MilViz Beechcraft Baron 55 Owner's manual

BEECHCRAFT Baron B55
Version 1.0 – 15 May 2012
[1]
Military Visualizations
Beechcraft Baron 55

BEECHCRAFT Baron B55
Version 1.0 – 15 May 2012
[2]
Pilot’s Operating Handbook
Version 1.
Contents
Section 1 Genera 3
Section 2 Limitations 16
Section 3 Emergency Procedures 24
Section 4 Norma Procedures 36
Section 5 Performance 52
Section 6 Weight and Ba ance; Equipment List 93
Section 7 Systems Description 113
Section 8 Credits and Disc aimer 139

BEECHCRAFT Baron B55
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SECTION 1
GENERAL
TABLE OF CONTENTS
Important Notice …………………………………………………………………………………………. 4
Use of the Handbook ………………………………………………………….………..………………. 4
Revising the Handbook ..……………………………………………………………..………………. 5
Airp ane F ight Manua Supp ements Revision Record ……………………..…………. 6
Vendor-Issued STC Supp ements ……………………………………………………..…………. 6
Airp ane Three View …………………………………………………………………..………………. 7
Ground Turning C earance ……………………………………………………..………………….. 8
Descriptive Data ………………………………….…………………..…………………………………. 9
Engines ………………………………………….……..…………..……………………………. 9
Prope ers …………………………………….………….……………………………………… 9
Fue ………………………………….……..…………..……………………………… 10
Standard System ………………………….……..………………………………. 10
Optiona System …………………………..………….………………………….. 10
Oi ……………………………………………………….……………..…………………………… 10
Weights ………………………………………………………….…………..………………………………. 10
Cabin Dimensions ……………………………….…………..………………………………. 10
Baggage ……………………………………………….……….……….……………………….. 11
Specific Loadings ……………………………………..………….…………………………… 11
Symbo s, Abbreviations and Termino ogy ……………………………………………………. 11
Airspeed Termino ogy ……………………………………………………………..………………….. 11
Meteoro ogica Termino ogy …………………………………………………..…………………… 12
Power Termino ogy ………………………………………………………………..……………………. 13
Engine Contro s and Instruments ………………………………………….…………………….. 13
Airp ane Performance and F ight P anning Termino ogy ……………………….…….. 13
Weight and Ba ance Termino ogy …………………………………………….…………………. 14

BEECHCRAFT Baron B55
Version 1.0 – 15 May 2012
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Thanks you for disp aying confidence in us by purchasing the Mi itary Visua ization Beechcraft
Baron 55. Our design engineers, assemb ers and inspectors have uti ized their ski s and years of
experience to ensure that the BEECHCRAFT Baron meets the high standard s of qua ity and
performance for which BEECHCRAFT airp anes have become famous throughout the wor d.
IMPORTANT NOTICE
This handbook must be read carefu y by the owner and operator in order to become fami iar
with the operation of the BEECHCRAFT Baron. The handbook presents suggestions and
recommendations to he p obtain safe and maximum performance without sacrificing economy.
The BEECHCRAFT Baron must be operated according to the Pi ot's Operating Handbook and FAA
Approved Airp ane F ight Manua , and/or p acards ocated in the airp ane.
As a further reminder, the owner and operator of this airp ane shou d a so be fami iar with the
Federa Aviation Regu ations app icab e to the operation and maintenance of the airp ane and
FAR Part 91 Genera Operating and F ight Ru es. Further, the airp ane must be operated and
maintained in accordance with FAA Airworthiness Directives which may be issued against it.
The Federa Aviation Regu ations p ace the responsibi ity for the maintenance of this airp ane
on the owner and the operator who must ensure that a maintenance is done by qua ified
mechanics in conformity with a airworthiness requirements estab ished for this airp ane.
A imits, procedures, safety practices, time imits, servicing, and maintenance requirements
contained in this handbook are considered mandatory for the continued airworthiness of this
airp ane, in a condition equa to that of its origina manufacture.
Authorized BEECHCRAFT Aero or Aviation Centers or Internationa Distributors or Dea ers can provide
recommended modification, service, and operating procedures issued by both FAA and Beech Aircraft
Corporation, which are designed to get maximum uti ity and safety from this airp ane.
USE OF THE HAND BOOK
The Pi ot's Operating Handbook is designed so that necessary documents may be maintained for the
safe and efficient operation of the Baron. The handbook has been prepared in oose eaf form for ease in
maintenance and in a convenient size for storage. The handbook has been arranged with quick
reference tabs imprinted with the tit e of each section and contains ten basic divisions:
Section 1 Genera
Section 2 Limitations
Section 3 Emergency Procedures
Section 4 Norma Procedures
Section 5 Performance
Section 6 Weight and Ba ance; Equipment List
Section 7 Systems Description
Section 8 Hand ing, Servicing and Maintenance

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Section 9 Supp ements
Section 10 Safety Information
NOTE
Except as noted, a airspeeds quoted in this handbook are Indicated
Airspeeds (IAS) and assume zero instrument error.
In an effort to provide as comp ete coverage as possib e, app icab e to any configuration of the airp ane,
some optiona equipment has been inc uded in the scope of the handbook. However, due to the variety
of airp ane appointments and arrangements avai ab e, optiona equipment described and depicted
herein may not be designated as such in every case.
The fo owing information may be provided to the ho der of this manua automatica y:
1. Origina issues and revisions of C ass I and C ass II Service Instructions
2. Origina issues and revisions of FAA Approved Airp ane F ight Manua Supp ements
3. Reissues and revisions of FAA Approved Airp ane F ight Manua s, F ight Handbooks, Owner's Manua s,
Pi ot's Operating Manua s, and Pi ot's operating Handbooks.
This service is free and wi be provided on y to ho ders of this handbook who are isted on the FAA
Aircraft Registration Branch List or the BEECHCRAFT Internationa Owners Notification Service List, and
then on y if isted by airp ane seria number for the mode for which this handbook is app icab e. For
detai ed in- formation on how to obtain "Revision Service" app icab e to this handbook or other
Beechcraft Service Pub ications, consu t a BEECHCRAFT Aero or Aviation Center, Internationa
Distributor or Dea er, or refer to the atest revision of BEECHCRAFT Service Instructions No. 0250-01 0.
BEECH AIRCRAFT CORPORATION EXPRESSLY RESERVES THE RIGHT TO SUPERCEDE, CANCEL, AND/OR
DECLARE OBSOLETE, WITHOUT PRIOR NOTICE, ANY PART, PART NUMBER, KIT OR PUBLICATION
REFERENCED IN THIS HANDBOOK.
The owner/operator shou d a ways refer to a supp ements, whether STC Supp ements or Beech
Supp ements, for possib e p acards, imitations, norma , emergency and other operationa procedures
for proper operation of the airp ane with optiona equipment insta ed.
REVISING THE HANDBOOK
Immediate y fo owing the tit e page is the "Log of Revisions" page(s). The Log of Revisions pages are
used for maintaining a isting of a effective pages in the handbook (except the SUPPLEMENTS section),
and as a record of revisions to these pages. In the ower right corner of the out ined portion of the Log of
Revisions is a box containing a capita etter which denotes the issue or reissue of the handbook. This
etter may be suffixed by a number which indicates the numerica revision. When a revision to any
information in the handbook is made, a new Log of Revisions wi be issued. A Logs of Revisions must be
retained in the handbook to provide a current record of materia status unti a reissue is made.

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WARNING
When this handbook is used for airp ane operationa purposes, it is the pi ot's responsibi ity to maintain
it in current status.
AIRPLANE FLIGHT MANUAL SUPPLEMENTS REVISION RECORD
Section IX contains the FAA Approved Airp ane F ight Manua Supp ements headed by a Log of
Supp ements page. On the "Log" page is a isting of the FAA Approved Supp ementa Equipment
avai ab e for insta ation on the airp ane. When new supp ements are received or existing supp ements
are revised, a new "Log" page wi rep ace the previous one, since it contains a isting of a previous
approva s, p us the new approva . The supp ementa materia wi be added to the grouping in
accordance with the descriptive isting.
NOTE
Upon receipt of a new or revised supp ement, compare the "Log" page
just received with the existing "Log" page in the manua . Retain the
"Log" page with the atest date on the bottom of the page and discard
the other og.
VENDOR-ISSUED STC SUPPLEMENTS
When a new airp ane is de ivered from the factory, the handbook de ivered with it contains either an
STC (Supp ementa Type Certificate) Supp ement or a Beech F ight Manua Supp ement for every
insta ed item requiring a supp ement. If a new handbook for operation of the airp ane is obtained at a
ater date, it is the responsibi ity of the owner/operator to ensure that a required STC Supp ements (as
we as weight and ba ance and other pertinent data) are transferred into the new handbook.

BEECHCRAFT Baron B55
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Aircraft Three View
Figure 1

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Aircraft Turning C earance
Figure 2
A. Radius for Wing Tip ………………………………….…. 29 feet, 6 inches
B. Radius for Nose Whee ……………………………….. 12 feet, 2 inches
C. Radius for Inside Gear ………………………………… 5 feet, 9 inches
D. Radius for Outside Gear …………………………….. 15 feet, 7 inches

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DESCRIPTIVE DATA
ENGINES
Two Continenta IO-520-C fue injected, air coo ed six cy inder, horizonta y-opposed engines each rated
at 285 horsepower at 2700 rpm.
Take-off and Maximum
Continuous Power Fu thrott e and 2700 rpm
Maximum One-Engine Inoperative Power Fu thrott e and 2700 rpm
Cruise C imb Power 25.0 in. Hg at 2500 rpm
Maximum Cruise Power 24.5 in. Hg at 24 50 rpm
PROPELLERS
HARTZELL
2 B ade Hubs: BHC-C2YF-2CHF
B ades: 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 B ade Hubs: BHC-C2YF-2CH B ades: 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 B ade Hubs: PHC-C3YF-2F B ades: FC7663-2R
Pitch Setting at 30 inch Station: Low 13. 5°; Feathered 84.0° Diameter: 76 inches, cut-off permitted to
74.5 inches
or
3 B ade Hubs: PHC-C3YF-2
B ades: C7663-2R
Pitch Setting at 30 inch Station: Low 13.5°; Feathered 84.0°
Diameter: 76 inches, cut-off permitted to 74.5 inches

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or
McCAULEY
2 B ade Hubs: 2AF34C55
B ades: 78FF-O
Pitch setting at 30 inch Station: Low 1 5°; high 79° Diameter: Maximum 78 inches. Minimum 76 inches
FUEL
Aviation Gaso ine 1OOLL (b ue) preferred. 100 (green) minimum grade.
STANDARD SYSTEM:
Tota Capacity 106 Ga ons
Tota Usab e 100 Ga ons
OPTIONAL SYSTEM:
Tota Capacity 142 Ga ons
Tota Usab e 136 Ga ons
OIL
The oi capacity is 12 quarts for each engine.
1-10
WEIGHTS
95-B55
Maximum Ramp Weight 5121 bs
Maximum Take -Off Weight 5100 bs
Maximum Landing Weight 5100 bs
95- B55A
Maximum Ramp Weight 5011 bs
Maximum Take-Off Weight 4990 bs
Maximum Landing Weight 4990 bs
CABIN DIMENSIONS
Length 10 ft 1 in.
Height (Max. ) 4 ft 2 in.
Width (Max. ) 3 ft 6 in.
Entrance Door 37 in. x 36 in.
Standard Baggage Door 18. 5 in. x 22.5 in.
Optiona Baggage Door 38 in. x 22.5 in.

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BAGGAGE
Aft cabin compartment 35 cu ft STD Aft
Hatshe f 1. 7 cu ft
Extended rear compartment 10 cu ft
Nose compartment 12 cu ft
SPECIFIC LOADINGS
Wing Loading 25.6 bs/sq ft
Power Loading 9.8 bs;hp
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
The fo owing Abbreviations and Termino ogies have been isted for convenience and ready
interpretation where used within this handbook. Whenever possib e, they have been categorized for
ready reference.
AIRSPEED TERMINOLOGY
CAS Ca ibrated Airspeed is the indicated speed of an airp ane, corrected for position and instrument
error. Ca ibrated airspeed is equa to true airspeed in standard atmosphere at sea eve .
GS Ground Speed is the speed of an airp ane re ative to the ground.
IAS Indicated Airspeed is the speed of an airp ane as shown on the airspeed indicator when
corrected for instrument error. IAS va ues pub ished in this handbook assume zero instrument error.
TAS True Airspeed is the airspeed of an airp ane re ative to undisturbed air which is the CAS
corrected for a titude, temperature, and compressibi ity.
VMCA Air minimum contro speed is the minimum f ight speed at which the airp ane is directiona y
contro ab e as determined in accordance with Federa Aviation Regu ations. The airp ane certification
conditions inc ude one engine be coming inoperative and windmi ing; a 5° bank towards the operative
engine; takeoff power on operative engine; anding gear up; f aps up; and most rearward e. g. For some
conditions of weight and a titude, sta can be encountered at speeds above VMCA as estab ished by the
certification procedure described above, in which event sta speed must be regarded as the imit of
effective directiona contro .
Vsse The Intentiona One-Engine-Inoperative Speed is a speed above both VMCA and sta speed,
se ected to provide a margin of atera and directiona contro when one engine is sudden y rendered
inoperative. Intentiona fai ing of one engine be ow this speed is not recommended.
Va Maneuvering Speed is the maximum speed at which app ication of fu avai ab e aerodynamic
contro wi not overstress the airp ane.
Vf Design f ap speed is the highest speed permissib e at which wing f aps may be actuated.

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Vfe Maximum F ap Extended Speed is the highest speed permissib e with wing f aps in a prescribed
extended position.
V e Maximum Landing Gear Extended Speed is the maximum speed at which an airp ane can be
safe y f own with the anding gear extended.
V o Maximum Landing Gear Operating Speed is the maximum speed at which the anding gear can
be safe y extended or retracted.
Vne Never Exceed Speed is the speed imit that may not be exceeded at any time.
Vno Maximum Structura Cruising Speed is the speed that shou d not be exceeded except in smooth
air and then on y with caution.
Vs Sta ing Speed or the minimum steady f ight speed at which the airp ane is contro ab e.
Vso Sta ing Speed or the minimum steady f ight speed at which the airp ane is contro ab e in the
anding configuration.
Vx Best Ang e-of-C imb Speed is the airspeed which de ivers the greatest gain of a titude in the
shortest possib e horizonta distance.
Vy Best Rate-of-C imb Speed is the airspeed which de ivers the greatest gain in a titude in the
shortest possib e time.
METEOROLOGICAL TERMINOLOGY
ISA: Internationa Standard Atmosphere in which
1) The air is a dry perfect gas;
2) The temperature at sea eve is 15° Ce sius (59° Fahrenheit);
3) The pressure at sea eve is 29.92 inches Hg. (1 013.2 mi ibars);
4) The temperature gradient from sea eve to the a titude at which the
temperature is -56.5° C (-69.7° F) is -0.00198° C (-0.003566° F) per foot
and zero above that a titude.
OAT: Outside Air Temperature is the free air static temperature, obtained either from inf ight
temperature indications adjusted for instrument error and compressibi ity effects, or ground
meteoro ogica sources.
Indicated Pressure A titude: The number actua y read from an a timeter when the barometric sub-
sca e has been set to 29.92 inches of mercury (10 13. 2 mi ibars).
Pressure A titude: A titude measured from standard sea- eve pressure (29.92 in. Hg) by a pressure or
barometric a timeter. It is the indicated pressure a titude corrected for position and instrument error. In
this Handbook, a timeter instrument errors are assumed to be zero. Position errors may be obtained
from the A timeter Correction Chart.
Station Pressure: Actua atmospheric pressure at fie d e evation.

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Wind: The wind ve ocities recorded as variab es on the charts of this handbook are to be understood as
the headwind or tai wind components of the reported winds.
POWER TERMINOLOGY
Takeoff/Max. Continuous …… The highest power rating not imited by time.
Cruise C imb …………………..…… Power recommended for cruise c imb.
Maximum Cruise ……………….. The highest power settings recommended for cruise.
Recommended Cruise ………. Intermediate power settings presented for cruise power settings.
Economy Cruise ………………… The owest power setting for which cruise power settings are presented.
ENGINE CONTROLS AND INSTRUMENTS TERMINOLOGY
Thrott e Contro s ………………. The ever used to contro the introduction of a fue -air mixture into the
intake passages of an engine.
Prope er Contro s …………….. This ever requests the governor to maintain rpm at a se ected va ue
and, in the maximum decrease rpm, position, feathers the prope ers.
Mixture Contro s ……………… This ever, in the id e cut-off position, stops the f ow of fue at the
injectors and in the intermediate thru the fu rich positions. Regu ates the fue air mixture.
Prope er Governors ………… The governors maintain the se ected rpm requested by the prope er
contro evers.
Manifo d Pressure Gage ….. An instrument that measures the abso ute pressure in the intake
manifo d of an engine, expressed in inches of mercury (in. Hg).
Tachometers …………………….. An instrument that indicates the rotationa speed of the prope er (and
engine) in revo utions per minute (rpm).
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
C imb Gradient ………………… The ratio of the change in height during a portion of a c imb, to the
horizonta distance traversed in the same time interva .
Demonstrated Crosswind …. The demonstrated crosswind ve ocity is the ve ocity of the crosswind
component for which adequate contro of the airp ane during take-off and anding was actua y
demonstrated during certification tests.
Acce erate- Stop Distance ….. The distance required to acce erate to a specified speed and, assuming
fai ure of an engine at the instant that speed is attained, to bring the airp ane to a stop.

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Acce erate- Go Distance ……… The distance required to acce erate to a specified speed and, assuming
fai ure of an engine at the instant that speed is attained, feather inoperative prope er and continue
takeoff on the remaining engine to a height of 50 feet.
MEA …………………………………… Minimum enroute IFR a titude.
Route Segment ………………… A part of a route. Each end of that part is identified by: (1) a
geographica ocation; or (2) a point at which a definite radio fix can be estab ished.
GPH ……………………………….. U.S. Ga ons per hour.
WEIGHT AND BALANCE TERMINOLOGY
Reference Datum …………….. An imaginary vertica p ane from which a horizonta distances are
measured for ba ance purposes.
Station ………………………………. A ocation a ong the airp ane fuse age usua y given in terms of distance
from the reference datum.
Arm ………………………………….. The horizonta distance from the reference datum to the center of
gravity (C.G.) of an item.
Moment ………………………….. The product of the weight of an item mu tip ied by its arm. Moment
divided by a constant is used to simp ify ba ance ca cu ations by reducing the number of digits.)
Airp ane Center of Gravity …. The point at which an airp ane wou d ba ance if suspended. Its distance
from the reference datum is found (C.G.) by dividing the tota moment by the tota weight of the
airp ane.
C.G. Arm …………………………… The arm obtained by adding the airp ane's individua moments and
dividing the sum by the tota weight.
C.G. Limits ………………………… The extreme center of gravity ocations within which the airp ane must
be operated at a given weight.
Usab e Fue ……………………… Fue avai ab e for f ight p anning.
Unusab e Fue …………………. Fue remaining after a runout test has been comp eted in accordance
with governmenta regu ations.
Standard Empty Weight ….. Weight of a standard airp ane inc uding unusab e fue , fu operating
f uids and fu oi .
Basic Empty Weight …………. Standard empty weight p us optiona equipment.
Pay oad …………………………… Weight of occupants, cargo and baggage.
Usefu Load ……………………… Difference between ramp weight and basic empty weight.

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Maximum Ramp Weight …… Maximum weight approved for ground maneuvering. (It inc udes
weight of start, taxi, and run up fue ).
Maximum Takeoff Weight …. Maximum weight approved for the start of the take off run.
Maximum Landing Weight …. Maximum weight approved for the anding touchdown.
Zero Fue Weight ……………….. Weight exc usive of usab e fue .

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SECTION 2
LIMITATIONS
TABLE OF CONTENTS
Airspeed Limitations ……………………………………………………………………….………………………. 17
Airspeed Indicator Markings …………………………………………………….…………………………….. 18
Power P ant Limitations …………………………………………………………………….……………………. 18
Engines ……………………………………………………………………………….……………………… 18
Fue …………………………………………………………………………………….……………………… 18
Oi ……………………………………………………………………………………….…………………….. 18
Prope ers …………………………………………………………………………….……………………. 18
Starters -Time for Cranking ………………………………………………………………….…….…………… 19
Power P ant Instrument Markings ………………………………………………….…….………………… 19
Oi Temperature ……………………………………………………………….…….…………………. 19
Oi Pressure …………………………………………………………………….……..…………………. 19
Fue Pressure …………………………………………………………………………..…………………. 20
Manifo d Pressure …………………………………………………………………..…………………. 20
Tachometer ……………………………………………………………………………..………………… 20
Cy inder Head Temperature …………………………………………………….………………… 20
Misce aneous Instrument Markings …………………………………………………….………………… 20
Suction (vacuum) …………………………………………………………………….…………………. 20
Fue Quantity ………………………………………………………………………….………………….. 20
Weights ……………………………………………………………………………………………….………………….. 20
CG Limits …………………………………………………………………………………………….…………………… 21
Maneuvers ………………………………………………………………………………………….…………………… 21
F ight Load Factors (51 00 Pounds) …………………………………………………….……………………. 21
Minimum F ight Crew ………………………………………………………………………….………………….. 21
Kinds of Operation ……………………………………………………………………………….………………….. 21
Required Equipment for Various Conditions of F ight ………………………….………………….. 21
Legend …………………………………………………………………………………………………………………….. 22
Fue …………………………………………………………………………………………………………………………. 22
Oxygen Requirements ……………………………………………………………………………………………… 23
Maximum Passenger Seating Configuration …………………………………………………………….. 23
Seating ……………………………………………………………………………………………………………………… 23

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The imitations inc uded in this section have been approved by the Federa Aviation Administration.
The fo owing imitations must be observed in the operation of this airp ane.
Figure 3

BEECHCRAFT Baron B55
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Figure 4
POWER PLANT LIMITATIONS
ENGINES
Two Continenta IO-520-C fue injected, air-coo ed six cy inder, horizonta y-opposed engines each rated
at 285 horsepower at 2700 rpm.
Take-off and Maximum continuous power Fu thrott e, 2700 rpm
Maximum Cy inder Head Temperature 460°F
Maximum Oi Temperature 22 5°F
Minimum Take-off Oi Temperature 75°F
Minimum Oi Pressure (Id e) 30 psi
Maximum Oi Pressure 80 psi
FUEL
Aviation Gaso ine 1OOLL (b ue) preferred, 100 (green)
OIL
Ash ess dispersant oi s must meet Continenta Motors Corporation Specification MHS-24 8.
PROPELLERS
HARTZELL
2 B ade Hubs: BHC-C2YF-2 CHF
B ades: FC846 5-6

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Pitch Setting at 30 inch Station: Low 1 6.0°; Feathered 80. 0°
Diameter: 78 inches, cut-off permitted to 76. 5 inches or
2 B ade Hubs: BHC- C2YF-2CH B ades: C8465-6
Pitch Setting at 30 inch Station: Low 1 6.0°; Feathered 80.0°
Diameter: 78 inches, cut-off permitted to 76.5 inches
HARTZELL
1 3 B ade Hubs: PHC-C3YF-2F B ades: FC7663-2R
Pitch Setting at 30 inch Station: Low 13.5°; Feathered 84.0°
Diameter: 76 inches, cut-off permitted to 74.5 inches or
3 B ade Hubs: PHC- C3YF-2
B ades: 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 B ade Hubs: 2AF34C55
B ades: 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 continuous y for more than 30 seconds. A ow starter to coo before cranking
again.
POWER PLANT INSTRUMENT MARKINGS
OIL TEMPERATURE
Caution (Ye ow Radia ) 75°F
Operating Range (Green Arc) 75° to 225°F
Maximum (Red Radia ) 225°F
OIL PRESSURE
Minimum Pressure (Red Radia ) 30 psi
Operating Range (Green Arc) 30 to 60 psi
Maximum Pressure (Red Radia ) 80 psi

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FUEL PRESSURE
Minimum (Red Radia ) 1.5 psi
Operating Range (Green Arc) 5 to17 psi
Cruise Power (Heavy Green Arc) 5 to 9.5 psi
Maximum (Red Radia ) 1 7.5 psi
MANIFOLD PRESSURE
Operating Range (Green Arc) 15 to 29 .6 in.Hg
Maximum (Red Radia ) 29.6 in.Hg
TACHOMETER
Operating Range (Green Arc) 2000 to 2700 rpm
Maximum (Red Radia ) 2700 rpm
CYLINDER HEAD TEMPERATURE
Operating Range (Green Arc) 200 ° to 460°F
Maximum Temperature (Red Radia ) 460°F
MISCELLANEOUS INSTRUMENT MARKINGS
SUCTION (VACUUM)
Minimum (Red Radia ) 3. 75 in.
Hg Operating Range (Green Arc) 3.75 to 5.25 in. Hg
Maximum (Red Radia ) 5.25 in. Hg
Red Button Source Fai ure Indicators or
Operating Range (Green Arc) 4.3 to 5.9 in. Hg
PROPELLER DEICE AMMETER
Norma Operating Range (Green Arc) 7 to 12 amps (2 b ade)
Norma Operating Range (Green Arc) 14 to 18 amps (3 b ade)
FUEL QUANTITY
Ye ow Arc E to 1/ 8 Fu
WEIGHTS
95-B55
Maximum Ramp Weight 5121 bs
Maximum Take-Off Weight 5100 bs
Maximum Landing Weight 5100 bs
Maximum Baggage/Cargo Compartment Weights:
Aft Cabin compartment ( ess occupants and equipment) 400 bs
Extended Rear Compartment 120 bs
Nose Compartment (baggage ess equipment) 300 bs