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Beechcraft Debonair 35-33, Руководство по эксплуатации для пилотов

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Содержание Debonair 35-33

Страница 1: ...ALL FLIGHT OPERATIONS THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY FAR PART 23 o Mfr s Serial No _ _ l ll __ v _ _ _ _ __ Registralion No 4A FAA Approvedby _ K _ W H SCHULTZ BEECH AIRCRAFT CORPORATION DOA CE 2 THIS HANDBOOK SUPERSEDES ALL BEECH PUBLISHED OWNER S MANUALS FLIGHT MANUALS AND CHECK LISTS ISSUED FOR THIS AIRPLANE WITH THE EXCEPTION OF FAA APPAOVED AIRPLA...

Страница 2: ...ONS ORIGINAL A JUNE 1977 REISSUE B A PRIL 1982 PAGE DESCRIPTION OF REVISION Title Page Logo Page A Page a thru b 1 1 thru 1 20 2 1 thru 2 24 3 1 thru 3 10 4 1 thru 4 16 5 1 thru 5 32 6 1 thru 6 22 7 1 thru 7 30 8 1 thru 8 52 Section 9 See Log of Supplements 10 1 thru 10 67 March 1981 1 B PageA ...

Страница 3: ...me type data in the same place in all of the handbooks In recent years BEECHCRAFT handbooks contained most of the data now provided however the new handbooks contain more detailed data and some entirely new data For example attention is called to Section X SAFETY IN FORMATION BEECHCRAFT feels it is highly important to have SAFETY INFORMATION in a condensed form in the hands of the pilots The SAFET...

Страница 4: ...ral 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 b April 1982 ...

Страница 5: ... Clearance 1 10 Descriptive Data 1 11 Engine 1 11 Propeller 1 11 Fuel 1 11 Oil Capacity 1 12 Weights 1 12 Cabin And Entry Dimensions 1 12 Baggage Space and Entry Dimensions 1 12 Specific Loadings 1 12 General Airspeed rerminology and Symbols 1 13 Meteorological Terminology 1 15 Power Terminology 1 16 Engine Controls and tnstruments 1 16 Airplane Performance and Flight Planning Terminology 1 17 Wei...

Страница 6: ...plane Flight Manual and lor placards located in the airplane As a further reminder the owner and operator of this airplane should also be familiar with the Federal Aviation Regulations applicable to the operation and maintenance of the airplane and FAR Part 91 General Operating and Flight Rules Further the airplane must be operated and maintained in accordance with FAA Airworthiness Directives whi...

Страница 7: ...ntained for the safe and efficient operation of the BEECHCRAFT Debonair The handbook has been prepared in loose leaf form for ease in maintenance and in a convenient size for storage The handbook has been arranged with quick reference tabs im printed with the title of each section and contains ten basic divisions Section 1 General Section 2 Li mitations Section 3 Emergency Procedures Section 4 Nor...

Страница 8: ...in every case The following information may be provided to the holder of this manual automatically 1 Original issues and revisions of Class and II Service lnstructions 2 Original issues and revisions of FAA Ap proved Airplane Flight Manual Supple ments 3 Reissues and Revisions of FAA Ap proved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Manuals and Pilot s Oper ating...

Страница 9: ...d All Logs of Revisions must be re tained in the handbook to provide a current record of ma terial status until a reissue is made WARNING Wheri this handbook is used for airplane operational purposes it is the pilot s respon sibility to maintain it in current status AIRPLANE FLIGHT MANUAL SUPPLEMENTS REVISION RECORD Section IX contains the FAA Approved Airplane Flight Manual Supplements headed by ...

Страница 10: ... airplane is delivered from the factory the _ handbook delivered with it contains either an STC Supplemental Type Certificate Supplement or a Beech Flight Manual Supplement for every installed item requiring a supplement lf a new handbook for operation of the airplane is obtained at a later date it is the responsi bility of the owner operator to ensure that all requ ired STC Supplements as well as...

Страница 11: ...BEECHCRAFT Debonair33 WING AREA 177 6 sq ft THREE VIEW 12 2 1 Section 1 General 32 9 9 i t 25 6 8 3 7 5 min 84 DIAMETER 9 6 7 April 1982 1 9 ...

Страница 12: ...RNING CLEARANCE A A Radius for Wing Tip 26 ft 4 in B Radius for Nose Wheel 12 ft 2 in C Radius for Inside Gear 5 ft 1 in D Radius for Outside Gear 14 ft 8 in TURNING RADI ARE CALCULATEO USING FULL STEER ING ONE BRAKE AND PARTIAL POWER 1 10 April 1 82 ...

Страница 13: ... J engine PROPELLER Hartzell constant speed two blade 84 inch diameter pro peller using a Hartzell BHC 92ZF 1 Dl hub with 8447 blades FUEL NOTE Other propellers are approved but not installed as original equipment These are listed in the FAA Aircraft Specification 3A15 or approved by Supplemental Type Certificate Aviation Gasoline 80 87 red minimum grade or alternate grades lOOLL blue or 100 green...

Страница 14: ...No Structural Limit Maximum Weight in Baggage Compartment 270 lbs CABIN AND ENTRY DIMENSIONS Length 6 ft 11 in Height 4 ft 2 in Width 3 ft 6 in Cabin Door 37 in wide by 36 in high BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment Volume 16 5 cu ft Door Width Minimum 18 5 in Door Height Minimum 22 5 in SPECIFIC LOADINGS Maximum Take Off Weight Wing Loading 16 3 lbs sq ft Power Loadi ng 12 9 lbs hp 1 1...

Страница 15: ...ed indicator when corrected for instrument error IAS values published in this handbook assume zero instrument error KCAS Calibrated Airspeed expressed in knots KIAS lndicated Airspeed expressed in knots TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude temperature and compressibility VA Maneuvering Speed is the maximum speed at whi...

Страница 16: ...ral Cruising Speed is the or Vc speed that should not be exceeded except in smooth air and then only with caution Vs Stalling Speed or the minimum steady flight speed at which the airplane is controllable Vso Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration Vx Best Angle of Climb Speed is the airspeed which delivers the greatest g...

Страница 17: ... air static temperature obtained either from inflight temperature indica tions adjusted for instrument error and compressibility effects or ground meteorological sources lndicated The number actually read from an Pressure alti meter when the barometric sub Altitude scale has been set to 29 92 in Hg 1013 2 millibars Pressure Altitude measured from standard Altitude sea level pressure 29 92 in Hg by...

Страница 18: ...ff and Maximum Cont inuous Cruise Climb Highest power rating not limited by time Power recommended for cruise climb ENGINE CONTROLS AND INSTRUMENTS Throttle Control Propeller Control 1 16 Used to control power by intro ducing fuel air mixture into the intake passages of the engine Settings are reflected by readings on the manifold pressure gage This control requests the propeller governor to maint...

Страница 19: ...m of the engine propeller Regulates the rpm of the engine propeller by increasing or decreasing the propeller pitch through a pitch change mechanism in the propeller hub AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb Gradient Demonstrated Crosswind Velocity April 1982 The ratio of the change in height during a portion of a climb to the horizontal distance traversed in the same time int...

Страница 20: ...ane from which all horizontal distances are measured for balance purposes A location along the airplane fuselage usually given in terms of distance from the reference datum The horizontal distance from the ref erence datum to the center of gravity C G of an item The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify bal ance calculations by redu...

Страница 21: ...n accordance with governmental regulations Standard Weight of a standard airplane Empty including unusable fuel full Weight operating fluids and full oil Basic Standard empty weight plus Empty optional equipment Weight Payload Weight of occupants cargo and baggage Useful Difference between take off weight Load or ramp weight if applicable and basic empty weight _ _ Maximum Maximum weight approved ...

Страница 22: ...e fuel Weight Tare The weight of chocks blocks stands etc used on the scales when weighing an airplane Leveling Those points which are used during the Points weighing process to level the airplane Jack Points on the airplane identified by the Points manufacturer as suitable for supporting the airplane for weighing or other purposes 1 20 April 1982 ...

Страница 23: ...es 2 5 Oil Specifications 2 5 Propeller Specifications 2 6 Power Plant Instrument Markings 2 6 Miscellaneous Instrument Markings 2 7 Weight Limits 2 8 Center of Gravity Limits 2 8 Maneuver Limits 2 8 Approved Maneuvers 2 9 Flight Load Factors 2 9 Minimum Flight Crew 2 9 Kinds of Operation Limits 2 9 Required Equipment for Various Conditions of Flight 2 10 Fuel 2 19 Seating 2 19 Placards 2 20 April...

Страница 24: ...t exceed Structural this speed Cruising except in smooth VNo or Vc air and then only with caution Maneuvering 123 142 123 142 Do not make full VA or abrupt control movements above this speed Maximum 104 120 107 123 Do not extend Flap flaps or operate Extension with flaps ex Extended tended above VFE this speed Maximum 122 140 122 140 Do not extend Landing Gear retract or operate Operating with lan...

Страница 25: ... 1 85 60 162 69 186 Yellow Are 161 195 185 225 162 197 186 227 Red Line 195 225 197 The Airspeed lndieator is marked in CAS values CD X N 227 SIGNIFICANCE Full Flap Operating Range Normal Operating Range Operate with eaution only in smooth air Maximum speed for ALL operations c 3 CD g 0 J III IJJ m Cm CD c T z g Q c J w w l ...

Страница 26: ...exceed Structural this speed Cruising except in smooth VNo or Vc air and then only with caution Maneuvering 123 142 123 142 Do not make full VA or abrupt control movements above this speed Maximum 104 120 107 123 Do not extend Flap flaps or operate Extensior f w ith flaps ex Extended tended above VFE this speed Maximum 122 140 122 140 Do not extend Landing Gear retract or operate Operating w ith l...

Страница 27: ...62 161 71 185 60 162 69 186 Yellow Are 161 195 185 225 162 197 186 227 Red Line 195 225 197 227 The Airspeed lndieator is marked in CAS values SIGNIFICANCE Full Flap Operating Range Normal Operating Range Operate with eaution only in smooth air Maximum speed for ALL operations c 3 o III 0 0 Ul CJ m Om r r i g III 0 W TI w 1 ...

Страница 28: ...107 C Oil Pressure Minimum Maximum Fuel Pressure 30 psi 80 psi Minimum 1 5 psi Maximum 17 5 psi FUEL GRADES Aviation Gasoline 80 87 red minimum grade or alternate grades 1OOLL blue or 100 green See Engine Manufacturer s Bulletin Oll SPECIFICATIONS Ashless dispersant oils must meet Teledyne Continental Motors Corporation Specification MHS 248 Refer to APPROVED ENGINE OILS in the Handling Servicing ...

Страница 29: ... approved but not installed as original equipment These are listed in the FAA Airerah Speeifieation 3A15 or approved by Supplemental Type Certifieate POWER PLANT INSTRUMENT MARKINGS Oll TEMPERATURE Caution Yellow Radial 100 F 38 C Operating Range Green Are 100 to 225 F 38 to 107 C Maximum Red Radial 225 F 107 C Oll PRESSURE Minimum Pressure Red Radial 30 psi Operating Range Green Are 30 to 60 psi ...

Страница 30: ...60 F 238 C MANIFOLD PRESSURE Operating Range Green Are 15 to 29 6 in Hg Maximum Red Radial 29 6 in Hg MISCELLANEOUS INSTRUMENT MARKINGS INSTRUMENT VACUUM With Autopilot Minimum Red Radial 3 75 in Ag Operating Range Green Are 3 75 to 4 25 in Hg Maximum Red Radial 4 6 in Hg r _ Without Autopilot Minimum Red Radial 4 4 in Hg Operating Range Green Are 4 8 to 5 2 in Hg Maximum Red Radial 5 5 in Hg FUEL...

Страница 31: ...7 inches aft of datum to 2525 lbswith straight line variation to 85 7 inches at 2900 lbs REFERENCE DATUM Datum is 83 1 inches forward of center line through forward jack points MAC leadi ng edge is 66 7 inches aft of datum MAC length is 65 3 inches MANEUVER LIMITS This is a utility category airplane Spins are prohibited No acrobatic maneuvers are approved except those listed below Maximum slip dur...

Страница 32: ... Lazy Eight 123 kts 1142 mph Stall Except Whip Use slow deceleration Minimum tue for above maneuvers 10 gallons each main tank Spins are prohibited FLIGHT LOAD FACTORS 2900 POUNDS Positive Maneuvering Load Factors Flaps Up 4 4G Flaps Down 2 0G MINIMUM FLIGHT CREW One 1 Pilot KINDS OF OPERATION LIMITS 1 VFR day and night 2 IFR day and night April 1982 2 9 ...

Страница 33: ...onditions the airplane could not be flown unless all equipment was operable With appropriate limitations 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 operation Operation in accordance with limitations established to maintain airworthiness can permit continued or uninterrupted ...

Страница 34: ...ilot to determine whether the lack of or inoperative status of a piece of equipment on his airplane will limit the conditions under which he may operate the airplane WARNING FLIGHT IN ICING CONDITIONS IS PRO HIBITED LEGEND Numbers refer to quantities required to be operative for a specified condition lndicates that the item may be inoperative for the specified condition Refer to the REMARKS AND OR...

Страница 35: ...ght ATA 100 CHAPTER 23 COMMUNICATIONS VHF communications system ATA 100 CHAPTER 24 ELECTRICAL POWER Battery DC generator VFR Day VFR Night FR Day FR Night Remarks andl or Exceptions Per FAR 91 Per FAR 91 1 1 1 1 1 1 1 1 c l I 0 J 0 J II lJ m Om 1 tT I g I c w w ...

Страница 36: ...gency locator trans mitter ATA 100 CHAPTER 26 FIRE PROTECTION Portable fire extinguisher ATA 100 CHAPTER 27 FLIGHT CONTROLS Elevator trim tab indicator 1 1 1 1 1 1 1 1 1 1 1 1 Per Person or Per FAR 91 Pilot and copilot if installed Per FAR 91 Optional c CJ m CT m 0 J w D w T1 3 C I 0 0 J J 1 ...

Страница 37: ... 100 CHAPTER 28 FUEL EQUIPMENT Auxiliary fuel pump Engine driven fuel pump Fuel quantity indicator Fuel pressure indicator VFR Day VFR Night FR Day FR Night Remarks andl or Exceptions 2 2 2 2 1 1 1 1 1 1 1 1 1 1 1 1 2 2 2 2 1 1 1 1 c C 3 CD III 0 s 0 s In IJJ m Cm CD lj g III Jl w w 1 ...

Страница 38: ...AND RAIN PROTECTION Pitot heater ATA 100 CHAPTER 32 LANDING GEAR Landing gear motor Landi ng gear position indication lights Landing gear aural warni ng horn 1 2 1 1 1 1 1 1 2 2 2 1 1 1 Optional 0 CD Dm er m 0 z w u w r Tl 1 r J D i o g J III ...

Страница 39: ...Landing light Rotati ng beacon Position light ATA 100 CHAPTER 34 NAVIGATION INSTRUMENTS Altimeter Airspeed indicator VFR Day VFR Night FR Day FR Night Remarks andI or Exceptions Lights must be operative Per FAR 91 1 1 3 3 1 1 1 1 1 1 1 1 c C 3 D g_ 0 J 0 J Cll Cl o rn CD CT C g Q II w Tl w l ...

Страница 40: ...rectional gyro Clock Transponder Navigation equipment ATA 100 CHAPTER 35 OXYGEN Oxygen system ATA 100 CHAPTER 37 VACUUM Vacuum system for instrument air Vacuum gage 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 Optional Per FAR 91 Per FAR 9 1 Per FAR 91 0 IXl CD m CT m 0 C c C w 1J w T1 CD 0 s 0 0 l l III ...

Страница 41: ...i ne tachometer indicator Manifold pressure indicator ATA 100 CHAPTER 79 ENGINE Oll INSTRUMENTS Oil pressure indicator Oil temperature indicator VFR Day VFR Night FR Day FR Night Remarks and or Exceptions 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 c t 3 CD II 0 ö 1 iil al m Cm CD c r J g II 0 w T1 w 1 ...

Страница 42: ...t least 10 gallons from left main tank before use of auxiliary fuel When operati ng fuel selector feel for detent position Do not take oft when Fuel Quantity Gages indicate in Yellow Band or with less than 13 gallons in each main tank Maximum slip duration 30 seconds for airplanes with baffled main fuel cells in both wings 20 seconds for airplanes with unbaffled main fuel cells in either wing SEAT...

Страница 43: ...BEECHCRAFT Debonair33 ILh ao NOT TAKE OFF IF FUEL QUANTITY GAGES V INDICATE IN YELLOW BAND OR WITH LESS L THAN 13 GALLONS IN EACH MAIN TANK _J Standard 44 Gallon Usab e System 2 20 OFFÜ USE 10 GAL FIRST LH TANKO 22 GAL L 0 OFF ORH TANK 22 GAL _J April 1982 ...

Страница 44: ...SECOND LEVEL FLIGHT ONLY _J Above Emergency Landing Gear Extension Handle EMERGENCY LANDING GEAR INSTRUCTIONS TO EXTEND ENGAGE HANDLE IN REAR OF FRONT SEAT AND TURN COUNTERCLOCKWISE AS FAR AS POSSIBLE 50 TURNS Above Landing Gear Mechanical Position lndicator When Winter Baff es Are lnstalled NOTICE REMOVE WINTER BAFFLES WHEN OAT EXCEEDS 70 F L _J April 1982 2 21 ...

Страница 45: ... Hand Subpanel l I FIRE DOOR PULL TO CLOSE On Inner Side Of Baggage Compartment Door BAGGAGECOMPARTMENT LOAD IN ACCORDANC E WITH AIRPLANE FLIGHT MANUAL MAXIMUM STRUCTURAL CAPACITY 270 POUNDS On Storm Window CAUTION 00 NOT OPEN ABOVE 145 MPH 126 KNOTS L _J 2 22 April 1982 ...

Страница 46: ...ANEUVERS APPROVED EXCEPT THOSE LISTED IN THE AIRPLANE FLIGHT MANUAL _J AUX FUEL PUMP OPERATION TAKE OFF AND LAND WITH AUX FUEL PUMP OFF EXCEPT IN CASE OF LOSS OF FUEL PRESSURE AIRSPEED LIMITATIO N MAXIMUM SPEED WITH LANDING GEAR EXTENDEO INORMALI 140 MPH MAXIMUM DESIGN MANEUVERING SPEED 142 MPH L _J Above Inside Door Handle CAUTION AFTER DOOR CLOSING ROTA TE HANDLE TO FULL L LOCKED POSITION _J Apr...

Страница 47: ...t BEECHCRAFT Debonair33 Unless baffled main fuel cel s are installed in both wings ITuRNING TYPE TAKEOFFS ANOI TAKEOFF IMMEDIATELY FOLLOWING FAST TAXI TURN PROHIBITED AVOID PROLONGED SLIPS 20 SECONDS OR 1 MORE WITH FUEL TANKS LESS THAN HALF FULL _j 2 24 April 1982 ...

Страница 48: ... Airstart Procedure 3 5 Engine Fire 3 6 In FI ight 3 6 On The Ground 3 6 Maximum Glide Configuration 3 6 Emergency Descent 3 7 Landing Emergencies 3 7 Landi ng W ithout Power 3 7 Landing Gear Retracted W ith Power 3 7 Systems Emergencies 3 8 Propeller Overspeed 3 8 Generator Out Procedure 3 8 Landing Gear Manual Extension 3 8 Landing Gear Retraction After Practice Manual Extension 3 9 Unlatched Do...

Страница 49: ...l during flare without power 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 practicable the emergencies requiring immediate corrective action are treated in check list form for easy reference and familiari zation Other situations i...

Страница 50: ...neuvering accomplish the fol owing 1 Fuel Selector Valve SELECT OTHER MAIN TANK Check to feel detent 2 Auxiliary Fuel Pump ON 3 Mixture FULL RICH then LEAN as required 4 Magnetos CHECK LEFT and RIGHT then BOTH NOTE The rnost probable cause of engine failure would be loss of fuel flow or improper functioning of the ignition system lf No Restart 1 Select most favorable landing site 2 See EMERGENCY L...

Страница 51: ... c Auxiliary Fuel Pump OFF if performance does not improve in a few moments 2 Fuel Quantity lndicator CHECK for fuel supply in tar being used lf tank being used is empty Fuel Tank Selector Valve SELECT ANOTHER MAIN FUEL TANK feel for detent AIR START PROCEDURE a Fuel Selector Valve SELECT MAIN TANK MORE NEARLY FULL check to feel detent b Throttle RETARD c Mixture FULL RICH d Auxiliary Fuel Pump ON...

Страница 52: ...ture IDLE CUT OFF 3 Fuel Selector Valve OFF 4 Battery and Generator Switches OFF Extending the landing gear can be accomplished manually if desired 5 Do not attempt to restart engine ON THE GROUND 1 Mixture IDLE CUT OFF 2 Fuel Selector Valve OFF 3 Battery Generator and lgnition Switches OFF 4 Extinguish with Fire Extinguisher MAXIMUM GLIDE CONFIGURATION 1 Landing Gear UP 2 Flaps UP 3 Propeller PUL...

Страница 53: ...oach 1 Airspeed 80 kts 92 mph 2 Fuel Selector Valve OFF 3 Mixture IDLE CUT OFF 4 Flaps AS REQUIRED 5 Landing Gear DOWN OR UP DEPENDING ON TERRAIN 6 Battery and Generator Switches OFF r LANDING GEAR RETRACTED WITH POWER lt possible choose firm sod or foamed runway Make a normal approach using flaps as necessary When you are sure of making the selected landing spot 1 Throttle CLOSED 2 Mixture IDLE C...

Страница 54: ...CEDURE A failure of the generator will place the entire electrical operation of the aircraft on the battery Generator failure may be indicated by the ammeter When a generator failure occurs in flight all non essential electrical load should be discontinued to conserve the battery life LANDING GEAR MANUAL EXTENSION Manual extension of the landing gear can be facilitated by first reducing airspeed T...

Страница 55: ... 7 Handcrank DISENGAGE Always keep it stowed when not in use WARNING Do not operate the landing gear electrically with the handcrank engaged as damage to the mechanism could occur After emergency landing gear extension do not move any landing gear controls or reset any switches or circuit breakers until airplane is on jacks as failure may have been in the gear up circuit and gear might retract on ...

Страница 56: ...to the direction of the spin continue to hold this control position until rotation stops and then neutralize all controls and execute a smooth pullout Ailerons should be neutral and throttle in idle position at all times during recovery EMERGENCY SPEED REDUCTION In an emergency the landing gear may be used to create additional drag Should disorientation occur under in strument conditions the lower...

Страница 57: ... 4 4 Before Starting 4 7 Starting 4 7 After Starting and Taxi 4 9 Before Take Off 4 9 Take Off 4 11 Climb 4 11 Cruise 4 11 Descent 4 1 1 Before Landing 4 12 Balked Landing 4 12 After Landing 4 12 Shutdown 4 13 Environmental Systems 4 13 Cold Weather Operation 4 13 lcing Conditions 4 15 Engine Break in Information 4 15 April 1982 4 1 ...

Страница 58: ...PERATION Take off Lift oft 67 kts 77 mph 50 Ft 73 kts 84 mph Maximum Climb Best Rate Vy 90 kts 104 mph Best Angle Vxl 71 kts 82 mph Cruise Climb 113 kts 130 mph Maximum Turbulent Air Penetration 123 kts 142 mph Balked Landing Climb 70 kts 81 mph Landing Approach 70 kts 81 mph Maximum Demonstrated Crosswind 17 kts 20 mph April 1982 4 3 ...

Страница 59: ...ocator Transmitter ARMED Location may vary with individual airplanes 1 CABIN a Parking Brake SET b Control Lock REMOVE c All Switches OFF 2 RIGHT FUSELAGE BEECHCRAFT Debonair33 a Baggage Compartment Door SECURE b Static Pressure Button UNOBSTRUCTED 4 4 April 1982 ...

Страница 60: ...ECK b Aileron CHECK c Wing Tip CHECK d Position Light CHECK 6 LEFT WING LEADING EDGE a Stall Warning CHECK b Pitot Tube CHECK Remove Cover c Fuel Tank s CHECK OUANTITY Filler Cap s SECURE d Cabin Air lntake CHECK e Tie Down and Chocks REMOVE 7 LEFT LANDING GEAR a Wheel Weil Door Tire and Strut CHECK b Fuel Vent CHECK r c Fuel Sump s DRAIN d Fuel Selector Valve Sump and Auxiliary Fuel Cell lntercon...

Страница 61: ...HECK f lnduction Air lntake CLEAR g Engine CHECK GENERAL CONDITION h Right Cowl SECURE i Chocks REMOVE 9 RIGHT LANDING GEAR a Fuel Vent CHECK b Fuel Sump s DRAIN c Wheel Weil Door Tire and Strut CHECK 10 RIGHT WING LEADING EDGE a Tie Down and Chocks REMOVE b Fuel Tank s CHECK OUANTITY Filler Cap s SECURE 11 RIGHT WING TRAILING EDGE a Position Light CHECK b Wing Tip CHECK c Aileron CHECK d Flap CHE...

Страница 62: ... S LECT LEFT MAIN TANK 10 Battery and Generator Switches ON lt external power is used turn Generator Switch OFF See Sections 7 and 8 11 Fuel Quantity lndicators CHECK QUANTITY WARNING Do not take oft if gages indicate in yellow arc or with less than 13 gallons in each main tank STARTING CAUTION Vernier type engine controls should not be rotated clockwise after being advanced to the full forward po...

Страница 63: ...arts CAUT ON Do not engage Starter for more than 30 seconds in any 4 minute period 7 In the Event of Overprime Condition a Mixture IDLE CUT OFF b Throttle OPEN c Starter Button PRESS d As engine starts reduce throttle to IDLE and advance mixture to FULL RICH NOTE During hot starts if there is an indication of vapor in the fuel system fluctuating fuel pressure switch the auxiliary fuel pump to ON t...

Страница 64: ...airplane should be shut down AFTER STARTING AND TAXI 1 Brakes RELEASE AND CHECK 2 Avionics Equipment ON AS REQUIRED 3 Lights AS REQUIRED CAUTJON Do not operate engine above 1200 RPM until oil temperature reaches 75 F 24 C BEFORE TAKEOFF 1 Parking Brake SET 2 Seat Belts and Shoulder Harnesses CHECK NOTE All reclining seats must be in the upright posi tion during takeoff 3 Avionics CHECK 4 Engine In...

Страница 65: ...CK at 1700 rpm variance between individual magnetos should not exceed 50 rpm maxi mum drop not to exceed 150 rpm 11 Trim SET a Aileron NEUTRAL if installed b Elevator 0 3 nose up if only front seats are occupied 12 Flaps Check operation then UP 13 Door and Windows SECURE 14 Controls CHECK PROPER DIRECTION AND FREE DOM OF MOVEMENT 15 Mixture FULL RICH or as required by field el evation 16 Brakes RE...

Страница 66: ...unway remains for landing 4 Airspeed ESTABLISH DESIRED CLIMB SPEED when clear of obstacles CLIMB Maximum Continuous Full throttle 2600 rpm Cruise Climb 25 in Hg or full throttle 2500 rpm 1 Engine Temperatures MONITOR 2 Power SET AS DESIRED 3 Mixture SET FUEL PRESSURE CRUISE See Cruise Charts in PERFORMANCE Section 1 Power SET 2 Mixture SET FUEL PRESSURE DESCENT 1 Altimeter SET 2 Power AS REQUIRED ...

Страница 67: ...evation 4 Landing Gear DOWN and CHECK Observe rnaxirnurn extension speed 5 Landing Light AS REQUIRED 6 Flaps DOWN Observe rnaxirnurn extension speed 7 A irspeed ESTABLISH LANDING APPROACH SPEED 8 Propeller HIGH RPM BALKED LANDING 1 Power FULL THROTILE 2600 RPM 2 Airspeed 70 kts 81 rnph until clear of obstacles then trirn to normal clirnb speed 3 Landing Gear UP 4 Flaps UP AFTER LANDING 1 Landing L...

Страница 68: ...TION PREFLIGHT INSPECTION All accumulations of ice snow and frost must be removed from the wings tail control surfaces and hinges pro peller windshield fuel cell filler caps crankcase vents and fuel vents lf such accumulations are not removed completely the airplane shall not be flown The deposits will not blow off in flight While an adverse weight factor is clearly involved in the case of heavy d...

Страница 69: ...n the oil pressure may de crease when residual oil in the engine is pumped back with the congealed oil in the sump lf an engine heater capable of heating both the engine sump and cooler is not available the oil should be drained while the engine is hot and stored in a warm area until the next flight lf there is no oil pressure within the first 30 seconds of running or if oil pressure drops after a...

Страница 70: ...uring letdown and landing give Special attention to en gine temperatures since the engine w ill have a tendency toward overcooling ICING CONDITIONS Flight in lcing Conditions ls Prohibited ENGINE BREAK IN INFORMATION See Section 7 Systems April 1982 4 15 ...

Страница 71: ...s Temperature Conversion 5 12 ISA Conversion 5 13 Stall Speeds Power ldle 5 14 Wind Components 5 15 Take Off Distance 5 16 Climb 5 17 Time Fuel and Distance to Climb 5 18 Cruise Power Settings 75 MCP Or Full Throttle 5 19 65 MCP Or Full Throttle 5 20 55 MCP Or Full Throttle 5 21 45 MCP Or Full Throttle 5 22 Cruise Speeds 5 23 Manifold Pressure vs RPM 5 24 Fuel Flow vs Brake Horsepower 5 25 Fuel Fl...

Страница 72: ...SectionV Performance BEECHCRAFT Debonair33 TABLE OF CONTENTS Continued SUBJECT PAGE Endurance Profile 63 Gallons 5 29 Endurance Profile 44 Gallons 5 30 Landing Distance 5 31 _ 5 2 April 1982 ...

Страница 73: ...re detailed below All examples and calculations utilize the following conditions CONDITIONS At Denver Outside Air Temperature 15 C 59 F Field Elevation 5330 ft Altimeter Setting 29 60 in Hg Wind 270 at 10 kts Runway 26L length 10 010 ft Route of Trip DEN VS1 AMA For VFR Cruise at 11 500 feet ROUTE MAGNETIC DIST SEGMENT COURSE NM DEN COS 161 55 COS PUB 153 40 PUB TBE 13 0 74 TBE DHT 132 87 DHT AMA ...

Страница 74: ... 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 29 60 32 in Hg The pressure altitude at DEN is 320 feet above the field elevation 5330 320 5650 ft Pressure Altitude at AMA 29 92 29 56 36 in Hg The pressure altitude at AMA is 360 feet above the field elevation 5 4 3605 360 3965 ft NOTE For flight planning the diffe...

Страница 75: ...either the cruise power setting table for 75 percent or 65 per cent maximum continuous power The temperatures for cruise are presented for a standard day ISA 20 C 36 F above a standard day ISA 20 C and 20 C 36 F below a standard day ISA 20 C These should be used for flight planning The IOAT values are true temperature values which have been adjusted for the compressibility effects IOAT should be u...

Страница 76: ...N HG GPH KNOTS IN HG GPH KNOTS 10000 20 1 6 1 12 0 156 20 1 5 6 1 1 2 155 12000 18 6 5 5 11 1 154 18 6 5 1 10 5 152 lnterpol ate for 11 500 feet and the temperature for the appropriate route segment Results of the interpolations are 5 6 MAN FUEL ROUTE PRESS FLOW TAS SEGMENT IN HG PSl GPH KNOTS DEN PUB 18 9 5 6 11 2 154 PUB TBE 18 9 5 5 11 1 154 TBE DHT 18 9 5 3 10 8 153 DHT AMA 18 9 5 3 10 7 153 N...

Страница 77: ... COS PUB 40 180 PUB TBE 74 139 TBE DHT 87 141 DHT AMA 65 143 FUEL TIME AT USED CRUISE FOR ALTITUDE CRUISE HRS MIN GAL 0 09 1 7 0 13 2 4 0 32 5 9 0 37 6 7 0 27 4 8 Distance required to climb has been subtracted from segment distance TIME FUEL DISTANCE TIME FUEL DISTANCE ITEM HRS MINS GAL NM Start Runup Taxi and Take off acceleration 0 00 1 7 0 Climb 0 13 3 7 27 Cruise 1 58 21 5 294 Total 2 11 26 9 ...

Страница 78: ... Reserve fuel 45 min 8 3 GPH 6 2 gallons Total Fuel 26 9 6 2 33 1 gallons The estimated landing weight is determined by subtracting the fuel required for the trip from the ramp weight Assumed ramp weight 2910 lbs Estimated fuel from DEN to AMA 26 9 gal 6 lbsjgal 1611bs Estimated landing weight 2910 161 2749 lbs Examples have been provided on the performance graphs The above conditions have been us...

Страница 79: ...gin following guide lines Always project to the reference line first then follow the guide lines to the next known item 3 lndicated airspeeds IAS were obtained by using the AIRSPEED CALIBRATION NORMAL SYSTEM Graph 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 val...

Страница 80: ...20 130 140 150 160 170 1 190 200 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 70 80 90 100110 120130140 150 160 170 180 190 200 210220230 IAS INDICATEO AIRSPEED MPH 230 220 210 200 if 190 190 70 l2 160 160 140 5130 120 3110 100 90 80 70 190 180 170 160 1 160 0 140 l2 130 0 120 110 100 390 eo 70 60 CAS 88 KNOTS 101 MPHI FLAPS DOWN 60 M 90 1001W120130140 IAS INOICATEO AIRSPEED KNOTS 1 1 1 1 1 10 eo oo 100 110 ...

Страница 81: ...1 1 1 I I 1 1 1 1 1 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 IAS INDICATEO AIRSPEED MPH 80 EXAMPLE IAS FLAPS INOICATEO PRESSUAE ALTITUOE ALTIMETER CORRECTlON ACTUAL PRESSURE ALTITUOE FLAPS DOWN 112 KN OTS UP 5000 FEET 10 FEET 5000 10 4990 FEET 50 60 70 80 90 100 110 120 130 140 IAS INOICATEO AIASPEED rv KNOTS T 1 1 1 1 1 1 1 1 I 1 1 1 I 60 70 80 90 100 110 120 130140 150...

Страница 82: ...Section V Performance BEECHCRAFT Debonair33 1 e I zi 0 2 0 2 2 0 0 0 t n 1 7 1 1 1 J S33H l30 5 12 A pril 1982 ...

Страница 83: ... BEECHCRAFT Debonair33 w c z 0 a c w z 0 0 u c 2 c w w April 1982 SectionV Performance u j 1 r ol UJ a Y i o f r 0 133 30n Ll L111 31lnSS3ijd a UJ 1 1 1 0 0 I _ 0 5 13 ...

Страница 84: ...WAS 200 rT 2 ANORMAL STALL RECOVERY TECHNIOUE MAY BE USED 2800 2600 2400 2200 WEIGHT POU NDS 2000 0 10 20 30 40 50 60 ANGLE OF BANK DEGREES S tia1 fE FLAPS ANGLE OF BANK STALL SPEED 90 100 BO 90 V I 0 z 70 l 80 0 w w w w 70 l 60 l 60 50 1 50 40 2600 LBS UP 30 62 KNOTS 7 1 MPH O Cfl CD CD i 0 0 3 s III s 0 CD o J o CD CT I g III lJ w Tl w 1 ...

Страница 85: ...ated Crosswind Component is 17 kts EXAMPLE WINOSPEED ANGLE BETWEEN WIND OIRECTION ANO FLIGHT PATH HEADWIND COMPONENT CROSSWIND COMPONENT FLIGHT PATH V 20 0 z l z w 10 z 0 Q 0 u 0 z 0 0 w X 10 0 April 1982 10 20 CROSSWINO COMPONENTS 30 KNOTS 20 KTS 500 13 KTS 15 KTS 5 15 ...

Страница 86: ...SSURE ALTITUDE TAKE OFF WEIGHT HEAO WIND COMP GROUND ROLL TOTAL DISTANCE OVER A 10 FT OBSTACLE TAKE OFF SPEED AT UFT OFF 50 FT d P S 40 30 20 10 0 10 20 30 40 50 2800 2800 2400 2200 OUTSIDE AIR TEMPERATURE C WEIGHT POUNDS 1 1 1 1 1 1 1 1 1 1 i 1 11 1 40 20 0 20 40 60 so 100 120 OUTSIDE AIR TEMPEAATUAE F 15 C 159 Fi 5650 FT 2900 LBS 9 5 KNOTS 1900 fEET 1 67 KNOTS 77 MPH 73 KNOTS 8d MPHI A _ q 9 q f...

Страница 87: ...i 1 1 1 1 1 1 1 1 1 70 60 50 40 30 20 10 0 10 20 30 4 50 OUTSIDE AtR TEMPEAATUAE 0 c 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 80 60 40 20 0 20 40 60 80 100 120 OUTSIDE AIR TEMPEAATURE 0 f IIJ T 2800 3S 33KC16 RATE OF CUMB CUMB GRADIENT CUMB SPEED 1300 1200 00 1000 z 900 800 2 700 J 600 0 llimmm1 s 1500 400 300 200 100 o 2600 2400 2200 WEIGHT rv POUNDS 13 12 11 10 9 B 7 6 5 5 C 123 F 11500FT 2...

Страница 88: ...20 10 10 20 30 40 50 60 OUTSIDE AIR TEMPERATUREf v C 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 o w m w oo 100 1w 1m OUTSIDE AIR TEMPERATUAE oF TIME T0 CLIMB 22 91 FUE l TO CUMB 6 2 2 5 DISTANCE TO CLIMB 45 18 q w i 210Q 10 20 30 40 TIME TO CLIMßrvMINUTES f t 1 l 1 1 l l T 1 T l r l 1 1 0 1 2 3 4 5 6 7 B 9 10 FUEL TO CUMB GALLONS t t f T r r T 1 1 1 1 1 1 1 1 111 0 10 20 30 40 50 60 70 80 OISTANCE ...

Страница 89: ...ESS FLOW TAS OAT OF j oC PSI IGPHIKTSIMPH oFloc PSI IGPH KTSIMPH oF oc FEET RPM IN HG RPM IN HG SL 211 3 2450 23 4 7 3 113 411 461 168 631 17 2450 24 0 7 3 113 4 149 2000 201 7 2450 22 9 7 3 113 41148 NOTES 1 FULL THROTTLE MANIFOLD PRESSURE SETTINGS ARE APPROXIMATE 2 SHADED AREA REPRESENTS OPERATION WITH FULL THROTTLE ISA 36 F l 20 cJ ENGINE MAN FUE L SPEED PRESS FLOW 1 TAS RPM IN HG cm CD m CT m ...

Страница 90: ...12 11 2450 20 3 5 8 11 5 142 164 48 9 2450 208 5 8 11 5 145 167 84 29 2450 6000 5 15 2450 19 8 5 8 11 5 145 167 41 5 2450 20 4 6 8 11 5 148 170 77 25 2450 8000 2 19 2450 19 4 5 8 11 5 147 170 34 1 2450 19 9 6 8 11 5 151 174 70 21 2450 1 10000 9 23 2450 18 9 5 8 11 5 150 173 27 3 2450 19 5 6 8 11 5 153 177 17 245 12000 16 27 24 50 18 5 5 8 11 5 153 176 2 7 W 24 1 18 6 M 11 1 164 1itij 116 3 2450 f4...

Страница 91: ... 1 1 4 7 9 8 133 153 2300 19 7 4 7 9 8 130 150 55 13 2300 20 3 4 7 9 8 133 153 9 1 33 2300 20 7 4 7 9 8 135 156 2300 19 2 4 7 9 8 132 152 48 9 2300 19 8 4 7 9 8 135 155 84 29 2300 20 2 4 7 9 8 138 158 2300 18 7 4 9 8 135 155 41 5 2300 19 3 4 7 9 8 137 158 77 25 2300 19 8 4 7 9 8 140 16 1 2300 18 2 4 7 9 8 137 157 34 1 2300 18 8 4 7 9 8 140 161 70 21 2300 19 3 4 7 9 R 14 11 4 2300 17 8 4 7 9 8 139 ...

Страница 92: ... 8 3 122 140 40 5 2 100 19 1 4 0 8 3 124 142 76 25 2100 18 2 4 0 8 3 123 142 33 1 2 100 18 7 4 0 8 3 125 144 69 21 2 100 17 7 4 0 8 3 125 144 26 3 2 100 18 2 4 0 8 3 127 146 62 17 2 100 17 3 4 0 8 3 126 146 19 7 2100 k L7 4 0 8 3 128 148 55 13 2 100 16 8 4 0 E i l 1 ir 12 21cio 4 1 3 3 9 8 2 128 1Ai 48 9 ttoo 1e e a 1 9 122 t41 4 t 2 100 tl 3 8 7 ll 1111 7 3 3 1 FULL THROTTLE MANIFOLD PR ESSURE SE...

Страница 93: ...T TEMPERATURE STANDARD OAY ISAI FULL THROTILE 450 RPM rnue AIRSPEED 154 KNOTS 16000 15000 14000 13000 12000 11000 UJ UJ 10000 u 2 UJ 9000 Cl 5 8000 UJ 7000 a Cf Cf 6000 UJ a a _ 5000 4000 3000 Q Q ii ii J J J J Jg i i i f a a a a g g X X 2000 1000 Q Q 1 w l l 1 Q w Q Q Q w Q Q i 0 2 SL 1 1 1 110 120 130 140 150 160 TAUE AIRSPEED rv KNOTS April 1982 5 23 ...

Страница 94: ...8 1700 1800 MANIFOLD PRESSURE vs RPM NOTRECOMMENDED FOR CRUISE SEITING 1900 2000 2100 2200 2300 2400 2500 ENGJNE SPEED APM EXAMPLE ENGINE SPEED 2450 RPM MAN FOLD PAESSURE 18 9 IN HG WITHIN AECOMMENDED LIMITS 2600 tl Cf CD CD i 0 0 3 i III i CD CD m Om CD CT C 0 u l w w ...

Страница 95: ...N 65 MCP LEVEL FLIGHT CRUISE LEAN FUEL FLOW 11 4 GAlJHA 12 FUEL FLOW 11 0 GAlftiA CONDITION LEVEL FLIGHT CRUISE LEAN BRAKE HORSEPOWER 22 21 20 19 18 75 17 TAKE OFF 16 AND CLIMB 65 15 J 2 14 i 13 w 12 11 10 55 CRUISE 45 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 BRAKE HOASEPOWER April 1982 5 25 ...

Страница 96: ... FUEL FLOW vs FUEL PRESSURE EXAMPLE FUfl FLOW 10 6 GA HR 15 _ t l 14 _ i _ f 13 r _ 12 II _ tt I I Q g 1 c w w 8 u Cl _ I 1 _ r _ 5 t 4 EE e t t t 41 4 i 3 III _ _ y _ 1 1 l 5 7 8 10 II 12 13 14 15 16 17 18 19 20 FUEL fLOW GAUiR 5 26 April 1982 ...

Страница 97: ...AL 378 LBS 20000 w 15000 w RANGE INCLUDES START TAXI ANO CUMB WITH 45 MINUTES RESERVE FUEL AT 45 MCP EXAMPLE PRESSURE ALTITUOE 11500 rT POWER SETTING FULL THROTTLE 2450 RPM RANGE 715 NM 0 t 10000 1 CRUISE TRUE Y 0 AIRSPEED rv KNOTS w a P 1 15 1 140 125 Ul Ul 5000 w a 0 l SL 550 600 650 700 750 800 850 900 950 RANGE rv NAUTICAL MILES ZERO WIND om CD m c r m 0 C J C w lJ w CD C 0 CD 0 3 111 0 J J g ...

Страница 98: ...000 w 0 5 10000 U J a cn cn w lt 5000 SL 300 350 STANDARD OAY llSAI RANG INCLUDES START TAXI ANO CLIMB WITH 45 MINUTE RESERVE FUEL AT 45 Jii MCP IU 0 Q a a r 0 0 _ _ 500 CRUISE TRUE AIRSPEED KNOTS tl 550 600 RANGErvNAUTICAL MILES ZERO WIND EXAMPLE PRESSURE ALTITUOE POWER SEmNG RANGf 650 l fl ö 700 ll SOOFT FULL THROnLE 24 50 RPM 452 NM o rn III III i 0 0 3 1 g n III m m Om III er J 0 JJ l w w t ...

Страница 99: ...5 MINUTES RESERVE FUEL AT 45 MCP tti t 1 9 v v o A 1 EXAMPLE PRESSURE ALTITUDE 11 500 FT POWER sen1NG FULL THROTILE 2450 RPM ENDURANCE 4 7 HOURS 4 HOURS 42 MINUTE 15000 w 0 i 1 o J O _D m 0 0 0 154 r 44 s CRUISE TRUE 5 10000 w a i w a 0 5000 SL 3 5 _y i 0 I l t 158 151 140 s 0 b u 0 f 155 145 135 tr i l 149 140 P H131 1 1 1 4 0 4 5 5 0 5 5 6 0 ENDURANCE HOURS 128 AIRSPEED 125 3 i 119 1 6 5 7 0 KNO...

Страница 100: ...TIAL f UH LOAOING 44 US GAL 611 LUSI EN5iJRANCE INCLUOES S1AIH TAXI AND CLIMB W ITH 45 MINUTES R nvr 1Vll AT 450 MCP 9 u 2 w 0 E w a w a a 20000 15000 5000 SL 1 2 0 d 117 1 1 2 5 3 0 3 5 4 0 4 5 5 0 ENDURANCE HOURS 5 5 PRESSURE ALTITUOE 11500 fl POWER SETIING FULL TH l01 lll 2450 RPM ENOURANCE 3 02 HOURS 1 pi l l l 6 0 3 HOUAS 1 MINUrt 1 2 C ä 0 3 s g m Cm CD C c g m J J w Tl w i ...

Страница 101: ...TT 1 1 1 1 40 20 0 20 40 60 80 100 120 OUTSIDE AIR TEMPERATUAE F W ElGHT PEEO AT 50 FT POUNDS KNOTS MPH 2900 70 81 2800 69 79 2600 67 77 2400 65 75 2200 63 73 2800 2600 2400 WEtGHT POUNDS OAT PRESSURE ALTITUOE WEIGHT W IND COMPONENT GROUNO ROLL TOTAL OVEA 50 FT OBSTACLE APPROACH SPEED 2200 10 20 30 1 25 C 177 Fi 3965 FT 2708 LBS 8 0 KNOTS HEADWINO 1140 FEET 1750 FEET 68 KNOTS 78 MPH so 3000 2500 1...

Страница 102: ...ons 6 10 Seating Baggage and Equipment Arrangements 6 11 Center of Gravity Graph 6 12 Moment Limits vs Weight Table 6 13 Computing Procedure 6 16 Sample Weight and Balance Loading Form 6 18 Weight and Balance Loading Form 6 19 Useful Load Weights and Moments 6 20 Occupants 6 20 Baggage 6 20 Cargo 6 21 Usable Fuel 6 22 Auxiliary Wing Tanks 6 22 Oil 6 22 Equipment List Provided for each airplane Apr...

Страница 103: ...he airplane in static ground attitude When tanks are drained 1 5 pounds of undrainable fuel remain in the airplane at Fuselage Station 76 0 The remainder of the unusable fuel to be added to a drained system is 34 5 pounds at Fuselage Station 79 1 and 5 pounds at Fuselage Station 94 0 for airplanes with 10 gallon auxiliary tanks installed 3 Engine oil must be at the full level or completely drained...

Страница 104: ...heel axle center line The main wheel axle center line is best located by stretching a string across from one main wheel to the other All measurements are to be taken with the tape level with the hangar floor and parallel to the fuselage center line The locations of the wheel reactions will be approximately at Fuselage Station 96 7 for main wheels and Fuselage Station 12 7 for the nose wheel 7 Jack...

Страница 105: ... Equip List 8 Weighing should always be made in an enclosed area which is free from air currents The scalP S used should be properly calibrated and certified LEVELING POINTS pr FRONT JACK POINTS REAR JACK POINT F S 83 1 F S 271 0 April 1982 6 5 ...

Страница 106: ...13 1 97 AFT 271 0 Signature REACTION SCALE NET WHEEL JACK POINTS READING TARE 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 DRY ENGINE Oll 22 557 UNUSABLE FUEL 36 79 2844 WITH AUX TANKS INSTALLED 5 94 470 BASIC EMPTY WEIGHT III l s Q 0 ca s III rii 0 c a c i ca m Om CD tT I 0 iil IJ ...

Страница 107: ...it is suggested that a running tally of equipment changes and their effect on empty weight and c g is a suitable means for meeting both requirements The current equipment list and empty weight and c g information must be retained with the airplane when it changes ownership Beech Aircraft Corporation cannot maintain this information the current status is known only to the owner lf these papers beco...

Страница 108: ...N OUT WEIGHT AND BALANCE RECORD REGISTRATION NO PAGE NO WEIGHT CHANGE RUNNING BASIC DESCRIPTION OF ARTICLE ADDE D OR REMOVED EMPTY WEIGHT OR CHANGE WT ARM MOM WT MOM LBS IN 100 LBS 100 g a ll 0 Ol J III c c 0 c Ol m Cm CD C c g III 1 w T1 W 4 ...

Страница 109: ...O IN OUT WEIGHT AND BALANCE RECORD REGISTRATION NO PAGE NO WEIGHT CHANGE RUNNING BASIC DESCRIPTION OF ARTICLE ADDED OR REMOVED EMPTY WEIGHT OR CHANGE WT ARM MOM WT MOM LBS IN 100 LBS 100 c al m c r m 0 J w z i w I s c al I 4 c c o 5 c s cn ...

Страница 110: ... are the responsibility of the airplane owner and or operator ihe empty weight and moment of the airplane at the time of delivery are shown on the airplane Empty Weight and Balance form Useful load items which may be loaded into the airplane are shown on the Useful Load Weight and Moment tables The minimum and maximum moments are indicated on the Moment Limits vs Weight graph These mome_nts corres...

Страница 111: ...M WEIGHT 200 POUNDS FORWARD OF REAR SPAR INCLUDING EQUIPMENT AND CARGO WITH REAR SEAT REMOVED MAXIMUM WEIGHT 270 POUNDS AFT OF REAR SPAR INCLUDING EQUIPMENT AND CARGO WITH REAR SEAT REMOVED NOTE The floor structure load limit is 100 pounds per square foot except for the area between the front and rear spars where the floor structure load limit is 50 pounds per square foot NOTE All baggage cargo mu...

Страница 112: ...00 1 1 1 1 1 1 1 1 1 1 1 1 L l 2500 r I 1 1 APPROVED CENTER OF GRAVITY LIMITS 2400 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 2300 1 1w 1 1 1 1 1 1 1 1 1 1 1 1 t 1 2200 __ _ _ ___ _ ____ __ J _ 76 77 78 79 80 81 82 83 84 85 86 1 87 88 89 1 1 78 0 86 7 CENTER OF GRAVITY INCHES AFT OF DATUM m z 4 m D 0 Tl Ci D a c 0 m i III s 0 c g c II m m Cm CD C c g Cll D w Tl w 4 ...

Страница 113: ...take off 82 1 85 7 or landing 2550 lb 78 0 86 6 2525 lb or less 78 0 86 7 Minimum Maximum Moment Moment Weight 100 100 2100 1638 1821 2110 1646 1829 2120 1654 1838 2130 1661 1847 2140 1669 1855 2150 1677 1864 2160 1685 1873 2170 1693 1881 2180 1700 1890 2190 1708 1899 2200 1716 1907 2210 1724 1916 2220 1732 1925 2230 1739 1933 2240 1747 1942 2250 1755 1951 2260 1763 1959 2270 1771 1968 2280 1778 1...

Страница 114: ...1825 2029 2350 1833 2037 2360 1841 2046 2370 1849 2055 2380 1856 2063 2390 1864 2072 2400 1872 2081 2410 1880 2089 2420 1888 2098 2430 1895 2107 2440 1903 2115 2450 1911 2124 2460 1919 2133 2470 1927 2141 2480 1934 2150 2490 1942 2159 2500 1950 2168 2510 1958 2176 2520 1966 2185 2530 1973 2193 2540 1981 2201 2550 1989 2209 2560 2000 2217 2570 2011 2225 2580 2021 2233 2590 2032 2241 6 14 April 1982...

Страница 115: ...1 2650 2098 2289 2660 2109 2297 2670 2120 2305 2680 2131 2312 2690 2142 2320 2700 2153 2328 2710 2165 2336 2720 2176 2344 2730 2187 2352 2740 2198 2360 2750 2209 2368 2760 2221 2376 2770 2232 2383 2780 2243 2391 2790 2255 2399 2800 2266 2407 2810 2277 2415 2820 2289 2423 2830 2300 2431 2840 2312 2438 2850 2323 2446 2860 2335 2454 2870 2346 2462 2880 2358 2470 2890 2369 2478 2900 2381 2485 April 19...

Страница 116: ...irplane 3 Total the weight column and moment column The SUB TOTAL is the Zero Fuel Condition 4 Determine the weight and corresponding moment for the fuel loading to be used This fuel loading includes fuel for the flight plus that required for start taxi and take off Add the Fuel to Zero Fuel Condition to obtain the SUB TOTAL Ramp Condition 5 Subtract the fuel to be used for start taxi and take off...

Страница 117: ...s must be shifted aft or forward load items reduced lf the total moment is greater than the maximum moment al lowed useful load items must be shifted forward or aft load items reduced lf the quantity or location of load items is changed the calculations must be revised and the moments rechecked The Empty Weight for the airplane may be converted to Basic Empty Weight by adding the weight and moment...

Страница 118: ... OCCUPANTS 340 292 3 REAR SEAT OCCUPANTS 340 402 4 BAGGAGE 5 CARGO 6 CARGO c i 7 SUB TOTAL ZERO FUEL CONDITION 2550 2136 8 FUEL MAIN 44 GAL 264 198 FUEL AUX 16 GAL 96 90 9 SUB TOTAL RAMP CONDITION 2910 2424 10 LESS FUEL FOR START TAXI AND TAK OFF 10 8 11 SUB TOTAL TAKE OFF CONDITION 2900 2416 12 LESS FUEL LEFT MAIN 15 GAL 90 68 13 SUB TOTAL 2810 2348 14 LESS FUEL AUX 16 GAL 96 90 15 SUB TOTAL 2714...

Страница 119: ...3 REAR SEAT OCCUPANTS 4 BAGGAGE 5 CARGO 6 CARGO 7 SUB TOTAL ZERO FUEL CONDITION 8 FUEL MAI N GAL FUEL AUX GAL 9 SUB TOTAL RAMP CONDITION 10 LESS FUEL FOR START TAXI AND TAKE OFF 11 SUB TOTAL TAKE OFF CONDITION 12 LESS FUEL LEFT MAIN GAL 13 SUB TOTAL 14 LESS FUEL AUX GAL 15 SUB TOTAL 16 LESS FUEL MAIN GAL 17 LANDING CONDITION Fuel for start taxi and take off is normally 10 lbs at an average mom 100...

Страница 120: ...30 112 116 153 140 120 125 165 150 129 134 177 160 138 142 189 170 146 151 201 180 155 160 212 190 163 169 224 200 172 178 236 NOTE OCCUPANT POSITIONS FOR ADJUSTABLE SEATS ARE SHOWN AT THEIR EXTREME POSITIONS INTER MEDIATE POSITIONS WILL REOUIRE INTERPOLATION OF THE MOMENT 100 VALUES Weight 10 20 30 40 50 6 20 BAGGAGE ARM 140 Moment 100 Weight 14 60 28 70 42 80 56 90 70 100 Moment 100 84 98 112 12...

Страница 121: ... 6 Flight Instruments 7 6 Power Plant Instruments 7 7 Cluster Type Power Plant Instruments 7 7 Manifold Pressure Tachometer and Fuel Pressure Gage 7 7 Instrument Panel Schematic 7 8 Instrument Panel Legend 7 9 Switches 7 10 Ground Control 7 11 Wing Flaps 7 11 Landing Gear System 7 12 Control Switch 7 12 Position lndicators 7 13 Circuit Breaker 7 13 Safety Switch 7 13 Warning Horn 7 14 Brakes 7 14 ...

Страница 122: ...7 17 lnduction System lcing 7 18 Lubrication System 7 18 Starter 7 18 Propeller 7 19 Fuel System 7 19 Fuel Cells 7 19 Fuel System Schematic 7 20 Fuel Quantity lndication System 7 21 Auxiliary Fuel Pump 7 22 Fuel Tank Selection 7 22 Fuel Required for Flight 7 22 Electrical System 7 23 Battery 7 23 Generator 7 23 External Power Receptacle 7 24 Lighting System 7 25 lnterior Lighting 7 25 Exterior Lig...

Страница 123: ...CONTENTS Continued SUBJECT PAGE Cabin Ventilation 7 28 Cabin Fresh Air Outlets 7 28 Pitot and Static Systems 7 28 Pitot System 7 28 Pitot Heat Optional 7 29 Static Air System 7 29 Vacuum System 7 29 Stall Warning 7 30 Engine Break in Information 7 30 April 1982 7 3 ...

Страница 124: ...d aileron control can be placed in front of either front seat Pull the T handle latch at the back of the control arm and position the control wheel as desired The optional aileron trimmer on the control column hub should be held until the column is repositioned Check for full freedom of movement after repositioning the control The optional dual control column is required for flight instruction RUD...

Страница 125: ...adio grouping on the left side of the instrument panel and subpanels which provide a compact circuit breaker group on the right side and switch panels on both sides All configurations of the instrument panel are similar in grouping and convenient arrangement FLIGHT INSTRUMENTS Standard flight instrumentation on the Debonair includes an airspeed indicator and altimeter mounted in the instrument pan...

Страница 126: ...tity gages oil pressure gage the oil temperature and cylinder head temperature indicators and ammeter The fuel quantity gage is a single instrument a switch on the left subpanel selects the cell on which a reading is desired When the two ten gallon auxiliary wing tanks are installed an auxiliary fuel quantity gage is added to the cluster Like the main cell system a switch on the subpanel selects t...

Страница 127: ...Section VII BEECHCRAFT Systems Description Debonair33 r 0 t CO cn c 1 c c 1 c 1 _ c c 1 c 1 cn c 1 CO t c 1 c 1 r c 1 r c 1 CO _ c 1 t cn c 1 c 0 c 1 i 0 ö c 1 7 8 April 1982 ...

Страница 128: ...ity gages oil pressure gage the oil temperature and cylinder head temperature indicators and ammeter The fuel quantity gage is a single instrument a switch on the left subpanel selects the cell on which a reading is desired When the two ten gallon auxiliary wing tanks are installed an auxiliary fuel quantity gage is added to the duster Like the main cell system a switch on the subpanel selects the...

Страница 129: ... 2 3 4 5 6 7 8 9 10 11 12 13 14 15 cn cn a 00 l a 3 g Cll o a Cll C es 1 gJ m Cm a C er i g m 0 00 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 w w i ...

Страница 130: ...or 13 Instrument Lights 14 Landi ng Gear Switch 15 Fire Door Control 16 Beacon Switch 17 Generator Switch 18 Battery Switch 19 Nav Lights Switch 20 Landi ng Light Switch 21 Cabin Heat Control 22 Parki ng Brake Control 23 Propeller Control 24 lgnition Key Switch 25 Mixture Control 26 Aux Fuel Pump Switch 27 Throttle 28 Starter Switch 29 Elevator Trim Tab Control 30 Flap Switch 31 Aux Fuel Gage Swit...

Страница 131: ...uel pressures In the cruise power range the green sectors cover the fuel pressure required from 45 to 75 power The lowest value of a given sector is the cruise lean setting and the highest value of the sector is the best power setting for that particular power range The take off and climb range is covered by green sectors for full power at various altitudes The high side of each green sector repre...

Страница 132: ...ted The steering link attaches to the steering mechanism on the nose strut with a swivel connection which permits the mechanism to disengage when the nose gear is retracted and operation of the rudder pedals will have no tendency to turn the nose wheel with the gear retracted The minimum wing tip turning radius using full steering one brake and partial power is 26 feet 4 inches WING FLAPS The wing...

Страница 133: ... strut The landing gears are operated through adjustable linkage connected to an actuator assembly mounted beneath the front seats The actuator assembly is driven by an electric motor The landi ng gears may be electrically retracted and extended and in an emergency may be extended manually CONTROL SWITCH The landing gear is controlled by a two position switch on the right side of the subpanel The ...

Страница 134: ...d a dynamic brake automatically stop the retract mechanism when the gear reaches its full up or full down position CIRCUIT BREAKER The landing gear circuit breaker is located on the right subpanel This circuit breaker is a pull and reset type breaker The breaker will pop out under overload conditions SAFETY SWITCH To prevent inadvertent retraction of the landing gear on the ground a main strut saf...

Страница 135: ... pedals in conjunction with an overriding pumping action from the op posite brake pedals could result in the loss of braking action on the side which continuous pressure is being applied The parking brake push pull control is located on the right subpanel To set the parking brakes pull control out and depress both toe pedals until firm Push the control in to release the brakes 7 14 CAUTION The par...

Страница 136: ...be secured WARNING Do not carry hazardous material anywhere in the airplane Do not carry children in the baggage compart ment SEATS AND SEAT BELTS SEAT ADJUSTMENTS Both of the individual front seats are adjustable fore and aft by pulling up on the small lever in front of each seat cushion and pulling or pushing on the seat In addition the front seat backs are adjustable by a set screw located on t...

Страница 137: ...e latch handle is free to move approximately one inch in either direction before engagement of the locking mechanism Then grasp the door and firmly pull the door closed Rotate the door handle fully counterclockwise into the locked position When the door is properly locked the door latch handle is free to move approximately one inch in either direction NOTE When checking the door latch handle do no...

Страница 138: ...The BEECHCRAFT Debonair 33 is powered by a Conti nental 10 470 J wet sump fuel injection engine This six cylinder powerplant is rated at 225 hp at 2600 rpm for take off and maximum continuous operation The 10 470 K engine is eligible for installation but not directly inter changeable with the 10 470 J engine ENGINE CONTROLS THROTTLE PROPELLER AND MIXTURE The push pull throttle propeller and mixtur...

Страница 139: ...cally and the induction system will operate on alternate air LUBRICATION SYSTEM The engine oil system is the full pressure wet sump type and has a 10 quart capacity Oil operating temperatures are controlled by an automatic thermostat bypass control The bypass control will limit oil flow through the oil cooler when operating temperatures are below normal and will permit the oil to bypass the cooler...

Страница 140: ...lost the propeller will go to the full high rpm position This is because propeller low rpm is obtained by governor boosted engine oil pressure working against the centrifugal twisting moment of the blades FUEL SYSTEM The airplane is designed for operation on 80 87 grade red aviation gasoline In the event this grade is not available only a higher rated fuel shall be used CAUTION Before refueling ma...

Страница 141: ...tionVll Systems Description BEECHCRAFT Debonair33 AUX 7 20 FUEL SYSTEM SCHEMATIC ENGINE AUXILIARY FUEL PUMP t FUEL SELECTOR VALVE STRAINER MAIN LEGEND FUEL SUPPLY FUEL RETURN FUEL TANK VENT AUX April 1982 ...

Страница 142: ...o each main cell Except for the aux iliary cells fuel is returned to the cell from which it is drawn The auxiliary cells return fuel to the left main cell only To provide space for the returned fuel from the aux iliary cells the left main cell should be used to approxi mately half full before switching to auxiliary lf the engine is allowed to stop firing due to insufficient fuel refer to the EMERG...

Страница 143: ...s should be made using the left main tank and landings should be made using the main tank that is more nearly full In no case should a take off be made if the fuel indicators show less than 13 gallons of fuel in each main tank lf the engine stops because of insufficient fuel refer to the EMERGENCY PROCEDURES Section for the Air Start procedures FUEL REQUIRED FOR FLIGHT lt is the pilot s responsibi...

Страница 144: ...he ground return The battery ON OFF switch and the generator ON OFF switch are located on the right subpanel The IGNITION key switch is located below the control column The circuit breaker panel is located on the right subpanel and contains the protective circuit breakers for the various electrical systems BATIERY A 35 ampere hour 12 volt battery is located on the right aft side of the firewall Ba...

Страница 145: ...oad of electrical equipment then in use EXTERNAL POWER RECEPTACLE The external power receptacle accepts a standard AN type plug Before connecting an external power unit turn gen erator alternator switch and avionic equipment OFF CAUTION A negative ground external power source is required Check polarity before using external power lf the external power unit does not have a Standard AN type plug con...

Страница 146: ...witches for all of the exterior lights are located on the pilot s right subpanel The exterior lights consist of navigation lights on the wing tips and tail cone rotating beacon optional and a landing light on the nose gear strut For longer battery and lamp life use the landing light sparingly avoid prolonged operation which could cause overheating during ground maneuvering NOTE Particularly at nig...

Страница 147: ...a controlled quantity of unheated ram air Air of the desired temperature is then ducted from the mixer valve to the outlets in the cabin HEATER AND DEFROSTER OPERATION The cabin heat control is located on the lower right pilot s subpanel To obtain heated air to the cabin outlets pull the CABIN HEAT control The control regulates the amount of cold air that is mixed with the air from the heater muff...

Страница 148: ...BEECHCRAFT Debonair33 Section VII Systems Description HEATING AND VENTILATION SYSTEM SCHEMATIC 1 1 April 1982 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 7 27 ...

Страница 149: ...ll the FIRE DOOR control and use only the fresh air outlets described in the following paragraphs CABIN FRESH AIR OUTLETS A duct in the left wing root is connected directly to an adjustable outlet in the upholstery panel just below the in strument panel The volume of air from the outlet is regulated and the direction of airflow is controlled by rotating the louvered cover with the small knob on th...

Страница 150: ...rear baggage compartment and removing the section of rubber hose The rubber hose section should be re moved and the moisture drained from the line every 100 hours and after exposure to visible moisture either in the air or on the ground VACUUM SYSTEM Vacuum for air driven gyroscopic flight instruments and other air driven equipment is supplied by an engine driven vacuum pump An adjustable relief v...

Страница 151: ...oil changes may be necessary Oil changes are more critical during the break in period than at any other time Use full throttle at recommended rpm for every take off and maintain until at least 400 feet AGL then reduce as necessary for cruise climb or cruise Maintain the highest power recommended for cruise operations during the break in period avoiding altitudes above 8000 feet Inter rupt cruise p...

Страница 152: ... or Repairs to Airplane 8 8 Ground Handling 8 8 Towing 8 8 Parking 8 9 Tie Down 8 10 Main Wheel Jacking 8 10 Prolonged Out of Service Care 8 11 Flyable Storage 7 to 30 Days 8 1 1 Mooring 8 11 Engine Preparation For Storage 8 11 Fuel Cells 8 11 Flight Control Surfaces 8 12 Grounding 8 12 Pitot Tube 8 1 2 Windshield and Windows 8 12 During Flyable Storage 8 12 Preparation For Service 8 12 External P...

Страница 153: ...ish Strut Hydraulic Fluid 8 18 Shock Strut Shimmy Damper 8 19 Brakes 8 20 Vacuum System 8 20 lnduction Air Filter 8 21 To Remove and Clean the Filter 8 21 Propeller Blades 8 21 Minor Maintenance 8 22 Rubber Seals 8 22 Generator 8 22 Magnetos 8 23 Cleaning 8 23 Exterior Painted Surfaces 8 23 Windshield and Windows 8 26 lnterior 8 26 Engine 8 27 Recommended Servicing Schedule 8 28 Lubrication Points...

Страница 154: ...ONTENTS Continued SUBJECT PAGE Overhaul or Replacement Schedule 8 46 Special Conditions Cautionary Notice 8 46 Landing Gear 8 47 Power Plant 8 47 Fuel System 8 48 Instruments 8 49 Electrical System 8 49 Flaps and Flight Controls 8 50 Miscellaneous 8 50 April 1982 8 3 ...

Страница 155: ...nce is done by qualified mechanics in conformity with all airworthiness requirements established for this airplane A ll limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandatory Authorized BEECHCRAFT Aero or Aviation Centers and International Distributors or Dealers will have recommended modification service and operat...

Страница 156: ...ns of FAA Ap proved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Manuals and Pilot s Oper ating Handbooks This service is free and will be provided only to holders of this handbook who are listed on the FAA Aircraft Registration Branch List or the BEECHCRAFT International Owners Notifi cation Service List and then only if you are listed by airplane serial number for t...

Страница 157: ... retract rods gear doors and flaps for damage or distortion PREVENTATIVE MAINTENANCE THAT MAY BE ACCOMPLISHED BY A CERTIFICATED PILOT 1 A certificated pilot may perform limited maintenance Refer to FAR Part 43 for the items which may be accomplished To ensure proper procedures are followed obtain a BEECHCRAFT Shop Manual for performing preventative maintenance 2 All other maintenance must be perfo...

Страница 158: ...r clearances for a standard airplane Allowances must be made for any special radio antennas CAUTION To ensure adequate propeller clearance al ways observe recommended shock strut ser vicing procedures and tire inflation pressures TOWING One man can move the airplane on a smooth and level surface using a hand tow bar Attach the tow bar to the tow lugs on the nose gear lower torque knee Where moveme...

Страница 159: ...sed when removing the tow bar to prevent damage to the lubrication fittings on the landing gear PARKING The parking brake push pull control is located on the right side of the lower subpanel Toset the parking brakes pull control out and depress both toe pedals until firm Push the control in to release the brakes CAUTION The parking brake should be left oft and wheel chocks installed if the airplan...

Страница 160: ...ively tight the nose may rise and produce litt due to the angle of attack of the wings 4 Release the parking brake lf high winds are anticipated a vertical tail post should be installed at the rear tie down lug and a tie down line attached to the nose gear MAIN WHEEL JACKING 1 Check the shock strut for proper inflation to prevent damage to the landing gear door by the jack adapter and to facilitat...

Страница 161: ...nnot be placed in a hangar tie down securely at the three points provided Do not use hemp or manila rope lt is recommended a tail support be used to compress the nose strut and reduce the angle of attack of the wings Attach a line to the nose gear ENG NE PREPARATION FOR STORAGE Engines in airplanes that are flown only occasionally tend to exhibit cylinder wall corrosion much more than engines that...

Страница 162: ...ler 60 or 120 from the position it was in WARNING Before rotation of propeller blades ascertain ignition switch is OFF throttle in CLOSED position and mixture control is in the IDLE CUT OFF position Always stand in the clear while turning propeller lf at the end of 30 days airplane will not be removed from storage the engine shall be started and run The preferred method will be to fly the airplane...

Страница 163: ...ide pin 2 To prevent arcing make certain no power is being sup plied when the connection is made 3 Make certain that the battery switch is ON all avi onics and electrical switches OFF and a battery is in the system before connecting an external power unit This protects the voltage regulators and associated electrical equipment from voltage transients power fluctuations CHECKING ELECTRICAL EQUIPMEN...

Страница 164: ...ller cap in each wing leading edge In the optional installation an auxiliary tank in each wing adds 20 gallons 19 gallons usable to the standard system A filler neck for each auxiliary tank is outboard and aft of the main cell filler neck FUEL DRAINS On the standard fuel system open the three snap type fuel drains daily to purge any water from the system Each fuel cell drain is located on the bott...

Страница 165: ...iners in the fuel cell outlets should not require cleaning unless there is a definite indication of solid foreign material in the cells or the airplane has been stored for an extended period Oll SYSTEM CAUT ON Oil consumption tends to be higher during break in periods on new engines therefore maximum range flights should be avoided and oil level brought to full after each flight during this period...

Страница 166: ...See Consumable Materials and Approved Engine Oils for specified oils The engine manufacturer recommends ashless dis persant oils In order to promote faster ring seating and oil control a straight mineral oil should be used for the first oil change period or until oil consumption stabilizes Oils must meet Teledyne Continental Motors Specification MHS 248 Refer to APPROVED ENGINE OILS BATIERY The ba...

Страница 167: ... kept open TIRES An inflation pressure of 30 psi should be maintained on the 6 00 x 6 main wheel tires The 5 00 x 5 nose wheel tire should be inflated to 40 psi Maintaining proper tire inflation will minimize tread wear and aid in preventing tire failure caused from running over sharp stones When inflating tires visually inspect them for cracks and breaks CAUTION Beech Aircraft Corporation cannot ...

Страница 168: ...is extended 3 inches 3 1 2 inches on the nose gear CAUTION lf a compressed air bettle containing air under extremely high pressure is used exercise care to avoid over inflating the shock strut WARNING NEVER FILL SHOCK STRUTS WITH OXYGEN 3 Remove all foreign material from the exposed piston with a soft cloth moistened with hydraulic fluid TO REPLENISH STRUT HYDRAULIC FLUID 1 Support the airplane on...

Страница 169: ...rut as described in the preceding inflation procedure SHOCK STRUT SHIMMY DAMPER The shimmy damper has a reservoir of fluid carried in the piston rod Two coil springs installed in the piston rod keep fluid in the shimmy damper under pressure As fluid is lost through leakage it is automatically replenished from the reservoir until the reservoir supply is exhausted To check the fluid level in the shi...

Страница 170: ... The brake hydraulic fluid reservoir is located on the firewall in the engine compartment A dipstick is attached to the reservoir cap Refer to Consumable Materials for hydraulic fluid specification The brakes require no adjustments since the pistons move to compensate for lining wear VACUUM SYSTEM The vacuum system incorporates two screens a relief valve screen and an oil separator screen These sc...

Страница 171: ...TO REMOVE AND CLEAN THE FILTER 1 Remove the fuselage nose section grill 2 Remove the wing nuts securing the filter and remove the filter 3 Clean as described in the manufacturer s instructions on the fi lter PROPELLER BLADES The daily preflight inspection should include a careful examination of the propeller blades for nicks and scratches Each blade leading edge should receive particular attention...

Страница 172: ...rmal cleaning methods GENERATOR Since the generator and voltage regulator are designed for use on only one polarity system the following precautionary measures must be observed when working on the charging circuit or serious damage to the electrical equipment will result 1 When installing a battery make certain that the ground polarity of the battery and the ground polarity of the generator are th...

Страница 173: ... noise filter capacitor with a wire which is grounded to the engine case Otherwise all spark plug leads should be disconnected or the cable outlet plate on the rear of the magneto should be removed CLEANING EXTERIOR PAINTED SURFACES WARNING Do not expose the elevator trim tab hinge lines and their pushrod systems to the direct stream or spray of high pressure soap and water washing equipment Fluid...

Страница 174: ... enamel lacquer and dope finishes require a curing period of approximately 90 days acrylic urethane polyester urethane and epoxy finishes eure in seven days at 75 F Wash uncured painted surfaces with cold or lukewarm water and a MILD NON DETERGENT SOAP Any rubbing of the surface should be done gently and held to a minimum to avoid cracking the paint film Prior to cleaning cover the wheels making c...

Страница 175: ... enamel lacquer and dope finishes require a curing period of approximately 90 days acrylic urethane polyester urethane and epoxy finishes eure in seven days at 75 F Wash uncured painted surfaces with cold or lukewarm water and a MILD NON DETERGENT SOAP Any rubbing of the surface should be done gently and held to a minimum to avoid cracking the paint film Prior to cleaning cover the wheels making c...

Страница 176: ... is some var ation in the procedures required for proper care of the several types of exterior paint Alkyd enamel lacquer and dope finishes must be polished and waxed periodically to maintain luster and to assure pro tection from the weather Acrylic enamel should be waxed and may be polished if desired Acrylic urethane may be waxed for protection from the elements but should not be polished unless...

Страница 177: ...her fluid anti ice fluid lacquer thinner or glass cleaner These materials will soften plastic and may cause it to craze After thoroughly cleaning the surface should be waxed wth a good grade of commercial wax The wax will fill in the minor scratches and help prevent further scratching Apply a thin even coat of wax and bring it to a high polish by rubbing lightly with a clean dry soft flannel cloth...

Страница 178: ...e and remove it with a vacuum cleaner The plastic trim instrument panel and control knobs need only be wiped with a damp cloth Oil and grease on the control wheel and control knobs can be removed with a cloth moistened with isopropyl alcohol Volatile solvents such as mentioned in the article on care of plastic windows should never be used since they soften and craze the plastic _ ENGINE Clean the ...

Страница 179: ...ttom of fuselage drain left side Drain auxiliary fuel cells Bottom of fuselage drain left side Service fuel cells main Top of w ings leading edge Service auxiliary fuel cells Aft and outboard of main cells Check battery electrolyte Under right cowling door and thru access door in firewall Change engine oil Lower side of engine LUBRICANT Number refers to item on Consumable Materials 5 6 6 See Shop ...

Страница 180: ...s K retract mechanism and uplock rollers 100 Hrs Clean fuel selector valve Left side belly strainer Clean vacuum pump Engine compartment regulator screen t Lubricate aileron control Each wing J linkage t Lubricate cabin door Aft edge of cabin door E mechanism Lubricate control column Forward of instrument linkage panel C Unless BEECHCRAFT S I 0448 211 has been complied with 7 4 7 7 4 10 4 4 c tt1 ...

Страница 181: ...el weil door hinges L N Lubricate landing gear Wheel wells A K retract mechanism and uplock rollers Lubricate nose wheel Nose wheel weil 8 steering mechanism Lubricate rudder pedals Cockpit M Lubricate trim tab control Control pedestal 0 tt Lubricate wheel bearings Nose and main wheels A K and feit seals tt After BEECHCRAFT S I 0448 2 11 has been comolied with LUBRICANT Number refers to item on Co...

Страница 182: ...uators Lubricate flap flex driveshafts Lubricate elevator tab actuators Clean spark plugs Service main and nose shock struts Under front seats in cabin G Under front seats in cabin F Under front seats in cabin F Under front seats in cabin G Inside wing aft of wheel well G Under floor in cabin Inside each horizontal stabilizer 1 Engine compartment Landing gear 8 3 10 9 10 10 2 0 aJ Cl m o m 0 I w i...

Страница 183: ...ir lines Behind aft cabin side panel access door Remove one end of the hose which forms the static line drain and permit the system to drain NOTE The static air line should be drained frequently during periods of high humidity Also drain the line each time the airplane is flown through heavy rain or is washed down Replace emergency locator At emergency locator transmitter battery c Cl J n 0 t 0 J ...

Страница 184: ...atteries Replace after one cumulative hour of use or after 50 of the useful charge life t Lubricate aileron control rod ends in place using SAE 20 or SAE 10W30 or remove aileron control rod assembly clean and relubricate control rod ends using MIL G 23827 grease Ro tate rod end bearings to assure adequate lubricant coverage Check aileron rigging after re installation of rod end assembly tt Lightly...

Страница 185: ...Section VIII Handling Serv Meint LUBRiCATION POINTS A B F G N M NOSE GEAR RETRACT 8 34 BEECHCRAFT Debonair33 April 1982 ...

Страница 186: ...BEECHCRAFT Debonair33 Section VIII Handling Serv Meint ELEVATOR TRIM CONTROL April 1982 8 35 ...

Страница 187: ...Section VIII Handling Serv Maint BEECHCRAFT Debonair33 E CABIN DOOR F LANDING GEAR ACTUATOR GEAR BOX G FLAP MOTOR AND ACTUATOR 8 36 April 1982 ...

Страница 188: ...BEECHCRAFT Debonair33 Section VIII Handling Serv Maint H 1 J April 1982 ELEVATORS AND RUDDER CONTROL MECHANISM ELEVATOR TAB M ECHANISM AILERON BELL CRANKS 8 37 ...

Страница 189: ...Section VIII Handling Serv Maint BEECHCRAFT Debonair33 MAIN GEAR RETRACT MAIN GEAR DOOR HINGES M RUDDER PEDALS 8 38 April 1982 ...

Страница 190: ...ction VIII Handling Serv Maint NOSE GEAR DOOR HINGES HAND OR PACK ZERK FITTING 1 FLUID CONTAINER SQUIRT CAN NOTE Letters are keyed to the Service Schedule Numbers refer to items in the Consumable Materials Chart April 1982 8 39 ...

Страница 191: ...oration consequently any product conforming to the specification listed may be used The products listed below have been tested and approved for aviation usage by Beech Aircraft Corporation by the vendor or by compliance with the ap plicable specifications Other products that are locally procurable which conform to the requirements of the applicable Military Specification may be used even though no...

Страница 192: ...ings and r bearing area before changing grease 2 Hydraulic Fluid MIL H 5606 3 Lubricating Grease MIL G 81322 General Purpose Wide Temperature 4 Lubricating Oil SAE No 20 or SAE10W 30 5 Engine Oil SAE No 30 Below 40 F SAE No 50 Above 40 F _ Approved Multiviscosity Oils 6 Engine Fuel Grade 80 87 Red 7 Solvent Federal Specification PD680 8 Lubricant Mobil Compound GG or Mobil 636 9 Lubricating Oil Ge...

Страница 193: ...paint Ashless dispersant oil Teledyne Continental Motors Corp Spec MHS 24B recommended straight mineral oils recommended during break in period See ser vicing data lf 80 87 RED grade fuel not available use 1OOLL BLUE or 100 GREEN grade fuel t Product of Oakite Products lnc 50 Valley Road Berkley Heights NJ 07922 Product of Bray Oil Co Los Angeles Calif Product of CRC Chemicals lnc Warminster Pa 18...

Страница 194: ...iation Oil EE U S A Gulf Oil Corporation Gulfpride Aviation AD Mobil Oil Company Mobil Aero Oil Pennzoil Company Pennzoil Aircraft Engine Oil Phillips Petroleum Co Phillips 66 Aviation Oil Type A Phillips X C Aviation Multiviscosity Oil SAE 20W 50 Phillips X C Aviation Multiviscosity Oil SAE 25W 60 Quaker State Oil Quaker State AD Aviation Refining Corp Engine Oil Red Ram Limited Red Ram X C Aviat...

Страница 195: ...nclair Avoil Texaco lnc Texaco Aircraft Engine Oil Premium AD Union Oil Co of Union A ircraft Engine Oil California 8 44 NOTE This chart lists all oils which were certified as meeting the requirements of Teledyne Continental Motors Specification MHS 248 at the time this handbook was published Any other oil which conforms to this specification may be used April 1982 ...

Страница 196: ...n 89 Elevator tab position indicator light 53R Fuel pump placard light 1813 Instrument flood light overhead 89 Landing gear position light 1813 Landing gear visual position light 53 Landing light 4522 Navigation light tail cone 93 Navigation light wing 1512 Rotating beacon Grimes A7079 12 Stall warning light 1813 April 1982 8 45 ...

Страница 197: ...s handbook are based on average usage and average environmental conditions SPECIAL CONDITIONS CAUTIONARY NOTICE Airplanes operated for Air Taxi or other than normal operation and airplanes operated in humid tropics or cold and damp climates etc may need more frequent inspections for wear corrosion and or lack of lubrication In these areas periodic inspections should be performed until the operator...

Страница 198: ...hours Every 4000 hours Every 1000 hours Every 500 hours or on condition Every 1000 hours On condition On condition On condition On condition On condition On condition On condition POWER PLANT NOTE When an engine has been overhauled or a new engine installed it is recommended that low power settings not be used until oil consumption has stabilized The average time for piston ring seating is approxi...

Страница 199: ...n Propeller governor At engine overhaul but not to exceed 1500 hours or 3 years Fuel pressure pump Every 1500 hours Cabin heat muff lnspect every 100 hours FUEL SYSTEM Fuel cells Wing fuel quantity transmitters Fuel cell drai n valve Fuel system check valves Fuel selector valve Auxiliary fuel pump All hose 8 48 On condition On condition On condition On condition lnspect every 600 hours Overhaul ev...

Страница 200: ...dition Airspeed indicator On condition Rate of climb On condition Fuel quantity On condition indicator Fuel pressure On condition indicator Manifold pressure indicator On condition Tachometer On condition Free air temperature On condition indicator All hose On condition Vacuum system filter Every 100 hours Vacuum regulator valve On condition ELEG RICAL SYSTEM Battery master relay All other relays ...

Страница 201: ... On condition inspect every 12 months The recommended engine overhaul period applies only to engines with nickel coated exhaust valves or nimonic exhaust valves provided that normal periodic inspections are properly carried out Engines that should conform to a shorter TBO period are listed in Teledyne Continental Motors Corporation Service Bulletin M79 14 Rev 1 dated April 21 1980 or later issue C...

Страница 202: ...andling Serv Maint Refer to Hartzell Propeller lnc Service Letter No 61 F dated August 31 1979 or later issue Applies only to propellers with hub serial number 71 XXXX and higher all other propellers 1200 hours or 5 years April 1982 8 51 ...

Страница 203: ...led or not Supplements for equipment for which the vendor obtained a Supplemental Type Certificate were included as loose equipment with the airplane at the time of delivery These and other Supplements for other equipment that was installed after the airplane was delivered new from the factory should be placed in this SUPPLEMENTS Section of this Pilot s Operating Handbook and FAA Approved Airplane...

Страница 204: ...T MANUAL LOG OF SUPPLEMENTS FAA Supplements must be in the airplane for flight operation when subject equipment is installed Supp Part Subject Rev Date No Number No 1 33 590013 1 Tactair T 2 Autopilot 1 6 77 2 33 590013 3 Tactair T 3 Autopilot 2 6 77 3 35 590101 9 McCauley Propeller 1 6 77 April 1982 9 3 ...

Страница 205: ...andbook only where covered in the items con tained herein LIMITATIONS 1 Autopilot operation not certificated above 20 000 feet 2 Do not use autopilot during take off or landing EMERGENCY PROCEDURES 1 lt a drop in suction below 3 5 is noted on the Instrument Suction Gage push Master Pilot OFF to return instruments to normal flight operation Check for leaks in Autopilot system at earliest convenienc...

Страница 206: ...onal Gyro with the Course Selector Knob Autopilot will bring airplane to desired heading if within 80 of either side of desired heading Past 80 the Heading Lock will turn the airplane to the re ciprocal of the heading requested All corrections using the Course Selector Knob have a turn rate of ap proximately 1 per second The Roll Trim Knob can be moved left or right to shift the roll zero point in...

Страница 207: ...he Pilot s Operating Handbook only where covered in the items con tained herein LIMITATION 1 Autopilot operation not certificated above 20 000 feet 2 Do not use autopilot during take off or landing EMERGENCY PROCEDURES 1 Maximum altitude lost during malfunctioning tests in cruise configuration 100 feet 2 Maximum altitude lost during malfunctioning test in approach configuration 100 feet 3 lt a dro...

Страница 208: ...ed Check for leakage at the earliest convenience NOTE The Altitude Hold may be overpowered manually however upon release ot the 1 controls the airplane w ill attempt to return to the set altitude unless Altitude Hold is dis engaged before changing altitude NORMALPROCEDURES 1 To Engage Autopilot Trim airplane for cruising flight Have Course Selector Card coincide with Directional Gyro heading Set P...

Страница 209: ...esired heading if within 80 of either side of desired heading Past 80 the Heading Lock will turn the airplane to the reciprocal of the heading requested All corrections using the Course Selector Knob have a turn rate of approxi mately 1 per second The tab beneath the Turn Knob can be moved left or right to shift the roll zero point up to two degrees in the corresponding direction When desired alti...

Страница 210: ...ilot s Operating Handbook and FAA Approved Airp ane Flight Manual when the McCauley 2A36C23 84 8 0 Propeller is installed LIMITATIONS Propeller Hub 2A36C23 81ade 848 0 Spinner D 3290 Pitch Setting Refer to Aircraft Specification 3A15 EMERGENCY PROCEDURES No change NORMAL PROCEDURES No change PERFORMANCE No change FAA Approved Revised June 1977 P N 35 590101 9 Chester A Rembleske Beech Aircraft Cor...

Страница 211: ...lars FAA General Aviation News FAA Accident Prevention Program Additional Information General Information on Specific Topics Maintenance Hazards of Unapproved Modifications Flight Planning Passenger Information Cards Stowage of Articles Flight Operations General Preflight lnspection Weight and Balance Autopilots and Electric Trim Systems Turbulent Weather Wind Shear Weather Radar Mountain Flying V...

Страница 212: ...t and Training 32 Spins 32 Descent 3 Vortices Wake Turbulence 32 Takeoff and Landing Conditions 32 Medical Facts for Pilots 3E General 3 Fatigue 3E Hypoxia 3t Hyperventilation 3C Alcohol 3 Drugs t Scuba Diving 4 Carbon Monoxide and Night Vision 4 Decompression Sickness 4 A Final Word 42 b April 1993 ...

Страница 213: ...6 17 6 18 8 21 0 45 101 0 17 2 18 4 20 6 4000 FEET 6000 FEET 20 75 169 0 21 8 65 146 0 19 5 21 0 21 3 55 124 O 17 5 18 6 20 9 18 8 45 101 0 15 3 16 3 18 4 22 4 75 169 0 22 1 20 l 21 7 65 146 0 19 7 21 3 18 0 19 2 21 6 55 124 0 17 7 18 9 21 3 15 8 17 0 18 9 45 101 O 15 5 16 6 18 6 22 7 20 75 169 0 22 5 20 4 21 9 65 146 0 20 1 21 6 18 2 19 6 22 0 55 124 0 18 0 19 2 21 6 16 0 17 2 19 2 45 101 O 15 7 ...

Страница 214: ...0 18 4 19 7 55 124 O 18 1 19 4 16 0 17 2 19 3 45 101 0 15 7 16 9 18 8 12 000 FEET 40 75 169 0 18 5 65 146 0 16 2 17 4 i ö 55 124 0 14 2 15 3 45 101 0 20 75 169 O 18 7 65 146 0 16 4 17 7 55 124 0 14 4 15 6 17 2 45 101 0 NOTES 75 169 O 1 Under 65 p wer use RPM 65 146 0 under 2450 Cor best pro 15 7 17 9 55 124 0 peller eUiciency 14 6 15 8 17 5 45 101 0 2 Do not exceed manUold 20 75 169 0 pressure and...

Страница 215: ...88 3 0 311 58 561 Summe Wägung 884 90 1768 018 Abzüge Tankinhalt Liter Dichte kg L Netto kg Hebelarm m Momentkgm KraftstoffTank 1 0 0 0 72 0 0 0 000 Kraftstoff Tank 2 0 0 0 72 0 0 0 000 0 0 0 000 Summe Abzüge 0 0 0 000 Berechnung Leergewicht und Leergewlchtsschwerpunkt Summe Wägung 884 9 1768 018 Summe Abzüge 0 0 0 000 Leergewicht l ergewichtsmoment Schwerpunktlage bezogen auf BE Schwerpunktlage b...

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