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Aero-East-Europe SILA 450 C, Руководство по эксплуатации для пилотов

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OPERATION  MANUAL                                   

SILA 450 c                 

                      AERO EAST EUROPE 

Date 01.09.2015.  

Revision 00 

Page | 48

 

 

AIRPLANE & SYSTEMS DESCRIPTION

 

Each fuel tank is in communication with the central drain bowl and no selection right/left is 
previewed. 
The  fuel  flows  by  gravity  from  the  two  wing  tanks  trough  a  drain  bowl  to  a  two-position 
selector  valve  labeled  ON  and  OFF.  Fuel  system  venting  is  essential  to  system  operation. 
Blockage  of  the  venting  system  will  result  in  decreasing  fuel  flow  and  eventual  engine 
stoppage. Venting is accomplished by two dynamic air intakes located close the wing struts. 
The fuel level in the tanks is directly showed by a transparent hose located in the upper left 
and right side of the cockpit.  
The  indicators  cannot  be  relied  upon  for  accurate  readings  during  skids,  slips,  or  unusual 
attitudes.  A  red  line  marked  on  the  transparent  hoses  indicates  the  quantity  of  remaining 
fuel considered unusable. The availability of the above defined “unusable fuel” depends on 
the attitude of the aircraft but for safety reasons the red line must stand for EMPTY tank. 
When a 10 Liters reserve tank is present the red LOW FUEL light will switch on as soon as the 
volume of fuel in the reserve tank is decreased. Low fuel Light ON has to be intended as a 
distress situation and a correct and safe flight planning must never lead to the use of the fuel 
in the reserve tank. 
The  reserve  fuel  tank  is  equipped  with  an  air  valve  drainer;  in  case  of  a  non  correct  air 
draining  during  preflight  procedures  may  result  in  anomalous  LOW  FUEL  indication  while 
flying above about 4000ft. 
In case of distress flight condition of low fuel: 
 

As soon as the red indicator light turns on reduce speed and allow the aircraft to fly 

with a “nose up” attitude in order to maximize the availability of  the remaining fuel in the 
tow main tanks until the light turns again off. This operation may be carried on for one or  
two times until the alarm LOW FUEL red light will be constantly ON, from this moment no 
more of about 0,5 Liters of fuel must be taken into account. 
Prolonged slips, deeps and skids may lead to an anomalous LOW FUEL alarm indication when 
the fuel amount in the two wing tanks contain less then about 1/3 of their capacity: the red 
light will turn off as soon as the aircraft will return in a usual flight attitude. Anomalous or 
unusual prolonged deep attitudes must be avoided if no reserve fuel tank is installed when 
the total fuel amount is less then about 1/3 of the tanks capacity. 
Unequal fuel flow from each tank may occur if the wings are not maintained exactly leveled.  
 

NOTE: 

The fuel system is equipped with drain valves to provide a means for the examination of fuel 
in the system fuel contamination and grade. The system should be examined before the first 
flight of every day and after each refueling, by using the sampler cup provided to drain fuel 
from the tank sump. The fuel tanks should be filled after each flight to prevent condensation.

 

 

NOTE: 

Let the fuel to flow out also up to 20-30Ltr if you feel it is necessary to drain out dirtiness or 
water. Fuel MUST flow and spill out CLEAN!  

The airplane is equipped with a standard fuel system. 
The fuel system consist form two tanks (one in each wing) connected at one collection tank 
at the bottom of the fuselage, which volume is 0,4 liters. Systems have two positions ON or 
OFF. When switch in in position ON fuel flow in same quantity from both tanks through the 
collection  tank.  When  wing  tanks  are  empty  system  give  the  signal  by  red  lamp,  low  fuel, 
that  means  system  suck  fuel  from  collection  tank,  pilot  must  landed  in  maximum  of  35 
minutes 

** 

Please be informed what kind of additional equipment is installed on aircraft 

Содержание SILA 450 C

Страница 1: ..._________________ Civil Aviation Directorate of the Republic of Serbia Stamp Original date of approval Serial No XXXXXX AEE XXXX This airplane is to be operated in compliance with information and limitations contained herein September 2015 ...

Страница 2: ...wings are rectangular with sweep angle equal to zero twist angle of 2 from wing root to wing tip and dihedral angle of 0 5 Wings are made from approved aeronautical aluminum with wing tips from epoxy plastic Wings are connected to the top of the fuselage and supported by two struts on each wing Wings are main lift surfaces which supporting the aircraft in flight The tail surfaces are with classic ...

Страница 3: ... noticed in table below Log of revisions Revision No Date released Section Reason for revision Approved by 00 01 09 2015 1 Initial issue 00 01 09 2015 2 Initial issue 00 01 09 2015 3 Initial issue 00 01 09 2015 4 Initial issue 00 01 09 2015 5 Initial issue 00 01 09 2015 6 Initial issue 00 01 09 2015 7 Initial issue 00 01 09 2015 8 Initial issue 00 01 09 2015 9 Initial issue ...

Страница 4: ...__________________ SECTION 1 GENERAL INFORMATION 6 SECTION 2 LIMITATIONS 10 SECTION 3 EMERGENCY PROCEDURES 17 SECTION 4 NORMAL PROCEDURES 23 SECTION 5 PERFORMANCE 33 SECTION 6 WEIGHT AND BALANCE 38 SECTION 7 AIRPLANE SYSTEM DESCRIPTION 40 SECTION 8 AIRPLANE HANDLING SERVICING AND MAINTENANCE 56 SECTION 9 SUPPLEMENTS 75 ...

Страница 5: ...17 01 00 01 09 2015 53 01 00 01 09 2015 18 01 00 01 09 2015 54 01 00 01 09 2015 19 01 00 01 09 2015 55 01 00 01 09 2015 20 01 00 01 09 2015 SECTION 8 21 01 00 01 09 2015 Page Issue Revision Rev date 22 01 00 01 09 2015 56 01 00 01 09 2015 SECTION 4 57 01 00 01 09 2015 Page Issue Revision Rev date 58 01 00 01 09 2015 23 01 00 01 09 2015 59 01 00 01 09 2015 24 01 00 01 09 2015 60 01 00 01 09 2015 25...

Страница 6: ...1 _____TABLE OF CONTENTS_______________________________________ 1 1 Introduction 7 1 2 Certification Basis 7 1 3 Performances specifications 7 1 4 Dimensions 8 1 5 Descriptive Data 9 1 5 1 Engine 9 1 5 2 Propeller 9 1 5 3 Fuel 9 1 5 4 Oil 9 1 5 5 Maximum Certificated Weight 9 1 6 Warnings cautions and notes 9 ...

Страница 7: ...t to destination or closest alternative airport and air field 45 minutes reserve average consumption is 15 liters per hour or 3 97 gallons per hour RATE OF CLIMB AT SEA LEVEL 5 6 m s 1000 FPM SERVICE CEILING 3 658 m 12000 FT TAKEOFF PERFORMANCE Ground Roll 90 meters 295 FT LANDING PERFORMANCE Ground Roll 140 meters 460 FT STALL SPEESDS KCAS Flaps Up Power Off 83 km h 38 Knots Flaps Down Power Off ...

Страница 8: ... MANUAL SILA 450 c AERO EAST EUROPE Date 01 09 2015 Revision 00 Page 8 1 4 DIMENSIONS GENERAL INFORMATION 5 90 ft 9 460mm 31 04ft 9 460 mm 31 04ft 1270mm 4 17ft 6470mm 21 2 ft 2400mm 7 87ft 1700mm 5 58ft 1800 mm ...

Страница 9: ... right 1 5 3 FUEL Approved Fuel Grades BMB 95 Octane alternative 100LL Fuel Capacity Total Capacity 90 lit 23 8 gallons Total Capacity Each Tank 45 lit 11 9 gallons Total Usable 86 lit useful 22 8 g useful gallons 1 5 4 OIL Oil Grade Specifications 10w 40 5w 50 Straight semisynthetic oil As provided in Engine Maintenance Manual 1 5 5 MAXIMUM AIRCRAFT WEIGHT Maximum Takeoff Weight 472 5 Kg Maximum ...

Страница 10: ... 2 2 Air Speed Limitations 11 2 3 Airspeed Indicator Markings 11 2 4 Power Plant Limitations 12 2 5 Power Plant Limitations Markings 12 2 6 Weight Limits 13 2 7 Center of Gravity Limits 13 2 8 Maneuver Limits 14 2 9 Maneuvering load factors 14 2 10 Flight crew 14 2 11 Kinds of Operational Limits 15 2 12 Fuel Limitations 15 2 13 Maximum passenger seating 16 2 14 Limitation placards 16 ...

Страница 11: ...wn Take care about flaps setting VNE Maximum gear operating speed 223 km h 120 knots The landing gear is not retractable Figure 2 1 Airspeed Limitations 2 3 AIR SPEED INDICATOR MARKINGS Airspeed Indicator markings and their color code significance are shown in figure 2 2 MARKING IAS VALUE OF RANGE SIGNIFICANCE White Arc From 1 1 VS0 72 106 km h 38 57 knots Full Flap Operating Range Lower limit is ...

Страница 12: ... throttle 5800rpm per 5 minute in case redactor per engine 2 43 100hp is 2389 rpm redactor 2 27 per engine 80hp is 2555 rpm 2 5 POWER PLANT INSTRUMENT MARKINGS ROTAX 912 UL Power plant instrument markings and their color code significance are shown in figure 2 3 INSTRUMENT RED LINE GREEN ARC YELLOW ARC RED LINE MINIMUM LIMIT NORMAL OPERATING MAXIMUM LIMIT Tachometer Sea Level 5000 ft 10000 ft 1400...

Страница 13: ... of MAC or 340 mm from leading edge Forward limit C G MTOW 29 of MAC or 368 mm from leading edge Aft limit C G MTOW 34 of MAC or 432 mm from leading edge Figure 2 5 Warning Aircraft commander is obligate to take care about center of gravity positions by weighing the aircraft and take care about approved weights for aircraft loadings if any baggage crew and fuel Picture 2 showing weighing plan of t...

Страница 14: ...rplane is clean in aerodynamic design and will increase up speed quickly with the nose down Proper speed control is an essential requirement for execution of any maneuver and care should always be exercised to avoid excessive speed which in turn can impose excessive loads In the execution of all maneuvers avoid abrupt use of the controls Intentional spins with flaps extended are prohibited 2 9 MAN...

Страница 15: ...k capacity 10 liters 2 6 gallons only if installed Total Usable 86 lit useful 22 8 gallons Approved fuel grades 95 Octane Premium automotive benzene 100 LL AV Gas Special instructions for fuel management During replenishment of fuel tanks in wing take care to aircraft be parked at plane surface to assure proper estimate of level of fuel and fulfillment of fuel tanks NOTE Especially take attention ...

Страница 16: ...d C G with flaps retracted Upper limit is maximum structural cruising speed bar 165km h 89knots From 1 1 VS1 183 km h 99 knots Yellow Arc 183 223 km h 223 120 knots Operating must be conducted with caution and only in smooth air Red Line 2223 km h 120 knoots Maximum speed for all operations NOTE The difference between stated speeds and airspeed indicator marking is consequence from tested and cert...

Страница 17: ... 18 3 3 2 Engine Failure immediately after T O 18 3 3 3 Engine Failure during Flight 19 3 4 Forced Landings 19 3 4 1 Emergency Landing without Engine Power 19 3 4 2 Precautionary Landing with Engine Power 19 3 5 Landing with flat main tire 19 3 6 Landing with a defective landing gear 20 3 7 Fires 20 3 7 1 During Start on Ground 20 3 7 2 Engine Fire in Flight 20 3 7 3 Electrical Fire in Flight 20 3...

Страница 18: ...e After Takeoff Wing Flaps Up 120 km h 65 knots IAS Wing Flaps Down 102 km h 55 knots IAS Maneuvering Speed maximum glide 472 5 kg 1041 lbs 139 km h 75 knots IAS 420 0 kg 926 lbs 130 km h 70 knots IAS 367 5 kg 810 lbs 111 km h 60 knots IAS Precautionary approach speed for Landing With Engine Power 472 5 kg 1041 lbs 120 km h 65 knots IAS 420 0 kg 926 lbs 102 km h 55 knots IAS 367 5 kg 810 lbs 92 km...

Страница 19: ...AL APPROACH 5 Master Switch OFF 6 Doors UNLATCH PRIOR TO TOUCHDOWN 7 Touchdown SLIGHTLY TAIL LOW 8 Brakes APPLY HEAVILY if necessary 3 4 2 PRECAUTIONARY LANDING WITH ENGINE POWER 1 Wing Flaps 19 2 Airspeed 111 km h 60 knots IAS 3 Selected Field FLY OVER noting terrain obstruction and wind direction from safe altitude and airspeed 4 Electrical Switches OFF 5 Wing Flaps 38 on final approach 6 Speed ...

Страница 20: ... OFF 2 Fuel Selector Valve OFF 3 Master Switch OFF 4 Cabin Heat and Air OFF except overhead vents 5 Leave the aircraft IMMEDIATELY 6 TRY TO EXTINGUISH FIRE WITH EXTINGUISHER IF POSSIBLE 7 Call fire department and start with extinguishing fire if safe 3 7 2 ENGINE FIRE IN FLIGHT 1 Mixture IDLE CUT OFF 2 Fuel Selector Valve OFF 3 Master Switch OFF 4 Flying in such a way that the air stream rejects t...

Страница 21: ...e shift plane to opposite side from burned wing NOTE As soon as possible select field for precautionary emergency landing 3 8 GLIDE 1 Level the aircraft if necessary 2 Adjust air speed for maximum glide 472 5 kg 1041 lbs 139 km h 75 knots IAS 420 0 kg 926 lbs 130 km h 70 knots IAS 367 5 kg 810 lbs 111 km h 60 knots IAS 3 Keep with a steady and free flight 4 Find adequate airport or field for landi...

Страница 22: ...TICK Ailerons in neutral position till start recovery and then opposite 4 RUDDER In neutral position till start recovery and then opposite 5 AIRSPEED Make sure to not exceed VNE 223 kmh 120Knots 6 RUDDER Immediately spin stop set rudder in neutral position 7 CONTROL STICK Pull backward to recover from dive NOTE Aircraft have no tendency of spontaneously entering to spin under normal maneuvers and ...

Страница 23: ...Speeds for Normal Operation 27 4 4 1 Before Starting Engine 27 4 4 2 Starting Engine 28 4 4 3 Before Taxying 28 4 4 4 Taxying 28 4 4 5 Before Takeoff 28 4 4 6 Normal Takeoff 29 4 4 7 Short Field Takeoff 29 4 4 8 Takeoff in wind conditions 29 4 4 9 Enroute Climb 31 4 4 10 Cruise 31 4 4 11 Descents 31 4 4 12 Before Landing 31 4 4 13 Normal Landing Approach 31 4 4 14 Short Field Landing 31 4 4 15 Aft...

Страница 24: ...neral condition of propeller check damages attachment to engine flange attachment blades to hub inspect leaking of fuel oil or refrigerant fluid in engine compartment inspect attachments to engine mount inspect attachment of engine mount to the structure inspect damage and leaking of engine hoses inspect electrical wires inspect fluids to be at optimal level oil coolant inspect fuel pump inspect c...

Страница 25: ...VERTICAL TAIL Inspect general condition of surfaces leading and trailing edge check rivets and attachment to fuselage When elevator and rudder acting simultaneously check there are no contact between rudder and elevator check deflections 7 RIGHT PART OF HORIZONTAL AND VERTICAL TAIL Inspect general condition of surfaces leading and trailing edge check rivets and attachment to fuselage When elevator...

Страница 26: ... functioning Inspect windshield and windows for visibility and clean if necessary Inspect position and functionality of breakers WARNING Assuring of the execution of pre flight check is task of aircraft commander These is extremely important task which can prevent accidents if proper executed 4 3 RIGGING Before flight rigging and check of control surface deflection is necessary For easier use of a...

Страница 27: ...km h 55 knots IAS Short Field Approach Flaps 38 83 km h 45 knots IAS Maximum Crosswind Velocity Takeoff or Landing 28 km h 15 knots IAS Maximum Frontal wind Velocity Takeoff or Landing 46 km h 25 knots IAS Maximum Tailwind Velocity Takeoff or Landing 15 km h 8 knots IAS NOTE Demonstrated values executed by experienced pilot and given only for information Maximum Demonstrated Crosswind Velocity Tak...

Страница 28: ...lve ON 6 Engine instruments CHECK All in green 4 4 4 TAXYING 1 Taxi area monitoring CLEAR 2 Flight steering controls SET CHECK 3 Flight instruments FINAL CHECK 4 General Fuel Valve ON 4 4 5 BEFORE TAKEOFF 1 Parking Brake SET 2 Cabin Doors and Windows CLOSED and LOCKED 3 Flight Controls FREE and CORRECT 4 Flight Instruments SET 5 General Fuel Valve ON 6 Elevator Trim and Rudder Trim TAKEOFF 7 Throt...

Страница 29: ... 2 Carburetor Heat OFF 3 Brakes APPLY 4 Throttle FULL OPEN progressively 5 Brakes RELEASE 6 Elevator Control at 75 kmh 40kts SLIGHTLY TAIL DOWN 7 Climb Speed 102km h 55ktsIAS until obstacles are cleared 4 4 8 TAKE OF IN WIND CONDITIONS WARNING Flying with wind conditions of 15 knots crosswind 8 knots tailwind and 25 knots of frontal wind is prohibited Cross wind kmh Take off distance m 0 90 10 87 ...

Страница 30: ...8 54 70 10 17 40 6 34 70 20 34 80 12 69 80 10 18 24 3 23 80 20 36 47 6 46 10 30 9 64 54 72 10 40 12 86 72 96 20 30 18 99 52 21 20 40 25 32 69 62 30 30 27 77 48 12 30 40 37 02 64 16 40 30 35 70 42 57 40 40 47 60 56 77 50 30 42 55 35 73 50 40 56 73 47 64 60 30 48 10 27 81 60 40 64 14 37 07 70 30 52 20 19 03 70 40 69 60 25 38 80 30 54 71 9 69 80 40 72 95 12 92 Table 4 4 8 Wind calculations due to tes...

Страница 31: ...CURE 2 General Fuel Valve ON 3 Buster pump if installed ON 4 Carburetor Heat AS REQUIRED in base of meteorological conditions 5 Autopilot if installed OFF 6 Air Conditioner if installed OFF 7 Set up pitch of propeller for take off land 8 Landing lights and strobe lights ON 4 4 13 NORMAL LANDING APPROACH 1 Airspeed approach 111 130 km h 60 70 knots IAS flaps up 2 Airspeed final 92 km h 111 km h 50 ...

Страница 32: ...gine before shut down for two minutes at 1800 RPM 5 Throttle pull at 1500 RMP switch off left magneto after left magneto switch off right Magneto 6 Master switch OFF 4 4 16 SECURING AIRPLANE 1 Parking Brake SET if installed 2 Control Locks INSTALL 3 Mats for wheels SET 4 Fix the pilot stick by secure belts 5 Fix the aircraft to the ground by belts and lugs under the wing if necessary outside park ...

Страница 33: ...tem calibration 34 5 2 2 Stall speed 35 5 2 3 Take off performance 35 5 2 4 Landing distances 35 5 2 5 Climb performance 36 5 3 Additional information 36 5 3 1 Cruise 36 5 3 2 Endurance Cruising Speed range 36 5 3 3 Balked Landing Climb 36 5 3 4 Takeoff Measurement From a Dry Shirt Mown Grass Surface 37 5 3 5 effects on Flight Performances Caused by Rain or Accumulation of Insects 37 5 3 6 Demonst...

Страница 34: ...istics are tested on different aircrafts according manufacturing procedures for new aircrafts Values are interpolated and given in conservative manner for any pilot with average pilot skills 5 2 1 AIRSPEED INDICATOR SYSTEM CALIBRATION Before delivery of every aircraft company performs testing of pitot static system in flihght speed calibration and buyer executing procedure in approved organization...

Страница 35: ... kg and wing level flight SILA 450 C Indicated Stall speed IAS Flaps retracted 83 kmh 45 knots Flaps take off position Flaps 74kmh 40 knots Flaps in landing position Full flaps 64 kmh 35 knots Figure 5 1 5 2 3 TAKE OFF PERFORMANCE SILA 450 C Take off run Take off with 0bstacle 15 m Flaps take off position 90 m 190 m Figure 5 2 5 2 4 LANDING DISTANCES Figure 5 3 SILA 450 C Lnd ground roll Lnd dist ...

Страница 36: ...a are for engine ROTAX 912 UL ULS as standard equipment for SILA 450 C Figure 5 5 SILA 450 C RPM 4800 5000 5100 5200 5500 IAS Km h 160 170 180 190 205 Suction Liters hour 13 5 14 15 16 20 Endurance hours 6 7 6 4 6 5 6 4 3 Range Km 1100 1100 1100 1000 950 CAUTION Recommended minimum engine speed is 4 800 rpm because of propeller efficiency 5 3 3 BALKED LANDING CLIMB In cases when is for any reason ...

Страница 37: ...cted pre flight inspection of these surfaces 5 3 6 DEMONSTRATED CROSSWIND PERFORMANCE For crosswind performance see chapter 4 4 and 4 4 8 Next figure showing demonstrated and recommended crosswind frontal wind and tail wing performances SILA 450 C Crosswind Frontal wind Tail wind Demonst Recomm Demonst Recomm Demonst Recomm 45 kmh 30 kmh 83 kmh 50 kmh 28 kmh 15 kmh Figure 5 7 CAUTION Performing of...

Страница 38: ... c AERO EAST EUROPE Date 01 09 2015 Revision 00 Page 38 SECTION 6 WEIGHT AND BALANCE _____TABLE OF CONTENTS__________________________________________ 6 1 Introduction 39 6 2 Weight and balance record permitted payload range 39 ...

Страница 39: ...Y LAOD RANGE Aircraft weighing procedure need to be performed when aircraft is leveled on plane surface The all operating fluids are in recommended boundaries with unusable fuel in fuel tanks Determining of center of gravity is in respect of leading edge of the wing as wing is rectangular there are the same where respect point is but according aviation standards the point is at the half of wing sp...

Страница 40: ...em 43 7 6 Seats and Safety Belts 43 7 7 Baggage Compartment 43 7 8 Doors Windows and Exits 43 7 9 Engine Oil System 43 7 10 Ignition Starter System 45 7 11 Air Induction System 45 7 12 Carburetor and Priming System 46 7 13 Cooling System 47 7 14 Propeller 47 7 15 Fuel System 47 7 16 Ignition Starter System 50 7 17 Air Induction System 51 7 18 Brake System 51 7 19 Electrical System 52 7 20 Minimum ...

Страница 41: ...aft landing gear is non retractable tricycle with nose leg Power plant consists from four stroke engine and tractor propeller with clockwise rotation Engine mount is fabricated from welded chrome molybdenum steel The engine compartment is from fire proof epoxy plastic Certification basis for SILA 450 C was primarily German Airworthiness Requirements LTF UL CS VLA and Serbian Regulation for Ultra L...

Страница 42: ...OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01 09 2015 Revision 00 Page 42 AIRPLANE SYSTEMS DESCRIPTION 7 4 INSTRUMENT PANEL ...

Страница 43: ...weight of baggage is limited to 20 kg 7 8 DORS WINDOWS AND EXITS Doors are positioned on left and right aircraft side in manner to make easier entrance and exit to aircraft in flight doors are closed Windshield and windows are from makrolon because better visibility 7 9 ENGINE OIL SYSTEM Oil for the engine lubrication is supplied from a tank out of the engine The full capacity of the engine oil ta...

Страница 44: ...o it is normal that the oil temperature decrease after the worming up of the engine to stabilize on a fixed value Because of the presence of an oil circuit separated from the engine case through radiator and pipeline it is very important the constant monitoring in occasion of the pre flight inspections verifying eventual leaking or critical points as the connections along the pipeline more no cont...

Страница 45: ...on the left of the control panel The engine should be operated on BOTH magnetos except for magneto checks and emergency use only When the switch is rotated the master relay is energized and battery is giving tension to the circuits Pressing the start button crankshaft an propeller will rotate in this way but for no more than 6 10 secds let the oil pressure gouge show a pressure increase than turni...

Страница 46: ...apparently reasonable worm weather conditions Do not hesitate to pull WORM air or to perform the ice test at the minimum doubt Cold exhaust pipes will no more give worm air do not risk Pull Warm air always when rain falls when misty when descending when passing through clouds 7 12 CARBURETORS AND PRIMING SYSTEM The system is consisting in two carburetors which are on the standard engine attached b...

Страница 47: ...r critical points as the connections along the pipeline more no contact points between the engine parts must be in the potential condition to impair trough vibrations any element of the pipeline including the radiator Inspect carefully the connection between the pump and the hose 7 14 PROPELLER The airplane equipment varies according the following Wooden two bladed fixed pitch Wood Composite Three...

Страница 48: ...er to maximize the availability of the remaining fuel in the tow main tanks until the light turns again off This operation may be carried on for one or two times until the alarm LOW FUEL red light will be constantly ON from this moment no more of about 0 5 Liters of fuel must be taken into account Prolonged slips deeps and skids may lead to an anomalous LOW FUEL alarm indication when the fuel amou...

Страница 49: ...NOTE Flying at temperatures higher than 35 Celsius is danger because of possibility of vapor in fuel system NOTE Use only fuel suitable for the respective climatic zone risk of vapor formation if using winter fuel for summer operation Fuel characteristics are depicted in the engine user manual If AVGAS 100LL is often used provide adequate servicing ...

Страница 50: ... fuel air mixture with dual ignition Ignition and starter operation is controlled by a rotary type switch located on the left switch and control panel The switch is labeled clockwise OFF R L BOTH and START The engine should be operated on BOTH magnetos except for magneto checks The R and L position are for checking purposes and emergency use only When the switch is rotated to the spring loaded STA...

Страница 51: ...de source Use of full carburetor heat at full throttle will result in a loss of approximately 75 to 150 RPM Ram air for engine cooling enters through two intake openings in the front of the engine cowling The cooling air is directed around the cylinders and other areas of the engine by baffling and is then exhausted through an opening at the bottom aft edge of the cowling No manual cooling system ...

Страница 52: ...are installed on request As concerning lighting conventional aviation lights are located on the wing tips and in tail A single landing light is located in the cowling Available are also flashing strobe lights on the wing tips as well as on the fuselage Panel and cabin lights also available The flashing lights should not be used when flying through clouds or overcast the flashing lights reflected f...

Страница 53: ...d for DC output is in connection with rectifier regulator type electronic full wave Effective voltage is 14 0 3V from 1000 250RPM The current limit is 22A and the max Permissible component temperature is 80 C A low voltage warning light is present on the instr Panel CIRCUIT BREAKERS AND FUSES All of the electrical circuits in the airplane are protected by push to reset type circuit breakers mounte...

Страница 54: ...ACUUM SYSTEM AND INSTRUMENTS As depicted in the Annex 2 ATTITUDE INDICATOR As depicted in the Annex 2 DIRECTIONAL INDICATOR As depicted in the Annex 2 SUCTION GAGE May be engine driven or Venturi driven As depicted in the Annex 2 WARNING The indications and suggestions of the present manual are valid ONLY within the limits and in compliance with what stated by the competent CAA or anyway since not...

Страница 55: ...ent on the aircraft when this is supposed to be used in VFR Flights o Magnet Compass o Aneroid Speed Indicator o Aneroid Altimeter o Radio VHF 7 20 2 ENGINE GAUGES AND OTHER DEVICES As for the engine or other instruments or devices here follows the minimum required equipment for a safe VFR o RPM indicator o Low volt light alarm o Oil pressure indicator o Oil temperature indicator o CHT Cilynder He...

Страница 56: ... and Repairs 57 8 4 Ground Handling 58 8 4 1 Towing 58 8 4 2 Parking 58 8 4 3 Mooring 58 8 4 4 Jacking 59 8 4 5 Leveling 59 8 4 6 Road Transport 60 8 5 Cleaning and Care 60 8 5 1 Painted Exterior Surfaces 60 8 5 2 Propeller 60 8 5 3 Engine 60 8 5 4 Interior Surfaces 60 8 6 Protocol for parachute installation 61 8 6 1 Parachute installation place 61 8 6 2 Parachute and rocket connection 66 8 6 3 Co...

Страница 57: ...tenance Program for airplane 8 2 AIRPLANE INSPECTION PERIOD Periodical inspections and reviews of airplane need to be performed at least in the following intervals After first 25 2 hours of operation After first 50 3 hours of operation After first 100 5 hours of operation After every 200 5 hours of operation Annual inspection Details of periodical inspections are described in Maintenance Program f...

Страница 58: ...gnition before ground handling with airplane CAUTION Carry out and avoid hard pressure to the airframe structure especially to the wing tips horizontal tail vertical tail ailerons flaps 8 4 2 PARKING The best solution for the aircraft parking is hangar with stabile atmospheric conditions such as humidity temperature good venting and dust free environment If parking isn t possible in hangar airplan...

Страница 59: ...rtable rests which will support the aircraft The aircraft can be jack by the following procedure push down the fuselage rear part from above put the template or rest below the firewall put the template or rest below the fuselage after cockpit at third framework The picture below showing possible way of airplane jack Picture 8 2 Airplane jacking 8 4 5 LEVELING Airplane leveling is on production tem...

Страница 60: ...ne can increase risk and decrease safety and aslo dissable guarantee 8 5 CLEANING AND CARE 8 5 1 PAINTED EXTERIOR SURFACES Cleaning of painted exterior surfaces performing by soft rag clean watter and non abrasive cleaning fluid for polishing 8 5 2 PROPELLER According to Propeller Maintenance Manual 8 5 3 ENGINE According to Engine Maintenance Manual 8 5 4 INTERIOR WINDSHIELD AND WINDOWS Cleaning ...

Страница 61: ...t parachute is installed in aircraft always is installed in accordace with certified staff and procedure 8 6 1 Parachute instalation place Parachute is installed in the rear middle part of the fuselage behind the pilot seats Picture 8 1 shows the position of the parachute on the SILA 450 C airplane Picture 8 1 Position of the parachute on the SILA 450 C aircraft Parachute mount consists of a cage ...

Страница 62: ... certified aeronautical material aluminum 6061T6 For the assembly of parachute mount and it s connection to the fuselage standard rivets and bolts were used The connections of the parachute mount to the fuselage are shown in the picture 8 3a and b Plate Plate top connection to the reinforcement Parachute cage Plate bottom connection Connection of the parachute cage to the plate Parachute hole Conn...

Страница 63: ... EUROPE Date 01 09 2015 Revision 00 Page 63 Picture 8 3a Connections to the fuselage Picture 8 3b Connections to the fuselage Reinforcement between two stringers for the top connection Reinforcement at the place for plate bottom connection ...

Страница 64: ...chute connections to the aluminum plate Parachute hole is located on the rear top part of the fuselage Dimensions of the parachute hole are given in the picture 8 5a Picture 8 5b shows parachute hole location on the SILA 450 C aircraft Picture 8 5a Parachute hole Plates for the parachute connection ...

Страница 65: ...he parachute hole are covered with bended sheet metal to prevent the damage of the parachute during the ejection This is shown in the picture 8 5c Also the holes on the parachute cover have grooves for easier ejection of the parachute This is shown in the picture 8 5d Picture 8 5c Protection of the parachute from sharp edges with bended sheet metal Bended sheet metal ...

Страница 66: ...plates shown in the picture 8 4 Picture 8 6 shows the position of the parachute inside it s mount Position of the rocket is shown in pictures 8 7a and b Rocket is connected to the parachute cage with four M5 bolts Parachute and rocket are connected with steel cables and carbine hook The connection of parachute and rocket is shown in picture 8 8 In the picture 8 1 one can see that there is nothing ...

Страница 67: ...OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01 09 2015 Revision 00 Page 67 Picture 8 6 Position of the parachute ...

Страница 68: ... Revision 00 Page 68 Picture 8 7a Position of the rocket Picture 8 7b Position of the rocket Connection of the rocket to the parachute cage Steel cable for the connection of rocket and parachute Connection of the rocket to the parachute activating control handle ...

Страница 69: ...ection of the parachute to the fuselage Parachute ropes are connected to the fuselage cabin frame front connection points which are shown in pictures 8 9a and b and to the main landing gear box rear connection points which are shown in pictures 8 10a and b Principial sheme of the parachute layout through the fuselage is given in the picture 8 12 ...

Страница 70: ...OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01 09 2015 Revision 00 Page 70 Picture 8 9a Parachute ropes front connection points Picture 8 9b Parachute ropes front connection points ...

Страница 71: ... rear connection point Picture 8 10b Parachute ropes rear connection point Drawing of the plate for the parachute connection is shown in the picture 8 11 To revent the damaging of parachute ropes half rod was welded to the plate Welding is done so as to prevent sharp edges that could damage the parachute ropes ...

Страница 72: ... Date 01 09 2015 Revision 00 Page 72 The length of the parachute ropes is 3m for backward connections and 2m for forward connections This gives the angle of descending of 30 degrees Picture 8 11 Drawing of the parachute connection plate Half rod ...

Страница 73: ...OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01 09 2015 Revision 00 Page 73 Picture 8 12 Principial sheme of parachute instalation on SILA 450 C airplane ...

Страница 74: ... be pulled even in the case of g load The parachute activating controll handle is held by using provided supportng plate which is directly connected to the central console with to M5 bolts The activating cable runs on lover side of central console under the fuselage and all the way to the connection to the rocket The parachute activating control handle is shown in the picture 8 13 Picture 8 13 Par...

Страница 75: ...____________________________________ 9 1 Introduction 76 9 2 List of Inserted Supplements 76 9 3 For Each Inserted Supplement 76 9 3 1 Section 1 General 76 9 3 2 Section 2 Limitations 76 9 3 3 Section 3 Emergency Procedures 77 9 3 4 Section 4 Normal Procedures 77 9 3 5 Section 5 Performance 77 9 3 6 Section 6 Weight and Balance 77 ...

Страница 76: ... AND BALANCE RECORD SERIAL NUMBERS OF AIRCRAFT IMPORTANT PARTS AND EQUIPMENT AICRAFT GEOMETRY MAINTENANCE PROGRAM FOR SILA 450 C AEE Form 35 FLIGHT TEST RECORD EMERGENCY PROCEDURES NORMAL PROCEDURES ABNORMAL PROCEDURES 9 3 FOR EACH INSERRTED SUPPLEMENT 9 3 1 Section 1 General For this chapter the next supplements are relevant Engine Manual INSTALATION MANUAL FOR ROTAX ENGIE TYPE 912 SERIES http ww...

Страница 77: ...ellow paper 9 3 4 Section 4 Normal Procedures For this chapter the next supplement is relevant NORMAL PROCEDURES With every delivered aircraft in the scope of delivery is Normal Procedures in hard copy printed on green paper 9 3 5 Section 5 Performance For this chapter the next supplements are relevant Engine Manual INSTALATION MANUAL FOR ROTAX ENGIE TYPE 912 SERIES http www rotax aircraft engines...

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