Beechcraft Duchess 76 Page 250 Pilot'S Operating Handbook And Faa Approved Airplane Flight Manual Download

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Summary of Contents for Duchess 76

Page 1: ...lane at all times and be kept within reach of the pilot during all flight operations This handbook includes the material required to be furnished to the pilot by FAR 23 Jackson Beech Aircraft Corporation DOA CE 2 Airplane Serial Number Airplane Registration Number FAA Approved If COPYRIGHT BEECH 1994 PIN 105 590000 5 Issued January 1978 PIN 105 590000 5A9 Revised July 1994 ...

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Page 3: ...RATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL A8 Revision October 1990 LOG OF REVISIONS Page Description Title Page Updated Page A A8 New 10 1 thru Revised Section X 10 68 Safety Information October 1990 A8 PAGE A ...

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Page 5: ...ensed form in the hands of the pilots The Safety Information should be read and studied Periodic review will serve as a reminder of good piloting techniques 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 proc...

Page 6: ...henticated 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 B EECHCRAFT expressly disclaims any responsibility for malfunctions...

Page 7: ...GENERAL SECTION II LIMITATIONS SECTION III EMERGENCY PROCEDURES SECTION IV NORMAL PROCEDURES SECTION V PERFORMANCE SECTION VI WEIGHT AND BALANCE EQUIPMENT LIST SECTION Vii SYSTEMS DESCRIPTION SECTION VIII HANDLING SERVICING AND MAINTENANCE SECTION IX SUPPLEMENTS SECTION X SAFETY INFORMATION September 1983 e ...

Page 8: ... fN 8 J I3 A VNOI lN3 1NI 9L SSal f na l IV OH0338 p ...

Page 9: ... DATA 1 9 Engines 1 9 Propellers 1 9 Fuel 1 10 Oil 1 10 Maximum Certificated Weights 1 10 Standard Airplane Weights 1 11 Cabin and Entry Dimensions 1 11 Baggage Space and Entry Dimensions 1 11 Specific Loadings 1 11 SYMBOLS ABBREVIATIONS AND TERMINOLOGY 1 11 Airspeed Terminology 1 12 Meteorological Terminology 1 14 Power Terminology 1 15 Engine Controls and Instruments Terminology 1 16 Airplane Pe...

Page 10: ... lNV1e U31 A1 VNOIl N3l NI 9LSSal4 na l IVHOH0338 ...

Page 11: ...ordance with the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual and or placards which are located in the airplane As a further reminder the owner and the operator should also be familiar with the Federal Aviation Regulations appli cable to the operation and maintenance of the airplane and FAR Part 91 General Operating and Flight Rules Further the airplane must be operated and m...

Page 12: ...s Operating Handbook is designed to facilitate maintaining the documents necessary for the safe and effi cient operation of the airplane The handbook has been prepared in loose leaf form for ease in maintenance and in a convenient size for storage The handbook has been ar ranged with quick reference tabs imprinted with the title of each section and contains ten basic divisions I 1 4 Section 1 Sect...

Page 13: ...and revisions of FAA Approved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Manuals and Pilot s Operating Handbooks This service is free and will be provided only to airplane owners who are listed on the FAA Aircraft Registration Branch List or the BEECHCRAFT International Owners Notification Service List and then only if listed by airplane serial number for the model ...

Page 14: ...ced in this handbook REVISING THE HANDBOOK Immediately following the Title Page is the Log of Revi sions page s The Log of Revisions pages are used for maintaining a listing of all effective pages in the handbook except the SUPPLEMENTS section and as a record of revisions to these pages In the lower right corner of the outlined portion is a box containing a capital letter which denotes the issue o...

Page 15: ...upplemental material will be added to the grouping in accordance with the descriptive listing NOTE Upon receipt of a new or revised supplement compare the Log page just received with the existing Log page in the manual Retain the Log page with the latest date on the bottom of the page and discard the other log VENDOR ISSUED STC SUPPLEMENTS When a new airplane is delivered from the factory the hand...

Page 16: ... lNV1S 31 A1 VNOI LN31 NI 9LssC 4 no L IVI JOH033S ...

Page 17: ...BEECHCRAFT Duchess 76 section I General o o o o r _ WING AREA 181 SQ FT I I 12 6 J 76 DIA 76 607 4 OJ I 38 29 5 Ci T I I I 9 6 THREE VIEW January 1978 1 7 ...

Page 18: ...EARANCE Radius for Wing Tip 27 feet 2 inches Radius for Nose Wheel 9 feet 10 inches Radius for Inside Gear 3 feet 1 inch Radius for Outside Gear 13 feet 8 inches TURNING RADII ARE PREDICATED ON THE USE OF PARTIAL BRAKING ACTION AND DIFFERENTIAL POWER 1 8 January 1978 ...

Page 19: ...nuous Power Full throttle 2700 rpm Recommended Maximum Cruise Power 24 in Hg 2700 rpm PROPELLERS The airplane is equipped with two Hartzell constant speed full feathering two blade propellers the left engine clock wise rotating has an HC M2YR 2CEUF hub with FC 7666A blades and a C2285 3P spinner the right engine coun terclockwise rotating incorporates an HC M2YR 2CLEUF hub with FJC 7666A blades an...

Page 20: ...AINTENANCE section for a list of oils meeting this specification Average Ambient MIL L 6082 MIL L 22851 Air Temperature Grades Ashless Dispersant Grades Above 60 F SAE 50 SAE 40 or SAE 50 30 0 to 90 F SAE 40 SAE 40 o 0 SAE 30 SAE 40 SAE 30 o to 70 F or SAE 20W40 0 SAE 20 SAE 30 or SAE 20W30 Below 10 F Oil Capacity 8 quarts each engine MAXIMUM CERTIFICATED WEIGHTS MaximumHamp Weight Maximum Take of...

Page 21: ... Compartment Width nominal Compartment Length nominal Compartment Height nominal Door Width minimum Door Height minimum SPECIFIC LOADINGS 19 5 cu ft 38 in 26in 37in 22in 33in Wing Loading at Maximum Take off Weight 21 5Ibs sq ft Power Loading at Maximum Take off Weight 10 8Ibs hp SYMBOLS ABBREVIATIONS AND TERMINOLOGY The following Abbreviations and Terminologies have been listed for convenience an...

Page 22: ...d compressibility Ground Speed is the speed of an air plane relative to the ground Air Minimum Control Speed is the minimum flight speed at which the air plane is directionally controllable as de termined in accordance with Federal Aviation Regulations The airplane cer tification conditions include one engine becoming inoperative and windmilling a 5 degree bank towards the operative engine take of...

Page 23: ...cation of full avail able aerodynamic control will not over stress the airplane Design Flap Speed is the highest speed permissible at which wing flaps may be actuated Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear ex...

Page 24: ...air speed which delivers the greatest gain of altitude in the shortest possible hori zontal distance Best Rate Of Climb Speed is the air speed which delivers the greatest gain in altitude in the shortest possible time METEOROLOGICAL TERMINOLOGY ISA 1 14 International Standard Atmosphere in which 1 The air is a dry pertect gas 2 The temperature at sea level is 15 Celsius 59 Fahrenheit 3 The pressur...

Page 25: ...rom standard sea level pressure 29 92 in Hg by a pressure or barometric altimeter It is the indicated pressure altitude corrected for position and instrument error In this handbook altimeter instrument errors are assumed to be zero Position errors may be obtained I from the Altimeter Correction graph Actual atmospheric pressure at field elevation The wind velocities recorded as vari ables on the c...

Page 26: ...pm position feathers the propeller This lever is used to set fuel flow in all modes of operation and cuts off fuel completely for engine shutdown Indicates the rotational speed of the en gine propeller in revolutions per minute rpm Regulates the rpm of the engine propel ler by increasing or decreasing the pro peller pitch through a pitch change mechanism in the propeller hub An instrument that mea...

Page 27: ...anding was actually demonstrated during certification tests The value I shown is not limiting The distance required to accelerate an airplane to a specified speed and as suming failure of an engine at the in stant that speed is attained to bring the airplane to a stop The distance required to accelerate an airplane to a specified speed and as suming failure of an engine at the in stant that speed ...

Page 28: ...fuII oil Standard empty weight plus optional equipment Fuel available for flight planning Fuel remaining after a runout test has been completed in accordance with governmental regulations Weight of occupants cargo and baggage Difference between ramp weight and basic empty weight Maximum weight approved for ground maneuvering It includes weight of start taxi and run up fuel Maximum weight approved ...

Page 29: ...ce from the reference datum The horizontal distance from the refer ence datum to the center of gravity CG of an item The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify ba lance calculations by reducing the number of digits The point at which an airplane would balance if suspended Its distance from the reference datum is found by divid ing th...

Page 30: ...nt weight which may be indi cated by a scales before any load is applied Those points which are used during the weighing process to level the airplane Points on the airplane identified by the manufacturer as suitable for supporting the airplane for weighing or other pur poses January 1978 ...

Page 31: ...s 2 5 Oil 2 5 Propellers 2 5 Power Plant Instrument lv1arkin s 2 6 lv1isc ellaneous Instrument lv1arkings 2 6 Weight Limits 2 7 Center of Gravity 2 7 Maneuvers 2 7 Flight Load Factors 3900 Pounds 2 8 Minimum Flight Crew 2 8 Kinds of Operation 2 8 Fuel 2 9 Fuel Management 2 9 Seating 2 9 Structural Life 2 9 Required Equipment for Various Conditions of Flight 2 10 Plac ards 2 21 September 1983 2 1 ...

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Page 33: ... in Smooth Air and Then Cruising Only With Caution VNO Maneuvering 132 19 Do Not Make Full or Abrupt VA Control Movements Above This Speed Maximum Flap 110 1JQ Do Not Extend Flaps or Oper Extension Extended ate With Flaps Extended VF and VFE Above This Speed Full Down 35 Maximum 140 140 Do Not Exceed This Speed Landing Gear With Landing Gear Extended Extended VLE Maximum Do Not Extend or Retract L...

Page 34: ...Only In Smooth Air Red Maximum Speed Radial 194 194 For All Operations Never Exceed The airspeed indicator is marked in lAS values POWER PLANT LIMITATIONS ENGINES Two Avco Lycoming engines installed one 0 360 A1G6D clockwise rotating located on the left Wing and one LO 360 A1G6D counterclockwise rotating located on the right wing The engines are four cylinder direct drive horizontally opposed and ...

Page 35: ...ccordance with Aveo Lycoming I Service Instruction NO 1 014J or subsequent revisions Refer to the Approved Engine Oils Section VIII SERVICING PROPELLERS Two Hartzell constant speed full feathering two blade pro pellers the left engine clockwise rotating has an HC M2YR 2CEUF hub with FC 7666A blades and C2285 3P spinner the right engine counterclockwise rotating incorporates an HC M2YR 2CLEUF hub w...

Page 36: ... Radial 100 psi Manifold Pressure Normal Operating Range Green Arc 15 to 29 6 in Hg Tachometer Normal Operating Range Green Arc 2000 to 2700 rpm Maximum Red Radial 2700 rpm Fuel Pressure Minimum Red Radial 0 5 psi Normal Operating Range Green Arc 0 5 to 8 0 psi Maximum Red Radial 8 0 psi Cylinder Head Temperature Normal Operating Range Green Arc 200 to 500 F Maximum Red Radial 500 F MISCELLANEOUS ...

Page 37: ...xtended Forward Limits 106 6 inches aft of datum at 3250 lbs and under then straight line variation to 110 6 inches aft of datum at a weight of 3900 Ibs Aft Limit 117 5 inches aft of datum at all weights Reference Datum 129 37 inches forward of the center of wing spar jack points MAC Leading Edge 99 08 inches aft of datum MAC Length 57 65 inches MANEUVERS This is a normal category airplane Acrobat...

Page 38: ...52G MINIMUM FLIGHT CREW One pilot KINDS OF OPERATION This airplane is approved for the following type operations when the required equipment is installed and operational as defined herein 1 VFR day and night 2 IFR day and night 3 FAR 91 operations when all pertinent limitations and performance considerations are complied with WARNING FLIGHT IN ICING CONDITIONS PROHIBITED 2 8 January 1978 ...

Page 39: ...ndicators indicate in the yellow band on either indicator Maximum slip duration is 30 seconds The fuel crossfeed system to be used during emergency conditions in level flight only SEATING All occupied seats must be in the upright position for takeoff and landing STRUCTURAL LIFE The basic wing structure has a substantiated life of 20 000 flight hours provided the mandatory inspection requirements o...

Page 40: ...onditions the airplane could not be flown unless all equipment were operable With appropriate limita tions the operation of every system or component installed in the airplane is not necessary when the remaining operative instruments and equipment provide for continued safe opera tion Operation in accordance with limitations established to maintain airworthiness can permit continued or uninterrupt...

Page 41: ...nsibility of the pilot to determine whether the lack of or inoperative status of a piece of equip ment on the airplane will limit the conditions under which the pilot may operate the airplane LEGEND Numbers refer to quantities required to be operative for a specified condition Indicates that the item may be inoperative for the specified condition Refers to the REMARKS AND OR EXCEPTIONS col umn for...

Page 42: ... VFRNight COMPONENT fFRDay fFRNight Remarks and or Exceptions GENERAL OVERWATER FLIGHT Per FAR 91 COMMUNICATIONS VHF communications system Per FAR 91 I ELECTRICAL POWER Battery system 1 1 1 1 DC alternator 2 2 2 2 DC loadmeter 2 2 2 2 I I I i J i J IJ g co to J CD S CD 3 i ...

Page 43: ... 1 1 1 1 May be inoperative provided Y I I lO ME 333 ME 346 and after loadmeters are operative w and monitored I I I I I I I EQUIPMENT AND FURNISHINGS Seat belts and I shoulder harnesses 1 I I1 1 1 Per Person or Per FAR 9 1 Emergency locator transmitter 1 1 1 Per FAR 91 I FIRE PROTECTION I Portable fire extinguisher I I I 1 1 Optional I i N I I I I I I I 0 g J W fh ...

Page 44: ...tab indicators Rudder 1 1 1 1 May be inoperative provided Elevator 1 1 1 1 that tabs are visually checked in the neutral position prior to each takeoff and checked for full range of operation Flap position indicator 1 1 1 1 May be inoperative provided flap travel is visually inspected prior to takeoff Stall warning system 1 1 1 1 I I I 4 A f i i 3 i 4 W ...

Page 45: ... 0 OJ Fuel quantity indicator 2 2 2 2 One may be inoperative provided w other side is operational and amount of fuel on board can be established to be adequate for the intended flight Fuel pressure indicator 12 12 I 2 I 2 L I I ICE AND RAIN PROTECTION Alternate static air source 1 1 1 1 C Pitot heater 1 1 te N 1 1 I I 1 1 I 0 g J Ul I ...

Page 46: ...RDay IFRNight Remarks and or Exceptions I LANDING GEAR Landing gear motor 1 1 1 1 Landing gear position lights 4 4 4 4 landing gear warning horn 1 1 1 1 I LIGHTS Cockpit and instrument lights Lights must be operative Taxi Light 2 fit 0 1 o _ I en m m em co n t 3 0 m o en I ...

Page 47: ...1110 0 I 0 1 l CD NAVIGATION INSTRUMENTS ro w Altimeter 1 1 1 1 Airspeed indicator 1 1 1 1 Vertical speed Magnetic compass 1 1 1 1 Attitude indicator 1 1 Turn and slip indicator 1 1 Directional gyro 1 1 Clock 1 1 I Transponder Per FAR 91 Navigation equipment Per FAR 91 r ii N I I I I I I 0 g J u III ...

Page 48: ...Night COMPONENT IFRDay IFR Moht Remarks and or Exceptions I PNEUMATIC Pressure system for instrument air 1 1 Pressure gage 1 1 I ENGINE INDICATING INSTRUMENTS Engine tachometer indicator 2 2 2 2 Exhaust gas temperature indicator Optional I I I I I I I I I co en c 3 g tD 00 W ...

Page 49: ...e indicator 2 2 2 2 om OJ em Cylinder head temperature 2 2 2 2 m CD 3 To indicator l J g w 0 I u O l ao 0 l 00 ENGINE Oil INSTRUMENTS w Oil pressure indicator 2 2 2 2 Oil temperature indicator 2 2 2 2 I w r if 00 I l W ...

Page 50: ...9l sS84 na L IVl IOH0338 lNV1a L I31 A11VNOIJ N3J NI SUOlIUJlwn II uOlJ S ...

Page 51: ...OR FAR 135 NO ACROBATIC MANEUVERS INClUDING SPINS APPROVED WARNING TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING FLIGHT THROUGH CLOUD FOG OR HAZE AIRSPEEDS NEVER EXCEED 194 KNOTS MAX STRUCTURAL CRUISE 154 KNOTS MAX MANEUVERING 132 KNOTS MAX FLAPS 20 120 KNOTS MAX FULL DOWN FLAPS 3S 110 KNOTS MAX LANDING GEAR EXTENSION 140 KNOTS MAX LANDING GEAR RETRACTION 113 KNOTS AL...

Page 52: ...ot s Seat 0n EMERGENCY GEAR EXTENSION II ACCESS DOOR f l11 On Inside of Emergency Gear Extension Access Door r EMERGENCY LANDING GEAR EXTENSION 1 Landing Gear Motor Circuit Breaker OFF Pull 2 Gear Position Switch DOWN 3 Maximum Indicated Airspeed 100 KNOTS 4 Emergency Extension Valve OPEN L Use Handle Turn Counterclockwise 2 22 January 1978 ...

Page 53: ...all Panel Section II Limitations r O LEVEl AIRCRAFT LEVE I IBAGGAGE COMPARTMENT FLOOR I On Left Side Panel EFRos0 1 PUll O I CABIN AIR PUll OFF Ip tBIN H t I elINCR On Aft Cabin Bulkhead j j J L HAT SHELF NO HEAVY OBJECTS I e January 1978 2 23 ...

Page 54: ...s BEECHCRAFT Duchess 76 PLACARDS Cont d On Fuel Selector Panel I I ON CROSS FEED LEVEL FLIGHT ONLY OFF LEFT RIGHT ENGINE ENGINE 50 GALS 50 GALS USABLE USABLE FUEl SELECTOR CROSS FEED LEVEL FLIGHT ONLY L J 2 24 January 1978 ...

Page 55: ...BEECHCRAFT Duchess 76 On Pedestal section II Limitations I OFF CARB HEAT ON I r I cn n L o S E H A L F MIC 0 P PHONE E NU u COWL L L FLAP January 1978 2 25 ...

Page 56: ...Section II Limitations PLACARDS Cont d On Pedestal Between Front Seats I WING DOWN IT I l BEECHCRAFT Duchess 76 RT l R I 2 26 L RUDDER TAB N 1 N 0 5 o E LUP J ELEVATOR TAB October 1979 ...

Page 57: ...h Seat I NSTRUCTION SHOUlDERSTRA l 1 OCCUPANTS SHORTER THAN 4 FT 7 IN DO NOT USE SHOULDER STRAP 2 PLACE SEAT BACK IN THE UPRIGHT POSITION DURING TAKEOFF AND LANDING I L _ On Baggage Door Adjacent to Handle I I PULL PIN ROTATE HANDLE TO OPEN L I January 1978 2 27 ...

Page 58: ...tion II Limitations On Baggage Compartment Door BEECHCRAFT Duchess 76 2 28 BAGGAGE COMPARTMENTI LOAD IN ACCORDANCE WITH WEIGHT AND BALANCE INSTRUCTION MAXIMUM STRUCTURAL L CAPACITY 200 POUNDS January 1978 ...

Page 59: ...AUSTRALU Av1ATlION COLLEGE B 76 SECTION III EMERGENCY PROCEDURES TIJE EMERGENCY CHECKLIST FOR AAC FLIGHT OPERATIONS IS FOUND IN AAC Standard Operating Procedures ...

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Page 61: ...cent 3 8 Maximum Glide Configuration 3 8 Landing Emergencies c 3 9 Gear up Landing 3 9 One engine inoperative Landing 3 9 One engine inoperative Go Around 3 10 Systems Emergencies 3 10 Operation on Crossfeed 3 10 Electrical Smoke or Fire 3 11 Complete Loss of Electrical Power 3 12 Illumination of Alternator Out Light 3 12A Starter Engaged Warning Light Illuminated 3 128 Unscheduled Electric Elevat...

Page 62: ...Section III Emergency Procedures BEECHCRAFT Duchess 76 TABLE OF CONTENTS Continued SUBJECT Simulated One Engine Inoperative Unlatched Door in Flight Spins PAGE 3 15 3 15 3 16 3 2 April 1979 ...

Page 63: ... are turned off The following information is presented to enable the pilot to form in advance a definite plan of action for coping with the most probable emergency situations which could occur in the operation of the airplane Where practir able the emergencies requiring immediate corrective action are treated in check list form for easy reference and familiarization Other situations in which more ...

Page 64: ...in control pressures or in the sound of the en gine if the correct throttle has been selected AT LOW ALTITUDE AND AIRSPEED THIS CHECK MUST BE ACCOMPLISHED WITH EXTREME CAUTION Do not attemptto determine the inoperative engine by means of the tachometers or the manifold pressure gages These instruments often indicate near normal readings ONE ENGINE INOPERATIVE PROCEDURES ENGINE FAILURE DURING GROUN...

Page 65: ...r inoperative engine FEATHER 4 Power operative engine AS REQUIRED 5 Airspeed AT OR ABOVE THE 50 FT TAKE OFF SPEED 80 KNOTS After positive control of the airplane is established 6 Secure inoperative engine a Mixture Control IDLE CUT OFF b Fuel Selector OFF c Aux Fuel Pump OFF d Magneto Start Switch OFF e Alternator Switch OFF f Cowl Flap CLOSE 7 Airspeed ESTABLISH 85 KTS 8 Electrical Load MONITOR M...

Page 66: ...EN BACK TO MIDRANGE USE STARTER MOMENTARILY IF AIRSPEED IS BELOW 100 KTS If propeller does not unfeather or engine does not turn proceed to WITHOUT UNFEATHERING ACCUMULATORS procedure 6 Mixture FULL RICH 7 If engine fails to run clear engine by allowing it to windmill with mixture in the FULL LEAN position When engine fires advance mixture to FULL RICH 8 When Engine Starts ADJUST THROTTLE PROPELLE...

Page 67: ...EATHERING DETENT TO MIDRANGE 7 Magneto Start Switch START and PUSH TO PRIME hold on START until windmilling begins and continue to prime as required NOTE If air start is unsuccessful return propeller control to the FEATHER position and secure engine 8 When Engine Starts ADJUST THROTTLE PROPELLER AND MIXTURE CONTROLS 9 Aux Fuel Pump OFF when reliable power has been regained 10 Alternator Switch ON ...

Page 68: ...rding to the following procedure and land immediately Follow the applicable single engine procedures in this section 1 Fuel Selector OFF 2 Mixture Control IDLE CUT OFF 3 Propeller FEATHER 4 AJ Jx Fuel Pump OFF 5 Magneto Start Switch OFF 6 Alternator Switch OFF EMERGENCY DESCENT 1 Propellers 2700 RPM 2 Throttles IDLE 3 Airspeed 140 KTS 4 Landing Gear DOWN MAXIMUM GLIDE CONFIGURATION 1 Propellers FE...

Page 69: ... Wing Flaps FULL DOWN ON 3 Throttles IDLE 4 Mixture Controls IDLE CUT OFF 5 Battery Alternator and Magneto Start Switches OFF 6 Fuel Selectors OFF 7 Keep wings level during touchdown 8 Get clear of the airplane as soon as possible after it stops NOTE The gear up landing procedures are based on the best available information and no actual tests have been conducted ONE ENGiNE INOPERATIVE LANDING On ...

Page 70: ... be possible for certain com binations of weight temperature and altitude In any event DO NOT attempt a one engine in operative go around after flaps have been fully extended 1 Power MAXIMUM ALLOWABLE 2 Landing Gear UP 3 Wing Flaps UP 4 Airspeed MAINTAIN 85 KTS MINIMUM SYSTEMS EMERGENCIES OPERATION ON CROSSFEED NOTE The fuel crossfeed syst m is to be used during emergency conditions i level flight...

Page 71: ...CTRICAL SMOKE OR FIRE Action to be taken must consider existing conditions and equipment installed 1 Battery and Alternator Switches OFF WARNING Electrically driven instruments and stall warning horn will become inoperative 2 All Electrical Switches OFF 3 Battery and Alternator Switches ON 4 Essential Electrical Equipment ON Isolate defective equipment NOTE Ensure fire is out and will not be aggra...

Page 72: ... Breakers PULL 4 Remove all electrical loads 5 Both Alternator Switches ON 6 Minimize all electrical loads Select only that electrical equipment which is essential for safe flight 7 Extend landing gear with emergency system 8 LAND AS SOON AS PRACTICAL HAVE THE COMPLETE ELECTRICAL SYSTEM CHECKED BEFORE THE NEXT FLIGHT CAUTION Since the battery is off line when this procedure is used large changes i...

Page 73: ...lights and loadmeter for proper operation CAUTION If proper operation is not restored turn alternator switch OFF In the event of the Hlumination of both AL TERNA TOR OUT UNDERVOL TAGE lights or both AL TERNA TOR OUT oVERVOL TAGE lights Check loadmeters for load indication If condition indicates malfunction of both alternator circuits a 80th ALT Switches OFF b Minimize electrical load since only ba...

Page 74: ...ches OFF 2 Do not take off Illuminated In Flight After Air Start 1 Perform action for COMPLETE LOSS OF ELECTRICAL POWER see this section 2 Land as soon as practical UNSCHEDULED ELECTRIC ELEVATOR TRIM 1 Airplane Attitude MAINTAIN using elevator control 2 Elevator Trim Thumb Switch on control wheel DEPRESS AND MOVE IN DIRECTION OPPOSITE UNSCHEDULED PITCH TRIM 3 Elevator Trim ON OFF Switch on instrum...

Page 75: ...hts and warning horn Check Landing GEAR CONTROL circuit breaker engaged WARNING After emergency landing gear extension d Imo imQ v e By laoding e geamECQnttels Th Of fesetti any switQb 2hQ fif QjIgY h gr JltilJ aifjplaQe is on dq ql s failure may have been in the gear up circuit and gear might retract with the airplane on the ground LANDING GEAR RETRACTION AFTER PRACTICE MAN UAL EXTENSION After pr...

Page 76: ...lt in the rate at climb indication being sluggish during a climb or de scent Verification ot suspected obstruction is possible by switching to the alternate system and noting a sudden sus tained change in rate ot climb This may be accompanied by abnormal indicated airspeed and altitude changes beyond normal calibration differences Whenever any obstruction exists in the Normal Static Air System or ...

Page 77: ... hazards 1 Throttle Lever 86tT 8rO ir gd t MANIFc ill J ElESSURE 2 Propeller Lever RETARD TO FEATHER DETENT NOTE This setting will approximate Zero Thrust using recommended one engine inoperative climb speeds I UNLATCHED DOOR IN FLIGHT If the cabin door is not secured it may come unlatched in flight This usually occurs during or just after takeoff The door will trail in a position approximately 3 ...

Page 78: ...ns should be done as nearly simultaneously as possible then continue to hold this control position until rotation stops and then neutralize all controls and execute a smooth pullout Ailerons should be neutral during recovery NOTE Federal Aviation Administration Regulations do not require spin demonstration of airplanes of this class therefore no spin tests have been conducted The recovery techniqu...

Page 79: ...AUSTRALIAN AVIATIION COLLEGE B76 SECTION IV NORMAL PROCEDURES 1HE NORMAL CHECKLIST FOR MC FLIGlIT OPERATIONS IS FOUND IN AAC Standard Operating Procednres ...

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Page 81: ...tarting and Taxi 4 1 OA Before Takeoff 4 1 OB Takeoff 4 11 Climb 4 12 Cruise 4 12 Leaning Mixture Using EGT Indicator 4 13 Descent 4 13 Before Landing 4 13 Balked Landing 4 14 After Landing 4 14 Shutdown 4 15 Environmental Systems 4 15 Heating and Ventilation 4 15 Electric Elevator Trim 4 15 Cold Weather Operation 4 16 Preflight Inspection 4 16 Engines 4 16 Taxiing 4 17 Practice Demonstration of Y...

Page 82: ... BL6 uenuer lNYl9 1 131 A11VNOI LN3 1NI 9L ssa4 no 1 I o l t H 339 saJnpaooJd leWJoN A uon as ...

Page 83: ... kts I 50 ft Speed 80 kts Two Engine Best Angle ot Climb VX 71 kts Two Engine Best Rate ot Climb Vy 85 kts Cruise Climb 100 kts Turbulent Air Penetration 132 kts Landing Approach Flaps UP 87 kts Flaps DOWN ON 76 kts I Balked Landing Climb 71 kts Intentional One Engine Inoperative Speed VSSE 71 kts Air Minimum Control Speed VMCA 65 kts I PREFLIGHT INSPECTION 76 604 1 o u t o flF L 9 J 1t J _ c i r ...

Page 84: ...ler caps 2 LEFT WING TRAILING EDGE a Flap CHECK GENERAL CONDITION b Fuel Vent CHECK UNOBSTRUCTED c Aileron CHECK GENERAL CONDITION AND FREEDOM OF MOVEMENT d Wing Tip CHECK e Position and Strobe Light CHECK 3 LEFT WING LEADING EDGE a Pitot REMOVE COVER EXAMINE FOR OB STRUCTIONS b Landing and Taxi Light CHECK c Stall Warning Vane CHECK FREEDOM OF MOVEMENT d Fuel Tank CHECK QUANTITY Cap SECURE e Tied...

Page 85: ...tool 4 NOSE SECTION a Nose Cowling and Nose Cone CHECK CONDI TION AND SECURITY b Heater Air Intake CLEAR c Heater Exhaust and Vents CLEAR d Wheel Well Doors Tire and Strut CHECK 5 RIGHT WING LEADING EDGE a Flush type Crossfeed Fuel Drains 2 DRAIN use fuel drain tool b Wheel Well Door Tire Brake Line and Strut CHECK c Engine Cowling CHECK CONDITION AND SECURITY d Air Intakes CLEAR e Propeller EXAMI...

Page 86: ... Tip CHECK o Position and Strobe light CHECK 6 RIGHT WING TRAILING EDGE a Aileron CHECK CONDITION AND FREEDOM OF MOVEMENT b Fuel Vent CHECK UNOBSTRUCTED c Flap CHECK GENERAL CONDITION 7 FUSELAGE RIGHT SIDE a Battery Vents CHECK UNOBSTRUCTED b Static Port CLEAR OF OBSTRUCTIONS c Emergency Locator Transmitter ARMED 8 EMPENNAGE a Control Surfaces and Trim Tabs CHECK b Tail Cone and Position light CHE...

Page 87: ...ITION AND LOCK Seat Backs UPRIGHT 3 Seat Belts and Shoulder Harnesses FASTEN 4 Parking Brake SET 5 All Avionics OFF 6 Circuit Breakers IN 7 Landing Gear Handle DOWN 8 Carburetor Heat OFF up position 9 Cowl Flap Controls OPEN down position 10 Fuel Selectors CHECK OPERATION THEN ON 11 Light Switches OFF 12 Battery and Alternator Switches ON 13 Fuel Quantity Indicators CHECK QUANTITY See LIMITATIONS ...

Page 88: ...ents power fluctuations 2 The airplane has a negative ground system Be sure to connect the positive lead of the auxiliary power unit to the positive terminal of the airplane s external power receptacle and the negative lead of the auxiliary power unit to the negative terminal of the external power receptacle 3 To prevent arcing make certain no power is being supplied when the connection is made ST...

Page 89: ...NDERVOLTAGE Lights ILLUMINATED 2 Mixture FULL RICH 3 Propeller HIGH RPM Low Pitch 4 Throttle FAST IDLE 1 4 Travel 5 Aux Fuel Pump ON 6 Magneto Start Switch Engage starter PUSH TO PRIME as engine is cranking Release to BOTH position when engine starts WARNING Do not pump throttles during starting procedures Hot Start Engine Hot a Mixture FULL RICH b Throttle FAST IDLE 1 4 Travel c Fuel Boost Pump O...

Page 90: ...tarter Engaged Warning Light if installed CHECK should be illuminated during start and extinguished after start Using same procedure start other engine Left Alternator Switch and Battery Switch OFF Check for Left ALTERNATOR OUT UNDERVOLTAGE Light illuminated and an indication of less than 75 14 volt system or 40 28 volt system on the right loadmeter Left Alternator Switch and Battery Switch ON Rig...

Page 91: ...s not installed or is inoperative and the loadmeters and or ALTERNATOR OUT UNDERVOLTAGE lights do not indicate illuminate properly an electrical malfunction is indicated The battery switch and both alternator switches should be placed in the OFF position Do not take off AFTER STARTING AND TAXI CAUTION Never taxi with a flat tire or flat shock strut During taxi operations particular attention shoul...

Page 92: ...UTION Detuning the counterweight system of the engine can occur by rapid throttle operation high rpm low pitch and low manifold pressure or propeller feathering See latest revision of Lycoming Service Bulletin No 245 BEFORE TAKEOFF 1 Seat Belts and Shoulder Harnesses CHECK 2 Parking Brake SET 3 Radios CHECK 4 Flight Instruments CHECK AND SET 5 Engine Instruments CHECK 6 Starter Engaged Warning Lig...

Page 93: ...n and recheck 15 Carburetor Heat CHECK and set OFF cold for takeoff 16 Throttles 1500 RPM 17 Propellers FEATHER CHECK Do not exceed 500 rpm drop Repeat 3 or 4 times in cold weather 18 Gyro Pressure and Loadmeters CHECK 19 Throttles IDLE 20 Aux Fuel Pumps CHECK ON 21 Doors and Window SECURE 22 Parking Brake RELEASE 23 Engine Instruments CHECK TAKEOFF Take off Power Full Throttle 2700 rpm 1 Power SE...

Page 94: ...m Climb Full Throttle 2700 RPM ICruise Climb Full Throttle 2600 RPM 1 Engine Temperatures MONITOR 2 Power SET 3 Mixtures LEAN AS REQUIRED 4 Cowl Flaps AS REQUIRED 5 Aux Fuel Pumps OFF CRUISE Maximum Cruise Power Recommended Cruise Power Recommended Cruise Power Economy Cruise Power 24 0 in Hg or full throttle at 2700 rpm 24 0 in Hg or full throttle at 2500 rpm 24 0 in Hg or full throttle at 2300 r...

Page 95: ...tor shows a drop of 7SoF to 100 F on rich side of peak CAUTION Do not continue to lean mixture beyond the point necessary to establish peak temperature Continuous operation is recommended at 2SoF or below peak EGT only on rich side of peak 2 Changes in altitude and power setting require EGT to be rechecked and mixture reset 3 A mixture resulting in an EGT 2SoF on the rich side of peak should also ...

Page 96: ...esses FASTENED SEAT BACKS UPRIGHT 2 Fuel Selectors CHECK ON 3 Aux Fuel Pumps ON 4 Mixture Controls FULL RICH or as required by field elevation 5 Carburetor Heat FULL ON or FULL OFF AS REQUIRED NOTE In the event of a go around Carburetor Heat shall be in the full OFF cold position after full throttle application 6 Cowl Flaps AS REQUIRED 7 Landing Gea DOWN 140 KTS Maximum 8 Landing and Laxi Lights A...

Page 97: ...ED 2 Wing Flaps UP 3 Trim Tabs SET TO TAKE OFF RANGE 4 Cowl Flaps OPEN SHUTDOWN 1 Parking Brake SET 2 Aux Fuel Pumps OFF 3 Electrical and Avionics Equipment OFF 4 Propellers HIGH RPM 5 Throttles 1000 RPM I 6 Mixtures IDLE CUT OFF 7 Magneto Start Switches OFF after engines stop 8 Battery and Alternator Switches OFF 9 Controls LOCKED 10 Install wheel chocks and release brakes if the airplane is I to...

Page 98: ...Section IV Normal Procedures BE CHCRAFT Duchess 76 4 148 INTENTIONALLY LEFT BLANK September 1983 ...

Page 99: ...peration of heating and ventilation controls ELECTRIC ELEVATOR TRIM 1 On Off Switch ON 2 Control Wheel Trim Switch Depress and move forward for nose down aft for nose up and when released the switch returns to the center OFF position Procedure for UNSCHEDULED ELECTRIC ELEVATORI TRIM is given in EMERGENCY PROCEDURES Section September 1983 4 15 ...

Page 100: ...ils The normal preflight procedures should then be completed with particular attention given to check of flight controls for complete freedom of movement ENGINES Use engine oil in accordance with Consumable Materials in the HANDLING SERVICING AND MAINTENANCE section WARNING Ascertain that magneto start switches and battery master switch are OFF before moving propeller by hand Always pull the prope...

Page 101: ...r broken oil lines oil cooler leaks or the possibility of congealed oil NOTE It is advisable to use external power for starting in cold weather During warm up monitor engine temperatures closely since it is quite possible to exceed the cylinder head temperature limit in trying to bring up the oil temperature Exercise the propellers several times to remove cold oil from the pitch change mechanism T...

Page 102: ...5 Throttle simulated inoperative engine IDLE 6 Throttle other engine FULL FORWARD 7 Airspeed REDUCE approximately 1 knot per second until either VMCA or stall warning is obtained CAUTION Use rudder to maintain directional control heading and ailerons to maintain 5 bank towards the operative engine lateral attitude At the first sign of either VMCA or stall warning which may be evidenced by inabilit...

Page 103: ...the surface weather permitting even though flight at a lower level may be consistent with the provisions of government regulations NOTE The preceding recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions or where in the pilot s judgement an altitude of less than 2000 feet is necessary to adequately exercise his duty to see and avoid other...

Page 104: ... ...

Page 105: ...imeter Correction Alternate System 5 19 Fahrenheit to Celsius Temperature Conversion 5 20 ISA Conversion 5 21 Manifold Pressure vs RPM 5 22 Take OffWeight 5 23 Stall Speeds Power Idle 5 24 Wind Components 5 25 Take Off Distance 5 26 Take Off Distance Grass Surface 5 27 Accelerate Stop Distance 5 28 Accelerate Go Distance 5 29 Climb Two Engine 5 30 Take Off Climb Gradient One Engine Inoperative 5 3...

Page 106: ... Power 5 37 Recommended Cruise Power 5 38 Recommended Cruise Power 5 39 Economy Cruise Power 5 40 Range Profile 100 Gallons 5 408 Endurance Profile 100 Gallons 5 41 Holding Time 5 42 Time Fuel and Distance to Descend 5 43 Climb Balked Landing 5 44 Landing Distance Flaps Down DN 5 45 Landing Distance Flaps Up 5 46 Landing Distance Grass Surface Flaps Down DN 5 47 5 2 January 1982 ...

Page 107: ...at various parameters of weight power altitude and tempera ture FAA approved performance information is included in this section Examples are presented on all performance graphs In addition the calculations for flight time block speed and fuel required are presented using the conditions listed CONDITIONS At Denver Outside Air Temperature 15 C 59 F Field Elevation 5330 ft Altimeter Setting 29 60 in...

Page 108: ...ow Altitude Chart L 6 At Amarillo Outside Air Temperature 25 C 77 F Field Elevation 3605 ft Altimeter Setting 29 56 in Hg Wind 180 at 10 kts Runway 21 Length 10 000 ft To determine pressure altitude at origin and destination air ports add 100 feet to field elevation for each 1 in Hg below 29 92 and subtract 100 feet from field elevation for each 1 in Hg above 29 92 Pressure Altitude at DEN 29 92 2...

Page 109: ...between cruise altitude and cruise pressure altitude has been ignored Maximum Allowable Take off Weight 3900 Ibs Ramp Weight 3900 16 3916 Ibs NOTE Fuel for start taxi and takeoff is normally 16 pounds Enter the Take Off Weight graph at 5650 feet pressure alti tude and 15 C The take off weight to achieve a positive rate of climb at lift off for one engine inoperative is Take off Weight 2925 pounds ...

Page 110: ...ccelerate Stop Distance 3250 ft NOTE Since 3250 feet is less than the available field length 10 010 ft the accelerate stop procedure can be performed at any weight Takeoff at 3900 Ibs can be accomplished How ever if an engine failure occurs prior to retraction of landing gear the accelerate stop procedure must be performed even if airborne unless suf ficient altitude is available for retraction of...

Page 111: ...altitude 3350 pounds and 10 knots headwind component Total Distance Over 50 ft Obstacle 4700 ft Ground Roll 940 ft Enter the graph for Take off Climb Gradient One Engine Inoperative at 15 C SL pressure altitude and 3350 pounds Climb Gradient 4 6 A 4 6 climb gradient is 46 feet of vertical height per 1000 feet of horizontal distance NOTE The Take off Climb Gradient One Engine I Inoperative graph as...

Page 112: ...0 870 5570 feet The above results are illustrated below w o wlI t t g i 0 r II fiJa 46 FT 1000 ENGINE FAILURE HERE FT 1 3 2 I I CD AcceIerate go take off distance 4700 feet CD Distance to climb from 50 ft to 90 ft above I Nnway 870 feet The following calculations provide information for the flight planning procedure All examples are presented on the per formance graphs A take off weight of 3900 po...

Page 113: ... F below a standard day SA 20 C These should be used for flight planning The OAT values are true temperature values which have been adjusted for the com pressibility effects IOAT should be used for setting cruise power while enroute Enter the graph for ISA conversion at 11 500 feet and the temperature for the route segment DEN PUB PUB TBE TBE DHT DHT AMA OAT 5 C ISA Condition ISA 3 C OAT DOC ISA C...

Page 114: ... 8 157 19 4 8 5 158 12 000 18 7 8 5 156 18 7 8 2 156 Interpolate for 11 500 feet and the temperature for the ap propriate route segment Results of the interpolations are MAN FUEL ROUTE PRESS FLOW TAS SEGMENT IN HG GPH ENG KNOTS DEN PUB 19 1 8 7 157 PUB TBE 19 1 8 6 157 IrBE DHT 19 1 8 5 157 PHT AMA 19 1 8 4 157 NOTE The above are exact values for the assumed conditions 5 10 January 1918 ...

Page 115: ...nd fuel used were calculated at Recommended Cruise Power 24 in Hg 2500 RPM as follows T Distance Ime Ground Speed Fuel Used Time Total Fuel Flow Results are FUEL EST TIME AT USED GROUND CRUISE FOR ROUTE DISTANCE SPEED ALTITUDE CRUISE SEGMENT NM KNOTS HRS MIN GAL DEN COS 41 184 13 3 8 COS PUB 40 183 13 3 7 PUB TBE 74 143 31 8 9 TBE DHT 87 146 36 10 2 DHT AMA 44 148 18 5 1 Distance required to climb...

Page 116: ...8 321 Total Flight Time 2 hours 5 minutes Block Speed 321 NM 2 hours 5 minutes 154 knots Reserve Fuel 45 minutes at Economy Cruise Power Enter the cruise power settings table for Economy Cruise Power at 11 500 feet for ISA assume ISA Fuel Flow Rate Fuel Flow Per Engine 8 0 gallhr Total Fuel Flow 16 0 gal hr 96 Ibs hr Reserve Fuel 45 min 96 Ibs hr 72 Ibs 12 gal Total Fuel 39 8 12 0 51 8 gallons 5 1...

Page 117: ...e performance graphs The above conditions have been used throughout Rate of climb was determined for the initial cruise altitude conditions Enter the graph for Landing Distance Flaps Down DN at 25 C 3965 feet pressure altitude 3677 pounds and 9 5 kts headwind component Ground Roll 1050 ft Total Distance over 50 ft Obstacle 1970 ft Approach Speed 76 kts Enter the graph for Climb Balked Landing at 2...

Page 118: ...o begin following guide lines always project to the reference line first then follow the guide lines to the next known item 3 Indicated airspeeds lAS were obtained by using the Airspeed Calibration Normal System 4 The associated conditions define the specific conditions from which performance parameters have been determined They are not intended to be used as instructions however performance value...

Page 119: ...9L6 usnuer 4NV18 1 131 Al1VNOI lN3J NI 9L SS84 na uVI OH l338 ...

Page 120: ... FLAPS DOWN ON CAS 75KTS w 3 g IlJ J 2 c I J II I A CD en 140 b 130 1 o ill 120 a 110 iJ 100 co 90 80 70 60 120 t H cn FLAPS DOWN ON b 110 z I o 100 w w a cn 90 II 0 eo co 70 m m 60 om CO C E 50 1 m u 60 70 eo 90 100 110 120 130 140 150 160 50 60 70 80 90 100 110 120 0 11 lAS INDICATED AIRSPEED KNOTS JAS INDICATED AIRSPEED KNOTS at ...

Page 121: ...XAMPLE 60 70 80 90 100 110 120 lAS INDICATED AIRSPEED KNOTS em c m o m To ell J 0 0 tTI 1 1 llell i Q 3 III 0 130 140 l l 20 000 SL W 11 0 I I G PS DOWN ON 50 20 10 Iii Ie 5 I Z 0 0 W a 0 8 a 10 o 20 IE i J 30 150 160 80 90 100 110 120 130 140 lAS INDICATED AIRSPEED KNOTS 70 30 tu w w u 0 I j z i Q 20 f 0 W a a o 0 a 2 10 0 0 0 Vi 60 j w co t III l C III ...

Page 122: ...o m D 0 at 1 Ucn CO CO la o _ 0 3 J II J 2 i 1 trn lI o v 9 fp s c i f i is l EXAMPLE rn FLAPS Up STORM WINDOW OPEN lAS NORMAL SYSTEM 85 KTS lAS ALTERNATE SYSTEM 91 KTS 120 lmffff l f ffi ffii Im Im li J l AP C nnwh tn n I 110 100 l2 90 80 a 70 80 I50 i 40 lJl OG 170 160 E 12 FLAPS UP 150 I o 140 w w Go 130 a I 120 u i5 110 100 I 90 C 80 III r t t l ln1141 2 I i c 70 III 80 A U 80 70 80 90 100 110...

Page 123: ... J 0 0 OIl 60 70 80 90 100 110 120 130 140 150 160 170 ALTERNATE SYSTEM INDICATED AIRSPEED KNOTS D II i 3 _ III 0 140 S s S L _ WINDOW 20 000 tOPEN o 60 70 80 90 100 110 120 13 ALTERNATE SYSTEM INDICATED AIRSPEED KNOTS 100 o lii I 100 m Z i t 1 300 160 PAils I t ITr Suf IT _ tfr 1 EiA trUD 1212 W Sfl fitt fl WCfAr D i10 00 H r V O N _J ooo FLAPS UP 6 1 OdO LffB 100 5 51 tu 0 I ZW 00 E 2 ex 00 5 20...

Page 124: ...I 1 I I A 8 0 0 0 0 0 o 0 0 0 1 0 I 8 I T1 A lJo 0 I 1 a 0 m z 1 I 0 m I t 0 0 0 0 m fJ 0 c fJ 0 0 t m Cl m ll 3 m m 0 V rJ m A u 0 lJo t 8 C a m 0 0 0 Z m zJ fJ 0 0 Z 0 8 0 STo oo 44A 9LSSa40na J JVl IOH033a ueWJOjJad AUOlJOas ...

Page 125: ... J o 3 3 g 40 50 60 70 80 80 70 60 50 40 30 20 10 10 20 30 TEMPERATURE c D O J T I 1 j 5000 rrlTTTTrlTriT II f om em n m f 25 000 i 0 a 0 I 20 000 r w w LL C5 15 000 J r r J w II 10 000 J j j W II a ...

Page 126: ...TING AREA OPERATING AREA g 1 o _ 0 3 s AI m m em c 0 x ro m o I 2700 2600 2500 RECOMMENDED VALUES OF 1 1 1 MP AND RPM FOR CRUISE 4 POWER SETTINGS 2100 2200 2300 2400 ENGINE SPEED RPM _ J3ItfltIJJ ltl uf l1Imlill1tt 2000 1900 30 29 28 27 el r 26 I ll 25 ill 24 a Q 23 9 0 22 21 20 19 18 I 1800 Ul N f lD j 00 e III s c III ...

Page 127: ...FLAPS UP LANDING GEAR DOWN INOPERATIVE PROPELLER FEATHERED PRESSURE ALnTUDE 5650 FT OAT 15 C TAKE OFF WEIGHT 2925 LBS T r r I I j I j I I I L L L J 1 I 1 i 1 I i 1 tllitL _ PU S o 9 1 1 0 0 1 1 v 00 I o 0 o b Q 0 Ci b j 10 000 9000 8000 7000 f w w u I 6000 w 0 J 5000 i J w 4000 a J 3000 w a a 2000 1000 SL 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 WEIGHT POUNDS August 1980 5 23 ...

Page 128: ...RMAL STALL RECOVERY TECHNIQUE MAY BE USED EXAMPLE WEIGHT 3 77 LBS FLAPS DOWN ON ANGLE OF BANK 30 STALL SPEED 64KTS lAS 62KTSCAS w t a 0 0 I I I I S q jt IJ1 1 1 1 1 1 _ lAS INDICATED AIRSPEED CAS CALIBRATED AIRSPEED I iii I I I Iii iii I I iii I m I 4 t t J I J l I d 1 1 1 FLAPS UP w I 0 Ih 0 90 5 60 2 I J 70 Ii li t tt t t li J l l l l lttl l I I l Co I I c I eo FLAPS DOWN ON llmITP EEl 3 00 3600...

Page 129: ... KNOTS L1FT OFF 50 FEET ASSOCIATED CONDITIONS POWER TAKE OFF AT 2700 RPM SET BEFORE BRAKE RELEASE FLAPS UP LANDING GEAR RETRACTAFTER POSITIVE CLIMB ESTABLISHED RUNWAy SHORT DRY GRASS LEVEL SURFACE COWL FLAPS OPEN MIXTURE FULL RICH ABOVE SOOO FT LEAN TO 75G 100 F ON RICH SIDE OF PEAK EGn fr c W i CO ilol C ilol _ 1 J yp r O OIJ _ I c Y I O 4000 Iii If I W U 3000 o 40 30 20 0 0 0 20 30 OUTSIDE AIR T...

Page 130: ... DECISION SPEED 71 KTS ili W __ _ tiil a a ACCELERATE STOP DISTANCE DECISION SPEED 71 KNOTS ALL WEIGHTS EXAMPLE 0 1 ASSOCIATED CONDITIONS i 1Et1J Qi1 ffiijifflJT J j ttW 1 r iI O 1 1 t Qo l tt Oli I f i1f wt Sl il1l Fffffif1 POWER 1 TAKE OFF POWER AT 2700 APM SET BEFORE BRAKE RELEASE 2 ENGINE IDLE AT DECISION SPEED FLAPS UP RUNWAy PAVED LEVEL DRY SURFACE COWl FLAPS OPEN MIXTURE FULL RICH ABOVE 5ll...

Page 131: ...T AFTER lIFT OFF RUNWAy PAVED LEVel DRY SURFACE COWL FLAPS OPEN MIXTURE FULL RICH ABOVE 5000 FT SET TO 7S 100 F ON RICH SIDE OF PEAK EGT em c m om f IJ 0 J 6000 1 tu t wi z 7000 I J w J ffi J a 6000 13 w 0 a fi 5000 a 0 w J 4000 i1 0 LL iOOOq w 3 2000 I 0 0 10 20 30 WIND COMPONENT KNOTS EXAMPLE OAT 15 C PRESSURE ALTITUDE SL TAKE OFF WEIGHT 3350 LBS HEADWIND COMPONENT 10 KTS TOTAL DISTANCE OVER 50 ...

Page 132: ...EGT EXAMPLE OAT 1O C PRESSURE ALTITUDE 11 500 FT WEIGHT 3880 las RATE OF CLIMB 500 FTIMIN CLIMB GRADIENT 4 6 3 g II g 2000 24 Z J 22 2Q m 1500 lB b SA a lB 14 12 1000 I I I 10 ffi 10 i oo III e LI f l 6 g 2 000 J 14 000 500 I III Ii 4 l fi T J J 20 fJOi 2 to m I 0 0 m I em c c 0 ill j 2 n t To 500 4 m o 0 tIl lo I 60 50 40 30 2Q 10 0 10 20 30 40 50 60 3800 3500 3400 3200 3000 2600 C OUTSIDE AIR TE...

Page 133: ...T 3350 LBS GRADIENT OF CLIMB 4 6 _I J I I I J J I 7 em c m elm 10 CD t l 0 u C ll o 1 H I I I I I I I I l j I w ttl l Ijjjj ltl z J _ rmrrrm rrl l llj llfllitlItmfllJ P I L ffi R ss j I i ttl tl I UF It __ l l r ALrl7 UD W l a mWJjum gISAHfEHH l t1f1 tmf jtl l J I1ll 6 5 4 rfl I 3 w 2 J en o a 40 30 20 10 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURE c 3800 3800 3400 3200 3000 WEIGHT POUNDS I itmf lfll...

Page 134: ...I 1 1v 4 I f SSUI SO flV _ pI f l 1 J 1m ASSOCIATED CONDITIONS POWER FULL THROTTLE AT 2600 RPM FUEL OENSITY 6 0 lBS OAL COWL FLAPS OPEN MIXTURE FULLRICH ABOVE 5000 FT LEAN TO 7S loo F ON RICH SIDE OF PEAK EGT C 1 w ii Ebti 8000 6QOO tI jQt c W l C W co so 40 30 20 10 0 10 20 30 40 OUTSIDE AIR TEMPERATURE C 50 o t 20 30 0 t TIMEtTO CLIMB MINUT ES I I I I I I I I I I I I I o 2 6 6 10 12 14 r r t FUl...

Page 135: ...T LEAN TO 75 iWFON RICH SIDE OF PEAK EGT EXAMPLE OAT 25 C PRESSURE ALTITUDE 3965 FT WEIGHT 3677lBS RATEOFCLlMB 140FT MIN CLIMB GRADIENT 1 5 CLIMB SPEED 85 KTS CtD c m n m TO CD x 0 I Il en 50 40 3 20 10 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURE _ C Ji W W il L1r SA 1 1 1 w tBi 3800 f 1 3600 j 3400 3200 WEIGHT POUNDS 3000 400 l 300 l1 200 1 100 t I o i 00 9 I 200 Cl 300 400 500 2800 7 6 5 4 3 2 I z ...

Page 136: ...PERATIve PROPELLER FEATHERED EXAMPLE OAT AT MEA soc ROUTE SEGMENT MEA 9700 FT WEIGHT FOR SERVICE CEIUNG AT ROUTE SEGMENT MEA 3480 LBS NOTE SeRVICE CEIUNG IS ALTITUDE WHERE AlRPlANE HAS CAPABILITY OF CUMBING so FTIMIN WITH ONE PROPEUER FEATHERED sooo 15 000 m I Cl 5 10 000 iii u w U SL 5 34 lVEJGHT POUNDs Oti J l t o 1 1 3901i 60 so 40 30 20 10 0 10 20 30 40 so 60 OUTSIDE AIR TEMPERATURE C January ...

Page 137: ...MPERATURE STD DAY ISA POWER SETTING 20 IN HG 2300 RPM TRUE AIRSPEED 139 5 KTS 14 000 0 r d 1 1 O C e 11 rt 12 000 T _ _ 170 160 1 T k 0 t I 0l f Q r R c curS J o V 0 0 Q tffii c d b Ii Q 120 130 140 150 TRUE AIRSPEED KNOTS 110 I i 100 S L 6000 j rff i I JJ tf t T O t t V 2000 0 C 0 4000 8000 I W W u I 10 000 w o I 5 w a f f w a a January 1982 5 35 ...

Page 138: ... 3 156 153 15 59 24 0 65 10 8 152 155 35 95 24 0 63 10 5 148 156 24 0 68 11 3 156 155 13 55 24 0 66 11 0 152 157 33 91 24 0 63 10 5 148 158 24 0 69 11 5 156 158 11 52 24 0 66 11 0 152 159 31 88 24 0 64 10 7 148 161 24 0 69 11 5 157 160 9 48 24 0 67 11 2 153 162 30 86 24 0 65 10 8 149 163 24 0 70 11 7 157 163 8 46 24 0 68 11 3 153 164 28 82 24 0 65 10 8 148 165 23 5 70 1 1 1 156164 643 3 5 6 8h 3 1...

Page 139: ...0 2 144 163 7000 17 1 22 7 63 10 5 150 160 4 39 2 t7 61 10 145 161 24 75 22 1 59 9 13 141 162 8000 19 2 21 9 61 10 2 146 159 2 36 21 9 59 9 8 142 160 22 12 21 9 57 9 5 136 1 1 9000 21 6 21 0 59 9 8 143 158 0 32 21 0 57 9 5 139 159 20 a8 21 55 9 2 135 160 10 000 23 9 20 2 57 9 5 140 157 3 27 20 2 55 9 2 136 15B 1a 64 20 2 53 8 8 132 159 11 000 25 13 19 4 55 9 2 137 156 5 23 19 4 53 13 8 133 is 16 8...

Page 140: ...000 13 9 24 0 60 10 0 148 154 7 45 24 0 58 9 7 144 155 27 Sl 24 0 56 9 3 140 156 0 16 23 7 61 i 16 148 i1 Sij i5 f Mj7 5 Jj 4 gr 25 1 f 79 5 i1W1 8 600 7 000 1 1 2 2 5 9 8 j S 1 5 7 2 S 5 4 9 5 J i 6 i S 2 a 9 ii 1 3 7 S J tJ 9 r 1 JP _ t Y 00 8 006 l1 l 2 H g7 r 5 Ff J i Yf gj it S i2 1 j55 f1 7 j l 5 8 8 1 34 156 1 if 1 39153 laO 2flGS a s sifls 1 g j n s1 s if H It d 3 ij a6 1 2 7 20 3 1 8 S b ...

Page 141: ... 88 20 0 41 6 8 122 132 4000 11 12 20 0 45 7 5 131 134 9 48 20 0 43 7 2 127 135 29 84 20 0 42 7 0 122 135 5000 13 9 20 0 46 7 7 131 136 7 45 20 0 44 7 3 127 137 27 81 20 0 43 7 2 123 137 6000 15 5 20 0 47 7 8 132 139 5 41 20 0 45 7 5 128 140 25 77 20 0 44 7 3 124 140 7000 17 1 20 0 48 8 0 133 142 3 37 20 0 46 7 7 128 143 23 73 20 0 45 7 5 124 143 8000 19 2 20 0 49 8 2 133 145 1 34 20 0 47 7 8 129 ...

Page 142: ... 0 33 5 5 108 118 26 79 18 0 32 5 3 103 117 6000 16 4 18 0 36 6 0 113121 540 18 0 35 5 8 109 121 25 76 18 0 33 5 5 105120 7000 17 1 18 0 37 6 2 115 125 3 37 18 0 36 6 0 110 124 23 73 18 0 34 5 7 106 124 8000 19 3 18 0 38 6 3 116 128 1 33 18 0 37 6 2 111 127 21 69 18 0 35 5 8 106 127 9000 21 6 18 0 39 6 5 117 131 1 30 18 0 38 6 3 112 130 19 66 18 0 36 6 0 108 130 10 000 23 10 18 0 40 6 7 117 134 3 ...

Page 143: ... I10v S la6 AJenuer 4NV S L I3 A 1N0 IJ N3 l NI aoueWJOJ Jad I UO IOas 9L SSalt0na l IVl f H 33S ...

Page 144: ... I I l l I I I I 1 I i I I f ril I ttl I f l l I f It Wt 1 1 t liiIj liil l tfI O Ei g NTI t frU IEK s AE R IMFBUE A 20 000 L 1 I I I I I till RECOMMENDED CRUISE 201 30 0 fr _ f IIIJ II 1 11 1 1 I U 1 I II 11 iJ iT H H1l1H w I lt l 1 Iii I lili j FT FULL THROTTLE I I 1 I Ii t T T IT 1 111 ill J j J L 1 T 1 1 1 1 iT I I Ii II II I i I 153 148 h 137 1 i j II w 1 i II I I RlM I 4I i II g15 000 1 I II...

Page 145: ...l Il ItllUJI IJ1ll1U I 1Ullfln11WHtHHlllUJ llmmlffiJ lTU NOTE ENDURANCE INCLUDES START TAXI CLIMB AND j l DESCENT WITH 45 MINUTES RESERVE FUEL AT iI RECOMMENDED CRUISE 20 2300 B 20 000 Hi 1 1 I t J A t I LE 153 7 W FT FULL THROTT 1 1 1 t t T o 15 000 l t t ht l 1 1 1 I IJII I i n n Z A l I f __ v j iI 160 t b 5f 36 TRUE AIRSPEED KNOTSIt 11 i ll II 1II II Ii 1 11 a 10 000 rtf n I j rH 1 I 11 fJl I ...

Page 146: ...NG TIME 3 3 HOURS nr ifJ t f 1 _ _ _ _ M _ _ _ __ 0_ _ __ _ In 0 l I I 00 0 I I i j I tltLtLlttlllttltttt ttt fT1 j li C FJ t C O O i r f lIT _ Let 1 O O 1 J 30 40 50 60 70 FUEL REQUIREMENT GALLONS ttlt1 I Utlfhll llttJ j 20 J tl H nHHH1 HlJ f l j ji j t l lJ l l t I m l lf HHffiL1TI r j nTn nTULlll IT ITTJ1 JIT T TJT1JTr r J l _ _ __ TTJ _ _ r lt t 11 t 11 I j J I j I j I II j I I I I l I I _ 1 _...

Page 147: ...E OF PEAK EGT EXAMPLE INITlALAlnTUDE 11 500 Fr FiNAl AlTITUDE 3965 FT TIME TO DESCEND 10 4 6 MINUTES FUELTO DESCEND 3 4 1 3 2 1 GAL DlSTANCETOOESCEND 32 11 21NM 16 I 12 14 p p ri i 4 2 6 8 14 I TIME TO DESCEND MINlJTES t T 16 000 15 000 14 000 13 000 12 0c0 11 000 l 10 000 w 9000 0 eooo w a 7000 U U w a 6000 a sooo 4000 3000 2000 1000 SL I 0 5 4 o 2 3 I FUEL TO DESCENO GAlLONS t I I I 1 1 Ir I 1 1...

Page 148: ... 9OO I 700 600 15 500 m 000 100 3800 3800 3 lO 3200 WOO 2900 WEIGHT POUNDS w 5 I CLIMB BALKED LANDING I o IlA Y Q U PmJ1 I Uli 1 til IJ U Il f E i ASSOCIATED CONDITION POWER TAKE OFF A12700 RPM FtAPS DOWN DN CLIMB SPEED 71 KNOTS ALL WEIGHTS lANDING GEAR DOWN MIXTURE FULL RICH IIBOVE 5000 FT lEAN TO 75 l00 F ON RICH SIDE OF PEAK EGl w w 10 0 10 W OUTSIDE AIR TEMPERATURE C i A t ...

Page 149: ...t z lil z tltH q 11 1 I ftlili 1 I hlll l IF l i _ e l fJ l lt 1 1 1 1 I _ oJ _ a 0 Q 1 5 I 0 t 2500 wv Y lf r j f j 1 tf f 1 I f __ t tj 2000 w 0 w I u D is ASSOCIATED CONDITIONS POWER RETARD TO MAINTAIN 600 FT MIN ON FINAL APPROACH FLAPS DCWN ION LANDING GEAR DOWN RUNWAY SHORT DRY GRASS APPROACH SPEED 76 KTS BRAKING MAXIMUM 40 30 20 10 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURE C if LANDING DISTAN...

Page 150: ......

Page 151: ...rm 6 7 Loading Instructions 6 8 Weight and Balance Record 6 9 Moment Limits vs Weight Graph 6 12 Moment Limits vs Weight Table 6 13 Computing Procedure 6 14 Sample Weight and Balance Loading Form 6 15 Weight and Balance Loading Form 6 16 Useful Load Data Occupants 6 17 Baggage 6 18 Usable Fuel 6 19 Airplane Papers furnished with individual airplane August 1980 1 ...

Page 152: ...BL6 An mUer fNV18 1 131 A11VNOIJ N3J NI G 9 9L ssall ma 1 IVHOH0338 lSn d nb3 1B8 S lM IA UO lOas ...

Page 153: ...rainable fuel remain in the airplane at F S 124 8 The remainder of the unusable fuel to be added to a drained system is 18 0 pounds at F S 123 0 If the airplane is weighed with fuel tanks topped off full the fuel specific weight pounds gallon should be determined by using a hydrometer Compute total fuel weight by multiplying mea sured specific weight by 100 gallons Fuel moment is de termined by in...

Page 154: ...ocated by stretching a string from one wheel to the other All measurements are to be taken with the tape level with the floor and parallel to fuselage water lines The loca tion of the wheel reactions will be approximately at F S 132 for the main wheels and F S 47 for the nose wheel 8 The wing and fuselage weighing points are used by placing scales on the points as specified in Step 1 Since the cen...

Page 155: ...eighing should be made in an enclosed area which is free from air currents The scales used should be properly calibrated and certified 114 0 76 603 6 F S 312 0 AFT REACTION POINT F S 278 61 WING JACK POINTS F S 129 37 JIG POINT LEVELING LOCATION BAGGAGE FLOOR F S 181 0 I f APPROX 85 ID F S 0 0 I L E M AC MA C I348S C 7f 99 08 r 57 65 F S I F S F S 68 0 I 1 F l l 0 75 I j i r d nril11 January 1978 ...

Page 156: ... 9LGI Jenuer lNYl8 J J3 A VNOI lN3l N1 9 9 9LSS04ona l JV H l33e ISn d nb3 IBS Ii 1M IAuonoas ...

Page 157: ...CRAFT BASIC EMPTY WEIGHT AND BALANCE DUCHESS 76 STRUT POSITION EXTENDED COMPRESSED VI t _ _ _ _ _ REACTION SCALE WHEEL JACK POINTS READING TARE NET WEIGHT ARM MOMENT LEFT MAIN RIGHT MAIN NOSE OR TAIL TOTAL AS WEIGHED Space below provided for additions and subtractions to as weighed conditIon EMPTY WEIGHT ENGINE OIL 37 75 4 2790 UNUSABLE FUEL 20 123 2 2464 BASIC EMPTY WEIGHT 0 tOO I l II II ...

Page 158: ...ech Aircraft Corporation cannot maintain this information the current status is known only to the owner If these papers become lost the FAA will require that the airplane be re weighed to establish the basic empty weight and c g and that an inventory of installed equipment be con ducted to create a new equipment list It is recommended that duplicate copies of the Basic Empty Weight and Balance she...

Page 159: ...ND BALANCE RECORD REGISTRATION NO WEIGHT CHANGE RUNNING BASIC DATE ITEM NO DESCRIPTION OF ARTICLE ADDED OR REMOVED 1 EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM lBSI IN 100 lBSI 100 ID j iOO c l g SER IAL NO m flo OJ Dl 0 men am t 0 0 cl r l iii ...

Page 160: ... DESCRIPTION OF ARTICLE ADDED OR REMOVED EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM LBS IN 100 LBS 100 C1I o SERIAL NO C Illl CO WEIGHT AND BALANCE RECORD REGISTRATION NO _ PAGE NO _ a tv O II 0 m D c 6 C a m m em c 0 Ox to C1I JJ 3 Qi l ...

Page 161: ...maximum moments are shown on the Moment Limits vs Weight graph or table These moments correspond to the forward and aft center of gravity flight limits for a particular weight All mo ments are divided by 100 to simplify computations F S PILOT F PASS FWD pas 105 AFT pas 112 3RD 4TH SEAT PASS 144 OR BENCH SEAT 142 QQ i F S 167 I NOTE THE FLOOR STRUCTURE LOAD LIMIT IS 100 POUNDS PER SQUARE FOOT ALL B...

Page 162: ...ITY INCHES AFT OF DATUM f k I l t 1 1 t l E t TJ1 2600 3600 S 3400 0 0 0 z 0 c z I 3200 I 0 3 3000 ENVELOPE BASED ON THE FOLLOWING WEIGHT AND CENTER OF GRAVITY LIMIT DATA LANDING GEAR DOWN 1 7 s 117 5 AFT C G LIMIT I FWD C G LIMIT 110 6 106 6 WEIGHT CONDITION 3900 POUNDS MAX TAKE QFF LANDING 3250 POUNDS OR L1ESS o I I 6 12 January 1978 ...

Page 163: ...6 2575 2745 3026 3375 3624 3966 2600 2772 3055 3400 3656 3995 2625 2798 3084 3425 3688 4024 2650 2825 3114 3450 3720 4054 2675 2852 3143 3475 3753 4083 2700 2878 3173 3500 3785 4113 2725 2905 3202 3525 3817 4142 2750 2932 3231 3550 3850 4171 2775 2958 3261 3575 3882 4201 2800 2985 3290 3600 3915 4230 2825 3012 3319 3625 3948 4259 2850 3038 3349 3650 3981 4289 2875 3065 3378 3675 4014 4318 2900 309...

Page 164: ...OTAL Ramp Condition 5 Subtract the fuel to be used for start and taxi to arrive at the SUB TOTAL Take off Condition 6 Subtract the weight and moment of the FUEL TO DES TINATION from the take off weight and moment Determine the weight and moment of this fuel by subtracting the amount on board at landing from the amount on board at takeoff TheZero Fuel Condition the Take off Condition and the Landin...

Page 165: ...IC EMPTY CONDITION 2543 2775 2 FRONT SEAT OCCUPANTS 340 380 3 3rd 4th SEAT OCCUPANTS OR BENCH SEAT OCCUPANTS 340 490 4 5 AFT BAGGAGE 93 155 6 SUB TOTAL ZERO FUEL CONDITION 3500 LBS MAX 3316 3800 7 FUEL LOADING 100 gal 600 702 8 SUB TOTAL RAMP CONDITION 3916 4502 9 LESS FUEL FOR START TAXI AND TAKEOFF 16 19 10 SUB TOTAL TAKE OFF CONDITION 3900 4483 11 LESS FUEL TO DESTINATION 80 gal 480 562 12 LAND...

Page 166: ...T OCCUPANTS 3 3rd 4th SEAT OCCUPANTS OR BENCH SEAT OCCUPANTS 4 5 AFT BAGGAGE 6 SUB TOTAL ZERO FUEL CONDITION 3500 LBS MAX 7 FUEL LOADING gal 8 SUB TOTAL RAMP CONDITION 9 LESS FUEL FOR START TAXI AND TAKEOFF 10 SUB TOTAL TAKE OFF CONDITION 11 LESS FUEL TO DESTINATION 12 LANDING CONDITION Fuel for start taxi and takeoff is normally 16 Ibs at an average moml100 of 19 6 16 January 1978 ...

Page 167: ... 202 256 259 190 198 200 213 270 274 200 208 210 224 284 288 210 218 220 235 298 302 220 228 231 246 312 317 241 230 239 258 327 331 240 250 252 269 341 346 250 260 262 280 355 360 t Effective ME 1 thru ME 20 tt Effective ME 21 and after Reclining seat with back in full up position Values computed from a e G criterion based on a 170 pound male Differences in physical characteristics can cause vari...

Page 168: ... Duchess 76 USEFUL LOAD WEIGHTS AND MOMENTS BAGGAGE ARM 167 WEIGHT MOMENT 100 10 17 20 33 30 50 40 57 50 84 50 100 70 117 80 134 90 150 100 157 110 184 120 200 130 217 140 234 150 251 150 257 170 284 180 301 190 317 200 334 6 18 January 1978 ...

Page 169: ...VI Wt Bal Equip List USEFUL LOAD WEIGHTS AND MOMENTS USABLE FUEL ARM 117 0 GALLONS WEIGHT MOMENT LBS 100 10 60 70 20 120 140 30 180 211 40 240 281 50 300 351 60 360 421 70 420 491 80 480 562 90 540 632 100 600 702 January 1978 6 19 ...

Page 170: ......

Page 171: ...lectric Elevator Trim 7 6 Aileron Trim 7 7 Instrument PaneL 7 7 Illustration 7 t Flight Instruments 7 9 Engine Instrumentation 7 9 Ground Control 7 9 Wing Raps 7 10 Landing Gear System 7 10 Control Switch 7 1 0 Position Indicators 7 11 Time delay Relay 7 11 Safety Retraction Switch 7 11 Warning Horn 7 12 W H Q S t h 7 arnlng om WI C 12 Warning Horn Silence Button 7 12A Circuit Breaker 7 12A Emerge...

Page 172: ...ine Controls 7 17 Throttle Propeller and Mixture 7 17 Engine Instrumentation 7 18 Manifold Pressure Gage 7 18 Exhaust Gas Temperature Indicator EGT 7 18 Engine Brealc in Information 7 19 Engine L ubrication 7 19 Engine Ice Protection 7 19 Carburetor Heat 7 Induction Air 7 Cowl Flaps 7 Starters 7 Propellers 7 1 Fuel System 7 1 Fuel Tanks 7 Fuel Selector Valves 7 Schematic 7 3 Fuel Drains 7 4 Fuel Q...

Page 173: ...arning Light 7 30 External Power 7 30 Lighting Systems Interior Lighting 7 34 Exterior Lighting 7 34 Environmental Systems cabin Heating 7 35 Illustration 7 lR Heater Operation Cabin Ventilation oJ oJ Overhead Fresh Air Outlets 7 38 Exhaust Vent 7 39 Pitot and Static Systems 7 39 Pitot System 7 39 Pitot Heat 7 39 Static System 7 40 Pressure System 7 40 Stall Warning System 7 41 August 1980 7 3 ...

Page 174: ...BL6 AJenuer lNY18 l 31 All iNOUN3J NI 9Lssallona J fV IOH0338 uond Josaa swalsAS IIi UO ...

Page 175: ...low the left forward seat comer pull to the right then up and slide the seat forward or aft to th desired position Each seat should be locked securely in place after adjustment The backs of all individual seats can be placed in any of three positions by means of a lever located on the side of each seat Headrests are available for each of the individual seats Outboard arm rests for the front seats ...

Page 176: ...lectric or manual pitch trim system MANUAL ELEVATOR TRIM The manual elevator trim is actuated by a handwheellocated between the pilot seats An elevator tab position indicator is located adjacent to the trim control handwheel Forward rota tion of wheel trims the airplane nose down aft rotation trims nose up ELECTRIC ELEVA TOR TRIM The electric elevator trim system is controlled by the ON OFF circui...

Page 177: ... INSTRUMENT PANEL The standard instrument panel consists of flight navigation and engine instruments on the left and an avionics section on the right The lower left subpanel contains the switches for control of the battery and alternators magneto start and prime lights environmental and optional equipment Also contained on the left sUbpanel are the auxiliary fuel pump switches instru ment air gage...

Page 178: ...8L61 A nmuer l 1 r Z VI l tl C m Z l c l Z m 9Lssa4ona l IVI IOH0338 f uond Josaa swats s IIA uonoas ...

Page 179: ... quantity fuel pressure oil pressure oil temperature cylinder head temperature and loadmeters The alternator out annunciator lights for each alternator and the test switch are located adjacent to the loadmeters The balance of the engine instruments located above the left subpanel include a dual indicating manifold pressure gage tachometers and a dual indicating exhaust gas temperature indicator A ...

Page 180: ... OFF position during flap extension or retraction Lowering the flaps in flight will produce the following effects Attitude Nose Down Airspeed Reduced Stall Speed Lowered When the flaps are extended beyond approximately 16 the landing gear warning horn will sound regardless of throttle position if the landing gear is not down and locked LANDING GEAR SYSTEIV The retractable tricycle landing gea r is...

Page 181: ... All of the lights will be extinguished when the gear is up Pressing the face of each landing gear position indicator light will verify the landing gear lights are functional The intensity of the lamps can be controlled by turning the lens holder on each lamp TIME DELAY RELAY ME 183 and after Landing gear retraction operation is protect d by a time delay relay which will disengage electrical power...

Page 182: ... oper ations WARNING HORN If either or both throttles are retarded below an engine setting sufficient to sustain flight and the landing gear is retracted the landing gear warning horn will sound intermittently Also when the flaps are extended beyond approximately 16 the warning horn will sound regardless of throttle position if the landing gear is not down and locked WARNING HORN Q SWITCH An optio...

Page 183: ...e resulting warning horn silenced with the button readvancing the throttle resets the warning horn and it will again sound when either throttle is retarded The warning horn is also reset when the landing gear are lowered When the flaps are extended beyond approximately 16 the button will not silence the warning horn CIRCUIT BREAKER The landing GEAR MOTOR circuit breaker and the landing GEAR CONTRO...

Page 184: ...Section VII Systems Description INTENTIONALLY LEFT BLANK 7 128 BEECHCRAFT Duchess 76 August 1980 ...

Page 185: ...luid level is checked with the dipstick attached to the reservoir cap The brakes require no adjust ment since the pistons move outward to compensate for lining wear CAUTION Install wheel chocks and release the parking brake if the airplane is to be left unattended Changes in ambient temperatures can cause the brakes to release or exert excessive pressures BAGGAGE COMPARTMENT The aft baggage compar...

Page 186: ...p and slide the seat forward or aft to the desired position Make certain each seat is locked securely in place after adjustment The backs of all individual seats can be placed in any of three positions by means of a release lever located on the side of each seat Headrests are available for each of the individual seats Outboard armrests for the front seats are attached to the cabin doors SEAT BELTS...

Page 187: ...le seats are attached to the lower cabin sidewall structure at the aft edge of the respective seat The inertia reel is covered with an escutcheon and the strap runs up from the reel to a looped fitting attached to the window frame just aft of the seat For stowing these shoulder harness straps stowage attach points are provided adjacent to the inertia reel on the cabin sidewall WARNING The seat bel...

Page 188: ... releases AFT UTILITY DOOR The aft utility door on the left side of the fuselage is provided for loading baggage into the aft cabin area This door can be opened from outside the airplane or from the inside To open the door from the outside lift the handle from its recess and pull until the door opens To open the door from the inside pull out on the locking pin adjacent to the door handle then rota...

Page 189: ... in the underside of the control column tube assembly 3 Ensure positive retention of the lock pin by positioning the hook over the control column WARNING Before starting the engines remove the control lock by reversing the above procedure To Insta the Control Lock ME 339 and after and airplanes prior to ME 339 complying with BEECHCRAFT Service Instructions No 1136 1 Install throttle control lock o...

Page 190: ...S9L IN t1S 1 131 A 11 tNOI 1N3 1NI 9Lssa4ona L I tHOH033S UO ldposaa SWalSAS IIA UO l J8S ...

Page 191: ...cedure ENGINES Two direct drive four cylinder horizontally opposed Avco Lycoming engines are installed An 0 360 A1 G6D clock wise rotating as viewed from the pilot s seat engine is mounted on the left wing and an LO 360 A1G6D coun terclockwise rotating engine is mounted on the right wing Each engine is rated at 180 horsepower at 2700 rpm ENGINE CONTROLS THROTILE PROPELLER AND MIXTURE The control l...

Page 192: ...e alter nator out annunciator lights for each alternator and the test switch for the lights are located adjacent to the loadmeters The balance of the engine instruments located above the left subpanel include a dual indicating manifold pressure gage tachometers and a dual indicating exhaust gas temperature indicator MANIFOLD PRESSURE GAGE The dual indicating manifold pressure gage indicates the pr...

Page 193: ...llow ing cylinder replacement or top overhaul of one or more cylinders as well as to new engines ENGINE LUBRICATION The engines are equipped with a wet sump pressure type oil system Each engine sump has a capacity of 8 quarts The oil level may be checked through the access door in each en gine cowling A calibrated dipstick attached to the filler cap indicates the oil level Due to the canted positi...

Page 194: ... the engine inside the nacelle area COWL FLAPS The manual cowl flaps are controtled by separate levers located just below the carburetor heat controls on the pedes tal Each control lever has three placarded positions CLOSE up HALF OPEN down The control levers allow the cowl flaps to be positioned so that the desired cylinder head tem peratures can be maintained STARTERS The magnetoistart switches ...

Page 195: ...hts move the blades to high pitch Engine oil under governor boosted pressure moves the blades to the high rpm low pitch position The propellers should be cycled occasionally during cold weather operation This will help maintain warm oil in the propeller hubs so that the oil will not congeal FUEL SYSTEM The airplane is designed for operation ongrCide1 00 greeO j Qr Q ql 4 RJl Ie iaviation gasoline ...

Page 196: ...ons of fuel FUEL SELECTOR VALVES The fuel selector valves are located in each nacelle on the outboard side just forward of the wing leading edge The valve is of the rotary type and is operated by push pull cable from the floor console between the front seats The valve has three positions ON CROSSFEED OFF which are determined by detents in the valve The floor console has a slot for each selector va...

Page 197: ...fiITf FLAME ARRESTOR ENGINE PRIMING ENGINE DRIVEN PUMP CARBURETOR FIREWALL AUXILIARY PUMP SELECTOR VALVE STRAINER AND DRAIN STRAINER SUMP DRAIN PRIMER FUEL SELECTOR FUEL QUANTITY SOLENOID CONTROL SENSOR FUEL SYSTEM SCHEMATIC CROSSFEED DRAINS HEATER HEATER FUEL j LINE FROM RIGHT FUEL TANK ONLY ____ 7_ HEATER FUEL PUMP FUEL SELECTORS EATER SOLENOID f l c 1 _ 0 e I _ _0 r l I iW CD l eo e m l c m 72 ...

Page 198: ...t Flush type fuel drains are actuated by pushing in on the valve and then releasing when the desired amount of fuel has been drained These drain valves can be locked open for the purpose of fuel off loading or for totally draining the fuel system Pushing in and turning coun terclockwise will lock the drains in the open position To close turn clockwise and release FUEL QUANTITY INDICATORS Fuel quan...

Page 199: ... i tl l gireGtIYiintb the no J 2 J lJg 4 GyllDQe slJQrj engine primingfwEngine priming should be used in accordance with the recommendations in the NORMAL PROCEDURES section FUEL CROSSFEED The fuel lines for the engines are interconnected by cross feed lines During normal operation each engine uses its own fuel pumps to draw fuel from its respective wing fuel system However on emergency crossfeed ...

Page 200: ... breakers for the various electrical systems and all avionics circuit breakers BATIERY ne 24 Y0It 155 amner e hbur reaCl aGiag r fatterv f M5 183 j i Ii d1Ai gi tJjriiftJSlf i i s l itt 0 c c _ X 1i tL t _ c ic ti ltt1ijlj iiil i 1 I 2 i t fuselage compartment An optional installation ME 183 and after provides two 12 volt 25 ampere hour lead acid batteries electrically connected in series and inst...

Page 201: ... FUSE IME 103 AND AFTER 6J R AUXILIARY FUEL PUMP R ENGINE INSTA R START CQNT PRIMER LOG GR MOTOR I GEAR CONTROL FLAP MOTOR I CIGAR LIGHTER OVERHEAD INSTR PNL DOME MAP LALT FIELD L AUXILIARY FUEL PUMP L ENGINE INST L STARTCONT PRIMER FLAP GEAR INDICATOR STALL GEAR WARN HORN INST POST COMp LT TURN COORD LANDING L1GHT TAXI LIGHT NAV LIGHT STROBE LIGHT PiTDT HEAT f ELE TRIM ALiTo PILOT FRESH AlA BLOWE...

Page 202: ...cuit The regulators automatically maintain the bus voltage at a set value for all loads up to the alternator rating The voltage regulators also maintain approximately equal load sharing between the two alternators The self excitation load capability of the alternators is directly related to engine RPM The self excitation feature will not come on until approximately 1200 to 1400 RPM with a load cap...

Page 203: ... undervoltage alternator out Iight wi II illuminate When the battery is turned on with both alternators off both alternator out undervoltage lights will illuminate The alternator out overvoltage light one for each alternator will illuminate when the corresponding overvoltage relay is actuated The overvoltage relay opens the affected alternator field and the affected alternator voltage will drop to...

Page 204: ...L POWER The external power receptacle is located either on the right ME 1 through ME 440 or on the left ME 441 and after side of the fuselage just aft of the cabin area A negatively grounded external power source may be used for engine starting or for ground electrical system checks Airplanes equipped with 14 volt systems ME 1 through ME 182 require a power unit setting of 14 volts 2 volts Airplan...

Page 205: ...avionics switches off before connecting the auxiliary power unit Assure correct polarity before connecting external power When auxiliary power is desired connect the clamps of the power cable to the remote power source ensuring proper polarity Turn OFF the ALT switches and ensure that all avionics equipment is OFF and then turn ON the BATT switch Insert the power cable plug into the receptacle tur...

Page 206: ...6L6 I Jd q IN tI8 L I31 A11 qNOIl N3 LNI 9Lssallona L IVt iOH0338 UO JOSaa swalsAS 11 UO IOas ...

Page 207: ... 4N V18 1 131 A11 O NOUN3J Nl UO ld J lsaa SWatSAS itAUO l lOS 9L SSa4 lna J J O I IOH0338 ...

Page 208: ...located on the lower portion of the pilot s subpanel Each circuit is protected by a circuit breaker type switch The exterior lights consist of a landing light on the outboard leading edge portion of the left wing a taxi light on the outboard leading edge portion of each wing navigation lights on the wing tips and empennage and a strobe light located on each wing tip For longer battery and lamp lif...

Page 209: ...d valve to the heater fuel pump located under the heater and into the combustion chamber of the heater Fuel consumption of the heater is approximately 213 gallons per hour and should be considered during flight planning NOTE The fuel solenoid is energized only if the duct thermostat which controls the heater requires a higher temperature Three outlets are located in the cabin to distribute the hea...

Page 210: ...SH AIR OUTLETS INSTRUMENT PANEL COMBUSTION AIR BLOWER H HEATER FWD VENT AIR BLOWER FRESHAIR INLET d OVERHEAD FRESH AIR OUTLETS FRESH AIR INLET AFT CABIN HEAT OUTLET FORWARD CABIN HEAT OUTLET x 1 1 fi FIXED EXHAUST g u AIR INTAKE 11 DORSAL FIN Ii lJ ENVIRONMENTAL SCHEMATIC 7 36 January 1978 ...

Page 211: ...em in operation 2 The push pull knob on the left sidewall placarded DE FROST PULL ON controls the amount of air required for windshield defrosting 3 The push pull knob located below the defrost knob placarded CABIN AIR PULL OFF controls the amount of air entering the cabin from the heater Pulling the knob more than approximately one half closed c I activates the heater in order to prevent heater o...

Page 212: ...place the three position switch on the pilot s subpanel in the BLOW ER ONLY position The BLOWER ONLY position is for ground operation only and will shut off the blower when the landing gear is retracted Fresh ram air is also provided through an outlet located on each side of the instrument panel Fresh air for these outlets enters the two vents located immediately forward of the wind shield Rotatio...

Page 213: ...ight instruments PITOT SYSTEM A standard pitot tube for the pilot s flight instruments is located on the outboard portion of the left wing leading edge The optional pitot tube ME 44 and after for the copilot s flight instruments is located on the outboard portion of the right wing leading edge PITOTHEAT A heating element is installed in the pitot mast and is control led by the rocker type switch l...

Page 214: ...tic air refer to the EMER GENCY PROCEDURES section Airspeed Calibration and Altimeter Correction graphs are in the PERFORMANCE section I The static air plumbing is drained by placing the lever in the ON ALTERNATE position momentarily and then returning it to the OFF NORMAL position PRESSURE SYSTEM Pressure for the flight instruments and autopilot if installed is supplied by two engine driven dry p...

Page 215: ...n the overhead speaker console The stall warning horn will sound a warn ing signal while there is time for the pilot to correct the attitude The horn is triggered by the sensi ng vane on the left wing anytime the flaps are above approximately 16c When the flaps are extended beyond approximately 16 the vane on the right wing will activate the warning horn NOTE With the BATT and ALT switches in the ...

Page 216: ......

Page 217: ...That May Be Accomplished By a Certificated Pilot 8 5 Alterations or Repairs to Airplane 8 5 GROUND HANDLING 8 6 Towing 8 6 Parking 8 6 Tie Down 8 7 Jacking 8 8 Prolonged Out of Service Care 8 8 Flyable Storage 7 to 30 Days 8 8 Extemal Power 8 11 SERVICiNG 8 13 Fuel System 8 13 Fuel Tanks 8 13 Fuel Drains 8 13 Fuel Strainers 8 14 Oil System 8 14 Battery 8 16 Tires 8 17 Shock Struts 8 18 January 197...

Page 218: ...ade Bearing Lubrication 8 23 MINOR MAINTENANCE 8 23 Cabin Heater 8 23 Alternators 8 24 Magnetos 8 25 Ieaning 8 2E5 Exterior F ainted Surfaces 8 2E5 Windshield and Windows 8 27 Engine 8 28 Interior 8 28 Lubrication Points 8 30 Recommended Servicing Schedule 8 38 onsumable Materials 8 4E5 AJ J roved Engine Oils 8 48 LamJ Bulb ReJ lacement Guide 8 51 Overhaul and ReJ lacement Guide 8 52 Wing Structur...

Page 219: ...nformity with all airworthiness re quirements established for this airplane All limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandatory Authorized BEECHCRAFT Aero or Aviation Centers or I International Distributors or Dealers can provide recommended modification service and operating procedures issued by both the FAA...

Page 220: ...s handbook For information on how to obtain Revision Service applicable to this handbook consult a BEECHCRAFT Aero or Aviation Center or International Distributor or Dealer or refer to the latest revision of BEECHCRAFT Service Instructions No 0250 010 AIRPLANE INSPECTION PERIODS 1 FAA Required 100 Hour and or Annual Inspections 2 Continuous Care Inspection Guide 3 See Recommended Servicing Schedul...

Page 221: ... preventive maintenance 2 All other maintenance must be performed by licensed personnel NOTE Pilots operating airplanes of other than U S registry should refer to the regulations of the country of certification for information on preven tive maintenance that may be performed by pilots ALTERATIONS OR REPAIRS TO AIRPLANE The FAA should be contacted prior to any alterations on the airplane to ensure ...

Page 222: ...G One person can move the airplane on a smooth and level surface with the hand tow bar Attach the tow bar to the nose landing gear tow bar fitting It is recommended to have some one in the airplane to operate the brakes CAUTION Do not exert force on the propellers or control surfaces When towing with a tug limit turns to prevent damage to the nose gear Do not tow when the main gear is obstructed b...

Page 223: ...the wind Three tie down lugs are provided one on the lower side of each wing and a third at the rear of the fuselage 1 Install the control lock assembly 2 Chock the main wheels fore and aft 3 Using nylon line or chain of sufficient strength secure the airplane at the three points provided DO NOT OVER TIGHTEN if the line at the rear of the fuselage is excessively tight the nose may rise and produce...

Page 224: ...ering or leav ing the airplane while it is on jacks The landing gear circuit breaker should be pulled and the emergency gear extension valve should be open to relieve pressure in the hydraulic system in order to prevent inadvertent retraction of the landing gear when airplane is jacked PROLONGED OUT OF SERVICE CARE The storage procedures are intended to protect the airplane from deterioration whil...

Page 225: ...g angle of attack Attach a line to the nose gear I FUEL TANKS Fill fuel tanks to capacity to minimize fuel vapor FLIGHT CONTROL SURFACES Lock flight control surfaces with internal and external locks GROUNDING Static ground airplane securely and effectively PITOT TUBE Install pitot tube cover WINDSHIELD AND WINDOWS Close all windows It is recommended that covers be instal led over the windshield an...

Page 226: ...xture control in the IDLE CUT OFF position before turning the propeller Do not stand in the path of propeller blades Also ground running the engine for brief periods of time is not a substitute for turning the engine over by hand in fact the practice of ground running will tend to aggravate rather than minimize corrosion formation in the engine After 30 days the airplane should be flown for 30 min...

Page 227: ...nd continually energized Turn off alternato r switches all electrical and avionics switches and turn on battery switch before connecting the auxiliary power unit plug Assure correct polarity negative ground before connecting auxiliary power unit On 2B volt airplanes a reverse polarity diode protection system is between the external power receptacle and the main bus With external power applied the ...

Page 228: ... the power source connect the positive terminal of the cable to the positive terminal of the power source or battery Isolate the negative cable clamp 5 Connect the external power cable into the external power receptacle Turn the auxiliary power source ON If a battery is used as the power source connect the negative cable clamp to the negative terminal of the power source or to a suitable ground po...

Page 229: ...ce unit and the air plane to ground during fueling operations This procedure reduces fire hazard To prevent damage to the fuel tanks do not insert the fuel nozzle more than three inches into the filler neck Secure the filler caps immediately after filling FUEL DRAINS The fuel system is equipped with a total of 8 drains 4 drains per wing A drain valve is located outboard of each nacelle on the unde...

Page 230: ...strainers should be considered to be of the utmost importance as a regUlar part of preventive main tenace Normally the fuel selector valve strainer should be cleaned and inspected every 100 hours of operation However the strainer should be inspected and cleaned at more frequent intervals depending on service conditions fuel handling equipment and when operating in localities where there is an exce...

Page 231: ...the oil and the oil filter Check the used oil filter for metal particles Refer to the Duchess 76 Maintenance Manual The engine manufacturer recommends the use of ashless dispersant oil after the oil consumption has stabilized or after the first 50 hours of operation In order to promote faster ring seating and oil control a straight mineral type oil conforming to MIL L 608 may be used until the oil...

Page 232: ...vice Instruction 1014J or later revision for additional information BATTERY Access to the lead acid battery or batteries is obtained by removing the rear baggage compartment panel and the battery box lid located aft of the panel Check the electrolyte level after each 25 hours of operation and add only distilled water as required NOTE I 8 16 Do not fill the battery or batteries over one half inch a...

Page 233: ...ally for obstructions and for proper protrusion one to three inches from the skin line Since either vent may serve as the intake one vent chamfer should face forward the other aft ME 1 thru ME 182 Airplanes ME 183 and after have no protruding tubes These vents are designed to produce a venturi effect TIRES The main wheel tires are 6 00x6 6 ply rating type I tube type The nose wheel tire is a 5 00x...

Page 234: ...with compressed air and MIL H 5606 hydraulic fluid The same procedure is used for servicing both the main and nose shock struts The shock strut may be served as follows 1 Remove the air valve cap and depress the valve core to release the air pressure WARNING Do not unscrew the air valve assembly until the air pressure has been released Otherwise it may be blown off with considerable force caus ing...

Page 235: ...he fuel tanks full inflate the nose gear strut until four and one fourth inches of the piston is exposed and main gear strut until two inches of the piston is exposed Rock the airplane gently to prevent possible binding of the piston in the barrel while inflating with the airplane on the ground NOTE The preferred method of inflation is with the air plane on jacks and set the pressure rather than t...

Page 236: ...e left side of the nose compartment Fill the reservoir with the MIL H 5606 I hydraulic fluid to the FULL mark on the dipstick Maintain the fluid level between the FULL and ADD marks Do not overfill The brake disc should be replaced when its thickness mea sures 0 450 inch INDUCTION AIR FILTERS The induction air filters should be removed cleaned and inspected each 50 hours of service Replacement is ...

Page 237: ...stem is a disposable unit and must be discarded and replaced at 300 to 500 hour intervals or more often if conditions warrant 1 Remove the nose compartment access panel and ac cess plates on the nose compartment floor to gain access to the filter located below the floor on the left side forward of the cabin bulkhead 2 Remove the clamps at the inlet and outlet of the filter 3 Remove tl e filter fro...

Page 238: ...ooled completely STAND IN THE CLEAR WHEN MOVING A PROPELLER THERE IS ALWAYS SOME DANGER OF A CYLINDER FIRING WHEN A PROPELLER IS MOVED PROPELLER DOME AIR PRESSURE SETTING 1 Remove the propeller spinner dome cap retaining screws and remove the propeller spinner dome cap 2 Service the propeller air dome cylinder with dry air or nitrogen to a correct pressure as follows 70 F to 100 F 41 1 psi 40 F to...

Page 239: ...the hole where the opposite fitting was removed 6 Clean the excess grease from the propeller reinstall the grease fittings covers and safety wire on each blade 7 Position the spinner dome and install the retaining screws 8 Position the spinner dome cap and install the retaining screws WARNING The propellers are not interchangeable between left and right engines MINOR MAINTENANCE CABIN HEATER The h...

Page 240: ...rking on the charging circuit or serious damage to the electrical equip ment will result 1 When installing a battery make certain that the ground polarity of the battery and the ground polarity of the alternator are the same 2 When connecting a booster battery be sure to connect the negative battery terminals together and the positive bat tery terminals together 3 When using a battery charger conn...

Page 241: ...100 hours thereafter Contact point clearance for the magneto right main breaker is 016 004 left main breaker is 016 002 Points with deep pits or with excessively burned areas should be discarded Inspect the cam follower felt pad for proper lubrication and clean the breaker compartment with a clean dry cloth WARNING To be safe treat all magnetos as hot whenever the ground lead is disconnected To gr...

Page 242: ...soap Any rubbing of the painted surface should be done gently and held to a minimum CAUTION When washing the airplane with mild soap and water use special care to avoid washing away grease from any lubricated area After washing with solvent in the wheel well areas lubricate all lubrication points Premature wear of lubricated surfaces may result if the above precautions are not taken Prior to clean...

Page 243: ...phtha the surface should be rewaxed WINDSHIELD AND WINDOWS CAUTION Do not scratch windows when cleaning Do not use an ice scraper to remove ice from windows A commercial cleaning compound made specifically for ac rylic 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 instruc tions should be f...

Page 244: ...ngine cleaning fluid Spray or brush the fluid over the en gine then wash off with water and allow to dry INTERIOR The seats rugs upholstery panels and headliner should be vacuum cleaned frequently Do not use water to clean fabric surfaces Commercial foam type cleaners or shampoos can be used to clean carpets fabrics and upholstery however the instructions on the container should be followed carefu...

Page 245: ...erial that is alcohol soluble CAUTION The interior cabin trim can be easily damaged if cleaned with methyl ethyl ketone naphtha Mufti standard solvent gasoline lacquer thinner and other types of thinners Sharp edges or cuts on the edge of the interior cabin trim material may cause it to crack January 1978 8 29 ...

Page 246: ... J 0 0 o I o BL6 Amnuer ji i 9LSScn ona l nfl lOH033S L r m I o Z 0 o z 4 en JU 81N pU8 AJa5 6U lPUBH iliA UOIl J03S ...

Page 247: ...s 16 section VIII Handling Serv and Maim _C2 APPLICABLE TO BOTH INBOARD AND OUTBOARD HINGE A AILERON BELL CRANK AND PUSHROD B L If l 7 ELEVATOR BELL CRANK PUSHROD AND HORN c 15 CONTROL COLUMN 76 604 11 January 1918 8 31 ...

Page 248: ...Section VIII Handling Serv and Maint BEECHCRAFT Duchess 76 o RUDDER PEDAL ASSEMBLY AND BRAKE MASTER CYLINDERS E ELECTRIC FLAP ACTUATOR ASSEMBLY F 8 32 CABIN DOOR 1 76 604 12 January 1978 ...

Page 249: ...BEECHCRAFT Duchess 76 G H Section VIII Handling Serv and Main 1 BAGGAGE DOOR 2 J BRAKE RESERVOIR AND PARKING BRAKE VALVE I S I LANDING GEAR HYDRAULIC PUMP AND RESERVOIR 76 604 13 January 1978 8 33 ...

Page 250: ...Section VIII Handling SeN and Maint BEECHCRAFT Duchess 76 0 0 4 J o NOSE GEAR INSTALLATION AND DOORS K ElEVATOR STABiliZER HINGE L FLAP INSTALLATION 76 604 14 8a 34 January 1978 ...

Page 251: ...BEECHCRAFT Duchess 76 M z J Section Viii Handling Serv and Maint Q RUDDER AND ELEVATOR TAB ACTUATOR N MAIN LANDING GEAR o COWL FLAP 76 604 15 January 1978 8 35 ...

Page 252: ...Section VIII Handling Serv and Maim p l HI r BEECHCRAFT Duchess 76 UPPER AND LOWER RUDDER INSTALLATION R I ELEVATOR AND RUDDER TAB HINGE s cD 8 36 HEATER 76 604 16 August 1980 ...

Page 253: ...mbers refer to items in Consumable Materials chart Sym bols as shown above indicate the method of lubrication Lubricate all plain bearing bushings all push pull control housings and all flight control pulley bushings as required or every 500 hours with SAE 10W30 oil Exercise care when using MIL G 23827 greases as they contain a rust preventative which will discolor painted sur faces January 1978 8...

Page 254: ... Aft of aft cabin bulkhead Distilled water only level lube Nose landing Gear Nose landing gear J 4 Linkage 13 places lube lower Fork Attach Point Main landing gear N 4 2 places 50 Hrs Change Engine Oil Filters Remove engine cowl Refer to Maintenance Manual Clean Engine Induction Air Remove upper engine cowling Clean per instructions on filter Filters a Co 0 l l w III l Co s III _ 3 to m om co n x ...

Page 255: ... and Regap Spark Remove engine cowl both Plugs sides of each engine Check Magneto Timing Remove engine cowl Refer to Maintenance Manual Check Emergency Locator Right side of aft fuselage Tune radio to 121 5 MHz on x Transmitter VHF or 243 MHz on UHF then 1 1 s turn ELT switch to ON and c monitor for one signal Turn ELT switch OFF then place in ARM position lube Aileron Bell Crank and Left and righ...

Page 256: ...B 1 Conrd age 6 places lube Electric Flap Actuator Under aft cabin floorboards 3 Torque Shaft 3 places under rear passenger seats E lube Electric Flap Actuator Flap E 1 Rod Assembly 4 places Lube Cabin Door Hinges and Lett and right cabin doors F 1 Latch Mechanisms 12 places Lube Baggage Door Hinge Baggage door G 1 and Latch Mechanisms 3 places ig J C ll Q 0 J J E m J a f a ED m C ll ll ro ID Xi t...

Page 257: ...0 Wheet Bearing 0 Lube ElevatorStabilizer Hinge IElevator K 1 2 places lube Flap Installation Hinge Flap L 1 6 places lube Rudder and Elevator Tab Empennage M 1 E I lI Actuator Rod Hinges J Cl 2 places s Q Lube Main Landing Gear Main landing gear N 5 g Wheel Bearings f Lube Cowl Flap Hinge and AtjLeft and right nacelles 0 1 11 g g I Itach Points 4 plaCeS ___ s ...

Page 258: ... Installation Attach Points 4 places I Lube Elevator Tab and Rudder Elevator tab and rudder tab 7 Tab Hinges R Clean Static Air Buttons Aft fuselage Clean with solvent 10 and wipe dry with a clean rag Drain Static Air Lines Flight compartment left side panel forward of door frame Check Scupper Drains Drain Rear fuselage and empen Guards Open Facing Aft and nage Drain Holes are Free from Ob structi...

Page 259: ...dder Pedals and Link Flight Compartment 0 1 age 18 places 1000 Hrs Lube Control Column Unkage Forward of instrument panel 1 5 places C 1200 Hrs LubeRudder Tab and Elevator Empennage 4 Refer to Maintenance Tab Actuator Manual As Req Lube Magneto Cam Follower Remove engine cowl 9 Felt 2 places Service Brake Reservoir Through small access door on 2 large access door left side of nose compartment H em...

Page 260: ...nt d servoir t Ill I Service Nose Landing Gear Nose landing gear J 2 Refer to Maintenance Q f Shock Strut and Shimmy Manual Dampener J Service Main Landing Gear Main landing gear N 2 Refer to Maintenance Shock Struts Manual Lube Heater Iris Valve Through access door right 7 lower nose compartment S m to tt Check Emergency Locator Right side of aft fuselage m ill em lI Transmitter Battery 0 CO X I ...

Page 261: ... the first 100 hour inspection and at the first 100 hour inspection after each reinstallation of the wing attach bolts Rechargeable Batteries Recharge after one cumulative hour of use or after 50 of the useful charge life Non Rechargeable Batteries Replace after one cumulative hour or after 50 of the useful life em r m o m to I ll J 0 Ii C7l I J Il l I Q _ I cc W I 0 1 g 1 ...

Page 262: ...for aviation usage by Beech Aircraft Corporation by 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 Spe...

Page 263: ...of MIL G 81322 These greases are harmful to paint Ashless dispersant oil complying with MIL L 22851 is recommended after the oil consumption has stabilized or after the first 50 hours of operation A straight mineral oil conforming to MIL L 60S2 may be used until the oil consumption has stabilized not to exceed 50 hours of operation Oil of seasonal viscosity added to maintain the proper oil level d...

Page 264: ...8 Aeroshell W120 Aeroshell W80 Texaco Incorporated TX 6309 Aircraft Engine Oil Premium AD120 Aircraft Engine Oil Premium AD80 American Oil and Sup PO Aviation Lubricant 753 ply Co Chevron Oil Company Chevron Aero Oil Grade 120 Humble Oil and Refin ing Co Esso Aviation Oil E 120 Enco Aviation Oil E 120 Esso Aviation Oil A 100 Enco Aviation Oil A 100 Esso Aviation Oil E 80 Enco Aviation Oil E 80 Sta...

Page 265: ...obil Oil Corporation Phillips Petroleum Co Shell Oil Company Conoco Aero Oil 1065 Conoco Aero Oil 1100 Avrex 101 1065 101 1100 Phillips 66 Aviation Engine Oil Grade 1065 Phillips 66 Aviation Engine Oil Grade 1100 Aeroshell Oil 65 Aeroshell Oil 100 Ashless Dispersant Oils Complying with MIL L 22851 NOTE Ashless dispersant oil complying with MIL L 22851 is recommended after the oil con sumption has ...

Page 266: ...tabilized not to exceed 50 hours of operation Oil of seasonal viscosity added to maintain the proper oil level during this break in period must comply with MIL L 6082 Vendors listed as meeting Federal and Military Specifications are provided as reference only and are not specifically rec ommended by Beech Aircraft Corporation Any product con forming to the specification may be used 8 50 January 19...

Page 267: ...Light 1777 1683 Landing Gear In transit Lights 330 327 Overhead Instrument Panel Lights 89 303 J Engine Instrument Cluster Light 266 267 Ql s Wing Tip Lights A7512 12 A7512 24 Q _ Strobe Light Wing 55 0221 3 55 0221 3 s to Flashtube Flashtube f Engine Instrument Post Lights 330 327 ll en Landing Gear Down and Locked Lights 330 327 Ql ll s a t CIO 14 VOLT ME 1 thru ME 182 I g g Ql _ 01 28 VOLT ME 1...

Page 268: ...IAL CONDITIONS CAUTIONARY NOTICE Airplanes operated for Air Taxi or other than normal opera tion and airplanes operated in humid tropics or cold and damp climates etc may need more frequent 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 experience NOTE The required peri...

Page 269: ...ended TBO for the particular operation NOTE When an engine has been overhauled or a new engine installed it is recommended that low power settings NOT be used until oi I consumption has stabilized The average time for piston ring seating is approximately 50 hours Refer to Lycoming Engine Operator s Manual Engines Propellers Magnetos Dry air pressure pumps All hoses January 1982 Refer to latest edi...

Page 270: ...verhaul or every 5 years whichever occurs first ELECTRICAL SYSTEM Starter Alternator Battery Emergency Locator Transmitter At engine overhaul At engine overhaul Per applicable regulations or by date stamped on battery whichever occurs first 1 Cabin heater 8 54 UTILITY SYSTEM Refer to latest edition Janitrol Maintenance Overhaul Manual 11074 and applicable Airworthiness Directives January 1982 ...

Page 271: ...e has a substantiated life of 20 000 flight hours provided the mandatory inspection requirements of chapter four of the BEECHCRAFT DUCHESS 76 MAINTENANCE MANUAL are complied with NOTE Anytime the control surfaces are repaired or repainted they must be rebalanced as described in the Maintenance Manual January 1982 8 55 ...

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