Raytheon Beech Bonanza A36 Скачать руководство пользователя страница 238 | Manualshive

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Handling, Serv & Maint

Section 8

Model A36

8-13

SERVICING

FUEL SYSTEM

Refer to Section 2, Limitations, for a list of approved engine
fuels.

FUEL CELLS

Never leave the fuel cells completely empty
for more than a few days, as the cell inner
lining may dry out and crack, permitting fuel
to diffuse through the walls of the cell after
refueling. If the cells are to remain empty
for a week or more, a thin coating of light
engine oil should be sprayed or flushed
onto the inner lining of the cells.

The fuel cell installation consists of a 40-gallon capacity (37
gallons usable) fuel cell and filler cap in 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 indicates 27 gallons
of usable fuel. Filling to the slot on the tab indicated 32 gallons
of usable fuel. The airplane must be level for the tabs to indi-
cate accurately.

FUEL DRAINS

The fuel system is drained at 3 locations: one under each wing
just outboard of the fuselage, and a system low point drain in
the bottom of the fuel selector valve. All three drains are of
snap-type actuation. The fuel selector valve drain is accessible
through a door in the fuselage adjacent to the left wing. Open
the three drains daily during preflight to purge any water from
the system.

January, 2006

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Содержание Beech Bonanza A36

Страница 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 ______...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

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

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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 _____...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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 _...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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 __________...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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 ___...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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

Страница 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...

Страница 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...

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

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

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

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