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AEROPRAKT-32 Pilot Operating Handbook

A32-240-POH

2.6 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 the table in the paragraph

2.7 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).

2.7 Engine

Engine data and operational limitations (as specified in the "OPERATORS MANUAL FOR
ROTAX ENGINE TYPE 912 SERIES") are given in the table below:

Engine manufacturer

BRP-Rotax GmbH&Co KG, Austria

Engine model

Rotax-912UL

Rotax-912ULS

Take-off performance

59.6 kW

73.5 kW

Max. continuous performance

58 kW

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.

140 °C (285 °F)

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)

Содержание AEROPRAKT-32

Страница 1: ...A32 240 POH Airplane Model AEROPRAKT 32 A 32 Airplane Registration Number Airplane Serial Number 240 Date of issue 10 08 2022 Approved by Yuriy Yakovlyev Position Chief designer Date of approval 10 08...

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: ...sswind limitation 10 2 10 Markings and placards 10 3 Emergency procedures 12 3 1 General 12 3 2 Emergency checklists 12 4 Normal Procedures 17 4 1 General 17 4 2 Preflight check 17 4 3 Fuel levels fue...

Страница 4: ...ystem 43 7 10 Electrical system 44 7 11 Seats and harness belts 50 7 12 Cockpit doors 50 7 13 Baggage compartment 50 7 14 Recovery system 50 8 Aircraft Ground Handling and Servicing 52 8 1 Introductio...

Страница 5: ...This A 32 airplane was manufactured by Aeroprakt Ltd 24 Polyova str Kyiv 03056 UKRAINE Tel 380 44 496 77 21 Fax 380 44 496 77 31 E mail aeroprakt kiev gmail com www aeroprakt kiev ua Should the origin...

Страница 6: ...el track 5 ft 9 in 1 75 m Gross weight Maximum Take Off Weight MTOW 992 lb 450 kg Maximum level speed at sea level ISA conditions 116 6 kts 216 km h Cruising speed IAS at 1000 ft ISA conditions engine...

Страница 7: ...d by full control movement VFE Maximum flap extended speed 117 km h 73 mph 63 kts Do not exceed this speed with flaps extended VS1 Stalling speed flaps up 55 km h 34 mph 30 kts At maximum takeoff weig...

Страница 8: ...ceiling of A 32 with Rotax 912ULS 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...

Страница 9: ...ne Engine data and operational limitations as specified in the OPERATORS MANUAL FOR ROTAX ENGINE TYPE 912 SERIES are given in the table below Engine manufacturer BRP Rotax GmbH Co KG Austria Engine mo...

Страница 10: ...ts 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 2 10 M...

Страница 11: ...ioned markings there is a fire resistant aircraft identification plate made off 1 mm aluminum sheet that is attached with rivets to fuselage structure in a clearly visible place left hand side rear ve...

Страница 12: ...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 13: ...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 14: ...mph 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...

Страница 15: ...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 Air...

Страница 16: ...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 17: ...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 18: ...CK 4 2 6 Empennage 1 Empennage surface 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...

Страница 19: ...rd 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 READ...

Страница 20: ...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 21: ...AGAINST CROSSWIND 8 Rudder pedals maintain takeoff direction 9 Liftoff at 65 km h 40 mph 35 kts 10 Accelerate to at least 80 km h 50 mph 43 kts and start to climb 11 Speed SET best angle of climb spe...

Страница 22: ...oid 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 condi...

Страница 23: ...rt field ENGAGE as required Avoid braking at a high speed or nose wheel up 4 14 Balked landing 1 Throttle gradually FULL POWER 2 Descent DISCONTINUE 3 Speed accelerate to at least 90 km h 56 mph 49 kt...

Страница 24: ...mph 43 kts Best rate of climb speed VY 120 km h 75 mph 65 kts 120 km h 75 mph 65 kts Maximum rate of climb at VX 3 5 m s 689 fpm 4 3 m s 846 fpm Maximum rate of climb at VY 4 2 m s 826 fpm 5 m s 984 f...

Страница 25: ...al empty airplane weight and CG position This subsection contains weighing and CG location data of the aircraft in configuration as built Any permanent modification of the aircraft configuration such...

Страница 26: ...pilots 1 663 position of pilots CG total weight of fuel in the tanks 1 60 position of fuel tank CG weight of the baggage in the baggage container 2 320 position of the baggage CG Computation must be p...

Страница 27: ...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 aft...

Страница 28: ...re 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 to 0 04 thickness Engine cowling is made of composites The doors c...

Страница 29: ...automatic valve clearance adjustment two carburetors mechanical membrane fuel pump double electronic ignition system integrated water pump electrical starter integrated gearbox of 2 43 reduction ratio...

Страница 30: ...ed 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 va...

Страница 31: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 31 Fig 3 Fuel system schematic...

Страница 32: ...l system see Fig 4 is combined it consists of two 4 0 mm 5 32 cables passing through a block of pulleys and a fairlead bellcrank and pushrod Push and pull forces are applied by the pilot to the yoke 1...

Страница 33: ...seats and is accessible for both pilots The trim tab control lever is connected with cables 2 to the trim tab control bellcrank 3 The cables are running through the flexible sheaths 6 in the central...

Страница 34: ...wo pulleys 9 near the frame No 9 Adjustment of the nose landing gear position is achieved with pedals set to neutral position using pushrods 4 and 5 The cable tension and adjustment of the rudder posi...

Страница 35: ...e cables are routed using two pulleys 14 on the control column two pulleys 15 aft of the frame No 3 low in the middle two pulleys 16 aft of the frame No 3 low on the sides and two pulleys 17 on the fr...

Страница 36: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 36 Fig 8 Flap extension mechanism Aileron drooping flap extension angles 1st position 10 1 2nd position 20 1...

Страница 37: ...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 pushing it...

Страница 38: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 38 Fig 10 Engine pre start mixture control Fig 11 Carburetor heating control...

Страница 39: ...lied 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 diameter of 3 mm...

Страница 40: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 40 Fig 12 Brake control system...

Страница 41: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 41 7 8 Instrument panel This airplane has the following flight instruments set and instrument panel arrangement Fig 13...

Страница 42: ...rol knob and marking 7 Cockpit heating control knob and marking 8 Left tank fuel level indicator and marking 9 Right tank fuel level indicator and marking 10 Left tank Fuel Low warning light and marki...

Страница 43: ...ft wing is removed during aircraft disassembly The full and static pressure lines are connected to airspeed indicator s altimeter and vertical speed indicator Good condition of the full and static pre...

Страница 44: ...ct the electrical system 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 pow...

Страница 45: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 45 Fig 15 Wiring diagram of A 32 electrical system main...

Страница 46: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 46 Fig 16 Wiring diagram for installation of the SV EMS 220 engine monitor...

Страница 47: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 47 Fig 17 Wiring diagram for installation of the SV HDX1100 SkyView...

Страница 48: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 48 Fig 18 Wiring diagram for installation of the Trig TY91 radio Fig 19 Wiring diagram for installation of the Trig TT21 transponder...

Страница 49: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 49 Fig 20 Wiring diagram for installation of PTT buttons...

Страница 50: ...glass and providing pilot view for landing in poor visibility conditions snow rain etc 7 13 Baggage compartment A 32 has baggage compartment located behind the pilot seats and accessible from inside o...

Страница 51: ...AEROPRAKT 32 Pilot Operating Handbook A32 240 POH 51 Fig 21 Recovery system...

Страница 52: ...8 2 Towing parking and tie down instructions A 32 may be towed manually or using any suitable towing device tow power bar car etc Before towing the airplane make sure that the parking brake is off and...

Страница 53: ...using 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 ca...

Страница 54: ...components left and right wings horizontal tail propeller engine 8 5 1 Wing removal NOTE Before wing removal empty the wing tanks Left and right wings shall be removed in turn in any order according...

Страница 55: ...Wing removal wing to fuselage attachment points Fig 24 Wing removal wing strut attachment points 8 5 2 Removal of the AMHT Remove the AMHT see Fig 25 as follows 1 Remove the tail fairing of fuselage 2...

Страница 56: ...T attachment to fuselage and remove the AMHT Insert all fasteners back and secure them Fig 25 Removal of the AMHT 8 5 3 Propeller removal Before dismantling the engine from the aircraft remove the pro...

Страница 57: ...stem cables connector is installed on the firewall disconnect the throttle and choke control cables disconnect fuel lines drain the fuel from the float chambers of the carburetors pull away the exhaus...

Страница 58: ...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 59: ...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 60: ...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 61: ...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 62: ...90 km h 56 mph 49 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 2...

Страница 63: ...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 64: ...peller 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 training...

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