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Beech Beechcraft Bonanza V35, Pilot Operating Handbook

The Beech Beechcraft Bonanza V35 is a high-performance aircraft cherished by pilots worldwide. To maximize your flying experience, ensure you have the essential Pilot Operating Handbook handy. Visit our website to effortlessly download this manual for free, complete with comprehensive instructions and vital information for safe and efficient operation of the Bonanza V35.

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pursuant to a limited license granted by Raytheon Company. Prior to March 26, 2007, Beechcraft 
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Bonanza V35, V35A, V35B  

Pilot’s Operating Handbook/ 

FAA Approved Airplane Flight Manual 

Supplement Pack 

35-590118-31 Supplement Pack 

Summary of Contents for Beechcraft Bonanza V35

Page 1: ...be furnished to the pilot by CAR 3 NOTICE This handbook does not apply to models V35TC V35A TC and V35B TC with turbocharged systems installed per BEECH drawing 35 910028 and or STC SA 1035WE Airplane Serial Number C Jackson Beech Aircraft Corporatio DOA CE 2 Except as noted above this handbook supersedes all BEECH pub lished owner s manuals flight manuals and check lists issued for this airplane ...

Page 2: ...will be taken to read Raytheon Aircraft Company Exported under the authority of license exception TSU These commodities technology or software were exported from the United States in accordance with Export Administration Regulations Diversion contrary to U S law prohibited Raytlleea Aircraft Beeell Hawker Member of GAMA General Aviation GAMAManufacturers Association ...

Page 3: ...nual must be in the airplane for all flight operations Part Number subject Date 35 590118 31 BTC1 Fuel Selector Placard 8 26 97 Installation Note This page should be filed in the front of the Pi ors Operating Handbook and FAA Approved Airplane Flight Manual immediatelyfol lowing the Title page This page replaces any Log of Temporary Changes page dated prior to the date in the lower right comer of ...

Page 4: ...V35B D 9069 THffU D 9947 PILOT S OPERATINGHANDBOOK AND FAAAPPROVEDAIRPLANEFLIGKT MANUAL B4 Revision July 1994 LOG OF REVISIONS Page Description Title Page Updated Page A B4 New 10 1 thru Revised Section X Safety 10 48 lnfonnation May 1994 PAGE A ...

Page 5: ...D 9O69 THRU D 9947 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL 83 Revision October 1990 LOG OF REVISIONS Page Description Title Page Updated Page A B3 New 10 1 thru Revised Section X 10 48 Safety Information October 1990 PAGE A ...

Page 6: ...on Title Page Update Page A 82 New 2 9 Revise Maximum Baggage Compartment Load 2 10 Revise Center of Gravity Limits 2 32 Add WARNING Placard 6 1 Update Table of Contents 6 9 Add WARNING 6 10 Shift Material 6 10A Shift Material 6 108 Shift Material 6 14A 6 14B 6 14C 6 140 6 14E 6 14F 6 14G 6 14H 6 141 6 14J 6 14K 6 14L Add SAMPLE LOADINGS F Page A ...

Page 7: ...le of Contents Revise Important Notice Revise NOTE Shift Material and Revise Airplane Flight Manual Supplements Revision Record Add CAS for Placards Revise Emergency Exit Placard and Add CAS to Storm Window Placard Update Table of Contents Revise Emergency Exits Revise Vx Airspeed Revise Starting Caution Revise Before Takeoff Procedure Update Table of Contents Shift Material Revise Openable Cabin ...

Page 8: ...AL LOG OF REVISIONS ORIGINAL A MAY 1977 REISSUE B JANUARY 1982 PAGES DESCRIPTION Title Page Logo Page PageA a thru b 1 1th ru 1 20 2 1 th ru 2 32 3 1 thru 3 14 4 1 th ru 4 20 5 1 thru 5 32 6 1 thru 6 18 7 1 thru 7 44 8 1 thru 8 56 Section 9 See Log of Supplements 10 1 th ru 10 67 March 1981 18 PageA ...

Page 9: ...ls it is highly important to have SAFETY INFORMATION in a condensed 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 BEECHCRAFTor BEECHCRAFTapproved parts obtained from BEECHCRAFT approved sources in connection with the maintenance and repair of Beech airplanes Genuine BEE...

Page 10: ...his may render the part component or structural assembly even though originally manufactured by BEECHCRAFT unsuit able and unsafe for airplane use BEECHCRAFT expressly disclaims any responsibility for malfunctions failures damage or injury caused by use of non BEECHCRAFT approved parts TABLE OF CONTENTS SECTION 1 General SECTION 2 Limitations SECTION 3 Emergency Procedures SECTION 4 Normal Procedu...

Page 11: ... 1 9 Ground Turning 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 Terminology and Symbols 1 13 Meteorological Terminology 1 15 Power Terminology 1 16 Engine Controls and Instruments 1 16 Airplane Performance and Flight Planning T...

Page 12: ...Section I General 1 2 BEECHCRAFT Bonanza V35 V35A V35B thru D 9947 INTENTIONALLY LEFTBLANK January 1982 ...

Page 13: ...thout sacrificing economy The BEECHCRAFTBonanza must be operated according to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual andjor 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 Ope...

Page 14: ... and safety from this airplane USE OF THE HANDBOOK The Pilot s Operating Handbook is designed so that nec essary documents may be maintained for the safe and efficient operation of the BEECHCRAFT Bonanza 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...

Page 15: ...older of this manual automatically 1 Original issues and revisions of Class I and Class II Service Instructions 2 Original issues and revisions of FAA Ap proved Airplane Flight Manual Supplements 3 Reissues and revisions of FAA Approved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Man uals and Pilot s Operating Handbooks This service is free and will be provided only ...

Page 16: ...IRCRAFT CORPORATION EX PRESSLY RESERVES THE RIGHT TO SUPER SEDE CANCEL AND OR DECLARE OB SOLETE WITHOUT PRIORNOTICE ANY PART PART NUMBER KIT OR PUBLICATION REF ERENCEDIN THIS HANDBOOK The owner operator should always refer to all supplements whether STC Supplements or Beech Supplements for possible placards limi tations normal emergency and other opera tional procedures for proper operation of the...

Page 17: ...on of the Log of Revisions is a box containing a capital letter which denotes the issue or reissue of the handbook This letter may be suffixed by a number which indicates the numerical revision When a revision to any information in the handbook is made a new Log of Re visions will be issued All Logs of Revisions must be re tained in the handbook to provide a current record of ma terial status unti...

Page 18: ...ance 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 handbook delivered with it contains either an STC Supple mental ...

Page 19: ...BEECHCRAFT Bonanza V35 V35A V358 thru D 994 7 Section I General f 26 5 6 7 I I 7 7 33 6 WING AREA 181 sq ft I i 10 2 0 0 L o I 9 7 AIRPLANE THREE VIEW January 1982 1 9 ...

Page 20: ...9947 GROUND TURNING CLEARANCE 8 Radius for Wing Tip 26 ft 4 in Radius for Nose Wheel 12 ft 2 in Radius for Inside Gear 5 ft 1 in Radius for Outside Gear 14 ft 8 in TURNING RADII ARE CALCULATED USING FULL STEER ING ONE BRAKE AND PARTIAL POWER 1 10 January 1982 ...

Page 21: ...er using a McCauley 2A36C23 hub with 848 0 blades and a D3290A spinner assembly or McCauley constant speed three blade propeller using a McCauley 3A32C76 hub with 82NB 2 blades FUEL NOTE Other propellers are approved and are listed in the FAA Aircraft Specification 3A15 or are ap proved by Supplemental Type Certificate Aviation Gasoline 1OOLL blue or 100 green minimum grade STANDARD SYSTEM Total C...

Page 22: ...l Weight No Structural Limit Maximum Weight in Baggage Compartment 270 lbs CABIN AND ENTRY DIMENSIONS Length 10 ft 1 in Height 4 ft 2 in Width 3 ft 6 in Cabin Door 37 in wide by 36 in high BAGGAGE Compartment Volume 35 cu ft Door Width Minimum 18 5 in Door Height Minimum 22 5 in Volume Above Hat Shelf 1 7 cu ft SPECIFICLOADINGS Maximum Take Off Weight Wing Loading 18 8 lbs sq ft Power Loading 11 9...

Page 23: ... airspeed indicator when corrected for instrument error IAS values published in this handbook assume zero instrument error KCAS Calibrated Airspeed expressed in knots KIAS Indicated 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...

Page 24: ...mum Structural Cruising Speed is the or Ve 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...

Page 25: ...foot and zero above that altitude Outside Air Temperature is the free air static temperature obtained either from inflight temperature indica tions adjusted for instrument error and compressibility effects or ground meteorological sources The number actually read from an altimeter when the barometric sub scale has been set to 29 92 in Hg 1013 2 millibars Altitude measured from standard sea level p...

Page 26: ...ting not limited by time Power recommended for cruise climb ENGINE CONTROLS AND INSTRUMENTS Throttle Control Propeller Control Mixture 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 maintain engine propeller rpm at a selected v...

Page 27: ...ller hub AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb Gradient Demonstrated Crosswind Velocity MEA Route Segment January 1982 The ratio of the change in height during a portion of a climb to the horizontal distance traversed in the same time interval The maximum 90 crosswind com ponent for which adequate control of the airplane during take off and land ing was actually demonstrated d...

Page 28: ...rizontal 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 reducing the number of digits The point at which an airplane would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight...

Page 29: ...accordance with governmental regulations Weight of a standard airplane including unusable fuel full operating fluids and full oil Standard empty weight plus optional equipment Weight of occupants cargo and baggage Difference between take off weight or ramp weight if applicable and basic empty weight Maximum weight approved for ground maneuvering It includes weight of start taxi and run up fuel Max...

Page 30: ...7 Theweight of chocks blocks stands etc used on the scales when weighing an airplane 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 purposes January 1982 ...

Page 31: ...ions 2 5 Engine 2 5 Operating Limitations 2 5 Fuel 2 5 Oil 2 5 Propeller 2 6 Power Plant Instrument Markings 2 7 Weight Limits 2 9 Center of Gravity Limits 2 10 Approved Maneuvers 2 10 Flight Load Factors 2 10 Minimum Flight Crew 2 10 Kinds of Operation Limits 2 11 Required Equipment for Various Conditions of Flight 2 11 Fuel 2 21 Seating 2 21 Placards 2 22 January 1982 2 1 ...

Page 32: ...Section II Limitations 2 2 BEECHCRAFT Bonanza V35 V35A V358 thru D 9947 INTENTIONALLY LEFT BLANK January 1982 ...

Page 33: ... aximum 165 190 167 192 Do not exceed Structural this speed Cruising except in smooth VNO or Ve air and then only with caution Maneuvering 132 152 134 154 Do not make full VA or abrupt control movements above this speed Maximum 113 130 117 135 Do not extend Flap flaps or operate Extension with flaps ex Extended 122 140 123 142 tended above VFE this speed Maximum 143 165 145 167 Do not extend Landi...

Page 34: ... KNOTS MPH 52 117 60 135 52 123 60 142 64 167 74 192 167 196 192 226 196 226 The Airspeed Indicator is marked in CAS values Effective 0 8872 and After 0 00 N SIGNIFICANCE Full Flap Operating Range Normal Operating Range Operate with caution only in smooth air Maximum speed for ALL operations r u CD 3 n i5 I 0 I It cS cS 1ZO m wl U I Ill D J 2 l cm I 0 0 I CODI i l l ...

Page 35: ...pm Cylinder Head Temperature 460 F 238 C Oil Temperature 240 F 116 C Oil Pressure Minimum 30 psi Maximum 100 psi Fuel Pressure Minimum 1 5 psi Maximum 17 5 psi FUEL Aviation Gasoline lOOLL blue or 100 green minimum grade OIL SPECIFICATIONS Ashless dispersant oils must meet Teledyne Continental Motors Corporation Specification MHS 248 Refer to APPROVED ENGINE Olj S in the Handling Servicing and Mai...

Page 36: ...822 or 03396 assembly Governor Woodward C210452 or 0210680 or McCauley constant speed three bladed propeller Hub 3A32C76 2 6 Blades 82NB 2 Diameter Maximum 80 in Minimum 78 5 in Pitch settings at 30 in sta Low 13 3 0 2 High not under 29 0 0 5 Spinner McCauley 03584 assembly Governor Woodward C210452 or 0210680 NOTE Other propellers are approved and are listed in the FAA Aircraft Specification 3A 1...

Page 37: ...erating Range Green Arc 30 to 60 psi Maximum Pressure Red Radial 100 psi FUEL FLOW Minimum Red Radial 1 5 psi Operating Range Green Arc 6 9 to 24 3 gph Maximum Red Radial 17 5 psi TACHOMETER Operating Range Green Arc 1800 to 2700 rpm Maximum RPM Red Radial 2700 rpm CYLINDER HEAD TEMPERATURE Operating Range Green Arc 200 to 460 F 93 to 238 C Maximum Temperature Red Radial 460 F 238 C MANIFOLD PRESS...

Page 38: ...in Hg FUEL QUANTITY Yellow Band 44 gallon system Yellow Band 74 gallon system E to 1 2 full E to 3 8full POWER PLANT INSTRUMENT MARKINGS VERTICAL ELECTRICALLY OPERATED TYPE V35B When Installed OIL TEMPERATURE Caution Yellow Line 100 F 38 C Operating Range Green Band 100 to 240 FJ38 to 116 C Maximum Red Line 240 F 1 16 C OIL PRESSURE Minimum Pressure Red Line 30 psi Operating Range Green Band 30 to...

Page 39: ... to 29 6 in Hg Maximum Red Line 29 6 in Hg INSTRUMENT PRESSURE Minimum Red Radial 3 5 in Hg Operating Range Green Arc 3 5 to 5 5 in Hg Maximum Red Radial 5 5 in Hg or Operating Range Green Arc 4 3 to 5 9 in Hg FUEL QUANTITY Yellow Band 22 gal Main Tank Yellow Band 37 gal Main Tank WEIGHT LIMITS 0 to 80 lbs 0 to 80 lbs Maximum Ramp Weight 3412 lbs Maximum Take off and Landing Weight 3400 lbs Zero F...

Page 40: ...traight line variation to 84 4 inches at 3400 lbs REFERENCE DATUM Datum is 83 1 inches forward of center line through forward jack points MAC leading edge is 66 7 inches aft of datum MAC length is 65 3 inches PPROVED MANEUVERS 3400 POUNDS MANEUVER ENTRY SPEED CAS Chandelle 132 kts 152 mph Steep Turn 132 kts 152 mph Lazy Eight 132 kts 152 mph Stall Except Whip Use slow deceleration Minimum fuel for...

Page 41: ...ating condition and should be maintained to assure continued airworthiness If deviations from the installed equipment were not permitted or if the operating rules did not provide for various flight conditions 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 r...

Page 42: ...requirements necessary for a flight into specific conditions the following equipment requirements and exceptions are presented It is the final responsibility of the pilot 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 ref...

Page 43: ... COMMUNICATIONS VHF communications system ATA 100 CHAPTER 24 ELECTRICALPOWER Battery DC alternator VFR Day VFR Night FR Day FR Night Remarks and or Exceptions Per FAR 91 Per FAR 91 1 1 1 1 1 1 1 1 a wm CJIm n c w n JI a J J jlll 4 w a CJIO a 111 r I N C Ill C I CD co en CD n Ill t 0 0 I I Ill ...

Page 44: ...oulder harness Emergency locator trans mitter ATA 100 CHAPTER 26 FIRE PROTECTION Portable fire extinguisher VFRDay VFR Night FR Day FR Night Remarks and or Exceptions 1 1 1 1 Optional 1 1 1 1 Per person or per FAR 91 Pilot and copilot if installed 1 1 1 1 Per FAR 91 Optional r I GI I n g ct I o 1 Ill c5 w Cl m J m Pm o w c Cl 0 m D 2 cm I 0 co I coI i I I ...

Page 45: ...OLS Elevator trim tab indicator 1 Flap position indicator 1 Stall warning 1 ATA 100 CHAPTER 28 FUEL EQUIPMENT Auxiliary fuel pump 1 Engine driven fuel pump 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 m wm enm o z WO JI 0 J J wm JI 0 a Ill r N C Ill 0 0 U en l d 0 0 Ill ...

Page 46: ...tor Fuel flow indicator ATA 100 CHAPTER 30 ICE AND RAIN PROTECTION Emergency static air source Pitot heater VFRDay VFRNight FR Day FR Night Remarks and or Exceptions 2 2 2 2 1 1 1 1 Optional 1 1 Optional en 3 n g ct I g w m J m RD m n w Z n m a J 2 I om I 0 co I coIll _ i ...

Page 47: ...ng gear warning horn ATA 100 CHAPTER 33 LIGHTS Cockpit and instrument lights Taxi light Landing light Rotating beacon Position light 1 4 1 1 1 4 4 1 1 1 3 1 4 1 1 3 2 on the V35 and V35A Lights must be operative Per FAR 91 Optional m wm enm o c c 0 II D l l c m II 0 m 111 r N C Ill C CD CD C 3 fl t 0 0 Ill ...

Page 48: ...l speed Magnetic compass Attitude indicator Turn and slip indicator Directional gyro Clock Transponder Navigation equipment VFRDay 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 1 1 1 1 Per FAR 91 Per FAR 91 I I CD 3 n Eer 0 Ill w 1 w UI m J m IP m n w c Uln m a J 2 I cm I 0 co coIll II Ii ...

Page 49: ...100 CHAPTER 36 PNEUMATIC V36A V368 Pressure system for instrument air Pressure gage ATA 100 CHAPTER 37 VACUUM V36 Vacuum system for instrument air Vacuum gage 1 1 1 1 1 1 1 1 Per FAR 91 m wm C1 Im 0 c Wo JI D J J fZII I wm O I O m i I r I N r Ill C I C0 C0 en g 5 0 I I Ill ...

Page 50: ...dicator Exhaust gas temperature indicator Mar ifold pressure indicator ATA 100 CHAPTER 79 ENGINE OIL INSTRUMENTS Oil pressure indicator Oil temperature indicator VFRDay VFRNight FRDay FR Night Remarks and or Exceptions 1 1 1 1 Optional 1 1 1 1 1 1 1 1 1 1 1 1 C f 1 a c t o s w enm m fP m n w C cnn m2 9 c I 9 oaf 0 ...

Page 51: ...more nearly full When operating fuel selector feel for detent position Do not take off 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 SEATING All seats must be in the upright position for ta...

Page 52: ...HT MANUAL INTENTIONAL SPINS PROHIBITED NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED IN THE AIRPLANE EB FLIGHT MANUAL D 7977 thru D 8871 AIR SPEED LIMITATION MAXIMUM SPEED WITH LANDING GEAR EXTENDED NORMAL 175 MPH 152 KTS MAXIMUM DESIGN MANEUVERING SPEED 152 MPH 132 KTS UTILITY CATEGORY AIRPLANE OPERATE IN ACCORDANCE WITH FAA APPROVED AIRPLANE FLIGHT MANUAL INTENTIONAL SPINS PROHIBITED NO AC...

Page 53: ... OF FUEL PRESS Section II Limitations w FUELMIX PUSHRICH ALTERNATE AIR PULL AND RELEASE On Left Side of Control Console Support D 9O69 thru D 9537 GENERATOR CIRCUIT BREAKER PUSt t TO RESET On Topof Front Spar Carry Thru Structure Between Front Seats January 1982 EMERGENCY LANDING GEAR INSTRUCTIONS TO EXTEND ENGAGE HANDLE IN REAR OF FRONT SEAT AND TURN COUNTERCLOCKWISE AS FAR AS POSSIBLE 50 TURNS 2...

Page 54: ... Left Side Panel Near Firewall Air Controls VENT SHUTOFF PULL TO CLOSE D 7977 thru D 9O68 r IN CASE OF ENGINE FIRE B PULL FIREWALL AIR B CONTROL TO CLOSE D 9O69 thru D 9947 On Emergency Crank Access Cover D 9538 thru D 9947 2 24 LANDING GEAR EMERGENCY CRANK PULL OUT LIFT UP January 1982 ...

Page 55: ... FAA Approved Airplane Flight Manual P N 35 590118 31 B Reissued January 1982 or Subse quent D 7977thru D 9947 The addition of a placard to the fuel selectorto warn of the no flow condition that exists between the fuel selector detents Insert this temporary change into the V35 V35A V35B Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Immediately following page 2 24 Section II LI...

Page 56: ...S LocatedOn The FaceOf TheFuel SelectorValve For Those AirplanesIn ComplianceWith S 8 2670 WARNING POSITIONSELECTOR IN DETENTSONLY NO FUELFLOWTO ENGINEBETWEEN DETENTS Approved 2ot2 A C Jackson RaytheonAircraftCompany DOACE 2 P N 35 590118 31BTC1 August 26 1997 ...

Page 57: ...IFFUEL QUANTITY GAGES y INDICATE INYELLOW BAND OR WITH LESS L THAN 13GALLONS INEACH MAIN TANK _J OFFO LH TANK 0 22 GAL 0 RH TANK 22 GAL Optional 74 Gallon Usable Fuel System 11n _ DO NOT TAKE OFF IFFUEL QUANTITY GAGES y INDICATE INYELLOW BAND OR WITH LESS L THAN 13GALLONS INEACH MAIN TANK _J OFF 0 LH TANK 0 37 GAL January 1982 ORHTANK 37 GAL 2 25 ...

Page 58: ...alled 0 WARNING 0 EMERGENCY AIRSPEED STATIC SOURCE ON EMERGENCY SEE PILOTS CHECK LIST 1 OR FLIGHT MANUAL EMERGENCY PROCEDURES FOR AIRSPEED ALTIMETER CALIBRATION ERROR 0 OFF Q NORMAL On Instrument Panel When Anti Collision Light Is Not Installed THIS AIRCRAFT NOT FULLY EQUIPPED FOR NIGHT FLIGHT Under Left Subpanel 2 26 ALT CIRCUIT BREAKER D 9538 thru D 9817 January 1982 ...

Page 59: ...ls on Control Console 0 NOTICE REMOVE WINTER BAFFLES WHEN OAT EXCEEDS 70 F 0 On Oxygen Console WARNING Section II Limitations DO NOT SMOKE WHILE OXYGEN IS IN USE HOSE PLUG MUST BE PULLED OUT TO STOP FLOW OF OXYGEN Around Each Oxygen Outlet January 1982 2 27 ...

Page 60: ...ompliance with BEECHCRAFTService Instructions 1241 EMERGENCY EXIT LIFT LATCH PULL PIN PUSH WINDOW OUT On Openable Windows DO NOT OPEN IN FLIGHT LATCH WINDOW BEFORE TAKE OFF I On Storm Window Used prior to D 9O69 CAS r CAUTIO DO NOT OPEN ABOVE 145 MPH 126 KNOTS i L _J On Hat Shelf HAT SHELF NO HEAVY OBJECTS 2 28 Revised March 1983 ...

Page 61: ...D 9538 thru D 9947 On Inner Side Of Baggage Compartment Door BAGGAGE CARGO OR FAMILY SEATS 0 LOAD IN ACCORDANCE WITH WEIGHT AND BALANCE DATA 0 MAXIMUM STRUCTURAL CAPACITY 270 POUNDS or BAGGAGEAND CARGO COMPARTMENT FLOOR STRUCTURAL CAPACITY 270 POUNDS MAXIMUM CHECK AIRCRAFT FLIGHT MANUAL FOR WEIGHT AND CENTER OF GRAVITY LIMITS WHEN LOADING BAGGAGE CARGO OR FAMILY SEATS January 1982 2 29 ...

Page 62: ... USE SNUG LAP BELT WITH BUCKLE CENTERED IN FRONT OF OCCUPANT WITH SEAT BACK UPRIGHT On Windows Adjacent to Pilot s and Copilot s Seats D 9862 thru D 9947 SHOULDER HARNESS MUST BE WORN AT ALL TIMES WHILE AT PILOT POSITIONS On Windows Adjacent to 3rd 4th 5th 6th Seats D 9862 thru D 9947 2 30 SHOULDER HARNESS MUST BE WORN DURING TAKE OFF AND LANDING WITH SEAT BACK UPRIGHT January 1982 ...

Page 63: ... 9862 thru D 9947 0 TURN RED HANDLE TO UNLOCK SEAT BACK 0 In Full View Of The Pilot Unless baffled main fuel cells are installed in both wings TURNING TYPE TAKEOFFS ANol TAKEOFF IMMEDIATELY FOLLOWING FAST TAXI TURN PROHIBITED AVOID PROLONGED SLIPS 20 SECONDS OR IMORE WITH FUEL TANKS LESSTHAN HALF FULL _j January 1982 2 31 ...

Page 64: ... V35B thru 0 9947 In Full Viewon Inside of Cabin Door and on Inside of Baggage Compartment Door WARNING THISAIRPLANE IS EASILY LOADED BEYOND AFTCGLIMITS WEIGHT ANDCGMUST BEWITHIN LIMITS FOR EACH FLIGHT REFER TO PILOTS OPERATING HANDBOOK 2 32 March 1987 ...

Page 65: ... Start Procedure 3 5 Engine Fire 3 6 In Flight 3 6 On The Ground 3 6 Maximum Glide Configuration 3 6 Emergency Descent 3 7 Landing Emergencies 3 7 Landing Without Power 3 7 Landing Gear Retracted With Power 3 7 Systems Emergencies 3 8 Propeller Overspeed 3 8 Alternator Out Procedure 3 8 Alternator Overvoltage 3 8 Engine Instrument Malfunction 3 9 Unscheduled Electric Elevator Trim 3 9 Landing Gear...

Page 66: ...V35 V35A V35B thru D 9947 TABLE OF CONTENTS Continued SUBJECT PAGE Induction System Blockage 3 11 Emergency Static Air Source System 3 12 Emergency Exits 3 13 Unlatched Door in Flight 3 13 Spins 3 14 Emergency Speed Reduction 3 14 3 2 Revised March 1983 ...

Page 67: ...ty of control 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 familiarization Other s...

Page 68: ... following 1 Fuel Selector Valve SELECT OTHER 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 5 Alternate Air T handle PULL AND RELEASE NOTE The most probable cause of engine failure would be loss of fuel flow improper functioning of the ignition system or blockage of the induction system If No Restart 1 Select ...

Page 69: ...ired c Auxiliary Fuel Pump OFF if performance does not improve in a few moments 2 Fuel Quantity Indicator CHECK for fuel supply in tank being used 3 Alternate Air T handle PULL AND RELEASE ff tank being used is empty Fuel Tank Selector Valve SELECTOTHERFUELTANK feel for detent and check visually AIR START PROCEDURE a Fuel Selector Valve SELECT TANK MORE NEARLY FULL check to feel detent b Throttle ...

Page 70: ...O CLOSE 2 Mixture IDLE CUT OFF 3 Fuel Selector Valve OFF 4 Battery Alternator and Magneto Start 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 Alternator and Magneto Start Switches OFF 4 Extinguish with Fire Extinguisher MAXIMUM GLIDE CONFIGURATION 1 Landing ...

Page 71: ...eed 83 kts 96 mph 2 Fuel Selector Valve OFF 3 Mixture IDLE CUT OFF 4 Magneto Start Switch OFF 5 Flaps AS REQUIRED 6 Landing Gear DOWN OR UP DEPENDING ON TERRAIN 7 Battery and Alternator Switches OFF LANDING GEAR RETRACTED WITH POWER If 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 ...

Page 72: ...ternator will place the entire electrical operation of the airplane on the battery Alternator failure will be indicated by the illumination of the ALT OUT warning light located on the instrument panel below the flight instruments When an alternator failure occurs in flight all nonessential electrical load should be dis continued to conserve the battery life ALTERNATOROVERVOLTAGE If an alternator o...

Page 73: ...en mixture appropriately CAUTION At high altitudes and low power settings full rich mixtures may result in poor engine opera tion Adjust the mixture for smooth engine op eration upon power reduction UNSCHEDULED ELECTRIC ELEVATOR TRIM 1 Airplane Attitude MAINTAIN using elevator control 2 Elevator Trim Thumb Switch On Control Wheel MOVE IN DIRECTION OPPOSITE UNSCHEDULED PITCH TRIM to open circuit br...

Page 74: ... landing gear only DO NOTATTEMPT TO RETRACTTHE GEAR MANUALLY 5 If electrical system is operative check landing gear position lights and warning horn check LOG GEAR INDICATORand LOGGEARWARNING circuit breakers engaged 6 Check mechanical landing gear indicator DOWN V35 V35A 7 Handcrank DISENGAGE Always keep it stowed when not in use 3 10 WARNING Do not operate the landing gear electrically with the ...

Page 75: ...nduction air door spring loaded to the closed position is located downstream from the induction air filter If the induction air filter becomes blocked e g ice etc the differential air pressure normally opens the alter nate induction air door to provide induction air from the bottom of the engine compartment If the alternate induction air door becomes stuck in the closed position it can be opened b...

Page 76: ...h during a climb or descent Verification of suspected obstruction is possible by switching to the emergency system and noting a sudden sustained change in rate of 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 the Emergency Static Air System is desired for use...

Page 77: ... On 0 9862 and after for access past the 3rd and lor 4th seats rotate the red handle lo cated on the lower inboard side of the seat back and fold the seat back over UNLATCHED DOOR IN FLIGHT If the cabin door is not locked it may come unlatched in flight This may occur during or just after take off The door will trail in a position approximately 3 inches open butthe flight characteristics of the ai...

Page 78: ...es 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 lowering of the landing gear will reduce the tendency for excessive speed build up This procedure would also be appropriate for a non instrument rated pilot who unavoidably encounters instrument condi tions or in other emer...

Page 79: ...uxiliary Power Unit 4 8 Starting 4 8 After Starting and Taxi 4 10 Before Takeoff 4 10 Takeoff 4 12 Climb 4 12 Cruise 4 12 Leaning Using the Exhaust Gas Temperature Indicator EGT 4 13 Descent 4 14 Before Landing 4 14 Balked Landing 4 15 After Landing 4 15 Shutdown 4 15 Environmental Systems 4 16 Oxygen System 4 16 Preflight 4 16 Oxygen Duration 4 17 Oxygen Duration Chart 4 17 In Flight 4 18 After U...

Page 80: ...cedures BEECHCRAFT Bonanza V35 V36A V35B thru D 9947 TABLE OF CONTENTS Continued SUBJECT PAGE Heating and Ventilation 4 18 Cold Weather Operation 4 19 Icing Conditions 4 20 Engine Break in Information 4 20 4 2 January 1982 ...

Page 81: ...7 kts 89 mph I Cruise Climb 107 kts 123 mph Maximum Turbulent Air Penetration 134 kts 154 mph Balked Landing 70 kts 81 mph Landing Approach 70 kts 81 mph Maximum Demonstrated Crosswind 17 kts 20mph PREFLIGHT INSPECTION Emergency Locator 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 a Baggage Compa...

Page 82: ...CRAFT Bonanza V35 V35A V35Bthru D 9947 8 3 EMPENNAGE a Control Surfaces CHECK b Tie Down REMOVE c Position Light CHECK d Cabin Air Intake CHECK 4 LEFT FUSELAGE a Static Pressure Button UNOBSTRUCTED b All Antennas CHECK 4 4 January 1982 ...

Page 83: ...and Chocks REMOVE 7 LEFT LANDING GEAR a Wheel Well Door Tire and Strut CHECK b Fuel Vent CHECK c Fuel Sump DRAIN d Fuel Selector Valve Sump DRAIN Cover SECURE 8 NOSE SECTION a Left Cowl Flap CHECK b Engine Oil CHECK see Servicing Section 8 Cap and Dipstick SECURE c Left Cowl SECURE d Propeller CHECK General Condition Nicks etc e Wheel Well Doors Tire and Strut CHECK f Induction Air Intake CLEAR g ...

Page 84: ...ECURE 11 RIGHT WING TRAILING EDGE a Position Light CHECK b Wing Tip CHECK c Aileron CHECK d Flap CHECK CAUTION NEVER TAXI IF ANY STRUT IS FLAT BEFORE STARTING 1 Seats POSITIONAND LOCK Seat Backs UPRIGHT 2 Seat Belts and Shoulder Harnesses FASTEN 3 Parking Brake SET 4 All Avionics OFF 5 Circuit Breakers IN 6 Landing Gear Handle DOWN Safety System CHECK If installed 7 Flaps UP 8 Cowl Flaps OPEN 9 Li...

Page 85: ...ane has a negative ground system Exercise care to avoid reversed polarity Be sure to connect the positive lead of the external power unit to the positive terminal of the airplane s external power receptc Cle and the negative lead to the negative terminal of the external power receptacle A positive voltage must also be applied to the small guide pin 2 To prevent arcing make certain no power is bein...

Page 86: ...OFF after engine has been started 8 Auxiliary Power Unit DISCONNECT 9 Alternator Switch ON STARTING CAUTION Vernier type engine controls should not be rotated clockwise after being advanced to the full forward position 1 Mixture FULL RICH 2 Propeller HIGH RPM 3 Throttle FULL OPEN NOTE If the engine is hot and the ambient tempera ture is 90 F or above place mixture control in IDLE CUT OFF switch au...

Page 87: ...ires reduce throttle to IDLE and advance the mixture control to FULL RICH NOTE During hot starts the Auxiliary Fuel Pump is turned on momentarily after starting to purge system then turned off 8 Throttle 1000 to 1200 RPM 9 Oil Pressure CHECK 10 External Power if used DISCONNECT 11 Alternator Switch ON CHECK FOR CHARGING 12 All Engine Indicators CHECK CAUTION The ammeter indication should be less t...

Page 88: ...der Harnesses CHECK NOTE All reclining seats must be in the upright posi tion during takeoff 3 Avionics CHECK 4 Engine Instruments CHECK 5 Flight Instruments CHECK AND SET 4 10 NOTE To ensure adequate gyro pressure when oper ating two air driven gyros during ground operation and or holding prior to takeoff main tain an engine speed of 700 800 rpm in order to hold a value in the green arc on the in...

Page 89: ...iance between individual magnetos should not exceed 50 rpm maximum 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 Flight Controls CHECK PROPER DIRECTION FULL I TRAVEL AND FREEDOM OF MOVEMENT 15 Mixture FULL RICH or as required by field elevation 16 Brakes RE...

Page 90: ... Gear RETRACT when positive rate of climb is established and insufficient runway remains for landing 4 Airspeed ESTABLISH DESIREDCLIMB SPEED when clear of obstacles CLIMB Maximum Continuous Full Throttle 2700 rpm Cruise Climb 25 in Hg or full throttle 2500 rpm 1 Engine Temperatures MONITOR 2 Power SET AS DESIRED 3 Mixture SET FUEL FLOW CRUISE See Cruise Charts in PERFORMANCESection 1 Cowl Flaps CL...

Page 91: ... Lean the mixture and note the point on the indicator that the temperature peaks and starts to fall a CRUISE LEAN MIXTURE Increases the mixture until the EGTshows a drop of 25 F below peak on the rich side of peak b BEST POWER MIXTURE Increase the mixture until the EGT shows a drop of 100 F below peak on the rich side of peak CAUTION Do not continue to lean mixture beyond that necessary to establi...

Page 92: ...CURE NOTE All reclining seats must be in the upright posi tion during landing 2 Fuel Selector Valve SELECT TANK MORE NEARLY FULL 3 Cowl Flaps AS REQUIRED 4 Mixture FULL RICH or as required by field elevation 5 Landing Gear DOWN and CHECK Observe maximum extension speed 6 Landing and Taxi Lights AS REQUIRED 7 Flaps DOWN Observe maximum extension speed 8 Airspeed ESTABLISH LANDING APPROACH SPEED 9 P...

Page 93: ...AFTER LANDING 1 Landing and Taxi Lights AS REQUIRED 2 Flaps UP 3 Trim Tab SET TO 0 4 Cowl Flaps OPEN SHUTDOWN 1 Brakes SET 2 Electrical and Radio Equipment OFF 3 Propeller HIGH RPM 4 Throttle CLOSE 5 Mixture IDLE CUT OFF 6 Magneto Start Switch OFF after engine stops 7 Battery and Alternator Switches OFF 8 Control Lock INSTALL if conditions warrant 9 Install wheel chocks and release brakes if the a...

Page 94: ...ation in minutes by percent of full bottle EXAMPLE People 5 Gage Pressure 1500 psig Oxygen Available from chart 80 Cylinder Capacity full 49 cu ft Altitude planned flight 15 000 ft Full Bottle Duration from chart 149 min Duration 80 full 119 min 4 16 OXYGEN AVAILABLE WITH PARTIALLY FULL BOTILE c 2000 CJ CL w 1500 cc i H _ HH4 1 i f 4 i ffi1000 t r h J JJ u 4 I HI I I 11 1 cc CL w 500 C C 0 11 0 I ...

Page 95: ...UTION Since 90 of the system efficiency is deter mined by the fit of the oxygen mask make cer tain the masks fit properly and are in good condition OXYGEN DURATION CHART Full Bottle Duration in minutes at the following altitudes Bottle Persona 12 600 16 000 20 000 Capacity Using FT FT FT 1 1014 746 507 2 507 373 253 49 cu ft 3 338 248 169 4 253 186 126 5 202 149 101 6 169 124 84 WARNING NO SMOKING...

Page 96: ...ECK INDICATOR FOR FLOW AFTER USING 1 Discontinue use by unplugging mask from outlet NOTE Closing the control valve while in flight is not necessary due to automatic sealing of the out let when the mask is unplugged However it is desirable to shut off supply when not in use 2 Oxygen Control Valve CLOSED may be accom plished during shut down HEATING AND VENTILATION Refer to the SYSTEMS DESCRIPTION S...

Page 97: ... that even slight accumulations will disturb or completely destroy the de signecf ae rodynamic properties of the airfoils The normal preflight procedures should then be com pleted with particular attention given to check of flight controls for complete freedom of movement ENGINE Use engine oil in accordance with Consumable Materials in the HANDLING SERVICING AND MAINTENANCE Sec tion WARNING Ascert...

Page 98: ... flight If there is no oil pressure within the first 30 seconds of running or if oil pressure drops after a few minutes of ground operation shut down and check for broken oil lines oil cooler leaks or the possibility of congealed oil NOTE It is advisable to use external power for start ing in cold weather During warm up monitor engine temperatures closely since it is quite possible to exceed the c...

Page 99: ...n Normal System 5 12 Altimeter Correction Emergency System 5 13 Fahrenheit to Celsius Temperature Conversion 5 14 ISA Conversion 5 15 Stall Speeds Power Idle 5 16 Wind Components 5 17 Take Off Distance 5 18 Climb 5 19 Time Fuel and Distance to Climb 5 20 Cruise Power Settings 75 MCP Or Full Throttle 5 21 65 MCP Or Full Throttle 5 22 55 MCP Or Full Throttle 5 23 45 MCP Or Full Throttle 5 24 Cruise ...

Page 100: ...BEECHCRAFT Bonanza V35 V35A V35B thru D 9947 TABLE OF CONTENTS Continued SUBJECT PAGE Range Profile 44 Gallons 5 29 Endurance Profile 74 Gallons 5 30 Endurance Profile 44 Gallons 5 31 Landing Distance 5 32 5 2 January 1982 ...

Page 101: ...ed flight are 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 V81 AMA For VFR Cruise at 11 500 feet WIND 11500 ROUTE MAGNETIC DIST FEET SEGMENT COURSE NM DIR KTS DEN COS 161 55 010 30 COS PUB 153 ...

Page 102: ...d 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 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 5 4 29 92 29 56 36 in Hg The pressure altitude at AMA is 360 feet above the field elevation 3605 360 3965 ft NOTE For flight plannin...

Page 103: ...ow should be read from the cruise power setting table for 75 percent 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 ...

Page 104: ...FLOW TAS PRESS FLOW TAS FEET IN HG GPH KNOTS IN HG GPH KNOTS 11000 19 2 13 1 167 19 2 12 6 167 12000 18 3 12 6 165 18 3 12 2 165 Interpolate for 11 500 feet and the temperature for the appropriate route segment Results of the interpolations are MAN FUEL ROUTE PRESS FLOW TAS SEGMENT IN HG GPH KNOTS DEN PUB 18 8 12 8 166 PUB TBE 18 8 12 7 166 TBE DHT 18 8 12 5 166 DHT AMA 18 8 12 5 166 NOTE The abov...

Page 105: ...STANCE SPEED ALTITUDE CRUISE SEGMENT NM KNOTS HRS MIN GAL DEN COS 28 195 09 1 9 COS PUB 40 192 13 2 8 PUB TBE 74 153 29 6 1 TBE DHT 87 154 34 7 1 DHT AMA 65 156 25 5 2 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 2 0 0 Climb 0 13 3 6 27 Cruise 1 50 23 1 294 Total 2 03 ...

Page 106: ...9 6 gallons per hour Reserve fuel 45 min 9 6 GPH 7 2 gallons Total Fuel 28 7 7 2 35 9 gallons The estimated landing weight is determined by subtracting the fuel required for the trip from the ramp weight Assumed ramp weight 3412 lbs Estimated fuel from DEN to AMA 28 7 gal 6 lbs gal 172 lbs Estimated landing weight 3412 172 3240 lbs Examples have been provided on the performance graphs The above co...

Page 107: ...here to begin following guide lines Always project to the reference line first then follow the guide lines to the next known item 3 Indicated 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 perfo...

Page 108: ...110 l 110 OI m 120 u 120 m n 100 n 100 110 i 110 RD m 11c u o 100 90 100 90 w c 90 80 90 80 JI 0 80 70 80 70 m a Ill I 70 70 r C 60 60 2 I Ill 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 60 70 80 90 100 110 120 130 140 IAS INDICATED AIRSPEED KNOTS IAS t INDICATED AIRSPEED KNOTS cm I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I 0 I I I I I I I I I I I I I I I I I I co I...

Page 109: ...ii i e Ii SJ ON f QJ WSIHV QllVYtliY If 1 1 r r 1111 1 rn 1 1111111 111 I lirlillfl i fJ If II I j 1 I 1 1 1 Ir I I I 1 I I 1 1 I l a ss HdW oOJ3 Sl IIY03 1YY811V SY 0 z i I t t l 0 l ii ii e Ii SLON l oOJJdSYIVauvwa11v SV January 1982 I 0 N l Ii 1 si o _ o Slil a 11 51 a l l Ii 0 ci 11 o _ I i 0 ii l i ii e ii iii e 5 11 ...

Page 110: ...o lo 1 0 1 lo lo 1 0 11 o 0 1 1 1 1 ld2 i 2 0 1 2 0 1 2 0 IAS INDICATED AIRSPEED MPH 0 i i ii 10 i 20 zO 05 30 Ela40 8 60 a a Ii 2 80 IAS FLAPS INDICATEDPRESSURE 70 KNOTS 80 MPH DOWN ALTITUDE 4500 FT ALTIMETERCORRECTION 12FT ACTUALPRESSURE Al TITUDE 4500 12 4488 FT FLAPSDOWN Ii 60 80 80 80 1001WU01W IAS iNOICATEOAIRSPEED v KNOTS 1 I I I I I I I I I I I I I I 60 70 80 80 100110120130140 160 160 IAS...

Page 111: ...IIr I111111 I11 I I I1111111 I i t I I I I 1 I I I I I I 1 I I I i I I I 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 IAS INUICATEOAIRSPEED MPH EXAMPLE lAS 70 KTS 81 MPH OPEN STORMWINDOW INDICATEDPRESSUREALTITUDE 5000FT Al TITUDECOR RECT Oflt ACTUAL PRESSURE ALTITUDE 33 FT 5000 33 4967 FT w C tt t zo 50 50 2 rO rz o 100 _ r l 150 200 60 70 80 90 100 110 120 130 IAS INDICATED AI...

Page 112: ...SectionV Performance 5 14 BEECHCRAFT Bonanza V35 V35A V35B thru D 9947 ffl l09 0 1S i 2 l 2 51 0 lil Iii 5 0 0 i IiiI lil I iI 2 I 2 I 0 lil i 51 i I I I 1 3311 30 January 1982 ...

Page 113: ...ECHCRAFT Bonanza V35 V35A V358 thru D 9947 C1 z ii 0 _ enc ai 111 w2 z8 o u s C iit January 1982 J 33 30nJ IJ 1 cf 31 nSS311d SectionV Performance 0 g g u 00 I w a o a w OA lw I g I 0 I 0 I 0 7 0 0 I 5 15 ...

Page 114: ...ic 1 Mr gA Jfseiw h i Jip 3400 3200 3000 2800 2600 2400 WEIGHT POUNDS EXAMPLE WEIGHT FLAPS ANGLEOF BANK STALLSPEEOS 10 20 30 40 3300 LBS DOWN 300 CAS 56 KTS 65 MPH IAS 55 KTS 63 MPH 110 90 100 80 E t z 70lfil 60 60 50 Ffl 50 40 w 50 60 ANGLE OF BANK DEGREES en GI GI i n 0 ct g n GI Cot 1 Cot oim J m f2D m o Cot c oiO m z r Tl 2 I cm 0 co coII s i ...

Page 115: ...7 kts EXAMPLE WINO SPEED ANGLE BETWEEN WINO DIRECTION ANO FLIGHT PATH HEADWIND COMPONENT CROSSWINDCOMPONENT FLIGHT 1 z 40 30 10 8 0 z i 0 w c 10 20 PATH t I rf 1 1 1rf 17D 1SfP m 1BD ttt 160 f I I 0 10 140 13D I I 20 CROSSWINDCOMPONENTS January 1982 I 30 KNOTS 7u 20KTS 5fP 13 KTS 15KTS 9r 110 40 5 17 ...

Page 116: ...STANCE i 1 _ c yrF SPEED EIGHT LBS 3400 3200 _ 2400 71 89 N M W M M 81 81 W 77 3400 3200 _ WEIGHT POUNOSI 2600 EXAMPLE OAT PRESSUREALTITUDE TAKE OFFWEIGHT HEADWINOCOMPONENT 15 C 159 F 5650FT 3400 LBS 9 5 KTS GROUNDROLL 1600FT TOTAL DISTANCE OVER A 50 FT OBSTACLE 3000 FT TAKE OFFSPEEDAT LIFT Off 71 KTS 82 MPH w z l 1i1 J w f k 4o 4 AT50FT 77KTS 89MPH 1 1 _ ifl t l if ff J ill l ol 6000 l 5000 4000 ...

Page 117: ... 1 0 I 1I r1 o w ro w OUTSIOEAIR TEMPERATURF 0c E f tiP i ll F f Hl f fBtH I 100 80 I 60 I 40 20 0 0 40 60 80 fOQ 120 OUTSIDEAIR TEMPERATURE F r 4 1 m i Ii 3 00 3200 EXAMPLE OAT PRESSURE ALTITUD WEIGHT RATE OF CLIMB CLIMBGRADIENT CUMBSPEEO 1 __ 3QOO _1 00_ WEIGHT POUNDS 2600 s0c 73 F 11 600FT 3380 LBS 470 FT MIN 3 8 96KTSl110MPHI 1 00 1300 1200 1100 1000 900 7001 600 600 400 300 200 100 o 2400 13 ...

Page 118: ...TSIDE AIR TEMPERATURE Of OAT AT TAKE OFF 15oc OAT AT CRUISE s0c AIRPORTPRESSUREAl TITUOE 6650 FT CRUISEPRESSUREALTITUDE 11 500 FT INITIALCLIMBWEIGHT 3400 LBS TIME TO CLIMB 121 8 13 MIN FUEL TO CLIMB 16 26 2 65 3 6 GALS DISTANCET0CLIMB 42 16 21NM IJ l 1 Al f c 14jj ITT i Fl i o 10 20 ro CLIMB MINUTE f8 t Ftj3 1 83f1 11 fll tI111 111 11 Ij f l 0 1 2 3 4 5 6 1 8 9 10 11 12 13 FUEL TO CLIMB GALLONS jI...

Page 119: ... 162 96 36 2000 20 7 2500 23 4 91 4 152 162 163 56 14 2500 24 1 91 4 15 2 166 161 93 34 3000 17 8 2500 23 1 91 4 15 2 164 163 53 12 2500 23 8 91 4 15 2 167 160 89 32 4000 13 10 2500 22 8 91 4 15 2 165 162 49 10 2500 23 5 91 4 15 2 169 159 86 30 JI N NOTES 1 Full throttle manifold prwsure settings are approximate 2 Shaded arN repn eents operatkxl with full ltwottle ISA WF C ENGINE MAN SPEED PRESS F...

Page 120: ...300 23 6 80 0 13 3 155 153 96 35 20 7 2300 22 8 80 0 13 3 153 154 56 13 2300 23 4 80 0 13 3 156 152 92 33 16 9 2300 22 5 80 0 13 3 154 153 52 11 2300 23 1 80 0 13 3 157 151 89 31 13 11 2300 22 3 80 0 13 3 155 152 49 9 2300 22 9 60 0 13 3 159 150 85 29 9 13 2300 22 0 80 0 13 3 157 151 45 7 2300 22 6 80 0 13 3 160 148 82 28 ISA 38 F 20 C 1 SPEED FUE FLOW NHG GPN 2300 24 5 80 0 13 3 2300 24 2 80 0 13...

Page 121: ... 142 52 11 2100 22 9 88 9 11 5 146 140 99 31 4000 12 11 2100 22 1 68 8 11 5 144 141 46 9 2100 22 6 68 9 11 5 147 138 94 29 5000 9 13 2100 21 9 68 8 11 5 145 140 45 7 2100 22 4 68 9 11 5 149 137 81 27 6000 5 15 2100 21 6 68 9 11 5 146 139 41 5 2100 22 1 68 9 11 5 148 136 77 25 JI N w NOTES 1 Full throttle manttold pressure settings are approximate 2 Shaded area n presents operation with full thl Ol...

Page 122: ... 9 8 134 124 80 27 2100 19 7 57 6 9 6 136 122 6000 5 15 2100 18 5 57 6 9 8 133 126 41 5 2100 19 0 57 6 9 6 135 123 77 25 2100 19 4 57 6 9 6 136 120 w 7000 1 17 2100 18 2 57 6 9 6 134 125 37 3 2100 18 7 57 8 9 6 135 122 73 23 2100 19 1 57 6 9 6 137 119 GI 1111 6000 3 19 2100 17 9 57 6 9 6 134 124 34 1 2100 18 4 57 6 9 6 136 121 70 21 2100 18 6 57 6 9 6 137 118 m 9000 6 21 2100 17 6 57 6 9 6 135 123...

Page 123: ...RAGE CRUISEWEIGHT 3200 LBS PRESSURE ALTITUDE 11 500FT TEMPERATURE STANDARD DAY ISA POWERSETIING FULL THAOTILE 2500 RPM TRUE AIRSPEED 166 KTS 16 000 15 000 14 000 13 000 12 000 11 000 10 000 9000 w 0 8000 7000 w ffi 6000 5000 4000 3000 2000 1000 SL 120 130 140 150 160 170 180 TRUE AIRSPEED KNOTS January 1982 5 25 ...

Page 124: ...Ill CD 20 X II 1700 1800 1900 2000 MANIFOLD PRESSURE VS RPM EXAMPLE ENGINESPEED MANIFOLD PRESSURE WITHIN RECOMMENDED LIMITS 1100 2200 2300 ENGINE SPEED v RPM 2450 RPM 24 5 IN HG 2400 2500 2600 2700 2800 a I CD CD i n 0 ct g n CD w s JI Ill l m RD m C w C JI C Ill ti l r Tl 2 t cm 0 CD s CDI I Jli ...

Page 125: ...ORSEPOWER 45 EXAMPLE RSEPOWER 213 75 75 MCP CONDITION LEVEL FLIGHT CRUISE FUEL FLOW 15 25 GAL HR FUELFLOW CONDITION 14 6 GAL HR LEVEL FLIGHT CRUISE BRAKE HORSEPOWER 204 1 t J 1 H i t H I 75 f a t S ff _ t t ri OFF JfF AND CLIMB_ _ r t f CRUISE_ i C 13 i 1 12 11 10 8 120 140 160 January 1982 180 200 220 240 280 280 BRAKE HORSEPOWER 5 27 ...

Page 126: ... FULL THAOTTLE 2500 RPM BOO NM 20 000 NOTE AANGE INCLUDES START TA_XI AND CLl B WIT_H 46 MINUTES RESERVE FUEL AT 45 MCP t i 15 000 w 0 I 10 000 w a fil a 6000 SL 600 1 t 1 i tr m ttJ 1 I t If a t3 i9 fl _ i y I 650 700 4 l 1 H 167 l j 146 138 CRUISE TRUE A RSPEED o KTS 1 0 O rt l w 170 163 i 136 159 i a 147 133 I H H a j 1 1 i I 760 BOO B60 900 950 1000 1050 RANGE v NAUTICAL MILES ZERO WIND a 0 CD...

Page 127: ...NOTE RANGEINCLUDESSTART TAXI ANDCLIMB WITH45 MINUTESRESERVEFUELAT45 MCP 16 000 w C E 10 000 t w 0 I f 6000 SL 300 170 163 160 i i Q e e ct w u 169jlli 169 147 i fl Ir Ir I 350 400 450 FULLTHROTTLE 2500 RPM FULL THROTTLE 2300 RPM FULCTH fionLe 2100 RPM CRUISETRUEAIRSPEED v KNOTS 136 u 133 500 550 600 RANGE NAUTICAL MILES ZEROWINDJ 11 500FT FULLTHROTTLE 2600RPM 413NM Ii I 650 700 m Wm aim z WC CII 0...

Page 128: ...ESSUREALTITUDE POWERSETTING ENDURANCE 11 600 FT FULL THROTTLE 2600 RPM 4 9 HRS 4 HRS64 MINI 20 000 NQT _ fif EJ l E S STAR f T_Ax _A N_D C L Y T H s_r l f fES RESERVEFUEi t w 0 16 000 E i 10 w 0 m f 4 0 170 163 4 5 s o 16 11 1 S _ N _ 45tttttt 138 136 11 4 tie 147 1 I 6 5 s o a s ENDURANCE HOURS R S E T R_U 1 I 1 f I KNOTS 133 11 I 1 0 1 5 8 0 8 5 o rn CD CD in Oct g cS w CJI0 m flllffl w c CJI 0 ...

Page 129: ... INCLUDES START TAXI AND CLIMB WITH 45 MINUTES RESERVE FUEL AT 45 MCP 15 000 w 0 I 10 000 J w a 1Z w 5000 SL 1 5 i z E a l f 2 0 165 170 163 169 159 t t I 2 5 FULL THROTTLE 2500 RPM FULL THROTTLE 2300 RPM FULL THROTTLE 2100 RPM 157 145 138 CRUISE TRUE AIRSPEED KNOTS 150 136 L 147 133 t o ll I 3 0 3 5 4 0 4 5 ENDURANCE v HOURS 11 500 FT FULL THROTTLE 2500 RPM 2 57 HRS 2 HRS 34 MIN I 5 0 5 5 6 0 m w...

Page 130: ...Q OUTSIDE AIR TEMPERATURE Of N LANDING DISTANCE WEIGHT L8S SPEEDAT 50 FT 3400 3200 3000 2800 2400 320 KTS 70 63 Bl 3000 2800 WEIGHT POUNDS MPH Bl 7B 16 13 71 2600 EXAMPLE OAT 25 c 177 F PRESSURE ALTITUDE 3965ft WEIGHT 3242 L8S HEADWINDCOMPONENT 9 KTS GROUND ROll 763 FT TOTALOVER50FTOBSTACLE 1324FT APPROACH SPEED 69 KTS 180 MPH M i lffi Ii Ii k 2400 0 10 20 3Q WIND COMPONENT KNOTS 2500 1500 m i 100...

Page 131: ... Record 6 7 Loading Instructions 6 9 Seating Baggage and Equipment Arrangements 6 10 Moment Limits vs Weight Graph 6 11 Computing Procedure 6 12 Sample Weight and Balance Loading Form 6 13 Weight and Balance Loading Form 6 14 Sample Loadings 6 14A Useful Load Weights and Moments 6 15 Occupants 6 15 Baggage 6 17 Cargo 6 17 Usable Fuel 6 18 Oil 6 18 Equipment List Provided for each airplane March 19...

Page 132: ...Section VI BEECHCRAFT Bonanza Wt and Ba quip List V35 V35A V35B thru D 9947 INTENTIONALLY LEFT BLANK 6 2 January 1982 ...

Page 133: ...a drained system is 34 5 pounds at Fuselage Station 79 1 3 Engine oil must be at the full level or completely drained Total engine oil when full is 26 pounds at Fuselage Station 24 5 Includes 3 pounds undrain able oil 4 To determine airplane configuration at time of weighing installed equipment is checked against the airplane equipment list or superseding forms All installed equipment must be in i...

Page 134: ...els and Fuselage Station 12 7 for the nose wheel 7 Jack point weighings are accomplished by placing scales at the jack points specified in step 1 above Since the center of gravity of the airplane is forward of Fuselage Station 83 1 the tail reaction of the airplane will be in an up direction This can be measured on regular scales by placing ballast of approximately 200 pounds on the scales and att...

Page 135: ..._____ _ COMPRESSED 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 oetow provided for additions and subtractions to as weighed condition EMPTY WEIGHT ENGINE OIL 26 638 UNUSABLE FUEL 36 79 2844 BASIC EMPTY WEIGHT m wm enm n c Wn en z wm eno m s I 2 GI C I co co a f en 3 a s C s ...

Page 136: ...of doing this it is suggested that a running tally of equipment changes and their effect on empty weight and e g is a suitable means for meeting both requirements The current equipment list and empty weight and e 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 If the...

Page 137: ...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 01 m n c Wn 01 u J J I Wm 010 m i I r I 2 GI 0 co co I a m I en 0 Ill C ir s r I a S ...

Page 138: ...IGHT 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 fl CD DI n g m DI Cl C i5 r i w w cnm l m QI m n w C cnO m u 2 1 cm I Q co CO DI GI ...

Page 139: ...e aft seats and compartments It is the responsibility of the airplane operator to ensure that the airplane is properly loaded At the time of delivery Beech Aircraft Corporation provides the necessary weight and balance data to compute individual loadings All subse quent changes in airplane weight and balance are the re sponsibility of the airplane owner and or operator The basic empty weight and m...

Page 140: ...1 F S PILOT F PASS FWD POS AFT POS QQ Q 3RD 4TH SEAT PASS FWD POS 121 AFT POS 135 5TH 6TH SEAT PASS 154 Q Q QQ IT s 150 s 108 s 145 SEATING BAGGAGE AND EQUIPMENT ARRANGEMENTS PILOT F PASS F S FWD POS 85 AFT POS 89 3RD 4TH SEAT PASS FWD POS 121 AFT POS 127 5TH 6TH SEAT PASS 154 6 10 I D 9815 thru D 9947 1 1 IT s 150 l s 108 s 145 March 1987 ...

Page 141: ...ING EQUIPMENT AND CARGO WITH 3rd and 4th SEATS REMOVED MAXIMUM WEIGHT 270 POUNDS AFT OF REAR V SPAR INCLUDING EQUIPMENT AND CARGO WITH 3rd 4th 5th and 6th SEATS REMOVED NOTE The floor structure load limit is 100poundsper 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 must be secured with an a...

Page 142: ...Section VI BEECHCRAFT Bonanza Wt and Ba quip List V35 V35A V35B thru D 9947 INTENTIONALLY LEFT BLANK 6 10B March 1987 ...

Page 143: ...ENT LIMITS VS WEIGHT CENTER OF GRAVITY INCHESAFT OF DATUM ENVELOPE BASEDON THE FOLLOWINGWEIGHT AND CENTER OF GRAVITY LIMIT DATA LANDING GEAR DOWN WEIGHT CONDITION FORWARDC G LIMIT 3400 LB MAX TO LOG 3000 LB 82 1 78 0 77 0 AFT C G LIMIT 84 4 85 7 2900 LB OR LESS 85 7 January 1982 6 11 ...

Page 144: ...ed 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 to arrive at the SUB TOTAL Take off Condition 6 Subtract the weight and moment of the fuel in the incremental sequence in which it is to be used from the take off weight and moment The Zero Fuel Condi tion the Take Off Condition and th...

Page 145: ...GHT MOM 100 1 BASIC EMPTY CONDITION 2167 1700 2 FRONTSEAT OCCUPANTS 340 288 3 3rd and 4th SEAT OCCUPANTS 340 412 4 5th and 6th SEAT OCCUPANTS 5 BAGGAGE r 60 90 6 CARGO 7 SUB TOTAL ZERO FUEL CONDITION 2907 2490 8 FUEL LOADING 74 GALI 444 333 9 SUB TOTAL RAMP CONDITION 3351 2823 10 LESS FUEL FOR START TAXI AND TAKE OFF 12 9 11 SUB TOTAL TAKE OFF CONDITION 3339 2814 12 LESS FUEL TO DESTINATION 60 GAL...

Page 146: ...PTY CONDITION 2 FRONT SEAT OCCUPANTS 3 3rd and 4th SEAT OCCUPANTS 4 5th and 6th SEAT OCCUPANTS 5 BAGGAGE 6 CARGO 7 SUB TOTAL ZERO FUEL CONDITION 8 FUEL LOADING 9 SUB TOTAL RAMP CONDITION 10 LESS FUEL FOR START TAXI AND TAKE OFF 11 SUB TOTAL TAKE OFF CONDITION 12 LESS FUEL TO DESTINATION 13 LANDING CONDITION Fuel for start taxi and take off is normally 12 lbs at an average mom 100 of 9 6 14 January...

Page 147: ...ADINGS The following sample loadings show some of the problems associated with loading the aft seats and compartments Similar loadings should be made for your airplane Follow the loading instructions in the Pilot s Operating Handbook plus those on the sample loading form March 1987 6 14A ...

Page 148: ...able fore and aft use the position in which that seat is located during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely using fuel during flight will move the airplane center of gravity aft Flight safety requires that during flight the airplane weight...

Page 149: ...H Weight and Balance Section tor the latest occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate tor the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely using fuel during flight will move the airp...

Page 150: ...n your airplane Consult the POH Weight and Balance Section for the latest occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely using fuel du...

Page 151: ... C G MOM 100 for the occupants as they are posi tioned in your airplane Consult the POH Weight and Balance Section for the latest occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the...

Page 152: ...si tioned in your airplane Consult the POH Weight and Balance Section for the latest occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely us...

Page 153: ... fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely using fuel during flight will move the airplane center of gravity aft Flight safety requires that during flight the airplane weight an...

Page 154: ...occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely using fuel during flight will move the airplane center of gravity aft Flight safety req...

Page 155: ...d in your airplane Consult the POH Weight and Balance Section for the latest occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely using fuel...

Page 156: ...cupants as they are posi tioned in your airplane Consult the POH Weight and Balance Section for the latest occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G...

Page 157: ...i tioned in your airplane Consult the POH Weight and Balance Section for the latest occupant positions If the seats are ad justable fore and aft use the position in which that seat is locat ed during flight The Basic Empty Weight Data shall be current and accurate for the airplane as equipped NOTE The addition of fuel to the above loading will move the cen ter of gravity C G forward Conversely usi...

Page 158: ...Section VI Wt and Bal Equip List BEECHCRAFT Bonanza V35 V35A V35B thru D 9947 INTENTIONALLY LEFT BLANK 6 14L March 1987 ...

Page 159: ...62 30 46 130 110 116 167 176 40 62 140 119 123 169 189 60 77 150 128 134 182 202 60 92 160 136 142 194 216 70 108 170 144 151 206 230 80 123 180 163 160 218 243 90 139 190 162 169 230 256 100 154 200 170 178 242 270 110 169 120 185 NOTE OCCUPANTPOSITIONSSHOWN ARE FOR 130 200 THE SEATSADJUSTED THE MAXIMUM RANGE 140 216 INTERMEDIATEPOSITIONSWILL REQUIREINTER 150 231 POLATIONOF THE MOMENT 100 VALUES ...

Page 160: ...160 136 142 194 203 170 144 151 206 216 180 153 160 218 229 190 162 169 230 241 200 170 178 242 254 NOTE OCCUPANTPOSITIONSSHOWN ARE FOR THE SEATS ADJUSTED THE MAXIMUM RANGE INTERMEDIATEPOSITIONSWILL REQUIREINTER POLATIONOF THE MOMENT 100 VALUES Fifth and Sixth Seats ARM 154 WEIGHT MOM 100 30 46 40 62 50 77 60 92 70 108 80 123 90 139 100 154 110 169 120 185 130 200 140 216 150 231 160 246 170 262 E...

Page 161: ...100 Mom 100 Mon 1100 10 15 11 15 20 30 22 29 30 45 32 44 40 60 43 58 50 75 54 73 60 90 65 87 70 105 76 102 80 120 86 116 90 135 97 131 100 150 108 145 110 165 119 160 120 180 130 174 130 195 140 189 140 210 151 203 150 225 162 218 160 240 173 232 170 255 184 247 180 270 194 261 190 285 205 276 200 300 216 290 210 315 305 220 330 319 230 345 334 240 360 348 250 375 363 260 390 377 270 405 392 Janua...

Page 162: ...EADING EDGE TANKS ARM 75 Moment Gallons Weight 100 5 30 23 10 60 45 15 90 68 20 120 90 25 150 113 30 180 135 35 210 158 40 240 180 44 264 198 50 300 225 55 330 248 60 360 270 65 390 293 70 420 315 74 444 333 OIL Moment Quarts Weight 100 12 23 6 Included in Basic Empty Weight 6 18 January 1982 ...

Page 163: ...ic Elevator Trim 7 6 Instrument Panel 7 6 Flight Instruments 7 7 Power Plant Instruments 7 7 Manifold Pressure and Fuel Flow Indicator Round 7 8 Multiple Readout Type Instrument V35B 7 8 Electrically Operated Vertical Instruments V35B 7 9 Fuel Flow Indicator Vertical 7 9 Cluster Type Power Plant Instruments 7 14 Switches 7 15 Annunciator System 7 15 Warning Light 7 15 Ground Control 7 16 Wing Flap...

Page 164: ...rnesses 7 20 Seat Adjustments 7 20 Shoulder Harness Installation Prior to D 9862 7 21 Shoulder Harness Installation D 9862 and After 7 21 Doors Windows and Exits 7 22 Cabin Door 7 22 Openable Cabin Windows 7 22A Emergency Exits 7 23 Control Column Lock Pin 7 24 Power Plant Description 7 24 Engine Controls 7 25 Throttle Propeller and Mixture 7 25 Cowling 7725 Cowl Flaps 7 25 Induction System Icing ...

Page 165: ...rior Lighting 7 33 Exterior Lighting 7 34 Environmental Systems 7 35 Cabin Heating 7 35 Heater and Defroster Operation 7 35 Cabin Ventilation 7 36 Cabin Fresh Air Outlets 7 36 Exhaust Vents 7 37 Heating and Ventilation System Schematics 7 38 Oxygen System 7 40 Pitot and Static Systems 7 40 Pitot System 7 40 Pitot Heat 7 40 Normal Static Air System 7 41 Emergency Static Air System 7 41 Vacuum Syste...

Page 166: ...Section VII BEECHCRAFT Bonanza Systems Description V35 V35A V35B thru D 9947 INTENTIONALLY LEFT BLANK 7 4 January 1982 ...

Page 167: ... tail in response to elevator and rudder control action FLIGHT CONTROLS CONTROL SURFACES Control surfaces are operated through push pull rods and conventional cable systems terminating in bellcranks CONTROL COLUMN The throw over type control column for elevator and 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 co...

Page 168: ...ned by cable loads imposed by the trimmer ELECTRIC ELEVATOR TRIM The optional electric elevator trim system controls include the ON OFF switch located on the instrument panel a thumb switch on the control wheel and a circuit breaker on the right subpanel The ON OFF switch must be in the ON position to operate the system The thumb switch is moved forward for nose down aft for nose up and when relea...

Page 169: ... head temperature sensor is installed in the engine cylinder which because of location in the compart ment has the highest temperature reading Monitor cylinder head temperature after power setting ad justments are made to assure that the engine operating temperature remains in the desired range The oil pressure normal operating range is 30 to 60 psi The oil pressure should be checked when starting...

Page 170: ...for normal operating limits Redradials are placed at the mini mum and maximum allowable fuel pressures In the cruise power range the green sectors cover the fuel flow 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 par ticular power range The take off and climb range is covered by gree...

Page 171: ...pressure tachometer fuel flow m ter calibrated in pounds per hour cylinder head temperature and oil temperature indicator both calibrated in degrees centigrade oil pressure indicator ammeter and left and right fuel quantity indicators calibrated in pounds FUEL FLOW IND CA TOR Vertical Type The fuel flow indicator is calibrated in pounds per hour The normal operating range of 41 4 pph to 145 8 pph ...

Page 172: ...r cruise power settings between 45 and 75 The upper portion indi cates fuel flow for take off and climb at various altitudes The lower fuel flow figure is the normal lean setting while the higher flow is the best power setting for that percent age of power The high side of each green sector repre sents the fuel flow setting required to achieve maximum power of the specified altitude when operating...

Page 173: ...BEECHCRAFT Bonanza V35 V35A V358 thru D 9947 Section VII Systems Description 0 s s i s 0 0 0 0 s s L 1 j o oij January 1982 1 0 0 B zo 5 qp 0 oQ C D 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 7 11 ...

Page 174: ...ECHCRAFT Bonanza SystemsDescription V36 V36A V358 thru 0 9947 v 7 12 Bonanza V35B T I r 1 i 1 1 Hl f i i tli i lH i iH I i ll ll li i JL 1 l o 00 0 i i i l ie ie i 11 l w Cl z t LLI Q E z a oti a z I z J a CJ Z t w ...

Page 175: ...BEECHCRAFT Bonanza Section VII V35 V35A V35B thru D 9947 Systems Descriotion ID v Bonanza V35B January 1982 i r w I Jz w a a w I z J w z c a z w 7 13 ...

Page 176: ...low and tachometer Included in the square cluster are the cylinder head temperature and oil temperature both calibrated in degrees Centigrade ammeter and oil pressure A fuel quantity indicator is located on each side of the cluster the left indicator for the left wing fuel and the right indicator for the right wing fuel TACHOMETER 00 SO 00 ZS zso __ I c c CV LTEMP OIL TEMP ljj I l S O IS Pl I I 0 ...

Page 177: ...lighting switches are located on either the right V35 V35A or left V35B subpanel ANNUNCIATOR SYSTEM WARNINGLIGHT Overvoltage Warning light V35 V35A A press to test overvoltage warning light on the instru ment panel will come on should the alternator be discon nected from the airplane bus by the overvoltage relay NOTE To reset the overvoltage relay refer to the EMERGENCYPROCEDURESsection Alternator...

Page 178: ...o 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 flaps are controlled by a three position switch UP OFF and DOWN located in the subpanel above the power quadrant The switch must...

Page 179: ...ed to the opposite position CAUTION Do not change the position of the control switch to reverse the direction of the landing gear while the gear is in transit as this could cause damage to the retract mechanism POSITION INDICATORS V35 V35A Landing gear position indicator lights on the right side of the control console show red when the gear is up or green when it is down illuminating only when the...

Page 180: ... the floating instrument panel The intensity of the lamps is automatically lowered for night flights when the naviga tion lights are turned on CIRCUIT BREAKER The landing gear circuit breaker is located on the left sub panel of V35 and V35A models and on the right subpanel of V35B models It is a pull and reset type breaker The breaker will pop out under overload conditions SAFETY SWITCH To prevent...

Page 181: ...lt 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 sub panel right subpanel V35 V35A left subpanel V358 To set 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 off and wheel chocks installed if the ai...

Page 182: ...lane Do not carry children in the baggage compart ment unless secured in a seat SEATS SEAT BELTS AND SHOULDER HARNESSES SEAT ADJUSTMENTS To adjust any of the four standard seats forward or aft pull up on the release bar below the seat and slide the seat to the desired position The seat backs of all standard seats can be placed in any of four positions by operating a release lever on the inboard si...

Page 183: ... the seats in the upright position Tt espring loading at the inertia reel keeps the harness snug but will allow normal movement required during flight operations The inertia reel is designed with a locking device that will secure the harness in the event of sudden forward movement or an impact action SHOULDER HARNESS INSTALLATION D 9862 and after The shoulder harness is a standard installation for...

Page 184: ...ependent of the shoulder harness but the outboard seat belt and the shoulder harness must be connected for stow age when the seat is not occupied DOORS WINDOWS AND EXITS CABIN DOOR The outside cabin door handle is spring loaded to fit into a recess in the door to create a flat aerodynamically clean surface To open the door from the outside lift the handle from its recess and pull until the door op...

Page 185: ... clockwise OPENABLE CABIN WINDOWS To Open Window For Ventilation Only On Ground I Release latch front of bar pull bar at the bottom of the window out and upward Window will open approximately two inches To Close Window Pull inward and down on the bar at the bottom of the window Resista neewill befelt as the bar moves downward Continue moving bar downward to its lowest position Check that bar is lo...

Page 186: ...Section VII BEECHCRAFT Bonanza Systems Description V35 V35A V35B thru D 9947 INTENTIONALLY LEFT BLANK 7 22B Revised March 1983 ...

Page 187: ...XITS To open the emergency exit provided by the openable window on each side of the cabin 1 Lift the latch 2 Pull out the emergency release pin and push the window out The above procedure is described on a placard installed below the left and right openable windows Revised March 1983 7 23 ...

Page 188: ...ttle and propeller controls WARNING Before starting engine remove the lock re versing the above procedure Airplane serials D 9705 and after Installation is the same as earlier serials except the control column lock pin is in serted from the top of the control column Illustration at right shows lock in place and is placarded on the con trol column lock itself POWER PLANT CONTROLS LOCKED INSTALL AS ...

Page 189: ...ngine To close the cowling requires only to lower the cowling to the closed position with the handle in the prelatch position The handle has three positions flush with the fuselage latched held fully forward un latched open cowling approximately 90 to the fuselage prelatch ready to close cowl An audible click denotes the bayonet fittings located forward and aft on the upper cowl sliding into the l...

Page 190: ...mes frozen in the closed position a pull and release T handle is provided to force the door open LUBRICATIONSYSTEM The engine oil system is the full pressure wet sump type and has a 12 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 ...

Page 191: ...ameter Maximum 80 in Minimum 78 5 in Pitch settings at 30 in sta Low 13 3 0 2 High not under 29 0 0 5 Spinner McCauley D3584 assembly Governor Woodward C210452 or 0210680 Propeller rpm is controlled by aWoodward governor which regulates hydraulic oil pressure to the blades A push pull knob on the control console allows the pilot to select the governor s rpm range If oil pressure is lost the propel...

Page 192: ...ler cap A visual measuring tab is attached to the filler neck of the optional system The bottom of the tab indicates 27 gallons of usable fuel and the detent on the tab indicates 32 gallons of usable fuel in the tank provided the wings are level The engine driven fuel injector pump delivers approxi mately 10 gallons of excess fuel per hour which bypasses the fuel control and returns to the tank be...

Page 193: ...UEL FLOW GAGE l l AUX f I I _ _r I t 11 c 1 1 _ VENT 18J s l O VENT CHECK L i ___ __ s STRAINER CHECK VALVE FLUSH VENT j 1 FLUSH VENT VALVE VENT VENT SELECTOR VALVE STRAINER AND DRAIN FUEL SYSTEM SCHEMATIC m wm u m 0 WO J1 D J J I Wm J1 0 m DI r N C Ill C I co co en l Ill Cu ID ID Ill n n o S a ...

Page 194: ...r near maximum engine performance should the engine driven pump fail FUEL TANK SELECTION The fuel selector valve handle is located forward and to the left of the pilot s seat Take offs and landings should be made using the tank that is more nearly full If the engine stops because of insufficient fuel refer to the EMERGENCY PROCEDURES Section for the Air Start procedures FUEL REQUIREDFOR FLIGHT It ...

Page 195: ...switch and the magneto start switch are located on either an escutcheon at the left of the instrument panel V35 V35A or the left subpanel V35B The V35 V35A models have an interlock between the bat tery and alternator switch A placard clarifies operation as follows 1 BAT ALT switch ON Battery and Alternator are func tioning provided the ALT switch is in the ON position 2 BAT ALT switch OFF Battery ...

Page 196: ...load of the electrical equipment in use The alternator field circuit breaker is located on the right sub panel and the alternator output circuit breaker is in stalled on the left side of the nose wheel well cover The al terr iator out warning light can be tested on the V35B by the warning test switch on the instrument panel and by the press to test feature on the V35 and V35A If a mal function occ...

Page 197: ...nternal lights in the radio installation The cabin dome light is operated by an ON OFF switch next to the light V35B Lighting for the instrument panel is controlled by thumb rotated disc type rheostats located on the pilot s sub panel to the left of the control column The first rheostat is labeled RADIO and ENG and controls the lighting of the avionics panel and the multiple readout engine instru ...

Page 198: ...becomes overloaded or shorted The exterior lights consist of navigation lights on the wing tips and tail cone a landing light in the fuselage nose sec tion and a taxi light attached to the nose strut The landing Iight can be used for approach and taxiing Use the landing light for approach and the taxi light for taxiing For longer battery and lamp life use the landing light and taxi light sparingly...

Page 199: ... controlled quantity of unheated ram air which enters an intake on the right side of the nose Air of the desired temperature is then ducted from the mixer valve to the outlets in the cabin On the V358 fresh ram air enters an intake on the right side of the nose passes through the heater muffler then into a mixer valve on the forward side of the firewall In the mixer valve the heated air is combine...

Page 200: ...tion To obtain heated air for defrosting the wind shield pull the DEFROSTcontrol out It may be necessary to vary or close the AFT CABIN HEAT control to obtain maximum air flow for defrosting To close off all air from the heater system pull the red control located at the ex treme left of the pilots lower subpanel It is placarded either VENT SHUTOFF V35 V35A or FIREWALL AIR V35B CABIN VENTILATION In...

Page 201: ... A system shutoff valve is installed in the duct be tween the overhead fresh air scoop and the individual fresh air outlets The valve is operated by a push pull con trol or by turning a knob in the overhead panel EXHAUST VENTS V35 V35A A manually controlled cabin air exhaust vent is located aft of the radio speaker in the overhead panel In addition a fixed exhaust in the upholstery panel below the...

Page 202: ...OUTLETS STANDARD t A ROL DEFROSTERCONTROL CABIN VENT CONTROL AFT1 0UTLET R HI FRONT SEAT I I I OVERHEAD FRESHAIR SHUTOFF CONTROL t AFT OUTLET I RH REARSEAT FIXE EXHAUST _ u 1 FUSElAGE eonOM J j O g x ig GE DOOR INOIVIOUAL OVERHEAD I FRESHAIROUTLETS OPTIONAL 1 0 I I OVERHEAD FRESHAIR SHUTOFF VALVE I j I I I I I I I I I I I I I OVERHEAD FRESHAIR sco I I I I I I I I I HEATING AND VENTILATION SYSTEM S...

Page 203: ...tion V35 V35A V35B thru 0 9947 FRESH AIR INTAKE NOSE I HEATEDAIR OVERBOARD VENT I FRESH AIR rWING ROOT RH r RH FORWARDOUTLET OVERHEADFRESHAIR r Tt _ _ SHUTOFFCONTROL 10 9287 ANO AFTER HEATING AND VENTILATION SYSTEM SCHEMATIC V35B January 1982 7 39 ...

Page 204: ...h altitude Flow is varied auto matically from 0 5 liters per minute at 5 000 feet to 3 5 liters per minute at 30 000 feet The use of oxygen is rec ommended to be in accordance with current FARoperating rules PITOT ANO STATIC SYSTEMS PITOT SYSTEM The pitot systems provides a source of impact air for opera tion of the airspeed indicator The pitot mast is located on the leading edge of the left wing ...

Page 205: ...ery 100 hours and after exposure to visible moisture either in the air or on the ground EMERGENCYSTATIC AIR SYSTEM An emergency static air source may be installed to pro vide air for instrument operation should the static ports become blocked Refer to the EMERGENCY PRO CEDURES Section for procedures describing how and when to use this system VACUUM SYSTEM V35 Suction for gyroscopic flight instrume...

Page 206: ...e pressure operated instruments STALL WARNING A stall warning horn on the forward side of the instrument panel sounds a warning signal as the airplane approaches a stall condition The horn is triggered by a sensing vane on the leading edge of the left wing and is effective at all flight attitudes Irregular and intermittent at first the warning signal will become steady as the airplane approaches a...

Page 207: ...ruise climb or cruise Maintain the highest power recommended for cruise operations during the break in period avoiding altitudes above 8000 feet Inter rupt cruise power every 30 minutes or so by smoothly ad vancir1g to take off power settings for about 30 seconds then returning to cruise power settings Avoid long power off descents especially during the break in period Maintain sufficient power du...

Page 208: ...Section VII BEECHCRAFT Bonanza Systems Description V35 V35A V35B thru D 9947 INTENTIONALLY LEFT BLANK 7 44 January 1982 ...

Page 209: ...Alterations 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 11 Mooring 8 11 Engine Preparation For Storage 8 11 Fuel Cells 8 12 Flight Control Surfaces 8 12 Grounding 8 12 Pitot Tube 8 12 Windshield and Windows 8 12 During Flyable Storage 8 12 Preparation For Service 8 13 E...

Page 210: ...sh Strut Hydraulic Fluid 8 19 Shock Strut Shimmy Damper 8 20 Brakes 8 21 Vacuum System 8 21 Instrument Pressure System 8 21 Induction Air Filter 8 22 To Remove and Clean the Filter 8 22 Propeller Blades 8 22 Oxygen System 8 23 Oxygen Cylinder Retesting 8 24 Minor Maintenance 8 25 Rubber Seals 8 25 Generator 8 25 Alternator 8 25 Magnetos 8 22 Cleaning 8 26 Exterior Painted Surfaces 8 26 Windshield ...

Page 211: ...E Lubrication Points 8 38 Consumable Materials 8 44 Overhaul or Replacement Schedule 8 48 Special Conditions Cautionary Notice 8 48 Landing Gear 8 49 Power Plant 8 49 Fuel System 8 50 Instruments 8 51 Electrical System 8 51 Flaps and Flight Controls 8 52 Miscellaneous 8 52 Approved Engine Oils 8 54 January 1982 8 3 ...

Page 212: ...Section VIII BEECHCRAFT Bonanza Handling Serv Ma int V35 V35A V35B thru D 994 7 INTENTIONALLY LEFT BLANK 8 4 January 1982 ...

Page 213: ...y with all airworthiness requirements 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 and International Distributors or Dealers will have recommended modification service and operating procedures issued by both FAA and Beech Airc...

Page 214: ...ssues and revisions of FAA Approved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Man uals and Pilot s Operating 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 Notifica tion Service List and then only if listed by air plane serial num...

Page 215: ...gear doors and flaps for damage or distortion before the next flight P EVENTATIVE 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 obtai a BEECHCRAFT Shop Manual for performing preventative maintenance 2 All other maintenance must ...

Page 216: ... hangar 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 person 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 Whe...

Page 217: ...ng Care should be used 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 sub panel To set the parking brakes pull control out and depress the pilot s toe pedals until firm Push the control in to release the brakes NOTE The parking brake should be left off and wheel chocks installed if the airpla...

Page 218: ...ge is excessively tight the nose may rise and produce lift due to the angle of attack of the wings 4 Release the parking brake If high winds are anticipated a vertical tail post may be in stalled at the rear tie down lug and a tie down line at tached 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 t...

Page 219: ...LYABLE STORAGE 7 TO 30 DAYS MOORING If airplane cannot be placed in a hangar tie down securely at the three points provided Do not use hemp or manila rope It 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 ENGINE PREPARA TJON FOR STORAGE Engines in airplanes that are flown only occasionally tend to exhibit ...

Page 220: ...lose all windows and window vents It is recommended that covers be installed over windshield and windows DURING FLYABLE STORAGE Each seven days during flyable storage the propeller shall be rotated by hand After rotating the engine six revolutions stop the propeller 60 or 120 from the position it was in 8 12 WARNING Before rotation of propeller blades ascertain ignition switch is OFF throttle in C...

Page 221: ...ollowing precautions be observed 1 The airplane has a negative ground system Exercise care to avoid reversed polarity Be sure to connect the positive lead of the external power unit to the positive terminal of the airplane s external power receptacle and the negative lead to the negative terminal of the external power receptacle A positive voltage must also be applied to the small guide pin 2 To p...

Page 222: ...umable Materials for recommended fuel grades CAUTION Never leave bladder cells completely empty for more than a few days as the cell inner liners may dry out and crack permitting fuel to diffuse through the walls of the cell after refueling If the cells are to be left empty for a week or more a thin coating of light engine oil should be sprayed or flushed onto the inner liner of the cells The stan...

Page 223: ...f the fuel selector valve The drain is accessible through a door in the fuselage adjacent to the left wing FUEL STRAINERS At each 50 hour inspection the strainer plug should be removed from the fuel injection control valve and the fuel injection control valve screen washed in fresh cleaning solvent After the strainer plug has been reinstalled and safetied the installation should be checked for lea...

Page 224: ...y 100 hours under normal operating conditions To assure complete drainage the engine should be at operating temperature Oil CHANGE PROCEDURE 1 Remove the access plate from the engine cowl on the lower right side 2 Locate the oil sump drain plug at the low point of the engine sump 3 Remove the plug button below the sump drain and insert the oil drain duct 4 Remove the oil sump drain plug 5 Remove t...

Page 225: ...ible by opening the right engine cowling Check the electrolyte level after each 25 hours of operation and add distilled water as necessary Do not overfill the battery Excessive water consumption may be an indication that the voltage regulator requires resetting The specific gr13vityof the electrolyte should be checked periodically and maintained within the limits placarded on the battery The batte...

Page 226: ... recapped tires Recappedtires have a tendency to swell as a result of the increased temperature generated during takeoff Increased tire size can jeopardize proper function of the landing gear retract system with the possibility of damage to the landing gear doors and retract mechanism SHOCK STRUTS The following procedures may be used for servicing both the main and the nose gear shock struts TO IN...

Page 227: ...s the valve core and allow the strut to fully deflate 3 Raise and block the strut 1 4 inch from the com pressed position WARNING Do not remove the valve body assembly until all air pressure has been released or it may blow off causing injury to personnel or damage to equipment 4 Carefully remove the valve body assembly 5 Fill the strut to the level of the valve body assembly with hydraulic fluid s...

Page 228: ...iston rod until it touches the bottom of the hole in the floating piston Mark the wire remove it and measure the depth of the insertion When the shimmy damper is full insertion depth is 2 3 16 inches when empty 3 1 16 inches NOTE The measuring wire should be inserted in the hole in the floating piston rather than against the piston face to give a more accurate reading To determine if the wire is i...

Page 229: ... every 100 hours If the airplane is operated in dusty conditions the screens should be cleaned more frequently Clean the suction relief valve screen by removing and washing in cleaning solvent Remove and clean the oil separator screen by backflushing or submerging the unit in cleaning fluid Blow dry with air pressure The filter assemblies on the air driven instruments should be replaced every 100 ...

Page 230: ...s recommended 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 filter 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 particu...

Page 231: ...res WARNING Keep hands tools clothing and oxygen equip ment clean and free from grease and oil KEEP FIRE AND SPARKS AWAY FROM OXYGEN Use only recommended leak testing soaps 1 Read the pressure gage on the oxygen console panel just forward and to the left of the pilot s seat 2 The gage will not indicate pressure unless the shutoff valve on the oxygen cylinder is open The shutoff valve is located un...

Page 232: ... bottle valve remove the recharging outlet and replace the filler valve cap 7 Slowly open the cylinder shutoff valve to prepare the system for use 8 Reinstall the access panel and slide the pilot s seat for ward to its original position 9 The console panel shutoff valve should remain closed until the system is used OXYGEN CYLINDER RETESTING The oxygen cylinders light weight cylinders stamped 3HT o...

Page 233: ...s 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 alternator are the same 2 When connecting a booster battery be sure to connect the negative battery terminals together and the positive battery terminals together 3 When using a battery charger connect the positive lead of the charger to t...

Page 234: ...ed 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 EXTERIORPAINTED SURFACES 8 26 WARNING Do not expose control surface trim tab hinge lines and their pushrod systems to the direct stream or spray of high pressure soap and water washing equipment Fluid dispensed at high pressure could remove the...

Page 235: ... enamel acrylic enamel lacquer and dope finishes require a curing period of approxi mately 90 days Acrylic urethane polyester urethane and epoxy finishes undergo a curing process for a period of 30 days after application Wash uncured painted surfaces with a mild non detergent soap MILD detergents can be used on urethane finishes and cold or luke warm water only Use soft cloths keeping them free of...

Page 236: ...Section VIII BEECHCRAFTBonanza Handling Serv Maint V35 V35A V35B thru D 9947 INTENTIONALLY LEFT BLANK 8 26B Revised March 1983 ...

Page 237: ...aline soaps or detergents which could cause corrosion or scratches Thorough clear water rinsing pre vents buildup of cleaning agent residue which can dull the paint s appearance To remove oily residue or exhaust soot use a cloth dampened with an automotive tar remover Wax or polish the affected area if necessary There is some variation in the procedures required for proper care of the several type...

Page 238: ...halking occur For waxing select a high quality automotive or aircraft waxing product Do not use a wax containing silicones as silicone polishes are difficult to remove from surfaces A buildup of wax on any exterior paint finish will yellow with age therefore wax should be removed periodically Generally alphatic naptha see Consumable Materials is adequate and safe for this purpose 8 28 NOTE Before ...

Page 239: ... extinguisher 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 fla...

Page 240: ...y as possible 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 ...

Page 241: ...t overhead Instrument light post Internal wedge lights Landing gear position light Landing gear visual indicator light Landing light nose section Landing light nose shock strut Navigation light tail cone Navigation light wing Overvoltage warning light Rotating beacon Grimes Rotating beacon Whelen Strobe lights Bullock January 1982 NUMBER 330 89 53R 53 89 330 58 380022 9 330 53 4313 4522 93 1512 33...

Page 242: ...de Service fuel cells Top of wings leading edge 6 25 Hrs Check battery electrolyte Under right cowling door See Shop Manual 50 Hrs Clean fuel injection control Lower engine compartment 7 valve screen Clean induction air filter Behind nose section grill Drain static air lines Behind aft cabin bulkhead Lubricate landing gear Wheel wells K 4 retract mechanism and uplock rollers D 7977 thru D 9287 unl...

Page 243: ...bricate aileron control linkaget Lubricate cabin door mechanism Lubricate control column linkage Lubricate cowl flap hinges If Applicable Forward of left front seat Lower right side of engine 5 Upper left side of engine Left side belly 7 Engine compartment 7 Engine compartment Each wing J 4 10 Aft edge of cabin door E 4 Forward of instrument 4 panel C Bottom of cowl N 4 cu wm 01 m C c WC 01 J J J ...

Page 244: ...tor tab Forward of tail bulk 3 4 mechanism head I Lubricate landing gear Edge of wheel well 4 door hinges L 0 Lubricate landing gear Wheel wells A K 3 10 retract mechanism and uplock rollers Lubricate nose wheel Nose wheel well B 3 steering mechanism Lubricate rudder pedals Cockpit M 4 Lubricate wheel bearings Nose and main wheels 1 4 and felt sealstt A K D 9288 and after Also prior airplanes afte...

Page 245: ...Clean spark plugs Service main and nose shock struts Service shimmy damper Drain static air lines Under front seats in cabin G Under front seats in cabin F Forward of instrument panel Under front seats in cabin F Under front seats in cabin G Inside wing aft of wheel well G Under floor in cabin Engine compartment Landing gear Nose gear Behind aft cabin bulkhead 8 Airborne Mfg 1J4 7 3 10 9 10 2 2 gJ...

Page 246: ... 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 rair t or is washed down Air conditioner compressor oil level Air conditioner refrigerant See shop manual See shop manual Suniso No 5 or Texaco Capella E 500 viscosity oil Refrigerant No 12 r Cl 111 CD C Q ct 0 IP Cl CD I s Ill...

Page 247: ...ge life Non rechargeable Batteries Replace after one cumulative hour of useor after 50 of the useful charge life tLubricate 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...

Page 248: ...Section VIII BEECHCRAFT Bonanza Handling Serv Maint V35 V35A V35B thru D 9947 LUBRICATION POINTS NM A NOSE LANDING GEAR RETRACT 8 38 January 1982 ...

Page 249: ...BEECHCRAFT Bonanza SectionVIII V35 V35A V35B thru D 9947 Handling Serv Maint B NOSE WHEEL STEERING C CONTROL COLUMN LINKAGE D ELEVATOR TRIM CONTROL January 1982 8 39 ...

Page 250: ...Section VIII BEECHCRAFT Bonanza Handling Serv Maint V35 V35A V35B thru D 9947 E CABIN DOOR F LANDING GEAR ACTUATOR GEAR BOX G FLAP MOTOR AND ACTUATOR 8 40 January 1982 ...

Page 251: ...BEECH CRAFT Bonanza Section VIII V35 V35A V35B thru 0 9947 Handling Serv Maint H DIFFERENTIAL CONTROL MECHANISM I RUDDERVATOR TAB MECHANISM J AILERON BELL CRANKS January 1982 8 41 ...

Page 252: ...Section VIII BEECHCRAFT Bonanza Handling Serv Maint V35 V35A V35B thru D 9947 MAIN LANDING GEAR DOOR HINGES M RUDDER PEDALS 8 42 January 1982 ...

Page 253: ...u D 9947 Handling Serv Maint N 0 I I COWL FLAP HINGES NOSE GEAR DOOR HINGES HAND OR PACK FLUID CONTAINER ZERK FITTING SQUIRT CAN NOTE Letters are keyed to the Service Schedule Numbers refer to items in the Consumable Materials Chart January 1982 8 43 ...

Page 254: ...rcraft Corporation consequently any product conforming to the specification listed may be used The products listed below have been tested and approved for aviation usage by Beech Aircraft Corporation 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 eve...

Page 255: ...lean grease from bearings and bearing area before changing grease Hydraulic Fluid Lubricating Grease General Purpose Wide Temperature Lubricating Oil MIL H 5606 MIL G 81322 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 1OOLL Blue 7 Solvent Federal Specification PD680 8 Lubricant Mobil Compound GG or Mobil 636 9 Lubricating ...

Page 256: ...1 Lubricant Rubber Seal 12 Naptha Aliphatic ttl 3 Tape Anti Seize Tetrafluorethylene 14 Leak Test Compound Oxygen Systems 15 Oxygen Aviators Breathing 16 Lubricant 8 46 SPECIFICATION MIL G 23827 Oakite 6 Compound Federal Specification TI N 95 MIL T 27730 MIL L 25567 MIL 0 27210 BRAYCO 300 HCRC 3 36 HLPS No 1 WD40 January 1982 ...

Page 257: ...s recommended during break in period See ser vicing data 100LL Blue preferred or 100 Green t Product of Oakite Products Inc 50 Valley Road Berkley Heights NJ 07922 tt For sealing tapered threads on high pressure oxygen lines Product of Bray Oil Co Los Angeles Calif HProduct of CRC Chemicals Inc Warminster Pa 18974 Product of LPS Research Laboratories Inc 2050 Cotner Ave W Los Angeles Calif 90025 P...

Page 258: ...oted in this 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 t...

Page 259: ...Brake assembly Brake lining Master cylinder Shuttle valve assembly Parking brake valve All hose 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...

Page 260: ...dition On Condition On Condition replace when contamiated 1500 hours or 4 years 1500 hours or 5 years On condition At engine overhaul but not to exceed 1500 hours or 3 years Eve 1500 hours Inspect every 100 hours FUEL SYSTEM Fuel cells Wing fuel quantity transmitters Fuel cell drain valve Fuel system check valves Fuel selector valve Auxiliary fuel pump All hose 8 50 On condition On condition On co...

Page 261: ...on On condition On condition On condition On condition On condition On condition On condition Manifold pressure indicator On condition Tachometer On condition Flap position indicator Free air temperature indicator All hose Vacuum system filter Vacuum regulator valve Pressure system filter Air pressure regulator valve On condition On condition On condition Every 100 hours On condition Every 300 hou...

Page 262: ...hours Every 2000 hours Every 2000 hours MISCELLANEOUS Seat belts or Shoulder Harnesses Hand fire extinguisher Cabin heating and venti lating ducts Oxygen regulator Oxygen cylinder 8 52 Inspect every 12 months replace on condition Inspect every 12 months recharge as necessary On condition inspect every 12 months Every 48 months or 2000 hours 3HT cylinders Hydrostatic test every three years replace ...

Page 263: ... Bulletin M79 14 Rev I dated April 21 1980 or later issue Continental recommends a maximum of 1200 hours TBO on engines employed in aerial top dressing dusting or spraying With particular attention to throttle response smooth power and oil consumption a qualified mechanic must determine that the engine is operating normally at the time of each periodic inspection Refer to Hartzell Propeller Inc Se...

Page 264: ...y Exxon Aviation 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 Quaker State Oil Refining Corp Red Ram Limited Canada Shell Canada Ltd 8 54 Phillips X C Aviation Multiviscosity Oil SAE 20W 50 Phillips X C Aviation Multiviscosity Oil SAE 25W 60 Quaker State A...

Page 265: ...HT Aeroshell Oil W SAE 15W 50 Aeroshell Oil W Sinclair Avoil Texaco Aircraft Engine Oil Premium AD Union Aircraft Engine Oil 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 January 1982 8 55 ...

Page 266: ...Section VIII BEECHCRAFT Bonanza Handling Serv Maint V35 V35A V35B thru 0 9947 INTENTIONALLY LEFT BLANK 8 56 January 1982 ...

Page 267: ...tion Any Raytheon marks contained in this document are owned by Raytheon Company and are employed pursuant to a limited license granted by Raytheon Company Prior to March 26 2007 Beechcraft Corporation was owned by Raytheon Company but is no longer affiliated with Raytheon Company Beechcraft Corporation was formerly named Hawker Beechcraft Corporation from March 26 2007 until March 1 2013 Bonanza ...

Page 268: ... was installed 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 Approv...

Page 269: ...le with the airplane are listed on the Log of Supplements Supplements of a larger format are not included in this manual Make certain you retain all supplements that were provided for equipment on your airplane These documents should be accessible to the pilot during all flight operations January 1982 ...

Page 270: ... 21 66 11401 PC 1 Pitch Assist D 9 16 66 11445 BI 300 BI 301 or BI 304 B 9 16 66 Navigation Coupler 35 590110 19 Tactair T 3 AL Autopilot 10 75 BR 3 Tactair T 3 ALL Autopilot 1 24 66 TAH 3 Tactair AH 1 Altitude Hold 6 16 58 TOL 3 Tactair OL 1 Omni Lock C 1 18 66 96015 BSA 2 Stability 10 25 65 Augmentation System 35 590110 13 Landing Gear Safety 5 4 81 System 7 330 15 BSA 4 Stability 6 17 68 Augmen...

Page 271: ...ermal Propeller 2 11m Deice 2 or 3 Blade 35 590118 35 Air Conditioning System 1 11 77 7 333 53 Brittain B VII Autopilot 1 1117 69 SA785CE Hartzell Propeller 2 2 26 80 36 590002 39 Fuel Selector Valve 3183 Stop Installation 58 590000 49 Inside Cabin Door Handle 12 90 With Open Closed Placard Supplements applicable to equipment other than that installed may at the discretion of the owner operator be...

Page 272: ... 800 rctT A80YC THC TCRA AIN 0 NAY IC AT ION OU L A MALL NOT BC usco ro LOCAL I it ANO VCR IIO ICNt t 11 QP RAJINGPRQCEOLRES srcr ION SANC AS CSCRl8CO IN A PRO RIATC CAA f AA OA DCR A IIOYCO Alll LANC FLIONT MANUAL CICCC T A I MAK C RTAIN THAT AIA CRAf T IS ALT T co ecro11c CNOAGlltQ AUTO ILOT STSTrM 2 fO NC AC AUTO ILOT PULL AUTO LOT MAST R S l TCN ANO IIOTATC l IOOC S L CTOR sw TC TO OCS A O MOO...

Page 273: ...lOCIU 1 1 St 1M TURIIUL HT AIR SLOW f LICHT OR IN NOS MICH ATTITUOCS lltt SSIV 0 t t CTION ON TM 1101 L All IS MAY II MINIMIZ O 1 IIOTATINC TH AUTO ILOT 5EN5 AOJU ST MCNT COUMT R CLOCl WISC 10 PJTCH TRIM 1 0 cATOlt ROVIO S roR VISUAL lltrtll HC or TN L UTOllt TIIIM STATUS WM N TRIM INDICATOR IIAR IS AIIOV Ht MIO NARK 1RCIIArT HAS NOS U LCVATOR TRIM A O VIC V IISA 11 co ANO Allll CR11or ATTITUO WIT...

Page 274: ...whea aircraft 1a operated below 800 feet above tbe terrain 3 Pzae1 t1c Pitch Aui t _ to be operated above V Green Arc 4 Brittain Pneumatic Pitch Assist PC 1 and Altitude AH 1 ahall be installed for use only in conjunction with an FAA Approved 1ustallat1on of Br1 tta1n Clarksob Autopilot or l actair IIodel B1O1 Autopilot 11 OPEKATiml PRO EDURES SECT I OK KOlU1AL A l A pilot ccmaarid SXNS adJust111e...

Page 275: ... 1nsta llat1on The Altitude Hold Control 1 a actua ted by Pull for On and Push for Ott To be engaged 1 c cru1 con 1gurat1on oni P FM App d Z _ c harlH R Ha rkS JE 3 1 o ciiiei Engtneeririg and lanu acturing Branch Western RegioD Federal Aviation ency Date __ Dec __ mbo r_l3 _19_6_2 __ _ Items denoted by CA incorporated in rev1s1 on dated February Z7 19 63 w Approved c Items denoted bJ Cb incorpora...

Page 276: ...RES NOT CONTAINED IN THIS SUPPLEMENT CONSULT THE MANUAL PROPER ANO TH BASIC BEECH AFM SuP OATED Auc uST 10 196 I l MITATIONS SECTION I TO BE OPERATED N CONJUNCTION WITH A NORMALLY F UNCTIONINC FAA APr ROVEO 6RITTAIN 6tECHCRAF r AUTOPILOT CREF ER TO BASIC BEEC t 1 AFM SuP OATEO AUGUST 0 1961 2 MANUAL TURN KNOB ON BAS C AUTOPILOT NOT TO BE OPERATED WHEN NAv CouPL R IS IN H X MOOE XC ESS1VE SANK ANGL...

Page 277: ...I NC CAPTURE MOOE 6 TRK MOOE IS USED TO OPTIMIZE TRACKING OF THE CAPTURED VOR COURSE ANO PREVENTS XC SSIV HCA DING HANG S WH N PASSING OV R THC VOR STAT JON B EMERGENCY 1 IN THC EVENT Of MALF UNCTION PUSH THC AUTOPILOT MAST R S tTCH TO OFF POSITION THC HUMAN PILOT CAN CASI LY OVERRIDE THE SYSTEM AT ANY TIME 2 IN THC EVENT Of PARTIAL OR COMPL TE VACUUM f AJLURE INOICATED 9Y A OROP Of VACUUM PRESSUR...

Page 278: ...k only where covered in the items contained herein LIMITATIONS 1 Autopilot operation not certificated above 20 000 feet 2 Do not use autopilot during take off or landing EMERGENCY PROCEDURES 1 Basic Autopilot Maximum altitude lost during malfunctioning tests in cruise configuration 160 feet Maximum altitude lost during malfunctioning test in approach configuration 50 feet If a drop in suction belo...

Page 279: ...ence NOTE The Altitude Hold may be overpowered manually however upon release of the controls the airplane will again fly to the set altitude unless Altitude Hold is disengaged before changing altitude 3 Omni Lock In the event of malfunction the Omni Lock can be dis engaged by pushing the Omni Pull knob to its full IN position It can also be manually overpowered by exerting enough force on the cont...

Page 280: ... Lock button can be pushed in to provide heading reference to the Directional Gyro Heading can be selected by setting the upper card of the Directional Gyro with the Course Selector Knob Autopilot will bring airplane to desired heading if within 80 of either side of desired heading All corrections using the Course Selector Knob have a turn rate of approximately two degrees per second The tab benea...

Page 281: ...e the Heading Lock Engage the Omni Lock by Pulling out Omni Pull knob b Operation of Omni Lock 4 of 5 If the Omni needle indicates 5 or more from the selected bearing the airplane will turn until the Directional Gyro heading is within 30 to 45 of the selected bearing This heading will be main tained until the needle indicates approximately 5 At this point the intercept angle will gradually decreas...

Page 282: ...is desired to fly with the Omni needle centered the D G Course Card should be turned to align with the 0 G Heading Card The Omni Lock is automatically neutralized whenever the microphone button is depressed When this occurs the airplane will maintain the heading set on the D G Course Card NOTE This Omni Lock is to be used only as an aid in flying the Omni Directional Navigation Range It is not to ...

Page 283: ...ent supersedes or adds to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only where covered in the items contained herein LIMITATIONS The landing gear safety system is designed to help prevent gear up landings and premature or inadvertent operation of the landing gear mechanism The system is to be used as safety backup device only normal usage of the landing gear position s...

Page 284: ...ition 5 Airplanes equipped with on off and press to test switches Place the ON OFF switch in the ON position and push the PRESS TO TEST Proper functioning of the automa tic landing gear extension portion of the system is indi cated by the noise or movement of the solenoid in the landing gear position switch The PRESS TO TEST switch will not operate the solenoid unless the on off switch is in the O...

Page 285: ...ph IAS and 3 the engine is operating at a throttle position corresponding to approximately 18 to 20 inches or more of manifold pressure depending on setting NOTE If landing gear retraction is desired before the indicated airspeed reaches approximately 78 kts 90 mph the landing gear safety system must be inactivated by placing the switch in the OFF position preferably before placing the landing gea...

Page 286: ... installed in accordance with BEECHCRAFT FAA approved data The informationin this supplement supersedesor adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only as set forth below LIMITATIONS 1 This system shall not be used as a primary system under IFR conditions except on approved approach procedures approved area navigation airways and random area navigation r...

Page 287: ...REQUIRED 2 VOA or Distance flag appears while in APPR mode If flag appears while on an approach execute a missed approach and utilize another approved facility NORMAL PROCEDURES 1 VHF NAV ON 2 DME ON 3 Mode Selector SELECT VOR DME RNAV or APPR 4 NAV Frequency SET 5 DME Frequency SET 6 Waypoint Bearing SET WAYPOINT RADIAL FROM VORTAC 7 Waypoint Distance SET WAYPOINT DISTANCE FROM VORTAC 8 OBS Contr...

Page 288: ...PERFORMANCE No change Approved _ W H Schultz c FAA Approved Revised December 1978 PIN 35 590118 13 Beech Aircraft Corporation DOA CE 2 3of3 ...

Page 289: ...ved Airplane Flight Manual when the airplane IS equipped with a factory installed Standby Generator Power System In accordance with BEECHCRAFT FAA approved data or if the system Is installed by kit in accordance with BEECH KIT 35 3012 The 1nformat1on In this supplement supersedes or adds to the basic Pilofs Operating Handbook and FAA Approved Air plane Flight Manual only as set forth below LIMITAT...

Page 290: ...dinator c Transponder if installed d Audio Amplifier if installed e If RNAV 1s not installed NAV COMM I or NAV COMM II only one at a time If RNAV 1sinstalled COMM I or NAV COMM II only one at a time NOTE If an electric compass system s installed and the standby generator system s n operation no d1 rect1onal gyro indication will be available unless a second air driven directional gyro is installed ...

Page 291: ...ctional gyro 1nd1cation will be available unless a second air driven directional gyro is installed D 6 Failure of a NAV COMM all other instruments operable a If RNAV is not installed select other NAV COMM if installed b If RNAV is installed select COMM I 7 Failure of any one instrument indicates a malfunction in that system only 8 Failure of all instruments indicates a malfunction of the Standby G...

Page 292: ... it indicates a malfunction in that part of the system Check operation of components listed under step 5 of EMERGENCY PROCEDURES to ensure system is functioning properly 3 Standby Generator Power ON OFF TEST Switch TEST Hold Momentarrly 1n Test Position BAT GEN lights will illuminate 4 Standby Generator Power ON OFF TEST Switch OFF 5 Battery and Alternator Switches ON PERFORMANCE No Change Approve...

Page 293: ... Flight Manual when the airplane is equipped with an Electrothermal Propeller Deice System that has been installed in accordance with BEECHCRAFT FAA approved data or if the system is installed by kit in accord ance with Beech Kit 35 9001 35 9003 or 35 9005 LIMITATIONS Do not operate the system unless engine is operating PLACARDS On Instrument Panel ITOPREVENT ELECTRICAL OVERLOAD I I OPERATE THE PR...

Page 294: ...ng gear are not listed but may be operated whenever required NOTE Items are listed as factory equipped Any change in equipment will require changes to this list LIST OF EQUIPMENT VFR IFR DAY NIGHT DAY NIGHT WARNING This airplane may not be operated in a Terminal Controlled Area under VFR or IFR night conditions when propeller deice system is operating Items installed on the airplane that are not s...

Page 295: ...r the propeller deice system inoperative b Zero to 20 Amps 2 Blade Zero to 30 Amps 3 Blade If propeller deice system ammeter occasionally or regularly indicates less than 20 amps 2 blade 30 amps 3 blade operation of the propeller deice system can continue unless serious propeller imbal ance results from irregular ice throw offs c More than 24 Amps 2 Blade More than 34 Amps 3 Blade If the propP ler...

Page 296: ...m in operation move propeller deice switch to the ON position The system will function auto matically until the switch is turned off CAUTION The system is not to be operated continuously due to its electrical load 3 Propeller imbalance may be relieved by varying rpm Increase rpm briefly and return to desired setting re peating if necessary PERFORMANCE No Change 4of4 Approved 74 Jcj 4 y Chester A R...

Page 297: ... has been installed in accordance with BEECHCRAFT FAA approved data The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only as set forth below LIMITATIONS The air conditioning system must be off during takeoff The AIR COND CONDENSEREXT warning light must be extin guished condenser retracted before takeoff The aii co...

Page 298: ...S AIR START PROCEDURE Air conditioning system must be turned off before attempt ing air start procedures AIR CONDITIONING SYSTEM MALFUNCTION Turn off air conditioning system If air conditioning system circuit breaker trips do not reset until the cause of the malfunction has beendetermined and corrected NORMAL PROCEDURES PREFLIGHT INSPECTION NOSE SECTION Air Conditioner Condenser CHECK SECURITY AND...

Page 299: ...racted and airplane is clear of all obstacles air conditioning system may be turned ori as desired SHUTDOWN Turn off air conditioner before engine shutdown PERFORMANCE CRUISEPERFORMANCE NOTE Using the power settings given in the PER FORMANCEsection with the air conditioner in operation Rangeand airspeed will decrease by approximately 5 due to the extension of the condenser to the flight extension ...

Page 300: ... and controlled by two internal stops in the motor two limit switches on the condenser the landing gear safety switch and a throttle limit switch The three retractable condenser positions are ground extension flight extension and retracted When the airplane is on the ground and the air conditioner is turned on the condenser extends to the ground exten sion lowest position below the fuselage bottom...

Page 301: ...ole The cabin air continues to circulate as described until the air conditioner is turned off After engine start the air conditioner may be turned on by actuating a three way toggle switch on the control console below the center of the upper subpanel Either a high or a low blower speed may be selected and the airflow can be distributed by moving the adjustable louvers up and down and from side to ...

Page 302: ...owever should a go around be necessary the application of full throttle will cause the throttle limit switch to shut down the compressor for maximum engine power and retract the condenser to the retracted position to minimize drag When the landing gear is retracted and or the throttle is retarded the compressor will resume operation and the condenser will return to the flight extension position Ap...

Page 303: ...F C C3YF lR or HIC C3YF lRF Blades B468 6R B468A 6R or F8l168A 6R Spinner A 2295 1 5 lbs Ii Station l Covcrnor e2011152or D2lo680 Pitch Settincs at 30 inch station J ov 12 0 Hich 32 0 Min Diameter Not over 80 inche not under 78 inches Engine Continento l I0 520 B I0 520 BA and I0 520 BB OR 2 Hartzell const Lnt speed t lo bladed pro eller 51 lbs Station l Hubs RHC C2YF lB or BtC C2YF lBF Bl 2 des 8...

Page 304: ...LANE FLIGHT MANUAL SUPPLEMENT for the FUEL SELECTOR VALVE STOP INSTALLATION BEECHCRAFT SERVICE INSTRUCTIONS NO 1248 GENERAL This document is to be attached to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the airplane is equipped with the Fuel Selector Valve Stop Installation which has been installed in accordance with BEECHCRAFT Service Instructions No 1248 This docu...

Page 305: ...e Brittain wing tip fuel system LIMITATIONS PLACARDS On Fuel Selector Panel LEFT RIGHTAND Lb_ OFF NOT IN SAME __Lh_ i7 POSITIONS ON ALL V BONANZAS and DEPRESS STOpl TURN HANDLE L TO OFF _J EMERGENCY PROCEDURES No Change 2of4 FAA Approved Issued March 1983 P N 36 590002 39 ...

Page 306: ...at is more nearly full On airplanes equipped with the fuel selector valve stop installation BEECHCRAFT Service Instructions No 1248 the pilot is cautioned to observe that the short pointed end of the handle aligns with the fuel tank position being selected The tank positions are located on the aft side of the valve The OFF position is forward and to the left An OFF position lock out feature has be...

Page 307: ...the handle counterclockwise from OFF to LEFT MAIN or RIGHT MAIN When selecting the LEFT MAIN or RIGHT MAIN fuel tanks position handle by sight and by feeling for detent If the engine stops because of insufficient fuel refer to the EMERGENCY PROCEDURES Section for the Air Start procedures Approved 4of4 W H Schultz Beech Aircraft Corporation DOA CE 2 FAA Approved Issued March 1983 PIN36 590002 39 ...

Page 308: ...CLOSED PLACARD THIS SUPPLEMENT IS APPLICABLE TO PILOT S OPERATING HANDBOOKS AND FAA APPROVED AIRPLANE FLIGHT MANUALS SEE NEXT PAGE FOR APPLICABILITY Airplane Serial Number __________ _ Airplane Registration Number ________ _ FAA Approved Beech Aircraft Corporation DOA CE 2 COPYRIGHT BEECH 1990 FAA Approved P N 58 590000 49 Issued December 1990 1 of 7 ...

Page 309: ...7B All 33 590009 13 CE 674 after CJ 129 after 33 590009 15 CE 290 thru CE 673 CJ 26 thru CJ 128 33 590027 3 All 35 590071 13 All 35 590072 9 All 35 590073 15 All 35 590094 7 All 35 590110 3 All 35 590110 11 B All 35 590113 3 All 35 590116 3 All 35 590118 23 0 9069 thru 0 9947 35 590118 29 0 9948 after 35 590118 31 B 0 7977 thru 0 9947 36 590002 17 E 927 thru E 2110 except E 1946 E 2104 36 590002 1...

Page 310: ...5 58TC 106 590000 5 58TC 58TCA 106 590000 19 FAA Approved P N 58 590000 49 Issued December 1990 A C SERIALS EA 242 EA 273 thru EA 388 except EA 326 EA 326 EA 389 after All TC 1 thru TC 501 except TC 350 TC 371 TH 773 thru TH 1395 except TH 1389 TH 1 thru TH 772 TH 1389 TH 1396 thru TH 1471 TH 1476 TH 1487 TH 1489 TH 1498 TH 1472 after except TH 1476 TH 1487 TH 1489 TH 1498 TE 1084 after TC 350 TE ...

Page 311: ...MODEL 58TC 58TCA 4 of 7 PART NUMBER A C SERIALS 106 590000 21 TK 147 TK 151 after FAA Approved P N 58 590000 49 Issued December 1990 ...

Page 312: ...rplane has been modified by installation of the Inside Cabin Door Handle With Open Closed Placard in accor dance with Beech Kit 35 5050 The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only as set forth below Users of the manual are advised to always refer to the supplement for possibly superseding information and...

Page 313: ...RMANCE No change WEIGHT AND BALANCE No change SYSTEMS DESCRIPTION DOORS WINDOWS AND EXITS CABIN DOOR The airplane has a conventional cabin door on the for ward right side of the fuselage and when closed the out side cabin door handle is spring loaded to fit into a re cess in the door to create a flat aerodynamically clean surface The door may be locked with a key To op n the door from the outside ...

Page 314: ...e CLOSED position When the door is properly locked the door latch handle is free to move approxi mately one inch in either direction NOTE When checking the door latch handle do not move it far enough to engage the door latch release mechanism Press firmly outward at the top rear corner of the door If any movement of the door is detected completely open the door and close again following the above ...

Page 315: ...sory Circulars 10 12 FAA General Aviation News 10 15 FAA Accident Prevention Program 10 15 Additional Information 10 16 General Information on Specific Topics 10 17 Maintenance 10 17 Hazards of Unapproved Modifications 10 19 Flight Planning 10 20 Passenger Information Cards 10 20 Stowage of Articles 10 21 Flight Operations 10 21 General 10 21 Preflight Inspection 10 21 Weight and Balance 10 22 Aut...

Page 316: ...36 Spins 10 36 Descent 10 38 Vortices Wake Turbulence 10 39 Takeoff and Landing Conditions 10 40 Medical Facts for Pilots 10 40 General 10 40 Fatigue 10 41 Hypoxia 10 41 Hyperventilation 10 43 Alcohol 10 43 Drugs 10 45 Scuba Diving 10 45 Carbon Monoxide and Night Vision 10 45 Decompression Sickness 10 46 A Final Word 10 47 10 2 May 1994 ...

Page 317: ...b Be thor oughly familiar with your airplane Know its limitationsand your own Maintain your currency or fly with a qualified instructoruntilyou are currentand proficient Practiceemer gency proceduresat safe altitudes and airspeeds prefer ablywith a qualifiedinstructorpilot untilthe requiredaction can be accomplishedwithoutreferenceto the manual Peri odicallyreviewthis safety informationas part of ...

Page 318: ...n and the other operating and maintenance manu als which accompany the airplane that FAA requirements for ratings certifications and reviewbe scrupulously com plied with and that you allow only persons who are properly licensed and rated and thoroughly familiar with the contents of the Pilot s Operating Handbook and FAA Approved Air plane Flight Manual to operate the airplane IMPROPER OPERATION OR...

Page 319: ...instructor until you are current Practice until you are proficient Preplan all aspects of your flight including a proper weather briefing and adequate fuel reserves Use services available weather briefing inflight weather and Flight Service Station Carefully preflight your airplane Use the approved checklist Have more than enough fuel for takeoff plus the trip and an adequate reserve Be sure your ...

Page 320: ... action can be accomplished without reference to the manual Keep your airplane in good mechanical condition Stay informed and alert fly in a sensible manner DON T Don t take off with frost ice or snow on the airplane Don t take off with less than minimum recommended fuel plus adequate reserves and don t run the tank dry before switching Don t fly in a reckless show off or careless manner Don t fly...

Page 321: ...zation of your airplane When the airplane was manufac tured it was equipped with one or more of the following placards Owner s Manual FAA Approved Airplane Flight Manual FAA Approved Airplane Flight Manual Supple ments Pilot s Operating Handbook and FAA Approved Air plane Flight Manual Beech has revised and reissued many of the early manuals for certain models of airplanes in GAMA Standard Format ...

Page 322: ...sions of BEECHCRAFT Safety Communiques to BEECH CRAFT Owner addresses as listed by the FAA Aircraft Reg istration Branch List and the BEECHCRAFT International Owner Notification Service List While this information is dis tributed by Beech Aircraft Corporation Beech can not make changes in the name or address furnished by the FAA The owner must contact the FAA regarding any changes to name or addre...

Page 323: ...uest may be made by using the owner notification request card furnished with the loose equipment of each airplane at the time of delivery or by a letter requesting this service referencing the specific airplane serial number owned Write to Supervisor Special Services Dept 52 Beech Aircraft Corporation P O Box85 Wichita Kansas 67201 0085 From time to time Beech Aircraft Corporation issues BEECHCRAF...

Page 324: ...t regulations The regulations are designed for your protection and the protection of your passengers and the public Com pliance is mandatory AIRWORTHINESS DIRECTIVES FAR Part 39 specifies that no person may operate a product to which an Airworthiness Directive issued by the FAA applies except in accordance with the requirements of that Airworthiness Directive AIRMAN S INFORMATION MANUAL The Airman...

Page 325: ... Icing Radio Phraseology and Technique Mountain Flying Airport Operations Wake Turbulence Vortices Clearances and Separations Medical Facts for Pilots Preflight Bird Hazards Departures IFR Good Operating Practices En route IFR Airport Location Directory Arrival IFR All pilots must be thoroughly familiar with and use the infor mation in the AIM ADVISORY INFORMATION NOTAMS Notices to Airmen are docu...

Page 326: ...iation bookstores or at FBO s These documents are subject to periodic revision Be certain the Advisory Circular you are using is the latest revision available Some of the Advisory Circulars of interest to pilots are 00 6 00 24 00 30 00 45 00 46 20 5 20 32 20 35 20 43 20 105 20 113 20 125 10 12 Aviation Weather Thunderstorms Rules of Thumb for Avoiding or Minimizing Encounters with Clear Air Turbul...

Page 327: ...Guide lines for the Conduct of the Biennial Flight Review 60 13 The Accident Prevention Counselor Pro gram 61 9 61 21 61 23 61 27 61 67 61 84 67 2 90 23 90 42 May 1994 Pilot Transition Courses for Complex Single Engine and Light Twin Engine Air planes Flight Training Handbook Pilot s Handbook of Aeronautical Knowl edge Instrument Flying Handbook Hazards Associated with Spins in Airplanes Prohibite...

Page 328: ...alance Handbook Maintenance and Handling of Air Driven Gyroscopic Instruments Use of Alternate Grades of Aviation Gaso line for Grade 80 87 and Use of Automotive Gasoline Noise Hearing Damage and Fatigue in General Aviation Pilots Unreliable Airspeed Indications Operational and Maintenance Practices for Emergency Locator Transmitters and Receivers Gyroscopic Instruments Good Operating Practices Im...

Page 329: ... specialists to each Flight Standards and General Aviation District Office to organize accident prevention program activities In addition there are over 3 000 volunteer airmen serving as accident prevention counselors sharing their technical expertise and professional knowledge with the general aviation commu nity The FM conducts seminars and workshops and dis tributes invaluable safety informatio...

Page 330: ...al Aviation Accident Prevention Program These can be obtained at FAA Offices Weather Stations Flight Service Stations or Airport Facilities Some of these are titled 12 Golden Rules for Pilots Weather or Not Disorientation Plane Sense Weather Info Guide for Pilots Wake Turbulence Don t Trust to Luck Trust to Safety Rain Fog Snow Thunderstorm TRW Icing Pilot s Weather Briefing Guide Thunderstorms Do...

Page 331: ...ed and promptly corrected Schedule your maintenance regularly and have your air plane serviced by a reputable organization Be suspicious of bargain prices for maintenance repair and inspections It is the responsibility of the owner and the operator to assure that the airplane is maintained in an airworthy condi tion and that proper maintenance records are kept Use only genuine BEECHCRAFT or BEECHC...

Page 332: ...essly disclaims any responsibility for malfunctions failures damage or injury caused by use of non BEECHCRAFT parts 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 ope...

Page 333: ...r Supple mental Type Certificates STC s Before installing an STC on your airplane check to make sure that the STC does not conflict with other STC s that have already been installed Because approval of an STC is obtained by the individual STC holder based upon modification of the original type design it is possible for STC s to interfere with each other when both are installed Never install an una...

Page 334: ...e track and stations and make a list for quick reference It is strongly recommended a flight plan be filed with Flight Service Sta tions even though the flight may be VFR Also advise Flight Service Stations of changes or delays of one hour or more and remember to close the flight plan at destination The pilot must be completely familiar with the performance of the airplane and performance data in ...

Page 335: ... utilized to provide space for seat displacement If hard solid objects are stored beneath seats the energy absorbing feature is lost and severe spinal injuries can occur to occupants Prior to flight pilots should insure that articles are not stowed beneath seats that would restrict seat pan energy absorption or penetrate the seat in event of a high vertical velocity accident FLIGHT OPERATIONS GENE...

Page 336: ...lling speed will be higher rate of climb the cruising speed and the range of the airplane at any level of fuel will all be lower than shown in the Performance section If an airplane is loaded so that the C G is forward of the for ward limit it will require additional control movements for maneuvering the airplane with correspondingly higher con trol forces The pilot may have difficulty during take...

Page 337: ...ibed in the Airplane Flight Manual Supplements Ensure a full understanding of the methods of engagement and disengagement of the autopi lot and trim systems Compare the descriptions and procedures contained in the Supplements to the actual installation in the airplane to ensure that the supplement accurately describes your instal lation Test that all buttons switches and circuit breakers function ...

Page 338: ...function from an electric trim system malfunction The safest course is to deactivate both Do not re engage either system until after you have safely landed Then have the systems checked by a qualified service facility prior to further flight Depending upon the installation on your airplane the follow ing additional methods may be available to disengage the autopilot or electric trim in the event t...

Page 339: ... FLT switch on the autopilot control ler if installed NOTE After the autopilot is positively disengaged it may be necessary to restore other electrical functions Be sure when the master switches are turned on that the autopilot does not re engage The above ways may or may not be available on your auto pilot It is essential that you read your airplane s AFM SUPPLEMENT for your autopilot system and ...

Page 340: ...p of the air plane Airplanes are designed so that flutter will not occur in the normal operating envelope of the airplane as long as the airplane is properly maintained In the case of any airplane decreasing the damping and stiffness of the structure or increasing the trailing edge weight of control surfaces will tend to cause flutter If a combination of those factors is suf ficient flutter can oc...

Page 341: ...ure which could create an increased trailing edge heavy control surface and flutter If an excessive vibration particularly in the control column and rudder pedals is encountered in flight this may be the onset of flutter and the procedure to follow is 1 IMMEDIATELLY REDUCE AIRSPEED lower the land ing gear if necessary 2 RESTRAIN THE CONTROLS OF THE AIRPLANE UNTIL THE VIBRATION CEASES 3 FLY AT THE ...

Page 342: ...e Airplane may be momentarily out of control Occupants are thrown violently against the belts and back into the seat Unsecured objects are tossed about Occupants require seat belts and occasion ally are thrown against the belt Unsecured objects move about Occupants may be required to use seat belts but objects in the airplane remain at rest Thunderstorms squall lines and violent turbulence should ...

Page 343: ...xcessive airspeed you run the risk of structural damage or failure on the other hand if your air speed is too low you may stall If turbulence is encountered reduce speed to the turbulent air penetration speed if given or to the maneuvering speed which is listed in the Limitations section of the Pilot s Oper ating Handbook and FAA Approved Airplane Flight Manual These speeds give the best assurance...

Page 344: ...ere downdrafts The prediction of wind shears is far from an exact science Monitor your airspeed carefully when flying near storms particularly on approach Be mentally prepared to add power and go around at the first indication that a wind shear is being encountered WEATHERRADAR Airborne weather avoidance radar is as its name implies for avoiding severe weather not for penetrating it Whether to fly...

Page 345: ...choes should be separated by at least 40 miles before you fly between them With weaker echoes you can reduce the distance by which you avoid them Above all remember this never regard any thunderstorm lightly Even when radar observers report the echoes are of light intensity avoiding thunderstorms is the best policy The following are some do s and don ts of thunderstorm avoid ance 1 Don t land or t...

Page 346: ...r shoulder harness and secure all loose objects 1o Plan and hold your course to take you through the storm in minimum time 11 To avoid the most critical icing establish a penetration altitude below the freezing level or above the level of 15 C 12 Verify that pitot heat is on and turn on carburetor heat or engine anti ice Icing can be rapid at any altitude and cause almost instantaneous power failu...

Page 347: ...s should not be taken as assurance that mountain wave turbulence will not be encountered A mountain wave downdraft may exceed the climb capability of your airplane Avoid mountain wave downdrafts VFR LOW CEILINGS If you are not instrument rated do not attempt VFR on Top or Special VFR flight or clearances Being caught above a solid cloud layer when an emergency descent is required or at destination...

Page 348: ...rpretations illusions result and may confuse the pilot s conception of the attitude and position of his air plane Under VFR conditions the visual sense using the horizon as a reference can override the illusions Under low visibil ity conditions night fog clouds haze etc the illusions pre dominate Only through awareness of these illusions and proficiency in instrument flight procedures can an airpl...

Page 349: ...hould not be made or it should be discontinued as soon as possible The result of vertigo is loss of control of the airplane If the loss of control is sustained it will result in an excessive speed accident Excessive speed accidents occur in one of two manners either as an inflight airframe separation or as a high speed ground impact and they are fatal accidents in either case All airplanes are sub...

Page 350: ... deactivated by interruption of circuits circuit breakers or fuses Compliance with this requirement is especially important in all high performance single engine airplanes during simulated engine out practice or stall dem onstrations because the stall speed is critical in all low speed operation of airplanes Training should be accomplished under the supervision of a qualified instructor pilot with...

Page 351: ... intentional spins are entered by delib erately inducing a yawing moment with the controls as the airplane is stalled Inadvertent spins result from the same combination stall plus yaw That is why it is important to use coordinated controls and to recover at the first indication of a stall when practicing stalls Always remember that extra alertness and pilot techniques are required for slow flight ...

Page 352: ...oidance is your best protection against an inadvertent spin MAINTAIN YOUR AIRSPEED In airplanes not certificated for aerobatics spins are prohib ited If a spin is entered inadvertently Immediately move the control column full forward and simul taneously apply full rudder opposite to the direction of the spin continue to hold this position until rotation stops and then neutralize all controls and e...

Page 353: ...tices The larger and heavier the airplane the more pronounced and turbulent the wakes will be Wing tip vortices from large heavy airplanes are very severe at close range degenerating with time wind and distance These are rolling in nature from each wing tip In tests vor tex velocities of 133 knots have been recorded Encounter ing the rolling effect of wing tip vortices within two minutes after pas...

Page 354: ...e friction Snow and ice covered runways are also hazardous The pilot should also be alert to the possibility of the brakes freezing Use caution when taking off or landing during gusty wind conditions Also be aware of the special wind conditions caused by buildings or other obstructions located near the runway MEDICAL FACTS FOR PILOTS GENERAL When the pilot enters the airplane he becomes an integra...

Page 355: ...system to let you know when you are not getting enough oxygen It is impossible to predict when or where hypoxia will occur during a given flight or how it will manifest itself Some of the common symptoms of hypoxia are increased breathing rate a light headed or dizzy sensation tingling or warm sensation sweating reduced visual field sleepiness blue coloring of skin fingernails and lips and behavio...

Page 356: ...equire or may require the use of supplemental oxygen should be thoroughly familiar with the operation of the airplane oxygen systems A preflight inspection of the system should be performed including proper fit of the mask The passengers should be briefed on the proper use of their oxygen system before flight Pilots who wear beards should be careful to ensure that their beard is carefully trimmed ...

Page 357: ...nd consciously slow your breathingrate until symptomsclear and then resumenor mal breathingrate Normalbreathingcan be aided by talk ing aloud ALCOHOL Common sense and scientific evidence dictate that you must not fly as a crew memberwhile underthe influenceof alcohol Alcohol even in small amounts produces among otherthings A dullingof criticaljudgement A decreasedsense of responsibility Diminished...

Page 358: ...bout one third of an ounce per hour Even after the body completely destroys a moderate amount of alcohol a pilot can still be severely impaired for many hours by hangover The effects of alcohol on the body are magnified at altitudes as 2 oz of alcohol at 18 000 feet produce the same adverse effects as 6 oz at sea level Federal Aviation Regulations have been amended to reflect the FAA s growing con...

Page 359: ...en simple home or over the counter remedies and drugs such as aspirin anti histamines cold tablets cough mixtures laxatives tranquil izers and appetite suppressors may seriously impair the judgment and coordination needed while flying The safest rule is to take no medicine before or while flying except after consultation with your Aviation Medical Examiner SCUBADIVING Flying shortly after any prol...

Page 360: ...itrogen bubble formation in body tissue as the ambient air pressure is reduced by climbing to higher alti tudes The symptoms are pain in the joints abdominal cramps burning sensations in the skin visual impairment and numbness Some of these symptoms are similar to hyp oxia The only known remedy for decompression sickness is recompression which can only be accomplished in an unpressurized airplane ...

Page 361: ...ems is even more remarkable Radar RNAV LORAN sophisticated autopilots and other devices which just a few years ago were too large and pro hibitively expensive for general aviation size airplanes are becoming increasingly commonplace in even the smallest airplanes It is thus that this Safety Information is directed to the pilot for it is in the area of the skill and proficiency of you the pilot tha...

Page 362: ...SectionX ft SafetyInformation SingleEngine Piston THIS PAGE INTENTIONALLY LEFT BLANK 10 48 May 1994 ...

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