Beechcraft Baron 58 Pilot Operating Handbook Download

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Summary of Contents for Baron 58

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Page 4: ...CEPT TH 1389 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL A13 Revision July 1994 LOG OF REVISIONS Page Description Title Page Updated Page A A13 New 10 1 thru Revised Section X Safety 10 64 Information May 1994 r PAGE A ...

Page 5: ...T TH 1389 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL A12 Revision OctoberI 1990 LOG OF REVISIONS Page Description Title Page Updated Page A New A12 10 1 thru Revised Section X 10 68 Safety Information October 1990 PAGE A ...

Page 6: ...and FAA Approved Airplane Flight Manual Log of Revisions PIN 58 590000 21A11 A11 March 1988 Page Description Title Page Updated Page A A11 New 2 10 Revised KINDS OF OPERATION and WARNING 4 21 Revised ICE PROTECTION SYSTEMS 8 48 Revised OVERHAUL OR REPLACEMENT SCHEDULE F Page A ...

Page 7: ...vised Required Equipment for Various Con ditions of Flight title to Kinds of Operations Equipment list Revised System and or Com ponent List of Same Relocated Same from Pages 2 10 thru 2 19 to Pages 2 24 thru 2 30 Deleted Revised Table of Contents Revised Air Start and Shifted Material Added Serialization to Illumination of Alter nator Out Light Added Illumination of Alternator Out light TH 1377 a...

Page 8: ...ed Material 8 1 and 8 2 Revised Table of Contents 8 6 8 6A and Revised Publlcancns and Shifted Material 8 68 8 7 Revised Alterations to Airplane 8 13 and 8 14 Deleted Recharging the Battery and Shifted Material 8 16 thru 8 18 Revised Oil System Battery and Tires Shifted Material IAl0 Page B ...

Page 9: ...on 58J58AI TH 773 Through TH 1395 Except TH 1389 Pilot s Operating Handbook and FAA Approved Airplane Flight Manual A9 April 1984 LOG OF REVISIONS Page Description Title Page Update Page A A9 New r Page A ...

Page 10: ...nding 3 16 3 17 Revise Emergency Exits 4 Update Table of Contents 4 3 Revise Airspeeds For Safe Operation 4 8A 4 88 Revise Starting and After Starting and Taxi and Shift Material 4 13 Revise Balked Landing 5 27 Revise Climb Two Engine 3 Blade Pro palter Graph 7 2 Update Table of Contents 7 17 7 18 Revise Openable Cabin Windows 7 18A Add Emergency Exits 8 2 Update Table of Contents 8 23 Revise Heat...

Page 11: ...1 LOG OF REVISIONS Page Description Title Page Added Revision Date Page A A7 New 7 2 Revised Table of Contents 7 3 Revised Table of Contents 7 28 Revised Alternators 7 31 Shifted Material 7 32 Revised Interior Lighting 7 32A Added Page Revised Exterior Lighting 7 328 Added Page 7 33 Shifted Material r Page A ...

Page 12: ...IONS Page Title Page Logo Page A Page A6 7 32 7 33 7 34 7 35 7 36 Description Added Revision Date Added Update Revised Cabln Heating Revised Environmental Schematic Revised Heater Operation Revised Heat Regulation Revised Cabin Ventilation 10 1 Thru 10 67 Revised Safety Section Dated March 1981 o C t eo C t a 0 1 _ Page A ...

Page 13: ...hifted Material 2 11 Revised Required Equipment for Various Conditions of Flight 2 12 Revised Electrical Power 2 30 and 2 31 Revised Placards 3 1 Revised Table of Contents 3 11 Added Starter Energized Warning light Illuminated 3 12 and 3 13 Shifted Material 4 7 Revised Before Starting 4 8 and 4 8A Revised Starting 4 9 and 4 10 Revised Before Take Off 4 10A Revised Maximum Normal Operating Power 4 ...

Page 14: ... Compartment Revised Utility Door Shifted Material Revised Fuel Flow and Pressure Indicator Revised Fuel Flow and Pressure Indicator and Added Fuel Flow Indicator Added Fuel Flow Indicator Shifted Material Revised Battery and Alternator Revised Power Distribution Schematic Revised Alternator and Starters Revised Starters Shifted Material l I 1 _ 2 of 2 Page A ...

Page 15: ...r Markings 2 5 Revise Engines and Fuel 2 6 Revise Propellers 2 7 Revise Tachometer 2 10 Revise Flight Load Factors and Required Equipment for Various Conditions of Flight 2 12 Revise Electrical Power 2 16 Revise Lights 2 18 Revise Engine Indicating Instruments 2 21 thru 2 32 Revise Placards and Shifted Material 4 1 and 4 2 Revise Table of Contents 4 3 Revise Speeds for Safe Operation 4 5 and 4 6 R...

Page 16: ...r Operation 7 35 Revise Heat Regulation 7 39 Revise Stall Warning 7 40A Add Windshield Anti ice Electrothermal and Shifted Material 7 41 Shifted Material 8 1 thru 8 3 Revise Table of Contents 8 5 Revise Introduction 8 6 Revise Publications and Airplane Inspection Periods 8 8 Shifted Material 8 9 Revise Parking 8 12 Revise Preparation for Service 8 15 Revise Fuel Drains 8 16 Revise 0 iI System 8 l8...

Page 17: ...ge Add Revision Date and Letter Page A A3 Up date 2 26 and 2 27 Revise Placards 2 28 and 2 29 Shifted Material 2 30 Revise Placards 2 31 Shifted Material 3 16 Shifted Material 3 1 7 Revise Emergency E x it 3 18 and 3 19 Sh ifted Material 7 17 and 7 18 Revise Openable Cabin Windows 7 18A Revise Openable Cabin Windows 7 18 B Shifted Material F Page A ...

Page 18: ... and Letter eVa ENGINES eVa Vmea Definition eVe Vsse Definition eVe Table of Contents eVe AIRSPEED LIMITATIONS eVe AIRSPEED LIMITATIONS eVa OIL ev MANEUVERS hifted Data dd Placard eVa Placard eVe Table of Contents eVa EMERGENCY AIRSPEEDS elete PRACTICE DEMONSTRA TION OF Vmea eVe Table of Contents eVa SPEEDS FOR SAFE OPERATION dd PRACTICE DEMONSTRATION of Vmca dd PRACTICE DEMONSTRATION of Vmca eVa ...

Page 19: ... a and b Renumbered Pages 1 5 and 1 6 Revise General Information 2 27 Revise Placards 2 29 Revise Placards 5 36 Revise Performance 7 16 Rearrange Material 7 17 Add NOTE 7 43 and 7 44 Revise Engine Break in Information 8 16 Revise Oil System 8 36 Revise Recommended Servicing Schedule 8 41 Revise Consumable Materials 8 45 Revise Bulb Replacement Guide p Page A ...

Page 20: ...6 a thru c Original October 1976 1 1 thru 1 20 Original October 1976 2 1 thru 2 30 Original October 1976 3 1 thru 3 20 Original October 1976 4 1 thru 4 26 Original October 1976 5 1 thru 5 48 Original October 1976 6 1 thru 6 22 Original October 1976 7 1 thru 7 44 Original October 1976 8 1 thru 8 52 Original Section 9 See Log of Supplements October 1976 10 1 thru 10 34 Original I Original A Page A O...

Page 21: ...und Turning Clearance 1 8 Descriptive Data 1 9 Engines 1 9 Propellers 1 9 Fuel 1 1 0 Oil Capacity 1 11 Weights 1 11 Cabin Dimensions 1 11 Baggage 1 11 Specific Loadings 1 11 Symbols Abbreviations and Terminology 1 12 Airspeed Terminology and Symbols 1 12 Meteorological Terminology 1 14 Power Terminology 1 15 Engine Controls and Instruments 1 16 Airplane Pertormance and Flight Planning Terminology ...

Page 22: ...Section I General 1 2 BEECHCRAFT Baron 58 Serial TH 773 and After INTENTIONALLY LEFT BLANK October 1976 ...

Page 23: ... Airplane Flight Manual and or placards located in the airplane As a further reminder the owner and operator of this airplane should also be familiar with the applicable Federal Aviation Regulations concerning operation and maintenance of the airplane and FAR Part 91 General Operating and Flight Rules Likewise this airplane must be operated and maintained in accordance with FAA Airworthiness Direc...

Page 24: ...cuments necessary for the safe and efficient operation of the Baron The handbook has been prepared in loose leaf form for ease in maintenance and in a convenient size for storage The handbook has been arranged with quick reference tabs imprinted with the title of each section and contains ten basic divisions Section 1 Section 2 Section 3 Section 4 Section 5 Section 6 Section 7 Section 8 Section 9 ...

Page 25: ...mation may be provided to the holder of this manual automatically 1 Original issues and revisions of Beechcraft I Service Bulletins 2 Original issues and revisions of FAA Ap proved Airplane Flight Manual Supplements 3 Reissues and revisions of FAA Approved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Man uals and Pilot s Operating Handbooks This service is free and wi...

Page 26: ...tions I No 2001 Beech Aircraft Corporation expressly reserves the right to supersede cancel and or declare obsolete without prior notice any part part number kit or publication referenced in this manual The owner operator should always refer to all supplements whether STC Supplements or Beech Supplements for possible placards limitations normal emergency and other operational procedures for proper...

Page 27: ...n of the Log of Revisions is a box containing a capital letter which denotes the issue or reissue of the hand book This letter may be suffixed by a number which indi cates the numerical revision When a revision to any informa tion in the handbook is made a new Log of Revisions will be issued All Logs of Revisions must be retained in the hand book to provide a current record of material status unti...

Page 28: ...n accordance with the descriptive listing NOTE Upon receipt of a new or revised supplement compare the Log page you have just received with the Log page in the manual Retain the Log page with the latest date on the bottom of the page and discard the other log VENDOR ISSUED STC SUPPLEMENTS When a new airplane is delivered from the factory the hand book will contain either an STC Supplemental Type C...

Page 29: ...BEECHCRAFT Baron 58 Serial TH 773 and After Section I General f 37 1 0 I 1 L j 99 I 8 11 29 10 o j October 1976 1 7 ...

Page 30: ...EARANCE A A Radius for Wing Tip 31 feet 6 inches B Radius for Nose Wheel 15 feet 6 inches C Radius for Inside Gear 7 feet 11 inches D Radius for Outside Gear 17 feet 6 inches TURNING RADII ARE PREDICATED ON THE USE OF PAR TIAL BRAKING ACTION AND DIFFERENTIAL POWER 1 8 October 1976 ...

Page 31: ...Power Full Throttle and 2700 rpm Maximum Normal Operating Power TH 1090 and After I With 2 blade propellers installed With 3 blade propellers installed Maximum One Engine Inoperative Power Cruise Climb Power Maximum Cruise Power PROPELLERS HARTZELL 2 Blade Hubs BHC J2YF 2CUF Blades FC8475 6 Spinner C 2285 6P Pitch Setting at 30 inch Station Low 14 5 Feathered 80 0 Diameter 78 inches maximum 76 inc...

Page 32: ...3AF32C35 Blades 82NB 6 Spinner PD 4068 or PD 4069 Pitch Setting at 30 inch Station Low 14 00 2 Feathered I 81 2 3 Diameter 76 inches no cut off permitted FUEL Aviation Gasoline 100LL blue or 100 green minimum grade 115 145 purple Aviation Gasoline alternate grade STANDARD SYSTEM Total Capacity 142 Gallons Total Usable 136 Gallons OPTIONAL SYSTEMS Total Capacity 172 Gallons Total Usable 166 Gallons...

Page 33: ...aximum Ramp Weight 50141bs Maximum Take Off Weight 4990 Ibs Maximum Landing Weight 4990 Ibs CABIN DIMENSIONS Length 12 ft 7 in Height Max 4 ft 2 in Width Max 3 ft 6 in Entrance Door 37 in x 36 in Utility Door Opening 45 in x 35 in BAGGAGE Aft cabin compartment 37 cu ft Extended rear compartment 10 cu ft Nose compartment 18 cu ft SPECIFIC LOADINGS Wi ng Loading 27 1 lbs sq ft Power Loading 9 47 Ibs...

Page 34: ... ground Indicated Airspeed is the speed of an airplane as shown on the airspeed indicator lAS values pubfished in this handbook assume zero instrument error True Airspeed is the airspeed of an airplane relative to undisturbed air which is the CAS corrected for altitude temperature and compressibility YMCA Air Minimum Control Speed is the minimum flight speed at which the airplane is directionally ...

Page 35: ...t which application of full available aero dynamic control will not overstress the airplane VF Design flap speed is the highest speed permissible at which wing flaps may be actuated VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a pre scribed extended position VLE Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown ...

Page 36: ...OGY ISA International Standard Atmosphere in which 1 The air is a dry perfect gas 2 The temperature at sea level is 150 Celsius 590 Fahrenheit 3 The pressure at sea level is 29 92 inches Hg 1013 2 millibars 4 The temperature gradient from sea level to the altitude at which the temperature 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 ...

Page 37: ... Chart Actual atmospheric pressure at field elevation The wind velocities recorded as variables on the charts of this hand book are to be understood as the head wind or tailwind components of the reported winds POWER TERMINOLOGY Take off and Maximum Continuous Cruise Climb Maximum Cruise The highest power rating not limited by time Power recommended for cruise climb The highest power settings reco...

Page 38: ...o control the introduc tion of a fuel air mixture into the intake passages of an engine This lever requests the governor to maintain rpm at a selected value and in the maximum decrease rpm position feathers the propellers This lever in the idle cut off position stops the flow of fuel at the injectors and in the intermediate thru the full rich positions regulates the fuel air mixture The governors ...

Page 39: ... interval The demonstrated crosswind velocity is the velocity of the crosswind com ponent for which adequate control of the airplane during take off and land ing was actually demonstrated during certification tests The distance required to accelerate to a specified speed and assuming failure of an engine at the instant that speed is attained to bring the airplane to a stop The distance required to...

Page 40: ... horizontal distances are measured for balance purposes A location along the airplane fuselage usually given in terms of distance from the reference datum The horizontal distance from the ref erence datum to the center of gravity C G of an item The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify bal ance calculations by reducing the number of...

Page 41: ...irplane must be operated at a given weight Fuel available for flight planning Fuel remaining after a runout test has been completed in accordance with governmental regulations Weight of a standard airplane including unusable fuel full operating fluids and full oil Standard empty weight plus optional equipment Weight of occupants cargo and baggage Difference between ramp weight and basic empty weig...

Page 42: ...ection I General Maximum Landing Weight Zero Fuel Weight 1 20 BEECHCRAFT Baron 58 Serial TH 773 and After Maximum weight approved for the landing touchdown Weight exclusive of usable fuel September 1979 ...

Page 43: ...rs 2 6 Starters Time for Cranking 2 6 Power Plant Instrument Markings 2 7 Oil Temperature 2 7 Oil Pressure 2 7 Fuel Flow and Pressure 2 7 Fuel Flow 2 7 Manifold Pressure 2 7 Tachometer 2 7 Cylinder Head Temperature 2 8 Miscellaneous Instrument Markings 2 8 Instrument Pressure 2 8 Propeller Deice Ammeter 2 8 Fuel Quantity 2 8 Weights 2 8 CG Limits 2 9 Maneuvers 2 9 Flight Load Factors 5400 Pounds 2...

Page 44: ...d After SUBJECT TABLE OF CONTENTS Continued PAGE Minimum Flight Crew 2 10 Kinds of Operation 2 10 Fuel 2 10 Oxygen Requirements 2 11 Maximum Passenger Seating Configuration 2 11 Seating 2 11 Placards 2 12 Kinds of Operations Equipment List 2 24 2 2 AugU8t 1984 ...

Page 45: ...ng air and then only VNO or Vc with caution Maneuvering 156 156 Do not make full or VA abrupt control move ments above this speed Maximum Flap Do not extend flaps or Extension operate with flaps ex Extended VF tended above this Approach 15 152 152 speed Full Down 30 122 122 Maximum 152 152 Do not extend Landing Gear retract or operate Operating with gear ex Extended tended above VLO and VLE this s...

Page 46: ...m Flap Trianqle Approach Position 15 Blue Radial 100 100 Single Engine Best Rate ot Climb Speed Red Radial 81 81 Minimum Single Engine Control VMCA Green Arc 83 195 84 195 Normal Operating Range Yellow Arc 195 223 195 223 Operate with caution only in smooth air Red Radial 223 223 Maximum speed tor ALL operations The Airspeed Indicator is marked in lAS values I Series TH 1080 and After 2 4 Septembe...

Page 47: ...l Operating Power TH 1090 and After I With 2 blade propellers installed Full Throttle and 2550 rpm With 3 blade propellers installed Full Throttle and 2650 rpm Maximum Cylinder Head Temperature 460 GF Maximum Oil Temperature 240 GF Minimum Take off Oil Temperature 75 GF Minimum Oil Pressure idle 30 psi Maximum Oil Pressure 100 psi FUEL Aviation Gasoline 100LL blue preferred 100 green minimum grade...

Page 48: ...ed 82 0 Diameter 76 inches maximum 74 inches minimum McCAULEY TH 773 thru TH 1089 2 Blade Hubs D2AF34C30 Blades 78FF 0 Spinner D 3953 or D 4046 Pitch Setting at 30 inch Station Low 15 0 Feathered 79 0 Diameter 78 inches maximum 76 inches minimum 3 Blade Hubs D3AF32C35 Blades 82NB 6 Spinner PD 4068 or PD 4069 Pitch Setting at 30 inch Station Low 14 0 2 Feathered 181 20 30 Diameter 76 inches no cut ...

Page 49: ...nimum Red Radial Operating Range Green Arc Cruise Power Green Arc Take off and Climb Power Wide Green Arc Maximum Red Radial I FUEL FLOW Serials TH 1194 and after Operating Range Green Arc Take off and Climb Power White Radials Maximum Red Radial 69 to 243 gph 17 8 to 24 3 gph 243 gph 15t0296in Hg 296in Hg MANIFOLD PRESSURE Operating Range Green Arc Maximum Red Radial TACHOMETER Operating Range Gr...

Page 50: ...blade Normal Operating Range Green Arc 14 to 18 amps 3 blade FUEL QUANTITY Yellow Arc E to 1 8 Full WEIGHTS 58 Maximum Ramp Weight 5424 Ibs Maximum Take Off Weigh 5400 Ibs Maximum Landing Weight 5400 Ibs 58A Maximum Ramp Weight 50141bs Maximum Take Off Weight 4990 Ibs Maximum Landing Weight 4990 Ibs Maximum Baggage Cargo Compartment Weights Aft Cabin compartment less occupants and equipment 400 Ib...

Page 51: ...l weights Baron 58A Forward Limits 74 inches aft of datum at 4200 Ibs and under then straight line variation to 76 6 inches aft of datum at gross weight of 4990 Ibs Aft Limits 86 inches aft of datum at all weights Datum is 83 1 inches forward of center line through forward jack points MAC leading edge is 67 2 inches aft of datum MAC length is 63 1 inches MANEUVERS This is a normal category airplan...

Page 52: ...r the following type operations when the required equipment is installed and operational asdefined herein 1 VFR day and night 2 IF R day and night WARNING Ice protection equipment which may be in stalled on this airplane has not been demon strated to meet requirements for flight into known icing conditions FUEL TOTAL FUEL with left and right wing fuel systems full Standard Fuel System Capacity 142...

Page 53: ... be used during emergency conditions in level flight only Maximum slip duration 30 seconds OXYGEN REQUIREMENTS One mask for minimum crew and one mask per passenger with I an adequate supply of oxygen when operating above 12 500 feet MSL Refer to FAR 91 for variations concerning supple I mental oxygen requirements for a particular flight MAXIMUM PASSENGER SEATING CONFIGURATION Five 5 passengers and...

Page 54: ...ITH FLAPS EXTENDED 15 DOWN 152 KTS MAX SPEED WITH FLAPS EXTENDED NORMAL 122 KTS MAX DESIGN MANEUVER SPEED 156 KTS MIN CONTROL SPEED SINGLE ENGINE 81 KTS NEVER EXCEED SPEED 223 KTS o MAX STRUCTURAL CRUISE SPEED 195 KTS 0 On Pilot s Left Sidewall Panel 58A Serials TH 773 Thru TH 1079 Except TH 1027 TH 1062 and TH 1067 o THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY 0 AIRPLANE IN COMPLIANCE WIT...

Page 55: ...MAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF W PLACARDS MARKINGS AND MANUALS MAXIMUM WEIGHT IS 5400 LBS W PILOrS CHECK L1STI II OCCUPIED SEATS MUST BE IN UPRIGHT POSITIONFOR TAKEOFF AND LANDING II L NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED d On Upper Left Hand Side Panel 58A Serials TH 1027 TH 1062 TH 1067 TH 1080 and after rr OPERATION LIMITATION...

Page 56: ... FEED I JL I a a F F F F 00 NOT TAKE OFF IF FUEL QUANTITY GAGES 0 INDICATE IN YELLOW ARC OR WITH LESS 0 THAN 13 GAllONS IN EACH WING SYSTEM Optional 166 Gallon System 0 FUEL SELECTOR 0 LEFTWING USE CROSS FEED RIGHT WING 83 GAL IN LEVEL FLIGHT ONLY 83 GAL ON ON r ROSS FFFD I JL I 0 a F F F F 00 NOT TAKE OFF IF FUEL QUANTITY GAGES 0 INDICATE IN YEllOW ARC OR WITH LESS 0 THAN 13 GALLONS IN EACH WING ...

Page 57: ...erating Handbook and FAA Approved Airplane Flight Man ual PIN 58 590000 21 Issued Octo ber 1976 or Subsequent TH 773 thru TH 1395 except TH 1389 The addition of a placard to the fuel selectors to warn of the no flow condi tion that exists between the fuel selec tor detents Insert this temporary change Into the 58 and 58A Pilot s Operating Handbook and FAA Approved AIrplane Flight Man ual Immediate...

Page 58: ...Located On The Face Of The Fuel Selector Valves For Those Airplanes In Compliance With S 8 2670 WARNING POSITION SELECTORS IN DETENTS ONLY NO FUEL FLOW TO ENGINES BETWEEN DETENT Approved 2012 Jackson Raytheon Aircraft Co DOACE 2 PIN 580000 21TC1 10 21 97 ...

Page 59: ...L SELECTOR 0 LEFT WING USE CROSS FEED RIGHT WING 97 GAL IN LEVEL FLIGHTONLY 97 GAL ON ON CROSS FEED I JL I 0 r F F 00 NOT TAKE OFF If fUEl QUANTITY GAGES 0 INDICATE IN YELLOW ARC OR WITH LESS 0 THAN 13 GALLONS IN EACH WING SYSTEM On Inboard Side Of Seat Backs For 3rd And 4th Seats o TURN RED HANDLE TO UNLOCK SEAT BACK o August 1984 2 1 ...

Page 60: ...CY LANDING GEAR INSTRUCTIONS TO EXTEND ENGAGE HANDLE IN REAR OF FRONT SEAT AND TURN COUNTERCLOCKWISE AS FAR AS POSSIBLE 50 TURNS On Emergency Crank Access Cover LANDING GEAR EMERGENCY CRANK PULL OUT LIFT UP On Instrument Panel When Anti Collision Lights Are Not Installed THIS AIRCRAFT NOT FULLY EQUIPPED FOR NIGHT FLIGHT 2 16 August 1984 ...

Page 61: ... AIRSPEED STATIC SOURCE ON EMERGENCY SEE PILOTS CHECK LIST OR FLIGHT MANUAL EMERGENCY PROCEDURES FOR AIRSPEED ALTIMETER CALIBRATION ERROR o OR OFF 0 NORMAL STATIC AIR DRAIN VALVE TO BE CLOSED BEFORE FLIGHT WARNING o o o OPEN _R IN SE DRAIN o Adjacent To Cabin Door Handle ROTATE HANDLE TO FULL LOCKED POSITION August 1984 2 17 ...

Page 62: ...CHCRAFT Service Instructions 1241 Serials TH 773 thru TH 1079 Except TH 1027 TH 1062 and TH 1067 EMERGENCY EXIT LIFT LATCH PULL PIN PUSH WINDOW OUT On Face of Emergency Exit Latch Cover Serials TH 1027 TH 1062 TH 1067 TH 10BOandAfter EMERGENCY EXIT PULL COVER ROTATE HANDLE UP BREAKING SAFETY WIRE PUSH WINDOW OUT 2 18 August 1984 ...

Page 63: ...NG SAFETY WIRE USH WINDOW OU On Openable Cabin Windows DO NOT OPEN IN FLIGHT LATCH WINDOW BEFORE TAKE OFF Adjacent to Openeble Cabin Window Handles Serials TH 1316 and after UNLOCKED LOCKED On Oxygen Console r OXYGEN I NO SMOKING WHEN IN USE L 0SE PLUG MUST BE PULLED OUT TO STOP OXYGEN FLO On Each Oxygen Mask Stowage Container IOXYGEN MASK I August 1984 ...

Page 64: ... and TH 1067 and On All Pilot and Copilot Outlets All Serials On Oxygen Manifold Serials TH 1027 TH 1062 TH 1067 and TH 10BO and after r OXYGEN NO SMOKING WHILE IN USE I PULL PLUG TO STOP FLOW I L MOH d01S 01 orna una I ssn NI 311HM Nl tOWS ON NWAXO Adjacent to Oxygen Outlet when 5th 6th Seats Are Installed MASK STOWED UNDER 2 20 August 1984 ...

Page 65: ...RING TAKE OFF AND LANDING I WITH SEAT BACK UPRIGHT L c On Windows Adjacent to 3rd 4th Aft Facing Club Seats SHOULDER HARNESS MUST BE WORN DURING TAKE OFF AND LANDING WITH SEAT BACK UPRIGHT AND AFT FACING SEATS MUST HAVE HEADREST FULLY EXTENDED On Inside of Utility Door on Left Sidewall of UfJlity Compartment or on Aft Bulkhead BAGGAGE COMPARTMENTS o LOAD IN ACCORDANCE WITH WEIGHT AND BALANCE DATA ...

Page 66: ...NDS o WHEN UTILITY DOORS ARE REMOVED THE FOLLOWING RESTRICTIONS APPLY TO CABIN AREA 1 NO SMOKING 2 ALL LOOSE OBJECTS MUST BE SECURED 3 PERSONNEL NOT SECURED IN SEATS BY SAFETY BELTS MUST WEAR PARACHUTES On Floating Panel when Utility Doors are Removed WHEN UTILITY DOORS ARE REMOVED AIR SPEED IS NOT TO EXCEED 174 KNOTS In Plain View When Nose Baggage Compartment Door Is Open o BAGGAGE COMPARTMENT L...

Page 67: ...ER SIDE FACING PILOT 1 CLOSE THROTTLES INSTALL PIN BETWEEN LEVERS THROUGH COLLAR LOCK CONTROL COLUMN ROTATE CONTROL WHEEL APPROX 12 TO THE RIGHT 2 ROUTE CABLE RUDDER LOCK AROUND RIGHT SIDE OF CONTROL COLUMN POSITION PEDALS IN AFT POSITION INSTALL LOCK IN RUDDER PEDALS CONTROLS LOCKED REMOVE BEFORE FLIGHT August 1984 2 23 ...

Page 68: ... operated in accordance with a current Minimum Equipment List MEL issued by the FAA Or 2 An alternate procedure is provided in the Pilot s Operat ing Handbook and FAAApproved Airplane Flight Manual for the inoperative state of the listed equipment Numbers on the Kinds of Operations Equipment List refer to quantities required to be operative for a specified condition NOTE The following Kinds of Ope...

Page 69: ... 2 2 2 2 Alternator Out Light 2 2 2 2 Starter Energized 1 1 1 1 Warning Light TH 1194 and after ENGINE INDICATING INSTRUMENTS Engine Tachometer Dual Indicating 1 1 1 1 Manifold Pressure 1 1 1 1 Indicator Dual Indicating Cvlinder Head Temo Gaae 2 2 2 2 I fn 3 _ _ III 0 t I o I In OJ fnm CD m x 4 X EI ft W 4 III OJ I III 0 0 1 en co ...

Page 70: ...il Pressure Indicator 2 2 2 2 Oil Temperature Indicator 2 2 2 2 FLIGHT CONTROLS Trim Tab Indicators 3 3 3 3 Rudder Aileron and Elevator Flap System 1 1 1 1 Flap Position Indicator 1 1 1 1 Stall Warning System 1 1 1 1 Cff 3 n _ III 0 0 _ fn aJ cnm CDm o 10 D 1 1 llIaJ III e g CDCIl CII ...

Page 71: ... 1 1 1m Q III Clock 0 0 1 1 Outside Air Temperature Indicator 1 1 1 1 tg t UI FUEL EQUIPMENT CD Engine Driven Fuel Pump 2 2 2 2 Electrically Driven Aux Fuel Pump 2 2 2 2 Fuel Quantity Indicator 2 2 2 2 Fuel Flow Indicator 1 1 1 1 Fuel selector Valve 2 2 2 2 ICE AND RAIN PROTECTION Emergency Static Air System 0 0 If Installed r Pilot Heater 0 0 1 1 3 en_ 111 Heated Fuel Vent 0 0 2 2 0 III II _ 0 o ...

Page 72: ...1 0 1 Ught System Landing Ught 0 2 0 2 Landing Ught With Opt Wing 0 1 0 1 Tip Fuel Tanks TH 773 thru TH 873 Landing Ught With Opt Wing 0 2 0 2 Tip Fuel Tanks TH 874 and after Rotating Beacon 0 1 0 1 Navigation Ught 0 3 0 3 3 n _ III 0 to J o J III D l fnm CD m C I C I Jl I III D l J III 11 0 J en co ...

Page 73: ... Indicating Lights Landing Gear Aural 1 1 1 1 Warning Horn i g Emergency Landing Gear 1 1 1 1 Extension System PNEUMATIC SYSTEM Instrument Air System 0 12 I 2 1 2 Pressure Gage 0 1 1 1 PUBLICATIONS I I I I I I r Pilot s Operating Handbook 1 1 1 1 I I HN II and FAA Approved Airplane g t Flight Manual ...

Page 74: ...Y SYSTEM VFR NIGHT and or IFR DAY COMPONENT IFR NIGHT RESTRAINT SYSTEM Seat Belts Per Seat 1 1 1 1 Shoulder Harness Per Seat 1 1 1 1 f 3 n _ Dl 0 d J o J III lJ3 cnm CD m o I t I D T W t Dl lJ3 J Dl c 0 J 0 1 ClO ...

Page 75: ... Flight 3 7 Emergency Descent 3 7 Glide 3 8 Landing Emergencies 3 8 Gear Up Landing 3 8 One Engine Inoperative Landing 3 9 One Engine Inoperative Go Around 3 9 Systems Emergencies 3 10 One Engine Inoperative Operation on Crossfeed 3 10 Electrical Smoke or Fire 3 10 Starter Energized Warning Ught Illuminated 3 11 Illumination of Alternator Out Ught TH 773 thru TH 1376 3 11 Illumination of A1ternato...

Page 76: ... PAGE Landing Gear Retraction After Practice Manual Extension 3 13 Ice Protection 3 14 Surface Deice System 3 14 Electrothermal Propeller Deice System 3 14 Emergency Static Air Source 3 15 Emergency Exits 3 16 Unlatched Door in Flight 3 17 Simulated One Engine Inoperative 3 17 Spins 3 18 3 2 Revised March 1983 ...

Page 77: ...all warning horn is inoperative when the banery and ahernator switches are turned off The following information is presented to enable the pilotto form in advance a definite plan at action for coping with the most probable emergency situations which could occur in the operation of the airplane Where practicable the emergencies requiring immediate corrective action are treated in check list form fo...

Page 78: ...d the throttle for the engine that is believed to be inoperative there should be no change in control pressures or in the sound of the en gine if the correct throttle has been selected AT LOW ALTITUDE AND AIRSPEED THIS CHECK MUST BE AC COMPLISHED WITH EXTREME CAUTION Do not attempt to determine the inoperative engine by means of the tachometers or the manifold pressure gages These instruments ofte...

Page 79: ... off weights will result in a loss of altitude while retracting the landing gear and feathering the propeller Continued flight requires immediate pilot re sponse to the following procedures 1 landing Gear and Flaps UP 2 Throttle inoperative engine CLOSED 3 Propeller inoperative engine FEATHER 4 Power operative engine AS REQUIRED 5 Airspeed MAINTAINSPEEDATENGINEFAILURE l00 KTS MAX UNTIL OBSTACLES A...

Page 80: ...Use starter momentarily if necessary b Return control to high pitch low rpm position when wind milling starts to avoid overspeed Ifpropellerdoes not unfeatheror engine doesnot turn proceed to WITHOUT UNFEATHERING ACCUMULATORS procedure WITHOUT UNFEATHERING ACCUMULATORS a Move propeller control forward of the feathering detent to midrange b Engage Starter to accomplish unfeathering c If engine fail...

Page 81: ...Battery and Alternator Switches OFF 5 Extinguish with Fire Extinguisher ENGINE FIRE IN FLIGHT Shut down the affected engine according to the following procedure and land immediately Follow the applicable single engine procedures in this section 1 Fuel Selector Valve OFF 2 Mixture Control IDLE CUT OFF 3 Propeller FEATHERED 4 Aux Fuel Pump OFF 5 MagnetojStart Switch OFF 6 Alternator Switch OFF EMERG...

Page 82: ...ANDING EMERGENCIES GEAR UP LANDING If possible choose firm sod or foamed runway When assured of reaching landing site 1 Cowl Flaps CLOSE0 2 Wi ng Flaps AS DESIRED 3 Throttles CLOSED 4 Fuel Selectors OFF 5 Mixture Controls IDLE CUT OFF 6 Battery Alternator and Magnetq 5tart Switches OFF 7 Keep wings level during touchdown 8 Get clear of the airplane as soon as possible after it stops NOTE The gear ...

Page 83: ...tain 800 ft min rate of descent When it is certain there is no possibility of go around 5 Flaps DOWN 30 6 Execute normal landing ONE ENGiNE INOPERATIVE GO AROUND WARNING Level flight might not be possible for certain combinations of weight temperature and alti tude In any event DO NOT attempt a one engine inoperative go around after flaps have been fully extended 1 Power MAXIMUM ALLOWABLE 2 Landin...

Page 84: ...tor Valve CROSSFEED 4 Right Aux Fuel Pump LOW or OFF as required Right engine inoperative 1 Left Aux Fuel Pump LOW 2 Right Fuel Selector Valve OFF 3 Left Fuel Selector Valve CROSSFEED 4 Left Aux Fuel Pump LOW or OFF as required ELECTRICAL SMOKE OR FIRE Action to be taken must consider existing conditions and equipment installed 1 Battery and Alternator Switches OFF WARNING Electrically driven flig...

Page 85: ...tinuing to supply power to the starter will result in eventual loss of electrical power ON THE GROUND 1 Battery Master and both Alternator Switches OFF 2 Do not take off IN FLIGHT AFTER AIR START 1 Battery Master and both Alternator Switches OFF 2 Land as soon as practical ILLUMINATION OF ALTERNATOR OUT LIGHT TH 773I thru TH 1376 In the event of the illumination of a single AL TERNATOR OUT light 1...

Page 86: ...QUIPPED WITH KIT NO 55 3024 In the event of the illumination of a single ALTERNATOR OUT light 1 Check the respective loadmeter for load indication a No Load Turn off affected alternator b Regulate load to less than 100 of remaining alternator c Affected Alternator ON Check load indication d No Load Turn affected alternator off and leave off In the event of the illumination of both ALTERNATOR OUT l...

Page 87: ...left handle grip of the pilot s control wheel This button can be depressed to deactivate the system quickly in case of a malfunction in the system The system will remain deactivated only while the release button is being held in the depressed position 1 Airplane Attitude MAINTAIN using elevator control 2 Trim Release under pilot s thumb adjacent to control wheel trim switch HOLD IN DEPRESSED POSIT...

Page 88: ...Section III Emergency Procedures BEECHCRAFT Baron 58 Serial TH 773 and After 3 128 INTENTIONALLY LEFT BLANK AUgU8t 1984 ...

Page 89: ...l extension system is designed only to lower the landing gear do not attempt to retract the gear manually WARNING Do not operate the landing gear electrically with the handcrank engaged as damage to the mechanism could occur After emergency landing gear extension I do not move any landing gear controls or reset any switches or circuit breakers until airplane is on jacks as failure may have been in...

Page 90: ... turn off unnecessary electrical equipment Turn the prop deice system off while operating the cabin heater blower or the landing gear motor Monitor electrical loads so as not to exceed alternator capacity of 1 0 on the loadmeter An abnormal reading on the Propeller Deice Ammeter indi cates need for the following action a Zero Amps Check prop deice circuit breaker If the circuit breaker has tripped...

Page 91: ... system can continue unless serious propeller im balance results from irregular ice throw offs d More than 15 Amps 2 Blade Propeller More than 23 amps 3 Blade Propeller If the prop deice system ammeter occasionally or regularly indicates more than 15 amps for 2 blade or more than 23 amps for 3 blade the system should not be operated unless the need for prop deicing is urgent EMERGENCY STATIC AIR S...

Page 92: ... is desired for use 1 Emergency Static Air Source Switch to ON EMERGENCY lower sidewall adjacent to pilot 2 For Airspeed Calibration and Altimeter Corrections refer to the PERFORMANCE section CAUTION The emergency static air valve should remain in the OFF NORMAL position when system is not needed EMERGENCY EXITS Emergency exits provided by the openable window on each side of the cabin may be used ...

Page 93: ...tilation Emergency Exit latch 2 Rotate handle up as indicated by placard breaking safety wire and push window out NOTE Anytime the window has been opened by breaking the safety wire on the red emergency latch the window must be reattached and wired by a qualified mechanic using OQ W 343 Type S 020 diameter copper wire prior to further airplane operation UNLATCHED DOOR IN FLIGHT If the cabin door i...

Page 94: ...culties of restarting an engine and pre serves the availability of engine power The following procedure should be accomplished by al ternating small reductions of propeller and then throttle until the desired setting has been reached 1 Propeller Lever RETARD TO FEATHER DETENT 2 Throttle Lever SeT 12 in Hg MANIFOLD PRESSURE NOTE This setting will approximate Zero Thrust using recommended One Engine...

Page 95: ...n until rotation stops and then neutralize all controls and execute a smooth pullout Ailerons should be neutral during recovery NOTE Federal Aviation Administration Regulations do not require spin demonstration of airplanes of this weight therefore no spin tests have been conducted The recovery technique is based on the best available information July 1979 3 19 ...

Page 96: ...f 4 10 Maximum Performance Climb 4 10 Cruise Climb 4 10 Normal Operating Power Climb 4 1OA Cruise 4 1OA Leaning Using the Exhaust Gas Temperature Indicator 4 1OA Descent 4 12 Before Landing 4 12 Balked Landing 4 13 After Landing 4 13 Shutdown 4 13 Oxygen System 4 14 Electric Elevator Trim 4 16 Cold Weather Operation 4 17 Preflight Inspection 4 17 Engines 4 17 External Power 4 19 Starting Engines U...

Page 97: ... 21 Surface Deice System 4 22 Electrothermal Propeller Deice 4w 22A Windshield Anti ice System Electrothermal 4 23 Propeller and Windshield Anti ice System Fluid Flow 4 24 Pitot Heat and Heated Stall Warning 4 24 Fuel Vent Heat 4 25 Windshield Defogging 4 25 Engine Break In Information 4 25 Practice Demonstration of VMCA 4 25 Noise Characteristics 4 26 4 2 September 1979 ...

Page 98: ...BS Maximum Demonstrated Crosswind Component 22 kts Takeoff Lift off 86 kts 50 ft Speed 94 kts Two Engine Best Angle of Climb Vx 86 kts Two Engine Best Rate of Climb Vy 104 kts Cruise Climb 139 kts Turbulent Air Penetration 156 kts Landing Approach Flaps ON 96 kts Balked Landing Climb 96 kts Intentional One Engine Inoperative Speed VSSE 86 kts Air Minimum Control Speed VMCA 81 kts Revised March 198...

Page 99: ...1 COCKPIT a Control Lock REMOVE AN D STOW b Parking Brake SET c All Switches OFF d Trim Tabs SET TO ZERO 2 RIGHT FUSELAGE a Load Distribution CHECK AND SECURED b Utility Door SECURE c Static Port UNOBSTRUCTED d Emergency Locator Transmitter ARMED 3 EMPENNAGE a Control Surfaces Tabs and Deice Boots CHECK CONDITION SECURITY AND ATTACHMENT b Tail Cone Tail Light and Rudder Beacon CHECK c Tie Down REM...

Page 100: ...UTRAL 6 LEFT WING LEADING EDGE a Lights and Deice Boot CHECK FOR CONDITION b Stall Warning Vane CHECK FREEDOM OF MOVEMENT c Fuel CHECK QUANTITY AND CAP S SECURE AL WAYS CHECK WING TIP TANK FIRST IF IN STALLED DO NOT REMOVE INBOARD CAP IF FUEL IS VISIBLE IN TIP TANK d Wing Tip Tank if installed Sump DRAIN e Fuel Sight Gage CHECK f Tie Down Chocks REMOVE g Engine ou CHECK QUANTITY CAP AND DOOR SECUR...

Page 101: ...Section IV Normal Procedures BEECHCRAFT Baron 58 Serial TH 773 and After 4 48 INTENTIONALLV LEFT BLANK August 1984 ...

Page 102: ... Oxygen CHECK f Baggage Door SECURE 8 RIGHT WING LEADING EDGE a Wheel Well Doors Tire Brake Line and Shock Strut CHECK b Landing Gear Uplock Roller CHECK c Cowl Flap CHECK d Fuel Drains DRAIN e Engine Oil CHECK QUANTITY CAP AND DOOR SECURE f Engine Cowling and Doors CHECK CONDITION AND SECURITY g Landing Ught if installed CHECK h Propeller EXAMINE FOR NICKS SECURITY AND OIL LEAKS i Engine Air Inta...

Page 103: ... CHECK c Fuel Sump Aft of Wheel Well DRAIN d Flaps CHECK GENERAL CONDITION NOTE Check operation of lights if night flight is anticipated CAUTION DO NOT TAXI WITH A FLAT SHOCK STRUT BEFORE STARTING 1 Seats POSITION AND LOCK SEAT BACKS UPRIGHT 2 Seat Belts and Shoulder Harnesses FASTEN 3 Parking Brakes SET 4 All Avionics OFF 5 Oxygen CHECK QUANTITY AND OPERATION 6 Landing Gear Handle DOWN 7 Cowl Fla...

Page 104: ...ity Indicators CHECK QUANTITY See LIMITATIONS for take off fuel 12 Landing Gear Position Lights CHECK STARTING 1 Throttle Position APPROXIMATELY 1 2 IN OPEN 2 Propeller Control LOW PITCH high rpm 3 Mixture Control FULL RICH NOTE If the engine is hot and the ambient tempera ture is 90 F or above place mixture control in IDLE CUT OFF switch aux fuel pump to HIGH for 30 to 60 seconds then OFF Return ...

Page 105: ...rime con dition place mixture control in IDLE CUT OFF and open the throttle operate the starter to remove excess fuel As engine starts reduce the throttle to idle rpm and place the mixture control in FULL RICH 6 Warm up 1000 to 1200 RPM 7 Oi I Pressure 25 PSI WITHIN 30 SECONDS 8 External Power if used DISCONNECT WARNING When using external power start the right en gi ne fi rst si nce the externa I...

Page 106: ...on and the indication shows no signs of decreasing an electrical malfunction is indicated The battery master and both alter I nator switches should be placed in the OFF position Do not take off CAUTION Low voltage high ammeter or loadmeter readings dimming of lights or excessive noise in radio receivers could be indications that problems are developing in the starter system A noted change in such ...

Page 107: ...TING AND TAXI BEECHCRAFT Baron 58 serial TH 773 and After I CAUTION Do not operate engine above 1200 RPM until oil temperature reaches 75 F 1 Brakes RELEASE AND CHECK 2 Avionics ON AS REQUIRED 3 Exterior Lights AS REQUIRED Revised March 1983 ...

Page 108: ...the control lever aft past the detent Todo so will allow the propeller to change rapidly to the full feathered position imposing high stresses on the blade shank and engine 8 Starter Energized Warning Light if installed CHECK should be illuminated during start and extinguished after start If light is not installed or is inoperative check loadmeters for proper indication 9 Throttles 1700 RPM 10 Mag...

Page 109: ...speed ACCELERATE TO AND MAINTAIN RECOM MENDED SPEED 3 Landing Gear RETRACT when positive rate of climb is established 4 Airspeed ESTABLISH DESIRED CLIMB SPEED when clear of obstacles MAXIMUM PERFORMANCE CLIMB TH 773thru TH 1089 1 Power SET MAXIMUM CONTINUOUS POWER 2 Mixtures LEAN TO APPROPRIATE FUEL FLOW 3 Cowl Flaps OPEN 4 Airspeed ESTABLISH 104 KTS CRUISE CLIMB 1 Power SET 25 0 in Hg or Full Thr...

Page 110: ...ended Cruise Power 21 0 in Hg at 2300 rpm Economy Cruise Power 20 5 in Hg at 2100 rpm 1 Power SET AS DESIRED Use Tables in PERFORM ANCE section 2 Fuel Flow LEAN AS REQUIRED 3 Cowl Flaps AS REQUIRED LEANING USING THE EXHAUST GAS TEMPERATURE INDICATOR EGT The system consists of a thermocouple type exhaust gas temperature EGT probe mounted in the right side of each exhaust system This probe is connec...

Page 111: ...Section IV Normal Procedures BEECHCRAFT Baron 58 Serial TH 773 and After 4 108 INTENTIONALLY LEFT BLANK September 1979 ...

Page 112: ...ow peak on the rich side of peak b BEST POWER MIXTURE Increase the mixture until the EGT shows a drop of 100 F below peak on the rich side of peak CAUTION Do not continue to lean mixture beyond that necessary to establish peak temperature 2 Continuous operation is recommended at 25 F or more below peak EGT only on the rich side of peak 3 Changes in altitude and power settings require the peak EGT ...

Page 113: ... LANDING 1 Seat Belts and Shoulder Harnesses FASTENED SEAT BACKS UPRIGHT 2 Fuel Selector Valves CHECK ON 3 Aux Fuel Pumps OFF OR LOW AS PER AMBIENT TEMPERATURE 4 Cowl Flaps AS REQUIRED 5 Mixture Controls FULL RICH or as required by field elevation 6 Flaps APPROACH 15 POSITION Maximum extension speed 152 kts 7 Landing Gear DOWN Gear extension speed 152 kts 8 Flaps FULL DOWN 30 Maximum extension spe...

Page 114: ...ers HIGH RPM 3 Throttles 1000 RPM 4 Aux Fuel Pumps OFF 5 Electrical and Avionics Equipment OFF 6 Mixture Controls IDLE CUT OFF 7 Magneto Start Switches OFF AFTER ENGINES STOP 8 Battery and Alternator Switches OFF 9 Controls LOCKED 10 If airplane is to be parked for an extended period of time install wheel chocks and release the parking brake as greatly varying ambient temperatures may build ex ces...

Page 115: ...l system EXAMPLE People 5 Gage Pressure 1500 psi Percent Capacity from chart 80 Cyli nder Capacity full 49 cu ft Altitude planned flight 15 000 feet Duration full cylinder 149 minutes Duration 80 full 119 minutes OXYGEN DURA TION Oxygen duration is computed for a Scott Altitude Com pensated System assuming 90 of cylinder volume usable and using Scott oxygen masks rated at 3 0 Standard Liters Per M...

Page 116: ... en en w g 1000 w 500 o 25 50 75 100 PERCENT OF USABLE CAPACITY Duration in minutes at the following altitudes August 1984 Persons Using J U CD CD 1 2 3 4 5 6 1 2 3 4 5 6 12 500 15 000 20 000 1014 746 507 507 373 253 338 248 169 253 186 126 202 149 101 169 124 84 1344 988 672 672 494 336 448 329 224 336 247 168 268 197 134 224 164 112 4 15 ...

Page 117: ...serted into the oxygen coupling AFTER USING 1 Discontinue use by unplugging mask from outlet NOTE Closing the control valve while in flight is not necessary due to automatic sealing of the out let when the mask is unplugged 2 Oxygen Control Valve CLOSE may be accomplished during shut down ELECTRIC ELEVATOR TRIM 1 ON OFF switch ON 2 Control Wheel Trim Switch Forward for nose down aft for nose up wh...

Page 118: ...onditions for accumulating moisture in the fuel tanks are most favorable at low temperatures due to the conden sation increase and the moisture that enters as the system is serviced Therefore close attention to draining the fuel system will assume particular importance during cold weather ENGINES Use engine oil in accordance with Consumable Materials in the SERVICING section Always pull the propel...

Page 119: ...re drops after a few minutes of ground operation shut down and check for broken oil lines oil cooler leaks or the possibility of congealed oil NOTE It is advisable to use external power for starting in cold weather During warm up watch engine temperatures closely since it is quite possible to exceed the cylinder head temperature limit in trying to bring up the oil temperature Exercise the propelle...

Page 120: ...e and the negative lead of the auxiliary power unit to the negative terminal of the external power re ceptacle A positive voltage must also be applied to the small guide pin 2 To prevent arcing make certain no power is being sup plied when the connection is made 3 Make certain that the battery switch is ON all avionics and electrical switches OFF and a battery is in the sys tem before connecting a...

Page 121: ...Auxiliary Power Unit ON 6 Right Engine START use normal start procedures 7 Auxiliary Power Unit OFF after engine has been started 8 Auxiliary Power Unit DISCONNECT before starting left engine 9 Alternator Switches ON TAXIING Avoid taxiing through water slush or muddy surfaces if possible In cold weather water slush or mud when splashed onto landing gear mechanisms or control surface hinges may fre...

Page 122: ...ved heated fuel vents 8 Beech approved windshield defogging and openable storm window 9 Beech approved alternate induction air 10 Beech approved external antenna masts capable of withstanding ice loads WARNING Stalling airspeeds should be expected to increase due to the distortion of the wing airfoil when ice has accumulated on the airplane For the same reason stall warning devices are not accurat...

Page 123: ...e Switch AUTO UP 2 Deice Pressure 9 to 20 PSI while boots are in flating 3 Repeat AS REQUIRED CAUTION Rapid cycles in succession or cycling before at least 1 2 inch of ice has accumulated may cause the ice to grow outside the contour of the in flated boots and prevent ice removal Stall speeds are increased 4 kts in all config urations with surface deice system operating NOTE Either engine will sup...

Page 124: ...CK 7 to 2 amps 2 Blade 14 to 18 amps 3 Blade b IN FLIGHT 1 Propeller Deice Switch ON The system may be operated continuously in flight and will func tion automatically until the switch is turned OFF 2 Relieve propeller imbalance due to ice by in creasing rpm briefly and returning to the desired setting Repeat as necessary CAUTION If the propeller deice ammeter indicates ab normal reading refer to ...

Page 125: ...Section IV Normal Procedures BEECHCRAFT Baron 58 Serial TH 773 and After 4 228 INTENTIONALLY LEFT BLANK September 1979 ...

Page 126: ...meter 2 Windshield CHECK feel for warming CAUTION Ground operation is limited to 10 minutes b IN FLIGHT NOTE Continuous operation is permitted 1 WSHLD Heat Switch AS REQUIRED Heat should be applied before ice forms NOTE If directional gyro is to be reset turn off the electrothermal windshield heat for 15 seconds to allow a stable reading of the standby compass September 1979 4 23 ...

Page 127: ...ng and lines for obstructions 3 Check propeller boots for damage b IN FLIGHT 1 Prop Anti ice Switch ON 2 Windshield Anti ice Switch CYCLE AS RE QUIRED 3 Anti ice Quantity Indicator MONITOR NOTE See SYSTEM description for endurance 6 PilOT HEAT AND HEATED STALL WARNING a Pitot Heat Switch es ON Note deflection on Load meter Heated Stall Warning is activated by the left pitot heat switch NOTE Switch...

Page 128: ...INFORMATION Refer to Systems section PRACTICE DEMONSTRATION OF VMCA VMCA demonstration may be required for multi engine pilot certification The following procedure shall be used at a safe altitude of at least 5000 feet above the ground in clear air only WARNING Inflight engine cuts below Vsse speed of 86 kts 99 mph are prohibited 1 Landing Gear UP 2 Flaps UP 3 Airspeed ABOVE 86 KNOTS 99 MPH Vsse 4...

Page 129: ... buffet or stall warning horn sound immediately initiate recovery reduce power to idle on the operative engine and immediately lower the nose to regain VSSE NOISE CHARACTERISTICS Approach to and departure from an airport should be made so as to avoid prolonged flight at low altitude near noise sensitive areas Avoidance of noise sensitive areas if practical is preferable to overflight at relatively...

Page 130: ... his duty to see and avoid other airplanes Flyover noise levels established in compliance with FAR 36 are For Serials TH 1090 and After 2 Blade Propeller Using MNOP 78 9 dB A I 3 Blade Propeller Using MNOP 78 8 dB A NOTE Flyover noise levels given are not applicable for Serials TH 773 thru TH 10a9 No determination has been made by the Federal Aviation Administration that the noise level of this ai...

Page 131: ...on Normal System 5 15 Airspeed Calibration Alternate System 5 16 Altimeter Correction Alternate System 5 17 Fahrenheit to Celsius 5 18 ISA Conversion 5 19 Manifold Pressure vs RPM 5 20 Take Off Weight 5 21 Stall Speeds Power Idle 5 22 Wind Components 5 23 Take Off Distance 5 24 Accelerate Stop 5 25 Accelerate Go 5 26 Climb Two Engine TH 773 thru TH 1089 5 26A Climb Two Engine TH 1090 and After 2 b...

Page 132: ... 33 Cruise Power Settings 5 34 5 37 Maximum Cruise Power 5 34 Recommended Cruise Power 5 35 Recommended Cruise Power 5 36 Economy Cruise Power 5 37 Range Profile 136 Gallons 5 38 Endurance Profile 136 Gallons 5 39 Range Profile 166 Gallons 5 40 Endurance Profile 166 Gallons 5 41 Range Profile 194 Gallons 5 42 Endurance Profile 194 Gallons 5 43 Holding Time 5 44 Time Fuel and Distance to Descend 5 ...

Page 133: ...temperature FAA approved performance information is included in this section Examples are presented on all performance graphs In addition the calculations for flight time block speed and fuel required are presented using the conditions listed Performance with a gross weight of 4990 Ibs Baron 58A will be equal to or betterthan that of the higher gross weight Baron 58 CONDITIONS At Denver Outside Ai...

Page 134: ...CE Enroute Low Altitude Chart L 6 At Amarillo Outside Air Temperature 25 C 77 F Field Elevation 3605 ft Altimeter Setting 29 56 in Hg Wi nd 180 at 1a kts Runway 21 Length 10 000 ft To determine pressure altitude at origin and destination airports add 100 feet to field elevation for each 1 in Hg below 29 92 and subtract 100 feet from field elevation for each 1 in Hg above 29 92 Pressure Altitude at...

Page 135: ...ght 5400 Ibs Ramp Weight 5400 24 5424 Ibs NOTE Fuel for start taxi and take off is normally 24 pounds Enter the Take Off Weight graph at 5650 feet pressure altitude and 15 C The take off weight to achieve a positive rate of c1imb at lift off for one engine inoperative is Take off Weight 4850 pounds Enter the Take Off Distance graph at 15 C 5650 feet pres sure altitude 5400 pounds and 9 5 knots hea...

Page 136: ...be coming airborne the accelerate stop pro cedure must be performed The following example assumes the airplane is loaded so that the take off weight is 4850 pounds Although not required by regulations information has been presented to determine the take off weight field require ments and take off flight path assuming an engine failure occurs during the take off procedure The following illustrates ...

Page 137: ...feet of horizontal distance NOTE The Climb Gradient One Engine Inoperative graph assumes zero wind conditions Climbing into a headwind will result in higher angles of climb and hence better obstacle clearance capabilities Calculation of horizontal distance to clear an obstacle 90 feet above the runway surface Horizontal distance used to climb from 50 feet to 90 feet 90 50 1000 21 1905 feet Total D...

Page 138: ...The following calculations provide information for the flight planning procedure All examples are presented on the performance graphs A take off weight of 5400 pounds has been assumed Enter the Time Fuel and Distance to Climb graph at 15 C to 5650 feet and to 5400 pounds Also enter at 5 C to 11 500 feet and to 5400 pounds Read Time to Climb 22 7 15 min Fuel Used to Climb 12 7 4 7 8 gal Distance Tr...

Page 139: ...cruise power while enroute Enter the graph for ISA conversion at 11 500 feet and the temperature for the route segment DEN PUB OAT 5 C ISA Condition ISA 3 C PUB TBE OAT O C ISA Condition ISA 8 C TBE DHT OAT goC ISA Condition ISA 17 C DHT AMA OAT 1QoC ISA Condition ISA 18 C Enter the table for recommended cruise power 24 in Hg 2300 rpm at 10 000 ft 12 000 ft ISA and ISA 20 C TEMPERATURE ISA ISA 200...

Page 140: ...BE DHT 18 9 11 5 185 DHT AMA 189 11 4 185 NOTE The preceding are exact values forthe assumed conditions Enter the graph for Descent at 11 500 feet to the descent line and enter again at 3965 feet to the descent line and read Time to Descend 23 8 15 min Fuel Used to Descend 9 7 3 3 6 4 gal Descent Distance 72 25 47 NM Time and fuel used were calculated at Recommended Cruise Power 24 in Hg 2300 RPM ...

Page 141: ...N COS 17 215 05 1 9 COS PUB 40 213 11 4 4 PUB TBE 74 171 26 10 0 TBE DHT 87 173 30 11 6 DHT AMA 18 176 06 2 3 Distance required to climb or descend has been sub tracted from segment distance TIME FUEL DISTANCE TIME FUEL DISTANCE ITEM HRS MINS GAL NM Start Runup Taxi and Take off 0 00 4 0 0 Climb 0 15 8 0 38 Cruise 1 18 30 2 236 Descent 0 15 6 4 47 Total 1 48 48 6 321 October 1976 5 11 ...

Page 142: ...r Total Fuel Flow 20 6 gal hr 124 Ib hr Reserve Fuel 45 min 124 Ib hr 93 Ibs 15 5 gal Total Fuel 48 6 15 5 64 1 gallons The estimated landing weight is determined by subtracting the fuel required for the flight from the ramp weight Assumed ramp weight 5424 Ibs Estimated fuel from DEN to AMA 64 1 gal 385 Ibs Estimated landing weight 5424 385 5039 Ibs Examples have been provided on the performance g...

Page 143: ... presents the order in which the graphs should normally be used i e if the first item in the example is OAT then enter the graph at the known OAT 2 The reference lines indicate where to begin following guide tines Always project to the reference line first then follow the guide lines to the next known item 3 Indicated airspeeds lAS were obtained by using the Airspeed Calibration Normal System 4 Th...

Page 144: ... l FLAPS UP l l 190 190 n CD 180 180 170 170 f f f f 160 160 150 150 85 140 140 a a i 130 i 130 0 fiJ w tD 120 120 a a C m CD m 110 110 0 u u J 100 100 10 u u J o 0 90 90 J n 80 80 0 W I C l tD CD 70 70 l l c 60 60 J O CD 70 80 90 100 110 120 130 140 150 160 170 180 190 200 _ l 60 70 80 90 100 110 120 130 U 1 en lAS INOICATED AIRSPEED KNDTS lAS INDICATED AIRSPEED KNOTS Q ...

Page 145: ...RSPEED KNOTS 50 lAS FLAPS INDICATED PRESSURE ALTITUDE ALTIMETER CORRECTION ACTUAL PRESSURE ALTITUDE EXAMPLE o 40 W w 30 woO u z t 20 z O o 8 10 u 0 o o a 0 10 W a tu u 5 t c 20 0 j m u 41 FLAPS UP 70 80 90 100 110 120 130 140 150 160 170 180 190 200 lAS INDICATED AIRSPEED KNOTS 30 40 50 w 0 0 a t u tJ i 0 a W lii u i5 NOTE INDICATED ALTITUDE AND INDiCATED AIRSPEED ASSUME ZERO INSTRUMENT ERROR en e...

Page 146: ...z 160 I 150 0 0 150 140 Q J 140 130 130 0 al w 120 l m CDm J in 120 Ci 110 n w 110 100 In 0 s D 100 90 n w TI 0 W I 90 80 tT z DIal CD a 80 w 70 I DI J a 80 90 100 110 120 130 140 150 160 170 180 190 200 70 80 90 100 110 120 130 140 150 0CD 1 NORMAL SYSTEM INDICATED AIRSPEEO KNOTS NORMAL SYSTEM INDICATED AIRSPEED KNOTS en m 9lal ...

Page 147: ...iwO a 300 a to llililllliillillIElill 400 95 0 0 n 0 0 1 CD en 100 a0 s 0 w0 w 100 I z 0 g 0 0 200 a z 0 u 2 a 0 w a tJ 300 a OJ 400 01 80 90 100 110 120 130 140 150 160 170 18D 190 200 ALTERNATE SYSTEM INDICATED AIRSPEED KNOTS 500 I I I I I I I I I I 70 80 90 100 0 120 130 140 ISO 160 ALTERNATE SYSTEM INDICATED AIRSPEED KNOTS rnO 1 m m to 4 E E O u w III 4 l 0 e G 0 l 1 01 co tJ 1 rn o 1 n 3 e II...

Page 148: ...3 g lJJ cnm CDm o I to I a W t IlIlJJ III a 0 CD UI 00 1 1 11 rrt J lh 1 1 til II ll f H I H tt t t t t j H ffii Illrl 1 j r l l t f rr i 1i1 _ r i d t r r r lt TEMPERATURE CONVERSION oC vs of 1 S5g j o 10 40 50 30 20 1 _ _ TlJ l rr tr 40 l _ p 10 60 30 50 20 UII 00 o n g l r CD CD c ...

Page 149: ...erial TH 773 and After Section V Performance R o I fi I o i R H t J H l 0 w a 4 J I I 1 j 4 0 c a w i f l H I t l bj F L3H 30n LI L 3llnSS311d i t Jf 4 H l tf tt t t JH tH t 1 tf tt t H t f z o Vi al Z o u October 1976 5 19 ...

Page 150: ...ormance BEECHCRAFT Baron 58 Serial TH 773 and After 0 0 0 N 0 0 I l N 0 0 E N a a III 0 0 M W N a 0 a 0 I 0 w I 0 W N a W N en a w a z C 0 a z 0 w 0 N u Z ct 8 E 0 N 8 0 0 DH NI 3HnSS3Hd OlO lINVVII 5 20 October 1976 ...

Page 151: ...nce ASSOCIATED CONDITIONS EXAMPLE AIRPLANE POWER FLAPS LANDING GEAR INOPERATIVE PROPELLER 13000 12000 11000 10000 I w 9000 8000 J 7000 6000 J J ffl 5000 a Q 4000 3000 2000 1000 AIRBORNE TAKE OFF UP DOWN FEATHERED PRESSURE ALTITUDE OAT TAKE OFF WEIGHT 5650 FEET 15 C 4850 SL 3000 3500 4000 4500 5000 5500 October 1976 WEIGHT rv POUNDS 5 21 ...

Page 152: ...K STALL SPEED 70 60 110 120 100 s z 90 o 80 50 I I I I I I I 3000 0 10 20 30 40 50 60 ANGLE OF BANK tv DEGREES STAll SPEEDS POWER IDLE 5000 4500 4000 3500 WEIGHT POUNDS NOTES 1 THE MAXIMUM ALTITUDE LOSS EXPERIENCED WHILE CONDUCTING STALLS IN ACCORDANCE WITH CAM 3120 WAS 350 FT 2 A NORMAL STALL RECOVERY TECHNIQUE MAY BE USED en N N o e o a CD CD en ...

Page 153: ... COMPONENTS Demonstrated CrosswindComponent is 22 kts EXAMPLE WIND SPEED ANGLE BETWEEN WIND DIRECTION AND FLIGHT PATH HEADWIND COMPONENT CROSSWIND COMPONENT FLIGHT PATH 30 10 e 1 8 Q Z i 0 w I 10 20KTs 500 13KTs 15 KTs 20 o 10 20 CROSSWIND COMPONENTS 40 October 1976 5 23 ...

Page 154: ...NOTS 0 GROUND ROLL 900 FEET 3 I III TOTAL OISTANCE OVER I 50 FT OBSTACLE 3090 FEET n TAKE OFF SPEED AT CD LIFT OFF B6 KTS 50 FT 94 KTS 6000 4ObO 0 0 20 30 0 WIND COMPONENT OBSTACLE HEIGHT KNOTS FEET 5000 4500 WEIGHT POUNDS TAKE OFF SPEEDS ALL WEIGHTS LIFT OFF B6 KNOTS 50 FEET 94 KNOTS r il ASSOCIATED CONDITION POWER TAKE OFF POWER MIXTURE LEAN TO APPROPRIATE FUEL FLOW FLAPS uP LANOING GEAR RETRACT...

Page 155: ...RATE STOP DiSTANCE DECISION SPEED liAS EXAMPLE OAT PRESSURE ALTITUDE TAKE OFF WEIGHT HEADWIND 2000 I I I 4000 0 10 20 30 WIND COMPONENT KNOTS t Eff l fillIlll UlUB 7000 t o z o w W Q Ul Z o in U w o w t a w J W U w U Z 15 4500 5000 40 30 20 10 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURE C ASSOCIATED CONDITIONS POWER 1 TAKE OFF POWER 2 ENGINE IDLE AT DECISION SPEED FLAPS UP COWL FLAPS OPEN 0 1 I N 0 1...

Page 156: ...OBSTAClE HEIGHT KNOTS FEET TAKE OFF SPEEDS ALL WEIGHTS Lin OFF 86 KNOTS 50 FEET 94 KNOTS ACCELERATE GO DISTANCE TAKE OFF POWER UP RETRACT AnER L1n OFF PAVED LEVEL DRY SURFACE ASSOCIATED CONDITIONS FLAPS LANDING GEAR RUNWAY POWER NOTES 1 DISTANCES ASSUME AN ENGINE FAILURE AT LIFT OFF AND PROPELLER IMMEDIATELY FEATHERED 2 WEIGHTS IN SHADED MAY NOT PROVIDE ONE ENGINE INOPERATIVE CLlMB_ REFER TO TAKE ...

Page 157: ...4 15C C 11500 FEET 5352 LBS 25 o 2000 L 20 1500 15 w Ci 10 l u 5 500 RATE OF CLIMB CUMB GRADIENT EXAMPLE OAT PRESSURE ALTITUDE WEIGHT oI 4000 5000 4500 WEIGHT POUNDS 50 CLIMB TWO ENGINE TH 773 thru TH 1089 CLIMB SPEED 104 KNOTS ALL WEIGHTS MAXIMUM CONTINUOUS UP UP OPEN LEAN TO APPROPRIATE FUEL FLOW POWER FLAPS LANDING GEAR COWL FLAPS MIXTURE to t o c n N O l C lit 3 15 ...

Page 158: ...l 0 0 C1I ClO 0 1 I I o _ 0 3 18 16 14 12 10 8 15 6 a o lD 2 d WC 11 500 FT 5352 LBS 500 1000 4000 EXAMPLE RATE OF CLIMB 500 FTlMIN CLIMB GRADIENT 4 2500 2000 OAT PRESSURE ALTITUDE WEIGHT 1 5000 4500 WEIGHT POUNDS L a R r 60 i FULL THROTTLE AT 2550 RPM UP UP OPEN LEAN TO APPROPRIATE FUEL FLOW ASSOCIATED CONDITIONS POWER FLAPS LANDING GEAR COWL FLAPS MIXTURE CQ u l C1I N al l Xl g 3 e I ...

Page 159: ...0 I I g WC 11 500 FT 5352 LBS 535 FT MIN 4 2 18 z 14 12 I I 10 is 8 f i o D 6 J U 2000 500 1000 1500 4000 4S00 EXAMPLE OAT PRESSUREALTITUOE WEIGHT RATE OF CLIMB CLIMB GRADIENT 2500 5000 10 20 30 40 50 60 FULL THROTILE AT 2650 RPM UP UP OPEN LEAN TO APPROPRIATE FUEL FLOW ASSOCIATED CONDITIONS POWER FLAPS LANDING GEAR COWL FLAPS MIXTURE 0 1 iii 1 Q CD CO W Y l N s III o ...

Page 160: ... UP UP FEATHERED CLIMB SPEED ALL WEIGHTSI 94 KTS 40 30 20 10 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURE oC EXAMPLE OAT PRESSURE ALTllUDE WEIGHT GRADIENT OF CLIMB CLIMB SPEED 6 4 F z w is a o III 0 u 1 2 3 4 I 1 I I I 5000 4500 4000 WEIGHT POUNOS 15 C 5650 FT 4850 LBS 2 1 94 KTS ftn 1 o 0 3 j n CD co tnm CD m o t 40 t a T 4 III coj III c 0 j r Jl co ...

Page 161: ...IME TO CLIMB FUEL TO CLIMB DISTANCE TO CLIMB I I 1 I I I I I I o 10 20 30 40 50 60 70 80 DISTANCE TO CUMBrvN M I1III1111 TTrTTl II I o 2 4 6 8 10 12 14 16 FUEL TO CLIMB GALS t t l L CLIMB SPEED 139 KNOTS 50 40 30 20 10 0 0 20 30 40 50 0 10 20 30 OUTSIDE AlA TEMPERATUAE oC TIME TO CUMBrvM1NUTES t t TIME FUEL AND DISTANCE TO CLIMB ASSOCIATED CONDITIONS POWER 25 IN HG OR FULL THROTIlE 2500 RPM FUEL D...

Page 162: ...FT 3 J LANDING GEAR UP WEIGHT 4850 LBS INOPERATIVE PROPELLER FEATHERED COWL FLAPS OPEN RATE OF CLIMB 200 FPM e MIXTURE LEAN TO APPROPRIATE CLIMB GRADIENT 2 CD FUEL FLOW 1 10 i fI 5 2 f Z til w 15 mm l CD m 0 0 0 o o I to J 0 u I J I oJ oJ 0 w t C 5 II til CD J II 1000 0 0 co 60 50 40 30 20 10 0 10 20 30 40 50 5000 4500 4000 t J oJ OUTSIDE AIR TEMPERATURE oC WEIGHT POUNDS CD UI J Xl ...

Page 163: ...APS MAXIMUM CONTINUOUS UP FEATHERED UP EXAMPLE QAT 15 C WEIGHT 4850 SERVICE CEILING 8425 FT 14000 12000 10000 Iii w LL 8000 Cl z W u w 6000 u a w Vl 4000 2000 NOK SERVICE CEIUNG IS THE PRESSURE ALTITUDE WHERE AIRPLANE HAS CAPABILITY OF CLIMBING 50 FT MINUTE WITH ONE PROPELLER FEATHERED 60 50 40 30 20 10 0 10 20 30 40 50 60 OUTSIDE AIR TEMPERATURE oc October 1976 5 31 ...

Page 164: ...ONS AVERAGE CRUISE WEIGHT 5000 LBS TEMPERATURE STANDARD DAY ISA EXAMPLE PRESSURE ALTITUDE 11500 FEET POWER SETIING FULL THROTILE 2300 RPM TRUE AIRSPEED 185 KNOTS 210 200 160 170 180 190 TRUE AIRSPEED KNOTS 150 2000 14000 1 6 0 0 0 _ 4000 12000 t looo0 2 w Cl 8000 c w a en 6000 a Q 5 32 October 1976 ...

Page 165: ...R EXAMPLE FUEL FLOW ENGINE 11 7 GALJHR CONDITIONS LEVEL FLIGHT CRUISE LEAN BRAKE HORSEPOWER 160 HP PER ENGINE 25 2 23 22 21 20 19 a 8 J 17 I w 16 z a 15 5 a s 13 w i2 12 11 0 5_ 0 120 130 140 150 160 170 180 190 200 210 220 230 240 250 260 270 280 290 BRAKEHOASEPOWER lENGINE september 1980 5 33 ...

Page 166: ...RESS ENGINE ITASI CAS RPM liN HGlpPHIGPHIKTSIKTS ISA 36 oF 1 20 oCI ENGINEI MAN I I I I I I IENGINEI MAN I I OAT I SPEED PRESS ENGINE TAS CAS OAT SPEED PRESS ENGINE ITASI CAS Floc I RPM liN HGlpPHIGPHIKTSIKTSlioFlocl RPM liN HGlpPHIGPHIKTSIKTS o n o C CD CO Q NOTES 1 FULL THROTTLE MANIFOLO PRESSURE SETTINGS ARE APPROXIMATE 2 SHADED AREA REPRESENTS OPERATION WITH FULL THROTTLE lU tnm CDm o I 1 I xI...

Page 167: ... PRESS ALT I OAT FEET I of I c I RPM CRUISE POWER SETTINGS CRUISE POWER SETTINGS RECOMMENDED CRUISE POWER 24 0 IN HG 2300 RPM OR FULL THROTTLE S200 LBS STANDARD DAY USA ENGINEIMAN I FUEL OAT I SPEED PRESS gl ITASlcASIl OAT Floc I RPM liN HG IpPHIGPHIKTSIKTS cnal m l m O 4 1 1 0 I XJ I J aI Q 1ll ISA 36 oF 20 0C I 0 J t UI TAsl CAS I CO tl cn o 3 III 0 J J ...

Page 168: ...0 3 J 111 J n CD NOTES 1 FULL THROTTLE MANIFOLD PRESSURE SETTINGS ARE APPROXIMATE 2 SHADED AREA REPRESENTS OPERATION WITH FULL THROTTLE I PRESS ALT I OAT FEET 1 F I c OAT Floc ENGINEIMAN O I SPEED PRESS ENGINE ITASI CAS RPM liN HGlpPHIGPHIKTSIKTS ENGINEIMAN I ci 1 OAT I SPEED PRESS ENGINE ITASlcAS Floc I RPM lIN HGlpPHIGPHIKTSIKTS lJI cnm CDm C E C E JJ w IIIlJ1 J III 0 0 J CJl l co ...

Page 169: ...lJ CD l l o CD 3 eoIII 0 l l g ISA 36 F 20 oC ENGINEI MAN I I OAT SPEED PRESS ENGINE TAS CAS OF lOCI RPM RPM liN HGlpPHIGPHIKTSIKTS ENGINEIMAN I SPEED PRESS ENGINE ITAS CAS CRUISE POWER SETTINGS ECONOMY CRUISE POWER 20 5 IN HG Ciil2100 RPM OR FULL THROTTLE 5200 LBS ISA 36 F 20 C RPM liN HGlpPHIGPHIKTSIKTSlioFI c ENGINEI MAN j O I SPEED PRESS ENGINE TAS CASI OAT OAT OF I c FEET PRESS ALT o o cr CD ...

Page 170: ...I CLIMB AND DESCENT WITH 45 MINUTES RESERVEFUEL AT ECONOMY CRUISE EXAMPLE PRESSUREALTITUDE 11500 FEET POWER SETTING FULL THROTTLE 2300 RPM RANGE 870 NM oCt CD CD n o to 0 3 J g n CD 25000 20000 FT FULL THROTTLE 10000 RANGE NAUTICAL MILES ZERO WIND o n s0 CD CO en t w 2 15000 w II rJJ rJJ W II 0 5000 SL I 600 650 700 750 800 850 900 950 1000 1050 1100 lJJ Ct m CD m I n J In J J I I III lJJ J III 0 ...

Page 171: ...4 0 4 5 5 0 5 5 6 0 6 5 7 0 I 0 I ENDURANCE HOURS ZERO WIND CD NOTE ENDURANCE INCLUDES START TAXI CLIMB AND DESCENT WITH 45 MINUTES RESERVE FUEL AT ECONOMY CRUISE ENDURANCE PROFILE 136 GALLONS 5000 LBS AVIATION GASOLINE 6 0 LBSIGAL 136 U S GALS 816 LBSI ASSOCIATED CONDITIONS WEIGHT FUEL FUEL DENSITY INITIAL FUEL LOADING 25000 zoooo w 1 15000 c _ U CJ U z2 w 5000 0 a J w 3 z 0 c n sL IIlllllllllljl...

Page 172: ...XI CLIMB AND DESCENT WITH 45 MINUTES RESERVE FUEL AT ECONOMY CRUISE EXAMPLE PRESSUREALTITUDE POWER SETTING RANGE 1500 FEET FULL THROTILE 2300 RPM 1115 NM lJC CD CD L o _ 0 3 j III j n CD CD C m CD m o I 10 I a T1 W I III CD j III c 0 j 0 1 CO 1300 1250 FT FULL THROTTLE 1200 1150 1100 1050 1000 RANGE NAUTlCAL MILES ZERO MILES 950 900 850 25 _I W w 2 g 15000 I 5 w 0 10000 en n en w a 0 c D 5000 CD C...

Page 173: ...ll 8 5 8 0 ENDURANCE 6 0 HRS EXAMPLE PRESSUREALTITUDE 11500 FEET POWER SETTING FULL THROTTLE 2300 RPM 7 5 7 0 6 5 6 0 5 5 STANDARD DAY lSA 5 0 ENDURANCE HOURS ZERO WIND NOTE ENDURANCE INCLUDES START TAXI CLIMB AND DESCENT WITH 45 MINUTES RESERVEFUEL AT ECONOMY CRUiSE 4 5 4 0 3 5 5000 25000 20000 w 2 15000 c 10000 Ul Ul W cr c WEIGHT FUEL FUEL DENSITY INITIAL FUEL LOADING o a CT CD CD O l CJl ...

Page 174: ...ER SETTING RANGE 11500 FEET FULL THROTILE 2300 RPM 1325 NM cn CD CD a g 0 3 III n CD o n o C CD CD 0 U1111111111111111111 Lib111111111111111111111111111111111111111111111111111111IIIIIlllifFT FULL THROTILE 15000 3MmlllillIl 118H fI lOffl7l 10000 I 111111111111111111111 Wi flf W 1111111111111 r r lm CRU S TAS vKNOTS 1 0 wc 5000 UlCl t 199 gt 188 1175 a I f61 z 0 0 0 164 1 151 SL N 188 N 78 900 950 ...

Page 175: ...FEET FULL THROITLE 2300 RPM 7 15 HRS 7 HRS 9 MIN 10 0 9 5 EXAMPLE ENDURANCE PRESSURE AtTITUDE POWER SETTING 9 0 8 5 8 0 7 5 7 0 STANDARD DAY ISA 6 5 ENDURANCE HOURS ZEROWIND NOTE ENDURANCE INCLUDES START TAXI CLIMB AND DESCENT WITH 45 MINUTES RESERVE FUEL AT ECONOMY CRUISE 6 0 5 5 5 0 5000 tu w u 2 w o E i 0 l 10000 J en en w II a WEIGHT FUEL FUEL DENSITY INITIAL FUEL LOADING o o l r CD CD 0 C7I C...

Page 176: ...LDING TIME FUEL AVAILABLE FOR HOLDING PRESSURE ALTITUDE HOLDING TIME 400 LBS 5000 FT 31 HR OmCD CD n o 0 3 s I s n CD 10 9 8 en 7 a 0 I 6 2 w 5 o 4 z Ci 0 3 I 0 n 2 0 cr CD 0 CD 100 200 300 400 I FUEL REQUIREMENT POUNDS J 500 600 CD mm CD m o J I J J I I I W I I CD s I c g Jl l ClD ...

Page 177: ...S UP EXAMPLE INITIAL ALTITUDE FINAL ALTITUDE TIME TO DEScENO FUEL TO DESCEND DISTANCE TO DESCEND 500FT 3965 FT 123 8 5 MIN 19 7 3 31 6 4 GAL 172 25 47 NM DESCENTSPEEO 175 KNOTS 16000 15000 4000 13000 12000 000 I ll 0000 I w 9000 c J g 8000 w 7000 a J J J 6000 w a c 5000 4000 3000 2000 1000 SL 0 0 I I I i I 0 3 4 I I I I 0 to 20 3D October 1976 15 20 25 30 35 40 TIME TO DESCEND tv MINUTES t 5 45 ...

Page 178: ...Otn l l a g 0 3 J III J n l o 1000 I I I I I I I I I 70 60 50 40 30 20 10 0 10 20 30 40 50 OUTSIDE AIR TEMPERATURErvoC 500 500 lJJ tnm l m o ox 1 x W I III lJJ J III c 0 J P tn CD 10 oft I 5 l5 o o a 15 20 500 1000 I 500 a w o a 2000 I toOO 4000 5000 4500 wEIGHT rvPOUNDS P w Z J W u ALTITUDE FUEL FLOW ENGINE FEET j GALtHR SL i 24 1 2009 1122 3 4000J l20 9 196 8 18 4 1 17 2 12000 161 14000 15 4 E t...

Page 179: ...SPEED 91 KTS W III I 3500 ID Q 1lI 0 0 3000 ft CO 2500 ffi 2000 z V C 1500 4600 0 10 20 30 0 50 WIND COMPONENT OBSTACLE HEIGHT rv KNOTS rv FEET _ _ 500 5000 4500 WEIGHT rv POUNDS WEIGHT SPEED AT 50 FT POUNDS KNOTS 5400 96 500D 91 4600 B7 4DDD B1 LANDING DISTANCE 40 30 20 10 RETARDED TO MAINTAIN 800 FT lMIN ON FINAL APPROACH DOWN DOWN lAS AS TABULATED MAXIMUM PAVED LEVEL DRY SURFACE POWER FLAPS LAN...

Page 180: ...Section V Performance BEECHCRAFT Baron 58 Serial TH 773 and After 5 48 INTENTIONALLY LEFT BLANK October 1976 ...

Page 181: ...ance Record 6 7 Seating Baggage and Equipment Arrangements 6 9 Loading Instructions 6 10 Moment Limits vs Weight Table 6 11 6 13 Moment Limits vs Weight Graph 6 14 Computing Procedure 6 15 Sample Weight and Balance Loading Form 6 16 Weight and Balance Loading Form 6 17 Useful Load Weights and Moments 6 18 6 21 Occupants 6 18 Baggage 6 19 Cargo 6 20 Usable Fuel 6 21 Airplane Papers furnished with i...

Page 182: ...Section VI Wt and BaljEquip list BEECHCRAFTBaron58 Serial TH 773 and After 6 2 INTENTIONALLY LEFT BLANK October 1976 ...

Page 183: ...ation 81 6 The remainder ofthe unusable fuel to be added to a drained system is 30 3 pounds at Fuselage Station 78 5 3 Engine oil must be at the full level or completely drained Total engine oil when full is 45 pounds at Fuselage Station 43 4 To determine airplane configuration at time of weighing installed equipment is checked against the airplane equipment list or superseding forms All installed...

Page 184: ...imately at Fuselage Station 96 7 for rna n wheels and Fuselage Station 10 3 for the nose wheel 7 Jack point weighings are accomplished by placing scales at the jack points specified in step 1 above Since the center of gravity of the airplane is forward of Fuselage Station 83 1 the tail reaction of the airplane will be in an up direction This can be measured on regular scales by placing ballast of ...

Page 185: ...D 9 8 97 AFT 271 0 Signature REACTION SCALE NET WHEEL JACK POINTS READING TARE WEIGHT ARM MOMENT LEFT MAIN RIGHT MAIN NOSE OR TAIL TOTAL AS WEIGHED Space below provided for additions and subtractions to as weighed condition EMPTY WEIGHT DRY ENGINE OIL 45 1935 UNUSABLE FUEL 36 79 2844 BASIC EMPTY WEIGHT J aJ CD m m on t I xC 0 w m t J aJ Q m It 11 0 J CD J1 co E S J Co aJ I J JJ CD c ii o s Cit ...

Page 186: ...f doing this it is suggested that a running tally of equ ipment changes and their effect on empty weight and e g is a suitable means for meeting both requirements The current equipment list and empty weight and e g information must be retained with the airplane when it changes ownership Beech Aircraft Corporation cannot maintain this information the current status is known only to the owner If the...

Page 187: ...RTICLE ADDED OR REMOVED EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM lBS IN 1150 lBS 1 00 o n g SERIAL NO CD CD I m mI I WEIGHT AND BALANCE RECORD REGISTRATION NO PAGE NO Cf tD CD m m on 4J J n u I w I 4 s til l 0 s U1 CD I s e aJ C cn c CD c 2 0 0 r S iii ...

Page 188: ...CLE ADDED OR REMOVED H EMPTY WEIGHT IN OUT OR CHANGE WT ARM MOM WT MOM LBS liN 100 LBS 100 en co o n o 0 CD A to e n SERIAL NO WEIGHT AND BALANCE RECORD REGISTRATION NO PAGE NO 2 cn CD I n J e 0 0 CD J I c r C r e CD cnm CD m o 40 n J W t m CD s I c 0 s r C1I co ...

Page 189: ...ear spars where the floor structure load limit is 50 pounds per square foot MAXIMUM WEIGHT 300 POUNDS INCLUDING EQUIP MENT AND BAGGAGE 3 MAXIMUM WEIGHT 120 POUNDS INCLUDING EQUIP MENT AND BAGGAGE 8 MAXIMUM WEIGHT 400 POUNDS INCLUDING EQUIPMENT AND BAGGAGE l3 MAXIMUM WEIGHT 200 POUNDS FORWARD OF REAR SPAR INCLUDING EQUIPMENT AND CARGO WITH 3rd and 4th SEATS REMOVED ALL CARGO MUST BE SECURED WITH AP...

Page 190: ...e shown on the airplane Empty Weight and Balance form Useful load items which may be loaded into the airplane are shown on the Useful Load Weight and Moment tables The minimum and maximum moments are indicated on the Moment Limits vs Weight table These moments correspond to the forward and aft center of gravity flight limits for a particular weight All moments are divided by 100 to simplify comput...

Page 191: ...989 3500 2590 3010 3525 2609 3032 3550 2627 3053 3575 2646 3075 3600 2664 3096 3625 2683 3118 3650 2701 3139 3675 2720 3161 3700 2738 3182 3725 2757 3204 3750 2775 3225 3775 2794 3247 3800 2812 3268 3825 2831 3290 3850 2849 3311 3875 2868 3333 3900 2886 3354 3925 2905 3376 3950 2923 3397 3975 2942 3419 4000 2960 3440 4025 2979 3462 4050 2997 3483 4075 3016 3505 October 1976 6 11 ...

Page 192: ...3569 4175 3090 3591 4200 3108 3612 4225 3130 3634 4250 3152 3655 4275 3174 3677 4300 3196 3698 4325 3218 3720 4350 3240 3741 4375 3263 3763 4400 3285 3784 4425 3308 3806 4450 3330 3827 4475 3352 3849 4500 3374 3870 4525 3398 3892 4550 3420 3913 4575 3442 3935 4600 3465 3956 4625 3488 3978 4650 3510 3999 4675 3534 4021 4700 3556 4042 4725 3579 4064 4750 3602 4085 4775 3625 4107 6 12 October 1976 ...

Page 193: ...4150 4850 3694 4171 4875 3717 4193 4900 3740 4214 4925 3764 4236 4950 3786 4257 4975 3810 4279 4990 3824 4291 5000 3833 4300 5025 3856 4322 5050 3880 4343 5075 3904 4365 5100 3926 4386 5125 3950 4408 5150 3974 4429 5175 3998 4451 5200 4021 4472 5225 4045 4494 5250 4068 4515 5275 4092 4537 5300 4116 4558 5325 4140 4580 5350 4164 4601 5375 4188 4622 5400 4212 4644 October 1976 6 13 ...

Page 194: ...J OO JGIJO 3 00 76 ctr TER OF GRAVITY INCHES AFT O DATUM ENVELOPE BASED ON THE FOLLOWING WEIGHT I ND ctNTE R OF GRAVITY LIMI r DATA ILANDING GEAR DOWNI 6 14 WEIGH1 CONDITION 5400 LBs IMAXIMUM TAKE OFF OR LANDING I WEIGHT CONDITION 4990 LBS MAXIMUM TAKE OFF OR LANDINGl 4200LBS FOAWARo C G LIMIT 8ARON 5SA FORWARD CG LIMIT 860 October 1976 ...

Page 195: ...he Fuel to Zero Fuel Condition to obtain the SUB TOTAL Ramp Condition 5 Subtract the fuel to be used for start and taxi to arrive at the SUB TOTAL Take off Condition 6 Subtract the weight and moment of the fuel to be used from the take off weight and moment Determine the weight and moment of this fuel by subtracting the amount on board on landing from the amount on board on take off The Zero Fuel ...

Page 196: ...RONT SEAT OCCUPANTS 340 256 3 3rd and 4th SEAT OCCUPANTS FWD FACING 4 3rd and 4th SEAT OCCUPANTS AFT FACING 340 378 5 5th and 6th SEAT OCCUPANTS 170 258 6 NOSE BAGGAGE 61 9 7 AFT BAGGAGE S 8 CARGO 9 SUB TOTAL ZERO FUEL CONDITION 4428 3664 10 FUEL LOADING 166 GAL 996 824 11 SUB TOTAL RAMP CONDITION 5424 4488 12 LESS FUEL FOR START TAXI AND TAKE OFF 24 20 13 SUB TOTAL TAKE OFF CONDITION 5400 4468 14...

Page 197: ...AT OCCUPANTS FWD FACING 4 3rd and 4th SEAT OCCUPANTS AFT FACING 5 5th and 6th SEAT OCCUPANTS 6 NOSE BAGGAGE 7 AFT BAGGAGE 8 CARGO 9 SUB TOTAL ZERO FUEL CONDITION 10 FUEL LOADING 11 SUB TOTAL RAMP CONDITION 12 LESS FUEL FOR START TAXI AND TAKE OFF 13 SUB TOTAL TAKE OFF CONDITION 14 LESS FUEL TO DESTINATION 15 LANDING CONDITION Fuel for start taxi and take off is normally 24 Ibs at an average mom l0...

Page 198: ...20 111 115 152 110 82 90 126 132 122 126 167 120 90 98 138 144 133 138 182 130 98 106 150 156 144 150 198 140 105 114 161 168 155 161 212 150 112 123 172 180 166 172 228 160 120 131 184 192 178 184 243 170 128 139 196 204 188 196 258 180 135 148 207 216 200 207 274 190 142 156 218 228 210 218 288 200 150 164 230 240 222 230 304 NOTE OCCUPANT POSITIONS SHOWN ARE FOR THE SEATS ADJUSTED THE MAXIMUM R...

Page 199: ... Mom 100 Mom 100 10 2 15 18 20 3 30 36 30 5 45 54 40 6 60 72 50 8 75 90 60 9 90 108 70 11 105 126 80 12 120 144 90 14 135 162 100 15 150 180 110 17 165 198 120 18 180 216 130 20 195 140 21 210 150 23 225 160 24 240 170 26 255 180 27 270 190 29 285 200 30 300 220 33 330 240 37 360 260 39 390 280 42 420 300 45 450 320 480 340 510 360 540 380 570 400 600 October 1976 6 19 ...

Page 200: ...4 150 162 0 65 160 173 0 76 170 184 0 86 180 194 a 97 190 205 0 108 200 216 G1 2 3 4 5 6 7 8 9 10 CARGO AFT OF SPAR CENTER AFT SEATS REMOVED ARM 145 I Weight Moment Moment 100 Weight 100 10 15 150 218 20 29 160 232 30 44 170 247 40 58 180 261 50 73 190 276 60 87 200 290 70 102 210 305 80 116 220 319 90 131 230 334 100 145 240 348 110 160 250 363 120 174 260 377 130 189 270 392 140 203 280 406 6 20...

Page 201: ...166 GAL 194 GAL Gallons Weight Mom 100 10 60 46 46 46 20 120 92 92 92 30 180 140 140 140 40 240 189 189 189 50 300 238 238 238 60 360 288 288 288 70 420 338 338 338 80 480 388 388 388 90 540 439 439 439 100 600 489 489 489 110 660 539 539 539 120 720 590 590 590 130 780 641 641 641 136 816 671 140 840 692 692 150 900 743 743 160 960 793 793 166 996 824 170 1020 845 180 1080 899 190 1140 953 194 11...

Page 202: ...Section VI Wt and Bal Equip List BEECHCRAFT Baron 58 Serial TH 773 and After 6 22 INTENTIONALLY LEFT BLANK October 1976 ...

Page 203: ...levator Trim 7 6 Instrument Panel 7 6 Flight Instruments 7 6 Power Plant Instruments 7 7 Ground Control 7 7 Wing Flaps 7 7 Panel Illustration 7 8 7 9 Landing GearSystem 7 10 Control Switch 7 10 Position Indicators 7 10 Safety Switch 7 11 Warning Horn 7 11 Manual Extension 7 11 Brakes 7 12 Baggage Cargo Compartments 7 13 Aft Baggage Cargo Compartment 7 13 NoseBaggage Cargo Compartment 7 13 Seating ...

Page 204: ...8 Lubrication System 7 19 Cowl Flaps 7 19 Propellers 7 19 Hartzell Air Charged Propeller Domes 7 20 Propeller Synchronizer 7 20 Propeller Synchroscope 7 21 Fuel System 7 21 Fuel Flow and Pressure Indicator 7 22A Fuel Flow Indicator 7 228 Illustrations 7 22A 7 23 Fuel Crossfeed 7 27 Auxiliary Fuel Pumps 7 27 Fuel Off loading 7 27 Fuel Required for Flight 7 27 Electrical System 7 28 Battery 7 28 Sch...

Page 205: ...7 35 Heater Blower 7 35 Cabin Ventilation 7 35 Individual Fresh Air Outlets 7 36 Oxygen System 7 36 Pitot and Static System 7 37 Pitot System 7 37 Static System 7 37 Pressu re System 7 38 Stall Warning 7 39 Ice Protection Systems 7 40 Surface Deice System 7 40 Windshield Anti ice Electrothermal 7 40A Propeller and Windshield Anti ice System Fluid Flow 7 41 Electrothermal Propeller Deice 7 42 Pitot...

Page 206: ...Section VII Systems Description BEECHCRAFT Baron 58 Serial TH 773 and After 7 4 INTENTIONALLY LEFT BLANK October 1976 ...

Page 207: ... seat Pu11 the T handle latch at the back of the control arm and position the control wheel as desired Check for full freedom of move ment after repositioning the control NOTE If a reduced power throttle position exists when throwing over the control column it will be necessary to momentarily move the throttle levers forward for passage of the control column The optional dual control column is req...

Page 208: ... and a circuit breaker on the left sidewall The ON OFF switch must be in the ON position to operate the system The thumb switch is moved forward for nose down aft for nose up and when released returns to the center OFF position When the system is not being electrically actuated the manual trim control wheel may be used Incorporated in the system is an emergency release button located on the left h...

Page 209: ...uantity and deice pressure are usually installed on the right side of the instrument panel Two multi purpose instruments one for each engine indicate cylinder head temperature oil pres sure and oil temperature GROUND CONTROL Spring loaded linkage from the nose gear to the adjustable rudder pedals allows for nose wheel steering Smooth turning is accomplished by allowing the airplane to roll while d...

Page 210: ...Section VII Systems Description BEECHCRAFT Baron 58 Serial TH 773 and After I W Z Q Z w a r I z October 1976 ...

Page 211: ...BEECHCRAFT Baron 68 Serial TH 773 and After Section VII Systems Description J w z ct J Q W C CI t LL W J 0 z o w t J t CJ CI w w o en Z o J o a z o o o October 1976 7 9 ...

Page 212: ...ank engaged I CAUTION Do not change the position of the control switch to reverse the direction of the landing gear while the gear is in transit as this could cause damage to the retract mechanism POSITION INDICATORS Landing gear position lights are located above the control switch Three green lights one for each gear are illumi nated whenever the landing gears are down and locked The red light il...

Page 213: ... engine flight with the land ing gear retracted a warning horn will sound inter mittently During one engine operation the horn can be silenced by advancing the throttle of the inoperative engine until the throttle warning horn switch opens the circuit MANUAL EXTENSION The landing gear can be manually extended but not re tracted by operating the handcrank on the rear ofthe pilot s seat The landing ...

Page 214: ...control out and depress each toe pedal until firm Push the control in to release the brakes NOTE The parking brake should remain off and wheel chocks installed if the airplane is to remain unattended Changes in ambient temperature can cause the brakes to release or to exert excessive pressure On Serials TH 773 thru TH 1005 with shuttle valves installed only the pilot s brake pedals can be used in ...

Page 215: ...thin the baggage cargo compartment must be in accordance with the data in the WEIGHT AND BALANCE section All cargo must be secured with approved cargo I retention nets WARNING Do not carry hazardous material anywhere in the airplane NOSE BAGGAGE CARGO COMPARTMENT The forward baggage cargo compartment is easily ac cessible through a large door on the right side of the nose The door hinged at the to...

Page 216: ...n the lower in board side of the seat back The optional fifth and sixth seats can be folded up to provide additional floor space or folded down to provide access to the extended baggage cargo compartment Club seating is available When occupied aft facing chairs in the club seating arrangement must havethe headrests in the fully raised position during takeoff and landing If de sired these seats can...

Page 217: ...ts the strap is contained in an inertia reel attached to the upper fuselage side structure just aft of the seat back and is covered with an escutcheon NOTE The seat belt is independent of the shoulder harness but the outboard seat belt and the shoulder harness must be connected for stowage when the seat is not occupied DOORS WINDOWS AND EXITS CABIN DOOR The airplane has a conventional cabin door o...

Page 218: ...ding bulky cargo or to accommodate passengers The utility door is a double door with each half hinged at the forward and aft edge of the door opening The rear half of the door must be closed first A latch on the forward edge of the door moves downward to a locked position to secure the hooks atthe top and bottom of the door to the door frame The front half of the door cannot be fully closed until ...

Page 219: ...may select either BRT or DIM lights by moving the switch to the desired position OPENABLE CABIN WINDOWS NOTE Windows are to be closed before and during flight Serials TH 773 thru TH 1 079 Except TH 1 027 TH 1 062 and TH 1 067 To Open Window For Ventilation Only On Ground I Release latch front of bar pull bar at the bottom of the window out and upward Window will open approximately two inches To Cl...

Page 220: ...Red handle for emergency exit only 1 Lift thumb catch window will release 2 Push up and outward until mechanism clicks into detent To Close Window Pull inward and down until locked Listen for detent Serials THA 1316 and after To Open Window For Ventilation Only On Ground NOTE Red handle for emergency exit only 1 Rotate lock handle to UNLOCKED position 2 Lift thumb catch window will release 3 Push ...

Page 221: ... indicated by placard in the center of the Ventilation Emergency Exit latch 2 Rotate handle up as indicated by placard breaking safety wire and push window out NOTE Anytime the window has been opened by breaking the safety wire on the red emergency latch the window must be reattached and wired by a qualified mechanic using QQ W 343 Type S 020 diameter copper wire prior to further airplane operatio...

Page 222: ...from filtered ram air or alternate air Filtered ram air enters from the intake air scoop on top of the cowling Should the filter become obstructed a spring loaded door on the alternate air intake will open auto matically and the induction system will operate on alter nate air taken from the engine accessory section ENGINE ICE PROTECTION Engi ne ice protection consists of electrothermal fuel vent h...

Page 223: ...Due to the canted position of the engines the dip sticks are calibrated for either right or left engines and are not interchangeable The oil grades listed in the Approved Engine Oils in the SER VICING section are general recommendations only and will vary with individual circumstances The determining factor for choosing the correct grade of oil is the average ambient temperature COWL FLAPS The cow...

Page 224: ...d to regain rpm control The malfunction should be corrected by an au thorized service center before further flight PROPELLER SYNCHRONIZER The propeller synchronizer automatically matches the rpm of both propellers The system s range of authority is limited to approximately 25 rpm Normal governor operation is un changed but the synchronizer will continuously monitor propeller rpm and adjust one gov...

Page 225: ... the synchroscope a black and white cross pattern spins in a clockwise rotation Counterclock wise rotation indicates a higher rpm of the left propeller This instrument aids the pilot in accomplishing manual syn chronization of the propellers FUEL SYSTEM The fuel system is an OFF ON CROSSFEED arrangement The fuel selector panel located on the floor forward of the front seats contains the fuel selec...

Page 226: ... two additional filler caps one per wing Refer to the SERVICING section for additional information CAUTION When the wet wing tip tanks are filled with fuel DO NOT open the outboard wing leading edge filler caps as fuel will exit from those openings The standard 142 gallon fuel system and the optional 172 gallon fuel system have six drain locations There are two additional drain locations when the ...

Page 227: ...nel senses fuel pressure at the fuel distributor and is calibrated to indicate fuel flow to each engine in gallons per hour The green arc indicates the normal fuel flow operating range while the red radials indicate the minimum and maximum allowable fuel pressures CRUISE 1 4 1 550 0 WER 1 0 RANGE 65 75 FUEL FLOW AND PRESSURE INDICATOR Serials TH 773 thru TH 1193 September 1980 I 7 22A ...

Page 228: ... CRUISE POWER which indicates the approximate fuel flows for powers ranging from 45 to 75 of maximum continuous power The lower fuel flow of each sawtooth corresponds to the cruise lean fuel flow while the higher fuel flow of each sawtooth corresponds to the best power fuel flow When power is set in accordance with the cruise power setting tables in the PERFORMANCE Section these sawtooth marks pro...

Page 229: ...le the red radial indicates the maximum allowable fuel flow A segment of fuel flows at the higher end of the green arc is labeled TAKEOFF AND CLIMB and indicates the approximate fuel flow required for takeoff and climb at sea level 3000 5000 and 7000 feet The pilot should use these markings as a guide only and refer to the tables in the PERFORMANCE Section for takeoff climb at maximum continuous p...

Page 230: ...WITH FUEL FILTER FUEL DISTRIBUTOR t _ HEATER FUEL LINE FROM LEFT FUEL CELL ONLY FUEL SELECTORS 9 CHECK VALVE FROM RIGHT 0 FUEL CELL TO RIGHT ENGINE FUEL LEVEL SIGHT GAGE ENGINE DRIVEN PUMP CHECK VALVE FUEL RETURN FUEL LINE o FUEL SUPPLY o VENT LINE MECHANICAL CONNECTOR VENT LINE CHECK VALVE h FILLER CAP PRESSURE RELIEF VALVE EXTERNAL VENT HEATED SIPHON BREAK I N o n o 0 CD CO I en ...

Page 231: ...TER _ HEATER FUEL LINE FROM LEFT FUEL CELL ONLY FUel DISTRIBUTOR D 0 ru t _ VALVE FROM RIGHT _ FUEL CelL TO RIGHT ENGINE TRANSMITIER BOTIOM MOUNTED I FUel LEVel SIGHT GAGE VENT LINE CHECK VALVE 172 GALLON CAPACITY 166 GALLONS USABLE FUEL SYSTEM FUel RETURN FUel LINE o FUElSUPPLY o VENT LINE MECHANICAL CONNECTOR N UI o n o go CO a CJ ...

Page 232: ... J FUEL SUPPLY o VENT LINE MECHANICAL CONNECTOR TRANSMITTER BOTTOM MOUNTEO FROM RIGHT FUEL CELL TO RIGHT ENGINE SIPHON BREAK 200 GALLON CAPACITY 194 GALLONS USABLE FUEL SYSTEM en en CD In n CD _ 3 g In e CD In n i o J III enm CD m o t to t g W t 111111 J III o J 01 Cll ...

Page 233: ...each auxiliary fuel pump switch on the pilot s subpanel High pressure is used for providing fuel pressure before starting and provides near maximum en gine performance should the engine driven pumpfail Low pressure may be used in any operating mode to eliminate pressure fluctuations resulting from high ambient temper atures and or high altitudes The high pressure position should not be selected wh...

Page 234: ...t subpanel This panel con tains most ofthe electrical system switches and switch type circuit breakers Each is placarded asto its function The re mainder of the electrical equipment circuit breakers are lo cated on the pilot s side panel Avionics circuit breakers are located on the right subpanel BATIERY One 15 5 ampere hour 24 volt lead acid battery is standard Two 25 ampere hour 12 volt lead aci...

Page 235: ...BEECHCRAFT Baron 58 Serial TH 773 and After r 1 9Lr I tii o I m I g I 1 I O I I I I I ffi I I I I l I I I I I I I September 1980 Section VII Systems Description o w U VJ Z o co D VJ Q a w o 0 7 29 ...

Page 236: ...protection Each alternator system is controlled by a switch located on the subpanel I TH 773 AND AFTER Individual alternator output is indicated by two loadmeters on the instrument panel The loadmeters give a percentage reading of the load on the system Two warning lights placarded ALTERNATOR L R located in the floating instrument panel will illuminate whenever the respective alternator is disconn...

Page 237: ... alternator switches should be placed in the OFF position if the light remains illuminated after starting If the light does not illuminate during starting the indicator system is inoperative and the loadmeters should be monitored to ensure that the starters do not remain energized after starting This light can be tested by the TEST WARN LIGHT switch located on the floating instrument panel EXTERNA...

Page 238: ...by switches adjacent to the lights There are four rheostat dimmer control knobs located on the lower level of the circuit breaker panel the individual instrument lights located above the pilot s subpanel are controlled by the knob placarded INCREASE OFF SUBPANEL LIGHTING the avionics panel and trim tab indicator lights are controlled by the knob placarded INCREASE OFF INST FLOOD the instrument lig...

Page 239: ...tip fuel tanks TH 773 thru TH 873 a single nose gear landing light replaces the two leading edge landing lights and the optional nose gear taxi light With optional wing tip fuel tanks TH 874 and after the landing lights are located on the front lower section of each engine cowling For longer battery and lamp service life use the landing Iight s only when necessary Avoid prolonged operation during ...

Page 240: ...Section VII Systems Description BEECHCRAFT BARON 58 Serial TH773 and After 7 32B INTENTIONALLY LEFT BLANK september 1981 ...

Page 241: ...copilot seats at the rear of the copilot s seat and at the 5 D TST AIR GLASS SERVICE VALVES FRESH AIR CONTROL AIR CONDITIONER OUTLETS 4 PLACES ill CABIN AIR CONTROL CABIN HEAT CONTROL CD DEFROST CONTROL PILOT AIR CONTROL COPILOT AIR CONTROL AFT BULKKEAD AFT EVAPORATOR OR OPTIONAL FRESH AIR BLOWER CABIN AIR EXHAUST HEATER J liiW _HEATER AlA c J AIR CONDITIONER J _ VENTILATION AIR EXHAUST AIR ENVIRO...

Page 242: ... HEATER AGAIN HEATER OPERA nON 1 A three position switch placarded BLOWER OFF and HEATER is located on the pilot s subpanel To place the heating system in operation move the switch to the HEATER position 2 The CABIN AIR T handle which regulates the amount of intake air is below the left side of the pilot s subpanel On TH 873 TH 895 and after it is below the circuit breaker panel on the left sidewa...

Page 243: ...ach control individually More heated air will be available for defrosting by reducing the flow of air from the pilot outlet copilot outlet or both The PILOT AIR and COPILOT AIR controls can be used to regulate the volume of air distributed to the rear outlets HEATER BLOWER When the three position switch on the pilot s subpanel is placed in either the HEATER position or the BLOWER position the blow...

Page 244: ...s enables the pilot to adjust the amount of ram air available to all outlets The volume of air at each outlet can be regulated by rotating the outlet Each outlet can be positioned to direct the flow of air as desired OXYGEN SYSTEM WARNING Proper safety measures must be employed when using oxygen or a serious fire hazard will be created NO SMOKING PERMITIED DESCRIPTION The recommended masks are pro...

Page 245: ...is lo cated immediately to the left of the nose gear doors The optional pitot tube for the copilot s instrument is located to the right of the nose gear doors Left and right pitot heat switches located on the pilot s left subpa nel supply heat to the left and right pitot masts respectively The pitot system needs no drain because of the location of the components STATIC SYSTEM Static air is taken f...

Page 246: ...irspeed Calibrations and AI timeter Corrections charts are in the PERFORMANCE sec tion PRESSURE SYSTEM Pressure for the flight instruments deice boots and auto pilot if installed is supplied by two engine driven dry pressure pumps interconnected to form a single system If either pump fails check valves automatically close and the remaining pump continues to operate all gyro instruments A pressure ...

Page 247: ...er is inoperative when the battery and alternator switches are OFF while in flight In icing conditions stalling airspeeds should be expected to increase due to the distortion of the wing airfoil when ice has accumulated on the airplane For the same reason stall warning devices tend to lose their accuracy The sensing vane is installed on a plate that can be electrically heated preventing ice from f...

Page 248: ...three position spring loaded switch with a center OFF position a MAN manual down position and an up AUTO automatic position controls the system When the switch is in the AUTO position the deice boots inflate for a period of five to six seconds then deflate automatically and return to the vacuum hold down position The switch must be tripped for each complete cycle In the MAN position the deice boot...

Page 249: ...subpanel Windshield heat is designed for continuous in flight use and should be applied prior to or upon first encountering icing conditions This system is also beneficial as an aid in preventing frost and fogging due to rapid descents from higher altitudes into warm moist air Operation of the windshield heat will cause the standby compass to become erratic therefore windshield heat should be turn...

Page 250: ...Section VII Systems Description BEECHCRAFT Baron 58 Serial TH 773 and After 7 408 INTENTIONALLY LEFT BLANK september 1979 ...

Page 251: ...s anti ice fluid from the same source as the propeller anti ice system Ice is prevented from forming on the windshield by wetting the windshield surface with anti ice fluid This combined sys tem is controlled by a three position switch MOM ON OFF ON located on the pilot s subpanel The system will not function unless the propeller anti ice pump switch is turned ON For windshield system only the flo...

Page 252: ... uously in flight it will function automatically until the switch is turned off Propeller imbalance can be relieved by varying rpm Increase rpm briefly then return to the de sired setting Repeat if necessary CAUTION Do not operate the system with the engines in operatve PITOT HEAT Heating elements are installed in the pitot mast s Each heating element is controlled by an individual switch lo cated...

Page 253: ...e used until oil consumption stabilizes usually a total of approximately 50 hours After oil consumption has stabilized MIL L 22851 Ashless Dispersant Oil should be used Drain and replace the engine oil as recommended in HANDL lNG SERVICING AND MAINTENANCE If operating condi tions are unusually dusty or dirty more frequent oil changes may be necessary Oil changes are more critical during the break ...

Page 254: ...ring the break in period Maintain sufficient power during descent to permit cylinder head temperatures to remain in the green arc Minimize ground operation time especially during warm weather During the break in period avoid engine idling in excess of 15 minutes especially in high ambient tempera tures 7 44 AugU8t 1984 ...

Page 255: ...icated Pilot 8 6A Alterations or Repairs to Airplane 8 68 Ground Handling 8 8 Towing 8 8 Parking 8 8 Tie Down 8 9 Main Wheel Jacking 8 10 Prolonged Out of Service Care 8 10 Storage 8 10 Flyable Storage 7 to 30 Days 8 10 Mooring 8 10 Engine Preparation For Storage 8 11 During Flyable Storage 8 11 Fuel Cells 8 11 Flight Control Surfaces 8 11 Grounding 8 11 Engines Pitot Tube 8 12 Windshield and Wind...

Page 256: ... 8 17 Tires 8 17 Shock Struts 8 18 Shock Strut Shimmy Damper 8 19 Brakes 8 20 Induction Air Filter 8 20 To Remove and Clean the Filter 8 20 Propellers 8 20 Propeller Blade Bearing lubrication 8 21 Propeller and Windshield Anti ice Tank Fluid 8 21 Oxygen System 8 22 Oxygen Cylinder Retesting 8 23 Minor Maintenance 8 23 Rubber Seals 8 23 Heating and Ventilating System 8 23 Alternators 8 24 Magnetos ...

Page 257: ... Servicing Schedule 8 35 Consumable Materials 8 41 Approved Engine Oils 8 43 Bulb Replacement Guide 8 45 Overhaul or Replacement Schedule 8 46 Special Conditions Cautionary Notice 8 46 landing Gear 8 47 Power Plant 8 47 Fuel System 8 48 Instruments 8 49 Electrical System 8 49 Utility Systems 8 50 Flaps and Flight Controls 8 50 Miscellaneous 8 51 September 1979 8 3 ...

Page 258: ...Section VIII Handling Serv Maint BEECHCRAFT Baron 58 Serial TH 773 and After 8 4 INTENTIONALLY LEFT BLANK October 1976 ...

Page 259: ... is done by qualified mechanics in conformity with all airworthi ness requirements established for this airplane All limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandatory Authorized BEECHCRAFT Aero or Aviation Centers orl International Distributors or Dealers can provide recommended modification service and operati...

Page 260: ...er of this manual automatically 1 Original issues and revisions of BEECHCRAFT Service Bulletins 2 Original issues and revisions of FAA Approved Airplane Flight Manual Supplements 3 Reissues and revisions of FAAApproved Airplane Flight Manuals Flight Handbooks Owner s Manuals Pilot s Operating Manuals and Pilot s Operating Handbooks This service is free and will be provided only to holders of this ...

Page 261: ...PLANE INSPECTION PERIODS 1 FAA required 1DO hour and or Annual Inspections 2 BEECHCRAFT Approved Inspection Guide 3 Continuing Care Inspection Guide 4 See Recommended Servicing Schedule and Overhaul or Replacement Schedule for further inspection schedules NOTE Check the wing bolts for proper torque at the first 1DO hour inspection and at the first 100 hour inspection after each reinstallation of t...

Page 262: ...ots operating airplanes of other than U S registry should refer to the regulations of the country of certification for information on pre ventative maintenance that may be performed by pilots ALTERATIONS OR REPAIRS TO AIRPLANE The FAA should be contacted prior to any alterations on the airplane to ensure the airworthiness of the airplane is not violated NOTE Alterations or repairs to the airplane ...

Page 263: ...ifferent in fabrication techniques and materials and may be dangerous when installed in an airplane Salvaged airplane parts reworked parts obtained from non BEECHCRAFT approved sources or parts components or structural assemblies the service history of which is unknown or cannot be authenticated may have been subjected to unacceptable stresses or temperatures or have other hidden damage not discer...

Page 264: ...to have someone in the air plane to operate the brakes CAUTION Do not exert force on the propellers control surfaces or horizontal stabilizer When towing with a tug Iimit turns to prevent damage to the nose gear Do nottowwhen the main gear is ob structed by mud or snow Also ensure the rudder lock is removed Care should be used when removing the tow bar to prevent damage to the lubrication fittings...

Page 265: ...ert excessive pressures TIE DOWN I It is advisable to nose the airplane into the wind Three tie down lugs are provided one on the lower side of each wing and a third at the rear of the fuselage 1 Install the control locks 2 Chock the main wheels fore and aft 3 Using nylon line or chain of sufficient strength secure the airplane at the three points provided DO NOT OVER TIGHTEN if the line at the re...

Page 266: ...rplane while it is on a main wheel jack PROLONGED OUT OF SERVICE CARE STORAGE Storage procedures are intended to protect the airplane from deterioration while it is not in use The primary objectives of these measures are to prevent corrosion and damage from exposure to the elements Flyable Storage 7 30 days has been considered here For more extended storage periods consult the Beech Airplane Shop ...

Page 267: ...ng each engine six revolutions stop the propellers 600 or 1200 from the position they were in WARNING Before rotation of propeller blades ascertain magneto start switches are OFF throttles are in the CLOSED position and mixture controls are in the IDLE CUT OFF position Always stand in the clear while turning propellers If at the end of 30 days airplane will not be removed from storage the engine s...

Page 268: ...tic pressure openings Preflight the airplane EXTERNAL POWER When using external power it is very important that the fol lowing precautions be observed 1 The airplane has a negative ground system Exercise care to avoid reversed polarity Be sure to connect the positive lead of the auxiliary power unit to the positive terminal of the airplane s external power receptacle and the negative lead to the n...

Page 269: ...nsure that the current is stabilized prior to mak ing any electrical equipment or avionics check NOTE If the external power unit has poor voltage regu 1ation or produces voltage transients the air craft electrical equipment connected to the unit may be damaged SERVICING FUEL SYSTEM FUEL CELLS See Consumable Materials for recommended fuel grades The standard 142 gallon capacity fuel system has a fu...

Page 270: ... will exit from that opening If this occurs wash the fuel from the wing surface to prevent possible paint damage Ground the aircraft with a static line before refueling and secure the filler caps immediately after filling Before let ting the airplane stand for several days it is a good practice to fill the wing fuel system to ensure that the cell inner Iiners do not dry out and crack allowing fuel...

Page 271: ...ks if installed When the flush type drains are installed a drain wrench is provided in the loose tools and accessories FUEL STRAINERS To preclude the possibility of contaminated fuel always cap any disconnected fuel tines or fittinqs The fue strainer in each wheel well should be inspected and cleaned with sol vent at regular intervals The frequency of inspection and cleaning will depend upon servi...

Page 272: ...nboard corner of the oil sump 2 Open the oil drain valve 3 Remove the oil filter and replace with a new unit A torque of 18 to 20 foot pounds should be applied to the nut of the oil filter 4 Close oil drain valve and fill with oil Moisture that may have condensed and settled in the oil sump should be drained occasionally by opening the oil drain plug and allowing a small amount of oil to escape Th...

Page 273: ... level after each 25 hours of operation and add distilled water as necessary Avoid filling over the baffles and never fill more than one quarter inch over the separator tops Excessive water consumption may be an indication that the voltage regulators require resetting The battery box is vented overboard to dispose of electrolyte and hydrogen gas fumes discharged during the normal charging operatio...

Page 274: ...doors and retract mechanism SHOCK STRUTS CAUTION DO NOT taxi with a flat shock strut The shock struts are filled with compressed air and hydraulic fluid The same procedure is used for servicing both the main and the nose gear shock struts To service a strut proceed as follows 1 Jack the airplane remove the air valve cap depress the valve core and allow the strut to fully deflate WARNING Do not uns...

Page 275: ...ruts until 3 inches of the piston are exposed Rock the airplane gently to prevent possible binding of the piston in the barrel while inflating NOTE It is recommended that the nose strut inflation di mension and the tire inflation pressures be carefully adhered to Properly inflated tires and struts reduce the possibility of ground damage occuring to the propellers Exercise caution when taxiing over...

Page 276: ...Section VIII Handling Serv Maint BEECHCRAFT Baron 58 Serial TH 773 and After 8 18B INTENTIONALLY LEFT BLANK September 1979 ...

Page 277: ...ston rod until it touches the bottom of the hole in the floating piston Mark the wire remove it and measure the depth of the insertion When the shimmy damper is full insertion depth is 2 3 16 inches when empty 3 1 16 inches NOTE The measuring wire should be inserted in the hole in the floating piston rather than against the piston face to give a more accurate reading To determine if the wire is in...

Page 278: ...hould be re placed when its thickness measures 330 inch INDUCTION AIR FILTERS The filters should be inspected for foreign matter at least once during each 50 hour operating period In adverse climatic conditions or if the airplane is stored preflight inspection is recommended TO REMOVE AND CLEAN THE FILTER 1 Remove the access plate in the top of the engine cowling 2 Remove the filter and clean as n...

Page 279: ...d covers from grease zerks 3 Remove one zerk from each blade 4 Lubricate by placing the grease gun fitting on one zerk of each blade and filling until the grease is visible from the zerk openi ng on the opposite side of the blade 5 Clean the excess grease from the propeller reinstall the grease zerks covers and safety wire on each blade 6 Reinstall the spinner PROPELLER AND WINDSHIELD ANTI ICE TAN...

Page 280: ...s open the cylinder shutoff valve slowly to prevent damage to the system 2 Make certain that the oxygen control valve is closed PUSH IN 3 Close the cylinder shutoff valve remove the cap from the filler va1ve and attach the recharging outlet Open valve on supply bottle 4 Open the cylinder shutoff valve and fill the cylinder to 1800 50 psi add 3 5 psi per degree above 70 F sub tract 3 5 psi per degr...

Page 281: ...windows doors and engine cowling the seals should be coated with Oakite 6 compound The compound is noninjurious to paint and can be removed by employing normal cleaning methods HEATING AND VENTILATING SYSTEM The heater fuel pump filter in the nose wheel well should be removed and cleaned after each 100 hours of airplane operation Remove the filter by turning the base of the pump counterclockwise W...

Page 282: ...ad of the charger to the positive battery terminal and the negative lead of the charger to the negative battery terminal 4 Do not operate an alternator on open circuit Be sure all circuit connections are secure 5 Do not short across or ground any of the terminals on the alternator or electronic voltage regulator 6 Do not attempt to polarize an alternator MAGNETOS Ordinarily the magnetos will requi...

Page 283: ...im tab hinge lines and trim tab pushrod end fittings Brayco 300 per Federal Specification VV L 800 preferred See Consumable Materials CAUTION When cleaning landing gear areas with solvent especially if high pressure equipment is used exercise care to avoid washing away grease from landing gear components After washing the landing gear areas with solvent lubricate all lubrication points or prematur...

Page 284: ...ch the pitot cover securely and plug or mask offal other openings Be particularly careful to mask off all static air buttons before washing or waxing Use special care to avoid removing lubricant from lu bricated areas When using high pressure washing equipment keep the spray or stream clear of wheel bearings propeller hub bearings etc and openings such as pitot tubes static air buttons and battery...

Page 285: ...esired Acrylic urethane may be waxed for protection from the elements but should not be polished unless polishing or buffing is required to restore a damaged area Waxing of polyester urethane finishes although not required is permitted however never use abrasive cleaner type waxes polishes or rubbing compounds as these products cause eventual deterioration of the characteristic urethane gloss Epox...

Page 286: ...s will soften plastic and may cause it to craze After thoroughly cleaning the surface should be waxed with a good grade of commercial wax The wax will fill in the minor scratches and help prevent further scratching Apply a thin even coat of wax and bring it to a high polish by rubbing lightly with a clean dry soft flannel cloth Do not use a power buffer the heat generated by the buffing pad may so...

Page 287: ...area Oily spots may be cleaned with household spot removers used sparingly Before using any solvent read the instruc tions on the container and test it on an obscure place on the fabric to be clea ned Never saturate the fabric with a volatile solvent it may damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type detergent used according to the manufactur...

Page 288: ...Section VIII Handling Serv Maint BEECHCRAFT Baron 58 Serial TH 773 and After t t Z 0 D Z 0 t 2 J a i m J I 2 Il O 0 1 0 8 28 October 1976 ...

Page 289: ...BEECHCRAFT Baron 58 Serial TH 773 and After Section VIII Handling Serv Maint A CONTROL COLUMN LINKAGE B CABIN DOOR c RUDDER PEDALS October 1976 8 29 ...

Page 290: ...ection VIII Handling Serv Maint BEECHCRAFT Baron 58 Serial TH 773 and After D LANDING GEAR BOX 58 604 45 MAIN LANDING GEAR DOOR HINGES F 5 r i hL x UTILITY DOOR 58 604 46 5 58 604 47 8 30 September 1979 ...

Page 291: ...BEECHCRAFT Baron 58 Serial TH 773 and After Section VIII Handling Serv Maint G RUDDER TAB 58 604 48 H I ELEVATOR TAB AILERON TAB 58 604 50 Revised March 1983 8 31 ...

Page 292: ...Section VIII Handling Serv Maint BEECHCRAFT Baron 58 Serial TH 773 and After J AILERON BELL CRANKS 58 604 51 K FLAP ACTUATOR 58 604 52 L MAIN GEAR RETRACT 58 604 53 September 1979 ...

Page 293: ...BEECHCRAFT Baron 58 Serial TH 773 and After Section VIII Handling Serv Maint M N o NOSE WHEEL DOOR HINGES September 1979 58 604 55 58 604 56 ...

Page 294: ...aron 58 Serial TH 773 and After NOSE WHEEL STEERING Q I HEATER IRIS VALVE HAND OR PACK FLUID CONT AINER ZERK FITTING SQUIRT CAN NOTE Letters are keyed to the Service Schedule Numbers refer to items in the Consumable Materials Chart 8 34 October 1976 ...

Page 295: ...door on upper 6 flight cowling I Drain main fuel cell drains Lower wing surface leading edge Drain fuel strainer drains Wing surface fwd of main wheel well Drai n box section cell Aft bottom wing surface Service fuel cells Top of wings leading edge 7 25 Hrs Check battery electrolyte Fwd baggage compartment See Shop Manual under floor tAm CD m m etn f t J a w m m CD g CD 0 1 co x m 9 5 cc en CD CD ...

Page 296: ...gh cowl opening 6 Replace engine Access plate on left Hastings oil oil filter cowling door filter P 128 Clean fuel strainers In wheel wells 9 Clean fuel injection Access door on side of 9 control valve screen nacelle Clean heater fuel pump Nose wheel well 9 filter Lubricate trim tab Empennage G H 19 hinges and push rods Aileron I Clean with solvent and blow dry with compressed air 1 CD CD J Q 0 J ...

Page 297: ...eel well P 3 0 r J steering mechanism C1I II I Lubricate landing gear Nose wheel and main gear 3 CD retract mechanism wheel wells 0 L Lubricate wheel bearings Landinq gear 0 L 1 Lubricate cabin door Cabin door latch B 5 mechanism c Lubricate aileron bell Access panel underside 5 m J cranks wings J Q 5 Lubricate control column Forward of instrument 5 linkage panel A l cn Lubricate rudder pedals Coc...

Page 298: ... system and Oil or grease landing gear as required Service landing gear Under front seats 0 11 actuator gear box 500 Hrs Replace pressure system Aft of engine firewall Airborne IJ4 7 filters Replace pressure system Rear engine baffle Airborne D9 14 1 inlet filter 600 Hrs Service landing gear Under front seats 0 3 I motor reduction gears I 900 Hrs Lubricate flap actuators Forward of flap K 12 and f...

Page 299: ...r compartment Service oxygen cylinder Nose baggage compartment 18 Service brake fluid Nose baggage compartment 2 reservoir Drain moisture from Through cowl flap opening engine oil sump Service main gear struts Top of each strut L 2 Service nose gear strut Top of strut 0 2 Service shimmy damper Nose landing gear 0 2 Check brake lining wear Main landing gear wheels Lubricate heater iris Forward nose...

Page 300: ... emergency On right side of aft locator transmitter fuselage access through Replace left side access panel t Rechargeable Batteries Recharge after one cumulative hour of use or after 50 of the useful charge life Non Rechargeable Batteries Replace after one cumulative hour or after 50 of the useful life ten m CD s n a t 0 s en I 3 m ED l m I m n I 0 J a W I Q CD s Al a l g 0 1 CD ...

Page 301: ...e been tested and approved for aviation usage by Beech Aircraft Corporation by the vendor or by compliance with the ap plicable specifications Other products that are locally procurable which conform to the requirements of the appli cable Military Specification may be used even though not specifically included herein It is the responsibility of the operatorluser to determine the current revision o...

Page 302: ...fide MIL M 7866 5 Lubricating Oil SAE No 20 or SAE 1OW 3D 6 Engine Oil SAE 30 Below 40 F SAE 50 Above 40 F I Approved Multi viscosity Oils 7 Engine Fuel Grade 1DOLL Blue I preferred 100 Green 8 Anti Ice Fluid MIL F 5566 9 Solvent Federal Specification PD6S0 10 Lubricant Scintilla 10 86527 I 11 Lubricant Mobil Compound GG or Mobil 636 I 12 Lubricating Oil Gear MIL L 1 0324 or MIL L 2105C Grade 75W ...

Page 303: ... Aliphatic Federal Specification TI N 95 tt16 Tape Antiseize Tetrafluorethylene MIL T 27730 17 Leak Test Compound Oxygen Systems MIL L 25567 18 Oxygen Aviator s Breathing MIL O 27210 19 Lubricating Oil Brayco 300 per General Purpose Federal Specifi Preservative Water cation VV L BOO Displacing Low Preferred Temperature Alternates for Brayco 300 Lubricant Revised March 1983 CRe 3 36 LPS No 1 WD 40 ...

Page 304: ...e servicing data If 1DOLL grade fuel blue is not available use 100 green as minimum grade See Engine Manufacturer s Service Letter for recommended maintenance and servicing techniques Product of Bray Oil Co 1925 North Marianna Los Angeles Calif 90032 Product of CRe Chemicals Inc Warminster Pa 18974 Product of LPS Research Laboratories Inc 2050 Cotner Ave W Los Angeles Calif 90025 Product of WD 40 ...

Page 305: ...ning Company Pennzoil Company Phillips Petroleum Co Quaker State Oil Reiining Corp Revised March 1983 BRAND AND WEIGHT SIP Aero Oil 065 80 Grade 40 Castrolaero AD Type Iff Grade 50 Castrolaero AD1 Type II Conoco Aero S SAE 10W30 Delta Avail Grades 30 40 50 Gulfpride Aviation AD Esso Aviation Oil Enco Aviation Oil Pennzoil Aircraft Engine Oil Heavy Duty Dispersant Grades 30 40 50 Phillips 66 Aviati...

Page 306: ...0 Grade 65 Nominal SAE 20 or 30 Military Grade 1065 Sinclair Avoil 20W 40 Mobil Aero Oil 65 Ashless Mobil Aero Oil 80 Dispersant Mobil Aero Oil 100 Aviation Mobil Aero Oil 120 Engine Oil Texaco Aircraft Engine Oil Premium AD Grades 65 80 100 Union Aircraft Engine Oil HD Grades 80 100 NOTE This chart lists all oils which were certified as meeting the requirements of Teledyne Continental Motors Corp...

Page 307: ...ight A 7079B 24 Instrument light flood 313 Instrument light post 327 Landing gear position light 327 Landing light 4596 Map light 1495 Navigation light tail 93 Navigation light tail w strobe 701557 6 801 or I 30 0815 5 Grimes Navigation light wing A7512 24 Grimes Alternator out light 327 Reading light 303 Rotating beacon A 7079B 24 Grimes Tab position indicator light 1819 Taxi light if installed 4...

Page 308: ...oted in this handbook are based on average usage and average environmental conditions SPECIAL CONDITIONS CAUTIONARY NOTICE Airplanes operated for Air Taxi or other than normal operation and airplanes operated in humid tropics or cold and damp climates etc may need more frequent inspections for wear corrosion and or lack of lubrication In these areas periodic inspections should be performed until t...

Page 309: ...rs Every 2000 hours Every 500 hours or on condition Every 1000 hours On condition On condition On condition On condition On condition On condition On condition POWER PLANT NOTE When an engine has been overhauled or a new engine installed it is recommended that low power settings not be used until oil consump tion has stabilized The average time for piston ring seating is approximately 50 hours Eng...

Page 310: ...dition At engine overhaul but not to exceed 1500 hours or 3 years Every 600 hou rs Hose carrying flammable liquids at engine overhaul or every 5 years All other hose on condition FUEL SYSTEM Fuel cells Wing fuel quantity tra nsmitters Fuel cell drain valve Fuel system check valves Fuel selector valves Aux fuel pump All hose Vent line check valve 8 48 On condition On condition On condition On condi...

Page 311: ...ge All hose On condition Every 24 months per FAA Directive Inspect and Calibrate On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition On condition ELECTRICAL SYSTEM Dynamic brake relay Battery master relay All other relays Voltage regulator Starter Starter relay Alternator Landing gear selector switch October...

Page 312: ... replace every 24 years or 4 380 refills ICC Regulation Hydrostatically test every 5 years no replacement duration On Condition All Hose Cabin heater Heater spark plug Heater fuel pump Heater fuel spray nozzle Heater fuel shut off valve Combustion blower Combustion blower brushes Heater vent blower Heater vent blower brushes Oxygen regulator COMPONENT I FLAPS AND FLIGHT CONTROLS Flight controls Ai...

Page 313: ...Harnesses Hand fire extinguisher Inspect every 12 months replace on condition Inspect every 12 months recharge as necessary Refer to Continental Service Bulletin M74 20 Rev 1 or later issue for detailed overhaul period instructions With particular attention to throttle response smooth power and oil consumption a qualified certificated mechanic must determine that the engine is operating normally a...

Page 314: ...Section VIII Handling Serv Maint BEECHCRAFT Baron 58 Serial TH 773 and After 8 62 INTENTIONAllY LEFT BLANK October 1976 ...

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Page 317: ...em 3 10 83 58 590000 25 AirData AD611 D Area Navigation 6 21m 106 590000 15 Collins ANS 351 Area Navigation 11 16f77 System 58 590000 27 AirData AD 511 AD 511 G Area 1 7 79 Navigation System 102 590000 45 KNC 610 Area Navigation System 11 78 58 590000 29 King KNS 80 Integrated Navigation 1f79 System 96 590010 27 Narco RNAV 161 Multi Waypoint Area 1 79 Navigation System 102 590000 53 King KNS 81 In...

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Page 451: ... Airworthiness Directives Airman s Information Manual Advisory Information FAA Advisory Circulars FAA General Aviation News FAA Accident Prevention Program Additional Information General Information on Specific Topics Maintenance Hazards of Unapproved Modifications Flight Planning Passenger Information Cards Stowage of Articles Flight Operations General Preflight Inspection Weight and Balance Auto...

Page 452: ...Engine Inoperative Speed g ngi e i p i ii B i R ai i c lir b 45 Speed VYSE 45 One Engine Inoperative Best Angle at Climb Speed VXSE Single Engine Service Ceiling Basic Single Engine Procedures Engine Failure on Takeoff When to Fly Vx Vy VXSE and VYSE Stalls Slow Flight and Training Spins Descent Vortices Wake Turbulence Takeoff and Landing Conditions Medical Facts for Pilots General Fatigue Hypoxi...

Page 453: ... 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 safe altitudes and airspeeds prefer ably with a qualified instructor pilot until the required action can be accomplished without reference to the manual Peri odically review this Safety Information as ...

Page 454: ...the other operating and maintenance manu als which accompany the airplane that FAA requirements for ratings certifications and review be scrupulously com plied with and that you allow only persons who are properly licensed and rated and thoroughly familiar with the contents of the Pilot s Operating Handbook and FAA Approved Air plane Flight Manual to operate the airplane IMPROPER OPERATION OR MAIN...

Page 455: ...tructor until you are current Practice until you are proficient Preplan all aspects of your flight including a proper weather briefing and adequate fuel reserves Use services available weather briefing inflight weather and Flight Service Station Carefully preflight your airplane Use the approved checklist Have more than enough fuel for takeoff plus the trip and an adequate reserve Be sure your wei...

Page 456: ... DON TS Don t take off with frost ice or snow on the airplane Don t take off with less than minimum recommended fuel plus adequate reserves and don t run the tank dry before switching Don t fly in a reckless show off or careless manner Don t fly into thunderstorms or severe weather Don t fly in possible icing conditions unless the airplane is approved properly equipped and all required equipment i...

Page 457: ...s Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Beech has revised and reissued many of the early manuals for certain models of airplanes in GAMA Standard Format as Pilot s Operating Handbooks and FAA Approved Airplane Flight Manuals For simplicity and convenience all official manuals in various models are referred to as the Pilot s Operating Handbook and FAA Approved Airplane ...

Page 458: ... in the name or address furnished by the FAA The owner must contact the FAA regarding any changes to name or address Their address is FAA Aircraft Registration Branch AAC250 P O Box 25082 Oklahoma City OK 73125 Phone 405 680 2131 It is the responsibility of the FAA owner of record to ensure that any mailings from Beech are forwarded to the proper persons Often the FAA registered owner is a bank or...

Page 459: ...aft Corporation P O Box 85 Wichita Kansas 67201 0085 From time to time Beech Aircraft Corporation issues BEECHCRAFT Safety Communiques dealing with the safe operation of a specific series of airplanes or airplanes in general It is recommended that each owner operator main tain a current file of these publications Back issues of BEECHCRAFT Safety Communiques may be obtained with out charge by sendi...

Page 460: ...es except in accordance with the requirements of that Airworthiness Directive AIRMAN S INFORMATION MANUAL The Airman s Information Manual AIM is designed to pro vide airmen with basic flight information and ATC proce dures for use in the national airspace system of the United States It also contains items of interest to pilots concerning health and medical facts factors affecting flight safety a p...

Page 461: ...otices to Airmen are documents that have information of a time critical nature that would affect a pilot s decision to make a flight for example an airport closed ter minal radar out of service or enroute navigational aids out of service FAA ADVISORY CIRCULARS The FAA issues Advisory Circulars to inform the aviation public in a systematic way of nonregulatory material of inter est Advisory Circula...

Page 462: ...0 125 21 4 43 9 10 12 Aviation Weather Thunderstorms Rules of Thumb for Avoiding or Mini mizing Encounters with Clear Air Tur bulence Aviation Weather Services Aviation Safety Reporting Program Plane Sense Carbon Monoxide CO Contamination in Aircraft Detection and Prevention Tie Down Sense Aircraft Fuel Control Engine Power Loss Accident Preven tion Pilot Precautions and Procedures to be Taken in ...

Page 463: ...al Flight Review The Accident Prevention Counselor Program Pilot Transition Courses for Complex Single Engine and Light Twin Engine Airplanes Flight Training Handbook Pilot s Handbook of Aeronautical Knowledge Instrument Flying Handbook Hazards Associated with Spins in Air planes Prohibited from Intentional Spinning Role of Preflight Preparation Medical Handbook for Pilots Aircraft Wake Turbulence...

Page 464: ...Aviation Gasoline for Grade 80 87 Noise Hearing Damage and Fatigue in General Aviation Pilots Unreliable Airspeed Indications Operational and Maintenance Prac tices for Emergency Locator Transmit ters and Receivers Gyroscopic Instruments Good Oper ating Practices Importance of Transponder Operations and Altitude Reporting Airplane Deice and Anti ice Systems Inspection and Care of General Avia tion...

Page 465: ...000 volunteer airmen serving as accident prevention counselors sharing their technical expertise and professional knowledge with the general aviation commu nity The FAA conducts seminars and workshops and dis tributes invaluable safety information under this program Usually the airport manager the FAA Flight Service Station FSS or Fixed Base Operator FBO will have a list of accident prevention cou...

Page 466: ...eather or Not Disorientation Plane Sense Weather Info Guide for Pilots Wake Turbulence Don t Trust to Luck Trust to Safety Rain Fog Snow Thunderstorm TRW Icing Pilot s Weather Briefing Guide Thunderstorms Don t Flirt Skirt em IFR VFR Either Way Disorientation Can Be Fatal IFR Pilot Exam O Grams VFR Pilot Exam O Grams Flying Light Twins Safely Tips on Engine Operation in Small General Aviation Airc...

Page 467: ... maintenance repair and inspections It is the responsibility of the owner and the operator to assure that the airplane is maintained in an airworthy condi tion and that proper maintenance records are kept Use only genuine BEECHCRAFT or BEECHCRAFT approved parts obtained from BEECHCRAFT approved sources in connection with the maintenance and repair of Beech airplanes Genuine BEECHCRAFT parts are pr...

Page 468: ...for Air Taxi or other than normal opera tion and airplanes operated in humid tropics or cold and damp climates etc may need more frequent inspections for wear corrosion and or lack of lubrication In these areas periodic inspections should be performed until the operator can set his own inspection periods based on experience NOTE The required periods do not constitute a guarantee that the item will...

Page 469: ... STC on your airplane check to make sure that the STC does not conflict with other STC s that have already been installed Because approval of an STC is obtained by the individual STC holder based upon modification of the original type design it is possible for STC s to interfere with each other when both are installed Never install an unapproved modi fication of any type however innocent the appar...

Page 470: ...ack and stations and make a list for quick reference It is strongly recommended a flight plan be filed with Flight Service Sta tions even though the flight may be VFR Also advise Flight Service Stations of changes or delays of one hour or more and remember to close the flight plan at destination The pilot must be completely familiar with the performance of the airplane and performance data in the ...

Page 471: ...tilized to provide space for seat displacement If hard solid objects are stored beneath seats the energy absorbing feature is lost and severe spinal injuries can occur to occupants Prior to flight pilots should insure that articles are not stowed beneath seats that would restrict seat pan energy absorption or penetrate the seat in event of a high vertical velocity accident FLIGHT OPERATIONS GENERA...

Page 472: ...g speed will be higher rate of climb the cruising speed and the range of the airplane at any level of fuel will all be lower than shown in the Performance section If an airplane is loaded so that the C G is forward of the for ward limit it will require additional control movements for maneuvering the airplane with correspondingly higher con trol forces The pilot may have difficulty during takeoff ...

Page 473: ...ribed in the Airplane Flight Manual Supplements Ensure a full understanding of the methods of engagement and disengagement of the autopi lot and trim systems Compare the descriptions and procedures contained in the Supplements to the actual installation in the airplane to ensure that the supplement accurately describes your instal lation Test that all buttons switches and circuit breakers function...

Page 474: ...icult to distinguish an autopilot malfunction from an electric trim system malfunction The safest course is to deactivate both Do not re engage either system until after you have safely landed Then have the systems checked by a qualified service facility prior to further flight Depending upon the installation on your airplane the foltow ing additional methods may be available to disengage the auto...

Page 475: ...ve Consult the AFM for further infor mation 5 Push the GA switch on throttle grip if installed depend ing upon the autopilot system 6 Push TEST EACH FLT switch on the autopilot control ler if installed NOTE After the autopilot is positively disengaged it may be necessary to restore other electrical functions Be sure when the master switches are turned on that the autopilot does not re engage The a...

Page 476: ...airflow over the surface The ampli tude of the vibration can 1 decrease if airspeed is reduced 2 remain constant if airspeed is held constant and no failures occur or 3 increase to the point of self destruction especially ifairspeed is high and or is allowed to increase Flutter can lead to an in flight break up of the air plane Airplanes are designed so that flutter will not occur in the normal op...

Page 477: ...spection Guide Worn control surface attachment hardware must be replaced Any repainting or repair of a moveable control surface will require a verification of the control surface balance before the airplane is returned to service Control surface drain holes must be open to prevent freezing of accumulated moisture which could create an increased trailing edge heavy control surface and flutter If an...

Page 478: ...ns Plan the flight to avoid areas of reported severe turbulence It is not always possible to detect individual storm areas or find the in between clear areas The National Weather Service classifies turbulence as fol lows Class of Turbulence Extreme Severe Moderate 10 28 Effect Airplane is violently tossed about and is practically impossible to control May cause structural damage Airplane may be mo...

Page 479: ...prior to additional flight A roll cloud ahead of a squall line or thunderstorm is visible evidence of extreme turbulence however the absence of a roll cloud should not be interpreted as denoting that severe turbulence is not present Even though flight in severe turbulence must be avoided flight in turbulent air may be encountered unexpectedly under certain conditions The following recommendations ...

Page 480: ...change veloc ityand direction If necessary to avoid excessive airspeeds lower the landing gear WIND SHEAR Wind shears are rapid localized changes in wind direction which can occur vertically as well as horizontally Wind shear can be very dangerous to all airplanes large and small particularly on approach to landing when airspeeds are slow A horizontal wind shear is a sudden change in wind directio...

Page 481: ...t over 1 hour Occasional use of deicing anti icing equipment removes prevents accumulation It does not present a problem if the deicing anti icing equipment is used The rate of accumulation is such that even short encounters become poten tially hazardous and use of deicing anti icing equipment or diversion is necessary The rate of accumulation is such that deicing anti icing equipment fails to red...

Page 482: ...here icing conditions might be expected inspect the airplane and review the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual to be certain that you are supported by the full complement of required IFR and deicing anti icing equip ment Remember that regardless of its combination of deicinglanti icing equipment any airplane not fully equipped and func tional for IFR flight is not p...

Page 483: ...the same reasons that airplanes however designed or equipped for IFR flight cannot be flown safely into conditions such as thunderstorms tornadoes hurri canes or other phenomena likely to produce severe turbu lence airplanes equipped for flight in icing conditions cannot be expected to cope with Severe icing conditions as defined by the National Weather Service The prudent pilot must remain alert ...

Page 484: ...ly to build up on the unprotected areas the fuselage and unpro tected wing leading edge inboard of the engine nacelle Under some atmospheric conditions it may even build up aft of the boots despite the maintenance of the prescribed rnlnl mum speed The effect of ice accumulation on any unpro tected surface is aggravated by length of exposure to the icing conditions Ice buildup on unprotected surfac...

Page 485: ...l of the airplane prior to landing In no case should this be less than the minimum altitude specified in the Autopilot Airplane Flight Manual Supplement Observe the procedures set forth in your Pilot s Operating Handbook and FAA Approved Airplane Flight Manual during operation in icing conditions Activate your deice and anti icing systems before entering an area of moisture where you are likely to...

Page 486: ...inexperienced or uneducated pilot who presses on regardless hoping that steadily worsening conditions will improve only to find him self flying an airplane which has become so loaded with ice that he can no longer maintain altitude At this point he has lost most if not all of his safety options including perhaps a 180 degree turn to return along the course already traveled The responsible and well...

Page 487: ...ulence may extend to as much as 20 miles from the echo edge The intensity of the radar echo from hail varies with the size and nature of the hailstone A hailstone with a wet surface gives a strong radar return while a dry hailstone gives a relatively weak return Avoid intense or extreme level echoes by at least 20 miles that is such echoes should be separated by at least 40 miles before you fly be...

Page 488: ...requent lightning indicates the probability of a severe thunderstorm 8 Do regard as extremely hazardous any thunderstorm with tops 35 000 feet or higher whether the top is visu ally sighted or determined by radar If you cannot avoid penetrating a thunderstorm the follow ing are some do s BEFORE entering the storm 9 Tighten your safety belt put on your shoulder harness and secure all loose objects ...

Page 489: ...in and below the rotor zone which is usually 8 to 10 miles down wind from the ridge This zone is sometimes characterized by the presence of roll clouds if sufficient moisture is present altocumulus standing lenticular clouds are also vis ible signs that a mountain wave exists but their presence is likewise dependent on moisture Mountain wave turbulence can of course occur in dry air and the absenc...

Page 490: ...sely populated country can be the same as IFR and must be avoided by inexperienced or non IFR rated pilots VERTIGO DISORIENTATION Disorientation can occur in a variety of ways During flight inner ear balancing mechanisms are subjected to varied forces not normally experienced on the ground This com bined with loss of outside visual reference can cause ver tigo False interpretations illusions resul...

Page 491: ...rk load of flying by refer ence to his instruments is augmented by such factors as turbulence Even an instrument rated pilot encountering instrument conditions intentional or unintentional should ask himself whether or not he is sufficiently alert and profi cient in the airplane he is flying to fly under low visibility conditions and in the turbulence anticipated or encountered If any doubt exists...

Page 492: ...fully deflected above maximum maneuvering speed Turbulence penetration should not be performed above that speed The accidents we are discussing here occur at airspeeds greatly in excess of these limitations No airplane should ever be flown beyond its FAA approved operating limitations FLIGHT OF MULTI ENGINE AIRPLANES WITH ONE ENGINE INOPERATIVE The major difference between flying a twin engine and...

Page 493: ...t Yaw forces must be balanced with the rudder Loss of power on one engine also reduces airflow over the wing causing a roll toward the dead engine which must be balanced with the aileron The net result of these forces cause the airplane to sideslip slightly toward the dead eng ine This sideslip may be balanced by banking slightly up to 5 into the operating engine In the event of an engine failure ...

Page 494: ...ees heading change and thereafter maintain straight flight with not more than 5 degrees of bank if one engine fails suddenly with Takeoff power on both engines Rearmost allowable center of gravity Flaps in takeoff position Propeller windmilling in takeoff pitch configuration However sudden engine failures rarely occur with all factors listed above and therefore the actual VMCA in any particu lar s...

Page 495: ...ter rain and with power reduction on one engine made at or above VSSE ONE ENGiNE INOPERATIVE BEST RATE OF CLIMB SPEED VYSE VYSE is designated by the blue radial on the airspeed indi cator VYSE delivers the greatest gain in altitude in the short est possible time and is based on the following criteria Critical engine inoperative and its propeller in the mini mum drag position Operating engine set a...

Page 496: ...SE SINGLE ENGINE SERVICE CEILING The single engine service ceiling is the maximum altitude at which an airplane will climb at a rate of at least 50 feet per minute in smooth air with one engine inoperative The single engine service ceiling chart should be used dur ing flight planning to determine whether the airplane as loaded can maintain the Minimum En Route Altitude MEA if IFR or terrain cleara...

Page 497: ...ting engine to achieve rated performance Another note of caution Be sure to identify the dead eng ine positively before securing it Remember First identify the suspected engine Le Dead foot means dead eng ine second verify with cautious throttle movement then secure ENGINE FAILURE ON TAKEOFF If an engine fails before attaining lift off speed or below YMCA the only proper action is to discontinue t...

Page 498: ...irspeed will give you better engine cool ing increased inflight visibility and better fuel economy However at first indication of an engine failure during climb out or while on approach establish VYSE or VXSE which ever is appropriate Consult your Pilot s Operating Hand book and FAA Approved Airplane Flight Manual for specif lcs STALLS SLOW FLIGHT AND TRAINING The stall warning system must be kept...

Page 499: ...e conducted in multi engine airplanes by other than qualified engineering test pilots Ymca STALL FIRST SPEED w o r H t J W 0 fJ fJ W e t 0 INDICATED AIRSPEED RELATIONSHIP BETWEEN STALL SPEED AND Ymca FOR AIRCRAFT WITH NORMALLY ASPIRATED ENGINES C93THOOCOl04 C Engine out minimum control speed generally decreases with altitude while the single engine stall speed remains approxi mately constant for n...

Page 500: ... s Operating Handbook and FAA Approved Airplane Flight Manual for your airplane This procedure calls for simulating one engine inoperative by reducing the power level throttle on one engine to idle while operating at an airspeed above VSSE Power on the other engine is set at maximum then airspeed is reduced at approximately one knot per second until either YMCA or stall warning is obtained During ...

Page 501: ... uncontrollable in a spin since its performance characteristics beyond cer tain limits specified in the FAA regulations may not have been tested and are unknown This is why airplanes are placarded against intentional spins and this is why stall avoidance is your protection against an inadvertent spin Pilots are taught that intentional spins are entered by delib erately inducing a yawing moment wit...

Page 502: ...neutral ize all controls and execute a smooth pullout Ailerons should be neutral during recovery THE LONGER THE PILOT DELAYS BEFORE TAKING CORRECTIVE ACTION THE MORE DIFFICULT RECOVERY WILL BECOME Always remember that extra alertness and pilot techniques are required for slow flight maneuvers including the practice or demonstration of stalls or YMCA In addition to the forego ing mandatory procedur...

Page 503: ...f an airplane flown under instrument conditions is permitted to stall or enter a spin the pilot without reference to the horizon is certain to become disoriented He may be unable to recognize a stall spin entry or the spin condition and he may be unable to determine even the direction of the rotation Finally never forget that stall avoidance is your best protection against an inadvertent spin MAIN...

Page 504: ...will be Wing tip vortices from large heavy airplanes are very severe at close range degenerating with time wind and distance These are rolling in nature from each wing tip In tests vor tex velocities of 133 knots have been recorded Encounter ing the rolling effect of wing tip vortices within two minutes after passage of large airplanes is most hazardous to light airplanes This roll effect can exce...

Page 505: ...riction Snow and ice covered runways are also hazardous The pilot should also be alert to the possibility of the brakes freezing Use caution when taking off or landing during gusty wind conditions Also be aware of the special wind conditions caused by buildings or other obstructions located near the runway MEDICAL FACTS FOR PILOTS GENERAL When the pilot enters the airplane he becomes an integral p...

Page 506: ...ystem to let you know when you are not getting enough oxygen It is impossible to predict when or where hypoxia will occur during a given flight or how it will manifest itself Some of the common symptoms of hypoxia are increased breathing rate a Iight headed or dizzy sensation tingling or warm sensation sweating reduced visual field sleepiness blue coloring of skin fingernails and lips and behavior...

Page 507: ... 1 2 minutes There fore in the event of depressurization oxygen masks should be used immediately Should symptoms occur that cannot definitely be identified as either hypoxia or hyperventilation try three or four deep breaths of oxygen The symptoms should improve markedly if the condition was hypoxia recovery from hypoxia is rapid Pilots who fly to altitudes that require or may require the use of s...

Page 508: ...s at nominal cost Information regarding this training may be obtained by request from the Chief Civil Aeromedical Institute Attention Aeromedical Education Branch AAC 140 Mike Monroney Aeronautical Center P O Box 25082 Oklahoma City Okla homa 73125 HYPERVENTILATION Hyperventilation or overbreathing is a disturbance of respi ration that may occur in individuals as a result of emotional tension or a...

Page 509: ...f visual fields Decreased ability to see under dim illuminations Loss of efficiency of sense of touch Decrease of memory and reasoning ability Increased susceptibility to fatigue and decreased atten tion span Decreased relevance of response Increased self confidence with decreased insight into immediate capabilities Tests have shown that pilots commit major errors of judg ment and procedure at blo...

Page 510: ...y drug that affects the per son s faculties in any way contrary to safety or 4 While having 04 percent by weight or more alcohol in the blood b Except in an emergency no pilot of a civil air craft may allow a person who appears to be intoxi cated or who demonstrates by manner or physical indications that the individual is under the influence of drugs except a medical patient under proper care to b...

Page 511: ... of carbon monoxide results in hypoxia which will affect night vision in the same manner and extent as hypoxia from high altitudes Even small levels of carbon monoxide have the same effect as an altitude increase of 8 000 to 10 000 feet Smoking several cigarettes can result in a carbon monoxide saturation sufficient to affect visual sensitivity equal to an increase of 8 000 feet altitude DECOMPRES...

Page 512: ...pilot should immediately descend if it is suspected that this condition exists since the effects will only worsen with continued exposure to the reduced pressure environment at altitude and could result if uncorrected iii complete incapacitation The possibility of decompression sickness can be greatly reduced by pre breathing oxygen prior to flight and by com mencing oxygen breathing well below th...

Page 513: ...ms is even more remarkable Radar RNAV LORAN sophisticated autopilots and other devices which just a few years ago were too large and pro hibitively expensive for general aviation size airplanes are becoming increasingly commonplace in even the smallest airplanes It is thus that this Safety Information is directed to the pilot for it is in the area of the skill and proficiency of you the pilot that...

Page 514: ...Section X Safety Information ft Twin Engine Piston THIS PAGE INTENTIONALLY LEFT BLANK 10 64 May 1994 ...

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