lancair pilots operating handbook

Lancair Pilots Operating Handbook Type IV-P

Revision 0 Sep 2010 Page | 2

AIRCRAFT PARTICULARS

THIS AIRCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE APPROVED DATA AND

LIMITATIONS CONTAINED WITHIN THIS MANUAL AT ALL TIMES

Registration: _________________

Manufacturer: _________________

Aircraft Serial Number: _________________

Certification Categories: _________________

Bottom of page



AMENDMENTS Amendment

Date Section Affected

Pages Summary Signature

Bottom of page



INTRODUCTION This Operating Handbook has been prepared by Orbx Simulation Systems to resemble the approximate nature of a real world Pilots Operating Handbook for the Lancair IV-P

It does not comply with the requirements of ATSM F2245 and therefore should under no circumstances be used for real world operations or training.

This basic handbook provides essential Information, Limitations and Procedures required to operate the simulated version of the Lancair IV-P as a facsimile of a real world Experimental Aircraft. Additional specific Information is provided within the Supplements section of the handbook.

The operating Procedures described herein are based on knowledge and experiences gained from various sources up to the date of issue or amendment issued. This handbook is NOT INTENDED AS A TRAINING MANUAL. It may be used for operating purposes only if amendments are supplied to date. It contains all the information considered required to operate the aircraft described in the aircraft Particulars safely.

In Australia the operator must have the following endorsements and training to operate this aircraft.

VFR

Private Pilots License

Constant Speed Propeller endorsement

Retractable Landing Gear endorsement

Pressurization endorsement

Insert ARN and Details of endorsements here:

______________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________

IFR

Instrument Rating endorsement and all of the above

Insert ARN and Details of endorsements here:

______________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________

Bottom of page



WARNINGS & CAUTIONS Warning

FAILURE TO OPERATE THIS AIRCRAFT WITHIN THE SPECIFIED OPERATING ENVELOPE MAY RESULT IN INJURY OR DEATH.

Warning

THIS AIRCRAFT DOES NOT COMPLY WITH VARIOUS BASIC MINIMUM FLIGHT REQUIREMENTS. THEREFORE IT DOES NOT BEHAVE IN THE SAME WAY THAT NORMAL CERTIFIED AIRCRAFT DO

WHEN IN CONDITIONS CLOSE TO THE EDGE OF ITS NORMAL OPERATING ENVELOPE. NOTE THAT PUSHING THESE BOUNDARIES WILL LIKELY RESULT IN INJURY OR DEATH.

Passenger Warning

THIS AIRCRAFT IS CERTIFIED UNDER AMATEUR BUILD CATEGORY. IT IS NOT BUILT TO THE SAME STANDARD AS FACTORY CERTIFIED

AIRCRAFT. PERSONS ENTER THIS AIRCRAFT AT THEIR OWN RISK.

Caution

OPERATING PROCEDURES, TECHNIQUES ETC WHICH ARE NOT STRICTLY OBSERVED MAY RESULT IN DAMAGE TO THE AIRCRAFT OR ITS INSTALLED EQUIPMENT

Bottom of page



ABBREVIATIONS, SYMBOLS AND TERMINOLOGY Symbols and Abbreviations

Symbol Definition A Ampere

AGL Above ground Level AMSL Above mean sea level

AVGAS Aviation Gasoline BHP Brake Horse Power

CASA Civil Aviation Safety Authority (Australia) CAO Civil Aviation Order (Australia) CAR Civil Aviation Regulation °C Degrees Celsius

CHT Cylinder Head Temperature cm Centimeter, centimeters DC Direct Current

FAA Federal Aviation Administration (USA) °F Degrees Fahrenheit

FAR Federal Aviation Regulation (USA) ft foot, feet

Ft/min Feet per minute g Acceleration due to gravity

Gal Gallon hPa Hectopascal, hectopascals HF High Frequency

ICAO International Civil Aviation Organization IFR Instrument Flight Rules IMC Instrument Meteorological Conditions in Inch, inches

In Hg Inches of mercury In lbs Inch pounds ISA International standard atmosphere kg Kilogram

kg/l Kilogram per litre kHz Kilohertz

Kts, K knots kPa kilopascals kW Kilowatt, kilowatts

l Litre, litres lb Pound, pounds LH Left hand

LHS Left hand side Bottom of page



…Continued

Symbol Definition MOGAS Automotive fuel

nm Nautical mile OAT Outside air temperature PAX Passenger POH Pilots Operating Handbook

PROP Propeller psi Pounds per square inch

QTY Quantity qts Quarts RH Right hand

RHS Right hand side RON Research Octane Number RPM Revolutions per minute SAE Society of automotive engineers sec Seconds SQ Square

STBY Standby TBO Time between overhauls T/O Takeoff U/S Unserviceable

USG, US Gal US gallon V Volts

VFR Visual flight rules VHF Very high frequency VMC Visual meteorological conditions

General Airspeed Terminology and Symbols

CAS Calibrated Airspeed: the indicated speed of an aircraft corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level

KCAS Calibrated airspeed expressed in knots IAS Indicated airspeed: The speed of an aircraft displayed on

the aircraft indicator. IAS values used in this manual assume zero instrument error

KIAS Indicated airspeed expressed in knots TAS True airspeed: the airspeed of an aircraft relative to the

undisturbed air through which it passes. T.O.S.S Take off safety speed: the airspeed chosen to ensure

control of the aircraft is within adequate levels after takeoff

Bottom of page



…Continued

VA Maneuvering speed: the maximum speed at which application of full available aerodynamic control will not damage or overstress the aircraft

VFE Maximum flap extend speed: the highest speed permissible with wing flaps in a prescribed extended position.

VNE Never exceed Speed: the limiting airspeed that may not be exceeded

VC Maximum structural cruising speed: The speed that should not be exceeded except in smooth air.

VS Stalling speed: The speed at which the wing stops producing lift

VSO Stalling speed: The speed at which the wing stops producing lift in landing configuration

Vx Best angle of climb speed: the airspeed which results in the best gain in altitude in the shortest possible horizontal distance

Vy Best rate of climb speed: the airspeed that results in the best gain in altitude in the shortest possible time.

Meteorological Terminology

• OAT - Outside air temperature - the outside air static temperature • Airfield Pressure Height- The height registered at the surface of an aerodrome with the pressure sub scale set to

1013 hPa or 29.92 in Hg. • Pressure Altitude – Altitude measured from a barometric altimeter corrected for position and instrument error

from a setting of 1013 hPa or 29.92 in Hg. • Indicated Pressure Altitude – The altitude actually displayed by barometric altimeter when correctly set. • QNH – The local pressure setting that if set on the sub scale of an altimeter will result in the altimeter displaying

the local altitude above mean sea level. • Wind – The wind velocities to be used as variables on aircraft performance.

Aircraft Performance and Flight Planning Terminology

• Climb Gradient – The ratio of the change in height during a climb, to the horizontal distance travelled. • Demonstrated Crosswind Component – The crosswind component, during takeoff and landing, demonstrated

during certification to determine the maximum allowable crosswind present while maintaining control over the aircraft.

Weight and balance Terminology • Datum – An imaginary vertical plane from which all horizontal distances are measured from for balance and

design purposes. • Station – a location along the aircraft fuselage given in distance from the reference datum. • Arm – The horizontal distance from the reference datum to the centre of gravity of an item. • Moment – The product of the weight of an item multiplied by its arm. • Index Unit – Moment divided by a constant. Used to simplify the calculation of balance information.

Bottom of page



…Continued

• C of G Arm – the arm obtained by adding the aircrafts individual moments and dividing by the sum of the total weight.

• C of G Limits (MAC) – The extreme centre of gravity locations of which the aircraft must be operated at a given weight, also known as the mean aerodynamic chord.

• Usable fuel – The quantity of fuel available for flight planning purposes. • Unusable Fuel – The quantity of fuel that is not available for flight. • Empty weight – The weight of the aircraft with only unusable fuel and full oil on board. • Useful Load – The difference between takeoff weight and empty weight. • Maximum takeoff weight – maximum weight approved for takeoff. • Maximum landing weight – maximum weight approved for landing.

Bottom of page



METRIC IMPERIAL UNIT CONVERSION This POH uses a combination of both the US Imperial and Metric unit system. Where relevant both units are quoted however the most commonly used examples and their conversion factors are listed below.

1 Pound (lb) = 0.4536 Kilogram (kg) 1 Pound per sq in (psi) = 6.895 Kilopascal (kPa) 1 Inch (in) = 25.4 Millimeters (mm) 1 Foot (ft) = 0.3048 Meter (m) 1 Statute mile = 1.609 Kilometers (km) 1 Nautical mile (NM) = 1.852 Kilometers (km) 1 Millibar (mb) = 1 Hectopascal (hPa) 1 Millibar (mb) = 0.1 Kilopascal (kPa) 1 Imperial gallon = 4.546 Litres (l) 1 US gallon = 3.785 Litres (l) 1 US quart = 0.946 Litre (l) 1 Cubic foot (ft3) = 28.317 Litres (l) 1 Acre = 0.4047 Hectares 1 Degree Fahrenheit (EF) = [1.8 x EC]+32 1 Inch Pound (in lb) = 0.113 Newton Meters (Nm) 1 Foot Pound (ft lb) = 1.356 Newton Meters (Nm)

Bottom of page



Index Title Page

1 GENERAL INFORMATION .…………………………………………………………………………………………13 1.1 Manufacturer Details ………………………………………………………………………………………………………13 1.2 Experimental Aircraft Notices ………………………………………………………………………………………………………13 1.3 Performance and Specification Summary ……………………………………………………….……………………13 2 AIRCRAFT SYSTEMS DESCRIPTIONS .…………………………………………………………………………………………14 2.1 Engine ………………………………………………………………………………………………………14 2.2 Propeller ………………………………………………………………………………………………………14 2.3 Fuel ………………………………………………………………………………………………………14 2.4 Engine Oil ………………………………………………………………………………………………………14 2.5 Operating weights and loading ………………………………………………………………………………………………………14 2.6 Minimum Equipment List ………………………………………………………………………………………………………15 3 OPERATING LIMITATIONS ………………………………………………………………………………………………………17 3.1 Airspeed Limits ………………………………………………………………………………………………………17 3.2 Crosswind ………………………………………………………………………………………………………17 3.3 Aircraft service ceiling ………………………………………………………………………………………………………17 3.4 Load Factors ………………………………………………………………………………………………………17 3.5 Powerplant Limitations ………………………………………………………………………………………………………17 3.5.1 Fuel Grade ………………………………………………………………………………………………………18 3.5.2 Lubricating Oil ………………………………………………………………………………………………………18 3.6 Power Generation ………………………………………………………………………………………………………18 3.7 Other Limitations ………………………………………………………………………………………………………19 3.8 Placards ………………………………………………………………………………………………………19 4 WEIGHT AND BALANCE INFORMATION .……………..…………………………………………………………………………20 4.1 C of G Range ………………………………………………………………………………………………………20 4.2 Baggage ………………………………………………………………………………………………………20 4.3 Aircraft weight Data ………………………………………………………………………………………………………20 4.4 Weight and balance Sheet ………………………………………………………………………………………………………21 4.5 Sample Calculation Sheets ………………………………………………………………………………………………………22 4.5.1 Calculate operating CG ………………………………………………………………………………………………………24 4.5.2 Allowable Loading conditions ………………………………………………………………………………………………………24 5 PERFORMANCE ………………………………………………………………………………………………………25 5.1 Takeoff and Landing distances ………………………………………………………………………………………………………25 5.2 Rate of Climb ………………………………………………………………………………………………………25 5.3 Cruise Speeds/MP/Fuel Consumption/Range .……………………………………………………………………………25 6 NORMAL PROCEDURES ………………………………………………………………………………………………………30 6.1 General ………………………………………………………………………………………………………30 6.2 Speeds for normal operation ………………………………………………………………………………………………………30 6.3 Best angle of climb speed ………………………………………………………………………………………………………30 6.4 Best rate of climb speed ………………………………………………………………………………………………………30 6.5 Preflight Inspection ………………………………………………………………………………………………………31 6.6 Normal Procedures Checklist ………………………………………………………………………………………………………33 6.6.1 Before Start ………………………………………………………………………………………………………33

Bottom of page



…Continued 6.6.2 After Start ………………………………………………………………………………………………………33

6.6.3 Taxi ………………………………………………………………………………………………………33 6.6.4 Before Takeoff ………………………………………………………………………………………………………33 6.6.5 Run-up ………………………………………………………………………………………………………34 6.6.6 Lineup ………………………………………………………………………………………………………34 6.6.7 Takeoff and Climb ………………………………………………………………………………………………………34 6.6.8 Cruise ………………………………………………………………………………………………………34 6.6.9 Descent ………………………………………………………………………………………………………35 6.6.10 Approach ………………………………………………………………………………………………………35 6.6.11 Taxi to parking ………………………………………………………………………………………………………35 6.6.12 Shutdown ………………………………………………………………………………………………………35 7 EMERGENCY PROCEDURES ………………………………………………………………………………………………………36 7.1 Speeds For Emergency Operations .…………………………………………………………………………………………36 7.2 Emergency Procedures Checklist .…………………………………………………………………………………………36 7.2.1 Engine Failure during Takeoff Run .…………………………………………………………………………………………36 7.2.2 Engine Failure after Takeoff ………………………………………………………………………………………………………36 7.2.3 Engine Failure during Flight ………………………………………………………………………………………………………36 7.2.4 Landing without Engine Power ………………………………………………………………………………………………………37 7.2.5 Ditching ………………………………………………………………………………………………………37 7.2.6 Fire on ground ………………………………………………………………………………………………………37 7.2.7 Engine fire in flight ………………………………………………………………………………………………………37 7.2.8 Cabin fire in flight ………………………………………………………………………………………………………37 7.2.9 Spins ………………………………………………………………………………………………………38 8 AIRCRAFT GROUND HANDLING AND SERVICING ..……………………………………………………….………39 8.1 Fuel ………………………………………………………………………………………………………39 8.2 Oil ………………………………………………………………………………………………………39 8.2.1 Engine Oil Specifications .…………………………………………………………………………………………39 8.2.2 Engine Oil Viscosity ………………………………………………………………………………………………………39 8.3 Brakes ………………………………………………………………………………………………………40 8.4 Hydraulics ………………………………………………………………………………………………………40 8.5 Tires ………………………………………………………………………………………………………40 9 CLIMATIC RESTRICTIONS ………………………………………………………………………………………………………41 9.1 Pressurization ………………………………………………………………………………………………………41 9.2 Oxygen ………………………………………………………………………………………………………41 9.3 Hypoxia ………………………………………………………………………………………………………41 10 SUPPLEMENTS ………………………………………………………………………………………………………42 10.1 Log of supplements ………………………………………………………………………………………………………43

Bottom of page



1 GENERAL INFORMATION

1.1 Manufacturer Details Orbx Simulations Systems

PO Box XXXX Melbourne Victoria

XXXX Phone: XX XXXX XXXX

Fax: XX XXXX XXXX Email: [email protected]

1.2 Experimental Aircraft Notices There are risks associated with participation in sport aviation. This is particularly the case in the experimental category. Operators and passengers of experimental aircraft, by participation, accept the risks inherent in such participation of which the ordinary person is or should be aware. Pilots and passengers have a duty to exercise good judgment and act in a responsible manner while using the aircraft and to obey all oral and written warnings prior to and during use of the aircraft.

1.3 Performance and Specification Summary Empty Weight 2431lb (1102.7kg)

Top speed at Sea Level 220KCAS

Full Fuel Range 1130nm (with reserves @ 8,000ft)

Rate of climb at sea level 2,000fpm (solo), 1,500fpm (gross)

Takeoff Distance 1,500ft (gross @ sea level)

Landing Distance 1,900ft

Stall Speed Clean 75KCAS

Stall Speed Landing Configuration 69KCAS

Fuel Capacity (Usable) 93USG

Approved Fuels AVGAS 100-130

Maximum Engine Power 350hp @ 2750RPM

Refer to section 3, 4, 5 and 6 for more information

Bottom of page

mailto:[email protected]�



2 AIRCRAFT SYSTEMS DESCRIPTIONS

2.1 Engine Manufacturer: Continental Motors Model: TSIO-550-E Rated HP: 350 Arrangement: Horizontally Opposed Number of Cylinders: 6 Compression Ratio: 7.5:1 Bore (in): 5.25 Stroke (in): 4.25 Piston Displacement (cu in): 550

2.2 Propeller Manufacturer: MT Model: MTV-9-D/198-58a Type: Constant Speed, Wood Composite core Number of Blades: 4 Diameter (in): 75 Max RPM: 2750

2.3 Fuel Capacity: 93 US Gallons (352l) Usable 3 US gallons (11.4l) unusable. Grade: AVGAS 100LL AVGAS 100/130

2.4 Engine Oil Approved oils consist of lubricating oils of any brand that conform to specifications MIL-L-6082 for non dispersant mineral oil or MIL-L-22851 for ashless dispersant mineral oil. Some synthetic oils meet MIL-L-22851 requirements however when used can reduce engine life.

2.5 Operating Weights and Loading Max Takeoff and Landing weight: 3,850lb Max Baggage: 110lb Foreward Limit: 86.5in Measured from datum Aft Limit: 94.5in Measured from datum Datum: 51.25in forward of the bottom face of the firewall. Leveling: Spirit level placed on the centre carry through spar box.

Bottom of page



…Continued

ARM front seat 95.0in Measured from datum ARM PAX 129.0in Measured from datum ARM Baggage 140.0in Measured from datum ARM Fuel Station 94.0in Measured from datum

2.6 Minimum Equipment list System, instrument, Equipment

VFR (Day)

VFR (Night)

IFR

Comunications

VHF COM x x x Mode C Transponder x x Electrical Power

Alternator x x x Battery x x x Voltage indicator x x Amperage indicator x x Fire Protection

Portable Fire Extinguisher A/R A/R x Flight Controlls

Pitch trim indicator x x Pitch trim system x x x Aileron trim indicator x x Aileron trim system x x Rudder trim indicator A/R Rudder trim system x x Flap position indicator x x x Stall warning system x x x Fuel

Fuel Quantity indicator x x x Fuel on off valve x x x Ice and Rain

Engine alternate air x Bottom of page



…Continued System, instrument, Equipment

VFR (Day)

VFR (Night)

IFR

Navigation

ADF x or x VOR1 x or x VOR2 Recommended GPS1 Recommended GPS2 A/R Compass x x x DG x x Chronometer x x Turn coordinator x x x Pitot, Static, Vacuum

ASI x x x Altimeter x x x VSI x x AH x x VAC pressure x x Engine

CHT x x Tachometer x x x Oil pressure x x x Oil temperature x x x EGT x Fuel pressure x x Oil quantity (Dip Stick) x x x Documents

POH x x x Charts x x Weather reports x x -( ) = Not required -(A/R) = As required by local regulations -( x ) = Required -(x or) = one or the other -(Recommended) = recommended

Bottom of page



3 OPERATING LIMITATIONS

3.1 Airspeed Limits

MARKING SPEED SPEED (KCAS) VA Maneuvering speed 170 VNE Never exceed speed 274 VC Caution smooth air only (Yellow Arc) 220-274 VFE (0-10) Flap 10 degrees extension 174 VFE Maximum flap extension speed 69-132 VX Best angle of climb 110 VY Best rate of climb 135 VS Stall speed clean 75 VSO Stall speed landing configuration 69 VLO (Down) Landing gear operating speed (down) 150 VLO (Up) Landing gear operating speed (up) 120 VLE Landing gear extension speed 165 T.O.S.S Allowable safe control speed 100

3.2 Crosswind The allowable crosswind component varies with pilot skill, the average pilot skill level (for this aircraft) allows direct crosswinds of 19knots. The max demonstrated crosswind component is 25knots only when well above T.O.S.S

3.3 Aircraft Service Ceiling 28 000ft ASL Pressurized to cabin differential of 4.7psi and cabin altitude of 14 000ft

3.4 Load Factors Flap UP Speed VA +4.4 to -2.3g’s Flaps DN Speed FE +3.8 to -2.0g’s

3.5 Powerplant Limitations The aircraft is powered by the continental TSIO-550-E. A350hp six cylinder horizontally opposed, fuel injected, air cooled, twin turbocharged and twin intercooled engine. Outputs:

Max continuous: 350BHP (-5+20) 2750RPM Max Continuous Manifold Pressure: 38.5 in hg

Bottom of page



…Continued

Max recommended Climb: 262BHP 2500RPM Max recommended climb Manifold Pressure: 31.0 in hg

CHTs (⁰F): Maximum: 498 Min, Max. limits In cruise: 380 - 460

TITs (⁰F): Maximum continuous: 1810 Peak (1 min): 1960 Oil Temperatures (⁰F): Maximum: 255 Recommended Takeoff Minimum: 120 Min, Max. limits In cruise: 160 - 220 Oil Pressure (PSI): Normal Operation: 30 - 60 Idle Minimum: 10 Max allowable (Cold): 100 Fuel Flow vs HP: see Charts Fuel Pressure (PSIG): Idle: 7 - 9 Takeoff: 32 - 36 Vacuum Pressure: Normal: -4.8 - -5.2

3.5.1 Fuel Grades • AVGAS 100LL • AVGAS 100-130 • Octane Boosters are not approved for use in this aircraft as some may contain additives that can

adversely effect tank and fuel line seals.

3.5.2 Lubricating Oil Capacity 12 quarts recommend 10 quarts Refer to section 8.2 for additional Information

3.6 Power Generation This aircraft is equipped with an automatic secondary alternator system that supplies power to the main instrument bus under the sum of the following conditions.

• The master and alternator switches are on. • The primary alternator is not producing adequate power to keep the battery voltage above 23 volts.

Bottom of page



…Continued • The only indication that this system is active is that an annunciation will be displayed. All systems will

function as normal.

3.7 Other Limitations Smoking in this aircraft is prohibited due to inadequate ventilation at altitude and fuel systems that operate inside the cabin. Noise exceeds 95 dB during normal operation so hearing protection must be worn.

3.8 Placards See Construction Manual for required Placards. Additionally see local regulations for required placarding of experimental aircraft.

Bottom of page



4 WEIGHT AND BALANCE INFORMATION

4.1 C of G Range Range Forward Limit: 86.5in Measured from datum Aft Limit: 94.5in Measured from datum Datum: 51.25in forward of the bottom face of the firewall. Leveling Longitudinal: Spirit level longitudinally placed on the centre carry through spar box. Lateral: Spirit level laterally placed on the centre carry through spar box. Arms Pilot/Copilot: 95.0in Measured from datum Pax1/Pax2: 129.0in Measured from datum Baggage: 140.0in Measured from datum Fuel Station: 94.0in Measured from datum

4.2 Baggage The aircraft has one approved baggage location which is a separate compartment located in the aft section of the aircraft. The maximum allowable baggage weight is 110 lbs. Baggage is restrained using the straps fitted in the baggage area.

4.3 Aircraft Weight Data Max Takeoff and Landing weight: 3,850lb Empty Weight: 2,431lb Useful Load: 1,419lb Max Baggage: 110lb

Bottom of page



4.4 Weight and Balance Sheet ISSUE 2 Lancair IV-P V406 Weighed for FS calculation Orbx Simulation Systems 30-Sep-2010 Weighed with full engine oil and unusable fuel. Aircraft painted and interior fitted, 4 seat configuration. Re-weigh following work as follows:

• Aircraft completed and paintwork finished. • Aircraft completed initial light testing annex. • Aircraft underwent final certification in experimental category.

ITEM NET WT LBS MOM ARM In Moment Empty ARM Port 943 107.8 101655.4

Starboard 943 107.8 101655.4 Nose 545 35.2 19184

Main Gear up Position Shift

68 16 1088

Empty weight, C of G 2431 223583.8 91.52

Measured Stations In Pilot 95.0 Pax 95.0 Fuel 94.0

Rear Seat 129.0 Luggage 140.0

Bottom of page



4.5 Sample Calculation Sheets The following is a sample calculation sheet for a basic load of; full fuel, pilot, copilot and 30 lbs baggage.

Weight X Arm = Moment

Empty

2431

X

91.52

=

222485

Pilot

180

X

95.0

=

17100

Co-Pilot

180

X

95.0

=

17100

Pax 1

0

X

129.0

=

0

Pax 2

0

X

129.0

=

0

Baggage

30

X

140.0

=

4200

Fuel

548

X

94.0

=

51512

Sum of =

3369

312397

Moment divided by

TOW equals CG

Moment

/

TOW

=

CG

312397

/

3369

=

92.7

TOW: 3369 lb Max: 3850 lb CG: 92.7 in MAC: 86.5 - 94.5 in

Bottom of page



…Continued The following is an empty calculation sheet for pilot use.

Weight X Arm = Moment

Empty

2431

X

91.52

=

222485

Pilot

X

95.0

=

Co-Pilot

X

95.0

=

Pax 1

X

129.0

=

Pax 2

X

129.0

=

Baggage

X

140.0

=

Fuel

X

94.0

=

Sum of =

Moment divided by

TOW equals CG

Moment

/

TOW

=

CG

/

=

TOW: __________ lb Max (MTOW): 3850 lb CG: __________ in MAC: 86.5 - 94.5 in

Bottom of page



4.5.1 Calculate Operating C of G To calculate the operating C of G print a copy of the second table provided in section 4.5

• Step 1 Fill in the weight column down to the fuel row. (It is acceptable to use the following convention for estimating weights however it is recommended to use actual measured weights.) -Male adult: 180lb -Female adult: 160lb -Child: 120lb -Infant: 50lb

• Step 2 Multiply weights by arms to fill in the moment column. • Step 3 Add up the weight and moment column to fill in the Sum of = row. • Step 4 Copy the moment sum into the moment position on the last row and copy the weight sum into

the TOW position on the last row. • Step 6 Divide the moment by the TOW to fill in the CG. • Step 7 Ensure that the takeoff weight is less than Max (MTOW) listed at the bottom of the page and

that the CG is within the range (MAC) listed below it and you are ready to fly!

4.5.2 Allowable Load Conditions Allowable load condition is defined by the aircraft falling within the parameters listed in step 7 of section 4.5.1 Operating the aircraft outside this condition is strictly prohibited!

Bottom of page



5 PERFORMANCE

5.1 Takeoff and Landing Distances The following distances are quoted for the aircraft at MTOW, and operating from a sealed runway at sea level in an ICAO standard atmosphere. Take off Distance: 1500 ft (457m) Landing Distance: 2000 ft (610m)

5.2 Rate of Climb Rate of climb at sea level (MTOW) 1500 fpm Rate of climb at sea level (Pilot and fuel) 2000 fpm

5.3 Cruise Speeds/MP/Fuel Consumption/Range The following Charts show how power settings affect fuel consumption range and cruise speeds at different altitudes.

Bottom of page



…Continued

Bottom of page



6 NORMAL PROCEDURES

6.1 General This section describes the required procedures to be adhered to for normal operations of the aircraft These procedures are arranged in an order designed for the most efficient use of this section. Therefore steps should be performed in the order listed unless good reasons exist for deviation. The lists below are designed for the instrument and systems list inherent to this aircraft.

6.2 Speeds for normal operation Unless otherwise stated the following speeds are based on MTOW of 3850lb. Any weight less than this can assume the same speeds. Takeoff (KIAS): Rotate: 70 T.O.S.S: 100 Climb out: 140-150 Climb (KIAS): Initial: 140 Gear Up: 120 Flaps Up: 140 Reroute: 140-150 Landing Approach (KIAS): Circuit: 140 Final (VREF): 100 Go round minimum: 95

6.3 Best angle of climb speed VX Best angle of climb speed (KIAS) 110

6.4 Best rate of climb speed VY Best Rate of climb speed (KIAS) 135

Bottom of page



…Continued

6.5 Preflight inspection Before flight, a careful inspection of the aircraft must be carried out.

1. Fuel

Quantity in both tanks: ………………………………………..CHECK visually (cannot Dip Wing). Fuel Caps: ………………………………………..Secure. Water Check: ………………………………………..Both wing tank drains and fuel bowl drain.

2. Pitot Head/AOA All parts open to air unobstructed: .…………………………..CHECK.

3. Cockpit Ignition Switch: ………………………………………..OFF. Fuel valve: ………………………………………..ON. Master switch: ………………………………………..ON. Fuel: ………………………………………..CHECK contents. Master switch: ………………………………………..OFF. Controls (all): ………………………………………..CHECK free movement. Harness & Seats: ………………………………………..CHECK condition. Windshield: ………………………………………..CHECK cleanliness. Cockpit Area: ………………………………………..CHECK general condition.

Bottom of page



…Continued Loose Objects: ………………………………………..Secure. Cockpit Doors and Latches: ………………………………………..CHECK operation.

4. Main Undercarriage Tires: ………………………………………..CHECK condition/inflation. Brake Pads: ………………………………………..Inspect for wear limit. Wheel well: ………………………………………..CHECK for loose items.

5. Static Source Static Source: ………………………………………..CHECK for obstruction.

6. Empennage Tail Tie Down: ………………………………………..Disconnect. Control Surfaces: ………………………………………..CHECK bearings, security, full movement. Static Wicks: ………………………………………..Attach. Exposed Cables: ………………………………………..CHECK condition. H stab root: ………………………………………..CHECK no cracks. Trim Rods: ………………………………………..CHECK security.

7. Left Wing Wing Tie down: ………………………………………..Remove. Control Surfaces: ………………………………………..CHECK bearings, security, full movement. Flap Tracks: ………………………………………..CHECK cleanliness. Control Rods: ………………………………………..CHECK security. Leading Edges: ………………………………………..CHECK damage. Pitot: ………………………………………..Remove cover.

8. Right Wing Wing Tie down: ………………………………………..Remove. Control Surfaces: ………………………………………..CHECK bearings, security, full movement. Flap Tracks: ………………………………………..CHECK cleanliness. Control Rods: ………………………………………..CHECK security. Leading Edges: ………………………………………..CHECK damage.

9. Nose Propeller and spinner: ………………………………………..CHECK for damage and security. Cowl: ………………………………………..Remove blanks. Cowl: ………………………………………..CHECK security, fasteners. Engine Oil: ………………………………………..CHECK Nose Wheel: ………………………………………..CHECK condition/inflation.

It is recommended also to do a “Pull Through” of the engine before the first start of the day. This is the process of turning the engine over by hand. The compressions of each cylinder will be felt as the engine is rotated as a resistance to pulling. The engine must be rotated through at least 16 compressions.

WARNING Prior to turning the engine by hand the engine must be cold and the ignition switch must be off.

DO NOT pull through a warm engine!

Bottom of page



6.6 Normal Procedures Checklist

6.6.1 Before Start Oxygen: ………………………………………..CHECK quantity Brakes: ………………………………………..SET Circuit Breakers: ………………………………………..SET Gear: ………………………………………..CHECK handle down Fuel Selector: ………………………………………..ON both Mixture: ………………………………………..RICH Throttle: ………………………………………..CRACKED 1-1.5cm Master Switch: ………………………………………..ON Instrument Lights: ………………………………………..AS REQUIRED Navigation Lights: ………………………………………..AS REQUIRED Fuel Pump: ………………………………………..ON check pressure Magneto: ………………………………………..BOTH Area: ………………………………………..CLEAR Start: ………………………………………..ENGAGE

6.6.2 After Start Throttle: ………………………………………..1000RPM Oil Pressure: ………………………………………..GREEN in 30 seconds Alternator: ………………………………………..ON and charge Fuel Pump: ………………………………………..OFF pressure remains in green Suction: ………………………………………..CHECK Avionics Master: ………………………………………..ON Transponder: ………………………………………..STANDBY VFR frequency GNS430s: ………………………………………..ON set COM frequency ADF: ………………………………………..ON Circuit Breakers: ………………………………………..CHECK still set VM1000: ………………………………………..AUTOTRACK

6.6.3 Taxi Brakes : ………………………………………..RELEASE Turn Left and Right: ………………………………………..CHECK compass turn coordinator and HSI Turn Left and Right: ………………………………………..CHECK artificial horizon

6.6.4 Before Takeoff Trim: ………………………………………..SET takeoff back 2 bars Mixture: ………………………………………..RICH Propeller: ………………………………………..FINE Fuel Pressure: ………………………………………..CHECK Fuel: ………………………………………..SELECTOR change tank pump ON Flaps: ………………………………………..CHECK full travel Flaps: ………………………………………..SET 10-15 degrees Instruments: ………………………………………..CHECK left to right

Bottom of page



…Continued Switches: ………………………………………..ON battery alternator mags both Controls: ………………………………………..CHECK full and free Hatches: ………………………………………..CLOSED Harness: ………………………………………..SECURE Door Seal: ………………………………………..ON inflate

6.6.5 Runup Oil Temperature: ………………………………………..100 degrees Power: ………………………………………..1800RPM Mag Drop: ………………………………………..100 or less Mags: ………………………………………..COMPARE difference 0-50 Gauges: ………………………………………..CHECK normal temps and pressures Power: ………………………………………..2000 RPM Propeller: ………………………………………..DROP reduce to 1500 RPM Idle: ………………………………………..CHECK 500-800 RPM Briefing: ………………………………………..EXECUTE passenger and experimental

6.6.6 Lineup Fuel Pump: ………………………………………..ON Switches: ………………………………………..MAGS both strobe ON Transponder: ………………………………………..ALT or ON Pressurization: ………………………………………..SET final cruise altitude Pressurization: ………………………………………..DUMP switch OFF

6.6.7 Takeoff and Climb Power: ………………………………………..FULL Instrument: ………………………………………..CHECK oil and fuel pressure Instrument: ………………………………………..CHECK manifold pressure 38 RPM 2750 Rotate: ………………………………………..70 KIAS Altitude: ………………………………………..100 AGL - GEAR UP Gear: ………………………………………..CHECK transit lights then Off Fuel Pump: ………………………………………..OFF after 700 ft AGL CHECK pressure Flaps: ………………………………………..UP Pressurization: ………………………………………..CHECK increasing Power: ………………………………………..SET manifold pressure 30 RPM 2500 Fuel Pump: ………………………………………..ON above FL100 Trim: ………………………………………..SET as required Mixture: ………………………………………..SET per 2000 ft

6.6.8 Cruise Power Economy: ………………………………………..Manifold pressure 25 RPM 2200 Power Normal: ………………………………………..Manifold pressure 26 RPM 2400 Power Fast: ………………………………………..Manifold pressure 28 RPM 2500 Trim: ………………………………………..SET once at speed

Bottom of page



…Continued Engine: ………………………………………..MONITOR temperatures and pressures

6.6.9 Descent Fuel: ………………………………………..SELECT fullest tank Speed: ………………………………………..CHECK maintain 140-200 KIAS Pressurization: ………………………………………..SET destination altitude Power: ……………………………………….. Manifold pressure 15 propeller FINE Mixture: ………………………………………..RICH below FL100 Fuel Pump: ………………………………………..OFF below FL100

6.6.10 Approach Brakes: ………………………………………..CHECK pressure then handbrake OFF Gear: ………………………………………..DOWN and locked Mixture Propeller: ………………………………………..RICH FINE Fuel Pump: ………………………………………..ON Pressures: ………………………………………..CHECK oil and fuel Hatches: ………………………………………..Secure harness Flaps: ………………………………………..SET as required Lights: ………………………………………..ON as required Speed Reference: ………………………………………..100 KIAS final

6.6.11 Taxi to Parking Flaps: ………………………………………..UP Fuel Pump: ………………………………………..OFF Pressurization: ………………………………………..CHECK 0 differential Pressurization: ………………………………………..SELECT dump ON Door Seal: ………………………………………..Deflate Switches: ………………………………………..OFF strobe, landing light

6.6.12Shutdown Mixture: ………………………………………..CUT

Key: ………………………………………..REMOVE Avionics Master: ………………………………………..OFF Navigation Lights: ………………………………………..OFF as required Alternator: ………………………………………..OFF Master: ………………………………………..OFF Brakes: ………………………………………..SET handbrake

Bottom of page



7 EMERGENCY PROCEDURES

7.1 Speeds for Emergency Operations Maximum Glide ……………………………………….. 140KIAS Landing Without Engine Power ……………………………………….. 115KIAS

7.2 Emergency Procedures Checklist

7.2.1 Engine Failure During Takeoff Run Throttle: ………………………………………..CLOSED Brakes: ………………………………………..APPLY Ignition: ………………………………………..OFF Wing Flaps: ………………………………………..UP Master: ………………………………………..OFF Fuel Selector: ………………………………………..OFF

7.2.2 Engine Failure After Takeoff Airspeed: ………………………………………..140 if possible Gear: ………………………………………..DOWN pump if required Ignition: ………………………………………..OFF If time available Fuel Selector: ………………………………………..OFF If time available Wing Flaps: ………………………………………..HALF Braking: ………………………………………..HEAVY AFTER TOUCHDOWN Master: ………………………………………..OFF

7.2.3 Engine Failure During Flight Below 2000 ft AGL: ………………………………………..LAND (See 7.2.4 or 7.2.5) Above 2000 ft AGL: ………………………………………..RESTART Airspeed: ………………………………………..140 or above Fuel Selector: ………………………………………..ON Fuel Pump: ………………………………………..ON Wing Flaps: ………………………………………..HALF Ignition: ………………………………………..LEFT Propeller: ………………………………………..FINE Throttle: ………………………………………..CRACKED Airspeed: ………………………………………..SLOW until Propeller stops turning Starter: ………………………………………..ENGAGE Repeat: ………………………………………..AS NESSECARY Altitude: ………………………………………..MONITOR if below 2000 ft AGL LAND

Bottom of page



…Continued

7.2.4 Landing Without Engine Power Airspeed: ………………………………………..140 Ignition: ………………………………………..OFF Fuel Selector: ………………………………………..OFF Gear: ………………………………………..DOWN pump if required Flaps: ………………………………………..HALF (Descent) Throttle: ………………………………………..CLOSED Flaps: ………………………………………..FULL (Before Touchdown) Master: ………………………………………..OFF Airspeed: ………………………………………..100 (Last Minute) Braking: ………………………………………..HEAVY AFTER TOUCHDOWN Fires: ………………………………………..CHECK abandon aircraft

7.2.5 Ditching Airspeed: ………………………………………..140 Approach: ………………………………………..INTO WIND (Light Swells) Approach: ………………………………………..PARALLEL TO SWELLS (Heavy Swells) Door: ………………………………………..UNLATCHED, SEAL DEFLATED Ignition: ………………………………………..OFF Gear: ………………………………………..UP Flaps: ………………………………………..HALF (Descent) Throttle: ………………………………………..CLOSED Flaps: ………………………………………..FULL (Before Touchdown) Master: ………………………………………..OFF Airspeed: ………………………………………..75 (Last Minute) Evacuate: ………………………………………..IF REQUIRED BREAK WINDOWS Life Jackets/Raft: ………………………………………..INFLATE PLB: ………………………………………..ACTIVATE

7.2.6 Fire On Ground Fuel: ………………………………………..OFF Fuel Pump: ………………………………………..OFF Abandon Aircraft: Fire: ………………………………………..EXTINGUISH if possible

7.2.7 Engine Fire in flight Throttle: ………………………………………..CLOSED Mixture: ………………………………………..CLOSED Forced Landing: ………………………………………..EXECUTE (See 7.2.4 or 7.2.5)

7.2.8 Cabin Fire in flight Master: ………………………………………..OFF Cabin Heat: ………………………………………..CLOSE Cabin air: ………………………………………..OPEN Extinguisher: ………………………………………..ACTIVATE

Bottom of page



…Continued IF FIRE GOES OUT Ventilate: ………………………………………..Open cabin door slightly < 120 KIAS Land: ………………………………………..As soon as practical IF FIRE DOES NOT GO OUT Land: ………………………………………..IMMEDIATELY

7.2.9 Spins Throttle: ………………………………………..CUT Ailerons: ………………………………………..NEUTRALIZE Rudder: ………………………………………..APPLY full deflection opposite to rotation Elevator: ………………………………………..FOREWARD IF ROTATION STOPS Controls: ………………………………………..NEUTRALIZE rudder and gently recover IF ROTATION DOESN’T STOP Throttle: ………………………………………..GENTLY apply throttle and cut as soon as rotation stops Controls: ………………………………………..NEUTRALIZE rudder and gently recover

Bottom of page



8 AIRCRAFT GROUND HANDLING AND SERVICING

8.1 Fuel

• AVGAS 100LL • AVGAS 100/130 • Octane Boosters are not approved for use in this aircraft as some may contain additives that can adversely effect

tank and fuel line seals.

8.2 Oil

8.2.1 Engine Oil Specs

Approved oils consist of lubricating oils of any brand that conform to specifications MIL-L-6082 for non dispersant mineral oil or MIL-L-22851 for ashless dispersant mineral oil. Some synthetic oils meet MIL-L-22851 requirements however these can reduce engine life.

Non Dispersant Oil must be used for the first 50 hours of operation for a new or overhauled engine, or until the oil consumption has stabilized. After this time Ash less Dispersant oil is recommended.

8.2.2 Engine Oil Viscosity

It is recommended to carefully choose the correct grade of oil by viscosity. This will depend upon the conditions that you operate the aircraft in.

For pressurized operations the flight levels ambient temperatures can easily reach as low as -40 degrees therefore you need to choose an engine oil viscosity of the correct SAE Number. This will likely be at the smaller end of the scale.

Alternatively if you operate only at normal GA altitudes you may want to choose from the high end of the scale.

The following table shows how viscosity should be chosen dependent on AVERAGE ambient temperature.

Average Ambient Temperature Range ⁰C SAE Number 35 and above 60 15 to 35 50 -22 to 25 40 -35 to 20 30 -40 to 10 20

Bottom of page



…Continued

8.3 Brakes

The brakes of the aircraft use aviation grade hydraulic fluid part number MIL-H-5606 or equivalent. The reservoir is located on the engine side of the firewall on the left hand side looking forward. Access the reservoir by removing the top cowl by its fasteners.

8.4 Hydraulics

This aircraft is equipped with electro hydraulically operated flaps and undercarriage. This system uses aviation grade hydraulic fluid part number MIL-H-5606 or equivalent. The reservoir is located behind the rear bulkhead of the baggage compartment. Access to this area is achieved by removing the screwed on panel on the rear face of the baggage floor.

8.5 Tires

Due to the high landing speed of the aircraft tire condition and inflation must be checked before each flight. Any flat spots discovered on a tire are considered an unservicability and the tire should be replaced immediately.

Bottom of page



9 CLIMATIC RESTRICTIONS Maximum Ambient Operating Temperature: 42 ⁰C Flight into known Icing Conditions: Prohibited

9.1 Pressurization Flight above 14,000ft AMSL without pressurization or supplemental Oxygen is prohibited. Operation of the Pressurization system is limited to a maximum cabin differential of 4.7 psi.

9.2 Oxygen This aircraft is equipped with Emergency supplemental oxygen only. In the event of cabin pressurization loss, the supplemental oxygen system can sustain 4 people at continuous operation for a limit of 30 minutes.

9.3 Hypoxia In the event of a cabin pressurization loss without supplemental oxygen a person can suffer from a variety of symptoms that can lead to brain damage and death. The following table shows time that lack of oxygen allows a person to remain conscious dependent on altitude.

Altitude Time of Useful Consciousness 45,000 ft ASL 9-15 seconds 40,000 ft ASL 15-20 seconds 35,000 ft ASL 30-60 seconds 30,000 ft ASL 1-2 minutes 28,000 ft ASL 2-3 minutes 25,000 ft ASL 3-5 minutes 22,000 ft ASL 5-10 minutes 20,000 ft ASL 30 minutes or more,

symptoms of hypoxia will be evident

Bottom of page



10 SUPPLEMENTS This section consists of a series of supplements that are self contained separately indexed publications. Each supplement must be placed after this page and a line generated in the Log of supplements describing its content.

Bottom of page



10.1 Log of Supplements

Document Number Description Date

Bottom of page