CESSNA SECTION 1

MODEL 208B 867 SHP GENERAL

GARMIN G1000

GENERAL

TABLE OF CONTENTS

Page

Three View - Normal Ground Attitude . . . . . . . . . . . . . . . . . . . . . . . . 1-3

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5
Descriptive Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6
Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6
Propeller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-6
Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-7
Oil . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-10
Maximum Certificated Weights . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11
Cabin And Entry Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11
Baggage/Cargo Compartment and
Cargo Door Entry Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . 1-11
Specific Loadings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11
Navigational Capabilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-12
ADS-B Out (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-16
Symbols, Abbreviations and Terminology . . . . . . . . . . . . . . . . . . . . 1-17
General Airspeed Terminology And Symbols . . . . . . . . . . . . . . . 1-17
Meteorological Terminology . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-18
Engine Power Terminology . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-18
Airplane Performance And Flight Planning Terminology. . . . . . . 1-20
Autopilot/Flight Director and AFCS Terminology. . . . . . . . . . . . . 1-21
Weight And Balance Terminology . . . . . . . . . . . . . . . . . . . . . . . . 1-22
Metric/Imperial/U.S. Conversion Charts. . . . . . . . . . . . . . . . . . . . . . 1-24
Weight Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-25
Length Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-27
Distance Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-31
Volume Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-32
Temperature Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-35
Pressure Conversion. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-36

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GENERAL MODEL 208B 867 SHP
GARMIN G1000

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

THREE VIEW - NORMAL GROUND ATTITUDE

Figure 1-1 (Sheet 1 of 2)*

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

THREE VIEW - NORMAL GROUND ATTITUDE

NOTE
• Normal ground attitude shown is based on standard
empty weight, proper inflation of nosewheel and main
gear tires and wings level. Tail height will increase with
oversized tires.
• Wing span shown with position/strobe lights installed.
• Maximum height shown with nose strut barrel fully
compressed as far as possible.
• Wheel base length is 13 feet - 3.5 inches (4.05 m).
• Wing area is 279.4 square feet (25.95 sq. m).
• Minimum turning radius (*pivot point to outboard wing tip
strobe light) is 33 feet - 8 inches (10.26 m).
• Propeller ground clearance varies between 2.5 inches
(63.50 mm) and 14.75 inches (374.65 mm) depending
upon configuration and installed options. Refer to
Descriptive Data, Propeller, in this section for complete
listing of propeller ground clearances.

Figure 1-1 (Sheet 2)*

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

INTRODUCTION
This POH/AFM contains 9 sections, and includes the material required
to be furnished to the pilot by 14 CFR 23. It also contains supplemental
data supplied by the manufacturer. This POH/AFM constitutes the FAA
Approved Airplane Flight Manual.
WARNING
• This POH/AFM is not intended to be a guide for
basic flight instruction or a training manual and
should not be used as one. It is not a substitute
for adequate and competent flight instruction,
pilot skill, and pilot knowledge of current
Airworthiness Directives, applicable Federal
Aviation Regulations and/or Advisory Circulars.
• Assuring the airworthiness of the airplane is the
responsibility of the airplane owner or operator.
Determining if the airplane is safe for flight is the
responsibility of the pilot in command. The pilot
is also responsible for adhering to the operating
limitations set forth by instrument markings,
placards, and this POH/AFM.
Generally, information in this POH/AFM is applicable to both the cargo
version and the passenger version of the Model 208B. Some
equipment differences exist between these versions. Specific versions
are identified through use of the terms “Cargo Version” and “Passenger
Version”. When one of these terms appears in text or on an illustration,
the information applies only to that group of airplanes. If no term
appears, the information applies to all airplanes.

Section 1 provides basic data and information of general interest. It

also contains definitions or explanations of symbols, abbreviations, and
terminology commonly used.

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

DESCRIPTIVE DATA
ENGINE
Number of Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
Engine Manufacturer . . . . . . . . . . . . . Pratt & Whitney Canada, Inc.
Engine Model Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . PT6A-140
Engine Type:
Free turbine, two-shaft engine utilizing a compressor section having
three axial stages and one centrifugal stage, an annular reverse-flow
combustion chamber, a one-stage compressor turbine, a one-stage
power turbine, and a single exhaust. The power turbine drives the
propeller through a two-stage planetary gearbox at the front of the
engine.
Horsepower . . . . . . . . . . . . . . . . . . . . . . . . . . . Flat rated at 867 SHP
PROPELLER
HARTZELL
Propeller Manufacturer . . . . . . . . . . . . . . . . . . Hartzell Propeller Inc.
Propeller Model Number . . . . . . . . . . . HC-B3TN-3AF/T10890CN-2
Number of Blades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
Propeller Diameter. . . . . . . . . . . . . . . Maximum 106 Inches (2.69 m)
Minimum 104 Inches (2.64 m)
Propeller Type:
Constant-speed, full-feathering, reversible, hydraulically-
actuated aluminum-bladed propeller, with a feathered blade
angle of 78.0° +1.0°, a low pitch blade angle of 8.5° +0.2°, and a
maximum reverse blade angle of -21° +0.5° at FS 42.00.
Propeller ground clearance with standard tires and standard length
nose gear fork:
With nose tire inflated and nose strut barrel extended
3.625 inches (92.07 mm), propeller ground clearance is
11.25 inches (285.75 mm).
With nose tire deflated and nose strut barrel fully
compressed, propeller ground clearance is 2.5 inches
(63.50 mm).
Propeller ground clearance with standard tires and extended length
nose gear fork:
With nose tire inflated and nose strut barrel extended
3.625 inches (92.07 mm), propeller ground clearance is
14.75 inches (374.65 mm).
With nose tire deflated and nose strut fully compressed,
propeller ground clearance is 5.875 inches (149.22
mm).

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

DESCRIPTIVE DATA (Continued)

FUEL

WARNING
Use of unapproved fuels may result in damage to
the engine and fuel system components, resulting
in possible engine failure.

APPROVED FUEL GRADES:

JET A (ASTM-D1655) JP-8+100 (MIL-DTL-83133)

JET A-1 (ASTM-D1655) AN8 (MIL-DTL-83133)
JET No. 3 (GB 6537) RT (GOST 10227)
JP-5 (MIL-DTL-5624) RT (GSTU 320.00149943.007)
JP-8 (MIL-DTL-83133) TS-1 (GOST 10227)

NOTE
Refer to Section 2, Limitations, Fuel Limitations, for more
information on Approved Fuels.

ANTI-ICING FUEL ADDITIVES

Airplane Serials 208B5000 thru 208B5271 not incorporating CAB-

34-03.
Anti-icing fuel additive must be used for all flight operations in ambient
temperatures at or below 5°C.

Airplane Serials 208B2197; 208B5272 and On; and 208B5000 thru

208B5271 incorporating CAB-34-03.
Anti-icing fuel additive may be used for all flight operations at the
discretion of the pilot.

(Continued Next Page)

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

DESCRIPTIVE DATA (Continued)

FUEL (Continued)
APPROVED FUEL ADDITIVES
If fuel system anti-ice additives are being used they must be added to
the fuel as noted at the following concentrations. Refer to Section 8,
Airplane Handling, Service and Maintenance, Servicing, Fuel, for
additional information and recommended blending instructions for
approved fuel additives. Use of an approved static dissipater or biocide
additives is recommended but not required.
CAUTION
JP-5 fuels per MIL-T-5624 and JP-8 fuel per MIL-T-
83133A contain the correct premixed quantity of an
approved type of anti-icing fuel additive and no
additional anti-ice compounds should be added.
NOTE
• MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME),
Type: Anti-Ice Additive, in a concentration of 0.10 to 0.15
percent by volume. Dependent on fuel used.
• MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME),
Type: Anti-Ice Additive, in a concentration of 0.10 to 0.20
percent by volume. Dependent on fuel used.
• GOST 8313 (Fluid I), Type: Anti-Ice Additive, in a
concentration of 0.10 to 0.30 percent by volume.
• CIS TU6-10-1458 (Fluid I-M), Type: Anti-Ice Additive, in
a concentration of 0.10 to 0.30 percent by volume.
• T1301 (SH0396-92), Type: Anti-Ice Additive, in a
concentration of 0.10 to 0.15 percent by volume.
• DuPont Stadis 450, Type: Static Dissipator, in a
concentration as required to bring fuel up to 300
conductive units, not to exceed 1 Parts Per Million
(PPM).
• SOHIO Biobor JF, Type: Biocide, at a concentration not
to exceed 20 PPM of elemental boron (270 PPM of total
additive).
• Kathon FP, Type: Biocide, at a concentration not to
exceed 100 PPM of total additive.

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

DESCRIPTIVE DATA (Continued)

FUEL (Continued)
FUEL CAPACITY
TOTAL FUEL
Both Tanks and Reservoir: . . . . . . . . . 339.1 U.S. Gallons (1283.3 l)
Both Tanks: . . . . . . . . . . . . . . . . . . . . 335.6 U.S. Gallons (1270.0 l)
Each Tank: . . . . . . . . . . . . . . . . . . . . . . 167.8 U.S. Gallons (635.0 l)

TOTAL USABLE FUEL

Both Tanks ON and Reservoir: . . . . . . 335.3 U.S. Gallons (1268.9 l)
Both Tanks ON: . . . . . . . . . . . . . . . . . 332.0 U.S. Gallons (1256.4 l)
Single Tank ON: . . . . . . . . . . . . . . . . . . 165.0 U.S. Gallons (624.4 l)

TOTAL UNUSABLE FUEL

Both Tanks ON: . . . . . . . . . . . . . . . . . . . . . 3.6 U.S. Gallons (13.6 l)
Single Tank ON: . . . . . . . . . . . . . . . . . . . . . 2.8 U.S. Gallons (10.5 l)

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

DESCRIPTIVE DATA (Continued)

OIL
OIL SPECIFICATION
Refer to Pratt & Whitney Canada Service Bulletin No. 1001,
Revision 33, or subsequent revision for a complete listing of
approved synthetic lubricating oils.

OIL CAPACITY
Total: . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.0 U.S. QUARTS (13.2 I)
(including filter, cooler, and hoses)
Drain and Refill Quantity:. . . . . . . . . . . . . . 9.5 U.S. QUARTS (9.0 l)
(approximately)

OIL QUANTITY OPERATING RANGE

Fill to within 1.5 quarts (1.4 l) of MAX HOT or MAX COLD (as
appropriate) on dipstick. Quart markings indicate U.S. quarts low if
oil is hot. For example, a dipstick reading of 3 indicates the system is
within 2.0 quarts (1.8 l) of MAX if the oil is cold and within 3.0 quarts
(2.8 l) of MAX if the oil is hot.

WARNING
Make sure oil dipstick cap is securely latched
down. Operating the engine with less than the
recommended oil level and with the dipstick cap
unlatched will result in excessive oil loss and
eventual engine stoppage.

NOTE
To obtain an accurate oil level reading, it is recommended
the oil level be checked within 10 minutes after engine
shutdown while the oil is hot (MAX HOT marking) or prior to
the first flight of the day while the oil is cold (MAX COLD
marking). If more than 10 minutes has elapsed since
engine shutdown and engine oil is still warm, perform an
engine dry motoring run before checking oil level.

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

DESCRIPTIVE DATA (Continued)

MAXIMUM CERTIFICATED WEIGHTS

Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . 8842 POUNDS (4010.6 kg)
Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . 8807 POUNDS (3994.7 kg)
Landing Weight . . . . . . . . . . . . . . . . . . . . . 8500 POUNDS (3855.5 kg)

NOTE
Refer to Section 6, Weight and Balance for recommended
cabin internal loading arrangements.

CABIN AND ENTRY DIMENSIONS

Refer to Section 6, Weight and Balance, Cabin Internal Dimensions, for
detailed dimensions of the cabin interior and entry door openings.

BAGGAGE/CARGO COMPARTMENT AND CARGO DOOR

ENTRY DIMENSIONS
Refer to Section 6, Weight and Balance, Cabin Internal Dimensions, for
detailed dimensions of the baggage/cargo area and cargo door
openings.

SPECIFIC LOADINGS
Wing Loading. . . . . . . . . . . . . . . . . . . . . . 31.5 lbs./sq. ft. (152.9 kg/m2)
Power Loading. . . . . . . . . . . . . . . . . . . . . 10.2 lbs./SHP (4.58 kg/SHP)

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

DESCRIPTIVE DATA (Continued)

NAVIGATIONAL CAPABILITIES
Airplane Serials 208B5000 thru 208B5271 not incorporating CAB-
34-03

The G1000 GNSS navigational system is a GPS system with a Satellite

Based Augmentation System (SBAS) comprised of two TSO-C145a
Class 3 approved Garmin GIA 63Ws, three TSO-C146a Class 3
approved Garmin GDU 1040A Display Units, Garmin-approved GPS/
SBAS antennas and GPS software version 3.2 or later approved
software version. The G1000 GNSS navigation system in this airplane
is installed in accordance with AC 20-138D. The navigation system
meets the requirements for operations requiring two GNSS systems if
both PFDs are operating and both GPS receivers are providing
required accuracy (amber BOTH ON GPS1 or GPS2 message not
displayed).

Airplane Serials 208B5272 thru 208B5400; and 208B5000 thru

208B5271 incorporating CAB-34-03

The G1000 GNSS navigational system is a GPS system with a Satellite

Based Augmentation System (SBAS) comprised of two TSO-C145a
Class 3 approved Garmin GIA 63Ws, three TSO-C146a Class 3
approved Garmin GDU 1040A Display Units, Garmin-approved GPS/
SBAS antennas and GPS software version 5.0 or later approved
software version. The G1000 GNSS navigation system in this airplane
is installed in accordance with AC 20-138D. The navigation system
meets the requirements for operations requiring two GNSS systems if
both PFDs are operating and both GPS receivers are providing
required accuracy (amber BOTH ON GPS1 or GPS2 message not
displayed).

(Continued Next Page)

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

DESCRIPTIVE DATA (Continued)

NAVIGATIONAL CAPABILITIES (Continued)

Airplane Serials 208B5401 thru 208B5500
The G1000 GNSS navigational system is a GPS system with a Satellite
Based Augmentation System (SBAS) comprised of two TSO-C145a
Class 3 approved Garmin GIA 63Ws, three TSO-C146d Class 3
approved Garmin GDU 1050A Display Units, Garmin-approved GPS/
SBAS antennas and GPS software version 5.1 or later approved
software version. The G1000 GNSS navigation system in this airplane
is installed in accordance with AC 20-138D. The navigation system
meets the requirements for operations requiring two GNSS systems if
both PFDs are operating and both GPS receivers are providing
required accuracy (amber BOTH ON GPS1 or GPS2 message not
displayed).

Airplane Serials 208B2197; and 208B5501 and On

The G1000 GNSS navigational system is a GPS system with a Satellite
Based Augmentation System (SBAS) comprised of two TSO-C145d
Class 3 approved Garmin GIA 64Ws, three TSO-C146d Class 3
approved Garmin GDU 1050A Display Units, Garmin-approved GPS/
SBAS antennas and GPS software version 7.0 or later approved
software version. The G1000 GNSS navigation system in this airplane
is installed in accordance with AC 20-138D. The navigation system
meets the requirements for operations requiring two GNSS systems if
both PFDs are operating and both GPS receivers are providing
required accuracy (amber BOTH ON GPS1 or GPS2 message not
displayed).

(Continued Next Page)

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

DESCRIPTIVE DATA (Continued)

NAVIGATIONAL CAPABILITIES (Continued)

The Garmin G1000 system has been demonstrated capable of, and
has been shown to meet the accuracy requirements for, the following
operations provided it is receiving usable navigation data. Operational
approval may be required for some operations.
1. VOR/LOC/ILS Navigation.
2. ADF Navigation (if installed).
3. Enroute and Terminal Navigation:
a. GPS and GPS/SBAS navigation for enroute and terminal
navigation per AC 20-138D.
b. Oceanic/Remote, RNP-10 and RNP-4 per AMC 20-12, AC
20-138D, AC 90-105A, AC 91-70A and FAA Orders
8400.12C and 8400.33. Both GPS receivers are required to
be operating except for routes requiring only one Long
Range Navigation (LRN) sensor. GPS Fault Detection/
Exclusion (FDE) availability must be verified prior to flight
with either the onboard RAIM prediction tool or other
approved FDE software.
NOTE
Each display computes an independent navigation solution
based on the on-side GPS sensor. However, either display
will automatically revert to the cross-side sensor if the
on-side sensor fails or if the cross-side sensor is
determined to be more accurate. A BOTH ON GPS1 or
BOTH ON GPS2 message does not necessarily mean that
one GPS has failed. Refer to the MFD AUX-GPS STATUS
page to determine the status of the unused GPS.

c. Enroute and Terminal B-RNAV/RNAV5 per AMC 20-4A, AC

20-138D, AC 90-96A and AC 90-105A.
d. Enroute and Terminal P-RNAV (RNP-1) per JAA TGL 10,
AC 90-96A and AC 90-105A.
e. RNAV and RNP Terminal (RNP-1 or RNP-2, RNAV-1 or
RNAV-2) per AC 20-138D, AC 90-100A, and AC 90-105A.

(Continued Next Page)

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

DESCRIPTIVE DATA (Continued)

NAVIGATIONAL CAPABILITIES (Continued)

4. Non-Precision Approaches:
a. RNAV, GPS and RNP APCH to LPV minimums per AC
20-138D, AC 90-107 and AMC 20-28.
b. RNAV, GPS and RNP APCH to LNAV or LNAV/VNAV
minimums per AC 20-138D, AC 90-105A and AMC 20-27.
Vertical guidance is based on GPS/SBAS when within
SBAS coverage.
Airplane Serials 208B2197; and 208B5501 and On; and
208B5401 thru 208B5500 incorporating CAB-34-08
Vertical guidance is based on baro-VNAV when outside
SBAS coverage, when SBAS has been disabled by pilot
selection, or for approaches with “WAAS VNAV NA”.

The following non-precision approaches are approved for

Airplane Serials 208B2197; and 208B5272 and On; and
208B5000 thru 208B5271 incorporating CAB-34-03
c. RNAV, GPS and RNP APCH to LP minimums per AC
20-138D, AC 90-107 and AMC 20-28.
5. Baro-VNAV:
a. Enroute and Terminal baro-VNAV per AC 20-138D and
AMC 20-27.
Airplane Serials 208B2197; and 208B5501 and On; and
208B5401 thru 208B5500 incorporating CAB-34-08
b. Approach baro-VNAV (APV baro-VNAV) to LNAV, or LNAV/
VNAV minimums per AC 20-138D and AMC 20-27.
Approach vertical guidance is normally provided by GPS
and SBAS, but will switch to baro-VNAV if SBAS is not
available. If approach baro-VNAV is in use, the approach
glidepath is always temperature compensated.
Airplane Serials 208B2197; and 208B5272 and On; and
208B5000 thru 208B5271 incorporating CAB-34-03
6. RF legs are supported for departures, arrivals, and approaches
per AC 20-138D.

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

DESCRIPTIVE DATA (Continued)

Airplane Serials 208B5272 thru 208B5400; and 208B5000 thru
208B5271 incorporating CAB-34-03 and CAB-34-04.

ADS-B OUT (if installed)

The installed ADS-B Out system meets the equipment requirements of
14 CFR 91.227.

Airplane Serials 208B2197; and 208B5401 and On

ADS-B OUT (if installed)

The installed ADS-B Out system meets the equipment requirements of
14 CFR 91.227 and is compliant with the requirements of CS
ACNS.D.ADSB. The System as installed also complies with the
guidance provided in AC 20-165B and AMC 20-24.

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MODEL 208B 867 SHP GENERAL
GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS

KCAS Knots Calibrated Airspeed is indicated airspeed
corrected for position and instrument error and expressed
in knots. Knots calibrated airspeed is equal to KTAS in
standard atmosphere at sea level.
KIAS Knots Indicated Airspeed is the speed shown on the
airspeed indicator and expressed in knots.
KTAS Knots True Airspeed is the airspeed expressed in knots
relative to undisturbed air which is KCAS corrected for
altitude and temperature.
VA Maneuvering Speed is the maximum speed at which full
or abrupt control movements may be used without
overstressing the airframe.
VFE Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended
position.
VMO Maximum Operating Speed is the speed that may not
be deliberately exceeded at any time.
VS Stalling Speed or the minimum steady flight speed is
the minimum speed at which the airplane is controllable.
VSO Stalling Speed or the minimum steady flight speed is
the minimum speed at which the airplane is controllable in
the landing configuration at the most forward center of
gravity.
Vx Best Angle of Climb Speed is the speed which results in
the greatest gain of altitude in a given horizontal distance.
VY Best Rate of Climb Speed is the speed which results in
the greatest gain in altitude in a given time.

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SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

METEOROLOGICAL TERMINOLOGY
OAT Outside Air Temperature is the free air static
temperature. It may be expressed in either degrees
Celsius (°C) or degrees Fahrenheit (°F).
ISA International Standard Atmosphere is an atmosphere
in which:
1. The air is a perfect dry gas.
2. The temperature at sea level is 15°C.
3. The pressure at sea level is 29.92 inches of
mercury (inHg) (1013.2 mb).
4. The temperature gradient from sea level to the
altitude at which the temperature is -56.5°C is
-1.98°C per 1000 feet.
Standard Standard Temperature is 15°C at sea level pressure
Temperature altitude and decreases by 2°C for each 1000 feet of
altitude.
Pressure Pressure Altitude is the altitude read from an altimeter
Altitude when the altimeter's barometric scale has been set to
29.92 inches of mercury (inHg) (1013.2 mb).

ENGINE POWER TERMINOLOGY

Beta Mode Beta Mode is the engine operational mode in which
propeller blade pitch is controlled by the power lever.
The beta mode may be used during ground operations
only.
Flameout Flameout is the unintentional loss of combustion
chamber flame during operation.
Flat Rated Flat Rated denotes constant horsepower over a specific
altitude and/or temperature.
Gas Gas Generator RPM indicates the percent of gas
Generator generator RPM based on a figure of 100% being 37,468
RPM (Ng) RPM.
GCU Generator Control Unit
Hot Start Hot Start is an engine start, or attempted start, which
results in an ITT exceeding 1090°C.

(Continued Next Page)

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

ENGINE POWER TERMINOLOGY (Continued)

ITT Interstage Turbine Temperature
Maximum Maximum Climb Power is the maximum power
Climb Power approved for normal climb. Use of this power setting is
limited to climb operations. This power corresponds to
that developed at the maximum torque limit, ITT of
825°C or Ng limit, whichever is less. This power
corresponds to that shown in Section 5, Performance,
Maximum Engine Torque for Climb.
Maximum Maximum Rated Power is the maximum power rating
Rated Power not limited by time. Use of this power should be limited to
those abnormal circumstances which require maximum
airplane performance (i.e., severe icing conditions or
windshear downdrafts). This power corresponds to that
developed at the maximum torque limit, ITT of 825°C or
Ng limit, whichever is less.
Ng Ng signifies gas generator RPM.
Propeller Propeller RPM indicates propeller speed in RPM.
RPM
RPM Revolutions Per Minute
Reverse Reverse Thrust is the thrust produced when the
Thrust propeller blades are rotated past flat pitch into the
reverse range.
SHP SHP is shaft horsepower and is the power delivered at
the propeller shaft.
SHP = Propeller RPM x Torque (foot-pounds)
5252
Takeoff Takeoff Power is the maximum power rating and is
Power limited to a maximum of 5 minutes whenever ITT is
greater than 825°C, under normal operation. Use of this
power should be limited to normal takeoff operations.
This power corresponds to that shown in Section 5,
Performance, Maximum Engine Torque For Takeoff.
Torque Torque is a measurement of rotational force exerted by
the engine on the propeller.
Windmill Windmill is propeller rotation from airstream inputs.

208BPHCUS-04 U.S. 1-19

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

AIRPLANE PERFORMANCE AND FLIGHT PLANNING

TERMINOLOGY
Demonstrated Demonstrated Crosswind Velocity is the velocity of
Crosswind the crosswind component for which adequate control
Velocity of the airplane during takeoff and landing was actually
demonstrated during certification tests. The value
shown is not considered to be limiting.
Usable Fuel Usable Fuel is the fuel available for flight planning.
Unusable Fuel Unusable Fuel is the quantity of fuel that cannot be
safely used in flight.
PPH Pounds Per Hour is the amount of fuel consumed per
hour.
NM/1000 lbs Nautical Miles Per Thousand Pounds of Fuel is the
distance which can be expected per 1000 pounds of
fuel consumed at a specific engine power setting and/
or flight configuration.
g g is acceleration due to gravity.
Land As Soon Land at the nearest suitable airport. Unless
As Possible otherwise specified, use Normal Procedures for
Approach, Before Landing, and Landing. Extreme
situations can require an off airport landing. Primary
consideration is safety of occupants.
Land As Soon Land at a suitable airport. Unless otherwise
As Practical specified, use Normal Procedures for Approach,
Before Landing, and Landing. The primary
consideration is the urgency of the emergency or
abnormal situation. Continuing to the destination or an
alternate with appropriate service facilities can be an
option.

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

AUTOPILOT/FLIGHT DIRECTOR AND AFCS

TERMINOLOGY
NOTE
A thorough understanding of the difference between an
autopilot, a flight director, and an AFCS is required before
operating any of the components of the Garmin G1000/
GFC 700 Flight Control System. Refer to Garmin Cockpit
Resource Guide (CRG) for complete operating details.

Autopilot Autopilot is a system which automatically controls

attitude and/or flight path of the airplane as directed by
the pilot through the system's computer.
Flight Flight Director is a system which provides visual
Director recommendations to allow the pilot to manually control
the airplane attitude and/or flight path in response as
selected through the system's computer.
Automated AFCS applies to the union of autopilot and flight director
Flight systems which allows the pilot to manage the flight by
Control observing computed visual recommendations while the
System autopilot automatically follows these recommendations as
(AFCS) selected by the pilot using the system's controls.
Course Course Datum is the compass reference used by the
Datum autopilot, along with course deviation, to provide lateral
control when tracking a navigation signal.

208BPHCUS-04 U.S. 1-21

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

WEIGHT AND BALANCE TERMINOLOGY

Reference Reference Datum is an imaginary vertical plane from
Datum which all horizontal distances are measured for
balance purposes.
Station Station is a location along the airplane fuselage given
in terms of the distance from the reference datum.
Arm Arm is the horizontal distance from the reference
datum to the center of gravity (C.G.) of an item.
Moment Moment is the product of the weight of an item
multiplied by its arm. (Moment divided by the constant
1000 is used in this POH/AFM to simplify balance
calculations by reducing the number of digits.)
Center of Center of Gravity is the point at which an airplane or
Gravity (C.G.) equipment would balance if suspended. Its distance
from the reference datum is found by dividing the total
moment by the total weight of the airplane.
C.G. Arm Center of Gravity Arm is the arm obtained by adding
the airplane's individual moments and dividing the sum
by the total weight.
C.G. Limits Center of Gravity Limits are the extreme center of
gravity locations within which the airplane must be
operated at a given weight.
Standard Standard Empty Weight is the weight of a standard
Empty Weight airplane, including unusable fuel, full operating fluids
and full engine oil.
Basic Empty Basic Empty Weight is the standard empty weight
Weight plus the weight of optional equipment.
Useful Load Useful Load is the difference between ramp weight
and the basic empty weight.

(Continued Next Page)

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

(Continued)

WEIGHT AND BALANCE TERMINOLOGY (Continued)

MAC Mean Aerodynamic Chord is a chord of an imaginary
rectangular airfoil having the same pitching moments
throughout the flight range as that of the actual wing.
Maximum Maximum Ramp Weight is the maximum weight
Ramp Weight approved for ground maneuver, and includes the
weight of fuel used for start, taxi and runup.
Maximum Maximum Takeoff Weight is the maximum weight
Takeoff approved for the start of the takeoff roll.
Weight
Maximum Maximum Landing Weight is the maximum weight
Landing approved for the landing touchdown.
Weight
Tare Tare is the weight of chocks, blocks, stands, etc. used
when weighing an airplane, and is included in the
scale readings. Tare is deducted from the scale
reading to obtain the actual (net) airplane weight.
Scale Drift Scale Drift may occur on some types of electronic
scales because of the inability of the scale to return to
a true zero reading after weighing. If present, this
deviation from zero should be accounted for when
calculating the net weight of the airplane.
Residual Fuel Residual Fuel is the fuel remaining when the airplane
is defueled in a specific attitude by the normal means
and procedures specified for draining the tanks.

208BPHCUS-04 U.S. 1-23

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

METRIC/IMPERIAL/U.S. CONVERSION CHARTS

The following charts have been provided to help international operators
convert U.S. measurement supplied with the POH/AFM into metric and
imperial measurements.

The standard followed for measurement units shown is the National

Institute of Standards Technology (NIST), Publication 811, "Guide for
the Use of the International System of Units (SI)."
Refer to the following pages for these charts.

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CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

WEIGHT CONVERSIONS

Figure 1-2 (Sheet 1 of 2)

208BPHCUS-04 U.S. 1-25

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

WEIGHT CONVERSIONS

Figure 1-2 (Sheet 2)

1-26 U.S. 208BPHCUS-04

CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

LENGTH CONVERSIONS

Figure 1-3 (Sheet 1 of 4)

208BPHCUS-04 U.S. 1-27

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

LENGTH CONVERSIONS

Figure 1-3 (Sheet 2)

1-28 U.S. 208BPHCUS-04

CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

LENGTH CONVERSIONS

Figure 1-3 (Sheet 3)

208BPHCUS-04 U.S. 1-29

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

LENGTH CONVERSIONS

Figure 1-3 (Sheet 4)

1-30 U.S. 208BPHCUS-04

CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

DISTANCE CONVERSIONS

Figure 1-4

208BPHCUS-04 U.S. 1-31

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

VOLUME CONVERSIONS

Figure 1-5 (Sheet 1 of 3)

1-32 U.S. 208BPHCUS-04

CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

VOLUME CONVERSIONS

Figure 1-5 (Sheet 2)

208BPHCUS-04 U.S. 1-33

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

VOLUME CONVERSIONS

Figure 1-5 (Sheet 3)

1-34 U.S. 208BPHCUS-04

CESSNA SECTION 1
MODEL 208B 867 SHP GENERAL
GARMIN G1000

TEMPERATURE CONVERSIONS

Figure 1-6

208BPHCUS-04 U.S. 1-35

SECTION 1 CESSNA
GENERAL MODEL 208B 867 SHP
GARMIN G1000

PRESSURE CONVERSION
HECTOPASCALS TO INCHES OF MERCURY

Figure 1-7

1-36 U.S. 208BPHCUS-04