Cessna T206H Technical specifications

SOLOY, LLC
450 Pat Kennedy Way S.W.
Olympia, WA 98501
PILOT’S OPERATING HANDBOOK
SUPPLEMENT
AND
FAA APPROVED AIRPLANE FLIGHT MANUAL
FOR
CESSNA T206H/206H
SERIAL NO.: ___________________________
KIT SERIAL NO.: ________________________
REGISTRATION NO.: ____________________
This Supplement must be attached to the Pilot’s Operating Handbook (POH) when a
Soloy, LLC Turbine Pac engine is installed in accordance with S.T.C. SA2353NM.
Information contained herein supplements or supersedes the basic POH only in those
areas listed herein. For limitations, procedures and performance information not
contained in this Supplement, consult the basic POH.
F.A.A. Approved __________________________________________
Manager, Seattle Aircraft Certification Office
Date:
Publication Number: S2001A
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SOLOY TURBINE PAC
POHS CESSNA T206H/206H
A
F.A.A. Approved May 23, 2003
CONGRATULATIONS . . . . .
Your airplane is SPECIAL! A Soloy Corporation Turbine Pac
engine has been installed for those whose operation requires extra
performance and greater utility than is available with the basic engine.
This Pilot’s Operating Handbook Supplement has been
prepared to specify the difference in operating procedures and
performance. In some cases, only a specific item is changed while in
others, the entire paragraph or checklist is rewritten. For information
not included in this Supplement, consult the basic POH.
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SOLOY TURBINE PAC
POHS CESSNA T206H/206H
i
F.A.A. Approved November 17, 2015
LOG OF EFFECTIVE PAGES
This handbook supplement will be kept current with revisions
distributed to the last known owner of each airplane equipped with a
Soloy Turbine Pac engine.
It is the responsibility of the owner to maintain this handbook in a
current status when it is being used for operational purposes.
Owners should contact the Soloy Product Support Department
whenever the revision status of their handbook is in question.
A revision bar will extend the full length of new or revised text
and/or illustrations added on new or presently existing pages. This bar
will be located adjacent to the applicable revised area on the outer
margin of the page.
LOG OF EFFECTIVE PAGES
Dates of issue for original and revised pages are:
Original ...................... 5/23/03
Revision 1 .................. 11/14/14
Revision 2 .................. 11/17/15
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POHS CESSNA T206H/206H
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F.A.A. Approved November 17, 2015
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SOLOY TURBINE PAC
POHS CESSNA T206H/206H
v
F.A.A. Approved November 14, 2014
LOG OF REVISIONS
Revision
Pages
Revised
Comments
FAA Approval
No.
Date
0
5/23/03
Original
Original of
Manual.
Jeffery A. Morfitt
for Manager, Seattle
Aircraft Certification
Office, ANM-100S
Renton, WA 98055-
4056
Date: May 23, 2003
1
11/14/14
Cover
Removed prev.
revision signature
and date.
________________
for Manager, Seattle
Aircraft Certification
Office, ANM-100S
Renton, WA 98057-
3356
Date: (Rev 1 Date)
i-v
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revision log
pages, no
content change.
Added Rev 16.
2-12
Corrected cold
weather fuel
spec. number.
2-13
Updated Engine
Oil Specs.
6-7, 7-19
Added provisions
for optional
battery.
8-1, 8-2,
8-6 - 8-9
Updated Engine
Oil, Fuel specs.
(8-8 - 8-12)
Entire contents of
8-8 deleted. All
following pages
shifted up as a
result.
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SOLOY TURBINE PAC
POHS CESSNA T206H/206H
vi
F.A.A. Approved November 17, 2015
Revision
Pages
Revised
Comments
FAA Approval
No.
Date
2
11/17/15
Cover
i - viii
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2-11 –2-12
2-13
4-1 - 4-2
4-4
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4-17 - 4-20
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6-7
8-1
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8-11
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revision signature
and date.
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company name.
Added Rev 2.
Table of Contents
moved from pg. vii
to pg. viii.
Added propeller
RPM speed avoid
range.
Updated Fuel
section formatting.
Updated Oil
Specifications.
Updated Table of
Contents.
Updated to extend
flaps in preflight.
Updated engine
start procedures.
Updated Auto
feather procedure.
Updated amplified
start procedures.
Updated amplified
prop avoid speed
procedures.
Updated Table of
Contents.
Corrected battery
rack installation
weights.
Updated Table of
Contents.
Updated Section
Title.
Updated Caution
Note.
Updated nose gear
shock strut fill
procedure.
for Manager, Seattle
Aircraft Certification
Office, ANM-100S
Renton, WA 98055-
4056
Date:
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SOLOY TURBINE PAC PERFORMANCE
POHS CESSNA T206H/206H SPECIFICATIONS
vii
F.A.A. Approved November 17, 2015
PERFORMANCE –SPECIFICATIONS
RATE OF CLIMB AT SEA LEVEL (3600 LBS)
MCP
1,447 FPM
APPROVED CEILING
20,000 FT.
TAKEOFF PERFORMANCE:
Ground Roll
Total Distance Over a 50’ Obstacle
570 FT.
1,063 FT.
LANDING PERFORMANCE:
Ground Roll
Total Distance Over a 50’ Obstacle
553 FT.
1,094 FT.
STALL SPEEDS (CAS):
Flaps Up, Power Off
58 KNOTS
Flaps Down, Power Off
52 KNOTS
MAXIMUM WEIGHT
3,617 LBS.
TAKEOFF WEIGHT
3,600 LBS.
STANDARD EMPTY WEIGHT
2,274 LBS.
MAXIMUM USEFUL LOAD
1,343 LBS.
BAGGAGE ALLOWANCE
180 LBS.
WING LOADING
20.7 PSF
POWER LOADING
8.61 LBS/SHP
FUEL CAPACITY: TOTAL
92 GAL.
OIL CAPACITY
9 U.S. QTS.
ENGINE: Soloy Turbine Pac
418 SHP @ 1810 RPM (5 Minute Takeoff
Rating)
321 SHP @ 1810 RPM (Maximum
Continuous Rating)
780-1000-1
PROPELLER: 3-Bladed, Auto-Feather, Full
Feathering, Constant Speed
95 IN. DIA.
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SOLOY TURBINE PAC PERFORMANCE
POHS CESSNA T206H/206H SPECIFICATIONS
viii
F.A.A. Approved November 17, 2015
TABLE OF CONTENTS
SECTION
GENERAL ...............................................................................1
LIMITATIONS ..........................................................................2
EMERGENCY PROCEDURES................................................3
NORMAL PROCEDURES .......................................................4
PERFORMANCE ....................................................................5
WEIGHT & BALANCE/EQUIPMENT LIST............................... 6
AIRPLANE & SYSTEMS DESCRIPTION ................................7
AIRPLANE HANDLING, SERVICE & MAINTENANCE............8
SUPPLEMENTS
(Optional Systems Description & Operating Procedures) ....9
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-1
F.A.A. Approved May 23, 2003
SECTION 1
GENERAL
TABLE OF CONTENTS Page
Three View - Normal Ground Attitude ....................................................1-3
Introduction ...........................................................................................1-4
Descriptive Data ...................................................................................1-4
Engine ...............................................................................................1-4
Propeller ............................................................................................1-4
Fuel ...................................................................................................1-4
Oil ......................................................................................................1-5
Maximum Certified Weights ...............................................................1-5
Standard Airplane Weights ................................................................1-5
Cabin & Entry Dimensions .................................................................1-5
Baggage Space and Cargo Door Dimensions ....................................1-5
Specific Locations ..............................................................................1-5
Symbols, Abbreviations and Terminology .............................................1-6
General Airspeed Terminology ..........................................................1-6
Meteorological Terminology ...............................................................1-7
Engine Power Terminology ................................................................1-7
Engine Controls and Instruments .......................................................1-8
Airplane Performance and Flight Planning Terminology .....................1-9
Weight and Balance Terminology ....................................................1-10
Metric / Imperial / US Conversion Charts .............................................1-10
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-2
F.A.A. Approved May 23, 2003
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-3
F.A.A. Approved May 23, 2003
Figure 1-1. Three View
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-4
F.A.A. Approved May 23, 2003
INTRODUCTION
This handbook supplement contains nine sections and includes the material
required to be furnished to the pilot by FAR Part 23. It also contains
supplemental data.
Section I provides basic data and information of general interest. It also
contains definitions or explanations of symbols, abbreviations, and terminology
commonly used.
DESCRIPTIVE DATA
ENGINE
Number of Engines: 1
Engine Manufacturer: Soloy Corporation/Rolls Royce
Engine Model Number: Soloy Turbine Pac, 780-1000-1
Horsepower Rating and Engine Speed:
Takeoff power (5 minute): 418 SHP @ 1810 RPM
Maximum continuous Power: 321 SHP @ 1810 RPM
PROPELLER
Propeller Manufacturer: Hartzell
Propeller Model Number: HC-C3YN-5A/FC9587D-2
Number of Blades: 3
Propeller Diameter: 95 Inches
Propeller Type: Constant speed, hydraulically
actuated, full feathering
FUEL
Approved Fuel Grades: See handling, service and
maintenance, Section 8
Fuel Capacity:
Total Capacity: 92 Gallons
Total Usable: 88 Gallons
Total Capacity Each Tank: 46.0 Gallons
Total Usable Each Tank: 44.0 Gallons
NOTE
To ensure maximum fuel capacity and minimize cross feeding
when refueling, always park the airplane in a wings-level,
normal ground attitude and place the fuel selector in the Left
or Right position. Refer to Figure 1-1 for normal ground
attitude dimensions. See Section 2 for approved fuels.
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-5
F.A.A. Approved May 23, 2003
OIL
Oil Specifications: See handling, service and maintenance, Section 8
Oil Capacity: 9 U.S. Quarts, including oil filter.
MAXIMUM CERTIFIED WEIGHTS
Ramp Weight: 3,617 lbs.
Takeoff: 3,600 lbs.
Landing: 3,600 lbs.
Weight in Baggage Compartment –Station 109 –145: 180 lbs. maximum
NOTE
Refer to Section 6 of this handbook for loading
arrangements with one or more seats removed
for cargo accommodations.
STANDARD AIRPLANE WEIGHTS
Standard Empty Weight: 2274 lbs.
Maximum Useful Load: 1342 lbs.
CABIN AND ENTRY DIMENSIONS
Detailed dimensions of the cabin interior and entry door opening are
illustrated in Section 6.
BAGGAGE SPACE AND CARGO DOOR ENTRY DIMENSIONS
Dimensions of the baggage/cargo area and cargo door opening are
illustrated in detail in Section 6.
SPECIFIC LOADINGS
Wing Loading: 20.7 lbs./sq. ft.
Power Loading: 8.61 lbs./hp.
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-6
F.A.A. Approved May 23, 2003
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
GENERAL AIRSPEED TERMINOLOGY & 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 you may use
abrupt control travel.
VFE
Maximum Flap Extended Speed is the highest speed permissible
with wing flaps in a prescribed extended position.
VMO
Maximum Operating Limit Speed is the speed limit that may not
be deliberately exceeded in normal flight operations.
VS
Stalling Speed or the minimum steady flight speed at which the
airplane is controllable.
VSO
Stalling Speed or the minimum steady flight 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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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-7
F.A.A. Approved May 23, 2003
METEOROLOGICAL TERMINOLOGY
OAT
Outside Air Temperature is the free air static
temperature. It is expressed in either degrees Celsius
(formerly Centigrade) or degrees Fahrenheit.
STANDARD
TEMPERATURE
Standard Temperature is 15C at sea level pressure
altitude and decreases by 2C for each 1000 feet of
altitude.
STANDARD DAY
Standard Day is 15C at 29.92”hg.atmospheric
pressure at sea level.
PRESSURE
ALTITUDE
Pressure Altitude is the altitude read from an altimeter
when the altimeter’s barometric scale has been set to
29.92 inches of mercury (1013.2 mb).
ENGINE POWER TERMINOLOGY
AUTO FEATHER
A system designed to automatically reduce drag of an
inoperative engine by moving the propeller to a greater
pitch angle.
ENGINE START
(NORMAL)
The sequence of events that occur between starter
actuation and N1stabilization at GROUND IDLE.
FLAMEOUT
Unintentional loss of combustion chamber flame during
operation.
FLIGHT IDLE
Minimum position of the power control while airborne.
GAS PRODUCER
RPM (N1)
Indicates the percent of gas producer (compressor)
RPM based on a figure of 100% at 50,970 RPM.
GROUND IDLE
Minimum position of the power control when the airplane
is not airborne.
HOT START
An engine start or attempted start in which the TOT
exceeds 927C, or 927C for more than 1 second, or
810C to 927C for more than 10 seconds.
MAXIMUM
CONTINUOUS
POWER
The power developed at the maximum continuous
torque limit, TOT limit, or N1limit.
MINIMUM
SPECIFICATION
ENGINE
(MIN.SPEC.)
An engine that meets only the minimum requirements
for performance. (Torque, TOT and N1)
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-8
F.A.A. Approved May 23, 2003
ENGINE POWER TERMINOLOGY (Continued)
POWER TURBINE
SPEED (N2)
Determined by using the propeller RPM at a ratio of
18.1 RPM to 1% N2speed.
PROPELLER RPM
Indicates the speed of the propeller in revolutions per
minutes. Can also be expressed as a percent of N P
(1810 RPM)
RPM
Revolutions per minute.
SHP
Shaft horsepower is the power delivered at the propeller
shaft.
STAGNATED
START
Slow acceleration during an engine start, possibly
deteriorating to total stoppage of acceleration even
though combustion is still occurring in the combustion
section.
TORQUE
The torsional force exerted at the output shaft, usually
measured in foot-pounds, PSI or percent. Torque is
proportional to the power output of the engine at any
constant RPM. 1 PSI = 4.12 SHP
TOT
Turbine outlet temperature.
ENGINE CONTROLS AND INSTRUMENTS
ENGINE
OVERSPEED
GOVERNOR
An engine mounted component which operates in
conjunction with the gas producer fuel control to serve
as overspeed and loss of load protection for the engine.
FUEL CUTOFF
CONTROL
A cockpit control that is connected to the fuel control
unit. The cockpit control has two positions only, RUN
(IN) and CUTOFF (OUT).
GAS PRODUCER
FUEL CONTROL
An engine mounted component that regulates fuel flow
to the engine. It responds to compressor discharge
pressure, gas producer turbine speed (N1), and the
cockpit power control.
PROPELLER
GOVERNOR
Adjusts the propeller blade pitch angle to maintain the
RPM selected by the cockpit propeller control regardless
of the POWER CONTROL setting.
POWER CONTROL
A cockpit control to regulate power output of the engine
through GAS PRODUCER FUEL CONTROL
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-9
F.A.A. Approved May 23, 2003
ENGINE CONTROLS AND INSTRUMENTS (Continued)
PROPELLER
CONTROL
Cockpit control to set propeller RPM.
PROPELLER
OVERSPEED
GOVERNOR
A propeller gearbox mounted component which provides
overspeed protection in the event of a propeller
governor failure.
TACHOMETER
An instrument that indicates the speed of the gas
producer (N1) or the propeller (RPM).
TORQUE METER
An instrument that indicates engine torque output by
recording torque meter oil pressure in pounds per
square inch. (Torque X RPM is proportional to engine
power output delivered to the propeller gearbox.
STD
Standard temperature as defined in meteorological
terminology.
FF
Fuel flow in pounds per hour of fuel consumed.
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
DEMONSTRATED
CROSSWIND
VELOCITY
Demonstrated Crosswind Velocity is the velocity of
the crosswind component for which adequate control 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 (in pounds)
consumed per hour.
NMPG
Nautical Miles Per Gallon is the distance (in nautical
miles) which can be expected per gallon of fuel
consumed at a specific engine power setting and/or
flight configuration.
g
gis acceleration due to gravity.
MINIMUM FUEL
Minimum Fuel is the minimum amount of fuel as shown
in Section 2 for takeoff or steep climbs at airspeeds
below Vy.
COURSE DATUM
Course Datum is the compass reference used by the
autopilot, along with course deviation, to provide lateral
control when tracking a navigation signal.
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SOLOY TURBINE PAC SECTION 1
POHS CESSNA T206H/206H GENERAL
1-10
F.A.A. Approved May 23, 2003
WEIGHT AND BALANCE TERMINOLOGY
REFERENCE DATUM
Reference Datum is an imaginary vertical plane from
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 handbook to simplify balance
calculations by reducing the number of digits.)
CENTER OF
GRAVITY (C.G.)
Center of Gravity is the point at which an airplane or
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 EMPTY
WEIGHT
Standard Empty Weight is the weight of a standard
airplane, including unusable fuel, full operating fluids
and full engine oil.
BASIC EMPTY
WEIGHT
Basic Empty Weight is the standard empty weight
plus the weight of optional equipment.
USEFUL LOAD
Useful Load is the difference between ramp weight
and the basic empty weight.
MAXIMUM RAMP
WEIGHT
Maximum Ramp Weight is the maximum weight
approved for ground maneuver. (It includes the weight
of start, taxi and run-up fuel.)
MAC
MAC (Mean Aerodynamic Chord) is the chord of an
imaginary rectangular airfoil having the same pitching
moments throughout the flight range as that of the
actual wing.
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