FlightSafety BARON G8 Installation guide

“The best safety device in any aircraft is a well-trained crew.”™
BARON G58
PILOT TRAINING MANUAL
REVISION 0.2
FlightSafety International, Inc.
Marine Air Terminal, LaGuardia Airport
Flushing, New York 11371
[phone]
www.FlightSafety.com
BARON G58
PILOT
TRAINING
MANUAL
REVISION 0.2

FOR TRAINING PURPOSES ONLY
FOR TRAINING PURPOSES ONLY
NOTICE
The material contained in this training manual is based on information obtained from the aircraft
manufacturer’s Airplane Flight Manual, Pilot Manual, and Maintenance Manuals. It is to be used for
familiarization and training purposes only.
At the time of printing it contained then-current information. In the event of conict between data
provided herein and that in publications issued by the manufacturer or the FAA, that of the manu-
facturer or the FAA shall take precedence.
We at FlightSafety want you to have the best training possible. We welcome any suggestions you
might have for improving this manual or any other aspect of our training program.

Courses for the Baron G58 are taught at the following FlightSafety learning center:
Wichita (Hawker Beechcraft) Learning Center
9720 East Central Avenue
Wichita, Kansas 67206
Phone: [phone]
Toll-Free: [phone]
Fax: [phone]
Copyright © 2012 by FlightSafety International, Inc.
All rights reserved.
Printed in the United States of America.

INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES
LIST OF EFFECTIVE PAGES
Dates of issue for original and changed pages are:
Original ...........0......... May 2007
Revision........ 0.1........ August 2011
Revision........ 0.2........ June 2013
NOTE:
For printing purposes, revision numbers in footers occur at the bottom of every page that has
changed in any way (grammatical or typographical revisions, reow of pages, and other changes
that do not necessarily affect the meaning of the manual).
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CONTENTS
CHAPTER 1 AIRCRAFT GENERAL
CHAPTER 2 ELECTRICAL POWER SYSTEMS
CHAPTER 3 LIGHTING
CHAPTER 4 MASTER WARNING SYSTEM
CHAPTER 5 FUEL SYSTEM
CHAPTER 6 AUXILIARY POWER SYSTEM
CHAPTER 7 POWERPLANT
CHAPTER 8 FIRE PROTECTION
CHAPTER 9 PNEUMATICS
CHAPTER 10 ICE AND RAIN PROTECTION
CHAPTER 11 AIR CONDITIONING
CHAPTER 11A AIR CONDITIONING
CHAPTER 12 PRESSURIZATION
CHAPTER 13 HYDRAULIC POWER SYSTEM
CHAPTER 14 LANDING GEAR AND BRAKES
CHAPTER 15 FLIGHT CONTROLS
CHAPTER 16 AVIONICS
CHAPTER 17 MISCELLANEOUS SYSTEMS
CHAPTER 18 PERFORMANCE, WEIGHT AND BALANCE
APPENDIX A FLIGHT PROFILES
APPENDIX B TERMS AND ABBREVIATIONS

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BARON G58 PILOT TRAINING MANUAL
1 AIRCRAFT GENERAL
INTRODUCTION .................................................................................................................. 1-1
GENERAL.............................................................................................................................. 1-1
History and Significant Design Changes......................................................................... 1-1
STRUCTURES ....................................................................................................................... 1-4
Aft Fuselage and Cabin ................................................................................................... 1-4
Nose Baggage Compartment........................................................................................... 1-5
Forward Cabin Door........................................................................................................ 1-5
Aft Cabin Doors .............................................................................................................. 1-6
Cabin Windows ............................................................................................................... 1-7
Executive Writing Desk................................................................................................... 1-7
Seats and Seat Belts......................................................................................................... 1-8
GROUND CONTROL............................................................................................................ 1-8
LIMITATIONS........................................................................................................................ 1-9
QUESTIONS ........................................................................................................................1-10
CHAPTER 1
AIRCRAFT GENERAL
CONTENTS
Page

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1 AIRCRAFT GENERAL
ILLUSTRATIONS
Figure Title Page
TABLES
Table Title Page
1-1 Beechcraft Baron 58 ................................................................................................... 1-2
1-2 Baron G58 Dimensions .............................................................................................. 1-3
1-3 Aft Cargo Area............................................................................................................ 1-4
1-4 Nose Baggage Compartment...................................................................................... 1-5
1-5 Forward Cabin Door ................................................................................................... 1-5
1-6 Aft Cabin Doors ......................................................................................................... 1-6
1-7 Emergency Exits......................................................................................................... 1-7
1-8 Executive Writing Table.............................................................................................. 1-7
1-9 Baron G58 Ground Turning Clearance....................................................................... 1-8
1-1 Airspeed Limitations ....................................................................................................1-9
1-2 Airspeed Indicator Markings........................................................................................1-9

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1 AIRCRAFT GENERAL
Revision 0.1
CHAPTER 1
AIRCRAFT GENERAL
INTRODUCTION
This chapter provides a brief history of the Beech Baron, as well as a partial list of the signifi-
cant design changes that have been made on the Baron G58 aircraft. Descriptions of the general
structure of the aircraft, baggage compartments, and interior are discussed.
GENERAL
HISTORY AND SIGNIFICANT
DESIGN CHANGES
The Beech Model 95-55 Baron was the founding
member of a remarkable family of aircraft.
First flown on February 29, 1960, the Model
95-55 was developed from the earlier Model 95
Travel Air, diering primarily in having more
powerful engines, and design refinements. These
improvements included a swept vertical tail
surface and improved all-weather capability.
Deliveries began in November 1960, and
acceptance of the new twin-engine four/five-
seat aircraft resulted in further improvement and
development of the aircraft.
The Model B55, introduced in 1963, had four
seats or an optional five/six-seat option. In 1965, a
Model C55 was available with the more powerful

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BARON G58 PILOT TRAINING MANUAL
1 AIRCRAFT GENERAL
Revision 0.1
285-horsepower Continental IO-520-C engines.
The Model C55 included increased tailplane span
and an extended nose baggage compartment and
evolved as a separate Baron model, distinct from
the B55.
The United States Army selected the Model
95-B55 for military service as an instrument
trainer under the designation T-42A Cochise. By
1982, production of civil and military 95-B55
Barons surpassed 2,400.A total of 1,201 examples
of the Model E55 (formerly the C/D55) had been
delivered when production ended.
In 1969, the Baron family introduced the Model
58 (Figure 1-1). It was first flown in June of that
year. The 58 was a Model 55 fuselage lengthened
10 inches, providing a larger cabin. Double cargo
doors (on the right side of the fuselage) created
greater access to the aft cabin and rear baggage
areas.
The Model 58 was initially powered by
Continental IO-520-C engines (found on the
E55), but was upgraded to the more powerful
IO-550-C engines. The pressurized Model 58P
was introduced in 1975, and the Model 58TC was
introduced in 1976.
In 1984, Beechcraft changed the configuration
of the Model 58 instrument panel, incorporating
smaller, turbine-style engine instruments and
a more conventional throttle quadrant with
propeller and mixture controls.
In 1984, the 300-horsepower IO-550-C engines
were made standard along with the addition of dual
control columns and known-icing certification.
The production total of all model Barons, as of
August 2002, was approximately 6,500.
In December 2005, Hawker Beechcraft received
certification for and began delivering the latest
Baron Model G58 aircraft. The G58 Baron
introduced the technically advanced Garmin
G1000 avionics suite. The avionics suite utilizes
Garmin’s new GFC 700 automatic flight control
system, as well as Garmin’s new GWX 68 all
weather radar platform. XM Satellite technology
provides near real-time Nexrad composite radar
information, while terrain and trac awareness
are enhanced by standard terrain awareness and
warning system (TAWS-B), trac information
system (TIS), and optional trac advisory system
(TAS).
The Baron G58 is an all-metal, low-wing, four-
to-six seat, twin-engine aircraft with retractable
landing gear. It is constructed primarily of
aluminum and is certified under Part 23 of the
Federal Aviation Regulations in the Normal
Category. The Baron G58 is approved for day
and night visual flight rule (VFR) and instrument
flight rule (IFR) operations and is also approved
for flight into known icing conditions when
properly equipped.
Refer to Figure 1-2 for the Baron G58 dimensions.
Figure 1-1. Beechcraft Baron 58

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1 AIRCRAFT GENERAL
Revision 0.1
77" DIAMETER
15'11"
WING AREA: 199.2 SQ FT
9'7"
9'9"
29'10"
8'11"
10.4"
37'10"
Figure 1-2. Baron G58 Dimensions

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BARON G58 PILOT TRAINING MANUAL
1 AIRCRAFT GENERAL
STRUCTURES
AFT FUSELAGE AND CABIN
The aft fuselage contains control cables, bell-
cranks, pulleys, autopilot servos, and the
emergency locator transmitter (ELT). The aft
cabin contains a cargo/baggage compartment and
net, coat hanger, hat shelf, and display area for
aircraft documentation. The maximum weight
allowable for the aft baggage compartment is
120 pounds. Baggage should be secured with the
installed cargo net (Figure 1-3). Heavy objects
must not be placed on the hat shelf, or damage
may result. Objects in the aft compartment must
always be secured properly.
Figure 1-3. Aft Cargo Area

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1 AIRCRAFT GENERAL
NOSE BAGGAGE
COMPARTMENT
The nose baggage compartment (Figure
1-4) is an unheated cargo/baggage area that
contains avionics and electrical equipment. The
maximum allowable weight in the nose baggage
compartment is 300 pounds. Refer to Section
6, Weight and Balance of the Pilot’s Operating
Handbook (POH) for information regarding the
proper loading of cargo and/or baggage, as well
as any limitations that apply.
The nose baggage compartment door is on the
right side of the fuselage (forward of the cockpit),
and is held open by a lever during the loading or
unloading of baggage. The door is held closed
by two latch mechanisms and can be secured for
flight (or storage) with lock and key. An additional
safety latch is on the door to prevent the door from
opening in flight. The nose baggage lock prevents
operation of the forward latch mechanism, but
does not otherwise physically secure the door.
The door must be locked prior to flight to prevent
movement of the forward latch due to vibration.
There is no cockpit annunciation or indication to
warn the pilot of an unsecured nose baggage door.
A light for the nose baggage compartment is pow-
ered by the hot bus and controlled by a switch. All
G58 models have manual ON/OFF switches but
no AUTO switches.
FORWARD CABIN DOOR
The forward cabin entry door is on the right side
of the aircraft for use by the pilot and front seat
occupant (Figure 1-5). If seats No. 3 and No. 4
are configured for forward facing passengers, the
occupants of seats No. 3 and No. 4 also use this
door.
The forward cabin door is held closed by two
pins that insert into the fuselage door frame and a
hook-and-latch mechanism on the top of the door.
The front door is unlatched from inside the cabin
by depressing the lock button and then rotating
the handle to the most clockwise position. To
open the door from the outside, pull the handle
out from its recess until the door opens.
The forward cabin door is held open by a stay bar
that slides up and into the bottom of the door when
fully opened. To avoid damage to the stay bar and
door, park the aircraft facing into the wind.
To close, pull the door firmly into position and
rotate the handle to its most counterclockwise
position. Two distinct clicks are heard and the
handle swings freely through a small arc.
Figure 1-4. Nose Baggage Compartment Figure 1-5. Forward Cabin Door

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To ensure the door is properly secured for flight,
complete the following checks:
1. Verify that the interior handle swings
freely through an approximate 3-inch arc.
2. Press firmly on the upper rear corner of
the door. The top door latch must be prop-
erly engaged. Pressing the door verifies
security. If the door corner moves out-
ward, the latch is not engaged.
3. Courtesy lights—O.
If not properly latched, the forward door may open
during takeo or in flight. Aircraft controllability
is not aected, but a large amount of wind noise
and some slight aerodynamic bueting occurs. Do
not attempt to close an open door in flight. Make
a normal landing and secure the door properly
when clear of the runway.
The forward cabin door can be used as an emer-
gency exit and, while unattended, the aircraft may
be locked with the key for security.
AFT CABIN DOORS
Dual cabin doors are installed for use by the
rear seat passengers (Figure 1-6). If the aircraft
is configured for club seating, all passengers use
these doors for entry and exit.
The aft cabin door assembly consists of two
halves. The forward door is held closed by two
bayonet pins actuated by an exterior D-ring handle
and an interior conventional handle. The rear half
of the aft cabin door is held closed by two J-hooks
actuated by a lift lever recessed into the edge of
the aft door. The aft cabin doors are held open by
stay bars that lock overcenter when fully opened.
The forward door overlaps and secures the aft
door (the aft door must be closed prior to closing
and securing the forward door).
The pilot should secure the aft cabin doors. The
doors can be used as an emergency exit and can
be locked from the outside for security.
Do not lock the rear doors prior to flight. This
prevents them from being used as an emergency
Figure 1-6. Aft Cabin Doors

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BARON G58 PILOT TRAINING MANUAL
1 AIRCRAFT GENERAL
exit. If the doors are not locked, they can be
opened in flight by simply rotating the interior
handle. To prevent an inadvertent opening of
the doors in flight, brief the passengers on door
operation prior to flight. If the aft cabin doors are
not properly latched, an AFT DOOR alert displays
on the primary flight display (PFD).
To ensure that the doors are secure for flight, per-
form the following checks:
1. Ensure that the aft door J-hooks fully
engage against the door frame.
2. Ensure that the exterior D-ring handle is
in a horizontal position.
3. Verify that the AFT DOOR alert on the
PFD is cleared.
4. Courtesy lights—O.
The aircraft may be flown with the aft cabin doors
removed provided that all applicable limitations
are complied with.
CABIN WINDOWS
The Baron G58 windows are of Plexiglas
construction and are cleaned using only a soft
cloth and nonabrasive soap and water. Never
use gasoline, benzene, alcohol, acetone, carbon
tetrachloride, fire-extinguisher fluid, anti-ice
fluid, lacquer thinner, or glass cleaner to clean the
windows. After drying, apply a thin coat of wax
to help prevent scratches, bung by hand only.
The windscreen is a one-piece, wraparound
assembly. Four side windows are on each side of
the cabin. The pilot side window has an openable
storm window. The forward passenger windows
may be opened for ventilation on the ground, but
must be closed for flight and may also be used
as emergency exits (Figure 1-7). The procedure
for opening the windows for emergency exit is
described on a placard near the window and in
the FlightSafety Training Checklist. When the
emergency exit latch is disengaged, the window
swings up allowing exit. Brief passengers on
window operation prior to flight.
The windows are safety-wired to prevent inad-
vertent release of the emergency exit mechanisms
and .020 copper wire is specified for use (refer
to the POH). Preflight inspection must include
verifying the use of proper wire and its condition
after maintenance prior to carrying passengers.
EXECUTIVE WRITING DESK
The Baron G58 is equipped with an executive
writing desk on the side wall of the aft cabin
area (Figure 1-8). The desk is is for light loads
and must be stowed for takeo and landing. Brief
passengers on its use before flight.
Figure 1-7. Emergency Exits
Figure 1-8. Executive Writing Table

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SEATS AND SEAT BELTS
Standard seats in the aircraft are adjustable fore
and aft by a latch release bar under the seat. The
seat backs of the four standard seats can also be
adjusted to any of four positions by a release lever
on the inboard side of each seat.
The No. 3 and No. 4 seats can be folded over by
rotating the red handle on the lower inboard side
of the seat back. Seats No. 5 and No. 6 are not
adjustable but may be placed in the stowed position
to provide additional floor space, or folded down
for access to the aft baggage compartment.
Some passenger seats may be fully reclined but
must be in the upright position for takeo and
landing. Outboard armrests for all seats are built
into the cabin sidewalls. Center armrests can be
elevated or positioned flush with the seat cushion.
The aircraft can be flown with the aft four seats
removed if the Weight and Balance Data and
Equipment List is updated.
The center row of seats can be installed in a
forward- or rear-facing configuration. If reversing
the seats, ensure that the center armrests are
positioned correctly and the seat stops are
installed properly to preclude the seats from
rolling o their rails.
When installed in the club-seating configuration,
the No. 3 and No. 4 seats must have the headrests
fully raised during takeo and landing. Lap belts
and shoulder harnesses are standard for all seats
in the aircraft and all occupants are required to
wear these for takeo and landing. The pilot is
required to wear a seat belt and shoulder harness
at all times during flight.
GROUND CONTROL
The Baron is maneuvered on the ground using
a combination of dierential power, dierential
braking, and nosewheel steering. A spring-loaded
linkage from the nosewheel to the rudder pedals
provides nosewheel steering.
Smooth turning is accomplished by allowing the
aircraft to roll while pressing the appropriate rud-
der pedal (Figure 1-9). Sharper turns require light
rudder/brake pedal pressure. The inboard wheel
must rotate during a sharp turn to prevent the
nosewheel from dragging across the ground. If a
wingtip can clear an object in the turn, the tail
will also.
B
C
D
ARADIUS FOR WINGTIP.................. 31 FEET 6 INCHES
RADIUS FOR NOSEWHEEL........... 15 FEET 6 INCHES
RADIUS FOR INSIDE GEAR........... 7 FEET 11 INCHES
RADIUS FOR OUTSIDE GEAR ....... 17 FEET 6 INCHES
B
C
A
D
Figure 1-9. Baron G58 Ground
Turning Clearance

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BARON G58 PILOT TRAINING MANUAL
1 AIRCRAFT GENERAL
LIMITATIONS
The limitations of the aircraft and subsystems are
discussed in this manual as they apply to each
system. For the full list of limitations, refer to the
POH.
Airspeed limitations are shown in Table 1-1.
Airspeed indicator markings are shown in Table
1-2.
SPEED KCAS KIAS REMARKS
Never Exceed
(VNE)223 223
Do not exceed
this speed in any
operation.
Maximum
Structural
Cruising
(VNO or VC)
195 195
Do not exceed this
speed except in
smooth air and then
only with caution.
Maneuvering (VA) 156 156
Do not make full
or abrupt control
movements above
this speed.
Maximum Flap
Extension/
Extended (VFE)
Approach (15°)
Full Down (30°)
152
122
152
122
Do not extend aps
or operate with aps
extended above this
speed.
Maximum Landing
Gear Operating/
Extended
(VLO/VLE)
152 152
Do not extend, retract
or operate with gear
extended above this
speed.
Single-Engine
Minimum Control
Speed (VMCA )
83 83
Minimum speed
for directional
controllability after
sudden loss of
engine.
Maximum With
Utility Doors
Removed
174 174 Utility door removal
kit must be installed.
COLOR
CODED SPEED
RANGE STRIP
OR MARKING
KIAS
RANGE SIGNIFICANCE
White Strip 74–122
Full Flap Operating Range
Lower Limit = Stall speed
with aps down at maximum
weight.
Upper Limit = Maximum
speed permissible with aps
fully extended.
White Triangle 152 Maximum Speed for
approach aps
Blue Strip 101 Minimum Single-Engine
Control (VMCA)
Red Strip 84
Normal Operating Range
Lower Limit = Stall speed
with aps up at maximum
weight.
Upper Limit = Maximum
Structural Cruise Speed
Green Strip 84–195
Do not extend, retract or
operate with gear extended
above this speed.
Yellow Strip 195–223
Caution Range.
Approved for smooth air only.
Upper Limit = Never Exceed
Speed. Maximum speed for
all Operations.
Red & White Strip >223 High Speed Warning
Table 1-1. AIRSPEED LIMITATIONS
Table 1-2. AIRSPEED INDICATOR
MARKINGS

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1 AIRCRAFT GENERAL
To answer the following questions, refer to the
FlightSafety PilotTraining Manual, PilotTraining
Checklist, and ground school notes:
1. What cockpit indication alerts the pilot
that the nose baggage door is not properly
secured?
2. List the three checks that ensure the forward
door is properly secured for flight:
1.
2.
3.
3. List the four checks that ensure the aft door
is properly secured for flight:
1.
2.
3.
4.
4. Should the rear doors be locked for flight?
5. When are crewmembers and passengers
required to wear seat belts and shoulder har-
nesses?
6. What procedure is followed if the forward
door opens in flight?
QUESTIONS

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BARON G58 PILOT TRAINING MANUAL
2 ELECTRICAL POWER
SYESTEMS
INTRODUCTION .................................................................................................................. 2-1
GENERAL.............................................................................................................................. 2-1
Description ...................................................................................................................... 2-1
COMPONENTS ..................................................................................................................... 2-2
Batteries........................................................................................................................... 2-2
Alternators....................................................................................................................... 2-2
Bus Tie Relays................................................................................................................. 2-2
Starters............................................................................................................................. 2-2
External Power Receptacle.............................................................................................. 2-2
CONTROLS AND INDICATIONS........................................................................................ 2-3
Alternator Switches......................................................................................................... 2-3
BUSES TIED Message.................................................................................................... 2-3
Battery Switches.............................................................................................................. 2-3
Start Magneto Switches................................................................................................... 2-3
Indicators......................................................................................................................... 2-4
Electrical Buses ............................................................................................................... 2-4
Circuit Breakers............................................................................................................... 2-7
Current Limiters .............................................................................................................. 2-7
OPERATION .......................................................................................................................... 2-7
EMERGENCY/ABNORMAL................................................................................................ 2-7
GLOSSARY OF ELECTRICAL TERMS ............................................................................. 2-8
QUESTIONS .......................................................................................................................... 2-9
CHAPTER 2
ELECTRICAL POWER SYSTEMS
CONTENTS
Page

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2 ELECTRICAL POWER
SYESTEMS
ILLUSTRATIONS
Figure Title Page
2-1 External Power Receptacle ......................................................................................... 2-2
2-2 MASTER Electrical Toggle/Breaker Switches........................................................... 2-3
2-3 Alternator Load Display on Default Engine Page ...................................................... 2-4
2-4 Electrical System Diagram......................................................................................... 2-5
2-5 Circuit-Breaker Panels................................................................................................ 2-6