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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH RECORD OF MANUAL REVISIONS No part of this manual may be reproduced or changed in any manner without a written consent of the Manufacturer. Any revision of the present manual, except actual weighing data, must be recorded in the following table according to information from the Manufacturer.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Table of contents Introduction ........................5 1 General information ..................... 6 1.1 General description of the airplane ................. 6 1.2 Airplane specifications .................... 6 2 Limitations ........................7 2.1 Airspeeds and Airspeed Indicator markings ............7 2.2 Service ceiling ......................
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 6.2 Installed equipment list ..................25 7 Airplane and Systems Descriptions ................. 27 7.1 General ......................... 27 7.2 Airframe......................... 27 7.3 Landing gear ......................27 7.4 Engine and its controls ..................28 7.5 Propeller ........................ 28 7.6 Fuel system ......................
The following ASTM standards have been and/or shall be used for the design, construction and continued airworthiness of this Aeroprakt-32 (A-32) 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...
1 General information 1.1 General description of the airplane AEROPRAKT-32 (A-32) 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-Sport engine with tractor three-blade on-ground adjustable pitch propeller.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 2 Limitations 2.1 Airspeeds and Airspeed Indicator markings Airspeed limitations and corresponding IAS values are given in the table below. Scheme of color markings of airspeed indicator is shown on Fig. 1. Its explanation is given in the table below.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 2.2 Service ceiling Service ceiling of A-32 with Rotax-912iS Sport (100 hp) engine is equal to at least 5000 m (16 000 ft). However A-32 has neither pressurized cockpit nor oxygen equipment and therefore may not be used for high-altitude flight.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 2.6 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...
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 2.7 Kinds of operation limits This aircraft is approved for flying day and night, VFR, simple meteorological conditions. Flight into icing conditions is prohibited. 2.8 Crosswind limitation Maximum crosswind component for A-32 airplane is 7 m/s (14 kts).
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 3 Emergency procedures 3.1 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.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 3.2.3.2 in level flight 1. Airspeed – 110 km/h (59 kts) – best glide. 2. Landing area – SELECT (consider altitude and wind). 3. Engine – RESTART (if time and altitude permit), see section 3.2.4.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 6. Radio – REPORT decision to land on the selected place if necessary. 7. Landing – follow NORMAL or SHORT-FIELD landing procedure as appropriate. 3.2.7 Fire in flight 1. Lane A and B – OFF.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7. Terrain – CONTROL. 8. At safe altitude – PULL YOKE GENTLY to level off. 9. G loads – DO NOT EXCEED +4g. 3.2.12 Alternator failure Follow PRECAUTIONARY LANDING procedure, see section 3.2.6. 3.2.13 Inadvertent spin 1.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 3. Airspeed and vertical speed – CONTROL using throttle. 4. Follow PRECAUTIONARY LANDING procedure, see section 3.2.6. 3.2.15.3 Powerplant instruments failure (Tachometer, oil, water and exhaust temperature indicators, fuel quantity indicator) 1. IGNORE powerplant instruments readings.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 4 Normal Procedures 4.1 General This section describes normal procedures recommended for safe operation of the A-32. 4.2 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.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 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.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 6. Fuel leaks – NONE. 7. Wing fuel tank cap – IN PLACE and SECURE. 8. Wing tip and navigation/strobe light – INTACT. 9. Wing and strut attachment fittings and bolts – IN PLACE, INTACT and SECURE.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 5. Doors – check CLOSED. 6. Battery switch (under left seat) – ON. 7. Master switch – ON. 8. Fuel level – CHECK. 9. Fuel shutoff valves – one OPEN, the other CLOSED. 10. Strobes – ON.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 10. Accelerate to at least 90 km/h (49 kts) at 1-2 m (3-7 ft) and start to climb. 11. Speed – SET best angle of climb speed V = 100 km/h (54 kts). 4.9 Climb 1.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 4.13 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 (49 kts), +10 km/h (5 kts) in rain or strong turbulence.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 5 Performance 5.1 General This section contains performance data of A-32 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.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 6 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.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7 Airplane and Systems Descriptions 7.1 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.
SERIES engine operation and installation manuals. 7.5 Propeller A-32 airplane may be fitted with any propeller, approved by Aeroprakt Ltd. 7.6 Fuel system 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.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH NOTE: Both fuel pumps have capacity 120 l/h. Due to different flow resistance of the return lines from the T-connector 26 (Fig. 3. Fuel system schematic) to the return outlets inside the right and left tanks with both fuel valves 7 and 8 open (Fig. 3), the fuel will be pumped from one of the tanks to the other.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.7 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.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.7.2 AMHT antiservo/trim tab control system The AMHT antiservo/trim tab is used for controlling the force on control yokes in pitch. Fig. 5 AMHT antiservo/trim tab control system The AMHT antiservo/trim tab control system (Fig. 5) is combined, it consists of a lever (1), two Ø1.5 mm (1/16 in) cables (2), a rocker (3), a friction clamp (9) and a rod (4).
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.7.3 Rudder and nose wheel control system The rudder and nose wheel control system (Fig. 6) is combined, it consists of pedals, nose landing gear strut control rocker, two pushrods, two Ø2.5 mm (3/32 in) cables, passing through two front and two rear pulleys.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH (3/32 in) cables, passing through a system of pulleys, two inner and two outer rockers, two inner and two outer pushrods. Fig. 7. Control system of flaperons (drooping ailerons) The control force applied by the pilot to the control stick (1) is passed via the lever (2) to the cables (4) by cable’s terminals (3).
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH The aileron drooping (flap extension) mechanism (Fig. 8) consists of a beam with lever (1) hinged to the upper rim of the frame No.3. Flap position setting is achieved with the fixer (2) having three holes for the pin (3) on the lever. Unfixing is achieved by bending the spring- like lever to the right.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.7.5 Engine controls Fig. 9 Engine RPM 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.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Fig. 10. Brake control system...
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.8 Instrument panel This airplane has the following flight instruments set and instrument panel arrangement: Fig. 11. Instrument panel...
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Numbers in Fig. 11 denote the following: 1. LANE A indicator and marking 2. LANE B indicator and marking 3. Placard with passenger warning: THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT...
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.9 Full and static pressure system The full and static pressure probe (1) (see Fig. 12) is located on the left wing strut. It supplies the air pressure to the altimeter and the airspeed, vertical speed (if installed), angle of attack (if installed) indicators (6).
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.10 Electrical system Electrical system of A-32 serves for generation of electrical power and supplying it to the onboard electrical consumers. When engine is running (at RPM above 1400), electrical power is generated by the engine alternator, converted by a rectifier-regulator (located on the firewall) and is supplied to the consumers and stored in a 12V DC 18Ah battery, located behind the left pilot seat.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Fig. 13. Wiring diagram of A-32 electrical system (main)
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Fig. 14. Wiring diagram of installation of the SV-EMS-221 engine instrument...
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Fig. 15. Wiring diagram of installation of the SV-D1000 flight instrument...
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Fig. 16. Wiring diagram of installation of the servo autopilot...
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH Fig. 17. Wiring diagram for installation of the SV-COM-425 radio Fig. 18. Wiring diagram for installation of PTT buttons...
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 7.11 Seats and harness belts The airplane is equipped with adjustable 4-position seats with rigid structure and soft cushions. The seats are hinged at the front to a transverse beam and at the rear they are resting on nylon support at the lower part of the frame No.3.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 8 Aircraft Ground Handling and Servicing 8.1 Introduction This section contains recommendations on aircraft ground handling and servicing important for safe and efficient operation of this aircraft. Besides owners/pilots should keep contact with the aircraft manufacturer in order to obtain in time all service bulletins relevant to their aircraft.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH the oil tank, remove and clean the oil probe and turn the propeller several times until you hear the sound of air bubbles coming into the oil tank which means that the oil from the oil tank was pumped thus into the engine forcing the air from it back into the oil tank.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 6. Disconnect the wing at its forward and rear attachment points. After disconnecting the wings it is recommended to insert all the fasteners back and lock them with safety wire or pins not to loose them. Also secure with safety wire the spherical bearings in the forward and rear wing attachment fittings.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 8.6.2 Removal of the AFHT Remove the AFHT (see Fig. 22) as follows: 1. Remove the tail fairing of fuselage. 2. Disconnect the control rod from the antiservo/trim tab arm. 3. Disconnect the control rod from the AFHT arm.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 8.6.3 Propeller removal Before dismantling the engine from the aircraft remove the propeller as follows: - undo and remove the attachment bolts; - remove the propeller by pulling gently by its hub. When installing the engine on the aircraft propeller should be installed in reversed order.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 9 Supplements 9.1 General This section contains information concerning the particular configuration of this airplane (list of installed equipment) along with its actual empty weight and balance data. Any additional manuals for the installed equipment are indicated here.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 9.6 List of installed equipment 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 section 6.2 Installed equipment list.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 9.7 Actual empty weight and CG position data This subsection contains information 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 weighed and respective weight...
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 9.8 Airplane Flight Training Supplement Flight training on Aeroprakt-32 airplane foresees 5 hours of flying in accordance with the normal flight procedures, described in Pilot Operating Handbook (POH). It covers the following: 1. Preflight preparation including determining the takeoff mass and airplane CG position, preflight check and preflight servicing of the airplane.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 2. Taxiing is described in the section 4.5. Airfield traffic shall be performed in accordance with the airfield traffic diagram. Before lining up full and free movements of the flight controls must be checked. 3. After lining up the engine power setting shall be increased to full and takeoff shall be performed.
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AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH 9.8.4 Balked landing Balked landing (go around) situation occurs due to errors made during approach which can not be corrected or in case if an obstacle is suddenly detected on the runway. The balked landing procedure is described in the section 4.14.
AEROPRAKT-32 Pilot Operating Handbook A32-iS-129-POH the ground before the other. During the landing roll the nose wheel shall be kept lifted as long as possible and the heading shall be maintained using the rudder pedals. Immediately before the nose wheel is finally touching the ground the rudder pedals shall be set neutral in order to prevent the side load on the nose leg.
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