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Beechcraft Bonanza E33, Pilot'S Operating Handbook And Faa Approved Airplane Flight Manual

The Beechcraft Bonanza E33 is a renowned single-engine aircraft, ideal for pilots seeking an exhilarating flying experience. Enhance your flying knowledge with the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. Download this comprehensive manual for free from manualshive.com, ensuring a safe and enjoyable flight every time.

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Summary of Contents for Bonanza E33

Page 1: ...THE PILOT DURING ALL fLIGHT OPERATIQNS THIS HANDBOOK INCLUDES THE MATERIAL JAEQUIRED TO BE FURNISHED TO THE PILOT BY FAB PART 23 Mfr s Seri11I Ne Registration Ne FAA APpro11ed by W H SCHULTZ BEECH AIA Cf AFT CORPORATION DOA CE 2 THIS HANDBOOK SUPERSEDES A l BEECH ED OWNERS MANUALS FLIGHT MANUALS A ND Cfl ECK L ISTS ISSUED FOR THIS AIRPLArte WtT J m Of ffl 1 APPROVED AIRPLANE Flt GHT M NUAI SUPPfEi...

Page 2: ...l USLIS IED llY COMMERCIA L PROIJUCT SUPl Ol T J BEECH AIRCRAFT CORPORATION WICHTTA KANSAS 67201 U S A ...

Page 3: ...e Title Page A Page 81 I Update a b Page Add Warning 2 17 Add Emergency Exit placard 3 2 Update Table of Co111tents 3 12 3 13 Re11ise Emergency Exits and Shift Material 4 11 Revise Before Takeoff 7 1 7 2 Update Table of Contents 7 20 Revise Openable Cabin Windowi and add Emergency Exits 8 29 8 30 Revise Cleaning Exterior Painted 8 JOA 8 308 Surfaces 8 31 1 B1 Page A ...

Page 4: ......

Page 5: ...Of REVISIONS ORIGINAL A SEPTEMBER 1977 REISSUE B AUGUST 1982 PAGE DESCRIPTION Of REVISION Titie Page Logo Page Page A a thru b 1 1 thru 1 20 2 1 thru 2 28 3 1 thru 3 14 4 1 thru 4 20 5 1 thru 5 32 6 1 thru 6 22 7 1 thru 7 40 8 1 thru 8 58 Section 9 See log of Supplements 10 1 thru 10 67 March 1981 1 B Page A ...

Page 6: ......

Page 7: ...s 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 BEECHCRAFT or BEECHCRAFT approved parts obtained from BEECHCRAFT approved sources in connection with the maintenance and repair of Beech airplanes Genuine BEECHCRA...

Page 8: ...y render the part cornponent or structural assembly even though originally manufactured by BEECHCRAFT unsuit able and unsafe for airplane use BEECHCRAFT expressly disclaims any responsibility for rnalfunctions failures damage or injury caused by use of non BEECHCRAFT approved parts TABLE OF CONTENTS SECT ON 1 General SECTION 2 Limitations SECTION 3 Emergency Procedures SECTION 4 Normal Procedures ...

Page 9: ...ew 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 1 2 Cabin And Entry Dimensions 1 1 2 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 Airpiane Performance and Flight Planni...

Page 10: ...Section 1 General 1 2 BEECHCRAFT Oebonair C33 Bonanza E33 and F33 INTENTIONAllV LEFT BLANK August 1982 ...

Page 11: ...ted according to the Pilot s Operating Handbook and FAA Approv1ed Airplane Flight Manual andjor placards located in the airplane As a further rerninder the owner and operator of this airplane should also be farniliar with the Federal Aviation Regulations applicable to the operation and rnaintenance of the airplane and FAR Part 91 General Operating and Flight Rules Further the airplane rnust be ope...

Page 12: ...Handbook is designed to maintain documents necessary for the safe and efficient Operation of the BEECHCRAFT Debonair Bonanza The handbook has been prepared in loose leaf form for esse in maintenance and in a convenient size for storage The handbook has been arranged with quick reference tabs imprinted with the title of each section and contains ten basic divisions Section 1 General Section 2 Limit...

Page 13: ...ay not be designated as such in every case The following information may be provided to the holder of this manual automatically 1 Original issues and revisions of Class 1 and Class II Service lnstructions 2 Original issues and revisions of FAA Ap proved Airplane Flight Manual Supple ments 3 Reissues and revisions of FAA Approved Airplane Flight Manuals Flight Hand books Owner s Manuals Pilot s Op ...

Page 14: ...ealer or refer to the latest revision of BEECHCRAFT Service lnstructions No 0250 010 BEECH AIRCRAFT CORPORATION EX PRESSLY RESERVES THE RIGHT TO SUPER SEDE CANGEL AND OR DECLARE OB SOLETE WITHOUT PRIOR NOTICE ANY PART PART NUMBER KIT OR PUBUCATION REF ERENCED IN THIS HANDBOOK The owner operator should always refer to all supplements whether STC Supplements or Beech Suppl ments for possible placard...

Page 15: ...rtion 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 numbec 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 u...

Page 16: ...cordance with the descriptive listing NOTE Upon receipt of anew 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 Supplementa...

Page 17: ...nair C33 Bonanza E33 and F33 WING AREA 177 6 sq ft Section 1 General i r F J 0 1_ 1 I r 1 i 1 jlt j 3 ______J 26 8 i t _ _ r 4_ j Ll __ f CLJ ____ OD __ __ s J 6 6 r_ _L_I r l _J t 7 5 min 84 DIAMETER August 1982 1 9 ...

Page 18: ... F33 GROUNID TURNING ClEARANCE Radius for Wing Tip 26 ft 4 in 12 ft 2 in 5 ft 1 in 14 ft 8 in 1Radius for Nose Wheel Radius for Inside Gear Radius for Outside Gear TURNING RADI Af E CALCULATED USING FULL STEER ING ONE BRAKE AND PARTIAL POWER 1 10 August 1982 ...

Page 19: ... 848 0 blades or Optional on C33 only Hartzell constant speed three blade 80 inch diameter pro peller using a Hartzell PHC A3VF 4 hub with V8433 4R blades FUEI NOTE Other propellers are approved but not installed as original equipment These are listed in the FAA Aircraft Specification 3A15 or approved by Supplemental Type Certificate Aviation Gasoline 80 87 red minimum grade or alternate grades 10...

Page 20: ...uctural Limit Maximum Weight in Baggage Cornpartment 270 lbs CABIN AND ENTRY DIMENSl ONS Length 6 ft 11 in Height 4 ft 2 in Width 3 ft 6 in Cabin Door 37 in wide by 36 in high BAGGAGE SPACE AND ENTRY DIMENSIONS Cornpartment Volume 16 5 cu ft With Utility Shelf 22 4 cu ft Door Width Minimum 18 5 in Door Height Minimum 22 5 in SPECIFIC LOADINGS Maximum Take Off Weight Wing Loading 17 2 lbsßq ft Powe...

Page 21: ...airspeed indicator when corrected for instrument error IAS values published in this handbook assume zero instrument error KCAS Calibrated Airspeed expressed in knots KIAS lndicated Airspeed expressed in knots TAS True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude temperature and compressibility VA Maneuvering Speed is the maximum speed ...

Page 22: ...ximum S tructural Cruising Speed is the or Vc speed that should not be exceededl except in smooth air and then only with caution Vso Vy 1 14 Stalling Speed or the minimum steady flight speed at which the airplane is controllable Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration Best Angle of Climb Speed is the airspeed which delive...

Page 23: ...oot 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 actuallv 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 pr...

Page 24: ...ing not imited 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 Setti ngs are reflected by readings on the manifold pressure gage This control requests the propeller governor to maintain engine propeller rpm at a selected va...

Page 25: ...NING TERMINOLOGY Climb Gradient Demonstrated Crosswind Veiocity MEA Route Segment August 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 demonstrated crosswind 11elocity is the veJocity of the crosswind compommt for which adequate control of the airplane during takeott and landing was actually dernonstrated durin...

Page 26: ...s of distance from the reference datum The horizontal distance from the ref erence datum to the center of gravity C G of an item The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify bal ance calculations by reducing the number of digits The point at which an airplane would balance if suspended lts distance from the reference datum is found by ...

Page 27: ...e Empty including unusable fuel full Weight operating fluids and full oil Basic Standard empty weight plus Empty optional equipment Weight Payload Weight of occupants cargo and baggage Useful Difference between take off weight Load or ramp weight if applicable and basic empty weight Maximum Maximum weight approved for ground Ramp maneuvering lt includes weight of Weight start taxi and run up fuel ...

Page 28: ... exclusive of usable fuel The weight 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 August 1982 ...

Page 29: ...el Grades 2 5 Oil Specifications 2 5 Propeller Specifications 2 6 Power Plant Instrument Markings 2 7 Miscellaneous Instrument Markings 2 8 Weight Limits 2 8 Center of Gravity Limits 2 9 Maneuver Limits 2 9 Appro11ed Maneuvers 2 9 Flight Load Factors 2 10 Minimum Flight Crew 2 10 Kinds of Operation Limits 2 10 Fuel 2 11 Seating 2 11 Piacards 2 12 Required Equipment for Various Condition s of Fligh...

Page 30: ...Sectionll Umitations BEECHCRAFT Debonair C33 Bonanza E33 and F33 The limitations included in this section have been approved by the Federal Aviation Administration 2 2 August 1982 ...

Page 31: ...th caution Maneuvering 128 147 128 147 Do not make full VA or abrupt control mo11ements above this speed Maximum 0104 120 104 120 Do not extend Flap 0113 flaps or operate Extensiory 130 116 134 with flaps ex Extended 122 tended above VFE 140 125 144 this speed Maximum 143 165 144 166 Do not extend Landing Gear retract or operate Operating 152 with landing gear Extended 175 153 176 extended above V...

Page 32: ...162 197 186 227 ICI c D Red Une 195 225 197 The Airspeed lndicator is marked in CAS values 227 SIGNIFICANCE Full Flap Operating Range Serials CD 814 thru CD 1118 except CD 982 See 3A15 Spec Serials C0 1119 thru CD 1199 Serials CD 1200 thru CD 1254 Normal Operating Range Operate with caution only in smooth air Maximum speed for ALL operations m 0 J c g l Cll 0 t s 0 s t 11 c m111 m w n w 0 i 111 s ...

Page 33: ... Pressure Minimum Maximum Fuel Pressure 30 psi 80 psi Minimum 1 5 psi Maximum 17 5 psi Mixture Set per leaning instructions on performance charts FUEL GRADES Aviation Gasoline 8Ql87 red minimum grade or alternate grades 100LL blue or 100 green See Engine Manufacturer s Bulletin Oll SPECIFICATIONS Ashless dispersant oils must mee t Teledyne Continental Motors Corporation Specification MHS 246 Refer...

Page 34: ...w 12 High not under 29 2 or Optional on C33 only Hartzell constant speed three blade propeller Hub Hartzell PHC A3VF 4 2 6 Blades V8433 4R Diameter Maximum 80 in Minimum 78 114 in Pitch settings at 30 in sta Low 1O S 0 2 High not under 32 NOTE Other propellers are approved but not installed as original equipment These are listed in the FAA Aircraft Specification 3A15 or approved by Supplemental Ty...

Page 35: ...ng Range Green Are 30 to 60 psi Maximum Pressure Red Radial 80 psi TACHOMETER Operating Range Green Are 2000 to 2600 rpm Maximum RPM Red Radial 2600 rpm CYLINDER HEAD TEMPERATURE Operating Range Green Are 200 to 460 F 193 to 238 C Maximum Temperature Red Radial 460 Fj238 C MANIFOLD PRESSURE Operating Range Green Are 15 to 29 6 in Hg Maximum Red Radial 29 6 in Hg FUEL FLOW Minimum Red Radial 1 5 ps...

Page 36: ...PRESSURE E33 F33 Minimum Red Radial 3 5 in Hg Operating Range Green Are 3 5 to 5 5 in Hg Maximum Red Radial 5 5 in Hg or Operating Rang Green Are 4 3 to 5 9 in Hg FUEL QUANTITY Yellow Band 44 gallon system Yellow Band 74 galfon system WEIGHT LIMITS E to 1 2 full E to 3 8 full Maximum Ramp Weight 3060 lbs Maximum Take off and Landing Weight 3050 lbs Zero Fuel Weight No Strueturat Limitation Maximum...

Page 37: ...th is 65 3 inches MANEUVER LIMITS This is a utility category airplane Spins are prohibited No acrobatic maneuvers are approved except those listed below Maximum slip duration is 30 seconds for airplanes with baffledmain fuel cells in both wings and 20 seconds for airplanes with unbaffled main fuel cells in either wing APPROVED MANEUVERS 3050 POUNDS MANEUVER ENTRY SPEED CAS Chandelle 128 kts 147 mp...

Page 38: ...irplane is approved for the following type operations when the required equipment is installed and operational as defined herein 1 VFR day and night 2 IFR day and night 3 FAR 91 operations when all pertinent limitations and performance considerations are complied with WARNING FUGHT IN ICING CONDITIONS IS PROHIBITED 2 10 NOTE Refer to REQUIRED EOUIPMENT FOR VARIOUS CONDnrlONS OF FUGHT at the end of...

Page 39: ...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 40: ...d F33 1rb _ 00 NOT TAKE OFF IF FUEL QUANTITY GAGES INDICATE IN YELLOW BAND DR WITH LESS t l L THAN 13 GALLONS IN EACH MAIN TANK _J Standard 44 Gallon Usabfe System OFFÜ LHTANK 0 22 GAL 0 RH TANK 22 GAL Optional 74 Gallon Usable Fuel System 2 12 OFFÜ LHTANK 0 37 GAL O RHTANK 37 GAL August 1982 ...

Page 41: ...CY LANDING GEAR INSTRUCTIONS TO EXTEND ENGAGE HANDLE IN REAR OF FRONT SEAT AND TURN COUNTERCLOCKWISE AS FAR AS POSSIBLE 50 TURNSI Above Landir1g Gear Mechanical Position lndicator When Winter Baffle Are lnstalled NOTICE REMOVE WINTER BAFFLES WHEN OAT EXCEEDS 70 F L _J On Left Subpanel C33 E33 VENT SHUTOff PULL TO CLOSE August 1982 2 13 ...

Page 42: ...ofs F33 r IN CJ 1SE OF ENGINE FIRE PULL FIREWALL AIR CONTROL TO CLOSE On Inner Side Of Baggage Compartment Door BAGGAGE COMPARTMENT LOAD IN ACCORDANCE WITH AIRPLAl llE FUGHT MANUAL MAXIMUM STRUCTURAL CAPACITY 270 POUNDS On Storm Window C33 and E33 only CAS r CAUTION 00 NO T OPEN ABOVE 145 MPH 126 KNOTS L _J 2 14 August 1982 ...

Page 43: ...VED AIRPLANE FLIGHT MANUAL INTENTIONAL SPINS PROHIBITED NO ACR08ATIC MANEUVERS APPROVED U CEPT THOSE LISTED IN THE AIRPLANE FLIGHT MANUAL 1 CD 1200 and After AIR SPEED LIMITATION MAXIMUM SPEED WITH LANDING GEAR EXTENDED NORMAL 176 MPH 162 KTSI MAXIMUM DESIGN MANEUVERING SPEED 147 MPH 1128 KTSl UTILITY CATEGORY AIRPLANE Of ERATE IN ACCORDANCE WITH FAA APPROVED AIRPl ANE FLIGHT MANUAL INTENTIONAL SP...

Page 44: ...le THROTTlE PUSH OPEN ONW OFFO PROPEUER PUSH HI RPM AUX FUEL PUMP OPERATION TAKE OFF AND LAND WITH AUX FUEL PUMP OFF EXCEPT IN CASE OF LOSS OF FUEL PRESS FUEL MIX PUSH RfCH ALTERNATE AIR PULl AND RELEASE On left Side of Control Console Support 2 16 GENERATOR CIRCUIT BREAKER PUSH TO RESET August 1982 ...

Page 45: ... in both wings TURNING TYPE TAKEOFFS ANDl TAKEOFF IMMEDIATELY FOLLOWING FAST TAXI TURN PROHIBITED AVOID PROLONGED SLIPS 20 SECONDS OR 1 MORE WITH FUEL TANKS LESS THAN HALF FULL _j Below Lett and Right Middle Windows alter compliance with BEECHCRAFTService lnstructions 1241 E33 andF33 with Optional Openable Cabin Windows EMERGENCY EXIT LIFT LATCH PULL PIN PUSH WINDOW OUT Revised March 1983 2 17 ...

Page 46: ...ious flight conditions the airplane could not be flown unless all equiprnent was operable With appropriate limitations the operation of every system or component installed in the airplane is not necessary when the remaining operative instruments and equipment provide for continued safe operation Operation in accordance with limitations established to maintain airworthiness can permit continued or ...

Page 47: ...y 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 FUGHT IN ICING CONDITIONS IS PRO HIBITED LEGEND Nurnbers refer to quantities required to be operative for a specified condition lndicates that the item may be inoperative for the specified condition Refer to the RE M...

Page 48: ... 23 COMMUNICATIONS VHF communications system ATA 100 CHAPTER 24 ElECTRICAl POWER Battery DC alternator generator VFR Day VFR Night FR Day FR Night Remarks andI or Exceptions Per FAR 91 Per FAR 91 1 1 1 1 1 1 1 1 g 1 c cn 3 Cl l at ö t 1 0 1 III l o m ai m w Cl w 0 1 III i a ww Tl ww t ...

Page 49: ...lder harness Emergency locator trans mitter ATA 100 CHAPTER 26 FIRE PROTECTION Portable fire extinguisher 1 1 1 1 1 1 Per Person or Per FAR 91 Pilot and copilot if installed 1 Per FAR 91 Optional mom 0 III m i c r m Ql 0 i3 i I mn ll w c d w w Tl Cl Tl w w 3 IZI n 0 0 i i III I 1 1 ...

Page 50: ...NTROLS Elevator trim tab indicator Flap position indication lights C33 Dial E33 F33 Stall warning VFR Day VFR Night FR Day FR Night Remarks andlor Exceptions 1 1 1 1 2 2 2 2 1 1 1 1 1 1 1 1 a I 0 1 III 1 c Cll 3 Cll 8 0 1 II 1 c m 11 c i IT m wo 0 lll 1 r III 1 1 n w w Tl w w f ...

Page 51: ...ven fuel pump Fuel quantity indicator Fuel flow indicator ATA 100 CHAPTER 30 ICE AND RAIN PROTECTION Emergency static air source Pitot heater 1 1 1 2 2 1 1 1 1 1 1 2 2 1 1 Optional Per FAR 135 1 1 Optional c 0 CD m er m lll 0 i3 il i lll m n o Ww io Ww n lll 1 Cl w r 3 Cl lll 6 s i i ...

Page 52: ...LANOING GEAR Landing gear motor Landing gear position lights Landing gear warning horn VFR Day VFR Night FR Day FR Night Remarks andlor Exceptions 1 1 1 1 4 4 4 4 2 on the C33 and E33 1 1 1 1 m 0 1 1111 i c cn 3 ai n Q i 0 i 1 11 r c m11 m wer 0 w 0 c 1111 i i Q D w w w w 4 ...

Page 53: ...otating beacon Position light ATA 100 CHAPTER 34 NAVIGATION INSTRUMENTS Altimeter Airspeed indicator Vertical speed Magnetic compass 1 1 1 1 1 3 3 1 1 1 1 1 1 1 1 1 Lights must be operative Per FAR 91 Per FAR 135 ai om 0 CD m er m I 0 0 a c III O mo i i c c w w n III 1 c w w r 3 1 III g ö r t ...

Page 54: ...icator Turn Coordinator Oirectional gyro Clock Transponder Navigation equipment ATA 100 CHAPTER 35 OXYGEN Oxygen system VFR Oay VFR Night IFR Day IFR Night Remarks and or Exceptions 1 1 1 1 1 1 1 1 Per FAR 91 Per FAR 91 Per FAR 91 m 0 1 s c tn 3 CD 3 ao 1 0 1 fjl o m e1 m wgn w 1 c n a D n n w w n ww ...

Page 55: ...TER 37 VACUUM Vacuum system for instrument air Vacuum gage ATA 100 CHAPTER 77 ENGINE INDICATING INSTRUMENTS Engine tachometer indicator Exhaust gas temperature indicator Manifold pressure indicator 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 Optional 1 ClllCClll oem er m on i c n cn ww w t Q w w c 3 Ul S n et g g ...

Page 56: ...T ATA 100 CHAPTER 79 ENGINE Oll INSTRUMENTS Oil pressure indicator Qil temperature indicator VFR Day VFR Night FR Day FR Night Remarks andlor Exceptions 1 1 1 1 1 1 1 1 m 0 J J c Cl 3 III 0 e 0 J Cll SI c m111 m w c r n wo x III J a nO WW l I IJ w ...

Page 57: ...wer 3 5 Air Start Procedure 3 5 Engine Fire 3 6 In Aight 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 Generator Alternator Out Procedure 3 8 Engine Instrument Malfunction 3 9 Unscheduled Electric Elevator Trim 3 9 Landing Gear Manual...

Page 58: ...F33 Emergency Procedures TABLE OF CONTENTS Continued SUBJECT PAGE lnduction System Blockage 3 11 Emergency Static Air Source System 3 11 Emergency Exits 3 12 Unlatched Door in Flight 3 12 Spins 3 13 Emergency Speed Reduction 3 13 3 2 Revised March 1983 ...

Page 59: ...this section are indicated airspeeds AS The following information is presented to enable the pilot to form in advance a definite plan of action for coping with the most probable emergency Situations which could occur in the operation of the airplane Where practicable the emergencies requiring immediate corrective action are treated in check list form for easy reference and familiari zation Other s...

Page 60: ...the following 1 Fuel Se ector 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 a nd 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 inductio1n system ff No Restart 1 Se...

Page 61: ...ired c Auxiliary Fuel Pump OFF if performance does not improve in a few moments 2 Fuel Quantity lndicator CHECK for fuel supply in tank being used 3 Alternate Air T handle PULL AND RELEASE II tank being used is empty Fuel Tank Selector Valve SELECT OTHER FUEL TANK feel for detent and check visually AIR START PROCEDURE a Fuel Selector Valve SELECT TANK MORE NEARLY FULL check to feel detent b Thrott...

Page 62: ...ntrol PULL TO CLOSE 2 Mixture IDLE CUT OFF 3 Fuel Selector Valve OFF 4 Battery Generator Alternator Switches OFF Extending the landing gear can be accomplished manually if desired 5 Do not attempt to restart engine ON THE GROUND 1 Mixture IDLE CUT OFF 2 Fuel Selector Valve OFF 3 Battery Generator Alternator and Magnete Switches OFF 4 Extinguish with Fire Extinguisher MAXIMUM GLIDE CONFIGURATION 1 ...

Page 63: ...oach 1 Airspeed 80 kts 92 mph 2 Fuel Selector Valve OFF 3 Mixture IDLE CUT OFF 4 Flaps AS REQUIRED 5 Landing Gear DOWN OR UP DEPENDING ON TERRAIN 6 Battery and Generator Altemator Switches OFF LANDING GEAR RETRACTED WITH POWER lf possible choose firm sod or foamed runway Make a normal approach using fiaps as necessary When you are sure of making the selected landing spot 1 Throttle CLOSED 2 Mixtur...

Page 64: ...enerator alternator will place the entire electrical operation of the aircraft on the battery Failure may be indicated by the ammeter When a failure occurs in flight all non essential electrical load should be discontinued to conserve the battery life ALTERNATOR OVERVOLTAGE lf an alternator overvoltage condition occurs in flight 1 Battery Switch and Alternator Switch OFF MO MENTARILY THEN ON this ...

Page 65: ...wer settings full rich mixtures may result in poor engine opera tion Adjust the rnixture for srnooth 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 breaker 3 Elevator Trim ON OFF Switch On Instrument Panel OFF...

Page 66: ...the landing gear only DO NOT ATTEMPT TO RETRACT THE GEAR MANUALLY 5 lf electrical system is operative check landing gear position lights and warning horn check LOG GEAR INDICATOR and LOG GEAR WARNING circuit breakers engaged 6 Check mechanical landing gear indicator DOWN 7 Handcrank DISENGAGE Always keep it stowed when not in use 3 10 WARNING Do not operate the landing gear electrically with the h...

Page 67: ...on air door becomes stuck in the closed position it can be opened by pulling and releasing the T handle located directly below the propeller control knob This T handle is placarded ALTERNATE AIR PULLAND RELEASE EMERGENCY STATIC AIR SOURCE SYSTEM THE EMERGENCY STATIC AIR SOURCE SHOULD BE USED FOR CONDITIONS WHERE THE NORMAL STATIC SOURCE HAS BEEN OBSTRUCTED When the airplane has been exposed to moi...

Page 68: ...ystem is not needed EMERGENCY EXITS E33 F33 WITH OPTIONAL OPENABLE CABIN WINDOWS Emergency exits provided by the openable window on each side of the cabin may be used for egress in addition to the cabin door An emergency exit placard is installed below the left and right middle windows To open each emergency exit 1 Lift the latch 2 Pull out the emergency release pin and push the window out UNLATCH...

Page 69: ...neutraiize all controls and execute a smooth pullout Ailerons should be neutral and throttle in idle position at all times during recovery EMERGENCY SPEED REDUCTION In an emergenc y the landing gear may be used to create additional drag Should disorientation occur under in strument condittions the lowering of the landing gear will reduce the tendency for excessive speed build up This procedure wou...

Page 70: ...J Sectionlll Emergency Procedures BEECHCRAFT Debonair C33 Bonanza E33 and F33 INTENTIONALLY LEFT BLANK 3 14 August 1982 ...

Page 71: ... Using Auxiliary Power Unit 4 8 Starting 4 8 After Starting and Taxi 4 10 Before Takeoff 4 10 Takeott 4 12 Climb 4 12 Cruise 4 12 Leaning Using the Exhaust Gas Temperature lndicator 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...

Page 72: ... BEECHCAAFT DebonairC33 Bonanza E33 and F33 TABLE OF CONTENTS Continued SUBJECT PAGE After Using 4 18 Heating and Ventilation 4 18 Cold Weather Operation 4 19 lcing Conditions 4 20 Engine Break in Information 4 20 4 2 August 1982 ...

Page 73: ...tration Balked Landing Landing Approach Maximum Demonstrated Crosswind PREFUGHT INSPECTION 68 kts 78 mph 74 kts 85 mph 90 kts 104 mph 74 kts 85 mph 104 kts 120 mph 128 kts 147 mph 70 kts Bl mph 70 kts Bl mph 17 kts 20 mph 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 Co...

Page 74: ...AGE a Control Surfaces CHECK b Tie Down REMOVE c Position Light CHECK BEECHCRAFT Debonair C33 Bonanza E33 and F33 d Cabin Air lntake CHECK E33 F33 4 LEFT FUSELAGE a Static Pressure Button UNOBSTRUCTED b All Antennas CHECK 4 4 August 1982 ...

Page 75: ...lntake CHECK e Tie Down and Chocks REMOVE 7 LEFT LANDJNG GEAR a Wheel Weil 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 Engine Oil CHECK See Servicing Section 8 Cap and Dipstick SECURE b Left Cowl SECURE c Propeller CHECK General Condition Nicks etc d Landing Light CHECK e Wheel Weil Doors Tire and Strut CHECK f lnduct...

Page 76: ...p SECURE 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 POSITION AND LOCK Seat Backs UPRIGHT 2 Seat Belts FASTEN 3 Parking Brake SET 4 All Avionics OFF 5 Circuit Breakers IN 6 Landing Gear Handle DOWN 7 Flaps UP 8 light Switches As required 9 Electric Elevator Trim Switch OFF lf instal...

Page 77: ...d system Exer cise care to avoid reversed polarity Be sure to con nect 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 ter minal 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 being supplied when the co...

Page 78: ... Unit OFF after engine has been started 8 Auxiliary Power Unit DISCONNECT 9 Generator Alternator Switch ON STARTING CAUTION Vernier type engine controls should not be rotated clockwise after being advanced to the full forward pc1sition 1 Mixture FULL RICH 2 Propeller HIGH RPM 3 Throttle Approximatefy 1 2 inch open NOTE lf the engine is hot and the ambient tempera ture is 90 F or above place mixtur...

Page 79: ...tch START position d As engine fires reduce throttle to IDLE and advance the mixture control to FULL AICH NOTE During hot starts the Auxiliary Fuel Pump is turned on momentarily after starting to purge system then turned off 9 Throttle 1000 to 1200 rpm 10 Oil Pressure CHECK 11 External Power if used DISCONNECT Battery and Generator Alternator Switches ON 12 All Engine lndicators CHECK CAUTION The ...

Page 80: ...200 RPM until oil temperature reaches 75 F 24 C BEFORE TAKEOFF 1 Parking Brake SET 2 Seat Belts and Shoulder Harnesses CHECK NOTE All reclining seats must be in the upright posi tion during takeoff 3 Avionics CHECK 4 Engine Instruments CHECK 5 Flight Instruments CHECK AND SET 6 Ammeter CHECK for stabilized indication between 0 and 25 of full charge at 1000 to 1200 rpm 7 Auxiliary Fuel Pump CHECK O...

Page 81: ... 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 1 TRAVELAND FREEDOM OF MOVEMENT 15 Mixture FULL AICH or as required by field elevation 16 Brakes RELEASED 17 Instruments CHECK Make final check of manifold pressure fuel f...

Page 82: ...3 Landing Gear RETRACT when positive rate of climb is established and insufficient runway remains for landing 4 Airspeed ESTABUSH DESIRED CLIMB SPEED when clear of obstacles CLIMB Maximum Continuous Full throttle 2600 rpm Cruise Climb 25 in Hg or full throttle 2500 rpm 1 Engine Temperatures MONITOR 2 Power SET AS DESIRED 3 Mixture SET FUEL FLOW CRUISE See Cruise Charts in PERFORMANCE Section 1 Pow...

Page 83: ...ean the mixture and note the point on the indicator that the temperature peaks and starts to fall a CRUISE LEAN MIXTURE lncreases the mix ture until the EGT shows a drop of 25 F below peak on the rich side of peak b BEST POWER MIXTURE lncrease 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 84: ...NOTE All reclining seats must be in the upright posi tion during landing 2 Fuel Selector Valve SELECT TANK MORE NEARLY FULL 3 Mixture FULL RICH or as required by field elevation 4 Landing Gear DOWN and CHECK Observe maximum extension speed 5 landing light AS REQUIRED 6 Flaps DOWN Observft maximum extension speed 7 Airspeed ESTABLISH LANOING APPROACH SPEED 8 Propeller HIGH RPM 9 Electric Elevator T...

Page 85: ...4 Flaps UP AFTER LANDING 1 Landing Light AS REQUIRED 2 Flaps UP 3 Trim Tab SET TO 0 SHUTDOWN 1 Brakes SET 2 Electrical and Radio Equipment OFF 3 Throttle CLOSE 4 Mixture IDLE CUT OFF 5 Magneto Stan Switch OFF after engine stops 6 Battery and Generator Alternator Switches OFF 7 Control Lock INSTALL if conditions warrant 8 lnstall wheel chocks and releasE1 brakes if the airplane is to be left unatte...

Page 86: ... 3 Multiply oxygen duration in minutes by percent of full bottle EXAMPLE People 5 Gage Pressi ire 1500 psig Oxygen Availabfe from chart 80 Cylinder Capacity full 49 cu ft Attitude planned flight 15 000 ft Full Bott e Dmation from chart 149 min Duration 80 full 119 min 4 16 OXYGEN AVAllABLE WITH PARTIAllY FULL BOTTlE 50 0 ttt 1ttttl l tttttt1 ttttl 0 f i oj W Plool a i i 0 50 100 CAPACITY August 19...

Page 87: ... by the fit of the oxygen mask make cer tain the masks fit properly and are in good condition OXYGEN DURArJON CHART full Bottle Duration in minutes at the following altitudes Bottle Persons 12 500 15 000 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 NOTE To calculate duration times for bottle capaci ties other than 49 cu ft use 77 38...

Page 88: ...CK 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 iet 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 Se...

Page 89: ...ight 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 ANO MAINTENANCE Sec tion Always pull the propeller through by hand opposite the direction of rotation several times to clear the engine and limber up the cold heavy oil before u...

Page 90: ...oil lines oil cooler leaks or the possibility of congealed oil NOTE lt is advisable to use external power for start ing in cold weather Ouring warm up monitor engine temperatures closely since it is quite possible to exceed the cylinder head temperature limit in trying to bring up the oil temperature Exercise the propeller several times to remove cold oil from the pitch change mechanism The propel...

Page 91: ...5 11 Airspeed Calibration Emergency System 5 12 Altimeter Correction Emergency System 5 13 Temperature Conversion 5 14 ISA Conversion 5 15 Stall Speeds Power ldle 5 16 Wind Components 5 17 Take Off Distance 5 18 Climb 5 19 Time Fuel and Distance to Clirnb 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 C...

Page 92: ...onair C33 Bonanza E33 end F33 TABLE OF CONTENTS Continued SUBJECT PAGE Range Profile 74 Gallons 5 28 Range Profile 44 Gallons 5 29 Endurance Profile 14 Gallons 5 30 Endurance Profile 44 Gallons 5 31 landing Distance 5 32 5 2 August 1982 ...

Page 93: ... 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 cit 11 500 feet ROUTE MAGNETIC DIST SEGMENT COURSE NM DEN COS rn1 55 COS PUEI 1153 40 PUEl TBE 1 34 74 TBE DHT 13...

Page 94: ...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 Attitude at DEN 29 92 29 60 32 in Hg The pressure altitude at DEN is 320feet 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 planning...

Page 95: ... read from either the cruise power setting table for 75 percent or 65 per cent maximum continuous power The temperatures for cruise are presented for a standard day ISA 20 C 36 F above a stan lard 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 vatues which have been adjusted for the c ompressibility effects IOA...

Page 96: ... TAS FEET IN HG GPH KNOTS IN HG GPH KNOTS 10000 20 1 6 6 12 0 154 20 1 6 1 11 2 152 12000 18 6 6 0 11 0 151 18 6 5 6 10 5 148 lnterpolate 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 PSl GPH KNOTS DEN PUB 19 0 6 1 11 2 152 PUB TBE 19 0 6 Ql11 0 151 TBE DHT 19 0 5 8 10 8 149 DHT AMA 19 0 5 7 10 7 ...

Page 97: ...COS 30 181 COS PUB 40 179 PUB TBE 74 136 TBE DHT 87 136 DHT AMA 65 139 FUEL TIME AT USEO CRUISE FOR ALTITUOE CRUISE HRS MIN GAL 0 10 1 9 0 13 2 4 0 33 6 1 0 38 6 8 0 28 5 0 Distance required to climb has been subtracted from segment distance TIME FUEL DISTANCE TIME FUEL OISTANCE ITEM HRS MINS GAL NM Start Runup Taxi and Take off acceleration 0 00 1 7 0 Climb 0 13 3 5 25 Cruise 2 02 22 2 296 Total ...

Page 98: ...s per hour Reserve fuel 45 min 8 3 GPH 6 2 gallons Total Fuel 27 4 6 2 33 6 gallons The estimated landing weight is determined by subtracting the fuel required for the trip from the ramp weight Assumed ramp weight 3060 lbs Estimated fuel from DEN to AMA 27 4gal 61bs tgal 164 lbs Estimated landing weight 3060 164 2896 lbs Examples have been provided on the performance graphs The above conditions ha...

Page 99: ...ere to begin following guide lines Always project to the reference line first then follow the guide lines to the next known itern 3 lndicated airspeeds IAS were obtained by using the AIRSPEED CALIBRATION NORMAL SYSTEM Graph 4 The associated conditions define the specific conditions frorn which performance parameters have been determined They are not intended to be used as instructions however perf...

Page 100: ... FLAPS DOWN 1 160 l 180 frl 170 150 140 II USO 0150 130 120 8110 100 90 eo 10 130 a i12a 110 100 90 10 tlO 60 70 80 90 100 110 120 160 180 170 180 190 200 AS INOICATED JASPEED K NOTS fTTrr rr 1 1 1 1 J 1 1 1 1 1 1 1 1 1 1 11 70 60 100 110 120 13 150 ll O 110 190 190 200 210 220 230 IAS IND4CATEO AJRSPEEO MPH eo 10 eo 90 100 110 120 uo 1 co IASt l O CATEO AIRSPEED NOTS 1b oo1J 1 Ja 1to b b1 1lo1 1 ...

Page 101: ...100 110120130 1 0150160 170 180 190200 210 220 230 IAS INDJCATED AIRSPEED MPH NORMAL SYSTEM 1AS 70 KNOTS 81 MPH FLAPS DOWN INDICATED PRESSURE ALTITUDE 4500 FT ALTIMETER CORRECTION 8 FT cTUAL PRESSURE ALTITUDE 4500 8 4492 FT 10 FLAPS DOWN 0 10 t m 1 l g fi S 15 20 30 Q 50 8i E i t 90 5 lii 8 50 50 80 80 1001W1201301 JAS flDICATED AIRSPEED KNOTS Ji 1 1 o el 1 1lio1 1lo1 1Jo11 01 1Jo k 1Jo JAS INDICA...

Page 102: ... r 1 e 60 70 90 9D 100 ITO 120 130 T4Q 150 100 110 180 190 200 AS iNOICATEO AIRSPfED KNOTS 1 y i yr Tj i Ti S T r j 1i j y i1i 1 10 80 90 100 1 0 l 20 1JD lliO 150 160 110 UIO 190 200 210 220 230 IAS INOICA rEO AIRSPEEO MPH EXAfttPLE iAS 100KTSl115MPM OPEN S l OAMWINOOW CAS 130 92KTSl106 MPHI 60 1Q 1 90 110 120 130 AS INOICATEO AIRSPEEO i N OTS T1 1r 1 i f1 1 i 1 n 10 80 90 100 110 120 130 140 150...

Page 103: ...17 i 1 rT 1 1 i 10 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 tAS TNOICATED Ä1RSfifED MPH 0 EXAMPLE iAS STORM WINDOW INDICATED PRESSURE ALTITUDE ALTITUOE CORRECTION ACTUAL PRESSURE AlTITUOE 0 70 KTS 81 MPHl Ol EN 6000 FT 33 FT 6000 JJ 967 FT 60 1 T r 1 r 1 o lOO o v o w t r60 1 1 T r t 1 60 70 80 90 100 110 120 130 IAS INOICATED AIRSPEED tr NOTS 1 1 i 1 1 i 1 1 1 1 1 1 1 1 1 1 1...

Page 104: ...formance j z 0 _ Cii a it w z t 0 w a 1 c a w D ä w 1 _ w 0 1 w c z w a c u Sl g i1 g 5 14 Li 2 0 J S33H 30 BEECHCRAFT Debonair C33 Bonanza E33 and F33 2 0 8 g 0 g i l g UJ 0 Cl t 0 0 l l g g 2 g 0 g Sl August 1982 ...

Page 105: ...tionV Performance 0 CO 0 0 0 0 0 2 l l t1H l t t 1 _ f H t H j t f t H t f l j f H O a i a Q Wiii 5 zo 0 0 Qf 1 f i l H 5 f t r Hr H 1 µ_ a l f i t lrl i H H t U1 rM M T _ 1 i t t f t t H f F H ll Blf til 0 0 0 N August 1982 0 8 0 w 0 0 f 0 2 w 1 0 ry 0 0 0 0 0 r 0 8 0 0 5 15 ...

Page 106: ... l DICATEOA N J LA PS LJp ll SeEEOg iJ I01cAtfo AN J CALIBRAreo A IRSPE eos PS oo NNd tib b 1 1 1 w w u z w ffi u w a CD Cl N 3000 2800 2600 2400 2200 0 WEIGHT POUNDS EXAMPLE WEIGHT FlAPS 2800 LBS UP ANGLE OF SANK 30 STALL SPEED CAS 64 J NQTS 74 MPH 90 100 80 90 t 0 0 z 701 i 80 1 Q Q w w w 60 70 l t 60 50 50 10 20 30 40 50 60 ANGLE Of BANK OEGAEES C J 0 1 QI 1 tl J al 0 0 3 s 1 g t c m ai m O WO ...

Page 107: ...Crosswind Component is 17 kts __ EXAMPLE WINOSPEEO ANGLE BETWEEN WIND OIRECTION ANO FLIGHT PATH HEAOWIND COMPONENT CROSSWIND COMPONENT Fl IGHT PATH 20 KTS 5 J 13KTS t5KTS 40 z rTI rrnrrn r r r rTT r rrrrr r r n ri 20 0 z 1 z w 10 z 0 E 0 u 0 z j 0 0 UJ X 0 10 20 CROSSWIND COMPONENTS August 1982 30 KNOTS 6 17 ...

Page 108: ...40 50 60 OUTSIOE AIR TEMPEAATVRE c 111111r1111 rr1 m 0 20 40 60 120 140 OUTSIDE AIR TEMPEAATUAE F 50 FT KNOTS MPH 74 85 73 84 71 82 68 78 3000 EXAMPLE OAT PRESSURE ALTrfUOE TAKE OFF WEIGHT HEAD WlNO COMP GROUND ROLL TOTAL OISTANCE OVER A 50 FT 08STACLE TAKE OFF SPEED AT LIFT OFF 50 FT 2800 2600 2 400 WEIGHT POUNDS t5 C 59 FJ 5650 FT 3050 LBS 9 5 KNOTS 2000 FT 3150 FT 68 KNOTS 178 MPHI 74 KNOTS 85 ...

Page 109: ... KCI J 3000 2800 2800 EXAMPJ E OAl PRE SSUAE AlTITUDE WflGHl RATE OF CLIMB CLIMB GRADIENT CLIMB SPEED 1200 1100 1000 900 1 800 1 700 800 500 400 300 200 100 o 2400 ro so 40 30 20 10 o 10 20 30 40 so OUTSIOE AtR TEM ERATUR E C WEIGHT POUNDS 1 1 1 1 1 1 1 1 1 1 1 TTT ITT o m 40 ro 100 1 OUTSIDE AIR TEMPERATURE F 5 C 23 FJ 11500 n 3035 LBS 400 F l IN 3 B 90 NOTS 104 MPHJ 13 12 11 10 9 1 8 7 i 6 m 5 a...

Page 110: ...OSEO 50 OUTSIDE AIA TEMPERATUREN C 1TTT1 1 l 1 1 1 1 1 1 1 1 1 1 1 oo 40 20 o 20 40 eo oo 100 120 OUTSIDE AIR TEMPERATURE F TIME TO CLIMB 122 91 FUEL TO CLIMB 16 1 2 61 DISTANCE TO CLIMB 142 171 fo 20 30 40 50 TIME TOfLIM6N INUTES_ 1 1 1 1 1 1 1 1 T 1 0 1 2 3 4 5 8 7 8 g 10 11 FUEl TO tCLIM_BN LLONS J 1 1 1 1 1 rr r 0 10 20 30 40 50 60 70 80 90 100 01STANCE TO CUMll NAUTICAL MILES 15 C 59 F 5 C 23...

Page 111: ...6 178 36 1 1460 21 7 llO l 1 3 12 7 155 178 27 3 24 0 20 1 18 6 6 8 1UI 16 1 t16 20 1 2460 18 fi 17 3 U HI 1 17t H 1 l lMOO 17 3 7 8 7 8 7 8 7 8 7 4 6Jl 6 0 5 5 13 4 13 4 13 4 13 4 2 9 2 0 u 10 3 148 170 9 il 37 150 173 92 33 153 176 BS 29 156 179 78 t Wl 1 8 1 21 1 177 63 n 151 173 13 HE UIB 4 toooo 11 ia 2 1 2000 16 27 2450 i4000 23 31 2450 tt5000 3l 3 2450 lfl o 8 4 10 114 1 66 5 15 24SO 16 0 5...

Page 112: ...64 41 5 2450 20 4 6 3 1 5 146 168 77 25 2450 19 4 6 3 11 5 145 167 34 1 2450 19 9 6 3 1 5 148 171 70 21 2450 18 9 6 3 11 5 148 170 27 3 2450 19 5 8 3 11 5 151 174 3 17 2450 18 5 6 3 11 5 150 171 20 1 2 sn uu lkO M 1111 13 ise t 2460 JU 5 t HU 148 171 t3 o 11 24 SI t l1 3 5 l 0 3 1 tl 1411 2450 tll O 5 3 tCU t44 188 s u 2 48 l te o 1 u 14 un 41 1 FULL THROTTLE MANIFOLD PRESSURE SETTINGS ARE APPROXI...

Page 113: ...2300 121 1 2000 19 7 2300 19 7 5 2 9 8 128 147 55 13 2300 20 3 5 2 9 8 130 150 91 33 2300 20 7 4000 12 11 2300 19 2 5 2 9 8 130 149 48 9 2300 19 B 5 2 9 8 132 152 84 29 2300 6000 4 16 2300 18 7 5 2 9 8 132 152 41 5 2300 19 3 5 2 9 8 134 154 77 25 2300 8000 3 19 2300 18 2 5 2 9 8 134 154 34 1 2300 18 8 5 2 9 8 136 157 70 21 2300 10000 10 23 2300 17 B 5 2 9 8 136 156 27 3 2300 18 3 5 2 9 8 138 12000...

Page 114: ...3 TAS KTS fl4PH 113 130 115 132 116 134 118 135 119 137 STANDARD OAV ISA ENGINE MAN 1 FUEL OAT 1SPEED PRESS FLOW OF c RPM IN HG 61 16 2100 20 4 54 12 2100 19 9 47 8 2100 19 5 40 4 2100 19 1 33 120 138 26 120 121 m1 11m 111 t 1 NOTES 1 FULL THROTTLE MANIFOLD PRESSURE SETTINGS ARE APPROXIMATE 2 SHADEO AREA AEPRESENTS OPERATION WITH FULL THROTTLE TAS ISA 36 F 20 CI ENGINE MAN FUEL OAT 1SPEED PllESS F...

Page 115: ... u 14000 13000 n 12000 11000 1 w w 10000 w 9000 0 l 1 8000 4 w 7000 a ii U Cl IJJ 6000 w a 0 i iX Q 5000 4000 8 N II X 3000 IXl II Q J 2000 1000 SL 110 120 130 EXAMPLE 11500 FT PRESSURE AlTITUOE POWER SETIING FULL THAOTILE 2450 RPM TRUE AIRSPEED 151 KNOTS t 1tm ir 1 y i z I 0 ll i i tc Q f5 0 ll II ll r r IXl IXl Q c j f8 140 150 m w w n 160 TRUE AIRSPEED rv KNOTS August 1982 5 25 ...

Page 116: ...00 N MANIFOLD PRESSURE vs RPM 1800 1900 2000 2100 2200 2300 2400 2500 ENGINE SPEED RPM EXAMPLE ENGINE SPEED 2450 RPM MANlFOLD PRESSURE 18 9 IN HG WITHIN RECOMMENDED LIMITS 2600 m 0 s i tl fl Cll CD 1 0 0 3 i g c ma1 m W CT wox CD a EI w w Tl WW t ...

Page 117: ...7 16 15 1 3 14 13 w ii 12 II IQ ß EXAMPLE llJ BRAKE HORSEPOWER 146 J i65 MCP CONDITION LEVEL FUGHT CHUISE LEAN fUH FLOW 11 4 GAUHR li FUEl FLOW 11 0 GAL 1 lR CONDITION LEVEL FUGHT CRUlSE LEAN BRAKE HOA SEPOWEA 141 80 90 100 110 120 130 140 150 150 170 180 190 200 210 220 230 240 250 BRAKE HORSEPOWER August 1982 5 27 ...

Page 118: ...RESERVE FUEL AT 45 MCP PRESSURE ALTITUOE l l 500 FT POWER SETilNG FULL THROITLE 2450 RPM RANGE 845 NM 20000 t tJ t tt f go ttl 15000 a 1 l f O r I ti µ t CRUISE TAUE f i L i il f51 121 AIRSPEED V 0 rr KNOTS i 10000 J LIJ g 156 48 136 120 C t ö fil 5000 J j J J g o r 1 5 1 43 m R 118 PJ 111 ffl j J R n t i 148 138 128 tt115 SL 1 1 650 700 750 800 850 900 950 1000 1050 RANGE rv NAUTICAL MILES ZERO W...

Page 119: ...SA Qli RANGE INCLUDES STAAT TAXI AN CUMB WITH 45 MINUTES RESERVE fUEL Al 45 MCP j ft 0 Oll a a iE PllESSURE AlTllUDE POWER SETIING RANGE gN 0 151 u w CRUISE TRUE r R AIRSPEED rvKNOTS y ti X S w i2o 156 148 136 t l rno Tt to C CL fi li 11 B J Et l O 0 148 138 11 X J 115 1 1 1 1 1 400 450 500 550 600 RANGE rvNAUTICAL MILES ZERO WIND 1 500 F1 FULL THROTILE 2450 RPM 445 NM mom o CD m i icr m Al 0 i c ...

Page 120: ...1 LU tl 15000 LU Cl i 1 5 10000 LU a 56 i NOTE EN öüRANCE INCLUDES START TAXI AND CUMS WfTH 45 MINUTES RESERVE FVEL AT 45 MCP 148 136 LU a ll 111111111r111r 13 SL 138 128 t 5 5 6 0 6 5 7 0 7 5 ENDURANCE HOURS EXAMPLE PRESSURE AltlTUDE 11 500 T POWER SETI1NG FULL THRQITlE 2450 RPM ENDURANCE 5 70 HRS H9 IQ Z 11a ii4 115 1 8 0 C5 HRS 42 MIN 8 5 E w m Q s 1 CD CD s a Q Q 3 s CD c m CD m WO w Q r j n i...

Page 121: ...000 w a rn rn 5000 IU a IL Sl 2 0 2 5 w STANDARD OAY ISA RANCE INCLUOES START TAX ANO CUMB WITH 45 MINVTES RESERVE FUEL AT 45 MCP PRESSURE ALTITUOE 11500 F1 POWER SETIING fULL THROTTLE 2450 RPM ENOURANCE 3 03 HRS 3 0 136 3 5 FULL THROTILE 2100 RPM CRUISE TAUE AIRSPEED KNOTS 4 0 120 118 1 115 rr 4 5 5 0 ENOURANCE HOURS 13 HRS 2 MIN 5 5 tD c tu c ai m i 17 m DI 0 ia X DI 0 mn r i w w J w w I t i Q w...

Page 122: ...40 30 20 10 0 10 20 30 40 50 60 OUTSIDE AIR reMPERATURE C l r TT I 1 1 1 1 1 1 1 TTTI 1 1 1 1 40 20 0 20 40 60 80 100 t20 140 OUTSIDE AIR TEMPERATURE F z a li tiil 1 j 1 1 1 I 1 r 3000 2800 2600 2400 WEIGHT POUNDS OAT PRESSURE ALTITUOE WEIGHT WINO COMPONENT GROUNO ROLL TOTAL OVER 50 FT OBSTACLE APPROACH SPEED b 1 10 20 30 0 25 C 77 Ft 3965 FT 2884 LBS 9 0 KfodOTS HEADW NOI 1150 FT 1775 FT 68 KNOTS...

Page 123: ...ord 6 7 Loading lnstructions 6 9 Seating Baggage and Equipment Arrangements 6 10 Gross Weight Moment Limits 6 11 Moment Limits vs WeightTable 6 12 Computing Procedure 6 15 Sample Weight and Balance loading Form 6 17 Weight and Balance loading Form 6 18 Useful Load Weights and Moments 6 19 Occupants 6 19 Baggage 6 20 Cargo 6 20 Usable Fuel 6 21 Oil 6 21 Equiprnent List Provided for each airplane Au...

Page 124: ...SectionVI Wt and Bal Equip List BEECHCRAFT Debonair C33 Bonanza E33 and F33 INTENTIONAllY lEFT BLANK 6 2 August 1982 ...

Page 125: ... at Fuselage Station 271 0 2 Fuel should be drained preparatory to weighing Tanks are drained from the regular drain ports with the airplane in static ground attitude When tanks are drained 1 5 pounds of undrainable fuel remain in the airplane at Fuselage Station 76 0 The remainder of the unusable fuel to be added to a drained system is 34 5 pounds at Fuselage Station 79 1 3 Engine oil must be at ...

Page 126: ...g a steel measuring tape Measurements are taken with the airplane level on the scales from the reference a plumb bob dropped from the center of either main jack point to the axle center line of the main gear and then to the nose wheel axle center line The main wheel axle center line is best located by Stretching a String across from one main wheel to the other All measurements are to be taken with...

Page 127: ...irplane lt is the owner s responsibility to ensure that changes in equipment are reflected in a new weight and balance and in an addendurn to the equipment list There are rnany ways of doing this it is suggested that a running tally of equipment changes and their effect on ernpty weight and c g is a suitable rneans for meeting both requirements The current equipment ist and empty weight and c g in...

Page 128: ...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 below provided for additions and subtractions to as weighed condition EMPTY WEIGHT DRY ENGINE Oll 22 557 UNUSABLE FUEL 36 79 2844 BASIC EMPTY WEIGHT gi 1 III 1 g III n 1 Q 0 m i s c c ii c c m e1 m w O 0 wg c III III 0 a a 0 ww WW f ...

Page 129: ...ALANCE RECORD REGISTRATION NO PAGE NO WEIGHT CHANGE RUNNING BASIC DESCRIPTION Of ARTICLE ADDED OR REMOVED H EMPTY WEIGHT OR CHANGE WT ARM MOM WT MOM LBS IN 100 LEIS 100 CD C IX 0 CD m i g m i 1 11 i 1 11 o m n ri w r d W J w c III i Q Cl III di 1 C CD c l 6 i ...

Page 130: ...T AND BALANCE RECORD REGISTRATION NO PAGE NO WEIGHT CHANGE RUNNING BASIC DESCRIPTION OF ARTIClE ADDED OR REMOVED EMPTV WEIGHT OR CHANGE WT ARM MOM WT MOM lBS IN ToO LBS 100 m g llll 1 iff III 1 Cl Cl w 1 III Cl c c l o m 111 rn 8 0 m s C s n Cl D n w w Tl ww ...

Page 131: ...ht and balance are the responsibility of the airplane owner anq or operator The empty weight and moment of the airplane at the time of delivery are shown on the airplane Empty Weight and Balance form Useful load items which may be loaded into the airplane are shown on the Useful Load Weight and Moment tables The minimum and maximum moments are indicated on the Moment Limits vs Weight table These m...

Page 132: ...AND BAGGAGE OR 5th SEAT AND PASSENGER MAXIMUM WEIGHT 200 POUNDS FORWARD OF V REAR SPAR INCLUDING EOUIPMENT ANO CARGO WITH 3rd AND 4th SEATS REMOVED MAXIMUM WEIGHT 270 POUNDS AFT OF REAR SPAR INCLUDING EQUIPMENT AND CARGO WITH 3rd 4th AND 5th SEATS REMOVED 6 10 NOTE The floor structure load limit is 100 pounds per square foot except for the area between the front and rear spars where the floor stru...

Page 133: ...SS WEIGHT MOME n LIMITS 2eao 3600 70o 3500 60o 3400 sao 3300 3200 4oo 3100 230o 3000 Ul 8 ao 0 2900 z i 10o 0 z lL w 2800 _ 0 0oo 2700 r w 111oo 2600 Boo 2500 l Oo 2400 1s0o 2300 2200 sao 2100 71 73 75 77 79 81 83 85 87 89 2000 CENTER OF GRAVITY INCHES AFT OF DATUM August 1982 6 11 ...

Page 134: ...FT CG UMIT 3050 lb take off 81 5 86 7 or landing 2700 lb or less 77 0 86 7 Minimum Maximum Moment Moment Weight 100 100 2100 1617 1821 2110 1625 1829 2120 1632 1838 2130 1640 1847 2140 1648 1855 2150 1656 1864 2160 1663 1873 2170 1671 1881 2180 1679 1890 2190 1686 1899 2200 1694 1907 2210 1702 1916 2220 1709 1925 2230 1717 1933 2240 1725 1942 2250 1732 1951 2260 1740 1959 2270 1748 1968 2280 1756 ...

Page 135: ...30 1794 2020 2340 1802 2029 2350 1810 2037 2360 1817 2046 2370 1825 2055 2380 1833 2063 2390 1840 2072 2400 1848 2081 2410 1856 2089 2420 1863 2098 2430 1871 2107 2440 1879 2115 2450 1886 2124 2460 1894 2133 2470 1902 2141 2480 1910 2150 2490 1917 2159 2500 1925 2168 2510 1933 2176 2520 1940 2185 2530 1948 2194 2540 1956 2202 2550 1964 2211 2560 1971 2220 2570 1979 2228 2580 1987 2237 2590 1994 22...

Page 136: ... 2280 2640 2033 2289 2650 2040 2298 2660 2048 2306 2670 2056 2315 2680 2064 2324 2690 2071 2332 2700 2079 2341 2710 2090 2350 2720 2101 2358 2730 2113 2367 2740 2124 2376 2750 2135 2384 2760 2146 2393 2770 2158 2402 2780 2169 2410 2790 2181 2419 2800 2192 2428 2810 2203 2436 2820 2215 2445 2830 2226 2454 2840 2238 2462 2850 2249 2471 2860 2261 2480 2870 2273 2488 2880 2284 2497 2890 2296 2506 6 14...

Page 137: ...558 2960 2378 2566 2970 2390 2575 2980 2402 2584 2990 2414 2592 3000 2426 2601 3010 2438 2610 3020 2450 2618 3030 2462 2627 3040 2474 2636 3050 2486 2644 COMPUTING PROCEDURE 1 Record the Basic Empty Weight and Moment from the Basic Empty Weight and Balance form or from the latest superseding form under the Basic Empty Condition block The moment must be divided by 100 to correspond to Useful Load W...

Page 138: ...ition 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 the Landing Condi tion moment must be within the minimum and maxi mum moments shown on the Moment Limit vs Weight table for that weight lf the total moment is less than the minimum moment allowed useful load...

Page 139: ..._____ ITEM WEIGHT MOM 100 1 BASIC EMPTY CONDITION 2030 1612 2 FRONT SEAT OCCUPANTS 340 288 3 3rd and 4th SEAT OCCUPANTS 340 412 4 5th SEAT OCCUPANT 5 BAGGAGE b 26 36 6 CARGO o 7 SUB TOTAL ZERO FUEL CONDITION 2736 2348 8 FUEL LOADING 54 GAL 324 243 9 SUB TOTAL RAMP CONDiTION 3060 2591 10 LESS FUEL FOR START TAXI AND TAKE OFF 10 8 11 SUB TOTAL TAKE OFF CONDITION 3050 2583 12 LESS FUEL TO DESTINATION...

Page 140: ...C EMPTY CONDITION 2 FRONT SEAT OCCUPANTS 3 3rd and 4th SEAT OCCUPANTS 4 5th SEAT OCCUPANT 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 10 lbs at an average monv 1 00 of 8 6 18 August 198...

Page 141: ... 157 161 40 57 140 119 123 169 174 50 71 150 128 134 182 186 60 85 160 136 142 194 198 70 99 170 144 151 206 211 80 114 180 153 160 218 223 90 128 190 162 169 230 236 100 142 200 170 178 242 248 110 156 120 170 NOTE OCCUPANT POSITIONS SHOWN ARE FOR 130 185 THE SEATS ADJUSTED THE MAXIMUM RANGE 140 199 INTERMEDIATE POSITIONS WILL REQUIRE INTER 150 213 POLATION OF THE MOMENT 100 VALUES 160 227 170 24...

Page 142: ... 135 Weight Mom 100 Mom 100 Mom 100 10 14 11 14 20 28 22 27 30 42 32 40 40 56 43 54 50 70 54 68 60 84 65 81 70 98 76 94 80 112 86 108 90 126 97 122 100 140 108 135 110 154 119 148 120 168 130 162 130 182 140 176 140 196 151 189 150 210 162 202 160 224 173 216 170 238 184 230 180 252 194 243 190 266 205 256 200 280 216 270 210 294 284 220 308 297 230 322 310 240 336 324 250 350 338 260 364 351 270 ...

Page 143: ...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 Oll Moment Quarts Weight 100 10 19 5 lncluded in Basic Empty Weight August 1982 6 21 ...

Page 144: ...SectionVI Wt and Bal Equip List BEECHCRAFT Debonair C33 Bonanza E33 and F33 INTENTIONAllY LEFT BLANK 6 22 August 1982 ...

Page 145: ... 7 6 Instrument Panel 7 7 Flight Instruments 7 7 Power Plant Instruments 7 7 Instrument Panel Schematic C33 E33 7 8 Instrument Panel Legend 7 9 Instrument Panel Schematic F33 7 10 Manifold Pressure and Fuel Flow lndicator 7 11 Multiple Readout Type Instrument 7 12 Avionics Panel 7 12 Switches 7 13 Ground Control 7 13 Wing Flaps 7 14 Landing Gear System 7 15 Control Switch 7 15 Position lndicators ...

Page 146: ...nt Engine Controls Throttle Propeller and Mixture Cowling F33 lnduction System lcing Lubrication System Starter Propeller Fuel System Fuel Cells Fuel System Schematic Fuel Quantity lndication System Auxiliary Fuel Pump Fuel Tank Selection Fuel Required for Flight Electrical System Battery Generator Alternator External Power Receptacle PAGE 7 16 7 16 7 17 7 17 7 17 7 18 7 18 7 19 7 19 7 19 7 20 7 2...

Page 147: ...n System Schematic C33 E33 7 32 Heating and Ventilation System Schematic F33 7 33 Heater and Defroster Operation 7 34 Cabin Ventilation 7 35 Cabin Fresh Air Outlets 7 35 Exhaust Vents 7 36 Oxygen System 7 36 Pitot and Static Systems 7 37 Pitot System 7 37 Pitot Heat 7 37 Normal Static Air System 7 37 Emergency Static Air System 7 38 Vacuum System 7 38 Instrument Pressure System 7 38 Stall Warning ...

Page 148: ...SectionVll Systems Description BEECHCRAFT Debonair C33 Bonanza E33 and F33 INTENTIONALLV LEFT BLANK 7 4 August 1982 ...

Page 149: ...tional FLIGHT CONTROLS CONTROL SURFACES Control surtaces 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 control wheel as desired The aileron trimmer on the...

Page 150: ...of the trim control handwheel The aileron trimmer on the control column hub displaces the ailerons displacement is maintained 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 ...

Page 151: ...g to the right of the engine instruments and a sub panel which provides for a compact circuit breaker group on the right side and switching panel on the left FLIGHT INSTRUMENTS The floating instrument panel contains all flight instru ments except the magnetic compass On this panel are the airspeed indicator gyro horizon altimeter turn coordina tor directional gyro and vertical speed indicator with...

Page 152: ... VII Sect1on ption Systems Descri M M w C i M u 7 8 BEECHCRAFT Debonair C33 EJ3andF33 Bonanza August 1982 ...

Page 153: ...Control 13 Flap Position Switch 14 Auxiliary Fuel Pump Switch 15 Alternate Air Control 16 Propeller Control 17 Aft Cabin Heat Control 18 Radio Lights Rheostat 19 Instrument Panel Flood Light 20 Landing Gear Position Switch 21 Lower Landing Light Switch 22 Upper Landing Light Switch 23 Parking Brake Control 24 Rotating Beacon Switch 25 Navigation Lights Switch 26 Pitot Heat Switch 27 Cabin Heat Con...

Page 154: ...Section VII Systems Description Dcp 01 CD i w1 CD j 1 M M u 7 10 e oCDCD C0 CDCD C0 CDCD 0CD BEECHCRAFT O 000 l j r f 1 Cn e i e e e i1 ii qj t o 1 l August 1982 ...

Page 155: ... above minimum before advancing the throttle above warm up rpm and on descent with power reduced to avoid overcooling The tachometer is driven by a flexible shaft from the engine accessory section lncorporated in the tachometer is an engine hour meter which automatically records the total engine operating time MANIFOLD PRESSURE AND FUEL FLOW INDICATOR The manifold pressure portion of this instrume...

Page 156: ...een sectors for full power at various altitudes The high side of each green sector represents the fuel pressure setting re quired to achieve maximum power at the specified altitude when operating full throttle at 2600 rpm These values should correspond to the fuel pressure values on the Climb graph in the PERFORMANCE Section MULTIPLE READOUT TYPE INSTRUMENT F33 The multiple readout type instrument...

Page 157: ...ing switches are located on either the right C33 E33 or left F33 subpanel GROUND CONTROL Steering is accomplished by use of the rudder pedals through a linkage arrangement which connects the nose strut to the rudder pedal shaft Nose wheel straightening is accomplished by engagement of a roller with a track as the nose wheel is retracted The steering link attaches to the steering mechanism on the n...

Page 158: ...f the left flap The intermediate pe sitions are reached when the marks are aligned with the trailing edge of the wing E33 F33 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 be pulled out of detent before it can be repositioned A dial type indicator has markings for UP 10 20 and ON The indicator is located to...

Page 159: ... to the oppos1te position CAUTION Do not change the position of the control switch to reverse the directlon of the landing gear while the gear is in transit as this could cause darnage to the retract rnechanisrn POSITION INDICATORS C33 E33 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 illurninating only when th...

Page 160: ...test button on the floating instrument panel The intensity of the lamps is automatically lowered for night flights when the naviga tion lights are turned on SAFETY SWITCH To prevent inadvertent retraction of the landing gear on the ground a main strut safety switch opens the control circuit when the strut is compressed WARNING Never rely on the safety switch to keep the gear down during taxi or on...

Page 161: ...bpanel C33 E33 left subpanel F33 To set the parking brakes depress both toe pedals until firm then pul contro out Push the control in to release the brakes CAUTION The parking brake should be left oft and wheei chocks installed if the airplane is to be left unattended Changes in ambient temperature can cause the brakes to release or to exert excessive pressures MANUAL EXTENSION The landing gear ca...

Page 162: ...secured with an FM approved restraint system WARNING Do not carry hazardous material anywhere in the airplane Do not carry children in the baggage compartment unless secured in a seat SEAT ADJUSTMENTS To adjust any of the four standard seats forward or aft pul 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 o...

Page 163: ...or and firmly pull the door closed Rotate the door handle fully counterclockwise into the locked position When the door is properly locked the door latch handle is free to move approximately one inch in either direction NOTE When checking the door latch handle do not move it far enough to engage the door latch release mechanism Press firmly outward at the top rear corner of the door lf any movemen...

Page 164: ...the emergency exit provided by the openable middle window on each side of the cabin 1 Lift the latch 2 Pull out the emergency release pin and push the windowout The above procedure is described on a placard installed below the left and right middle windows CONTROL COLUMN LOCK PIN 1 Rotate control wheel and move column so the hole in the bracket and the column align to accept pin 2 Push the control...

Page 165: ...ol may be repositioned by pushing O pulling and locked into position by rotating the knob clockwise COWLING F33 The Bonanza is equipped with Hartwell latch mechanisms on the right and left upper engine cowling for quick and easy access to the engine compartments without the aid of tools Each cowl latch is locked and released by a single recessed handle located in the lower cowling panel on each si...

Page 166: ...l open automatically and the induction system will operate on alternate air lf the alternate air source door becomes frozen in the closed position a pull and release T handle is provided to force the door open LUBRICATION SYSTEM The engine oil system is the full pressure wet sump type and has a 10 quart capacity Oil operating temperatures are controlled by an automatic thermostat bypass control Th...

Page 167: ...8433 4R Diameter Maximum 80 in Minimum 78 1 4 in Pitch settings at 30 in sta Low 10 8 i 0 2 High not under 32 Propeller rpm is controlled by a governor which regulates hydraulic oil pressure to the blades A push pull knob on the control console allows the pilot to select the gov ernor s rpm range lf governor oil pressure is lost the propeller will go to the full high rpm position This is because p...

Page 168: ...le The fuel systern consists of a rubber fuel cell in each wing leading edge with a flush type filler cap A visual measuring tab is attached to the filler neck of the optional systern 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 r...

Page 169: ...ple margin of fuel for any flight ELECTRICAL SYSTEM The system circuitry is the single wire ground return type in which the airplane structure itseif is used as the ground return C33 E33 The battery ON OFF switch the generator atternator ON OFF switch and the magneto Start switch are located on an escutcheon at the left of the instrument panel The circuit breaker panel extends across the base of t...

Page 170: ...ng the rate of charge or discharge of the battery A zero reading which should be the normal condition in cruising flight indicates that the battery is fully charged and the generator output has been adjusted by the regulator to balance the load of electrical equipment then in use ALTERNATOR A 60 ampere 12 volt gear driven alternator is optional equipment The alternator is designed to maintain its ...

Page 171: ...overheating during ground maneuvering NOTE ht Particularly a night reflections from anti collision lights on clouds dense haze or dust can produce optical illusions and intense vertigo Such tights when installed should be turned off before entering an overcast their use mav not be advisable under instrument or limited VFR conditions ENVIRONMENTAL SYSTEMS CABIN HEATING A heater muffler on the right...

Page 172: ...A VA LVf ICOU PQSfTIQNI FRESH AIR INTAKE NOSE FAESH AIR fNtAKE iENGtNE BAFFU FRESHAIR 1 WfNG ROOT ILH JI J LH FORWARD OUTLET u 1 GE DOOAI I fPnortoCO f2CXJJ f I 1 f 1 1 I 1 f 1 1 1 1 I 1 1 1 ATING AND VENTILATION SYSTEM SCHEMATIC C33 E33 7 32 August 1982 ...

Page 173: ...1N HEAT CONTAOL _ _ _ OVERHEAO E XiiAuST AD JUS A6lE1 1 1 1fllOIV1DUAL OVl Rl t AO fRf_SH AIR OUTLET S tSTANOAROJ ovt RHE AO FRE5H A SHUTOFf CONTAOL l 1 l 1 1 l 1 o lo0 i r10NlL1 1 A H FORWARD OUflET 1 1 1 1 1 1 AFT0uTLET H H FRONT SE ATJ 1 1 1 1 J 1 Afl OUTLEJ RH AEAR SEA T1 1 1 1 1 1 1 1 1 J 1 1 1 1 1 1 i FIXEO EXHAUSf i EAR OF HAT SHEl F 1 1 1 1 1 1 XHAUSl A JI 1 1 1 1 1 1 1 1 i l 1 1 1 1 1 1 t...

Page 174: ... then ducted from tHe mixer valve to the outiets in the cabin HEATER AND DEFROSTER OPERATION The cabin heat control is located on the upper right sub panel in the C33 and E33 models and on the lower left subpanel in the F33 To provide heated air to the cabin out lets pull the CABIN HEAT control The control regulates the amount of cold air that is mixed with the air from the heater muff When the co...

Page 175: ...m the left outlet is regulated and the direction of airflow is controlled by rotating the louvered cover with the small knob on the rim The large knob in the center of this outlet is a friction lock which may be tightened to hold the valve position selected Individual Overhead FreshAJr Out ets CD 814 thru CD 1026 A manually retractable air scoop on top of the cabin con ducts outside air to individ...

Page 176: ...D 814 thru CD 1199 Air is exhausted from the cabin through a fixed vent below the baggage compartment door which flows to an exhaust vent in the belly CD 1027 thru CD 1254 A manually controlled cabin air exhaust vent is located aft of the radio speaker in the overhead panel CD 1200 thru CD 1254 A fixed exhaust vent is provided through the rear of the hat shelf OXYGEN SYSTEM The oxygen cylinder is ...

Page 177: ...n flying in visible moisture lt is not advisable to operate the pitot heating element on the ground except for testing or tor short intervals of time to remove ice or snow NORMAL STATIC AIR SYSTEM The normal static system provides a source of static air to the flight instruments through a flush static fitting on each side of the airplane fuselage Drain moisture accumula tions from the system CD 81...

Page 178: ...from the air are located on the forward side of the firewall A suction gage indicates system vacuum in inches Hg This instrument is located on the instrument panel exact location may vary according to panel configuration The vacuum should be maintained within the green arc for proper operation of the air driven instruments INSTRUMENT PRESSURE SYSTEM E33 F33 Instrument pressure is supplied by an en...

Page 179: ...sually a total of about 50 hours Drain and replace the engine oil as recommended in HANDLING SERVICING AND MAINTENANCE lf operating conditions are unusually dusty or dirty more frequent oil changes may be necessary Oii changes are more criticai during the break in period than at any other time Use full throttle at recomrnended rpm for every take off and maintain until at least 400 teet AGL then re...

Page 180: ...BEECHCRAFT Debonair C33 Bonanza E33 and F33 Minimize ground operation time especially during warm weather During the break in period avoid engine idling in excess of 15 minutes especially in high ambient temperatures 7 40 August 1982 ...

Page 181: ... A Certificated Pilot 8 9 Alterations or Aepairs to Airplane 8 9 Ground Handling 8 10 Towing 8 10 Parking 8 11 Tie Down 8 11 Main Wheel Jacking 8 12 Prolonged Out ot Service Care 8 12 Flyable Storage 7 to 30 Days 8 12 Mooring 8 12 Engine Preparation For Storage 8 13 fuel Cells 8 13 Flight Control Surfaces 8 13 Grounding 8 13 Pitot Tube 8 13 Windshield and Windows 8 13 During Flyable Storage 8 14 P...

Page 182: ...18 Tires 8 20 Shock Struts 8 20 To lnflate Struts 8 20 To Replenish Strut Hydraulic Fluid 8 21 Shock Strut Shimmy Damper 8 22 Brakes 8 23 lnduction Air Filter 8 23 To Remove and Clean the Filter 8 23 Vacuum System 8 23 Instrument Pressure System 8 24 Propeller Blades 8 24 Oxygen System 8 25 Oxygen Cylinder Retesting 8 26 Minor Maintenance 8 27 Rubber Seals 8 27 Generator 8 27 Alternator 8 28 Magne...

Page 183: ...chedule B 34 Lubrication Points B 40 Consumable Materials 8 46 Approved Engine Oils 8 50 Bulb Replacement Guide 8 52 Overhaul or Replacement Schedule 8 53 Special Conditions Cautionary Notice 8 53 Landing Gear 8 54 Power Plant 8 54 Fuel System 8 55 Instruments 8 56 Electrical System 8 56 Flaps and Flight Controls 8 57 Miscellaneous 8 57 August 1982 8 3 ...

Page 184: ...SectionVlll Handling Serv Maint BEECHCRAFT Debonair C33 Bonanza E33 and F33 INTENTIONAllY lEFT BLANK 8 4 August 1982 ...

Page 185: ...s requirements established for this airplane All limits procedures safety practices time lim1ts servicing and maintenance requirements contained in this handbook are considered mandatory Authorized BEECHCRAFT Aero or Aviation Centers or In ternational Distributors or Dealers will have recorn mend1ed modification service and operating procedures issued by both FAA and Beech Aircraft Corporation des...

Page 186: ...ns 2 Original issues and revisions of FAA Ap proved Airplane Flight Manual Supple ments 3 Reissues and revisions of FAA Approved Airplane Flight Manuals Flight Hand books Owner s Manuals Pilot s Op erating Manuals and Pilot s Operating Handbooks This service is free and wil be provided only lto holders of this handbook who are listed on the FAA Aircraft Registration Branch List or the BEECHCRAFT I...

Page 187: ...10 AiRPlANE INSPECTION PERIODS 1 FAA Required Annual lnspections 2 BEECHCRAFT Recommended lnspection Guide 3 Continuing Care lnspection Guide 4 See Recommended Servicing Schedule and Overhaul or Replacement Schedule for further inspection schedules NOTE In event of emergency gear or flap extension at speeds above the respective normal extension speeds inspect gear retract rods gear doors and flaps...

Page 188: ...Section VIII Handling Serv Maint BEECHCRAFT Debonair C33 Bonanza E33and F33 INTENTIONALLY LEFT BLANK 8 8 August 1982 ...

Page 189: ...entative maintenance 2 All other maintenance must be performed by licensed personnel NOTE Pilots operating airplanes of other than U S registry should refer to the regulations of the registering authority for information con cerning preventative maintenance that may be performed by pilots ALTERATIONS OR REPAIRS TO AIRPLANE The FAA should be contacted prior to any alterations on the airplane to ens...

Page 190: ... hand tow bar Attach the tow bar to the tow lugs on the nose gear lower torque knee Where movement is restricted two men can pivot the airplane on the main wheels One man should push on the wing leading edge or hold the wing tip while the other operates the tow bar CAUTION Do not exert force on the propeller or control surfaces Do not place weight on the stabilizers to raise the nose1 wheel When t...

Page 191: ...E DOWN lt is advisable to nose the airplane into the wind Three tie down lugs are provided one on the lower side of each wing and a third at the rear of the fuselage 1 lnstall the control column lock pin 2 Chock the main wheels fore and aft 3 Using nylon line or chain of sufficient strength secure the airplane at the three points provided 00 NOT OVER TIGHTEN if the line at the rear of the fuselage...

Page 192: ...E Storage procedures are intended to protect the airplane from deterioration while it is not in use The primary objectives of these measures are to prevent corrosion and damage from exposure to the elements Flyable Storage 7 30 days has been considered here For more extended storage periods consult the Beech Airplane Shop Manual and Continental Service Bulletin M 74 9 or later issue FLYABLE STORAG...

Page 193: ... and cylinder head temperatures in the normal operating range Check for correct oil level and add oil if necessary to bring level to full mark FUEL CELLS Fill to capacity to minimize fuel vapor and protect cell inner liners FUGHT CONTROL SURFACES Lock with internal and external locks GROUND NG Static ground airplane securely and effectlvely P TOT TUBE lnstall cover WINDSHIELD AND WINDOWS Close all...

Page 194: ...tle in CLOSED position and mixture control is in the IDLE CUT OFF position Always stand in the clear while turning propeller lf at the end of 30 days airplane will not be removed from storage the engine shall be started and run The preferred method will be to fly the airplane for 30 minutes and up to but not exceeding normal oil and cylinder temperatures PREPARATION FOR SERVICE Remove all covers a...

Page 195: ...he small guide pin 2 To prevent arcing make certain no power is being sup plied when the connection is made 3 Make certain that the battery switch is ON all avi onics and electrical switches OFF and a battery is in the system before connecting an external power unit This protects the voltage regulators and associated electrical equipment from voltage transients power fluctuations CHECKING ELECTRIC...

Page 196: ...n each wing leading ge In the optional installation a 40 gallon capacity fuel cell 37 gallon usable replaces the smaller capacity cell The filler neck in this installation contains a visual measuring tab to permit partial filling of the tank Filling the tank until the fuel touches the bottom of the tab indicates 27 gallons of usable fuel and filling to the slot in the tab indicates 32 gallons of u...

Page 197: ...ot require cleaning unless there is a definite indication of solid foreign material in the cells or the airplane has been stored for an extended period Oll SYSTEM CAUTION During break in periods on new engines oil consumption tends to be higher therefore maximum range flights should be avoided and oil level brought to full after each flight during this period On the C33 and E33 the engine oil fill...

Page 198: ...rain plug and fill the engine with oil See Consumable Materialsand Approved Engine Oils for specifiecl oils The engine manufacturer recommends ashless dis persant oils In order to promote faster ring seating and oil control a straight mineral oil should be used for the first oil change period or until oil consumption stabilizes Oils must meet Teledyne Continental Motors Specification MHS 248 Refer...

Page 199: ...c gravity of the electrolyte should be checked periodically and maintained within the limits placarded on the battery The battery box is vented overboard to dispose of electrolyte and hydrogen gas fumes discharged during the normal charging operation To ensure disposal of these fumes the vent tube should be checked frequently for obstructions and should be kept open August 1982 8 19 ...

Page 200: ... result of the increased temperature generated during takeoff lncreased 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 INFLATE STRUTS 1 Check to see that the airplane is empty exce...

Page 201: ...rt the airplane on jacks at the wing jack points 2 Remove the air valve cap depress 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 9r it may blow off causing injury to personnel or damage to equipment 4 Carefully remove the valve body assemb...

Page 202: ...ately 1 32 inch in diameter through the hole in the disc at the aft end of the piston 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 again...

Page 203: ...ign matter at least once during each 50 hour operating period In adverse climatic conditions or if the airplane is stored preflight inspection is recommended TO REMOVE AND CLEAN THE FILTER 1 Remove the fuselage nose section grill 2 Remove the wing nuts securing the fitter and remove the filter 3 Clean as described in the manufacturer s instructions on the filter VACUUM SYSTEM The vacuum system inc...

Page 204: ... on the rear engine baffle The foam rubber suction screen should be washed with soap and water every 100 hours of normal operation lf the aircraft is op erated in dusty conditions the filter should be cleaned more frequently The in line filter is located between the pressure regulator and the instruments This filter should be changed every 300 hours of operation PROPELLER BLADES The daily prefligh...

Page 205: ...and oil KEEP FIRE AND SPARKS AWAY FROM OXYGEN Use only recommended leak testing soaps 1 On earlier model Debonairs prior to CD 932 check cylinder pressure by slowly opening the shut off valve on the oxygen console forward and to the left of the pilot seat On later model Debonairs serial CD 932 and after the cylinder pressure is connected directly to the pressure gage on the console 2 The gage will...

Page 206: ...e increased an additional 3 5 psi for each degree of increase in temperature Similarly for each degree of drop in temperature reduce the cylinder pressure 3 5 psi 6 Close the cylinder shutoff valve close the supply 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 ...

Page 207: ... be removed by employing normal cleaning methods GENERATOR Since the generator and voltage regulator are designed for use an only one polarity system the following precautionary measures must be observed when working an the charging circuit or serious damage to the electrical equipment will result 1 When installing a battery make certain that the ground polarity of the battery and the ground polar...

Page 208: ... the negative batterv terminals together and the positive battery terminals together 3 When using a battery charger connect the positive lead of the charger to the positive battery terminal and the negative lead of the charger to the negative battery terminal 4 Do not operate an alternator on open circuit Be sure all circuit connections are secure 5 Do not short across or ground any of the termina...

Page 209: ...of the magneto should be removed ClEANING EXTERIOR PAINTED SURFACES 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 protective lubri cant allowing moisture from heavy or pro longed rain to collect at hinge lines and then to freeze at...

Page 210: ...hes seal the paint from the air and prevent curing CAUTION Alkyd enamel sometimes called automotive 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...

Page 211: ... and moving pans Hand washing may be accomplished by flushing away loose dirt with clean water then washing with a mild soap and water using soft cleaning cloths or a chamois Avoid harsh abrasive or alkaline 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 resid...

Page 212: ...Section VIII Handling Serv Maint BEECHCRAFT Debonair CJJ Bonanza E33 and F33 INTENTIOhlAllV lEFT BLANK 8 308 Revised March 1983 ...

Page 213: ...loss Epoxy finishes should be waxed on a regular basis and may be polished and buffed to restore appearance should chalking occur For waxing select a high quality automotive or aircraft waxing product Oo 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 per...

Page 214: ... extinguisher fluid anti ice fluid lacquer thinner or glass cleaner These materials will soften plastic and may cause it to craze After thoroughly deaning 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 flan...

Page 215: ...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 216: ...ervice fuel cells Top of wings feading edge Check battery e ectrolyte Under right cowling door Change engine oil Lower side of engine Clean fuel injection control Lowar engine compartment valve screen Clean induction air filtar Behind nose section grill Drain static air lines Behind aft cabin side panel C33 thru CD 1013 access door LUBRICANT Number refers to item on Consumable Materials 5 6 See Sh...

Page 217: ...ake fiiter as necessary Lubricate aileron controi linkage Lubricate cabin door mechanism Lubricate control column linkage Behind aft cabin bulkhead Wheel wells K Left side belly Engine compartment Engine compartment I_ t acn wmg J Aft edge of cabin door E Forward of instrument panel C a Unless BEECHCRAFT S I 0448 211 has been complied with lf Applicable 4 7 7 4 10 4 4 1 13 0 0 o m m 2 er m III 0 r...

Page 218: ...weil door hinges L N Lubricate landing gear Wheel wells A K retract mechanism and uplock rol ers Lubricate nose wheel Nose wheel weil B steering mechanism Lubricate rudder pedals Cockpit M Lubricate trim tab control Control pedestal 0 tt Lubricate whee bearings Nose and main wheels A K and feit seals After BEECHCRAFT S I 0448 211 has been cornplied with LUBRICANT Number refers to item on Consumabl...

Page 219: ...ricate fiep actuators 1 Lubricate flap flex driveshafts Lubricate elevator tab actuators Under front seats in cabin G Under front seats in cabin F 8 Forward of Airborne Mfg 1J4 7 instrument panel Under front seats in cabin F 3 Under front seats in cabin G 10 Inside wing aft of wheel 9 weit G Under floor in cabin 10 Inside each horizontal 10 stabilizer 1 wem o mm i er m fll o n i6 t 111 n mn c c c ...

Page 220: ...se gear 2 Drain static air lines Behind aft cabin side panel C33 thru C0 1013 access door Remove one end of the hose which forms the static line drain and permit the system to drain Drain static air lines Behind aft cabin bulkhead CD 1014 thru CD 1254 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 he...

Page 221: ...mulative hour of use or after 50 of the useful charge life Non rechargeable Batteries Replace after one cumulative hour of use or after 50 of the useful charge life t Lubricate aileron control rod ends in place using SAE 20 or SAE 1OW30 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 covera...

Page 222: ...SectionVlll Handling Serv Maint BEECHCRAFT Debonair C33 Bonanza E33 and F33 LUBRICATION POINTS A B CDE F G N M l K A NOSE GEAR RETRACT 8 40 August 1982 ...

Page 223: ...BEECHCRAFT Debonair C33 Bonanza E33and F33 Section VIII Handling Seiv Maint B NOSE WHEEL STEERING c CONTAOL COLUMN UNKAGE D ELEVATOR TRIM CONTROL August 1982 8 41 ...

Page 224: ...SectionVlli Handling Serv Meint BEECHCRAFT Debonair C33 Bonanza E33 and F33 E F LANDING GEAR ACTUATOR GEAR BOX FLAP MOTOR AND ACTUATOR 8 42 August 1982 ...

Page 225: ...BEECHCRAFT Debonair C33 Bonanza E33 and F33 H SectionVlll Handling Serv Maint ELEVATORS AND RUDDER CONTROL MECHANISM ELEVATOR TAB MECHANISM J AILERON BELL CRANKS August 1982 8 43 ...

Page 226: ...SectionVlll Handling Serv Maint BEECHCRAFT Debonair C33 Bonanza E33 and F33 MAIN GEAR RETRACT MAIN GEAR DOOR HINGES M RUDDER PEDALS 8 44 August 1982 ...

Page 227: ... N SectionVlll Handling Serv Meint NOSE GEAR DOOR HINGES 1 HAND 01 PACK FLUID CONTAINER AEROSOL CAN ZERK FITTING SOUIRT CAN NOTE Letters are keyed to the Service Schedule Numbers refer to items in the Consumable Materials Chart August 1982 8 46 ...

Page 228: ...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 focally procurable which conform to the requirements of the applicable Military Specification may be used eve...

Page 229: ... No 5 with MIL G 81322 Thoroughly clean grease from bearings and bearing area before chan 1ing grease Hydraulic Fluid Mll H 5606 lubricating Grease MIL G 81322 General Purpose Wide Temperature Lubricating Oil SAE No 20 or SAElOW 30 Engine Oil SAE No 30 Below 40 F SAE No 50 Above 40 F Approved Multiviscosity Oils Engine Fuel Grade 80 87 Red Solvent federal Specification PD680 lubricant Mobil Compou...

Page 230: ...rade 75W 10 Grease Aircraft and Instrument MIL G 23827 t 11 Lubricant Rubber Seal Oakite 6 Compound 12 Naptha Aliphatic Federal Specification TI N 95 tt13 Tape Anti Seize MIL T 27730 Tetrafluorethylene 14 Leak Test Compound MIL L 25567 Oxygen Systems 15 Oxygen Aviators MIL 0 27210 Breathing 16 Lubricant BRAYCO 300 HCRC 3 36 HLPS No 1 WO 40 8 48 August 1982 ...

Page 231: ...eak in period See ser vicing data lf 80 87 RED grade fuel not available use 100LL BLUE or 100 GREEN grade fuel t Product of Oakite Products linc 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 Product of CRC Chemicals nc Warminster Pa 18974 HProduct of LPS Research L1 1boratories lnc 2050 Cotner Ave W Los...

Page 232: ...il Exxon Company Exxon Aviation Oil EE U S A Gulf Oil Corporation Gulfpride Aviation AD Mobil Oil Company Mobil Aero Oil Pennzoll Company Pennzoil Aircraft Engine OH Phillips Petroleum Co Phillips 66 Aviation Oil Type A Ouaker State Oil Refining Corp Red Ram Limited Canada 8 50 Phillips X C Aviation Multiviscosity Oil SAE 20W 50 Phillips X IC Aviation Multiviscosity Oil SAE 25W 60 Quaker State AD ...

Page 233: ...l W Sindair Refining Co Sinclair Avoil Texaco lnc Texaco Aircraft Engine Oil Premium AD Union Oil Co of Union Aircraft Engine Oil California NOTE This chart lists all oils which were certified as meeting the requirements of Teledyne Continental Motors Specification MHS 24B at the time this handbook was published Any other oil which conforms to this specification may be used August 1982 8 61 ...

Page 234: ...lights C33 Engine instrument lights C33 Instrument light overhead C33 E33 F33 Instrument light post Optional landing gear position light landing gear visual position light landing light Navigation light tail cone Navigation light wing Rotating beacon Grimes Rotating beacon Whelen Overvoltage warning light Strobe lights 8 52 NUMBER 330 89 53 1813 53 330 1891R 89 1816 330 330 53 4313 93 1512 A 7079 ...

Page 235: ...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 anqtor lack of lubrication In these areas periodic inspections should be performed until t...

Page 236: ...y 2000 hours Every 2000 hours Every 4000 hours Every 1000 hours Every 500 hours or on condition Every 1000 hours On condition On condition On condition On condition On condition On condition On condition POWER PLANT NOTE When an engine has been overhauled or a new engine installed it is recommended that low power settings not be used until oil consumption has stabilized The average time for piston...

Page 237: ...n replace when contaminated 1500 hours or 4 v ears 0 1500 hours or 5 years On condition At engine overhaul but not to exceed 1500 hours or 3 years Every 1500 hours lnspect every 100 hours FUEL SYSTEM Fuel cells Wing fuel quantity transmitters Fuel cell drain valve Fuel system check valves Fuel selector 11al11e Auxiliary fuel pump All hose August 1982 On condition On condition On condition On condi...

Page 238: ...re indicator All hose Vacuum system filter Vacuum regulator valve Pressure system filter Air pressure regulator valve On condition Every 24 months per FAA Directive lnspect and Calibrate On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition Every 100 hours On condition Every 300 hours...

Page 239: ...very 2000 hours Every 2000 hours Every 2000 hours MISCELLANEOUS Seat belts Hand fire extinguisher Cabin heating and venti lati ng ducts Oxygen regulator Ü ygen cylinder August 1982 lnspect every 12 months 11 eplace on condition nspect 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 aft...

Page 240: ...tention to throttle response smooth power and oil consumption a qualified certificated mechanic must detennine that the engine is operating normally at the time of each periodic inspection Refer to Hartzell Propeller lnc Service Letter No 61 F dated August 31 1979 or later issue Applies on y to propellers with hub serfal number 71XXXX and higher all other propellers 1200 hours or 5 years 8 58 Augu...

Page 241: ... 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 airpiane was delivered new from the factory should be placed in this SUPPLEMENTS Section of this Pilot s Operating Handbook and FAA Approv...

Page 242: ... Supplements BEECHCRAFT Debonair C33 Bonanza E33 and F33 9 2 NOTE Supplements applicable to equipment other than that installed may at the discretion of the owner operator be removed from the manual August 1982 ...

Page 243: ... ßight operation when subjecl equipment is iflslal jd Supp Part Rev No Number SubjeCI No Date 1 33 590013 3 Tactair T 3 Autopilot 3 9177 2 33 500002 1 Taclair T 3AL anc1 1 9177 T 3All Autopilot 3 35 590110 13 Landing Gear Safety System 5 4181 4 33 534033 9 Filth Seal 1 9fT7 Side Facing 5 130694 Electrothermal 1 10 n Prop Deice 6 36 590002 39 Fuel Selector Valve Ml3 Stop Installation llarch 1983 ...

Page 244: ...SectionlX Supplements BEECHCRAFT Debonair C33 Bonanza E33 and F33 INTENTIONALLY LEFT BLANK 9 4 August 1982 ...

Page 245: ...s the Pilot s Operating Handbook only where covered in the items con tained herein UMITATIONS 1 Autopilot operation not certificated above 20 000 feet 2 Do not use autopilot during take off or landing EMERGENCYPROCEDURES 1 Maximum altitude lost during maltun tioning tests in cruise configuration 100 feet 2 Maximum altitude lost during malfunctioning test in approach configuration 100 feet 3 lf a d...

Page 246: ...ed Check for leakage at the earliest convenience NOTE The Altitude Hold may be overpowered manually however upon release of the 1 controls the airplane will attempt to return to the set altitude unless Altitude Hold is dis engaged before changing altitude NORMAL PROCEDURES 1 To Engage Autopilot Trim airplane for cruising flight Have Course Selector Card coincide with Directional Gyro heading Set P...

Page 247: ...ne to desired heading if within 800 of either side of desired heading Past 80 the Heading Lock will turn the airplane to the reciprocal of th heading requested All corrections using the Course Selector Knob have a turn rate of approxi mately 1 per sscond The tab beneath the Turn Knob can be moved left or right to shift the roll zero point up to two degrees in the corrosponding direction When desir...

Page 248: ......

Page 249: ...cordance with BEECHCRAFT FAA approved data The information in this document supersedes the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual 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 malfun...

Page 250: ... dis engage Altitude Hold by pushing knob i n Then re engage Altitude Hold as indicated above lf it still deviates a malfunction exists and the Altitude Hold should be disengaged Check for leakage at the earliest convenience NOTE The Attitude Hold may be overpowered manually however upon release of the controls the airplane will attempt to retur n to the set altitude unless Altitude Hold is disen ...

Page 251: ...ed turns left or right up to 26 bank angles can be made by rotating Turn Control Knob off center Operation of the Turn Knob off center disconnects the Heading Lock When the Turn Knob is set at center of level flight the Heading Lock button can be pulled out to provide heading reference to the Directional Gyro Heading can be selected by setting the upper card of the Directional Gyro with the Course...

Page 252: ... takeoff and at a safe altitude engage the Basic Autopilot as above Tune in Omni Station and set Omni Bearing Selector to the desired course Set the Directional Gyro Course Card to match the Omni Bearing Selector and select the HOG Switch to ON Engage the Omni Lock Switch lf Localizer Adapter is installed select VOR LOC Switch to VOR and Autopilot NAV Switch to ON b Operation of Omni Lock lf the O...

Page 253: ... Omni needle will remain to one side of center up to several de grees depending on wind velocity and direction if it is desired to fly with the Omni needle centered the D G Course Card should be turned to align with the D G Heading Card When the Autopilot is coupled to COMM NAV equipment in lieu of only NAV equipment the Omni lock is automatica ly neutralized whenever the microphone button is depr...

Page 254: ...craft heading is the same as Course Card setting To track exact center of localizer beam D G Course Card should be turned to align it with D G Heading Card to efiminate effects of crosswind and gyro precession When the Autopilot is coupled to COM NAV equip ment in tieu of only NAVequipment LOC mode is automatically neutralized whenever microphone button is depressed Autopilot then reverts to HDG m...

Page 255: ...PERFORMANCE No change FAA Approved Approved 4ßßi f or Chester A Rembleske Beech Aircraft Corporation DOA CE 2 Revised September 1977 P N 33 600002 1 7 of 7 ...

Page 256: ......

Page 257: ...ument 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 des1gned to help prevent gear up landings and premature or inadvertent operation of the landing gear mechanism The system is tobe used as salety backup device only normal usage ot the landing gear position ...

Page 258: ...ion 5 Airplanes equipped with on off and press to test switches Place the ON OFF switch in the ON position and push the PAESS 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 ON ...

Page 259: ... IAS and 3 the engine is operating at a throttle position corresponding to approximately i 8 to 20 inches or more of manilold pressure depending on setting NOTE lf landing gear retraction is desired before the indicated airspeed reaches approxHTiately 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 260: ......

Page 261: ...d FAA Approved Airplane Flight Manual when the airplane is equipped with a fifth seat installation in accordance with Beech FAA Approved Data This document supersedes or adds to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only where covered in the items contained herein UMITATIONS PLACARDS On Baggage Door NO SMOKING IN FIFTH SEAT e MAXIMUM FIFTli SEAT e STRUCTURAL CA PAC...

Page 262: ...RGENCY PROCEDURES No change NORMAL PROCEDURES No change PERFORMANCE No change 2of 2 Approved fc t Chester A Rembleske Beech Aircraft Corporation DOA CE 2 FAA Approved Revised September 1977 P N 33 534033 9 ...

Page 263: ... 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 accordance with Beech Kit 35 9001 35 9003 or 35 9005 This docurnent supersedes or adds to the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only where covered in the items contained herein llMITA...

Page 264: ...s 3 Blade lf propeller deice system ammeter occasionally or regularly indicates less than 20 amps 2 blade 30 amps 3 blade operation of the propeller deice svstem can continue unless serious propeller im balance results from irregular ice throw offs c More than 24 Amps 2 Blade More than 34 Amps 3 Blade lf the propeller deice system ammeter occasionally or regularly indicates more than 24 amps 2 bla...

Page 265: ...propeller deice switch to the ON position The system will function au tomatically until the switch is turned oft CAUTION The system is not to be operated continuously due to its electrical load 2 Propeller imbalance may be relieved by varying rpm lncrease rpm briefly and return to desired setting re peating if necessary 3 The use of propeller deice is acceptable only if the electrical load is moni...

Page 266: ......

Page 267: ...RPLANE FUGHT 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 lnstructions No 1248 This doc...

Page 268: ...th the Brittain wing tip fuel system LIMITATIONS PLACARDS On Fuel Selector Panel lEFT RIGHT ANO OFF NOT IN SAME VPOSITIONS ON All V BONANZAS and toEPRESS STOPl TURN HANDLE L TO OFF _J EMERGENCY PROCEDURES No Change 2of4 FAA Approved lssued March 1983 PIN 36 590002 39 ...

Page 269: ...at is m re nearly full On airplanes equipped with the fuel selector valve stop installation BEECHCRAFT Service lnstructions 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 270: ...he 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 lf the engine stops because of insufficient fuel refer to the EMERGENCY PROCEDURES Section for the Air Start procedures Approved 4of4 W H Schu tz Beech Aircraft Corporation DOA CE 2 FAA Approved lssued March 1983 PIN 36 590002 39 ...

Page 271: ...irman s Information Manual 10 11 Airman s Information Manual 10 11 Advisory lnformation 10 13 FAA Advisory Circulars I0 13 FAA General Aviation News I0 18 FAA Accidenl Prevention Program I0 19 GENERAL INFORMATION ON SPECiFIC TOPICS 10 20 Flight Planning 10 20 Passenger Information Cards 10 21 lnspections Maintenance 10 22 Flight Operations 10 22 General 10 22 Turbulent Weather I0 22 Flight in king...

Page 272: ... of Climb Speed Vyse 10 42 Best Single Engine Angle of Climb Airspeed Vxse I0 43 Single Engine Service Ceiling 10 44 Basic Single Engine Procedures 10 44 Engine Failure on Take Off I0 45 When to fly Vx Vy Vxse and Vyse I0 46 Stalls Slow Flight and Training 10 47 Spins 10 50 Descent 10 55 Vortices Wake Turbulence I0 56 Takeoff and Landing Conditions I0 57 Medical Facts for Pilots 10 58 General 10 5...

Page 273: ...BEECHCRAFT SectionX Safety Information TABLE OF CONTENTS Cont d ADDITIONAL INFORMATION I0 64 Special Conditions I0 66 Maintenance 10 66 March 1981 10 3 ...

Page 274: ... or more of the following placards Owners Manual FAA Flight Manual Pilots Operating Handbook and FAA Approved Flight Manual For simplicity and convenience we will refer to all official manuals in various models as the Information Manual If the airplane has changed ownership the Information Manual may have been misplaced or may not be currenl lf missing or out of date replacement Information Manual...

Page 275: ... built to provide owners and pilots with many years of safe and efficient transportation By maintaining it properly and flying it prudently you will realize its full potential WARNING Because your aircraft is a high performance high speed transportation vehicle designed for operation in a_ three dimensional environment special safety precautions must be observed to reduce the risk of fatal or seri...

Page 276: ...roperly licensed and rated and thoroughly familiar with the contents of the Information Manual to operate the aircraft IMPROPER OPERATION OR MAINTENANCE OF AN AIRCRAFT NO MATIER HOW WELL BUILT INITIALLY CAN RESULT IN CONSIDERABLE DAMAGE OR TOTAL DESTRUCTION OF THE AIRCRAFT ALONG WITH SERIOUS OR FATAL INJURIES TO ALL OCCUPANTS BEECH AIRCRAFT CORPORATION 10 6 March 1981 ...

Page 277: ... in limited detail Here are some condensed Do s and Don ts DO S Be thoroughly familiar with your airplane know its limitations and your own Be current in your airplane or fly with a qualified instructor until you are current proficient Pre plan all aspects of your flight incJuding weather and adequate fuel reserves Use services available Weather briefing in flight weather and Flight Service Statio...

Page 278: ...ols during pre flight inspection and before takeoff Maintain the prescribed airspeeds in takeoff climb descent and landing Avoid big airplane wake turbulence Preplan fuel and fuel tank management before the actual flight Utilize auxiliary tanks only in level cruise flight Take off and land on the fullest main tank Practice emergency procedures at safe altitudes and airspeeds preferably with a qual...

Page 279: ...in a reckless show off careless manner Don t fly into thunderstorms or severe weather Don t fly in possible icing conditions unless the airplane is approved and properly equipped Don t fly close to mountainous terrain Don t apply controls abruptly or with high forces that could exceed design loads of the airplane Don t fly into weather conditions that are beyond your ratings or current proficiency...

Page 280: ...d be prepared for an emergency in the remote event that one should occur You as a pilot have responsibilities under government regulations These are designed for your protection and the protection of your passengers Compliance is mandatory RULES AND REGULATIONS F A R Part 91 General Operating and Flight Rules is a document of law governing operation of aircraft and the owner s and pilot s responsi...

Page 281: ...pilot s responsibility to be thoroughly familiar with all items in F A R Part 91 and to follow them AIRWORTHINESS DIRECTIVES F A R Part 39 specifies that no person may operate a product to which an airwort hiness directive issued by the FAA applies except in accordance with the requirements of that airworthiness directive AIRMAN INFORMATION ADVISORIES AND NOT CES FAA AIRMAN S INFORMATION MANUAL AI...

Page 282: ...ormation on safety and accident and hazard reporting lt is revised at six month interyals and can be purchased locally or from the Superintendent of Documents U S Govemment Printing Office Washington D C 20402 This document contains a wealth of pilot information Among the subjects are Controlled Air Space Services Available to Pilots Radio Phraseology and Technique Airport Operations Clearances an...

Page 283: ...mpie an airport closed terminal radar out of service enroute navigational aids out of service etc Airmen can subscribe to services to obtain FAA NOTAMS and Airman AdvisClries and these are also available at FAA Flight Service Stations FAA ADVISORY CIRCULARS The FAA issues advisory drculars to inform the aviation public in a systemati1c way of non regulatory material of interest Advisory Circulars ...

Page 284: ... 00 6A 00 24 00 30 00 45A 00 46A 00 50 20 50 20 93 20 105 39 7 43 12 60 4 10 14 Aviation Weather Thunderstorms Rufes of Thumb for Avoiding or Minimizing Encounters with Clear Air Turbulence Aviation Weather Services Aviation Safety Reporting Program Low Level Wind Shear Plane Sense Flutter Due to Ice or Foreign Substance on or in Aircraft Control Surfaces Engine Power Loss Accident Prevention Airw...

Page 285: ... IOA 61 12 J 61 19 61 21 6l 231A 61 278 61 32B 61 34 B March 1981 Instrument Rating Written Test Guide Pilot Transi1tion Courses for Complex Single Engine and Light Twin Engine Airplanes Private and Commercial Pilots Refresher Courses Student Pilot Guide Safety Hazard Associated with Simulated Instrument Flights Flight Training Handbook Pilot s Handbook of Aeronautical Knowledge Instrument Flying ...

Page 286: ... Pilot Airplane Flight lnstructor Practical Test Guide Part 61 Revised Certification Pilot and Flight lnstructors Hazards Associated with Spins in Airplanes Prohibited from Intentional Spinning Flight lnstructor Instrument Airplane Written Test Guide Commercial Pilot Airplane Written Test Guide Flight lnstructor Airplane Written Test Guide Role of Preflight Preparation Medica1 Handbook for Pilots ...

Page 287: ...m ARTS III Recommended Standard Traffic Pallems for Airplane Operations at Uncontrolled Airports Waier Slush and Snow on runway Use of Oxygen by General Aviation Pilots Passengers Annual lnspection Reminder Cold Weather Operation of Aircraft The use of View Limiting Devices on Aircraft Pilot s Weight and Balance Handbook Aircrafl Hydroplaning or Aquaplaning on Wet Runways 91 25A Loss of Visual Cue...

Page 288: ... Dioxide Dry lce Aboard Aircraft 150 5200 3A 210 IA 210 5 Bird Hazards to Aircraft National Notice to Airmen System Military Flying Activities Advisory Circulars that are for sale FAA GENERAL AVIATION NEWS FAA General Aviation News is published by the FAA in the interest of flight safety The magazine is designed to promote safety in the air by calling the attention of general aviation airmen to cu...

Page 289: ...conducts seminars and workshops and distributes invaluable safety information under this program Usually the airport manager the FAA Flight Service Stations FSS or Fixed Base Operator F B 0 will have a ist of accidenl prevention counselors and their phone numbers available All Flight Standards and General Aviation District Offices have a ist of the counselors serving the district Before flying ove...

Page 290: ...nd destination weather and enroute navaid information Enroute terrain and obstructions alternate airports airport runways active length of runways and take off and landing distances for the airplane for conditions expected should be known The prudent pilot will review his planned enroute track and stations and make a ist for quick reference It is strongly recommended a flight 1 lan be filed with F...

Page 291: ...oduction airplanes passenger information cards which contain important information on the proper use of restraint systems oxygen masks emergency exits and emergency bracing procedures Passenger i nformation cards may be obtained at any Beechcraft Aviation or Aero Center A pi1ot should not oniy be familiar with the information contained in the cards himself but should prior to flight always inform ...

Page 292: ...n and that proper maintenance records are kept Each airplane has a checklist for the pre flight inspection which must be followed USE THE CHECKLIST FUGHT OPERATIONS GENERAL The pilot must be thoroughly familiar with all information published by the manufacturer concerning the airplane and is required by law to operate the airplane in accordance with the FAA Approved Airplane Flight Manual and or p...

Page 293: ...s Thunderstorms squall lines and violent turbulence should be regarded as extremely dangerous and must be avoided Hai and tornadic wind velocities can be encountered in thunderstorms that can destroy any airplane just as tornadoes destroy nt arly everything in their path on the ground Turboprop Engines Thund rstorms also pose the possilbility of a lightning strike on an aircraft Any structure or e...

Page 294: ...d flight in turbulent air may be encountered unexpectedly under certain conditions The following recommendations should be observed for airplane operation in turbulent air Flying through turbulent air presents two basic problems the answer to both of which is proper airspeed On one hand if you maintain an excessive airspeed you run the risk of structural damage or failure on the other hand if your...

Page 295: ...ng forward or back pressure to keep the nose level Maintain straight and level attitude in either up or down drafts Use trim sparingly to avoid being grossly out of trim as the vertical air columns change velocity and direction If necessary to avoid excessive airspeeds lower the landing gear FLIGHT IN ICING CONDITIONS Every pilot of Beech airplanes for that matter the pilot of any airplane should ...

Page 296: ...r Occasional use of deicing anti icing equipment removes prevents accumulation lt does not present a problem if the deicing anti icing equipment is used The rate of accumulation is such that even short encounters become potentially hazardous and use of deicing anti icing equipment or diversion is necessary The rate of accumulation is such that deicing anti icing equipment fails lo reduce or contro...

Page 297: ... in icing conditions and plan the flight accordingly if icing conditions are k nown or forecast along the route Every owner and pilot of an airplane should understand that it is not uncommon to find aircraft equipped with less than the full complement of available systems and equipment For example props and pitot tube may be protected but the aircraft might not have wing boots or tail boots The re...

Page 298: ...ediate diversion by flying out of the area of visible moisture or going to an altitude where icing is not encountered Some mode1s of Beech airplanes were approved for flight in certain limited icing conditions under the FAA s Bureau of Flight Standards Release No 434 Under this release properly equipped airp1anes are approved for flight in light to moderate icing conditions only These aircraft are...

Page 299: ...tornados hurricanes or other phenomena likely to produce severe turbulence airplanes equipped for flight in icing conditions cannot be expected to cope with severe icing conditions as defined by the National Weather Service The prudent pilot must remain alert to the possiblity that icing conditions may become severe and that bis equipment will not cope with them At the first indication that such c...

Page 300: ... the area protected by the boots The fact or extent of ice build up in unprotected areas will not be directly observable from the cockpit Oue to distortion of the wing airfoil increased drag and reduced lift stalling speeds will increase as ice accumulates on the airplane For the same reasons stall warning devices are not accurate and cannot be relied upon in icing conditions Even though the pilot...

Page 301: ... operating even a fully equipped airplane in sustained icing conditions must remain sensitive to any indication such as observed ice accumulation loss of airspeed the need for increased power reduced rate of climb or sluggish response that ice is accumulating on unprotected surfaces and that continued flight in these conditions is extremely hazardous regardless of the performance of the deicing an...

Page 302: ... important ingredients to safe flight in icing conditions regardless of the aircraft or the combination of deicing anti icing equipment are a complete and current weather briefing sound pilot judgment close attention to the rate and type of ice accumulations and the knowledge that severe icing as defined by the National Weather Service is beyond the capability of modern aircraft and immediate dive...

Page 303: ...ects of topographic features on weather conditions Many good articles have been published and a synopsis of mountain flying operations is included in the FAA Airman s Information Manual Part l Avoid flight at low altitudes over mountainous terrain parlicularly near the lee slopes lf the wind velocity near the level of the ridge is in excess of 25 knots and approximately perpendicular to the ridge ...

Page 304: ...raft may exceed the climb capability of your airplane Avoid mountain wave downdrafts VFR LOW CEIUNGS lf 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 is an extremely hazardous position for the VFR pilot Accepting a clearance out of certain airport control zone...

Page 305: ...ime to miss them Flight on dark nights over sparsely populated country can be the same as IFR and must be avoided by inexperienced or non IFR rated pilots VERTIGO DISORIENTATION Disorientation can occur in a variety of ways During flight inner ear balancing mechanisms are subjected to varied forces not normally experienced on the ground This combined with loss of outside visual reference can cause...

Page 306: ...ing flights The VFR pilot should use extra caution in avoiding low visibility conditions Motion sickness often precedes or accompanies disorientation and may further jeopardize the flight Disorientation in low visibility conditions is not limited to VFR pilots Although IFR pilots are trained to look at their instruments to gain an artificial visual reference as a replacement for the loss of a visu...

Page 307: ... 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 separatuon or as a high speed ground impact and they are fatal accidents in either case All airplanes are subject to this form of accident For years Beech Information Manuals have contained instructions that the landing gear should be extended in ...

Page 308: ... a certain speed max imum maneuvering speed As a result the control surfaces should riever be suddenly or fully deflected above maximum maneuvering speed Turbulence penetration should not be performed above that speed The accidents we are discussing here occur at airspeeds greatly in excess of these limitations No airplane should ever be flown beyond its FAA approved operating limitations FLIGHT O...

Page 309: ...ne obviously represents a 50 loss of horsepower but in virtually all light twins climb performance is reduced by at least 80 A study of the harts in your Information Manual will confirm this fact Single engine climb performance depends on four factors Airspeed Drag Power Weight too little or too much wili decrease climb performance gear flaps cowl flaps prop and speed amount available in excess of...

Page 310: ...es may be balanced by banking slightly up to 5 into the operating engine Airspeed is the key to safe single engine operalions For most light twins there is an airspeed below which directional control cannot be maintained airspeed below which an intentional engine cut should never be made airspeed that wm give the best single engine rate of climb or the slowest loss of altitude airspeed that will g...

Page 311: ...heading change and thereafter maintain straight flight with not more than 5 degrees of bank if one engine fails suddenly with Take off power on both engines Rearmost allowable center of gravity Flaps in takeoff position Landing gear retracted Propeller windmilling in takeoff pitch configuration or feath red if automatically featherable However sudden engine failures rarely occur with all of the fa...

Page 312: ...e INTENTIONAL ONE ENGINE INOPERA TIVE SPEED Vsse Vsse is specified by the airplane manufacturer and is the minimum speed at which to perform intentional engine cuts Use of Vsse is inlended to reduce the accident potential from loss of control after engine cuts at or near minimum control speed Vmca demonstrations are necessary in training but should only be made at a safe altitude above the terrain...

Page 313: ...gle Drag caused by a windmilling propeller extending landing gear or flaps in the landing position will severely degrade or destroy single engine climb performance Since engine climb performance varies widely with type of airplane weight temperature altitude and airplane configuration the climb gradient altitude gain or loss per mile may be marginal or even negative under some_conditions Study the...

Page 314: ...g chart should be used during flight planning to determine whether the airplane as loaded can maintain the Minimum Enroute Altitude MEA if IFR or terrain clearance if VFR foJlowing an engine failure BASIC SINGLE ENG NE PROCEOURES Know and follow to the letter the single engine emergency procedures specified in your Information Manual for your specific make and model airplane However the basic fund...

Page 315: ...o be sure that the inoperative engine is secured properly and that the appropriate switches are placed in the correct position The airplane must be banked about 5 into the live engine with the sliplskid ball out of center toward the live engine to achieve rated performance Another note of caution Be sure to identify the dead engine positively before feathering it Remember First identify the suspec...

Page 316: ...g the runway length required to stop if the engine fails before reaching lift off speed and also has charts showing single engine performance after lift off Study your charts carefully No airplane is capable of climbing out on one engine under all weight pressure altitude and temperature conditions Know before you take the actual runway whether you can maintain control and climb out if you lose an...

Page 317: ... must be kept operational at all times and must not be deactivated by interruption of circuils circuit breakers or fuses Compliance with this requirement is especially important in all high performance single and multi engine airplanes during engine out practice or stall demonstrations because the stall speed is critical in all low speed operations of high performance airplane Training should be a...

Page 318: ...ecommended Single engine stalls have never been required by the FAA regulations for multi engine flight tests and should not be pracliced in high performance airplanes by other than qualified engineering test pilots Engine out minimum control speed demonstrations in multi engine airplanes should be conducted in w 0 t w a Cf Cf UJ a a Vmca Rela ionship Between Stall Speed And Vmca For Aircraft With...

Page 319: ... below which an engine should not be intentionally rendered inoperative for practice purposes was established because of the apparent practice of some pilots instructors and examiners of intentionally rendering an engine inoperative at a time when the airplane is being operated at a speed close to or below the power idle stall speed Unless the pilot takes immediate and proper corrective action und...

Page 320: ...er Vmca or stall warning which may be evidenced by inability to maintain longitudinal lateral or directional control aerodynamic stall buffet or stall warning horn sound recovery must be initiated immediately by reducing power to idle on operative engine and lowering the nose to regain Vsse Resume normal flight This entire procedure should be used at a safe altitude of at least 5 000 feet above th...

Page 321: ...ainst intentional spins The pilot of an airplane placarded against intentional spins should assume that the airplane may become uncontrollable in a spin since its performance characteristics beyond certain limits specified in the FAA regulations may not have been tested and are unknown This is why aircraft are placarded against intentional spins and this is why stall avoidance is your protection a...

Page 322: ...awing motion may develop even against full aileron and rudder resulting in the airplane becoming inverted during the onset of a spinning motion Once the airplane has been permitted to progress beyond the stall and is al1owed to reach the rapid rolling and yawing condition the pilot must then immediately initiate the generally accepted spin recovery procedure for multi engine airplanes which is as ...

Page 323: ...center of gravity of the airplane is as far forward as possible Forward C G aids stall recovery spin avoidance and spin recovery An aft C G can create a tendency for a spin to flatten out which delays recovery 2 Whenever a student pilot will be required to practice slow flight or single engine maneuvers be certain that the qualified instructor pilot has a full set of operable controls in front of ...

Page 324: ...se Recognize that under some conditions of weight densit y altitude and aircraft configuration a twin engine aircraft cannot climb or accelerate on a single engine Hence a single engine go around is impossible and the aircraft is committed to a landing Plan your approach accordingly 5 Remember that if an airplane flown under instrument conditions is permitted to stall or enter a spin the pilot wit...

Page 325: ...n the engine may not respond to the throttle when it is desired to discontinue the desc nt Both problems are amenabie to one solution maintain adequate power to keep cylinder head temperatures in the green range during descent and lean to best power mi xture that is progressively enrich the mixture from cruise only slightly as altitude decreases This pr edure will lengthen the descent of course an...

Page 326: ... in nature from each wing tip In tests vortex velocities of 133 knots have been recorded Encountering the rolling effect of wing tip vortices within two minutes after passage of arge airplanes is most hazardous to light airplanes This roll effect can exceed the maximum counter roll obtainable in a light airplane The turbulent areas may remain for as long as three minutes or more depending on wind ...

Page 327: ...rmal allowing the wheels to spin and dissipate the freezing moisture The landing gear should then be cycled up then down wait approximately five seconds and then retract again Caution must be exercised to insure that the entire operation is performed below Maximum Landing Gear Operating Airspeed Use caution when l nding on runways that are covered by water or slush which cause hydroplaning aquapla...

Page 328: ...he pilot in pre flight planning would be as senseless as failing to inspect the integrity of the control surfaces or any other vital part of the machine The pilot himself has the responsibility for determining his reliability prior to entering the airp1ane for flight When piloting an airplane an individual should be free of conditions which are harmful to alertness ability to make correct decision...

Page 329: ...kohol and various drugs decrease the brain s tolerance to hypoxia Your body has no built in alarm system to let you know when you are not getting enough oxygen lt 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 sensati...

Page 330: ...lity may also vary in the same individual from day to day or even morning to evening Use oxygen on flights above I0 000 feet and at any time when symptoms appear Depending upon altitude an hypoxic individual has a limited time to make decisions and perform useful acts even though he may remain conscious for a longer period lf pressurization equipment fails at certain altitudes the pilot and passen...

Page 331: ...f respiration that may occur in individuals as a result of emotional tension or anxiet y Under conditions of emotional stress fright or pain breathing rate may increase causing increased lung ventilation ahhough the carbon dioxide output of the body cells does not increase As a result carbon dioxide is washed out of the blood The most common symptoms of hyperventilation are dizziness hot and cold ...

Page 332: ...alcohol constriction of visual fields decreased ability to see under dim illuminations loss of efficiency of sense of touch decrease of memory and reasoning ability increased susceptibility to fatigue and decreased attention span decreased relevance of response increased seif confidence with decreased insight into immediate capabilities Tests have shown that pilots commit major errors of judgment ...

Page 333: ... a pilot may still be under influence eight hours after drinking a moderate amount of alcohol Therefore an excellent rule is to allow at least 12 to 24 hours between bottle and throttle depending on the amount of alcoholic beverage consumed DRUGS Self medication or taking medicine in any form when you are flying can be extremely hazardous Even simple home or over the counter remedies and drugs suc...

Page 334: ...nds at altitudes even under 10 000 feet where most light planes fly CARBON MONOXIDE AND NIGHT VISION The presence of carbon monoxide results in hypoxia which will affect night vision in the same manner and extent as hypoxia from high altitudes Even smalt levels of carbon monoxide have the same effect as an altitude increase of 8 000 to 10 000 feet Smoking several cigarettes can result in a carbon ...

Page 335: ...tions Flight Service Stations or Airport Facilities and are very good sources of information and are highly recommended for study Some of these are titled Airman s Information Manual 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 lcing Pilot s Weather Briefing Guid...

Page 336: ...dder Some Hard Facts About Soft Landings Propeller Operation and Care Torque Whal it Means to the Pilot Weight and Balance An Important Safety Consideration for Pilots SPECIAL CONDITIONS MAINTENANCE 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...

Page 337: ...he earliest possible opportunity A clean dry surface is virtually immune to corrosion Make sure that all drain holes remain unobstructed Protective films and sealants help to keep corrosive agents from contacting metallic surfaces Corrosion inspections should be made most frequently under high corrosion risk operating conditions such as in areas of excessive airborne salt concentrations e g near t...

Page 338: ......

Page 339: ... FLOW GAGE ot r T 1 1 L _1r 1 i L H FUEL TANK i 1SELECTOR R H FUEL TANK l i VALVE l i i STRAINER i i DRAINQ FWD DRAIN i QDRAIN VENT IBJ VENT CHECK STRAINER STRAINER CHECK VALVE l SEAL l VALVE FLUSH VENT DRAIN r FLUSH VENT VENT VENT DJ C CD 0 CD m 1 m III 0 c III m xi w w w i Q Tl w w Cl fll c Cl CD CD g g g 1 0 i ...

Page 340: ...l pump can be used to purge the system of vapor caused by an extremely high ambient temperature or a start with the engine hot The auxiliary fuel pump provides for near maximum engine performance should the engine driven pump fail FUEL TANK SELECTION The fuel selectot 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 mo...

Page 341: ...ION A negative ground external power source is required Check polaritv before using external power lf the external power unit does not have a Standard AN type plug connect the positive lead frqrn the external power source to the positive battery terminal and the negative lead to the negative battery terminal UGHTING SYSTEM INTERIOR UGHTING C33 E33 Lighting for the instrument panel is furnished by ...

Page 342: ...e intensity of the complete subpanel lighting The second rheostat is labeled FLOOD and controls the glareshield lighting which ill minates the full upper panel The cabin dome light is operated by an ON OFF switch ad jacent to the light The optional reading lights above the rear seats have individual switches at the light The op tional map light has a press type switch on the wheel The OAT and comp...

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