AEROPRAKT-22LS Pilot Operating Handbook

7.2 Installed equipment list .......................................................................................... 26 8 Airplane and Systems Descriptions ......................................................................... 28 8.1 General.................................................................................................................. 28 8.2 Airframe ................................................................................................................. 28 8.3 Landing gear ......................................................................................................... 29 8.4 Engine and its controls .......................................................................................... 29 8.5 Propeller ................................................................................................................ 29 8.6 Fuel system ........................................................................................................... 30 8.7 Airplane control systems ....................................................................................... 32 8.8 Instrument panel.................................................................................................... 39 8.9 Full and static pressure system ............................................................................. 41 8.10 Electrical system ................................................................................................... 42 8.11 Seats and harness belts ........................................................................................ 49 8.12 Cockpit doors ........................................................................................................ 49 8.13 Baggage container ................................................................................................ 49 9 Aircraft Ground Handling and Servicing .................................................................. 50 9.1 Introduction............................................................................................................ 50 9.2 Towing, parking and tie-down instructions ............................................................ 50 9.3 Servicing fuel, oil and coolant................................................................................ 50 9.4 Approved fuel and oil............................................................................................. 51 9.5 Cleaning and care ................................................................................................. 51 9.6 Disassembling and assembling the airplane ......................................................... 51 10 Supplements ............................................................................................................... 54 10.1 General.................................................................................................................. 54 10.2 Engine manual ...................................................................................................... 54 10.3 Avionics and special engine instruments .............................................................. 54 10.4 Recovery system ................................................................................................... 54 10.5 Floats..................................................................................................................... 54 10.6 List of installed equipment ..................................................................................... 55 10.7 Actual empty weight and CG position data ........................................................... 56 10.8 Airplane Flight Training Supplement ..................................................................... 57 10.9 Airplane Owner Feedback to Manufacturer........................................................... 60 10.10 Glider and banner towing ................................................................................. 61 AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 5 1 Introduction This Pilot Operating Handbook has been prepared to provide the airplane owner and operators with information required for the safe and efficient operation of this airplane. The following ASTM standards have been and/or shall be used for the design, construction and continued airworthiness of this Aeroprakt-22LS (A-22LS) airplane: F2245-16c Standard Specification for Design and Performance of a Light Sport Airplane, F3198-18 Standard Specification for Light Sport Aircraft Manufacturer’s Continued Operational Safety (COS) Program, F2339-17 Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft, F2506-13 Standard Specification for Design and Testing of Light Sport Aircraft Propellers, F2746-14 Standard Specification for Pilot's Operating Handbook (POH) for Light Sport Airplane, F2972-15 Standard Specification for Light Sport Aircraft Manufacturer’s Quality Assurance System. This A-32 airplane was manufactured by: AEROPRAKT Manufacturing Sp. z o.o.. Address: ul. Zadziele 10. 32-406 Zakliczyn, POLAND Tel.: +48 602 215854 E-mail: aleksander.opoczynski@aeroprakt.pl Should the original manufacturer of the aircraft loose its ability to support this aircraft make and model, contact: ULTRASPORT LTDA Dennis Long 65 Country Place Oakland, TN. USA Aeroprakt.usa@gmail.com +1 901-356-5175 AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 6 2 General information 2.1 General description of the airplane AEROPRAKT-22LS (A-22LS) is a two-seat, high-wing strut braced monoplane of "classic" aerodynamic layout with closed cockpit, non-retractable landing gear with steerable nose wheel, Rotax-912-iS engine with tractor three-blade on-ground adjustable pitch propeller. AEROPRAKT-22LS is approved for flying in VFR, simple meteorological conditions. AEROPRAKT-22LS is certified in the LSA (Light Sport Airplane) category. 2.2 Airplane specifications Specification US units Metric Wing span 31 ft 4 in 9.55 m Wing area 136 sq. ft 12.62 m² Length 20 ft 5 in 6.23 m Height 8 ft 2 in 2.47 m Wheel base 4 ft 2 in 1.26 m Wheel track 5 ft 7 in 1.71 m Gross weight (Maximum Take-Off Weight, MTOW) 1320 lb 600 kg Top speed at sea level, ISA conditions (with wheels landing gear) 114 mph 183 km/h Cruising speed at 1000 ft, ISA conditions, and engine RPM: 4000 68 mph 110 km/h 4600 92 mph 148 km/h 4800 97 mph 156 km/h 5000 100 mph 161 km/h 5200 104 mph 167 km/h Range with full tanks (with 2x45 l tanks, 30 min. reserve) at 1000 ft, ISA conditions, 4000 RPM (with wheels landing gear) 609 mi 981 km Best angle of climb speed (VX), IAS 56 mph 90 km/h Best rate of climb speed (VY), IAS 62 mph 100 km/h Stalling speed at MTOW, flaps up (VS), IAS 48 mph 77 km/h Stalling speed at MTOW, full flaps (VS0), IAS 37 mph 60 km/h Maximum engine power at 5800 RPM (5 minutes limit) 100 hp 73.5 kW Total fuel capacity (standard tanks) 23.8 US gal 90 l Usable fuel (standard tanks) 23.3 US gal 88 l Total fuel capacity (optional tanks) 30.1 US gal 114 l Usable fuel (optional tanks) 29.6 US gal 112 l Approved fuel types: see paragraph 3.6 AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 7 3 Limitations 3.1 Airspeeds and Airspeed Indicator markings Scheme of color markings of airspeed indicator is shown on Fig. 1. Explanations are given in the table below: Marking IAS value or range Significance km/h mph kts White arc start 60 37 32 Stalling speed at maximum takeoff weight with full flaps (VS0) Green arc start 77 48 42 Stalling speed at maximum takeoff weight with flaps up (VS) White arc 60-148 37-92 32-80 Flap extended speed range (VS0 to VFE) Green arc 77-168 48-104 42-90 Normal operating range (VS to VO) Green arc end - Yellow arc start 168 104 90 Operating maneuvering speed (VO) at gross weight and minimum weight Yellow arc 168-229 104-142 90-124 Maneuvers must be conducted with caution and only in smooth air (VO to VNE) Red line 229 142 124 Maximum speed for all operations (VNE) Fig. 1 AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 8 3.2 Service ceiling Service ceiling of A-22LS with Rotax-912iS Sport (100 hp) engine is equal to at least 5000 m (16 000 ft). However A-22LS has neither pressurized cockpit, no oxygen equipment and therefore may not be used for high-altitude flight. 3.3 Maneuvering load factors Limit load factors for the airplane at gross weight of 600 kg (1320 lb) are as follows: Maximum positive limit load factor +4.0 Maximum negative limit load factor -2.0 3.4 Approved maneuvers A-22LS airplane belongs to a non-aerobatic category. All maneuvers shall be done within its airspeed and maneuvering load factor limits (G limits). Approved maneuvers include: - turns with bank angles up to 60°, - side-slipping with angles up to 15°, - level and accelerated stalls without spinning, - diving at a speed below VNE of 229 km/h (142 mph, 124 kts) IAS. Any aerobatics including intentional spinning is prohibited! 3.5 Fuel capacity and type standard optional Capacity of tanks: 2×45 l (2×11.9 US gal) 2×57 l (2×15.05 US gal) Total fuel capacity: 90 l (23.8 US gal) 114 l (30.1 US gal) Total usable fuel: 88 l (23.3 US gal) 112 l (29.6 US gal) Non-usable fuel: 2 l (0.5 US gal) 2 l (0.5 US gal) Approved fuel types: see table in paragraph 3.6 Engine. NOTE: The readings of the fuel level indicators have to be read as follows (for both standard and optional fuel tanks): «F» — 42 l (11.1 US gal); «3/4» — 32 l (8.4 US gal); «1/2» — 21 l (5.5 US gal); «1/4» — 14 l (3.7 US gal); «E» — 4.5 l (1.2 US gal); «LOW FUEL» lamp is ON — less than 4.5 l (1.2 US gal). AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 9 3.6 Engine This aircraft is equipped with a four-cylinder four-stroke Rotax-912iS Sport (100 hp) combined cooling engine produced by BRP-Powertrain GmbH&Co. KG. (Austria). The engine is has the flat-four layout, dry sump lubrication system with a separate oil tank of 3 l (0.8 US gal) capacity, automatic valve clearance adjustment, integrated gearbox of 2.43 reduction ratio and fully redundant electronic engine management system (EMS) which includes fuel injection, ignition, etc. All engine systems (fuel, electrical, cooling) are assembled in accordance with Rotax-912i SERIES engine operation and installation manuals. Engine data and operational limitations are given in the table below: Engine manufacturer BRP-Rotax GmbH & Co KG (Austria) Engine model Rotax-912iS Sport Engine type Flat-four, four-stroke Take-off performance 73.5 kW (100 h.p.) Max. continuous performance 72 kW (97.9 h.p.) Take-off speed 5800 rpm (max. 5 minutes) Max. continuous speed 5500 rpm Idle speed min. 1400 rpm Oil pressure, maximum minimum normal 7 bar (102 psi) (for a short period at cold start) 0,8 bar (12 psi) (below 3500 RPM) 2,0 to 5,0 bar (29-73 psi) (above 3500 RPM) Oil temperature, maximum minimum normal 130 °C (266 °F) 50 °C (120 °F) 90-110 °C (190-230 °F) Exhaust gas temperature max. 950 °C (1742 °F) Coolant temperature (coolant exit temperature) max. 120 °C (248 °F) Engine start, operating temperature max. 50 °C (120 °F) (ambient temperature) min. -25 °C (-13 °F) (oil temperature) Fuel pressure, minimum maximum 2.8 bar (41 psi) 3.2 bar (46 psi) Acceptable fuel pressure exceedance (max. 3 sec.)1 2.5 bar (36 psi) 3.5 bar (51 psi) Fuel antiknock properties min. RON 95 (min. AKI 912) European standard of fuel EN 228 super, EN 228 super plus Aviation Standard of fuel AVGAS 100 LL (ASTM D910) Oil specification Use only oil with Rotax norm RON 424 classification NOTE: On all issues of engine operation see Rotax engine Operator's Manual. Follow its instructions to ensure safe and efficient operation of the engine. 1 Fuel pressure exceedance only allowed after power setting change 2 Anti-Knock Index (RON+MON)/2 AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 10 3.7 Kinds of operation limits This aircraft is approved for flying day and night, VFR, simple meteorological conditions. Flight into icing conditions is prohibited. 3.8 Crosswind limitation Maximum crosswind component for A-22LS airplane is 7 m/s (14 kts). It is highly recommended to choose upwind direction for takeoff and landing with the least crosswind. It will significantly shorten takeoff and landing distances and increase degree of safety. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 11 4 Emergency procedures 4.1 General This section contains recommendations to the pilots in case of emergency in flight. However, such situations, caused by airframe or engine malfunction are extremely rare provided that pre-flight inspections and checks are performed regularly. 4.2 Emergency checklists 4.2.1 Engine fire during start 1. Throttle – IDLE. 2. Lane A and B – OFF. 3. Fuel pumps 1 and 2 – OFF. 4. Unfasten seat belts, abandon cockpit. 5. Take measures to extinguish the fire. 4.2.2 Engine failure during take-off 4.2.2.1 during takeoff roll 1. Throttle – IDLE. 2. Lane A and B – OFF. 3. Fuel pumps 1 and 2 – OFF. 4. Brakes – APPLY as necessary. 4.2.2.2 immediately after takeoff 1. Direction – NO TURN BACK. 2. Airspeed – 100 km/h (62 mph, 54 kts) - best glide. 3. Throttle – IDLE. 4. Lane A and B – OFF. 5. Fuel pumps 1 and 2 – OFF. 6. Battery switch – OFF. 7. Fuel valves – CLOSE. 8. Landing – STRAIGHT AHEAD, avoid colliding with obstacles. 4.2.3 During climb above 300m (1000 ft) or in level flight 1. Fuel valves – BOTH OPEN. 2. Fuel pump 1 – OFF and Fuel pump 2 – ON. 3. ECU Voltage – CHECK. 4. EMERGEN POWER switch – ON if ECU Voltage 9 V or less. 5. Airspeed – 100 km/h (62 mph, 54 kts) - best glide. 6. Landing area – SELECT (consider altitude and wind). AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 12 4.2.4 Restarting engine in flight 1. Throttle – IDLE. 2. Fuel level – CHECK. 3. Fuel valves – BOTH OPEN. 4. Fuel pump 1 – ON and 2 – OFF. 5. Lane A and B – CHECK ON. 6. EMERGEN POWER switch – ON. 7. START button – PRESS until engine start (maximum 10 seconds). 8. Fuel pump 2 – ON. 9. Throttle – AS REQUIRED. 10. EMERGEN POWER switch – OFF (if engine runs smoothly and at least one of the Lane A or Lane B warning lights is not permanently ON). 11. EMS lamps A and B ON – perform PRECAUTIONARY LANDING see section 4.2.6 4.2.5 Emergency landing without engine power 1. Airspeed – 100 km/h (62 mph, 54 kts) - best glide. 2. Flaps – position 1. 3. Fuel pumps 1 and 2 – OFF. 4. Fuel valves – CLOSE. 5. Landing area – SELECT, consider altitude and wind. (No place suitable for landing – use recovery system.) 6. Emergency call – TRANSMIT (121.5 MHz or nearest airfield frequency). 7. Flaps – EXTEND FULLY on final. 8. Landing – in the SELECTED place, avoid colliding with obstacles. 9. Touchdown – at minimum speed. 4.2.6 Precautionary landing with engine power (In case of decision to discontinue the flight with engine running) 1. Airspeed – SELECT SAFE for the particular situation. 2. Throttle – SET to maintain selected airspeed. 3. Fuel – CHECK level and valves. 4. Map – CHECK for nearest airfields/area suitable for landing. 5. Landing area – SELECT. 6. Radio – REPORT decision to land on the selected place if necessary. 7. Landing – follow NORMAL or SHORT-FIELD landing procedure as appropriate. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 13 4.2.7 Fire in flight 1. Lane A and B – OFF. 2. Fuel pumps 1 and 2 – OFF. 3. Fuel valves – CLOSE. 4. Yoke – PUSH to descend. 5. Airspeed – BELOW 229 km/h (142 mph, 124 kts). 6. Landing area – SELECT (consider altitude and wind). 7. Landing – in the SELECTED place, avoid colliding with obstacles. 8. Unfasten seat belts, abandon cockpit. 9. Take measures to extinguish the fire or stop formation of smoke. 4.2.8 Failures of the engine management system (EMS warning lights) Lane A Lane B Action OFF Flashing Land at the nearest airfield, see section 5.12 Flashing OFF OFF ON Flashing Flashing Flashing ON ON OFF ON Flashing ON ON Perform precautionary landing, see section 4.2.6 4.2.9 Loss of oil pressure 1. Follow PRECAUTIONARY LANDING procedure, see section 4.2.6. 2. Engine overheating or stopped – follow EMERGENCY LANDING procedure, see section 4.2.5. 4.2.10 High oil pressure 1. Throttle – REDUCE rpm, IDLE if necessary. 2. Airspeed – 100 km/h (62 mph, 54 kts) - best glide. 3. Oil pressure – CONTROL. 4. Oil pressure normal – follow PRECAUTIONARY LANDING procedure, see section 4.2.6. 5. Oil pressure high – follow EMERGENCY LANDING procedure, see section 4.2.5. 4.2.11 Emergency descent 1. Yoke (Stick) – PUSH to descend. 2. Throttle – IDLE. 3. Airspeed – BELOW 229 km/h (142 mph, 124 kts). 4. Engine speed – BELOW 5800 rpm. 5. Air traffic – CONTROL to avoid collisions. 6. Altitude – CONTROL. 7. Terrain – CONTROL. 8. At safe altitude – PULL YOKE (STICK) GENTLY to level off. 9. G loads – DO NOT EXCEED +4g. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 14 4.2.12 Alternator failure Follow PRECAUTIONARY LANDING procedure, see section 4.2.6. 4.2.13 Inadvertent spin 1. Rudder pedals – FULLY AGAINST ROTATION. 2. Yoke (Stick) – PUSH to stops. 3. Rotation stopped – rudder pedals NEUTRAL. 4. Speed reached 100 km/h (62 mph, 54 kts) – PULL YOKE (STICK) GENTLY to recover from diving. Do not exceed +4g and 229 km/h (142 mph, 124 kts)! WARNING: Intentional spinning in A-22LS is prohibited! NOTE: In level flight and during turn stall warning is assured by the aerodynamic characteristics of A-22LS – gentle shaking of the airplane and yoke (stick) due to the starting airflow separation. 4.2.14 Inadvertent icing encounter 1. Abandon icing build-up area. 2. Icing build-up not stopped – FOLLOW PRECAUTIONARY LANDING procedure, see section 4.2.6. 4.2.15 Loss of primary instruments 4.2.15.1 ASI failure due to full pressure line blockage Signs of the blockage – airspeed indicator reading either: - does not change with changing airspeed in level flight or, - reduces during a steady descent or, - increases during a steady climb. 1. Airspeed indicator readings – IGNORE. 2. In level flight – SET THROTTLE to 4000-4500 rpm. 3. Altitude – MAINTAIN. 4. In descent – SET THROTTLE to IDLE. 5. Sink rate – SET to 3 m/s (600 ft/min). 6. Follow PRECAUTIONARY LANDING procedure, see section 4.2.6. 4.2.15.2 Altimeter, VSI and ASI failure due to static pressure line blockage Signs of the blockage: - altimeter and vertical speed indicator readings do not change with changing altitude or, - airspeed indicator reading increases during a steady descent or, - airspeed indicator reading reduces during a steady climb. 1. IGNORE altimeter, VSI and ASI readings. 2. Airplane attitude – CONTROL by the position of the horizon line with relation to the wings and engine cowling. 3. Airspeed and vertical speed – CONTROL using throttle. 4. Follow PRECAUTIONARY LANDING procedure, see section 4.2.6. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 15 4.2.15.3 Powerplant instruments failure (Tachometer, oil, water and exhaust temperature indicators, fuel quantity indicator) 1. IGNORE powerplant instruments readings. 2. Engine rpm – CONTROL by engine noise. 3. Follow PRECAUTIONARY LANDING procedure, see section 4.2.6. 4.2.16 Loss of flight controls 1. Elevator control fails – use elevator TRIM TAB control. 2. Rudder control fails – use AILERONS to control direction. 3. Aileron control fails – use RUDDER to control bank. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 16 5 Normal Procedures 5.1 General This section describes normal procedures recommended for safe operation of the A-22LS. 5.2 Preflight check Pilots must inspect the general condition of the airplane during its preflight check. The airplane must have no damage or maladjustments that may be critical for the flight safety. The cockpit glass, propeller, wing and empennage must be clean of rainwater, snow, frost, ice, and dirt as they impair visibility and aerodynamics and increase weight. Preflight check must be performed according to the following order and requirements: 5.2.1 Entire airplane 1. Covers and clamps – REMOVED. 2. Airplane – CLEAN of rainwater, snow, frost, ice and dirt. 3. Rigging – CHECK visually. 4. External damage – NONE. 5.2.2 Power plant 1. Propeller and spinner – CLEAN, INTACT and SECURE. 2. Top cowling – REMOVE for engine inspection. 3. Oil, coolant and braking fluid – CHECK level. 4. Engine mount and vibration dampers – NO CRACKS and INTACT. 5. Cables and hoses – INTACT and SECURE. 6. Fuel, oil, coolant leaks – NONE. 7. Exhaust system, its attachments, joints and springs – NO CRACKS and INTACT. 8. Top cowling – INSTALL back. 9. Cowling and its locks – INTACT and LOCKED. 5.2.3 Landing gear 1. Wheel fairings – CLEAN, INTACT and SECURE. 2. Wheel pressure – OK. 3. Tires – NO CRACKS, WEAR OK. 4. Main wheel brakes – CLEAN, INTACT and SECURE. 5. Braking fluid – NO LEAKS. 6. Nose and main legs – NO CRACK and INTACT. 7. Nose leg shock absorber – INTACT. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 17 5.2.4 Right wing 1. Wing and strut surface – CLEAN and INTACT. 2. Wing and strut attachment fittings and bolts – IN PLACE, INTACT and SECURE. 3. Wing fuel tank cap – IN PLACE and SECURE. 4. Fuel leaks – NONE. 5. Fuel tank vent outlet – CLEAN and INTACT. 6. Wing tip and navigation/strobe light – INTACT. 7. Flaperon clamp – REMOVED. 8. Flaperon – CLEAN and INTACT. 9. Flaperon hinge brackets – INTACT, BOLTS SECURE, HINGES GREASED. 10. Flaperon control linkage attachment – INTACT and SECURE. 5.2.5 Right side of fuselage 1. Fuselage surface – CLEAN and INTACT. 2. Cockpit glass – CLEAN, INTACT and NO CRACKS. 3. Door hinges and lock – INTACT. 4. Recovery system condition – CHECK visually. 5. Drain valve – CLOSED, NO FUEL LEAKS. 6. Fuel residue – DRAIN and CHECK. 5.2.6 Empennage 1. Empennage surface – CLEAN and INTACT. 2. Horizontal stabilizer attachment fittings and bolts – INTACT and SECURE. 3. Rudder, elevator and trim tab – CLEAN and INTACT. 4. Rudder, elevator and trim tab hinge brackets – INTACT, SECURE and GREASED. 5. Rudder, elevator and trim tab control linkage attachment – INTACT and SECURE. 5.2.7 Left side of fuselage 1. Fuselage surface – CLEAN and INTACT. 2. Cockpit glass – CLEAN, INTACT and NO CRACKS. 3. Door hinges and lock – INTACT. 4. Battery and power cables' attachment – SECURE, CONDITION OK. 5. Control system linkages inside the rear fuselage – CHECK visually. 6. Baggage container condition – CHECK visually. 5.2.8 Left wing 1. Flaperon control linkage attachment – INTACT and SECURE. 2. Flaperon hinge brackets – INTACT, BOLTS SECURE, HINGES GREASED. 3. Flaperon – CLEAN and INTACT. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 18 4. Fuel tank vent outlet – CLEAN and INTACT. 5. Fuel leaks – NONE. 6. Wing fuel tank cap – IN PLACE and SECURE. 7. Wing tip and navigation/strobe light – INTACT. 8. Wing and strut attachment fittings and bolts – IN PLACE, INTACT and SECURE. 9. Wing and strut surface – CLEAN and INTACT. 10. Pitot/static pressure probe – COVER REMOVED, CLEAN and INTACT. 5.2.9 Cockpit 1. Cockpit interior – CLEAN, INTACT, NO FOREIGN OBJECTS. 2. Seats – INTACT, ADJUSTED and SECURE. 3. Harness belts – INTACT, ADJUSTED and LOCKED (with pilots in the seats). 4. Doors – CLOSED and LOCKED. 5. Flight planning including weight and CG check – PERFORMED. 6. Onboard documentation/maps required for the flight – AVAILABLE. 7. Baggage container – BAGGAGE SECURED, CONTAINER CLOSED. 8. Starter key – REMOVED 9. All electrical switches – OFF. 10. Flight instruments – INTACT, CHECK READINGS. 11. Yoke (Stick) fixing pin – REMOVE. 12. Movements of controls – check FREE and FULL. 13. Yokes (Stick), rudder pedals, elevator trim tab lever – NEUTRAL. 14. Flaps – RETRACTED. 15. Parking brake – ON. 16. Recovery system (if installed) safety pin – REMOVE. 5.3 Fuel levels, fuel valve settings and respective actions 1. BOTH TANKS ARE FULL – CLOSE ONE OF THE FUEL VALVES (to prevent fuel escaping from the tanks through the air vent). 2. FUEL LEVEL IS BETWEEN 3/4 AND 1/4 IN ONE OF THE TANKS – OPEN BOTH FUEL VALVES. It is recommended to keep the fuel level equal in both tanks by using the fuel valves. WARNING: Before closing one of the fuel valves in flight make sure that the other valve is open! 3. FUEL LEVEL IS BELOW 1/4 IN ONE OF THE TANKS – BOTH FUEL VALVES MUST BE ALWAYS OPEN. 5.4 Engine starting 1. Doors – check CLOSED. 2. Propeller – CHECK CLEAR. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 19 3. Throttle – APPROX. 50% OF THROTTLE VALVE OPENING AT THE NORMAL AMBIENT TEMPERATURE. 55% at cold weather condition and 45% at hot weather condition. For more information see Operators Manual of Rotax 912iS engine. 4. Battery switch (under left seat) – ON. 5. Master switch – ON. 6. Fuel level – CHECK. 7. Fuel shutoff valves – one OPEN, the other CLOSED. 8. Strobes – ON. 9. Fuel pump 1 – ON. 10. Fuel pump 2 – OFF 11. Lane А – ON. 12. Lane B – ON. 13. Start POWER switch – UP (ON) and HOLD. 14. Fuel pressure – min. 3 bar. 15. Warning lights A and B – weight till OFF. 16. START button – PRESS for a maximum of 10 seconds only (without interruption), followed by a cooling period of 2 minutes. 17. START button, Start POWER switch – RELEASE. 18. SET THROTTLE AS REQUIRED: Cold engine Warm engine a) Throttle – 2000 RPM 2 minutes. b) CHECK Oil pressure above 3 bar. c) Throttle – 2500…2600 RPM. d) Battery charge – check ON. e) Throttle – 2500 RPM till oil temp. 50°C. f) Throttle – IDLE. a) Throttle – IDLE b) CHECK Oil pressure above 3 bar. c) Throttle – 2500…2600 RPM. d) Battery charge – check ON. e) Throttle – IDLE. 19. Engine instruments – CHECK READINGS: a) oil temperature: MIN 50°C; b) oil pressure: 2.0…5.0 bar over 3500 rpm, MIN 0.8 bar below 3500 rpm, MAX 7.0 bar; c) coolant temperature: MIN 60°C; d) engine RPM – MIN 1400; e) fuel pressure – 2.8…3.3 bar. 20. Throttle – 4000 RPM. 21. Lane A and B – CHECK MAX 180 RPM DROP. 22. Throttle – 2500 RPM 23. Fuel pump 2 – ON, Fuel pump 1 – OFF. 24. Fuel pressure – 2.8…3.3 bar. 25. Fuel pump 1 – ON, Fuel pump 2 – ON. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 20 26. Fuel pressure – 2.8…3.3 bar. 27. Throttle – IDLE. 5.5 Taxiing 1. Throttle – IDLE. 2. Parking brake – OFF. 3. Coolant and oil temperature – CHECK 4. Taxiway – CHECK CLEAR. 5. Throttle – SET REQUIRED TAXI SPEED. 6. Yoke (Stick) – elevator NEUTRAL, ailerons AGAINST crosswind. 7. Brakes – use as required, set throttle to IDLE when stopping. 8. To stop immediately – IGNITION OFF and ENGAGE BRAKES. 5.6 Before takeoff 1. Hold position – OCCUPY. 2. Brakes – ENGAGE. 3. Coolant temperature – CHECK minimum 60°C (140°F). 4. Oil temperature – CHECK minimum 50°C (122°F). 5. Fuel level – CHECK (see 5.3). 6. Fuel valves – CHECK (see 5.3). 7. Flaps – EXTEND position 1. Wind stronger 8 m/s (16 kts) – FLAPS UP. 5.7 Normal takeoff 1. Hold position – OCCUPY. 2. Rudder pedals – NEUTRAL. 3. Brakes – RELEASE. 4. Throttle – gradually FULL POWER. 5. Yoke (Stick) – elevator NEUTRAL, ailerons AGAINST CROSSWIND. 6. Rudder pedals – maintain takeoff direction. 7. Yoke (Stick) – PULL gently to lift the nose wheel at 40 km/h (25 mph, 22 kts). 8. Liftoff – at 80 km/h. 9. Accelerate to at least 100 km/h (62 mph, 54 kts) at 1-2 m (3-7 ft) and start to climb. 5.8 Short/soft field takeoff 1. Flaps – EXTEND FULLY. 2. Hold position – OCCUPY. 3. Take-off distance – CHECK if sufficient. 4. Rudder pedals – NEUTRAL. 5. Throttle – gradually FULL POWER. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 21 6. Brakes – RELEASE. 7. Yoke (Stick) – elevator NEUTRAL, ailerons AGAINST CROSSWIND. 8. Rudder pedals – maintain takeoff direction. 9. Yoke (Stick) – PULL gently to lift the nose wheel at 40 km/h (25 mph, 22 kts). 10. Liftoff – at 65 km/h (40 mph, 35 kts). 11. Accelerate to at least 90 km/h (56 mph, 49 kts) at 1-2 m (3-7 ft) and start to climb. 12. Speed – SET best angle of climb speed VX = 90 km/h (56 mph, 49 kts). 5.9 Climb 1. Speed – SET: best angle of climb speed VX = 90 km/h (56 mph, 49 kts) or best rate of climb speed VY = 100 km/h (62 mph, 54 kts) in strong turbulence +10 km/h (6 mph, 5 kts). 2. Flaps – RETRACT SLOWLY at safe altitude. 3. EGT – max. 950°C (1742°F). 4. CHT – max. 135°C (275°F). 5. Oil pressure – max. 5.0 bar (73 psi). 6. Oil temperature – max. 130°C (266°F) 5.10 Cruise 1. Flight altitude – OCCUPY and monitor, in strong turbulence – at least 100 m (300 ft). 2. Cruise speed – SET, in strong turbulence – minimum 100 km/h (62 mph, 54 kts), maximum 168 km/h (104 mph, 90 kts). 3. Elevator trim tab – ADJUST as required. 4. Fuel level – CHECK (see 5.3). 5. Fuel valves – CHECK (see 5.3). 6. Turns – perform with caution in strong turbulence and at low altitudes. 5.11 Approach 1. Speed – REDUCE below 148 km/h (92 mph, 80 kts), minimum 100 km/h (62 mph, 54 kts). 2. Flaps – EXTEND position 1. Wind stronger 8 m/s (16 kts) – FLAPS UP. 3. Elevator trim tab – ADJUST as required. 4. Approach speed on final – 100 km/h (62 mph, 54 kts), +10 km/h (6 mph, 5 kts) in rain or strong turbulence. 5. Too high on final – REDUCE RPM to idle, SLIP if necessary. 6. Too low on final – INCREASE RPM. DO NOT RETRACT FLAPS when flying low over high obstacles or close to the ground! 5.12 Normal landing 1. Direction – ALIGN the airplane WITH THE RUNWAY using rudder pedals. 2. Side drift – ELIMINATE by banking against the drift (crosswind, if any). AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 22 3. Flare – start at 5 m (15 ft), level off at approximately 0.3 m (1 ft). Gradually reduce bank and side drift while flaring and leveling off. 4. Throttle – IDLE. 5. Touchdown – at minimum speed. In cross-wind conditions – maintain banking into wind till touching the runway with one of the wheels. Avoid touching ground with the tail. 6. Yoke (Stick) – HOLD to reduce the speed and PUSH gently to lower the nose wheel slowly. Pedals – set NEUTRAL before touching ground with the nose wheel (in cross-wind conditions). 7. Brakes – ENGAGE as required. Avoid braking at a high speed or with nose wheel up! 8. Flaps – RETRACT. 5.13 Short/soft field landing 1. Flaps – EXTEND FULLY. 2. Approach distance – REDUCE by side slipping when clear of obstacles. 3. Approach speed on final – 90 km/h (56 mph, 49 kts), +10 km/h (6 mph, 5 kts) in rain or strong turbulence. 4. Direction – ALIGN the airplane WITH THE RUNWAY using rudder pedals. 5. Side drift – ELIMINATE by banking against the drift (crosswind, if any). 6. Flare – start at 5 m (15 ft), level off at approximately 0.3 m (1 ft). Gradually reduce bank and side drift while flaring and leveling off. 7. Throttle – IDLE. 8. Touchdown – at minimum speed at the beginning of the runway. In cross-wind conditions – maintain banking into wind till touching the runway with one of the wheels. Avoid touching ground with the tail. 9. Flaps – RETRACT. 10. Yoke (Stick) – HOLD to reduce the speed and PUSH gently to lower the nose wheel slowly. Pedals – set NEUTRAL before touching ground with the nose wheel (in cross- wind conditions). 11. Brakes – soft field: DO NOT USE; short field – ENGAGE as required. Avoid braking at a high speed or nose wheel up! 5.14 Balked landing 1. Throttle – gradually FULL POWER. 2. Descent – DISCONTINUE. 3. Speed – accelerate to at least 100 km/h (62 mph, 54 kts) flying level. 4. Climb – at 100 km/h (62 mph, 54 kts). 5. Flaps – RETRACT SLOWLY at safe altitude. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 23 6 Performance 6.1 General This section contains performance data of A-22LS airplane of standard (basic) configuration at maximum takeoff weight in the following environmental conditions: ICAO standard atmosphere (ISA), mean sea level (MSL), no wind, hard and even runway. Those data may vary depending upon the configuration and technical condition of a particular aircraft and actual environmental conditions of its operation. 6.2 Takeoff and landing distances The minimum takeoff and landing distances of A-22LS for the above conditions are specified below. However pilots should always keep in mind that actual takeoff and landing distances depend on condition of the aircraft, environment and pilot skill. Engine Rotax-912UL Rotax-912ULS Takeoff run 140 m (460 ft) 105 m (344 ft) Landing run 185 m (607 ft) 185 m (607 ft) Takeoff distance to 15 m (50 ft) 405 m (1329 ft) 335 m (1100 ft) Landing distance from 15 m (50 ft) 440 m (1445 ft) 440 m (1445 ft) 6.3 Climb performance The rate of climb depends on atmospheric conditions, airplane takeoff weight and flap setting. The climb performance data of A-22LS in ISA conditions at MSL, maximum takeoff weight are specified below: Engine Rotax-912UL Rotax-912ULS Best angle of climb speed VX 90 km/h (56 mph, 49 kts) 90 km/h (56 mph, 49 kts) Best rate of climb speed VY 100 km/h (62 mph, 54 kts) 100 km/h (62 mph, 54 kts) Maximum rate of climb at VX 2.3 m/s (453 fpm) 3.2 m/s (630 fpm) Maximum rate of climb at VY 2.6 m/s (512 fpm) 4 m/s (787 fpm) 6.4 Cruise speeds and fuel consumption at various RPM settings The cruise speeds and fuel consumption depend upon a multitude of factors: propeller pitch and engine adjustments, fuel quality, atmospheric conditions, flight altitude, aircraft loading and condition of its outer surface, etc. With the KievProp three-blade propeller adjusted to take-off RPM of 5100 per minute and standard condition of atmosphere and aircraft the following cruise speeds and fuel consumption values may be used for flight planning: RPM Cruise speed, IAS Fuel consumption, US gal/h 4000 110 km/h (68 mph, 59 kts) 10 l/h (2.6 US gal/h) 4600 148 km/h (92 mph, 80 kts) 15 l/h (3.9 US gal/h) 5000 161 km/h (100 mph, 87kts) 19 l/h (5.0 US gal/h) 5400 180 km/h (112 mph, 97 kts) 25 l/h (6.6 US gal/h) AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 24 However these values should be considered as approximate as they may vary due to effect of the above mentioned factors. It is recommended to verify those values for the particular conditions in which the exact values are required. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 25 7 Weight and Balance and Equipment List This section contains information about weight and balance requirements for the safe operation of the airplane. It is responsibility of the pilot in command to ensure before every flight that weight and balance of the airplane remains within the specified limits. Failure to do so may cause deterioration in airplane's flight performance and stability characteristics and, as consequence, lead to unsafe operation. 7.1 Weight and Balance Chart This subsection contains weighing and CG location data of the aircraft in configuration “as manufactured”. Any permanent modification of the aircraft configuration (such as replacement, removal/installation of any parts or/and equipment) essentially affecting those data shall be accounted for in this weight and balance chart by appropriate revisions of this subsection data. Weight readings at: front wheel 163 lbs. left wheel 287 lbs. right wheel 287 lbs. Total empty weight: .............................. 737 lbs. Total maximum take-off weight: 1323 lbs. Fig. 2 AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 26 C.G. position for the maximum take-off weight: Item Weight, lbs × CG arm, inch = Moment, kg×m/lb×inch Empty airplane 747.0 × 59.8 = 44671 Crew (2×175 lbs) 350 × 63.0 = 25,200 Baggage 44 × 90.6 = 3986 Fuel (2×57 l) 181.0 × 78.7 = 14,245 Total: 1322 88102 XCG = Total moment / Total weight = 66.6 Note: XCG must be between 59” and 69” (19% and 37% MAC) as shown in Fig. 2. Note: Leveling is accomplished by setting the bottom of the door frame to +3°. 7.2 Installed equipment list This subsection contains a table with the list of the installed optional equipment affecting weight and balance of the aircraft. It is responsibility of the aircraft owner/operator that any such equipment installed in the aircraft after the date of its manufacture is listed in the table below. No. Equipment description and Part No. Weight, kg CG arm, m AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 27 No. Equipment description and Part No. Weight, kg CG arm, m AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 28 8 Airplane and Systems Descriptions 8.1 General This section provides description and operation of the airplane and its systems. Some equipment described herein is optional and may not be installed in the airplane. Refer to Section 9, Supplements, for details of other optional systems and equipment. 8.2 Airframe Wing: high placed, strut braced, constant chord. Wing section is P-IIIa-15%. Wing primary structure consists of a single spar, ribs and aft web. Forward of the spar the wing has 2024T3 aluminum alloy skin of 0.020-0.032 in (0.5-0.8 mm) sheet, which together with the spar web forms the wing torsion box. Aft of the spar the wing is covered with the metal skin on top and thermoshrinkable fabric on the bottom side. Wing ribs are made of 6061T6 sheet of 0.020- 0.032 in (0.5-0.8 mm) thickness. The spar is a riveted structure consisting of a web, made of 0.032 in (0.8 mm) 6061T6 sheet, and caps, made of an extruded section (D16chT alloy angle). The wing strut attachment bracket and front attachment bracket of the wing are fixed to the spar. The rear attachment bracket of the wing is fixed to the aft web. The flaperon (drooping aileron) hinge brackets are fixed to ribs No. 1, 5, 9 and 13. All brackets are made of 5 mm 2024T3 sheet. The primary structure of the flaperon consists of the leading edge skin, spar, trailing edge section and ribs. The LE skin and spar comprise the torsion box. Flaperon covering is made of synthetic thermoshrinkable fabric. The fuselage is an all-metal structure. The mid-section is made of the 2024T3 aluminum alloy bent sheet sections of 0.063 to 0.080 in (1.5 to 2 mm) thickness, which form the edges of the mid-section. The tail boom is a monocoque structure made of 0.032 in (0.8 mm) 2024T3 aluminum alloy sheet. Engine cowling is made of composites. The fuselage has 6 frames (bulkheads). Frames No. 1, 2, 4, 5 and 6 are press-formed of an aluminum alloy sheet; frame No. 3 is made of bent sheet sections. Power plant and nose LG attachment points are attached to the frame No. 1, the engine mount taking part in transferring the loads from the nose LG onto the fuselage structure. The wing and strut attachment brackets as well as the main LG legs attachment brackets are attached to the frame No. 3. Frames No. 4, 5, 6 are installed in the tail boom. The fin and ventral fin with the tail wheel are attached to the frames No. 5 and 6. The bottom and part of the topside of the mid fuselage section are covered with aluminum alloy sheets of 0.020 in (0.5 mm) thickness. The doors, cockpit and part of the fuselage have windows of organic glass. The primary structure of the stabilizer consists of ribs and a spar. The skin is a 2024T3 aluminum alloy sheet of 0.020 in thickness. The stabilizer has brackets of its attachment to fuselage and 3 elevator hinge brackets. The fin, structurally similar to the stabilizer, is made as integral part of the fuselage. Elevator and rudder structures are similar to that of the flaperons. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 29 8.3 Landing gear Airplane landing gear is of tricycle type with steerable nose wheel. The main LG is of the cantilever spring type. The main LG leg is a spring machined of a round aluminum bar. It is attached to the lower boom of the frame No. 3 at two points: upper and lower supports. The support brackets are machined of aluminum alloy. The main LG wheels are fitted with hydraulic disk brakes. The nose LG leg is steerable, of trailing link type. The steering is ensured using the rudder pedals via pushrods, connecting the left and right side pedals with bellcrank on the strut. The leg consists of a strut and a trailing link in form of nose wheel fork. The trailing link is connected to the strut with a spring shock absorber/damper. The nose leg is attached to the frame No. 1 at 2 points – on upper and lower supports. The upper support is made of 4 mm aluminum alloy sheet and the lower one is build-up. The supports are fitted with bronze bushings. Landing gear data: wheel base – 1.262 m (4 ft 2 in), wheel track – 1.712 m (5 ft 7 in), min. turn radius ~ 2 m (7 ft). Main wheels: size – 6.00×6 or 8.00×6 pressure – 1.6 bar (22.7 psi) for 6.00×6 wheels – 1.3 bar (19.0 psi) for 8.00×6 wheels Nose wheel: size – 6.00×6 or 8.00×6 brakeless wheel steering angle – ±30° pressure – 1.0 bar (14.5 psi) Each wheel may be fitted with a mud screen or a wheel spat (fairing) in case of 6.00×6 wheels installation. 8.4 Engine and its controls This aircraft is equipped with a four-cylinder four-stroke Rotax-912iS Sport (100 hp) combined cooling engine produced by BRP-Powertrain GmbH&Co. KG. (Austria). The engine is has the flat-four layout, dry sump lubrication system with a separate oil tank of 3 l (0.8 US gal) capacity, automatic valve clearance adjustment, integrated gearbox of 2.43 reduction ratio and fully redundant electronic engine management system (EMS) which includes fuel injection, ignition, etc. All engine systems (fuel, electrical, cooling) are assembled in accordance with Rotax-912 i SERIES engine operation and installation manuals. 8.5 Propeller A-22LS can be equipped with any suitable propeller matching to Rotax-912iS Sport engine power output and the airplane speed range. One of the optional propellers is KievProp three- blade on-ground adjustable propeller of 1.7 m (5'7") diameter. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 30 8.6 Fuel system Fig. 3. Fuel system schematic CAUTION! If air gets to the fuel lines then starting the engine may take quite a long time (several dozens of seconds). For that reason it is strictly not allowed to empty completely any of the fuel tanks in flight. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 31 The fuel system (see Fig. 3) includes two wing fuel tanks 1 and 2 (each of 57 l capacity) with filler inlets 3 and 4. Fuel comes from left and right fuel tanks via fuel lines 5 and 6 to double fuel valves 7 and 8, each opening/closing the feed and return line simultaneously. Then fuel is fed through fuel lines 9 and 10 to sediment separator 11. From the sediment separator through the fuel line 12, coarse filter 13 and then through the fuel line 14 the fuel is fed to inlet of the 1st (main) fuel pump 15 and then to the inlet of the 2nd (auxiliary) fuel pump 17. The 1st and 2nd fuel pumps together with the return valves 16 comprise a single module, located under the right pilot seat. From the outlet of the 2nd fuel pump the fuel is supplied with pressure through the fine filter 20 to the rail injectors 21 of the cylinders 1 and 3. Then through the tube 22 – to the rail injectors 23 of the cylinders 2 and 4, outlet of which is joined with fuel pressure regulator 24. The fuel pressure regulator ensures constant fuel pressure in the range of 2.8-3.2 bar (42-45 psi) in rail injectors with regard to the air pressure in the intake manifold. From the outlet of the fuel pressure regulator the excessive fuel is returned through the low pressure fuel return line 25 and T-connector to the fuel tank 1 or 2 through the fuel line 27 or 28 depending upon which of the fuel valves 7 or 8 is opened. Fuel pressure after the fuel pumps is controlled using the fuel pressure sensor 19, installed immediately before the fine filter 20. The fuel tanks have vent tubes 31 and 32 installed in the fuel tank inlet caps. Fuel can be drained from the tanks on the ground via the drain valve 29, handle of which is accessible outside fuselage. Fuel: see paragraph 3.6. Fuel pressure: maximum permissible — 7 bar (101.5 psi); Fuel pumps: nominal voltage — 12 V; capacity — approx. 120 l/h (31.7 gal/h); pressure — min. 4.5 bar (65.3 psi) (absolute pressure). standard optional Capacity of tanks: 2×45 l (2×11.9 US gal) 2×57 l (2×15.05 US gal) Total fuel capacity: 90 l (23.8 US gal) 114 l (30.1 US gal) Total usable fuel: 88 l (23.3 US gal) 112 l (29.6 US gal) Non-usable fuel: 2 l (0.5 US gal) 2 l (0.5 US gal) AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 32 8.7 Airplane control systems Airplane control systems include control systems for drooping ailerons (flaperons), elevator with trim tab, rudder and nose wheel, engine and brakes. The control system is combined consisting of foot- and hand-actuated subsystems. Ailerons and elevator are hand-actuated and are controlled using central stick. 8.7.1 Elevator control system The elevator control system linkage (see Fig. 4) is rigid, comprising 3 pushrods and 2 bellcranks. “Push” and “pull” forces are applied by the pilot to the stick 1 is passed via the control column 2 to the pushrod 3, then via the bellcrank 4 to the pushrod 5. The force is transferred to the elevator via the pushrod 7, attached to the bellcrank 6. And the pushrod 7 is supported by the rollers 8 and connected to the elevator arm 9. The elevator angles of deflection are: upward 25±1°, downward 15±1°. Fig. 4. Elevator control system AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 33 8.7.2 Elevator trim tab control system Elevator trim tab is used for controlling the force on control yokes in pitch. The trim tab control lever is accessible from both pilot seats. Fig. 5. Elevator trim tab control system The trim tab control lever 1 (see Fig. 5) is placed on the central console. It is retained in place by friction adjusted using the wheel 2. The trim tab control lever is connected with a cable 3 to the trim tab control arm 4. The cable is running through the flexible conduits 5 (in the central console) and 6 (in stabilizer) and cable fairleads 7 and 8 inside the tail boom. The trim tab is hinged to the elevator trailing edge on a wire serving also as a torsion spring. The trim tab angles of deflection are: upward 21±1°, downward 22±1°. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 34 8.7.3 Rudder and nose wheel control system Rudder and nose landing gear are controlled using pedals. Rudder is connected to the pedals in the cockpit with two cables of 2.7 mm (0.11 in) diameter. The pedals are attached to two shafts (shaft for left pedals 1 and shaft for right pedals 2) hinged to the lower fuselage beams ( see Fig. 6Error! Reference source not found.). Each shaft has two arms. One of the arms is connected with a cable to the rudder control arm 3, the other - with a rod - to the nose landing gear control arm 4. Rudder control cables are running from the pedals to the rudder control arms via pulleys 5, 6 installed at frames No. 3 and 4 and fairleads 8, 9 on pilot seat beam and frame 5. Tension of the cables is adjusted using turnbuckles 7 attached to the pedal shaft arms. In its neutral position the rudder is rotated to the right by the angle of +2°20' for compensation of the engine torque. The rudder deflection angle is 25±1°. Fig. 6. Rudder and nose landing gear control system AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 35 8.7.4 Control system of flaperons (drooping ailerons) The airplane is equipped with flaperons (drooping ailerons), which serve as both ailerons and flaps. The flaperon control system ensures independent function of flaperons as ailerons and flaps using a differential mechanism. Fig. 7. Control system of flaperons (drooping ailerons) The control force in roll (see Fig. 7) applied by the pilot to the control stick 1 is passed to the central control shaft 2. Then from the bellcrank 9 attached to the shaft it is passed via the pushrods 7 to the flaperon control shafts 6. The shafts are attached via a Cardan joint 5 to the bracket at the root end rib of the flaperon 4 at one end and to the trunnion on the levers 3 of the flap control mechanism at the other. Stop 8 limits the rotation angle of bellcrank 9 on the central control shaft and, therefore, angles of Stick rotation and aileron deflection. Deflection angles of the flaperons (as ailerons): up – 19±1°, down – 13±1°. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 36 Fig. 8. Flap extension mechanism As flaps (see Fig. 8) the flaperons are extended by setting the flap extension lever 1 to the required positions and thus rotating the flap shafts 5 by the respective angles via link 3 and levers 4. Locking of the flap setting is achieved by means of the stopper block 2 with three slots for the locking pin on the flap extension lever. Unlocking is achieved by bending the flexible flap extension lever to the side and thus taking the locking pin out of the fixing slot. When the required flap setting is selected the locking pin is aligned with the fixing slot and the flap extension lever springs back inserting the locking pin into the fixing slot. Deflection angles of the flaperons (as flaps): 1st position–9°30´±1°, 2nd position–18°50´±1°. 8.7.5 Engine controls Rotax-912iS engine is equipped with an electronic control unit (ECU) for fuel injection into intake manifolds immediately before the intake valves. The ECU generates signals for fuel injection and mixture ignition according to the programmed algorithms and data from a number of sensors, including the throttle valve position sensor. Engine speed is controlled by moving the throttle valve from closed to fully open position using the throttle lever 1 (see Fig. 9) located on the central console in the cockpit. Displacement of the throttle lever moves the throttle valve arm 7 via the cable 2 inside the Bowden cable sheath 4. The sheath has an adjustable stop at the throttle valve housing bracket 5 and a fixed stop 3 at the throttle lever unit. Tension of the cable 2 is ensured by the return spring 6, that pulls the throttle valve arm to the fully open position. AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 37 Fig. 9. Engine controls AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 38 8.7.6 Brake control system The main wheel brakes (see Fig. 10) are actuated hydraulically using the brake lever 2, controlling the pressure supplied from the master cylinder 1 to the slave cylinders 4 in the wheels. The main LG wheels have disk brakes. The cylinders are connected to each other with copper tubing 5 with outside diameter of 3 mm. The master cylinder 1 is connected with a hose 7 to the extension tank 6, installed on the firewall in the engine compartment. When the brake lever is pulled the brake pads squeeze the brake disc creating the braking moment proportional to the applied force. A-22LS is equipped also with a parking brake, which is actuated with a lever 3 on the central console. To use the parking brake, set the lever to 'Parking brake ON', then pull and release the brake lever. The brake pads will remain pressed to the brake disc. To release the parking brake set its control lever to its initial position ('Parking brake OFF'). Fig. 10. Brake control system AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 39 8.8 Instrument panel This airplane has the following flight instruments set and instrument panel arrangement: Fig. 11 Instrument panel Numbers in Fig. 11 denote the following: 1. Placard with passenger warning: THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT CONFORM TO STANDARD CATEGORY AIRWORTHINESS REQUIREMENTS AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-06 40 2. Placard with operating limitations: OPERATE UNDER VMC ONLY NEVER EXCEED SPEED — 124 KTS IAS MAX CONTINUOUS ENGINE SPEED — 5500 RPM MAX TAKEOFF MASS — 600 KG (1320 LB) LIMIT LOAD FACTOR — +4.0 / -2.0 3. LANE A indicator and marking 4. LANE B indicator and marking 5. Cockpit heating control knob and marking 6. Data USB socket and marking 7. PTT button and marking 8. EMERGENCY POWER switch and marking 9. Autopilot disconnect button and marking 10. Left tank fuel level indicator and marking 11. Right tank fuel level indicator and marking 12. Left tank “Fuel Low” warning light and marking 13. Right tank “Fuel Low” warning light and marking 14. Landing light switch and marking 15. Wing land light switch and marking 16. WIG-WAG switch and marking 17. Navigation lights switch and marking 18. Strobe lights switch and marking 19. Cockpit lights switch and marking 20. Avionics light switch and marking 21. ADS-B switch and marking 22. Radio, transponder switch and marking 23. Reserved switch and marking 24. Reserved switch and marking 25. Windshield air fan switch and marking 26. Starter button and marking 27. FUEL PUMP 1 switch and marking 28. FUEL PUMP 2 switch and marking 29. LANE A switch and marking 30. LANE B switch and marking 31. START POWER switch and marking 32. Master key and marking 33. ON marking for electric and ignition switches 34. OFF marking for electric and ignition switches