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AEROPRAKT A22LS, Руководство по эксплуатации для пилотов

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AEROPRAKT-22LS Pilot Operating Handbook 

A22LS-POH-04 

31 

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 (

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°. 

Содержание A22LS

Страница 1: ...ration Number N226AM Airplane Serial Number 415 Date of issue 08 04 2021 Approved by Yuriy Yakovlyev Position Chief designer Date of approval 08 04 2021 This manual must be carried in the airplane at...

Страница 2: ...he present manual except actual weighing data must be recorded in the following table according to information from the Manufacturer New or amended text in the revised pages will be indicated by a bla...

Страница 3: ...ures 10 4 1 General 10 4 2 Emergency checklists 10 5 Normal Procedures 15 5 1 General 15 5 2 Preflight check 15 5 3 Fuel levels fuel valve settings and respective actions 17 5 4 Engine starting 18 5 5...

Страница 4: ...ggage container 47 9 Aircraft Ground Handling and Servicing 48 9 1 Introduction 48 9 2 Towing parking and tie down instructions 48 9 3 Servicing fuel oil and coolant 49 9 4 Approved fuel and oil 49 9...

Страница 5: ...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 Pr...

Страница 6: ...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...

Страница 7: ...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...

Страница 8: ...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...

Страница 9: ...C 275 F Engine start operating temperature max 50 C 120 F ambient temperature min 25 C 13 F oil temperature Fuel pressure maximum minimum 0 4 bar 5 8 psi 0 15 bar 2 2 psi Fuel antiknock properties mi...

Страница 10: ...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 Ignition OFF 3 Brakes APPLY as necessary 4 2 2 2 immediately after ta...

Страница 11: ...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...

Страница 12: ...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...

Страница 13: ...e 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 Airspe...

Страница 14: ...uel 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 Elevato...

Страница 15: ...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 I...

Страница 16: ...pit 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 Empenn...

Страница 17: ...LOSED 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...

Страница 18: ...lly when engine runs smoothly 16 Engine WARM UP at 2000 2500 RPM 17 Required electric equipment instruments switch ON and ADJUST 18 Ignition TEST at 4000 RPM holding brakes 19 Oil pressure check 2 0 5...

Страница 19: ...ient 4 Rudder pedals NEUTRAL 5 Throttle gradually FULL POWER 6 Brakes RELEASE 7 Yoke Stick elevator NEUTRAL ailerons AGAINST CROSSWIND 8 Rudder pedals maintain takeoff direction 9 Yoke Stick PULL gent...

Страница 20: ...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...

Страница 21: ...ing 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 g...

Страница 22: ...pends 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 Rot...

Страница 23: ...2LS POH 04 23 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 conditi...

Страница 24: ...acteristics 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 permane...

Страница 25: ...al moment Total weight 65 21 Note XCG must be between 59 inch and 69 inch 19 and 37 MAC as shown in Fig 2 7 2 Installed equipment list This subsection contains a table with the list of the installed o...

Страница 26: ...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...

Страница 27: ...or 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 s...

Страница 28: ...connector 11 Then fuel comes to the sediment collector 13 The sediment collector is located behind the main landing gear beam on the bottom rear panel of the fuselage The top outlet of the fuel sedim...

Страница 29: ...or when wings are not level on parking or during taxiing overfill it and spill out through the vent line To prevent this close one of the fuel valves Fuel see paragraph 3 6 standard optional Capacity...

Страница 30: ...olled using yokes 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 yoke...

Страница 31: ...ver 1 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 cab...

Страница 32: ...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 c...

Страница 33: ...ke 1 is passed via the lever 2 to the pushrod 3 and then to the central control shaft 5 The yokes are interconnected with the pushrod 4 Then from the bellcrank 6 attached to the shaft it is passed via...

Страница 34: ...om both right and left side pilot seat Engine RPM is controlled using a single throttle lever located on the central console Two control cables connect the throttle lever to the left and right carbure...

Страница 35: ...ent 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 wi...

Страница 36: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 36 8 8 Instrument panel This airplane has the following flight instruments set and instrument panel arrangement Fig 10 Instrument panel...

Страница 37: ...and marking 7 Left tank fuel level indicator and marking 8 Right tank fuel level indicator and marking 9 Left tank Fuel Low warning light and marking 10 Right tank Fuel Low warning light and marking...

Страница 38: ...nt of the flight parameters and therefore for flight safety Pilots must take measures to keep the system in good condition protect the full and static pressure probe with a cover marked with a red Rem...

Страница 39: ...sumers except for the engine ignition system and consumers with their own built in power source e g GPS together with the electrical switches for separate consumers The engine ignition system may be s...

Страница 40: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 40 Fig 12 Wiring diagram of A 22LS electrical system main...

Страница 41: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 41 Fig 13 Wiring diagram for installation of the SV EMS 220...

Страница 42: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 42 Fig 14 Wiring diagram for installation of the Dynon SkyView system...

Страница 43: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 43 Fig 15 Wiring diagram for installation of the autopilot servo...

Страница 44: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 44 Fig 16 Wiring diagram for installation of the radio SV COM 425 Fig 17 Wiring diagram for installation of the windshield air fans...

Страница 45: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 45 Fig 18 Wiring diagram for installation of Artex ELT 345 Fig 19 Wiring diagram for installation of PTT control buttons...

Страница 46: ...AEROPRAKT 22LS Pilot Operating Handbook A22LS POH 04 46 Fig 20 Wiring diagram for installation of the navigation and strobe lights...

Страница 47: ...ground 8 12 Cockpit doors The cockpit doors consist of organic glass attached to the metal tubular framework The doors are hinged on top and open upward In their open and closed position the doors are...

Страница 48: ...re towing the airplane make sure that the parking brake is off and the wheels are not blocked by chocks or anything else When towing use strong areas of the airplane structure for pulling pushing e g...

Страница 49: ...ing fuel pumps or and funnels with a fine mesh Fuel residue must be drained regularly from the tanks via the drain valve into a clean transparent container for checking WARNING At all times take care...

Страница 50: ...back the airplane or remove some of its components This section describes how to disassemble correctly the airplane by removing its main components left and right wings horizontal tail propeller engin...

Страница 51: ...e the propeller by pulling gently by its hub When installing the engine on the aircraft propeller should be installed in reversed order Locking of the nuts on the studs should be done in such a way th...

Страница 52: ...sed order After installation of the engine install the propeller on it NOTE Before wing removal empty the wing tanks 9 6 5 Aircraft assembling Aircraft assembling must be done in exactly reversed orde...

Страница 53: ...d with the manuals for that kind of equipment or special instruments Airplane owner pilot must follow the instructions of those manuals and respective subsections of this manual to ensure safe and eff...

Страница 54: ...uipment All equipment installed or replaced in this airplane must be listed in the table below The equipment affecting weight and balance of the airplane must be also listed in the table of the sectio...

Страница 55: ...ion about the actual empty weight and respective CG position of the airplane After final assembly major repair overhaul replacement and or additional installation of any equipment the aircraft must be...

Страница 56: ...ollowing a Level flight at various airspeeds and engine power settings Elevator trim tab shall be used for trimming the airplane in pitch b Climb at various airspeeds and full power of the engine Elev...

Страница 57: ...mph 54 kts and engine speed adjusted so that in the beginning of the final turn the airplane is at approximately 150 m 500 ft 9 It is recommended to make the final turn with a bank angle below 20 Whi...

Страница 58: ...to that During high speed flight the engine parameters must be monitored and exceeding its operational limits must be prevented To recover from a steep spiral the engine RPM must be reduced first and...

Страница 59: ...ropeller thrust Special attention shall be paid to maintaining the airspeed The imitated engine failures shall be done at every leg of the airfield circuit Total time of imitated engine failure traini...

Страница 60: ...t be used if constant quality is guaranteed The cable connections should be protected by appropriate covers The ultimate cable load must not be more than the cable load declared by the aircraft manufa...

Страница 61: ...that may catch the rope Release the rope over the landing strip threshold before landing 10 10 4 Banner towing Banner towing can be performed using the same tow release used for glider towing The atta...

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