MilViz Beechcraft Baron 55 Pilot Operating Handbook Download Page 50

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BEECHCRAFT Baron B55

Version 1.0 – 15 May 2012

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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 propeller imbalance due to ice by increasing rpm briefly and return1ng to

the desired setting. Repeat as necessary.

CAUTION

If the propeller deice ammeter indicates abnormal reading, refer
to the Emergency Procedures section.

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.

a. PREFLIGHT

(1) Check the quantity in reservoir

(2) Check slinger ring and lines for obstructions

(3) Check propeller boots for damage

b. INFLIGHT

(1) Prop Anti-ice Switch - ON

(2) Windshield Anti-ice Switch - CYCLE AS REQUIRED

(3) Anti-ice Quantity Indicator - MONITOR

NOTE

See SYSTEM description for endurance.

5. PITOT HEAT AND HEATED STALL WARNING

a. Pitot Heat Switch(es) - ON (Note deflection on Loadmeter) Heated Stall Warning is activated

by the left pitot heat switch.

NOTE

Switches may be left on throughout flight. Prolonged operation on
the ground could damage the Pitot Heat System.

6. FUEL VENT HEAT

a. Fuel Vent Switch - ON (If ice is encountered)

Summary of Contents for Beechcraft Baron 55

Page 1: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 1 Military Visualizations Beechcraft Baron 55 ...

Page 2: ... Version 1 0 Contents Section 1 General 3 Section 2 Limitations 16 Section 3 Emergency Procedures 24 Section 4 Normal Procedures 36 Section 5 Performance 52 Section 6 Weight and Balance Equipment List 93 Section 7 Systems Description 113 Section 8 Credits and Disclaimer 139 ...

Page 3: ...ne Three View 7 Ground Turning Clearance 8 Descriptive Data 9 Engines 9 Propellers 9 Fuel 10 Standard System 10 Optional System 10 Oil 10 Weights 10 Cabin Dimensions 10 Baggage 11 Specific Loadings 11 Symbols Abbreviations and Terminology 11 Airspeed Terminology 11 Meteorological Terminology 12 Power Terminology 13 Engine Controls and Instruments 13 Airplane Performance and Flight Planning Termino...

Page 4: ...viation Regulations place the responsibility for the maintenance of this airplane on the owner and the operator who must ensure that all maintenance is done by qualified mechanics in conformity with all airworthiness requirements established for this airplane All limits procedures safety practices time limits servicing and maintenance requirements contained in this handbook are considered mandator...

Page 5: ...le For detailed in formation on how to obtain Revision Service applicable to this handbook or other Beechcraft Service Publications consult a BEECHCRAFT Aero or Aviation Center International Distributor or Dealer or refer to the latest revision of BEECHCRAFT Service Instructions No 0250 01 0 BEECH AIRCRAFT CORPORATION EXPRESSLY RESERVES THE RIGHT TO SUPERCEDE CANCEL AND OR DECLARE OBSOLETE WITHOUT...

Page 6: ...proval The supplemental material will be added to the grouping in accordance with the descriptive listing NOTE Upon receipt of a new or revised supplement compare the Log page just received with the existing Log page in the manual Retain the Log page with the latest date on the bottom of the page and discard the other log VENDOR ISSUED STC SUPPLEMENTS When a new airplane is delivered from the fact...

Page 7: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 7 Aircraft Three View Figure 1 ...

Page 8: ...ersion 1 0 15 May 2012 8 Aircraft Turning Clearance Figure 2 A Radius for Wing Tip 29 feet 6 inches B Radius for Nose Wheel 12 feet 2 inches C Radius for Inside Gear 5 feet 9 inches D Radius for Outside Gear 15 feet 7 inches ...

Page 9: ...S HARTZELL 2 Blade Hubs BHC C2YF 2CHF Blades FC846 5 6 Pitch Setting at 30 inch Station Low 16 0 Feathered 80 0 Diameter 78 inches cut off permitted to 76 5 inches or 3 Blade Hubs BHC C2YF 2CH Blades C846 5 6 Pitch Setting at 30 inch Station Low 16 0 Feathered 80 0 Diameter 78 inches cut off permitted to 76 5 inches or HARTZELL 3 Blade Hubs PHC C3YF 2F Blades FC7663 2R Pitch Setting at 30 inch Sta...

Page 10: ...llons OPTIONAL SYSTEM Total Capacity 142 Gallons Total Usable 136 Gallons OIL The oil capacity is 12 quarts for each engine 1 10 WEIGHTS 95 B55 Maximum Ramp Weight 5121 lbs Maximum Take Off Weight 5100 lbs Maximum Landing Weight 5100 lbs 95 B55A Maximum Ramp Weight 5011 lbs Maximum Take Off Weight 4990 lbs Maximum Landing Weight 4990 lbs CABIN DIMENSIONS Length 10 ft 1 in Height Max 4 ft 2 in Widt...

Page 11: ...ndisturbed air which is the CAS corrected for altitude temperature and compressibility VMCA Air minimum control speed is the minimum flight speed at which the airplane is directionally controllable as determined in accordance with Federal Aviation Regulations The airplane certification conditions include one engine be coming inoperative and windmilling a 5 bank towards the operative engine takeoff...

Page 12: ...elivers 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 15 Celsius 59 Fahrenheit 3 The pressure at sea level is 29 92 inches Hg 1 013 2 millibars 4 The temperature gradient from sea level to the altitude at which the temperature is 56 5 C 69 7 F is ...

Page 13: ...n 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 Propeller Governors The governors maintain the selected rpm requested by the propeller control levers Manifold Pressure Gage An instrument that measures the absolute pressure in the intake manifold of an engine expressed in inches of mercury in Hg ...

Page 14: ... of an item Moment The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify balance calculations by reducing the number of digits Airplane Center of Gravity The point at which an airplane would balance if suspended Its distance from the reference datum is found C G by dividing the total moment by the total weight of the airplane C G Arm The arm ob...

Page 15: ... approved for ground maneuvering It includes weight of start taxi and run up fuel Maximum Takeoff Weight Maximum weight approved for the start of the take off run Maximum Landing Weight Maximum weight approved for the landing touchdown Zero Fuel Weight Weight exclusive of usable fuel ...

Page 16: ...arkings 19 Oil Temperature 19 Oil Pressure 19 Fuel Pressure 20 Manifold Pressure 20 Tachometer 20 Cylinder Head Temperature 20 Miscellaneous Instrument Markings 20 Suction vacuum 20 Fuel Quantity 20 Weights 20 CG Limits 21 Maneuvers 21 Flight Load Factors 51 00 Pounds 21 Minimum Flight Crew 21 Kinds of Operation 21 Required Equipment for Various Conditions of Flight 21 Legend 22 Fuel 22 Oxygen Req...

Page 17: ...n B55 Version 1 0 15 May 2012 17 The limitations included in this section have been approved by the Federal Aviation Administration The following limitations must be observed in the operation of this airplane Figure 3 ...

Page 18: ...and Maximum continuous power Full throttle 2700 rpm Maximum Cylinder Head Temperature 460 F Maximum Oil Temperature 22 5 F Minimum Take off Oil Temperature 75 F Minimum Oil Pressure Idle 30 psi Maximum Oil Pressure 80 psi FUEL Aviation Gasoline 1OOLL blue preferred 100 green OIL Ashless dispersant oils must meet Continental Motors Corporation Specification MHS 24 8 PROPELLERS HARTZELL 2 Blade Hubs...

Page 19: ... Blade Hubs PHC C3YF 2 Blades C7663 2R Pitch Setting at 30 inch Station Low 1 3 5 Feathered 84 0 Diameter 76 inches cut off permitted to 74 5 inches McCAULEY 2 Blade Hubs 2AF34C55 Blades 78F F O Pitch Setting at 30 inch Station Low 1 5 high 79 Diameter Maximum 78 inches minimum 76 inches STARTERS TIME FOR CRANKING Do not operate starter continuously for more than 30 seconds Allow starter to cool b...

Page 20: ... INSTRUMENT MARKINGS SUCTION VACUUM Minimum Red Radial 3 75 in Hg Operating Range Green Arc 3 75 to 5 25 in Hg Maximum Red Radial 5 25 in Hg Red Button Source Failure Indicators or Operating Range Green Arc 4 3 to 5 9 in Hg 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 WEIG...

Page 21: ...l category airplane Acrobatic maneuvers including spins are prohibited FLIGHT LOAD FACTORS 5100 POUNDS Positive maneuvering load factors Flaps Up 4 4G Negative maneuvering load factor Flaps Up 3 0G MINIMUM FLIGHT CREW One pilot KINDS OF OPERATION This airplane is approved for the following type operations when the required equipment is installed and operational as defined herein 1 VFR day and nigh...

Page 22: ...e that ALL ITEMS WHICH ARE RELATED TO THE AIRWORTHINESS OF THE AIRPLANE AND NOT INCLUDED ON THE LIST ARE AUTOMATICALLY REQUIRED TO BE OPERATIVE To enable the pilot to rapidly determine the FAA equipment requirements necessary for a flight into specific conditions the following equipment requirements and exceptions are presented It is the final responsibility of the pilot to determine whether the l...

Page 23: ...with an adequate supply of oxygen when operating above 12 500 feet MSL Refer to FAR 91 32 for variations concerning supplemental oxygen requirements for a particular flight MAXIMUM PASSENGER SEATING CONFIGURATION Five 5 passengers and one 1 pilot SEATING All seats must be in the upright position for takeoff and landing ...

Page 24: ...ent 28 Glide 28 Landing Emergencies 29 Gear Up Landing 29 One Engine Inoperative Landing 29 One Engine Inoperative Go Around 29 Systems Emergencies 30 One Engine Inoperative Operation on Crossfeed 30 Electrical Smoke or Fire 30 Illumination of Alternator Out Light 31 Landing Gear Manual Extension 32 Landing Gear Retraction After Practice Manual Extension 32 Ice Protection 33 Surface Deice System 3...

Page 25: ... form for easy reference and familiarization Other situations in which more time is usually permitted 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 5100 lbs ONE ENGINE OPERATION Two major factors govern one engine operations airspeed and directional control The ai...

Page 26: ...Continued flight requires immediate pilot response 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 REQUI RED 5 Airspeed MAINTAIN SPEED AT ENGINE FAILURE 100 KTS 115 MPH MAX UNTIL OBSTACLES ARE CLEARED After positive control of the airplane is established 6 Secure inoperative engine a Mix...

Page 27: ...ixture in IDLE CUT OFF When engine fires advance mixture to FULL RICH WITH UNFEATHERING ACCUMULATORS a Move propeller control full forward to accomplish unfeathering Use starter momentarily if necessary b Return control to high pitch low rpm position when windmilling starts to avoid overspeed 7 When Engine Starts ADJUST THROTTLE PROPELLER and MIXTURE CONTROLS 8 Aux Fuel Pump OFF when reliable powe...

Page 28: ... OFF 3 Propeller FEATHERED 4 Aux Fuel Pump OFF 5 Magneto Start Switch OFF 6 Generator Alternator Switch OFF EMERGENCY DESCENT 1 Propellers 2700 RPM 2 Throttles CLOSED 3 Airspeed 153 kts 176 mph 4 Landing Gear DOWN 5 Flaps 10 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 eac...

Page 29: ...tion and no actual tests have been conducted ONE ENGINE INOPERATIVE LANDING On final approach and when it is certain that the field can be reached 1 Landing Gear DOWN 2 Flaps AS REQUIRED 3 Airspeed NORMAL LANDING APPROACH SPEED 90 kts 104 mph 4 Power AS REQUIRED to maintain 800ft min rate of descent When it is certain there is no possibility of go around 5 Flaps DOWN 30 6 Execute normal landing ON...

Page 30: ... 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 Generator Alternator Switches OFF WARNING electrically driven flight instruments will become inoperative 2 Oxygen AS REQUIRED 3 All Electrical Switches OFF 4 Battery and Generator Alt...

Page 31: ...only battery power will be available 4 Battery and Generator Alternator Switches ON 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 ...

Page 32: ... warning horn check LDG GR RELAY circuit breaker engaged CAUTION The manual 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 do not move any landing gear controls or reset any switches or...

Page 33: ...er the circuit breaker has been reset turn the switch off and consider the prop deice system inoperative b Zero to 7 Amps 2 Blade Propeller Zero to 14 Amps 3 Blade Propeller If the prop deice system ammeter occasionally or regularly indicates less than 7 amps for 2 blade or 14 amps for 3 blade operation of the prop deice system can continue unless serious propeller imbalance results from irregular...

Page 34: ...e 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 for egress in addition to the cabin door and the optional cargo door An emergency exit placard is installed below the left and right middle windows To open each emergency exit 1 Lift the latch 2 Pull out the emergency release pin...

Page 35: ...ESSURE NOTE This setting will approximate Zero Thrust using recommended One Engine Inoperative Climb speeds 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 continue to hold this control ...

Page 36: ... 43 Balked Landing 44 After Landing 44 Shutdown 44 Oxygen System 44 Preflight 45 Inflight 45 After Using 45 Cold Weather Operation 46 Preflight Inspection 47 Engines 47 External Power 47 Starting Engines Using Auxiliary Power Unit 47 Taxiing 48 Ice Protection Systems 48 Emergency Static Air Source 48 Surface Deice System 49 Electrothermal Propeller Deice 49 Propeller and Windshield Anti Ice System...

Page 37: ...Climb Vx 84kts 97mph Two Engine Best Rate of Climb Vy 107kts 123mph Cruise Climb 122kts 140mph Turbulent Air Penetration 157kts 181mph Landing Approach Flaps DN 90kts 104mph Flaps 0 97kts 112mph Balked Landing Climb 90kts 104mph Intentional One Engine Inoperative Speed Vsse 84kts 97mph Air Minimum Control Speed Vmca 78kts 90mph PREFLIGHT INSPECTION Figure 5 1 COCKPIT a Control Lock REMOVE AND STOW...

Page 38: ...G EDGE a Lights and Deice Boot CHECK FOR CONDITION b Stall Warning Vane CHECK FREEDOM OF MOVEMENT c Fuel CHECK QUANTITY AND CAP SECURE d Fuel Sight Gage CHECK e Pitot REMOVE COVER EXAMINE FOR OBSTRUCTIONS f Tie Down Chocks REMOVE g Engine Oil CHECK QUANTITY CAP AND DOOR SECURE h Engine Cowling and Doors CHECK CONDITION AND SECURITY i Engine Air Intake EXAMINE FOR OBSTRUCTIONS j Propeller EXAMINE F...

Page 39: ...ipated 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 Brake SET 4 All Avionics OFF 5 Oxygen CHECK QUANTITY AND OPERATION 6 Landing Gear Handle DOWN 7 Cowl Flap CHECK OPEN 8 Fuel Selector Valves CHECK OPERATION THEN ON 9 All Circuit Breakers Switches and Equipment Controls CHECK 10 Battery...

Page 40: ...ondition place mixture controls 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 800 to 1200 RPM 7 Oil Pressure 25 PSI WITHIN 30 SECONDS 8 External Power if used DISCONNECT WARNING When using external power start the right engine first Disconnect external power befor...

Page 41: ...ghts AS REQUIRED 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 Indicators CHECK QUANTITY 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...

Page 42: ...MB SPEED when clear of obstacles MAXIMUM PERFORMANCE CLIMB 1 Power SET MAXIMUM CONTINUOUS POWER 2 Mixtures LEAN TO APPROPRIATE FUEL PRESSURE 3 Cowl Flaps OPEN 4 Airspeed ESTABLISH 107KTS 123MPH CRUISE CLIMB 1 Power SET 25 0in Hg or Full Throttle 2500RPM 2 Mixture Controls LEAN TO APPROPRIATE FUEL PRESSURE 3 Airspeed 122KTS 140MPH 4 Cowl Flaps AS REQUIRED NOTE In high ambient temperatures low press...

Page 43: ...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 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 prol...

Page 44: ...llers 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 Generator 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 ...

Page 45: ... with minimum leakage of oxygen WARNING Since 90 of the system efficiency is determined by the fit of the oxygen mask make certain the masks fit properly and are in good condition The use of oxygen is recommended to be in accordance with current FAR operating rules 1 Oxygen Control Valve OPEN SLOWLY 2 Mask INSERT FITTING DON MASK adjust mask for proper fit 3 Oxygen Flow Indicator CHECK red plunger...

Page 46: ...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 accumulating moisture in the fuel tanks are most favourable at low tempera...

Page 47: ...ting 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 propellers several times to remove cold Oil from the pitch change mechanisms The propellers should also be cycled occasionally in flight During letdown and landing give spec1al attention to engine tempe...

Page 48: ...ditions as soon 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...

Page 49: ...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 inflated boots and prevent ice removal Stall speeds are increased 4 kts 5 mph in all configurations with surface deice system operating NOTE Either engine will supply sufficient vacuum and pressure for deice operation c For ...

Page 50: ...igned to PREVENT the formation of ice Always turn the system ON before entering icing conditions a PREFLIGHT 1 Check the quantity in reservoir 2 Check slinger ring and lines for obstructions 3 Check propeller boots for damage b INFLIGHT 1 Prop Anti ice Switch ON 2 Windshield Anti ice Switch CYCLE AS REQUIRED 3 Anti ice Quantity Indicator MONITOR NOTE See SYSTEM description for endurance 5 PITOT HE...

Page 51: ...2 Flaps Up 3 Airspeed Above 84kts 97mph Vsse 4 Propeller Levers High RPM 5 Throttle Simulated inoperative engine Idle 6 Throttle Other engine Maximum Manifold Pressure 7 Airspeed Reduce approximately 1 knot per second until either VMCA or stall warning is obtained CAUTION Use rudder to maintain directional control heading and ailerons to maintain 5 bank towards the operative engine lateral attitud...

Page 52: ...68 Wind Components 69 Take Off Distance 70 Accelerate Stop Distance 71 Accelerate Go Distance 72 Climb Two Engine 73 Take Off Climb Gradient One Engine Inoperative 74 Time Fuel Distance to Climb 75 Climb One Engine Inoperative 76 Service Ceiling One Engine Inoperative 77 Cruise Speeds 78 Fuel Flow vs Brake Horsepower 79 Fuel Flow vs Fuel Pressure 80 Cruise Power Settings 81 84 Maximum Cruise Power...

Page 53: ...s 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 B55A will be equal to or better than that of the higher gross weight Baron B55 CONDITIONS At Denver Outside Air Temperature 15 C 59 F Field Elevation 5330ft Altimeter Setting 29 60 in Hg Wind...

Page 54: ... altitude and cruise pressure altitude has been ignored Maximum Allowable Take off Weight 5100lbs Ramp Weight 5100 21 5121lbs NOTE Fuel for start taxi and take off is normally 21 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 climb at lift off for one engine inoperative is Take off Weight 4550 pounds Enter the Take O...

Page 55: ...rts Enter the Accelerate Go graph at 15 C 5650 feet pressure altitude 4550 pounds and 9 5 knots headwind component Ground Roll 1800 ft Total Distance Over 50 ft Obstacle 7100 ft Lift off Speed 84kts 97mph 50 Foot Speed 91kts 105mph Enter the graph for Take off Climb Gradient One Engine Inoperative at 15 C 5650 feet pressure altitude and 4550 pounds Climb Gradient 2 2 Climb Speed 91kts 105mph A 2 2...

Page 56: ...l Used to Climb 5 7 2 5 3 2gal Distance Traveled 22 9 13NM The temperatures for cruise are presented for a standard day ISA 20 C 36 F above a standard day ISA 20 C and 20 C 36 F below a standard day ISA 20 C These should be used for flight planning The IOAT values are true temperature values which have been adjusted for the compressibility effects OAT should be used for setting cruise power while ...

Page 57: ...olations are Figure 10 NOTE 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 Time to Descend 23 8 15 min Fuel Used to Descend 6 9 2 2 4 7 gaI Descent Distance 72 24 48 NM Time and fuel used were calculated at Recommended Cruise Power 24 in Hg 2300RPM as follows Time Dis...

Page 58: ...utes 174kts 200mph 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 9 0 gal hr Total Fuel Flow 18 0 gal hr 108lb hr Reserve Fuel 45 min 108lb hr 81lbs 13 5gal Total Fuel 41 4 13 5 54 9 gallons The estimated landing weight is determined by subtracting the fuel required...

Page 59: ...nt 6 0 COMMENTS PERTINENT TO THE USE OF PERFORMANCE GRAPHS 1 The example in addition to presenting an answer for a particular set of conditions also 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 lines Always project to the reference line f...

Page 60: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 60 Figure 13 ...

Page 61: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 61 Figure 14 ...

Page 62: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 62 Figure 15 ...

Page 63: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 63 Figure 16 ...

Page 64: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 64 Figure 17 ...

Page 65: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 65 Figure 18 ...

Page 66: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 66 Figure 19 ...

Page 67: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 67 Figure 20 ...

Page 68: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 68 Figure 21 ...

Page 69: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 69 Figure 22 ...

Page 70: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 70 Figure 23 ...

Page 71: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 71 Figure 24 ...

Page 72: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 72 Figure 24 ...

Page 73: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 73 Figure 25 ...

Page 74: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 74 Figure 26 ...

Page 75: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 75 Figure 27 ...

Page 76: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 76 Figure 28 ...

Page 77: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 77 Figure 29 ...

Page 78: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 78 Figure 30 ...

Page 79: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 79 Figure 31 ...

Page 80: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 80 Figure 32 ...

Page 81: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 81 Figure 33 ...

Page 82: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 82 Figure 34 ...

Page 83: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 83 Figure 35 ...

Page 84: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 84 Figure 36 ...

Page 85: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 85 Figure 37 ...

Page 86: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 86 Figure 38 ...

Page 87: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 87 Figure 39 ...

Page 88: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 88 Figure 40 ...

Page 89: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 89 Figure 41 ...

Page 90: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 90 Figure 42 ...

Page 91: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 91 Figure 43 ...

Page 92: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 92 Figure 44 ...

Page 93: ...d 97 Loading Instructions 99 Seating Baggage and Equipment Arrangements 99 Moment Limits vs Weight Table 100 Moment Limits vs Weight Graph 101 Computing Procedure 105 Sample Weight and Balance Loading Form 106 Weight and Balance Loading Form 107 Useful Load Weights and Moments 108 Occupants 109 Baggage 110 Cargo 111 Usable Fuel 112 Airplane Papers furnished with individual airplane ...

Page 94: ...ge Station 152 25 approximately Level attitude is determined with a plumb bob 6 Measurement of the reaction arms for a wheel weighing is made using a steel measuring tape Measurements are taken with the airplane level on the scales from the reference a plumb bob dropped from the center of either main jack point to the axle center line of the main gear and then to the nose wheel axle center line Th...

Page 95: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 95 Figure 45 Figure 46 ...

Page 96: ...this it is suggested that a running tally of equipment 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 these papers...

Page 97: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 97 Figure 47 ...

Page 98: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 98 Figure 48 ...

Page 99: ...e are the responsibility of the airplane owner and or operator The empty weight and moment of the airplane at the time of delivery are shown on the airplane Empty Weight and Balance form Useful load items which may be loaded into the airplane are shown on the Useful Load Weight and Moment tables The minimum and maximum moments are indicated on the Moment Limits vs Weight table These moments corres...

Page 100: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 100 Figure 50 ...

Page 101: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 101 Figure 51 ...

Page 102: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 102 Figure 52 ...

Page 103: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 103 Figure 53 ...

Page 104: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 104 Figure 54 ...

Page 105: ...t 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 Condition the Take Off Condition and the Landing Condition moment must be withi...

Page 106: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 106 Figure 55 ...

Page 107: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 107 Figure 56 ...

Page 108: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 108 Figure 57 ...

Page 109: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 109 Figure 58 ...

Page 110: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 110 Figure 59 ...

Page 111: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 111 Figure 60 ...

Page 112: ...BEECHCRAFT Baron B55 Version 1 0 15 May 2012 112 Figure 61 ...

Page 113: ...ch 119 Warning Horn 119 Manual Extension 119 Brakes 120 Baggage Cargo Compartments 120 Aft Baggage Cargo Compartment 120 Nose Baggage Cargo Compartment 121 Seating 121 Seat Belts and Shoulder Harnesses 121 Doors Windows and Exits 122 Forward Cabin Door 122 Openable Cabin Windows 122 Emergency Exits 123 Control Locks 123 Installation Instructions 123 Power Plants 123 Power Plant Controls 123 Propel...

Page 114: ... 131 Heating and Ventilation System 132 Cabin Heating 132 Heater Operation 132 Heat Regulation 132 Environmental Schematic 133 Heater Blower 133 Cabin Ventilation 133 Exhaust Vents 134 Individual Fresh Air Outlets 134 Oxygen System 134 Pitot and Static System 134 Pitot System 134 Static System 134 Vacuum System 135 Stall Warning 135 Ice Protection Systems 135 Surface Deice System 135 Propeller and...

Page 115: ... models the optional dual control column therefore the T handle latch is removed as part of this STC upgrade The optional dual control column is required for flight instruction RUDDER PEDALS To adjust the rudder pedals press the spring loaded lever on the side of each pedal arm and move the pedal to its forward or aft position The adjustment lever can also be used to place the right set of rudder ...

Page 116: ...icators for each engine are as follows tachometers manifold pressure fuel pressure fuel quantity and loadmeters Other indicators such as the exhaust gas temperature system the propeller deice ammeter or propeller alcohol quantity and deice pressure are usually installed on the right side of the instrument panel figure 64 Two multi purpose instruments one for each engine indicate cylinder head temp...

Page 117: ... UP OFF DOWN The switch is located on the control console and must be pulled out of a detent before operating Any position within flap travel may be attained by returning the switch to the OFF position A dial type wing flap position indicator marked UP 10 20 and DN is located adjacent to the control switch Figure 67 Figure 66 ...

Page 118: ...n it will be necessary to momentarily move the throttle levers forward for passage of the control column The landing gear is operated through adjustable linkage connected to an actuator assembly mounted beneath the front seats The actuator assembly is driven by an electric motor The landing gear may be electrically retracted and extended and may be extended manually ...

Page 119: ... ground a main strut safety switch opens the control circuit when the strut is compressed CAUTION Never rely on the safety switch to keep the gear down during taxi or on take off landing roll or in a static position Always make certain that the landing gear switch is in the down position during these operations WARNING HORN If either or both throttles are retarded below an engine setting sufficien...

Page 120: ...ress the pilot s toe pedals until firm Push the control in to release the brakes NOTE The parking brake should be left off and wheel chocks installed if the airplane is to be left unattended Changes in ambient temperature can cause the brakes to release or to exert excessive pressures The brakes hydraulic fluid reservoir is accessible through the nose baggage door Fluid level is checked with the d...

Page 121: ...lded down to provide access to the optional extended baggage cargo compartment SEAT BELTS AND SHOULDER HARNESSES PRIOR TO TC 1947 The shoulder harness installation is available for the pilot seats only The belt is in the Y configuration with the single strap being contained in an inertia reel attached to the overhead canopy structure of the cockpit The two straps are worn with one strap over each ...

Page 122: ...tion the latch handle is free to move approximately one inch in either direction before engagement of the locking mechanism Then grasp the door and firmly pull the door closed Rotate the door handle fully counterclockwise into the locked position When the door is properly locked the door latch handle is free to move approximately one inch in either direction NOTE When checking the door latch handl...

Page 123: ...s facing the instrument panel Placard reading CONTROLS LOCKED REMOVE BEFORE FLIGHT will be facing pilot if properly installed INSTALLATION INSTRUCTIONS 1 Close throttles install pin between levers through collar lock and control column Rotate control wheel approximately 12 to the right 2 Route cable and rudder lock around right side of control column position pedals in aft position and install loc...

Page 124: ...cooler when operating temperatures are below normal and will permit the oil to bypass the cooler if it should become blocked The oil system may be checked through access doors in the engine cowling A calibrated dip stick adjacent to the filler cap indicates the oil level Due to the canted position of the engines the dip sticks are calibrated for either right or left engines and are not interchange...

Page 125: ... SYNCHROSCOPE A propeller synchroscope located in the tachometer case operates to give an indication of synchronization of propellers If the right propeller is operating at a higher rpm than the left the face of the synchroscope a black and white cross pattern spins in a clockwise rotation Counterclockwise rotation indicates a higher rpm of the left propeller This instrument aids the pilot in acco...

Page 126: ...63 FUEL PRESSURE INDICATOR The fuel pressure indicator see Figure 74 registers metered fuel pressure at the fuel injection manifold valve It does not indicate either engine driven fuel pump pressure or aux fuel pump pressure Red radials are placed at the minimum and maximum allowable operating fuel pressures The green sectors indicate normal operating range For fuel flow conversions see PERFORMANC...

Page 127: ...e wing fuel system However on emergency crossfeed operations either engine can consume the available fuel from the opposite side The fuel crossfeed system is provided for use during emergency conditions The system cannot be used to transfer fuel from one wing system to the other The procedure for using the crossfeed system is described in the EMERGENCY PROCEDURES section AUXILIARY FUEL PUMPS An in...

Page 128: ...g a reasonable degree of accuracy and be certain of ample fuel for a flight A minimum of 13 gallons of fuel is required in each wing system before takeoff An inaccurate indicator could give an erroneous indication of fuel quantity If the pilot is not sure that at least 13 gallons are in each wing system add necessary fuel so that the amount of fuel will not be less than 13 gallons per wing system ...

Page 129: ...tment Battery servicing procedures are described in the SERVICING section The battery can be turned off in flight and the alternator generators will remain online GENERATORS Two 25 ampere 24 volt generators are standard equipment The generators are belt driven from the engine accessory section The electrical output of each generator is automatically controlled by an individual voltage regulator an...

Page 130: ...r voltage condition or with the switch in the OFF position Any time a failure is detected the appropriate alternator should be turned off These lights can be tested by the TEST WARN LIGHT switch located on the floating instrument panel STARTERS The starters figure 80 are relay controlled and are actuated by rotary type momentary on switches incorporated in the magneto start switches located on the...

Page 131: ...regulates the lighting for the electrical panel avionics panel and the trim tab indicators The magnetic compass light outside air temperature indicator light and map light are operated by a switch on the pilot s control wheel EXTERIOR LIGHTING The switches for the navigation lights landing lights rotating beacons nose gear taxi light and wing ice light s are grouped along the top of the pilot s su...

Page 132: ...witch to the HEATER position 2 The CABIN AIR T handle control which regulates the amount of intake air is below the left side of the pilot s subpanel Push the CABIN AIR control full forward 3 Pull out the CABIN HEAT control to the right of the CABIN AIR control to increase the temperature of the heated air Push the CABIN HEAT control in to decrease temperature 4 For windshield defrosting push in t...

Page 133: ...d in either the HEATER position or the BLOWER position the blower will operate if the landing gear is in the extended position and the CABIN AIR control is more than halfway in The blower will automatically shut off if the landing gear is retracted or the CABIN AIR control is pulled out approximately halfway CABIN VENTILATION In flight to provide unheated air for the same cabin outlets used for he...

Page 134: ... positioned to direct the flow of air as desired OXYGEN SYSTEM NOTE The function and operation of the onboard oxygen system is not modeled on the MilViz Baron 55 PITOT AND STATIC SYSTEM The pitot and static system provides a source of impact and static air for the operation of flight instruments PITOT SYSTEM A standard pitot tube for the pilot s flight instruments is located under the left wing an...

Page 135: ...all weights and airspeeds Irregular and intermittent at first the warning signal will become steady as the airplane approaches a complete stall 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 ...

Page 136: ...ion of the fluid flow style propeller and windshield anti ice systems are not modeled on the MilViz Baron 55 The system is designed to prevent the formation of ice Always place the system in operation before encountering icing conditions Ice is prevented from forming on the propeller blades by wetting the blade anti ice boots with anti icing fluid The anti ice pump delivers a constant flow of flui...

Page 137: ...es are placarded PITOT HEAT LT RT and should remain off during ground operations except for testing or for short intervals of time to remove ice or snow from the mast s STALL WARNING ANTI ICE Optional The mounting pad and the stall warning vane are equipped with a heating element that is activated any time the switch placarded PITOT HEAT LT is on HEATED FUEL VENTS The fuel system vents one located...

Page 138: ...tings for about 30 seconds then returning to cruise power settings Avoid long power off descents especially during 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 ...

Page 139: ...laney DISCLAIMER Note While this POH was designed to strongly replicate the actual Beechcraft Baron 55 POH it must be remembered that this document is intended merely to support virtual flight operations of the MilViz Baron 55 in FSX Nothing written in this document nor in the modeling and presentation of the MilViz Baron 55 should be used to support actual flight operations or to satisfy formal f...

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MilViz Beechcraft Baron 55, Pilot Operating Handbook

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