Raytheon Beech Bonanza A36, Pilot'S Operating Handbook And Flight Manual

Page 1: ...uring all flight operations This handbook includes the material required to be furnished to the pilot by CAR Part 3 Airplane Serial Number _________________________ Airplane Registration Number ______...

Page 2: ...mpany The export of these commodities technology or software are subject to the US Export Administration Regulations Diversion contrary to U S law is prohibited For guidance on export control requirem...

Page 3: ...plane Flight Manual P N 36 590002 37B Revision B2 January 2006 Title Page January 2006 Logo Page Undated List Of Effective Pages January 2006 Log Of Revisions Revision B2 January 2006 Revision B1 Marc...

Page 4: ...ru 5 40 November 2002 6 1 thru 6 3 November 2002 6 4 March 2003 6 5 thru 6 20 November 2002 7 1 thru 7 39 November 2002 7 40 and 7 41 January 2006 7 42 thru 7 50 November 2002 8 1 thru 8 32 January 20...

Page 5: ...Page New List of Effective Pages 1 of 2 New 2 of 2 New Log of Revisions 1 of 1 New 1 7 Revised Revising The Handbook 2 11 Revised Maneuver Limits 7 40 and 7 41 Revised Interior Lighting and Shifted Da...

Page 6: ...tle Page New List of Effective Pages 1 of 2 New 2 of 2 New Log of Revisions 1 of 1 New 4 27 and 4 28 Added CAUTION and Shifted Data 5 1 and 5 2 Revised Table of Contents and Shifted Data 5 3 Revised T...

Page 7: ...ual P N 36 590002 37B B Reissue November 2002 Original Issue October 1983 PAGE DESCRIPTION Title Page New List of Effective Pages New Log of Revisions 1 of 1 New 1 1 thru 1 24 2 1 thru 2 30 3 1 thru 3...

Page 8: ...d 1 9 Airplane Three View 1 10 Ground Turning Clearance 1 11 Descriptive Data 1 12 Engine 1 12 Number of Engines 1 12 Engine Manufacturer 1 12 Engine Model Number 1 12 Engine Type 1 12 Horsepower Rati...

Page 9: ...ns 1 14 Cabin Baggage Volumes 1 15 Specific Loadings 1 15 Symbols Abbreviations and Terminology 1 16 General Airspeed Terminology 1 16 Meteorological Terminology 1 18 Power Terminology 1 19 Engine Con...

Page 10: ...read and studied Periodic review will serve as a reminder of good piloting tech niques Use only genuine Raytheon Aircraft or Raytheon Aircraft approved parts obtained from Raytheon Aircraft approved...

Page 11: ...ator in order to become familiar with the operation of the airplane Suggestions and recommendations have been made within it to aid in obtaining maximum performance without sac rificing economy Be fam...

Page 12: ...d in this handbook are considered mandatory for continued airworthiness and to maintain the airplane in a condition equal to that of its original manufacture Raytheon Aircraft Authorized Outlets can p...

Page 13: ...f each section NOTE In an effort to provide as complete cover age as possible applicable to any configu ration of the airplane some optional equipment has been included in the scope of the handbook Ho...

Page 14: ...he sequential revision 1st 2nd 3rd etc to the Original Issue or reissue covered by the Log of Revisions page Reference to the Log of Revisions page s provides a record of changes made since the Origin...

Page 15: ...rcraft Authorized Outlet or refer to the latest revision of Raytheon Aircraft Service Bulletin No 2001 Raytheon Aircraft Company expressly reserves the right to supersede cancel and or declare obsolet...

Page 16: ...contains the FAA approved Airplane Flight Manual Supplements headed by a Log of Supplements page When new supplements are received or existing supple ments are revised a new Log page will replace the...

Page 17: ...1 10 November 2002 Beech Bonanza A36 Section I Raytheon Aircraft WING AREA 181 SQ FT 9 5 MINIMUM CLEARANCE A36 607 31 AIRPLANE THREE VIEW...

Page 18: ...Radius for Wing Tip 27 feet 7 inches Radius for Nose Wheel 13 feet 8 inches Radius for Inside Gear 6 feet 3 inches Radius for Outside Gear 15 feet 10 inches TURNING RADII ARE CALCULATED USING FULL STE...

Page 19: ...MODEL NUMBER IO 550 B ENGINE TYPE Normally aspirated Fuel injected direct drive air cooled hori zontally opposed 6 cylinder 550 cubic inch displacement HORSEPOWER RATING 300 H P NUMBER OF PROPELLERS...

Page 20: ...pre sent minor variations in the propeller hub or blades They do not affect eligibility or interchangeability PITCH SETTINGS 30 INCH STATION Low 13 7 0 2 High 28 8 0 5 PROPELLER DIAMETER Maximum 80 in...

Page 21: ...G SERVICING AND MAINTENANCE for a list of approved oils MAXIMUM CERTIFICATED WEIGHTS Maximum Ramp Weight 3663 lbs Maximum Take off Weight 3650 lbs Maximum Landing Weight 3650 lbs Maximum Zero Fuel Wei...

Page 22: ...VOLUMES Rear Cabin Compartment Rear Spar to Sta 170 0 37 cu ft Extended Aft Compartment Sta 170 0 to 190 0 10 cu ft SPECIFIC LOADINGS Wing Loading at Maximum Take off Weight 20 2 lbs sq ft Power Load...

Page 23: ...peed of an airplane relative to the ground IAS Indicated Airspeed is the speed of an airplane as shown on the airspeed indi cator IAS values published in this hand book assume zero instrument error KC...

Page 24: ...ed limit that may not be exceeded at any time VNO Maximum Structural Cruising Speed is the airspeed that should not be exceeded except in smooth air and then only with caution VS Stalling Speed or the...

Page 25: ...to the altitude at which the tempera ture is 56 5 C 69 7 F is 0 00198 C 0 003566 F per foot and zero above that altitude OAT Outside Air Temperature is the free air static temperature obtained either...

Page 26: ...inds Cruise Climb Power Power recommended for cruise climb Economy Cruise Power Minimum power setting for which specific values of fuel flow and airspeed are pre sented Maximum Cruise Power Maximum po...

Page 27: ...Mixture Control Used to set fuel flow in all modes of opera tion and to cut off fuel completely for engine shutdown Propeller Control Used to control the rpm setting of the pro peller governor Movemen...

Page 28: ...as actually demonstrated during certification tests The value shown is not limiting GPH U S Gallons per hour MEA Minimum Enroute IFR Altitude Route Segment A part of a route Each end of that part is i...

Page 29: ...Weight The weight of an empty airplane before any oil or fuel has been added This includes all permanently installed equipment fixed bal last full hydraulic fluid full chemical toilet fluid and all o...

Page 30: ...ig its Payload Weight of occupants cargo and baggage Reference Datum An imaginary vertical plane from which all horizontal distances are measured for bal ance purposes Station A location along the air...

Page 31: ...1 24 November 2002 Beech Bonanza A36 Section I THIS PAGE INTENTIONALLY LEFT BLANK Raytheon Aircraft...

Page 32: ...6 Approved Engine Fuels 2 6 Fuel Capacity 2 6 Fuel Management 2 6 Oil Specification 2 6 Number of Propellers 2 6 Propeller Manufacturer 2 7 Number of Blades 2 7 Propeller Type 2 7 Pitch Settings 30 in...

Page 33: ...d 2 10 Forward Limits 2 10 Aft Limit 2 10 Reference Datum 2 10 Mean Aerodynamic Chord 2 10 Maneuver Limits 2 11 Flight Load Factor Limits 2 11 Minimum Flight Crew 2 11 Maximum Passenger Seating Config...

Page 34: ...aximum 165 167 Do not exceed this Structural speed except in Cruising smooth air and then VN0 orVc only with caution Maneuvering 139 141 Do not make full or VA abrupt control move ments above this spe...

Page 35: ...Speed for Approach Flaps Green Arc 68 165 68 167 Normal Operating Range Yellow Arc 165 203 167 205 Operate with Cau tion Only in Smooth Air Red Line 203 205 Do Not Exceed This Speed In Any Operation...

Page 36: ...C Oil Pressure Minimum idle 10 psi Maximum 100 psi Fuel Flow Serials prior to E 2165 except those serials complying with Raytheon Service Bulletin No 2024 Maximum 26 2 gph Serials E 2165 and After an...

Page 37: ...Quantity Gages indicate in Yellow Arc or with less than 13 gallons in each main tank Maximum Slip Duration 30 seconds OIL SPECIFICATION Use MIL L 22851 Ashless Dispersant Oils meeting the require men...

Page 38: ...lically Actuated consisting of X 82NDB 2 blades and a D3A32C409 X hub NOTE The letters appearing in the place of the X repre sent minor variations in the propeller hub or blades They do not affect eli...

Page 39: ...psi TACHOMETER Operating Range Green Arc 1800 to 2700 rpm Maximum Red Radial 2700 rpm CYLINDER HEAD TEMPERATURE Operating Range Green Arc 116 to 238 C Maximum Red Radial 238 C MANIFOLD PRESSURE Operat...

Page 40: ...Y Yellow Arc E to 3 8 full WEIGHT LIMITS Maximum Ramp Weight 3663 lbs Maximum Take off Weight 3650 lbs Maximum Landing Weight 3650 lbs Maximum Zero Fuel Weight No Structural Limitation Maximum Weights...

Page 41: ...tum at 3100 lbs or less with straight line vari ation to 81 0 inches at 3650 lbs AFT LIMIT 87 7 inches aft of datum at all weights REFERENCE DATUM Datum is 83 1 inches forward of center line through f...

Page 42: ...AD FACTOR LIMITS MINIMUM FLIGHT CREW One 1 Piot MAXIMUM PASSENGER SEATING CONFIGURATION Six 6 people including pilot APPROVED MANEUVERS MANEUVER ENTRY SPEED KCAS KIAS Chandelle 132 134 Steep Turn 132...

Page 43: ...eat back of an occupied optional copilot s full reclining seat and all other occupied seats must be in the most upright position for take offs and landings Occupied aft facing seats must have head res...

Page 44: ...S MAX MANEUVERING 141 KTS UTILITY CATEGORY AIRPLAtE OPERATE IN ACCORDANCE WITH FAA APPROVED AIRPLANE FLIGHT MANUAL INTENT SPINS PRO IIBITED NOACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED INTHE AIR...

Page 45: ...BLE CAPACITY NOTE LJ DEPRESS STOP TURN HANDLE TO OFF RIGHT MAIN 37 GALUSABLE CAPACITY C95E 02C0072 For Serials E 1946 E 2104 E 2111 thru E 3046 that are in compliance with Raytheon Aircraft S B 2670 a...

Page 46: ...On Fuel Tank Selector Cover Serials E 3047 and After FLEL TANK SELECTOR OFF 0 DEPRESSSTOP TURN HANDLE TO OFF C96EA00C25 I 5 C On Fuel Tank Selector Cover E 2249 and After I REMOVE WINTER BAFFLESWHEN 7...

Page 47: ...S B 28 3052 On Instrument Panel Adjacent To Fuel Flow Gage E 1946 E 2104 E 2111 thru E 3144 In Compliance With Raytheon Aircraft S B 28 3052 r 1 I LEANING I ISCHFEJ RULE I TAKEOFF I I B 1 1 1 iSL 2000...

Page 48: ...AGE HANDLE IN REAR OF FRONT SEAT AND TURN COUNTERCLOCKWISEAS FAR AS POSSIBLE 50 TURNS L C94CE02C 1976 On Landing Gear Emergency Crank Access Cover i L LANDING GEAR EMERGENCY CRANK PULLOUT LIFT UP 7 _J...

Page 49: ...Side Wall When Oxygen Is Installed r OXYGEN NOSMOKING WHEN IN USE L J OSE PLUGMUST BE PULLED OUTTO STOPOXYGEN FLO C94E 02C2442 Adjacent to 5th 6th Seats When Oxygen Is Installed MASKSTOWED UNDER REARS...

Page 50: ...IR SOURCE___ _ ALTERNATE SEE PILOT S OPERATING HANDBOOK PERFORMANCE SECTIONFOR ON AIRSPEEDCALIBRATION ANO ALTIMETER CORRECTION OFF V NORMAL C94E 02C2443 Copilot s Outlet When Oxygen Is Installed C94CE...

Page 51: ...02C 1952 On WindowAdjacent to Pilot s Seat I SHOULDER HARNESS MUST BE WORN I WHILE AT PILOT POSITIONS FOR TAKEOFF AND LANDING SEAT BACK I KJST NOT BE INFULL BACK POSIT C94E 02C2445 On WindowAdjacent t...

Page 52: ...ANDLANDING WITHSEATBACK UPRIGHT On WindowsAdjacentto 3rd 4th Aft FacingClubSeats SHOULDER HARNESS MUSTBE WORN DURING TAKE OFFANDLANDING WITHSEATBACKUPRIGHT ANDAFT FACINGSEATS MUSTHAVEHEADREST FULLYEX...

Page 53: ...GENCY EXIT PULL COVER ROTATE HANDLE UP BREAKING SAFETYWIRE PUSHWINDOW OUT On Emergency Exit Handle 1ROTATEHANDLE up7 BREAKINGSAFETY WIRE LPUSH WINDOW OUT_J C94CE02C l 955 On Inboard Side of Seat Back...

Page 54: ...E 2458 E 2468 and After C94CE02C1956 Adjacent to Cabin Door Handle on Window Moulding Above Utility Door ROTATE HANDLE TO FULL LOCKED POSITION C94CE02Cl958 On Instrument Panel In Full View of Pilot W...

Page 55: ...ST BESECURED 3 PERSONNEL NOT SECURED IN SEATS BYSAFETY BELTS MUST WEAR PARACHUTES C94E 02C2449 NOTE Maximum combined weight of aft seat occupants may be less than 250 lbs if required by CAR 3 74 due t...

Page 56: ...d of this sec tion KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR and day or night IFR conditions when the required systems and equipment are installed and operab...

Page 57: ...r equipment and all limitations are complied with I Numbers in the Kinds of Operations Equipment List refer to quantities required to be operative for the specified condition The list does not include...

Page 58: ...1 1 Exhaust Gas Temp Indicator 1 1 1 1 Manifold Pressure Indicator 1 1 1 1 Tachometer 1 1 1 1 ENGINE OIL Oil Pressure Indicator 1 1 1 1 Oil Temperature Indicator 1 1 1 1 FLIGHT CONTROLS Aileron Trim T...

Page 59: ...Fuel Selector Valve 1 1 1 1 ICE AND RAIN PROTECTION Alternate Static AirSystem ii 0 0 1 1 installed Pitot Heat if installed 0 0 1 1 LANDING GEAR Emergency Landing Gear Exten 1 1 1 1 sion System Landin...

Page 60: ...or EXCEPTIONS PNUMATIC SYSTEM Instrument Air System 0 1 1 1 Standby Instrument Air System 0 1 1 1 Optional Equip if installed ment Std on E 2217 and after Pressure Gage 0 1 1 1 RESTRAINT SYSTEM Seat...

Page 61: ...Beech Bonanza A36 Section II Raytheon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK 2 30 November 2002...

Page 62: ...With Power 3 8 Systems Emergencies 3 9 Propeller Overspeed 3 9 Starter Engaged START Annunciator Illuminated 3 10 Alternator Failure LOW BUS VOLTS Annunciator Illuminated Not Equipped With A Standby...

Page 63: ...Beech Bonanza A36 Raytheon Aircraft SUBJECT SECTION Ill EMERGENCY PROCEDURES TABLE OF CONTENTS Cont d PAGE Unlatched Door In Flight 3 18 Spins 3 18 Emergency Speed Reduction 3 19 3 2 November 2002...

Page 64: ...mergencies requiring immedi ate corrective action are treated in checklist form for easy reference and familiarization Other situations in which more time is usually permitted to decide on and execute...

Page 65: ...Selector Valve OFF 4 Alternator OFF 5 Battery OFF IN FLIGHT If engine failure occurs immediately after takeoff landing straight ahead is usually advisable 1 Airspeed Immediately After Takeoff 85 KTS m...

Page 66: ...art then 1 Aux Fuel Pump OFF 2 Mixture FULL RICH 3 Magnetos CHECK LEFT RIGHT I THEN BOTH 4 Alternate Air T Handle PULL AND RELEASE If still no restart then 1 Select most favorable landing site 2 Use o...

Page 67: ...hat smoke and fumes will not enter the cabin 2 Engine SHUTDOWN a Fuel Selector Valve OFF b Mixture IDLE CUT OFF c Alternator OFF d Battery OFF e Magnetos OFF 3 ENGINE DO NOT ATTEMPT TO RESTART See MAX...

Page 68: ...e landing gear will not retract unless the throttle is in a position cor responding to approximately 17 in Hg manifold pressure or above 2 Flaps UP 3 Cowl Flaps CLOSED 4 Propeller PULL LEVER FULL AFT...

Page 69: ...2468 and after the landing gear will not retract unless the throttle is in a position cor responding to approximately 17 in Hg manifold pressure or above 6 Airspeed ESTABLISH 85 KTS 7 Alternator OFF...

Page 70: ...2468 and after the landing gear will not retract unless the throttle is in a position cor responding to approximately 17 in Hg manifold pressure or above 2 Airspeed REDUCE UNTIL RPM IS AT OR BELOW 27...

Page 71: ...E OFF 4 Mixture IDLE CUT OFF IALTERNA TOR FAILURE LOW BUS VOLTS Annunciator Illuminated Not Equipped with a Standby Alternator An inoperative alternator will place the entire electrical operation of t...

Page 72: ...extinguishes 4 Continue to use the alternator If LOW BUS VOL TS annunciator remains illuminated 5 Alternator Switch OFF 6 Non essential Electrical Equipment OFF TO CONSERVE BATTERY POWER 7 If equippe...

Page 73: ...tive with the battery and alternator off 4 Firewall Air Control PULL if smoke or fire is present in engine compartment 5 All Electrical Switches OFF 6 Dissipation of smoke may be aided by the followin...

Page 74: ...10 Pilot s Storm Window if required OPEN 11 Land AS SOON AS PRACTICAL LANDING GEAR MANUAL EXTENSION 1 Airspeed 154 KTS OR LESS NOTE Manual extension of the gear can be facilitated by first reducing t...

Page 75: ...s retarded to idle 7 Handcrank DISENGAGE THEN STOW 8 Do not move the Landing Gear Handle or reset the LAND ING GEAR MOTOR Circuit Breaker 9 The landing gear should be considered UNLOCKED until the air...

Page 76: ...pproximately 17 in Hg manifold pressure or above INDUCTION SYSTEM ICING An alternate induction air door spring loaded to the closed posi tion is located downstream from the induction air filter If the...

Page 77: ...ed by abnormal indicated airspeed and altitude changes beyond normal calibration differences I Whenever any obstruction exists in the Normal Static Air System or the Alternate Static Air System is des...

Page 78: ...lower inboard side of seat back 2 Fold seat back over TO OPEN THE OPENABLE WINDOW EMERGENCY EXIT 1 Remove cover as indicated by placard in center of open able window ventilation emergency exit latch...

Page 79: ...t 5 Hold door during and after landing to prevent it from swing ing open SPINS Intentional spins are prohibited If an unintentional spin is encountered perform the following procedure IMMEDIATELY THE...

Page 80: ...R 4 Throttle AS REQUIRED 5 Landing Gear AS REQUIRED NOTE If disorientation is possible leave the landing gear down to reduce the tendency of subsequent speed buildups NOTE Should the landing gear be u...

Page 81: ...Beech Bonanza A36 Section Ill Raytheon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK 3 20 November 2002...

Page 82: ...4 1O Cold Starts 4 10 Flooded Engine 4 10 Hot Starts 4 11 After Starting 4 11 Before Takeoff 4 12 Takeoff 4 14 Climb 4 15 Cruise 4 21 Leaning Using The Exhaust Gas Temperature Indicator EGT 4 22 Desc...

Page 83: ...rcraft SECTION IV NORMAL PROCEDURES TABLE OF CONTENTS Cont d SUBJECT PAGE I Cold Weather Operation 4 31 Preflight Inspection 4 31 After Starting 4 32 Descent 4 32 Icing Conditions 4 32 Noise Character...

Page 84: ...r Maximum Demonstrated Crosswind Component 17 Kts Take off Speeds Flaps UP 0 I Rotation 73 Kts I 50 ft 84 Kts Flaps APPROACH 12 Rotation 67 Kts I 50 ft 77 Kts Best Angle of Climb Vx 84 Kts Best Rate o...

Page 85: ...for flight phase procedures for optional equipment installed in the airplane PREFLIGHT INSPECTION 1 CABIN a Parking Brake SET b Control Lock REMOVE c Landing Gear Handle DOWN I d Battery ON e Landing...

Page 86: ...tion Light and Rotating Beacon CHECK d Cabin Air Intake CHECK 4 LEFT FUSELAGE a Cabin Air Exhaust CHECK b Static Pressure Button UNOBSTRUCTED 5 LEFT WING TRAILING EDGE a Protruding Fuel System Vent UN...

Page 87: ...SE SECTION a Left Cowl Flap CHECK b Engine Oil CHECK 10 qts minimum for flight Cap SECURE c Engine CHECK GENERAL CONDITION d Left Cowl SECURE e Propeller CHECK f Wheel Well Doors Tire and Strut CHECK...

Page 88: ...POSITION AND LOCK Seat Backs POSITION FOR TAKEOFF 2 Rudder Pedals ADJUST 3 Seat Belts and Shoulder Harnesses FASTEN ADJUST 4 Parking Brake SET 5 Emergency Gear Handle STOWED 6 Avionics Circuit Breaker...

Page 89: ...gallons in each tank I 23 ELT Switch if installed ARM Transmit Light Extinguished 24 Auxiliary Fuel Pump LO listen momentarily to confirm pump operation 25 Auxiliary Fuel Pump OFF 26 Standby Instrume...

Page 90: ...G ENGINE USING EXTERNAL POWER I UNIT 1 Alternator Switch Battery Switch Electrical and Avionics Equipment OFF 4 External Power Unit SET OUTPUT 2 If a Standby Alternator is Installed SEE SUPPLEMENT I 3...

Page 91: ...Fuel Pump HI UNTIL FUEL FLOW PEAKS THEN OFF I I 5 Throttle CLOSE THEN OPEN APPROXIMATELY 1 2 INCH 6 Magneto Start Switch START Release to BOTH when engine starts 7 Throttle 1000 TO 1200 RPM AFTER STAR...

Page 92: ...Switch START I Release to BOTH when engine starts 9 Auxiliary Fuel Pump if required HI momentarily after starting to purge the system THEN OFF AFTER STARTING 1 Throttle 1000 to 1200 RPM 2 Oil Pressure...

Page 93: ...ECK Never taxi with flat shock strut BEFORE TAKEOFF 1 Parking Brake SET 2 Seat Belts and Shoulder Harnesses CHECK 3 Avionics CHECK 4 Engine Instruments CHECK within operating range 5 Flight Instrument...

Page 94: ...CHECK PRESSURE 11 If equipped with a standby generator I or a standby alternator REFER TO SUPPLEMENT 12 Throttle IDLE TO 1200 RPM 13 Autopilot and Electric Trim if installed CH ECK 14 Trim SET a Ailer...

Page 95: ...wer Full Throttle 2700 RPM Minimum Recommended Oil Temperature 24 C 1 Power SET a Throttle FULL FORWARD b Propeller HIGH RPM c Mixture E 1946 E 2104 E 2111 Thru E 3144 Not In Compliance With Raytheon...

Page 96: ...craft S B 28 3052 1 Power SET Maximum Continuous Power a Mixture FULL RICH b Propeller 2700 RPM c Throttle FULL FORWARD Cruise Climb Power a Mixture FULL RICH b Propeller 2500 RPM c Throttle FULL FORW...

Page 97: ...l Motors S1D97 3 or Raytheon Aircraft S B 28 3052 MANUAL LEANING FUEL FLOW SCHEDULE FOR FULL THROTTLE AND 2700 RPM PRESSURE FUEL ALTmJDE FLOW ft gph SL 26 0 2000 24 0 4000 22 5 6000 21 0 8000 19 5 10...

Page 98: ...yne Continental Motors S 097 3 or Raytheon Aircraft S B 28 3052 MANUAL LEANINGFUELFLOWSCHEDULE FORFULLTHROTTLE AND2700RPM PRESSURE FUEL ALTITUDE FLOW ft gph SL 25 5 2000 25 5 4000 24 0 6000 22 0 8000...

Page 99: ...015 Kit Serials 135 And After Not In Compliance With Raytheon Aircraft S B 28 3052 MANUAL LEANING FUELFLOWSCHEDULE FORFULLTHROTTLE AND2700RPM PRESSURE FUEL ALTITUDE FLOW ft gph SL 25 7 2000 25 7 4000...

Page 100: ...SET BY ALTITUDE b Propeller 2700 RPM c Throttle FULL FORWARD Cruise Climb Power a Mixture SET BY ALTITUDE b Propeller 2500 RPM c Throttle FULL FORWARD 2 Cowl Flaps AS REQUIRED 3 Power SET 4 Engine Tem...

Page 101: ...Manual leaning fuel flows for full throttle and 2500 rpm are 2 gph less than those shown on schedule 4 20 Engine roughness fuel flow fluctuation or low fuel flow can occur when climbing on hot days T...

Page 102: ...e As the air plane climbs with the mixture control in the FULL RICH position the pump will automatically reduce the fuel flow with increasing altitude E 3145 and After And Prior Airplanes In Compli a...

Page 103: ...ng is referred to as operation on the lean side of peak EGT Enrichening the mixture is referred to as operation on the rich side of peak EGT 2 At lower power settings the engine may be continuously op...

Page 104: ...the peak EGT to be rechecked and the mixture reset DESCENT 1 Altimeter SET 2 Mixture E 1946 E 2104 E 2111 Thru E 3144 Not In Compliance With Raytheon Aircraft S B 28 3052 FULL RICH E 3145 and After An...

Page 105: ...ter And Prior Airplanes In Compli ance With Raytheon Aircraft S B 28 3052 The mixture must be manually enriched as the air plane descends An optional procedure is to retard the throttle as the airplan...

Page 106: ...ts AS REQUIRED 8 Flaps 124 kts or below DOWN I 9 Airspeed ESTABLISH NORMAL APPROACH SPEED 10 Propeller HIGH RPM BALKED LANDING 1 Throttle FULL THROTTLE 2700 RPM 2 Mixture E 1946 E 2104 E 2111 Thru E 3...

Page 107: ...ED 4 Trim Tabs RESET AS REQUIRED SHUTDOWN 1 Parking Brake SET 2 Electrical Switches and Avionics Equipment OFF 3 Throttle 1000 RPM 4 Mixture IDLE CUT OFF 5 Magneto Start Switch OFF after engine stops...

Page 108: ...PROPER FIT STOW IWARNINGI Beards and mustaches should be carefully trimmed so that they will not interfere with the proper sealing of an oxygen mask The fit of the oxygen mask around the beard or mus...

Page 109: ...duration directly from the table a Read oxygen pressure from gage b Read the IOAT Assume IOAT to be equal to BOTTLE TEMPERATURE c Determine the percent of usable capacity from the fol lowing graph e g...

Page 110: ...rcent Of Usable Capacity 57 Planned Cruising Altitude 15 000 ft Duration 49 cu ft cylinder 0 57 x 149 85 minutes Duration 76 cu ft cylinder 0 57 x 229 130 minutes OXYGEN DURATION WITH A FULL BOTTLE 10...

Page 111: ...R USING OXYGEN 1 Discontinue use by unplugging mask from outlet NOTE I Closing the oxygen control while in flight is not nec essary due to automatic sealing of the outlet when the mask is unplugged Ho...

Page 112: ...l in accordance with Consumable Materials in Sec tion VIII HANDLING SERVICING AND MAINTENANCE Always pull the propeller through by hand opposite the direction of rotation several times to clear the en...

Page 113: ...y since it is quite possible to exceed the cylinder head temperature limit in trying to bring up the oil temperature Exercise the propeller sev eral times to remove cold oil from the pitch change mech...

Page 114: ...ce weather permitting even though flight at a lower level may be consistent with the provisions of government regulations NOTE The preceding recommended procedures do not apply where they would confli...

Page 115: ...Beech Bonanza A36 Section IV Raytheon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK 4 34 November 2002...

Page 116: ...5 8 Reserve Fuel 5 10 Total Fuel Requirement 5 10 I Landing Weight 5 10 Graphs Airspeed Calibration Normal System 5 12 Altimeter Correction Normal System 5 13 Airspeed Calibration Alternate System 5 1...

Page 117: ...0 RPM Lean 5 27 23 in Hg 2300 RPM Rich 5 28 23 in Hg 2300 RPM Lean 5 29 25 in Hg 2100 RPM Rich 5 30 25 in Hg 2100 RPM Lean 5 31 21 in Hg 2100 RPM Rich 5 32 Economy Cruise Power 21 in Hg 2100 RPM Lean...

Page 118: ...el The resulting performance is approximate and will vary with airspeed temperature and other ambient conditions E 3100 and after and Prior airplanes in compliance with S B 28 3052 or Prior airplanes...

Page 119: ...d ISA day Linearly interpolate to obtain corrections for other ambient temperatures between ISA and ISA 30 C GRAPHS TABLES ISA ISA ISA 10 c 20 c 30 c TAKE OFF DISTANCE FLAPS UP TAKE OFF DISTANCE FLAPS...

Page 120: ...me PROPORTIONAL DISTANCE between the guideline above and the guideline below the projected line For instance if the projected line intersects the reference line in the ratio of 30 downno up between th...

Page 121: ...perature 15 C 59 F I Field Elevation 5333 ft Altimeter Setting 29 60 in Hg Runway 26L Length 10 004 ft IAt Destination Outside Air Temperature 25 C 77 F I Field Elevation 3605 ft Altimeter Setting 29...

Page 122: ...ove the I field elevation 5333 ft 320 ft 5653 ft Pressure Altitude at Destination 29 92 29 56 36 in Hg 36 X 1000 ft 360 ft I The Pressure Altitude at the destination airport is 360 ft above I the fiel...

Page 123: ...ature values which have been adjusted for the compressibility effects IOAT should be used for setting cruise power while enroute Enter the ISA CONVERSION Graph at 11 500 ft and the temper ature for th...

Page 124: ...168 LEGE ISA 18 C 13 3 168 Time and fuel used were calculated as follows Time Distance Ground Speed Fuel Used Distance Ground Speed X Fuel Flow Results are ROUTE DISTANCE EST TIME AT FUEL SEGMENT NM...

Page 125: ...t ISA and ISA 20 c at 10 000 ft and 12 000 ft Interpolate to find the Fuel Flow at 11 500 ft at ISA 18 C Total Fuel Flow 9 3gph Reserve Fuel 45 minutes x 9 3 gph 7 0 gallons ITOTAL FUEL REQUIREMENT To...

Page 126: ...Raytheon Aircraft Beech Bonanza A36 Section V THIS PAGE INTENTIONALLY LEFT BLANK November 2002 5 11...

Page 127: ...ALIBRATION NORMAL SYSTEM NOTE INDICATED AIRSPEED ASSUMES ZERO INSTRUMENT ERROR 70 Cl EXAMPLE FLAPS IAS DOWN 100 KTS CAS 97 KTS ao tc q p t ll ll tli ttl t t tt ttti ttttt tttt u so I 60 70 80 90 100 1...

Page 128: ...I 1 w a lo 0 10 20 30 60 60 NOTE INDICATEDAIRSPEEDAND INDICATEDALTITUDE ASSUMEZERO INSTRUMENTERROR 70 80 90 100 110 120 130 140 150 160 170 180 190 200 IAS INDICATED AIRSPEED KNOTS November 2002 ALTI...

Page 129: ...ERROR 2 NORMAL STATIC PORTS ARE OBSTRUCTED t r tit t tt r_ 1 l t i i t 1 i 1 Hit 4 P t4 t EXAMPLE IAS 100 KNOTS STORM WINDOW CLOSED CAS 99 5 KNOTS 160 150 u b140 WI p I 130 C w 120 g 110 c oo hoi t t...

Page 130: ...TRUMENT ERROR 2 NORMAL STATIC PORTS ARE OBSTRUCTED 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 INDICATED AIRSPEED KNOTS November 2002 EXAMPLE IAS 100 KNOTS STORMWINDOW CLOSED INDIC...

Page 131: ...0 000 I w w LL w 15 000 a I I _J UJ 10 000 a U en UJ a 0 5000 80 70 60 50 40 30 Beech Bonanza A36 Section V ISA CONVERSION 20 10 0 10 20 30 TEMPERATURE 0 c 5 16 40 Raytheon Aircraft 50 60 70 80 Novemb...

Page 132: ...t __ _ r _ tt 1 _ H t t 1 H t ij t t T r r 1 rr r r 17 r n i LL L H rt r 1 L i t H 1 1 1 1 I t r r t i t r i t r l t1f j t t 1 1 tJ 1 f t t _ f t t r ttt t tr4x lit i 1 Tl H t t 1 c l 7 r H h t t t J...

Page 133: ...CENTER OF GRAVITY LIMIT FOR EACH WEIGHT AT SOME LOADINGS THE AIR LANE IS ELEVATOR LIMITED RESULTING IN A MINIMUM STEADY SPEED RATHER THANA STALL FLAPS UP B iiiii i m fil _u 1 1 i __ _ 11c Jta i1 3SOO...

Page 134: ...i i t i l S l i CONTINUOUS NOT RECOMMENDED FOR CRUISE POWER SETTINGS t _OPERATIQN AT EGTS HOTTER THAN 20 C BELOW PEAK EGT RICH SIDE OR LEAN SIDE 1 IS NOT APPROVED IN Jft t t t 4 H t ri N THI ARE H rt...

Page 135: ...Beech Bonanza A36 Section V Raytheon Aircraft THIS PAGE INTENTIONALL V LEFT BLANK 5 20 November 2002...

Page 136: ...nstrated Crosswind is 17 kts EXAMPLE WINO SPEED 20 KTS ANGLE BETWEEN WINO DIRECTION AND FLIGHT PATH so HEADWIND COMPONENT 13 KTS CROSSWIND COMPONENT 15 KTS FLIGHT PATH 20 0 z l z z 10 0 0 u C z i 0 C...

Page 137: ...LEVEL DRY SURFACE rt1 i t t t tt L J r _ 1 1 z w z ll w w a WEIGHT POUNDS 3650 3600 3400 3200 3000 2800 TAKE OFF SPEED ROTATION 50 FT KNOTS KNOTS 73 84 72 83 71 82 70 80 68 78 65 75 40 30 20 10 0 10 2...

Page 138: ...LISHED COWLFLAPS OPEN RUNWAY PAVED LEVEL DRYSURFACE___________ _ TAKE OFFSPEED WEIGHT ROTATION 50 FT POUNDS KNOTS KNOTS 3650 67 77 3600 67 77 3400 66 76 3200 65 75 3000 64 73 2800 62 71 R Q a Ji qi I...

Page 139: ...ANES OAT 5 C IN COMPLIANCE WITH RAYTHEON AIRCRAFT S B 28 3052 FLAPS UP LANDING GEAR UP COWL FLAPS AS REQUIRED p 112 s s j k _ 4 81 _ frr 0 50 40 30 20 10 0 10 20 30 40 50 60 OUTSIDE AIR TEMPERATURE c...

Page 140: ...E E 3145ANDAFTER AND PRIOR AIRPLANESINCOMPLIANCE WITH RAYTHEON AIRCRAFT S B 28 3052 COWLFLAPS AS REQUIRED November 2002 t h t r Y t L l i o 000 J eooo p I 1 50 40 30 20 10 0 10 20 30 40 50 60 OUTSIDE...

Page 141: ...50 25 0 104 6 17 4 167 175 000 6 43 24 1 101 8 17 0 164 176 C C 8000 2 36 22 3 93 9 15 7 157 174 C 10 000 2 28 20 6 86 9 14 5 150 171 a C 12 000 6 21 19 1 80 8 13 5 142 167 C z 14 IJ O 10 14 17 1 76 0...

Page 142: ...5 Cl 4000 10 50 25 0 88 5 14 8 163 170 C 6000 6 42 24 1 86 1 14 4 159 171 C Q 8000 2 35 22 3 79 3 13 2 152 169 Q a 10 000 2 28 20 6 73 3 12 2 145 166 12 000 6 21 19 1 67 8 11 3 137 162 z 14 000 10 13...

Page 143: ...81 4 13 6 153 155 Ill 4000 9 49 23 0 83 9 14 0 153 160 6000 6 42 23 0 86 5 14 4 153 165 8000 2 35 22 4 85 8 14 3 150 167 Q 10 000 J 28 20 7 80 0 13 3 143 163 a 12 000 20 19 2 75 1 12 5 135 159 14 000...

Page 144: ...4 11 2 147 149 U 4000 9 49 23 0 69 4 11 6 148 154 6000 5 42 23 0 71 7 12 0 148 159 8000 2 35 22 4 71 1 11 9 145 160 C IC 10 000 3 27 20 7 66 2 11 0 137 157 C C 12 800 7 20 19 2 61 8 10 3 129 152 z 9 8...

Page 145: ...3 151 153 t e 4000 9 49 25 0 82 9 13 B 152 158 6000 5 42 24 3 82 3 13 7 160 C 149 Q 8000 1 35 22 5 77 1 12 9 142 157 Q IC 10 000 3 27 20 8 72 9 12 2 134 153 12 000 7 20 19 3 69 5 11 6 126 148 z 1 14 0...

Page 146: ...l4U 2000 13 55 25 0 64 2 10 7 143 145 4000 9 48 25 0 66 6 11 1 144 150 6000 5 41 24 3 66 1 11 0 141 152 C C 8000 1 34 22 5 61 9 10 3 134 148 C 10 000 3 27 20 8 sa s 9 11 126 143 IC 12 000 7 19 19 3 5...

Page 147: ...3 11 1 131 133 4000 9 48 21 0 67 9 11 3 133 138 6000 5 41 21 0 69 7 11 6 134 144 C Cl 8000 1 34 21 0 71 5 11 9 135 149 Cl 10 000 72 9 134 a 3 27 20 8 12 2 153 12 000 7 20 19 3 89 5 11 6 126 148 z 14...

Page 148: ...1 c 2000 12 54 21 0 53 1 8 9 123 124 Ill 4000 9 48 21 0 54 4 9 1 124 129 6000 5 41 21 0 55 7 9 3 125 134 c C 8000 1 34 21 0 57 3 9 6 126 140 C IC 10 000 3 27 20 8 58 5 l8 126 143 c C 12 000 7 19 19 3...

Page 149: ...ISEWT 3400 LBS CRUISEALTITVDE 11 500 n TEMPERATURE STD DAY ISA POWER SETTING FUU THROTTLE 2500 RPM TRUEAIRSPEED 168 KTS 16 000 15 000 14 000 13 000 3 I 12 000 tii11 000 _ w 10 000 w 9000 0 I 8000 w 70...

Page 150: ...SE WT MOOLBS PRESSUREALTrT JDE 11 500FT TEMPERAT JRE STD DAY ISA POWER SETTING FULLTHROTTLE 2500 RPM TRUE AIRSl EEO 163KTS 16 000 15 000 14 000 13 12 000 li i 11 000 I 10 000 w 9000 0 I 8000 w 7000 a...

Page 151: ...EAKEGT 14 000 13 000 12 000 i 148 11 000 I 10 000 w w 9000 u I w 8000 0 149 7000 w 6000 a gj 5000 w a 4000 a a er 8 Cl r z 138 3000 2000 1000 SL I 620 640 720 740 760 780 800 RANGE NAUTICAL MILES 5 36...

Page 152: ...r t 4 i t ALLOWS FOR TAXI RUNUP AND 45 t 4 t t t ti t MINUTESRESERVEFUELAT ECONOMY 12 000 H H H H H R ISi POWER ttj pmh g t i l l 11 000 tt t l it c 4 i f _f li I20 C LEANI OF PEAK EGT 10 000 tu tt w...

Page 153: ..._ r_t t fO r R t JT TT f i h tt j f1 tlft l t t H r t ir t O ANO ALLOWS FOR TAXI RUNUP ANO 45 11 000 r 111 t f t rT trn r ti 1 NOTE ENDURANCE INCLUDES CRUISE CLIMB t a MINUTES RESERVE FUEL AT ECONOMY...

Page 154: ...S GAL 20 CLEAN INITIAL FUEL LOADING 74 U S GAL 444 LBS Iii ENDURANCE 5 39 HRS TAKE OFF ALTITUDE SL OF PEAK EGT 5 HAS 23 MIN 14 000 I w w LL I w 0 t w er UJ UJ w er C November 2002 NOTE ENDUR E INCLUDE...

Page 155: ...SURFACE APPROACH SPEED IA AS TABULATED BRAKING MAXIMUM s 40 0 0 10 I 10 20 30 40 50 OUTSIDE AIR TEMPERATURE C w z i w ffi a a 3600 WEIGHT POUNDS SPEEDAT 50 FT KNOTS 3650 79 3400 80 3200 81 3000 81 280...

Page 156: ...y Weight and Balance Form 6 7 Weight and Balance Record 6 9 Loading Instructions 6 11 Seating Baggage and Equipment Arrangements 6 12 Moment Limits vs Weight Graph 6 13 Computing Procedure 6 14 Weight...

Page 157: ...Beech Bonanza A36 Raytheon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK 6 2 November 2002...

Page 158: ...Raytheon Aircraft Beech Bonanza A36 Section VI BASIC EMPTY WEIGHT AND BALANCE ACTUAL THIS PAGE TO BE REPLACED UPON AIRCRAFT DELIVERY November 2002 6 3...

Page 159: ...I Beech Bonanza A36 Section VI Raytheon Aircraft SAMPLE LOADING THIS PAGE TO BE REPLACED UPON AIRCRAFT DELIVERY 6 4 March 2003...

Page 160: ...be drained prior 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 trapped fuel remain in the airplane at Fuse...

Page 161: ...ing a string across from one main wheel to the other All measurements are to be taken with the tape level with the hangar floor and parallel to the fuselage center line The locations of the wheel reac...

Page 162: ...AFT 271 0 Signature 0 I REACTION SCALE NET WHEEL JACK POINTS READING TARE WEIGHT ARM MOMENT LEFT MAIN RIGHT MAIN NOSE OR TAIL TOTAL AS WEIGHED Soaca below orovided for additions and subtractions to as...

Page 163: ...d in a new weight and balance and in an addendum to the equipment list There are many ways of doing this it is suggested that a running tally of equipment changes and their effect on basic empty weigh...

Page 164: ...E IN OUT WEIGHT AND BALANCE RECORD REGISTRATION NO WEIGHT CHANGE PAGE NO RUNNING BASIC DESCRIPTION OF ARTICLE ADDED t OR REMOVED EMPTY WEIGHT OR CHANGE WT ARM MOM WT MOM LBS IN mr LBS mr BT04946 l r I...

Page 165: ...ATE IN OUT WEIGHT AND BALANCE RECORD REGISTRATION NO WEIGHT CHANGE PAGE NO RUNNING BASIC DESCRIPTION OF ARTICLE ADDED t OR REMOVED EMPTY WEIGHT OR CHANGE WT ARM MOM WT MOM LBS IN 1 UU LBS 1 UU BT04946...

Page 166: ...he airplane owner and or operator The basic empty weight and moment of the airplane at the time of delivery are shown on the airplane Basic Empty Weight and Balance form Useful load items which may be...

Page 167: ...or structure load limit is 50 pounds per square foot D MAXIMUM WEIGHT 70 POUNDS INCLUDING EQUIPMENT AND BAGGAGE MAXIMUM WEIGHT 400 POUNDS INCLUDING EQUIPMENT AND BAGGAGE MAXIMUM WEIGHT 200 POUNDS FORW...

Page 168: ...fit Condition MOMENT LIMITS VS WEIGHT Envelope Based On The Following Weight And Center or Gravity Limit Data Landing Gear Down 3650 Lb Max Take Of or Landing Forward C G Limit 81 0 3100 Lo or Les 14...

Page 169: ...nd run up Add the Fuel Loading Condition to Zero Fuel Condition to obtain the SUBTOTAL Ramp Condition I 5 Subtract the fuel to be used for start taxi and run up to arrive at the SUBTOTAL Take off Cond...

Page 170: ...CUPANTS 3 3rd and 4th SEAT OCCUPANTS 4 5th SEAT 6th SEAT OCCUPANTS 5 BAGGAGE 6 BAGGAGE 7 SUB TOTAL ZERO FUEL CONDITION 8 FUEL LOADING 9 SUB TOTAL RAMP CONDITION 10 LESS FUEL FOR START TAXI AND RUN UP...

Page 171: ...CUPANTS 3 3rd and 4th SEAT OCCUPANTS 4 5th SEAT 6th SEAT OCCUPANTS 5 BAGGAGE 6 BAGGAGE 7 SUB TOTAL ZERO FUEL CONDITION 8 FUEL LOADING 9 SUB TOTAL RAMP CONDITION 10 LESS FUEL FOR START TAXI AND RUN UP...

Page 172: ...90 126 132 167 122 126 167 120 90 98 138 144 182 133 138 182 130 98 106 150 156 198 144 150 198 140 105 114 161 168 212 155 161 212 150 112 123 172 180 228 166 172 228 160 120 131 184 192 243 178 184...

Page 173: ...18 11 15 20 30 36 22 29 30 45 54 32 44 40 60 72 43 58 50 75 90 54 73 60 90 108 65 87 70 105 126 76 102 80 120 86 116 90 135 97 131 100 150 108 145 110 165 119 160 120 180 130 174 130 195 140 189 140 2...

Page 174: ...AND MOMENTS USABLE FUEL LEADING EDGE TANKS ARM 75 WEIGHT MOM 100 GALLONS WEIGHT 30 23 44 264 60 45 50 300 90 68 55 330 120 90 60 360 150 113 65 390 180 135 70 420 210 158 74 444 240 180 MOM 100 198 22...

Page 175: ...Beech Bonanza A36 Section VI Raytheon Aircraft THIS PAGE INTENTIONALL V LEFT BLANK 6 20 November 2002...

Page 176: ...Panel 7 10 Engine Instrument Panel Illustration 7 12 Avionics Panel 7 13 Instrument Air Pressure Gage 7 13 Subpanel 7 13 OAT Gage 7 14 Pedestal 7 14 Annunciator System 7 14 Annunciator Panel 7 14 Annu...

Page 177: ...Openable Cabin Windows 7 25 Control Locks 7 26 Power Plant 7 29 Engine Controls 7 29 Throttle Propeller and Mixture 7 29 Cowling 7 29 Cowl Flaps 7 30 Induction System Icing 7 30 Lubrication System 7 3...

Page 178: ...mental System 7 41 Cabin Heating 7 41 Heater and Defroster Operation 7 42 Cabin Ventilation 7 42 Cabin Fresh Air Outlets 7 43 Individual Overhead Fresh Air Outlets 7 43 Fresh Air Vent Blower If Instal...

Page 179: ...Beech Bonanza A36 Section VII Raytheon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK 7 4 November 2002...

Page 180: ...CONTROLS CONTROL SURFACES Control surfaces are operated through push pull rods and con ventional cable systems terminating in bellcranks CONTROL COLUMNS The airplane is equipped with dual control col...

Page 181: ...anel on the upper center portion and a subpanel The subpanel provides for electrical switches and the landing gear handle on the left instruments in the center portion and the flap switch panel lighti...

Page 182: ...Raytheon Aircraft Beech Bonanza A36 Section VII THIS PAGE INTENTIONALLY LEFT BLANK November 2002 7 7...

Page 183: ...Beech Bonanza A36 Section VII 7 8 Raytheon Aircraft E 07C 000739AA J w z C 1 z w cc I C z J C November 2002...

Page 184: ...Raytheon Aircraft November 2002 Beech Bonanza A36 Section VII w z in t w en w 0 w A 7 9...

Page 185: ...A transducer attached to the engine sends electrical pulses which are then interpreted by the tachometer Loss of electrical power will cause the instrument to indicate O rpm The fuel flow indicator i...

Page 186: ...cription E 1946 E 2104 E 2111 THRU E 3144 NOT IN COMPLIANCE WITH RAYTHEON AIRCRAFT SB 28 3052 E 3145 AND AFTER AND PRIOR AIRPLANES IN COMPLIANCE WITH RAYTHEON AIRCRAFT S B 28 3052 RED RADIAL GREEN ARC...

Page 187: ...ndicate minimum value if electrical power is lost AVIONICSPANEL Avionics equipment and arrangement is per customer speci fication INSTRUMENT AIR GAGE Instrument air pressure is supplied by an engine d...

Page 188: ...e pressure should be maintained within the green arc for proper operation of the pressure operated instruments SUBPANEL The magneto start switch and switches for the battery alternator avionics master...

Page 189: ...al The trim tab on the left aileron is adjustable with the knob mounted on the front of the pedestal ANNUNCIATOR SYSTEM ANNUNCIATOR PANEL Three annunciators placarded LOW BUS VOLTS START and AFT DOOR...

Page 190: ...oto electric cell located above the landing gear handle automatically dims for night or brightens for day the lights depending on how much ambient light is entering the cabin The START AFT DOOR and GE...

Page 191: ...witch located above the landing gear handle The lamps can be tested by pressing the annunciator test button ANNUN TEST on the left side of the pilot s subpanel Lowering the flaps in flight will produc...

Page 192: ...ghts one for each gear are illuminated whenever the landing gear is down The red IN TRANS light illuminates any time one or all of the landing gears are in transit or in any intermediate position All...

Page 193: ...KERS The LANDING GEAR RELAY LANDING GEAR MOTOR LOG I GEAR POS LTS and LOG GR WARN circuit breakers are located on the left side circuit breaker panel and will pop out under overload conditions These c...

Page 194: ...67 except E 2458 With the landing gear retracted if the throttle is retarded below approximately 12 in Hg manifold pressure a warning horn will sound intermittently NOTE The switch which activates the...

Page 195: ...area is divided into subcompartments each having a different weight limitation Loading within the baggage com I partment must be in accordance with the data in the Section VI WEIGHT AND BALANCE All ba...

Page 196: ...oulder har ness and the seat back can be folded over for access by rotating the red handle located on the lower inboard side of the seat back The optional 5th and 6th seats can be folded up to provide...

Page 197: ...45 SEAT CHANGE SCHEMATIC SEAT BELTS Every seat in the airplane is equipped with a seat belt The seat belt can be lengthened by turning the male half of the buckle at a right angle to the belt then pul...

Page 198: ...own across the body where it is fastened by a metal loop into the seat belt buckle For the pilot seats the harness strap is contained in an inertial reel attached to the side canopy structure of the c...

Page 199: ...ther direction before I engagement of the locking mechanism Grasp the door and firmly pull the door closed Rotate the door handle fully counter clockwise into the locked position Observe that the door...

Page 200: ...vides for opening or closing from the inside The AFT DOOR ajar annunciator located on the annunciator panel remains illuminated until the doors are properly latched OPERATION WITH AFT UTILITY DOORS RE...

Page 201: ...d and wired by a qualified mechanic using a single strand of QQ W 343 Type S 020 diameter copper wire prior to further airplane operation CONTROL LOCKS To Install The Control Locks 1 Rotate pilot s co...

Page 202: ...anza A36 Section VII 5 Position pilot s rudder pedals in aft position and install spring lock between pedals IWARNING Before starting engine remove the lock reversing the above procedure November 2002...

Page 203: ...ng InstrumentPanel with ControlLocks Properly Installed 7 28 INSTALLATION INSTRUCTIONS INSTALLOTHER SIDE FACINGPILOT I ROTATECONTROL WHEEL APPROX12 TD THE RIGHT INSTALLLOCKPIN THROUGH COLLAR LOCK CONT...

Page 204: ...ally located for ease of operation from either the pilot s or the copilot s seat An adjust I able friction knob located on the right side of the pedestal is pro vided to prevent creeping of the contro...

Page 205: ...n system icing is reduced by the non icing characteristics of the Bonanza s fuel injected engine and automatic alternate air source Under certain conditions how ever impact ice can form at several poi...

Page 206: ...e battery and alterna tor switches should be turned off if the annunciator remains illu minated after starting If the annunciator does not illuminate dur ing starting the annunciator system is inopera...

Page 207: ...green However the use of grade 100LL blue is preferred FUEL CELLS The fuel system consists of a rubber fuel cell located in each wing leading edge The fuel capacity consists of two 40 gallon cells 37...

Page 208: ...rical signals to the individual indicators which indicate usable fuel remaining in the tank ALTITUDE COMPENSATING FUEL PUMP Early airplanes E 1946 E 2104 E 2111 thru E 3144 not in compliance with Rayt...

Page 209: ...LO position is used to supply a low boost to the fuel flow during all flight conditions The HI position is used for priming the engine during cold starts and also to provide an alternate source of fue...

Page 210: ...left A stop lock out button prevents inadvertent selection of the OFF position To select OFF depress the stop button and rotate the handle to the full clockwise position Depression of the lock out st...

Page 211: ...inaccurate indicator could give an erroneous indi cation of fuel quantity A minimum of 13 gallons of fuel is required in each tank before takeoff The caps should be removed and fuel quantity checked...

Page 212: ...A I FUELSYSTEMSCHEMATIC I I I I l i l CHECK ICllVALVE I i 1 1 l I I I r I I I I I I I I _ _ _ _ _ I R FUELTANK e I I SELECTOR VALVE STRAINER A 40 GAL 137GAL USABLEI VENT 48 t DRAIN Q i DRAIN QDRAIN CH...

Page 213: ...p deice strobe lights rotating beacon navigation lights flood lights panel lights taxi light landing light and vent blower These circuit breaker type switches have a built in circuit breaker and will...

Page 214: ...which will automatically turn the alternator off should an overvoltage con dition occur Following an over voltage shutdown the LOW BUS VOLTS annun ciator will illuminate when the bus voltage falls be...

Page 215: ...subpanel The rheostat placarded FLIGHT INST controls the lighting of the flight instrument panel and the rheostat placarded INST FLOOD controls the glareshield light ing which illuminates the full up...

Page 216: ...ail cone Use the landing light and the taxi light sparingly Avoid prolonged operation which could cause overheating during ground maneuvering An optional anti collision light mounted on the vertical s...

Page 217: ...ters the cabin The forward vents located on the firewall forward of the rudder pedals deliver heated air to the forward cabin when the CABIN HEAT control is pulled out To deliver heated air to the aft...

Page 218: ...air is ducted through the optional cabin vent blower and overhead fresh air shutoff valve to the six overhead fresh air outlets Each outlet can be adjusted to control the volume and direction of air...

Page 219: ...TROL DEFROSTER CONTROL LH Raytheon Aircraft FRESH AIR INTAKE NOSE HEATEO AIR R H FORWARD OUTLET AFT OUTLET 3RD 4TH SEATS AFT OUTLET 5TH 6TH SEATS CONTROL CABLE CABIN AIR EXHAUST OVERHEAD FRESH AIR SHU...

Page 220: ...t s subpanel The knob operates the shutoff valve on the supply cylinder and is normally kept in the off position A pressure gage in the oxygen console indicates the supply of oxygen available to the s...

Page 221: ...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 A low point drain tube...

Page 222: ...d after Refer to Supplement 36 590006 23 in Section IX SUPPLEMENTS for information on operation and procedures STALL WARNING HORN A stall warning horn located forward of the instrument panel I sounds...

Page 223: ...ilized MIL L 22851 Ashless Dis persant Oil should be used Oils must meet the requirements of the latest revision of Teledyne Continental Motors Corporation I Specification MHS 24 or current applicable...

Page 224: ...r cruise climb Maintain the highest power recommended for cruise operation during the break in period 50 to 75 hrs and interrupt cruise power every 30 minutes or so by smoothly advancing to take off p...

Page 225: ...Beech Bonanza A36 Section VII Raytheon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK 7 50 November 2002...

Page 226: ...Parking 8 8 Tie Down 8 8 Main Wheel Jacking 8 9 Prolonged Out of Service Care 8 10 Flyable Storage 7 to 30 days 8 10 Mooring 8 10 Engine Preparation For Storage 8 10 Fuel Cells 8 10 Flight Control Su...

Page 227: ...ent Air Pressure System 8 21 Propeller 8 21 Oxygen System 8 22 Oxygen Cylinder Retesting 8 23 Minor Maintenance 8 23 Rubber Seals 8 23 Alternator 8 24 Magnetos 8 24 Cleaning 8 25 Exterior Painted Surf...

Page 228: ...nce requirements contained in this handbook are considered mandatory Raytheon Aircraft Authorized Outlets can provide recom mended modification service and operating procedures issued by both the FAA...

Page 229: ...stra tion Branch List or the Raytheon Aircraft Domestic Interna tional Owner s Notification Service List Further the owner and or operator will receive only those publications pertaining to the regist...

Page 230: ...mplished NOTE To ensure proper procedures are followed obtain a model Bonanza Series Mainte nance Manual before performing preventa tive maintenance 2 All other maintenance must be performed by licens...

Page 231: ...al in appearance may not have had the required tests and inspections performed may be different in fabrication techniques and materials and may be dan gerous when installed in an airplane Salvaged air...

Page 232: ...The nose landing gear is designed with tow lugs on the lower nose gear torque knee The tow lugs are the only area of attachment to be used when towing the airplane Under no cir cumstances should the a...

Page 233: ...ARKING The parking brake push pull control is located on the lower left subpanel To set the parking brake pull the parking brake con trol Knob out T Handle on serials E 2191 and after and depress each...

Page 234: ...be installed at the rear tie down lug and a tie down line attached to the nose gear MAIN WHEEL JACKING 1 Check the shock strut for proper inflation to prevent damage to the landing gear door by the ja...

Page 235: ...ly at the three points provided Do not use hemp or manila rope It is recommended a tail support be used to compress the nose strut and reduce the angle of attack of the wings ENGINE PREPARATION FOR ST...

Page 236: ...in Before rotation of propeller blades ascer tain magneto start switch is OFF throttle in CLOSED position and mixture control is in the IDLE CUT OFF position Always stand in the clear while turning p...

Page 237: ...prevent arcing make certain no power is being sup plied when the connection is made 4 Make certain that the BAT switch is ON all avionics and electrical switches are OFF and a battery is in the sys te...

Page 238: ...each wing leading edge The filler neck in this installation contains a visual mea suring tab to permit partial filling of the tank Filling the tank until the fuel touches the bottom of the tab indicat...

Page 239: ...ttings Ordinarily the finger strainers in the fuel cell outlets should not require cleaning unless there is a definite indication of solid for eign material in the cells or the airplane has been store...

Page 240: ...er 9 Remove the drain adapter fitting from the oil sump drain valve the spring loaded valve is self closing The engine may now be filled with oil 10 Re secure the cowl access plate The engine manufact...

Page 241: ...engine cowling Check the electrolyte level after each 25 hours of operation and add distilled water as necessary Do not fill the battery above the bottom of the split ring Excessive overcharging can...

Page 242: ...reventing tire failure caused from running over sharp stones When inflating tires visually inspect them for cracks and breaks Raytheon Aircraft cannot recommend the use of recapped tires Recapped tire...

Page 243: ...l inflate each main gear shock strut until 3 inches of the piston is showing Inflate the nose gear shock strut until the piston is extended 5 inches as indicated on the shock strut servicing instruc t...

Page 244: ...strut from the blocked position and replace the valve body assembly 7 Completely compress the strut to release excess air and oil then reinstall valve core 8 Inflate the strut as described in the pre...

Page 245: ...than when it rests against the piston face When the shimmy damper is found empty or nearly empty it should be refilled See Bonanza Series Maintenance Manual BRAKES The brake hydraulic fluid reservoir...

Page 246: ...be changed 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 Both filters are to be changed wh...

Page 247: ...e electrical power is off Do not operate electrical switches or connect or disconnect ground power generators during the oxygen charging operation 2 Make sure that no fueling or other flammable fluid...

Page 248: ...ssure 3 5 psig 8 Close the supply bottle valve remove the recharging adapter and replace the filler valve cap 9 Slide the seat forward to its original position 10 The oxygen push pull control knob sho...

Page 249: ...egative battery 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...

Page 250: ...ar of the magneto should be removed CLEANING EXTERIOR PAINTED SURFACES Polyester urethane finishes undergo a cur ing process for a period of 30 days after application Wash uncured painted sur faces wi...

Page 251: ...oot use a cloth dampened with an automotive tar remover Wax or polish the affected area if necessary Do not expose control surface trim tab hinge lines and their pushrod systems to the direct stream o...

Page 252: ...and avoid all operating conditions which might cause abrasion or premature finish deterioration Do not apply wax polish rubbing com pound or abrasive cleaner to any uncured painted surface Use of suc...

Page 253: ...t chamois Rubbing the surface of the plastic with a dry cloth should be avoided as it builds up an electrostatic charge on the surface which attracts dust particles NOTE The manufacturer of the windsh...

Page 254: ...switches con trols and seals Fluid applied at high pressure can unseat seals resulting in con tamination of the sealed systems LANDING GEAR After operation on salty or muddy runways wash the main gea...

Page 255: ...to the manufacturer s instructions To minimize wetting the fabric keep the foam as dry as possi ble and remove it with a vacuum cleaner The plastic trim instrument panels and control knobs need only b...

Page 256: ...er State Oil and Ref Corp Quaker State AD Aviation Engine Oil Red Ram Ltd Canada Red Ram X C Aviation Oil 20W50 Sinclair Refining Co Sinclair Avoil 20W40 Shell Oil Co Aeroshell Oil W in 4 grades Shell...

Page 257: ...sition Indicator Light 1819 Flap Position Light 327 Fuel Selector Placard Light 327 Instrument Flood Light Overhead 313 Instrument Light Post 327 Instrument Wedge Light 58 380022 11 Landing Gear Posit...

Page 258: ...ch for the supplement part number Any information pending foreign regulatory agency approval will be listed in the description 36 590002 37 Supplement Pack Raytheon Aircraft Company which has been ren...

Page 259: ...ble whether it was installed or not Airplane Flight Manual Supplements for equipment for which the vendor obtained a Supplemental Type Certificate were included as loose equipment with the airplane at...

Page 260: ...ng KN 74 Area Navigation System 3 12 78 35 590118 43 King KNS 80 Integrated Navigation System 1 12 78 36 590002 41 Air Conditioning System 1 4 84 36 590002 43 Operation of United Kingdom Registered Ai...

Page 261: ...io Panel with BF Goodrich WX 500 Weather Mapping Sensor with Shadin F ADC 200 or 200 Fuel Air Data Computer when used with Allied Signal KFC 225 Automatic Flight Control System 1 08 00 36 590002 0061...

Page 262: ...sed with Allied Signal KFC 225 Automatic Flight Control System 1 09 03 36 590002 0069 Israel Air Force Light Transport And Utility Aircraft RAC approved only 2 12 06 36 590003 11 King KNS 81 Integrate...

Page 263: ...Propeller per STC SA00719LA C 01 06 FMS410 1 B C Specialty Products BC410 1 Standby Alternator System per STC SA00724WI and STC SE00729WI A 4 2 03 or later 006 00838 0000 Bendix King KLN 90B GPS Navi...

Page 264: ...Beech Bonanza A36 Section IX Raytheon Aircraft THIS PAGE INTENTIONALLY LEFT BLANK 9 2 November 2002...

Page 265: ...adds to the basic Pilot s Operating Handbook and FM Approved Air plane Right Manual only as set forth within this document Users of the manual are advised always to refer to the supplement for possibl...

Page 266: ...s while in the enroute mode check for correct frequency 2 If VOR or DME equipment is intermittent or lost utilize other navigation equipment as required 3 If NAV flag appears during an approach execut...

Page 267: ...NS 351 has memory capacity for 8 waypoints d Pressthe RTN return push buttonto display the active waypoint 3 Changing waypoints in flight a Select heading mode on the autopilot if engaged b Rotate the...

Page 268: ...Note blink ing waypoint number b Set into the ANS 351 the desired waypoint bearing and distance c Press the RTN return push button and note that the presently used waypoint is displayed 5 Presetting...

Page 269: ...angle ground speed in knots i e the airplane does not have to be on a course directly to a waypoint to display a valid groundspeed A green annunciator light on the indicator is illuminated any time th...

Page 270: ...ector Two concentric knobs c1 1 n be used to set radial information into the dis play Knobs control information as follows Large knob Changes the display in 10 degree increments Small knob pushed in C...

Page 271: ...causes normal slant range DME distance to the VOR DME station to be presented on the DME indicator The WPT annunciator on the DME indicator will extinguish during this time If TO or FROM is selected...

Page 272: ...n in the normal mode and air plane magnetic bearing to the waypoint in the RNAVmode d FROM Displays airplane magnetic bearing from the VOA station in the normal mode and airplane bearing from the wayp...

Page 273: ...is applied to the NAV receivers and the 1 system is in the RNAV mode 6 RMI Bearing An output is provided by the ANS 351 that allows an RMI with builtin NAV converter to display bear ing to or from th...

Page 274: ...installed in accordance with BEECHCRAFT FAA approved data The informationin this supplementsupersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only as s...

Page 275: ...QUIRED 2 VOA or Distance flag appears while in APPR mode If flag appears while on an approach execute a missed approach and utilize another approved facility NORMAL PROCEDURES 1 VHF NAV ON 2 DME ON 3...

Page 276: ...PERFORMANCE No change Approved FAA Approved Revised December 1978 P N 35 590118 13 W H Schultz Beech Aircraft Corporation DOA CE 2 3of3...

Page 277: ...irplane Flight Manual only as set forth within this document Users of this manual are advised always to refer to the supplement for possibly superseding information and placarding applicable to operat...

Page 278: ...NAV flag appears during an approach execute published missed approach and utilize another approved facility NORMAL PROCEDURES PREFLIGHT AREA NAVIGATION FUNCTIONAL TEST The following procedure applies...

Page 279: ...to takeoff or during the flight Any combination of navigational facilities RNAV waypoint VOR DME ILS may be loaded into the computer however it is desirable that each facility be numbered and loaded i...

Page 280: ...colocated DME is similar to that for RNAV waypoints Inputting the waypoint number and frequency into the memory is accomplished in the same manner Since the station has no DME it cannot be electronic...

Page 281: ...l and distance may also be checked at this time by pressing the DSP button for each 2 Verify that the data is correct NOTE Revisions to the waypoint data can be programmed at this time by entering the...

Page 282: ...ted by pressing the VOA button once for VOA and a second time for VOA PAR In VOA mode DME is automatically tuned and distance groundspeed and time to station to the VORTAC station will be displayed up...

Page 283: ...mode may be used for runway location by placing a waypoint at the approach end of the runway during an approach to an airport Press the RNAV button to select RNV APR In RNV APR the deviation needle o...

Page 284: ...tive pushing of the RNAV button causes the system to alternate between RNV ENR and RNV APR modes All waypoint information station frequency waypoint distance and waypoint radial are entered with the i...

Page 285: ...n by depressing the HOLD button Subsequent rechanneling of the NAV receiver will cause the HLD light to illuminate The DME will hold the frequency it was tuned to at the time the button was depressed...

Page 286: ...d 3 MIN Display a VOA and VOA PAR modes Displays time to DME ground station in 1 minute increments from Oto 99 minutes Displays dashes whenever DME goes into search or when calculated time exceeds 99...

Page 287: ...umber of data 1 to 4 actually being used by the system In VOA modes only the frequency has meaning When changed always takes on DSP value 6 DSP Display Displays waypoint number 1 to 4 of data being di...

Page 288: ...mode causes the system to go to RNV ENR mode Otherwise the button causes the system to toggle between RNV ENR and RNV APR modes 3 HOLD Button Two position pushbutton which when in the depressed positi...

Page 289: ...d counterclockwise it will decrease audio level and switch off power The switch may be pulled out to hear VOR ident 8 DATA INPUT Control Dual concentric knobs with the center knob having an in and out...

Page 290: ...cells located in the lower left hand corner of the front panel Typical life of the cells is two years although high temperature and humidity conditions can shorten this period If the batteries should...

Page 291: ...talled in accordance with Beech 1 approved data The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only as set forth...

Page 292: ...d off before attempting I restart AIR CONDITIONING SYSTEM MALFUNCTION Turn off air conditioning system If air conditioning system circuit breakers trip do not reset until the cause of the malfunction...

Page 293: ...airplane is clear of all obstacles air conditioning system may be turned on as desired SHUTDOWN Turn off air conditioner before engine shutdown PERFORMANCE CRUISE PERFORMANCE NOTE Using the power sett...

Page 294: ...e motor two limit switches on the condenser the landing gear safety switch and a throttle Iimit switch The three retractable condenser positions are ground extension flight extension and retracted Whe...

Page 295: ...o approximately 56 F The evaporator module electric blower then forces the cooled air through outlet ducting to adjustable eyeball outlets in the instrument panel and subpanel The cabin air continues...

Page 296: ...h the landing gear extended and partial throttle the condenser is in the flight extension position However should a go around be necessary the application of full throttle will cause the throttle limi...

Page 297: ...K SUPPLEMENT FOR OPERATION OF UNITED KINGDOM REGISTERED AIRCRAFT THIS SUPPLEMENT IS APPLICABLE TO PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL P N 36 590002 37 Airplane Serial Nu...

Page 298: ...Operating Handbook and FAA Approved Air plane Flight Manual LIMITATIONS CERTIFICATION CATEGORY The BEECHCRAFT Bonanza A36 is eligible for certifica tion in the United Kingdom in the Transport Categor...

Page 299: ...ot exceed six nor exceed the number for which seating accommodations approved for use during takeoff and landing is provided Children under the age of three years who are carried in the arms of passen...

Page 300: ...an ILS glide slope it shall not remain engaged when the aeroplane is flying at a height of less than 320 feet above the terrain EMERGENCY PROCEDURES No Change NORMAL PROCEDURES FLAPLESS LANDING I Mano...

Page 301: ...t dry grass LANDING The total distances shown on the Normal Landing Dis I tance graph should be increased 20 for operation on short dry grass with a firm subsoil LANDING WITH FLAPS RETRACTED When appr...

Page 302: ...Iii w IL 000 00 0 6 of 10 oooc ooc oc E OOOl ooa a S3H 13ri 3 JN v SIO lfl08t 09 6 o oo oU r R al ti iil I ooo H a Si ij N J 0 Revised April 1989 P N 36 590002 43...

Page 303: ...OOO OL 0009 ooo 0009 000 000 ooo 008 oo 009 oos oo oo 08 Ol 09 OS 0 8 l 9 s SV ll ll 10071 1H l3M Revised April 1989 P N 36 590002 43 7 of 10...

Page 304: ...z 0 cij a w z r 0 4 0 en w a w E i J E 8 of 10 sn 100 01s al CD i5 r 12 lil J w z Ln il I w z I J i5 g 0 S31 U 311 1111111 1 3 NV lSIO Revised April 1989 P N 36 590002 43 i...

Page 305: ...z 0 en a w z 0 u 0 w a I i 0 z 0 J J ct CJ en r t 1 OE OOE sa osa t S3Y_J n 3 lnSV3W amen Revised April 1989 P N 36 590002 43 a oo g 09 2 0 5l mii R g u fil g Ntil 2 9 of 10 z ui i I w a w C 5 g...

Page 306: ...WEIGHT BALANCE No Change SYSTEMS DESCRIPTION No Change HANDLING SERVICE AND MAINTENANCE No Change 10 of 10 Revised April 1989 P N 36 590002 43...

Page 307: ...HORN SYSTEM THIS SUPPLEMENT IS APPLICABLE TO PILOT S OPERATING HANDBOOKS AND FAA APPROVED AIRPLANE FLIGHT MANUALS SEE NEXT PAGE FOR APPLICABILITY Airplane Serial Number __________ _ Airplane Registra...

Page 308: ...J 149 thru CJ 179 V358 Serials D 10179 thru D 10403 A36 Serials E 1371 thru E 2110 except E 1946 and E 2104 A36 Serials E 1946 E 2104 E 2111 thru E 2467 except E 2458 A36TC Serials EA 1 thru EA 272 ex...

Page 309: ...December 1990 E55 Serials TE 938 TE 943 thru TE 1083 E55 Serials TE 1084 thru TE 1201 58 Serials TH 1 thru TH 772 58 Serials TH 773 thru TH 1395 except TH 1389 58 Serials TH 1389 TH 1396 thru TH 1471...

Page 310: ...plane has been modified by installation of the Full Flap Warning Horn System in accordance with Beech Kit Drawing 36 3012 The information in this supplement supersedes or adds to the basic Pilot s Ope...

Page 311: ...IF INSTALLED BY KIT GEAR UP ANNUNCIATOR With the landing gear retracted and the flaps fully extend ed a warning horn will sound intermittently and the GEAR UP annunciator if installed will flash HAND...

Page 312: ...THE LANDING GEAR WARNING LIGHT SYSTEM THIS SUPPLEMENT IS APPLICABLE TO PILOT S OPERATING HANDBOOKS AND FAA APPROVED AIRPLANE FLIGHT MANUALS SEE NEXT PAGE FOR APPLICABILITY Airplane Serial Number _____...

Page 313: ...E 1301 F33C Serials CJ 149 thru CJ 179 V358 Serials D 10097 D 10120 thru D 10403 A36 Serials E 1111 E 1241 thru E 2110 except E 1946 and E 2104 A36 Serials E 1946 E 2104 E 2111 thru E 2467 except E 24...

Page 314: ...d PIN 36 590002 49 Issued December 1990 58 Serials TH 1389 TH 1396 thru TH 1471 TH 1476 TH 1487 TH 1489 and TH 1498 58 Serials TH 1472 thru TH 1475 TH 1477 thru TH 1486 TH 1488 TH 1490 thru TH 1497 TH...

Page 315: ...g Light System in accordance with Beech Kit Drawing 36 3013 The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only a...

Page 316: ...Light 1 EMERGENCY PROCEDURES No change NORMAL PROCEDURES No change PERFORMANCE No change WEIGHT AND BALANCE No change SYSTEMS DESCRIPTION INSTRUMENT PANEL 1 4 1 1 1 IFR DAY 1 4 1 1 1 GEAR UP WARNING L...

Page 317: ...f illumination intensity On some airplanes certain annunciators do not dim eg START AFT DOOR On these airplanes the GEAR UP light annunciator also will not dim LANDING GEAR SYSTEM GEAR UP WARNING LIGH...

Page 318: ...YSTEM THIS SUPPLEMENT IS APPLICABLE TO PILOT S OPERATING HANDBOOKS AND FAA APPROVED AIRPLANE FLIGHT MANUALS SEE NEXT PAGE FOR APPLICABILITY Airplane Serial Number __________ _ Airplane Registration Nu...

Page 319: ...002 17 36 590002 37 36 590006 19 2 of 9 F33A Serials CE 862 thru CE 1307 except CE 1301 F33C Serials CJ 150 thru CJ 179 V35B Serials D 10249 thru D 10403 A36 Serials E 1519 thru E 2110 except E 1946 E...

Page 320: ...of the Low Throttle Landing Gear Retract Prevention Gear Warning System in accordance with either Beech Kit Drawing 36 3014 or Beech Kit Drawing 36 3017 The information in this supplement supersedes o...

Page 321: ...lec trical Equipment OFF Glide distance is approximately 2 0 nautical miles 2 3 statute miles B36TC or 1 7 nautical miles 2 0 statute miles F33A V35B A36 per 1000 feet of altitude above the terrain LA...

Page 322: ...nway Make a normal approach using flaps as necessary NOTE The landing gear will not retract un less the throttle is in a position corre sponding to approximately 17 in Hg manifold pressure or above Wh...

Page 323: ...s of oil pressure was the cause of overspeed the engine will sieze af ter a short period of operation see LANDING WITHOUT POWER Proce dure in this section 4 Land as soon as practical LANDING GEAR RETR...

Page 324: ...SCRIPTION LANDING GEAR CONTROL SWITCH The landing gear is controlled by a two position switch on the the instrument subpanel The switch handle must be pulled out of the safety detent before it can be...

Page 325: ...ow approximately 17 in Hg manifold pressure position 8 of 9 NOTE The throttle switch which deactivates the landing gear control circuit will al ways activate at the same throttle po sition The resulta...

Page 326: ...HANDLING SERVICING AND MAINTENANCE No change FAA Approved P N 36 590002 51 Issued December 1990 9 of 9...

Page 327: ...ATION SYSTEM THIS SUPPLEMENT IS APPLICABLE TO PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUALS P N 33 590009 13 P N 36 590002 37 P N 36 590006 19 Airplane Serial Number ________ _ A...

Page 328: ...nt supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only as set forth within this docu ment Users of the handbook are advised always to refer to the s...

Page 329: ...nformation must be checked for accuracy reasonableness against a visual ground fix or other approved navigation equipment under the following conditions a Prior to compulsory reporting points during I...

Page 330: ...e navigation computer a CRT display and all the controls required to operate the unit It also houses the data base cartridge which plugs directly into the back of the unit The KLN88 system has analog...

Page 331: ...Illuminates approximately 20 seconds prior to the beginning of turn anticipation or approximately 36 seconds prior to reaching a Direct To waypoint WRN Illuminates whenever the system determines that...

Page 332: ...d Course deviation is angular Full scale left or right deviation is 10 in VOR mode and 2 5 in LOC mode 2 LORAN SELECTED a The course must be manually selected using the Course Knob b The KLN88 provid...

Page 333: ...rse c Course deviation is linear Full scale left or right deviation is 5 NM HANDLING SERVICING AND MAINTENANCE To replace the KLN88 LORAN data base refer to the Pi lot s Guide P N 006 08458 0000 dated...

Page 334: ...ced External Noise This Supplement is applicable to Pilot s Operating Handbook and FAA Approved Airplane Flight Manual P N 36 590002 37 Airplane Serial Number ________ _ Airplane Registration Number _...

Page 335: ...AA Approved Airplane Flight Manual when the airplane has been modified for reduced external noise in accordance with Beech FAA approved data The information in this supplement supersedes or adds to th...

Page 336: ...FAA Approved Issued April 1991 P N 36 590002 55 THREE VIEW 3 of 18...

Page 337: ...Hartzell constant speed three blade pro peller using a PHC C3YF IRF hub with Hartzell F7663 2R blades The pitch settings at the 30 inch propeller blade station are Low 17 5 1 High 33 0 1 The propel l...

Page 338: ...modified for reduced external noise is equipped with a Hartzell constant speed three blade pro peller using a PHC C3YF IRF hub with Hartzell F7663 2R blades The pitch settings at the 30 inch propeller...

Page 339: ...ad Limit Rear Spar to Sta 170 100 lbs per sq ft Aft Compartment Sta 170 to Sta 190 70 lbs CENTER OF GRAV TY LIMITS LANDING GEAR EXTENDED FORWARD LIMITS 74 0 inches aft of datum to 3100 pounds with str...

Page 340: ...ANEUIIERN8 141 KT8 l TIUTY CATEGORYAIRPLANE OPERATE II ACC ClfDNCE WITH FAA APPROVED AIFlNE FLl8HTMNI W Alff AffllN FLl8HTMANlW SUIPI EMENT FEDUCED NOISE 0PT10N INSWJ ED GROSS WEIGHT 3tOO LBS INTENTIO...

Page 341: ...of Climb Vx 84 Kts Best Rate of Climb Vy 100 Kts Climb at Maximum Continuous Power 105 Kts Cruise Climb 110 Kts Maximum Turbulent Air Penetration 141 Kts Landing Approach Flaps DOWN 30 80 Kts Flaps U...

Page 342: ...ISH DESIRED CLIMB SPEED when clear of obstacles CLIMB Maximum Continuous Power Mixture Full Rich Full Throttle 2550 rpm Cruise Climb Power Mixture Full Rich Full Throttle 2500 rpm 1 Mixture FULL RICH...

Page 343: ...0 16 000 12 0 BT02714 Engine roughness fuel flow fluctuation or low fuel flow can occur when climbing on hot days These can be eliminated by switching the auxil iary fuel pump from OFF to LO and manua...

Page 344: ...trim to normal climb speed 3 Flaps UP 0 4 Landing Gear RETRACT 5 Cowl Flaps OPEN NOISE CHARACTERISTICS Approach to and departure from an airport should be made so as to avoid porlonged flight at low a...

Page 345: ...id other airplanes Take off sound level established in compliance with FAR 36 is 76 9 dB A Flyover sound level established in accordance with FAR 36 is 71 9 dB A NOTE Flyover sound level is not FAA Ap...

Page 346: ...D lMl Ill SUIFICt 2100 NOi o f i i mltlitu 1 J ttttltlttHHclltHHttllltH 0 W OUTSIDE AIR TEMPERATURE C TAK OFF SPEEDS ROTATION KNOTS 50 Fm KNOTS 72 71 70 Iii l l 12 IO 71 75 3600 3500 400 3300 3200 310...

Page 347: ...fUIS OfOI IIIIIIAY PA IED lIVl1 rxrtSl llflCE ll lt 8 g 3600 3400 3200 3000 2000 fHHfHH HH l Hj fHfjHf l ff lf H jH jf ifj 40 JO 20 10 0 10 20 JO 40 60 OUTSIDE AIR TEMPERATURE c 17 16 65 62 n 7i 75 73...

Page 348: ...PS UP LANDING GEAR UP COWL flAPS OPEN CLIMB CLIMB SPEED 101 KNOTS ALL WIIQHTB EXAMPII OAT S C PRESSURE ALTITUDE 11 550 FT WEIGHT 3600 LBS RATE of CLIMB 424FT MIN CLIMB GRADIENT 2 7 1400 1 0 1200 1100...

Page 349: ...GRAVITY INCHESAFT OF DATUM ERYRPt Based On The FobmJ Weq I And Cenl9rOf Gtavily Limil 0ala Lancing Gem Down WEIGHTCONDITION 3600 LB MAX TAKE Ff OR LANDU 3 310Q LB OR LESS FORWARD C G UMIT 80 4 87 7 7...

Page 350: ...SYSTEMS DESCRIPTION ALTIMETER VERTICAL SPEED BEZEL AVIONICS RED RADIAL IS ioJ GREEN ARC YELLOW ARC ENGINE INSTRUMENT PANEL FAA Approved Issued April 1991 P N 36 590002 55 38 390 030 17 of 18...

Page 351: ...horsepower by reducing engine speed to 2550 rpm PROPELLER The A36 Bonanza modified for reduced external noise is equipped with a Hartzell constant speed three blade pro peller using a PHC C3YF IRF hu...

Page 352: ...nt for the Four Position Flap ControlSwitch This Supplement is applicable to Pilot s Operating Handbook and FAA Approved Airplane Flight Manual P N 36 590002 37 Airplane Serial Number ________ _ Airpl...

Page 353: ...Position Flap Control switch in accordance with Beech FAA approved data The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight...

Page 354: ...VFR DAY VFR NIGHT SYSTEM and or IFR DAY COMPONENT IFR NIGHT ICING CONDITIONS Remarks and or Exceptions FLIGHT CONTROLS 1 Flap position indica 1 1 1 1 1 Replaces Flap Posi tor tion Indicator Lights EM...

Page 355: ...t side of the switch guard facing the pilot is placarded UP AP and DN The aft facing placard is UP and DN with a white index corresponding to the AP posi tion between UP and DN When the flap handle is...

Page 356: ...struments GPS Annunciator Control Unit with PS Engineering PMA7000M S Audio Panel with BF Goodrich WX 500 Weather Mapping Sensor with I Shadin F ADC 200 or 200 Fuel Air Data Computer I when used with...

Page 357: ...ers Mid Continent Instruments GPS Annunciation Control Unit Garmin Course Deviation Indicator PS Engineering PMA7000M S Audio Panel BF Goodrich WX 500 Weather Mapping Sensor and Shadin F ADC 200 or 20...

Page 358: ...vision must be immediately available to the flight crew whenever navigation is predicated on the use of the sys tem 2 Each GNS must utilize the following or later FAA approved software versions SYSTEM...

Page 359: ...vigation 4 IFR enroute and terminal navigation predicated upon either GNS units GPS receiver is prohibited unless the pilot veri fies the currency of the database or verifies each selected waypoint fo...

Page 360: ...ational g VNAV information may be utilized for advisory informa tion only Use of VNAV information for Instrument Approach Procedures does not guarantee Step Down Fix altitude protection or arrival at...

Page 361: ...6 AC 20 138 and JAA AMJ 20X2 Leaflet 2 Revision 1 9 Navigation is accomplished using the WGS 84 NAD 83 coordinate reference datum Navigation data is based upon use of only the Global Positioning Syste...

Page 362: ...ng and hold ing the Comm transfer button on the GNS unit for 2 seconds I will select the emergency frequency of 121 500 MHz into the Active frequency window 4 In the event of an audio panel failure th...

Page 363: ...matic Flight Control System operating proce dures are described in the Bendix King KFC 225 Pilot s Guide P N 006 18035 0000 dated April 1999 or later appropriate revision and the FAA Approved Airplane...

Page 364: ...luminates to indicate that the No 1 GNS is in the normal mode and automatic waypoint sequencing is enabled OBS Green Illuminates in conjunction with the No 1 GNS unit OBS annunciator to indicate that...

Page 365: ...unciator to indicate that the No 2 GNS is in the GPS mode and the CDI is displaying GPS data 3 The following annunciators are located on the instrument panel above the pilot s airspeed indicator MM Am...

Page 366: ...TS GPS NAVSOURCESELECTED PHASE LATERAL EN ROUTE 5 0 nm TERMINAL 1 0 nm APPROACH 0 3nm The CDI displays No 2 GNS navigation data The course must I be manually set to the desired track DTK displayed on...

Page 367: ...No 1 GNS No 2 GNS GNS 430 Selection of VLOC or GPS as the active navigation source can only be accomplished by pressing the COi button on the No 2 GNS Selection of OBS mode can only be accomplished b...

Page 368: ...r REV modes of operation of the flight director and reversion to the AOL mode APPROACH OPERATIONS The APR mode should be selected when conducting flight direc tor autopilot coupled GPS approaches AUTO...

Page 369: ...ach causing added workload and possible confusion for the pilot Thus it is highly recommended that the ILS CDI CAP TURE option be set to MANUAL for all autopilot flight director operations IWARNING Us...

Page 370: ...patterns or missed approach procedures The pilot is responsible for naviga tion during these operations IWARNING I Procedure turns holding and missed approach pro cedures must be accomplished using HO...

Page 371: ...he throttle mounted GO AROUND button is not interfaced to either GNS When the airplane reaches the missed approach waypoint during approach procedures the GNS transitions to the SUSP mode and continue...

Page 372: ...or incoming radio transmission may be initiated by momentary aft activation of the AUD STAM switch located on the pilot s control wheel Subsequent activation of this switch will playback previously re...

Page 373: ...akers are located on the avion ics circuit breaker panel I The No 2 GNS navigation data is presented on the course devi ation indicator CDI and can not be coupled to the automatic flight control syste...

Page 374: ...y be selected by pressing the desired receive audio selector buttons Selected audio sources are identified by illumi nation of the green LED located on each selector button A split mode communication...

Page 375: ...io panel also incorporates a digital recorder capable of automatic recording of up to 16 incoming or outgoing radio trans missions Playback of the recorded messages is limited to the pilot s headset 1...

Page 376: ...at number 5 on the left sidewall Station Number 6 Located behind seat number 6 on the right sidewall Music Input No 1 Located below the center armrest between the pilot s and copilot s seat Music Inpu...

Page 377: ...ilot Music lflput No 2 Radio Radio Music Input No 1 Music Input No 1 MARKER BEACON The audio panel incorporates built in marker beacon receiver and annunciators Additional marker beacon annunciators a...

Page 378: ...Guide P N 190 00181 00 FUEL AIR DATA COMPUTER The Shadin F ADC 200 or 200 if installed is a remote mounted computer that measures pitot static pressures heading and fuel flow and sends the data to bot...

Page 379: ...pilot s airspeed indicator Selecting the T M position of the marker mode selector switch will test all of these annunciators Annunciator dimming is controlled by a built in photocell INTERIOR LIGHTING...

Page 380: ...the Honeywell KMD 550 Multi Function Display and Mid Continent Instrument Company MD41 1208 Terrain Awareness Annunciator Control Unit This Supplement is Applicable to the Following Manual s 36 59000...

Page 381: ...ual Supplement for the Honeywell KMH880 Multi Hazard Awareness System with the Honeywell KMD 550 Multi Function Display and Mid Continent Instrument Company MD41 1208 Terrain Awareness Annunciator Con...

Page 382: ...550 Multifunction Display and Mid Continent Instrument Company MD41 1208 Annunciator Control Panel in accordance with Raytheon Aircraft approved data The KMH880 system provides a General Aviation Enh...

Page 383: ...r revision for con trol and display of the KMH880 Traffic Advisory System SECTION II LIMITATIONS 1 The Bendix King KTA870 KMH880 Traffic Advisory System Multi Hazard Awareness System Pilot s Guide Hon...

Page 384: ...s intended to assist in visually locating traffic and lacks the resolution neces sary for use in evasive maneuvering 7 If the pilot is advised by Air Traffic Control to disable the altitude reporting...

Page 385: ...mply with an EGPWS warning NOTE If the GA EGPWS issues a terrain warning the Terrain Page on the KMD 550 will automatically be displayed if not currently selected In IMC or at Night 1 Wings LEVEL 2 Po...

Page 386: ...Annunciator Illumination of the amber TERR annunciator Terrain Display Threat area displayed in solid yellow color Definition of Threat A terrain or obstacle threat exists approxi mately 1 minute ahe...

Page 387: ...g frequency if the altitude continues to decrease EXCESSIVE RATE OF DESCENT ALERT Below 5000 Feet AGL Voice Alert SINK RATE SINK RATE Annunciator Illumination of the amber TERR annunciator Definition...

Page 388: ...T message is displayed at the bottom left of the KMD 550 Terrain Page DEACTIVATION OF THE GA EGPWS If the pilot in command determines that activation of the GA EGPWS will interfere in dealing with eme...

Page 389: ...rain Page of the KMD 550 for general altitude awareness IWARNING I The Geometric MSL altitude displayed on the Terrain Page of the KMD 550 is a calculated val ue and must not be considered as a primar...

Page 390: ...an operating transponder The TAS can detect and track aircraft with either an ATCRBS operating in Mode A or C or a Mode S transponder The TAS is only an aid in detecting other traffic and provides a m...

Page 391: ...other and of the KMD 550 The viewing angle altitude dis play is also independently controllable using the fol lowing procedure 1 Press the small knob to activate the cursor 2 Use the large knob to se...

Page 392: ...dvisory Voice Alert TRAFFIC TRAFFIC inhibited when any GA EGPWS voice alert is in progress and when the landing gear is down Traffic Display A filled yellow circle Pilot Response IWARNING Maneuvers ba...

Page 393: ...airplane is de scending at a rate greater than 1000 feet per minute the boundary is biased upward by one half of the rate of de scent Regardless of these facts the prudent pilot should always assume...

Page 394: ...Amber TERR N A Annunciator EXTINGUISHED 10 Yellow EGPWS TEST message EXTINGUISHED NOTE See the KMH880 Pilot s Guide for additional self test levels and a list of aural messages 2 TAS TEST a KMD 550 SE...

Page 395: ...it speakers at the conclusion of a successful test The TAS TST message will be replaced by the TAS SBY message 3 TAS LEAVE IN SBY UNTIL JUST PRIOR TO TAKEOFF Just prior to takeoff 4 TAS ON a Range 5 N...

Page 396: ...terrain features in close proximity inhibit the visual and aural alerts using the following pro cedure The Terrain Page will remain operational on the KMD 550 a TERR INHB Switch PRESS 1 TERR INHB Ann...

Page 397: ...880 Multi Hazard Aware ness System to the airplane results in the creation of a Bendix King IHAS 8000 Integrated Hazard Avoidance System The system consists of the following components 1 KMD 550 Multi...

Page 398: ...n the lower left corner of the display The display is protected by a 3 amp circuit breaker placarded MFD Illumination is controlled by the KMD 550 brightness control in the upper left corner and the E...

Page 399: ...ight Plan Flight Plan Stormscope Flight Plan Traffic MID CONTINENT INSTRUMENTS MD41 1208 GA EGPWS TERRAIN AWARENESS CONTROL PANEL The control panel includes the following items 1 Red and amber TERR wa...

Page 400: ...ndicates terrain function INOP TEST Switch Provides press to test function for the GA EGPWS TERRINHB White Push on to inhibit all terrain Ann Switch alerting functions BENDIX KING KMH880 GENERAL AVIAT...

Page 401: ...rain Page Pop Up feature If a terrain alert or warning occurs and the Terrain Page is not currently being displayed it will automatically be recalled This feature is controlled by the setup configurat...

Page 402: ...tem detects an unreasonably large difference between the geometric altitude and the air plane altitude system a yellow message CHECK ALT will be displayed below the geometric altitude display for as l...

Page 403: ...sion A 400 Series Pilot s Guide Addendum display interface for traffic and weather data P N 190 00140 10 Revision B The following additional information is provided TAS Sensitivity Level Sensitivity l...

Page 404: ...ed on the ground 3 The TAS Test feature is inhibited when airborne SECTION VIII HANDLING SERVICING AND MAINTENANCE Troubleshooting repair and maintenance of the installed EGPWS should be performed in...

Page 405: ...THIS PAGE INTENTIONALLY LEFT BLANK 26 of 26 FAA Approved lssued January 2003 PIN 36 590002 0061...

Page 406: ...em with the Mid Continent Instrument Company MD41 1208 Terrain Awareness Annunciator Control Unit This Supplement is Applicable to the Following Manual s 36 590002 37 Airplane Serial Number __________...

Page 407: ...FAA Approved Airplane Flight Manual Supplement for the Honeywell KMHBB0Multi Hazard Awareness System with the Mid Continent Instrument Company MD41 1208 Terrain Awareness Annunciator Control Unit REV...

Page 408: ...rol Panel in accordance with Raytheon Aircraft approved data The KMH880 system provides a General Aviation Enhanced Ground Proximity Warning System GA EGPWS and a Traffic Advisory System TAS The TAS i...

Page 409: ...ot when operating the KMH880 system 2 The Garmin GNS 530 Pilot s Guide Reference P N 190 00181 00 Revision B May 2001 or later revision must be readily accessible to the pilot when operating the KMH88...

Page 410: ...OBSTACLE OBSTACLE PULL UP or PULL UP PULL UP In either case the voice alert PULL UP will be continually re peated until the threat is eliminated Annunciator Illumination of the red TERR annunciator De...

Page 411: ...errain clearance is as sured 6 Advise Air Traffic Control as necessary IWARNING I Only vertical maneuvers are recommended un less the pilot using all available information and instruments determines t...

Page 412: ...threat no longer exists 2 Advise Air Traffic Control as necessary PENETRATION OF RUNWAY FIELD CLEARANCE FLOOR Voice Alert TOO LOW TOO LOW Annunciator Illumination of the amber TERR annunciator Definit...

Page 413: ...nway Elevation Voice Alert DON T SINK DON T SINK Annunciator Illumination of the amber TERR annunciator Definition of Threat Airplane experiences an inadvertent de scent or loss of altitude after take...

Page 414: ...has de tected an unreasonable difference between the pilot s altimeter system and the GA EGPWS calculated geometric altitude Pilot s Altimeter CHECK a Verify correct barometric setting b Check for rea...

Page 415: ...ATCRBS operating in Mode A or C or a Mode S transponder The TAS is only an aid in detecting other traffic and provides a means tor the pilot to visually acquire and avoid aircraft which may im pose a...

Page 416: ...c may be displayed on all pages of the GNS 530 in the field below the Nav fre quency data Refer to the Garmin GNS 530 Pilot s Guide 2 Traffic Advisories TA s can be expected to occur during normal fli...

Page 417: ...ontacted to obtain any information that may assist the crew concerning the intruder air craft c Evasive maneuvers rapid changes in pitch roll nor mal acceleration thrust or speed should only be con du...

Page 418: ...ED 7 Amber TERR N A Annunciator EXTINGUISHED 2 TAS TEST a GNS 530 On and Airplane Position Acquired b Select NAV Page 3 TRAFFIC WEATHER c Push small right knob to activate cursor d Rotate large right...

Page 419: ...laced by the STBY message 3 TAS LEAVE IN SBY UNTIL JUST PRIOR TO TAKEOFF Just prior to takeoff 4 TAS ON With NA V page 3 selected on the GNS 530 a Push small right knob to activate cursor b Rotate lar...

Page 420: ...S DERATIONS 1 If landing on a runway less than 2000 feet in length a run way that is not in the GA EGPWS database or a runway that may have unique terrain features in close proximity inhibit the visua...

Page 421: ...errain or operating procedures During day VFR these expected warnings may be considered as cautionary and the approach con tinued AFTER LANDING TAS SBY SECTION V PERFORMANCE No Change SECTION VI WEIGH...

Page 422: ...l Panel 3 Bendix King KA815 Directional Traffic Advisory Antennas located on the top and bottom of the fuselage MID CONTINENT INSTRUMENTS MD41 1208 GA EGPWS TERRAIN AWARENESS CONTROL PANEL The control...

Page 423: ...Color Control TERR Red TERR Amber TERR N A Amber TEST Switch TERR INHB White Ann Switch 18 of 22 Cause for Illumination Function Terrain Warning Terrain Alert Indicates terrain function INOP Provides...

Page 424: ...om the left gear down limit switch GEOMETRIC ALTITUDE This altitude is an approximation of the airplanes altitude above Mean Sea Level and is calculated by the GA EGPWS system using GPS altitude obtai...

Page 425: ...traffic and weather data P N 190 00140 10 Revision B The following additional information is provided TAS Sensitivity Level Sensitivity level A is invoked when the gear is down Sensitivity level B is...

Page 426: ...borne SECTION VIII HANDLING SERVICING AND MAINTENANCE Troubleshooting repair and maintenance of the installed EGPWS should be performed in accordance with the applicable Wiring Diagram Manual Bendix K...

Page 427: ...THIS PAGE INTENTIONALL V LEFT BLANK 22 of 22 FAA Approved Issued March 2003 PIN 36 590002 0063...

Page 428: ...ourse Deviation Indicator with Mid Continent Instruments GPS Annunciator Control Unit with PS Engineering PMA7000B Series Audio Panel with BF Goodrich WX 500 Weather Mapping Sensor with Shadin F ADC 2...

Page 429: ...ourse Deviation Indicator with Mid Continent Instruments GPS Annunciator Control Unit with PS Engineering PMA7000B Series Audio Panel with BF Goodrich WX 500 Weather Mapping Sensor with Shadin F ADC 2...

Page 430: ...id Continent Instruments GPS Annunciation Control Unit Garmin Course Deviation Indicator PS Engineering PMA7000B series Audio Panel BF Goodrich WX 500 Weather Mapping Sensor and Shadin F ADC 200 or 20...

Page 431: ...evision must be immediately available to the flight crew whenever navigation is predicated on the use of the sys tem 2 Each GNS must utilize the following or later FAA approved software versions y ul...

Page 432: ...ion 4 IFR enroute and terminal navigation predicated upon either GNS units GPS receiver is prohibited unless the pilot veri fies the currency of the database or verifies each selected waypoint for acc...

Page 433: ...operational g VNAV information may be utilized for advisory informa tion only Use of VNAV information for Instrument Approach Procedures does not guarantee Step Down Fix altitude protection or arrival...

Page 434: ...0 138 and JAA AMJ 20X2 Leaflet 2 Revision 1 9 Navigation is accomplished using the WGS 84 NAD 83 coordinate reference datum Navigation data is based upon use of only the Global Positioning System GPS...

Page 435: ...and hold ing the Comm transfer button on the GNS unit for 2 seconds will select the emergency frequency of 121 500 MHz into the Active frequency window 4 In the event of an audio panel failure the Fa...

Page 436: ...Flight Control System operating proce dures are described in the Bendix King KFC 225 Pilot s Guide P N 006 18035 0000 dated April 1999 or later appropriate revision and the FAA Approved Airplane Fligh...

Page 437: ...e Illuminates to indicate that the No 1 GNS is in the normal mode and automatic waypoint sequencing is enabled OBS Green Illuminates in conjunction with the No 1 GNS unit OBS annunciator to indicate t...

Page 438: ...or to indicate that the No 2 GNS is in the GPS mode and the CDI is displaying GPS data 3 The following annunciators are located on the instrument panel above the pilot s airspeed indicator MM Amber Il...

Page 439: ...ASE EN ROUTE 5 0nm TERMINAL 1 0 nm APPROACH 0 3nm The CDI displays No 2 GNS navigation data The course must be manually set to the desired track DTK displayed on the No 2 GNS when operating in the nor...

Page 440: ...No 2 GNS GNS 430 Selection of VLOC or GPS as the active navigation source can only be accomplished by pressing the CDI button on the No 2 GNS Selection of OBS mode can only be accomplished by pressing...

Page 441: ...EV modes of operation of the flight director and reversion to the AOL mode APPROACH OPERATIONS The APR mode should be selected when conducting flight direc tor autopilot coupled GPS approaches AUTOMAT...

Page 442: ...causing added workload and possible confusion for the pilot Thus it is highly recommended that the ILS CDI CAP TURE option be set to MANUAL for all autopilot flight director operations IWARNING I Use...

Page 443: ...rns or missed approach procedures The pilot is responsible for naviga tion during these operations IWARNING I Procedure turns holding and missed approach pro cedures must be accomplished using HDG as...

Page 444: ...ottle mounted GO AROUND button is not interfaced to either GNS When the airplane reaches the missed approach waypoint during approach procedures the GNS transitions to the SUSP mode and continues to p...

Page 445: ...incoming radio transmission may be initiated by momentary aft activation of the AUD STRM switch located on the pilot s control wheel Subsequent activation of this switch will playback previously reco...

Page 446: ...nd GPS NAV 1 The circuit breakers are located on the avion ics circuit breaker panel The No 2 GNS navigation data is presented on the course devi ation indicator CDI and can not be coupled to the auto...

Page 447: ...ceive audio is automatically selected Additional receiver audio sources may be selected by pressing the desired receive audio selector buttons Selected audio sources are identified by illumi nation of...

Page 448: ...panel also incorporates a digital recorder capable of automatic recording of up to 16 incoming or outgoing radio trans missions Playback of the recorded messages is limited to the pilot s headset 1 Al...

Page 449: ...number 5 on the left sidewall Station Number 6 Located behind seat number 6 on the right sidewall Music Input No 1 Located below the center armrest between the pilot s and copilot s seat Music Input N...

Page 450: ...ot Music Input No 2 Radio Radio Music Input No 1 Music Input No 1 MARKER BEACON The audio panel incorporates built in marker beacon receiver and annunciators Additional marker beacon annunciators are...

Page 451: ...Guide P N 190 00181 00 FUEL AIR DATA COMPUTER The Shadin F ADC 200 or 200 if installed is a remote mounted computer that measures pitot static pressures heading and fuel flow and sends the data to bo...

Page 452: ...irspeed indicator Selecting the T M position of the marker mode selector switch will test all of these annunciators Annunciator dimming is controlled by a built in photocell INTERIOR LIGHTING The PANE...

Page 453: ...THIS PAGE INTENTIONALLY LEFT BLANK 26 of 26 FAA Approved Revised September 2003 P N 36 590002 0065...

Page 454: ...craft E 3399 E 3525 E 3588 E 3589 E 3591 E 3595 E 3596 E 3597 E 3600 E 3603 E 3605 E 3606 E 3608 E 3609 E 3610 E 3612 E 3613 E 3614 E 3615 E 3616 E 3628 E 3629 This Supplement is Applicable to the Fol...

Page 455: ...ort ed under the authority of ECCN 9E991 NLR These com modities technology or software were exported from the United States in accordance with the Export Administration Regulations Diversion contrary...

Page 456: ...ht Transport And Utility Aircraft E 3399 E 3525 E 3588 E 3589 E 3591 E 3595 E 3596 E 3597 E 3600 E 3603 E 3605 E 3606 E 3608 E 3609 E 3610 E 3612 E 3613 E 3614 E 3615 E 3616 E 3628 E 3629 PAGE DESCRIP...

Page 457: ...FM Approved Airplane Flight Manual POH AFM for airplanes used as a Light Transport and Utility Aircraft by the Israel Air Force in accordance with Raytheon Aircraft Company approved data The informati...

Page 458: ...D Landing Gear Extended FORWARD LIMITS 81 0 inches aft of datum at 3650 lbs with a straight line variation to 83 55 inches at 3850 lbs AFT LIMIT 87 70 inches aft of datum at all weights FLIGHT LOAD FA...

Page 459: ...titude and to 3850 lbs and read Time to Climb 21 7 14 min Fuel Used to Climb 8 4 2 8 5 6 gals Distance Traveled 43 14 29 nm CRUISE The temperatures for cruise are presented for a Standard Day ISA 20 C...

Page 460: ...000 14 5 169 14 0 160 12 000 13 5 165 13 0 153 Interpolate for 11 500 ft and the temperature for the appropriate route segment Results of the interpolations are ROUTE ISA FUELFLOW TAS SEGMENT CONDITIO...

Page 461: ...6 4 TOTAL 293 1 55 25 7 Distance required to climb has been subtracted from segment distance TIME FUEL DISTANCE CHART ITEM TIME FUEL DISTANCE HRS MIN GAL NM Start Runup Taxi and 0 00 2 2 0 Take off A...

Page 462: ...REQUIREMENT Total Fuel Required Calculated Fuel Usage Reserve Fuel Total Fuel Required 33 5 gallons 10 0 gallons 43 5 gallons LANDING WEIGHT The estimated landing weight is determined by subtracting t...

Page 463: ...ATSOME LOADINGS THEAIRPLANE IS ELEVATOR LIMITED RESULTING IN A MINIMUM STEADY SPEED RATHER THAN A STALL INDICATED AIRSPEE g CALIBRATED AIRSPEED FLAPsuA FLAPs APPROACH C t LAPSDOWN 3 800 3 600 3 400 3...

Page 464: ...F SPEED 3850 3650 3600 3400 3200 3000 2800 79 73 72 71 70 68 65 86 84 82 83 80 78 75 EXAIIPLE OAT 15 C PRESSUREALTITUDE 5 653 FT WEIGHT 3 650 LB HEADWIND COPIPONENT 10 KTS OBSTACLE HEIGHT 50 FT GROUND...

Page 465: ...TURE C WEIGHT TAKE OFF SPEED POUNDS ROTATION 50 FT 3850 3650 3600 3400 3200 3000 2800 KNOTS KNOTS 73 67 67 66 65 64 62 79 77 77 78 75 73 71 OAT 15 C PRESSURE ALTITUDE 5 653 FT WEIGHT 3 650 LB HEADWIND...

Page 466: ...S OPEN RESSURE ALTIT joe FEET oa Illa Illa 8 lflo 10 f 1 16 oa I 0 ro H OUTSIDE AIR TEMPERATURE C RAC Approved Revised December 2006 P N 36 590002 0069 40 50 CLIMB CLIMB SPEED 100 KNOTS ALLWEIGHT EXAI...

Page 467: ...fo1 ooo a ooo 6 000 4 00 2 00 s 50 40 30 20 10 0 10 20 30 OUTSIDEAIR TEMPERATURE C 40 50 60 OATAT TAKEOFF 15 C OATAT CRUISE 5 C AIRPORTPRESSUREALTITUDE 5 653 FT CRUISE PRESSUREALTITUDE 11 500 FT INIT...

Page 468: ...ISE RICH MIXTURE 3600 LBS E AACR005 1 1 Full throttle manifold pressure settings are approximate 2 Shaded area represents operation with full throttle 3 Fuel flows are to be used for flight planning o...

Page 469: ...H KIAS KTAS SL 3 27 25 0 86 3 14 4 166 158 2 000 7 19 25 0 89 3 14 9 167 163 4 000 10 14 25 0 92 3 15 4 167 168 E AACR005 2 1 Full throttle manifold pressure settings are approximate 2 Shaded area rep...

Page 470: ...FUEL AIR SPEED FLOW PPH GPH KIAS KTAS 81 6 13 6 156 148 84 1 14 156 153 86 9 E MCR005 3 1 Full throttle manifold pressure settings are approximate 2 Shaded area represents operation with full throttle...

Page 471: ...LEAN MIXTURE 3600 LBS E AACR005 4 1 Full throttle manifold pressure settings are approximate 2 Shaded area represents operation with full throttle 3 Fuel flows are to be used for flight planning only...

Page 472: ...D PPH GPH KIAS KTA 25 0 79 4 13 2 154 146 25 0 82 6 13 8 155 151 E AACR005 5 1 Full throttle manifold pressure settings are approximate 2 Shaded area represents operation with full throttle 3 Fuel flo...

Page 473: ...11 lllill mml lil illllfilm I 1 1 I 25 0 63 8 10 6 146 25 0 11 1 147 E AACR005 8 1 Full throttle manifold pressure settings are approximate 2 Shaded area represents operation with full throttle 3 Fuel...

Page 474: ...9 11 132 126 21 0 67 4 11 2 134 131 21 0 69 2 11 5 136 136 71 11 8 137 142 E AACR005 7 1 Full throttle manifold pressure settings are approximate 2 Shaded area represents operation with full throttle...

Page 475: ...PH GPH KCAS KTAS 21 0 52 6 8 8 122 116 21 0 54 0 9 0 125 122 21 0 55 4 9 2 127 127 56 8 9 5 128 132 E AACR005 8 1 Full throttle manifold pressure settings are approximate 2 Shaded area represents oper...

Page 476: ...A PRESSffiiE ALTITUDE 11 500 FT POWER SETTING FULL THROTTLE 16 000 15 000 14 000 13 000 12 000 11 000 810 000 IL I 9 000 I 8 000 7 000 IILII 6 000 4 000 3 000 2 000 1 000 0 120 130 2 500 RP TRUE AIRSP...

Page 477: ...HROTTl E TEIIPERATURE STD DAY ISA 16 000 15 000 14 000 13 000 12 000 11 000 1 1 110 000 IL I 9 000 8 000 1 000 IEs ooo 5 000 4 000 3 000 2 000 1 000 0 24 of 35 110 t Ii 120 2500 RPH TRUE AIRSPEED 180...

Page 478: ...ND ZERO 12 000 164 156 11 000 NOTE RANGE INCLUDES CRUISE CLIMB AN 10 000 9 000 Iii w 8 000 II I w 7 000 C I 6 000 J c ALLOWS FORTAXI RUNUP AND 45 168 2 160 149 MINUTES RESERVE FUEL ATECONOMY l J CRUIS...

Page 479: ...11INUTES RESERVE FUELAT ECONOl1Y 163 EXAMPLE CRUISE ALTITUDE 11 500 FT POWER SETTING FULLTHROTTLE 2500 RPl1 RANGE 833 Nl1 158 148 153 138 9 000 Iii CRUISEPOWER t I w 8 000 II I w 7 000 C t i 6 000 f...

Page 480: ...NE 6 0 LBS GAL 74 U S GAL 444 LBS SL 11 000 rR UE AlRSPEED KNOT m II I w C cC w Di I 10 000 9 000 8 000 7 000 6 000 5 000 4 000 3 000 2 000 1 000 0 RAC Approved 3 Revised December 2006 P N 36 590002 0...

Page 481: ...20 C LEAN 74 U S GAL 444 LBS OFPEAKEG SL EXAl1PLE CRUISE ALTITUDE 11 500 FT POWER SETTING FULL THROTTLE 2500 RPM ENDURANCE 5 33 HRS 5 HRS 23 MIN NOTE ENDURANCE INCLUDES CRUISE CLIMB AND ALLOWS FORTAXI...

Page 482: ...3 8 50 _ 7 9 _ 1 WEIGHT 3 479 LBS 3650 79 HEADWIND COMPONENT 10 KTS 3400 80 GROUND ROLL 960 FT 3200 81 TOTAL OVER 50 FT OBSTACLE 2112 FT 3000 81 APPROACH SPEED 80 KTS 2800 78 w i w z II w II tttttttt...

Page 483: ...E FLOOR STRUCTURE LOAD LIMIT IS 50 POUNDS PER SQUARE FOOT Q MAXIMUM WEIGHT IS 70 POUNDS r __MAXIMUM BAGGAGE WEIGHT IS 200 POUNDS WITH THE 5TH OR 6TH SEAT REMOVED MAXIMUM WEIGHT IS 200 POUNDS BETWEEN S...

Page 484: ...I I 3 700 RACApproved I I I I I I I 3 600 MaxTake CDff Landing Wt 3 BSG lb UtilityCategory r 3 500 3 400 I II 3 300 C z J 3 200 a 11 J i I 3 1mm c CJ iii 3 omm 2 900 2 8mm 2 700 2 600 2 500 2 400 CEN...

Page 485: ...tiply the result by 100 to determine the arm 5 Record the weight and corresponding moment 100 for the fuel to be used for start taxi and take off on Line 12 Remove the fuel weight and moment 100 from...

Page 486: ...Baggage 5th or 6th Seat Location 150 0 7 Baggage Aft Compartment 180 0 8 Other 9 ZERO FUEL WEIGHT 10 Fuel Load 75 0 11 RAMP WEIGHT 12 Less Fuel for Start Taxi and Run up 13 TAKE OFF WEIGHT DO NOT EXC...

Page 487: ...MENTS BAGGAGE Between Spars Removed 5th or 6th 3rd and 4th Seats Aft Facing Seat Location ARM 108 11 22 32 43 54 65 76 86 97 108 119 130 140 151 162 173 184 194 205 216 ARM 150 MOMENT 100 15 30 45 60...

Page 488: ...SECTION VII SYSTEMS DESCRIPTION NO CHANGE SECTION VIII HANDLING SERVICING AND MAINTENANCE NO CHANGE RAC Approved Revised December 2006 P N 36 590002 0069 35 of 35...

Page 489: ...or adds to the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual only as set forth within this document Users of this manual are advised always to refer to the supplement for p...

Page 490: ...or lost utilize other navigation equipment as required 3 If NAV flag appears and or DME information is lost during an approach execute published missed approach and utilize another approved facility N...

Page 491: ...light Any combination of navigational facilities RNAVwaypoint VOR DME ILS maybe _loaded into the computer however it is desirable that each facility be numbered and loaded in the sequence it is to be...

Page 492: ...mplished in the same manner The RAD and DST displays will display dashes during VOA and VOA PAR operation LS APPROACH Front course and Back course 1 Programmingan ILS approach is accomplishedin the sa...

Page 493: ...WPT waypoint is desired press th USE button The WPT display will cease blinking and the displayed waypoint becomes the active waypoint 5 The raw VOA DME data can be checked at any time by pressing th...

Page 494: ...k on distance groundspeed and time to the VORTAC station will be displayed on the DME display The HSI COi will display conventional angular crosstrack deviation from the selected course 10 full scale...

Page 495: ...selector knob to select RNAV APR In RNAV APR the deviation needle on the HSI COi will display crosstrack deviation of t 1 1 4 NM full scale All other aspects of the RNAV APRmode are identical to the R...

Page 496: ...panel and displayed in their respectivedisplays The small knob affects the least sigliificant digitswhile the large knob changes the most significant digits The tenth s position of waypoint radial an...

Page 497: ...Display Displays the offset distance of the waypoint from the ground station over a range of 0 0 to 199 9 NM 2 VOA PAR RNAV ANAV APA Displays System mode lights 3 WPT Display Displays waypoint number...

Page 498: ...APR and then back to the VOA mode b The center knob selects the WPT to be displayed Turning the knob causes the displayed waypolnt t increment by one thru the waypolnt sequence of 1 2 e 9 1 or on lat...

Page 499: ...the caret display to change from FRO to RAD to DST and back to FRO 7 OFF PULL ID Control ON OFF Pull ID Control Rotary switch potentiometer which when turned clockwise applies power to the KNS 81 and...

Page 500: ...n varies the 0 1 degree digit c Distance Data The outer knob varies the 10 NM digit with a carryover occuring from the tens to hundred place lhe center knob in the in positionvaries the 1 NM digit and...

Page 501: ...Volt Electrothermal Propeller Deice System that has been installed in accordance with Beech approved data The information in this supplement supersedes or adds to the basic Pilot s Operating Handbook...

Page 502: ...A 320 EA 389 and after On Left Window Post Forward of Pilot CAUTION MAGNETIC COMPASS IS ERRATIC WHEN PROP DEICE IS ON EMERGENCY PROCEDURES LOSS OF ALTERNATOR Propeller Deice Switch Off ABNORMAL READIN...

Page 503: ...w offs 3 More than 18 amps If propeller deice system ammeter occasionally or regularly indicates more than 18 amps the system should not be operated unless the need for propeller deice is urgent NORMA...

Page 504: ...intended for use in the event icing conditions are inadvertently encountered This airplane is not approved for flight into icing conditions even with anti ice or deice equipment installed Electrother...

Page 505: ...should be turned on and left on until it is certain the icing areas have been evaded On the ground the system should not be turned on unless the engine is running Approved FAA Approved Revised April 1...

Page 506: ...rplane has been modified by the Standby Generator Power System 28 Volt Electrical System in accordance with Beech approved data The information in this supplement supersedes or adds to the basic Pilot...

Page 507: ...1 Engine Instruments and Fuel Gages Auxiliary fuel pump will not be operative if the standby generator system is in operation 2 Electric Turn Coordinator 3 Transponder If installed 4 Audio Amplifier...

Page 508: ...instruments on the standby bus 3 Reduce electrical load to conserve battery power c NAV COMM Switch SELECT NAV COMM I or NAV COMM II d NAV I and COMM I Circuit Breakers CHECK SET NOTE When Standby Ge...

Page 509: ...rator Switch ON The bus voltmeter should indicate 24 volts 4 Standby Generator Switch RESET MOMENTARILY THEN RELEASE TO ON POSITION The bus voltmeter should indicate 28 volts 5 Standby Generator Switc...

Page 510: ...standby bus When the standby generator switch is momentarily placed in the RESETposition then releasedto the ON position the standby generator circuit is activated and the standby bus is energized by...

Page 511: ...lane has been modified by installation of the Standby In strument Air Pressure System during manufacture or by subsequent incorporation of Beech Kit PIN 36 5009 PIN 36 5011 PIN 36 5014 or PIN 36 5015...

Page 512: ...rument air pressure system occurs 1 STBY GYRO P Switch located on pilot s subpanel ON The following will result a The amber STBY GYRO P annunciator or STBY GYRO PRESSURE light will illuminate b The re...

Page 513: ...ch ON b GYRO WARN Annunciator or GYRO WARN light CHECK should be illuminated c STBY GYRO P Switch ON d STBY GYRO P Annunciator or STBY GYRO PRESSURE Light CHECK should be illuminated GYRO WARN annunci...

Page 514: ...he two pri mary air driven instruments The standby instrument air pressure system has a pressure pump driven by an electric motor and incorporates two filters a pump intake filter and an inline filter...

Page 515: ...INSTRUMENT AIR PRESSURE SYSTEM The standby instrument air pressure system incorporates two filters a pump intake filter and an inline filter The pump intake filter is attached to the keel structure on...

Page 516: ...ACARD THIS SUPPLEMENT IS APPLICABLE TO PILOT S OPERATING HANDBOOKS AND FAA APPROVED AIRPLANE FLIGHT MANUALS SEE NEXT PAGE FOR APPLICABILITY Airplane Serial Number __________ _ Airplane Registration Nu...

Page 517: ...78 All 33 590009 13 CE 674 after CJ 129 after 33 590009 15 CE 290 thru CE 673 CJ 26 thru CJ 128 33 590027 3 All 35 590071 13 All 35 590072 9 All 35 590073 15 All 35 590094 7 All 35 590110 3 All 35 59...

Page 518: ...58TC 106 590000 5 58TC 58TCA 106 590000 19 FAA Approved PIN 58 590000 49 Issued December 1990 A C SERIALS EA 242 EA 273 thru EA 388 except EA 326 EA 326 EA 389 after All TC 1 thru TC 501 except TC 35...

Page 519: ...MODEL 58TC 58TCA 4 of 7 PART NUMBER A C SERIALS 106 590000 21 TK 147 TK 151 after FAA Approved P N 58 590000 49 Issued December 1990...

Page 520: ...plane has been modified by installation of the Inside Cabin Door Handle With Open Closed Placard in accor dance with Beech Kit 35 5050 The information in this supplement supersedes or adds to the basi...

Page 521: ...RMANCE No change WEIGHT AND BALANCE No change SYSTEMS DESCRIPTION DOORS WINDOWS AND EXITS CABIN DOOR The airplane has a conventional cabin door on the for ward right side of the fuselage and when clos...

Page 522: ...CLOSED position When the door is properly locked the door latch handle is free to move approxi mately one inch in either direction NOTE When checking the door latch handle do not move it far enough t...

Page 523: ...0 and After PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT for the ARTEX ELT 110 4 002 WITH REMOTE COCKPIT SWITCH SEE PAGE 2 FOR APPLICABILITY Airplane Serial Number ___...

Page 524: ...This Supplement is applicable to the following 2 of 6 Manual s PIN 36 590002 37 PIN 36 590006 19 PIN 58 590000 39 FAA Approved Revised December 1999 P N 58 590000 55...

Page 525: ...Manual when the airplane is equipped with an ARTEX 110 4 002 Emergency Locator Transmit ter ELT and remote cockpit switch which has been installed in accordance with Raytheon FAA approved data This d...

Page 526: ...equirements of TSO C91a The system consists of the ELT transmitter located in the aft fuselage area an antenna mounted on the aft fuselage and a remote switch with a red transmit light usually located...

Page 527: ...sing the following pro cedures Tests should be conducted between the times of on the hour until 5 minutes after the hour Notify any nearby control towers Provide power to an airplane radio and tune it...

Page 528: ...HANDLING SERVICING AND MAINTENANCE No Change 6of6 FAA Approved Revised December 1999 P N 58 590000 55...

Page 529: ...lheFAAAppiiuved An plane PlightManual when1heairplaneis modifiedbythe installation of a HmizellPHC C3YF lRPIP8468A B K 6R propellerin acco rdance withSTCSA00719J A Theinformation contained hereinsupp...

Page 530: ...A APPROVEDAIRPLANEFLIGHTMANUAL SUPPLEMENT A B C to tile RAYTHEON A36 G36BONANZA POK FAAAPPROVEDAFM m sst eqla LOG OFPAGES l m Date Desqiptjgg F MA pmoved l JZ 31 Compl ete 2 Supplement 3 1998 4 All 4...

Page 531: ...AFM lo 511engine STC No 8A00719LA c I limitatipmSec II PropeUer HartzeU PHC OYP lRF Pitdl Emergency Pmccd ur cf see m Nochange F8468A B K 6R High 36 0 1 0dcgrco5 Low 13 0 0 2 degrees Measured at 30inc...

Page 532: ...ncemguipmentList See VI Weightandbalanceinformationis containedin theSTC Installation Instructions HPA36 l orHP36 lA andthe Airoraft EquipmentList SystemsDescrimi onSee vn Constantspeed 3bladepropelle...

Page 533: ...OK AND FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT for the B C Specialty Products BC410 1 Standby Alternator System Airplane Serial Number_______ _ Airplane Registration Number_____ _ FAAApprove ft...

Page 534: ...2 ofl4 B C Specialty Products Newton Ks 67114 Document No FMS410 1 LOG OF REVISIONS Description FAAApp d Original Release E W Pittman Re Formatted PrJ1 Re Written FAA Approved Date December 18 1998 Da...

Page 535: ...age 4 Section II Limitations Page 4 Section III Emergency Procedures Page 5 Section IV Normal Procedures Page 10 Section V Performance Page 11 Section VI Weight and Balance Equipment List Page 11 Sect...

Page 536: ...f the manual are advised to always refer to the supplement for possibly superseding information and placarding applicable to operation of the airplane SECTION II LIMITATIONS The standby alternator is...

Page 537: ...start powering the battery bus Thus the standby alternator must be turned off at the same time the primary alternator is turned off when executing the following procedures If the primary alternator is...

Page 538: ...ery bus If the existing alternator load exceeds approximately 20 amps the LOW BUS VOLT annunciator may also be illuminated until the load is reduced Attempt to reset the primary alternator 1 Alternato...

Page 539: ...equipment loads LOAD TABLE Equipment Nominal Amps PROP DE ICE 19 if installed Air Conditioning 15 if installed Standby Gyro Pressure 4 if installed Autopilot 7 if installed Rotating Beacon 3 Landing...

Page 540: ...he STBY ALT ON annunciator extinguished indicates a failure of the primary alternator and a failure of the standby alternator to assume the load It may also merely indicate a failure of the primary al...

Page 541: ...lternator Switch OFF 6 Loadmeter Switch STANDBY 7 Standby Alternator Switch VERIFY ON 8 STBY ALT SENSE and STBY ALT FIELD Circuit Breakers VERIFY IN If circuit breakers are in the switch is on and the...

Page 542: ...tor Switch ON STARTING ENGINE USING EXTERNAL POWER UNIT Before external power is connected to the airplane I Standby Alternator Switch OFF After engine is started and Alternator Switch is turned on 2...

Page 543: ...OLT annunciator illuminated 7 Standby Alternator Switch a OFF STBY ALT ON annunciator extinguished b ON STBY ALT ON annunciator illuminated 8 Alternator Switch ON a STBY ALT ON annunciator EXTINGUISHE...

Page 544: ...ltage The automatic switching from the primary alternator to the standby alternator will be indicated by the illumination of the amber STBY ALT ON annunciator The primary alternator switch should be p...

Page 545: ...or the output of the standby alternator may be read in amps directly from the loadmeter e g a 20 amp output will indicate 20 on the loadmeter Output voltage of the standby alternator will be indicated...

Page 546: ...B C Specialty Products Newton Ks 67114 Document No FMS4I0 1 SECTION IX SUPPLEMENTS Place this document in the POH AFM supplements section 14 of 14 FAA Approved Date December 18 1998...

Page 547: ...ory Circulars 10 12 FAA General Aviation News 10 15 FAA Accident Prevention Program 10 15 Additional Information 10 16 General Information on Specific Topics 10 17 Maintenance 10 17 Hazards of Unappro...

Page 548: ...pins 10 36 Descent 10 38 Vortices Wake Turbulence 10 39 Takeoff and Landing Conditions 10 40 Medical Facts for Pilots 10 40 General 10 40 Fatigue 10 41 Hypoxia 10 41 Hyperventilation 10 43 Alcohol 10...

Page 549: ...oughly familiar with your airplane Know its limitations and your own Maintain your currency or fly with a qualified instructor until you are current and proficient Practice emer gency procedures at s...

Page 550: ...on and the other operating and maintenance manu als which accompany the airplane that FM requirements for ratings certifications and review be scrupulously com plied with and that you allow only perso...

Page 551: ...uctor until you are current Practice until you are proficient Preplan all aspects of your flight including a proper weather briefing and adequate fuel reserves Use services available weather briefing...

Page 552: ...action can be accomplished without reference to the manual Keep your airplane in good mechanical condition Stay informed and alert fly in a sensible manner DON TS Don t take off with frost ice or snow...

Page 553: ...on of your airplane When the airplane was manufac tured it was equipped with one or more of the following placards Owner s Manual FAA Approved Airplane Flight Manual FAA Approved Airplane Flight Manua...

Page 554: ...ions of BEECHCRAFT Safety Communiques to BEECH CRAFT Owner addresses as listed by the FAA Aircraft Reg istration Branch List and the BEECHCRAFT International Owner Notification Service List While this...

Page 555: ...uest may be made by using the owner notification request card furnished with the loose equipment of each airplane at the time of delivery or by a letter requesting this service referencing the specifi...

Page 556: ...gulations The regulations are designed for your protection and the protection of your passengers and the public Com pliance is mandatory AIRWORTHINESS DIRECTIVES FAR Part 39 specifies that no person m...

Page 557: ...d Icing Radio Phraseology and Technique Mountain Flying Airport Operations Wake Turbulence Vortices Clearances and Separations Medical Facts for Pilots Preflight Bird Hazards Departures IFR Good Opera...

Page 558: ...viation bookstores or at FBO s These documents are subject to periodic revision Be certain the Advisory Circular you are using is the latest revision available Some of the Advisory Circulars of intere...

Page 559: ...als Markings and Placards Airplanes Availability of Industry Developed Guide lines for the Conduct of the Biennial Flight Review The Accident Prevention Counselor Pro gram Pilot Transition Courses for...

Page 560: ...lance Handbook Maintenance and Handling of Air Driven Gyroscopic Instruments Use of Alternate Grades of Aviation Gaso line for Grade 80 87 and Use of Automotive Gasoline Noise Hearing Damage and Fatig...

Page 561: ...ecialists to each Flight Standards and General Aviation District Office to organize accident prevention program activities In addition there are over 3 000 volunteer airmen serving as accident prevent...

Page 562: ...n eral Aviation Accident Prevention Program These can be obtained at FAA Offices Weather Stations Flight Service Stations or Airport Facilities Some of these are titled 12 Golden Rules for Pilots Weat...

Page 563: ...d and promptly corrected Schedule your maintenance regularly and have your air plane serviced by a reputable organization Be suspicious of bargain prices for maintenance repair and inspections It is t...

Page 564: ...ressly disclaims any responsibility for malfunctions failures damage or injury caused by use of non BEECHCRAFT parts Airplanes operated for Air Taxi or other than normal opera tion and airplanes opera...

Page 565: ...Supple mental Type Certificates STC s Before installing an STC on your airplane check to make sure that the STC does not conflict with other STC s that have already been installed Because approval of...

Page 566: ...k and stations and make a list for quick reference It is strongly recommended a flight plan be filed with Flight Service Sta tions even though the flight may be VFR Also advise Flight Service Stations...

Page 567: ...is utilized to provide space for seat displacement If hard solid objects are stored beneath seats the energy absorbing feature is lost and severe spinal injuries can occur to occupants Prior to fligh...

Page 568: ...speed will be higher rate of climb the cruising speed and the range of the airplane at any level of fuel will all be lower than shown in the Performance section If an airplane is loaded so that the C...

Page 569: ...ibed in the Airpiane Flight Manual Supplements Ensure a full understanding of the methods of engagement and disengagement of the autopi lot and trim systems Compare the descriptions and procedures con...

Page 570: ...function from an electric trim system malfunction The safest course is to deactivate both Do not re engage either system until after you have safely landed Then have the systems checked by a qualified...

Page 571: ...FLT switch on the autopilot control ler if installed NOTE After the autopilot is positively disengaged it may be necessary to restore other electrical functions Be sure when the master switches are tu...

Page 572: ...the air plane Airplanes are designed so that flutter will not occur in the normal operating envelope of the airplane as long as the airplane is properly maintained In the case of any airplane decreas...

Page 573: ...ure which could create an increased trailing edge heavy control surface and flutter If an excessive vibration particularly in the control column and rudder pedals is encountered in flight this may be...

Page 574: ...age Airplane may be momentarilyout of control Occupants are thrown violently against the belts and back into the seat Unsecured objects are tossed about Occupants require seat belts and occasion ally...

Page 575: ...an excessive airspeed you run the risk of structural damage or failure on the other hand if your air speed is too low you may stall If turbulence is encountered reduce speed to the turbulent air pene...

Page 576: ...re downdrafts The prediction of wind shears is far from an exact science Monitor your airspeed carefully when flying near storms particularly on approach Be mentally prepared to add power and go aroun...

Page 577: ...hoes should be separated by at least 40 miles before you fly between them With weaker echoes you can reduce the distance by which you avoid them Above all remember this never regard any thunderstorm l...

Page 578: ...put on your shoulderharness and secure all looseobjects 10 Plan and hold your course to take you through the storm in minimumtime 11 To avoid the most critical icing establisha penetration altitude b...

Page 579: ...should not be taken as assurance that mountain wave turbulence will not be encountered A mountain wave downdraft may exceed the climb capability of your airplane Avoid mountain wave downdrafts VFR LO...

Page 580: ...interpretations illusions result and may confuse the pilot s conception of the attitude and position of his air plane Under VFR conditions the visual sense using the horizon as a reference can overrid...

Page 581: ...d not be made or it should be discontinued as soon as possible The result of vertigo is loss of control of the airplane If the loss of control is sustained it will result in an excessive speed acciden...

Page 582: ...ivated by interruption of circuits circuit breakers or fuses Compliance with this requirement is especially important in all high performance single engine airplanes during simulated engine out practi...

Page 583: ...t intentional spins are entered by delib erately inducing a yawing moment with the controls as the airplane is stalled Inadvertent spins result from the same combination stall plus yaw That is why it...

Page 584: ...avoidance is your best protection against an inadvertent spin MAINTAIN YOUR AIRSPEED In airplanes not certificated for aerobatics spins are prohib ited If a spin is entered inadvertently Immediately...

Page 585: ...rtices The larger and heavier the airplane the more pronounced and turbulent the wakes will be Wing tip vortices from large heavy airplanes are very severe at close range degenerating with time wind a...

Page 586: ...ction Snow and ice covered runways are also hazardous The pilot should also be alert to the possibility of the brakes freezing Use caution when taking off or landing during gusty wind conditions Also...

Page 587: ...m system to let you know when you are not getting enough oxygen It is impossible to predict when or where hypoxia will occur during a given flight or how it will manifest itself Some of the common sym...

Page 588: ...require or may require the use of supplemental oxygen should be thoroughly familiar with the operation of the airplane oxygen systems A preflight inspection of the system should be performed including...

Page 589: ...ly slow your breathing rate until symptoms clear and then resume nor mal breathing rate Normal breathing can be aided by talk ing aloud ALCOHOL Common sense and scientific evidence dictate that you mu...

Page 590: ...bout one third of an ounce per hour Even after the body completely destroys a moderate amount of alcohol a pilot can still be severely impaired for many hours by hangover The effects of alcohol on the...

Page 591: ...Even simple home or over the counter remedies and drugs such as aspirin anti histamines cold tablets cough mixtures laxatives tranquil izers and appetite suppressors may seriously impair the judgment...

Page 592: ...nitrogen bubble formation in body tissue as the ambient air pressure is reduced by climbing to higher alti tudes The symptoms are pain in the joints abdominal cramps burning sensations in the skin vis...

Page 593: ...is even more remarkable Radar RNAV LORAN sophisticated autopilots and other devices which just a few years ago were too large and pro hibitively expensive for general aviation size airplanes are beco...

Page 594: ...Section X Safety Information Oeemcra ft Single Engine Piston THIS PAGE JNTENTIONALL Y LEFT BLANK 10 48 May 1994...