Pilot Operating Handbook

Transcription

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3 Registration: G-JONL Serial Number: 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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5 TABLE OF CONTENTS The first page of each section has a more detailed table of contents for that section. 1 GENERAL INFORMATION AEROPLANE AND SYSTEMS DESCRIPTION OPERATING LIMITATIONS WEIGHT AND BALANCE PERFORMANCE EMERGENCY PROCEDURES NORMAL PROCEDURES AIRCRAFT GROUND HANDLING & SERVICING

6 1 GENERAL INFORMATION SECTION INDEX 1.1 Record of revisions List of effective pages General Warnings, cautions and notes Definitions and abbreviations Issue 0.6 Page Sep-2010

7 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 0.3 Various Added BRS documentation and additional electrical systems information 19-Dec-09 JRL 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 POH Supplement 03 (Canopy unlatched) added 05-Apr-10 JRL 27-Sep-10 JRL Issue 0.6 Page Sep-2010

8 1.2 List of effective pages (Updated to V0.6 release) Section Page Date of Issue Section Page Date of Issue Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Sep Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr Apr-10 Issue 0.6 Page Sep-2010

9 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, 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 This 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. Issue 0.6 Page Sep-2010

10 1.5 Definitions and abbreviations ALT Altitude or Altimeter ATC Air Traffic Control ASI Airspeed Indicator Bar pressure unit 1 bar = 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 = 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 = SM) km/h Speed in kilometre per hour (1 km/h = 0.54 knots = mph = m/s) knot Speed in NM per hour (1 knot = mph = km/h = 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 NM OFF ON OAT POH Newton - force unit Nautical Mile System is switched off or control element is in off-position System is switched on or control element is in on-position Outside Air Temperature Issue 0.6 Page Sep-2010

11 psi Pressure unit - pound per square inch (1 PSI = bar) rpm Revolutions per minute s or sec Second SM Statute Mile US gal US gallon 1 US gal = litres V Volt VFR Visual Flight Rules VMC Visual Meteorological Conditions VSI Vertical Speed Indicator VTU Vertical tail unit V A Manoeuvring airspeed V FE Maximum flap extended speed V NE Never exceed speed V NO Maximum designed cruising speed V SO Stall speed with wing flaps in extended position V S1 Stall speed with wing flaps in retracted position V X Best angle of climb speed Best rate of climb speed V Y Issue 0.6 Page Sep-2010

12 2 AEROPLANE AND SYSTEMS DESCRIPTION This section provides a description and operation of the aircraft and its systems. SECTION INDEX 2.1 Aeroplane description Aeroplane dimensions Aircraft layout Airframe Control system Landing gear Seats and safety harness Baggage compartment Canopy Pitot - static system Cockpit P1 Instrument panel layout and operational notes P2 Instrument panel layout and operational notes Avionics panel layout and operational notes Intercom/audio/flaps panel layout and operational notes Minimum instruments and equipment list for VFR flights Engine Coolant Throttle and Choke Carburettor preheating Heating Electrical system Propeller Fuel system Oil Operating weights and loading Issue 0.6 Page Sep-2010

13 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 semimonocoque construction with two side-by-side seats. The aeroplane is equipped with a fixed tricycle undercarriage with a castering nose wheel Aeroplane dimensions Wing span 8.81m (28.90 ft) Length 6.50m (21.33 ft) Height 2.37m (7.78 ft) Wing area 12.3m 2 (132.3 sq ft) Wing loading 49kg/m 2 (10 lb/sq ft) Cockpit width 1.17m (46 in) Issue 0.6 Page Sep-2010

14 2.1.2 Aircraft layout Issue 0.6 Page Sep-2010

15 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 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 / Landing gear Tricycle landing gear with a castering nose wheel. The main landing gear uses two fibreglass spring elements 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 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. Issue 0.6 Page Sep-2010

16 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 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 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 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 Issue 0.6 Page Sep-2010

17 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 Issue 0.6 Page Sep-2010

18 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 Issue 0.6 Page Sep-2010

19 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 V accessory outlet, 20A maximum load Issue 0.6 Page Sep-2010

20 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 Sep-2010

21 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 Sep-2010

22 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 Sep-2010

23 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 Coolant (Refer to the ROTAX the Rotax Operator s manual section Operating speeds and limits and section Coolant, Rotax Installation manual section 12 Cooling system, Rotax Service Instruction SI ) Water-free coolant concentrate can be used based on propylene glycol (refer to ROTAX engine Operator s Manual-section and Installation Manual section ). Conventional glycol/water coolant mixture can also be used (refer to ROTAX engine Operator s Manual section and Installation Manual section ). 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) 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 Sep-2010

24 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 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 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 Sep-2010

25 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 and Rotax Service Instruction SI ) Minimum RON 95, EN 228 Premium, EN 228 Premium plus or AVGAS100LL Issue 0.6 Page Sep-2010

26 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 Unusable fuel quantity 2 x 57 litres (2 x 15 US gal) 2 x 0.9 litres (2 x 0.24 US gal) 2.5 Oil (Refer to engine Operator s Manual-section and Rotax Service Instruction SI ) 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 Sep-2010

27 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 Issue 0.6 Page Sep-2010

28 3 OPERATING LIMITATIONS SECTION INDEX 3.1 Stall speeds at maximum take-off weight Flap extended speed range V S0 to V FE Maximum manoeuvring speed - V A Never exceed speed - V NE Maximum structural cruising speed V NO Crosswind and wind limitation Service ceiling Load factor Prohibited manoeuvres Engine operating speeds and limits Other limitations Issue 0.6 Page Sep-2010

29 3.1 Stall speeds at maximum take-off weight Conditions: Max. take-off weight Engine: idle Wing flaps position IAS CAS Altitude loss at recovery knot km/h mph knot km/h mph ft m Wing level stall Co-ordinated turn 30 bank Flap extended speed range V S0 to V FE Flap operating range (IAS): knots km/h mph 3.3 Maximum manoeuvring speed - V A Maximum manoeuvring speed (IAS): 88 knots 163 km/h 101 mph 3.4 Never exceed speed - V NE Never exceed speed (IAS): 138 knots 255 km/h 158 mph 3.5 Maximum structural cruising speed V NO 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 Issue 0.6 Page Sep-2010

30 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: Engine Manufacturer: Max Take-off: ROTAX 912 ULS Bombardier-Rotax GMBH 73.5 kw (98.6 hp) at 5800 rpm, max. 5 min. Power Engine RPM Max. Continuous: Cruising: Max. Take-off: Max. Continuous: Cruising: Idling: 69 kw (92.5 hp) at 5500 rpm 53 kw (71 hp) at 4800 rpm 5800 rpm, max. 5 min rpm 4800 rpm ~1400 rpm Cylinder head temperature Oil temperature Minimum: 50 C (122 F) Maximum: 120 / 135 C (248 / 275 F) * Optimum: C ( F) Minimum: 50 C (122 F) Maximum: 130 C (266 F) Optimum: C ( F) Oil pressure: Minimum: Maximum: Optimum: 0.8 bar (12 psi) - below 3500 rpm 7 bar (102 psi) - cold engine starting 2-5 bar (29-73 psi) - above 3500 rpm * see the Rotax Operator s manual section Operating speeds and limits and section Coolant, Rotax Installation manual section 12 Cooling system, Rotax Issue 0.6 Page Sep-2010

31 Service Instruction SI , POH section 2.2 Coolant and section 10.2 Supplement No.2 Type of coolant used in engine 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. Issue 0.6 Page Sep-2010

32 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 Centre of gravity (CG) range and determination Weight & balance report definitions Empty weight CG check Weight & balance report Forward CG check Weight & balance report Aft CG check Issue 0.6 Page Sep-2010

33 4.1 Installed equipment list Equipment description Engine Propeller Ballistic Recovery System Model number, etc. Rotax 912ULS with airbox Woodcomp Klassic 170/3/R Ballistic Recovery Systems Inc BRS Air speed indicator Attitude indicator Altimeter Course Deviation indicator Garmin MD102 Turn coordinator Direction indicator Vertical speed indicator Engine management system Analogue tachometer Dynon D120 Rotax Hobbs meter Nav and Com 1 transceiver Com 2 transceiver Mode-S transponder Holder for GPSMap 296/396/496 GPS Intercom Audio selector panel Garmin SL30 Garmin SL40 Garmin GTX328 Air Gizmo PS Engineering PM1000 Designed & built by builder Antennas for all radio systems Wingtip strobe/navigation lights Aveoflash Issue 0.6 Page Sep-2010

34 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 Issue 0.6 Page Sep-2010

35 4.2.1 Weight & balance report definitions Horizontal datum: Bottom edge of canopy frame Empty weight CG check ITEM WEIGHT [kg] ARM [mm] MOMENT (WEIGHT x ARM) AIRCRAFT EMPTY CG RIGHT MAIN WHEEL LEFT MAIN WHEEL NOSE WHEEL W N = 88 COMPUTED CG EMPTY Aircraft weighed 12-Mar-2010 W R = 149 L R = ,032 W L = 148 L L = ,816 Empty Weight: W E =385 kg L N = -736 negative arm CG E = 437 mm -64,768 Aircraft moment: M E =168,080 Issue 0.6 Page Sep-2010

36 Empty weight CG check (cont.) WEIGHT [kg] ARM [mm] MOMENT (WEIGHT x ARM) AIRCRAFT W E =385 CG E =437 M E = PILOT PASSENGER BAGGAGE COMPARTMENT WING LOCKERS ZERO FUEL TOTAL W ZF = 385 CG ZF =437 M ZF = FUEL TANKS TOTAL W T = 385 M T = Take-Off Weight Max.Take-off Weight: 600 kg 385kg CG= 437mm Date: By: 12-Mar-2010 Planeweighs Maximum useful weight W Max Useful = W Max Take-off W Empty W Max Useful = 600kg 385kg = 215kg This maximum useful weight must not be exceeded. Issue 0.6 Page Sep-2010

37 4.2.3 Weight & balance report Forward CG check ITEM WEIGHT [kg] ARM [mm] MOMENT (WEIGHT x ARM) AIRCRAFT EMPTY CG RIGHT MAIN WHEEL LEFT MAIN WHEEL NOSE WHEEL W N = 88 COMPUTED CG EMPTY W R = 149 L R = ,032 W L = 148 L L = ,816 Empty Weight: W E =385 kg L N = -736 negative arm CG E = 437 mm -64,768 Aircraft moment: M E =168,080 WEIGHT [kg] ARM [mm] MOMENT (WEIGHT x ARM) AIRCRAFT W E =385 CG E =437 M E = PILOT PASSENGER BAGGAGE COMPARTMENT WING LOCKERS FUEL TOTAL W T = 552 M T = Take-Off Weight Max.Take-off Weight: 600 kg 552kg CG= 439mm Date: By: 12-Mar-2010 Planeweighs Issue 0.6 Page Sep-2010

38 4.2.4 Weight & balance report Aft CG check ITEM WEIGHT [kg] ARM [mm] MOMENT (WEIGHT x ARM) AIRCRAFT EMPTY CG RIGHT MAIN WHEEL LEFT MAIN WHEEL NOSE WHEEL W N = 88 COMPUTED CG EMPTY W R = 149 L R = ,032 W L = 148 L L = ,816 Empty Weight: W E =385 kg L N = -736 negative arm CG E = 437 mm -64,768 Aircraft moment: M E =168,080 WEIGHT [kg] ARM [mm] MOMENT (WEIGHT x ARM) AIRCRAFT W E =385 CG E =437 M E = PILOT PASSENGER BAGGAGE COMPARTMENT WING LOCKERS FUEL TOTAL W T = 600 M T = Take-Off Weight Max.Take-off Weight: 600 kg 600kg CG= 535mm Date: By: 12-Mar-2010 Planeweighs Issue 0.6 Page Sep-2010

39 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 Rate of climb Cruise speeds Fuel consumption Airspeed indicator system calibration Issue 0.6 Page Sep-2010

40 5.1 Take-off and landing distances Take-off distances Runway type Landing distances Take-off distance over 50 Take-off run distance ft (15 m) obstacle [ft] [m] [ft] [m] CONCRETE GRASS Runway type Landing distance over 50 ft (15 m) obstacle Landing run distance (braked) [ft] [m] [ft] [m] CONCRETE GRASS Rate of climb Conditions: Max.continuous power: 5500 rpm Best rate of climb speed (IAS) Rate of climb Vz Weight: 600 kg (1320 lbs) knot km/h mph fpm m/s 0 ft ISA ft ISA ft ISA ft ISA Issue 0.6 Page Sep-2010

41 5.3 Cruise speeds Engine Altitude IAS CAS speed ft RPM kts MPH kts MPH Issue 0.6 Page Sep-2010

42 5.4 Fuel consumption The table below shows fuel consumption, endurance and range Altitude [ft ISA] 3000 Usable fuel [litres] 112 quantity [US gal] 29.5 Engine speed [rpm] Fuel consumption [l/h] [US gal/h] Airspeed IAS CAS [knot] [mph] [knot] [mph] Endurance [hh:mm] 9:49 08:04 06:51 06:06 05:23 04:55 Range [NM] [SM] Issue 0.6 Page Sep-2010

43 5.5 Airspeed indicator system calibration IAS CAS IAS CAS IAS CAS km/h KNOTS MPH Issue 0.6 Page Sep-2010

44 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 Engine failure during take-off run Engine failure after take-off (EFATO) Engine failure in flight In-flight engine starting Smoke and Fire Fire on ground at engine start Fire during take-off Fire in flight Fire in the cockpit Glide Landing emergencies Emergency landing Precautionary landing Landing with a flat tyre Landing with a defective landing gear Recovery from unintentional spin Other emergencies Vibration Carburettor icing Issue 0.6 Page Sep-2010

45 6.1 Engine failure Engine failure during take-off run 1. Throttle - idle 2. Magneto switches - switch off 3. Apply brakes 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 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 6. Flaps - extend as necessary 7. Fuel Selector - close 8. Ignition switch - switch off 9. Safety harness - tighten 10. Master switch - switch off before landing 11. Land Issue 0.6 Page Sep-2010

46 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 Fire on ground at engine start 1. Fuel Selector - close 2. Throttle - full power 3. Magneto switches - switch off 4. Leave the aeroplane 5. Extinguish fire by fire extinguisher or call for a fire-brigade if you cannot do it Fire during take-off 1. Speed - 60 knots (110 km/h, 70 mph) 2. Heating - close 3. Fuel Selector - close 4. Throttle - full power 5. Magneto switches - switch off 6. Land, stop and leave the aeroplane 7. Extinguish fire by fire extinguisher or call for a fire-brigade if you cannot do it. Issue 0.6 Page Sep-2010

47 6.3.3 Fire in flight 1. Heating - close 2. Fuel Selector - close 3. Throttle - full power 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 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! Fire in the cockpit 1. Master switch - switch off 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) Issue 0.6 Page Sep-2010

48 6.5 Landing emergencies 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 3. Safety harness - tighten 4. Flaps - extend as necessary 5. COMM - if installed then report your location if possible 6. Fuel Selector - close 7. Magneto switches - switch off 8. Master switch - switch off 9. Perform approach without steep turns and land on chosen landing area 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 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. Issue 0.6 Page Sep-2010

49 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) Issue 0.6 Page Sep-2010

50 Other emergencies 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 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 NOTE Use carburettors heating during long descents and in areas of possible carburettors icing. Remember: Aircraft is approved to operate in VMC conditions only. Issue 0.6 Page Sep-2010

51 7 NORMAL PROCEDURES This section provides checklists and recommended procedures for normal operation of the aircraft. SECTION INDEX 7.1 Pre-flight check Inspection checklist Engine starting Before engine starting Engine starting Engine warm up, Engine check Taxiing Normal Take-off Before take-off Take-off Climb Best angle of climb speed (V x ) Best rate of climb speed (V y ) Cruise Descend Approach Normal landing Before landing Landing After landing Engine shutdown Short field take-off and landing procedures Balked landing procedures Aircraft parking and tie-down Issue 0.6 Page Sep-2010

52 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: Issue 0.6 Page Sep-2010

53 7.1.1 Inspection checklist Magneto switches Master switch Fuel gauge ind. Master switch Avionics Control system Canopy - OFF - ON - check fuel quantity - OFF - check condition - visual inspection, function, clearance, free movement up to stops - check wing flaps operation - 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. Issue 0.6 Page Sep-2010

54 7.2 Engine starting 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 5. Safety harness - tighten 6. Brakes - fully applied 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 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 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). Issue 0.6 Page Sep-2010

55 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 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. 5. Safety harness - tighten 6. Fuel Selector - turn on (left or right fuel tank) 7. Ignition switch - switched on (both magnetos) 8. Wing flaps - extend as necessary 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 Issue 0.6 Page Sep-2010

56 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 rpm for max. 5 min.) - max. continuous power (5500 rpm) 2. Airspeed - V x = 60 knots (110 km/h, 70 mph) - V y = 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 Best angle of climb speed (V x ) 60 knots (110 km/h, 70 mph) Issue 0.6 Page Sep-2010

57 7.5.2 Best rate of climb speed (V y ) 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 2. Wing flaps - extend 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 rpm), speed between knots ( km/h, 75-87mph) and check that the engine instruments indicate values within permitted limits. 7.9 Normal landing Before landing 1. Throttle - as necessary 2. Airspeed - 60 knots (110 km/h, 70 mph) 3. Wing flaps - extend as necessary 4. Trim - as necessary Landing 1. Throttle - idle 2. Touch-down on main wheels 3. Apply brakes (after nose wheel touch-down) - as necessary After landing 1. Throttle - engine rpm set as required for taxiing 2. Wing flaps - retract Issue 0.6 Page Sep-2010