G-JONL Pilot Operating Handbookg-jonl.westmorlandaviation.co.uk/Documents/G-JONL Pilot Operating Handbook.pdfSportcruiser G-JONL Pilot Operating Handbook Issue 0.6 Page 1-3 27-Sep-2010

Pilot Operating Handbook

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Registration: G-JONL Serial Number: 338-14889

This aeroplane must be operated in compliance with

information and limitations contained in herein.

This POH must be available on board the aircraft.

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Sportcruiser G-JONL Pilot Operating Handbook

TABLE OF CONTENTS

The first page of each section has a more detailed table of contents for that section.

1 GENERAL INFORMATION........................................................................... 1-1 2 AEROPLANE AND SYSTEMS DESCRIPTION................................................... 2-1 3 OPERATING LIMITATIONS......................................................................... 3-1 4 WEIGHT AND BALANCE ............................................................................ 4-1 5 PERFORMANCE ........................................................................................ 5-1 6 EMERGENCY PROCEDURES........................................................................ 6-1 7 NORMAL PROCEDURES ............................................................................. 7-1 8 AIRCRAFT GROUND HANDLING & SERVICING.............................................. 8-1


Issue 0.6 Page 1-1 27-Sep-2010

1 GENERAL INFORMATION

SECTION INDEX

1.1 Record of revisions ............................................................................ 1-2 1.2 List of effective pages ........................................................................ 1-3 1.3 General............................................................................................ 1-4 1.4 Warnings, cautions and notes ............................................................. 1-4 1.5 Definitions and abbreviations .............................................................. 1-5



1.1 Record of revisions

Issue Pages Reason for revision Date Signature

0.1 All Initial draft 28-Oct-09 JRL

0.2 All Major additions and corrections throughout document

19-Dec-09 JRL

0.3 Various Added BRS documentation and additional electrical systems information

24-Dec-09 JRL

0.4 Various Weight & balance data partly added 12-Mar-10 JRL

0.5 Various Amended BRS documentation to comply with LAA requirements. Added picture of aircraft to cover page. Added instrument panel information. Added further weight & balance data.

05-Apr-10 JRL

0.6 7-5 POH Supplement 03 (Canopy unlatched) added

27-Sep-10 JRL



1.2 List of effective pages (Updated to V0.6 release)

Section Page Date of Issue Section Page Date of Issue

1 1-1 05-Apr-10 5 5-1 05-Apr-10

1-2 05-Apr-10 5-2 05-Apr-10

1-3 05-Apr-10 5-3 05-Apr-10

1-4 05-Apr-10 5-4 05-Apr-10

1-5 05-Apr-10 5-5 05-Apr-10

1-6 05-Apr-10

2 2-1 05-Apr-10

2-2 05-Apr-10

2-3 05-Apr-10

2-4 05-Apr-10

2-5 05-Apr-10

2-6 05-Apr-10

2-7 05-Apr-10 6 6-1 05-Apr-10

2-8 05-Apr-10 6-2 05-Apr-10

2-9 05-Apr-10 6-3 05-Apr-10

2-10 05-Apr-10 6-4 05-Apr-10

2-11 05-Apr-10 6-5 05-Apr-10

2-12 05-Apr-10 6-6 05-Apr-10

2-13 05-Apr-10 6-7 05-Apr-10

2-14 05-Apr-10

2-15 05-Apr-10

2-16 05-Apr-10 7 7-1 05-Apr-10

7-2 05-Apr-10

7-3 05-Apr-10

3 3-1 05-Apr-10 7-4 05-Apr-10

3-2 05-Apr-10 7-5 05-Apr-10

3-3 05-Apr-10 7-6 27-Sep-10

3-4 05-Apr-10 7-7 05-Apr-10

7-8 05-Apr-10

7-9 05-Apr-10

4 4-1 05-Apr-10 8 8-1 05-Apr-10

4-2 05-Apr-10 8-2 05-Apr-10

4-3 05-Apr-10 8-3 05-Apr-10

4-4 05-Apr-10 8-4 05-Apr-10

4-5 05-Apr-10

4-6 05-Apr-10

4-7 05-Apr-10



1.3 General The Sportcruiser is a Light Sport Aircraft designed and built by:

Czech Aircraft Works spol. s.r.o. Na Záhonech č.e. 212 Kunovice, 686 04 Czech Republic

G-JONL was constructed as an LAA kit in the UK by

John Linford Pennine View Sleagill Cumbria CA10 3HD

The Sportcruiser is based on FAA Light Sport Aircraft (LSA) category according to ASTM Standards F2245, F2279 and F 2295.

This Pilot Operating Handbook has been prepared to provide pilots with information for the safe and efficient operation of Sportcruiser. It also contains supplemental data supplied by the Aircraft Flight Training Supplement.

1.4 Warnings, cautions and notes The following definitions apply to warnings, cautions and notes in the Pilot Operating Handbook.

WARNING Means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety i.e. to

injury or death of persons.

CAUTION

Means that the non-observation of the corresponding procedure leads to a minor or possible long term degradation of the flight safety.

NOTE

Draws attention to any special item not directly related to safety but which is important or unusual.



1.5 Definitions and abbreviations

ALT Altitude or Altimeter ATC Air Traffic Control ASI Airspeed Indicator Bar pressure unit 1 bar = 14.5037 PSI BEACON anti-collision beacon °C Temperature in degrees Celsius (1°C = (°F - 32) / 1.8) CAS Calibrated Airspeed CDI Course deviation indicator CHT Cylinder head temperature COMM Communication transceiver EFIS Electronic Flight Instrument System ELT Emergency Locator Transmitter EMS Engine Monitoring System °F Temperature in degree of Fahrenheit (1°F = (°C x 1.8) + 32) ft Foot or feet fpm Vertical speed in feet per minute (1 fpm = 0.0051 m/s) GPS Global Positioning System hp Horse power IAS Indicated Airspeed IC Intercom IFR Instrument Flight Rules in Inch ISA International Standard Atmosphere KCAS Calibrated Airspeed in Knots kg Kilogram KIAS Indicated Airspeed in Knots km kilometre (1 km = 1000 m = 0.54 NM = 0.621 SM) km/h Speed in kilometre per hour (1 km/h = 0.54 knots = 0.621 mph = 0.278 m/s) knot Speed in NM per hour (1 knot = 1.151 mph = 1.852 km/h = 0.514 m/s) kW Kilowatt l Litre lb Pound lbf Pound Foot m Metre mm Millimetre MAC Mean Aerodynamic Chord max. Maximum min. Minimum or minute mph Speed in statute miles per hour (1 mph = 0.87 knots = 1.61 km/h) m/s Speed in meter per second N Newton - force unit NM Nautical Mile OFF System is switched off or control element is in off-position ON System is switched on or control element is in on-position OAT Outside Air Temperature POH Pilot Operating Handbook



psi Pressure unit - pound per square inch (1 PSI = 0.0689 bar) rpm Revolutions per minute s or sec Second SM Statute Mile US gal US gallon 1 US gal = 3.785 litres V Volt VFR Visual Flight Rules VMC Visual Meteorological Conditions VSI Vertical Speed Indicator VTU Vertical tail unit VA Manoeuvring airspeed VFE Maximum flap extended speed VNE Never exceed speed VNO Maximum designed cruising speed VSO Stall speed with wing flaps in extended position VS1 Stall speed with wing flaps in retracted position VX Best angle of climb speed VY Best rate of climb speed



2 AEROPLANE AND SYSTEMS DESCRIPTION

This section provides a description and operation of the aircraft and its systems.

SECTION INDEX

2.1 Aeroplane description ........................................................................ 2-2

2.1.1 Aeroplane dimensions .................................................................. 2-2 2.1.2 Aircraft layout............................................................................. 2-3 2.1.3 Airframe .................................................................................... 2-4 2.1.4 Control system ........................................................................... 2-4 2.1.5 Landing gear .............................................................................. 2-4 2.1.6 Seats and safety harness ............................................................. 2-4 2.1.7 Baggage compartment................................................................. 2-4 2.1.8 Canopy ...................................................................................... 2-5 2.1.9 Pitot - static system..................................................................... 2-5 2.1.10 Cockpit ...................................................................................... 2-5 2.1.11 P1 Instrument panel layout and operational notes ........................... 2-7 2.1.12 P2 Instrument panel layout and operational notes ........................... 2-8 2.1.13 Avionics panel layout and operational notes .................................... 2-9 2.1.14 Intercom/audio/flaps panel layout and operational notes .................2-10 2.1.15 Minimum instruments and equipment list for VFR flights ..................2-11

2.2 Engine ............................................................................................2-12 2.2.1 Coolant.....................................................................................2-12 2.2.2 Throttle and Choke.....................................................................2-12 2.2.3 Carburettor preheating ...............................................................2-13 2.2.4 Heating.....................................................................................2-13 2.2.5 Electrical system ........................................................................2-13

2.3 Propeller .........................................................................................2-14 2.4 Fuel system.....................................................................................2-14 2.5 Oil..................................................................................................2-15 2.6 Operating weights and loading ...........................................................2-16



2.1 Aeroplane description Sportcruiser is an aircraft intended especially for recreational and cross-country flying, non-aerobatics operation.

The Sportcruiser is a single-engine, all metal, low-wing monoplane of semi-monocoque construction with two side-by-side seats. The aeroplane is equipped with a fixed tricycle undercarriage with a castering nose wheel.

2.1.1 Aeroplane dimensions

Wing span 8.81m (28.90 ft)

Length 6.50m (21.33 ft)

Height 2.37m (7.78 ft)

Wing area 12.3m2 (132.3 sq ft)

Wing loading 49kg/m2 (10 lb/sq ft)

Cockpit width 1.17m (46 in)



2.1.2 Aircraft layout



2.1.3 Airframe

The airframe is of all-metal construction, stressed skin, single curvature metal skins riveted to stiffeners. Construction is of 6061-T6 aluminium sheet metal riveted to aluminium angles with Avex rivets. This high strength aluminium alloy construction provides long life and low maintenance costs thanks to its durability and corrosion resistance characteristics.

The wing has a high lift aerofoil equipped with slotted flaps.

2.1.4 Control system

The aeroplane is equipped with a dual stick control and adjustable rudder pedals with pedal hydraulic brakes for easy ground control of the castering nose wheel.

The elevator and aileron trim are electrically actuated by buttons on the control stick. Wing flaps are electrically actuated by the rocker switch located on the middle panel.

Control surface deflection:

Rudder deflections 30° to each side

Elevator deflections + 28°/- 25°

Aileron deflections + 20°/- 15°

Flap deflections 0° to 30°

Aileron trim deflections + 20°/- 20°

Elevator trim deflections + 22°/- 28°

2.1.5 Landing gear

Tricycle landing gear with a castering nose wheel. The main landing gear uses two fibreglass spring elements.

2.1.6 Seats and safety harness

Side-by-side seating. Seat cushions are removable to make cleaning and drying easier. Four point safety belts provided to each seat. Additional seat upholstery to raise the small pilot or move him forward can be the option.

NOTE

Prior to each flight, ensure that the seat belts are firmly secured to the airframe and that the belts are not damaged. The buckle must be adjusted

to the central position of the occupant.

2.1.7 Baggage compartment

The rear baggage compartment is located behind the seats. It may accommodate up to 18kg (40lbs). This space is divided in two sections – forward baggage compartment A, and aft compartment B. Is not recommended place heavy things into baggage compartment B.



Baggage may also be loaded into the baggage compartment inside each wing up to 20kg (44 lbs), in each wing locker.

Make sure that baggage does not exceed maximum allowable weight, and that the aircraft CG is within limits with loaded baggage.

All baggage must be properly secured.

2.1.8 Canopy

Access to the cabin is from both sides. Make sure that the canopy is latched and mechanism is securely locked into position on both sides before operating the aircraft.

2.1.9 Pitot - static system

The Pitot-static tube is located below the left wing. Pressure distribution to the instruments is through flexible plastic hoses.

Keep the Pitot head clean to ensure proper function of the system.

2.1.10 Cockpit

Instruments and Avionics

G-JONL has a comprehensive instrumentation fit. The flight instruments are standard analogue units and the engine management system and instrumentation is of glass cockpit design.

Flight instruments

• Standard six pack comprising

o Air speed indicator

o Attitude indicator

o Altimeter

o Turn coordinator

o Direction indicator

o Vertical speed indicator

• Magnetic compass

Engine management instruments

• Dynon D120 Glass cockpit engine management system

• Separate analogue tachometer

• Separate analogue Hobbs meter

Avionics

• Garmin GTX328 Mode-S transponder

• Garmin SL30 Nav/Com 1 transceiver



o MD106 course deviation indicator (CDI) with glide slope

• SL40 Com 2 transceiver

• PM1000 intercom

• Locally designed and manufactured audio switch panel

• Garmin GPS296/396/496 GPS mount, with external antenna and power

NOTE

For operating instructions refer to the documentation supplied with the instruments

Miscellaneous equipment

• G-205 PTT/trim controls on both P1 and P2 control sticks, providing PTT, aileron and elevator trim from either seat

• Aveoflash wing top navigation/strobe lights

• Dual hydraulic brakes

• External temperature sensor (feeding D120 EMS)

All electrical systems are independently switched and separately protected by manually pop-able circuit breakers. The entire electrical system is energised via a master switch which controls a master solenoid.

NOTE

Small rocker switches are used for control of all power circuits. The circuit is ON when the rocker switch is DOWN, i.e. the lower half of the rocker is

pressed IN



2.1.11 P1 Instrument panel layout and operational notes

Key and notes

1. Air speed indicator 2. Attitude indicator 3. Altimeter 4. Nav (VOR & ILS) Course Deviation Indicator 5. Turn coordinator 6. Directional indicator 7. Vertical speed indicator 8. Alarm indicators

a. EMS – this LED flashes if there is an engine management system alarm. Refer to the D120 EMS display for further information

b. Unsafe – this LED is lit if any of the following conditions apply i. One or both of the magnetos are cut ii. The alternator switch is turned off iii. The alternator is not charging for any other reason

9. Parking brake. Apply both footbrakes and pull this knob to apply parking brake. 10. Master switch. Activates the master solenoid. All electrical systems are dead until

this switch is turned on 11. Alternator switch. Turns the alternator on or off. When the alternator is switched

on, the Master switch cannot be turned off (electrical lock). Turn off both alternator and master to remove all power

12. Magneto A cut switch 13. Magneto B cut switch 14. Starter key switch 15. Avionics power switch 16. Instruments power switch (for flight instruments) 17. Instrument lights switch 18. Navigation lights switch 19. Strobes switch 20. Landing light switch (landing light is not currently installed) 21. Fuel pump switch 22. Carburettor heat. Pull for carb heat



2.1.12 P2 Instrument panel layout and operational notes

Key and notes

1. Engine Management System (D120) display unit. See Pilot’s guide for full information

2. Analogue tachometer (backup for D120 EMS) 3. Hobbs meter 4. Elevator trim position indicator 5. Aileron trim position indicator 6. Cabin heater control. Pull for heat 7. Contact breaker; Flight instruments; CB1; 5 amps 8. Contact breaker; D120 Engine management System; CB2; 2 amps 9. Contact breaker; Nav receiver; CB3; 2 amps 10. Contact breaker; COM 1 transceiver; CB4; 5 amps 11. Contact breaker; COM 2 transceiver; CB5; 5 amps 12. Contact breaker; Transponder; CB6; 5 amps 13. Contact breaker; GPS; CB7; 2 amps 14. Contact breaker; Intercom; CB8; 2 amps 15. Contact breaker; Flaps; CB9; 10 amps 16. Contact breaker; Trimmers; CB10; 5 amps 17. Contact breaker; Navigation lights; CB11; 5 amps 18. Contact breaker; Strobe lights; CB12; 10 amps 19. Contact breaker; Landing light; CB13; 2 amps 20. Contact breaker; 12V accessory outlet; CB14; 20 amps 21. 12V accessory outlet, 20A maximum load



2.1.13 Avionics panel layout and operational notes

Key and notes

1. GPSMap 296 or similar VFR GPS. Power and antenna connections are available at the rear of the unit

2. Combined COM1 and NAV radios (SL30)

3. COM2 radio (SL40)

4. GTX328 transponder


Issue 0.6 Page 2-10 27-Sep-2010

2.1.14 Intercom/audio/flaps panel layout and operational notes

Key and notes

1. Intercom unit. Pilot and passenger have separate volume and squelch controls. Note that the volume controls only affect intercom audio levels, not the radio levels. Adjust the radio volume control as required.

2. Transmit selector switch. Up to transmit on COM1, down to transmit on COM2.

3. Receive selector switches. Set the switch down to enable the audio from the specified radio. Any combination of switch settings is acceptable.

4. Flap control switch.

5. Flap position indicator.


Issue 0.6 Page 2-11 27-Sep-2010

2.1.15 Minimum instruments and equipment list for VFR flights

The following list is the minimum equipment that must be serviceable prior to the commencement of any flight.

• Airspeed indicator • Altimeter • Compass (not required by ASTM F 2245) • Tachometer (RPM). Either the D120 EMS tachometer or the standalone

analogue tachometer meet this requirement • D120 EMS, providing as a minimum the following engine instruments as

required by the engine manufacturer: a. Oil temperature indicator b. Oil pressure indicator c. Cylinder head temperature indicator


Issue 0.6 Page 2-12 27-Sep-2010

2.2 Engine A ROTAX 912 ULS engine 73.5 kW (98.6 hp) is installed in the Sportcruiser. The Rotax 912 ULS is a 4-stroke, 4 cylinder, horizontally opposed, spark ignition engine with one central camshaft-push-rod-OHV. The engine has liquid cooled cylinder heads and ram air cooled cylinders.

Lubrication: Dry sump forced lubrication.

Ignition: Dual contact-less capacitor discharge ignition.

The engine is fitted with an electric starter, AC generator and mechanical fuel pump. Propeller drive is via a reduction gear with integrated shock absorber.

2.2.1 Coolant

(Refer to the ROTAX the Rotax Operator’s manual section 10.1.2 Operating speeds and limits and section 10.2.1 Coolant, Rotax Installation manual section 12 Cooling system, Rotax Service Instruction SI-912-016)

Water-free coolant concentrate can be used based on propylene glycol (refer to ROTAX engine Operator’s Manual-section 10.2.1 and Installation Manual section 11.6.1).

Conventional glycol/water coolant mixture can also be used (refer to ROTAX engine Operator’s Manual section 10.2.1 and Installation Manual section 11.6.2).

WARNING

The coolant concentrate (propylen glycol) must not be mixed with conventional (glycol/water) coolant or with additives.

Non observance can lead to damage to the cooling system and engine.

CAUTION

Conventional glycol/water coolant reduce to apply the maximum permissible cylinder head temperature.

Type of coolant used by aircraft manufacturer:

See section 10 supplement No.2

Coolant liquid volume:

Approximately 2.5 litres (0.7 US gal)

2.2.2 Throttle and Choke

Engine power is controlled by means of the THROTTLE lever with the CHOKE lever which are positioned in the middle channel between the seats side by side. Both levers are mechanically connected (by cable) to the flap on the carburettors. Springs are added to the throttle push rods to ensure that the engine will go to full power if the linkages fail.


Issue 0.6 Page 2-13 27-Sep-2010

2.2.3 Carburettor preheating

Heated air streaming from a heat exchanger to the carburettors through the airbox. The control lever is installed on the P1 instrument panel.

2.2.4 Heating

Heating consists of a heat exchanger on the exhaust manifold and control mechanism located on the right hand side of instrument panel.

CAUTION

Incidents involving exhaust gases entering the heating or ventilation system may result in fatal accidents due to carbon monoxide poisoning of the

aircraft occupants. A carbon monoxide detector is recommended.

2.2.5 Electrical system

Battery

The 12 Volt battery is mounted on the front side of forward bulkhead.

Master switch

The master switch connects the various aircraft electrical systems to the 12 Volt battery via the master solenoid. With the master switch off, power is removed from all electrical systems in the aircraft.

NOTE

Ignition system is independent on the power source and will operate even with Master switch and/or breaker off.

Ignition and starter switches

Both ignition (mag) switches must be on to operate the engine normally. The ignition switches feature a red LED which is illuminated when the associated magneto is disabled. If either magneto is disabled, the Unsafe alarm LED also lights.

The starter motor is actuated by a separate keyswitch. For safety turn both ignition switches off and remove the key when engine is not running.

NOTE

All switches are down for “on”. Engine controls are "push forward" for operation, except the choke, cabin heating and carburettor preheat, which

are "Pull" for "On". Optional equipment, switches and/or circuit breakers are subject to change or installed as requested. See Aircraft Equipment List and Instrument panel layout and Description of equipment and controls in the

cockpit.


Issue 0.6 Page 2-14 27-Sep-2010

Alternator switch

The alternator switch allows the alternator output to be turned on or off. In normal operation the alternator should be on. If the alternator is on and is producing a charging current then an LED in the alternator switch lights. If the alternator switch is turned off then the Unsafe alarm LED is illuminated. If the alternator switch is on but the alternator has failed then the Unsafe alarm LED is illuminated.

CAUTION When the alternator switch is on, the master switch is overridden and the master solenoid will remain engaged regardless of master switch

position. When turning off the master switch you must also turn off the alternator switch.

Services switches

Various aircraft services, such as avionics, instruments, lights, etc. can be separately turned on or off via individual switches. An LED in the switch lights when that service is turned on.

2.3 Propeller The propeller is a standard, fixed three blade, ground adjustable composite propeller type WOODCOMP KLASSIC 170/3/R

NOTE

For technical data refer to documentation supplied by the propeller manufacturer

2.4 Fuel system Wing tanks volume: 2 x 57 litres (2 x 15 US gal)

Each tank is equipped with a vent outlet and finger screen filter.

A drain valve is located in the lowest point of the each tank and on the bottom edge of the firewall, on the gascolator.

Main fuel selector valve is on the central console in the cockpit.

The electric fuel pump is located on the engine side of the firewall.

CAUTION Do not overfill the tanks to avoid fuel overflow through venting tubes.

Recommended fuel type:

(Refer to the ROTAX engine Operator’s Manual-section 10.2.2 and Rotax Service Instruction SI-912-016)

• Minimum RON 95, EN 228 Premium, EN 228 Premium plus or AVGAS100LL


Issue 0.6 Page 2-15 27-Sep-2010

• Fuel according to FAA - Standard Spec. for Automotive Spark Ignition Engine Fuel, ASTM D 4814 or AVGAS 100 LL

• Fuel according to DOT - CAN/CGSB-3.5 Quality 3 min AKI 91 or AVGAS 100 LL

Due to higher lead content in AVGAS, the wear of the valve seats and deposits in the combustion chamber will increase. Therefore, use AVGAS only if you encounter problems with vapour lock or if the other fuel types are not available.

Fuel volume:

Wing fuel tank volume 2 x 57 litres (2 x 15 US gal)

Unusable fuel quantity 2 x 0.9 litres (2 x 0.24 US gal)

2.5 Oil (Refer to engine Operator’s Manual-section 10.2.3 and Rotax Service Instruction SI-912-016)

G-JONL is initially filled with AeroShell Sport Plus 4 Aviation Oil. Other suitable oils include

• Motorcycle 4-stroke engine oil of registered brand with gear additives.

• Use only oil with API classification “SG” or higher.

• Use of multi-grade no mineral oils is recommended.

Type of oil used by aircraft manufacturer:

See section 10 supplement No.2

Oil volume:

Minimum 3.3 litres (0.9 US gal)

Maximum 3.8 litres (1 US gal)


Issue 0.6 Page 2-16 27-Sep-2010

2.6 Operating weights and loading Empty weight (see section 4) 385 kg (847 lbs)

Max. take-off weight 600 kg (1320 lbs)

Max landing weight 600 kg (1320 lbs)

Max. weight of fuel 82 kg (180 lbs)

Max. baggage weight in rear fuselage 18 kg (40 lbs)

Max. baggage weight in each wing locker 20 kg (44 lbs)

WARNING

Do not exceed maximum take-off weight 600 kg (1320 lbs)

Number of seats 2

Minimum crew 1 pilot in the left seat

Minimum crew weigh 43 kg (95 lbs)

Maximum crew weight See section 4



3 OPERATING LIMITATIONS

SECTION INDEX

3.1 Stall speeds at maximum take-off weight ............................................. 3-2 3.2 Flap extended speed range – VS0 to VFE ................................................ 3-2 3.3 Maximum manoeuvring speed - VA ...................................................... 3-2 3.4 Never exceed speed - VNE ................................................................... 3-2 3.5 Maximum structural cruising speed – VNO.............................................. 3-2 3.6 Crosswind and wind limitation............................................................. 3-2 3.7 Service ceiling .................................................................................. 3-2 3.8 Load factor....................................................................................... 3-2 3.9 Prohibited manoeuvres ...................................................................... 3-3 3.10 Engine operating speeds and limits ................................................... 3-3 3.11 Other limitations ............................................................................ 3-4



3.1 Stall speeds at maximum take-off weight

IAS CAS

Altitude loss at

recovery

Conditions: Max. take-off weight Engine: idle

Wing flaps pos-ition

knot km/h mph knot km/h mph ft m

0° 39 72 45 43 80 49 65 20

15° 35 65 40 39 72 45 49 15 Wing level stall

30° 32 59 37 37 69 43 33 10

0° 42 78 48 46 85 53 82 25

15° 38 70 44 42 78 48 66 20 Co-ordinated turn

30° bank

30° 35 65 40 39 72 45 49 15

3.2 Flap extended speed range – VS0 to VFE Flap operating range (IAS): 32 - 75 knots

59 - 139 km/h

37 - 86 mph

3.3 Maximum manoeuvring speed - VA Maximum manoeuvring speed (IAS): 88 knots

163 km/h

101 mph

3.4 Never exceed speed - VNE Never exceed speed (IAS): 138 knots

255 km/h

158 mph

3.5 Maximum structural cruising speed – VNO Maximum structural cruising speed (IAS): 108 knots

200 km/h

124 mph

3.6 Crosswind and wind limitation Maximum permitted head wind velocity for take-off and landing 24kts (12 m/s)

Maximum permitted cross wind velocity for take-off and landing 12kts (5 m/s)

3.7 Service ceiling Service ceiling 10,000ft (3,000 m)

3.8 Load factor Maximum positive limit load factor +4 g



Maximum negative limit load factor - 2 g

3.9 Prohibited manoeuvres

WARNING AEROBATICS AND INTENTIONAL SPINS ARE PROHIBITED

The Sportcruiser is approved for normal flying and the following manoeuvres:

• Steep turns not exceeding 60° bank

• Lazy eights

• Chandelles

• Stalls (except whip stalls)

3.10 Engine operating speeds and limits

Engine Model: ROTAX 912 ULS

Engine Manufacturer: Bombardier-Rotax GMBH

Max Take-off: 73.5 kW (98.6 hp) at 5800 rpm, max. 5 min.

Max. Continuous: 69 kW (92.5 hp) at 5500 rpm

Po

wer

Cruising: 53 kW (71 hp) at 4800 rpm

Max. Take-off: 5800 rpm, max. 5 min.

Max. Continuous: 5500 rpm

Cruising: 4800 rpm En

gin

e

RP

M

Idling: ~1400 rpm

Minimum: 50° C (122° F)

Maximum: 120 / 135 ° C (248 / 275 ° F) *

Cylin

der

head

te

mp

era

ture

Optimum: 75 - 110° C (167 - 230° F)

Minimum: 50° C (122° F)

Maximum: 130° C (266° F) Oil

te

mp

era

ture

Optimum: 90 - 110° C (194 - 230° F)

Minimum: 0.8 bar (12 psi) - below 3500 rpm

Maximum: 7 bar (102 psi) - cold engine starting Oil

p

ress

ure

:

Optimum: 2 - 5 bar (29 - 73 psi) - above 3500 rpm

* see the Rotax Operator’s manual section 10.1.2 Operating speeds and limits and section 10.2.1 Coolant, Rotax Installation manual section 12 Cooling system, Rotax



Service Instruction SI-912-016, POH section 2.2 Coolant and section 10.2 Supplement No.2 Type of coolant used in engine.

3.11 Other limitations • No smoking on board the aircraft • Day VFR flights only permitted

WARNING IFR FLIGHTS AND INTENTIONAL FLIGHTS UNDER ICING CONDITIONS

ARE PROHIBITED

Flight in rain

When flying in the rain, no additional steps are required. Aircraft qualities and performance are not substantially changed. However VMC must be maintained.



4 WEIGHT AND BALANCE

This section contains weight and balance records and the payload range for safe operating of Sportcruiser.

SECTION INDEX

4.1 Installed equipment list...................................................................... 4-2 4.2 Centre of gravity (CG) range and determination .................................... 4-3

4.2.1 Weight & balance report – definitions............................................. 4-4 4.2.2 Empty weight CG check ............................................................... 4-4 4.2.3 Weight & balance report – Forward CG check .................................. 4-6 4.2.4 Weight & balance report – Aft CG check ......................................... 4-7



4.1 Installed equipment list

Equipment description Model number, etc.

Engine Rotax 912ULS with airbox

Propeller Woodcomp Klassic 170/3/R

Ballistic Recovery System Ballistic Recovery Systems Inc BRS-6 1350

Air speed indicator

Attitude indicator

Altimeter

Course Deviation indicator Garmin MD102

Turn coordinator

Direction indicator

Vertical speed indicator

Engine management system Dynon D120

Analogue tachometer Rotax

Hobbs meter

Nav and Com 1 transceiver Garmin SL30

Com 2 transceiver Garmin SL40

Mode-S transponder Garmin GTX328

Holder for GPSMap 296/396/496 GPS Air Gizmo

Intercom PS Engineering PM1000

Audio selector panel Designed & built by builder

Antennas for all radio systems

Wingtip strobe/navigation lights Aveoflash



4.2 Centre of gravity (CG) range and determination

Centre of gravity (CG)

Operating CG range 27% to 38% of MAC

405 to 570 mm (16 to 22.5 in) aft of datum (AOD)

Determination of CG

Weight and Balance report lists:

- Empty CG check

- Forward CG check



4.2.1 Weight & balance report – definitions

Horizontal datum: Bottom edge of canopy frame.

4.2.2 Empty weight CG check

Aircraft weighed 12-Mar-2010

ITEM

WEIGHT

[kg]

ARM

[mm]

MOMENT

(WEIGHT x ARM)

RIGHT MAIN WHEEL

WR= 149 LR= 784 116,032

LEFT MAIN WHEEL

WL= 148 LL= 784 116,816

NOSE WHEEL WN= 88 LN= -736

negative arm -64,768

AIR

CR

AFT E

MP

TY

C

G

COMPUTED CG EMPTY

Empty Weight:

WE=385 kg

CGE= 437 mm

Aircraft moment:

ME=168,080



Empty weight CG check (cont.)

WEIGHT

[kg]

ARM

[mm]

MOMENT

(WEIGHT x ARM)

AIRCRAFT WE=385 CGE=437 ME=168080

PILOT 0 700 0 PASSENGER 0 700

BAGGAGE COMPARTMENT 0 1600

WING LOCKERS 0 600

ZERO FUEL TOTAL

WZF = 385 CGZF=437 MZF =168080

FUEL TANKS 0 180

TOTAL WT = 385 MT = 168080

Take-Off Weight

385kg

CG= 437mm

Max.Take-off Weight: 600 kg

Date: 12-Mar-2010

By: Planeweighs

Maximum useful weight

W Max Useful = W Max Take-off – WEmpty W Max Useful = 600kg – 385kg = 215kg

This maximum useful weight must not be exceeded.



4.2.3 Weight & balance report – Forward CG check

WEIGHT

[kg]

ARM

[mm]

MOMENT

(WEIGHT x ARM)


PILOT 85 700 59500 PASSENGER 0 700

BAGGAGE COMPARTMENT 0 1600

WING LOCKERS 0 600

FUEL 82 180 14742

TOTAL WT = 552 MT = 242322

Take-Off Weight

552kg

CG= 439mm


Date: 12-Mar-2010

By: Planeweighs

ITEM

WEIGHT

[kg]

ARM

[mm]

MOMENT

(WEIGHT x ARM)

RIGHT MAIN WHEEL

WR= 149 LR= 784 116,032

LEFT MAIN WHEEL

WL= 148 LL= 784 116,816



AIR

CR

AFT E

MP

TY

C

G

COMPUTED CG EMPTY

Empty Weight:

WE=385 kg

CGE= 437 mm

Aircraft moment:

ME=168,080



4.2.4 Weight & balance report – Aft CG check

WEIGHT

[kg]

ARM

[mm]

MOMENT

(WEIGHT x ARM)


PILOT 85 700 59500 PASSENGER 85 700 59500

BAGGAGE COMPARTMENT 18 1600 28800

WING LOCKERS 0 600

FUEL 27 180 4860

TOTAL WT = 600 MT = 320740

Take-Off Weight

600kg

CG= 535mm


Date: 12-Mar-2010

By: Planeweighs

ITEM

WEIGHT

[kg]

ARM

[mm]

MOMENT

(WEIGHT x ARM)

RIGHT MAIN WHEEL

WR= 149 LR= 784 116,032

LEFT MAIN WHEEL

WL= 148 LL= 784 116,816



AIR

CR

AFT E

MP

TY

C

G

COMPUTED CG EMPTY

Empty Weight:

WE=385 kg

CGE= 437 mm

Aircraft moment:

ME=168,080



5 PERFORMANCE

The following data have been computed from actual flight tests with the aircraft and engine in good conditions and using average piloting techniques.

If not stated otherwise, the performance stated in this section is valid for maximum take-off weight and under ISA conditions.

The performance shown in this section is valid for aircraft fitted with given engine ROTAX 912 ULS 73.5 kW (98.6 hp) with WOODCOMP Klassic 170/3/R propeller.

SECTION INDEX

5.1 Take-off and landing distances ............................................................ 5-2 5.2 Rate of climb .................................................................................... 5-2 5.3 Cruise speeds ................................................................................... 5-3 5.4 Fuel consumption .............................................................................. 5-4 5.5 Airspeed indicator system calibration ................................................... 5-5



5.1 Take-off and landing distances

Take-off distances

Take-off run distance Take-off distance over 50

ft (15 m) obstacle Runway type [ft] [m] [ft] [m]

CONCRETE 328 100 820 250

GRASS 361 110 918 280

Landing distances

Landing distance over 50 ft (15 m) obstacle

Landing run distance (braked) Runway type

[ft] [m] [ft] [m]

CONCRETE 591 180 180 55

GRASS 558 170 197 60

5.2 Rate of climb

Best rate of climb speed (IAS)

Rate of climb Vz

Conditions: Max.continuous power: 5500 rpm Weight: 600 kg (1320 lbs) knot km/h mph fpm m/s

0 ft ISA 65 120 75 1200 6.1

3000 ft ISA 65 120 75 850 4.3

6000 ft ISA 60 110 70 550 2.8

9000 ft ISA 55 100 63 315 1.6



5.3 Cruise speeds

Altitude Engine speed

IAS CAS

ft RPM kts MPH kts MPH

4200 77 89 77 89

4500 86 99 85 98

4800 95 109 93 107

5000 101 116 98 113

5300 110 116 98 113

5500 116 133 111 128

1000

5800 125 143 119 137

4200 75 86 75 86

4500 83 96 82 94

4800 92 106 90 104

5000 97 112 95 109

5300 106 122 103 118

5500 112 129 108 124

3000

5800 120 139 116 133

4200 72 83 72 83

4500 80 92 79 91

4800 88 101 86 99

5000 94 108 92 106

5300 102 117 99 114

5500 107 124 104 120

5000

5800 116 134 112 129

4200 69 79 70 80

4500 77 88 77 88

4800 84 97 83 96

5000 90 103 88 101

5300 97 112 95 109

5500 103 118 100 115

7000

5800 111 127 107 123

4200 65 75 66 76

4500 73 84 73 84

4800 80 93 80 93

5000 86 98 84 97

5300 93 107 91 104

5500 98 112 95 109

9000

5800 105 121 102 117



5.4 Fuel consumption

The table below shows fuel consumption, endurance and range

Altitude [ft ISA] 3000

[litres] 112 Usable fuel quantity [US gal] 29.5

Engine speed [rpm] 4200 4500 4800 5000 5300 5500

[l/h] 11.5 14 16.5 18.5 21 23 Fuel

consumption [US gal/h] 3.04 3.7 4.36 4.89 5.55 6.08

[knot] 75 83 92 97 106 112 IAS

[mph] 86 96 106 112 122 129

[knot] 75 82 90 95 103 108

Airsp

eed

CAS [mph] 86 94 104 109 119 124

Endurance [hh:mm] 9:49 08:04 06:51 06:06 05:23 04:55

[NM] 737 662 616 580 554 530 Range

[SM] 845 759 712 666 635 609



5.5 Airspeed indicator system calibration

IAS CAS IAS CAS IAS CAS km/h KNOTS MPH

55 64 30 35 35 41 60 68 35 39 40 45 70 77 40 44 45 49 80 86 45 48 50 54 90 95 50 53 55 58 100 104 55 57 60 63 110 113 60 62 65 67 120 122 65 66 70 72 130 131 70 71 75 76 140 140 75 75 80 81 150 149 80 79 85 85 160 158 85 84 90 89 170 167 90 88 95 94 180 176 95 93 100 98 190 185 100 97 105 103 200 194 105 102 110 107 210 203 110 106 115 112 220 212 115 111 120 116 230 221 120 115 125 121 240 230 125 120 130 125 250 239 130 124 135 130 255 243 135 129 140 134

140 133 145 139 150 143 155 148 160 152



6 EMERGENCY PROCEDURES

This section provides checklists and amplified procedures for coping with various emergencies that may occur. Emergencies caused by aircraft or engine malfunction are extremely rare if proper pre-flight inspections and maintenance are practiced.

However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem.

SECTION INDEX

6.1 Engine failure ................................................................................... 6-2

6.1.1 Engine failure during take-off run .................................................. 6-2 6.1.2 Engine failure after take-off (EFATO).............................................. 6-2 6.1.3 Engine failure in flight .................................................................. 6-2

6.2 In-flight engine starting ..................................................................... 6-3 6.3 Smoke and Fire................................................................................. 6-3

6.3.1 Fire on ground at engine start....................................................... 6-3 6.3.2 Fire during take-off...................................................................... 6-3 6.3.3 Fire in flight................................................................................ 6-4 6.3.4 Fire in the cockpit........................................................................ 6-4

6.4 Glide ............................................................................................... 6-4 6.5 Landing emergencies ......................................................................... 6-5

6.5.1 Emergency landing ...................................................................... 6-5 6.5.2 Precautionary landing .................................................................. 6-5 6.5.3 Landing with a flat tyre ................................................................ 6-5 6.5.4 Landing with a defective landing gear ............................................ 6-6

6.6 Recovery from unintentional spin ........................................................ 6-6 6.7 Other emergencies ............................................................................ 6-7

6.7.1 Vibration .................................................................................... 6-7 6.7.2 Carburettor icing ......................................................................... 6-7



6.1 Engine failure 6.1.1 Engine failure during take-off run

1. Throttle - idle

2. Magneto switches - switch off

3. Apply brakes

6.1.2 Engine failure after take-off (EFATO)

1. Speed - gliding at 60 knots (110 km/h, 70 mph)

2. Altitude - below 150 ft (50m): land in take-off direction over 150 ft (50m) : choose a landing area

3. Wind - find direction and velocity

4. Landing area - choose free area without obstacles

5. Flaps - extend as necessary

6. Fuel Selector - close

7. Ignition switch - switch off

8. Safety harness - tighten

9. Master switch - switch off before landing

10. Land

6.1.3 Engine failure in flight

1. Push control stick forward

2. Speed - gliding at 60 knots (110 km/h, 70 mph)

3. Height - below 150 ft (50m): land in take-off direction over 150 ft (50m): choose a landing area

4. Wind - find direction and velocity

5. Landing area - choose free area without obstacles



8. Ignition switch - switch off


10. Master switch - switch off before landing

11. Land



6.2 In-flight engine starting 1. Switches - switch off unnecessary electrical equipment

2. Master switch - switch on

3. Fuel Selector - turn on (to tank with more quantity of fuel)

4. Throttle - idle

5. Electric pump - switch on

6. Magneto switches - both on (red lights out)

7. Starter switch - hold activated to start the engine

8. After engine starting - electric pump - switch off other switches - switch on as necessary

6.3 Smoke and Fire

6.3.1 Fire on ground at engine start


2. Throttle - full power


4. Leave the aeroplane

5. Extinguish fire by fire extinguisher or call for a fire-brigade if you cannot do it.

6.3.2 Fire during take-off

1. Speed - 60 knots (110 km/h, 70 mph)

2. Heating - close




6. Land, stop and leave the aeroplane

7. Extinguish fire by fire extinguisher or call for a fire-brigade if you cannot do it.



6.3.3 Fire in flight

1. Heating - close



4. Master switch - switch off

5. Magneto switches - switch off after the fuel in carburettors is consumed and engine shut down

6. Choose landing area - heading to the nearest airport or choose emergency landing area

7. Emergency landing - perform according to 6.5.1

8. Leave the aeroplane

9. Extinguish fire by yourself or call for a fire-brigade if you cannot do it.

NOTE Estimated time to pump fuel out of carburettors is 30 sec.

WARNING Do not attempt to re-start the engine!

6.3.4 Fire in the cockpit


2. Heating - close

3. Use the fire extinguisher

6.4 Glide An example of the use of gliding is in the case of engine failure

1. Speed - recommended gliding speed 60 knots (110 km/h, 70 mph)



6.5 Landing emergencies 6.5.1 Emergency landing

Emergency landings are generally carried out in the case of engine failure and the engine cannot be re-started.

1. Speed - adjust for optimum gliding 60 knots (110 km/h, 70 mph)

2. Trim - adjust



5. COMM - if installed then report your location if possible




9. Perform approach without steep turns and land on chosen landing area.

6.5.2 Precautionary landing

A precautionary landing is generally carried out in the cases where the pilot may be disorientated, the aircraft has no fuel reserve or possibly in bad weather conditions.

1. Choose landing area, determine wind direction

2. Report your intention to land and land area location if a COMM is installed in the aeroplane.

3. Perform low-altitude passage into wind over the right-hand side of the chosen area with flaps extended as needed and thoroughly inspect the landing area.

4. Perform circle pattern.

5. Perform approach at increased idling with flaps fully extended.

6. Reduce power to idle when flying over the runway threshold and touch-down at the very beginning of the chosen area.

7. After stopping the aeroplane switch off all switches, close the fuel selector, lock the aeroplane and seek for assistance.

NOTE Watch the chosen area steadily during precautionary landing.

6.5.3 Landing with a flat tyre

1. During landing keep the damaged wheel above ground as long as possible using the ailerons control

2. Maintain the direction on the landing roll out, applying rudder control.



6.5.4 Landing with a defective landing gear

1. If the main landing gear is damaged, perform touch-down at the lowest practicable speed and if possible, maintain direction during landing run.

2. If the nose wheel is damaged perform touch-down at the lowest practicable speed and hold the nose wheel above the ground by means of the elevator control as long as possible.

6.6 Recovery from unintentional spin

WARNING Intentional spins are prohibited!

There is no an uncontrollable tendency of the aeroplane to enter into a spin provided the normal piloting techniques are used.

Unintentional spin recovery technique:

1. Throttle - idle

2. Lateral control - ailerons neutralized

3. Rudder pedals - full opposite rudder

4. Rudder pedals - neutralize rudder immediately when rotation stops

5. Longitudinal control - neutralise or push forward and recovery dive.

6.7 Use of Ballistic Recovery System (BRS) The BRS is intended for use in last resort situations where the aircraft has become fundamentally un-flyable. Examples include major structural failures or serious damage to flying surfaces, such that there is no prospect of controlled flight.

Use of the BRS will almost certainly result in sufficient damage to the airframe that the aircraft will be written off.

To activate the BRS:

1. Throttle - idle

2. Ignition switches - both off

3. Harnesses - tight

4. BRS - remove safety pin from activation handle

5. BRS - pull activation handle fully out (approx 5cm)



Other emergencies 6.7.1 Vibration

If any forced aircraft vibrations appear, it is necessary:

1. To set engine speed to such power rating where the vibrations are lowest.

2. To land on the nearest airfield or to perform a precautionary landing according to 6.5.2.

6.7.2 Carburettor icing

The carburettor icing shows itself through a decrease in engine power and an increase of engine temperatures.

To recover the engine power, the following procedure is recommended:

1. Carburettors heating - open

2. Throttle - set to 1/3 of power

3. Speed - min. 76 knots (140 km/h, 87mph)

4. Leave the icing area - as soon as possible

5. Engine power - increase gradually

If you fail to recover the engine power, land on the nearest airfield (if possible) or depending on the circumstances, perform a precautionary landing according to 6.5.2

NOTE Use carburettors heating during long descents and in areas of possible carburettors icing. Remember: Aircraft is approved to

operate in VMC conditions only.



7 NORMAL PROCEDURES

This section provides checklists and recommended procedures for normal operation of the aircraft.

SECTION INDEX

7.1 Pre-flight check................................................................................. 7-2 7.1.1 Inspection checklist ..................................................................... 7-3

7.2 Engine starting ................................................................................. 7-4 7.2.1 Before engine starting.................................................................. 7-4 7.2.2 Engine starting ........................................................................... 7-4 7.2.3 Engine warm up, Engine check...................................................... 7-4

7.3 Taxiing ............................................................................................ 7-5 7.4 Normal Take-off ................................................................................ 7-5

7.4.1 Before take-off............................................................................ 7-5 7.4.2 Take-off ..................................................................................... 7-5

7.5 Climb............................................................................................... 7-6 7.5.1 Best angle of climb speed (Vx) ...................................................... 7-6 7.5.2 Best rate of climb speed (Vy) ........................................................ 7-7

7.6 Cruise.............................................................................................. 7-7 7.7 Descend........................................................................................... 7-7 7.8 Approach ......................................................................................... 7-7 7.9 Normal landing ................................................................................. 7-7

7.9.1 Before landing ............................................................................ 7-7 7.9.2 Landing ..................................................................................... 7-7 7.9.3 After landing............................................................................... 7-7 7.9.4 Engine shutdown......................................................................... 7-8

7.10 Short field take-off and landing procedures........................................ 7-8 7.11 Balked landing procedures............................................................... 7-8 7.12 Aircraft parking and tie-down........................................................... 7-9



7.1 Pre-flight check Carry out the pre-flight inspection every day prior to the first flight or after aeroplane assembly. Incomplete or careless inspection can cause an accident. Carry out the inspection following the instructions in the Inspection Check List.

NOTE The word "condition" in the instructions means a visual

inspection of surface for damage deformations, scratching, chafing, corrosion or other damages, which may lead to flight

safety degradation.

The manufacturer recommends carrying out the pre-flight inspection as follows:



7.1.1 Inspection checklist

− Magneto switches - OFF − Master switch - ON − Fuel gauge ind. - check fuel quantity − Master switch - OFF − Avionics - check condition − Control system - visual inspection, function, clearance,

free movement up to stops - check wing flaps operation

− Canopy - condition of attachment, cleanness − Check cockpit for loose objects

− Engine cowling condition − Propeller and spinner condition − Engine mount and exhaust manifold condition − Oil and coolant quantity check − Visual inspection of the fuel and electrical system − Fuel system draining − Other actions according to the engine manual

− Wing surface condition − Leading edge condition − Pitot head condition

− Wing tip - surface condition, attachment − Aileron - surface condition, attachment,

clearance, free movement − Wing flap - surface condition, attachment,

clearance − Landing gear - wheel attachment, brakes,

condition and pressure of tyres − Wing lower surface and fuselage bottom condition

− Vertical tail unit - condition of surface, attachment, free movement, rudder stops

− Horizontal tail unit - condition of surface, attachment, free movement, elevator stops

− The checks on the left side the fuselage and wing are the same as right side

WARNING Physically check the fuel level before each takeoff to make sure

you have sufficient fuel for the planned flight.

CAUTION In case of long-term parking it is recommended to turn the engine several times (Magneto switches OFF!) by turning the propeller.

Always handle by palm the blade area i.e. do not grasp only the blade edge. It will facilitate engine starting.



7.2 Engine starting 7.2.1 Before engine starting

1. Control system - free, full & correct movement

2. Aileron and elevator trims - full movement, set to neutral

3. Flaps - full movement, set as required for takeoff

4. Canopy - clean


6. Brakes - fully applied

7.2.2 Engine starting

Start the engine according to its manual procedure

1. Master switch - switch on

2. Fuel Selector - turn on (left or right fuel tank)

3. Choke (cold engine) - pull to open and gradually release after engine start

4. Electrical fuel pump - switch on

5. Both Magnetos - on

6. Ignition switch - turn clockwise to start the engine

7. After engine has started - instruments - switch on - elec. pump - switch off - avionics - switch on - other switches - switch on as necessary

CAUTION The starter should be activated for a maximum of 10 sec., followed by

a 2 min. pause for starter motor cooling. As soon as engine runs, adjust the throttle to achieve smooth running at approx. 2500 rpm. Check the oil pressure, which should increase within 10 sec. Increase the engine speed after the oil pressure has

reached 2 bars (29 psi) and is steady. To avoid shock loading, start the engine with the throttle lever set for idling or 10 % open at maximum, then wait 3 sec. to reach constant

engine speed before new acceleration. Only one magneto should be toggled off/on at a time during ignition

magneto checks.

7.2.3 Engine warm up, Engine check

Prior to engine check block the main wheels using chocks.

Initially warm up the engine to 2000 rpm for approximately 2 min., then continue to 2500 rpm till oil temperature reaches 50°C (122°F).



The warm up period depends on ambient air temperature.

Check both ignition circuits at 4000 rpm for Rotax 912 ULS. The engine speed drop during the time either magneto switched off should not exceed 300 rpm. The maximum engine speed drop difference between circuits A and B should be 120 rpm.

NOTE Only one magneto should be switched on (off) during

ignition magneto check

Set maximum power for verification of maximum speed with given propeller and engine parameters (temperatures and pressures).

Check acceleration from idling to maximum power. If necessary, cool the engine at 3000 rpm before shut down.

CAUTION The engine check should be performed with the aircraft heading

upwind and not on loose terrain (the propeller may suck grit which can damage the leading edges of blades).

7.3 Taxiing Apply power and brakes as needed. Apply brakes to control movement on ground. Taxi carefully when wind velocity exceeds 20 knots. Hold the control stick in neutral position.

7.4 Normal Take-off 7.4.1 Before take-off

1. Altimeter - set

2. Trim - set neutral position

3. Control system - check free movement

4. Cockpit canopy - closed and locked. Check that the canopy is locked by pushing up on the canopy.


6. Fuel Selector - turn on (left or right fuel tank)

7. Ignition switch - switched on (both magnetos)

8. Wing flaps - extend as necessary

7.4.2 Take-off

1. Brakes - apply to stop wheel rotation

2. Take-off power - throttle fully forward (maximum 5800 rpm for maximum 5 min.)

3. Engine speed - check rpm



4. Instruments within limits - check

5. Brakes - release

6. Nose wheel unstick - 32 knots (60 km/h, 37 mph)

7. Aeroplane lift-off - 42 knots (78 km/h, 48 mph)

8. Transit to climb - after reaching airspeed 65 knots (120 km/h, 75 mph

9. Wing flaps - retract at safe altitude (maximum airspeed for flaps use is 75 knots, 139 km/h, 86 mph)

WARNING The Take-off is prohibited if:

The engine is running unsteadily The engine instruments values are beyond operational limits

The crosswind velocity exceeds permitted limits (see 3.6)

7.5 Climb

1. Throttle - max. take-off power (max. 5800 rpm for max. 5 min.) - max. continuous power (5500 rpm)

2. Airspeed - Vx = 60 knots (110 km/h, 70 mph) - Vy = 65 knots (120 km/h, 75 mph)

3. Trim - trim the aeroplane

CAUTION Pitch trim is powerful and fast acting.

Expect high stick forces when excessively out of trim.

4. Instruments - oil temperature, oil pressure and CHT within limits

CAUTION If the cylinder head temperature or oil temperature approach their limits, reduce the climb angle to decrease airspeed and thus remain

within the limits.

7.5.1 Best angle of climb speed (Vx)

60 knots (110 km/h, 70 mph)



7.5.2 Best rate of climb speed (Vy)

65 knots (120 km/h, 75 mph)

7.6 Cruise Refer to section 5 for recommended cruising figures

7.7 Descend Optimum glide speed - 60 knots (110 km/h, 70 mph)

7.8 Approach Approach speed - 60 knots (110 km/h, 70 mph)

1. Throttle - as necessary


3. Trim - as necessary

CAUTION It is not advisable to reduce the engine throttle control lever to

minimum on final approach and when descending from very high altitude. In such cases the engine becomes under-cooled and a loss of power may occur. Descent at increased idle (approx. 3000 rpm), speed between 65-76 knots (120-140 km/h, 75-87mph) and check that the

engine instruments indicate values within permitted limits.

7.9 Normal landing 7.9.1 Before landing

1. Throttle - as necessary

2. Airspeed - 60 knots (110 km/h, 70 mph)


4. Trim - as necessary

7.9.2 Landing

1. Throttle - idle

2. Touch-down on main wheels

3. Apply brakes (after nose wheel touch-down) - as necessary

7.9.3 After landing

1. Throttle - engine rpm set as required for taxiing

2. Wing flaps - retract



3. Trim - set neutral position

7.9.4 Engine shutdown & BRS security

1. Throttle - idle

2. Instruments - engine instruments within limits

3. Switches - switch off except Instrument and Master

4. Magneto switches - off

5. Instruments - switch off



CAUTION Rapid engine cooling should be avoided during operation. This

happens, above all, during aircraft descent, taxiing, low engine rpm or at engine shutdown immediately after landing.

Under normal conditions the engine temperatures stabilize during descent, taxiing and at values suitable to stop engine by switching the ignition off. If necessary, cool the engine at 3000 rpm to stabilize the

temperatures prior to engine shut down.

7.10 Short field take-off and landing procedures None

7.11 Balked landing procedures 1. Throttle - max. take-off power

(max. 5800 rpm for max. 5 min.)

2. Passing to climb - after reaching 65 knots (120 km/h, 75 mph)

3. Trim - adjust as necessary

4. Wing flaps - retract at safe altitude

(max. airspeed for flaps using is 70 knots, 130 km/h, 81 mph)

5. Trim - adjust as necessary

6. Repeat circle pattern



7.12 Aircraft parking and tie-down 1. Magneto switches - OFF

2. Master switch - OFF

3. Fuel selector - close

4. Parking brake - use it as necessary

5. Canopy - close, lock as necessary

6. Secure the aircraft

NOTE It is recommended to use parking brake (if installed) for short-time

parking only, between flights during a flight day. After ending the flight day or at low temperatures of ambient air, do not use parking brake, but

use the wheel chocks instead.

NOTE Use anchor eyes on the wings and fuselage rear section to fix the

aeroplane. Move control stick forward and fix it together with the rudder pedals. Make sure that the cockpit canopy is properly closed and locked.

The anchoring before leaving the aeroplane is important if the aeroplane is not equipped with a parking brake.



8 AIRCRAFT GROUND HANDLING & SERVICING

This section contains factory-recommended procedures for proper ground handling and servicing of the aeroplane. It also identifies certain inspection and maintenance requirements, which must be followed if the aeroplane is to retain that new-plane performance and dependability.

SECTION INDEX

8.1 Servicing fuel, oil and coolant ............................................................. 8-2 8.2 Towing and tie-down instructions ........................................................ 8-2

8.2.1 Towing....................................................................................... 8-2 8.2.2 Tie down.................................................................................... 8-2 8.2.3 Parking ...................................................................................... 8-2 8.2.4 Jacking ...................................................................................... 8-3 8.2.5 Road transport............................................................................ 8-3 8.2.6 Cleaning and care ....................................................................... 8-3

8.3 Assembly and Disassembly ................................................................. 8-4 8.4 Aircraft inspection periods .................................................................. 8-4 8.5 Aircraft alterations or repairs .............................................................. 8-4



8.1 Servicing fuel, oil and coolant See appropriate chapters in the ROTAX engine Maintenance and Operator’s manuals and Sportcruiser Aircraft Maintenance and Inspection Procedures.

8.2 Towing and tie-down instructions 8.2.1 Towing

To handle the aircraft on ground use the Tow Bar, or the fuselage rear pushed down in the place of a bulkhead.

CAUTION Avoid excessive pressure at the aircraft airframe, especially around

control surfaces. Keep all safety precautions, especially in the propeller area.

8.2.2 Tie down

The aircraft should be moored when parked outside a hangar after the flight day. Tying down is necessary to protect the aeroplane against possible damage caused by wind and gusts.

For this reason the aircraft is equipped with tie down eyes located on the lower surfaces of the wings.

Tie down procedure:

1. Check: Fuel Selector close, Master switch and other switches switched off, Ignition switch switched off.

2. Fix the hand control using e.g. safety harness

3. Ensure that the BRS safety pin is installed in the handle

4. Close air vent

5. Close and lock canopy

6. Tie down the aircraft to the ground by means of a rope passed through the tie down eyes located on the lower surfaces of the wings and below rear fuselage.

NOTE In the case of long term parking, especially during winter, it is

recommended to cover the cockpit canopy or possibly the whole aircraft by means of a suitable tarpaulin attached to the airframe.

8.2.3 Parking

It is advisable to park the aircraft inside a hangar or alternatively inside any other suitable space (garage) with stable temperature, good ventilation, low humidity and dust-free environment.



It is necessary to moor the aircraft when it is parked outside a hangar. Also when parking for a long time, cover the cockpit canopy, possibly the whole aircraft by means of a suitable tarpaulin.

8.2.4 Jacking

Since the empty weight of this aircraft is relatively low, two people can lift the aircraft easily.

First of all prepare two suitable supports to support the aircraft.

It is possible to lift the aircraft by handling the following parts:

• By pushing the fuselage rear section down in the place of a bulkhead the fuselage front section may be raised and then supported under the firewall.

• By holding the fuselage rear section under a bulkhead the fuselage rear may be raised and then supported under that bulkhead.

• To lift up a wing, push from underneath that wing only at the main spar area. Do not lift up a wing by handling the wing tip.

8.2.5 Road transport

The aircraft may be transported after loading on a suitable car trailer. It is necessary to dismantle the wings before road transport. The aircraft and dismantled wings should be attached securely to protect these parts against possible damage.

8.2.6 Cleaning and care

Use efficient cleaning detergents to clean the aircraft surface. Oil spots on the aircraft surface (except the canopy!) may be cleaned with petrol.

The canopy may only be cleaned by washing it with a sufficient quantity of lukewarm water and an adequate quantity of detergents. Use either a soft, clean cloth sponge or deerskin. Then use suitable polishers to clean the canopy.

CAUTION Never clean the canopy under “dry” conditions and never use petrol or

chemical solvents!

Upholstery and covers may be removed from the cockpit, brushed and eventually washed in lukewarm water with an adequate quantity of detergents. Dry the upholstery thoroughly before insertion into the

cockpit.

CAUTION In the case of long term parking, cover the canopy to protect the

cockpit interior from direct sunshine.



8.3 Assembly and Disassembly Refer to the Sportcruiser Maintenance and Inspection Procedures and the Sportcruiser Aircraft Assembly photo manual.

8.4 Aircraft inspection periods Periods of overall checks and contingent maintenance depends on the condition of the operation and on overall condition of the aeroplane.

Inspections and revisions should be carried out in the following periods, at least:

after the first 25 flight hours

after every 50 flight hours

after every 100 flight hours or at least annual inspection

Refer to the Engine Operator's Manual for engine maintenance.

Maintain the propeller according to its manual.

All repairs and maintenance should be made in accordance with AC 43.13-1B.

8.5 Aircraft alterations or repairs It is recommended to contact the aircraft manufacturer prior to any alternations to the aircraft to ensure that the airworthiness of the aircraft is not violated. Always use only the original spare parts produced by the aeroplane (engine, propeller) manufacturer.

If the aircraft weight is affected by that alternation, a new weighing is necessary, then record the new empty weight into the Weight and Balance record / Permitted payload range and up-date the placard showing weights in the cockpit


Issue 0.1 Page A 28-Oct-2009