Cessna U206G STATIONAIR Pilot Operating Handbook

SOLOY, LLC

450 Pat Kennedy Way S.W.

Olympia, WA 98501

PILOT’S OPERATING HANDBOOK

SUPPLEMENT

AND

FAA APPROVED AIRPLANE FLIGHT MANUAL

FOR

CESSNA U206G & TU206G STATIONAIR

SERIAL NOS. U20602589, U20603522 TO U20606846

1985 SERIAL NOS. U20606847 TO U20606920

1986 SERIAL NOS. U20606921 TO U20607020

SERIAL NO.: ___________________________

REGISTRATION NO.: ____________________

COPY

UNCONTROLLED

F.A.A. Approved

Date:

Publication Number: S1016A

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.

__________________________________________

Manager, Seattle Aircraft Certification Office

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

CONGRATULATIONS

CONGRATULATIONS . . . . .

Your airplane is SPECIAL! A Soloy, LLC 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 S upplement 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.

COPY

UNCONTROLLED

F.A.A. Approved

A

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

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 – 1/4/85

Revision … 1 … 1/11/85

Revision … 2 … 1/18/85

Revision … 3 … 4/15/85

Revision … 4 … 1/27/86

Revision … 5 … 4/11/86

Revision … 6 … 11/13/86

Revision … 7 … 3/29/90

Revision … 8 … 3/30/90

Revision … 9 … 5/11/90

Page Revision

Revision … 10 … 3/29/91

Revision … 11 … 4/2/91

Revision … 12 …

Revision … 13 … 12/23/99

Revision … 14 … 5/7/01

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Revision … 17 … COPY

7/30/92

10/4/05

11/14/14

11/17/15

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November 17, 2015 F.A.A. Approved

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POHS CESSNA U/TU 206G

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POHS CESSNA U/TU 206G

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November 17, 2015 F.A.A. Approved

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

Revision

No. Date

0

LOG OF REVISIONS

Pages

Revised

1/4/85 Original

Comments

Original of

Manual.

1 1/11/85 i, ii, iii, iii(a),

6-8, 9-2 and SSI 1 thru 3

Added Log of

Revisions

Page. Added

Soloy Supp.

No. 1, Exhaust

Heat

Exchanger Kit.

FAA Approval

Lester H. Berven for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 1/4/85

Lester H. Berven for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 1/11/85

2 1/18/85 i, ii, iii, iii(a),

6-8, 9-2 and SS2 1 thru 4

Added Soloy

Supp No. 2,

Engine Inlet

Anti-Ice Kit

Lester H. Berven for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055COPY

3 4/15/85 i, ii, iii, iii(a), Added UNCONTROLLED

4-20, 5-1,

5-6, 5-7, 5-

8, 5-11 thru

5-26 speeds and procedures.

Added bleed air information to checklist procedures.

Added performance information to performance section.

Lester H. Berven for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 4/15/85 v

F.A.A. Approved November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

4

Revision

No. Date

LOG OF REVISIONS (Continued)

Pages

Revised Comments

1/27/86 i, ii, iii, iii(a),

2-10, 8-11

Added 5.00-5, 6-

Ply Nose Wheel

Size

F.A.A. Approval

Lester H. Berven for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 1/27/86

5 4/11/86 i, ii, iii, iii(a),

2-1, 2-4, 2-5,

2-6, 2-6A, 7-

1, 7-2A, 7-2B,

7-2C, 7-3, 7-

3A, 7-8

Added information on 2” engine instruments.

Lester H. Berven for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 4/11/86

6 11/13/86 i, ii, iii, iii(a),

7-2C, 7-2D

Original of

Manual.

Lester H. Berven for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056 COPY

Donald B. Wilson

7 3/29/90 Title, I, iii(a) Added 1986

Serial Number UNCONTROLLED

4056

Date: 11/13/86

F.A.A. Approved vi

November 14, 2014

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LOG OF REVISIONS (Continued)

No

Revision

Date

8

Pages

Revised

3/30/90 I, ii, iii(a), 9-

1

Comments

Added

Cessna

Skydiving Kit to

Supplements,

Section 9

F.A.A. Approved

Donald B. Wilson for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 3/30/90

9 5/11/90 I, ii, iii, iii(a), iii(b), 4-5, 4-

6, 7-12A

Added schematic showing revised fuel vent and balance system.

Changed preflight inspection procedures.

Added second page to Log of

Revisions.

Collet E. McElroy for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 5/11/90

10 3/29/91 I, ii, iii, iii(b),

2-7, 6-4

Richard A. Paul

UNCONTROLLED

11 4/2/91 I, ii, iii(b), 7-

2E, 7-2F for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 3/29/91

Richard A. Paul

Added new

Figure # 7-3 showing instrument panel with

Grimes

Warning

Lights for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 4/2/91

F.A.A. Approved vii

November 14, 2014

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POHS CESSNA U/TU 206G

LOG OF REVISIONS (Continued)

Revision

No. Date

Pages

Revised

12 7/30/92 I, ii, iii, iii(a), iii(b), 2-8, 2-

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18, 4-4, 4-6,

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13, 4-20, 7-

2E, 7-2F, 7-

12B, 7-13,

7-13A

13 12/23/99 I, ii, iii(b),

9-2, SS3 1 thru 3

Comments

Addition to

Fuel Low

Warning

Systems.

Addition of fuel management system using a four position fuel valve.

Revised Log of Revisions format.

Added Soloy

Supplement

No. 3,

Continuous

Ignition Kit

F.A.A. Approved

Richard A. Paul for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 7/30/92

T.E.A. for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 12/23/99

14 5/7/01 I, ii, iii, iii(a), iii(b), iii(c), iii(d), 2-6, 4-

8, 4-17

Changed markings on propeller tachometer in

Limitations

Section.

Changed auto feather test procedures in

Normal

Procedures.

Upgraded

Log of

Revisions to current format, adding pages iii(c) and iii(d).

COPY

UNCONTROLLED for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 4/10/02

F.A.A. Approved viii

November 14, 2014

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POHS CESSNA U/TU 206G

LOG OF REVISIONS (Continued)

No.

Revision

Date

Pages

Revised Comments

15 10/4/05 All pages Re-issuance of complete POHS in digital format.

Changed all references to Soloy

Corporation to

Soloy, LLC. for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98055-

4056

Date: 10-4-05

Changed all references to

Allison Gas

Turbines to Rolls-

Royce.

F.A.A. Approved

T.E.A.

Corrected minor errors that occurred at last revision.

16 11/14/14 Cover i - ix

Section 1,

Section 2

2-12

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Reformatted revision log pages, no content change.

Added Rev 16.

II to Section 1 and

2.

COPY

Corrected cold weather fuel spec. number.

Oil Specs. for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98057-

3356

Date:

6-9, 7-27 Added provisions for optional battery.

8-1,8-6,8-7,

8-8,8-9

Updated Engine

Oil, Fuel specs.

(8-8 - 8-14) Entire contents of

8-8 deleted. All following pages shifted up as a result.

F.A.A. Approved ix

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

LOG OF REVISIONS (Continued)

No.

Revision

Date

Pages

Revised Comments F.A.A. Approved

17 11/17/15 Cover i-iv, x-xii

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4-1,4-2,4-7

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Added Rev 17.

Table of Contents moved from pg. x to pg. xi. Added page xii.

Updated TOC.

Added propeller

RPM speed avoid range.

Updated Fuel

Section formatting.

Updated Oil

Specification

Reference.

Updated engine start procedures.

Updated Auto feather procedure.

Updated amplified start procedures.

Added start/gen cooling cycles.

Updated amplified COPY

Contents.

Corrected battery rack installation weights.

Updated formatting.

Updated nose gear shock strut fill procedure. for Manager, Seattle

Aircraft Certification

Office, ANM-100S

Renton, WA 98057-

3356

Date:

UNCONTROLLED

F.A.A. Approved x

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

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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F.A.A. Approved xii

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 1

GENERAL

SECTION 1

GENERAL

TABLE OF CONTENTS Page

Introduction ........................................................................................... 1-4

Descriptive Data ................................................................................... 1-4

Engine ............................................................................................... 1-4

Propeller ............................................................................................ 1-4

Fuel ................................................................................................... 1-4

Oil ...................................................................................................... 1-4

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 ...................................................... 1-9

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SECTION 1

GENERAL

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UNCONTROLLED

F.A.A. Approved

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POHS CESSNA U/TU 206G

SECTION 1

GENERAL

COPY

UNCONTROLLED

Figure 1-1. Three View

F.A.A. Approved

1-3

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 1

GENERAL

INTRODUCTION

This handbook supplement contains nine sections and includes the material required to be furnished to the pilot by CAR Part 3. 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:

Engine Manufacturer:

Engine Model Number:

Horsepower Rating and Engine Speed:

Takeoff power (5 minute):

Maximum continuous Power:

PROPELLER

Propeller Manufacturer:

Propeller Model Number:

Number of Blades:

Propeller Diameter:

Propeller Type:

1

Soloy, LLC/Rolls-Royce

Soloy Turbine Pac, 780-1000-1

418 SHP @ 1810 RPM

321 SHP @ 1810 RPM

FUEL

Approved Fuel Grades:

Fuel Capacity:

S/Ns: U20603522 thru U20604649

Total Capacity:

Total Usable:

80 Gallons

76 Gallons

Hartzell

HC-C3YN-5A/FC9587D-2

3

95 Inches

Constant speed, hydraulically actuated, full feathering COPY maintenance, Section 8 UNCONTROLLED

S/Ns: U20602589, U20604650 thru U20606847 and on

Total Capacity:

Total Usable:

92 Gallons

88 Gallons

See handling, service and

OIL

Oil Specifications: See handling, service and maintenance, Section 8

Oil Capacity: 9 U.S. Quarts, including oil filter.

F.A.A. Approved

1-4

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

MAXIMUM CERTIFIED WEIGHTS

Takeoff:

Landing:

3,600 lbs.

3,600 lbs.

Weight in Baggage Compartment – Station 109 – 145:

S/Ns U20602589 & U20603522 thru U20604649 – 120 lbs. maximum

S/Ns U20604650 thru U20606847 and on – 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

SECTION 1

GENERAL

Standard Empty Weight, Stationair 6 (6 seats):

Stationair 6 II (6 seats):

Utility Option (1 seat):

II Utility Option (1 seat):

Maximum Useful Load, Stationair 6 (6 seats):

Stationair 6 II (6 seats):

Utility Option (1 seat):

II Utility Option (1 seat):

CABIN AND ENTRY DIMENSIONS

1927 lbs.

1987 lbs.

1882 lbs.

1941 lbs.

1685 lbs.

1625 lbs.

1730 lbs.

1671 lbs.

Detailed dimensions of the cabin interior and entry door opening are illustrated in Section 6.

Dimensions of the baggage/cargo area and cargo door opening are illustrated in detail in Section 6.

COPY

Wing Loading:

Power Loading:

20.7 lbs./sq. ft.

8.61 lbs./hp.

F.A.A. Approved

1-5

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 1

GENERAL

SYMBOLS, ABBREVIATIONS AND TERMINOLOGY

GENERAL AIRSPEED TERMINOLOGY & SYMBOLS

KCAS

KIAS

KTAS

V

A

V

FE

V

MO

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.

Knots Indicated Airspeed

is the speed shown on the airspeed indicator and expressed in knots.

Knots True Airspeed

is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature.

Maneuvering Speed

is the maximum speed at which you may use abrupt control travel.

Maximum Flap Extended Speed

is the highest speed permissible with wing flaps in a prescribed extended position.

Maximum Operating Limit Speed

is the speed limit that may not be deliberately exceeded in normal flight operations.

V

S

Stalling Speed or the minimum steady flight speed

at which the airplane is controllable.

V

SO

V

X

V

Y

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. COPY

Best Rate-of-Climb Speed

is the speed which results in the UNCONTROLLED

F.A.A. Approved

1-6

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

METEOROLOGICAL TERMINOLOGY

OAT

STANDARD

TEMPERATURE

PRESSURE

ALTITUDE

SECTION 1

GENERAL

Outside Air Temperature

is the free air static temperature. It is expressed in either degrees Celsius

(formerly Centigrade) or degrees Fahrenheit.

Standard Temperature

is 15  C at sea level pressure altitude and decreases by 2  C for each 1000 feet of 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 mb).

ENGINE POWER TERMINOLOGY

AUTO FEATHER

ENGINE START

(NORMAL)

FLAMEOUT

A system designed to automatically reduce drag of an inoperative engine by moving the propeller to a greater pitch angle.

The sequence of events that occur between starter actuation and N

1

stabilization at GROUND IDLE.

Unintentional loss of combustion chamber flame during operation.

Minimum position of the power control while airborne. FLIGHT IDLE

GAS PRODUCER

RPM (N

1

)

Indicates the percent of gas producer (compressor)

RPM based on a figure of 100% at 50,970 RPM.

GROUND IDLE

HOT START

MAXIMUM

CONTINUOUS

POWER

Minimum position of the power control when the airplane is not airborne. exceeds 927 

COPY

810  C to 927  C for more than 10 seconds. UNCONTROLLED

POWER TURBINE

SPEED (N

2

)

Determined by using the propeller RPM (N p

18.1 N p

RPM to 1% N

2

speed.

) at a ratio of

PROPELLER RPM

(N p

)

Indicates the speed of the propeller in revolutions per minutes (RPM). The power turbine speed (N be determined with this indicator where 18.1 N equal to 1% N

2

speed.

2

) can also p

RPM is

F.A.A. Approved

1-7

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

ENGINE POWER TERMINOLOGY (Continued)

SECTION 1

GENERAL

RPM

SHP

STAGNATED

START

TORQUE

TOT

Revolutions per minute.

Shaft horsepower is the power delivered at the propeller shaft.

Slow acceleration during an engine start, possibly deteriorating to total stoppage of acceleration even though combustion is still occurring in the combustion section.

A modulated oil pressure measurement that is directly proportional to the power output of the engine where 1

PSI = 4.12 SHP

Turbine outlet temperature.

ENGINE CONTROLS AND INSTRUMENTS

ENGINE

OVERSPEED

GOVERNOR

FUEL CUTOFF

CONTROL

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.

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 (N

1 cockpit power control.

), and the

POWER CONTROL

PROPELLER

GOVERNOR

PROPELLER

CONTROL

COPY

Adjusts the propeller blade pitch angle to maintain the

RPM selected by the cockpit propeller control regardless UNCONTROLLED

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 (N

1

) or the propeller (N p

).

F.A.A. Approved

1-8

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 1

GENERAL

ENGINE CONTROLS AND INSTRUMENTS (Continued)

TORQUE METER

STD

FF

An instrument that indicates power output of the engine in psi of torque where 1 psi is equal to 4.12 shp.

Standard temperature

as defined in meteorological terminology.

Fuel flow

in pounds per hour of fuel consumed.

AIRPLANE PERFORMANCE AND FLIGHT PLANNING

TERMINOLOGY

DEMONSTRATED

CROSSWIND

VELOCITY

USABLE FUEL

UNUSABLE FUEL

GPH

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 Fue l is the fuel available for flight planning.

Unusable Fuel

is the quantity of fuel that cannot be safely used in flight.

Gallons Per Hou r is the amount of fuel (in gallons) 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

MINIMUM FUEL

REFERENCE

DATUM g

is acceleration due to gravity.

Minimum Fuel

is the minimum amount of fuel as shown in Section 2 for takeoff or steep climbs at airspeeds below V y

.

COPY

UNCONTROLLED purposes.

is an imaginary vertical plane from which all horizontal distances are measured for balance

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.

F.A.A. Approved

1-9

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 1

GENERAL

WEIGHT AND BALANCE TERMINOLOGY (Continued)

MOMENT

CENTER OF

GRAVITY (C.G.)

C.G. ARM

C.G. LIMITS

STANDARD EMPTY

WEIGHT

BASIC EMPTY

WEIGHT

USEFUL LOAD

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

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.

Center of Gravity Arm

is the arm obtained by adding the airplane’s indivi dual moments and dividing the sum by the total weight.

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

is the weight of a standard airplane, including unusable fuel, full operating fluids and full engine oil.

Basic Empty Weight

is the standard empty weight plus the weight of optional equipment.

Useful Load

is the difference between ramp weight and the basic empty weight.

MAXIMUM RAMP

WEIGHT

GROSS (LOADED)

WEIGHT

Maximum Ramp Weight

is the maximum weight approved for ground maneuver. (It includes the weight of start, taxi and run-up fuel.)

Gross (Loaded) Weight airplane.

Maximum Takeoff Weight

is the maximum weight approved for the start of the takeoff run.

MAXIMUM TAKEOFF

WEIGHT

MAXIMUM LANDING

WEIGHT

TARE

Maximum Landing Weight

is the maximum weight approved for the landing touchdown.

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.

F.A.A. Approved

1-10

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

SECTION 2

LIMITATIONS

TABLE OF CONTENTS PAGE

Introduction .......................................................................................... 2-3

Airspeed Limitations ............................................................................ 2-3

Airspeed Indicator Markings ................................................................ 2-4

Powerplant Limitations ........................................................................ 2-4

Engine Operating Limits ....................................................................... 2-5

Propeller Limitations ............................................................................ 2-6

Powerplant Instrument Markings .......................................................... 2-7

Miscellaneous Instrument Markings ...................................................... 2-8

Weight Limits ....................................................................................... 2-9

Center of Gravity Limits ....................................................................... 2-9

Maneuver Limits .................................................................................. 2-9

Flight Load Factor Limits ..................................................................... 2-9

Kinds of Operation Limits ..................................................................... 2-10

Fuel Limitations ................................................................................... 2-10

Minimum Fuel .................................................................................. 2-11

Approved Fuel Grades ..................................................................... 2-11

Cold Weather Fuel Altitude Restrictions ........................................... 2-11

Fuel Additive ...................................................................................... 2-11

Oil Specifications ................................................................................. 2-12

Other Limitations ................................................................................. 2-12 COPY

Placards .............................................................................................. 2-13 UNCONTROLLED

F.A.A. Approved

2-1

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

This page left blank intentionally.

SECTION 2

LIMITATIONS

COPY

UNCONTROLLED

F.A.A. Approved

2-2

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

INTRODUCTION

– No change except:

This Supplement contains the information required to be furnished to the pilot by CAR Part 3 and must be carried in the airplane during flight operations. It also provides additional information which will assist in operating the airplane at its maximum efficiency.

Compliance with the limitations section is mandatory.

AIRSPEED LIMITATIONS

Airspeed limitations and their operational significance are shown in

Figure 2-1.

SPEED KCAS KIAS REMARKS

V

MO

Maximum operating speed:

V

A

Maneuvering speed:

3600 pounds

2900 pounds

2200 pounds

V

FE

Maximum flap extended speed:

to 10  flaps

10  to 40  flaps

Maximum window open speed:

148 149 Do not exceed in any operation.

121 120

Do not make full or abrupt control

109 108 movements above

95

137

94

137 this speed.

Do not exceed these speeds with the given flap setting.

99

148

96 speed with window open.

Figure 2-1. Airspeed Limitations

F.A.A. Approved

2-3

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

AIRSPEED INDICATOR MARKINGS

Airspeed indicator markings and their color code significance are shown in Figure 2-2.

MARKING KIAS SIGNIFICANCE

White Arc

Narrow

Wide

40 – 96

40 – 49

49 – 96

Full flap operating range. Lower limit is maximum weight stalling speed in landing configuration V so

. The transition point from narrow to wide arc is the stall speed with wing flaps in up position. Upper limit is the maximum speed permissible with flaps extended.

149 Maximum speed for all operations.

Red Line

Figure 2-2. Airspeed Indicator Markings

POWERPLANT LIMITATIONS

Engine Manufacturer: Soloy, LLC/Rolls-Royce

Engine Model Number: Soloy Turbine Pac, 780-1000-1

Engine Horsepower Rating:

Takeoff Power, 5 Minutes: 418 SHP

Maximum Continuous:

COPY

UNCONTROLLED

F.A.A. Approved

2-4

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

CONDITION ENGINE OPERATING LIMITS

SECTION 2

LIMITATIONS

Power

Setting

TAKEOFF

Maximum

(5 Min.)

Max. Cont.

101.4

Acceleration

78

810 105 1810 50-130

(1)

0-107 40-60

738 105 1810 50-130

(1)

0-107 40-60

843

(2)

106

(3)

1990

(7)

Starting 12

(5)

150

(8) (6)

927

(4)

NOTES:

1. N

1

and oil pressure limits are noted by a step in their respective arcs.

2.

3.

4.

Figure 2-3. Engine Operating Limits.

N

1

79% and below

79% to 94%

94% and above

COPY

50 - 130 psi UNCONTROLLED

Transient TOT allowable from 810  C for 6 seconds. (Intentional use not recommended.)

N

1

should not exceed 105% to 106% for more than 15 seconds.

Starting TOT allowable from 810  C to 927  C up to 10 seconds, with 927  C for 1 second. (Refer to the Rolls-Royce 250-C20

Series Operation and Maintenance Manual when start temperature consistently exceeds 810  C.)

F.A.A. Approved

2-5

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

5. Minimum starting N

1

speeds are: 15% above 7  C (45  F); 13% at -18  to +7  C (0  to 40  F); and 12% below -18  C (-1  F).

6. Minimum starting oil temperature; MIL-L-7808G or later, -54  C

(-65  F); MIL-L-23699, -40  C (-40  F).

7.

8.

N p

should not exceed 1810 to 1990 rpm for more than 15 seconds.

150 psi oil pressure is allowable following an engine start. Do not increase power until normal oil pressure limits are attained.

PROPELLER LIMITATIONS

Propeller Manufacturer: Hartzell

Propeller Model Number: HC-C3YN-5A/FC9587D-2

Number of Blades:

Propeller Diameter:

3

95.0 Inches

Propeller Blade Angle at 30 Inch Station:

Low:

Feathered:

Propeller Operating Limits:

Maximum Operating Speed:

5 

81 

1810 RPM

COPY

UNCONTROLLED

F.A.A. Approved

2-6

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

POWERPLANT INSTRUMENT MARKINGS

SECTION 2

LIMITATIONS

POWERPLANT INSTRUMENT MARKINGS

INSTRUMENT

LIMIT

PROPELLER

------ 1630 to

1810

RPM

1480 to

1630

RPM

(4)(5)

1810

RPM

1990

RPM

(3)

------ 105% 106%

(3) N

1

12% to

15%

59% 59%-

105%

(1)

TORQUE ------ 0-78 78- 101.4

TOT 150



C ------

PSI

(2)

400

738





-

C

101.4

PSI

738



-

810



C

PSI

810



C 843



C

(3)

927



C

ENGINE OIL

(TEMP)

ENGINE OIL

(PRESSURE)

------ 0-

107



C

50 PSI 90-130

PSI

(1)

------ 107



C ------

50-90

PSI

(1)

130 PSI ------ 150 PSI

TRANS-

MISSION OIL

(PRESS.)

40 PSI 40-60

PSI

------ 60 PSI ------

Figure 2-4. Engine Instrument Markings.

F.A.A. Approved

2-7

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

MISCELLANEOUS INSTRUMENT MARKINGS

------ SUCTION

AMMETER

------ 4.6-5.4 in. Hg.

------ ---

---

150

AMP

80-150

AMP

FUEL QTY. E E to

1/8

NOTES

Figure 2-5. Miscellaneous Instrument Markings.

: (1) N

1

and oil pressure limits are noted by a step in their respective arcs.

N

1

79% and below

79% to 94%

94% and above

Engine Oil Pressure COPY

(2)* Minimum in flight torque is 14 psi. UNCONTROLLED

(4) Limit - 60 seconds at torque settings greater than 20 psi.

(5) Aircraft incorporating an “enhanced” power turbine wheel per

Rolls-Royce CEB A-1365 must include the yellow arc extending from 1358 rpm to 1630 rpm.

* These markings are depicted on the optional two inch engine instruments.

F.A.A. Approved

2-8

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

WEIGHT LIMITS

Maximum Takeoff Weight:

Maximum Landing Weight:

S/Ns U20602589, U20603522 thru U20604649: 120 lbs.

S/Ns U20604650 thru U20606847 and on:

3600 lbs.

3600 lbs.

Maximum Weight in Baggage Compartment – Station 109 to 145:

180 lbs.

NOTE

Refer to Section 6 of this handbook for loading arrangement with one or more seats for cargo accommodation.

CENTER OF GRAVITY LIMITS

Center of Gravity Range:

Forward: 33.0 inches aft of datum at 2500 lbs. or less, with straight line variation to

42.5 inches aft of datum at 3600 lbs.

Aft:

Reference Datum:

MANEUVER LIMITS

This airplane is certificated in the normal category. The normal category is applicable to aircraft intended for non-aerobatic operations.

These include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and turns in which the angle of bank is not more than 60  .

49.7 inches aft of datum at all weights.

Lower portion of front face of firewall.

COPY

UNCONTROLLED

FLIGHT LOAD FACTOR LIMITS

Flight Load Factors:

Flaps Up:

Flaps Down:

+3.8g, -1.52g

+2.0g

F.A.A. Approved

2-9

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

KINDS OF OPERATION LIMITS

Flight into known icing conditions is prohibited.

The engine alternate air must be activated for flight or ground operation in the following conditions:

A. In visible moisture at an OAT of 5  C (41  F) and below.

B. While operating in falling or blowing snow regardless of ambient temperature.

CAUTION

THE ENGINE ALTERNATE AIR SYSTEM MUST BE

OPERATED IN THE ABOVE MENTIONED CONDI-

TIONS EVEN IF THERE IS NO VISIBLE SIGN OF

AIRFRAME ICE AND/OR SNOW ACCUMULATION.

Deactivation of the system shall not be made until the above mentioned conditions no longer exist and all accumulated airframe ice and/or snow has dissipated.

CAUTION

SIGNIFICANT POWER LOSS WILL OCCUR

WHILE OPERATING IN THE ALTERNATE AIR

MODE. EXTREME CAUTION SHOULD BE

FUEL LIMITATIONS

USED TO MAINTAIN A MINIMUM OF 14 PSI

LANDING.

COPY

UNCONTROLLED

For Aircraft S/Ns U20603522 thru U20604649

Two interconnected tanks:

Usable Fuel:

Unusable Fuel: 4.0 U.S. gallons

For Aircraft S/ns U20602589, U20604650 thru U20606847 and on

Two interconnected tanks:

Usable Fuel:

Unusable Fuel:

40 U.S. gallons each

76 U.S. gallons

46 U.S. gallons each

88 U.S. gallons

4.0 U.S. gallons

F.A.A. Approved

2-10

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

MINIMUM FUEL

Due to the possibility of fuel starvation, takeoff or steep climbs at speeds below V y

(86 KIAS at sea level) with either fuel quantity gauge indicating in the yellow arc (1/8 fuel quantity), or if installed FUEL LOW lights are on, are prohibited.

If installed, illumination of a FUEL LOW light will be handled as follows:

LEFT FUEL LOW – ON Switch to RIGHT tank.

FUEL CONFIG light illuminated.

RIGHT FUEL LOW – ON Switch to LEFT tank.

FUEL CONFIG light illuminated.

Both FUEL LOW – ON Switch to BOTH and land as soon as practical.

APPROVED FUEL GRADES

(1) PRIMARY FUELS

(A) MIL-T-5624 Grade JP-5.

(B) MIL-T-83133 Grade JP-8.

(C) ASTM D-1655, Jet A or A1.

(D) JP-1 Fuel Conforming to ASTM D-1655, Jet A.

(E) Diesel #1 Fuel Conforming to ASTM D-1655, Jet A.

(2) COLD WEATHER FUELS

To assure consistent starts below 4 necessary:

COPY

(A) MIL-T-5624, Grade JP-4.

(B) ASTM D-6615, Jet B. UNCONTROLLED

COLD WEATHER FUEL ALTITUDE RESTRICTIONS

The maximum flight altitude is restricted to 8,000 feet when using any cold weather fuel and the fuel temperature is 4ºC or above.

FUEL ADDITIVE

For flight at ambient temperatures of 40°F and below, the fuel used in this aircraft MUST have an anti-icing additive in compliance with MIL-

DTL- 85470B, incorporated or added into the fuel during refueling in accordance with the additive manufacturer’s instructions.

F.A.A. Approved

2-11

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

CAUTION

PROPER MIXING OF THE ANTI-ICING ADDITIVE WITH

FUEL IS EXTREMELY IMPORTANT BECAUSE CON-

CENTRATION IN EXCESS OF THAT RECOMMENDED

(0.15% BY VOLUME) WILL RESULT IN DETRIMENTAL

EFFECTS TO THE FUEL TANKS. ASSURE THAT THE

FUEL ADDITIVE IS DIRECTED INTO AND BLENDING

WITH FLOWING FUEL FROM THE FUELING NOZZLE.

DO NOT ALLOW CONCENTRATED ADDITIVE TO

CONTACT THE FUEL CELL OR AIRPLANE FINISH.

SOME FUELS HAVE ANTI-ICING ADDITIVES PRE-

BLENDED IN THE FUEL AT THE REFINERY, SO NO

ADDITIONAL ADDITIVES SHOULD BE ADDED.

Refer to Section 8, Handling, Service & Maintenance for further information.

NOTE

Fuel containing Tri-Cresyl-Phosphate (TCP) additives shall not be used.

OIL SPECIFICATIONS

The 250 series engines are certified and approved for use with only certain lubricating oils that comply with MIL-PRF-7808, MIL-PRF-23699, DOD-PRF-

85734, or SAE AS5780 specifications. Refer to the Rolls-Royce M250-C20

Series Operation and Maintenance Manual for current approved oils and limitations.

OTHER LIMITATIONS

FLIGHT IDLE LIMITS

Flight operations with the power control retarded below FLIGHT IDLE

(14 psi torque minimum) are prohibited.

FLAP LIMITATIONS

COPY

UNCONTROLLED

Approved Takeoff Range:

Approved Landing Range:

0

0





to 20

to 40





F.A.A. Approved

2-12

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

LANDING GEAR LIMITATIONS

Nose Wheel Size: 6.00-6

5.00-5 (Limited to 6.00-6 main wheel size only with 5.00-5 nose wheel)

Main Wheel Size: 6.00-6

8.00-6

8.50-6

MAXIMUM OPERATING ALTITUDE LIMITS

Maximum Operating Altitude: 20,000 feet.

PLACARDS

The following information is displayed in the form of composite or individual placards.

(1) In full view of the pilot: (The “DAY-NIGHT-VFR-IFR” entry, shown on the example below, will vary as the airplane is equipped.)

For S/Ns U20602589, U20604650 thru U20606847 and on

The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the Normal

Category. Other operating limitations which must be complied with when operating this airplane in this category are contained in the Pilot’s Operating

Handbook and FAA Approved Airplane Flight Manual.

No acrobatic maneuvers, including spins, approved.

COPY

UNCONTROLLED

Flight into known icing conditions prohibited.

This airplane is certified for the following flight operations as of date of original airworthiness certificate:

DAY – NIGHT – VFR – IFR

F.A.A. Approved

2-13

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

(1) In full view of the pilot: (The “DAY-NIGHT-VFR-IFR” entry, shown on the example below, will vary as the airplane is equipped.)

For S/Ns U20603522 thru U20604649

This airplane must be operated as a normal category airplane in compliance with the operating limitations stated in the form of placards, markings and manuals:

_________________MAXIMUMS_________________

U206/TU206G Landplane

Maneuvering Speed (IAS)

Gross Weight

Flight Load Factor

120 Knots

3600 Lbs

Flaps Up +3.8, - 1.52

Flaps Down +2.0

No acrobatic maneuvers, including spins, approved.

Altitude loss in a stall recovery - 240 feet.

Flight into known icing conditions prohibited.

This airplane is certified for the following flight operations as of date of original airworthiness certificate.

(2) On control lock:

DAY – NIGHT – VFR – IFR

COPY

For S/Ns: U20602589, U20603522 thru U20606847 and on UNCONTROLLED

F.A.A. Approved

2-14

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

(3) On fuel selector plate:

For S/Ns: U20603522 thru U20604649

TWO-POSITION SELECTOR VALVE

USABLE FUEL 76 U.S. GAL.

FUEL SELECTOR

“ON” “OFF”

FOUR-POSITION SELECTOR VALVE

SECTION 2

LIMITATIONS

COPY

UNCONTROLLED

F.A.A. Approved

2-15

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

(3) On fuel selector plate:

SECTION 2

LIMITATIONS

For S/Ns: U20602589, U20604650 thru U20606847 and on

TWO-POSITION SELECTOR VALVE

USABLE FUEL 88 U.S. GAL.

FUEL SELECTOR

“ON” “OFF”

FOUR-POSITION SELECTOR VALVE

COPY

UNCONTROLLED

F.A.A. Approved

2-16

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

(4) Forward of fuel tank filler cap:

SECTION 2

LIMITATIONS

For S/Ns: U20602589, U20603522 thru U20606847 and on

FUEL

JET A

SEE PILOT’S OPERATING HANDBOOK

FOR ANTI-ICE ADDITIVE

REQUIREMENT AND ALTERNATE

FUELS.

(5) On oil filler cap:

For S/Ns: U20602589, U20603522 thru U20606847 and on

COPY

UNCONTROLLED

F.A.A. Approved

OIL

(6) Near alternate air control:

For S/Ns: U20602589, U20603522 thru U20606847 and on

N

O

R

M

A

L

T

A

I

R

A

L

T

ALT OPERATION REQUIRED:

- IN FALLING OR BLOWING

SNOW

- IN VISIBLE MOISTURE AT AN

OAT OF 5ºC (41ºF) AND BELOW

2-17

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

(7) On the flap control indicator:

For S/Ns: U20602589, U20603522 thru U20606847 and on

1

3

7

9

6

(8) On the warning lights dimmer switch:

For S/Ns: U20602589, U20603522 thru U20606847 and on

WARNING

I

LIGHTS

D

M

B

R

T

For S/Ns: U20602589, U20603522 thru U20606847 and on UNCONTROLLED

POWER

PUSH

INCR

COPY

F.A.A. Approved

2-18

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

(10) Next to the propeller control:

For S/Ns: U20602589, U20603522 thru U20606847 and on

PROP

RPM

PULL

FTHR

(11) Next to the fuel cutoff control:

For S/Ns: U20602589, U20603522 thru U20606847 and on

FUEL

PULL

CUT

OFF

(12) Between the fuel gauges:

For S/Ns: U20602589, U20603522 thru U20606847 and on COPY

Y

IF

FUEL GAUGES INDICATE IN YELLOW ARC. UNCONTROLLED

F.A.A. Approved

2-19

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

(13) On aft cargo door:

For S/N U20602589, U20603522 thru U20604649:

BAGGAGE NET 120 LBS MAX CAPACITY.

REFER TO WEIGHT AND BALANCE DATA

FOR BAGGAGE AND CARGO LOADING.

For S/Ns U20604650 thru U20606847 and on:

BAGGAGE NET 180 LBS MAX CAPACITY.

REFER TO WEIGHT AND BALANCE DATA

FOR BAGGAGE AND CARGO LOADING.

(14) On forward cargo door:

For S/N U20602589, U20603522 thru U20604649:

EMERGENCY EXIT OPERATION

1. OPEN FORWARD CARGO DOOR AS FAR AS

POSSIBLE.

2. ROTATE RED LEVER IN REAR CARGO DOOR

FORWARD.

COPY

UNCONTROLLED

EMERGENCY EXIT OPERATION

1. ROTATE FORWARD CARGO DOOR HANDLE

FULL FORWARD THEN FULL AFT.

2. OPEN FORWARD CARGO DOOR AS FAR AS

POSSIBLE.

3. ROTATE RED LEVER IN REAR CARGO DOOR

FORWARD.

4. FORCE REAR CARGO DOOR FULL OPEN.

F.A.A. Approved

2-20

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 2

LIMITATIONS

(15) Next to the fuel totalizer:

For S/Ns: U20602589, U20603522 thru U20606847 and on

MAXIMUM ALTITUDE 8,000 FEET WHEN USING

COLD WEATHER FUEL AT

FUELTEMPERATURES ABOVE 4°C.

(16) Near airspeed indicator:

For S/Ns: U20602589, U20604650 thru U20606847 and on

MANUVER SPEED

120 KIAS

(17) A calibration card is provided to indicate the accuracy of the magnetic compass in 30º increments.

(18) Forward of each fuel tank filler cap in line with forward arrow:

For S/Ns: U20602589, U20604650 thru U20606847 and on

COPY

UNCONTROLLED

F.A.A. Approved

2-21

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

This page left blank intentionally.

SECTION 2

LIMITATIONS

COPY

UNCONTROLLED

F.A.A. Approved

2-22

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

SECTION 3

EMERGENCY PROCEDURES

TABLE OF CONTENTS PAGE

Introduction ............................................................................. 3-3

Airspeeds For Emergency Operation ....................................... 3-3

OPERATIONAL CHECKLIST

Engine Failures ........................................................................ 3-3

Engine Failure During Takeoff Run .................................. 3-3

Engine Failure Immediately After Takeoff ......................... 3-4

Engine Failure During Flight ............................................. 3-4

Engine Restart Procedure During Flight ........................... 3-4

Forced Landings ...................................................................... 3-5

Emergency Landing Without Engine Power ..................... 3-5

Precautionary Landing With Engine Power ...................... 3-6

Ditching ........................................................................... 3-6

Fires ....................................................................................... 3-6

During Start on Ground .................................................... 3-6

Engine Fire In Flight ......................................................... 3-7

Electrical Fire In Flight ..................................................... 3-7

Cabin Fire ...................................................................... 3-8

Wing Fire ......................................................................... 3-8

Icing ........................................................................................ 3-9 COPY

Reading Suspected) ........................................................ 3-11 UNCONTROLLED

Auto Feather System Failure In Flight .................................... 3-11

Propeller Auto Feather ................................................... 3-11

F.A.A. Approved

3-1

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

TABLE OF CONTENTS (Continued)

.................................

PAGE

AMPLIFIED PROCEDURES

Engine Failure ...................................................................... 3-13

Forced Landings .................................................................... 3-14

Landing Without Elevator Control ............................................ 3-14

Fires ……………………………………………………………….. 3-14

Emergency Operation In Clouds ............................................ 3-15

Vacuum System Failure ................................................. 3-15

Executing a 180 Degree Turn In Clouds ........................ 3-15

Emergency Descent Through Clouds ............................. 3-15

Recovery From A Spiral Dive ......................................... 3-16

Flight In Icing Conditions ........................................................ 3-16

Engine Alternate Air System Failure ...................................... 3-16

Alternate Air Light Does Not Illuminate ........................... 3-17

Alternate Air Light Illuminates In Flight ........................... 3-17

Static Source Blocked .................................................... 3-17

Spins ...................................................................................... 3-17

Rough Engine Operation or Loss of Power ............................ 3-18

Compressor Stall ........................................................... 3-18

Fuel Filter Bypass .................................................................. 3-18

Auto Feather System Failure In Flight .................................... 3-18

Low Engine Oil Pressure and/or Low Transmission Pressure .. 3-19

Oil Chip Detector ................................................................... 3-19

Electrical Power Supply System Malfunctions ........................ 3-19

Excessive Generator Output .......................................... 3-19

Insufficient Generator Output ......................................... 3-20

Cargo Door Emergency Exit .................................................. 3-20 COPY

UNCONTROLLED

F.A.A. Approved

3-2

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

INTRODUCTION

Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced. Enroute weather emergencies can be minimized or eliminated by careful flight planning and good judgment when unexpected weather is encountered. However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. Emergency procedures associated with ELT and other optional systems can be found in Section 9.

AIRSPEEDS FOR EMERGENCY OPERATION

Engine Failure After Takeoff:

Wing Flaps Up

Wing Flaps Down

Maximum Glide:

3600 Lbs

3200 Lbs

2800 Lbs

Landing Without Engine Power:

Wing Flaps Up

Wing Flaps Down

80 KIAS

70 KIAS

82 KIAS

76 KIAS

70 KIAS

80 KIAS

70 KIAS

OPERATIONAL CHECKLISTS

ENGINE FAILURES

COPY

UNCONTROLLED

1. Power Control – GROUND IDLE.

2. Brakes – APPLY.

3. Wing Flaps – RETRACT.

4. Fuel Cutoff Control – CUTOFF (OUT)

5. Monitor TOT

F.A.A. Approved

3-3

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

NOTE

An internal engine fire (recognized by a rapid increase in TOT) can occur during shutdown if fuel cutoff is not complete. If a shutdown fire occurs, immediately engage the starter and motor the engine to minimize the temperature encountered.

The temperature limitations and associated maintenance actions must be observed.

ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF

1. Airspeed – 80 KIAS

2. Propeller Control – FEATHER (OUT)

3. Fuel Cutoff Control – CUTOFF (OUT)

4. Fuel Selector Valve – OFF (PRESS DOWN SAFETY SPRING

TO ALLOW MOVEMENT TO OFF)

5. Wing Flaps – AS REQUIRED (40  recommended)

6. Battery – OFF

ENGINE FAILURE DURING FLIGHT

1. Airspeed – BEST GLIDE SPEED

2. Fuel Cutoff Control – CUTOFF (OUT)

3. Monitor TOT

4. Propeller Control – FEATHER (OUT)

5. Power Control – FLIGHT IDLE

6. Generator – OFF COPY

WITHOUT ENGINE POWER CHECKLIST. UNCONTROLLED

2. Propeller Control – FEATHER (OUT)

3. Engine Inlet Anti-Ice – OFF

4. ACTIVATE engine alternate air system if in icing conditions.

5. Airspeed 75 – 120 KIAS below 15,000 FT. MSL.

110 – 120 KIAS 15,000 to 20,000 FT. MSL.

6. Fuel Selector – ON (BOTH if fuel low warning system installed).

7. Power Control – FLIGHT IDLE

8. Start Motor Switch – MOTOR

F.A.A. Approved

3-4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

9. TOT 150

N

1

 or lower and N

1

15% below 15,000 FT. MSL.

maximum obtainable above 15,000 FT. MSL.

10. Start Motor Switch – START and hold

11. Fuel Cutoff Control – RUN (IN)

12. TOT and N

1

– MONITOR (810  to 927  C FOR 10 SECONDS

MAXIMUM)

13. De-energize the starter at 58% N

14. Propeller Control – IN

1

NOTE

As the propeller comes out of feather, there will be an oscillation of power until the propeller RPM stabilizes.

15. Apply power as required.

WARNING

DUE TO THERMAL CHANGES WITHIN

THE TURBINE, THE GAS PRODUCER

SECTION OF THE ENGINE MAY LOCK UP

AFTER AN IN-FLIGHT SHUTDOWN. THIS

IS A TEMPORARY CONDITION WHICH

EXISTS AFTER THE ENGINE HAS BEEN

SHUTDOWN FOR APPROXIMATELY ONE

MINUTE AND WHICH MAY CONTINUE

FOR UP TO TEN MINUTES FOLLOWING

SHUTDOWN. THEREFORE, EXCEPT

DURING AN EMERGENCY, AIR STARTS COPY

MINUTES AFTER SHUTDOWN.

EMERGENCY LANDING WITHOUT ENGINE POWER

1. Airspeed – 80 KIAS Flaps up, 70 KIAS Flaps 40  .

2. Propeller Control – FEATHER (OUT)

3. Fuel Cutoff Control – CUTOFF (OUT)

4. Fuel Selector – OFF.

5. Flaps – AS REQUIRED (40  recommended)

6. Battery and Generator – OFF

7. Doors – UNLATCH PRIOR TO TOUCHDOWN

8. Touchdown – SLIGHTLY TAIL LOW

9. Brakes – APPLY HEAVILY

F.A.A. Approved

3-5

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

PRECAUTIONARY LANDING WITH ENGINE POWER

1. Airspeed – 80 KIAS

2. Wing Flaps -- 20 

3. Selected Field – FLY OVER NOTING TERRAIN &

OBSTRUCTIONS

4. Radio and Electrical Switches – OFF

5. Wing Flaps -- 40  (recommended on final approach)

6. Power Control – As Required (FLIGHT IDLE minimum 14 psi torque)

7. Airspeed – 70 KIAS

8. Battery Switch – OFF

9. Doors – UNLATCHED PRIOR TO TOUCHDOWN

10. Touchdown – SLIGHTLY TAIL LOW

11. Fuel Cutoff Control – CUTOFF (OUT)

12. Brakes – APPLY HEAVILY

DITCHING

1. Radio – TRANSMIT MAYDAY on 121.5 MHz, giving location and intentions.

2. Heavy Objects (in baggage area) – SECURE OR JETTISON

3. Wing Flaps -- 40 

4. Approach: High Winds, Heavy Seas – INTO THE WIND

Light Winds, Heavy Swells – PARALLEL TO SWELL

5. Power – ESTABLISH 300 FT/MIN DESCENT AT 65 KIAS.

6. Cabin Doors – UNLATCH

7. Touchdown – LEVEL ATTITUDE AT 300 FT/MIN DESCENT

8. Face – CUSHION at touchdown with folded coat

9. Airplane – EVACUATE through cabin doors. If necessary, open window and flood cabin to equalize pressure so doors can be opened.

COPY

UNCONTROLLED

CAUTION

AN ENGINE FIRE (WITH THE RESULTANT

FLAME EMANATING FROM THE TAILPIPE)

CAN OCCUR DURING START IF THE COM-

BUSTION CHAMBER BECOMES OVER-

LOADED WITH FUEL BEFORE IGNITION

TAKES PLACE.

F.A.A. Approved

3-6

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

1. Fuel Cutoff Control – CUTOFF (OUT)

2. Start Motor Switch – MOTOR to extinguish the fire.

3. Fuel Selector – OFF

4. Monitor – TOT

5. Fire Extinguisher – OBTAIN (have ground attendants obtain if not installed).

6. Engine Secure a. Start Switch – OFF b. Battery Switch -- OFF

7. Exit Aircraft – INSPECT FIRE DAMAGE, associated maintenance actions must be observed.

ENGINE FIRE IN-FLIGHT

1. Fuel Cutoff Control – CUTOFF (OUT)

2. Propeller Control – FEATHER (OUT)

3. Fuel Selector – OFF

4. Battery and Generator – OFF (except IFR)

5. Cabin Heat and Air – OFF (except overhead vent)

6. Airspeed – 105 KIAS (If fire is not extinguished, increase glide speed to find an airspeed which will provide an incombustible mixture.)

7. Forced Landing – EXECUTE (as described in Emergency

Landing Without Engine Power).

ELECTRICAL FIRE IN-FLIGHT

1. Battery and Generator – OFF

2. All Other Switches – OFF

3. Vents/Cabin Air/Heat – CLOSED COPY

AFTER THE FIRE IS EXTINGUISHED, IF UNCONTROLLED

UNTIL SMOKE AND DISCHARGED

POWDER CLEARS. AFTER DISCHARG-

ING EXTINGUISHER WITHIN A CLOSED

CABIN, VENTILATE THE CABIN.

F.A.A. Approved

3-7

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

If fire appears out and electrical power is necessary for continuance of the flight:

5. Battery and Generator – ON

6. Monitor electrical load

7. Circuit Breakers – CHECK for faulty circuit, do not reset.

8. Radio/Electrical Switches – ON one at a time, with delay after each until short circuit is localized.

9. Vents/Cabin Air/Heat – OPEN when it is ascertained that fire is completely extinguished.

CABIN FIRE

1. Master Switch- OFF

2. Vents/Cabin Air/Heat – CLOSED (to avoid drafts)

3. Fire Extinguisher – ACTIVATE (if available)

WARNING

AFTER THE FIRE IS EXTINGUISHED, IF AN

OXYGEN SYSTEM IS AVAILABLE, OCCUPANTS

SHOULD USE OXYGEN MASKS UNTIL SMOKE

AND DISCHARGED DRY POWDER CLEARS.

AFTER DISCHARGING AN EXTINGUISHER

WITHIN A CLOSED CABIN, VENTILATE THE

CABIN.

4. Land the airplane as soon as possible to inspect for damage.

WING FIRE COPY

UNCONTROLLED from the fuel tank and cabin, and land as soon as possible.

F.A.A. Approved

3-8

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

ICING

INADVERTENT ICING ENCOUNTER

NOTE

The engine alternate air must be activated for flight or ground operation in visible moisture at an OAT of 5  C (41  F) and below or while operating in falling or blowing snow regardless of ambient temperature.

This system must be operated in the above mentioned conditions even if there is no visible sign of airframe ice and/or snow accumulation.

Deactivation of the system shall not be made until the above mentioned conditions have been left and all accumulated airframe ice and/or snow has dissipated.

ALTERNATE AIR OPERATION

1. Engine alternate air lever – ALT monitor ALT AIR light.

2. Visually check that the ram inlet doors are raised.

NOTE

A drop in torque and a rise in TOT is normal with the actuation of the engine ice protection system. conducive to icing.

COPY

3. Turn pitot heat switch ON (if installed0.

4. Turn back or change altitude to obtain an OAT that is less UNCONTROLLED

6. If icing conditions are unavoidable, plan a landing at the nearest airport.

7. With an ice accumulation of ¼ inch or more on the wing leading edges, be prepared for a significantly higher power requirement, approach speed, stall speed, and landing roll.

8. Open left window and, if practical, scrape ice from a portion of the windshield for visibility during the landing approach.

F.A.A. Approved

3-9

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

9. Use a 10º to 20º landing flap setting for ice accumulations of 1 inch or less. With heavier ice accumulations, approach with flaps retracted to ensure adequate elevator effectiveness in the approach and landing.

10. Power Control – As required (FLIGHT IDLE minimum 14 psi torque).

CAUTION

SIGNIFICANT POWER LOSS WILL

OCCUR WHILE OPERATING IN THE

ALTERNATE AIR MODE. EXTREME

CAUTION SHOULD BE USED TO

MAINTAIN A MINIMUM OF 14 PSI

TORQUE IN FLIGHT ON APPROACH TO

LANDING.

11. Approach at 90 to 100 KIAS with 20  flaps and 105 to 115 KIAS with 0  to 10  flaps.

12. Land on main wheels first, avoiding the slow and high type of flare-out.

13. Missed approaches should be avoided.

ENGINE ALTERNATE AIR FAILURE

ALTERNATE AIR LIGHT DOES NOT ILLUMINATE:

1. Visually check that the ram inlet doors are raised.

2. If doors are not raised, cycle the alternate air control and check for reverse operation.

COPY

ALTERNATE AIR LIGHT ILLUMINATES IN FLIGHT:

UNCONTROLLED

3. If the ram inlet doors are raised, cycle the alternate air control and check for reverse operation.

4. If system has failed in the alternate position, land as soon as practicable and check the inlet and the pneumatic lines.

F.A.A. Approved

NOTE

During takeoff or steep climbs at low airspeeds and high power, the alternate air light can illuminate intermittently when in the normal air mode.

3-10

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

STATIC SOURCE BLOCKAGE

(Erroneous Instrument Reading Suspected)

1. Vents and Windows – CLOSED

2. Alternate Static Source Valve – PULL ON

3. Airspeed – Consult Calibration Table in Section 5.

LANDING WITH A FLAT MAIN TIRE

1. Wing Flaps – AS DESIRED (0  - 10  below 137 KIAS,

10  – 40  below 96 KIAS).

2. Make a normal approach.

3. Touchdown – GOOD TIRE FIRST, hold airplane off flat tire as long as possible with aileron control.

ELECTRICAL POWER SUPPLY SYSTEM

MALFUNCTIONS

AMMETER SHOWS 0 AMPS

(Indicated by the

GEN OFF BUS

Warning Light)

1. Trip and reset the generator trip reset switch.

If light remains on:

2. Generator Switch – OFF

3. Generator Field Circuit Breaker – RESET

4. Generator Switch – ON

If light remains on, and ammeter shows no amps:

5. Generator Field Circuit Breaker – PULL

6. Non-essential Radio/Electrical Equipment – OFF

7. Flight – TERMINATE as soon as practical.

AUTO FEATHER SYSTEM FAILURE IN FLIGHT

PROPELLER AUTO FEATHERS

COPY

UNCONTROLLED

1. Pull the “AUTO-FTHR ANN. LGHT” circuit breaker.

2. Land at the next suitable airport for repairs.

CAUTION

WITH THE AUTO FEATHER ANNUN-

CIATOR LIGHT CIRCUIT BREAKER

PULLED, THE ANNUNCIATOR PANEL

LIGHTS WILL BE DISABLED.

F.A.A. Approved

3-11

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

This page left blank intentionally

COPY

UNCONTROLLED

F.A.A. Approved

3-12

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

AMPLIFIED PROCEDURES

ENGINE FAILURE

If an engine failure occurs during the takeoff run, the most important thing to do is stop the airplane on the remaining runway. Those extra items on the checklist will provide added safety after a failure of this type.

Prompt lowering of the nose and feathering of the propeller to maintain airspeed and establish a glide attitude is the first response to an engine failure after takeoff. In most cases, the landing should be planned straight ahead with only small changes in direction to avoid obstructions. Altitude and airspeed are seldom sufficient to execute a 180  gliding turn necessary to return to the runway. The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown.

After an engine failure in flight, the best glide speed as shown in Figure 3-1 should be established as quickly as possible. While gliding toward a suitable landing area, an effort should be made to identify the cause of the failure. If time permits, an engine restart should be attempted as shown in the checklist. If the engine cannot be restarted, a forced landing without power must be completed.

COPY

UNCONTROLLED

Figure 3-1. Maximum Glide

F.A.A. Approved

3-13

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

FORCED LANDINGS

If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing as discussed under the

Emergency Landing Without Engine Power checklist.

Before attempting an “off airport” landing with engine power available, one should fly over the landing area at a safe but low altitude to inspect the terrain for obstructions and surface conditions, proceeding as discussed under the Precautionary Landing With Engine Power checklist.

Prepare for ditching by securing or jettisoning heavy objects located in the baggage area and collect folded coats for protection of occupants’ face at touchdown. Transmit Mayday message on 121.5 MHz giving location and intentions and squawk 7700 if transponder is installed. Avoid a landing flare because of difficulty in judging height over a water surface.

LANDING WITHOUT ELEVATOR CONTROL

Trim for horizontal flight (with an airspeed of approximately 90 KIAS and flaps set to 20  ) by using throttle and trim tab controls.

Then do not change the trim tab setting

and control the glide angle by adjusting power exclusively.

At flareout, the nose down moment resulting from power reduction is an adverse factor and the airplane may hit on the nose wheel. Consequently, at flareout, the trim tab should be set at full nose-up position and the power adjusted so that the airplane will rotate to the horizontal attitude for touchdown. Power control to ground idle at touchdown.

FIRES

COPY

UNCONTROLLED internal engine fire and hot start. In this event, follow the prescribed checklist.

Although engine fires are extremely rare in flight, the steps of the appropriate checklist should be followed if one is encountered. After completion of this procedure, execute a forced landing. Do not attempt to restart the engine.

The initial indication of an electrical fire is usually the odor of burning insulation. The checklist for this problem should result in elimination of the fire.

F.A.A. Approved

3-14

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

EMERGENCY OPERATION IN CLOUDS

VACUUM SYSTEM FAILURE

In the event of a vacuum system failure during flight, the directional indicator and attitude indicator will be disabled, and the pilot will have to rely on the turn coordinator or the turn and bank indicator if he inadvertently flies into clouds. The following instructions assume that only the electrically powered turn coordinator or the turn and bank indicator is operative, and that the pilot is not completely proficient in instrument flying.

EXECUTING A 180



TURN IN CLOUDS

Upon inadvertently entering the clouds, an immediate plan should be made to turn back as follows:

1. Note the compass heading.

2. Note the time of the minute hand and observe the position of the sweep second hand on the clock.

3. When the sweep second hand indicates the nearest half-minute, initiate a standard rate left turn, holding the turn coordinator symbolic airplane wing opposite the lower left index mark for 60 seconds. Then roll back to level flight by leveling the miniature airplane.

4. Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading.

5. If necessary, adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately.

6.

EMERGENCY DESCENT THROUGH CLOUDS

COPY

UNCONTROLLED

 turn, a

If possible, obtain radio clearance for an emergency descent through clouds. To guard against a spiral dive, choose an easterly or westerly heading to minimize compass card swings due to changing bank angles. In addition, keep hands off the control wheel and steer a straight course with rudder control by monitoring the turn coordinator.

Occasionally check the compass heading and make minor corrections to hold an approximate course.

F.A.A. Approved

3-15

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

Before descending into the clouds, set up a stabilized let-down condition as follows:

1. Reduce power to set up a 500 to 800 ft./min. rate of descent.

2. Adjust the elevator and rudder trim control wheels for a stabilized descent at 95 KIAS.

3. Keep hands off control wheel.

4. Monitor turn coordinator and make corrections by rudder alone.

5. Adjust rudder trim to relieve unbalanced rudder force, if present.

6. Check trend of compass card movement and make cautious corrections with rudder to stop turn.

7. Upon breaking out of clouds, resume normal cruising flight.

RECOVERY FROM A SPIRAL DIVE

If a spiral is encountered, proceed as follows:

1. Power control flight idle.

2. Stop the turn by using coordinated aileron and rudder control to align the symbolic airplane in the turn coordinator with the horizon reference line.

3. Cautiously apply control wheel back pressure to slowly reduce the indicated airspeed to 95 KIAS.

4. Adjust the elevator trim control to maintain a 95 KIAS glide.

5. Keep hands off the control wheel, using rudder control to hold a straight heading. Use rudder trim to relieve unbalanced rudder force, if present.

6. Upon breaking out of clouds, resume normal cruising flight.

Flight into icing conditions is prohibited. An inadvertent encounter with these conditions can best be handled using the checklist procedures. The best procedure, of course, is to turn back or change altitude to escape icing conditions.

COPY

UNCONTROLLED

ENGINE ALTERNATE AIR SYSTEM FAILURE

Malfunction of the engine alternate air system falls into the following categories: Alternate air light does not illuminate when in the alternate air mode and Alternate air light illuminates when in the normal air mode. The following paragraphs describe the recommended remedy for each situation.

F.A.A. Approved

3-16

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

ALTERNATE AIR LIGHT DOES NOT ILLUMINATE

Press to test the alternate air door light to check for a bad circuit.

Then visually check that the ram inlet doors are in the ALT position

(Raised). If the doors are not raised, cycle the alternate air control and check for reverse operation. If the ram inlet doors stay in the

NORM position (Down), leave the icing condition as soon as possible.

ALTERNATE AIR LIGHT ILLUMINATES IN FLIGHT

The alternate air door light can illuminate intermittently on takeoff or high power, low speed climbs when in the normal air mode.

However, if the alternate air door light illuminates under normal flight conditions, first check that the alternate air control is fully up in the normal position. Then check if the ram inlet doors are in the alternate air (raised) position. If the ram inlet doors are raised, cycle the alternate air control to check for reverse operation. If the ram inlet doors are not raised, land as soon as practicable and check for a blocked inlet or a faulty micro-switch on the alternate air door.

STATIC SOURCE BLOCKED

If erroneous readings of the static source instruments (airspeed, altimeter and rate-of-climb) are suspected, the alternate static source valve should be pulled on, thereby supplying static pressure to these instruments from the cabin.

NOTE

In an emergency on airplanes not equipped with an alternate static source, cabin pressure can be supplied to the static pressure instruments by breaking glass in the face of the rate-of-climb indicator.

COPY

UNCONTROLLED

SPINS

Intentional spins are prohibited in this airplane. Should an inadvertent spin occur, the following recovery procedure should be used:

1. POWER CONTROL FLIGHT IDLE POSITION.

2. PLACE AILERONS IN NEUTRAL POSITION.

F.A.A. Approved

3-17

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

3. SIMULTANEOUSLY APPLY AND

HOLD

FULL RUDDER

OPPOSITE TO THE DIRECTION OF ROTATION AND MOVE

THE CONTROL WHEEL

BRISKLY

FORWARD FAR ENOUGH

TO BREAK THE STALL. Full down elevator may be required at aft center of gravity loadings to assure optimum recoveries.

4. HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS.

Premature relaxation of the control inputs may extend the recovery.

5. AS ROTATION STOPS, NEUTRALIZE RUDDER, AND MAKE A

SMOOTH RECOVERY FROM THE RESULTING DIVE.

NOTE

If disorientation precludes a visual determination of the direction of rotation, the symbolic airplane in the turn coordinator or the needle of the turn and bank indicator may be referred to for this information.

ROUGH ENGINE OPERATION OR LOSS OF POWER

COMPRESSOR STALL

In the event of an engine compressor stall (noted by a bang or popping noise and/or engine surging), slowly reduce power and, if it continues, land as soon as practicable. If compressor stall is still noted at flight idle power, shut down the engine and proceed with the

Engine Out landing procedure. If a flameout occurs, attempt one restart to check for normal operation.

FUEL FILTER BYPASS

COPY becomes clogged. Land as soon as practicable. UNCONTROLLED

In the event of a propeller auto feather system failure caused by a faulty pressure switch or defective wiring (indicated by power surges, N

P

(Propeller) RPM oscillation and transmission pressure fluctuation) the

“AUTO -FTHR ANN. LGHT” circuit breaker should be pulled to disable the system. With this breaker pulled, the annunciator lights will be disabled also. A landing should be made at the next suitable airport for repairs.

F.A.A. Approved

3-18

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

LOW ENGINE OIL PRESSURE AND/OR LOW

TRANSMISSION OIL PRESSURE

The combined engine and transmission oil pressure warning light illuminates when the engine oil or the propeller reduction gearbox pressure is lower than normal. Should the light illuminate in flight, confirm the loss of oil pressure with the oil pressure gauges and land as soon as practicable.

OIL CHIP DETECTOR

The Oil Chip Detector light on the instrument panel illuminates to indicate possible internal deterioration of the engine or the propeller reduction gearbox. Land as soon as practicable if the light illuminates in flight.

ELECTRICAL POWER SUPPLY SYSTEM

MALFUNCTIONS

Malfunctions in the electrical power supply system can be detected by periodic monitoring of the ammeter and the generator warning light; however, the cause of these malfunctions is usually difficult to determine.

A broken generator wire is the most likely cause of failures, although other factors could cause the problem. A damaged or improperly adjusted voltage regulator can also cause malfunctions. Problems of this nature constitute an electrical emergency and should be dealt with immediately.

Electrical power malfunctions usually fall into two categories: excessive generator output and insufficient generator output. The paragraphs below describe the recommended remedy for each situation. COPY will be low enough to accept above normal charging during the initial UNCONTROLLED could be adversely affected by higher than normal voltage if a faulty regulator setting is causing the high output. To preclude these possibilities, an overvoltage sensor will automatically trip the generator system off at 32 volts, plus or minus 1 volt, and the GEN

OFF BUS warning light will illuminate. Assuming that the malfunction was only momentary, an attempt should be made to reactivate the system. To do this, turn the generator switch off, reset the generator trip/reset switch, and bring the generator switch back on again.

F.A.A. Approved

3-19

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU206G

SECTION 3

EMERGENCY PROCEDURES

If the problem no longer exists, normal generator charging will resume and the warning light will go off and the system should be checked at the completion of the flight.

If the light comes on again, a malfunction is confirmed. In this event, the flight should be terminated and/or the current drain on the battery minimized, because the battery can supply the electrical system for only a limited period of time. If the emergency occurs at night, power should be conserved for later use of the landing light and flaps during landing.

INSUFFICIENT GENERATOR OUTPUT

If the ammeter and GEN OFF BUS light indicate the generator is not supplying power to the system, it should be shut down. Circuit breakers should be checked and reset as required, the generator trip reset switch should be cycled and the generator restored. If normal generator operation does not occur, turn the system off. All nonessential equipment should be turned off and the flight terminated as soon as practicable.

CARGO DOOR EMERGENCY EXIT

If it is necessary to use the cargo doors as an emergency exit and the wing flaps are not extended, open the forward door and exit. If the wing flaps are extended, open the doors in accordance with the instructions shown on the placard, which is mounted on the forward cargo door.

FUEL LOW LIGHT ILLUMINATION (if installed)

The RIGHT/LEFT FUEL LOW light will illuminate when its respective wing tank fuel level reaches approximately 10 gallons. When this occurs, select the opposite tank on the fuel selector. If BOTH lights are illuminated,

When the fuel selector is in either the LEFT or RIGHT position, the FUEL

CONFIG light will be illuminated.

COPY select BOTH on the fuel selector and land as soon as practical. UNCONTROLLED

FUEL QUANTITY SYSTEM FAILURE

In the event of a fuel quantity system failure which would occur due to a fuel quantity transmitter gauge or electrical malfunction, low level warning will be lost. If the fuel selector is in either the LEFT or RIGHT position, change to BOTH and use fuel totalizer fuel remaining reading to determine when the flight should be terminated. If the totalizer was not reset prior to the flight or is unserviceable due to electrical failure, land as soon as practical.

F.A.A. Approved

3-20

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

SECTION 4

NORMAL PROCEDURES

TABLE OF CONTENTS PAGE

Introduction ........................................................................................ 4-3

Speeds for Normal Operation ............................................................ 4-3

CHECKLIST PROCEDURES

Preflight Inspection ............................................................................ 4-4

Cabin ............................................................................................. 4-4

Empennage ................................................................................... 4-4

Right Wing, Trailing Edge .............................................................. 4-4

Right Wing ..................................................................................... 4-5

Nose .............................................................................................. 4-5

Left Wing ....................................................................................... 4-6

Left Wing, Leading Edge ................................................................ 4-6

Left Wing, Trailing Edge................................................................. 4-6

Before Starting Engine ....................................................................... 4-6

Starting Engine .................................................................................. 4-7

Aborted Start Procedure .................................................................... 4-7

Before Takeoff ................................................................................... 4-8

Takeoff ............................................................................................. 4-9

Normal Takeoff .............................................................................. 4-9

Short Field Takeoff ........................................................................ 4-9 COPY

Cruise ................................................................................................ 4-10 UNCONTROLLED

Short Field Landing ........................................................................ 4-11

Balked Landing .............................................................................. 4-11

After Landing ..................................................................................... 4-11

Securing Airplane .............................................................................. 4-11

F.A.A. Approved

4-1

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

AMPLIFIED PROCEDURES

Preflight Inspection ............................................................................ 4-13

Before Starting The Engine ................................................................ 4-14

Starting Engine .................................................................................. 4-15

Taxiing ............................................................................................... 4-17

Before Takeoff ................................................................................... 4-18

Takeoff .............................................................................................. 4-19

Wing Flap Settings......................................................................... 4-20

Crosswind Takeoff ......................................................................... 4-20

Enroute Climb .................................................................................... 4-21

Cruise ................................................................................................ 4-21

Flight in Icing Conditions .................................................................... 4-22

Stalls ................................................................................................. 4-22

Landings ............................................................................................ 4-22

Short Field Landing ........................................................................ 4-23

Crosswind Landing ........................................................................ 4-23

Balked Landing .............................................................................. 4-23

Securing Airplane .............................................................................. 4-23

Cold Weather Operation .................................................................... 4-24

Hot Weather Operation ...................................................................... 4-26

Noise Abatement ............................................................................... 4-26

COPY

UNCONTROLLED

F.A.A. Approved

4-2

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

INTRODUCTION

Section 4 provides checklist and amplified procedures for the conduct of normal operation. Normal procedures associated with optional systems can be found in Section 9.

SPEEDS FOR NORMAL OPERATION

Unless otherwise noted, the following speeds are based on a maximum weight of 3600 pound and may be used for any lesser weight. However, to achieve the performance specified in Section 5 for takeoff distance and climb performance, the speed appropriate to the particular weight must be used.

Takeoff:

Normal Climb Out ........................................ 80-90 KIAS

Short Field Takeoff, Flaps 20 

Speed at 50 Feet (Best Angle) .................. 60 KIAS

Enroute Climb, Flaps Up:

Normal ……………………………………..

... 100-120 KIAS

Best Rate of Climb, Sea Level ........................ 87 KIAS

Best Rate of Climb, 20,000 Feet ..................... 71 KIAS

Best Angle of Climb, Sea Level ....................... 65 KIAS

Landing Approach:

Normal Approach, Flaps Up ............................ 75-85 KIAS

Normal Approach, Flaps 40  ........................... 65-75 KIAS

Short Field Approach, Flaps 40……………….

Balked Landing:

Maximum Power, Flaps 20 

COPY

..... 63 KIAS

UNCONTROLLED

2200 Lbs. ..................................................... ... 93 KIAS

Maximum Demonstrated Crosswind Velocity:

Takeoff or Landing ....................................... . 20 KNOTS

F.A.A. Approved

4-3

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

CHECKLIST PROCEDURES

PREFLIGHT INSPECTION

1.

CABIN

1. Control Wheel Lock – REMOVE.

2. Battery Switch – ON.

3. Fuel Quantity Indicators – CHECK QUANTITY

4. Wing Flaps – DOWN

5. Battery Switch -- OFF

6. Fuel Selector Valve – ON (BOTH if fuel low warning system installed)

2.

EMPENNAGE

1. Rudder Gust Lock – REMOVE

2. Tail Tie-Down – DISCONNECT

3. Control Surfaces – CHECK freedom of movement and security.

4. Check cargo doors securely latched and locked (right side only).

If cargo load will not permit access to the front cargo door inside handle, lock the door from the outside by means of the T-handle stored in the map compartment.

NOTE

COPY door is opened or removed, thus preventing the UNCONTROLLED the wing flap interrupt switch cover plate is installed so that the wing flaps can be lowered in flight.

3.

RIGHT WING Trailing Edge

1. Aileron – CHECK freedom of movement and security.

2. Wing Flaps – CHECK play and security.

F.A.A. Approved

4-4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

4. RIGHT WING

1. Wing Tie-Down – DISCONNECT

2. Fuel Tank Vent – CHECK for stoppage

3. Main Wheel Tire – CHECK for proper inflation

4. Fuel Tank Sump Quick-Drain Valve – DRAIN at least a cupful of fuel (using sampler cup) to check for water, sediment, and proper fuel grade before first flight of the day and after each refueling. If water is observed, take further samples until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points. Take repeated samples from all fuel drain points until all contamination has been removed.

5. Fuel Quantity – CHECK VISUALLY for desired level.

6. Fuel Filler Cap – SECURE and vent unobstructed.

7. Fuel Vent Sump Quick Drain Valves -- DRAIN all fuel from sump

(using sampler cup) before first flight of the day.

5. NOSE

1. Cowl – CHECK for security

2. Before first flight of the day and after each refueling, use sampler cup and drain small quantity of fuel from both header tanks and engine fuel filter to check for water and sediment. (The fuel selector valve must be “ON” while the engine fuel filter is being drained.) If water is observed, perform further draining at all fuel drain points until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points. Take repeated samples from all fuel drain points until all contamination has been removed.

3. Static Source Opening (both sides of fuselage) – CHECK for stoppage

4. Air Inlet – CHECK for any foreign objects

5. Oil Cooler Inlet – CLEAR quarts in the oil tank.

COPY

6. Engine Oil Level -- CHECK. Do not operate with less than 4 UNCONTROLLED disconnect tie down and rotate to check for freedom.

9. Landing and Taxi Lights – CHECK for condition and clean lenses

10. Nose Wheel Strut and Tire – CHECK for proper inflation

11. Optional Engine Oil Screen, Impending Filter bypass Indicator –

CHECK IN

12. Alternate Air System – CHECK pneumatic lines for condition and security.

13. Oil Reservoir, Impending Filter Bypass Indicator – CHECK IN

14. External Engine Oil Filter Impending Filter Bypass Indicator –

CHECK IN

F.A.A. Approved

4-5

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

6. LEFT WING

1. Main Wheel Tire – CHECK for proper inflation.

2. Fuel Tank Sump Quick Drain Valves -- DRAIN at least a cupful of fuel (using sampler cup) to check for water, sediment and proper fuel grade before each flight of the day and after each refueling. If water is observed, take further samples until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points. Take repeated samples from all fuel drain points until all contamination has been removed.

3. Fuel Quantity – CHECK VISUALLY for desired level.

4. Fuel Filler Cap – SECURE and vent unobstructed.

5. Fuel Vent Sump Quick-Drain Valve – Drain all fuel from sump

(using sampler cup) before first flight of the day.

7. LEFT WING Leading Edge

1. Pitot Tube Cover – REMOVE and check opening for stoppage.

2. Stall Warning Vane – CHECK for freedom of movement while master switch is momentarily turned on (horn should sound when vane is pushed upward).

3. Wing Tie-Down – DISCONNECT

4. Fuel Tank Vent – CHECK for blockage.

8. LEFT WING Trailing Edge

1. Aileron – CHECK freedom of movement and security.

2. Flap – CHECK play and security.

1. Preflight Inspection – COMPLETE

3. Cabin Doors and Windows – CLOSE and LOCK

4. Seats, Belts, Shoulder Harnesses – ADJUST and LOCK.

5. Brakes – TEST and SET

COPY

2. Passenger briefing - COMPLETE UNCONTROLLED

7. Alternate Air Control – NORM

8. Fuel Cutoff Control – CUTOFF (OUT)

9. Propeller Control – IN

10. Power Control – GROUND IDLE

11. All Switches and Circuit Breakers – OFF and SET

12. Avionics – OFF

13. Generator Switch – APU (OFF) POSITION

14. APU – IF AVAILABLE

15. Battery Switch – ON

16. Annunciator Panel and Warning Lights – AUTO FEATHER, OIL

PRESS LOW and GEN OFF BUS lights ON, PRESS-TO-TEST remaining lights.

17. Fuel Totalizer – CHECK and SET

F.A.A. Approved

4-6

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

STARTING ENGINE

1. Propeller – CLEAR

2. TOT 150  C or Lower

NOTE

TOT can readily be reduced to 150°C by motoring the starter.

3. Start Motor Switch – MOTOR and HOLD to 12 – 15% N

1

based on temperatures listed below.

NOTE

Starter Duty Cycle is located in Amplified Procedures.

4. Start Motor Switch – START and HOLD to 58% N

1

– Positive oil psi indication.

5. Fuel Cutoff Control – RUN (IN) AT:

N

1

RPM Temp  C (  F)

15% .................................... Above 7  (45  )

13% ............................ -18 to +7  (0 to 44  )

12% ................................... Below -18  (0  )

6. TOT and N

1

– MONITOR TOT (810  to 927  C), 10 seconds maximum and N

1

for normal acceleration.

7. Propeller (N

P

) – CHECK rotating by 25% N

1

.

8. Transmission Oil Pressure – POSITIVE indication at completion of the start.

9. Start Switch – RELEASE at 58% N

10. APU – DISCONNECT if used.

11. Generator Switch – ON.

12. N

1

– CHECK 59% MINIMUM. If not, turn off generator and add power to 70% N

13. Lights – As required

14. Avionics – As required

15. Wing Flaps – UP.

1

(within 25 to 60 seconds). COPY

1

, then turn on generator. UNCONTROLLED

ABORTED START PROCEDURE

1. Fuel Cutoff Control – CUTOFF (OUT)

2. Start Motor Switch – MOTOR 10 to 30 seconds

3. TOT – MONITOR

4. Perform corrective maintenance action if required.

F.A.A. Approved

4-7

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

BEFORE TAKEOFF

1. Parking Brake – SET

2. Cabin Doors and Windows – CLOSE and LOCK

3. Seat Belts and Shoulder Harnesses – SECURE

4. Engine Instruments -- CHECK

5. Flight Controls – FREE and CORRECT

6. Elevator and Rudder Trim --- TAKEOFF setting

7. Propeller Control – IN

CAUTION

AVOID CONTINUOUS OPERATION (>60 SECONDS) BETWEEN

1358 RPM AND 1630 RPM PROPELLER SPEED AT TORQUE

SETTING GREATER THAN 20 PSI

8. Auto Feather

A. Ensure the Propeller Control is at the FORWARD (Increase RPM) position.

B. Position the Power Control at GROUND IDLE.

C. Activate the propeller overspeed governor test switch.

D. Gradually increase the engine power by advancing the Power

Control. Proper functioning of the propeller overspeed governor will be indicated by the propeller speed being limited to approximately 1450 Np RPM as the power is increased.

E. Reduce the Power Control to GROUND IDLE. Propeller speed will reduce along with this power reduction.

F. Release the test switch.

9. Suction Gauge – CHECK (4.6 to 5.4 in Hg.)

10. Alternate Air – Cycle check for light and ram inlet doors.

11. Anti-Ice (if installed) – PULL ON. Check for rise in TOT, then

OFF.

12. Flight Instruments and Radios --- SET

13. Auto Pilot (if installed) – OFF as required.

15. Ice Protection – AS REQUIRED

16. Annunciator Panel – CLEAR except alternate air, if in use.

17. Power Control Function – ADJUST

18. Wing Flaps – 0º TO 20º

COPY

14. Flashing Beacon, Navigation Lights and/or Strobe Lights – On UNCONTROLLED

19. Fuel Selector – ON (Both if fuel low warning system installed)

20. Fuel Quantity – CHECK, with 1/8 fuel quantity or less, or if the installed LOW FUEL lights are on, takeoff is prohibited.

21. Fuel Temperature – CHECK, observe fuel limits

22. Parking Brake – RELEASE

F.A.A. Approved

4-8

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

TAKEOFF

NORMAL TAKEOFF

1. Wing Flaps – 0  to 20 

2. Power Control – FLIGHT IDLE and stabilize at 1810 N

P

RPM, then TAKEOFF POWER (101.4 PSI torque or 810  C TOT limits).

3. Elevator Control – LIFT NOSE at 50 KIAS

4. Climb Speed – 90 – 100 KIAS

5. Wing Flaps – RETRACT after obstacles are cleared.

SHORT FIELD TAKEOFF

1. Wing Flaps – 20 

2. Brakes – APPLY

3. Power Control – FLIGHT IDLE STABILIZED AT 1810 N

P then TAKEOFF POWER,

4. Brakes – RELEASE

RPM,

5. Elevator Control – SLIGHTLY TAIL-LOW ATTITUDE

6. Climb Speed – 60 KIAS until all obstacles are cleared.

7. Wing Flaps – RETRACT after obstacles are cleared and 80 – 90

KIAS is reached.

NOTE

Do not reduce power until wing flaps have been retracted.

WARNING COPY

NORMAL CLIMB

ARE ON, TAKEOFF IS PROHIBITED. UNCONTROLLED

1. Airspeed – 100 – 120 KIAS

2. Ice Protection – AS REQUIRED

3. Power Control – 78 PSI Torque or 738  C TOT and 1810 N p

RPM

MAXIMUM PERFORMANCE CLIMB (V y

)

1. Airspeed – 97 KIAS at sea level to 74 KIAS at 20,000 feet with 5 minute power and 87 KIAS to 71 KIAS with max. continuous power.

2. Ice Protection – AS REQUIRED

3. Power Control – 101.4 PSI Torque or 810 and 1810 N p

RPM

 C TOT and 1810 N

P

RPM for 5 Minutes Maximum, then 78 PSI Torque or 738  C TOT

4-9

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

WARNING

WITH 1/8 FUEL TANK QUANTITY OR LESS, OR IF

THE INSTALLED FUEL LOW LIGHTS ARE ON,

CLIMBS AT SPEEDS BELOW V y

ARE PROHIBITED.

CRUISE

1. Ice Protection – AS REQUIRED

2. Propeller Speed – SET 1630 – 1810 RPM (Propeller Control)

3. Power Control – SET (Observe TOT and/or Torque Limits)

4. Elevator and Rudder Trim – ADJUST

DESCENT

1. Ice Protection – AS REQUIRED

2. Power Control – SET FLIGHT IDLE

3. Seat Belts and Shoulder Harness – SECURE

BEFORE LANDING

1. Ice Protection – AS REQUIRED

CAUTION

SIGNIFICANT POWER LOSS WILL OCCUR WHILE

OPERATING IN THE ALTERNATE AIR MODE.

FLIGHT ON APPROACH TO LANDING.

2. Propeller Control – IN

3.

4.

5.

COPY

6. Wing Flaps – Down 0  to 10  (below 137 KIAS), 10  to 40 

(below 96 KIAS).

7. Power Control – FLIGHT IDLE (14 PSI torque minimum)

8. Airspeed – 75 – 85 KIAS (Flaps Up), 65 – 75 KIAS (Flaps Down)

9. Elevator Trim – ADJUST for landing

LANDING

NORMAL LANDING

1. Touchdown – MAIN WHEELS FIRST

2. Power Control – GROUND IDLE

3. Landing Roll – LOWER NOSE WHEEL

4. Braking – MINIMUM REQUIRED

4-10

F.A.A. Approved November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

SHORT FIELD LANDING

1. Airspeed – 75 – 85 KIAS (flaps UP)

2. Wing Flaps -- 40  (below 96 KIAS)

3. Airspeed – MAINTAIN 63 KIAS

4. Elevator Trim -- ADJUST

5. Power Control – REDUCE TO FLIGHT IDLE (14 PSI torque minimum) as obstacle is cleared.

6. Touchdown – MAIN WHEELS FIRST

7. Power Control – GROUND IDLE

8. Brakes – APPLY HEAVILY

9. Wing Flaps – RETRACT for maximum brake effectiveness.

BALKED LANDING

1. Power Control – ADVANCE for TAKEOFF POWER (101.4 PSI torque or 810  C TOT limits).

2. Airspeed – 60 KIAS

3. Wing Flaps – RETRACT to 20 

4. Airspeed – 70 – 80 KIAS after all obstacles are cleared.

5. Wing Flaps – UP as soon as all obstacles are cleared and a safe altitude and airspeed are obtained.

6. Trim – ADJUST for climb.

AFTER LANDING

1. Pitot Heat – OFF

2. Wing Flaps – RETRACT

3. Lights – AS REQUIRED

SECURING AIRPLANE

1. Parking Brake – SET

2. Avionics and Electrical Equipment – OFF

3.

4.

5.

Power Control – N

Propeller Control – FEATHER above 700 RPM

6. TOT – MONITOR

1

COPY

UNCONTROLLED

7. Switches – OFF

8. Control Lock – INSTALL

9. Compressor – WATER RINSE. Accomplish on a daily basis in salt water areas. (To be conducted by qualified person. Refer to Rolls-Royce 250-C20 Series Operation and Maintenance

Manual.)

10. Propeller – SECURE

11. Aircraft – SECURE

12. Parking Brake – RELEASE

F.A.A. Approved

4-11

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

This page left blank intentionally.

SECTION 4

NORMAL PROCEDURES

COPY

UNCONTROLLED

F.A.A. Approved

4-12

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

AMPLIFIED PROCEDURES

PREFLIGHT INSPECTION

The preflight inspection, described in the abbreviated procedures part of this section, is recommended before flight. The preflight should include a determination of the airplane’s o perational status, a check that the necessary papers are on board and in order, and a computation of weight and C.G. limits, takeoff distance and in-flight performance. Baggage should be weighed, stowed, and tied down. A weather briefing for flight should be obtained.

Particular attention should be given to the engine air induction system to ensure that it is free of snow or other debris that could flame out or damage the engine.

The propeller should be rotated by hand to ensure the power turbine is free.

Check the Turbine Pac oil tank oil level. Low oil level indication can be caused by insufficient oil quantity and/or a defective check valve. A defective check valve can allow oil in the storage tank to flow back into the system and gearboxes, thus causing an erroneous quantity indication.

Should this occur, start the engine (observe engine oil pressure requirements) and run at ground idle for 5 minutes, then shut down the engine and recheck the oil level. If the oil level is back up to normal, take the appropriate maintenance actions. If the quantity of the oil remains low following the check, add oil to the low operation limit of 4 U.S. quarts.

It is possible for the impending oil bypass indicators to extend during a start when the oil is cold, and give an erroneous indication of a dirty oil filter. If an impending bypass filter indicator is extended, run the engine until the oil is at operating temperature, and push the indicator button in. If further action is necessary.

COPY the button remains in throughout the engine’s normal operational range, no UNCONTROLLED are properly matched to prevent reverse operation. Also check for condition and security.

If any water is detected in the fuel system, the fuel tank sump quick-drain valves, fuel reservoir quick-drain valves, and fuel strainer drain should all be thoroughly drained again. Then, the wings should be gently rocked and the tail lowered to the ground to move any further contaminants to the sampling points. Repeated samples should be taken from all drain points until all contamination has been removed. If, after repeated sampling, evidence of contamination still exists, the fuel tanks should be completely drained and the fuel system cleaned.

F.A.A. Approved

4-13

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

To prevent loss of fuel in flight and to ensure equal flow, make sure the fuel tank filler caps are tightly sealed. The fuel tank vents on the lower surface of the tanks should also be inspected for obstructions.

BEFORE STARTING THE ENGINE

After the preflight interior and exterior checks have been completed and the airplane is determined ready for flight, the cabin doors and window should be secured. Passengers should be briefed on the use of seat belts and shoulder harnesses, the emergency exits, supplemental oxygen (if available), ventilation controls, seat adjustments, etc.. After all seats are adjusted and secured in position and seat belts and shoulder harnesses are properly fastened, the pilot may prepare to start the engine.

The parking brake should be set ON by pulling out on the brake handle and turning it 90  down. Check that the fuel selector is ON (BOTH if the fuel low warning system installed) and the fuel cutoff control is in the

CUTOFF position (OUT). Place the propeller control fully FORWARD and the power control at GROUND IDLE.

Prior to starting the engine, check that all electrical switches and avionics are OFF, and that all circuit breakers are IN.

CAUTION

PRIOR TO TURNING THE BATTERY SWITCH ON OR

APPLYING AN EXTERNAL POWER SOURCE, THE

-18  C (0 

AVIONICS POWER SWITCH, LABELED AVIONICS

POWER, SHOULD BE TURNED OFF TO PREVENT ANY

THE AVIONICS EQUIPMENT.

COPY

The generator switch should be in the APU (OFF) position to reduce the load on the engine’s N

UNCONTROLLED illuminate. This indicates that the auto feather pressure sensor is operating. In addition, the OIL PRESS LOW, and the GEN OFF BUS lights will be illuminated. The remaining lights should be checked by the

PRESS-TO-TEST feature.

NOTE

At the lower voltages prior to engine start, the

PRESS-TO-TEST feature of the annunciator lights will only operate with the light intensity set to bright.

F.A.A. Approved

4-14

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

The fuel totalizer computations are based on Jet A fuel with a density of

6.71 pounds/gallons at 80  F. Multiply your usable fuel by fuel density to obtain the fuel quantity in pounds, and reset the totalizer prior to starting the engine. (Detailed information on the totalizer is in the Airplane &

Systems Descriptions, Section 7.)

STARTING ENGINE

Prior to starting the engine, make sure the propeller area is clear.

Proper fuel and ignition management are the determining factors in obtaining a normal start of your Turbine Pac equipped Cessna.

NOTE

For the ultimate safety of all personnel who operate and depend upon the engine in the future, it is the responsibility of the pilot and maintenance personnel to record and to take the recommended corrective actions after overtemperature occurs.

Residual TOT should be no more than 150  C when lightoff is attempted.

The TOT can be readily reduced to or below 150  C by motoring the engine with the start motor switch. After motoring to cool the engine, proceed with the normal starting procedure.

CAUTION

COPY

1

. desired N

1

RESULT IN A STAGNATED OR HOT START. UNCONTROLLED

N

1

RPM Temp  C (  F)

15% ........................................................... Above 7

13% ..................................................-18  to +7 



12% ......................................................... Below –18

(45

(0 to 44

 (0 





)

)

)

F.A.A. Approved

4-15

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

CAUTION

DURING A START, THE FUEL CUTOFF CONTROL

MUST NEVER BE ADVANCED FROM THE

CUTOFF POSITION UNTIL AFTER THE STARTER

AND IGNITION EXCITER HAVE BEEN

ENERGIZED AND THE DESIRED CRANKING

SPEED HAS BEEN ATTAINED. TO DO SO MIGHT

RESULT IN AN EXPLOSIVE LIGHTOFF OR AN

OVERTEMPERATURE START. A START

SHOULD NEVER BE ATTEMPTED AT N

1

SPEEDS

LESS THAN 12%.

After advancing the fuel control cutoff, a delay of lightoff can occur under certain conditions. If this delay exceeds 3 seconds, return the fuel cutoff control to the CUTOFF (OUT) position to abort the start, but motor the engine for 10 seconds to clear the combustion chamber of residual fuel.

For subsequent starting attempts, repeat the complete starting sequence.

Monitor the TOT throughout the start. The TOT limits during the start are as follows:

TEMPERATURE RANGE TIME

Up to 810

810

927





– 927

C

Over 927 

 C



C

C

No Limit

10 Seconds

1 Second

Not Allowed consistently exceeds 860 

COPY and Maintenance Manual when start temperature UNCONTROLLED

It is the responsibility of the pilot and maintenance personnel to record the extent of and to take the recommended corrective actions after an overtemperature occurs.

CAUTION

IF THE PROPELLER IS NOT ROTATING BY 25%

N

1

SPEED, ABORT THE START. A SECOND OR

THIRD START ATTEMPT MAY BE MADE IF THE

PROPELLER CAN BE ROTATED BY HAND.

F.A.A. Approved

4-16

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

If a stagnated start is experienced, or if it appears that the TOT will exceed the starting limits, abort the start by putting the fuel cutoff control to the

CUTOFF (OUT) position and motor the engine for ten seconds to clear the combustion chamber of residual fuel. For subsequent starting attempts, repeat the complete starting sequence. A normal start should be completed 25 to 60 seconds after starter engagement; however, if N

N p longer than one minute.

1

and

are accelerating and the TOT is within limits, the start may be continued

If several starter cycles are necessary, the following starter/generator cooling periods are to be observed:

1

2 st nd

3 rd

cycle: 30 seconds ON – 1 minute OFF

cycle 30 seconds ON – 1 minute OFF

cycle: 30 seconds ON – 30 minutes OFF

A positive indication of engine oil pressure must be obtained by completion of the start (58% N

1 check the oil supply.

). If it is not, shut down the engine and

A positive indication of transmission oil pressure must be obtained by completion of the start.

NOTE

The OIL PRESS LOW warning light will be illuminated

Release the start switch when 58% N

1

speed is reached.

If an APU was used for the start, disconnect it prior to turning on the generator.

Monitor N

1 and the transmission oil pressure will remain at approximately 10 PSI until the propeller comes out of the feather position, then the pressure will rapidly increase to approximately 50 PSI and the warning light will go off.

when switching on the generator. If N off the generator, accelerate N

1

COPY

UNCONTROLLED

If the engine has been shut down for more than 15 minutes, stabilize at ground idle speed for one minute before increasing power.

TAXIING

Taxiing over loose gravel or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips. If desired, a more rapid response for taxi power can be obtained in the ground idle range by reducing the propeller governing speed. Set the propeller RPM to 1500 with the power control, then adjust the propeller control with the vernier feature back to 1450 RPM. Normal taxiing can now be easily accomplished with the power control. The propeller control must be returned to the FULL IN position prior to the auto feather check or takeoff.

4-17

F.A.A. Approved November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

Alternate engine air is required when the aircraft is in visible moisture and an OAT of 5  C (41  F) and below or while operating in falling or blowing snow.

Refer to Figure 4-2 in the Cessna Pilot’s Operating Handbook for additional taxiing instructions.

BEFORE TAKEOFF

Except for cold weather operation, discussed later in this section, stabilize at ground idle for one minute before increasing power if the engine has been shut down for more than 15 minutes.

Prior to engine run-up, set parking brake ON. Check that all doors and windows are closed and that the passenger’s seat belts and shoulder harnesses are secure.

Check fuel quantity and temperature. Refer to limitations section for restrictions. Check that the engine instruments are normal and the flight controls are free and correct. Set the propeller control fully forward. Trim should be set to the TAKEOFF position.

Set the power control to GROUND IDLE.

CAUTION

AVOID CONTINUOUS OPERATION (>60 SECONDS)

BETWEEN 1358 RPM AND 1630 RPM PROPELLER switch

SPEED AT TORQUE SETTING GREATER THAN 20

PSI little or no change in N p

COPY push the power control and observe an increase in torque pressure with UNCONTROLLED

The operation of the alternate engine air system should be checked daily especially after the cowling has been removed.

NOTE

A drop in torque and a rise in TOT is normal with the actuation of the engine ice protection system.

Reduce power control back to GROUND.

F.A.A. Approved

4-18

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

Check and set flight instruments and radios as desired. Be sure that the autopilot is OFF for takeoff. Check that the normal static source is selected. Check that necessary lights and electrical systems are ON, including ice protection systems if weather conditions warrant.

NOTE

The engine alternate air must be activated for flight or ground operation in visible moisture at an OAT of

5  C (41  F) and below or while operating in falling or blowing snow.

The annunciator panels should be clear unless the engine alternate air is in use. Wing flaps should be checked and set from 0  to 20  .

TAKEOFF

With the propeller control set fully FORWARD, advance the power control to FLIGHT IDLE and allow the engine to stabilize at 1810 N p advancing the power control to TAKEOFF.

RPM prior to

Monitor the engine instruments throughout the takeoff. The TOT, ENGINE

TORQUE and SPEED limits for takeoff are as follows:

TEMPERATURE RANGE TIME

Up to 738

738

810

TORQUE LIMIT

Up to 78 PSI

COPY

UNCONTROLLED

78 to 101.4 PSI

101.4 to 109 PSI

Over 109 PSI

N

1





C – 810

C – 843 is not recommended.)

Over 843

LIMIT



 C

C

Up to 105%

Over 106%





C

C (Intentional Use of temperatures in excess of 810

105% to 106%

 C

No Limit

5 Minutes

6 Seconds

Not Allowed

TIME LIMIT

No Limit

5 Minutes

10 Seconds

Not Allowed

TIME LIMIT

No Limit

15 Seconds

Not Allowed

F.A.A. Approved

4-19

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

N p

LIMIT

Up to 1900 RPM

1900 to 1990 RPM

Over 1990 RPM

TIME LIMIT

No Limit

15 Seconds

Not Allowed

Maintain torque and TOT within limits. As the airplane accelerates, an increase in torque and TOT at a fixed power control position is normal.

REDUCE power settings as required. ROTATE the nose wheel at 50

KIAS. When airborne, select a climb speed and retract the flaps after the obstacles have been cleared.

NOTE

Do not reduce power until wing flaps have been retracted.

WING FLAP SETTINGS

Using 20  wing flaps reduces the ground run and total distance over the obstacle by approximately 10%. Soft field takeoffs are performed with 20  flaps by lifting the nose wheel off the ground as soon as practical and leaving the ground in a slightly tail low attitude. However, the airplane should be leveled off immediately to accelerate to a safe climb speed.

If 20  wing flaps are used for takeoff, they should be left down until all obstacles are cleared. To clear an obstacle with 20  flaps, a 60 KIAS climb speed should be used. If no obstructions are ahead, a best rate-of-climb speed of 80 KIAS would be most efficient. Flap deflections greater than 20  are not approved for takeoff.

At sea level with 20  flap setting and 5 minute power, V approximately 60 KIAS, and V

CROSSWIND TAKEOFF

COPY

UNCONTROLLED

Takeoffs into strong crosswinds normally are performed with the minimum flap setting necessary for the field length, to minimize the drift angle immediately after takeoff. With the ailerons partially deflected into the wind, the airplane is accelerated to a speed slightly higher than normal, and then pulled off abruptly to prevent possible settling back to the runway while drifting. When clear of the ground, make a coordinated turn into the wind to correct for drift.

F.A.A. Approved

4-20

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

ENROUTE CLIMB

Normally, maximum continuous power and a climb speed of 100 – 120

KIAS is maintained to cruise altitude. At lower altitudes, the torque limit of

78 PSI will be set until the TOT limit of 738  C dictates the power available.

If it is necessary to climb rapidly to altitude, the best rate-of-climb speed should be used with the power limits shown in the table below. This speed is 97 KIAS at sea level with 5 minute power, decreasing to 74 KIAS at

20,000 feet and 87 KIAS to 71 KIAS with maximum continuous power.

If an obstruction dictates the use of a steep climb angle, climb with flaps retracted and the power limits shown below at 65 KIAS.

TEMPERATURE RANGE

Up to 738  C

738  C – 810  C

Over 810  C

TIME

No Limit

5 Minutes

Not Allowed

TORQUE LIMIT

Up to 78 PSI

78 – 101.4 PSI

Over 101.4 PSI

TIME

No Limit

5 Minutes

Not Allowed

CRUISE

COPY

PSI

CAUTION

AVOID CONTINUOUS OPERATION (>60 SECONDS) UNCONTROLLED

Check the reading of the engine instruments and monitor fuel gauges during flight. The power control may be secured in its position by use of the friction knob on the control rod.

During flight an imbalance can occur between the wing tanks. If the fuel low warning system is installed, the pilot may select to use fuel from either tank to correct for an imbalance, but the pilot must return the fuel selector to BOTH once the imbalance is corrected. If a FUEL LOW light illuminates during cruise, switch the fuel selector to the tank for which the FUEL LOW light is NOT illuminated. When both lights are on, select BOTH and land as soon as practical. When the fuel selector is in either the LEFT or

RIGHT position the FUEL CONFIG light will be illuminated.

F.A.A. Approved

4-21

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

FLIGHT IN ICING CONDITIONS

Flight into icing conditions is prohibited. An inadvertent encounter with these conditions can best be handled using the checklist procedures in

Section 3. The best procedure, of course, is to turn back or change altitude to escape icing conditions.

NOTE

Flight or ground operation in visible moisture at an

OAT of 5  C (41  F) and below or while operating in both failing or blowing snow, the engine alternate air must be activated.

Deactivation of the systems shall not be made until the above mentioned conditions have been left and all accumulated airframe ice has dissipated.

STALLS

The stall characteristics are conventional, and aural warning is provided by a stall warning horn, which sounds between 5 and 10 knots above the stall in all configurations.

Power off stall speeds at maximum weight for both forward and aft C.G. are presented in Section 5.

LANDINGS

COPY

Landing should be made on the main wheels first to reduce the landing speed and subsequent need for braking in the landing roll. The power UNCONTROLLED

CAUTION

WHEN LANDING ON A HOT DAY, HIGH

ALTITUDE AIRPORT OR WITH THE ENGINE

ALTERNATE AIR IN THE ALT POSITION,

THE BRAKING EFFECT OF THE

PROPELLER AT FLIGHT IDLE POWER IS

MORE PRONOUNCED, AND ADDITIONAL

CARE SHOULD BE USED TO ASSURE A

MAIN GEAR FIRST LANDING. MAINTAIN A

MINIMUM TORQUE SETTING OF 14 PSI

THROUGHOUT THE LANDING FLARE.

F.A.A. Approved

4-22

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

SHORT FIELD LANDING

For short field landings, make a power approach at 63 KIAS with full flaps. After all approach obstacles are cleared, progressively reduce power. Maintain 63 KIAS approach speed by lowering the nose of the airplane. Touchdown should be made at

FLIGHT IDLE (14 PSI torque minimum), and on the main wheels first. Immediately after touchdown, reduce power to GROUND

IDLE, lower the nose gear and apply heavy braking as required.

For maximum brake effectiveness, retract the flaps, hold full nose up elevator and apply maximum possible brake pressure without sliding the tires.

CROSSWIND LANDING

When landing in a strong crosswind, use the minimum flap setting required for the field length. Although the crab or combination method of drift correction may be used, the wing low method gives the best control. After touchdown, hold a straight course with the steerable nose wheel and occasional braking if necessary.

BALKED LANDING

In a balked landing (go-around) climb, apply power as required and maintain torque and TOT within allowable limits. The flap setting should be reduced to 20  . After all obstacles are cleared and a safe altitude and airspeed are obtained, the wing flaps should be retracted.

SECURING AIRPLANE

COPY

UNCONTROLLED speeds of 59% to 65%, move the Fuel Cutoff Control to the CUTOFF position. The propeller can also be feathered above 700 N p

RPM at shutdown to minimize the spool down time of the propeller.

WARNING

1

IDLE DWELL TIME PRIOR TO SHUTDOWN IS

IMPORTANT TO PREVENT HARMFUL

ACCUMULATION OF CARBON IN THE ENGINE,

WHICH CAN RESULT IN COMPLETE ENGINE

STOPPAGE.

F.A.A. Approved

4-23

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

CAUTION

AN AFTERFIRE (RECOGNIZED BY A RAPID

INCREASE IN TOT) CAN OCCUR DURING

SHUTDOWN IF FUEL CUTOFF IS NOT

COMPLETE. IF A SHUTDOWN FIRE OCCURS,

IMMEDIATELY ENGAGE THE STARTER AND

MOTOR THE ENGINE WITHOUT IGNITION TO

EXTINGUISH THE FIRE. THE TEMPERATURE

LIMITATIONS AND MAINTENANCE ACTION

MUST BE OBSERVED.

Engines subjected to salt water or other chemically laden atmosphere

(including pesticides) shall undergo water rinsing after shutdown following the last flight of the day. Procedures for the rinse, cleaning and preservation of the compressor are explained in the Rolls-Royce 250-C20

Series Operation and Maintenance Manual.

When the airplane is not stored in a hangar, the air inlet should be covered to protect the induction system from birds and debris. Install the control locks, propeller bungee and exhaust covers.

COLD WEATHER OPERATION

Use appropriate covers on the aircraft when it is parked. Make certain the compressor rotor is not frozen if the aircraft is in a freezing atmosphere.

To assure consistent starts below 4 described in the limitations, Section 2, are recommended. Additionally, for flight at ambient temperatures of 4 an anti-icing additive.





COPY

UNCONTROLLED

If the aircraft has been cold soaked at a temperature below –18  C (0  F) and a battery start must be made, preheat the engine fuel control and battery. When a cold weather start is anticipated, the battery should be removed and stored at normal room temperature.

CAUTION

DO NOT USE AN OPEN FLAME HEATER TO

PREHEAT THE BATTERY OR THE ENGINE FUEL

CONTROL.

F.A.A. Approved

4-24

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

NOTE

Variations in jet fuels can affect engine lightoff in cold ambient conditions. The engine may experience a short delay before lightoff after the Fuel Cutoff

Control is moved to the RUN position. This delay should be less than three seconds regardless of the type of fuel used. If the lightoff delay exceeds three seconds, return the Fuel Cutoff Control to CUTOFF and continue to motor the engine with the starter for thirty seconds to purge unburned fuel from the engine.

With a cold soaked engine, N

1

may accelerate slowly through the 25-30% speed range. If the start is not completed within the time limits, abort the start and allow one minute for the heat to soak back into the engine and battery for the restart.

If N

P

is not rotating by 25% N

1

speed, abort the start. If the propeller can be turned by hand, a second or third start attempt may be made.

If the engine has been shut down for more than 15 minutes, stabilize at

GROUND IDLE for one minute before increasing power.

NOTE

After a cold weather battery start, allow the engine to run at GROUND IDLE for two minutes before actuating the generator switch. This will prevent N

1 speed reduction resulting from high generator loading.

COPY

AUTO ACCELERATION MAY OCCUR FROM

UNCONTROLLED

RUN AT GROUND IDLE RPM. THIS WARM UP IS

RECOMMENDED WHEN THE AIRPLANE HAS

BEEN ALLOWED TO COLD SOAK (REMAIN OUT

OF A HANGAR OVERNIGHT) AT LOW

TEMPERATURES (+10



F OR BELOW) AND HIGH

RELATIVE HUMIDITY (45% OR GREATER).

IF AUTO ACCELERATION OCCURS, RETURN TO

GROUND IDLE AND SHUT DOWN THE ENGINE.

ALLOW AT LEAST ONE MINUTE FOR THE HEAT

TO SOAK BACK INTO THE ENGINE FOR THE

RESTART.

F.A.A. Approved

4-25

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 4

NORMAL PROCEDURES

HOT WEATHER OPERATION

On a hot day, takeoff power will be limited by TOT. There is a lag in the

TOT gauge; therefore, it should be monitored during the takeoff run.

NOISE ABATEMENT

Increased emphasis on improving the quality of our environment requires renewed effort on the part of all pilots to minimize the effect of airplane noise on the public.

We, as pilots, can demonstrate our concern for environmental improvements, by application of the following suggested procedures, and thereby tend to build public support for aviation.

1. Pilots operating aircraft under VFR over outdoor assemblies of persons, recreational and park areas, and other noise sensitive areas should make every effort to fly not less than 2000 feet above the surface, weather permitting, even though flight at a lower level may be consistent with the provisions of government regulations.

2. During departure from or approach to an airport, climb after takeoff and descent for landing should be made so as to avoid prolonged flight at low altitude near noise sensitive areas.

NOTE

The above recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions, or where, in the pilot’s judgment, an altitude of less than 2000 feet is necessary for him to adequately exercise his duty to see and avoid other aircraft.

IS 65.4 DB(A).

COPY

UNCONTROLLED

No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of any airport.

F.A.A. Approved

4-26

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

SECTION 5

PERFORMANCE

TABLE OF CONTENTS

..................................................

PAGE

Introduction ................................................................................. 5-3

Figure 5-1: Airspeed Calibration ................................................ 5-4

Figure 5-2: Temperature Conversion Chart ............................... 5-5

Figure 5-3: Stall Speeds ............................................................ 5-6

Figure 5-4: Minimum Engine Torque For Takeoff ...................... 5-8

Figure 5-5: Takeoff Distance, 3600 Lbs. ................................... 5-9

Figure 5-6: Takeoff Distance, 3300 Lbs. ............................. .... 5-10

Figure 5-7: Takeoff Distance, 3000 Lbs. .................................. 5-11

Figure 5-8: Maximum Rate of Climb, Maximum Continuous

Power .................................................................. 5-12

Figure 5-9: Maximum Rate of Climb, Takeoff Power .............. 5-13

Figure 5-10: Time, Fuel and Distance to Climb, Maximum

Rate of Climb, Maximum Continuous Power,

Temperature – Standard ................................... 5-14

Time, Fuel and Distance to Climb, Maximum

Rate of Climb, Maximum Continuous Power,

Temperature – Standard +20

Temperature – Standard -20 

 C ............................. 5-15

Time, Fuel and Distance to Climb, Maximum

Rate of Climb, Maximum Continuous Power,

C ............................. 5-16 COPY

Cruise Performance – 12,000 and 14,000 Feet ........ 5-20 UNCONTROLLED

Figure 5-12: Range Profile – 76 Gallons Fuel............................... 5-23

Range Profile – 88 Gallons Fuel............................... 5-24

Figure 5-13: Endurance Profile – 76 Gallons Fuel ........................ 5-25

Endurance Profile – 88 Gallons Fuel ........................ 5-26

Figure 5-14: Landing Distances – 3600 Lbs ................................. 5-27

F.A.A. Approved

5-1

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

This Page Left Blank Intentionally

COPY

UNCONTROLLED

F.A.A. Approved

5-2

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

INTRODUCTION

Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions, and also, to facilitate the planning of flights in detail and with reasonable accuracy. The data in the charts has been computed from actual flight tests using average piloting techniques with the airplane and engine in good condition.

COPY

UNCONTROLLED

F.A.A. Approved

5-3

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

AIRSPEED CALIBRATION

SECTION 5

PERFORMANCE

NORMAL STATIC SOURCE

FLAPS UP

KIAS

KCAS

50

59

60

66

70

74

80

83

90

91

100

101

110

111

120

121

130

130

140

139

150

149

FLAPS 20 

KIAS

KCAS

40

52

50

59

60

66

70

75

80

84

90

94

100

103

FLAPS 40 

KIAS

KCAS

40

52

50

59

60

66

70

75

80

85

90

94

100

104

ALTERNATE STATIC SOURCE

VENTS AND WINDOWS CLOSED

FLAPS UP

KIAS

KCAS

FLAPS 20 

KIAS

KCAS

50

60

60

65

50

53

70

71

60

60

70

67

80

78

90 100 110 COPY

80

76

90

85

100

94

120

115

130

124

140

133

150

143

FLAPS 40 

KIAS

KCAS

40

48

50

55

60

62

70

71

80

79

90

89

100

99

Figure 5-1. Airspeed Calibration

F.A.A. Approved

5-4

October 4, 2005

100

80

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

120

SECTION 5

PERFORMANCE

60

40

20

0

-20

-40

-40

COPY

UNCONTROLLED

-20 0 20

DEGREES CELSIUS

40

Figure 5-2. Temperature Conversion Chart

60

F.A.A. Approved

5-5

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

STALL SPEEDS

CONDITIONS:

Power Flight Idle

NOTES:

1. Maximum altitude loss during a stall recovery may be as much as 240 feet.

2. KIAS values are approximate.

MOST REARWARD CENTER OF GRAVITY

ANGLE OF BANK

0



30



45



60



3600

UP 46 56 52

COPY

67 76 79

49 42 53 49 58 64 69

3600

3600

UNCONTROLLED

66

Figure 5-3. Stall Speeds (Sheet 1 of 2)

F.A.A. Approved

5-6

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

MOST FORWARD CENTER OF GRAVITY

ANGLE OF BANK

0



30



45



60



0



49 58 54 62 64 69 79 82

3600

3600

42 53 48 57 56 63 71 75 20



3600

40

 40 52 52 56 60 62 74 74 COPY

UNCONTROLLED

Figure 5-3. Stall Speeds (Sheet 2 of 2)

F.A.A. Approved

5-7

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

MINIMUM ENGINE TORQUE FOR TAKEOFF

CONDITIONS:

1. Power – TAKEOFF

2. Propeller – 1810 RPM

3. Engine Air Induction System – NORM

NOTES:

4. The torque indicated below is the minimum value for which takeoff performance in this section can be obtained.

5. Torque on this chart shall be achieved without exceeding 810  C TOT or

105% N

1

.

COPY

UNCONTROLLED

EXAMPLE: OAT 16  C

Pressure Altitude 4000 Ft.

Minimum Engine Torque Acceptable 85 PSI

Figure 5-4. Minimum Engine Torque For Takeoff

F.A.A. Approved

5-8

October 4, 2005

TAKEOFF DISTANCE, SHORT FIELD

3600 LBS

PRESS

ALT FEET -20°C -10°C 0°C 10°C 20°C 30°C 40°C

0

1000

2000

3000

4000

5000

6000

7000

8000

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

452 844 479 895 507 946 541 1010 599 1116 667 1240 752 1394

477 892 506 945 535 999 593 1105 656 1221 730 1355 823 1521

504 942 538 1004 583 1087 651 1211 720 1337 801 1483 902 1662

550 1025 591 1101 641 1193 716 1329 792 1465 881 1624 992 1819

604 1126 650 1210 706 1312 789 1460 873 1609 971 1782 1092 1992

666 1238 717 1332 780 1445 872 1608 964 1770 1072 1958 1205 2185

731 1355 788 1458 857 1582 959 1761 1061 1939 1181 2145 1328 2393

803 1486 867 1599 944 1735 1057 1933 1170 2127 1303 2352 1467 2624

885 1631 955 1755 1041 1905 1168 2124 1294 2336 1442 2583 1624 2880

CONDITIONS:

1. Flaps 20º

2. Speed at liftoff 51 KIAS

3. Speed at 50 Ft. 60 KIAS

4. Level, hard surface, dry runway

5. Zero Wind

6. Inlet – Normal

NOTES:

1. Short field technique as specified in Section 4.

2. Decrease distance 10% for each 10 knots headwind. For operation with tail

Roll” figure.

COPY winds up to 10 knots, increase distances by 10% for each 2.5 knots.

3. For operation on a dry, grass runway, increase distances by 15% of the “Ground UNCONTROLLED

Figure 5-5. Takeoff Distance, 3600 Lbs.

TAKEOFF DISTANCE, SHORT FIELD

3300 LBS

PRESS

ALT FEET -20°C

GRND

ROLL

TOTAL

TO CLR

50FT

-10°C

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

0°C

TOTAL

TO CLR

50FT

10°C

GRND

ROLL

TOTAL

TO CLR

50FT

20°C

GRND

ROLL

TOTAL

TO CLR

50FT

30°C

GRND

ROLL

TOTAL

TO CLR

50FT

40°C

GRND

ROLL

TOTAL

TO CLR

50FT

0

1000

2000

3000

4000

5000

6000

7000

8000

387 727 410 771 433 816 463 871 512 963 570 1071 642 1204

408 768 433 814 458 861 507 954 561 1054 624 1171 703 1315

431 812 460 866 498 938 556 1045 615 1155 685 1282 771 1438

470 884 505 950 548 1030 612 1148 676 1267 753 1405 847 1575

517 971 556 1045 604 1133 674 1262 745 1392 829 1543 932 1726

569 1069 613 1150 667 1249 744 1390 823 1532 915 1697 1028 1895

624 1171 673 1260 732 1369 819 1525 906 1680 1008 1860 1133 2077

686 1284 740 1383 806 1502 902 1674 999 1844 1112 2041 1251 2280

756 1411 816 1519 889 1650 997 1841 1104 2027 1230 2244 1385 2505

CONDITIONS:

7. Flaps 20º

8. Speed at liftoff 48 KIAS

9. Speed at 50 Ft. 57 KIAS

10. Level, hard surface, dry runway

11. Zero Wind

12. Inlet – Normal

NOTES:

COPY tail winds up to 10 knots, increase distances by 10% for each 2.5 knots.

3. For operation on a dry, grass runway, increase distances by 15% of the UNCONTROLLED

Figure 5-6. Takeoff Distance, 3300 Lbs.

TAKEOFF DISTANCE, SHORT FIELD

3000 LBS

PRESS

ALT FEET -20°C -10°C 0°C 10°C 20°C 30°C 40°C

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

TOTAL

TO CLR

50FT

0

1000

2000

3000

4000

5000

6000

7000

8000

315 579 334 614 354 650 378 695 418 769 465 856 524 964

333 612 353 649 373 687 413 762 457 842 509 937 573 1054

352 647 375 691 406 749 453 836 501 924 558 1027 628 1153

383 706 412 759 447 823 498 918 551 1014 613 1127 689 1264

421 776 453 835 492 906 549 1011 607 1116 675 1238 758 1387

464 855 500 920 543 1000 606 1115 670 1229 745 1363 836 1525

509 937 548 1009 597 1097 667 1223 737 1349 820 1496 921 1673

559 1029 603 1108 656 1205 735 1345 813 1483 904 1644 1017 1839

615 1131 664 1219 724 1325 811 1481 898 1632 1000 1809 1125 2023

CONDITIONS:

13. Flaps 20º

14. Speed at liftoff 44 KIAS

15. Speed at 50 Ft. 52 KIAS

16. Level, hard surface, dry runway

17. Zero Wind

18. Inlet – Normal

NOTES:

COPY tail winds up to 10 knots, increase distances by 10% for each 2.5 knots. UNCONTROLLED

Figure 5-7. Takeoff Distance, 3000 Lbs.

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

MAXIMUM RATE OF CLIMB

CONDITIONS:

1. Flaps Up

2. 1810 RPM

3. Maximum Continuous Power, 78 PSI or 738  C TOT

4. Inlet – Normal

WEIGHT

POUNDS

PRESS ALT

FEET

CLIMB

SPEED KIAS RATE OF CLIMB - FPM

3600 0

4,000

8,000

12,000

16,000

20,000

87

84

81

77

74

71

STD  20  C

1477

1429

1373

1107

831

569

STD

1447

1399

1228

959

709

477

STD+20  C

1354

1162

961

744

548

404

3300

3000

0

4,000

8,000

12,000

16,000

20,000

0

4,000

8,000

86

82

79

76

72

69

86

81

78

71

68

1675

1628

1570

1286

994

718 COPY

1185

892

1644

1596

1416

1130

867

626

1876

1827

1635

1050

798

Figure 5-8. Maximum Rate of Climb, Maximum Continuous Power

1544

1342

1130

905

700

551

1768

1552

1326

1087

873

719

F.A.A. Approved

5-12

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

MAXIMUM RATE OF CLIMB

CONDITIONS:

1. Flaps Up

2. 1810 RPM

3. Takeoff Power 101.4 PSI or 810  C TOT

4. Inlet – Normal

SECTION 5

PERFORMANCE

WEIGHT

POUNDS

PRESS

ALT

FEET

CLIMB

SPEED

KIAS

RATE OF CLIMB - FPM

3600 0

4,000

8,000

12,000

16,000

20,000

96

92

88

83

79

74

STD



20



C

2026

1867

1536

1221

907

619

STD STD+20



C

1984

1687

1700

1460

1423

1122

829

558

1195

935

689

459

3300 0

4,000

8,000

12,000

95

91

87

82

2267

2097

2222

1907

1627

1307

1922

1665

1383

1107

16,000 78 1078 997 849

3000

20,000

0

73

94

774

2551

712

2503

608

2182

4,000 90 2368 2162 1906

8,000

12,000

16,000

20,000

84

81

76

71

1986

1626

1274

954

1867

1525

1193

890

1604

1310

1035

781

Figure 5-9. Maximum Rate of Climb, Takeoff Power

F.A.A. Approved

5-13

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

TIME, FUEL AND DISTANCE TO CLIMB

3600 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

3300 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

3000 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

MAXIMUM RATE OF CLIMB

CONDITIONS:

1. Flaps Up

2. 1810 RPM

3. Maximum Continuous Power, 78

PSI or 738°C

4. Inlet - Normal

5. Temperature - Standard

WT

LBS

PRESS

ALT FT

CLIMB

SPEED

KIAS

RATE OF

CLIMB

FPM

NOTES:

1. Add 20 lbs (3 gal.) of fuel for engine start, taxi & takeoff.

2. Distances shown are based on zero wind.

TIME

MIN

FUEL USED

LB. GAL.

DIST

NM

81

79

78

76

87

86

84

82

74

72

71

1447

1424

1399

1326

1228

1089

959

826

708

603

476

0.0 0.0 0.0 0.0

1.4 5.4 0.8 2.0

2.8 10.6 1.6 4.0

4.3 15.7 2.3 6.1

5.8 20.8 3.1 8.3

7.6 26.2 3.9 10.6

9.5 31.8 4.7 13.2

11.6 38.0 5.7 16.2

14.4 44.7 6.7 19.6

17.4 52.0 7.8 23.5

21.1 60.4 9.0 28.2

79

78

76

74

86

85

83

81

72

71

69

79

77

75

73

86

84

82

80

71

70

68

1644

1622

1596

1519

1416

1286

1130

989

867

759

626

1876

1853

1827

1746

1635

1476

1329

1179

1050

936

798

0.0 0.0 0.0 0.0

1.2 4.7 0.7 1.8

2.5 9.3 1.4 3.5

3.7 13.8 2.0 5.3

5.1 18.2 2.7 7.1 COPY

3.4

4.1

4.9

9.1

11.3

13.8

12.3 38.4 5.7 16.5

14.8 44.3 6.6 19.6

17.7 50.8 7.6 23.1

0.0 0.0 0.0 0.0

1.1 4.2 0.6 1.5

2.2 8.1 1.2 3.0

3.3 12.0 1.8 4.5

4.5 15.9 2.4 6.1

5.7 19.9 3.0 7.8

7.2 24.0 3.6 9.7

8.8 28.4 4.2 11.7

10.6 33.0 4.9 13.9

12.6 37.8 5.6 16.4

14.9 43.0 6.4 19.2

Figure 5-10. Time, Fuel and Distance to Climb (Sheet 1 of 3)

F.A.A. Approved

5-14

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

TIME, FUEL AND DISTANCE TO CLIMB

3600 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

3300 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

3000 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

MAXIMUM RATE OF CLIMB

CONDITIONS:

1. Flaps Up

2. 1810 RPM

3. Maximum Continuous Power, 78

PSI or 738°C

4. Inlet - Normal

5. Temperature - Standard +20°C

WT

LBS

PRESS

ALT FT

CLIMB

SPEED

KIAS

RATE OF

CLIMB

FPM

NOTES:

1. Add 20 lbs (3 gal.) of fuel for engine start, taxi & takeoff.

2. Distances shown are based on zero wind.

TIME

MIN

FUEL USED

LB. GAL.

DIST

NM

81

79

78

76

87

86

84

82

74

72

71

1354

1263

1162

1061

961

848

744

635

547

491

404

0.0 0.0 0.0 0.0

1.5 5.4 0.8 2.2

3.2 10.9 1.6 4.6

5.0 16.7 2.5 7.1

7.0 22.6 3.4 9.9

9.2 28.9 4.3 12.9

11.7 35.6 5.3 16.3

14.6 42.9 6.4 20.1

18.0 50.9 7.6 24.6

21.9 59.4 8.9 29.5

26.3 68.5 10.2 35.1

79

78

76

74

86

85

83

81

72

71

69

79

77

75

73

86

84

82

80

71

70

68

1544

1448

1342

1235

1130

1012

905

791

699

641

551

1768

1666

1552

1438

1326

1200

1087

969

873

814

719

0.0 0.0 0.0 0.0

1.3 4.7 0.7 1.9

2.8 9.5 1.4 3.9

4.3 14.5 2.2 6.1

6.0 19.6 2.9 8.4 COPY

3.7

4.5

5.4

10.9

13.7

16.8

15.0 42.7 6.4 20.2

18.0 49.3 7.3 23.9

21.4 56.2 8.4 28.0

0.0 0.0 0.0 0.0

1.2 4.1 0.6 1.7

2.4 8.3 1.2 3.4

3.7 12.5 1.9 5.2

5.2 16.9 2.5 7.2

6.8 21.4 3.2 9.3

8.5 26.1 3.9 11.5

10.5 30.9 4.6 14.0

12.7 36.1 5.4 16.8

15.0 41.3 6.2 19.7

17.6 46.7 7.0 22.8

Figure 5-10. Time, Fuel and Distance to Climb (Sheet 2 of 3)

F.A.A. Approved

5-15

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

TIME, FUEL AND DISTANCE TO CLIMB

3600 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

3300 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

3000 0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

16,000

18,000

20,000

MAXIMUM RATE OF CLIMB

CONDITIONS:

1. Flaps Up

2. 1810 RPM

3. Maximum Continuous Power, 78

PSI or 738°C

4. Inlet - Normal

5. Temperature - Standard -20°C

WT

LBS

PRESS

ALT FT

CLIMB

SPEED

KIAS

RATE OF

CLIMB

FPM

NOTES:

1. Add 20 lbs (3 gal.) of fuel for engine start, taxi & takeoff.

2. Distances shown are based on zero wind.

TIME

MIN

FUEL USED

LB. GAL.

DIST

NM

81

79

78

76

87

86

84

82

74

72

71

1477

1454

1430

1403

1373

1231

1107

965

831

704

569

0.0 0.0 0.0 0.0

1.4 5.8 0.9 2.0

2.8 11.3 1.7 4.0

4.2 16.6 2.5 5.9

5.6 21.8 3.2 7.9

7.1 26.9 4.0 10.0

8.8 32.3 4.8 12.3

10.8 38.0 5.7 14.9

13.0 44.2 6.6 17.8

15.6 51.0 7.6 21.1

18.8 58.6 8.7 25.0

79

78

76

74

86

85

83

81

72

71

69

79

77

75

73

86

84

82

80

71

70

68

1675

1652

1628

1600

1570

1419

1286

1136

994

859

717

1907

1885

1860

1832

1801

1638

1497

1336

1185

1042

892

0.0 0.0 0.0 0.0

1.2 5.1 0.8 1.7

2.4 10.0 1.5 3.4

3.7 14.6 2.2 5.1

4.9 19.1 2.8 6.9 COPY

3.5

4.2

4.9

8.6

10.6

12.7

11.3 38.3 5.7 15.1

13.4 44.0 6.6 17.8

16.0 50.2 7.5 20.9

0.0 0.0 0.0 0.0

1.1 4.5 0.7 1.5

2.1 8.7 1.3 3.0

3.2 12.8 1.9 4.4

4.3 16.7 2.5 5.9

5.5 20.6 3.1 7.4

6.7 24.6 3.7 9.1

8.2 28.8 4.3 10.9

9.7 33.2 4.9 12.8

11.5 37.9 5.6 15.0

13.6 42.9 6.4 17.5

Figure 5-10. Time, Fuel and Distance to Climb (Sheet 3 of 3)

F.A.A. Approved

5-16

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

CRUISE PERFORMANCE

CONDITIONS:

1. 3600 Pounds

2. 1810 RPM

3. Inlet – Normal

PRESSURE ALTITUDE

– SEA LEVEL

STD -20



C

(-5



C)

STD

(15



C)

STD +20



C

(35



C)

65

60

50

40

143

137

127

114

186

176

157

138

68

60

50

40

148 195

141 181

130 161

116 142

70

60

50

40

153 206

144 186

132 166

118 146

30 64 119 30 95 123 30 97

PRESSURE ALTITUDE – 2,000

STD -20



C

(-9



C) (11



COPY

STD +20



C

(31



C)

UNCONTROLLED

126

68

60

50

40

30

147 186

134 172

129 153

116 134

95 115

70

60

50

40

30

152 195

143 176

132 157

118 138

97 118

72

60

50

40

30

157 204

146 181

135 161

120 141

86 121

Figure 5-11. Cruise Performance (Sheet 1 of 6)

F.A.A. Approved

5-17

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

CRUISE PERFORMANCE

CONDITIONS:

1. 3600 Pounds

2. 1810 RPM

3. Inlet – Normal

PRESSURE ALTITUDE – 4,000

STD -20



C

(-13



C)

STD

(7



C)

STD +20



C

(27



C)

69

60

50

40

151

143

132

118

184

167

148

130

72

60

50

40

157 191

146 172

135 153

120 133

72

60

50

40

160 200

149 177

137 157

123 137

30

60

96 111

145 163

30

60

86 114

149 168

30

60

88

PRESSURE ALTITUDE

– 6,000

STD -20



C

(-17



C) (3



COPY

STD +20



C

(23



C)

71

UNCONTROLLED

156 186 74 161 196 68 160 191

117

152 172

50

40

30

134 144

120 125

85 107

50

40

30

137 148

122 129

87 110

50

40

30

140 152

125 132

89 113

Figure 5-11. Cruise Performance (Sheet 2 of 6)

F.A.A. Approved

5-18

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

CRUISE PERFORMANCE

CONDITIONS:

1. 3600 Pounds

2. 1810 RPM

3. Inlet – Normal

PRESSURE ALTITUDE – 8,000

STD -20



C

(-21



C)

STD

(-1



C)

STD +20



C

(19



C)

73

60

50

40

160

148

136

122

191

159

140

122

76

60

50

40

167 205

151 164

139 144

124 125

65

60

50

40

160 181

155 168

142 148

127 128

30 87 103 30 89 106 30 91 108

PRESSURE ALTITUDE – 10,000

STD -20



C

(-25



C) (-5



COPY

STD +20



C

(15



C)

76

70

UNCONTROLLED

166 199

161 183 71 165 191

60

50

40

30

151 155

139 137

124 118

88 99

60

50

40

30

154 160

142 140

126 121

91 102

62

50

40

30

159 168

145 144

129 124

92 104

Figure 5-11. Cruise Performance (Sheet 3 of 6)

F.A.A. Approved

5-19

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

CRUISE PERFORMANCE

CONDITIONS:

1. 3600 Pounds

2. 1810 RPM

3. Inlet – Normal

PRESSURE ALTITUDE – 12,000

STD -20



C

(-29



C)

STD

(-9



C)

SECTION 5

PERFORMANCE

STD +20



C

(11



C)

72

60

50

40

165

153

141

126

189

156

134

115

66

60

50

40

164

157

145

128

179

160

138

118

58

50

40

158

147

130

30 90 96 30 92 99 30 94

PRESSURE ALTITUDE

– 14,000

STD –20 

C

(-33



C)

COPY

STD +20



C

(7



C)

67

60

UNCONTROLLED

163

156

175

156 62 162 166 55 157 151

101

160

141

121

50

40

30

144

128

92

131

112

93

50

40

30

147

130

94

135

115

96

50

40

30

150

132

96

138

118

99

Figure 5-11. Cruise Performance (Sheet 4 of 6)

F.A.A. Approved

5-20

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

CRUISE PERFORMANCE

CONDITIONS:

1. 3600 Pounds

2. 1810 RPM

3. Inlet – Normal

PRESSURE ALTITUDE – 16,000

STD -20



C

(-37



C)

STD

(-17



C)

STD +20



C

(3



C)

62

50

40

161

146

130

162

130

109

58

50

40

160

150

132

156

134

112

53

50

40

156 143

152 137

134 115

30 93 90 30 96 93 30 97 95

PRESSURE ALTITUDE – 18,000

STD -20



C

(-41



C) (-21



COPY

STD +20



C

(-1



C)

58

UNCONTROLLED

159 151 55 159 148

50

40

30

149

132

95

131

106

87

50

40

30

152

134

97

134

109

89

52

40

30

157 142

135 112

99 92

Figure 5-11. Cruise Performance (Sheet 5 of 6)

F.A.A. Approved

5-21

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

CRUISE PERFORMANCE

CONDITIONS:

1. 3600 Pounds

2. 1810 RPM

3. Inlet – Normal

PRESSURE ALTITUDE

– 20,000

STD –20 

C

(-45



C)

STD

(-25



C)

STD +20



C

(-5



C)

53

50

40

30

156

151

133

97

140

131

103

84

51

40

30

156

135

99

137

106

87

49

40

30

157 136

137 109

101 89

COPY

UNCONTROLLED

Figure 5-11. Cruise Performance (Sheet 6 of 6)

F.A.A. Approved

5-22

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

RANGE PROFILE

45 Minute Reserve

76 Gallons Usable Fuel

CONDITIONS:

1810 RPM 100% N

2

STANDARD TEMPERATURE

ZERO WIND

3600 LB AT ENGINE START

NOTE:

1) THIS CHART ALLOWS FOR FUEL

USED IN START, TAXI, AND CLIMB

AND 45 MINUTES RESERVE FUEL

AT THE PARTICULAR CRUISE,

POWER AND ALTITUDE.

COPY

UNCONTROLLED

Figure 5-12. Range Profile

– 76 Gallons Fuel (Sheet 1 of 2)

F.A.A. Approved

5-23

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

RANGE PROFILE

45 Minute Reserve

88 Gallons Usable Fuel

CONDITIONS:

1810 RPM 100% N

2

STANDARD TEMPERATURE

ZERO WIND

3600 LB AT ENGINE START

NOTE:

1) THIS CHART ALLOWS FOR FUEL

USED IN START, TAXI, AND CLIMB

AND 45 MINUTES RESERVE FUEL

AT THE PARTICULAR CRUISE,

POWER AND ALTITUDE.

COPY

UNCONTROLLED

Figure 5-12. Range Profile

– 88 Gallons Fuel (Sheet 2 of 2)

F.A.A. Approved

5-24

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

ENDURANCE PROFILE

45 Minute Reserve

76 Gallons Usable Fuel

CONDITIONS:

1810 RPM 100% N

2

STANDARD TEMPERATURE

ZERO WIND

3600 LB AT ENGINE START

NOTE:

1) THIS CHART ALLOWS FOR FUEL

USED IN START, TAXI, AND CLIMB

AND 45 MINUTES RESERVE FUEL

AT THE PARTICULAR CRUISE,

POWER AND ALTITUDE.

COPY

UNCONTROLLED

Figure 5-13. Endurance Profile

– 76 Gallons Fuel (Sheet1 of 2)

F.A.A. Approved

5-25

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 5

PERFORMANCE

ENDURANCE PROFILE

45 Minute Reserve

88 Gallons Usable Fuel

CONDITIONS:

1810 RPM 100% N

2

STANDARD TEMPERATURE

ZERO WIND

3600 LB AT ENGINE START

NOTE:

1) THIS CHART ALLOWS FOR FUEL

USED IN START, TAXI, AND CLIMB

AND 45 MINUTES RESERVE FUEL

AT THE PARTICULAR CRUISE,

POWER AND ALTITUDE.

COPY

UNCONTROLLED

Figure 5-13. Endurance Profile

– 88 Gallons Fuel (Sheet 2 of 2)

F.A.A. Approved

5-26

October 4, 2005

LANDING DISTANCE, SHORT FIELD

3600 LB

PRESS

ALT FEET -20°C

GRND

ROLL

TOTAL

TO CLR

50FT

-10°C

GRND

ROLL

TOTAL

TO CLR

50FT

GRND

ROLL

0°C

TOTAL

TO CLR

50FT

10°C

GRND

ROLL

TOTAL

TO CLR

50FT

20°C

GRND

ROLL

TOTAL

TO CLR

50FT

30°C

GRND

ROLL

TOTAL

TO CLR

50FT

40°C

GRND

ROLL

TOTAL

TO CLR

50FT

0

1000

2000

3000

4000

5000

6000

7000

8000

486 992 505 1022 524 1050 543 1079 563 1108 582 1136 601 1164

504 1020 524 1050 544 1079 563 1109 583 1139 603 1168 623 1197

522 1048 543 1079 564 1110 584 1140 605 1170 626 1201 646 1231

542 1077 563 1109 585 1141 606 1172 628 1204 649 1235 671 1266

563 1108 585 1141 607 1173 629 1206 651 1238 674 1270 696 1302

584 1139 607 1173 630 1207 653 1241 676 1274 699 1307 722 1340

606 1172 630 1207 654 1242 678 1277 702 1311 726 1345 750 1379

630 1206 655 1243 679 1279 704 1314 729 1350 754 1385 779 1420

654 1242 680 1279 706 1316 732 1353 758 1390 783 1427 809 1463

CONDITIONS:

1. Flaps 40°

2. Speed at 50 ft. 63 KIAS

3. Maximum braking.

4. Set ground idle power immediately after touchdown.

5. Retract flaps for maximum brake effectiveness.

6. Paved, level, dry runway.

7. Zero wind.

NOTE: COPY

4. For operation on a dry, grass runway, increase distance by

40% of the “Ground Roll” figu re. UNCONTROLLED

Figure 5-14. High Altitude Landing Distances

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

This page left blank intentionally

SECTION 5

PERFORMANCE

COPY

UNCONTROLLED

F.A.A. Approved

5-28

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

SECTION 6

WEIGHT & BALANCE/EQUIPMENT LIST

TABLE OF CONTENTS PAGE

Introduction .................................................................................. 6-3

Airplane Weighing Procedures ....................................................... 6-3

Sample Weight & Balance Forms .................................................. 6-3

Weight and Balance ....................................................................... 6-3

Equipment List ............................................................................... 6-3

Sample Loading Problem ............................................................... 6-4

Loading Graph ............................................................................... 6-6

Equipment List ............................................................................... 6-8

COPY

UNCONTROLLED

F.A.A. Approved

6 -1

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

This page left blank intentionally

.

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

COPY

UNCONTROLLED

F.A.A. Approved

6 -2

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

INTRODUCTION

This section supplies supplemental information for establishing the basic empty weight and moment of the airplane.

Supplemental information for calculating the weight and moments for various operations is also provided.

It should be noted that specific information regarding the weight, arm, moment and installed equipment list for this airplane can only be found in the appropriate weight and balance records carried in the airplane.

AIRPLANE WEIGHING PROCEDURES

– No Change

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

SAMPLE WEIGHT AND BALANCE FORMS

(FIGURES 6-1 AND 6-2)

– No change except:

Figure 6 -1: Oil Quantity:

Quarts

Oil Weight:

Oil Arm:

Fuel Weight: lbs./gal.

WEIGHT AND BALANCE

– No Change

9 U.S.

8 lbs./gal.

6.7

Loading Arrangements (Figures 6-3, 6-4, 6-5 and 6-6) -- No

Change

COPY

Sample Loading Problem (See Figure 6-7) UNCONTROLLED

EQUIPMENT LIST

– No Change except:

The equipment list description has been revised to delete certain Code

R equipment and to install items as necessary for this modification.

F.A.A. Approved

6 -3

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SAMPLE

LOADING PROBLEM

SAMPLE AIRPLANE

WEIGHT

(LBS.)

MOMENT

(LB.-INS.

/1,000)

1. Basic empty weight

(includes unusable fuel and full oil)

2. Usable fuel (at 6.7 lbs./gal.) (76 gal. max)

(Sta. 46.0)

2079

509

73.2

23.4

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

YOUR AIRPLANE

WEIGHT

(LBS.)

MOMENT

(LB.-INS.

/1,000)

340

340

340

12.6

23.8

34.0

3. Pilot and co-pilot (Sta. 32 to 43)

4. Center Passengers:

Standard Seating (Sta. 69 to 79)

Club Seating (Sta. 63 to

74)

Aft Passengers

Standard Seating (Sta. 94 to 100)

Club Seating (Sta. 98 to

109)

Baggage IV or V (Sta. 109 to 145)

5. *Cargo “A” (Sta. 10 to 50)

*Cargo “B” (sta. 50 to 84)

*Cargo “C” (Sta. 84 to 109)

*Cargo “D” (Sta. 109 to

145)

6. RAMP WEIGHT AND

MOMENT

7. Fuel allowance for engine start, taxi and run-up

167

COPY

UNCONTROLLED

-4 -.2

8. TAKEOFF WEIGHT &

MOMENT 3600 166.8

9. Locate this point on the Center of Gravity Moment Envelope.

*Maximum allowable loads will be determined by the number of tie-downs used, as well as floor loading limits of 200 lbs. per square foot.

Figure 6-7. Sample Loading Problem (Sheet 1 of 2)

(For Aircraft S/Ns: U20603522 thru U20604649)

6 -4

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SAMPLE

LOADING PROBLEM

SAMPLE AIRPLANE

WEIGHT

(LBS.)

MOMENT

(LB.-INS.

/1,000)

1. Basic empty weight

(includes unusable fuel and full oil)

2. Usable fuel (at 6.7 lbs./gal.) (88 gal. max)

(Sta. 48.0)

2019

589.6

76.4

28.3

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

YOUR AIRPLANE

WEIGHT

(LBS.)

MOMENT

(LB.-INS.

/1,000)

340

340

170

157.4

12.6

17.0

23.8

15.4

3. Pilot and co-pilot (Sta. 32 to 43)

4. Center Passengers:

Standard Seating (Sta. 69 to 79)

Club Seating (Sta. 63 to

74)

Aft Passengers

Standard Seating (Sta. 94 to 100)

Club Seating (Sta. 98 to

109)

Baggage IV or V (Sta. 109 to 145)

5. *Cargo “A” (Sta. 10 to 50)

*Cargo “B” (sta. 50 to 84)

*Cargo “C” (Sta. 84 to 109)

*Cargo “D” (Sta. 109 to

145)

9. RAMP WEIGHT AND

MOMENT

10. Fuel allowance for engine start, taxi and run-up

173.5

COPY

UNCONTROLLED

-16 -.8

11. TAKEOFF WEIGHT &

MOMENT 3600 172.7

10. Locate this point on the Center of Gravity Moment Envelope.

*Maximum allowable loads will be determined by the number of tie-downs used, as well as floor loading limits of 200 lbs. per square foot.

Figure 6-7. Sample Loading Problem (Sheet 2 of 2)

(For Aircraft S/Ns: U20602590, U20604650 thru U20606847 & on)

6 -5

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

COPY

UNCONTROLLED

NOTE: Lines representing adjustable seats show the pilot or passenger center of gravity on adjustable seats positioned for an average occupant. Refer to Loading Arrangements diagram for forward and aft limits of occupant C.G. range.

Figure 6-8A. Loading Graph

(For Aircraft S/Ns: U20603522 thru U20604649)

6 -6

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

COPY

UNCONTROLLED

NOTE: Lines representing adjustable seats show the pilot or passenger center of gravity on adjustable seats positioned for an average occupant. Refer to Loading Arrangements diagram for forward and aft limits of occupant C.G. range.

Figure 6-8AB. Loading Graph

(For Aircraft S/Ns: U20602589, U20604650 thru U20606847 and on)

6 -7

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

EQUIPMENT LIST

ITEM NO.

EQUIPMENT LIST

DESCRIPTION

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

WT

(lbs)

ARM

(ins)

EQUIPMENT REMOVED

A01 -R

A05 -R

A09 -R

A33 -R

A37 -R-1

A41 -R

A88 -R

C01 -R-1

C04 -R

Powerplant and Accessories

Engine, Continental IO

Filter, Induction Air

Alternator 28V 60A

Propeller Assembly

Spinner, 3

Governor, Propeller

-bladed propeller

Air Induction System

-520F

Electrical Power

450.0

1

10.8

69

3

3.5

5.5

Battery, 24V 14 Amp Hr

Regulator – 28V Alternator

Instruments

27.5

.5

D34 -R

D55 -R

D85 -R

Instrument Cluster – Engine

Gauge, Manifold Pressure &

Fuel Flow

Tachometer, Recording

1.5

1.0

1.5

E93 -R

Cabin Accommodations COPY

14.9

7.2

7.7

UNCONTROLLED

Cabin Heating

Exhaust & Heater, Left

Side

Exhaust & Heater,

Right Side

-17.0

-9.5

-6.0

-41.1

-35.5

-44.5

-2.5

3.0

3.0

17.5

16.5

15.0

-23.5

-14.9

-10.2

F.A.A. Approved

6 -8

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

ITEM NO.

EQUIPMENT LIST

DESCRIPTION

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

WT

(lbs)

TURBINE PAC ADDITIONS

R

A

R

R

A

R

R

R

R

R

R

A

A

Powerplant and Accessories

Engine, Soloy Turbine Pac

Propeller HC -C3YN-5A/

FC9587D -2

Governor, Propeller

Spinner, Propeller

Filter, Oil Scavenge

Oil Tank

Oil Cooler

Vacuum Pump

Induction System, Engine Air

Exhaust

Exhaust Heat Exchanger Kit

Drawing Ref.: 763 -1004

Engine Wash Kit

Drawing Ref.: 763 -1022

Engine Inlet Anti -Ice Kit

Drawing Ref.: 763 -1051

320.0

95.0

8.4

.5

1.0

3.0

7.0

3.0

4.5

7.0

3.1

6.0

12.0

Electrical Systems

R

O

R

R

R

R

R

Battery, 24V, 25 Amp Hr, Gill

G -247 (w/ 763-8500-1

Battery Base Assy)

Battery, 24V, 25 Amp Hr,

Concorde RG

1085 -1 Battery Base Assy)

Regulator

Reverse Current Relay

Instrument Cluster, Engine

(Group 1)

Instrument Cluster, Engine

(Group 2)

Fuel Flow Indicator

Oil Pressure Gauge,

Transmission

46

55

1.6

3.0

1.5

1.5

.5

ARM

(ins)

-32.7

-58.2

-40.8

-62.0

0.0

-32.0

-10.0

-40.8

-4.0

-22.0

-21.4

-4.5

-20.0

-6.0

-6.1

2.0

1.0

16.5

16.5

17.0

16.5

F.A.A. Approved

6 -9

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

This page left blank intentionally

.

SECTION 6

WEIGHT & BALANCE/

EQUIPMENT LIST

COPY

UNCONTROLLED

F.A.A. Approved

6 -10

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

AIRPLANE & SYSTEMS DESCRIPTIONS

Seat Belts ............................................................................... 7-11

Shoulder Harnesses ............................................................... 7-12

Integrated Seat Belt/Shoulder Harnesses w/ Inertia Reels ...... 7-12

Entrance Doors and Cabin Windows .............................................. 7-12

Control Locks ................................................................................. 7-12

Engine .......................................................................................... 7-12

TABLE OF CONTENTS

................................................................

PAGE

Introduction ....................................................................................... 7-9

Airframe ............................................................................................ 7-9

Flight Controls .................................................................................. 7-9

Trim Systems ............................................................................ 7-9

Instrument Panel .............................................................................. 7-9

Optional 2” Engine Instruments ....................................................... 7-10

Annunciator Panel .......................................................................... 7-10

Ground Control ............................................................................... 7-11

Wing Flap System .......................................................................... 7-11

Landing Gear System ..................................................................... 7-11

Baggage Compartment ................................................................... 7-11

Seats .............................................................................................. 7-11

Seat Belt/Shoulder Harness ............................................................ 7-11

Engine controls ....................................................................... 7-13

Power Control ................................................................. 7-13

Propeller Control ............................................................ 7-14 COPY

UNCONTROLLED

Engine Torque Indicator ................................................. 7-14

Propeller RPM Indicator ................................................. 7-14

TOT Indicator ................................................................. 7-14

N

1

Percent RPM Indicator .............................................. 7-15

Engine Oil Pressure Indicator ........................................ 7-15

Engine Oil Temperature Indicator .................................. 7-15

Transmission Oil Pressure Indicator ............................... 7-15

Fuel Totalizer/Temperature Indicator ............................. 7-15

New Engine Break-In and Operation ....................................... 7-15

Engine Oil System .................................................................. 7-15

Ignition System ....................................................................... 7-16

Air Induction System ............................................................... 7-16

Engine Alternate Air ........................................................ 7-16

Exhaust System .............................................................. 7-17

Propeller ................................................................................ 7-18

7-1

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

TABLE OF CONTENTS (Continued) ........................................... PAGE

Fuel System .................................................................................. 7-22

Fuel Tanks .............................................................................. 7-22

Fuel Indicating System ............................................................ 7-22

Fuel Required For Flight ......................................................... 7-23

Fuel Totalizer ....................................................................... 7-24

Operating Details .................................................................... 7-24

Limitations ...................................................................... 7-24

Procedures ..................................................................... 7-24

Preflight Check ....................................................... 7-24

If No Extra Fuel Is Needed ...................................... 7-25

Tanks Full ............................................................... 7-25

If Extra Fuel Is Needed ........................................... 7-26

During Flight ........................................................... 7-26

Emergency.............................................................. 7-26

Brake System ................................................................................. 7-26

Electrical System ........................................................................... 7-27

Master Switch ......................................................................... 7-27

Battery and Generator Switches ............................................ 7-27

Ammeter ................................................................................. 7-27

Overvoltage Sensor & Warning Light ...................................... 7-27

Circuit Breakers and Fuses ..................................................... 7-28

Ground Service Plug Receptacles .......................................... 7-28

Lighting Systems ........................................................................... 7-28

Cabin Heating, Ventilation & Defrosting System ............................. 7-28

Pitot Static System and Instruments ............................................... 7-28

Airspeed Indicator ................................................................... 7-28

Rate-of-Climb Indicatorr .......................................................... 7-28 COPY

Avionics Support Equipment ........................................................... 7-29 UNCONTROLLED

F.A.A. Approved

7-2

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

COPY

UNCONTROLLED

Figure 7-1. Instrument Panel (Sheet 1 of 2)

For Aircraft S/Ns U20602589 thru U20606439

7-3

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

1. Suction Gauge

2. Ammeter

3. Clock

4. Annunciator Dimmer

5. Spare

6. Turn Coordinator

7. Airspeed Indicator

8. Directional Gyro

9. Altitude Indicator

10. ADF

11. Vertical Speed Indicator

12. Altimeter

25. Cabin Heat Control

26. Flap Control & Indicator

27. Propeller Control

28. Power Control

29. Engine Alternate Air Control

30. Fuel Cutoff Control

31. Engine Inlet Anti-Ice Control

32. Fuel Gauges

33. Engine Alternate Air Light

34. Elevator & Rudder Trim

35. Electrical Switches

36. Inst & Radio Dial Lights Ctrl UNCONTROLLED

17. Engine Three-In-One Gauge

18. Prop Gearbox Transmission Oil

Pressure Gauge

19. Annunciator Lights

20. Flight Hour Recorder

21. Map Compartment

22. Auxiliary Cabin Air Control

23. Cabin Air Control

24. Defrost Control

COPY

41. Auxiliary Mic Jack

42. Generator APU Switch

43. Alternate Static Air Valve

44. Start Motor Switch

45. Circuit Breakers

46. Avionics Power Switch

47. Spare

Figure 7-1. Instrument Panel (Sheet 2 of 2)

For Aircraft S/Ns U20606440 & on)

7-4

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

1. Clock

2. Aux Mic & Headset Jacks

3. Marker Beacon

4. Turn Coordinator

5. Airspeed Indiciator

6. ADF

7. Directional Dyro

8. Attitude Indicator

9. Vertical Speed Indicator

10. Altimeter

11. DME

12. Nav 1

13. Nav 2

14. Avionics Stack

15. TOT Indicator 40. Propeller Control UNCONTROLLED

19. Annunciator Lights Dimmer

20. Flight Hour Recorder

21. Suction Gauge

22. Fuel Totalizer

23. Ammeter

24. Prop Gearbox Transmission Oil

Pressure

25. Engine Oil Press/Temp Meter

26. N1 Tachometer

27. Maps Compartment

28. Defrost Control

29. Aux Cabin Air Control

30. Cabin Air Control

31. Co-Pilot Rudder Stow

32. Cabin Heat Control

33. Cigar Lighter

34. Flap Control COPY

39. Elevator & Rudder Trim

42. Avionics Power Switch

50. Start/Motor Switch

43. Electrical Switches

44. Circuit Breakers

45. Inst & Radio Dial Lights Ctrl

46. Auto Feather Test Button

47. Battery Switch

48. Generator Overvoltage Trip Reset

Switch

49. Generator/APU Switch

Figure 7-2. Instrument Panel (Sheet 1 of 2)

Optional 2” Engine Instruments

For Aircraft S/Ns U20603522 thru U20606439

7-5

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

1. Ammeter

2. Spare

3. Clock

4. Suction Gauge

5. Spare

6. Turn Coordinator

7. Annunciator Light Dimmer

8. Airspeed Indicator

9. Directional Gyro

10. Attitude Indicator

11. ADF

12. Vertical Speed Indicator

13. Altimeter

14. NAV #2

15. NAV #1

16. DME Opt.

17. Avionics Stack

18. Np Tachometer

19. N1 Tachometer

20. TOT Indicator

21. Torque Indicator

22. Oil Pressure Low (Light)

23. Auto Feather (Light)

24. Oil Chops (Light)

25. Engine Oil Press/Temp Meter

26. Transmission Oil Pressure

27. Fuel Totalizer

28. Spare

29. Cold Fuel Placard

30. Fuel Filter (Light)

31. Gen Off Buss (Light)

32. Defrost Control

33. Map Compartment

34. Aux Cabin Air Control

35. Cabin Air Control

36. Cabin Heat Control

37. Flap Control

38. Propeller Control COPY

43. Fuel Gauges

44. Engine Alt Air (Light) UNCONTROLLED

49. Battery Switch

50. Aux Mic Jack

51. Generator Trip/Reset

52. Phone Jack

53. Generator On/APU

54. Alt Static Air Controls

55. Start/Motor Switch

56. Circuit Breaker Panel

57. Avionics Power Switch

58. Engine Control Circuit Breakers

Figure 7-2. Instrument Panel (Sheet 2 of 2)

Optional 2” Engine Instruments

7-6

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

For Aircraft S/Ns U20606440 and on

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

COPY

UNCONTROLLED

Figure 7-3. Instrument Panel (Sheet 1 of 2)

2” Instruments

7-7

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

For Aircraft S/Ns U20603522 thru U20606439

COPY

UNCONTROLLED

Figure 7-3. Instrument Panel (Sheet 2 of 2)

2” Instruments

For Aircraft S/Ns U20606440 and on

7-8

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

INTRODUCTION

This section provides description and operation of the airplane and its systems. Some equipment described herein is optional and may not be installed in the airplane. Refer to Section 9, Supplements, for details of other optional systems and equipment.

AIRFRAME

– No Change

FLIGHT CONTROLS

– No Change

TRIM SYSTEMS

– No Change Except:

The Soloy Turbine Pac system consists of a dual actuator trim tab.

INSTRUMENT PANEL

The instrument panel (refer to Figure 7-1) is designed around the basic

“T” configuration. The gyros are located immediately in front of the pilot, and arranged vertically. The airspeed indicator and altimeter are located to the left and right of the gyros respectively. The TOT, N p

(propeller RPM), and torque indicators are located in a cluster gauge to the right of the altimeter. Avionics equipment is stacked approximately on the center line of the panel.. The right side of the panel contains the annunciator panel, flight hour recorder, suction gauge, fuel totalizer, engine cluster gauge (N

1

COPY

U20606440 and on, the suction gauge and ammeter are located on the left side of the panel. A switch and control panel at the lower edge of UNCONTROLLED switch, auto-feather test button, light intensity controls, electrical switches, avionics power switch and circuit breakers for installed equipment. On serial numbers U20606440 and on, all circuit breakers for general electrical equipment and avionics are mounted in a circuit breaker panel located on the left cabin sidewall adjacent to the pilot’s seat. The center area contains the power control, propeller control, and fuel cutoff control. The right side of the panel contains the wing flap switch and indicator, cabin heater, cabin air, defroster, auxiliary cabin air control knobs and the cigar lighter. A pedestal, extending from the lower edge of the switch and control panel to the floorboard,

7-9

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION contains the elevator and rudder trim control wheels, engine alternate air control lever, microphone bracket and the fuel selector valve handle. A parking brake handle is mounted under the switch and control panel in front of the pilot. An alternate static source valve control knob may also be installed beneath the switch and control panel.

OPTIONAL 2” ENGINE INSTRUMENTS

With the optional 2” engine instruments (refer to Figure 7 -2), the basic tri-cluster gauges are replaced with 2” instruments on the right side of the instrument panel.

For details concerning the instruments, switches, circuit breakers, and controls on this panel, refer in this section to the description of the systems to which these items are related.

ANNUNCIATOR PANEL

The annunciator panel, with the exception of the alternate air light which is located by the engine alternate air lever, is located below the glare shield on the right instrument panel. A dimmer switch is used to reduce the intensity of the lights for night operation. The panel annunciates items of interest to the pilot in the applicable color of red or amber.

When a hazardous condition requiring immediate corrective action COPY

OIL GEN

OIL FUEL

PRESS OFF

FEATHER CHIPS FILTER

LOW BUS

ALT

AIR

F.A.A. Approved

7-10

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

1. The amber AUTO FEATHER light advises that the overspeed governor and the auto feather solenoid are operating. Also, before starting the engine, it advises that the pressure sensor is providing power for the auto feather system.

2. The red OIL PRESS LOW light advises that the engine oil pressure is below 50 psi or that the propeller gearbox transmission oil pressure is below 35 psi.

3. The amber OIL CHIPS light advises that ferrous metal particles have been detected in either the turbine engine oil system or the propeller gearbox transmission oil system.

4. The amber FUEL FILTER light advises that the fuel filter bypass valve is in a bypass condition.

5. The amber GEN OFF BUS advises that the generator switch is off or a generator malfunction exists.

6. The amber ALT AIR light advises that the spring-loaded alternate air door on the plenum chamber is open.

GROUND CONTROL

– No Change Except:

Extreme caution should be used when using a tow bar so as not to damage the engine by collapsing the exhaust stacks.

WING FLAP SYSTEM

LANDING GEAR SYSTEM

COPY

UNCONTROLLED

SEATS

– No Change

SEAT BELT/SHOULDER HARNESS

– No Change

SEAT BELTS

– No Change

7-11

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

SHOULDER HARNESSES

– No Change

INTEGRATED SEAT BELT/SHOULDER HARNESSES WITH

INERTIA REELS

– No Change

ENTRANCE DOORS AND CABIN WINDOWS

– No

Change

CONTROL LOCKS

– No Change

ENGINE

The SOLOY TURBINE PAC powerplant consists of a lightweight

ROLLS ROYCE Model 250-C20S free turboshaft engine and a SOLOY propeller reduction gearbox. The engine utilizes two independent turbine sections; one driving a compressor in the gas generator section, and the second driving a reduction gearing for the Turbine Pac driveshaft that is further reduced by the SOLOY reduction gearing for the propeller.

Inlet air enters the engine through a plenum chamber formed around the compressor inlet bellmouth where it is directed to the compressor.

The compressor consists of six axial compressor stages and one centrifugal stage, assembled as an integral unit. It provides a compression ratio of 7.0:1.

COPY and skin. This air is mixed with fuel sprayed from the fuel nozzle to UNCONTROLLED combustion section and the power and accessories gearbox. The twostage gas producer turbine drives the compressor and accessories gear train. The two-stage power turbine furnishes the output power of the engine through the power gear train. The expanded gas discharges through the twin ducts of the exhaust collector in a downward direction.

F.A.A. Approved

7-12

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

A two-stage helical gear set in the engine power and accessory gearbox reduces rotational speed from 33,290 RPM at 100% N

2

power turbine speed to 6016 RPM at the output drive spline. A flex coupled drive shaft is connected to the Soloy gear reduction system which uses a single-stage helical gear set in the propeller gearbox to reduce rotational speed from 6016 RPM at the input drive to 1810 RPM at the propeller output at a reduction ratio of 3.32:1. The engine is rated at

418 shaft horsepower on a standard day at sea level, with 101.4 PSI of indicated torque at 1810 propeller (N producer (N

1 which is 53,519 RPM at 105% N

1

P

) RPM. The speed of the gas

) is the true speed of the compressor side of the engine

. Maximum permissible overspeed of the engine is 54,028 RPM which equals 106% N

1

.

The power turbine gear train drives the propeller tachometer generator and the power turbine governor. The compressor, fuel pump, gas producer tachometer generator, gas producer fuel control, starter generator and the vacuum pump are driven by the gas producer gear train. The rest of the accessories are driven by the Soloy propeller reduction gearbox. These include the propeller governor, propeller overspeed governor, and the propeller gearbox oil pump. A spare accessory pad is also drive by this gear train.

The Turbine Pac oil supply is contained in an integral tank. The system has a capacity of 9 U.S. quarts and is provided with a dipstick.

ENGINE CONTROLS

The propulsion system is operated by a set of three controls. They consist of the power control, propeller control, and fuel cutoff control.

POWER CONTROL

COPY

UNCONTROLLED engine will be operating in the GROUND IDLE mode and the mode pointer will be on GROUND. FLIGHT IDLE is obtained by pushing the power control in to the fixed stop and rotating it to the right so the mode pointer is on FLIGHT. The remaining power range can be obtained by pushing the power control in to increase the engine power. A friction lock is located at the base of the power control and is operated by rotating the lock clockwise to increase friction or counter clockwise to decrease friction

7-13

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

PROPELLER CONTROL

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

The vernier propeller control in the cockpit is connected to the propeller governor mounted on the Soloy propeller reduction gearbox. The propeller control controls propeller governor settings from the maximum RPM position (1810 RPM) to a minimum flight position (1450 RPM) to full feather.

FUEL CUTOFF CONTROL

The fuel cutoff control in the cockpit is connected to the fuel control unit. The cockpit control has two positions only, RUN (IN) and CUTOFF (OUT).

ENGINE INSTRUMENTS

Engine instrumentation consists of the engine torque indicator, propeller RPM indicator (N indicator, N

1

P

), turbine outlet temperature (TOT)

percent RPM indicator, engine oil pressure, engine oil temperature indicator, transmission oil pressure indicator and fuel flow/temperature indicator. The indicators are placarded as to their operational parameters.

ENGINE TORQUE INDICATOR

The power train portion of the engine gearbox consists of two stages of helical gearing. These gears are such that a forward axial thrust is produced on the torquemeter shaft during normal operation. This axial thrust is transmitted to the sliding cylinder counterbalanced by oil from the lubrication system. The cylinder oil pressure is quoted to an external connection for use with a torque indicator that is calibrated in PSI of torque.

PROPELLER RPM INDICATOR (N

P

)

The propeller RPM indicator (N

P

) is a tachometer which indicates the propeller speed in revolutions per minute. The power turbine speed (N

2

N

P

) can also be determined with the indicator where 18.1

RPM is equal to 1% N

2

speed.

TOT INDICATOR

COPY

UNCONTROLLED

The turbine outlet temperature gauge displays the air temperature in the gas producer turbine outlet.

7-14

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

N

1

PERCENT RPM INDICATOR

The N

1

RPM indicator indicates the percent of the gas producer

RPM based on a figure of 105% N

1

at 53,519 RPM.

ENGINE OIL PRESSURE INDICATOR

Oil pressure is displayed in pounds per square inch.

ENGINE OIL TEMPERATURE INDICATOR

Oil temperature is measured at the engine oil inlet and is electrically transmitted and displayed by the indicator in degrees C.

TRANSMISSION OIL PRESSURE INDICATOR

Oil pressure is directly measured and displayed in pounds per square inch.

FUEL TOTALIZER/TEMPERATURE INDICATOR

The fuel totalizer/temperature indicator displays the flow of fuel to the engine in pounds per hour, time remaining in hours and minutes, pounds used, pounds remaining and fuel temperature.

NEW ENGINE BREAK-IN AND OPERATION

There are no specific break-in procedures required for the SOLOY

TURBINE PAC turboprop engine. The engine may be safely operated through the normal ranges authorized by the manufacturer at the time of delivery of your airplane.

ENGINE OIL SYSTEM

COPY

UNCONTROLLED cools as well as lubricates the system. Oil is drawn from the tank through a pickup line to the engine-driven oil pump. Oil from the pump passes by an oil chip detector and is routed through a pressure screen to the engine. Then, from the engine past an oil chip detector, the oil is circulated through an external oil filter to a thermostatically controlled oil cooler.

F.A.A. Approved

7-15

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

Oil from the cooler is then circulated back to the integral tank. The propeller reduction gearbox oil is routed from the tank to the gearbox oil pump then through a filter in the gearbox. The oil is retrieved from the gearbox by a scavenge pump, and passes by an oil chip detector through a filter and back into the integral tank. Engine oil also operates the propeller pitch mechanism and the engine torquemeter system.

The total lubrication system capacity is 9 U.S. quarts. The oil tank capacity is 6 U.S. quarts with 4 through 6 quarts marked on the dipstick for measuring purposes. Recommended oils and oil servicing procedures are covered in Section 8 of this handbook.

IGNITION SYSTEM

The ignition system consists of a start motor switch, ignition exciter, spark igniter lead and spark igniter. A start counter is mounted on the engine gearbox adjacent to the ignition exciter. The counter records the total starts on the engine.

The three-position start motor switch located on the left side of the switch and control panel is placarded START, OFF and MOTOR. The switch automatically returns to the center (OFF) position when released. Electrical power will continuously be applied to the ignition exciter when the start motor switch is in the START position and the battery switch is on, and will be terminated when the switch is released, manually placed to the MOTOR position, or if the battery switch is turned off.

AIR INDUCTION SYSTEM

COPY

The engine air induction system receives ram air through the engine UNCONTROLLED entry of large articles, but does not filter the inlet air.

ENGINE ALTERNATE AIR

An alternate air system is built into the intake system to prevent moisture particles from entering the engine inlet plenum. It consists of two ram inlet doors and a cowl ventilation door that are pneumatically operated by bleed air and a spring-loaded alternate air door on the plenum chamber.

7-16

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

During normal operation of the engine air system, the movable ram inlet doors are retracted out of the direct ram air inlet. For cold weather operation (5  C or below) in visible moisture, or while operating in falling or blowing snow, the doors should be raised to block the ram air inlet. Suction created by the engine will open the spring-loaded alternate air door on the back of the plenum and draw air from inside the engine cowl area. Additionally, a door on the underside of the cowling will open to help supply the engine cowl area with cool air.

The engine alternate air system is operated by an alternate air control lever on the right side of the control pedestal. The pedestal is labeled NORM, ALT AIR, ALT. The system is operated by moving the lever to the right to clear a detent, then moving the lever all the way up to the NORM position.

NOTE

A drop in torque and a rise in TOT is normal with the actuation of the engine ice protection system.

CAUTION

SIGNIFICANT POWER LOSS WILL OCCUR

WHILE OPERATING IN THE ALTERNATE

AIR MODE. EXTREME CAUTION SHOULD

BE USED TO MAINTAIN A MINIMUM OF 14

PSI TORQUE IN FLIGHT ON APPROACH

TO LANDING.

EXHAUST SYSTEM

COPY

The exhaust system consists of exhaust stacks fitted to the left UNCONTROLLED

F.A.A. Approved

7-17

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

PROPELLER

The airplane is equipped with an all-metal, three-bladed, constant speed, full feathering, governor regulated propeller. A setting introduced into the governor with the propeller control establishes the propeller speed, and thus, the engine power turbine speed to be maintained. The propeller utilizes oil pressure that opposes the force of springs and counterweights to obtain correct pitch for engine load.

Oil pressure from the propeller governor drives the blades toward low pitch (increasing RPM) while the springs and counterweights drive blades toward high pitch (decreasing RPM). Oil pressure for propeller operation is furnished by the propeller gearbox oil system, boosted in pressure by the governor gear pump, and supplied to the propeller hub through the propeller oil transfer system. To feather the propeller blades, the propeller control on the control panel must be placed in the feather position (OUT). Unfeathering the propeller is accomplished by positioning the propeller control to the minimum pitch high RPM position (IN). The unfeathering system uses governor boosted propeller gearbox oil pressure to force the propeller out of feather.

An auto feathering system provides for automatic reduction in propeller

RPM in the event of the loss of engine power. This system is not a total feathering device. It is intended to reduce propeller drag due to an engine failure. The system is controlled by a pressure sensor that automatically reduces the propeller RPM (N

P

) to 1450 RPM with the propeller overspeed governor if the engine torquemeter oil pressure drops below 4 PSI. An AUTO FEATHER annunciator light will illuminate when the system is operating. To ground test the system,

RPM (N

P the oil being dumped from the propeller system, an OIL PRESS LOW light will illuminate.

COPY

), press the test button. Propeller RPM (N

P

) will drop to 1450 UNCONTROLLED

CAUTION

DUE TO THE INCREASE IN THRUST

CAUSED BY THE PROPELLER

CHANGING PITCH DURING THE AUTO

FEATHER TEST, EXTREME CARE

SHOULD BE USED IF THE GROUND IS

COVERED WITH ICE OR SNOW.

7-18

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

COPY

UNCONTROLLED

Figure 7-6. Fuel System

7-19

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

COPY

UNCONTROLLED

Figure 7-6A. Fuel System

7-20

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

COPY

UNCONTROLLED

Figure 7-6B. Fuel System

7-21

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

FUEL SYSTEM

The fuel system, see Figure 7-6, consists of left and right vented fuel tanks, two fuel reservoir tanks, a fuel selector valve, engine fuel filter, fuel system quantity and flow instrumentation.

CAUTION

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

UNUSABLE FUEL IS AT A MINIMUM DUE

TO THE DESIGN OF THE FUEL SYSTEM.

HOWEVER, ¼ FUEL QUANTITY OR LESS,

PROLONGED UNCOORDINATED FLIGHT

SUCH AS SLIPS OR SKIDS CAN

UNCOVER THE FUEL TANK OUTLETS,

CAUSING FUEL STARVATION AND

ENGINE STOPPAGE.

FUEL TANKS

The fuel storage system consists of the fuel tanks and vent system. Fuel flows by gravity from the two wing tanks to two reservoir tanks, and from the reservoir tanks to a selector valve labeled RIGHT, BOTH, LEFT and OFF. A safety spring prevents inadvertent selection to OFF by acting as a stop once the valve is moved from the OFF position to LEFT. To shutoff the fuel, the safety spring must be pressed down to allow selector movement to OFF.

Fuel system venting is essential to system operation. Complete blockage of the venting system will result in decreasing fuel flow and eventual engine stoppage. Venting is accomplished by check valve equipped interconnected flush inlet vents. There are two primary ram-type vents and two drains on the interconnected vent line. The fuel filler caps are equipped with vacuum operated vents which open, allowing air into the tanks should the fuel tank vent lines become blocked.

COPY

UNCONTROLLED

FUEL INDICATING SYSTEM

Fuel quantity is measured by two float-type fuel quantity transmitters (one in each tank) and indicated by two electricallyoperated fuel quantity indicators on the right side of the instrument panel. A yellow arc indicates when the fuel quantity is

1/8 th tank or less with a red line and the letter “E” to indicate when the fuel tank is empty. The indicators cannot be relied upon for

7-22

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION accurate readings during skids, slips, climbs, descents, or unusual attitudes. If both indicator pointers should rapidly move to a zero reading, check the circuit breaker for an electrical malfunction.

Connected to the fuel quantity transmitter in each tank of some aircraft is a fuel low warning circuit. When the transmitter is at the

10 gallon position, the fuel low circuit is activated and the respective FUEL LOW light on the warning panel will illuminate.

When testing the warning lights the RIGHT and LEFT FUEL LOW lights require between 1 and 5 seconds before coming on.

Due to sloshing in the tanks, the fuel transmitter must accumulate approximately 18 seconds of sensed fuel below 10 gallons over a span of time. Thus, the FUEL LOW lights may come on at quantities above 10 gallons and then extinguish. This may occur several times before remaining on. To confirm an accurate indication, press the caution lights test switch and release. When the fuel level is at 10 gallons or less the FUEL LOW light(s) will go out for approximately 18 seconds and then come on again. When a FUEL LOW light is confirmed, switch the fuel selector switch to the tank for which the FUEL LOW light is NOT on. If both are illuminated, select BOTH and land as soon as practical. When the fuel selector is in either the LEFT or RIGHT position, the

FUEL CONFIG light will be illuminated.

NOTE

It remains the pilot’s responsibility to ensure fuel quantities.

Flight planning and fuel loading is facilitated by the use of fuel UNCONTROLLED minimum of 1/8 tank (5.0 gallons for aircraft S/Ns U20603522 thru

U20604649 and 5.5 gallons for aircraft S/Ns U20602589,

U20604650 thru U20606847and on) of usable fuel is required in each wing system before takeoff. An inaccurate indicator could give an erroneous indication of fuel quantity. If you as the pilot are not sure that at least five and one-half gallons usable are in each wing system, add necessary fuel so that the amount of fuel will not be less than five and one-half gallons usable per wing system at takeoff. Plan for an ample margin of fuel for any flight.

7-23

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

FUEL TOTALIZER

A fuel totalizer system is also installed. The totalizer displays a continuous readout of total fuel flow in pounds per hour, time remaining in hours and minutes and fuel temperature in degrees F. Other features of the system include fuel remaining in pounds, fuel used in pounds, fuel temperature in degrees C, and a low fuel warning system set at 30 minutes.

OPERATING DETAILS

NOTE

The accuracy of the fuel totalizing system is totally dependent upon the accurate entry of data by the pilot, the following procedure should be followed.

LIMITATIONS

All computations are based on Jet A fuel with a density of 6.71 lb./gal. at 80  F. If JP-5, JP-4, Jet B or AVGAS/JET A mixture is used, the following procedures should be followed.

1. The time remaining function is considered inaccurate.

2. To determine the fuel used or fuel remaining, multiply the reading by the following factors.

Fuel Used Multiplier

Jet A, JP-5 1.02

Jet B, JP-4, or AVGAS/Jet Mix .96

Normal

COPY

UNCONTROLLED

1. Pre-Flight Check

A. Apply D.C. power to the totalizer by turning the battery switch to on. Press test switch for more than one second. All figures will flash sequentially for ten seconds. If the computer checks out, the word “Good” will show in the time remaining window for three seconds.

7-24

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

NOTE

Using the test function while engine is running causes the computer to lose 13 seconds of fuel count.

B. Time remaining shows no display at the upper display window. Pres “Lbs. Used” button – upper window will display lb. used since last reset.

C. Press ”Lb. Rem.” button – upper window will display lb. of fuel remaining on board. Pilot should confirm this figure with actual fuel on board

D. Fuel temperature will be displayed in the lower right side display window in degrees F.

2. If no extra fuel is needed for the trip:

A. No action is needed since data is already stored.

B. Upon starting the engine, the computer will display fuel flow, time remaining and the other two functions are available by pressing the appropriate buttons.

3 . Tanks Full

A. Press “Lb. Rem.” button and hold. COPY

C. Release “Test/Enter” and the total usable fuel on board UNCONTROLLED usable fuel, press the “Lb. Used” button and simultaneously press “Enter/Test” button. Lb. used will be reset and the fuel remaining will be displayed for 4 seconds. The figures will decrement (the longer you press, the faster the decrementing) until reaching the correct figure.

F.A.A. Approved

7-25

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

4. If Extra Fuel is Needed, (less than total usable lb.)

A. On paper, add the amount of fuel remaining displayed to the amount of fuel from the refueling truck meter using 6.71 lb/gal. density figure.

B. Press “Lb. Rem.” button and hold.

C. Press “Test/Enter” button to increment the fuel quantity

(the longer you press, the faster the incrementing) until the figure from step 4A is reached.

D. Release “Lb. Rem.” button and the total usable fuel on board is entered into the memory.

5. During Flight

A. Fuel flow and time remaining is normally displayed.

Time is displayed in hours and minutes.

B. To display Lb. used or remaining, press the appropriate button.

C. Lbs. used could be reset at any time by pressing “Lb.

Used” and momentarily pressing “Test/Enter” button no longer than 4 seconds, otherwise the computer will start decrementing the fuel remaining.

D. Fuel temperature in degrees F is normally displayed.

To display fuel temperature in degrees C, press the appropriate button.

6. Emergency

COPY

UNCONTROLLED accurate unless the duration of the power failure is known and the consumption during the power failure is recalculated and subtracted from the Lb. Remaining.

BRAKE SYSTEM

– No Change

7-26

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

ELECTRICAL SYSTEM

Electrical power for the aircraft is supplied by a 24 volt direct current negative ground electrical system A single 19 amp hour, 24 volt lead acid battery, or an optional 25 amp hour, 24V lead acid battery, supplies power for starting and furnishes a reserve source of power in the event of a generator system failure. An engine driven generator, controlled by a transistorized voltage regulator, provides power for the aircraft electrical system and charges the battery during operation. An

APU plug is installed to permit an external power source to supplement the battery system for starting and ground operation.

CAUTION

PRIOR TO TURNING THE BATTERY SWITCH

ON OR OFF, STARTING THE ENGINE, OR

APPLYING AN EXTERNAL POWER SOURCE,

THE AVIONICS POWER SWITCH, LABELED

AVIONICS POWER, SHOULD BE TURNED OFF

TO PREVENT ANY HARMFUL TRANSIENT

VOLTAGE FROM DAMAGING THE AVIONICS

EQUIPMENT.

MASTER SWITCH – Delete

BATTERY AND GENERATOR SWITCHES

Separate battery and generator switches are provided as a means of checking for a malfunctioning generator circuit and to COPY should be terminated and/or the current drain on the battery minimized, because the battery can supply the electrical system for only a limited period of time.

UNCONTROLLED

The ammeter indicates the output in amps of the generator system.

OVERVOLTAGE SENSOR AND WARNING LIGHT

– Delete.

F.A.A. Approved

7-27

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

CIRCUIT BREAKERS AND FUSES

The circuit breakers and fuses remains the same with the following exceptions:

The APU circuit fuse and clock circuit fuse are mounted adjacent to the electrical component housing on the left side of the firewall.

The three circuit breakers added during the turbine conversion

(auto-feather and annunciator lights, generator field, and engine start) can be pulled off to disable the applicable circuit(s). These additional circuit breakers are mounted on the lower left side of the instrument panel.

GROUND SERVICE PLUG RECEPTACLES

– No Change

LIGHTING SYSTEMS

– No Change

CABIN HEATING, VENTILATING AND DEFROSTING

SYSTEM

– No Change except No Heater Installed.

PITOT STATIC SYSTEM AND INSTRUMENTS

– No

Change.

AIRSPEED INDICATOR

The airspeed indicator is calibrated in knots. Limitation and range markings include the white arc (40 to 96 knots), with a step at (49 knots), and a red line (149 knots).

ALTIMETER

– No Change

COPY

UNCONTROLLED

VACUUM SYSTEM AND INSTRUMENTS

– No Change

OUTSIDE AIR TEMPERATURE (OAT) GAUGE

– No

Change

F.A.A. Approved

7-28

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

STALL WARNING SYSTEM

– No Change

AVIONICS SUPPORT EQUIPMENT

– No Change

AUDIO CONTROL PANEL

– No Change

MICROPHONE HEADSET

– No Change

STATIC DISCHARGERS

– No Change

COPY

UNCONTROLLED

F.A.A. Approved

7-29

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 7

AIRPLANE & SYSTEMS

DESCRIPTION

This page left blank intentionally.

COPY

UNCONTROLLED

F.A.A. Approved

7-30

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

AIRPLANE HANDLING, SERVICE & MAINTENANCE

TABLE OF CONTENTS PAGE

Introduction ................................................................................... 8-3

Identification Plate ........................................................................ 8-3

Owner Follow-Up System ............................................................. 8-3

Publications .............................................................................. 8-3

Airplane File ................................................................................. 8-4

Airplane Inspection Periods .......................................................... 8-4

Pilot Conducted Preventive Maintenance ...................................... 8-4

Alterations or Repairs ................................................................... 8-4

Ground Handling .......................................................................... 8-4

Towing ...................................................................................... 8-4

Parking ..................................................................................... 8-4

Tie-Down .................................................................................. 8-4

Jacking ..................................................................................... 8-5

Leveling .................................................................................... 8-5

Flyable Storage ........................................................................ 8-5

Servicing ....................................................................................... 8-6

Engine Oil ...................................................................................... 8-6

Recommended Oils at Specific Ambient Temps ....................... 8-7

Oil Drain Period ........................................................................ 8-8

Oil Level Check ........................................................................ 8-8

Fuel ............................................................................................... 8-8 COPY

Landing Gear ................................................................................ 8-12

Oxygen ......................................................................................... 8-12 UNCONTROLLED

Propeller Care .......................................................................... 8-12

Engine Care .............................................................................. 8-12

Compressor .............................................................................. 8-12

General ..................................................................................... 8-12

Interior Care .............................................................................. 8-13

Bulb Replacement During Flight ............................................... 8-13

F.A.A. Approved

8-1

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

This page left blank intentionally.

COPY

UNCONTROLLED

F.A.A. Approved

8-2

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

INTRODUCTION

This section contains factory recommended procedures for proper ground handling and routine care and servicing of your SOLOY

TURBINE PAC equipped Cessna. It also identifies certain inspection and maintenance requirements, which must be followed if your airplane is to retain that new-plane performance and dependability. It is wise to follow a planned schedule of lubrication and preventive maintenance based on climate and flying conditions encountered in your locality.

IDENTIFICATION PLATE

– No Change Except::

Adjacent to the basic Cessna identification plates can be found the

SOLOY TURBINE PAC identification plate which contains the model number, serial number, supplemental type certificate (STC) and the date of the aircraft conversion.

OWNER FOLLOW-UP SYSTEM

– No Changes Except:

In addition to the Cessna system, Soloy, LLC offers a support system consisting of technical publications and service information.

PUBLICATIONS

-- No Change Except:

In addition to the Cessna publications, Soloy, LLC furnishes various publications with the airplane at the time of delivery.

These items are listed below:

1. Pilot’s Operating Handbook Supplement

2. Pilot’s Checklist

COPY

UNCONTROLLED

7. Service Letters and Bulletins

8. Service Instructions applicable to accessory kits installed or ordered.

F.A.A. Approved

8-3

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

The following additional publications are supplied with your new engine from Rolls Royce:

1. 250-C20 Series Operations & Maintenance Manual

2. Parts Catalog

3. Distributor Directory

4. Service Instructions applicable to accessory items installed.

AIRPLANE FILE

-- No Change

AIRPLANE INSPECTION PERIODS

– No Change

PILOT CONDUCTED PREVENTIVE MAINTENANCE

No Change

ALTERATIONS OR REPAIRS

– No Change

–

GROUND HANDLING

TOWING

– No Change Except:

CAUTION

COPY

CONTACT THE EXHAUST STACKS.

STRUCTURAL DAMAGE TO THE UNCONTROLLED

PARKING

– No Change

TIE-DOWN

Proper tie-down procedure is the best precaution against damage to the parked airplane by gusty or strong winds. To tie-down the airplane securely, proceed as follows:

1. Head airplane into the wind, if possible.

F.A.A. Approved

8-4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

2. Set the parking brake and install the control wheel lock.

CAUTION

DO NOT SET PARKING BRAKE WHEN

THE BRAKES ARE OVERHEATED OR

DURING COLD WEATHER WHEN

ACCUMULATED MOISTURE MAY

FREEZE THE BRAKES OR FOR LONG

TERM PARKING WHEN TEMPERATURE

CHANGES COULD DAMAGE THE

BRAKE SYSTEM.

3. Install a surface control lock over the fin and rudder.

4. Tie sufficiently strong ropes or chains (700 l pounds tensile strength) to the wing and tail tie-down fittings and secure each rope or chain to a ramp tie-down.

5. Tie a rope (no chains or cables) to the nose gear torque link and secure to a ramp tie-down.

6. Tie a rope (no chains or cables) to the propeller and secure to the airframe to prevent the propeller from windmilling.

7. Install a pitot tube cover.

8. If dusty conditions exist or if the last flight of the day has been completed, install the engine inlet and exhaust covers.

The covers may be installed after the engines have cooled down.

JACKING

– No Change

LEVELING

– No Change

COPY

UNCONTROLLED

FLYABLE STORAGE

1. If the airplane is to be stored temporarily, or indefinitely, refer to the Airplane and Engine Maintenance Manuals for proper storage procedures. The Maintenance Manuals provide amplification for the following procedures: a. Compressor preservation shall be accomplished as warranted by local corrosive conditions encountered.

In no case shall the shutdown period exceed five days without preserving the compressor.

F.A.A. Approved

8-5

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

2. Re-preserve at least each thirty days if the aircraft is stored outdoors and each ninety days if stored indoors. a. Install covers on the compressor inlet and the exhaust collector stacks. Covers shall incorporate desiccant

(No. 88 Absorbent Protective Dehydrating Agent, or equivalent, MIL-D-3464). Inspect desiccant for color change periodically (time period based on environmental humidity conditions). Rejuvenate desiccant as necessary to maintain light blue color. b. Use wedge to hold compressor bleed valve closed.

Also, cover the diffuser vent orifice hole and engine gearbox overboard vent during storage. c. Accomplish fuel system preservation. If the engine will be stored for over 45 days, re-preserve at least each 90 days if stored outdoors and each 180 days if stored indoors.

CAUTION

RED TAG THE POWER CONTROL

AFTER ANY PRESERVATION HAS

BEEN MADE.

SERVICING

COPY

Maintenance Manuals for complete UNCONTROLLED

ENGINE OIL

The oil specifications listed in Table I are compliant with the engine manufacturer’s requirements. These oil specifications are approved for use in the Soloy Turbine Pac 780-1000-1 engine. Refer to the Soloy

Turbine Pac 780-1000-1 Maintenance and Overhaul Manual S1014T for the most current listing of oils and limitations.

F.A.A. Approved

8-6

November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

TABLE I

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

RECOMMENDED OILS AT SPECIFIC AMBIENT TEMPERATURES

Temperature Rating

-40°C (-40°F) and above

Specification

MIL-PRF-23699,

SAE AS5780,

MIL-PRF-7808,

DOD-PRF-85734

MIL-PRF-7808 -40°C (-40°F) and below

NOTE

Because of availability, decreased coking and better lubrication qualities at higher temperatures, MIL-PRF-23699 HTS or SAE

AS5780 HPC oils are recommended for use in Model 250 engines.

WARNING

ALTHOUGH MIL-PRF-23699, SAE

AS5780, DOD-PRF-85734 OR MIL-PRF-

7808G OIL IS ACCEPTABLE, DO NOT

MIX THESE OILS. COPY

USE OF MIXED OILS (OILS NOT IN THE

SAME GROUP) IN AN ENGINE IS LIMIT-

UNCONTROLLED

ENSURE THAT THE FIVE HOUR LIMIT IS

NOT EXCEEDED.

FAILURE TO COMPLY WITH MIXING

RESTRICTIONS CAN RESULT IN ENGINE

FAILURE.

F.A.A. Approved

8-7

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

OIL DRAIN PERIOD

It is recommended that the oil be changed every 200 hours or six months, whichever comes first.

CAUTION

USE OF OILS THAT ARE NOT

INCLUDED IN THE APPROVED OILS

LISTING, OR FAILURE TO DRAIN OIL

WITHIN THE PRESCRIBED INTERVAL

WILL BE CONSIDERED AS MISUSE

UNDER THE WARRANTY POLICY.

REFER TO THE MAINTENANCE

MANUALS FOR THE COMPLETE OIL

SYSTEM MAINTENANCE SCHEDULE.

OIL LEVEL CHECK

Check within 15 minutes of shutdown. Normal operating range on the oil dipstick is four to six U.S. quarts in the tank.

FUEL

PRIMARY FUELS

MIL-T-5624

MIL-T-83133

ASTMD-1655

JP-1 Fuel conforming to ASTM D-1655, Jet A

JP-5

JP-8 COPY

CAUTION

CONTAMINATION WHICH COULD CAUSE

ENGINE FLAME OUT, AN EXTERNAL LOW

PRESSURE FUEL FILTER SHOULD BE

USED ON ANY AIRCRAFT REFUELING

FROM REMOTE REFUELING SITES

(DRUMS, ETC.). NOT ALL NO. 1 DIESEL,

JP1 OR ARCTIC DIESEL FUELS WILL

MEET THE PRIMARY FUEL SPECIFI-

CATIONS, THE BURDEN OF PROOF

RESTS WITH THE OPERATOR AND HIS

SUPPLIER.

F.A.A. Approved

8-8

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

COLD WEATHER FUELS

To assure consistent starts below 4ºC (40ºF), the following fuels may be necessary:

1. MIL-T-5624, Grade JP-4

2. ASTM D-6615, Jet B

3. AVGAS/JET A, JET A1, or JP-5 Mixtures.

NOTE

Jet A, Jet A1, JP-5 or JP-8 may start the engine at temperatures below 40ºF; however, when cold soaked, marginal starts may result due to viscosity changes.

In order to obtain a lightoff when cold weather fuel is used, it may be necessary to:

1. Preheat the engine, or

2. Bleed the fuel system.

Preheat the engine in the area of the fuel control.

CAUTION

DO NOT USE AN OPEN FLAME HEATER

TO PREHEAT THE ENGINE.

PROCEDURES.

COPY

UNCONTROLLED

Grade 100/130 with 4.6 ml/U.S. Gal. lead content. Make the fuel mix in the aircraft tank. The AVGAS can be added before or after the JET FUEL. The only restriction is that the final mix (including fuel in the tank before starting the mix) be two parts JET FUEL to one part AVGAS.

F.A.A. Approved

8-9

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

CAUTION

THERE IS NO LIMIT FOR ENGINE

OPERATION USING THE AVGAS-JET

FUEL MIXTURE AS LONG AS 80/87

GRADE AVGAS IS USED AND THE

1:VOLUME RATIO IS OBSERVED. USE

OF 100/130 (100l) GRADE AVGAS-JET

FUEL MIXTURE SHALL BE RESTRICTED

TO 300 HOURS IN ONE OVERHAUL

PERIOD DUE TO THE HIGH LEAD

CONTENT OF THE FUEL.

CAUTION

WHEN MIXING THE FUELS, AVOID HIGH

FLOW RATES. DO NOT EXCEED A

FLOW RATE OF 50 GALLONS PER

MINUTE. ALSO, MAKE SURE THE FUEL

NOZZLE AND FUEL TANK ARE

GROUNDED TO THE AIRCRAFT.

NOTE

Anti-ice additive is needed for the jet fuel-

AVGAS fuel mixture.

NOTE

Prolonged and uninterrupted operation with only AVGAS mixture will induce lead buildup on turbine parts. This lead buildup can consequently, this AVGAS mixture should be used only for cold weather operation.

During operation with normal Jet A type turbine fuel, the lead buildup will slowly dissipate.

COPY cause a gradual power reduction; UNCONTROLLED

When the AVGAS-jet fuel mixture is used in the engine the lead from the gasoline accumulates on the turbine and exhaust collector outlet ducts. The normal appearance after operation on leaded fuel is pale yellow powder deposit on the exhaust system.

F.A.A. Approved

8-10

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

WARNING

HANDLING LEAD RESIDUE COATED

PARTS CAN BE EXTREMELY

DANGEROUS.

FUEL ADDITIVES

For flight at ambient temperatures of 40  F and below, the fuel used in this aircraft MUST have an anti-icing additive in compliance with MIL-L-27686D or E or Phillips PF A55MB, incorporated or added into the fuel during refueling in accordance with the additive manufacturer's instructions.

CAUTION

PROPER MIXING OF ANTI-ICING

ADDITIVE WITH FUEL IS EXTREMELY

IMPORTANT BECAUSE CONCENTRA-

TION IN EXCESS OF THAT RECOM-

MENDED (0.15% BY VOLUME) WILL

RESULT IN DETRIMENTAL EFFECTS

TO THE FUEL TANKS. ASSURE THAT

THE FUEL ADDITIVE IS DIRECTED INTO

AND BLENDING WITH FLOWING FUEL

FROM THE FUELING NOZZLE. DO NOT

ALLOW CONCENTRATED ADDITIVE TO

CONTACT THE FUEL CELL OR AIR-

PLANE FINISH. SOME FUELS HAVE COPY

ADDITIVES SHOULD BE ADDED.

UNCONTROLLED

F.A.A. Approved

8-11

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

LANDING GEAR

Nose Wheel Tire Pressure -- 29 PSI on 6.00-6, 4-Ply Rated Tire

49 PSI on 5.00-5, 6-Ply Rated Tire

Main Wheel Tire Pressure -- 42 PSI on 6.00-6, 6-Ply Rated Tire

35 PSI on 8.00-6, 6-Ply Rated Tire

30 PSI on 8.50-6, 6-Ply Rated Tire

Nose Gear Shock Strut -- Keep strut filled with MIL-H-5606 hydraulic fluid per filling instructions placard, and with no load on the strut, inflate with air to 80.0 PSI. Do not over inflate.

OXYGEN

– No Change

CLEANING AND CARE

WINDSHIELD-WINDOWS

– No Change

PAINTED SURFACES

– No Change

PROPELLER CARE

– No Change

ENGINE CARE

COMPRESSOR

The cleaning practices that are necessary for proper maintenance of the engine compressor are as follows:

1. Water Rinse. To be accomplished on a daily basis when operating in a salt water or other corrosive environment.

COPY

UNCONTROLLED of operation in smoggy areas.

Refer to the Engine Operations and Maintenance Manual for the detailed procedures.

GENERAL

The engine compartment should be cleaned using a suitable solvent (P-S-661 or equivalent). Most efficient cleaning is done using a spray-type cleaner. Before spray cleaning, ensure that protection is afforded those components, which might be adversely affected by the solvent, particularly the

8-12

F.A.A. Approved November 17, 2015

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE starter generator and the bleed air system. Refer to the

Airplane Maintenance and the Engine Operation and

Maintenance Manuals for proper lubrication of controls and components after engine cleaning.

INTERIOR CARE

– No Change

BULB REPLACEMENT DURING FLIGHT

– No Change

COPY

UNCONTROLLED

F.A.A. Approved

8-13

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 8

HANDLING, SERVICE &

MAINTENANCE

This page left blank intentionally.

COPY

UNCONTROLLED

F.A.A. Approved

8-14

November 14, 2014

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 9

SUPPLEMENTS

SECTION 9

SUPPLEMENTS

The Soloy Turbine Pac modification is considered compatible with the approved supplements to the Pilot’s Operating Handbook and FAA

Approved Airplane Flight Manual as listed below. Appropriate flight tests will be conducted to determine compatibility of those not listed as the need arises.

Ambulance Kit

Club Seating and Sidewall Table

Convenience Table

Digital Clock

Electrical Elevator Trim System

Oxygen System

Strobe Light System

Windshield Anti-Ice System

Audio Control Panels

AM/FM Cassette Stereo Entertainment Center

DME

Emergency Locator Transmitter (ELT)

Area Navigation System

Optional Slaved Horizontal Situation Indicator (HIS)

SSB HF Transceiver

Optional Unslaved Horizontal Situation Indicator (HIS)

Weather Radar (Type Weather Scout II)

Cessna Navomatic 200A Autopilot

Cessna 300 ADF (Type R-546E)

Cessna 300 Nav/Com (720 Channel – Type RT385A)

With or Without Cessna 400 Area Navigation System

Cessna 300 Transponder (Type RT 359A) and Optional Altitude

Encoder (Blind or Type EA-401A)

Cessna Navomatic 300A Autopilot (Type AF-395A)

Cessna 400ADF (Type R-446A)

Cessna 400 Area Navigation System (Type RN-478A)

Cessna 400 DME (Type R-476A)

COPY

UNCONTROLLED

Cessna 400 Marker Beacon Type R-402A

Cessna 400 Nav/Com (720 Channel Type RT-485A)

With or Without Cessna 400 Area Navigation System (Type RM-

478A)

Cessna 400 Nav/Com (720 Channel Type RT-485B)

With or Without Cessna 400 Area Navigation System (Type RN-

478A)

Cessna 400 Transponder (Type RT-459A) and Optional Altitude

Encoder (Blind or Type EA-401A)

Cessna 400B Autopilot (Type AF-550A)

Cessna Skydiving Kit

9-1

F.A.A. Approved October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SECTION 9

SUPPLEMENTS

INTRODUCTION

This section consists of a series of Soloy Turbine Pac supplements, each covering a single optional system that may be installed in the airplane. Each supplement contains a brief description and, when applicable, supplement to Sections 2 through 8.

Limitations contained in the following supplements are F.A.A. approved. Observance of these operating limitations is required by

Federal Aviation Regulations.

SOLOY

SUPPLEMENT

NUMBER

1.

2.

3.

TABLE OF CONTENTS

SUPPLEMENT NAME

Exhaust Heat Exchanger Kit

Engine Inlet Anti-Ice Kit

Continuous Ignition Kit

NO. OF PAGES

4

4

3

COPY

UNCONTROLLED

F.A.A. Approved

9-2

October 4, 2005

3

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 1

EXHAUST HEAT

EXCHANGER KIT

SUPPLEMENT NO. 1

BLEED AIR HEATER KIT

SECTION 1

GENERAL

The installation of an exhaust heat exchanger kit will provide cabin heater air. Outside air enters from an inlet in the cowl, through a heat exchanger mounted within the left hand engine exhaust duct and enters the existing aircraft manifold through the existing firewall heater valve. When the valve is closed, the heater air is ducted outboard. To provide this capability, the following items are installed:

1. Heat exchanger in left hand exhaust duct.

2. Fresh air inlet and ducting to heat exchanger, ducting from heat exchanger to heater valve and ducting from valve to overboard exit.

SECTION 2 COPY

There are no changes to the limitations when the heater kit is installed.

EMERGENCY PROCEDURES

There are no changes to the emergency procedures when the heater kit is installed.

F.A.A. Approved

1 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 1

EXHAUST HEAT

EXCHANGER KIT

SECTION 4

NORMAL PROCEDURES

There are no changes to the normal procedures when the heater kit is installed.

SECTION 5

PERFORMANCE

The installation of the heat exchanger in the exhaust duct reduces the available horsepower when operating at TOT limits. This results in a small change to the performance data in the Soloy Turbine Pac Section 5

Performance. With the heater installed, increase takeoff distances by 1% and decrease rate-of-climb tables by 30 FPM.

SECTION 6

WEIGHT & BALANCE/EQUIPMENT LIST

See Soloy Turbine Pac Section 6 Equipment List.

EXHAUST SYSTEM

SECTION 7 COPY

UNCONTROLLED

The left hand exhaust stack is constructed with an internal mounted heat exchanger that provides cabin heater air.

F.A.A. Approved

2 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 1

EXHAUST HEAT

EXCHANGER KIT

CABIN HEATING, VENTILATING AND DEFROSTING SYSTEM

The temperature and volume of airflow into the cabin can be regulated by manipulation of the push-pull CABIN HEAT and CABIN AIR control knobs. When partial cabin heat is desired, blending warm and cold air will result in improved ventilation and heat distribution throughout the cabin. Additional outside air for summer ventilation is provided through the heat and vent system by operation of the push-pull AUX CABIN AIR knob. All three control knobs are the double button type with locks to permit intermediate settings.

Front cabin heat and ventilating air is supplied by outlet hoses spaced across a cabin manifold just forward of the pilot’s and co-pilot’s feet.

Rear cabin heat and air is supplied by three ducts from the manifold, one extending down each side of the cabin to an outlet at the front door post area at floor level and one extending under the center of the cabin floor to an outlet in the floor behind the pilot and co-pilot seats. The cabin floor outlet is flush mounted, with a removable airflow diverter.

Windshield defrost air is supplied by a duct from the cabin manifold to an outlet on top of the glare shield; therefore, the temperature of the defrosting air is the same as heated cabin air. A push-pull type control knob, labeled DEFROST, regulates the volume of air to the windshield.

Pulling out on the knob increases defroster air flow.

Additional cabin ventilation can be obtained from separate adjustable ventilators, one near each upper corner of the windshield for the pilot and co-pilot, and four adjustable ventilators in the cabin ceiling adjacent to the center and rear seat passengers. COPY

UNCONTROLLED

F.A.A. Approved

3 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 1

EXHAUST HEAT

EXCHANGER KIT

This page left blank intentionally.

COPY

UNCONTROLLED

F.A.A. Approved

4 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 2

ENGINE INLET ANTI-ICE KIT

SUPPLEMENT NO. 2

ENGINE INLET ANTI-ICE KIT

SECTION 1

GENERAL

INTRODUCTION

The basic Soloy Turbine Pac 206 is equipped with an alternate air system to provide anti-ice protection to the engine inlet in visible moisture at an

OAT of 5ºC (41ºF) and below and while operating in falling or blowing snow regardless of ambient temperatures. There is a significant power loss when operating in this alternate air mode.

Installation of the engine inlet anti-ice kit enables the aircraft to be operated using engine bleed air instead of the alternate air system to provide anti-ice protection to the engine inlet in visible moisture at an

OAT of 5ºC (41ºF) to 1ºC (34ºF), thereby improving engine performance in this temperature range. The basic alternate air system would still have to be used when operating in falling or blowing snow regardless of ambient temperatures.

To provide this capability, the following items are installed:

1. An engine inlet anti-ice control handle installed adjacent to the alternate air door actuator on the central pedestal.

2. Control cable, brackets and attachments to the engine anti-ice valve.

3. Two limitation placards replacing a single placard on the control pedestal.

COPY

UNCONTROLLED

F.A.A. Approved

1 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 2

ENGINE INLET ANTI-ICE KIT

SECTION 2

LIMITATIONS

The following information must be presented in the form of a placard attached to the central pedestal:

1. Near alternate air control:

ALTERNATE AIR

OPERATION REQUIRED:

- IN FALLING OR BLOWING SNOW

- IN VISIBLE MOISTURE AT AN

OAT OF 1ºC (34ºF) AND BELOW

2. Near engine inlet anti-ice control:

PULL ON

ENGINE INLET ANTI-ICE

OPERATION REQUIRED:

IN VISIBLE MOISTURE AT AN

O.A.T. OF 5ºC (41ºF) TO 1ºC (34ºF)

WHEN ALT AIR NOT IN USE

COPY

SECTION 3 UNCONTROLLED

ICING

INADVERTENT ICING ENCOUNTER

Flight into known icing conditions is prohibited. If unexpected icing conditions are encountered, the Inadvertent Icing Encounter checklist in Section 3 of the basic handbook should be followed. In addition, the following procedure is recommended:

F.A.A. Approved

2 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 2

ENGINE INLET ANTI-ICE KIT

NOTE

The engine alternate air must be activated for flight or ground operation in visible moisture at an OAT of 1ºC (34ºF) and below or while operating in falling or blowing snow regardless of ambient temperature.

The engine inlet anti-ice may be used instead of the engine alternate air in visible moisture at an OAT of 5ºC (41ºF) to 1ºC (34ºF) excluding falling or blowing snow.

It is not necessary to operate the engine inlet anti-ice when the engine alternate air is in use.

This system must be operated in the above mentioned conditions even if there is no visible sign of airframe ice and/or snow accumulation.

De-activation of the system shall not be made until the above mentioned conditions have been left and the engine alternate air must be used until all accumulated airframe ice and/or snow has dissipated.

ENGINE INLET ANTI-ICE OPERATION

NOTE

COPY

A drop in torque and a rise in TOT is normal UNCONTROLLED

ENGINE RESTART PROCEDURE DURING FLIGHT

1. Fuel Cutoff Control – CUTOFF (OUT)

2. Propeller Control – FEATHER (OUT)

3. Engine Inlet Anti-Ice – OFF

4. ACTIVATE engine alternate air system if in icing conditions

5. Airspeed 75 – 120 KIAS below 15,000 FT. MSL

110 – 120 KIAS 15,000 to 20,000 FT. MSL

6. Fuel Selector – ON

F.A.A. Approved

3 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA U/TU 206G

SOLOY SUPPLEMENT NO. 2

ENGINE INLET ANTI-ICE KIT

7. Power Control – FLIGHT IDLE

8. Start Motor Switch – MOTOR

9. TOT 150 degrees or lower and N

N

1

1

15% below 15,000 FT. MSL.

maximum obtainable above 15,000 FT. MSL

10. Start Motor Switch – START and hold.

11. Fuel Cutoff Control – RUN (IN)

12. TOT and N1 – MONITOR (810ºC to 927ºC FOR 10 SECOND

MAXIMUM)

13. De-energize the starter at 58% N1

14. Propeller Control – IN

NOTE

As the propeller comes out of feather, there will be an oscillation of power until the propeller RPM stabilizes.

SECTION 4

NORMAL PROCEDURES

The only change to the airplane normal procedures when the Engine Inlet

Anti-Ice system is installed is to check operation on the run-up during the pre-flight check.

SYSTEM CHECK

1. Engine Inlet Anti-Ice – ON COPY with the actuation of the engine anti-ice UNCONTROLLED

SECTION 5

PERFORMANCE

There are no changes to the airplane performance when the Engine Inlet

Anti-Ice system is installed

F.A.A. Approved

4 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA T206H/206H

SOLOY SUPPLEMENT NO. 3

COWL LANDING LIGHTS

SUPPLEMENT NO. 3

CONTINUOUS IGNITION KIT

SECTION 1

GENERAL

The installation of the Continuous Ignition Kit provides an added level of safety when operating in rain or snow. When the pilot closes the switch, it causes the ignition exciter to operate continuously providing re-ignition in case of a flame out. A clear plastic guard prevents the switch from being inadvertently closed. An indicator light informs the pilot that the system is on. Use of the Continuous Ignition System does not affect the cycle counter operation.

SECTION 2

LIMITATIONS

There are no changes to the Limitations when the Continuous Ignition Kit is installed.

SECTION 3 COPY

There are no changes to the Emergency Procedures when the UNCONTROLLED

F.A.A. Approved

1 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA T206H/206H

SOLOY SUPPLEMENT NO. 3

COWL LANDING LIGHTS

SECTION 4

NORMAL PROCEDURES

The Continuous Ignition switch should be on during flight in adverse weather conditions.

CAUTION

THE CONTINUOUS IGNITION SYSTEM SHOULD NOT

BE USED IN LIEU OF ENGINE ANTI-ICE OR INLET

ALTERNATE AIR.

NOTE

The continuous ignition is a pilot option and should be used in cases of snow, sleet or icing conditions.

SECTION 5

PERFORMANCE

There are no changes to the Performance when the Continuous Ignition kit is installed.

SECTION 6 COPY

Installation of Continuous Ignition Kit has minimal effect on the aircraft weight and balance. UNCONTROLLED

F.A.A. Approved

2 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA T206H/206H

SOLOY SUPPLEMENT NO. 3

COWL LANDING LIGHTS

SECTION 7

AIRPLANE & SYSTEMS DESCRIPTIONS

IGNITION SYSTEM

The modification consists of installing one circuit breaker in the circuit breaker/switch panel, and installing one lighted push button switch on the circuit breaker/switch or the instrument panel. The additional wiring is routed with the original harness and uses the existing firewall connector.

The Continuous Ignition System supplies electrical power to the ignition exciter, through a 5 ampere circuit breaker, when the switch is closed by the pilot. When the switch is closed, the lamp in the switch illuminates to indicate that the Continuous Ignition is on and that the ignitor plug is active. The cycle counter is electrically isolated from the Continuous

Ignition System by a diode, to prevent accumulation of unwanted cycle indications.

INSTRUMENT PANEL

The Continuous Ignition switch is located in the circuit breaker/switch or the instrument panel and is protected from inadvertent activation by a clear plastic guard. A placard on the panel identifies it as Continuous

Ignition. A circuit breaker is mounted in the circuit breaker/switch panel below the instrument panel and is identified by a placard.

COPY

UNCONTROLLED

F.A.A. Approved

3 of 4

October 4, 2005

SOLOY TURBINE PAC

POHS CESSNA T206H/206H

SOLOY SUPPLEMENT NO. 3

COWL LANDING LIGHTS

This page intentionally left blank.

COPY

UNCONTROLLED

F.A.A. Approved

4 of 4

October 4, 2005