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“AERO” Sp. z o.o.

SECTION 7

AT-3 R100

DESCRIPTION OF THE AEROPLANE

AND ITS EQUIPMENT

JULY, 2010

Page 7-21

AEROPLANE FLIGHT MANUAL

7.7. Luggage compartment

The luggage compartment is located behind the seats and consists of

two containers (see illustration).

The containers are fitted with lids made of metal, locked by latches.

Pressing the latch releases it and enables the lid to be opened. The

luggage compartment allows for luggage of 30 kg total weight; 20 kg

in the port container and 10 kg in the starboard one.

Lid of the luggage
compartment

The port and the
starboard luggage
containers

Extinguisher

CAUTION

IT IS PROHIBITED TO CARRY INFLAMMABLE, CORROSIVE,
EXPLOSIVE, RADIOACTIVE AND OTHER MATERIALS IN THE
LUGGAGE COMPARTMENT, WHICH ARE HARMFUL FOR HUMAN
HEALTH OR LIFE.

Summary of Contents for AT-3 R100

Page 1: ...AVIATION TRAINING Pilot s Operating Handbook Aero AT3 R100 HA VOA ...

Page 2: ...stration Call sign Aeroplane Serial No Registered under No Approved CIVIL AVIATION OFFICE President of the CAO Originally signed for President of the CAO by Mr Z Mazan Date 2004 09 23 This aeroplane must be operated in accordance with information and limitations contained in this Manual This Manual must be carried in the aeroplane at all times Doc No ATL3 04 ...

Page 3: ...942 WARSAW POLAND UL WAŁ MIEDZESZYŃSKI 844 Approval of translation has been done to the best knowledge and judgment In any case the original Polish language version is authoritive English language version of the Polish Document No ATL3 03 AFM translated under delegation of authority CAIB No 54C Jan A Jasiński B S Eng ...

Page 4: ...00 SEPTEMBER 2004 Page 0 3 AEROPLANE FLIGHT MANUAL CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE 6 DESCRIPTION OF THE AEROPLANE AND ITS EQUIPMENT 7 SERVICING 8 SUPPLEMENTS 9 ...

Page 5: ...ion of actual changes of weighing data must be recorded in the table below The new or corrected text in the corrected pages is to be marked at the margin with a vertical line and the number of the revision and the date of the revision is to be printed at the bottom of the page For each revision the pages specified in the Log of Revisions must be replaced 6 ...

Page 6: ...TEMBER 2004 1 1 3 AUGUST 2008 1 1 4 SEPTEMBER 2004 1 1 5 SEPTEMBER 2004 1 1 6 SEPTEMBER 2004 1 1 7 SEPTEMBER 2004 1 1 8 SEPTEMBER 2004 1 1 9 SEPTEMBER 2004 1 1 10 SEPTEMBER 2004 1 1 11 SEPTEMBER 2004 1 1 12 SEPTEMBER 2004 1 1 11 SEPTEMBER 2004 1 1 12 SEPTEMBER 2004 2 Appvd 2 1 SEPTEMBER 2004 2 Appvd 2 2 SEPTEMBER 2004 2 Appvd 2 3 SEPTEMBER 2004 2 Appvd 2 4 SEPTEMBER 2004 2 Appvd 2 5 AUGUST 2008 2 ...

Page 7: ... SEPTEMBER 2004 4 Appvd 4 1 SEPTEMBER 2004 4 Appvd 4 2 SEPTEMBER 2004 4 Appvd 4 3 SEPTEMBER 2004 4 Appvd 4 4 SEPTEMBER 2004 4 Appvd 4 5 JULY 2010 4 Appvd 4 6 JULY 2010 4 Appvd 4 7 JULY 2010 4 Appvd 4 8 JULY 2010 4 Appvd 4 9 JULY 2010 4 Appvd 4 10 JULY 2010 4 Appvd 4 11 OCTOBER 2009 4 Appvd 4 12 JULY 2010 4 Appvd 4 13 OCTOBER 2009 4 Appvd 4 14 OCTOBER 2009 4 Appvd 4 15 JULY 2010 4 Appvd 4 16 SEPTEM...

Page 8: ...5 5 14 SEPTEMBER 2004 5 5 15 SEPTEMBER 2004 5 5 16 SEPTEMBER 2004 6 6 1 SEPTEMBER 2004 6 6 2 SEPTEMBER 2004 6 6 3 JULY 2010 6 6 4 SEPTEMBER 2004 6 6 5 SEPTEMBER 2004 6 6 6 JULY 2010 6 6 7 JULY 2010 6 6 8 JULY 2010 6 6 9 SEPTEMBER 2004 6 6 10 MARCH 2006 6 6 11 JULY 2010 6 6 12 JUNE 2011 7 7 1 JULY 2010 7 7 2 SEPTEMBER 2004 7 7 3 SEPTEMBER 2004 7 7 4 SEPTEMBER 2004 7 7 5 SEPTEMBER 2004 7 7 6 SEPTEMB...

Page 9: ... JULY 2010 7 7 18 JULY 2010 7 7 19 JULY 2010 7 7 20 JULY 2010 7 7 21 JULY 2010 7 7 22 JULY 2010 7 7 23 JULY 2010 7 7 24 JULY 2010 7 7 25 JULY 2010 7 7 26 JULY 2010 7 7 27 JULY 2010 7 7 28 JULY 2010 7 7 29 JULY 2010 7 7 30 JULY 2010 8 8 1 JULY 2010 8 8 2 SEPTEMBER 2004 8 8 3 SEPTEMBER 2004 8 8 4 JULY 2010 8 8 5 JULY 2010 8 8 6 JULY 2010 8 8 7 JULY 2010 8 8 8 JULY 2010 8 8 9 JULY 2010 8 8 10 JULY 20...

Page 10: ...3 R100 GENERAL INFORMATION JUNE 2011 Page 0 9 AEROPLANE FLIGHT MANUAL List of Effective Pages continued Section Page Date of issue 9 9 2 SEPTEMBER 2004 9 9 3 AUGUST 2008 9 9 4 JULY 2009 9 9 5 OCTOBER 2010 9 9 6 JUNE 2011 ...

Page 11: ... 6 12 7 15 to 7 30 9 3 9 4 29 08 2008 7 Introduction of the Supplement No 30 changed pages 9 26 3 9 in Supplement 26 0 5 0 7 to 0 9 6 12 9 4 10 07 2009 8 Introduction of the Supplement No 31 32 33 and text modifications 0 5 to 0 9 3 2 4 5 to 4 7 4 9 do 4 11 4 13 4 14 6 12 9 5 9 6 02 10 2009 9 Changes to parking brake system Tow bar Extending area of acceptable movement of center of gravity Changed...

Page 12: ...AL Section 1 GENERAL Page 1 1 Introduction 1 2 1 2 Basis of certification 1 3 1 3 Warnings cautions and remarks 1 3 1 4 Descriptive data 1 4 1 4 1 Airframe 1 4 1 4 2 Engine 1 5 1 4 3 Propeller 1 5 1 5 View of the aeroplane three projections 1 6 1 6 List of definitions and abbreviations 1 7 ...

Page 13: ...turer It is the pilot s responsibility to acquaint him herself with the contents of this manual as well as with any revisions to it CAUTION THIS AEROPLANE FLIGHT MANUAL IS NOT A FLIGHT TRAINING MANUAL SEPARATE FLIGHT TRAINING MANUALS EXIST FOR THAT PURPOSE Should this manual be lost the General Inspectorate of Civil Aviation Civil Aircraft Inspection Board is to be notified immediately and if outs...

Page 14: ...e No A 021 1 3 Warnings cautions and remarks The definitions below concern the following expressions warning caution note WARNING means that if the warnings concerned are not followed this will lead to an immediate or significant reduction in flight safety CAUTION means that if the precautions concerned are not followed this will lead to an immediate or significant reduction in flight safety NOTE ...

Page 15: ...3 Dihedral 3 Lifting area 9 30 m2 100 1 ft2 Mean aerodynamic chord 1 27 m 4 2 Wing loading 62 6 kg m2 12 8 lb ft2 Wing profile NACA 4415 2 Control surface displacements Slab tail angles related to the fuselage base red mark on the fuselage Trailing edge down 10 1 Trailing edge up 12 1 Trim balancing tab angles related to the fuselage base red mark at the fuselage When the slab tail trailing edge i...

Page 16: ...6 m 7 5 Main wheel tyre Type 380 x 150 Pressure 2 5 bar 36 psi Nose wheel tyre Type 5 00 4 Pressure 2 5 bar 36 psi Disc brakes Type of shock absorber elastic strut 1 4 2 Engine Four cylinder horizontally opposed BOMBARDIER ROTAX model 912S2 or 912S4 engine The cylinders are air cooled the cylinder heads by liquid coolant Dual ignition 73 5 kW 98 5 HP take off power 69 kW 92 5 HP continuous power 1...

Page 17: ...SECTION 1 AERO Sp z o o GENERAL AT 3 R100 Page 1 6 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL 1 5 View of the aeroplane three projections ...

Page 18: ...ic airflow in the conditions of the standard atmosphere at sea level without corrected errors of the airspeed measuring system All IAS values in this manual presume the airspeed measuring system error to be zero CAS CALIBRATED AIRSPEED means the speed of an air vessel after aerodynamic and instrument correction The calibrated airspeed is equal to the true airspeed in the conditions of the standard...

Page 19: ...f the structure VFE Maximum airspeed with wing flaps extended This is the maximum permitted airspeed of the aeroplane with wing flaps extended VS1 Stalling speed or minimum airspeed of steady flight at which the aeroplane is steerable in any other configuration than the landing configuration VS0 Stalling speed or minimum airspeed of steady flight at which the aeroplane is steerable in the landing ...

Page 20: ...a l evel up to the altitude at which the temperature is 56 5 C 70 F OAT Outside Air Temperature This is the temperature of the static air read from the thermometer or received from the ground meteorological service with instrument error and air compressibility effect corrected Pressure altitude This is the altitude read from the altimeter preset to the standard pressure at the average sea level 10...

Page 21: ...nt of operational agents oil cooling agent and hydraulic fluid Centre of Gravity imaginary point on the aeroplane The aeroplane suspended at this point is in equilibrium Limits of the CG range of C G positions which must not be exceeded when loading the aeroplane to a given total weight MAC the Mean Aerodynamic Chord Consumable fuel This is the amount of fuel which may be consumed without symptoms...

Page 22: ... 15 m 50 ft This distance is to be measured parallel to the takeoff surface Landing distance the distance from the location where the aeroplane has the altitude of 15 m 50 ft to the location where the aeroplane stops This distance is to be measured parallel to the takeoff surface Landing run the distance from the location where the aeroplane touches down on the landing surface to the location wher...

Page 23: ...SECTION 1 AERO Sp z o o GENERAL AT 3 R100 Page 1 12 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL THIS PAGE IS LEFT INTENTIONALLY BLANK ...

Page 24: ...eds 2 2 2 3 Marking of the airspeed indicator 2 3 2 4 Power plant 2 4 2 5 Marking of the engine monitoring instruments 2 6 2 6 Weight 2 7 2 7 Centre of Gravity 2 8 2 8 Approved manoeuvres 2 9 2 9 Controlled Load Factors 2 10 2 10 Crew of the aircraft 2 10 2 11 Types of operation 2 10 2 12 Fuel 2 12 2 13 Number of seats 2 12 2 14 Limitation placards 2 12 ...

Page 25: ...ed Limitations Designation IAS Airspeed km h mph kts REMARKS Maximum never exceed airspeed VNE 236 146 127 This airspeed must not be exceeded in any condition of operation Maximum structural cruising speed VNO 208 129 112 This airspeed cannot be exceeded except in non turbulent conditions and then only with care Manoeuvring speed VA 208 129 112 Above this airspeed no full or rapid displacement of ...

Page 26: ...White sector Range for safe deployment of wing flaps Green sector Range of normal operation Yellow sector Range of limited operation manoeuvres to be performed with care and in non turbulent air only Red line Maximum airspeed for any kind of operation Airspeed ranges IAS km h mph kts White sector from to 81 158 50 98 44 85 Green sector from to 96 208 60 129 52 112 Yellow sector from to 208 236 129...

Page 27: ...HP Engine maximum RPM take off 5 MIN continuous idle 5 800 rpm 5 500 rpm 1 400 rpm Maximum cylinder head temperature CHT 135 C 275 F Oil temperature maximum 130 C 266 F minimum 50 C 122 F normal operational 90 to 110 C 194 to 230 F Oil pressure minimum maximum normal 0 8 bar 11 6 psi 7 bar 101 5 psi 2 5 bar 29 72 5 psi Fuel pressure maximum minimum 0 40 bar 5 8 psi 0 15 bar 2 2 psi Engine Starting...

Page 28: ...o 104 F from 25 C to 40 C 13 F to 104 F from 30 C to 40 C 22 F to 104 F SAE 20W 50 SAE 20W 40 SAE 15W 40 15W 50 SAE 10W 40 SAE 5W 50 SAE 5W 40 maximum amount of oil minimum amount of oil 3 5 litres 3 6 US qts 2 5 litres 2 6 US qts Cooling agent Water free anti freeze liquid suitable for aluminium radiators Capacity of the system 2 litres 2 1 US qts For recommended by engine manufacturer types of c...

Page 29: ...sured parameter Minimum limit Range of normal operation Range of limited operation Maximum limit Tachometer 1 400 to 5 500 rpm 0 1400 rpm 5500 5800 rpm 5800 7000 rpm Oil temperature 50 C 120 F 90 110 C 194 230 F 50 90ºC 120 194 F 110 130ºC 230 266 F 130 C 266 F CHT 75 135 C 167 275 F 135 C 275 F Exhaust gas temperature 600 850 C 1112 1560 F 850 880 C 1560 1616 F 880 900 C 1616 1652 F Oil pressure ...

Page 30: ...HT MANUAL 2 6 Weight Maximum take off weight 582 kg 1283 lb Maximum landing weight 582 kg 1283 lb Empty equipped aeroplane weight 350 kg 772 lb Maximum load in the luggage compartment port luggage compartment large starboard luggage compartment small 30 kg 66 lb 20 kg 44 lb 10 kg 22 lb ...

Page 31: ... z o o LIMITATIONS AT 3 R100 Page 2 8 JULY 2010 AEROPLANE FLIGHT MANUAL 2 7 Limitation of C G position Distance of the extreme C G positions from the leading edge of the Mean Aerodynamic Chord MAC WEIGHT ARM MAC 9 9 9 9 ...

Page 32: ...ne is approved to perform the following manoeuvres All normal flight manoeuvres Stall except tail slide Lazy eight Chandelle Steep turn not exceeding 60 of bank Entry airspeed IAS km h mph kts Lazy eight 190 118 102 Chandelle 220 136 118 Steep turn with 60 of bank 170 105 91 WARNING AEROBATICS AND INTENTIONAL SPINS ARE PROHIBITED ...

Page 33: ...laps extended 0 to 2 2 10 Crew of the aircraft The minimum crew of this aeroplane is 1 pilot 2 11 Types of operation This aeroplane is approved for flights by day in Visual Meteorological Conditions VMC Day This aeroplane is approved to operate according to Day VFR when the equipment specified in the LIST OF MINIMUM EQUIPMENT is installed and working correctly WARNING FLIGHTS IN KNOWN ICING CONDIT...

Page 34: ... light 1 1 1 1 FLIGHT AND NAVIGATION INSTRUMENTS 1 Airspeed indicator 2 Altimeter 3 Magnetic compass 1 1 1 ENGINE MONITORING INSTRUMENTS 1 Tachometer 2 Cylinder head temperature indicator 3 Exhaust gas temperature indicator 4 Oil temperature indicator 5 Oil pressure indicator 6 Fuel quantity indicator 7 Fuel pressure indicator 1 1 1 1 1 1 1 In the column VFR DAY the equipment is marked which must ...

Page 35: ...oline of minimum RON 95 EN228 Premium EN228 Premium Plus Aviation gasoline AVGAS 100LL Refer to the Rotax 912S Series Engine Operating Manual for limitations and recommendations relating to fuel grades used 2 13 Number of seats This aeroplane has two seats The dual control system enables the aeroplane to be controlled from both the port and starboard seats 2 14 Limitation placards Placards on the ...

Page 36: ...D VA 208 km h IAS or MAX MANOEUVRING SPEED VA 112 KTS IAS or MAX MANOEUVRING SPEED VA 129 MPH IAS On the starboard luggage compartment LUGGAGE 10 kg or LUGGAGE 22 lb On the port luggage compartment LUGGAGE 20 kg or LUGGAGE 44 lb On the jettisoning handle of the canopy PULL TO JETTISON CANOPY On the opening handle of the canopy OPEN LOCK CANOPY LOCK OPEN CANOPY 6 6 6 6 ...

Page 37: ...MANUAL On the fuel tank filler airplane to AT3 054 FUEL 70 LITRES UNLEADED MIN RON 95 EN228 Premium Premium Plus AVGAS 100LL airplane from AT3 055 FUEL 65 LITRES UNLEADED MIN RON 95 EN228 Premium Premium Plus AVGAS 100LL On the oil filler one from below labels OIL 3 5 L OIL 3 6 US QTS ...

Page 38: ...3 4 Smoke and fire 3 4 3 4 1 Fire on ground 3 4 3 4 2 Fire in flight 3 4 3 5 Gliding 3 5 3 6 Emergency landing 3 5 3 6 1 Precautionary landing 3 5 3 6 2 Landing after engine failure 3 6 3 7 Recovering from unintentional spin 3 6 3 8 Other emergency procedures 3 7 3 8 1 Icing 3 7 3 8 2 Abandoning the aeroplane with use of parachute 3 7 3 8 3 Failure of the electric system 3 7 3 8 4 Failure of the s...

Page 39: ...uel pump OFF Fuel valve SHUT Throttle IDLE Ignition switch OFF Battery and generator OFF Landing ahead avoiding obstacles if any 3 2 2 Engine failures in flight Fuel pressure drop engine power drop Fuel pump Fuel valve opening Fuel quantity on board ON To be CHECKED To be CHECKED Excessive engine vibration Carburettor heating Fuel pump Switch ON Switch ON Exceeding the cylinder head temperature Te...

Page 40: ...e propeller does windmill ignition ON If the propeller has stopped engine starter ON If the engine starts to run Throttle according to the required power SET Operational parameters of the engine To be CHECKED Emergency fuel pump OFF If the engine does not start to work Perform EMERGENCY LANDING NOTE The engine can be re started in the entire range of operational airspeeds and altitudes The loss of...

Page 41: ...OFF Electrical equipment OFF Battery and generator OFF Fire extinguisher TO BE USED 3 4 2 Fire in flight In case of engine fire in flight Maintain airspeed IAS 120 km h 75 mph 65 kts Fuel valve PULL SHUT Throttle FULL OPEN Ignition switch OFF Battery and generator OFF Cabin canopy vents SHUT A side slip opposite to the fire to blow it out TO BE PERFORMED When the engine stops PERFORM EMERGENCY LAN...

Page 42: ... Gliding flight Recommended aeroplane configuration Wing flaps retracted Airspeed IAS 120 km h 75 mph 65 kts Throttle IDLE Gliding ratio No power 8 3 6 Emergency landing 3 6 1 Precautionary landing Landing place IDENTIFY Wing flaps to 40º EXTEND Maintain approach airspeed IAS 100 km h 62 mph 54 kts Safety belts FASTEN FIRMLY Electrical equipment OFF Locks of the canopy UNLOCK Before touch down Fue...

Page 43: ...FF Fuel valve PULL SHUT Battery and generator OFF Ignition switch OFF Throttle IDLE 3 7 Recovering from unintentional spin In case of an unintentional spin the following recovering procedure is to be used Throttle IDLE Rudder opposite to aeroplane rotation APPLY Control stick NEUTRAL Ailerons NEUTRAL Wing flaps RETRACT When the aeroplane stops to rotate Rudder NEUTRAL Control stick gentle proceed ...

Page 44: ...eroplane with use of parachute Maintain airspeed IAS 120 km h 75 mph 65 kts Fuel Valve PULL SHUT Ignition switch OFF Battery and generator OFF Headset cables DISCONNECT Safety belts UNFASTEN Canopy Pull both jettisoning levers and push out the canopy both hands TO BE JETISONED The aeroplane TO BE ABANDONED The parachute at a safe distance DEPLOY 3 8 3 Failure of the electric system Check the condi...

Page 45: ... with flight parameters monitored by the tachometer and other correctly working flight and navigational instruments only On ground water sediment is to be removed from the systems and the sensors of static and pitot pressure checked to be clean and not constricted Have the systems checked for leakage 3 8 5 Failure of balancing tab control system of slab tail In case of failure of the balancing tab...

Page 46: ...eeds for safe operation 4 8 4 5 2 Before starting engine 4 8 4 5 3 Using an electric ground power source 4 9 4 5 4 Engine starting 4 9 4 5 5 Before taxiing 4 12 4 5 6 Taxiing 4 12 4 5 7 Before takeoff 4 13 4 5 8 Takeoff 4 13 4 5 9 Climb 4 13 4 5 10 Cruise 4 14 4 5 11 Descent 4 14 4 5 12 Before landing 4 14 4 5 13 Landing 4 14 4 5 14 Balked landing 4 14 4 5 15 After the landing 4 14 4 5 16 Engine s...

Page 47: ...lane Section 2 6 Transport of the de rigged Aeroplane 4 3 Daily pre flight and post flight inspection Recommended daily pre flight inspection Check amount of fuel oil and engine coolant Check for leaks of oil fuel and coolant Drain fuel sediment Check condition of exhaust pipes Check condition of nose and main landing gear condition of the tyres tyre pressure visually condition of rubber shock abs...

Page 48: ...y check condition of the stabilisers and control surfaces Visually check condition and secure fixing of the safety belts Check free and smooth movement of the flight control system i e the elevator rudder ailerons and wing flaps and check it for significant play or excessive friction Check the levers controlling the engine move smoothly Visually check condition of all board instruments Check condi...

Page 49: ... antennas Check the general condition of the aeroplane and its landing gear 4 4 Preparation for flight 4 4 1 Determining weight and Centre of Gravity The pilot is responsible for the correct aeroplane loading It is his duty to ensure that the C G position does not move outside the permissible limits defined in item 2 7 Centre of Gravity The method for calculating total weight and C of G position i...

Page 50: ... Cabin Canopy Opening closing and operation of locks CHECK Inside cabin All foreign items REMOVE Collapsible tow bar from flying controls if installed REMOVE Condition of the seats Luggage collapsible tow bar if will carry CHECK SECURE Seat belts CHECK Flight controls Free movement lack of significant play and extensive friction CHECK Balancing tab Full travel Take off setting CHECK ESTABLISH Wing...

Page 51: ...osed and locked CHECK 3 Port landing gear Tyre Check the tyre pressure visually CHECK Brake system CHECK 3 4 Fuselage front part Canopy Visually check cleanliness CHECK Fuel tank Fuel quantity and locking the filler cap CHECK Engine cowling Locking and leaks CHECK Propeller and spinner Condition and cleanliness CHECK Exhaust pipes Condition CHECK Antenna of transponder Condition and fixing CHECK F...

Page 52: ...es CHECK Inspection flap to be closed and locked CHECK 8 Fuselage rear part starboard Structure Condition and cleanliness CHECK Antennae Condition and cleanliness CHECK 9 Empennage Fin Condition and cleanliness CHECK Rudder Hinges and their play CHECK Slab tail Hinges and their play CHECK Trim balancing tab Hinges and their play CHECK 10 Fuselage rear part port Structure Condition and cleanliness ...

Page 53: ... climb VY 15º 110 68 59 In rough air recommended 0º 160 99 86 Landing approach 40º 100 62 54 Maximum cross wind component 0 to 40º 21 6 13 4 11 7 4 5 2 Before starting engine Seat in the cabin TO BE OCCUPIED Canopy SHUT AND LOCK Luggage stow secure CHECK Seat belts FASTEN Reading of the fuel quantity indicator CHECK Ignition to be switched off CHECK Battery and generator to be switched off CHECK A...

Page 54: ...ust be 12 to 14 Volts The engine starting procedure when using an external power source is the same as when using the aeroplane s own battery After completing engine start the external source is to be disconnected from the aeroplane CAUTION Incorrect connection of the poles may result in damage of the electrical system of the aeroplane 4 5 4 Engine starting CAUTION During conducting the engine tes...

Page 55: ...rking the STARTER ENGAGED light is illuminated NOTE After completing the engine start check whether the oil pressure starts to rise within 10 sec The speed of the engine may be increased only when the oil pressure is stabilised above 2 bar 29 psi CAUTION To avoid damage to battery or starter never keep the starter switched on for longer than 10 sec Allow at least 2 min before switching on again Ne...

Page 56: ...ove the engine operations in low ambient temperature it is recommended that the air intake covers are used NOTE At low ambient temperature engine starting may prove difficult because of a drop in the capacity of the battery Using external electrical power is recommended After starting the engine Engine speed of 2500 RPM keep until smooth engine operation is achieved MAINTAIN GENERATOR FAILURE ligh...

Page 57: ...ust not exceed 120 RPM Carburettor heating CHECK Engine idle speed 1600 RPM CHECK Engine short time COOLING 4 5 5 Before taxiing Artificial horizon ON Turn indicator ON Altimeter SET Radio SET ON AND CHECK Transponder if required code and SBY SET 4 5 6 Taxiing Brakes RELEASE Operation of the brakes CHECK Control stick to be set according to wind condition EXECUTE Taxiing is to be performed using b...

Page 58: ...o be set properly CHECK Turn indicator and artificial horizon to operate correctly 4 5 8 Take off Brakes RELEASE Throttle to be opened to full travel gradually EXECUTE Take off direction maintain using rudder pedals EXECUTE Airspeed after lift off to be maintained at IAS 112 km h 70 mph 60 kts Landing gear rotating wheels BRAKE When height 15 m 50 reached increase to speed to IAS 120 km h 75 mph 6...

Page 59: ...el pump ON Carburettor heating as required SET Throttle as required SET Wing flaps as for landing δ 40 SET Airspeed for final approach to be maintained IAS 100 km h 62 mph 54 kts 4 5 13 Landing Engine rating at altitude below 15 m 50ft to be DIMINISHED Touch down with the main wheels at airspeed IAS 80 km h 50 mph 43 kts Throttle IDLE Braking AS REQUIRED 4 5 14 Balked landing Carburettor heating O...

Page 60: ...s under wheels EXECUTE Control stick to be pulled and fastened with the seat belts EXECUTE Canopy to be locked with the key EXECUTE Propeller to be set horizontally EXECUTE 4 6 Additional information 4 6 1 Stall Stall is to be performed by slowly pulling the control stick The engine is to be idle When the wing flaps are retracted the aeroplane practically does not stall Approaching the stalling sp...

Page 61: ... the throttle fully opened 4 6 3 Flight with a passenger The pilot is obliged to instruct the passenger on how to behave in an aeroplane cabin 4 6 4 Crosswind take off or landing The correct aeroplane handling characteristics during takeoff and landing have been demonstrated at crosswind velocity up to 6 m s 21 6 km h 13 4 mph 11 7 kts Take off The control stick is to be displaced against the cros...

Page 62: ...r and later with the brakes At the end of the landing run keep the control stick against the crosswind 4 6 5 Operational speed during takeoff and landing Stated below in the table are the operational airspeeds for the approved wing flap positions TAKE OFF IAS Lifting the nose wheel Lifting off After the takeoff Flaps km h mph kts km h mph kts km h mph kts 0º 65 40 35 85 53 46 120 75 65 15º 65 40 3...

Page 63: ...SECTION 4 AERO Sp z o o NORMAL PROCEDURES AT 3 R100 Page 4 18 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL THIS PAGE IS LEFT INTENTIONALLY BLANK ...

Page 64: ... 5 5 2 4 Landing distance 5 6 5 2 5 Climb performance 5 8 5 3 Supplementary information 5 11 5 3 1 Cruise 5 11 5 3 2 Climb after balked landing 5 13 5 3 3 Take off and landing on grass airstrips 5 13 5 3 4 Affect of rain or insect remains on aeroplane performance and handling 5 13 5 3 5 Demonstrated range of operational temperatures 5 13 5 3 6 Demonstrated crosswind on take off and landing 5 14 5 ...

Page 65: ...s approved data concerning the following issues Calibration of the airspeed indicator system Stalling speeds Take off performance Supplementary information from the manufacturer The diagrams have been computed on the basis of actual flight test data for correct engine and aircraft operation and applying average piloting techniques ...

Page 66: ...n of the airspeed indicator system The diagram is based on test flight data CAS IAS δ δ δ δV δV aerodynamic correction CLIMB LEVEL FLIGHT DESCENT WING FLAPS retracted for take off and for landing mph 149 137 124 99 112 87 75 62 50 mph 62 75 87 99 112 124 137 149 kts 43 54 65 76 86 97 108 118 130 130 118 108 86 97 76 65 54 43 kts ...

Page 67: ...tle idle Stalling speed IAS CAS Angle of wing flap displacement Value of the banking angle km h mph kts km h mph kts 0 VS1 86 53 46 93 58 50 15 VS1 81 50 44 90 56 49 40 0 VSO 72 45 39 82 51 44 0 VS1 93 58 50 100 62 54 15 VS1 90 56 49 97 60 52 40 30 VSO 79 49 43 88 55 47 0 VS1 129 80 70 131 81 71 15 VS1 124 77 67 127 79 69 40 60 VSO 111 69 60 116 69 60 ...

Page 68: ...ty To receive intermediate values of the data given in the table interpolation is to be made between the increasing values TAKE OFF RUN AND TAKE OFF DISTANCES Pressure altitude 0 m STD ºC 15 5 5 15 25 35 Ambient temperature OAT ºF 5 23 41 59 77 99 m 188 195 203 210 225 240 Take off run ft 617 640 666 689 738 787 m 403 419 434 450 482 515 Take off distance to H 15m 50 ft ft 1322 1374 1424 1476 1581...

Page 69: ... 814 876 945 1014 1086 m 491 537 573 617 662 708 Take off distance to H 15m 50 ft ft 1611 1762 1880 2024 2172 2323 Pressure altitude 2000 m 6562 ft STD ºC 28 18 8 2 12 22 Ambient temperature OAT ºF 18 4 0 4 17 6 35 6 53 6 71 6 m 254 276 298 321 344 412 Take off run ft 833 906 978 1053 1129 1352 m 545 591 638 687 738 884 Take off distance to H 15m 50 ft ft 1788 1939 2093 2254 2421 2900 5 2 4 Landin...

Page 70: ...0 666 689 712 735 Pressure altitude 1000 m 3281 ft STD ºC 21 11 1 9 19 29 Ambient temperature OAT ºF 5 8 12 2 30 2 48 2 66 2 84 2 m 444 461 479 496 513 530 Landing distance from 15m 50 ft ft 1457 1512 1572 1627 1683 1739 m 197 205 213 220 228 236 Landing run ft 646 673 699 722 748 774 Pressure altitude 1500 m 4921 ft STD ºC 25 15 5 5 15 25 Ambient temperature OAT ºF 13 5 23 41 59 77 m 467 485 503 ...

Page 71: ...nal power Airspeed VY 120 km h 75 mph 65 kts IAS This airspeed is to be reduced by 3 km h for each 1000 m of altitude 0 57 mph 0 5 kts for each 1000 ft of altitude Wing flaps for takeoff 15º Conditions Maximum weight 582 kg 1283 lb Rating nominal power Airspeed VY 110 km h 68 mph 59 kts IAS This airspeed is to be reduced by 3 km h for each 1000 m of the altitude 0 57 mph 0 5 kts for each 1000 ft o...

Page 72: ...1 ft STD ºC 25 15 5 5 15 25 Ambient temperature OAT ºF 13 5 23 41 59 77 m s 3 03 2 96 2 89 2 82 2 77 2 64 Rate of climb ft m 596 583 569 555 545 520 Pressure altitude 2000 m 6562 ft STD ºC 28 18 8 2 12 22 Ambient temperature OAT ºF 18 4 0 4 17 6 35 6 53 6 71 6 m s 2 56 2 51 2 45 2 39 2 31 2 23 Rate of climb ft m 504 494 482 470 455 439 Pressure altitude 2500 m 8202 ft STD ºC 31 21 11 1 9 19 Ambien...

Page 73: ...2 92 2 85 2 78 2 69 2 60 Rate of climb ft m 587 575 516 547 530 512 Pressure altitude 1500 m 4921 ft STD ºC 25 15 5 5 15 25 Ambient temperature OAT ºF 13 5 23 41 59 77 m s 2 54 2 49 2 43 2 37 2 29 2 22 Rate of climb ft m 500 490 478 467 451 437 Pressure altitude 2000 m 6562 ft STD ºC 28 18 8 2 12 22 Ambient temperature OAT ºF 18 4 0 4 17 6 35 6 53 6 71 6 m s 2 10 2 06 2 01 1 96 1 89 1 83 Rate of c...

Page 74: ...eight 582 kg 1283 lb Wing flaps retracted Automotive gasoline unleaded RON 95 Consumable fuel 65 litres 17 17 US GAL airplane from AT3 055 or glass cockpit equiped 70 litres 18 5 US GAL standard airplane to AT3 054 NOTE Range and endurance data given in the table relate to using of all of the fuel at the given altitude Taxiing take off and climb are not considered in this calculation ...

Page 75: ...AEROPLANE FLIGHT MANUAL Pressure altitude Pressure altitude Engine speed Engine speed Airspeed Airspeed Consumable fuel Fuel consumption Endur ance Range Consumable fuel Range Range Range Consumable fuel Consumable fuel Endur ance Endur ance Endur ance Fuel consumption ...

Page 76: ...grass strips with grass not longer than 15 cm a bit less than a half of the wheel diameter On short cut grass the takeoff run increases about 10 5 3 4 Affect of rain or insect remains on aeroplane performance and handling No observable affect of rain or sediment of insects on the aeroplane performance or handling has been noted 5 3 5 Demonstrated range of operational temperatures During the test f...

Page 77: ...osswind at take off and landing Correct aeroplane handling characteristics have been demonstrated during takeoff and landing with the crosswind velocity up to 6 m sec 21 6 km h 13 4 mph 11 7 knots Diagram for determination of the crosswind component mph km h 8 12 25 19 19 12 8 8 0 12 kts 7 10 17 22 17 10 7 7 10 0 22 ...

Page 78: ...NUAL 5 3 7 Combined diagram of aeroplane characteristics GT 2 173 VRR FW101SRTC Propeller Maximum aeroplane weight 582 kg Maximum power wing flaps retracted absolute ceiling static ceiling engine RPM when climbing maximum airspeed rate of climb time of climb RPM 70 76 81 86 92 98 103 108 kts ...

Page 79: ...0 Page 5 16 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL 5 3 8 Noise The outside noise level of the AT 3 R100 aeroplane determined in accordance with the procedure in Chapter 10 Annex 16 ICAO is 66 6 0 35 dB A while the permissible level is 70 32 dB A ...

Page 80: ...00 WEIGHT AND BALANCE SEPTEMBER 2004 Page 6 1 AEROPLANE FLIGHT MANUAL Section 6 WEIGHT AND BALANCE Page 6 1 Introduction 6 2 6 2 Weight and Balance Calculation 6 2 6 3 Weight and Balance Schedule 6 9 6 4 AT 3 R100 Equipment List 6 10 ...

Page 81: ... new equipment is fitted repairs or re painting will necessitate re calculation of the table 6 3 Weight and Balance Schedule of this manual The equipment installed in this aeroplane is shown in the List of Equipment in Section 6 4 6 2 Weight and Balance Calculation In order to calculate the weight and centre of gravity of the aeroplane one of the following procedures should be followed WARNING Whe...

Page 82: ...empty weight of the aeroplane is the weight of the aeroplane with the unusable amount of fuel engine oil cooling liquid and with the optional equipment according to 6 4 For known weights of fuel passenger pilot and luggage read off the values of the moments from the chart 1 values of the moments Weights and moments should be calculated according to the following table Aircraft Loading Example Your...

Page 83: ...t not be less than 409 kg or greater than 582 kg Using Chart 2 Aircraft loading it can be verified whether the Centre of Gravity is inside the acceptable marked range envelope for the specific maximum weight and moment If not the aircraft loading should be changed The Centre of the Gravity should be inside the marked range during the whole flight ...

Page 84: ...PTEMBER 2004 Page 6 5 AEROPLANE FLIGHT MANUAL Chart 1 Values of the moments Warning When calculating the total moment values for fuel are negative so must be deducted from the totals for pilot passenger and luggage Pilot and passenger fuel luggage Weight kg ...

Page 85: ... 6 AERO Sp z o o WEIGHT AND BALANCE AT 3 R100 Page 6 6 JULY 2010 AEROPLANE FLIGHT MANUAL Weight of the loaded aeroplane kg Moment of the loaded aeroplane kgm kgm Position of C G MAC Chart 2 Aircraft loading 9 ...

Page 86: ...rew kgm 0 60 arm x Qcrew Moment of the luggage Mlugg kgm 1 125 arm x Qlugg Moment of the fuel Mfuel kgm 0 257 arm x Qfuel where Q weight kg When calculating the Centre of Gravity the changes in the weight of oil and cooling liquid can be ignored since the difference of 0 5l 0 45kg between their max and minimum levels is insignificant Weights and moments should be calculated according to the follow...

Page 87: ...of the aeroplane Q total weight of the aeroplane calculate the centre of the gravity in mean aerodynamic cord WARNING The Arm of the Centre of Gravity XCG is measured rearwards from the leading edge of the wing The value XCG must not be less than 0 203 m or greater than 0 393 m WARNING The value XCG must not be less than 16 MAC or greater than 31 MAC XCG 9 XCG XCG 1 27 x 100 __ 9 ...

Page 88: ...MOM kgm ARM m CHANGE OF WEIGHT ADDED Q kg DESCRIPTION OF THE MODIFICARTION New factory built aeroplane with the equipment installed according to the equipment list SIGNATURE SERIAL NUMBER CALL SIGN WEIGHT AND MOMENT OF THE EMPTY AEROPLANE LAST TWO COLUMNS DATE Chronology of the construction and equipment modifications effecting changes of weight and moment of the aeroplane ...

Page 89: ...ator Variant 6 Engine monitoring instruments Electronic tachometer Oil temp indicator Oil pressure indicator Fuel pressure ind OAT indicator EGT indicator Cylinder head temp ind 7 Standard electric system volt ammeter battery 6 4 AT 3 R100 Equipment list NOTE ADDITIONAL EQUIPMENT IS TO BE INSTALLED BY THE AEROPLANE MANUFACTURER WEIGHT OF THE INSTALLED EQUIPMENT IS INCLUDED IN THE EMPTY WEIGHT OF T...

Page 90: ...indicator KI 208 11 Intercom SPA 400 12 Transponder TRT 13 Transponder KT 76A 14 Transponder TT31 15 Encoder A 30 16 GPS Bendix King Skymap IIIC 17 Engine run counter VDO MALAYSIA 18 Stall warning System ACI T1 19 Fuel flow meter TL 2512 20 Fuel flow meter TL 2524 21 Cabin air intake AT3 77 400 0 22 Cabin air outlet AT3 77 450 0 23 Extinguisher AT3 75 000 0 24 Wheel fairings AT3 45 000 0 25 Parkin...

Page 91: ...5 250 0 41 Instruments lighting AT3 73 200 0 42 Instruments lighting AT3 73 300 0 43 GARMIN System G500 44 Engine Monitoring System MVP 50P 45 Audio panel GMA 340 46 COMM NAV GPS GNS 430W 47 Radio transceiver SL 30 48 VOR ILS Indicator MD200 306 49 Transponder GTX 328 50 FLARM ECW100 51 Heated Pitot Tube AT3 71 200 0 52 Artificial horizon 4200 10 11 53 Pitot and static pressure system Variant II A...

Page 92: ...aps 7 7 7 3 3 Control of the elevator 7 8 7 3 4 Control of the trim balancing tab 7 9 7 3 5 Control of the rudder 7 10 7 4 Instrument panel 7 11 7 5 Landing gear system 7 15 7 5 1 Brake system 7 15 7 5 2 Parking brake 7 17 7 6 Seats and seat belts 7 20 7 7 Luggage compartment 7 21 7 8 Canopy 7 22 7 9 Power unit 7 23 7 9 1 Engine 7 23 7 9 2 Propeller 7 23 7 10 Fuel system 7 24 7 11 Pitot and static...

Page 93: ...n sheet has a rectangular section open in the area of the cabin In the rear the fuselage passes fluently into the fin being an integral part The sections between canopy and fuselage as well as those between fuselage and fin are made of epoxy fibreglass composite Fuselage 1 Fire wall 2 Upper fuel tank cover 3 Canopy 4 Canopy fuselage fairing made of epoxy fibreglass 5 Fuselage fin fairing made of e...

Page 94: ... fuselage by means of the main and of the rear spars The ailerons and the wing flaps are of similar design are connected to the wing by means of flat hinges Wing tips made of of epoxy fibreglass Wing 1 Wing frame 2 Aileron 3 Flap 4 Wing walk surface 5 Wing tip 6 Inspection hatch 7 Main spar 8 Rear spar SEPTEMBER 2004 Page 7 3 AEROPLANE FLIGHT MANUAL ...

Page 95: ...cture similar to the wing mass balanced hinged at two points The trim balancing tab are contained within the contour of the tail plane Slab tail 1 Structure of the slab tail 2 Trim and balancing tab 3 Balancing weight 4 Slab tail fittings 5 Trim and balancing tab flat hinges 6 epoxy fibreglass tips Page 7 4 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL ...

Page 96: ... 7 7 2 4 Fin and rudder The vertical tail unit consists of fin and rudder The fin is an integral part of fuselage structure Fin and rudder 1 Rudder 2 Anti collision strobe 3 Rudder mountings 4 Slab tail fittings 5 Lower rudder fitting SEPTEMBER 2004 Page 7 5 AEROPLANE FLIGHT MANUAL ...

Page 97: ... trim balancing tab and of the rudder 7 3 1 Control of the ailerons The ailerons are located at the trailing edge of the outboard wing part between the wing flaps and the wingtips The scheme of the control mechanism of the ailerons is shown below Control of the ailerons 1 Aileron 2 Push rods 3 Push rods 4 Angle lever 5 Control sticks 6 Push rods 7 Torsion tube Page 7 6 SEPTEMBER 2004 AEROPLANE FLI...

Page 98: ...e seats This lever is fitted with a knob which is to release the flap retaining pin and enables the flap to be set in either of its three positions In the extreme forward position of the lever the flap is set to GK 0 q In the middle position of the lever the flap is set to GK 15 q and in the extreme rear the setting is GK 40 q The wing flap control lever transmits its movement to the flaps via pus...

Page 99: ...elevator The slab tail elevator is fixed to the spar of the fin The scheme of the elevator control is shown in the illustration below Control of the elevator 1 Control stick 2 Torsion tube 3 Short push rod 4 Connecting lever 5 Long push rod 6 Slab tail arm Page 7 8 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL ...

Page 100: ... the trailing edge of the slab tail elevator is driven by torsion shaft self locking screw gear and assembly of levers and pushrods The illustration below shows the control wheel of the tab and the tab setting indicator NOSE DOWN TAKE OFF SETTING Tab position indicator NOSE UP Trim Balancing Tab Control Wheel SEPTEMBER 2004 Page 7 9 AEROPLANE FLIGHT MANUAL ...

Page 101: ...rudder is fixed to the fin The illustration below shows the schematic of the rudder control Schematic showing the set up of the pedals controlling the rudder 1 Rudder pedals 2 Cable pulley 3 Cables 4 Rudder lever 5 Rudder 6 Tension springs 7 Discharge cables Page 7 10 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL ...

Page 102: ...N 7 AT 3 R100 DESCRIPTION OF THE AEROPLANE AND ITS EQUIPMENT 7 4 Instrument panel The equipment installed in this aeroplane is specified in the List of Equipment on page 6 4 SEPTEMBER 2004 Page 7 11 AEROPLANE FLIGHT MANUAL ...

Page 103: ...arning light 5 Artificial horizon 6 Altimeter 7 Vertical speed indicator 8 Directional gyro 9 Turn co ordinator 10 Cabin heating control knob 11 Vent control knob 12 Choke 13 Carburettor heating 14 Fuel cut off valve 15 Battery switch 16 Generator switch 17 Fuel pump switch 18 Ignition switch Page 7 12 SEPTEMBER 2004 AEROPLANE FLIGHT MANUAL ...

Page 104: ...or 20 Cylinder head temperature indicator CHT 21 Oil pressure indicator 22 Starter engaged light 23 Generator failure light 24 Compass 25 Tachometer 26 Fuel reserve light 27 Oil temperature indicator 28 Exhaust Gas temperature indicator EGT 29 Throttle lever SEPTEMBER 2004 Page 7 13 AEROPLANE FLIGHT MANUAL ...

Page 105: ... Anti collision strobe light switch 39 Turn co ordinator switch 40 Artificial horizon switch 41 Directional gyro switch 42 Starter circuit breaker 43 Engine instruments circuit breaker 44 Fuel quantity meter circuit breaker 45 12V DC supply circuit breaker 46 Encoder circuit breaker 47 Transponder circuit breaker 48 Intercom circuit breaker 49 Radio transceiver circuit breaker optional equipment P...

Page 106: ...cylinders 3 located on rudder pedals In version 1 they are connected via insulating valve 4 and flexible pressure lines with brake callipers 8 The brake fluid container 1 is located at the highest point of the brake system on the firewall and it supplies each pump independently Cylinders of the left brake are activated by the left rudder pedals and the right cylinders are activated by the right ru...

Page 107: ...ND ITS EQUIPMENT Page 7 16 JULY 2010 AEROPLANE FLIGHT MANUAL Diagram of the braking system 1 Brake fluid container 2 Feeding line 3 Brake cylinder 4 Insulating valve 5 Parking brake valve option 6 Brake pressure line 7 Bleeding valve 8 Brake calliper 9 Brake disk 9 ...

Page 108: ...e is installed in break installation of left seat For role of the parking brake and the flight controls securing can be used the collapsible tow bar installed on control stick and rudder control pedals For collapsible tow bar using description see Section 8 4 2 Parking CAUTION ENGINE STARTING WITH PARKING BRAKE ON IS PROHIBITED NOTE IN ORDER TO APPLY THE PARKING BRAKE IT IS NECESSARY FROM THE LEFT...

Page 109: ...GHT MANUAL Parking Brake AT3 47 100 0 Valve of parking brake AT3 47 100 0 is non return valve After set this valve lever on is possible to increase pressure inside the breaking system lines and brake the airplane Parking brake AT3 47 100 0 in ON position 1 Valve lever 2 Parking brake placard 3 Information placard 9 ...

Page 110: ... brake cylinders are cut off from callipers Set the valve lever to position on with low level pressure inside the braking lines make impossible to brake the airplane In airplane with brake system variant 2 right seat toe brakes operate independently from parking brake lever position Parking brake AT3 47 130 0 in ON position 1 Valve lever 2 Parking brake placard 3 Information placard CAUTION DO NOT...

Page 111: ...age 7 20 JULY 2010 AEROPLANE FLIGHT MANUAL 7 6 Seats seat belts and harness The seat position is permanently fixed not adjustable The illustration below shows the installation of the seats Each seat is fitted with adjustable safety belts Rear frame of fuselage Harness Safety belts 9 ...

Page 112: ...ids made of metal locked by latches Pressing the latch releases it and enables the lid to be opened The luggage compartment allows for luggage of 30 kg total weight 20 kg in the port container and 10 kg in the starboard one Lid of the luggage compartment The port and the starboard luggage containers Extinguisher CAUTION IT IS PROHIBITED TO CARRY INFLAMMABLE CORROSIVE EXPLOSIVE RADIOACTIVE AND OTHE...

Page 113: ...cabin the canopy should be pulled on the handle and lowered until it rests on the fuselage sidewall edges and then locked with the levers with orange knobs Sliding venting tabs are installed on both sides of the canopy Jettisoning of the canopy is achieved by pulling the lever with the red knob and pushing the canopy upwards The locking and the jettisoning levers are arranged in the front part of ...

Page 114: ...heads cooled with fluid cylinders cooled with air Pressure lubrication Dual magneto ignition Propeller driven via reduction gear Electric starter Generator Two interconnected throttle levers located on the instrument panel are used to control the engine 7 9 2 Propeller Wooden fixed pitch two bladed GT 2 173 VRR FW101SRTC propeller of 1 73 m 5 8 diameter The propeller rotates in a clockwise directi...

Page 115: ...he fuel quantity is measured by the fuel level sensor The signal from this sensor is transmitted to the fuel quantity indicator and to the reserve fuel sensor The reserve fuel signal lamp starts to light when the fuel tank contains 10 litres of consumable fuel The fuel is filtered by the coarse filter located on the fuel tank outlet by the filter in the electric driven emergency fuel pump and by t...

Page 116: ...l level sensor 5 Reserve fuel sensor 6 Reserve fuel signalling lamp 7 Fuel quantity indicator 8 Shut off valve 9 Electrically driven fuel pump 10 Fine fuel filter 11 Engine driven fuel pump 12 Carburettors 13 Three way connectors 14 Fuel pressure sensor 15 Fuel pressure indicator 16 Fuel return line 17 Draining line of fuel filler 18 Three way connectors 19 Fuel flow meter sensor optional 20 Fuel ...

Page 117: ...re and transmit it to the airspeed indicator 3 altimeter 2 vertical speed indicator 1 and altitude encoder 7 option see the scheme on the illustration The sensors of pitot and static pressure are fixed under the port wing Water sediment containers 6 are installed to both the static pressure line 5 and to the pitot pressure line 4 The sediment containers are located beneath the pilot s seat and are...

Page 118: ...of generator failure the GENERATOR signalling lamp lights up In such a case the system is fed from the on board battery There is also an electrical ground power receptacle installed into the system being located in front of the wing on the port wall of the fuselage in front of the firewall An electric board socked is installed in the cabin on the instrument panel When using the ground power source...

Page 119: ...RIPTION OF THE AEROPLANE AT 3 R100 AND ITS EQUIPMENT Page 7 28 JULY 2010 AEROPLANE FLIGHT MANUAL Automatic circuit breaker permanently switched on Switch with automatic circuit breaker switched manually Switch switched manually 9 ...

Page 120: ...on inlet in the lower part of the cabin shares the air intake with the carburettor air inlet connected to the air mixer The air mixer enables adjustment of the volume and temperature of the cabin ventilating air The fresh air is ducted from the intake to the heat exchanger located under the muffler and then further to the air mixer From the mixer the air is ducted to the cabin outlet The control c...

Page 121: ...channelled through the air duct to the filter box where the air streams are mixed The cold air stream can be adjusted by the flap controlled by the Bowden cable and knob located on the middle console The temperature of the carburettor intake air can be read from the gauge on the instrument panel To increase of the temperature turn the knob to the left to unlock and pull to the selected position an...

Page 122: ...n case of airplane operation in low ambient temperature it is recommended that intake air covers are used to reduce the intensity of the cooling effect Inlet covers are installed in the lower cowling by the means of screws NOTE It is recommended that Air Intake Covers are installed when operating the aircraft in ambient temperature below 120 C 540 F 9 ...

Page 123: ...SECTION 7 AERO Sp z o o DESCRIPTION OF THE AEROPLANE AT 3 R100 AND ITS EQUIPMENT Page 7 32 JULY 2010 AEROPLANE FLIGHT MANUAL THIS PAGE IS LEFT INTENTIONALLY BLANK 9 ...

Page 124: ...ns 8 2 8 3 Aeroplane repair or modification 8 3 8 4 Ground servicing 8 3 8 4 1 Relocating the aeroplane on ground 8 4 8 4 2 Parking 8 5 8 4 3 Tying down 8 7 8 4 4 Lifting 8 8 8 4 5 Levelling 8 9 8 5 Cleaning and basic maintenance 8 10 8 5 1 External painted surfaces 8 10 8 5 2 Glass panels 8 11 8 5 3 Propeller 8 12 8 5 4 Engine 8 12 8 5 5 Cabin interior 8 12 9 9 9 9 ...

Page 125: ... lubrication and maintenance appropriate to the operating conditions and climate 8 2 Scheduled aeroplane inspections The scope and the intervals of the inspection schedule are defined in the Aeroplane Maintenance Manual A separate inspection system may be required for the aeroplane by the appropriate Civil Aviation Authority in order to renew the Certificate of Airworthiness Tasks to be carried ou...

Page 126: ...e Aeroplane Maintenance Manual the aircraft should be re weighed and the respective weighing report sheet completed and the Weight and Balance schedule in section 6 3 of this manual must be revised Also Section 9 of this manual is to be supplemented accordingly 8 4 Ground servicing The dimensions of the standard aeroplane are given in the aeroplane drawings see Section 1 This allows the size of th...

Page 127: ... standard and collapsible Collapsible tow bar for transport purpose can be fixed to the ferrules on the rear wall in the cockpit If the ground is not even and there are difficulties in moving the aeroplane two people may manage the relocation balancing the plane on the main wheels One person should guide the wingtip and the other should control the movement with the towing bar NOTE Do not push or ...

Page 128: ...cover if available 5 Position the propeller horizontally For secure of flight controls can be used collapsible tow bar installed on the control stick and rudder pedals Collapsible tow bar installed on the toe brakes over rudder pedals working as a parking brake and secure the controls For collapsible tow bar install place forks of tow bar on the left seat rudder pedals or toe brakes using safety p...

Page 129: ... MANUAL Collapsible tow bar installed on the control stick and rudder pedals 1 Catch pawl 4 Control stick grip 2 Safety pin 5 Rudders pedals 3 Tow bar 6 Tow bar handle Collapsible tow bar installed on toe brakes over rudder pedals 1 Tow bar forks 2 Safety pin 3 Catch pawl 9 9 9 9 ...

Page 130: ...ould be observed 1 It is recommended to have the aeroplane pointing into wind 2 Put chocks in front of the main wheels 3 Apply locks to the ailerons rudder and elevator or fasten the control sticks with safety belts 4 Put the ropes through the specified lugs and drive the mooring anchors in the ground There should only be slight tension on the tie downs to prevent sagging 5 Apply the cover to the ...

Page 131: ... jacks the aeroplane may also be lifted by hand when holding the lower fuselage edges in the area between the firewall and the wing and in front of the horizontal stabilizer 2 Locate one of the jacks under the nose landing gear ferrule and the other two each side next to the cabin walls under the main landing gear box Apply wooden blocks 3 Lift the aeroplane gradually to the required height Lift t...

Page 132: ...AT 3 R100 SERVICING JUNE 2010 Page 8 9 AEROPLANE FLIGHT MANUAL 8 4 5 Levelling After lifting the aeroplane should be levelled so that the cabin wall edges are horizontal see the illustration SPIRIT LEVEL EDGES OF CABIN WALLS 9 ...

Page 133: ...n the pitot and static pressure sensors Mask off all holes and orifices Use clean water to remove all fine particles and then wash the surface with water adding mild soap Do not use detergents or soaps which are acid alkaline or abrasive To remove spots of grease or oil use a piece of cloth with naphtha or aliphatic petrol After use of naphtha the surface should be re waxed and polished To polish ...

Page 134: ...hen wipe with soft clean cloth sponge or chamois leather To remove films of oil or grease use tribasic sodium phosphate well dissolved in water Sediments of grease or oil if difficult to remove should be cleaned with methanol hexane or naphtha Finally rinse with clean water avoiding excessive rubbing of the glass panel surface CAUTION DO NOT USE PETROL BENZENE ACETONE ANTI ICING COMPOUNDS OR PAINT...

Page 135: ...eat care 8 5 4 Engine The engine is to be cleaned as indicated in the Engine Maintenance Manual 8 5 5 Cabin interior The seats carpets and upholstery are to be cleaned with a vacuum cleaner Do not use water to clean items of cloth or fabric Foam based shampoos for general use on automotive upholstery may be applied but the indications given on the packing should be strictly observed 9 ...

Page 136: ...AERO Sp z o o SECTION 9 AT 3R100 SUPPLEMENT No 44 OCTOBER 2010 Page 9 44 1 AEROPLANE FLIGHT MANUAL Section 9 SUPPLEMENT No 44 VFR NIGHT analog instruments ...

Page 137: ...r the standard airplane Section 2 Limitations 2 11 Types of operation This aeroplane is approved for flights by day and night in Visual Meteorological Conditions VMC Day Night This aeroplane is approved to operate according to Night VFR when the equipment specified in the LIST OF MINIMUM EQUIPMENT is installed and working correctly ...

Page 138: ...Anti collision light 3 Landing and taxiing lights 4 Instruments and cockpit lighting 1 1 1 1 PRZYRZĄDY PILOTAŻOWO NAWIGACYJNE 1 Airspeed indicator 2 Altimeter 3 Magnetic compass 1 1 1 ENGINE MONITORING INSTRUMENTS 1 Tachometer 2 Cylinder head temperature indicator 3 Exhaust gas temperature indicator 4 Oil temperature indicator 5 Oil pressure indicator 6 Fuel quantity indicator 7 Fuel pressure indi...

Page 139: ...st of the section is the same as for the standard aeroplane Section 3 Emergency procedures The same as for the standard airplane Section 4 Normal procedures 4 4 Preparation for flight CAUTION FLIGHT IN VFR NIGHT CONDITION MUST BE CONDUCT IN ACCORDANCE WITH APPLAING COUNTRY FLIGHT RULES It is recommended to flight in VFR Night condition with efficiency and full charging battery Must be ensure addit...

Page 140: ...aeroplane 1 Cabin Position lights operating CHECK Taxiing light operating CHECK Landing light operating CHECK Anti collision light operating CHECK Instruments and cockpit lighting operating CHECK Instruments and cockpit lighting switch off CHECK 4 5 4 Engine starting Cool engine procedure Baterry generator alternator ON Cockpit lighting ON Engine instruments lighting ON 4 5 5 Before taxiing Instru...

Page 141: ...5 After landing Landing light OFF Taxiing light if necessary ON The rest of the section is the same as for the standard aeroplane Section 5 Performance The same as for the standard airplane Section 6 Weight and balance VFR night equipment weight is included in the empty aircraft weight Section 7 Description of the airplane and of its equipment ...

Page 142: ...l Fig 1 Instrument panel lighting 1 Dimmer FLIGHT INSTRUMENTS 2 Dimmer ENGINE INSTRUMENTS 3 Dimmer COCKPIT LIGHTING 4 Dimmer RADIO 5 Lighting of switches and circuit breakers light posts 6 Circuit breaker INSTRUMENTS LIGHTING 7 Cockpit lighting bulbs photo does not show a light on the left side of the instrument panel ...

Page 143: ...of selected circuit of lighting Rotation to the right knob causes an activation and subsequent increase in lighting intensity Two bulb lights are installed over the instrument panel for cabin lighting The direction of the light bulbs can be changed by rotating an internal spherical part of the light Those lights can be used to lighting maps or if needed as a additional lighting of the instrumentat...

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