# Beechcraft BE-55 _ BE-58 Baron — Beech_Baron_58_Study_Guide

> **NOT FOR FLIGHT** — source fidelity: unreviewed | operational review: none | completeness: full

> **content_gap**: Section "Instruments" item count differs between passes (13 vs 11); verify nothing was dropped.
> **content_gap**: Section "V-Speeds" item count differs between passes (25 vs 21); verify nothing was dropped.
> **content_gap**: Section "Weight/Balance" item count differs between passes (9 vs 8); verify nothing was dropped.

## Engines

> **NOTE:** IO-520-CB (285 HP @ 2700 RPM)
    > **NOTE:** (I) Fuel-injected (O) Horizontally Opposed (520) displacement (CB) specific model #
> **NOTE:** Starter: 24V direct gear drive
> **NOTE:** Wet sump, pressure type oil system with capacity of 12 quarts (SAE 50)
> **NOTE:** Ger driven oil pump  powered by accessory drive with output of 30-60 PSI
> **NOTE:** Magnetos: no drop more than 150 RPM or more than 50 RPM between both magnetos
> **NOTE:** Filtered ram air from top air scoops, if clogged door opens providing alternate air from nacelle

## Electrical System

> **NOTE:** 28V System with 5.5 amps, 24V lead acid battery (or 2 25 amp 12V batteries)
> **NOTE:** 28V Alternators (2) of 50-60 amps, separate from system, except tied Main Batt Bus
> **NOTE:** Two voltage regulators, only one functioning at a time (controlled through switch on subpanel)
> **NOTE:** ALT OUT light on if voltage drops 1.5-2.0V below bus voltage or if over-voltage relay actuated

## Fuel System

> **NOTE:** Wet wing tip with 200 gal total, 194 usable (drained at 8 locations)
> **NOTE:** Aux Pumps between fuel selector & eng-driven pump, fed from inboard leading-edge tanks
> **NOTE:** Three bladder-type fuel cells in each wing
> **NOTE:** Fuel pump driven off accessory drive of engine, fuel enters pump at 28-31 PSI

## Landing Gear/Brakes

> **NOTE:** 28V DC split-field, series wound motor; Drives worm gear
> **NOTE:** Left Gear strut houses auto safety switch and gear warning horn switch (squat switch?)
    > **NOTE:** Gear up and throttle below 15” MAP
    > **NOTE:** Gear handle in UP position while on ground
    > **NOTE:** Gear up with more than 15° Flaps used
> **NOTE:** Air-oil struts on landing gear
> **NOTE:** Main tires: 70 PSI; Nosewheel tire: 50 PSI

## Flight Controls

> **NOTE:** Flaps: electrically driven by motor under cabin floor; trailing edge fowler flaps (single-slotted)
    > **NOTE:** Flap position transmitter on flap actuator in left wing, forward of rear spar.
> **NOTE:** Ailerons: cables routed through bellcranks and pulleys
> **NOTE:** Aileron Trim: on left aileron; push-pull rod attached to jackscrew-type actuator
> **NOTE:** Elevator: connected to cables to a torque tube which is connected to a bellcrank in tail
> **NOTE:** Elevator Trim: located on left and right elevators; push-pull rods attached to jackscrew actuators
> **NOTE:** Rudder: bellcrank attached to bottom of rudder and cables
> **NOTE:** Rudder Trim: actuated by push-pull rods attached to a jackscrew-type actuator

## Instruments

> **NOTE:** Manifold Pressure:     green = 15”-29.6”     red line @ 29.6”
> **NOTE:** Tachometer:      green = 2000-2650 RPM red line @ 2700 RPM
> **NOTE:** Fuel Flow: green = 6.9-24.3 GPH        white arc = 17.8-24.3 GPH red line @ 24.3 GPH
> **NOTE:** Oil Temperature: yellow @ 75°          green  = 75-240°F      red line @ 240°F
> **NOTE:** Oil Pressure:    min. red line @ 30 PSI      green = 30-100 PSI max red line @ 100
> **NOTE:** CHT:  Indicates hottest cylinder in engine         green  = 200-460°F red line @ 460°F
> **NOTE:** EGT:  Less than 75% power cruise displays relative scale value, not actual temps

> **NOTE:** No static system drain due to location of plumbing and components
> **NOTE:** Instrument air and DEICE BOOTS provided by 2 eng-driven dry pressure pumps
    > **NOTE:** Automatic check valves close if one pump fails, 2 air filters per engine

> **NOTE:** Pitot System                      Static System
Electrical  Pressure

      Airspeed Indicator
                                   Altimeter
                                   VSI
                                                         Turn Coord
                                                                    Attitude Gyro
                                                                    DG

## Weight/Balance

> **NOTE:** Max Ramp: 5424
> **NOTE:** MGTOW: 5400
> **NOTE:** Max Landing: 5400
> **NOTE:** 5400 lb CG limit:           78.0 – 86.0 (datum line is 83.1 forward of front jack point)
> **NOTE:** 4200 or less CG limits:     74.0 – 86.0

> **NOTE:** Nose Compartment:      300 lbs MAX
> **NOTE:** Aft Cabin:       400 lbs MAX
> **NOTE:** Rear Compartment:      120 lbs MAX

## Emergencies



## Other Limitations

> **NOTE:** Load Factors:    Flaps up (0°) = 4.2G
    > **NOTE:** Flaps down (30°) = 2.0G

## V-Speeds

> **NOTE:** Va:        156
> **NOTE:** Vfe:       152/122
> **NOTE:** Vle/Vlo:   152
> **NOTE:** Vmca:      81
> **NOTE:** Vne:       223

> **NOTE:** Vno:       195

> **NOTE:** Vs:
> **NOTE:** Vso:
> **NOTE:** Vsse:      86
> **NOTE:** Vy:        120
> **NOTE:** Vx:
> **NOTE:** Vyse:       100 (also min single-engine landing speed)
> **NOTE:** Vxse:      96

> **NOTE:** Emer Descent:    152

> **NOTE:** Red Radial:            223
> **NOTE:** White Arc:       74 – 122
> **NOTE:** Green Arc:       84 – 195
> **NOTE:** Blue Radial:           120
> **NOTE:** Yellow Arc:            195 – 223
> **NOTE:** Red Radial:            81
> **NOTE:** White Triangle:  152

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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.