BEECHCRAFT Baron 58

i n smooth air and then only with caution. January 1983 1-15 Section I General BEECHCRAFT Baron 58 Serial TH 1thru TH 772 V~ Stalling Speed or the minimum steady flight speed at which the airplane is controllable. V~~ Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration. V~ Best Angle-of-Climb Speed is the airspea which delivers the greatest gain of altitude in the shortest possible horizontal distance. 'Y Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. METEOROLOGICAL TERMINOLOGY ISA International Standard Atmosphere in which (1) The air is a dry perfect gas; (2) The temperature at sea level is 15O C e l s i ~ s ' ( 5 9 ~ Fahrenheit); (3) The pressure at sea level is 29.92 in. Hg (.I013.2 millibars); (4) The temperature gradient from sea level to the altitude at which the temperature is -56.5O C (-69.7O F) is -0.0019 8 O C (-0.003566O F) per foot and zero above that altitude. OAT Outside Air Temperature is the free air static temperature, obtained either from inflight temperature indications adjusted for instrument error and compressibility effects, or ground meteorological sources. January 1983 BEECHCRAFTBaron 58 Serial TH 1thruTH 772 Section I General Indicated The number actually read from an Pressure altimeter when the barometric sub- Altitude scale has been set to 29.92 in. Hg (101 3.2 millibars). Pressure Altitude measured from standard Altitude sea-level pressure (29.92 in. Hg) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. In this Handbook, altimeter instrument errors are assumed to be zero. Position errors may be obtained.from the Altimeter Correction chart. Station Actual atmospheric pressure at field 1 Pressure elevation. II Wind The wind velocities recorded as I I variables on the charts of this hand- I I book are to be understood as the head- wind or tailwind components of the reported winds. POWER TERMINQLOGY Take-off The highest power rating to be used for takeoff. Maximum The highest power rating not limited by Continuous time. To be used only for conditions which warrant the use of this rating. Cruise Power recommended for cruise climb. Climb a Maximum The highest power settings recom- Cruise mended for cruise. January 1983 1-17 Section I General BEECHCRAFT Baron 58 Serial TH 1thru TH 772 Recommended Intermediate power settings Cruise for which cruise power settings are presented. Economy The lowest power setting for which Cruise cruise power settings are presented. ENGINE CONTROLS AND INSTRUMENTS TERMINOLOGY Throttle Control Propeller Control Mixture Control Propeller Governors The lever &ed to 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 maintain the selected rpm requested by the propeller control levers. Manifold An instrument that measures the ab- Pressure solute pressure in the intake manifold Gage of an engine, expressed in inches of mercury (in. Hg). Tachometer An instrument that indicates the ro- tational speed of the propeller (and en- gine) in revolutions per minute (rprn). 1-18 January 1983 BEECHCRAFT Baron 58 Serial TH 1thru TH 772 Section I General AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb The ratio of the change Gradient i n height during a portion of a climb, to the horizontal distance traversed i n the same time interval. Demonstrated The demonstrated crosswind veloc- Crosswind ity is the velocity of the crosswind Velocity component for which adequate con- trol of tQe airplane during takeoff and landing was actually demon-.. -,, strated during certification tests. The value shown is not limiting. Accelerate- The distance required to accelerate to Stop Distance a specified speed and, assuming failure of an engine at the instant that speed is attained, to bring the airplane to a stop. Accelerate- The distance required to accelerate to Go Distance a specified speed and, assuming failure of an engine at the instant that speed is attained, feather inoperative propeller and continue takeoff on the remaining engine to a height of 50 feet. MEA Minimum enroute IFR altitude. Route A part of a route. Each end of that Segment part is identified by: (1) a geograph- ical location; or (2) a point at which a definite radio fix can be established. GPH U.S. Gallons per hour, January 1983 1-19 Section l BEECHCRAFT Baron 58 General Serial TH 1thru TH 772 Reference A n imaginary vertical plane from Datum which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage usually given in terms of distance from the reference datum. Arm The horizontal distance from the ref- erence datum to the center of gravity (C.G.) of an item. I Moment Airplane Center of Gravity (C.G.) C.G. Arm The product of the weight of an item multiplied by .its arm. (Moment divided by a constant is used to simplify bal- ance calculations by reducing the number of digits.) The point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the t o t d weight of the airplane. The arm obtained by adding the air- plane's individual moments and dividing the sum by the total weight. C.G. Limits The extreme center of gravity loca- tions within which the airplane must be operated at a given weight. Unusable Fuel Fuel remaining after a runout test has been completed in accordance with governmental regulations. January 1983 BEECHCRAFT Baron 58 Serial TH 1thru TH 772 Section I General Usable Fuel Fuel available for flight planning. Standard Weight of a standard airplane Empty including unusable fuel, full Weight operating fluids and full oil. Basic Standard empty weight plus Empty optional equipment. Weight Payload Weight of occupants, cargo and baggage. Useful Difference between ramp weight Load and basil: emljty weight. Maximum Maximum weight approved for ground Ramp maneuvering. (It includes weight of Weight start, taxi, and run up fuel). Maximum Maximum weight approved for the Take-off start of the take off run. . Weight Maximum Maximum weight approved for the Landing landing touchdown. Weight Zero Fuel Weight exclusive of usable fuel. Weight January 1983 Section l General . BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 INTENTIONALLY LEFT BLANK January 1983 BEECHCRAFT Baron 58 SerialTH 1 thruTH 772 SECTION II LIMITATIONS TABLE OF CONTENTS SUBJECT PA GE Airspeed Limitations ............................. 2-3 Airspeed Indicator Markings ..................... 2-4 Power Plant Limitations ......................... 2-5 Engines ..................................... 2-5 Fuel ........................................ 2-5 Oil ........................................... 2-5 Propellers ................................... 2-6 ................. Starters .Time for Cranking 2-6 ................ Power Plant Instrument Markings 2-7 Miscellaneous Instrument Markings .............. 2-8 Weights ........................................ 2-8 CG Limits ....................................... 2-9 Maneuver Limits ................................ 2-9 Flight Load Factors (5400 Pounds) .............. 2-10 Minimum Flight Crew . ,........................ 2-10 Kinds of Operation ............................. 2-10 Fuel ........................................... 2-11 Oxygen Requirements .......................... 2-11 Maximum Passenger Seating Configuration ................................ 2-11 Seating ........................................ 2-11 Placards ................................. 2-1 2 .2-22 Required Equipment for Various Conditions of Flight .......................... 2-23 January 1983 . Section II Limitations BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 INTENTIONALLY LEFT BLANK January 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 ' Section II Limitations The limitations included in this section have been approved by the Federal Aviation Administration and must be observed in the operation of this airplane. AIRSPEED LIMITATIONS January 1983 2-3 except i n smooth air and then only Maximum Flap Extension/ Extended VFE (Approach 15 O ) (Full down 30°) Maximum Landing Gear Operating Extended V~~ and V~~ Air Minimum Control speed V~~~ Maximum With Utility Doors Removed 152 122 152 81 174 175 114 175 93 200 Do not extend flaps or operate with flaps ex- tended above this speed - Do not extend, retract or operate with landing gear extended above this speed Minimum speed for directional controllability aftar sudden loss of engine Utility door re- moval kit must be installed , 152 122 152 81 174 175 140 175 93 200 ?' f- w P 3. @ 'AIRSPEED INDICATOR MARKINGS z z. z. 5 C (Y a c 0 -a -(I) m Ul rn s.g = z 1 g d D * n = 4 SIGNIFICANCE Full Flap Operating Range One-Engine-Inoperative Best Rate-of-Climb Speed Normal Operating Range Operate with caution only in smooth air Maximum speed for ALL operations MARKING White Arc Blue Radial Green Arc Yellow Arc Red Radial *The Airspeed Indicator is marked in CAS values Z m A (D 2;w q = 0 '*I UI N QO CAS KNOTS 72-122 1 0 0 83-195 195-223 223 IAS M PH 83-140 115 95-225 225-257 257 KNOTS 74-122 100 84-195 195-223 223 MPH 85-140 13 5 96-225 225-257 257 BEECHCRAFT Baron 58 SerialTH 1thruTH 772 Section II Limitations POWER PLANT LIMITATIONS ENGINES Two Continental 10-520-C fuel injected, air cooled six- cylinder, horizontally opposed engines each rated at 285 horsepower at 2700 rpm. i Take-off and Maximum ! continuous power ............ Full throttle, 2700 rpm : .......... Maximum Cylinder Head Temperature 460°F ..................... Maximum Oil Temperature 240°F ............. Minimum Take-off Oil Temperature 75OF Minimum Oil Pressure (Idle) ................... 30 psi Maximum Oil Pressure ...................... 100 psi FUEL Aviation Gasoline 1OOLL (blue) preferred, 1 0 0 (green) minimum grade. OIL Ashless Dispersant oils must meet latest revision of Teledyne Continental Motors Corporation Specification MHS-24. Refer to Approved Engine Oils, Section VIII, HANDLING, SERVICING, and MAINTENANCE. January 1983 2-5 Section II Limitations BEECHCRAFT Baron 58 Serial TH 1thru TH 772 PROPELLERS HARTZELL 2 Blade Hubs: BHC-J2YF-2CF Blades: FC8475-6 Pitch Setting at 30 inch.Station: Low 14.5O; Feathered 80:0° Diameter: 78 inches maximum, 76 inches minimum 3 Blade Hubs: PHC-J3YF-2F Blades: FC7663-2R Pitch Setting at 3 0 inch Station: Low 13.0°; Feathered 82.0° Diameter: 76 inches maximum, 74 inches minimum 2 Blade Hubs: D2AF34C30 Blades: 78FF-0 Pitch Setting at 30 inch Station: Low 15.0"; Feathered 7.9.0° Diameter: 78 inches maximum, 76 inches minimum 3 Blade Hubs: D3AF32C35 Blades: 82NB-6 Pitch Setting at 30 inch Station: Low 14.0" f .2O; Feathered 81.2O f 3 O Diameter: 76 inches, no cut-off permitted STARTERS - TIME FOR CRANKING Do not operate starter continuously for more than 30 sec- onds. Allow starter to cool before cranking again. 2-6 January 1983 BEECHCRAFT Baron 68 Serial TH 1thru TH 772 Section II Limitations POWER PLANT INSTRUMENT MARKINGS , OIL TEMPERATURE Caution (Yellow Radial) ..................... 75OF Operating Range (Green Arc) ....................... 75" to 240°F Maximum (Red Radial) ..................... 240°F OIL PRESSURE Minimum (Red Radial) ..................... 30 psi Operating Range (Green Arc) ......... 30 to '60 psi Maximum (Red Radial) .................... 100 psi FUEL FLOW AND PRESSURE .................... Minimum (Red Radial) 1.5 psi Cruise Power (Green Arc) .... 9.7 gph to 17.0 gph Take-off and Climb Power (Wide Green Arc) .......... 17.8 gph to 24.3 gph Maximum (Red Radial) ................... 17.5 psi MANIFOLD PRESSURE Operating Range ................... (Green Arc) 15 to 29.6 in. Hg ................ Maximum (Red Radial) 29.6 in. Hg TACHOMETER Operating Range (Green Arc) ... 2000 to 2700 rpm Maximum (Red Radial) ................. 2700 rpm CYLINDER HEAD TEMPERATURE Operating Range (Green Arc) ...................... 200° to 460°F Maximum (Red Radial) .............................. 460°F January 1983 2-7 Section II Limitations BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 MISCELLANEOUS INSTRUMENT MARKINGS INSTRUMENT PRESSURE ............. Caution (Yellow Arc) 2.5 to 3.5 in. Hg Normal (Green Arc) .............. 3.5 to 5.5 in. Hg ............. Caution (Yellow Arc) 5.5 to 6.5 in. Hg Red Button Source Failure lndicators or Normal (Green Arc) ... ,.......... 4.3 to 5.9 in. Hg Red Button Source Failure lndicators PROPELLER DEICE AMMETER Normal Operating Range (Green Arc) ........... , . . 7 to 12 amps (2 blade) Normal Operating Range (Green Arc) ............. 14 to 18 amps (3 blade) FUEL QUANTITY Yellow Arc .......................... E to 1/8 Full II WEIGHTS 58 .............. Maximum Ramp Weight 5424 lbs ............ Maximum Take-Off Weight 5400 lbs ............ Max~mumLanding Weight 5400 Ibs 58A Maximum Ramp We~ght 5014 Ibs i .............. ............ Maximum Take-Off Weight 4990 lbs ............ Maximum Landing Weight 4990 lbs Maximum Baggagelcargo Compartment Weights: Main Cabin Compartment (less occupants and equipment) ......... 400 lbs Extended Aft Compartment ............... 120 lbs Nose Compartment (baggage less equipment) ............................. 300 lbs Refer to Weight and Balance section for additional information. 2-8 January 1983 BEECHCRAFT Baron 5 8 Serial TH 1 thru TH 7 7 2 Section II Limitations Baron 58 Forward Limits: 74 inches aft of datum at 4200 lbs and under, then straight line variation to 78.0 inches aft of datum at gross weight of 5400 lbs. Aft Limits: 86 inches aft of datum at all weights. Baron 58A Forward Limits: 74 inches aft of datum a t 4200 lbs and under, then straight line variation to 76.6 inches aft of datum at gross weight of 4990 lbs. Aft Limits: 86 inches aft of datum a t all weights. REFERENCE DATUM 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. MANEUVER LIMITS This is a normal category airplane. Acrobatic maneuvers, including spins, are prohibited. January 1983 2-9 Section I1 Limitations BEECHCRAFT Baron 58 Serial TH 1thru TH 772 FLIGHT LOAD FACTORS (5400 POUNDS) Positive maneuvering load factors: Flaps Up ................................... 4.2G ................... Flaps Down ........... .'. 2.OG MINIMUM FLIGHT CREW . . . . . . . . . . . . . . One ( I ) Pilot KINDS OF OPERATION LIMITS This airplane is approved for the following type operations when the required equipment is installed and operat~onal as defined herein: 1. VFR day and night 2. IFR day and night i 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. March, 1988 BEECHCRAFT Baron 58 SerialTH 1 thru TH 772 Section II Limitations FUEL TOTAL FUEL with left and right wing fuel systems full: Standard Fuel System ............................ Capacity 142 Gallons .............................. Usable 136 Gallons Optional Fuel System .................... Capacity ....... : 172 Gallons Usable .............................. 166 Gallons ............................. Capacity 200 Gallons Usable .............................. 194 Gallons Do not take off if Fuel Quantity Gages indicate in Yellow Arc or with less than 13 gallons in each wing fuel system. The fuel crossfeed system to be used during emergency conditions in level flight only. Maximum slip duration: 30 seconds OXYGEN REQUIREMENTS Refer to'FAR 91 for oxygen requirements. MAXIMUM PASSENGER SEATING CONFIGURATION Five (5) passengers and one (1) pilot SEATING All seats must be in the upright position for takeoff and landing. January 1983 2-11 BEECHCRAFT Baron 58 SerialTH 1thruTH 772 SECTION Ill EMERGENCY PROCEDURES TABLE OF'CONTENTS I SUBJECT PAGE I ........................... Emergency Airspeeds 3-3 i . .................... One Engine Operation * . 3-3 Determining Inoperative Engine 3-4 II .................. .............. One-Engine Inoperative Procedures 3-4 ............... Engine Failure During Take-Off 3-4 Engine Failure After Lift-off and I In Flight .................................. 3-5 I ! Air Start ........................................ 3-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Fire 3-7 Ground ..................................... 3-7 i! In Flight .................................... 3-7 Emergency Descent ............................. 3-7 IGlide .......................................... 3-8 i Landing Emergencies ............................ 3-8 Gear Up Landing ............................ 3-8 One-Engine Inoperative Landing .............. 3-9 II One-Engine Inoperative Go-Around ........... 3-9 Systems Emergencies .......................... 3-1 0 One-Engine lnoperative Operation on Crossfeed ................................ 3-10 Electrical Smoke or Fire .................... 3-10 Illumination of Alternator-Out Light .......... 3-1 1 ! I Unscheduled Electric Elevator Trim .......... 3-12 Landing Gear Manual Extension ............. 3-1 2 January 1983 3-1 Section Ill BEECHCRAFT Baron 58 Emergency Procedures SerialTH 1 thruTH 772 TABLE OF CONTENTS (Continued) SUBJECT PAGE Landing Gear Retraction After Practice Manual Extension ................ Ice Protection .............................. Surface Deice System ................... Electrothermal Propeller Deice System ................................ Alternate (Emergency) Static Air ........................ Source System Emergency Exits ............................ Unlatched Door in Flight ..................... ~irnulatedOne-Engine Inoperative .............. Spins ...................... .. ................. January 1983 I BEECHCRAFT Baron 58 Section Ill Serial TH 1thru TH 772 Emergency Procedures A l l airspeeds quoted in this section are indicated airspeeds (IASJ and assume zero instrument error. EMERGENCY AIRSPEEDS Air Minimum Control Speed (VMCA) ... 81 kts/93 mph Intentional One-Engine Inoperative Speed (VSSE) .......... 86 kts/99 mph Best Rate-of-Climb Speed One-Engine Inoperative (Vy) .... 100 k t s / l l 5 mph Best Angle-of-Climb Speed One-Engine Inoperative (V)o ..... 96 kts/l 11 mph Landing - One Engine Inoperative: Maneuvering to Final Approach (minimum) ........... 100 k t s / l l 5 mph Final Approach (minimum) ....... 9 0 kts/l04 mph The following information is presented to enable the pilot to form, i n advance, a definite plan of action for coping with the most probable emergency situations which could occur in the operation of the airplane. Where practicable, the emergencies requiring immediate corrective action are treated in check list form for easy reference and familiari- zation. Other situations, in which more time is usually per- mitted to decide on and execute a plan of action, are discussed at some length. In order to supply one safe speed for each type of emergency situation, the airspeeds presented were derived at 5400 lbs. ONE ENGINE OPERATION Two major factors govern one engine operations; airspeed and directional control. The airplane can be safely maneu- vered or tr~mmedfor normal hands-off operation and sustained in this configuration by the operative engine AS LONG AS SUFFICIENT AIRSPEED IS MAINTAINED. January 1983 3-3 Section Ill BEECHCRAFT Baron 58 Emergency Procedures Serial TH 1thru TH 772 DETERMINING INOPERATIVE ENGINE The following checks will he$ determine which engine has failed. 1. DEAD FOOT - DEAD ENGINE. The rudder pressure re- quired to maintain directional control will be on the side of the good engine. 2.THROTTLE. Partially retard the throttle for the engine that is believed to be inoperative; there should be no change in control pressores 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 often indicate near normal readings. ONE-ENGINE INOPERATIVE PROCEDURES ENGINE FAILURE DURING TAKE-OFF 1. Throttles - CLOSED 2. Braking - MAXIMUM if insufficient runway remains.for stopping: 3. Fuel Selector Valves - OFF 4. Battery, Alternator, and Magnetoptart Switches - OFF 3-4 January 1983 BEECHCRAFT Baron 58' Section Ill SerialTH 1thru TH 772 Emergency Procedures ENGINE FAILURE AFTER LIFT-OFF AND IN FLIGHT An immediate landing is advisable regardless of take-off I I weight. Continued flight cannot be assured if take-off I weight exceeds the weight determined from the TAKE-OFF I i WEIGHT graph. Higher take-off weights will result in a loss 1 of altitude while retracting the landing gear and feather- ! ing the propeller. Continued flight requires immediate pilot response to the following procedures. I 1. Landing Gear and Flaps - UP 2. Throttle (inoperative engine) - CLOSED 3. Propeller (inoperative4engine) - FEATHER 4. Power (operative engine) - AS REQUIRED 5. Airspeed - MAINTAIN SPEED AT ENGINE FAILURE (100 KTS/116 MPH MAX.) UNTIL OBSTACLES ARE CLEARED. ! After positive control o f the airplane is established: I 6. Secure inoperative engine: I a. Mixture Control - IDLE CUT-OFF b. Fuel Selector - OFF c. Auxiliary Fuel Pump - OFF 1 d. Magnetofitart Switch - OFF , e. Alternator Switch - OFF f. Cowl Flap - CLOSED 7. Electrical Load - MONITOR (Maximum load of 1.0 on remaining eng~ne) NOTE The most important aspect of engine failure is the necessity to maintain lateral and direc- tional control. If airspeed is below 81 kts (93 mph), reduce power on the operative engine as required to maintain. control. Refer to the SAFETY INFORMATION Section for additional information regarding pilot technique. January 1983 3-5 Section Ill BEECHCRAFT Baron 58 Emergency Procedures Serial TH 1thru TH 772 AIR START CAUTION The pilot should determine the reason for en- gine failure before attempting an air start. 1. Fuel Selector Valve - ON 2. Throttle - SET approximately 1/4 travel 3. Mixture Control - FULL RICH, below 5000 ft (112 travel above 5,000 ft) 4. Aux Fuel Pump - LOW ' 5. Magnetos - CHECK ON 6. Propeller: WITH UNFEA THERING ACCUMULA TORS: a. Move propeller control full forward to accomplish unfeathering. Use starter momentarily if necessary. b. Return control to high pitch (low rpm) position, when windmiliing starts, to avoid overspeed. If propeller does not unfeather or engine does not turn, proceed to WITHOUT UNFEA THERING ACCUMULATORS procedure. WITHOUT UNFEA THERING ACCUMULA TORS: a. Move propeller control forward of the feathering detent to midrange b. Engage Starter to accomplish unfeathering c. If engine fails to run, clear engine by allowing it to windmill with mixture in IDLE CUT-OFF. When engine fires, advance mixture to FULL RICH 7. When Engine Starts - ADJUST THROTTLE, PRO- PELLER and MIXTURE CONTROLS 8. Aux Fuel Pump - OFF (when reliable power has been regained) 3-6 January 1983 BEECHCRAFT Baron 58 Section Ill Serial TH 1thru TH 772 Emergency Procedures 9. Alternator Switch - ON 10. Oil Pressure - CHECK' 11. Warm Up Engine (approximately 2000 rpm and 15 in. Hg) 12. Set power as required and trim ENGINE FIRE ON THE GROUND 1. Mixture Controls - IDLE CUT-OFF 2. Continue to crank affected engine 3. Fuel Selector Valves - OFF 4. Battery and Alternator Switches - OFF 5. Extinguish with Fire Extinguisher IN FLIGHT Shut down the affected engine according to the following procedure and land immediately. Follow the applicable I single-engine procedures in this section. I 1. Fuel Selector Valve - OFF 2. Mixture Control - IDLE CUT-OFF 3. Propeller - FEATHERED 4. Aux Fuel Pump - OFF 5. Magnetofitart Switch - OFF 6. Alternator Switch - OFF EMERGENCY DESCENT 1. Propellers - 2700 RPM 2. Throttles - CLOSED 3. Airspeed - 152 kts (175 mph) 4. Landing Gear - DOWN 5. Flaps - APPROACH (1so) January 1983 Section Ill BEECHCRAFT Baron 58 Emergency Procedures Serial TH 1thruTH 772 GLIDE 1. Propellers - FEATHER 2. Flaps - UP 3. Landing Gear - UP 4. Cowl Flaps - CLOSED The glide ratio in this configuration is approximately 2 nautical miles of gliding distance for each 1000 feet of altitude above the terrain at an airspeed of 120 kts (138 mph). . LANDING EMERGENCIES GEAR-UP LANDING If possible, choose firm sod or foamed runway. When assured of reaching landing site: 1. Cowl Flaps - CLOSED 2. Wing Flaps - AS DESIRED 3. Throttles - CLOSED 4. Fuel Selectors - OFF 5. Mixture Controls - IDLE CUT-OFF 6. Battery, Alternator and Magnetcystart Switches - OFF 7. Keep wings level during touchdown. 8. Get clear of the airplane as soon as possible after it stops. NOTE The gear up landing procedures are based on the best available information and no actual tests have been conducted. 3-8 January 1983 BEECHCRAFT Baron 58 Section Ill Serial TH 1thru TH 772 Emergency Procedures ONE ENGINE INOPERATIVE LANDING On final approach and when it is certain that the field can be reached 1. Landing Gear - DOWN 2. Flaps - APPROACH (15O) 3. Airspeed - 90 kts/l04 mph 4. Power - AS REQUIRED to maintain 800 Wmin rate of descent When it is certain there is no possibility of go-around: 5 . Flaps - DOWN 6. Execute normal landing ONE ENGINE INOPERATI'VE GO-AROUND WARNING Level flight might not be possible for certain combinations of weight, temperature and alti- tude. In any event, DO NOT anernpt a one engine inoperative go-around after flaps have been fully extended. 1. Power - MAXIMUM ALLOWABLE 2. Landing Gear - UP 3. Flaps - UP 4. Airspeed - MAINTAIN 100 kts (1 15 mph) MINIMUM January 1983 3-9 Section Ill Emergency Procedures BEECHCRAFT Baron 58 Serial TH 1thm TH 772 SYSTEMS EMERGENCIES ONE-ENGINE INOPERATIVE OPERATION ON CROSSFEED NOTE The fuel crossfeed system is to be used only during emergency cond.itions i n level flight only. Left engine inoperative: 1. Right Aux Fuel Pump - LOW 2. Left Fuel Selector Valve - OFF 3. Right Fuel Selector Valve - CROSSFEED 4. Right Aux Fuel Pump - LOW or OFF as required Right engine inoperativet 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 flight instruments will become inoperative. 2. Oxygen - AS REQUIRED 3. All Electrical Switches - OFF 4. Battery and Alternator Switches - ON January 1983 BEECHCRAFT Baron 58 Section Ill SerialTH 1 thru TH 772 Emergency Procedures 5. Essential Electrical Equipment - ON (Isolate defective equipment: NOTE Ensure fire is out and will not be aggravated by draft. Turn off CABIN HEAT switch and push in the CABIN AIR control. Open pilot's storm window, if required. ILLUMINATION OF ALTERNATOR OUT LIGHT 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 I b. Regulate load In the event of the illumination of both AL TERNATOR OUT lights: 1. Check loadmeters for load indication a. No load indicates failure of regulator (1) Switch regulators (2) System should indicate normal b. If condition recurs (1) Switch to original regulator (2) System returns to normal, indicates overload condition causing malfunction (3) Reduce load c. If condition indicates malfunction of both alter- nator circuits (1) Both ALT Switches - OFF (2) Minimize electrical load since only battery power will be available January 1983 3-11 Section Ill BEECHCRAFT Baron 58 Emergency procedures Serial TH 1thru TH 772 UNSCHEDULED ELECTRIC ELEVATOR TRIM Incorporated in the system is an emergency release button located on the left handle grip of the pilot's control wheel. This button can be depressed to deactivate the system quickly i n case of a malfunction i n the system. The system will remain deactivated o n l i 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 POSITION 3. Trim - MANUALLY RE-TRIM AIRPLANE 4. Electric Trim - OFF 5. Trim Release - RELEASE 6. Circuit Breaker - PULL NOTE Do not attempt to operate the electric trim system until the cause of the malfunction has been determined and corrected. LANDING GEAR MANUAL EXTENSION Reduce airspeed before attempting manual extension of the landing gear. 1. LDG GR MOTOR Circuit Breaker - PULL 2. Landing Gear Handle - DOWN 3. Remove cover from handcrank at rear of front seats. Engage handcrank and turn counterclockwise as far as possible (approximately 50 turns). Stow handcrank. 4. If electrical system is operative, check landing gear po- sition lights and warning horn (check LDG GR RELAY circuit breaker engaged.) January 1983 BEECHCRAFT Baron 58 Section Ill SerialTH 1thruTH 772 Emergency Procedures CAUTION The manual extension system is designed only to lower the landing gear; do not attempt to re- tract the gear manually. WARNING Do not operate the landing gear electrically with the handcrank engaged, as damage to the mechanism could occur. After einergency landing gear extension, 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 the gear-up circuit and gear might retract with the airplane on the ground. LANDING GEAR RETRACTION AFTER PRACTICE MANUAL EXTENSION After practice manual extension of the landing gear, the ! gear may be retracted electrically, as follows: 1. Handcrank - CHECK, STOWED 2. Landing Gear Motor Circuit Breaker - IN 3. Landing Gear Handle - UP January 1983 Section Ill Emergency Procedures BEECHCRAFT Baron 58 Serial TH 1thru TH 772 ICE PROTECTION SURFACE DEICE SYSTEM a. Failure of AUTO Operation (1) Surface Deice Switch - MANUAL (Do not hold more than 8 seconds) CAUTION The boots will inflate only as long as the switch is held i n the MANUAL position. When the switch is released the boots will deflate. b. Failure of boots to deflate (1) Pull circuit breaker on pilot's side panel. ELECTROTHERMAL PROPELLER DEICE SYSTEM 1. Loss of one alternator; 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, a wait of approximately 30 seconds is necessary before resetting. If ammeter reads 0 and the circuit breaker has not tripped or if the ammeter still reads 0 after the circuit breaker has been reset, turn the switch off and consider the prop deice system inoperative. 3-14 January 1983 BEECHCRAFT Baron 58 Section Ill Serial TH 1 thru TH 772 Emergency Procedures b. Zero to 7 Amps, 2 Blade Propeller; Zero to 1 4 Amps. 3 Blade Propeller: If the prop deice system ammeter occasionally or regularly indicates less than 7 amps for 2 blade, (or 1 4 amps for 3 blade), operation of the prop deice system can continue unless serious propeller im- balance results from irregular ice throw-offs. c. 1 2 to 15 Amps, 2 Blade Propeller; 18 to 23 Amps, 3 Blade Propeller: If the prop deicing system ammeter occasionally or regularly indicates 1 2 to 15 amps for 2 Made (or 18 to 23 amps for 3 blade), operation of the prop deice 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. . ALTERNATE (EMERGENCY) STATIC AIR SOURCE SYSTEM THE EMERGENCY STATIC AIR SOURCE SHOULD BE USED FOR CONDITIONS WHERE THE NORMAL STATIC SOURCE HAS BEEN OBSTRUCTED. When the airplane has been exposed to moisture and/or icing conditions (especially on the ground), the possibility of obstructed static ports should be considered. Partial obstructions will January 1983 3-15 Section Ill BEECHCRAFT Baron 58 Emergency Procedures Serial TH 1thru TH 772 result in the rate of climb indication being sluggish during a climb or descent. Verification of suspected obstruction is possible by switching to the emergency system and noting a sudden sustained change in rate of climb. This may be accompanied by abnormal indicated airspeed and altitude changes beyond normal calibration differences. Whenever any obstruction exists in the Normal Static Air System or the Emergency ~ i a t i cAir System 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 i n the OFF NORMAL position when system is not needed. EMERGENCY EXITS Emergencyexits, provided by the openable window on each side of the cabin may be used for egress in addition to the cabin door and the utility door. A n emergency exit placard, "EMERGENCY EXIT, LIFT LATCH - PULL PIN, PUSH WINDOW OUT,'' is installed belowthe left and right middle windows after compliance with BEECHCRAFT Service Lnstructions 1241. To open each emergency exit: 1. Lift the latch 2. Pull out the emergency release pin and push the window out. 3-16 January 1983 BEECHCRAFT Baron 58 Section Ill Serial TH 1thru TH 772 Emergency Procedures NOTE On TH-733 and after, for access past the 3rd and/or 4th seats, rotate the red handle, lo- cated on the lower inboard side of the seat back, and fold the seat back over. UNLATCHED DOOR IN FLIGHT If the cabin door is not locked it may come unlatched in flight. This may occur during or just after take-off. The door will trail in a position approximately 3 to 4 inches open. Flight characteristics of the airplane will not be affected except for a reduction in performance. Return to the field in a normal manner. If practicable, during the landing flare-out have a passenger hold the door to prevent it from swinging open. SIMULATED ONE ENGINE INOPERATIVE , ZERO THRUST (Simulated Feather) Use the following power setting (only on one engine at a time) to establish zero thrust. Use of this power setting avoids the difficulties 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. H~ MANIFOLD PRESSURE NOTE This setting will approximate Zero Thrust using recommended One-Engine Inoperative Climb speeds. January 1983 Section Ill , BEECHCRAFT Baron 58 Emergency Procedures Serial TH 1thru TH 772 SPINS If a spin is entered inadvertently; Immediately move the control column full forward, apply full rudder opposite to the direction of the spin and reduce power on both engines to idle. These three actions should be done as near simultaneously as possible; then con- tinue to hold this control position 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. T h e recovery technique is based on the best available information. January 1983 BEECHCRAFT Baron 58 Serial TH 1thru TH 772' SECTION IV NORMAL PROCEDURES TABLE OF CONTENTS SUBJECT Airspeeds for Safe Operation ..................... 4-3 Preflight Inspection ................................ 4-4 Before Starting .................................. 4-7 Starting ..........................................4-8 After Starting and Taxi .......................... 4-10 Before Takeoff ..................................4-11 Takeoff .........................................4-12 Maximum Performance Climb .................... 4-12 Cruise Climb .................................... 4-12 Cruise ..........................;............... 4-13 Leaning Using the Exhaust Gas Temperature Indicator (EGT) ................... 4-13 Descent ........................................ 4-14 Before Landing ................................. 4-14 ................................. Balked Landing 4-15 ................................... After Landing 4-15 Shutdown ......................................4-15 Oxygen System .................................4-16 Electric Elevator Trim ............................4-18 Cold Weather Operation .......................... 4-19 Preflight Inspection .......................... 4-19 ..................................... Engines 4-19 ~xternalpower .............................. 4-20 Starting Engines Using Auxiliary Power Unit ....................... 4-21 January 1983 4- 1 Section IV BEECHCRAFT Baron 58 Normal Procedures Serial TH 1thru TH 772 TABLE OF CONTENTS (Continued) SUBJECT PAGE Taxiing .....................................4-22 .......................... Ice Protection Systems 4-22 ................. Emergency Static'Air Source 4-22 ....................... Surface Deice System 4-23 ............... Electrothermal Propeller Deice 4-24 Propeller and Windshield ............... Anti-Ice System (Fluid Flow) 4-25 ......... Pitot Heat and Heated Stall Warning 4-25 .............................. Fuel Vent Heat 4-26 ....................... Windshield Defogging 4-26 Engine Break-In Information ..................... 4-26 ................ Practice Demonstration of VMCA 4-26 January 1983 BEECHCRAFT Baron 58 Section IV Serial TH 1 thru TH 772 Normal Procedures AN airspeeds quoted in this section are indicated airspeeds (IAS) and assume zero instrument error. AIRSPEEDS FOR SAFE OPERATION (Settings established at 5400 lbs.} ....... Two-Engine Best Angle-of-Climb 86 kts/99 mph ..... Two-Engine Best Rate-of-Climb 104 kts/l20 mph 1 ... Single-Engine Best Angle-of-Climb 96 k t q l 11 mph Single-Engine Best Rate-of-Climb ... 100 k t q l l 5 rnph ; 1 .......... Air Minimum Control (VMCA) 81 kts/93 rnph Intentional One Engine Inoperative (VSSE) ................... 86 k t m 9 mph II Cruise Climb ....................... 139 ktq160 mph I I Balked Landing Climb ............... 95 kts/l09 mph ! Landing Approach Flaps 30° ....................... 96 k t q l l 0 mph Turbulent Air Penetration ........... 156 k t q l 8 0 mph Maximum Demonstrated Crosswind .... 22 kts/25 rnph January 1983 Section l V BEECHCRAFT Baron 58 Normal Procedures Serial TH 1thru TH 772 PREFLIGHT INSPECTION 1. COCKPIT: a. Control Lock - REMOVE AND 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 AlTACHMENT b. Tail Cone, Tail Light, and Beacon - CHECK c. Tie Down - REMOVE d. Cabin Air Inlet - CHECK 4. LEFT FUSELAGE: a. Cabin Air Outlet - CHECK b. Stat~cPort - UNOBSTRUCTED c. All Antennas and Lower Beacon - CHECK 5. LEFT WlNG TRAILING EDGE: 0 a. Fuel Sump Aft of Wheel Well - DRAIN b. Fuel Vents - CHECK c. Flaps - CHECK GENERAL CONDITION d. Aileron - CHECK CONDITION AND FREEDOM OF MOVEMENT, TAB NEUTRAL WHEN AILERON NEUTRAL 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 SECURE CAP(S). ALWAYS CHECK WlNG TIP TANK FIRST (IF IN- January 1983 BEECHCRAFT Baron 58 Section IV Serial TH 1thru TH 772 Normal Procedures 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 (if rnstalled) f. Tie Down, Chocks - REMOVE g. Engine Oil - CHECK QUANTITY, SECURE CAP AND DOOR h. Engine Cowling and Doors - CHECK CONDITION AND SECURITY i. Engine Air Intake - REMOVE COVER AND EX- AMINE FOR OBSTRUCTIONS j. Propeller - EXAMINE FOR NICKS, SECURITY AND OIL LEAKS k. Cowl Flap - CHECK I. Wheel Well Doors, Tire, Brake Line and Shock Strut - CHECK m. Landing Gear Uplock Roller - CHECK n. Fuel Drains - DRAIN 7. NOSE SECTION a. Wheel Well Doors, Tire and Shock Strut - CHECK b. Heater Fuel Strainer - DRAIN (if installed) c. Pitot(s) - REMOVE COVER, EXAMINE FOR OB- STRUCTIONS d. T a x ~ b n d i n gLtght - CHECK e. Heater Air Inlets - CLEAR f . Oxygen - CHECK g. 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, SECURE CAP AND DOOR January 1983- - 4-5 Section IV BEECHCRAFT Baron 58 Nonnal Procedures ' Serial TH 1thru TH 772 f. Engine Cowling and Doors - CHECK CONDITION AND SECURITY g. Propeller - EXAMINE FOR NICKS, SECURIN AND OIL LEAKS h. Engine Air Intake - REMOVE COVER AND EX- AMINE FOR OBSTRUCTIONS i. Fuel Sight Gage - CHECK (if installed) j. Fuel - CHECK QUANTITY AND SECURE CAP(S). ALWAYS CHECK WlNG TIP TANK FIRST (IF INSTALLED); DO NOT REMOVE INBOARD CAP IF FUEL IS VISIBLE IN TIP TANK. k. Wing Tip Tank (if installed) Sump - DRAIN I. Tie Down and Chocks - REMOVE rn. Lights and Deice Boot - CHECK FOR CONDITION 9. RIGHT WlNG TRAILING EDGE a. ~ i l e r o n- CHECK CONDITION AND FREEDOM OF MOVEMENT b. Fuel Vents - CHECK c. Fuel Sump Aft of Wheel Well - DRAIN d. Flaps - CHECK GENERAL CONDITION NOTE , Check operation of lights if night?flight is an- ticipated. CAUTION ! I DO NOT TAXI WITH A FLAT SHOCK STRUT. , January 1983 BEECHCRAFT Baron 58 Section IV Serial TH 1thru TH 772 Normal Procedures I BEFORE STARTING I 1. Seats - POSITION AND LOCK; Seat Backs - UPRIGHT 2. Rudder Pedals - ADJUST 1 3. Seat Belts and Shoulder Harnesses - FASTEN AND ADJUST 1I 4. Parking Brake - SET 5. All Avionics - OFF 6. Oxygen - CHECK QUANTITY AND OPERATION 7. Landing Gear Handle - DOWN 8. Cowl Flaps - CHECK, OPEN 9. Fuel Selector Valves - CHECK OPERATION THEN ON 10. All Circuit Breakers, Switches and Equipment Controls - CHECK I 11. Battery Switch and Alternator Switches - ON (If external power is used, Alternator switches - OFF) 12. Fuel Quantity -Indicators - CHECK QUANTITY (See LIMITATIONS for take-off fuel) 13. Landing Gear Position Lights - CHECK January 1983 Section IV BEECHCRAFT Baron 58 Normal Procedures Serial TH 1thru TH 772 STARTING 1. Throttle Position - APPROXIMATELY 112IN. 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, !hen OFF. Return mixture control to FULL RICH. 4. Aux Fuel Pump - HIGH (until pressure stabilizes then - OFF) 5 . MagnetoBtart Switch -- START (Observe Starter Limits) CAUTION Do not engage starter for more than 30 seconds in any 4-minute period. NOTE In the event of a balked start (or overprime con- dition) place mixture control in IDLE CUT-OFF and open the throttle; operate the starter to remove excess fuel. 4 s engine starts, reduce the throttle to idle rpm and place the mixture control in FULL RICH. 6. Warm-up - 1000 to 1200 RPM 7. Oil Pressure - 25 PSI WITHIN 30 SECONDS 8. External Power (if used) - DISCONNECT 4-8 January 1983 BEECHCRAFT Baron 58 Serial TH 1thru TH 772 Section IV Normal Procedures WARNING When using external power, start the right en- gine first, since the external power receptacle is on the left nacelle. Disconnect external power before' starting left engine. 9. Alternator Switch - ON 10. All Engine Indicators - CHECK CAUTION ' . i If the total of both loadmeters exceeds .2 , after two minutes at 1000-1200 rpm, with no additional electrical equipment on, and the indication shows no signs of decreasing, an electrical malfunction i s indicated. The battery master and both alternator switches should be placed in the OFF position. Do not take off. 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 normal conditions could indicate prolonged starter motor running and the engine should be shut down. No further flight operations should be attempted until the cause is determined and repaired. 11. Using the same procedure, start other engine. January 1983 4-9 Section IV BEECHCRAFT Baron 58 Normal Procedures Serial TH 1 thru T H 772 AFTER STARTING AND TAXI NOTE Do not operate engine above 1200 RPM until oil temperature reaches 75OF. 1. Brakes - RELEASE AND CHECK 2. Avionics - ON, AS REQUIRED 3. Exterior Lights - AS REQUIRED January 1983 BEECHCRAFT Baron 58 Section IV Serial TH 1thruTH 772 Normal Procedures WARNING When using external power, start the right en- gine first, since the external power receptacle is on the left nacelle. Disconnect external power before starting left engine. 9. Alternator Switch - ON 10. All Engine Indicators - CHECK CAUTION If the total of both loadmeters exceeds .2 after two minutes at 1000-1200 rpm, with no additional electrica'l equipment on, and the indication shows no signs of decreasing, an electrical' 'malfunction is indicated. The battery master and both alternator 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 normal conditions could indicate prolonged starter motor running and the engine should be shut down. No further flight operations should be attempted until the cause is determined and repaired. 11. Using the same procedure, start other engine. January 1983 Section IV BEECHCRAFT Baron 58 Normal Procedures SerialTH 1 thru TH 772 AFTER STARTING AND TAXI Do not operate engine above 1200 RPM until oil temperature reaches 75OF. 1. Brakes - RELEASE AND CHECK 2. Avionics - ON, AS REQUIRED 3. Exterior Lights - AS REQUIRED January 1983 BEECHCRAFT Baron 58 Serial TH 1thru TH 772 Section I V Normal Procedures BEFORE TAKEOFF -1. Seat Belts and Shoulder Harnesses - CHECK - 2. Parking Brake - SET - / 3. Aux Fuel Pumps - OFF (If ambient temperature is 90°F or above, use LOW pressure boost) - 4. All Instruments - CHECKED - 5. Fuel Selector Valves - CHECK ON -6. Mixture - FULL RICH (or'as required by field elevation) 7. Propellers - EXERCISE AT 2200 RPM CAUTION When exercising propellers in their governing range, do not move the control lever aft past the detent. To do so will allow the propeller to change rapidly to the full feathered position, imposing high stresses on the blade shank and engine. 8. Loadmeters - CHECK for proper indication 9. Throttles - 1700 RPM 10. Magnetos - CHECK (Variance between individual magnetos should notexceed 50 rpm, max. drop 150 rpm) 11. Throttles - 1500 RPM 12. Propellers - FEATHERING CHECK (Do not allow an rpm . l [ . drop Throttles of more - IDLE than 500 rpm) -14. Electric Trim - CHECK OPERATION -15. Trim - AS REQUIRED FOR TAKEOFF 16. Flaps - CHECK AND SET FOR TAKEOFF Y 7. Controls - CHECK PROPER DIRECTION, FULL TRAVEL, AND FREEDOM OF MOVEMENT -18. Doors and Windows - LOCKED -1 9. Parking Brake' - OFF Section IV BEECHCRA, Baron 58 Normal Procedures Serial TH 1thruTH 772 TAKEOFF Take-Off Power ............... Full Throttle, 2700 rpm Minimum Take-Off Oil Ternprature ............. 75OF 1. Power - SET TAKE-OFF POWER (MIXTURE - SET FUEL FLOW TO ALTITUDE) BEFORE BRAKE RELEASE 2. Airspeed - ACCELERATE TO AND MAINTAIN REC- OMMENDED 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 1. Power - SET MAXIMUM CONTINUOUS POWER 2. Mixtures -' LEAN TO APPROPRIATE FUEL FLOW 3. Cowl Flaps - OPEN 4. Airspeed - ESTABLISH 104 KTS/120 MPH CRUISE CLIMB 1. Power - SET (25.0 in. Hg or Full Throttle - 2500 RPM) 2. Mixture - LEAN TO APPROPRIATE FUEL FLOW 3. Airspeed - 139 KTS/1 GO MPH 4. Cowl Flaps - AS REQUIRED NOTE In high ambient temperatures, low pressure boost may be required to prevent excessive fuel flow fluctuations. 4-12 January 1983 BEECHCRAFTBaron 58 Section IV Serial TH 1thru TH 772 Normal Procedures CRUISE Maximum Cruise Power . . .. . 24.5 in. Hg at 2500 rpm Recommended Cruise Power . 24.0 in. Hg at 2300 rpm Recommended 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) A thermocouple type exhaust gas temperature (EGT) probe is mounted in the system. This probe is connected to an indicator on the instrument panel. The indicator is cali- brated in degrees Fahrenheit. Use EGT system to lean the fuewir mixture when cruising at maximum cruise power or less. 1. Lean the mixture and. note the point on the indicator that the temperature peaks and starts to fall. a. CRUISE (LEAN) MIXTURE - Increase the mixture until the EGT shows a drop of 25OF below peak on the rich side of peak. b. BEST POWER MIXTURE - Increase the mixture until the EGT shows a drop of 100°F below peak on the rich side of peak. Do not continue to lean mixture beyond that necessary to establish peak temperature. January. 1983 Section lV BEECHCRAFT Baron 58 Normal Procedures Serial TH 1thru TH 772 2. Continuous operation is recommended at 25OF or more below peak EGT only on the rich side of peak. 3. Changes in altitude and power settings require the peak EGT to be rechecked and the mixture reset. DESCENT 1. Altimeter - SET 2, Cowl Flaps - CLOSED 3. Windshield Defroster - AS REQUIRED 4. Power - AS REQUIRED (avoid prolonged idle settinp and low cylinder head temperatures) Recommended descent speeds: Smooth air ..................... 175 kts/201 mph Rough air ................ (Max.) 156 kts/l80 mph BEFORE 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 15O POSITION (Maximum extension speed 152 kts/175 rnph) 7. Landing Gear - DOWN (Gear extension speed 152 kts/175 mph) 8. Flaps - FULL DOWN (30°) (Maximum extension speed, 122 kts/l40 mph) 9. Airspeed - ESTABLISH NORMAL LANDING APPROACH SPEED. 10. Propellers - LOW PITCH (high rpm) 4-14 January 1983 BEECHCRAFT Baron 58 Section IV Serial TH 1 thruTH 772 Normal Procedures BALKED LANDING 1. Propellers - LOW PITCH (high rpm) 2. Power - MAXIMUM ALLOWABLE 3. Airspeed - BALKED LANDING CLIMB SPEED (95 KTS/lO9 MPH) 4. Flaps - UP (0°) 6. Landing Gear - UP 6. Cowl Flaps - AS REQUIRED AmER LANDING 1. Landing and Taxi Lights - AS REQUIRED 2. Flaps - UP 3. Trim Tabs - SET TO ZERO 4. Cowl Flaps - OPEN 5. Aux Fuel Pumps - AS REQUIRED SHUTDOWN-. 1. Parking Brake - SET 2. Propellers - HIGH RPM 3.Throttles - 1000 RPM 4. Aux Fuel Pumps - OFF 5. Electrical and Avionics Equipment - OFF 6. Mixture Controls - IDLE CUT-OFF 7. Magnetofitart 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 excessive pressures on the hydraulic system. NOTE Induction air scoop covers, included i n the loose tools and accessories, are to prevent foreign matter from entering the air scoops while the aircraft is-parked. January 1983 Section IV Normal Procedures BEECHCRAFT Baron 58 Serial TH 1thru TH 772 OXYGEN SYSTEM WARNING NO SMOKING permitted when using oxygen. PREFLIGHT 1. Check Oxygen Pressure Gage for pressure reading. 2. Determine percent of full system. 3. Multiply oxygen duration in minutes by percent of full system. EXAMPLE: People 5 Gage Pressure 1500 psi Percent Capacity (from chart) 80% Cylinder Capacity (f uil) 49 cu h Altitude (planned flight) 15,000 feet Duration (full cylinder) 149 minutes Duration (80%full) 119 minutes OXYGEN DURATtON The recommended masks are provided with the system. They are designed to be adjustable to fit the average with minimum leakage of oxygen. Since 90% of the system efficiency is deter- mined by the fit of the oxygen mask, make cer- tain the masks fit properly and are in good condition. 4-16 January 1983 BEECHCRAFT Baron 58' Section IV Serial TH 1 thru TH 772 Normal Procedures OXYGEN AVAILABLE WITH PARTIALLY.FULL BOTTLE s'o 160 % CAPACITY January 1983 4-17 OXYGEN DURATION CHART Duration in minutes at the following altitudes: - .z a 0 o) * c 3 0 w w . Persons Using 1 2 3 4 5 6 1 2 3 4 5 6 12,500 1014 507 338 253 202 169 1344 672 448 336 268 224 I II I I 15.000 746 373 248 186 149 124 988 494 329 247 197 164 20,000 507 253 169 126 101 84 672 336 224 168 134 112 Section I V BEECHCRAFT Baron 58 Normal Procedures Serial TH 1 thru TH 772 IN FLIGHT The use of oxygen is recommended to be in accordance with current FAR operating rules. 1. Oxygen Control Valve - OPEN SLOWLY 2. Mask - INSERT FIlTlNG, DON MASK (adjust mask for proper,fit) 3. Oxygen Flow Indicator - CHECK (red plunger lifts from its seat when the hose is inserted into the oxygen . coupling) AFTER USING 1. Discontinue use by unplugging mask from outlet. NOTE Closing the control v a l w while in flight is not necessary doe 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, (when released the switch returns to the center - OFF position) Malfunction procedures are given i n the EMERGENCY PROCEDURES section. 4-18 January 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 Section lV Normal Procedures COLD WEATHER OPERATION PREFLIGHT INSPECTION In addition to the normal' preflight exterior inspection, remove ice, snow and frost from the wings, tail, control surfaces and hinges, propellers, windshield, fuel cell filler caps and fuel vents, and crankcase breathers. If you have no way of removing these formations of ice, snow, and frost leave the airplane on the ground, as these deposits will not blow off. The wing contour may be changed by these formations sufficiently that its lift qualities are considerably disturbed and sometimes completely destroyed. Complete your normal preflight procedures. Check the flight controls for complete freedom of movement. Conditions for accumulatihg 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 s e ~ i c e d .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 propeller through by hand several times to clear the engine and "limber up" the cold, heavy oil before using the starter. This will also lessen the load on the battery if an auxiliary power unit is not used. .. Under very cold conditions, it may be necessary to preheat the engine prior to a start. Particular attention should be applied to the oil cooler, and engine sump to insure proper preheat. A start with congealed oil in the system may January 1983 4-19 Section 1V BEECHCRAFT Baron 58 Normal Procedures Serial TH 1thru TH 772 produce an indication of normal pressure immediately after the start, but then the oil pressure may decrease when residual oil in the engine is pumped back with the congealed oil in the sump. If an engine heater capable of heating both the engine sump, and cooler is not available, the oil should be drained while the engines are hot and stored in a warm area until the next flight. If there is no oil pressure within the first 60 seconds of running, or if oil pressure drops after a few minutes of ground operation, shut down and check for broken oil lines, oil cooler leaks or the possibility of congealed oil. NOTE It is advisable to use external power for stan- ing in cold weather. During warm-up, watch engine temperatures closely, since it is quite possible to exceed the cylinder head tem- perature limit in trying to bring up the oil temperature. Exercise the propellers severa1:time.s to remove w l d oil from the pitch change mechanisms. The propellers should also be cycled occasionally in flight. Doring letdown and landing, give special attention to en- gine temperatures, since the engines will have a tend- ency toward overcooling. EXTERNAL POWER It is very important that the following precautions be ob- served while using external power. 4-20 January 1983 BEECHCRAFT Baron 58 Section IV Serial TH 1 thruTH 772 Normal Procedures 1. The airplane has a negative ground system. 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 of the auxiliary power unit to the negative terminal of the external power receptacle. 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 an external power unit. This protects the voltage regulators and associated elec- trical equipment from voltage transients (power fluc- tuations). STARTING ENGINES USING AUXILIARY POWER UNIT 1. Battery switch - ON 2. Alternators, Electrical, and Avionics Equipment - OFF 3. Auxiliary Power Unit - CONNECT 4. Auxiliary Power Unit - SEF OUTPUT (27.0 to 28.5 volts) 5. 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 January 1983 4-21 Section IV Normal Procedures BEECHCRAFT Baron 58 Serial TH 1thru TH 772 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 freeze, preventing free movement and result- ing in structural damage. ICE PROTECTION SYSTEMS The following equipment, when Installed and operable, will provide a degree of protection when icing conditions are in- advertently encountered. Since this equipment has not been demonstrated to meet current requirements for flight into known icing conditions, the pilot must exit such condi- tions assoon as possible if ice accumulates on the airplane. 1. Equipment required for IFR flight 2. Beech approved emergency static air source 3. Beech approved surface deice system 4. Beech approved propeller deice or anti-ice system 5. Beech approved pitot heat 6. Beech approved heated stall warning 7. Beech approved 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 in- crease due to the distortion of the wing airfoil when ice has accumulated on the airplane. For the same reason, stall warning devices are not ' accurate and should not be relied upon. With ice on the airplane, maintain a comfortable margin of airspeed above the normal stall airspeed. . . . . 4- 22 . . ... March, 1988 BEECHCRAFT Baron 58 Section IV Serial TH 1thru TH772 Normal Procedures 1. EMERGENCY STATIC AIR SOURCE If the Emergency Static Air Source is desired for use: a. Emergency Static Air Source - ON EMERGENCY (lower sidewall adjacent to pilot) b. For Airspeed Calibration and Altimeter Correc- tions, refer to PERFORMANCE section CAU TION The emergency static air valve should be in the OFF NORMAL position when the system is not needed. a. BEFORE TAKE-OFF (1) Throttles - 2000 RPM (2) Suiface Deice Switch - AUTO (UP) (3) Deice Pressure - 9 to 20 PSI (while boots are inflating) (4) Wing Boots - CHECK VISUALLY FOR INFLA- TION AND HOLD DOWN .- b. IN FLIGHT When ice accumulates 1 / 2 to 1 inch (1) Surface Deice Switch - AUTO (UP) (2) Deice Pressure - 9 to 20 PSI (while boots are inflating) (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 inflated boots and prevent ice removal. Stall speeds are increased 4 kts/fi mph in all configurations with surface deice system oper- ating. March, lS88 4-23 Section IV Normal Procedures BEECHCRAFT Baron 58 SerialTH 1thru TH 772 NOTE Either engine will supply sufficient vacuum and pressure for deice operation. c. For Emergency Operation refer to the EMER- GENCY PROCEDURES section. 3. ELECTROTHERMAL PROPELLER DEICE CAUTION Do not operate the propeller deice when pro- pellers are static. a. BEFORE TAKEOFF (1) Propeller Deice Switch - ON (2) Propeller Deice Ammeter - CHECK, 7 to 12 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 function automatically until the switch is turned OFF. (2) Relieve propellei 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 the Emergency Pro- cedures seciion. 4-24 March, 1988 BEECHCRAFT Baron 58 a Section IV Serial TH 1thru TH 772 Normal Procedures 4. PROPELLER AND WINDSHIELD ANTI-ICE SYSTEM (FLUID FLOW) CAUTION This anti-ice system is designed to PREVENT the formation of ice. Always turn the system ON before entering icing conditions. 8. PREFLIGHT - . (1) Check the quantity in reservoir (2) Check stinger ring and .lines for obstructions (3) Check propeller boots for damage b. IN FLIGHT (1) Prop Anti-ice Switch - ON I (2) Windshield Anti-ice Switch - CYCLE AS RE- QUIRED (3) Anti-ice Quantity' Indicator - MONITOR NOTE ~!I See SYSTEM description for endurance. I 5. PlTOT HEAT AND HEATED STALL WARNING ; a. Pitot Heat Switch(es) - ON (Note deflection on I Loadmeter) Heated Stall Warning is activated by I the left pitot heat switch. NOTE Switches may be left on throughout flight. Pro- longed operation on the ground could damage the Pitot Heat System. January 1983 4-25 Section IV Normal Procedures BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 6. FUEL VENT HEAT a. Fuel Vent Switch - ON (If ice is encountered) 7. WINDSHIELD DEFOGGIN'G a. Defrost Control - PUSH ON b. Pilot's Storm Window - OPEN. AS REQUIRED ENGINE BREAK-IN 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 kts/99 mph (VSSE) 4. Propeller Levers - High RPM 5. Throttle (Simulated inoperative engine) - Idle 6. Throttle (Other engine) - Maximum Manifold Pressure 7. Airspeed - Reduce app;oximately 1 knot per second until either VMCA or stall warning is obtained. 4 2 6 January 1983 BEECHCRAFT Baron 58 SerialTH 1 thru TH 772 CAUTION Section IV Normal Procedures Use rudder to maintain directional control (heading) and ailerons to maintain 5 O bank towards the operative engine (lateral attitude). At the first sign of either VMCA or stall warn- ing (which may be evidenced by: inability to maintain heading or lateral anitude, aero- dynamic stall buffet, or stall warning horn sound) immediately initiate recovery: reduce power to idle on the operative qngine and immediately lower the nose to regain VssE. January 1983 Section lV BEECHCRAFT Baron 5 8 Normal Procedures Serial TH 1 thru 1H 772 INTENTIONALLY LEFT BLANK January 1983 BEECHCRAFT Baron58 Serial TH 1thru TH 772 SECTION V PERFORMANCE TABLE OF CONTENTS 1I SUBJECT PAGE Introduction to Performance and Flight Planning .. . . . . . . . . . . . . .. . . . . . . . ... . . . . . . . 5-3 Conditions . . . . . . .. . . . . . . . . . . . . . . . . . . . 5-3- 5-13 Comments Pertinent to the Use of Performance Graphs . . . . . . . ;. . . . . . . . . . . . . . . . . 5-13 Performance Graphs . .. . . . . . . . . . . . . . . . . . 5-14- 5-47 Airspeed Calibration - Normal System . . . . . . . . . . . 5-14 Altimeter Correction - Normal System . . . . . . . . . . . 5-15 IAirspeed Calibration - Alternate System . . . . . . . . . 5-16 i Altimeter Correction - Alternate System . . . . . . . . . 5-17 Fahrenheit to Celsius . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-18 ISA Conversion . . . . . . . . . . . . . . . . . . .. . . . . . . . . . . . . 5-19 Manifold Pressure vs RPM :. . . . . . . . . . . . . . . . . . . . . 5-20 I / Take-Off Weight . . . . . . .. . . . . . . . . . . . . ... .... . ... 5-21 I1 Stall Speeds - Power Idle . . . . . . . . . . . . . . . . . . . . . . . 5-22 i 1Wind Components . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . 5-23 ! Take-Off Distance . . . . . . . . . . . . . . . . .. . . . .. . ... . . . 5-24.. Accelerate - Stop . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-25 ! Accelerate - Go . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . '5-26 ! Climb - Two Engine . . . . . . . . . . . . .. . . . . . . . . . . . . . . 5-27 Take-Off Climb Gradient, One Engine lnoperative . . .. . . . . . . . . . . . . . . . .. . . . . . . 5-28 Time, Fuel, Distance to Climb . . . . . .. . . . . . . . . . . .. 5-29 Climb - One Engine lnoperative . . . . . . . . . . . . . . . . . 5-30 Service Ceiling - One Engine lnoperative . . . . . . . . 5-31 January 1983 5-1 Section V Performance BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 TABLE OF CONTENTS (Continued) SUBJECT PAGE Cruise Speeds ................................ 5-32 Fuel Flow vs Brake Horsepower ................. 5-33 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 R q g e Profile . 136 Gallons .................... 5-38 ~nd6r;ihce 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 ............. 5-45 Climb . Balked Landing ......................... 5-46 Landing Distance ................................ 5-47 January 1983 I BEECHCRAFT Baron 68 Serial TH 1thru TH 772 Section V Performance INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING All airspeeds quoted id this section are indicated air- speeds (/AS) except as n&ed and assume zero instrument error. The graphs and tables in this section present performance information for takeoff, climb, landing and flight planning at various parameters of weight, power, altitude, and 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 lbs (Baron 58A) will be equal to or better than that of the higher gross weight Baron 58. CONDITIONS At Denver: Outside Air Temperature ............. 15OC (5S°F) Field Elevation .......................... 5330 ft Altimeter Setting .................... 29.60 in. Hg Wind ............................. 270° at 10 kts Runway 26L length ..................... 10,010 ft Route of Trip *DEN-V81-AMA For VFR Cruise at 1 1,500 feet January 1983 Section V Performance BEECHCRAFT Baron 58 SerialTH 1thruTH 772 'REFERENCE: Enroute Low Altitude Chart L-6 At Amarillo: Outside Air Temperature 25OC (77OF) iI ............. Field Elevation 3605 ft !.......................... Altimeter Setting .................... 29.56 in. Hg Wind ............................. 180° at 10 kts Runway 21 Length ..................... 10,000 ft I ROUTE SEGMENT DEN-COS COS-PUB PUB-TBE TBE-DM DM-AMA To determine pressure altitude at origin and destination I 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: DIST NM 55 40 74 87 65 MAGNETIC COURSE 161 O 153O 134O 132O 125O Pressure Altitude at DEN: 29.92 - 29.60 = .32 in. Hg The pressure altitude at DEN is 320feet above the field elevation. WIND 11500 CEET DIR/KTS 01QBO 010/30 100,20 200120 200/20 5-4 January 1983 OAT 11500 FEET OC -5 -5 0 9 10 ALT SETTING IN.HG 29.60 29.60 29.56 29.56 29.56 BEECHCRAFTBaron 58 Serial TH 1thru TH 772 Section V Performance Pressure Altitude at AMA: 29.92 - 29.56 = .36 in. Hg The pressure altitude at AMA is 360 feet above the field elevation. 3605 + 360 = 3965 ft I NOTE For flight planning, the difference between cruise altitude and cruise pressure altitude has been ig,nored. Maximum Allowable Take-off Weight = 5400 lbs Ramp Weight = 5400 + 24'= 5424 lbs NOTE Fuel for start, taxi and take-off is normally 24 pounds. Enter the Take-Off Weight graph at 5650 feet pressure altitude and 15OC. The take-off weight to achieve a positive rate-of-climb at I lift-off for one engine inoperative is: Take-off Weight = 4850 pounds Enter the Take-Off Distance graph at 15OC. 5650 feet pres- sure altitude, 5450 pounds, and 9.5 knots headwind component. Ground Roll ............................. 1900 ft Total Distance over 50 f t Obstacle ........ 3090 ft Lift-off Speed ................... 86 kts (99 mph) 50 Foot Speed ................. 94 kts (108 mph) January 1983 5-5 Section V Performance BEECHCRAFT Baron 58 Serial TH 1thtuTH 772 Enter the Accelerate-Stop graph at 15OC, 5650 feet pres- sure altitude, 5400 pounds, and 9.5 knots headwind component: ................ Accelerate-Stop Distance 3960 ft Engine Failure Speed ............ 86 kts (99 mph) NOTE Since 3960 feet is less than the available field length (10,010 ti), the accelerate-stop pro- cedure can be performed at any weight. Take-off at 5400 lbs can be accomplished. However, if an engine failure occurs before 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 requirements and take-off flight path assuming an engine failure occurs during the take-off procedure. The fol- lowing illustrates the use of these charts. Enter the Accelerate-Go graph at 15OC. 5650 feet pres- sure altitude, 4850 pounds, and 9.5 knots headwind component: Ground Roll ............................. 1775 ft Total Distance Over 50 ft Obstacle ....... 8071 ti Lift-off Speed ................... 86 kts (99 mph) 50 Foot Speed ................. 94 kts (108 mph) 5-6 January 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 Section V Performance Enter the graph for Take-off Climb Gradient - One Engine lnoperative at 15OC. 5650 feet pressure altitude, and 4850 . pounds. ............................. Climb Gradient 2.1 % ................... Climb Speed 94 kts (108 mph) A 2.1% climbgradient is 21 feet of vertical height per 1000 feet of horizontal distance. NOTE The Climb Gradient - One Engine lnoperative 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)(to00+ 2 1) = 1905 feet Total Distance = 8071 + 1905 = 9976 feet The above results are illust'rated below: January 1983 Section V Performance BEECHCRAFT Baron 58 Serial TH 1 thruTH 772 > 03 m a ENGINE FAILURE HERE - *eO -------I--. - C @ACCELERATE - GO TAKE-OFF DISTANCE = 8071 FT @DISTANCE TO CLIMB FROM 50 FT TO 90 FT ABOVE RUNWAY = 1905 FT @ACCELERATE - STOP DISTANCE FOR 5400 LBS TAKE-OFF WEIGHT = 3960 FT 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 15OC to 5650 feet and to 5400 pounds. Also enter at -5OC 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 Traveled = (55 -17) = 38 NM 5-8 January 1983 BEECHCRAFT Baron 58 Serial TH 1thru TH 772 Section V Performance The temperatures for cruise are presented for a standard day (ISA); 20% (36OF) above a standard day (ISA + 20°C); and 20°C (36OF) below a standard day (ISA - 20°C). These should be used for flight planning. The IOAT values are true temperature values which have been adjusted for the compressibility effects. lOAT should be used for setting cruise power while enroute. Enter the graph for ISA conversion at 11,500 feet and the temperature for the route segment: DEN-PUB OAT - -5OC- ISA Condition = ISA + 3OC PUB-TBE OAT = O°C ISA Condition = ISA + 8OC TBE-DHT OAT = 9OC ISA condition = ISA + 17OC DHT-AMA OAT = 10°C ISA Condition = ISA + 18OC Enter the table for recommended cruise power - 24 in. Hg, 2300 rpm at 10,000 ft, 12,000 ft, ISA and ISA + 20°C. January 1983- ALTI- FEET 10000 12000 TEMPERATURE ISA MAN. TUDEPRESS. IN. HG 20.1 18.5 ISA + 20°C MAN. PRESS. IN. HG 20.1 18.5 - FUEL FLOW GPH/ ENG 12.3 11.6 TAS KTS/ MPH 187/ 215 184/ 212 FUEL FLOW GPH/ ENG 11.8 11.2 TAS KTS/ MPH 187/ 215 185/ 21 3 Section V BEECHCRAFT Baron 58 Performance Serial TH 1thru TH 772 Interpolate for 11,500 feet and the temperature for the appropriate route segment. Results of the interpolat~ons are: NOTE ROUTE SEGMENT DEN-PUB PUB-TBE TBE-DHT DKT-AMA The preceding are exact values for the 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: MAN. PRESS. IN. HG 18.9 18.9 18.9 18.9 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 as follows: FUEL FLOW GPH/ENG 11.7 11.6 11.5 1 1.4 Time = Distance Ground Speed TAS KTS/ MPH 1 86,' 214 186/ 214 1 85/ 21 3 1 85/ 21 3 Fuel Used = (Time) (Total Fuel Flow) January 1983 . - BEECHCRAFT Baron 58 Serial TH 1thru TH 772 Results are: Section V Performance "Distance required to climb or descend has been sub- tracted from segment distance. TIME - FUEL - DISTANCE FUEL USED FOR CRUISE GAL 1.9 4.4 10.0 1 1.6 2.3 ROUTE SEGMENT DEN-COS COS-PUB PUB-TBE TBE-DHT DHT-AMA January 1983 5-11 DISTANCE N M *I7 40 74 87 '18 ITEM Start, Runup, Taxi and Take- off Climb Cruise Descent Total EST GROUND SPEED KTS/ M PH 21 5/ 247 21 3/ 245 171/ 197 173/ 199 176/ 203 TIME HRS: MINS 0:OO 0:15 1:18 0:15 1 :48 TlME AT CRUISE ALTITUDE HRS: MIN : 05 : 1 1 : 26 : 30 : 06 FUEL GAL 4.0 8.0 30.2 6.4 48.6 DISTANCE N M 0 38 236 47 321 Section V BEECHCRAFT Baron 68 Performance Serial TH 1thru TH 772 Total Flight Time: 1 hour, 48 minutes Block Speed: 321 NM + 1 hour, 48 minutiJs = 178 kts/205 mph Reserve Fuel: (45 minutes at Economy Cruise Power): Enter the cruise power settings table for Economy Cruise Power at 11,500 feet for ISA (assume ISA Fuel Flow Rate). Fuel Flow Per Engine = 10.3 gal/hr Total Fuel Flow = 20.6 galhr (124 lbyhr) Reserve Fuel = (45 min)'(124 lbyhr) = 93 lbs (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 lbs Estimated fuel from DEN to AMA = 64.1 gal (385 lbs) Estimated landing weight = 5424 -385 = 5039 lbs Examples have been provided on the performance graphs. The above conditions have been used throughout. Rate of climb was determined for the initial cruise altitude conditions. Enter the graph for Landing Distance - Flaps 3 0 degrees at 25OC. 3965 feet pressure altitude, 5039 pounds and 9.5 kts headwind component: 5-12 January 1983 BEECHCRAFT Baron 58 Serial TH 1thruTH 772 Section V Performance ............................. Ground Roll 1450 ft Total Distance over 50 ft Obstacle ........ 2500 ft ................ Approach Speed 91 kts (105 mph) Enter the graph for Climb-Balked Landing at 25OC, 3965 feet pressure altitude and 5039 pounds: ................ ........ Rate-of-Climb ; 640 Wmin Climb Gradient ............................. 6.5% j COMMENTS PERTINENT TO fHE USE OF PERFORMANCE GRAPHS 1. The example, in addition to presenting an answer for a I particular set of conditions, also presents the order in L I which the graphs should normally be used, i.e., if the 1 first item'in the example is OAT, then enter the graph at the known OAT. 2. The reference lines indicate where to begin following 1 guide lines. Always project to the reference line frrst, I then follow the guide lines to the next known item. - 3. Indicated airspeeds (IAS) were obtained by using the Airspeed Calibration-Normal System. 4.The associated conditions define the specific conditions from which performance parameters have been determined. They are not intended to be used as instructions, however, performance values deter- mined from charts can only be achieved if specified conditions exist. 5. The full amount of usable fuel is available for all approved flight conditions. January 1983. Section V Performance BEECHCRAFf Baron 5 8 Serial TH 1 thru TH 772 5-14 January 1983 BEECHCRAFT Baron 5 8 Serial TH 1 thru TH 772 - Section V Performance U 3 9 ~ NOIW3MM03 U3UWIlW January 1983 Section V Performance BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 - January 1983 BEECHCRAFT Baron 58 SectionV Serial TH 1 thru TH 772 Performance January 1983 5-17 Section V Performance BEECHCRAFT Baron 5 8 Serial TH 1 thru TH 772 Januaw 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 Section V Performance January 1983 Section V Performance BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 January 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 TAKE-OFF WEIGHT Section V Performance TO ACHIEVE P o s r n w SINGLE ENGINE RATE-OF-CLIMB AT LIFT-OFF ASSOCIATE0 CONDITIONS. E E AIRFiANE AIRBORNE POWER TAKE-OFF FLAFS UP UNDING GEAR DOWN INOPERATIVE PROPELLER FEATHERED PRESSURE l l l T l T U M 5650 FEET OAT 15°C 159'FI TAKE.OFF WEIGHT 4850 14000 13000 12000 11000 loo00 I- W f 9000 z 8000 2 t 3 7000 u W K 6000 3 V) E 5000 u 0 4000 3000 2000 UI FD lo00 X 2 b SL 3000 3500 4500 5500 WEIGHT- POUNDS . . . . . January 1983 NOTES: STALL SPEEDS - POWER IDLE WEIGHT -POUNDS ANGLE OF BANK- DEGREES WEIGHT 4850 LBS FLAPS UP ANGLE OF BANK 20" STALL SPEED IIffiI 82 KTS 194 MPHl ICASI BO KTS (92 MPH) BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 Section V Performance WIND COMPONENTS Demonstrated Cmuwlnd Component is 22 ko EXAMPLE: WIND SPEED 20 KTS ANGLE BETWEEN WlND DIRECTION AND FLIGHT PATH 500 HEADWIND COMPONENT 13 KTS CROSSWIND COMPONENT 15 KTS FLIGHT PATH A 0 lb . 30 40 I CROSSWIND COMPONENTS N KNOTS 6 ' January 1983 Section V Performance BEECHCRAFT Baron 58 Serial TH 773 and After 5-24 October 1976 ... - ""V.4. . - \ \ U I * ~ GEAR DOWN AZP90JICW SPEED IAS 4 S I A B U U l E D BS4XlkG MAXIMUM QLMIYAV PAVED. LEVEL. DRY SURFACE LANDING DISTANCE SPEED A 1 5 0 F l 6 0 0 81 EXAMPLE - CO m OAT 2 S°C 'RESSUAE ALTITUDE 3965 n s. :WEIGHT 5 0 3 9 L8S 0- 0 WlNO COMPONENT 9 5 KTS + f GROUND ROLL 1 4 5 0 n I0 r o r n L OVER FT 2 5 ~ 3n 4 P OBSTACLE APPROACH SPECD 91 KrS 4 D 0 n ~~ . OUTSIDE AIR TEMPERAWRE-*C WEIGHT-POUNDS WINO COMPONEWI OSSTACtE H E I ~ H ~ ".KNOrS - F E f f ASSOCLATED CONDITIONS: POWER 1. TAKE-OFF POWER 2.ENGlNE IDLE AT DECISION SPEED FLAPS UP COWL FLAPS OPEN RUNWAY PAVED. LEVEL. DRY SURFACE ACCELERATE - STOP DISTANCE DECISION SPEED (ALL WEIGHTS) 86 KTS 199 MPHl EXAMPLE: OAT PRESSURE ALTITUDE T A K E G F WEIGHT HEAD WIND ACCELERATE . STOP DISTANCE DECISION SPEED (IASI t - tb OUTSIDE AIR TEMPERATURE w 0 C WIND COMPONENT 0 WElGHTw POUNDS UI N KNOTS 15-C 158'FI 5860 FT 5UY) LBS 9.5 KTS 3960 Fr 86 KNOTS (99 MPHl Section V BEECHCRAFT Baron 5 8 Performance Serial TH 1 thru TH 772 U33- 39NVlSl(l 5-26 January 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 Section V Performance January 1983 h, OD ASSOCIATED POWER LANDING GEI FLAPS INOPERATIM PROPELLER TAKE-OFF CLIMB GRADIENT - ONE ENGINE INOPERATIVE CONDITIONS: TAKGOFF 4R UP UP FEATHERED CLIMB SPEED (ALL WEIGHTS) -94 KTS I108 MPHI OUTSIDE AIR TEMPERATUREw0C WEIGHT -POUNDS EXAMPLE: - OAT PRESSURE ALTITUDE WEIGHT GHADIENT OF CLIMB I SPEED 15OC l 5 9 F l 5650 FT 4 s M LBS 2.1% 94 KTS llOB MPHl t l ~ l l l ~ l ~ l l l l 4 I I 10 12'14'18 FUEL TO CLIMB-GALS I I + I I I I t o lo 20 90 4 w A 76 Bb DISTANCE TO ~~~~~N M - - - ... 122-71 = 15 MIN fl2.7-4.7) - 8 GAL (55.171 = 38 NM Section V Performance BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 January 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 Section V Performance SERVICE CEILING - ONE ENGINE INOPERATIVE ASSOCIATED CONDITIONS: POW^ MAXIMUM CONTINUOUS IANDING GEAR UP INWERATWE PROPELLER FEATHERED F U P S UP OAT 15OC 159'FJ WEIGHT a 5 0 NOTE SERVICE CEILING IS THE PRESSURE 4LTITUDE WHERE AIRPIANE HAS U P A ~ I L ~OF CLIMBING 50 n MINUTE WITH ONE PROPELLER FEATHERED OUTSIDE AIR TEMPERATURE m0C January 1983 Section V BEECHCRAFT Baron 58 Performance Serial TH 1 thru TH 772 'CRUISE SPEEDS . " ASSOCIATED CONDITIONS- EXAMPLE: -AVERAGE CRUISE WEIGHT (T LBS TEMPERATURE STANDARD DAY IISA) PRESSURE ALTRUDE 11500 FEET POWER SEmNG FULL THROTTLE 2300 RPM TRUE AIRSPEED 185 KTS TRUE AIRSPEED-KNOTS January 1983 BEECHCRAFT Baron 5 8 Serial TH 1 thru TH 772 Section V Performance FUEL FLOW vs BRAKE HORSEPOWER EXAMPLE FUEL FLOWENGINE 1 1 7 GAL HR CONDITION LFVEL FUGHT CIIUISE LEAN BRAKE HORSEPOWER 160 HP PER ENGINE January 1983 Section V . BEECHCRAFT Baron 58 Performance Serial TH 1 thnr TH 772 CRUISE POWER SETTINGS MAXIMUM CRUISE POWER 24.5 IN. HG. @ 2500 RPM (OR FULL THROTTLE) 5200 LBS. NOTES: 1. FULL THROlTLE MANIFOLD PRESSURE SETTINGS ARE Ak!J'ROXlMATE 2. SHADED AREA REPRESENTS OPERATION WITH FULL THROTTLE January 1983 BEECHCRAFTBaron 58 Serial TH 1 thru TH 772 Section V Performance CRUISE POWER SETTINGS RECOMMENDED CRUISE POWER 24.0 IN. HG. @ 2300 RPM (OR FULL THROTTLE) 5200 L B . NOTES: 1.- FULL THROTTLE MANIFOLD PRESSURE I SETTINGS ARE APPROXIMATE 2. SHADED AREA REPRESENTS OPERATION WITH FULL THROTTLE January 1983 . 5-35 Section V . BEECHCRAFT Baron 58 Performance Serial TH 1 thru TH 772 CRUISE POWER SETTINGS RECOMMENDED CRUISE POWER 21.0 IN. HG. @ 2300 RPM (OR FULL THROTTLE) 5200 LBS. NOTES: 1. FULL THROTTLE MANIFOLD PRESSURE January 1983 BEECHCRAFT Baron 58. Section V SerialTH 1 thru TH 772 Performance CRUISE POWER SETTINGS ECONOMY CRUISE POWER 20.6 IN. HG. @ 2100 RPM (OR FULL THROTTLE) 5200 LBS. NOTES: 1. FULL THROTTLE MANIFOLD PRESSURE SE-TTINGS ARE APPROXIMATE 2. SHADED AREA REPRESENTS OPERATION WITH--FULL THROTTLE January 1983 6-37 Section V Performance BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 January 1983 k ENDURANCE PROFILE - 136 GALLONS V) m 3 = ASSOCIATED CONDITIONS STANDARD DAY IISAl @ m EXAMPLE. 3. m - : E2:m 5WO LBS PRESSURE ALTITUDE 11500 FEET 'DoAVIATION GASOLINE FUEL DENSITY 6.0 LBWAL POWER S m l N G FULL TnROlTLE -I= INITIAL FUEL LOADING 136 U S GALS (816 LBSl NOTE 2300 RPM I0 (D ENDURANCE a ENDURANCE INCLUDES START. TAM. CUM0 AND DESCENT 4.75 HRS w , WITH 45 MINUTES RESERVE FUEL AT ECONOMY CRUISE I 4 HRS. 46 MINI - D LU e 3 ffl ffl W aa ENDURANCE N HOURS (ZERO WIND) ii: UI RANGE PROFILE - 166 GALLONS W a A P, 0 ASSOCIATED CONMTIONS STANDARD DAY IISAI EXAMRE -WEIGHT MOO LBS PRESSURE ALTITUDE 11500 R E T 3 ! . FUEL AVIATION GASOLINE FUEL DENSITY 6 0 L B W POWER S W I N G NOTE FULL THROllLE 3 2 INITIAL FUEL LOAMNG 168 U S GAL 1996 LBS) 2100 RPM RANGE INCLUDES START. TAXI, CLIMB AN0 DESCENT WTH 45 MINUTES RESERVE FUEL AT ECONOMY CRUISE RANGE 1115 NM 2m RANGEN NAUTICAL MILES (ZERO MILES) ASSOCIATED CONDITIONS: ENDURANCE PROFILE - 166 GALLONS STANDARD DAY (ISA) -- WIGHT MOO LBS FUEL AVIATlOh GASOLINE FUEL DENSITY 6 0 LBWAL INITIAL FUEL LOADlhG 166 U S GALS (996 WSI NOTE ENDURANCE INUUDES START. TAXI. CLIMB AND DESCENT W T H 05 MINUTES RESERVE FUEL AT ECONOMY CRUISE EXAMPLE: - PRESSURE ALTITUDE 1 l M O FEET POWER SETTING FULL T u R o m E Z M O RPM ENDURANCE 6.0 HRS irA ENDURANCENHOURS (ZERO WIND) Section V BEECHCRAFT Baron 58 Performance Serial TH 1 thru TH 772 l334N 3 0 l l l l l l V 3LlflSS3Lld January 1983 BEECHCRAFT Baron 58 Serial TH 1 thru TH 772 Section V Performance - , ---- 133jeianuiv 3nnss3nd January 1 9 8 3 Section V Performance BEECHCRAFT Baron 58 SerialTH 1thruTH 772 January 1983 BEECHCRAFT Baron 5 8 Serial TH 1 thru TH 772 TIME, FUEL AND ASSOCIATED CONDITIONS POWER AS REOUIRED TO .....".... Sm FTMIY s-m,-,w > RATE-OF-D LANDING GEAR UP FLAPS IIP Section V Performance DISTANCE TO DESCEND EXAMPLE DESCENTSPEED 176 KTS 1201 MPH) JO 35 TIME TO DESCEND -MINUTES t 0 I ' ' 1 I ( I . 2 3 4 5 9 11 12 1\ FUEL T O D E S C E N O N G W O N S t I . , . , ! , . , . 1 ' 1 1 1 z 0 1 0 2 0 30 40 W 60 70 80 I ' 90 DISTANCE TO DESCEND-NM January 1983 ?' $ ASSOCIATED CONDITIONS: POWER TAKE-OFF FLAPS DOWN LANDING GEAR DOWN MIXTURE LEAN TO APPROPRIATE FUEL ROW CLIMB-BALKED LANDING CLIMB SPEED 96 KTS (ALL WEIGHTS1 (1 10 MPHl OAT PRESSURE ALTITUDE WFlGUl ..-.-... RATE Of CLIMB CUM0 GRADIENT OUTSIDE AIR TEMPERATUREN"C M'EIGHT *POUNDS Section V Performance BEECHCRAFT Baron 5 8 Serial TH 1 thruTH 772 INTENTIONALLY LEFT BLANK January 1983 BEECHCRAFT Baron 58 Section VI Serial TH 7 7 3 and After W t and B a v q u i p List I SECTION VI WEIGHT AND BALANCE/ 1 EQUIPMENT LIST TABLE OF CONTENTS SUBJECT PAGE Weighing lnstructions . . . . . . . . . . . . . . . . . . . . . . .. . . . 6-3 Basic Empty Weight and Balance Form . .. . . . . . . . . . 6-5 Weight and Balance Record . . . . . . . . . . . . . . ... . . . . . 6-7 ) Seating. Baggage and Equipment Arrangements .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-9 Loading Instructions . . . . . . . . .. . . . . . . . . . . . . . . . . . . 6-10 Moment Limits vs Weight Table . . . . . ..*. . .. 6-1 1 - 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . , , 6-1 9 Cargo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .6-20 Usable Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-21 Airplane Papers (furnished with individual airplane) 1 October 1976 BEECHCRAFTBaron 68 Section VI Serial TH 773 and After Wt and Bel/Equip List WEIGHING INSTRUCTIONS ' Periodic weighing of the airplane may be required to keep the Basic Empty Weight current. All changes totheairplane affecting weight and balance are the responsibility of the ) airplane's operator. 1. Three jack points are provided for weighing: two on the wlng front spar at Fuselage Stat~on83 1 andoneon the aft fuselage at Fuselage Station 271 0 ) 2. Fuel should be drained preparatory to weighing. Tanks are drained from the regular drain ports with the airplane in static ground attitude. When tanks are drained, 5.7 pounds of undrainable fuel remain in the airplane at Fuselage Station 81.6. The remainderofthe 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 equipment must be in its proper place during weighing. ) 5. The airplane must be longitudinally and laterally level with the landing gear fully extended at the time of weighing. Leveling screwsare locatedonthe left sideof the fuselage at Fuselage Station 152.25 (approx- imately). Longitudinally level attitude is determined with a plumb bob. Laterally level attitude is accom- plished by having the vertical distance.from the leftand right wingtips to the floor, equal. October 1976 6-3 SectionVl BEECHCRAFT Baron 68 Wt and BaVEquip List Serlal TH 773 and After INTENTIONALLY LEFT BLANK October 1976 BEECHCRAFTBaron 58 Section VI SerialTH 773 and After Wt and Sawquip List ~ October 1976 6-5 Section VI BEECHCRAFTBaron 58 Wt and Bal/Equip List Serial TH 773 and After 6. Measurement of the reaction arms for a wheel , j weighing is made using a steel measuring tape. 'Measurements are taken, with theairplane level on the scales, from the reference (a plumb bob dropped from the center of either main jack point) to the axle center line of the main gear and then to the nose wheel axle center line. The main wheel axle center line is best 1 located by stretching a string across from one main wheel to the other. All measurements are to be taken with the tape level with the hangar floor and parallel to the fuselage center li