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AEROPRAKT-32 Pilot Operating Handbook

A32-103-POH

2.6 Engine

Engine data and operational limitations are given in the table below:

Engine manufacturer

BRP-Rotax GmbH&Co KG, Austria

Engine model

Rotax-912ULS

Take-off performance

73.5 kW

Max. continuous performance

69 kW

Take-off speed

5800 rpm (max. 5 min.)

Max. continuous speed

5500 rpm

Idle speed

min. 1400 rpm

Oil pressure

max.

7 bar (102 psi)

min.

0.8 bar (12 psi) (below 3500 rpm)

normal

2.0 to 5.0 bar (27

–73 psi) (above 3500 rpm)

Oil temperature

max.

130 °C (266 °F)

min.

50 °C (120 °F)

normal

approx. 90 to 110 °C (190-230 °F)

Exhaust gas temperature, max.

880 °C (1616 °F)

Coolant temperature limit
measured in cylinder head

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

max.

0.5 bar (7.26 psi)

min.

0.15 bar (2.2 psi)

Fuel

antiknock properties

min. RON 95 (min. AKI 91

)

European standard

EN 228 super,

EN 228 super plus

Aviation standard

AVGAS 100 LL

(ASTM D910)

Oil:

with 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.

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).

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.

Anti Knock Index (RON+MON)/2

Содержание A32-103-POH

Страница 1: ...g Handbook A32 103 POH Airplane Model AEROPRAKT 32 A 32 Airplane Registration Number Airplane Serial Number 103 Date of issue XX XX 20XX Approved by Yuriy Yakovlyev Position Chief designer Date of app...

Страница 2: ...e 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 blac...

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

Страница 4: ...7 13 Baggage compartment 49 7 14 Recovery system 49 8 Aircraft Ground Handling and Servicing 51 8 1 Introduction 51 8 2 Towing parking and tie down instructions 51 8 3 Servicing fuel oil and coolant...

Страница 5: ...F2316 12 Standard Specification for Airframe Emergency Parachutes for Light Sport Aircraft F2339 06 Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Spor...

Страница 6: ...ase 4 ft 2 in 1 27 m Wheel track 5 ft 9 in 1 75 m Gross weight Maximum Take Off Weight MTOW 1320 lb 600 kg Top speed at sea level ISA conditions 116 kts 215 km h Cruising speed IAS at 1000 ft ISA cond...

Страница 7: ...50 27 VS0 stalling speed at maximum takeoff weight with full flaps Green arc start 60 32 VS stalling speed at maximum takeoff weight with flaps up White arc 50 147 27 79 VS0 to VFE flap extended spee...

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 2...

Страница 9: ...C 120 F ambient temperature min 25 C 13 F oil temperature Fuel pressure max 0 5 bar 7 26 psi min 0 15 bar 2 2 psi Fuel antiknock properties min RON 95 min AKI 911 European standard EN 228 super EN 228...

Страница 10: ...bandon cockpit 5 Take measures to extinguish the fire 3 2 2 Engine failure during takeoff 3 2 2 1 during takeoff roll 1 Throttle IDLE 2 Ignition OFF 3 Brakes APPLY as necessary 3 2 2 2 immediately aft...

Страница 11: ...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 o...

Страница 12: ...h 59 kts best glide 3 Oil pressure CONTROL 4 Oil pressure normal follow PRECAUTIONARY LANDING procedure see section 3 2 6 5 Oil pressure high follow EMERGENCY LANDING procedure see section 3 2 5 3 2 1...

Страница 13: ...ckage 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 in...

Страница 14: ...l quantity indicator 1 IGNORE powerplant instruments readings 2 Engine rpm CONTROL by engine noise 3 Follow PRECAUTIONARY LANDING procedure see section 3 2 6 3 2 16 Loss of flight controls 1 Elevator...

Страница 15: ...rainwater snow frost ice and dirt 3 Rigging CHECK visually 4 External damage NONE 4 2 2 Power plant 1 Propeller and spinner CLEAN INTACT and SECURE 2 Top cowling REMOVE for engine inspection 3 Oil coo...

Страница 16: ...rface CLEAN and INTACT 2 Clamps stops REMOVED 3 Horizontal stabilizer attachment fittings and bolts INTACT and SECURE 4 Rudder elevator and trim tab CLEAN and INTACT 5 Rudder elevator and trim tab hin...

Страница 17: ...r 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 Movements of controls che...

Страница 18: ...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 0 bar 29 73 psi at above 3500...

Страница 19: ...IND 8 Rudder pedals maintain takeoff direction 9 Liftoff at 65 km h 35 kts 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 VX 100 km...

Страница 20: ...gently to lower the nose wheel slowly Pedals set NEUTRAL before touching ground with the nose wheel in cross wind conditions 7 Flaps RETRACT 8 Brakes ENGAGE as required Avoid braking at a high speed o...

Страница 21: ...g Handbook A32 103 POH 21 4 14 Balked landing 1 Throttle gradually FULL POWER 2 Descent DISCONTINUE 3 Speed accelerate to at least 100 km h 54 kts flying level 4 Climb at 100 km h 54 kts 5 Flaps RETRA...

Страница 22: ...specified below Best angle of climb speed VX 100 km h 54 kts Best rate of climb speed VY 120 km h 65 kts Maximum rate of climb at VX 2 8 m s 551 fpm Maximum rate of climb at VY 4 2 m s 827 fpm 5 4 Cru...

Страница 23: ...nce lead to unsafe operation 6 1 Weight and Balance Chart This subsection contains weighing and CG location data of the aircraft in configuration as built Any permanent modification of the aircraft co...

Страница 24: ...must be between 1 529 m and 1 780 m 19 and 37 MAC as shown in Fig 2 6 2 Installed equipment list This subsection contains a table with the list of the installed optional equipment affecting weight an...

Страница 25: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 25 No Equipment description and Part No Weight kg CG arm m...

Страница 26: ...The fuselage is an all metal semimonocoque structure The frames are made of 6061T6 aluminum alloy sheets of 0 063 to 0 080 thickness The fuselage skin is made of 2024T3 aluminum alloy sheets of 0 02...

Страница 27: ...x 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 two carburetors mechani...

Страница 28: ...ted visually through a window in the protecting cover of the aileron control cables The bottom outlet of the fuel sediment collector is connected to the drain valve 28 with a drain line 27 The drain v...

Страница 29: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 29 Fig 3 Fuel system schematic...

Страница 30: ...g 4 is combined it consists of two 4 0 mm 5 32 cables passing through a block of pulleys and a fairlead rocker and pushrod Push and pull forces are applied by the pilot to the control stick 1 is passe...

Страница 31: ...cables are running through the flexible sheaths 6 in the central console and a fairlead 7 located near frame No 9 The antiservo trim tab is hinged at the trailing edge of the AMHT Tension of the cabl...

Страница 32: ...ched to the nose landing gear strut is connected to the pedals with the right 4 and left 5 pushrods The right 6 and left 7 cables connect the pedals to the rudder arms The cable routing is ensured wit...

Страница 33: ...lumn rocker two 2 5 mm 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 contr...

Страница 34: ...1 down 13 1 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 thre...

Страница 35: ...bolt 7 Rearmost throttle lever position corresponds to MIN engine RPM the foremost position to MAX engine RPM Pulling the friction force adjusting lever back increases the throttle lever friction pus...

Страница 36: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 36 Fig 10 Engine pre start mixture control...

Страница 37: ...he pressure supplied from the master cylinder 1 to the slave cylinders 5 in the wheels The main LG wheels have disk brakes The cylinders are connected to each other with copper tubing 6 with outside d...

Страница 38: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 38 Fig 12 Brake control system...

Страница 39: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 39 7 8 Instrument panel This airplane has the following flight instruments set and instrument panel arrangement Fig 13 Instrument panel...

Страница 40: ...MIT LOAD FACTOR 4 0 2 0 5 Carburetor control knob and marking 6 Cockpit heating control knob and marking 7 Left tank fuel level indicator and marking 8 Right tank fuel level indicator and marking 9 Le...

Страница 41: ...joints 5 used to disconnect the lines when the left wing is removed during aircraft disassembly The full 2 and static 3 pressure lines are connected to the airspeed indicator The altimeter and vertic...

Страница 42: ...em and consumers from short circuit and must be of appropriate type and size When battery is supplying power to the consumers while alternator is not generating and supplying power to the battery e g...

Страница 43: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 43 Fig 15 Wiring diagram of A 32 electrical system main...

Страница 44: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 44 Fig 16 Wiring diagram of Dynon SkyView system installation page 1...

Страница 45: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 45 Fig 17 Wiring diagram of Dynon SkyView system installation page 2...

Страница 46: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 46 Fig 18 Wiring diagram of Dynon SkyView system installation page 3...

Страница 47: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 47 Fig 19 Wiring diagram for installation of the Funkwerk ATR833 radio Fig 20 Wiring diagram for installation of the Funkwerk TRT800H transponder...

Страница 48: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 48 Fig 21 Wiring diagram for installation of PTT buttons...

Страница 49: ...the closed position with a lock Both left and right doors have air scoops for ventilation de misting of the glass and providing pilot view for landing in poor visibility conditions snow rain etc 7 13B...

Страница 50: ...AEROPRAKT 32 Pilot Operating Handbook A32 103 POH 50 Fig 22 Recovery system...

Страница 51: ...tie down shall be done with its nose into the wind preferably or at least across the wind but never tail to the wind to avoid damaging the control surfaces For tying the airplane down use the wing st...

Страница 52: ...oaked in water with addition of mild washing agents Never use gasoline solvents or other aggressive liquids for washing the airplane and especially the cockpit glass Cockpit glass must be finally wash...

Страница 53: ...ecting 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...

Страница 54: ...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 4 Unfasten the bolts of the AFHT attachment t...

Страница 55: ...the oil and close all drain openings with plugs remove the oil cooler disconnect electrical system cables connector is installed on the firewall disconnect the throttle and choke control cables disco...

Страница 56: ...ith 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 effici...

Страница 57: ...pment 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...

Страница 58: ...n 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 w...

Страница 59: ...following 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 Ele...

Страница 60: ...h 54 kts and engine speed adjusted so that in the beginning of the final turn the airplane is at approximately 500 ft 9 It is recommended to make the final turn with a bank angle below 20 While making...

Страница 61: ...ads due 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 fi...

Страница 62: ...g propeller 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 tra...

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