# Beechcraft BE-55 _ BE-58 Baron — Beech_Baron_58_Study_Guide # NOT FOR FLIGHT — source fidelity: unreviewed | operational review: none | completeness: full # Source: Beechcraft/BE-55 _ BE-58 Baron/Beech_Baron_58_Study_Guide.txt # Rights: licensed # Checklist hash: e6edbc9018ef6be907ad386a66c053cc1a1fe4dafdca387415b1fc32dd21a490 # Verify against the aircraft's own approved documentation before use. section_id phase criticality section_title item_index item_id type tickable memory_item indent text response condition detail reference normal Engines 0 note no no 0 IO-520-CB (285 HP @ 2700 RPM) reference normal Engines 1 note no no 1 (I) Fuel-injected (O) Horizontally Opposed (520) displacement (CB) specific model # reference normal Engines 2 note no no 0 Starter: 24V direct gear drive reference normal Engines 3 note no no 0 Wet sump, pressure type oil system with capacity of 12 quarts (SAE 50) reference normal Engines 4 note no no 0 Ger driven oil pump powered by accessory drive with output of 30-60 PSI reference normal Engines 5 note no no 0 Magnetos: no drop more than 150 RPM or more than 50 RPM between both magnetos reference normal Engines 6 note no no 0 Filtered ram air from top air scoops, if clogged door opens providing alternate air from nacelle reference normal Electrical System 0 note no no 0 28V System with 5.5 amps, 24V lead acid battery (or 2 25 amp 12V batteries) reference normal Electrical System 1 note no no 0 28V Alternators (2) of 50-60 amps, separate from system, except tied Main Batt Bus reference normal Electrical System 2 note no no 0 Two voltage regulators, only one functioning at a time (controlled through switch on subpanel) reference normal Electrical System 3 note no no 0 ALT OUT light on if voltage drops 1.5-2.0V below bus voltage or if over-voltage relay actuated reference normal Fuel System 0 note no no 0 Wet wing tip with 200 gal total, 194 usable (drained at 8 locations) reference normal Fuel System 1 note no no 0 Aux Pumps between fuel selector & eng-driven pump, fed from inboard leading-edge tanks reference normal Fuel System 2 note no no 0 Three bladder-type fuel cells in each wing reference normal Fuel System 3 note no no 0 Fuel pump driven off accessory drive of engine, fuel enters pump at 28-31 PSI reference normal Landing Gear/Brakes 0 note no no 0 28V DC split-field, series wound motor; Drives worm gear reference normal Landing Gear/Brakes 1 note no no 0 Left Gear strut houses auto safety switch and gear warning horn switch (squat switch?) reference normal Landing Gear/Brakes 2 note no no 1 Gear up and throttle below 15” MAP reference normal Landing Gear/Brakes 3 note no no 1 Gear handle in UP position while on ground reference normal Landing Gear/Brakes 4 note no no 1 Gear up with more than 15° Flaps used reference normal Landing Gear/Brakes 5 note no no 0 Air-oil struts on landing gear reference normal Landing Gear/Brakes 6 note no no 0 Main tires: 70 PSI; Nosewheel tire: 50 PSI reference normal Flight Controls 0 note no no 0 Flaps: electrically driven by motor under cabin floor; trailing edge fowler flaps (single-slotted) reference normal Flight Controls 1 note no no 1 Flap position transmitter on flap actuator in left wing, forward of rear spar. reference normal Flight Controls 2 note no no 0 Ailerons: cables routed through bellcranks and pulleys reference normal Flight Controls 3 note no no 0 Aileron Trim: on left aileron; push-pull rod attached to jackscrew-type actuator reference normal Flight Controls 4 note no no 0 Elevator: connected to cables to a torque tube which is connected to a bellcrank in tail reference normal Flight Controls 5 note no no 0 Elevator Trim: located on left and right elevators; push-pull rods attached to jackscrew actuators reference normal Flight Controls 6 note no no 0 Rudder: bellcrank attached to bottom of rudder and cables reference normal Flight Controls 7 note no no 0 Rudder Trim: actuated by push-pull rods attached to a jackscrew-type actuator reference normal Instruments 0 note no no 0 Manifold Pressure: green = 15”-29.6” red line @ 29.6” reference normal Instruments 1 note no no 0 Tachometer: green = 2000-2650 RPM red line @ 2700 RPM reference normal Instruments 2 note no no 0 Fuel Flow: green = 6.9-24.3 GPH white arc = 17.8-24.3 GPH red line @ 24.3 GPH reference normal Instruments 3 note no no 0 Oil Temperature: yellow @ 75° green = 75-240°F red line @ 240°F reference normal Instruments 4 note no no 0 Oil Pressure: min. red line @ 30 PSI green = 30-100 PSI max red line @ 100 reference normal Instruments 5 note no no 0 CHT: Indicates hottest cylinder in engine green = 200-460°F red line @ 460°F reference normal Instruments 6 note no no 0 EGT: Less than 75% power cruise displays relative scale value, not actual temps reference normal Instruments 7 blank no no 0 reference normal Instruments 8 note no no 0 No static system drain due to location of plumbing and components reference normal Instruments 9 note no no 0 Instrument air and DEICE BOOTS provided by 2 eng-driven dry pressure pumps reference normal Instruments 10 note no no 1 Automatic check valves close if one pump fails, 2 air filters per engine reference normal Instruments 11 blank no no 0 reference normal Instruments 12 note no no 0 "Pitot System Static System Electrical Pressure Airspeed Indicator Altimeter VSI Turn Coord Attitude Gyro DG" weight_and_balance normal Weight/Balance 0 note no no 0 Max Ramp: 5424 weight_and_balance normal Weight/Balance 1 note no no 0 MGTOW: 5400 weight_and_balance normal Weight/Balance 2 note no no 0 Max Landing: 5400 weight_and_balance normal Weight/Balance 3 note no no 0 5400 lb CG limit: 78.0 – 86.0 (datum line is 83.1 forward of front jack point) weight_and_balance normal Weight/Balance 4 note no no 0 4200 or less CG limits: 74.0 – 86.0 weight_and_balance normal Weight/Balance 5 blank no no 0 weight_and_balance normal Weight/Balance 6 note no no 0 Nose Compartment: 300 lbs MAX weight_and_balance normal Weight/Balance 7 note no no 0 Aft Cabin: 400 lbs MAX weight_and_balance normal Weight/Balance 8 note no no 0 Rear Compartment: 120 lbs MAX Emergencies normal Emergencies 0 blank no no 0 limitations normal Other Limitations 0 note no no 0 Load Factors: Flaps up (0°) = 4.2G limitations normal Other Limitations 1 note no no 1 Flaps down (30°) = 2.0G limitations normal V-Speeds 0 note no no 0 Va: 156 limitations normal V-Speeds 1 note no no 0 Vfe: 152/122 limitations normal V-Speeds 2 note no no 0 Vle/Vlo: 152 limitations normal V-Speeds 3 note no no 0 Vmca: 81 limitations normal V-Speeds 4 note no no 0 Vne: 223 limitations normal V-Speeds 5 blank no no 0 limitations normal V-Speeds 6 note no no 0 Vno: 195 limitations normal V-Speeds 7 blank no no 0 limitations normal V-Speeds 8 note no no 0 Vs: limitations normal V-Speeds 9 note no no 0 Vso: limitations normal V-Speeds 10 note no no 0 Vsse: 86 limitations normal V-Speeds 11 note no no 0 Vy: 120 limitations normal V-Speeds 12 note no no 0 Vx: limitations normal V-Speeds 13 note no no 0 Vyse: 100 (also min single-engine landing speed) limitations normal V-Speeds 14 note no no 0 Vxse: 96 limitations normal V-Speeds 15 blank no no 0 limitations normal V-Speeds 16 note no no 0 Emer Descent: 152 limitations normal V-Speeds 17 blank no no 0 limitations normal V-Speeds 18 note no no 0 Red Radial: 223 limitations normal V-Speeds 19 note no no 0 White Arc: 74 – 122 limitations normal V-Speeds 20 note no no 0 Green Arc: 84 – 195 limitations normal V-Speeds 21 note no no 0 Blue Radial: 120 limitations normal V-Speeds 22 note no no 0 Yellow Arc: 195 – 223 limitations normal V-Speeds 23 note no no 0 Red Radial: 81 limitations normal V-Speeds 24 note no no 0 White Triangle: 152