve inoperative Cabin altitude and dif ferential pressure in dicator inoperative Ambient air sense line between safety and differential control valve leaking Safety valve and differential control valve inoperative Ambient air sense line between safety and differential control valve ruptured loose fittings Cabin altitude control sense line kinked or restricted Cabin altitude control filter clogged Cabin altitude controller out of adjustment Cabin altitude indicator inoperative Cabin altitude control sense line kinked or restricted Cabin altitude control inoperative Cabin altitude control filter restricted Cabin altitude controller out of adjustment Cabin alt
243. leaks PROPELLER AND MOUNTING BOLTS Check for condition and security Check the tip of the blades for evidence of lightning strikes If there is evidence of lightning strikes consult the propeller manufacturer the engine manufacturer and Beech Aircraft Corporation Inspect the blades for cracks dents nicks scratches erosion corrosion security and movement in the hub PROPELLER SPINNER Check for deformation security and cracks PROPELLER HUB Check for cracks excessively leaking seals and condition Check propeller dome pressure PROPELLER ACCUMULATOR Check for proper operation STARTER Check for condition attachment and chafed or loose wires MAGNETOS Check contact points for proper clearance Points with deep pits or excessively burned areas must be discarded Inspect the cam follower felt pad for proper lubrication and clean the compartment with a clean dry cloth Check timing IGNITION HARNESS Inspect for fraying and attachment 5 20 00 Page 207 A18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CYLINDERS AND BAFFLES Check cylinders and exhaust man ifold for obvious leaks security and cracks check baffles for cracks and security Check cylinders for broken cooling fins and loose or missing base nuts NOTE Accomplish valve inspection every 400 hours of operation per Lycoming 110 541 Series Operating Manual EXHAUST SYSTEM Check for deformation s
244. led switch in either dump backward or pressure mode Check valve is dirty b Clean check valve Cabin pressure fiuc Vacuum solenoid inoperative a Replace vacuum solenoid tuates with dump switch in dump mode Dump solenoid inoperative b Replace safety valve Pressure circuit breaker Dump solenoid shorted a Locate cause repair and reset circuit tripped Airplane pressurizes on ground Vacuum solenoid shorted Press to test switch shorted Landing gear safety switch shorted Wire harness shorted inoperative Landing gear safety switch inoperative Open lead in wire bundle b breaker Locate cause repair and reset circuit breaker Locate cause repair and reset circuit breaker Locate cause repair and reset circuit breaker Locate cause and repair Wire harness improperly f Inspect and rewire as required installed Pressure circuit breaker g Replace circuit breaker Replace switch Locate and repair 21 00 00 Page 103 May 30 75 TROUBLE 12 Airplane pressurizes on ground TROUBLE 1 Unable to pressurize 21 00 00 Page 104 May 30 75 Circuit breaker tripped Press to test switch BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PRESSURIZATION SYSTEM Cont d P 3 THRU P 307 PROBABLE CAUSE REMARKS See 11 above d Replace switch inoperative TROUBLESHOOTING PRESSURIZATION
245. ler amplifier or harness or heading sensor Defective sensor or harness or faulty controller arnplifier Defective nav switching console or no nav informa tion or defective controller amplifier Wrong nav input signals Defective switching console if installed REMARKS Check for leaks Adjust system as outlined in Chapter 36 Replace the heading sensor Replace controller amplifier Replace controller amplifier Replace omni converter Repair or replace omni indicator Readjust Adiust Check A and ground Replace controller amplifier or power supply Replace controller amplifier Replace controiler amplifier or harness or heading sensor Replace heading sensor or check harness Replace controller amplifier Check nav input leads Replace controller amplifier Check wiring Repair or replace console 22 11 00 Page 103 Oct 27 75 TROUBLE ROLL AXIS Cont d 22 23 24 25 Output voltage in CAP mode decays to 0 voltage Cont d Voltage output in MAN CAP TRK and APP mode but none in HDG mode Nav indicator needle deflects left or right when controller amplifier or radio is turned on Low or high intercept angle PITCH AXIS 1 Pitch channel will not center up electrically Altitude channel will not center up electrically Altitude hold solenoid valve will not actuate 4 Servocontrol valve will not center 5
246. linder and recharging valve The system may be fitted with an 11 22 49 or 65 cubic foot cylinder When the system is not in use the control valve on the console should be shut off to prevent oxygen loss To recharge the oxygen system remove the protective cap from the filler valve WARNING Keep fires cigarettes and sparks away when outlets are in use Open and close all oxygen valves slowly inspect the filler connection for cleanliness before attaching it to the filler valve Keep tools hands and components clean as fire or explosion may occur when pure oxygen under pressure comes in contact with organic material such as grease or oil Attach a hose from an oxygen recharging cart to the filler valve To prevent overheating fill the oxygen system slowly by adjusting the recharging rate with the pressure regulating valve on the cart The oxygen cylinder should be filled to a pressure of 1800 50 psi at a temperature of 70 F This pressure may be increased an additional 3 5 psi for each degree of increase in temperature similarly for each degree of drop in temperature reduce the pressure by 3 5 psi When the oxygen system is properly charged disconnect the hase from the filler valve and replace the protective cap If at any time in the process of servicing and purging the system or replacing the oxygen cylinder it becomes necessary to disconnect a fitting the threads should be treated with MIL T 27730 tetrafluoroethylene t
247. llowing pro cedure a Attach a set of 16 gage test leads to a 2 ampere circuit breaker or fuse and a 150 ohm rheostat with a minimum rating of 50 watts b Disconnect the wire P117A18 from the voltage regulator base terminal which may be marked B or L Then disconnect the wire P116A18 from the terminal marked C or G TO ie gp TERMINAL OF VOLTAGE REGULATOR Y 16 GAGE 1 CIRCUIT 2A BREAKER OR FUSE 150 2 50W RHEOSTAT 16 GAGE TO B OR Le TERMINAL OF VOLTAGE REGULATOR 60 603 1 Overvoltage Test Circuit Figure 201 24 30 00 Page 201 May 12 78 a BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NOTE Refer to the Wiring Diagram Manual P N 60 590001 29 for the applicable wiring code Attach the test lead from the wiper contact of the 150 ohm rheostat to the or L terminal of the RH voltage regulator c Attach the test lead from the 2 ampere circuit breaker or fuse to the C or terminal of the RH voltage regulator Do not remove the existing wire from the C or G terminal d Monitor the overvoltage relay trip voltage with precision voltmeter that is known to be accurate within one percent over a range of 0 to 50 volts Connect the voltmeter test leads to the voltage test jacks located on the right circuit breaker panel P 436 and after On airplanes prior to P 436 connect the positive lead of the circuit breaker bus behind the subpane
248. ly mounted and the shaft clamp or slip ring must be replaced i Check for proper spacing between the brush block and slip rings If this distance is not within the specified lim its loosen the mounting screws and repo sition them in the elongated holes until the block is properly positioned If nec essary shims an be added between the thrust bearing plate and mounting bracke until the brush is properly located j Estimate the contact angle of th brush block in relation to the slip rings If this angle is not approximately degrees loosen the mounting bolts an reposition the brush block until th proper angle exists between the brus block and slip rings It should be note that the spacing established in step i must also be maintained after proper con tact angle is obtained k With the deicer system operatin and a man in the pilot s compartmen observing the ammeter visually inspec and physically flex the wiring from th brush block to each component of th deicer system and to the airplane powe supply Jumps of the ammeter needle othe than the momentary flicker that may occu when the step switch of the timer cycles indicate loose or broken wiring in th area under examination at the moment I such instances continue to flex the wir ing in the area that first indicate trouble while checking the continuit through the individual wires of th affected harness until the source o trouble is located Use the applicabl Wiri
249. me the overvoltage relay trips If the overvoltage relay does not operate within the prescribec limits it should be replaced with a new one then recheckec for proper operation as in steps f through h VOLTAGE REGULATOR ADJUSTMENT GENERATOR PARALLELING It is desirable that both generators share the electrical loac equally To obtain this condition the voltage regulators anc the paralleling rheostats must be properly adjusted The paralieling rheostats and voltage adjustment potentiometers are located in the cabin P 466 and after for convenient anc precise adjustments The adjustment procedure is outlined ir the following paragraphs PRELIMINARY POTENTIOMETER CHECK A potentiometer located on each voltage regulator in the lel nacelle must be permanently adjusted to minimum resist ance fully cew If the regulators have been changed or th setting altered for any reason remove the access cover top of the left nacelle aft of the engine cowling and ensur that these potentiometers are adjusted fully counterclock wise No other adjustments or connections to component located within the nacelle compartment will be necessary fc voltage and paralleling settings PRELIMINARY ADUSTMENT OF PARALLELING RHEO STATS a airplanes prior to P 466 open the electrica components compartment access cover top of the lel nacelle aft of the engine cowling On P 466 and after removi the access panel placarded GENERATOR VOLT
250. mission regu lations require that this testing be per formed in a screened or shielded test room or in a test enclosure that will hold the self contained ELT unit with the antenna fully extended CAUTION The ELT switch should not be turned ON unless the ELT is con nected to its associated antenna or a 50 ohm dummy load Operational testing of installed ELTs may be accomplished as follows NOTE Tests should not be longer than three audio sweeps audio sweep may be defined as amplitude modulating the carrier with an audio frequency sweeping downward over a range of not less than 700 CONTACT SEPARATOR PORTABLE ANTENNA CONTACT FINGER PORTABLE ANTENNA BLADE NOT MAKING CONTACT FIXED ANTENNA CABLE CONNECTOR CONTACT SEPARATOR COAX CABLE TO AIRPLANE FIXED ANTENNA SWITCH PORTABLE s HANDLE ANTENNA RESET STOP PIN SWITCH STD 356 48 Narco ELT Figure 201 25 60 00 Page 203 A18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL Hz within the range 1600 to 300 Hz and a sweep repetition rate between two and four Hz Tests should be conducted only the first five minutes of any hour If the operational tests must be made at a time not included within the first five minutes after the hour the tests should be coordi nated with the nearest FAA tower or flight service station a Turn COMM 1 ON transceiver to 121 5 MHz and tune b Turn the COMM 1 audio switch the to
251. mitter resets the transmitter lj in the event the impact switch is acci dentally triggered Airplane serials P 166 P 183 thru P 185 P 187 thru P 244 and P 246 thru P 536 equipped with Kit No 101 3039 1 have a remote switch located on the RH side of the rear fuselage The remote switch placarded REARM ARM XMIT is accessible thru an access hole with a spring loaded door located adjacent to the transmitter The XMIT position turns the set on for testing and the ARM position actuates the set to operate automatically upon impact The REARM position resets the transmitter in the event the impact switch lj is accidently triggered Airplane serials P 537 and after and earlier airplanes equipped with Kit No 101 3046 1 have a remote switch installed on the RH side of the rear fuselage The remote switch placarded ARM XMIT is accessible thru an access hole with a spring loaded door located adjacent to the transmitter optional installation is available for the remote switch so that it may be installed in the instrument panel The remote switch is a momentary switch that enables manual activation of the ELT for testing purposes while the unit is installed in the air plane END A18 25 60 00 Page 1 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL EMERGENCY MAINTENANCE PRAC TICES EMERGENCY LOCATOR TRANSMITTER MAINTENANCE Maintenance on the ELT is normally limited to replacing the battery The following is a
252. more than 3 inches into the filler neck to do so may cause damage to the rubber fuel cell DRAINING THE FUEL SYSTEM To ensure that alt fuel is removed from the system the fuel should be drained through the boost pumps To expedite the defueling operation the boost pumps may be used to pump the fuel out of the system The following steps must be accomplished before energizing the pumps a Apply external power to the airplane electrical system b Place the fuel selector valve in the ON position and the mixture lever in the IDLE CUT OFF c Remove the filler caps to vent the system d Disconnect the fuel line at the firewall and attach a drain hose Provide a suitable container for the fuel e Energize the boost pumps f When fuel is no longer pumped from the airplane open the sump drains to complete the defueling operation ENGINE FUEL FILTERS AND SCHEENS Most fuel injection system malfunctions carr be attributed to contaminated fuel Inspecting and cleaning the fuel strainers should be considered to be of the utmost importance as a regular part of preventive maintenance Normally the fuel strainers should be inspected and cleaned every 100 hours However the strainers should be inspected and cleaned at more frequent intervals depending on service conditions fuel handling equipment and when operating in localitites where there is an excessive amount of sand or dust Open each of the seven snap type fuel drains dail
253. move the skin b Remove the pins at the air ramp hinge points and lift the air ramp out c Disconnect the electrical wiring at the terminals on the condenser blower Remove the screws securing the blower to its mounting bracket and then lift out the blower d Remove the screws securing the blower mount bracket and the two baffles to the condenser compartment Lift out the mounting bracket and baffles e Disconnect the fittings on the condenser and cap WARNING The lines connected to the condenser are under high pressure Refer to CHARGING THE AIR CONDITIONING SYSTEM in this chapter before disconnecting any fitting in the refrigerant system f Remove the screws securing the condenser to its mounting flange and lift the condenser out of the compartment CONDENSER BLOWER INSTALLATION a Position condenser in condenser compartment and secure with attaching screws b Remove cap and install the fittings to the condenser c Position the two baffles to the condenser compartment and the blower mount bracket and secure with attaching screws d Position the blower to its mounting bracket and secure with attaching screws Attach the electrical wiring at 21 50 00 Page 204 Nov 2 73 the terminals on the blower e Position the air ramp to align the air ramp hinges and install the hinge pins f Position the air scoop and ramp vertically to install the skin covering the condenser compartment g Secure the skin with att
254. n 10 hours which can be used only if the additional time is required to reach a place where the inspection be sat isfactorily accomplished However any extension of 100 hour interval must be subtracted from the following 100 hour interval with no time extension permit ted For example if an inspection is done at 110 hours the next inspection is due 90 hours later with no extension allowed NOTE Ascertain that all placards are in plate and legible whenever the airplane has been repainted or touched up after repairs Replace any placards that have been inad B vertently defaced or removed NOTE Beech Aircraft s Recommended Inspection Program in accordance A18 with FAR Parts 43 and 91 consists of but is not limited to inspection items listed in this Inspection Guide any applicable Airworthiness Directives issued against the airframe or any equipment installed therein con formity to Type Certificate Data Sheet and M Maintenance Manual Airworthiness Limitations Chapter Chapter 4 as applicable The owner or operator is primarily responsible for maintaining the airplane in an airworthy condition including com pliance with all applicable Airworthiness Directives as specified in Part 39 of the Federal Aviation Regulations It is fur ther the responsibility of the owner or operator to ensure that the airplane is inspected in conformity with the require ments of Parts 43 and 91 of the Federal Av
255. n air blower Replace filter Remove combustion air motor for overhaul or replacement of motor Inspect fue supply to heater including shut off valve solenoid valve fuel filter fuel pump and fuel lines Make all necessary repairs Replace spark plug Tighten the connection Replace the vibrator Remove and overhaul the com bustion air blower assembly as required or correct low voltage condition 4 5 6 1 TROUBLE Heater fires but burns unsteadily Cont d Heater starts then goes out Heater fails to shut off Insufficient cooling BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING HEATER SYSTEM Cont d PROBABLE CAUSE High voltage teak in lead f between ignition assembly and spark plug Inoperative ignition assembly 9 Restriction in fuel nozzle h orifice Nozzle loose in retainer or i improper spray angle Lack of fuel at heater Inoperative or chattering b combustion air pressure switch Inoperative overheat switch Inoperative cycling switch d Low voltage Fuel solenoid valve in heater a stuck open Inoperative duct and cycling b switch Defective MASTER switch AIR CONDITIONING SYSTEM Blower not functioning a Obstructed or disconnected b air duct Compressor clutch or belt slipping Evaporator filter clogged d Refrigerant level low Hot gas bypass valve f
256. n airplane Salvaged airplane parts reworked parts obtained from non BEECHCRAFT approved sources Or parts components or structural assemblies the service history of which is unknown or cannot be authenticated may have been subjected to unacceptable stresses or temperatures or have other hidden damage not discernible through routine visual or usual nondestructive testing techniques This may render the part component or structural assembly even though originally manufactured by BEECHCRAFT unsuitable and unsafe for airplane use BEECHCRAFT expressly disclaims any responsibility for malfunctions failures damage or injury caused by use of non BEECHCRAFT approved parts NOTE It shall be the responsibility of the owner operator to ensure that the latest revision of publications referenced in this handbook are utilized during operation servicing and maintenance of the air plane INTRODUCTION Page 2 Sep 20 85 At BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL ATA 100 SYSTEM CHAPTER INDEX GUIDE The following chapters are not covered within this Maintenance Manual 26 29 31 37 39 49 54 60 70 75 76 78 and 83 SYSTEM SUB SYSTEM CHAPTER SECTION TITLE INTRODUCTION AIRCRAFT GENERAL 5 TIME LIMITS MAINTENANCE CHECKS 10 Time Limits 20 Scheduled Maintenance Checks 6 DIMENSIONS AND AREAS 7 LIFTING AND SHORING 00 General 8 LEVELING AND WEIGHING 00 General 9 TOWING AND TAXIING 00
257. n altitude will be maintained during the flight provided the cabin pressure is at or below the maximum differential pressure If the cabin reaches the maximum differential of 4 6 psi and the airplane is still climbing the cabin altitude will climb with the airplane If a cabin altitude change is required in flight it can be accomplished with a minimum of abrupt cabin pressure change by turning the selector dial very slowly and monitoring the rate of change on the cabin pressure indicator A time lapse of approximately two minutes for each thousand foot increment change on the dial will effect a comfortable change of pressure Rapid cabin pressure changes will be experienced if the altitude selector is moved quickly before reaching the maximum differential pressure of 4 6 psi CABIN ALTITUDE CONTROLLER MOTORIZED PRIOR TO P 308 The motorized controller is designed to maintain a constant cabin altitude rate of change during airplane climbs and descents and to make available a means of cabin altitude programming It can best be described as an adjustable isobaric controller incorporating a variable speed drive motor with automatic shut off The additional controls for the unit are the red altitude selector ring the motor rate rheostat and the directional toggle switch The inner cabin altitude selector is normally operated with the directional toggle switch The control can be moved to override the motor drive but under normal operation all
258. n amperes As an example assume that a 20 ampere hour battery is charged at a start rate of 8 amperes for 2 hours at which time the voltage rises to 29 5 volts The ampere hour input at the start rate is then Ig x Ts 16 ampere hours The ampere hours of additional charge required are Us x T 3 TE x lE 7216 3 5 3 ff a finish rate of 2 amperes is used the finish rate charge time will be Ic x Ta 16 2 7 hours 3x2 3 While the battery is being charged the charging current should be kept constant at the rate being used If the battery charger is not a self regulating type this operation can be achieved by manually adjusting the charger on a periodic basis During the finish charge the individual cell voltages should be measured with a precision voltmeter to determine if all cells are rising evenly Should some cells indicate a voltage lower than the others by 05 volts or more it is advisable to leave the battery on charge a while longer for additional equalization Do not allow the battery to overheat CONSTANT POTENTIAL CHARGING Nickel cadmium batteries can be charged much faster by the constant potential method but the charging time will depend on the current delivery capability 300 ampere generators are good charging sources A disadvantage of constant potential charging is that full capacity cannot normally be restored if a battery suffers from temporary loss of capacity It should also be n
259. n the aft fuselage Rig the rudder trim tab control system i Install the access panel in the floorboard aft of the rear spar the floorboard between the main and rear spar and the left passenger seat j Install both upholstery panels on the left side of the pedestal k Instali the left floorboard and the pilot s seat 1 Install the tail cone the access plate beneath the RH horizontal stabilizer and the access plate at the trim tab actuator RUDDER TRIM TAB RIGGING a Disconnect the tab from its actuator b Position the rudder in neutral and set the tab indicator at zero degrees c Rig the tab cables to the proper tension as determined by the Temperature Cable Tension Chart Safety wire the turnbuckles d Position the tab actuator screw at the midpoint of its travel e Adjust the actuator linkage until the tab is in the neutra position with the chain centered on the actuator sprocket and connect the tab to the actuator f Adjust the cable stops until the rudder tab has a travel of 19 to 21 degrees to both the left and right 9 Torque the cable stops to 40 to 60 inch pounds and safety h Check the tab control and tab surface for correct movement as indicated by the tab indicator When the tab control is moved to the left the tab should move to the right i Check the rudder trim tab control system for friction at the tab control wheel shaft At room temperature the maximum allowable torque limit is 12 inch pound
260. ncies should be corrected prior to checking the free play of the tab The rudder tab free play check should be performed at least once a year to ensure that the trim tab free play falis within the prescribed limits A check fixture P N 45 135030 9 810 or the equivalent as shown in Figure 202 a dial indicator and a push pull scale for applying accurate loading to the tab is required for making the inspection for free play of the tab amp Securely lock the control surface to prevent movement of the rudder Set the rudder tab in the neutral position b Tape the dial indicator check fixture to the rudder so that the dial indicator point is positioned 8 70 inches aft of the tab hinge line and at the top edge of the tab c Apply a smali piece of masking tape for paint protection 9 0 inches aft of the tab hinge line and along the centerline of the tab actuator This will be the point of pressure against the tab by the push pull scale d Apply another piece of masking tape in the corresponding position on the opposite side for the same purpose e Zero the dial indicator at no load initially Do not reset during the checking procedure 27 20 00 Page 204 Sep 14 79 f With the push pull scale at the point of masking tape apply a full 3 pound load to the right Record the dial reading as A 9 Release half the load until a 1 5 pound load is obtained Record the dial reading as h Apply a full 3 pound load at the m
261. nd power unit regulated at 28 25 25 VDC to the aircraft b Check flap motor amperage during down and up cycles Maximum 7 0 amps down 9 0 amps up c If the amperage is exceeded during the up or down Cycle the system must be inspected for excessive friction rough flap tracks or misrigging Avoid continuous operation of the flaps to prevent overheating of the motor FLAP POSITION TRANSMITTER ADJUSTMENT P 4 through P 246 Figure 201 An adjustable flap position indicator transmitter is installed 27 50 00 Page 201 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL FLAP SETTINGS Approach 15 from Neutrat Full Down 30 from Neutral FLAP SYSTEM 1 Flap Motor Gearbox 2 Flap Shaft and Housing 3 Flap Actuator 4 Limit Switches FLAP TRANSMITTER AND POSITION INDICATORS TO ADJUST LOOSEN MOUNTING BOLTS AND MOVE FORE AND AFT OR ROTATE SLIGHTLY 1 Transmitter 3 Indicator 2 Flap Actuator 4 indicator Lights FLAP LIMIT SWITCHES Down Limit Switch Up Limit Switch 14 Limit Switch 16 Limit Switches PUNS INDICATOR LIGHTS AND 2 16 LIMIT SWITCHES ARE IN STALLED ON SERIALS P 247 AND AFTER 60 161 1 Flap System Figure 201 27 50 00 Page 202 Nov 2 73 Beechcraft DUKE 60 SERIES MAINTENANCE MANUAL TEMPORARY REVISION NO 27 2 Manual Affected Duke 60 Series Maintenance Manual 60 590001 25 Filing Instructions Insert adjacent to 27
262. ng Diagram Manual to trace the circu itry of the deicer system CAUTION While following the instructions of step k move the propeller back and forth to prevent arcing between the brushes and the slip ring WARNING Before moving the propeller make certain that the ignition switch is OFF and that the engine has cooled completely There is always some danger of a cylinder firing when the propeller is moved END Lii 5 20 00 Page 228 Nov 20 87 A1 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 6 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 6 EFFECTIVITY CONTENTS 1 Nov 2 73 6 00 00 1 Nov 2 73 2 Nov 2 73 CHAPTER 6 DIMENSIONS AND AREAS TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE DIMENSIONS AND AREAS 6 00 00 1 Description and Operation 1 Aircraft Dimensions 1 Stations Diagram 2 END 6 EFFECTIVITY CONTENTS Page 1 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 39 3 25 60 607 1A Aircraft Dimensions Figure 1 6 00 00 Page 1 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 10 90 4 7 41 00 100 00 10 94 123 12 128 02 146 50 1 8 50 172 13 167 00 201 00 24 9 228 00 242 00 265 20 288 00 306 421 31 190 335 04 46 25 50 00 n o ci E d 1 ee ti i a m MERE por w L 100 a m A t V 1 i 4 t poat no d i as W L 87 00 e T 1 o ae
263. ng Gear Operation accu Ba Ge eS Nes as tree A ee Genera wn E Dm 224 Propeller Deicer System Inspection Omid AS ey dO Mate oocyst ete 227 Electric Propeller Deicer C100 Heu GUIGE a 227 Electric Propeller Deicer 100 Hour Guide lE Tap Ga Ge 227 END 5 CONTENTS Page 1 A18 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHED ULE The first overhaul or replacement must be performed not later than the recommended period The condition of the item at the end of the first period can be used as a criterion for determining subsequent periods applicable to the individual air plane or fleet operation provided the operator has an approved monitoring sys tem The time periods for inspections noted in this manual are based on average usage and average environmental conditions NOTE The recommended periods do not constitute a guarantee the item will reach the period without malfunction as the aforementioned factors cannot be controlled by the manufacturer SPECIAL CONDITIONS NOTICE CAUTIONARY WARNING Prior to performing maintenance on an engine or the Airframe ALWAYS pull the starter control circuit breakers and the Landing Gear circuit breaker This will kill power to the starter control as well as the igniter power relay and Landing Gear Con
264. ng through the throat of the nozzle each engine is producing the maximum fiow rate of 4 to 5 pounds per minute Total air flow from both engines will deliver approximately 8 to 10 pounds per minute and maintain a cabin pressure differential of 4 6 psi The air then passes through a firewall shutoff vaive through an intercooler and into the cabin beneath the pilot and copilot floorboards The intercooler reduces the heat acquired by the air during pressurization with a flow of ram air from a scoop at the leading edge of each wing root Within the cabin pressure vessel a check valve is installed at each pressurization outlet In the event of an engine failure at altitude the check valve will close on the dead engine side preventing a loss of cabin pressurization Located on the forward side of the aft pressure bulkhead 3 through P 246 and on the aft side of the aft pressure bulkhead P 247 and after are two valves the differential control valve and the safety dump valve A pressurization controller on the right subpanel pneumatically regulates the differential contro valve to maintain the selected cabin altitude AIR CONDITIONING SYSTEM The optional air conditioning system is a recirculating air cooling system containing a 16 000 BTU refrigerative type cooler The unit is controlled by an automatic temperature control and three sensing elements A six position mode switch controls the heater and air conditioner system however ea
265. ngs OUTFLOW VALVE AND SAFETY VALVE REMOVAL and OUTFLOW VALVE AND SAFETY VALVE INSTALLATION SAFETY VALVE GROUND CHECK a Connect a regulated cabin pressurization test unit to the airplane as outlined under the heading CABIN PRESSURIZATION LEAKAGE TEST P 4 and after in this Chapter Do not pressurize at this time b Working through the access opening behind the aft pressure bulkhead iocate the line that connects the dump solenoid valve to the safety valve and disconnect the line from the solenoid valve Connect a regulated vacuum source to the line which was disconnected from the solenoid valve Do not apply vacuum at this time d Pressurize the cabin to 3 psid e Slowly apply regulated vacuum to the safety valve if the valve opens before the vacuum reaches 4 inches Hg indication on the test unit the valve is operating satisfactorily if more than 4 inches Hg are required to open the safety valve the valve must be replaced CABIN ALTITUDE CONTROLLER REMOVAL a Remove the knobs handles screws etc to facilitate the removal of the edge lighted panel from the RH inboard subpanel b Tag the plumbing as removed to facilitate reinstallation Loosen and remove ail plumbing from the cabin pressurization controller as necessary to permit removal of the controller Cap all open plumbing to keep shop soil and foreign material from entering the plumbing and the controller Disconnect the electrical wiring from the cont
266. nna CAUTION To avoid damage to the antenna or the plastic tab on the upper end care must be exercised in extend ing the portable antena and han dling the control head e Remove the four screws attaching the control head to the battery casing and slide the control head and the battery case apart The battery connection leads are approximately 3 inches long NOTE Do not remove the sealant on the inside lip of the battery pack or a water tight seal will not be made when the ELT unit is reas sembled f Disconnect the battery by unsnap ping the battery terminals from the bottom of the transmitter PC board Discard the old battery NOTE Inspect for and properly treat any corrosion in the area when the battery is replaced 25 60 00 Page 202 Nov 20 87 WARNING DO NOT discard the battery in fire 4 Connect the terminals of the battery to the bottom of the transmitte PC board h Using a stick apply a bead c sealant supplied with each battery pack around the area of the control head whic 15 joined with the battery case whe reassembled NOTE This sealant provides a water tight seal when the unit is assembled i Insert the control head sectio into the battery case being careful no to pinch the wires and install the fou attaching screws Wipe any excess sealan from the outside of the unit NOTE If the four screw holes do not line up rotate the battery case 180 and reinsert
267. nstall INTERVAL Preflight Every 100 hrs As Required As Required Every 100 hrs Every 100 hrs Every 100 hrs or Annually Perform Function al Test Every 500 Hours Every 75 100 hrs Every 50 hrs Every 100 hrs Every 50 hrs Every 100 hrs Every 100 hrs Every 500 hrs 12 20 00 Page 212A Nov 30 83 ITEM CLEAN Cabin Pressurization Safety Valve Filter and Orifice P 308 and after Static Air Button Pos Oil Screen Heater Fuel Supply Susie Heater Fuel Pump Filter Heater Inline Fuel Filter DRAIN Fuel Sump Drain Fuel Strainer Drain Fuel Tank Drain Heater Fuel Drain Static Drain REPLACE Pressure System Inline Air Filter Pressure System Inline Air Filter Air Pump Intake Filter induction Air Filter Motorized Cabin Altitude Controller Filter Electric Trim Tab Actuator Motor Brushes 12 20 00 2128 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 203 Cont d SERVICING LOCATION SERVICE WITH Ait Pressure Bulkhead 1 Remove filter disassemble clean with solvent and air dry Ensure orifice is open reassemble and reinstall Aft fuselage skin 4 Clean with solvent and wipe dry vwith clean Engine oil sump 2 Clean with solvent and blow dry with air pressure LH wing stub 1 Clean with solvent and blow dry s with air pressure LH wing stub 1 tean with solvent and blow dry with air pressure
268. o service If there is a grinding and binding in the lock as the seat reclines or the return action becomes jerky a little grease properly applied as follows should improve the operation a Apply grease 30 Chart 207 91 00 00 to the threads as shown in Figure 202 b Compress the spring guide and counter balance spring approximately one inch c Remove the retaining ring d Relax pressure on the spring guide and counter balance spring slowly until the spring is fully extended e Remove the lock from the fixture and remove the spring guide counter balance spring and spring guide tube f Apply a small quantity of grease to the completely extended thrust screw 9 Reassemble the lock For service other than lubrication a new lock will need to be purchased CLEANING AND WAXING THE AIRPLANE FINISH Because the wax seals the paint from the outside air a new paint job should not be waxed for a period of 90 days to allow the paint to cure Wash uncured painted surfaces with only cold or lukewarm never hot water and a mild non detergent soap Any rubbing of the painted surface should be done gently and held to a minimum to avoid cracking the paint film After the paint cures a thorough waxing will protect painted and unpainted metal surfaces from a variety of RETAINING RING SPRING GUIDE SPRING GUIDE TUBE MAIN ASSY COUNTERBALANCE SPRING 60 3t4 1 Roton Lock Figure 202 12 20 00 Page 203 Apr 18 80 BE
269. o the clutch will result ELECTRIC TRIM TAB ACTUATOR MAGNETIC CLUTCH TORQUE TEST The following procedure should be performed any time the magnetic clutch is replaced f a Connect the red electrical lead of the magnetic clutch to ground and the white electrical lead to a 28 VDC power source Check that the clutch holds with 30 inch pounds of torque applied through a torque wrench at the actuator shaft b If the static torque of the clutch is less than inch pounds burn in the clutch as follows 1 Use a metal plate of sufficient thickness foi rigidity and large enough to fit in a vise with the actuatoi 27 30 00 Page 205 Sep 14 79 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL assembly attached Anchor the plate in a vise and mount the actuator on the plate 2 Insert the retaining pin in the actuator shaft 3 Slot the end of the tube so that it will fit snugly into the 375 inch diameter hole in the end of the shaft 4 Insert the tube into the shaft until the slot engages the retaining pins 5 Attach the free end of the tube to a slow speed approximately 450 rpm half inch drill motor 6 Remove the access plate from the clutch housing and blow the housing and clutch clean 7 Connect the red electrical lead of the clutch to ground and the white electrical lead to a regulated power source set at 14 to 16 VDC 8 Start the drill motor and run for fifteen seconds then remove the white lead from the power sour
270. of solenoid air valves One a normally closed air valve is actuated to open and permit the application of a negative pressure from the airplane vacuum system to the control chamber of the safety valve The safety valve poppet valve is thus opened to prevent pressurization of the airplane The second solenoid air valve a normally open valve is energized to close the supply line to the cabin altitude controller permitting it to be preset to the desired cabin altitude prior to take off for the flight When the airplane feaves the ground the contacts of the RH safety switch change over thus opening the circuits of the solenoid valves The normally closed air valve closes to remove the safety valve control chamber from the airplane vacuum system Cabin air enters the control chamber of the safety valve through a filter and orifice This permits the poppet valve return spring to close the poppet valve Simultaneously the normally open air valve opens thus connecting the cabin altitude controller to the airplane vacuum system The controller pre rates to the selected cabin altitude If the cabin altitude is above the field elevation the outflow valve poppet valve will modulate open preventing pressurization of the airplane until the selected altitude is reached As the airplane reaches the selected cabin altitude the reference pressure developed within the cabin altitude controller decreases permitting the outflow valve poppet valv
271. of the fuselage immediately aft of the rear pressure bulkhead H 14 AUTOPILOT For maintenance repair troubleshooting and testing refer Adjustment of the pneumatic pressure system is performed to the procedures described in the BEECHCRAFT H 14 by adjusting the various regulators in a specified sequence Autopilot Maintenance Manual P N 130333F and the A PRESSURIZATION SYSTEM ADJUSTMENT CHART Maintenance Manual Supplement P N 98 30603 corresponding to applicable illustrations and a general adjustment procedure for each individual regulator are Access for adjustment of the autopilot is through a provided in Chapter 36 00 00 END 22 10 00 Page 201 Oct 27 75 TROUBLE ROLL AXIS 1 Insufficient or excessive pressure indicated on aircraft system gage 2 Aircraft hunts or recovers slowly from turn in one direction 3 Autopilot sluggish 4 Aircraft turns continuously on basic stabilization Controller OFF BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING NEW MATIC AUTOPILOT PROBABLE CAUSE Leak in aircraft pressure a system Regulator valve improperly b adjusted Regulator improperly c adjusted Faulty pressure pump d Ambient air filter clogged e Clogged system filter f Regulator valve improperly a adjusted Loose aircraft primary cables b or excessive friction in aileron and or rudder cables pulleys bell cranks or loose servo cables Leak in servo or servo lines
272. om 30 to 110 F The horizontal scale on the graphs designates the temperature in degrees fahrenheit at which the control cables may be rigged and the vertical scale designates the correct tension in pounds for each temperature reading END 27 00 00 Page 1 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL MAINTENANCE PRACTICES regarding chain and cable tension control wheel movement and force and system friction Any time the control CONTROL COLUMN column has been removed and disassembled the following Figure 201 Refer to the applicable rigging procedures for details 1 Wheel 9 Collar 2 Collar Assembly 10 Collar Assembly 3 Column Torque Tube 11 Elevator Push Rod 4 Elevator Torque Arm 12 Connector 5 Elevator Torque Tube 13 Inner Column 6 Elevator Beli Crank 14 Sprocket 7 Elevator Torque Tube Support 15 Bearing Support 8 Bob Weight Assembly 16 Chain Control Column Figure 201 27 00 00 Page 201 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL precautions should be observed a When the taper pin just forward of the control wheel is to be installed use a light weight rawhide or nylon mallet to set the pin The small end of the tapered shank should be flush with or extend no more than 06 inch over the surface CAUTION The taper pin may crack the controt column torque tube if driven excessively b The procedure noted above shall apply to th
273. on connectors Loose connectors Tighten connectors 9 Overheating of inter cell con Loose or dirty inter celi con Disassembly ciean reassemble and pro nectors nectors perly torque inter cell connectors and ca pacity test 10 Foam or bubbling during Oil or grease contamination in Rep ace defective cells charging the electrolyte Low concentration of electro Recondition replace cells that continue to lyte foam 11 Below normal output Battery switch left ON Recharge and capacity test Voltage regulator set too low Recharge and capacity test Reset voltage regulator Internal connection links Torque recharge and capacity test loose External connector bumed or Clean or replace recharge and capacity pitted test Cell case current leakage Disassemble clean and recondition re place any defective cells and capacity test 24 31 00 Page 102 May 12 78 TROUBLE Battery will not hold its charge Battery will not come up to full charge Battery consumes water rapidly Electrolyte runs out of vent plugs Battery low Compound on top of battery meits Cell connector melted in center Battery freezes BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING LEAD ACID BATTERY PROBABLE CAUSE Battery is worn out Charging rate set too low Faulty battery _Voltage regulator set too high Electrolyte level too high Excessive charging rate Vent caps loose or broken Stand
274. or Petrolatum or Anti Seize 580 White Lead Base Oxygen Tetrafiuoroethylene Tape MIL T 27730 Johnson and Johnson Inc Permacel Div U S Highway 1 New Brunswick New Jersey 08901 Turbocharger inlet Probe Anti Seize Compound MIL A 907D Anti Seize Compound C5A Fel Pro Inc 7450 McCormick Skokie Illinois CHART 202 CONSUMABLE MATERIALS Only the basic number of each Military Specification is included in the Consumable Materials Chart No attempt has been made to update the basic number with the letter suffix that designates the current issues of the various specifications Vendors that are listed as meeting the Federal and Military Specifications are provided as refererice only and are not specifically recommended by Beech Aircraft Corporation consequently any product conforming to the specification listed may be used The products listed below have been tested and approved for aviation usage by Beech Aircraft Corporation the vendor or by compliance with the applicable specifications Other products that are locally procurable which conform to the requirements of the applicable Military Specification may be used even though not specifically included herein It is the responsibility of the operator user to determine the current revision of the applicable Military Specification prior to usage of that item This determination may be made by contacting the vendor of a specific item ITEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS
275. or switch to allow the blower to be selected without cycling through the opposite mode The mode switch controls both the heating and cooling systems however each system operates independently of the other In the manual heat position the switch bypasses the automatic Cabin heat controls and allows maximum heat output However the heater output in the manual position is limited by a heater cycling switch In the automatic heat position a temperature control rheostat placarded CABIN TEMP INCREASE be set for the desired cabin temperature Outlet air velocity may be changed in either MANUAL HEAT or AUTO HEAT mode by moving the VENT BLOWER switch located in the copilot s LH subpanel to either the or LO position MODE SWITCH Cabin Temperature Controls Figure 1 HEATER OPERATION a To place the heating system in operation select an operational mode either MANUAL HEAT or AUTO HEAT b If the AUTO position is chosen set the control rheostat for the desired heat The heater is now set up for normal operation providing thermostatic temperature regulation c IF MANUAL heat control is desired or required by a malfunction in the AUTO system move the switch to the MANUAL position This removes the automatic controller and the sensing elements from the control system The heater will then cycle continuously by the preset integral heater cycling switch d The CABIN AIR control which regulates the amount of outside
276. or airplanes originally equipped with units produced by Collins Communications Components Corporation a Place the RM OFF ON switch on the ELT in the OFF position b Disconnect the antenna cable and the remote switch wiring if installed and remove the ELT from the airplane c Remove the screws which hold the mounting base on the transmitter and remove the base d Remove the old battery and dis connect the electrical connector Discard the old battery WARNING DO NOT discard the battery in fire NOTE Inspect for and properly treat any corrosion in the area when the battery is replaced e Connect a fresh battery and install it in the compartment f Replace the base and screws g Install the transmitter in the airplane and attach the antenna cable and remote switch wiring if installed 25 60 00 Page 201 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL h The new replacement date should be marked on the ELT in a visible area This will aid in future inspections of the ELT This date is 50 of the useful life of the battery as defined by the battery manufacturer NARCO BATTERY REPLACEMENT a Place the ARM OFF ON switch on the ELT in the OFF position b Disconnect the antenna cable from the ELT Disconnect the remote switch wiring if installed from the terminals on the ELT Unlatch the mounting strap remove the ELT from the airplane Extend the portable ante
277. or maximum temperature control and to reduce the load on the heating and air conditioning system the intercooler temperature controls should be positioned in the closed position when the air condition system is in the HEAT mode and in the position when in the COOL mode AFT PRESSURE BULKHEAD 2 CONTROL VALVE 60601 74 Pressurization System Figure 1 END 21 10 00 Page 1 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL COMPRESSION MAINTENANCE PRACTICES INTERCOOLER REMOVAL a Remove the fiberglass air intake duct located on the lower forward side of the wing stub b Remove the skin panel under the air intake duct c Loosen the clamps attaching the flex duct on each end of the intercooler d Loosen the set screw and remove the push pull control cable Remove the three lower screws and the upper bolt attaching the intercooler to the outboard wing stub rib f Remove the intercooler through the bottom access opening INTERCOOLER INSTALLATION a Position the intercooler in place through the bottom access opening b Install the three lower screws and the upper bolt attaching the intercooler to the outboard wing stub rib c Attach the push pull control cable and tighten the set screw d Attach the flex duct on each end of the intercooler and tighten the clamps e Install the skin panel under the air intake duct f install the fiberglass air
278. or the benefit of owners and operating conditions operators in the form of two classes of Service Bulletins MANDATORY Red Border Fn the final analysis it is the responsi Service Bulletins are changes bility of the owner or operator to ensur inspections or modifications that could that all previously issued Class I and I affect safety The factory considers Service Instructions and Beechcraft Ser compliance with these Service Bulletins wice Bulletins which are pertinent to hi mandatory OPTIONAL No Border Service particular operation are complied with Bulletins cover changes modifications improvements or inspections which may NOTE benefit the owner Due to the wide range of information covered by the OPTIONAL In addition to the inspections Service Bulletin each owner or operator prescribed by this schedule the is responsible for conducting a thorough altimeter instrument and static review of each Optional Service Bulletin system and all ATC transponders to determine if compliance is required MUST be tested and inspected at based on the applicability of the OPTIONAL 24 month intervals in compliance with the requirements specified in FAR Part 91 100 HOUR INSPECTION A OPERATIONAL INSPECTION INSP STARTERS Check for proper operation unusual noises and dragging Check starter energized light if installed and or loadmeter to ensure starter disengage ment when the starter switch is released C
279. or the magnetic controller amplifier cardinal points 13 Cardinal headings in Controller amplifier im Calibrate for the magnetic accurate properly adjusted cardinal points 22 11 00 Page 102 Oct 27 75 TROUBLE ROLL AXIS Cont d 13 14 15 16 17 18 19 20 21 22 Cardinal headings accurate Cont d Cardinal headings accurate but intermediate headings inaccurate Insufficient or no control in CAP and TRK modes Localizer approach is either sluggish or too sensitive No electrical output left or right on controller amplifier test jacks Output only one way on controller amplifier test jacks No output on HDG mode on controller amplifier test jacks Heading output on two reciprocal headings but not op the other two O output when in CAP TRK or APP mode with nav signal Output voltage in CAP mode decays to O voltage BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING NEW MATIC AUTOPILOT Cont d PROBABLE CAUSE Leak in servo system Low primary pressure Faulty heading sensor Faulty controller amplifier Faulty controller amplifier Faulty omni converter Insufficient signal from omni NAV SENS improperly adjusted LOC GAIN is set high or low No At input or improperly grounded Defective controller amplifier or power supply Defective controller amplifier Defective control
280. ot use thinner or aromatic abrasive cleaners to clean the windows as they will damage the surface of the plastic Aliphatic naphtha and similar solvents are highly inflammable and extreme care must be exercised when used CHART 201 THREAD LUBRICANTS The vendor products appearing in this chart have been selected at random to help field personnel determine products conforming to the 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 SYSTEM MATERIAL SPECIFICATION VENDOR PRODUCTS Fuel Petrolatum VV P 236 Oil Manifold Pressure Air Pressure oline and Oil Resistant Lubricating Grease Gas MIL G 6032 Anti Seize White Lead TT A 580 L 237 Lehigh Chemical Co Chestertown Maryland Rockwell 950 Rockwell Mfg Pittsburg 8 Pa Royco 32 Royal Lubricants Co Hanover New Jersey Deicer Static Pitot Armite Product Armite Labora Base tories Los Angeles California Autopilot Pipe Threads Anti Seize White Lead JAN A 669 Only Base Brakes Hydraulic Fluid or Anti MIL H 5606 or Seize White Lead Base 580 12 20 00 Page 204 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 201 Cont d THREAD LUBRICANTS SYSTEM MATERIAL SPECIFICATIONS VENDOR PRODUCTS Air Conditioner Anti Seize Graphite MIL T 5544
281. oted that such a loss of capacity is quite common in batteries after prolonged use in the aircraft a Vented 19 cell 24 voit nickel cadmium batteries will normally be charged at 28 5 volts in the shop when charging with a constant potential voltage Note that charging a 19 cell battery at 28 5 volts is equivalent to charging each cell at 1 50 voits The initial charging current may be as high as 10 times the ampere hour rating of the battery depending on the amount of charge already in the battery The high initial current wil not damage the battery but the charging equipment shouid have an inherent current limiting capability or be provided with overload protection b The time required to charge will depend primarily on the current delivery capability of the charging unit The lower the charging current the longer the time required to charge If the battery does not suffer from temporary loss of capacity nearly full charge approximately 90 percent of rated capacity may be restored within 1 hour at 28 5 volts charging potential provided the charging equipment is also capable of delivering current equal to 2 to 3 times the ampere hour rating of the battery See Figure 202 CAUTION When a battery is connected to a constant potential charging source the initial high charging current will damage any 0 25 or 0 50 ampere scale ammeter connected in series with the battery c An ammeter with a range of zero to 25 or zero to 50
282. oughen ali scratches with nylon pad to insure a satisfactory paint base 4 Reclean the roughened surface with solvents to ensure removal of ail hand prints and dirt APPLICATION OF EXTERIOR PAINT ON ALUMINUM SKINS a Prime surfaces with wash primer 25 Chart 207 91 00 00 Mix only enough primer for use within an eight hour priod Primer mixed longer than eight hours must be discarded b Apply one coat of wash primer Keep air pressure at a minimum to preveat overspray NOTE Temperature and humidity will effect drying time of the primer it should dry at least 15 minutes before recoating the surface test surface with light fingernail pressure 20 00 00 Page 204 May 12 78 c Proceed to prime with a wet coat of MIL P 8585 zinc chromate primer 26 Chart 207 91 00 00 thinned one part primer and two parts toluol A heavy hiding coat of this primer is not desired and will impair performance d exterior surfaces are now ready for color coat e Spray on two thin topcoats of enamel EXTERIOR PAINT TOUCH UP REPAIR ENAMEL a Mask around the skin containing the damaged area b Remove any loose edges of paint by using a high tack adhesive tape around the edge of the damaged area c Using a coarse sandpaper fair the edge of the damaged area with the metal When the edge of the paint begins to feather into a smooth joint use a fine grade of sandpaper to eliminate the sand scratches left by the
283. ould indic ate a constantly decreasing charge current until the battery is charged When the loadmeter appears to stabilize see NOTE in condition 2 below turn the battery OFF while END observing the loadmeter for load change If the load change is satisfactory and the light has gone out the battery is charged and the system is operating properly 2 Battery is charged and is being excessively overcharged if the loadmeter stabilizes and indicates an unsatisfactory load change when the battery is turned OFF the battery is overcharging excessively and the light should not have gone out Check the battery and charging circuit for condition and proper operation NOTE As the battery approaches full charge the charge current may decrease slowly enough that the loadmeter would appear to stabilize before the charge current has decreased enough for the light to go out In the event of doubt as to the amount of charge current after the loadmeter appears to have stabilized an ammeter can be integrated into the charging circuit Install the ammeter and check the charge current as follows a An ammeter that will indicate approxi mately 10 amperes lead lines that wili reach from the battery relay to the pilot s compartment and an on off switch for the ammeter leads will be required b Wire the on off switch into one of the leads and connect the leads to the ammeter c Connect the negative side of the amme ter to the battery s
284. ox installation 203 STALL WARNING SYSTEM 27 60 00 1 Description and Operation 1 Troubleshooting 101 Maintenance Practices 201 Stall Waming Indicator Removal 201 Stall Warning Indicator Installation 201 Stall Warning indicating System Adjustment 201 GUST LOCK 27 70 00 201 Maintenance Practices 201 END 27 CONTENTS Page 2 Sep 20 85 16 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL DESCRIPTION AND OPERATION The flight controls with the exception of the flaps are conventional cable operated surfaces requiring no power assistance for normal contro by the pilot or copilot The aileron elevator and rudder have cable operated flight adjustable trim tabs The flaps have electrically powered actuators controlled by a switch on the subpanel Positive stops on the control surface bell cranks limit their travel while travel stops secured on the tab cables limit the trim tab movement Since the control cables can be disconnected at the turnbuckles each cable has one right hand and one left hand threaded cable end Cable routing off the pedestal contro column and actuator drums is shown in Figure 201 of 27 10 00 27 20 00 and 27 30 00 EFFECT OF TEMPERATURE UPON CABLE TENSION Graphs specifying the correct maximum and minimum cable tension permissible for the various controls appear on the individual rigging control system illustrations The graphs provide rigging limits at temperatures varying fr
285. p actuator rod end by removing the attaching bolt and nut b With power on run the actuator in to its internal limit and loosen the rod end check nut c With the air scoop faired to the nacelle adjust the rod end to the attaching bolt but do not secure the actuator to the air scoop at this time Tighten the rod end check nut d Manually raise the air scoop 1 9 inches above the top of the nacelle and hold this position while adjusting the switches i FLIGHT POSITION GROUND POSITION CONDENSER BLOWER A x V 60 426 1A Air Scoop Figure 202 21 50 00 Page 203 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL e Loosen the attaching screws and move the switches in their slotted mounts until they actuate a distinct click is audible in the following order the extend switch actuates first when the air scoop moves up from the closed position the retract switch actuates first when the air scoop moves down from the ground position Secure with the attaching screws f Because the ground position is automatically achieved by the internal limits of the actuator no adjustment is needed g Install the actuator rod end to the attaching bolt and secure the nut h Check for proper operation CONDENSER BLOWER REMOVAL The condenser compartment is located aft of the right nacelle firewall a Remove the screws securing the skin covering the condenser compartment Position the air scoop and ramp vertically to re
286. place Repair or replace any damaged hardware and capacity test Charge and capacity test Replace defective cell and capacity test Clean the battery recondition adjust the electrolyte level and capacity test Adjust voltage regulator of airplane Clean celi Clean cell replace or tighten vent cap Replace ceil clean battery 24 31 00 Page 101 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING NICKEL CADMIUM BATTERY Cont d TROUBLE PROBABLE CAUSE REMARKS 4 cases distorted Excessive charge rate Clean the battery recondition adjust the electrolyte level and capacity test Adjust voltage reguiator of airplane Cell with internal short Replace defective celi recondition and ca pacity test Plugged caps minor ex Disassemble replace defective parts plosion clean the battery recondition and capacity test 5 Unequal voltages among Cells unbalanced Equalize cell voltages perform full ca cells pacity discharge cycle and capacity test 6 Foreign matter within celis impure or acid contaminated Such cells will not normally respond to water charging They will show up as unba lanced cells and must be repiaced 7 Frequent addition of water Unbalanced cells Equalize cell voltages Leaky or defective cells dam Reptace defective parts and inspect for age to O ring or vent cap electrolyte leakage Clean recondition and level electrolyte 8 Burn marks
287. pm c Make all necessary adjustments before replaci the access panel 24 30 00 204 12 78 2 TROUBLE No power indicated with bat tery master switch ON Power on with master switch in OFF position Apparent loss of capacity Complete failure to operate 3 Excessive spewage crystal line deposits on outside of cells BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING BATTERY SYSTEM PROBABLE CAUSE Battery discharged or defec tive Open circuit between battery and master switch Master switch defective Defective relay Master switch defective Relay contacts stuck TROUSLESHOOTING NICKEL CADMIUM BATTERY Cells unbalanced Electrolyte level too low Charging rate too low in air plane Too little usage or shallow dis charges Loose or broken lead Loose or disengaged termi nals in battery Battery not charged Cell open internally Excessive charge rate Electrolyte level too high Vent caps loose or broken Cracked cell case a REMARKS Recharge or replace battery Check continuity Check switch for operation Check relay operation Check switch for operation Check and repiace relay if necessary Egualize cell voltage by performing full ca pacity discharge cycle Charge adjust electrolyte level and ca pacity test Check and adjust airplane charging system See a above Repair or re
288. pter 36 Repiace valve See System Block Diagram Figure 2 fun check for shorts Replace pressure switch Replace valve TROUBLE PITCH AXIS Cont d 8 System will not maintain trimmed configuration even though centered electrically 9 System will not respond to airspeed changes 10 System will not respond to up command adjust ment 11 System will not respond to altitude gain adjust ment 12 Aircraft has long term oscillation about pitch axis with altitude hold OFF 13 Aircraft has short term oscillation about pitch axis 14 Aircraft oscillates with altitude hold ON 15 Aircraft does not return to altitude when displaced BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING NEW MATIC AUTOPILOT Cont d PROBABLE CAUSE REMARKS Servo control valve not a Disconnect electrical power pneumatically centered Center valve pneumatically by use of differential gage to 04 in Hg Leak in servos or improperly b Check for leaks and rig rigged Leak in pitch altitude c Replace sensor sensor Primary vacuum pressure a Adjust pressure as outlined not set properly in Chapter 36 Pitot pressure inadequate b Check pitot plumbing Decay rate improperiy C Adjust as required adjusted Defective pitch altitude a Replace pitch altitude amplifier amplifier No EVT potentiometer b Replace turn coordinator Pitch altitude amplifier a Adjust as required limit
289. r 6 Continuous control wheel Turn coordinator faulty Replace turn coordinator oscillation in smooth air Improper gyro speed or Adjust system pressure as excessive pressure in outlined in Chapter 36 system 7 No turns or turns in one Faulty turn coordinator Replace turn coordinator direction only in response to turn contro or on all Faulty controller amplifier Replace controller amplifier modes of navigation coupler operation 8 Aircraft rolls in one Servos improperly phasud See System Block Diagram direction only either Figure 2 left or right Turn coordinator not Plumb per System Block plumbed properly Diagram Figure 2 9 Aircraft turns in the Nav input signal reversed Reverse connectors to VOR wrong direction in and TRK modes 10 No aircraft response from Faulty turn coordinator Replace turn coordinator navigation coupler in any gyro mode ground check shows electrical Obstruction in pressure lines Check for foreign matter 11 Aircraft fails to turn Faulty magnetic heading Replace magnetic heading to and hold magnetic sensor sensor headings Faulty heading selector Replace controller amplifier resolver Faulty controller amplifier Replace controller amplifier 12 Magnetic heading con Heading sensor misaligned in Check for proper installation sistently high or tow aircraft Heading azimuth dial shifted Tighten screw and re on shaft calibrate Improper adjustment of Calibrate f
290. r however a defective component will give a definite indication EENE xc ctt rcm NI S E 2 2 500 Sai ne li Ec IHE RGR 122 400 RESISTANCE OHMS 300 Sunes GI zl dcn EE 2 S Ei JJ c m eee Hit 100 TEMPERATURE F Temperature Resistance Curve for Cabin Sensing Element Figure 203 21 40 00 Page 203 Nov 2 73 i BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL E e 200 TETI cc s Hu E 160 140 RESISTANCE OHMS 120 H 100 BH so TEMPERATURE F Temperature Resistance Curve for Heater Discharge Sensing Element Figure 204 a Using the graph in Figure 203 determine the correct resistance for the cabin air sensing element Disconnect wire number H78E18 from terminal 8 of the 2 temperature control box terminal strip Measure the resistance between the terminal on wire number H78E18 and terminal 6 on the temperature control box terminal strip Disconnect wire number H75B18 from terminal 5 of the temperature contro box terminal strip Measure the resistance between the terminal on wire number H75B18 and terminal 10 on the temperature control box terminal strip If the measured resistances do not correspond to the value obtained from the graph the cabin air sensing element is defective NOTE Do not reinstali the disconnected wires on t
291. r Aircraft In Amps 20 00 13 00 0 06 275 00 2 00 1 50 0 85 0 50 2 50 0 09 0 17 1 18 1 75 1 20 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 25 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATI 25 EFFECTIVITY 1 Nov 20 8 25 CONTENTS 1 Nov 20 8 25 00 00 201 Apr 18 8 202 Apr 18 81 25 60 00 1 Nov 20 8 201 Nov 20 8 202 Nov 20 8 203 Nov 20 8 204 Nov 20 8 END 25 EFFECTIVITY i Page 1 A18 20 81 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 25 EQUIPMENT FURNISHINGS TABLE OF CONTENTS SUBJECT CHAPTER PAGE 25 00 00 General Maintenance Practices eee teks Bake Se et Rhy 201 Flight Compartment Seat Removal Svr Flight Compartment Seat Installation 201 Flight Compartment Seat Back iE ex det cde kia He te 232 ce MEVS 201 Passenger Seat Removal 2 a LR x Mee Je 201 Passenger Seat Installation V Wo NS eS Mae Ro Dee qus C NT AU D eO 201 Passenger Seat Back Adjustment Se ue tae de ee a PEE 201 25 60 00 Emergency Description And Operation Be ea hs ee cee YE 2 1 Emergency Locator Transmitter Kum dio db PE uo a Eg Sobo 1 Emergency Maintenance Practices 201 Emergency Locator Transmitter Maintenance CI P EE Collins
292. r Removal Motorized Cabin Altitude Controller Installation Motorized Cabin Altitude Controller Adjustment Motorized Pressurization Test Procedure PAGE 2 a 101 101 107 109 201 201 201 201 201 201 201 201 201 201 201 201 201 202 202 202 203 203 203 203 21 CONTENTS Page 1 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 21 AIR CONDITIONING TABLE OF CONTENTS Contd CHAPTER SECTION SUBJECT SUBJECT PAGE PRESSURIZATION CONTROL Cont d Maintenance Practices P 308 and after 21 30 00 204 Outflow Valve and Safety Valve Removal 204 Outflow Valve and Safety Vaive Installation 204 Outflow Valve and Safety Valve Adjustment 204 Outflow and Safety Valve Cieaning 204 Safety Valve Filter and Orifice Cleaning 205 Functional Test of Outflow and Safety Valve P 308 and after 205 Outflow Valve Flight Check 205 Safety Valve Ground Check 205 Cabin Altitude Controller Removal 205 Cabin Altitude Controller Installation 205 Cabin Pressurization Controller Adjustment 206 Cabin Altitude Controller Filter and Orifice Cteaning 206 Auxiliary Volume Tank Removal 206 Auxiliary Volume Tank Installation 206 Pressurization Test Procedure P 308 and after 206 Cabin Pressurization Leakage Test P 4 and after 207 Test Eguipment P 4 and after 207 Test Procedure 4 and after 208 HEATING 21 40 00 Description and Operation 1 Heater Control System 1 Heater Operation 1 Maintenance
293. r close breaker off circuit breaker Low voltage supply b Apply external power supply Attempt to start heater Fuel cut off from tank c Turn on manual shutoff valve if used or master solenoid Suction leak ahead of pump d Secure all fittings Insufficient fuel pressure e Low or no current to fuel pump Check for operation of pump and remove for repairs if not operating Regulator not operating f Check for low pressure or replace properly regulator Fuel pump operating but not g Remove and repair or replace building up sufficient pressure fuel pump Restriction in fuel nozzle h Remove the nozzle and clean or orifice replace it Fuel heater solenoid not i Remove and check solenoid Replace Operating if faulty Fuel lines clogged or broken j Inspect all lines and connections it may be necessary to disconnect lines at various points to determine where the restriction is located Fuel filter clogged k Clean fuel filter element Ignition vibrator inoperative Replace vibrator check for defective radio noise filter Manual reset limit overheat m Press reset button firmly and switch open recheck to determine reason for switch opening Combustion air pressure switch n Check for low blower output due open Defective switch or low to low voltage and correct it lf combustion air blower output switch is defective replace it Cycling switch open o Replace if defective Duct
294. r conditioning is not in use flight air scoop extended about 2 inches above the nacelle and ground air scoop fully extended When the air conditioning is turned on a switch incorporated on the landing gear selects air scoop position gear down the air scoop will open to the ground position gear off the ground the air scoop will open or lower to the flight position The condenser fan which is wired in circuit with the landing gear uplock switch operates only when the air conditioning mode is selected and the airplane 15 on the ground The air conditioning system is similar to many home and automotive units and consists of six major components The belt driven compressor which is coupled by a magnetic clutch compresses the refrigerant to a high pressure high temperature gas This gas passes through the condenser where cooling air removes heat from the gas condensing it to a liquid state The liquid is then passed through the receiver dryer where any moisture or foreign material is removed from the system The refrigerant flows to the expansion valve where it is metered into the evaporator at a rate which allows all the liquid to return to a gas The heat required for evaporation is absorbed from the cabin air passing over the evaporator coils After passing through the evaporator the refrigerant returns to the compressor at a reduced pressure For partial cooling a hot gas bypass valve allows a portion of the gas to
295. r cracked or broken lenses and replace buibs as necessary LANDING LIGHTS Check for security and operation Replace lens and bulbs as necessary FUEL BOOST PUMPS AND FUEL LINES Check for condition security and leaks Check lines for signs of chafing or cracks FUEL SELECTOR VALVE Check for security operation and leakage FUEL STRAINERS Inspect clean as outlined under the heading ENGINE FUEL FILTERS AND SCREENS Chapter 12 10 00 of this Maintenance Manual 5 20 00 Page 213 18 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL SKIN Inspect skins for deformation cracks and loose or missing rivets If damage is found check adjacent structure STRUCTURE Check for cracks and deformation Check for loose or missing rivets and concealed damage CABLES PULLEYS AND PRESSURE SEALS Check the flight control components cables and pulleys Replace control system components push rods turnbuckles end fittings castings etc that have bulges splits bends or cracks Check control cables pulleys and associated equipment for condition attachment alignment clear ance and proper operation Replace cables that have bro ken strands or evidence of corrosion Check cables for proper tension at the first inspection and every 100 hours thereafter PRESSURIZATION CONTROL VALVES On airplane serials 4 thru P 307 check the cabin pressurization safety valve and
296. r enters the combustion chamber tangent to its surface and imparts a whirling or spinning action to the air This produces a whirling flame that is stable and sustains combustion under the most adverse conditions because it is whirled around itself many times Therefore ignition is continuous and the combustion process is self piloting The burning gases travel the length of the combustion tube flow around the outside of the inner tube pass through cross over passages into an outer radiating area then travel the length of this surface and out the exhaust Ventilating air passes through the heater between the jacket and combustion tube assembiy outer surface and through an inner passage in the assembly Consequently ventilating air comes into contact with two or more heated cylindrical surfaces VIBRATOR REMO VAL a Remove the necessary access panels in the nose compartment to reach the ignition unit on the heater assembly NOTE Measure the distance the vibrator protrudes out of the ignition assembly to determine when a new unit is inserted properly b Grasp the vibrator and with slight back and forth movement pull it straight out of the ignition unit NOTE For a friction grip it may be necessary to use a piece of masking or friction tape around the exposed portion of the vibrator 21 40 00 Page 202 Nov 2 73 VIBRATOR INSTALLATION a To install a new vibrator carefully rotate the new vibrator until the inde
297. re and loosen the clamp on the heater exhaust shroud located under the heater f Remove the clamps located at each end of the heater g Lift the heater up and out of the aircraft HEATER INSTALLATION a Position the heater in the aircraft taking care to guide the fuel drain through the grommet in the skin and the exhaust shroud through its opening b Install the clamps at each end of the heater c Position the clamp on the heater exhaust shroud located under the heater and secure and safety d Install the fuel line to the heater Slide the boot down the fuet line and secure the clamps around the boot e Install the wire harness to the heater f Connect the duct to the combustion air blower and secure the clamps g Install the nose baggage compartment floorboards COMBUSTION AiR BLOWER REMOVAL a Remove the heater b Tag the wires and disconnect the wiring from the combustion air blower and combustion air controller c Loosen the clamps and disconnect the ducts on the combustion air blower d Remove the attaching screws from the combustion air blower and the two controller mounting brackets e Remove the combustion air blower and controller from the aircraft as a unit COMBUSTION AIR BLOWER INSTALLATION a Install the combustion air blower and controller in the aircraft as a unit b Instali the two controller mounting brackets and secure the combustion air blower with the attaching screws Ins
298. reciably with age However there can be a temporary 24 31 00 Page 205 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL loss of capacity under certain duty cycles A temporary loss of capacity is normally an indication of imbalance between ceils Imbalance can be caused by differences in temperature charge efficiency self discharge rate etc The purpose of reconditioning is to restore a battery to its full capability and to prevent premature damage and failure Effective reconditioning requires specific procedures for certain periods of time No step in the procedure can be eliminated nor can any time period be shortened and still yield effective battery reconditioning FREQUENCY OF RECONDITIONING Due to the variables involved in usage it is impossible to establish a time interval for reconditioning that will cover all batteries Until service experience dictates otherwise a visual and electroiyte check of the battery should be made after the first 50 hours of flight If the condition of the battery is normal and the level of electrolyte in the battery is satisfactory schedule the initial reconditioning at 100 hours Repeat the reconditioning procedure outlined below at 100 hour intervals until servicing experience justifies a change NOTE The log of battery services performed should be evaluated to determine the need for servicing the battery at the above recommended intervals or extending the intervals Accurate
299. reservoir for security attachment open vent proper fluid level and for leaks ELECTRICAL WIRING AND EQUIPMENT Inspect electrical wiring and associated equipment and accessories for con dition fraying and attachment HEATER FUEL SYSTEM Check lines for connection and chafing HEATER DUCTING AND WIRING Check security and chafing AIR CONDITIONER EVAPORATOR Check for condition and attachment OXYGEN If applicable Inspect oxygen cylinder and valves for condition and security of attachment Check the valves for proper condition TAXI LIGHT Check for security and operation Replace if necessary 11 BAGGAGE DOOR Check for condition and proper T Ia UME A18 5 20 00 Page 217 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL F NOSE SECTION Cont d INSP 12 PITOT MAST Check for condition and obstruction heating if applicable G REAR FUSELAGE AND EMPENNAGE INSP 1 SKIN Check for deformation cracks and obvious damage Check for loose or missing rivets If damage is found check adjacent structure Check STRUCTURE Inspect the two most aft bulkheads for cracks distortion loose rivets or other obvious dam age 3 CABLES PULLEYS AND TURNBUCKLES AND PRESSURE SEALS Check the elevator and rudder flight control components cables and pulleys Replace control system components push rods turnbuckles end fittings castings et
300. ressure bulkhead above the pilot pedals It also regulates the cabin temperature variations monitored at the sensing units The sensing units are located in the ram air inlet heater outlet duct and forward of the two pressure contro valves on the rear pressure bulkhead When placed in the MANUAL COOL HI position the switch bypasses the automatic controls and allows maximum air conditioning output The maximum output is limited by an evaporator thermal switch and an overpressure switch The MANUAL COOL LO position allows a hot gas bypass valve if installed to be cycled on and off by a timer The bypass valve regulates the flow of refrigerant to the condenser allowing partial cooling of the cabin On serials P 123 P 127 and after a MANUAL COOL position replaced the MANUAL COOL HI and LO positions on the mode selector switch Two BLOWER positions are placed on the mode switch to allow the blower to be selected without cycling through the opposite mode The air scoop and ramp assembly located in the upper RH nacelle controls the air circulation through the condenser compartment and is completely automatic The air scoop and ramp assembly has three positions closed when the air conditioning is not in use flight air scoop extended about 2 inches above the nacelle and ground air scoop fully extended When the air conditioning is turned on a switch incorporated on the landing gear selects air scoop position gear down the air
301. ricated from 1 8 inch diameter rod a nonferrous material which is not subject to corrosion is preferred Notches cut 1 10 inch apart will aid in visually detecting oil depth k Install the oil plug and O ring and check for leaks using a flameless leak detector l Unseat both the suction service valve and the discharge service valve and turn to the full aft position m Remove the service gages and install the caps to the service ports n The aircraft may now be returned to service EVAPORATOR AIR FILTER REPLACEMENT The evaporator air filter should normally be replaced annually Actual replacement may be required more often due to extremely dusty operating conditions a Remove the necessary equipment in the nose compartment to gain access to the floorboards forward of 6 INCH SCALE roga PLUG WELL GASKET HEATER COMBUSTION HEAD Heater Spark Plug Figure 203 3 16 TO 7 32 SPARK PLUG GAP GROUND ELECTRODE 60 153 1 12 10 00 Page 204 Nov 2 73 the pressure bulkhead b Remove the screws securing the top of the evaporator filter access plate c Cut the cord securing the filter to the evaporator plumbing d Remove the old filter e When installing the new filter be sure the reinforced backing of the filter is placed against the evaporator coil COMPRESSOR BELT TENSION ADJUSTMENT After 36 to 48 hours operating time a new belt will stretch to its normal operating len
302. ries of the Duke which do not use the optional motorized controller The optional motorized controller is utilized by the various series of the Duke as either a factory installed unit or upon compliance with Service instructions 0479 453 The motorized controller is similar to the manual controller except in the method of changing cabin altitude Both controllers employ an aneroid bellows controlled valve to allow a calibrated amount of air flow to the control diaphragm of the differential control valve PRESSURIZATION SYSTEM OPERATIONAL CHARACTERISTICS a Power Changes Normal application of power from a standing start or taxiing will produce a momenta fluctuation of the pressure level A momentary fluctuation of 1 000 fpm read on the cabin rate of climb indicator is normal and should provide little or no passenger discomfort This variation is minimized by slower application of power More rapid application of power will cause a higher momentary fluctuation and is also considered normal b Lift Off As the airplane leaves the ground a momentary cabin pressure fluctuation of as high as 1 500 fpm 1 000 fpm for airplane with a dashpot installed on CABIN ALTITUDE AND PRESSURE DIFFERENTIAL INDICATOR e PRESS TO TEST T SWITCH MANUAL CABIN ALTITUDE CONTROLLER PRESSURIZATION DUMP SWITCH 60 453 11 safety valve is considered normal and again will rarely produce passenger discomfort c Altitude Control
303. rim Tab Actuator Removal 203 Trim Tab Actuator Installation 204 Checking Trim Tab Free Play 204 ELEVATOR AND TAB 27 30 00 201 Maintenance Practices 201 Elevator Removal 201 Elevator Installation 201 Elevator Cable Removal 201 Elevator Cable Installation 201 Elevator Control System Rigging 201 Trim Tab Cable Removal 203 Trim Tab Cable Installation 204 27 CONTENTS Page 1 A16 Sep 20 85 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 27 FLIGHT CONTROLS TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE ELEVATOR AND TAB 27 30 00 Maintenance Practices Cont d Trim Tab Rigging 204 Trim Tab Actuator Removal 204A Trim Tab Actuator Installation 204A Electric Trim Tab Actuator Removal 204A Electric Trim Tab Actuator Installation 204A Electric Trim Tab Cable Installation 204A Electric Trim Tab Actuator Magnetic Clutch Removal 205 Electric Trim Tab Actuator Magnetic Clutch installation 205 Electric Trim Tab Actuator Magnetic Clutch Torque Test 205 Checking Trim Tab Free Play 206 FLAPS 27 50 00 1 Description and Operation 1 Maintenance Practices 201 Flap Removal 201 Flap Instaliation 201 Flap Track Roller Installation 201 Control System Rigging 201 Functional Ground Test 201 Position Transmitter Adjustment P 4 through P 246 201 Position Indicator Lights Adjustment and Functional Test P 247 and after 203 Actuator Removal 203 Actuator Installation 203 Motor Gearbox Removal 203 Motor Gearb
304. roller lamp wires c Remove the three screws securing the cabin altitude controller to the printed circuit board of the RH inboard subpanel d Remove the cabin altitude controller CABIN ALTITUDE CONTROLLER INSTALLATION a Install the cabin altitude controller in the printed circuit board of the RH inboard subpanel Secure with the three screws b Remove the caps and reinstall the plumbing as tagged during removal Reconnect the wiring to the controller lamps 21 30 00 Page 205 Feb 22 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL c Install the edge lighted panel Secure with the screws Replace the knobs and handles CABIN PRESSURIZATION CONTROLLER ADJUSTMENT The cabin pressurization controller is preset at the factory Field adjustments and maintenance of the controller is not recommended In the event of a malfunction the cabin pressurization controller should be returned to Beech Aircraft Corporation in exchange for an Overhauled Exchanged unit e CABIN ALTITUDE CONTROLLER FILTER AND ORIFICE CLEANING The filter and orifice in the cabin attitude controller should be removed cleaned and inspected every 500 hours The filter may be removed and cleaned by the foilowing suggested procedure a Remove the filter assembly from the housing of the cabin altitude controller Do not lose the packing b Remove the retaining ring from the filter assembly housing Remove one screen the copper ribbon and
305. rsedes MIL G 6711 Lubricating Graphite Superseded by Item 12 Lubricating Grease Solvent Laminated Glass Cloth Resin Lubricating Grease Ufethane Primer Enco Andok B MIL F 9084 MIL R 7575 Aeroshell 7A VENDOR PRODUCTS Humble Co Houston Texas CRC 2 26 Corrosion Reaction Consultants Limeklim Pike Dresher Pa Trevano Coast Manufactur ing and Supply inc Box 71 Livermore California Uniglass United Merchants and Manufacturing Inc 1407 Broadway New York New York 10018 Laminac 4116 American Cyanamid Co Wallingford Connecticut Glidpol 1001 The Glidden Company 925 Euclid Ave Cleveland Ohio 44114 Shell Oil Co 50 West 50th Street New York N Y U S Paint Lacguer and Chemical Co 1501 N Belmont P O Box 8151 Wichita Kansas 67208 Ameron industrial Coating Division P O Box 2153 Wichita Kansas Ali ITEM 37 38 39 40 41 42 45 A14 MATERIAL Thread Locking Compound Penetrating Oil Lubricating Grease Cement Primer Cleaner Paint Stripper Corrosion Preventive Compound Lubricating Grease Primer Degreasing BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 202 Cont d CONSUMABLE MATERIALS SPECIFICATIONS Loctite Sealant Grade A Mouse Milk Kano Kroil MIL G 3545 EC2262 Locquic N Turco Metal glo No 3 Turco 4260 MIL C 16173 Grade 2 MIL G 7118 EC3911 VENDOR P
306. s RUDDER TRIM TAB ACTUATOR REMOVAL a Remove the access plate at the trim tab actuator b Remove the tail cone and the access plate beneath the RH horizonta stabilizer c Remove the access panel in the floorboard aft of the rear spar d Disconnect the tab control cables at the turnbuckles in the aft fuselage e Disconnect the tab actuator at the tab f Remove the aft chain and cable assembly from the actuator sprocket 27 20 00 Page 203 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL g Remove the bolt attaching the actuator to the actuator hinge Remove the actuator RUDDER TRIM TAB ACTUATOR INSTALLATION a Position the tab actuator on the actuator hinge and install the attaching bolt b Connect the actuator at the tab c With the rudder tab in neutral position the aft chain and cable assembly on the actuator sprocket so that the ends of the chain are equi distant at the sprocket centerline within 20 inch d Connect the tab control cabies to the turnbuckles in the aft fuselage e Rig the rudder tab control system f Install the access panel in the floor board aft of the rear spar Install the tail cone and the access plate beneatn the RH horizontal stabilizer h Instali the access plate at the trim tab actuator CHECKING RUDDER TAB FREE PLAY Visually inspect the rudder tab for damage security of hinge attach points and for tightness of the actuating system inconsista
307. s and proper indication EMERGENCY EXTENSION Check system for freedom of opera tion and positive engagement of the downlocks Check for unusual noise LIMIT SWITCH RIGGING Check for security and proper adjustment of the limit switches Refer to Chapter 32 30 00 for correct landing gear geartox internal clearance DYNAMIC BRAKING ACTION Verify proper operation of dynamic brake relay WARNING HORN Check for proper operation NOTE Downlock tension should be checked at the first 100 hour inspection and every 200 hours thereafter UPLOCK CABLE TENSION Check uplock cable mechanism for cofidition and security Check uplock cable for proper tension and for possible fraying DOWNLOCK TENSION MAIN GEAR Check for proper deflection force on the main gear knee joints 5 20 00 Page 223 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL i J LANDING GEAR OPERATION Cont d MECH INSP DOWNLOCK TENSION NOSE GEAR Check the downlock ten sion on the nose gear as outlined in Chapter 32 30 00 13 UPLOCK ROLLERS Check condition and clearance of uplock rollers per Chapter 32 30 00 and lubricate as outlined in Chapter 12 20 00 Check for binding SAFETY SWITCH Check for security proper rig and ation NOSE GEAR UP TENSION Check the up tension on the nose gear per Chapter 32 30 00 NOSE GEAR STEERING Check for condition and security
308. s are in place and secured with cotter pins STRUT FLUID LEVEL Check and maintain the proper hydraulic fluid level in the struts as outlined in Chap ter 12 20 00 STRUT AND A FRAME HINGE BOLTS Inspect for cracks and security of attachment I NOSE GEAR oo MECH INSP 1 WHEEL AND TIRE Check wheel for cracks and tire for wear damage condition and proper inflation Check wheel bearings for condition and wear 5 20 00 Page 220 Nov 20 87 ko a AT 5 GEAR DOORS ANG LINKAGE Check doors for damage and cracks to the structure and skins Check linkage for wear and cracks at the attach points Check for condi tion and security Determine that ali clevis retaining ae A18 NOSE GEAR Cont d BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL LANDING GEAR STRUT Inspect the shock strut and compo nents for cracks attachment proper inflation and evi dence of leakage ACTUATING LINKAGE Check for wear at attach points Check for cracks and security GEAR DOORS AND LINKAGE Check doors for damage and cracks to the structure and skins Check linkage for wear and cracks at the attach points Check for condi tion and security NOSE GEAR STEERING LINKAGE Inspect linkages for tightness condition and security Check linkage boots for condition SHIMMY DAMPER Check for condition and attachment Check attach points for cracks Check fluid level as ou
309. s below 70 F The paint will not cure at temperatures below 60 F BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL Dukes painted with urethane paints are finished with pre treatment wash primer urethane primer and a topcoat of urethane enamel The following procedures include cleaning paint stripping repaint preparation priming applying a urethane topcoat and an alternate method for small repairs not requiring paint stripping Careful observation of these procedures should result in a smooth hard glossy finish with firm adhesion for maximum life STRIPPING AND CLEANING URETHANE PAINT Because of their resistance to chemicals and solvents urethane paints and primers require a special paint stripper If a urethane stripper is not available a good enamel stripper may be used Removing the finish with such a substitute wili require several applications while working the stripper in with a stiff brush or wooden scraper a Mask around the edge of the skin or skins contain ing the damaged area Use a double thickness of heavy paper to prevent accidental splashes of paint stripper from penetrating the masking ki b Apply urethane stripper as indicated by the manu facturer s direction Try to stay approximately 1 8 inch away from the masking tape This will necessitate a little more cleanup upon finishing but will prevent damage to the finish on the next skin The stripper will not attack aluminum during the stripping process an
310. s disconnected i After the cabin pressure has again stabilized note the readings on the CABIN ALT and DIFF PRESS indicator Disconnect the true static air vent which is connected to the outflow valve Refer to step a of this procedure The DIFF PRESS indicator shall indicate a change that is no greater than 1 psi n Reconnect the static air vent to the outflow valve and disconnect and cap the true static air vent from the safety valve The DIFF PRESS indicator should again indicate a change that is not greater than 1 psi Reconnect the safety valve true static air vent o Reconnect the plumbing to the VACUUM fitting of the cabin pressurization controller The cabin altitude will return to the aititude selected on the cabin pressurization controller The cabin altitude as indicated on the CABIN ALT indicator should stabilize at an altitude within 500 feet of the selected cabin altitude p Rotate the cabin altitude selector to select an altitude that is approximately 500 feet above the fieid elevation After the cabin altitude has again stabilized reset the cabin pressurization circuit breaker Shut down the engines as described in the applicable Duke Pilot s Operating Manual q Remove the plate over the outflow and safety valves Remove the test plumbing installed in step above Reconnect the true static air vent tubes to the outflow valve and the safety vaive Reinstall the plate Tighten the bolts evenl
311. scoop will open to the ground position gear off the ground the air scoop will open or lower to the flight position The condenser fan which is wired in circuit with the landing gear safety switch operates only when the air conditioning mode is selected and the airplane i on the ground REFRIGERATIVE AIR COOLING SYSTEM The air conditioning system is similar to many home and automotive units and consists of six major components The belt driven compressor which is coupled by a magnetic clutch compresses the refrigerant to a high pressure high temperature gas This gas passes through the condenser where cooling air removes heat from the gas condensing it to a liquid state The liquid is then stored in the receiver dryer where any moisture or foreign material is removed from the system The refrigerant flows to the expansion valve where it is metered into the evaporator at a rate which allows al the liquid to return to a gas The heat required for evaporation is absorbed from the cabin air passing over the evaporator coils After passing through the evaporator the refrigerant returns to the compressor at a reduced pressure For partial cooling a hot gas bypass valve allows a portion of the gas to bleed off from the condenser cycling back through the compressor NOTE Beginning with airplane serials P 123 P 127 and after and prior airplane s having installed Kit Number 60 5006 the hot gas bypass valve line and suction a
312. serials equipped with plastic outflow valves use a beaded tube fitting and clamps to secure the plumbing Use water only as a lubricant on EVA tubing being installed over beaded tubing or fittings e Remove the caps and install the plumbing as tagged when the plumbing was removed f Install the plate over the outfiow and safety valves Secure it with the two AN4 5A bolts at top and bottom and the sixteen AN3 5A bolts Tighten the bolts 21 30 00 Page 204 Feb 22 80 evenly to a torque of 50 to 70 inch pounds for the AN4 5 and 20 to 25 inch pounds for the AN3 5A bolts WARNING The airplane must not be pressurized prior to installation of the plate g Reinstall the access door on the lower LI fuselage aft of the rear pressure bulkhead h Reinstall the upholstery panel OUTFLOW VALVE AND SAFETY VALVI ADJUSTMENT The outflow valve and the safety valve are each preset the factory to regulate the cabin pressurization to maximum differential pressurization of 4 6 1 psi Fiel adjustment of these valves is not recommended In th event of a malfunction the valves should be returned t Beech Aircraft Corporation in exchange for an Overhaulec Exchange unit OUTFLOW AND SAFETY VALVE CLEANING CAUTION The outflow and safety valves are preset at the factory and field adjustment is not recommended Any time the valve seal is broken the WARRANTY 6 months in duration is VOIDED Fluctuation of cabin pressure often
313. shoulder harnesses for proper operation condition and security of attachment Inspect floorboards for condition and seat attachment Check for operation of the seat stops OXYGEN Check the oxygen masks for cleanliness and stowage Check the system for leakage Replace any com ponent that is leaking VENTILATING SYSTEM Check all fresh air and heat outlet vents for proper movement and operation FUEL SELECTOR VALVE Inspect for security freedom of movement proper detent feel and condition Check for proper placarding FILTERS Replace individual instrument air filters EMERGENCY EXIT HATCH Check the emergency release han dle and latch assembly for proper operation Check that the hatch moves out freely Check the complete hatch assembly for condition and all moving parts for proper operation With the hatch installed check for proper latching and seal SYSTEM Check and drain water from the static ines 5 20 00 Page 216 Nov 20 87 Al BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL NOSE SECT ON SKIN Inspect skin for corrosion condition and loose or missing rivets If damage is found check adjacent structure STRUCTURE Check for corrosion cracks loose or miss ing rivets and concealed damage RADAR ANTENNA COVER Check the fiberglass for security attachment and cracks BRAKE FLUID RESERVOIR Check
314. side of the wing between wing stations 66 00 and 108 281 and ait of the second stringer aft of the front wing spar should be given a protective coating as described and then primed with zinc chromate a Mix Alodine 1200 or 1200S a product of Amchem Products Ambler Pennsylvania with water in a ratio of 3 to 4 ounces per gallon of water b Piace in a plastic container and allow to dissolve at least one hour Add 10 milliliters nitric acid per gallon of solution d Prepare the surface by wiping with Stoddard Sol vent or methyl ethyl ketone then scrubbing with a nylon abrasive pad to remove oxide films Rinse with water and 20 00 00 Page 207 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL repeat the above procedure until water will not bead on the surface After cleaning immediately treat the surface using a cheesecloth pad celiulose sponge or nylon brush to apply the solution with light pressure and continuous even motion On curved or inclined surfaces begin application at the tower edge of the work to minimize streaking Keep the surface wet with the solution for 1 to 3 minutes so that a continuous film is obtained with neither a grayish appearance nor a dark pow dery non adherent coating Generally a light coating rather than a heavier coating is preferable for a paint base espe cially for epoxy primers Streaks from brushing or rundown of excess solution are allowable as are sl
315. spray nozzle Replace at heater overhaul 5 10 00 Page 205 18 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE Cont d ITEM UTILITY SYSTEM Cont d Heater fuel shut off valve Combustion blower Combustion blower brushes Vent blower Vent blower brushes Condenser blower Condenser blower brushes Oxygen regulator Oxygen cylinder 3HT Oxygen cylinder 3A or 3AA Differential control valve P 4 thru P 307 Outflow valve 308 and after Safety valve P 4 thru P 307 Safety valve P 308 and after FLAPS AND FLIGHT CONTROLS Flight controls Aileron tab actuator Elevator tab actuator Rudder tab actuator Rudder pedal arm 5 10 00 Page 206 Nov 20 87 OVERHAUL OR REPLACE On condition On condition Every 500 hours On condition Every 500 hours On condition On condition Every 2000 hours or 48 months Hydrostatically test every 3 years replace every 24 years or 4 380 refills ICC regulation Hydrostatically test every 5 years no replacement dura tion Inspect every 100 hours replace on condition Perform functional test every 500 hours Inspect every 100 hours replace on condition Perform functional test every 500 hours On condition On condition condition On coridition On condition or at 2000 hours ATE BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL OVERHAUL AND REPLACEMENT SCHEDULE Cont d ITEM OVERHA
316. ssure differentia will exist across the inner diaphragms of both the outflow valve and the safety valve When the control chamber to atmosphere pressure differential is sufficient to overcome the force of the poppet valve return springs the poppet valves will open permitting air at atmospheric pressure to flow into the cabin counteracting the negative pressure differential Depressurizing the cabin for emergencies such as smoke in the cabin may be accomplished by placing the mode select switch in the DUMP position The normally closed solenoid 21 30 00 Page 6 May 30 75 air valve opens to connect the control chamber of the safety valve to the airplane vacuum system The safety valve poppet valve is thus opened permitting the cabin air flow to exhaust to the atmosphere without restriction When the airplane touches down after a pressurized flight the actuation of the RH landing gear safety switch will again energize the two solenoid air valves to open the safety valve poppet valve and to block the source of vacuum from thescabin air controller BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL VACUUM VALVE L AIRCRAFT T ELECTRICAL FILTER AND ORIFICE SYSTEM DIAL LIGHTS VACUUM AUXILIARY LOCKOUT SOLENOID VOLUME VALVE TANK 4 ELECTRICAL BUS AIRCRAFT VACUUM 4 NO AIRCRAFT TEE FITTING PRESSURIZATION SYSTEM SWITCH LANDING V TEST GEAR SAFETY o SWITCH o DUMP 2 SOLENOI
317. stematic battery maintenance program should be estab lished and carefully followed a The batteries should be removed from the airplane for service b A iog of the services performed on each battery should be maintained c The battery should be removed from the airplane and serviced after 100 flight hours or 30 days whichever occurs first If the ambient temperatures are above 90 F or the time between engine starts averages less than 30 minutes the duty cycle should be reduced d The log of battery services performed should be evaluated to determine the need to service the batteries at the above recommended intervals or to extend the intervals if justified Accurate water consumption data is a valid barome ter to use for adjustment of the servicing intervals BATTERY REMOVAL a Remove the upper access door to the electrical equipment compartment aft of the left nacelle firewall b Remove the nuts from the hold down strap bolts c Release the battery box lid latches and remove the box lid d Remove the HEGATIVE battery cable from the batteries CAUTION Always remove the ground cable terminal first and install it last to prevent accidental short cir cuits 24 31 00 Page 208 May 12 78 e Remove the POSITIVE cable terminal from the batteries Remove the bus bar interconnect from the two batteries g Remove the batteries from the airplane BATTERY INSTALLATION a Position the batteries in the
318. stments are attempted Operate both engines at approximaely 1 000 rpm with both generators ON and a heavy electr cal load turned on Use the lights blowers radio equipment etc to obtain a 20 electri cal load for each generator Allow a minimum of 20 minutes to stabilize the system CAUTION Do not operate the heated windshield or pitot heat for extended periods during ground opera tion Excessive heat buildup may cause damage to these components VOLTAGE ADJUSTMENT MINIMUM LOAD PRIOR TO P 466 On airplanes prior to P 466 the voltage regulators are ad justed to produce a voltage of 28 25 0 25 volts measured at the battery relay with a minimum electrical load on the system as follows NOTE If the airplane is to be operated continuously where temperatures are 32 F or below the volt age should be adjusted to 28 50 0 25 volts a Connect the positive lead of a portable precision voltmeter to the battery relay The meter must be capable of measuring 28 25 volts with an accuracy of 1 Connect the negative lead of the voltmeter to a good ground b Operate both engines at 1 300 to 1 500 rpm with both generators ON and the electrical load reduced to a minimum c Tum the RH generator OFF Determine the bus voltage as maintained by the LH generator d Tum RH generator ON and LH generator OFF Determine the bus voltage as maintained by the RH generator e Turn the LH generator and idle the engines
319. switch open p Operate control to see if switch will come on Replace switch if defective 21 00 00 Page 107 May 30 75 TROUBLE 2 Ventilating air blower fails to run 3 Combustion air blower fails to run 4 Heater fires but burns unsteadily 21 00 00 Page 108 May 30 75 BCCUNULNAT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING HEATER SYSTEM Cont d PROBABLE CAUSE MASTER switch OFF Broken or loose wiring to motor Circuit breaker open Worn motor brushes Blower wheel jammed Motor burned out Defective radio noise filter Faulty wiring to motor Poor ground connection Worn motor brushes Blower wheel jammed Usually indicated by hot motor housing Defective radio noise filter Faulty or burned out motor Insufficient fuel supply Spark plug partially fouled Loose primary connection at ignition assembly Faulty vibrator Combustion air blower speed fluctuates Can be caused by low voltage loose blower wheel worn brushes or motor REMARKS Energize the MASTER switch Check and repair wiring Close circuit breaker Replace motor brushes Remove and check the ventilating air blower wheel and realign if necessary Remove blower assembly and remove motor Replace filter Inspect and replace faulty wiring Tighten ground screw Replace motor brushes Overhaul the combustio
320. system NOTE The force in line with the elevator tab cables re quired to move the cabie shall not exceed 23 pounds measured with a hand held force gage with or without electric trim i instali the access panel in the floorboard aft of the rear spar the floorboard between the main and aft spar and the left passenger seat j install the left floorboard and the pilot s seat k Install both upholstery panels on the pedestal CL Install the tail cone the access plate beneath the RI horizontal stabilizer and the access plate at the trim tab actuator ELEVATOR TRIM TAB RIGGING NOTE BEECHCRAFT recommends the use of the eleva tor travel gage shown in SPECIAL TOOLS in Chapter 12 20 00 a Place the elevator trim tab control in neutral position b Place the elevator in neutra position and connect the trim tab to the trim tab actuator turning the sprocket on the actuator adjust the trim tab to both extremes of travel measure both settings and return the tab to the mid point of the two extremes of travei This will place the actuator in the neutral position d the trim tab is not in the neutral position upon completion of step c adjust the actuator push rod to place the tab in neutral position e Center the chain on the sprocket and tighten the cable Rig cable tension as noted on the Elevator Rigging Illustr n Figure 201 et Check trim tab travel adjust stops and safety turnbu es A16 B
321. t Cowi Flap Oi Level Indicator Reverse Current Diode Remote Compass Detector Fuel Filler Wing Tip Access Openings One rectangular opening on P 223 through P 347 P 349 through P 364 P 223 through P 347 P 349 through P 364 Optional P 348 P 365 and after Wing Acess Openings Sheet 2 of 2 Figure 204 12 20 00 Page 225 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 807 60 610000 ELEVATOR AND ELEVATOR TAB TRAVEL GAGE 810 60 130001 AILERON TRAVEL GAGE 810 1 60 130001 AILERON TAB TRAVEL GAGE 807 60 630001 RUDDER AND RUDDER TAB TRAVEL GAGE 810 2 96 524000 FLAP TRAVEL GAGE 60 174 Special Tools Sheet 1 of 3 Figure 205 12 20 00 Page 226 Nov 2 73 922 60 960000 PROPELLER TORQUE WRENCH ADAPTER BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 50 590013 TS1171 1 TS1176 1 TS1176 2 TS1171 2 TS12224 TS1222 8 50 590014 TS1176 10 WING BOLT WRENCHES TS1171 10 TK1817 922 4 UPPER FORWARD WING BOLT WRENCH TS1171 2 or TS1176 2 UPPER FORWARD WING NUT TORQUE WRENCH ADAPTER for internal wrenching nut TS1171 10 Val or TS1176 10 TK1817 922 5 50 590014 TS1222 4 or TS1222 8 TS1171 1 Or TS1176 1 or 50 590013 TK1817 922 4 TS1171 2 Of se TS1176 2 TS1171 10 or TS1176 10 A14 UPPER FORWARD WING NUT TORQUE WRENCH ADAPTER for external wrenching nut LOWER FORWARD WING BOLT WRENCH TK1817 9224 LOWER FORWARD WING
322. t Troubleshooting Maintenance Practices New Matic Autopilot BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHAPTER 22 LIST OF PAGE EFFECTIVITY CHAPTER 22 AUTO FLIGHT TABLE OF CONTENTS END PAGE 101 102 103 104 105 201 CHAPTER SECTION SUBJECT 22 10 00 22 11 00 DATE Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 Oct 27 75 PAGE 201 201 101 201 201 22 EFFECTIVITY CONTENTS Page 1 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL DESCRIPTION AND OPERATION H 14 AUTOPILOT The primary components of the autopilot pneumatic system are shown in Figures 202 and 204 in Chapter 36 00 00 Air pressure picked up from the pressure manifold is admitted to the autopilot pneumatic system through the autopilot control valves Servo actuators powered by air pressure move the aircraft control surfaces The autopilot may be turned on anytime after the aircraft engines have been started Because the equipment is transistorized no warm up time is required however make certain that the gyros are erect and stable prior to engaging the system Electrical power to the autopilot is interrupted by pulling the autopilot circuit breaker END ih 22 10 00 Page 1 Oct 27 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL GENERAL MAINTENANCE PRACTICES removable panel on the left underside
323. tall the ducts the combustion air blower and secure with the clamps d install the wiring to the combustion air blower and HIGH VELOCITY WHIRLING FLAME EXHAUST GASES GROUND ELECTRODE WE LDED IN COMBUSTION HEAD N COMBUSTION AIR INLET SPARK PLUG i FUEL INLET MO Sts T SOLENOID VALVE FRESH AIR FROM BLOWER 50 412 1 C i ERN la a N SN I SU lt i s NJ NS SS No V Aircraft Heater Figure 201 21 40 00 Page 201 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL combustion air contraller e Install the heater HEATER IGNITION Figure 201 The controlled atomized spray from a specially designed spray nozzle coupled with high voltage spark plug ignition insures instant firing and continuous burning under flight conditions Heat is produced by burning a fuel air mixture in the combustion chamber of the heater Aviation gasoline is injected into the combustion chamber through the spray nozzle The resulting cone shaped fue spray mixes with combustion air and is ignited by a spark from the spark plug Electric current for ignition is supplied by an ignition unit which converts 24 volts to a high voltage oscillating current to provide a continuous spark across the spark plug gap A shielded high voltage lead connects the ignition assembly to the spark plug Combustion ai
324. tandard numbering system even though all chapters may not be applicable to the aircraft or to the publication INTRODUCTION Page 1 Nov 30 83 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 100 PAGE BLOCK GUIDE Following is a guide to the assignment of the blocks of pages within each System Chapter Sub System Section Unit Subject number in the maintenance manual Pages 1 to 100 Pages 101 to 200 Pages 201 to 300 Description and Operation Troubleshooting Maintenance Practices The text providing the coverage of the description and operation of a system or component would appear on pages numbered consecutively 1 through 100 if needed The information pertaining to the troubleshooting of this same system or component would appear on pages numbered consecutively 101 through 200 if needed The maintenance practices information would appear on pages numbered 201 through 300 The word END at the bottom of a page would indicate the last page in that block LIST OF EFFECTIVE REVISIONS The Log of Effective Revisions following the title page of the manual lists the revisions currently effective for the manual LIST OF EFFECTIVE PAGES The List of Effective Pages and the Table of Contents in the front of each chapter will each start with page 1 and be numbered consecutively thereafter as necessary ALPHABETICAL INDEX An alphabetical index as part of the introduction is provided as an assistance in loc
325. ter adjustment for the optional fifth and sixth passenger seat backs is controlled by RETAINING RING SPRING GUIDE SPRING GUIDE TUBE MAIN ASSY N COUNTERBALANCE EM SPRING 60 314 Roton Lock Figure 201 25 00 00 Page 201 Apr 18 80 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL two individually operated Hydrolok locks The adjustment levers for the Hydrolok locks are located on the outboard armrests For information concerning Roton or Hydrolok servicing refer to ROTON LOCKS or HYDROLOK LOCKS in this chapter ROTON LOCKS Figure 201 Usually Roton locks will need no service if there is grinding and binding in the lock as the seat or the return action becomes jerky a little grease properly applied as follows should improve the operation a Use only grease 30 Chart 207 91 00 00 on the threads as shown in Figure 201 Too much grease or grease in the wrong place can cause improper operation b Compress the spring guide and counter balance spring approximately one inch c Remove the retaining ring d Relax pressure on the spring guide and counter balance spring slowly until the spring is fully extended e Remove the lock from the fixture and remove the springguide counter balance spring and spring guide tube f Apply a small quantity of grease to the completely extended thrust screw see Figure 201 g Reassemble the lock NOTE new lock will need to be
326. ter the limit switches have been adjusted a Adjust the up limit switch so the flap will stop approximately 3 32 inch from the forward portion of the slot on the inboard flap track b Adjust the 14 limit inboard switch in its mounting slot until the flap is positioned at 14 to 14 5 after the flap has been actuated from the up to takeoff position 15 range Adjust the 16 fimit outboard switch es in its mounting stot until the flap is positioned at 15 5 to 16 after the flap has been actuated from the down to takeoff position Adjust the down limit switch in its mounting slots unti it actuates at 28 to 30 of flap travel d Remove the bolt attaching the right actuator to the right flap e Turn the jackscrew on the right actuator in or out to align the right flap with the left f install the bolt connecting the actuator to the flap CAUTION If flaps are removed for any reason the actuator switch should be in the Neutral position or the main power switch OFF NOTE After the flap is completely rigged adjust the rubber bumper flap down installed on the flap and aileron dividing rib Turn the adjusting screw in or out as required to take out play or stop vibration when the flap is in the up position A distinct change in sound of the f ap motor near the completion of the flap up travel may indicate an excessive outward adjustment of the bumper FLAP FUNCTIONAL GROUND TEST a Connect a grou
327. than selected altitude Not exceeding maximum differential pressure PROBABLE CAUSE Pressurization system switch inoperative Rate of climb indicator inoperative Manifold pressure too low during check Cabin altitude and differential pressure in dicator inoperative Safety valve and out flow valve out of adjustment True static air vent tubes loose or damaged Cabin pressurization control supply line or the outflow valve control line kinked or restricted Cabin pressurization controller filter restricted Cabin altitude con troller out of adjustment Cabin altitude indicator inoperative Cabin pressurization controller inoperative Cabin pressurization controlier filter restricted Outflow valve control line kinked or restricted Cabin pressurization controller out of adjustment REMARKS Replace switch Replace indicator Increase manifold pressure to a minimum of 20 in Hg Replace indicator Replace valves Inspect lines and fittings tighten or replace as required inspect lines and fittings repair or replace as required Clean filter Replace controller Replace indicator Replace Clean filter Inspect repair as necessary Replace controller 21 00 00 Page 105 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PRESSURIZA
328. the filler well until the open end rests lightly on the cell baffle then place the index finger over the top open end and withdraw the tube CAUTION Do not push down for the light material of the baffle will give enough to result in a false indication of the electrolyte level d The electrolyte level of a fully charged battery should be between 1 8 and 1 4 inch above the bottom of BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL the baffle If the level of liquid in the tube exceeds 1 4 inch remove the excess with a syringe or squeeze bottle If the level of the electrolyte is less than 1 8 inch above the bottom of the baffle add distilled water with a syringe or squeeze bottle CAUTION water contains minerals chlorines softening agents and other foreign materials which will contaminate a storage battery and shorten its life WARNING The battery may be damaged if the proper procedure is not followed when adding distilled water to the cells e Clean and reinstall the filler cap vent cap vent plugs and check the battery terminal links for tightness Discolored links or melted nylon around cell terrsinals indicate loose link connections CAUTION If water or electrolyte is spilled into the battery container the resultant electrolyte corrosion may cause battery failure The battery case must be cleaned as instructed in CLEANING AND INSPECTION ELECTRICAL LEAKAGE CHECK The self internal dischar
329. the remaining screen from the housing of the fitter assembly c Wash both screens the copper ribbon and the filter assembly housing in solvent 15 Chart 207 91 00 00 Ensure that the orifice of the filter housing is free of foreign material d Install one screen in the housing of the filter assembly install the copper ribbon in the filter assembly housing Do not over compress the copper ribbon install the remaining screen and secure the filter in the housing using the retaining ring e install the filter assembly in the cabin altitude controller using the packing removed with the filter assembly Tighten to a torque of 15 to 20 inch pounds AUXILIARY VOLUME TANK REMOVAL a Loosen and remove the plumbing Cap the plumbing and the auxiliary volume tank to prevent shop soil dirt and foreign material from entering the auxiliary volume tank or the plumbing b Remove the two screws securing the auxiliary volume tank to the forward cabin pressurization bulkhead Remove the tank AUXILIARY VOLUME TANK INSTALLATION Mount the auxiliary volume tank on the forward 21 30 00 Page 206 Feb 22 80 cabin pressure bulkhead and secure with the two screws previously removed b Remove the caps and connect the plumbing to the auxiliary volume tank PRESSURIZATION TEST PROCEDURE P 308 AND AFTER The pressurization systern may be functionally checked for operation by the following suggested procedure a If the outflow valve
330. the cabin reaches maximum differential pressure Once this altitude is reached the controller can be reset to any lower altitude with no effect on cabin altitude To change it under any other condition should be done with caution as rapid fluctuations can take place A recommended practice is prior to take off set the controlier to 1 000 feet above the altitude of the departure field or the arrival field whichever is the highest By doing this the controller does not have to be reset in flight and a smooth comfortable pressurized flight can be expected The following graph is provided to determine the relationship between cruise altitude cabin altitude and differential pressure The zero differential pressure line I PRESSURIZATION CONTROL W CABIN ALT Vly ON CABIN CLIMB THOS FT PRA MIN A60 453 10 Pressurization Controls Figure 1 21 30 00 Page 1 May 30 75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL DIAPHRAGM SEAT DUMP SOLENOID FILTER INLET AIR SAFETY VALVE SPRING CABIN ALTITUDE AND DIAPHRAGM CONTROLLER MOTORIZED SPRING DIAPHRAGM CA SAFETY VALVE AMBIENT AIR 1 SENSE LINE DASHPOT ASSEMBLY JAM NUT CONTROL KNOB VENT TO CABIN RED SELECTOR RING COLLAR SCREEN INLET AIR ANEROID BELLOWS CABIN ALTITUDE T CONTROLLER 1 SCREEN INLET AIR DIALSTOP VENT TO CAgIN MANUAL Jl EA CONT
331. the cause All worn parts should be replaced BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL 1 1 30 IN 2 ITEM QUANT DESCRIPTION NO 1 2 3 4 x 1 x 6 aluminum or eguiv 2 2 1 x 1 3 8 x 1 3 4 aluminum or equiv 3 1 1 2 x 7 1 2 x 10 aluminum or equiv 4 1 C810 Indicator 5 1 3 4 x 2 1 2 x 14 aluminum or eguiv 6 1 1 4 Dia x 2 corrosion res stl 7 1 1 4 Dia x 1 corrosion res stl 8 1 1 4 28 nut 9 1 3 8 x 5 x 10 rubber 10 1 3 8 x 2 x 10 rubber 11 1 1 4 x 2 x 10 corrosion res sti 12 2 1 2 x 13 x 3 VLIER Torque screw 13 722 KN813 Keensert or tap 1 2 13 14 2 1 8 x 1 x 3 4 rubber SECTION A A MI OR P N of Federal Products Corp Providence R i To DRL IMBIGRIOR S P N 45 135030 9 810 Check Fixture for Tab Deflection Figure 203 END 27 30 00 Page 207 Sep 14 79 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL FLAPS DESCRIPTION AND OPERATION The flaps consist of a section on each wing driven by a single electric motor A flexible drive shaft extends from the motor assembly to a jackscrew actuator for each section Limit switches installed on the outboard side of the inboard flap track of the left wing panel stop the flap travel at O full up 15 approach and 30 full down depending on the position of the flap control switch located to the right of the control console on the subpanel To indicate the position of the flaps on serials 4 through 246 an adjustable f
332. tional on serials P 348 P 365 and after All of the fuel cells in each wing and wing tip are interconnected in order to make all of the usable fuel in each wing available to its engine when the fuel selector valve is turned ON The interconnect ing fuel cells are serviced either through the single filler on each wing or the filler in each of the optional wet wing tips providing single point filling for each side The fuel sight gage P 402 and after located outboard of each nacelle may be used for partial filling of the fuel system or for balancing the fuel load when the fuel load is within the range of this gage 40 to 60 gallons for each wing The combined capacity of the standard and optional system is shown below CAPACITY IN GALLONS USABLE IN GALLONS SERIALS P 3 thru P 195 inboard leading 207 192 edge fuel cells unbaffled P 3 and after with inboard leading 207 202 edge baffled fuel cells Optional fuel system P 348 237 232 P 365 and after When filling the airplane fuel cells always observe the follow ing a Service the fuel ceils with grade 100 blue or 100LL green fuel or if not avaitable use 115 145 octane fuel 1 Chart 202 12 20 00 b Make sure the airplane is staticaily grounded to the servicing unit Do not fill fuel celis near open fiame or within 100 feet of any open energized electrical equipment capable of 17 producing sparks d not insert the nozzle
333. tlined in Chapter 12 20 00 STRUT FLUID LEVEL Check and maintain the proper hydraulic fluid level in the strut as outlined in Chap ter 12 20 00 STRUT AND A FRAME HINGE BOLTS Inspect for cracks cor rosion and security of attachment NOSE GEAR UPLOCK PIN Remove and inspect for corrosion _ Lubricate with MIL G 81322 prior to reinstallation NOSE GEAR ASSEMBLY P 3 thru P 296 After the first 1000 flight hours and each 1200 flight hours thereafter inspect the nose gear assembly as noted in BEECHCRAFT Instructions No 0669 206 Rev I or subse quent MECH INSP 5 20 00 Page 221 Nov 20 87 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL i J LANDING GEAR OPERATION MECH INSP CAUTION Under no circumstances should the landing gear be operated electrically while the handcrank is engaged In the event of such an operation a teardown and magnetic inspection should be performed for damage to engagement slot in worm shaft NOTE Since the battery voltage is not sufficient to properly cycle the landing gear for this inspection use only an external power source capable of delivering and maintaining 28 25 25 VDC to the airplane s electrical system throughout the extension and retraction cycles when performing the landing gear retraction inspection For more specific information which may be necessary to accom plish the following items refer to Cha ter 32 30 00
334. trol relay Airplanes operated for Air Taxi or other than normal operation and airplanes operated in humid tropics or cold and damp climates etc may need more fre quent inspections for wear corrosion and or lack of lubrication In these areas periodic inspections should be performed until the operator can set his own inspection periods based on experi ence i NOTE The date noted on the STANDARD AIRWORTHINESS CERTIFICATE FAA Form No 8100 2 which is issued with each new airplane is to be used as the basis for all TBO or replacement components listed in the following schedule NOTE An engine cycle is defined as the period of time from the initial start to shutdown of the engine This encompasses start up increase to full or partial power as required during a flight regime and back to complete engine shutdown Normal opera tion results in the number of landings being equivalent to engine cycles OVERHAUL AND REPLACEMENT SCHEDULE ITEM OVERHAUL OR REPLACE NOTE On Condition items are to be overhauled or replaced when inspection or performance of these items reveal potentially unsafe or unserviceable condition LANDING GEAR Main gear 18 Every 2000 hours 5 10 00 Page 201 Nov 20 87 MAINTENANCE MANUAL BEECHCRAFT DUKE 60 SERIES OVERHAUL AND REPLACEMENT SCHEDULE Cont d OVERHAUL OR REPLACE ITEM LANDING GEAR Cont d Nose Gear Actuator assembly R
335. ts 24 31 00 Page 201 May 12 78 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL MAINTENANCE LOG Catalog No _ No Date Installed REMOVAL DATE GENERAL AND REASON CONDITION END OF CC CHARGE VOLTAGE RANGE REMARKS i M Maintenance LEVEL ELECTRICAL LEAK CHECK CAPACITY ELECTROLYTE 3 E P Lowest Highest Indicate F Failure es SE sf Average water added hardware vo DJ 269 Indicate S 8 5 E 8 ES d 21 burns Type iscolorations etc 24 31 00 Page 202 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL b Connect the battery vent tubing c On serials P 226 and after connect the cooling ducts d Install the battery quick disconnect and safety wire e Reinstall the upper access door aft of the LH nacelle firewall BATTERY CHARGING The two basic methods of charging nickel cadmium batteries are the constant potential and constant current methods Variations of the two basic methods may be incorporated in automatic equipment WARNING Complete servicing of the battery is required if the battery is subjected to more than 32 volts for 2 minutes SPECIAL NOTES ON CHARGING The following special comments are made with respect to charging nickel cadmium batteries a Charging is rnost efficient at battery temperatures between 40 F and 80 F b Two or more batteries may be charged in parallel on a constant potential chargin
336. ttle is re quired in the form of servicing the system The boots should be checked for engine oil after servicing and at the end of each flight and any oil found should be removed This can be accomplished by the use of a neutral soap and water solu tion Care should be exercised to avoid scrubbing the surface of the boot as this will tend to remove the special conductive surfacing NOTE Because the deice boots are made of soft flex ible material care must be exercised against dragging gasoline hoses over them or resting ladder or platforms against the surface of the boots For surface deice boot maintenance refer to Chapter 30 10 00 SHOCK STRUTS The shock struts are filled with compressed dry air or nitro gen and MIL H 5606 or MIL H 83282 hydraulic fluid 13 Chart 202 The same procedure is used for servicing both the main and nose gear shock struts The shock strut may be serviced as follows a Remove the air valve cap and depress the valve core to release the air pressure 12 20 00 Page 202 May 12 78 CAUTION Do not unscrew the air valve assembly until the air pressure has been released or it may be blown off with considerable force causing injury to personnel or property damage b Remove the air valve assembly c Compress the strut and fill through the air valve assembly hole with MIL H 5606 or MIL H 83282 hydraulic fluid 13 Chart 202 approximately one pint until the fluid over
337. ture Check the system for normal operation DUAL BUS CONFORMITY INSPECTION Figure 201 A dual bus conformity inspection shoud be performed whenever the console or subpanel bus system has been modified or whenever repairs have been made that may result in the dual bus loops being interconnected or open Either battery or auxiliary power may be used when conducting this inspection Check for correct circuit connections by actual operation of the circuit as described by the appropriate power distribution circuit in the Wiring Diagram Manual P N 60 590001 29 The conformity inspection may be performed as follows a Open the four 50 ampere bus feeder circuit breakers labeled ELECTRICAL POWER on the right circuit breaker subpanel i b Turn the battery ON External power be used c Close the LH 1 bus feeder circuit breaker check each circuit and record the results d Open the LH 1 bus feeder circuit breaker and close the LH 2 bus feeder circuit breaker Repeat the circuit checks and record the results e Open the LH 2 bus feeder circuit breaker and close the RH 1 bus fecder circuit breaker Repeat the circuit checks and record the results i f Open the RH 1 bus feeder circuit breaker and close the RH 2 bus feeder circuit breaker Repeat the circuit checks and record the results g If any of the results that have been recorded reveal a discrepancy locate and repair to obtain the desired result h Close all
338. ty E e Remove cap P 3 through P 20 and reinstall th line RAKE SYSTEM 4Figure 201 Brake system servicing is limited primarily to maintaining th hydraulic fluid level in the reservoir The brake fluid reservoi accessible through the forward baggage compartment doo is hinged on the aft frame of the door Loosening the screw securing the reservoir to the airplar Structure allows the reservoir to swing out for easy servicin Fill the reservoir with MIL H 5606 hydraulic fluid 13 Cha 2202 12 20 00 to the full mark on the dip stick Mainta fluid level between full and add marks Do not overfi detailed information relating to the proper inspectic zand repair procedures for the brake assembly refer to tt Beech Manufactured Component Maintenance Manuz 60 590001 27 AIR CONDITIONING SYSTEM Servicing the air conditioning system consits of periodical checking the refrigerant level checking compressor oil leve and changing the system air filter Recharge the system a _outlined under CHARGING THE AIR CONDITIONING SYS TEM whenever the refrigerant level is low air has entered th system or components carrying refrigerant are replace Refrigerant leaks may be detected by inspection with flameless leak detector BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHARGING THE AIR CONDITIONING SYSTEM When working on a refrigerative air cooling system observe the following special serv
339. uction Pressure will slowly rise to about five pounds gage pressure g The remaining pressure is relieved by unscrewing the plug for 5 full turns and bieed to zero pressure h Remove the oil plug and O ring i place the crank throw in the best position for dip stick insertion point the keyway on the compressor shaft up toward the cylinder head j insert an oil dipstick until the end contacts the bottom of the crankcase Remove and measure the oil depth NOTE A compressor level depth of 1 5 to 1 8 inches is satisfactory lf the oil level is below 1 5 inches add oil per Chart 202 then remeasure CHART 202 CHECKING COMPRESSOR OIL LEVEL Dip Stick 00 Depth be Added Oz 6 8 0 8 65 1 0 5 0 12 30 1 4 1 5 OIL CHECK PLUG ALSO OTHER SIDE 60 451 TA Dipstick and Compressor Oil Check Plug Figure 202 12 10 00 Page 203 Nov 2 73 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL Oil should be removed when depths greater than 1 8 inch are observed Compressor oil level reduces 4 to 7 inches during operation at maximum rpm and also drops slightly with reduced evaporator loads Approximately 7 ounces of oil is required to initially wet the system and circulate with the refrigerant When an evaporator or condenser coil is changed add approximately 2 ounces of oil on installation then check and adjust the oil level as recommended A locally manufactured dip stick see Figure 202 may be fab
340. uen cy Indicator the instrument is located in the pilot s instrument panel below and to the left of the standard turn and slip instrument This instrument informs the flight crew when the ac voltage and frequency are not within the required limits for accurate operation of the ac power to the tum and slip directional gyro attitude and gyro horizon Two terminal posts are located on the back of the instrument The electri cal wire leading from the main bus is connected to the ieft terminal post and the line supply is connected to the right terminal post DC GENEBATION GENERATORS The Duke 60 Series electrical system includes two 125 am pere generators The generators are isolated from the air plane bus by reverse current diodes and generator control relays and are regulated individually by a carbon pile type regulator The circuit of each generator contains an overvol tage relay to protect the airplane system from excessive voltage Paralleling relays are used to connect the equaliza tion circuits of the voltage regulators and to sense generator output to the annunciators in the pilot s compartment BATTERY The Duke 60 Series airplanes P 4 through P 225 are equip ped with either General Electric or Gulton nickel cadmium batteries P 226 through P 445 are equipped with General Electric air cooled nickel cadmium batteries For mainte nance on these type batteries refer to BATTERY MAINTE NANCE PROGRAM Airplanes prior to P 4
341. uld be replaced if it has been worn to the indicator or if it is obvious that the brush will reach the minimum length before the next inspection time New brushes must be properly seated on the commutator surface before the generator is subjected to heavy loads to prevent arcing which will cause burning and pitting of the commutator New brushes should be sanded and run in to properly seat them on the commutator surface Refer to the applicable Vendor Publication Chapter 20 00 00 for re placement and run in procedures OVERVOLTAGE RELAYS No attempt should be made to adjust the overvoltage relays They are preset at the factory to trip at a voltage of 33 00 0 0 0 25 volts When the relay is determined defective it should be replaced with a new or exchange relay OVERVOLTAGE RELAY CHECK Figure 201 The overvoltage relays should be functionally checked for proper operation at 500 hour intervals or whenever over voltage relay voltage regulator or generator is replaced This test may best be accomplished in the airplane A variable resistance introduced in series with the voltage regulator input will allow the generator system to be driven into an overvoltage condition without disturbing the voltage regulator adjustment The electrical components involved in this check are located in the electrical equipment compart ment immediately aft of the LH nacelle firewall Test each overvoltage relay separately as outlined in the fo
342. ve and the safety valve are mounted within a box structure which is a portion of the aft pressure bulkhead Each valve consists of two sections a head and a base section Within the head section of each valve is a control chamber The control chamber of the outflow valve is closed except for the pneumatic fitting designated port 2 which connects the control chamber to the reference pressure developed in the cabin altitude controller The control chamber of the safety valve is connected to the airplane vacuum system through port 2 and is vented to the cabin air through a filter and orifice A differential control assembly mounted on the head section of each valve is vented to static atmosphere through the pneumatic fitting designated port 1 The base section of each valve houses the poppet valve poppet valve seat and noise suppression screen The poppet valves are spring loaded to the closed position whenever there is no controlling pressure applied The following description of the system operation is made assuming that the system is functioning normally both engines are operating bleed air from the turbochargers is flowing normally and the airplane vacuum system is functioning Prior to a normal pressurized flight with the system switch placed in the NOR normal position electrical power is royted to a ram air door magnetic latch and through a portion of the RH landing gear safety switch to actuate a pair
343. vice Oil Co 60 Wall Tower New York 5 N Y Rust Foil No 652 2 Franklin and Gas Co Bedford Ohio Kendex No 7038 Kendall Refining Co Bradford Pa 12 20 00 Page 206 Nov 30 83 14 ITEM MATERIAL 4 Lubricating Oil 5 Lubricating 6 Lubricating Aircraft Reciprocating Piston Engine 7 Lubricating Gear 14 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL CHART 202 Cont d CONSUMABLE MATERIALS SPECIFICATIONS MIL L 6081 SAE 20 or SAE 10W30 MIL L 6082 MIL L 6086 Grade M VENDOR PRODUCTS Gulflite Turbojet Oil No 1010 Gulf Oil Corp Pittsburg Pa 3 1286 Shell Co 50 West 50th Street New York N Y 10020 Jet Engine Oi No 1010 Texaco Inc 135 East 42nd Street New York N Y 10017 Conoco Aero 1065 Continental Oil Co Ponca City Oklahoma Phillips 66 Aviation Engine Oil Grade 1065 Phillips Petroleum Co Bartlesville Oklahoma Skilflite No 100 Skelly Oil Co El Dorado Kansas Avrey 10V1100 Socony Mobil Oil Co Inc 150 East 42nd Street New York N Y 10017 Or any approved aircraft engine oil graded at 1065 or 1100 Trojan Gear Oil No 6086 M Cities Service Oil Co 60 Wail Tower New York 5 N Y Aeroshell Fluid 5 M Shell Oil Co 50 West 50th Street New York N Y 10020 L 1195 Sinclair Refining Co 600 Fifth Avenue New York N Y 12 20 00 Page 207 Nov 30 83 ITEM 10
344. with MIL G 23827 grease 11 Chart 202 12 20 00 and Chart 207 91 00 00 and paint the controi cables through out its full travel through the pressure seals with MIL G 23827 grease 11 Chart 202 12 20 00 and Chart 207 91 00 00 Spread the electrical wire bundles apart and apply 1239 7 sealant around each wire After each wire is covered wrap Scotch 33 vinyl around the wire bundle butted against seal fitting and inject 1239 7 sealant in the notch of the seal fitting Apply EC1239B12 sealant to all plumbing fittings at the pressure vessel Ensure that the landing gear retract rods pressure boots are properly installed without damage Perform the pressurization leak test as described through 0 5 Remove all seats floorboards and upholstery panels Check the complete pressure vessel for leaks Isolate and repair all leaks Repeat Steps a through 0 h With the pressure leak test within tolerance depressurize the pressure vessel and remove the safety net i Remove all test hoses from the airplane and connect the hoses between the fuselage and the engines i Install the control port tubing on each outfiow and safety valves k Remove the plug from the atmosphere port of the Outflow valve and ensure that the back pressure test hose is removed from the atmosphere vent fitting of the safety valve located on the aft side of the aft bulkhead i Install floorboards upholstery panels seats and
345. x marks are aligned and the connector pins on the vibrator can be felt entering the pin sockets in the vibrator socket then press the vibrator fully and firmly into position b Check the heater for operation and close al access openings INSPECTION AND SERVICING SPARK PLUG Figure 202 if the spark plug appears to be in good condition except for a mild coating of oxide on the porcelain and electrodes it may be cleaned and reused Cleaning is accomplished on a conventional aircraft type spark plug cleaner except that it will be necessary to use two or more adapters in order to raise the long extension of the plug far enough out of the cleaner nozzle opening to provide an effective job Plug the ceramic insert cavity at the terminal end of the plug with a piece of paper or cloth to keep out any of the cleaning sand Wipe this cavity out thoroughly with a cloth wet with carbon tetrachloride 1f after cleaning the spark plug porcelain is white and the electrode is not eroded the spark plug gap may be set as follows Insert a six inch scale with a sliding clip into the spark plug well until it touches the ground electrode welded inside the combustion head Withdraw the scale and note the dimension between the sliding clip and the end of the scale Place the scale against the bottom of the spark plug gasket and determine the length of the spark plug positive electrode The difference 6 INCH SCALE PLUG WELL t 3 16 TO
346. xternal Fuel Celi Vent Line 203 INDICATING 28 40 00 Maintenance Practices 201 Fuel Quantity Indicators 201 Fuel Transmitter Removal 201 Fuel Transmitter installation 201 Adjusting and Testing Fuel Gaging System 201 Fuel Flow Indicator 201 Fuel Sight Gage 202 Fuel Sight Gage Removal 202 Fuel Sight Gage installation 202 END 28 CONTENTS Page 2 Oct 19 77
347. y to a torque of 50 to 70 inch pounds for the AN4 5A boits at the top and bottom of the plate and 20 to 25 inch pounds for the remaining bolts WARNING The airplane must not be pressurized prior to installation of the plate r Reinstall the upholstery panel CABIN PRESSURIZATION LEAKAGE TEST P 4 and after Figure 201 Test equiprnent is available for ground testing the cabin for pressurization leaks and for troubleshooting the pressurization system Such equipment must be capable of delivering 4 50 psi of air at 80 cubic feet per minute and must be protected by a complete safety system to prevent damage to the airplane The test unit listed in the following paragraph consists of an electric motor and blower assembly a dry air filter a flowmeter a cabin pressure gage and a large relief vaive to protect the pressure vessel of the airplane NOTE ft should be noted that the test unit to be used must be set at the psi of pressurization for which the airplane is designed if the safety system of the test unit is to fulfill its function The units listed in the following paragraph TEST EQUIPMENT also include a pneumatic air system that delivers from zero to 30 pounds of air at 25 cubic feet per minute for checking the deicer boot system and pressure instruments TEST EQUIPMENT 4 and after The following pressurization test units or their equivalent may be utilized for the cabin pressurization leakage test a
348. y to allow condensed moisture to drain from the system On the option al system P 348 P 365 and after open the fuel drain in the wet wing tip using the special tool P N 101 590020 1 NOTE If the cells are to remain unfilied for 10 days or more apply a thin coating of light engine oil to the inside surface of the cell to prevent deteriora tion and cracking OIL SYSTEM The engines are equipped with a wet sump pressure type oil system Each engine sump has a capacity of 13 quarts The oil system may be checked through access doors in the 712 10 00 201 Jan 9 86 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL engine cowling A calibrated dip stick attached to the filler cap indicates the oil level Due to the canted position of the engines the dip sticks are calibrated for either right or left engines and are not interchangeable The oil should be changed every 75 to 100 hours under normal operating con ditions and the oil filter changed every 50 hours CAUTION Any Time the oil system has been contaminated by metal particles the oil cooler must be re placed and the oil system flushed to prevent en gine damage Ail 541 series engines are limited to using only MIL L 22851 ashless dispersant multi grade oil 2 Chart 202 12 20 00 Oil equivalent to SAE 50 or SAE 60 above 60 F below 30 F SAE 40 is recommended However newly over hauled engines of this series may be run in on the test stand with s
349. zation system can be checked during ground run up Pressurization ground check may be accomplished a follows f ca Place the manual dump switch in the pressure position and the firewall shut off valves in the open position ib Run the engines at 2 000 rpm and press the peess to test switch momentary indication of a descent in cabin altitude on the cabin rate of climb indicator shows that the system will pressurize f BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL PRESSURIZATION CONTROL DESCRIPTION AND OPERATION P 308 AND AFTER The pressurization control system consists of a system mode switch cabin altitude controller auxiliary volume tank outflow valve and safety valve The system mode switch has three positions TEST NOR normal and DUMP to permit the operation of the system in the ground test pressurized flight and unpressurized flight modes The controller contains a visual display of the selected altitude an altitude selector and a rate control The outer scale of the selected altitude visual display indicates the selected cabin altitude the inner scale indicates the corresponding altitude at which the maximum differential pressure would occur The rate control regulates the rate at which cabin pressure ascends or descends to the selected altitude When the pointer of the rate control knob is set to the 12 o clock position the rate of change is approximately 500 feet per minute The outflow val

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