OPERATION MANUAL SILA 450 C AERO EAST EUROPE

OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 7 GENERAL INFORMATION 1.1 INTRODUCTION Section 1 provides basic data and information of general interest. Values stated in this chapter are based on calculation and tested values during flight tests and aircraft exploitation. Intention of aircraft manufacturer is to explain in safe manner using and exploitation of SILA 450 C. Basic aircraft characteristics are stated in foreword of this manual. 1.2 CERTIFICATION BASIS This flight manual has been prepared according to EASA CS – VLA and complies with LTF – UL (German Airworthiness Requirements) and Serbian Regulation for Ultra-Light Airplanes. 1.3 PERFORMANCES-SPECIFICATIONS(values according calculations and experience) SPEED: Maximum 223 kmh (120kts) Cruise, 75% power 204 kmh (110 kts) Stall speed flaps up 70 kmh (40 kts) CRUISE: Recommended with fuel allowance for engine start, takeoff, climb flight 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 64 km/h – 34Knots MAXIMUM TAKE-OFF WEIGH 472,5 kg STANDARD EMPTY WEIGHT 280 kg without parachute, 292,5 kg with parachute MAXIMUM USEFUL LOAD 180 kg=MTOW - (empty weight aircraft ) FUEL CAPACITY 100L ( 96 lit useful)–23,8 gallons (22,8 gallons useful) PROPELLER: Diameter 1600 – 1700 millimeters NOTE: The performance figures are estimated basically on the indicated weights, standard atmospheric conditions 15 °C (59 °F, 288,15K) and 101.325 kPa (14.696 psi, 1.01325 bar), sea level, hard-surface, dry runways and no wind. They are calculated values derive from calculations conducted by the Aero East Europe Company under carefully documented conditions and will vary with individual airplanes and numerous factors affecting flight performance. OPERATION 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 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 9 GENERAL INFORMATION 1.5 DESCRIPTIVE DATA 1.5.1 ENGINE - Number of engines: 1 piece - Engine Manufacturer: BRP Powertrain GmbH & Co KG - Engine Model Number: Rotax series , 912UL/ULS 2/ S/F/A - Engine Type: Normally aspirated, direct-drive, air-cooled, horizontally opposed, Carburetor equipped, four-cylinder engine with 319.8 cu.in. Displacement - Horsepower Rating and Engine Speed: 80/100 rated HP at 5800 RPM 1.5.2 PROPELLER - Propeller Manufacturer: WOODCOMP Czech Republik. MT Propeller and others - Propeller Model Number: Woodcomp……., MTV-33-1-A and others - Number of Blades: two and three blades etc - Propeller Diameter: Maximum: 1700 millimeters, Minimum: 1600 millimeters. - Propeller Type: Tractor 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 Landing Weight: 472,5 Kg 1.6 WARNINGS, CAUTIONS AND NOTES The next definitions are connected with warnings, cautions and notes used in Pilot Operation Handbook WARNING It means that non – observation of the appropriate procedure leads to an immediate or significant decreasing of flight safety. CAUTIONS It means that the non – observation of the appropriate procedure to a minor or to a more or less long term decreasing of flight safety. NOTES Draws attention to any special item or occurrence not related to safety but which is important or unusual. OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 10 LIMITATIONS SECTION 2 _____TABLE OF CONTENTS_______________________________________ • 2.1 Introduction 11 • 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 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 11 LIMITATIONS 2.1 INTRODUCTION Section 2 describing limitations which are must not to be exceed for safe flight. All limitations are market with appropriate placards. 2.2 AIR SPEED LIMITATIONS Air Speed Limitations and their operational significance are shown in Figure 2-1. Maneuvering speed shown apply to normal category operations SPEED IAS REMARKS VNE Never Exceed Speed 223 km/h 120(knots) Do not exceed this speed in any operation VH Maximum Structural Cruising Speed 204 km/h 110(knots) Do not exceed this speed except in smooth air. VRA Maximum speed for rough air 183 km/h 99 knots Exceed this speed only in smooth air VA Maneuvering Speed 165 km/h 89 (knots) Do not make full or abrupt control movements above this speed VFE Maximum Flaps ExtSpeed: 19° - 38° Flaps ½ - Full Flaps 106 km/h 57 (knots) Do not exceed this speed with flaps down. 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 maximum weight V in landing configuration. Upper limits maximum speed permissible with full flaps extend. Green Arc 91 km/h(49 knots) Normal Operating Range. Lower limit is maximum weight V at most forward C.G. with flaps retracted. Upper limit is maximum structural cruising speed. bar 165km/h(89knots) From 1.1 VS1 183km/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!!! Figure 2-2. Airspeed Indicator Makings Remark : The color of placard on Air Speed Indicator is the same as in Figure 2 – 2 WARNING Do not exceed speed of 223,6 km/h(120,6 knots) at any operation and at under any circumstances. OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 12 LIMITATIONS 2.4 POWER PLANT LIMITATIONS -Engine Manufacturer: BRP-Powertrain GmbH & Co KG -Engine Model Number: 912 UL -Maximum Power: 80 HP rating and others -Engine Operating Limits or Takeoff and continuous Operations: Maximum Engine Speed: 5800 RPM maximum for 5 min Maximum Oil Temperature: According Engine Manual NOTE Static engine RPM should be 5100+250 under clear weather without wind -Oil Pressure Minimum: 0.8 bar at 3000 rpm - 12 psi at 3000 rpm Maximum: 7 bar 101.5 psi. -Oil Grade (Specification): 10w – 40 / 5w - 50 -Propeller Manufacturer: Woodcomp s.r.o. and others -Propeller Model Number: Woodcomp SR 3000 and others -Propeller Diameter: 1700 millimeters NOTE: The static RPM range at full 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 RPM 1400 – 5500 RPM 1400 – 5500 RPM 1400 – 5500 RPM 5500 – 5800 RPM 5500 – 5800 RPM 5500 – 5800 RPM 5800 RPM 5800 RPM 5800 RPM Oil Temperature 50 0C 90 – 110 0C 50-90;110-130°C 130 0C Oil Pressure 0,83 bar 12 psi 2 – 5 bar 29 – 73 psi 0,83 – 2;5 – 7 bar 12 – 29;73 – 102 psi 7 bar 102 psi CHT 50 0C 50 – 130 0C 130-135 0C 135 0C Fuel Quantity 0 l 0 gallons 8 – 100 l 2,12– 26,4 gallons 0 – 8 l 0 – 2,12 gallons 100 l 26,4 gallons Suction 6,5 l/h 12,5 – 17,5 l/h N/A 25 l/h Figure 2-3 Power Plant Instrument Markings Remark : The colors on engine instruments are the same as in Figure 2 – 3 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 13 LIMITATIONS 2.6 WEIGHT LIMITS Maximum take – off weight 472,5 kg Maximum landing weight 472,5 kg Maximum empty weight 297,5 kg Maximum weight in baggage compartment 20kg Figure 2-4 2.7 CENTER OF GRAVITY LIMITS Center of Gravity range has two different categories for empty airplane and for different load cases. Center of Gravity range for empty airplane is calculated for the worst possible combination of loads from occupants, baggage(if any) and fuel, and considered the worst combination of weights during flight. Forward limit C.G. (empty airplane) 23,0% of MAC or 292 mm from leading edge Aft limit C.G. (empty airplane) 27,0% 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 the SILA 450 C, and figure 2-6 showing calculation for determining Center of Gravity position Picture 2 – Weighing plan Figure 2-6: Calculation of Center of Gravity positions Weighing point Scale reading Ri [kg] TareTi [kg] Net WeightNWi = Ri – Ti [kg] Nosewheel RN = [kg] TN = [kg] NWN = [kg] Left wheel RL = [kg] TL = [kg] NWL = [kg] Right wheel RR = [kg] TR = [kg] NWR = [kg] Total weight [lbs] or [kg] TW = NWN + NWL + NWR + + TW = [kg] C.G. position from Datum (Leading edge) [mm] C.G.=(𝑅𝐿+𝑅𝑅)𝑏−𝑅𝑁∙𝑎 𝑇𝑊 = ( + )633− 790 𝑇𝑊 = [𝑚𝑚] C.G. = [mm] C.G. position [% MAC] 𝐶. 𝐺 ̅̅̅̅̅ = 𝐶.𝐺. 𝑀𝐴𝐶 𝑥100 = 1270 ∙ 100 = [%] 𝑪. 𝑮 ̅̅̅̅̅ = [%] OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 14 LIMITATIONS 2.8 MANEUVER LIMITS This airplane is designed for non-aerobatic operations. These include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and turns in which the angle of bank is not more than 60°. WARNING Aerobatic maneuvers, including spins, are not approved. Non – aerobatic maneuvers are approved and they are listed below: MANEUVER RECOMMENDED ENTRY SPEED* Chandelles 167 km/h – 90 (knots) Lazy Eights 157 km/h – 85 (knots) Steep Turns 148 km/h – 80 (knots) WARNING Abrupt use of the controls is prohibited above 165 km/h - 89 (knots) CAUTION Aerobatics that may impose high loads should not be attempted. The important thing to bear in mind in flight maneuvers is that the airplane 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 MANEUVERING LOAD FACTORS According certification specifications and project calculations the load factor limits are the next, according maximum take – off weight and acceleration of gravity “g” Flaps retracted 0° Maximum positive load factor;VA,VNE +4 Maximum negative load factor -2 Figure 2 – 7: Limit load factor with flaps retracted Flaps deployed 19-38° (take-off and landing) Maximum positive load factor +2 Maximum negative load factor 0 Figure 2 – 7: Limit load factor with flaps deployed 2.10 FLIGHT CREW Minimum flight crew 1 pilot Maximum flight crew 2 (1pilot + 1copilot) Two seated aircraft side by side. OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 15 LIMITATIONS 2.11 KINDS OF OPERATIONAL LIMITS The airplane is equipped for day VFR and may be equipped for night VFR and/or IFR operations in any case no icing conditions. The reference to types of flight operations on the operating limitations placard reflects equipment installed at the time of Airworthiness issuance. WARNING A flight into known icing conditions is strictly prohibited. 2.12 FUEL LIMITATIONS Fuel Capacity: Total Capacity: 90 lit – 23,8 gallons Total Capacity Each Tank: 45 lit – 11,9 gallons Total reserve tank 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 in case when determining fuel quantity, is necessary that airplane be park at absolutely horizontal surface, it’s important to prevent spilling fuel from tanks because tanks are communicative. According to above mentioned facts parking at uneven surface can cause emphasis of fuel from inferior tank. Parking at absolutely horizontal surface is also important to have reliable information of fuel quantity. OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 16 LIMITATIONS 2.13 MAXIMUM PASSENGER SEATING SILA 450 C is two seated aircraft, as above mentioned this aircraft utility is sport and amateur flying and isn’t intended for passenger travel. Two seated aircraft, side by side, left pilot side, and right copilot side. Limitations for crew are stated in Chapter 2.10 of this document. 2.14 LIMITATIONS PLACARDS Limitation placards are installed on aircraft instruments and they are the same as depicted in this document, Chapter 2.3 and 2.5. the figures are shown below. Airspeed Indicator markings and their color code significance MARKING IAS VALUE OF RANGE SIGNIFICANCE White Arc From 1.1 VS0 72 – 106 km/h 39 – 57(knots) Full Flap Operating Range. Lower limit is maximum weight V in landing configuration. Upper limits maximum speed permissible with full flaps extend. Green Arc 91 km/h(49knots) Normal Operating Range. Lower limit is maximum weight V at most forward 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 certified values because of safety margin of 10%. Test pilots and manufacturing pilots are with much higher experience than amateur pilots. Power plant instrument markings and their color code significance INSTRUMENT RED LINE GREEN ARC YELLOW ARC RED LINE MINIMUM LIMIT NORMAL OPERATING MAXIMUM LIMIT Tachometer: Sea Level 5000 ft 10000 ft 1400 RPM 1400 – 5500 RPM 1400 – 5500 RPM 1400 – 5500 RPM 5500 – 5800 RPM 5500 – 5800 RPM 5500 – 5800 RPM 5800 RPM 5800 RPM 5800 RPM Oil Temperature 50 0C 90 – 110 0C 50-90;110-130°C 130 0C Oil Pressure 0,83 bar 12 psi 2 – 5 bar 29 – 73 psi 0,83 – 2;5 – 7 bar 12 – 29;73 – 102 psi 7 bar 102 psi CHT 50 0C 50 – 130 0C 130 – 135 0C 135 0C Fuel Quantity 0 l 0 gallons 8 – 90 l 2,12– 23,8 gallons 0 – 8 l 0 – 2,12 gallons 90 l 23,8 gallons Suction 7,5 l/h 14,5 – 18,5 l/h N/A 27 l/h OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 17 EMERGENCY PROCEDURES SECTION 3 _____TABLE OF CONTENTS_______________________________________ •3.1 Introduction 18 •3.2 Airspeeds for Emergency Procedures depend of emergency case but in general best rate of glide (circa 92-120 km/h 50 - 65knots) 18 •3.3 Engine Failures 18 -3.3.1 Engine Failure during Takeoff Run 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 -3.7.4 Cabin Fire 21 -3.7.5 Wing Fire 21 •3.8 Glide 21 •3.9 Approach and landing with flaps retracted 21 •3.10 Recovery from unintentional spin 22 •3.11 Other emergencies 22 - 3.11.1 Vibrations 22 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 18 EMERGENCY PROCEDURES 3.1 INTRODUCTION This Section provides checklists and amplified procedures for coping with emergencies that might occur. Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced. Enrooted weather emergencies can be minimized or eliminated by careful flight planning and good judgment when unexpected weather is encountered. However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to fix the problem. 3.2 AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure 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/h - 50(knots) IAS Precautionary approach speed for Landing Without Engine Power: Wing Flaps Up 120 km/h - 65(knots) IAS Wing Flaps Down 102 km/h - 55(knots) IAS 3.3 ENGINE FAILURES 3.3.1 ENGINE FAILURE DURING TAKEOFF RUN [1] Throttle --- IDLE [2] Brakes --- APPLY [3] Ignition Switch --- OFF [4] Master Switch --- OFF 3.3.2 ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF [1] Airspeed --- 120 km/h – 65(knots) IAS(flaps up) --- 102 km/h – 55(knots) IAS (flaps down) [3] Fuel Selector Valve --- OFF [4] Ignition Switch --- OFF [5] Wing Flaps --- AS REQUIRED [6] Master Switch --- OFF OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 19 EMERGENCY PROCEDURES 3.3.3 ENGINE FAILURE DURING FLIGHT [1] Airspeed --- 120 km/h - 65(knots) IAS [2] Check fuel quantity and selector --- ON [3] Carburetor Heat --- ON [4] Chock push --- OFF [5] Check engine instruments (temperature, etc) [6] Push start engine buttons, repeat several times [7] During recovery procedure, all the time take care about speed, attitude and selected field ! 3.4 FORCED LANDINGS 3.4.1 EMERGENCY LANDING WITHOUT ENGINE POWER [1] Airspeed --- 120 km/h - 65(knots) IAS (flaps up) --- 111 km/h - 60(knots) IAS (flaps down) [2] General Fuel Valve --- OFF [3] Change in flight direction up to 30° to left and right side. Highly recommended! [4] Wing Flaps --- AS REQUIRED, USUALY IN FINAL 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 at final approach --- 84 kmh 45 kts [7] Master Switch --- On [8] Doors --- UNLATCH PRIOR TO TOUCHDOWN [9] Touchdown --- SLIGHTLY TAIL LOW [10] Ignition Switch --- OFF AFTER TOUCHDOWN [11] Brakes --- APPLY HEAVILY(if necessary) 3.5 LANDING WITH FLAT MAIN TIRE [1] Wing Flaps --- DEPLOYED [2] Elevator control --- NOSE UP [3] Expect rotation after runway touch, to the flat tyre side [3] Aileron and rudder --- BANK TOWARD GOD TIRE [4] Rudder control --- KEEP NOSE STRAIGHT TO BALANCE ROTATION [5] Touchdown --- GOOD TIRE FIRST [6] Brakes --- APPLY CAREFULLY WITH HIGHER FORCE AT GOOD TYRE OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 20 EMERGENCY PROCEDURES 3.6 LANDING WITH A DEFECTIVE LANDING GEAR [1] Wing Flaps --- FULLY DEPLOYED [2] Elevator control --- NOSE HIGH [3] Aileron control --- ZERO POSITION [4] Rudder control --- KEEP NOSE STRAIGHT [5] Airspeed --- ADJUST TO MINIMUM POSSIBLE(CCA 65 KMH-35KNOTS) [6] Touchdown --- SLIGHTLY AND GENTLE [7] Landing roll --- KEEP STRAIGHT DIRECTION [8] Brakes --- APPLY (DEPPEND FROM DEFECTED LEG) Remark : If nose wheel damaged try to hold nose wheel over runaway using elevator till total decreasing of speed and kinetic energy. 3.7 FIRES 3.7.1 DURING START ON GROUND [1] Mixture --- IDLE CUT-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 the fire away from the airplane [5] Cabin Heat and Air --- OFF (except overhead vents) [6] Airspeed --- TAKE CARE ABOUT STALL SPEED [7] Precautionary Landing --- EXECUTE 3.7.3 ELECTRICAL FIRE IN FLIGHT [1] Master Switch --- OFF [2] Avionics Power Switch --- OFF [3] All other switches (except ignition switch) --- OFF [4] Continue with flight in opposite direction from fire to ensure that flue gases not entered to cockpit. [5] Cabin Air/Heat --- CLOSED (except overhead vents) OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 21 EMERGENCY PROCEDURES 3.7.4 CABIN FIRE IN FLIGHT [1] Master Switch --- OFF [2]Open window or snap vent in opposite side of the pilot and make shift plane in opposite direction from smoke source [3] Cabin Air/Heat --- CLOSED (except overhead vents) [4] Land the airplane as soon as possible to inspect for damage 3.7.5 WING FIRE [1] Navigation Light Switch --- OFF [2] Pitot Heat Switch --- OFF [3] Strobe Light Switch --- OFF [4] Fuel selector --- OFF BURNING WING [5Flight in opposite direction from fire and make 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 landing as soon as possible [5] Land according to 3.4.1 if necessary 3.9 APPROACH AND LANDING WITH FLAPS RETRACTED [1] AIRSPEED ---Take speed at least 92 kmh(50kts),because VS1=84 kmh(45kts) [2] Make landing approach with best glide slope [3] Start with landing at the beginning of the runaway, to ensure safe stop [4] TOUCHDOWN --- Slightly [5] BRAKES --- Apply (heavily if necessary) OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 22 EMERGENCY PROCEDURES 3.10 RECOVERY FROM UNINTENTIONAL SPIN WARNING Intentional spins are strictly prohibited. Information below is only for information to inform pilot about steps for recovery from emergency situation. [1] CONTROL STICK --- Push forward till start recovery and then pull back [2] THROTTLE --- FULL OPEN [3] CONTROL STICK --- 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 normal handling. 3.11 OTHER EMERGENCIES 3.11.1 VIBRATIONS [1] THROTTLE --- Adjust engine speed to minimize vibrations [2] Land as soon as possible; perform precautionary landing if necessary, chapter 3.4.2,3.4.1 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 23 SECTION 4 – NORMAL PROCEDURES _____TABLE OF CONTENTS_______________________________________ •4.1 Introduction 24 •4.2 Pre – flight inspection 24 •4.3 Rigging 26 •4.4 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 After Landing 32 - 4.4.16 Securing Airplane 32 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 24 NORMAL PROCEDURES 4.1 INTRODUCTION Section 4 provides checklists and amplified procedures for the conduct of normal operation. 4.2 PRE – FLIGHT INSPECTION Pre – flight inspection is absolutely necessary and mandatory. Steps necessary for pre – flight inspection are described below. Picture 4-1 : Aircraft pre – flight inspection 1. POWER PLANT Inspect general 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 condition of engine cowling. 2. NOSE LEG OF LANDING GEAR Inspect shock absorber, check legs attachments to firewall and wheel attachment to leg, inspect visually tire, check tire pressure (0,6 – 1,0 bar tundra tyres 1,1-1,3 15X6-6.00). OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 25 NORMAL PROCEDURES 3. LEFT WING Inspect general condition of upper surface, lower surface, leading and trailing edge, check rivets and attachment to fuselage and struts, inspect general condition of struts and attachment to wing and fuselage, inspect general condition ailerons, check freedom of movement and deflections, inspect attachments to wing, aileron hinges, inspect general condition flaps, check freedom of movement and deflections, inspect attachments to wing, flaps hinges, inspect wing root and wing tip and fuel tank cap, be sure that is properly tightened, to prevent fuel leaking. Visual inspection of pitot tube. 4. LEFT LEG OF MAIN LANDING GEAR Inspect brake system, check legs attachments to fuselage and wheels, visual inspect of tire and check tire pressure (0,6 – 1,0 bar tundra tyres 1,1-1,3 15X6-6.00). 5. LEFT SIDE OF FUSELAGE Inspect general condition of surfaces, check attachment with other parts of aircraft, check rivets visually. 6. LEFT PART OF HORIZONTAL AND 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 and rudder acting simultaneously, check there are no contact between rudder and elevator, check deflections. Inspect the trimmer on elevator and rudder. 8. RIGHT SIDE OF FUSELAGE Inspect general condition of surfaces, check attachment with other parts of aircraft, check rivets visually 9. RIGHT WING Inspect general condition of upper surface, lower surface, leading and trailing edge, check rivets and attachment to fuselage and struts, inspect general condition of struts and attachment to wing and fuselage, inspect general condition ailerons, check freedom of movement and deflections, inspect attachments to wing, aileron hinges, inspect general condition flaps, check freedom of movement and deflections, inspect attachments to wing, flaps hinges, inspect wing root and wing tip and fuel tank cap, be sure that is properly tightened, to prevent fuel leaking. OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 26 NORMAL PROCEDURES 10. RIGHT LEG OF MAIN LANDING GEAR Inspect brake system, check legs attachments to fuselage and wheels, visual inspect of tire and check tire pressure (0,6 – 1,0 bar0,6 – 1,0 bar tundra tyres 1,1-1,3 15X6-6.00). 11. COCKPIT Check that master and ignition switch in off position. Inspect freedom of control stick movement, inspect freedom of movement of rudder pedals, inspect freedom of movement of nose wheel. Check position of seats and locking mechanism if exist. Inspect safety belts from damage and check locking. Inspect instruments , and check for proper functioning. Inspect freedom of throttle lever movement, check engine cables. Inspect brakes, and check for proper 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 aircraft and this manual in next figure are given deflections of control surfaces with corresponding tolerances. All control surfaces need to set in zero position before flight. Aileron Up 19° + 2° Down 19° + 2° Elevator Up 25° + 2° Down 19° + 2° Flaps Down 1/2 19° + 2° Down full 38° + 2° Rudder Left 30° + 2° Right 30° + 2° Figure 4 - 1 Warning Rigging of any important part of aircraft structure is possible any in case of special approval of aircraft manufacturer and need to be connect to the specified aircraft serial number and specified type of rigging with clearly described reasons OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 27 NORMAL PROCEDURES 4.4 SPEEDS FOR NORMAL OPERATION The following speeds are based on a maximum weight of 472,5 kg and may be used for lesser weight. However, to achieve the performance specified in Section 5 for takeoff distance, the speed appropriate to the particular weight must be used. Takeoff, Flaps Up: Normal Climb Out 120 km/h - 65(knots) IAS Short Field Takeoff, Flaps 38°, Speed at 50 Feet 102km/h - 55(knots) IAS Enroute Climb, Flaps Up: Normal, Sea Level 149 km/h - 80(knots) IAS Best Rate of Climb, Sea Level 130 km/h - 70(knots) IAS Best Angle Of Climb, Sea Level 25̊ Landing Approach: Normal Approach, Flaps Up 111 km/h - 60(knots) IAS Normal Approach, Flaps down 38° 102 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: Takeoff or Landing 45 km/h 24,3(knots) IAS Maximum Demonstrated Frontal wind Velocity: Takeoff or Landing 83 km/h 45(knots) IAS Maximum Demonstrated Tailwind Velocity: Takeoff or Landing 28 km/h 15(knots) IAS 4.4.1 BEFORE STARTING ENGINE [1] Preflight Inspection --- COMPLETE [2] Seat Belts, Shoulder Harnesses --- ADJUST and LOCK. [3] General Fuel Valve --- ON [4] Avionics Power Switch, Electrical Equipment --- OFF [5] Brake --- TEST and SET [6] Circuit Breakers --- CHECK IN CAUTION:The Avionics Power Switch must be OFF during engine start to prevent possible damage to avionics. OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 28 NORMAL PROCEDURES 4.4.2 STARTING ENGINE [1] Start turn propeller without Master Switch –to get up oil pressure to 1,5 bar [2] Master Switch --- ON [3]Chock pull --- (only cold engine) [4] Throttle --- OPEN AT 1/4 APROXIMATELY TO 1800 RPM [5] Propeller Area --- CLEAR [6] General fuel valve --- ON [7]Push start engine buttons [8] Oil Pressure --- CHECK (To 2,5 bar in 10 secs max) [9] Flashing Beacon and Navigation Lights --- ON [10] Avionics, TXP, VHF Radio Power Switch --- ON 4.4.3 BEFORE TAXYING [1] Parking Brake --- RELEASE [2] Cabin Doors and Windows --- CLOSED and LOCKED [3] Flight Controls --- FREE and CORRECT [4] Flight Instruments --- SET [5] Fuel level check, general fuel valve --- 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] Throttle --- 3800 RPM a. Magnetos --- CHECK(both – left and right for RPM drop)* b. Carburetor Heat --- CHECK (for RPM drop) c. Engine Instruments and Ammeter --- CHECK d. Suction Gauge --- CHECK [8] Power check --- CHECK at 5000 RPM and POWER IDLE [9] Constant speed propeller controller --- CHECK & SET [8] Throttle --- 1800 RPM [9] Radios --- SET [10] Autopilot (if installed) --- OFF [11] Air Conditioner (if installed) --- OFF [12] Strobe Lights --- ON [13] Brakes --- RELEASE NOTE: RPM drop should not exceed 300 RPM on either magneto or 150 RPM difference between magnetos OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 29 NORMAL PROCEDURES 4.4.6 NORMAL TAKEOFF [1] Wing Flaps --- 19° [2] Carburetor Heat --- OFF [3] Throttle --- FULL OPEN(progressively) [4] Elevator Control(at 80 kmh/45kts) --- LIFT NOSE WHEEL [5] Climb Speed --- 100 – 140 km/h 54 - 75(knots) IAS 4.4.7 SHORT FIELD TAKEOFF [1] Wing Flaps --- 38° [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 20 83 30 80 Frontal wind[kmh] Take off distance[m] 0 90 20 80 30 75 40 70 50 65 Tail wind[kmh] Take off distance[m] 0 90 10 120 15 140 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 30 NORMAL PROCEDURES Angle[⁰] Wind[kts] Crosswind [kmh] Front wind[kmh] Angle[⁰] Wind[kts] Crosswind [kmh] Front wind[kmh] 10 10 3.21 18.24 10 20 6.43 36.48 20 10 6.33 17.40 20 20 12.66 34.81 30 10 9.26 16.04 30 20 18.51 32.08 40 10 11.90 14.19 40 20 23.80 28.38 50 10 14.18 11.91 50 20 28.36 23.82 60 10 16.03 9.27 60 20 32.07 18.54 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 tested cross wind conditions. Take of in red cells condition is prohibited Note: If you have only one component of wind, for example if frontal wind is equal to 45 kmh you can take off. Flight direction OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 31 4.4.9 ENROUTE CLIMB [1] Airspeed --- 120 – 140 km/h - 65 - 75 IAS [2] Throttle --- 90% of Power 4.4.10 CRUISE [1] Power --- 5000 – 5200 RPM(75-80% of Power) [2] Constant speed variable pitch --- SET & RPM ADJUST(in case of VPP) [2] Elevator Trim --- ADJUST [3] Rudder/Aileron Trim --- ADJUST 4.4.11 DESCEND [1] General Fuel Valve --- ON [2] Reduce power --- SET (balance MAP & RPM) [3] Constant speed variable pitch --- SET & RPM ADJUST(in case of VPP) [4] Airspeed --- (not exceed 223 kmh/120 kts IAS in smooth air) [5] Carburetor Heat --- FULL HEAT AS REQUIRED 4.4.12 BEFORE LANDING [1] Seat Belts, Shoulder Harnesses --- SECURE [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 - 60(knots) IAS (flaps DOWN) [3] Touchdown --- MAIN WHEELS FIRST [4] Landing Roll --- LOWER NOSE WHEEL GENTLY [5] Braking --- MINIMUM REQUIRED 4.4.14 SHORT FIELD LANDING [1] Airspeed --- 83 – 102 km/h - 45 - 55(knots) IAS (full flaps) [2] Wing Flaps --- FULL DOWN(in final approach) [3] Airspeed in flare --- 74 km/h - 40(knots) IAS (until flare) [4] Power --- Maintain required engine RPM to enable more vertical descend [5] Touchdown --- MAIN WHEELS FIRST [6] Brakes --- APPLY HEAVILY OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 32 NORMAL PROCEDURES 4.4.15 AFTER LANDING [1] Wing Flaps --- UP [2] Carburetor Heat --- OFF [3] Avionics Power Switch --- OFF [4] Remain engine 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) OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 33 PERFORMANCE SECTION 5 - PERFORMANCE _____TABLE OF CONTENTS__________________________________________ •5.1 Introduction 34 •5.2 Approved data 34 - 5.2.1 Airspeed indicator system 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 Demonstrated Crosswind Performances 37 - 5.3.7 Noise data 37 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 34 PERFORMANCE 5.1 INTRODUCTION Flight performances are valid for standard version of aircraft under maximum take – off weight of 472,5 kg, for pilots with normal pilot skills and ISA conditions (sea level, 15°C, 1013 hPa). Flight characteristic are tested and calculate, the all flight characteristic are tested and most of flight characteristics are tested and calculated, both ways. Difference between calculated and tested values are 5% for extremely cases, in majority of characteristics difference is less than 3%. 5.2 APPROVED DATA As above mentioned data of important flight characteristics 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. During pitot – static testing procedure, all important aircraft instruments are calibrated and level of mistake is minimal and in approved tolerances. After this pre – delivery check, periodical pitot – static testing and adjustments are obligation of aircraft owner, according to approved periods for maintenance and testing of equipment. Pictures 5 – 1 , 5 – 2 , 5 – 3 , 5 – 4 showing tested values of tested equipment Picture 5 – 1 CRS Picture 5 – 2 Airspeed indicator and altimeter OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 35 PERFORMANCE 5 – 3 Compass 5 – 4 Pitot – static test data 5.2.2 STALL SPEED Stalling speeds are mentioned in figure below. Stalling speeds are valid for aircraft weight of 472,5 kg and wing level flight. SILA 450 C Indicated Stall speed IAS Flaps retracted 83 kmh (45 knots) Flaps take off position ½ 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. From 15 m Obst. Flaps in landing position 140 m 380 m OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 36 PERFORMANCE 5.2.5 CLIMB PERFORMANCE SILA 450 C climb performances are shown at figure 5 – 4 below Altitude Rate of climb Airspeed to achieve maximum rate of climb 0 m 5,6 m/s (1100 ft/min) 120 kmh(65 knots) 1.000 m(3.300 feet) 4,1 m/s (800 ft/min) 120 kmh(65 knots) Figure 5-4 5.3 ADDITIONAL INFORMATION Additional information provide to pilot more useful information for easier handling with aircraft. 5.3.1 CRUISE Recommended cruising speed of SILA 450 C is 204 kmh(110 Knots), engine rpm 5.000 – 5.200 (75-80 % power) between 29-32 MAP, for IAS condition (standard atmosphere). Aircraft is correctly trimmed for wing level flight, with elevator trimmer and rudder trimmer if installed. 5.3.2 ENDURANCE, CRUISING SPEED & RANGE Endurance data 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 necessary to execute balked landing maneuver, its need to make next steps [1] Carburetor heating --- OFF [2] Throttle --- APPLY PROGRESSIVELY & SMOOTHLY [3] Engine RPM --- 5.000 – 5.300 [4] Control stick --- PULL BACKWARD SMOOTHLY TO LEVELED FLIGHT [5] Throttle --- FULL OPEN MAX CONTINOUS POWER [7]Flaps --- SET TO ½ POSITION [8]Climb --- Minimum altitude 200 M(650 feet)QFE [9] Speed --- INCREASE TO 100 KMH (54 Knots) [10] Flaps --- RETRACT [11] STEP TURN 90 + 90 ° --- EXECUTE [12] Repeat landing approach and landing procedure see 4.4.13 CAUTION During the balked landing maneuver keep the straight - line flight, except if otherwise requested from particular situation OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 37 PERFORMANCE 5.3.4 TAKE OFF MEASUREMENT FROM A DRY, SHORT – MOWN GRASS SURFACE Take – off measurement from a dry, short – mown surface are performed and data in table 5 – 6, ant it’s only can be used for take – off from short distances. Figure 5 - 6 5.3.5 EFECTS ON FLIGHT PERFORMANCES AND CHARACTERISTICS CAUSED BY RAIN OR ACCUMULATION OF INSECTS During the rainy weather, flight characteristics decreasing because aerodynamic characteristics of airplane and decreased visibility, and huge accumulation of insects on windshield and lift surfaces can also cause decreasing of aircraft characteristic. There is predicted 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 flights in wind conditions over recommended values can increase risk to significant level and shouldn’t be performed at any circumstances 5.3.7 NOISE DATA Measuring of noise level is performed in Germany by Deutche Aero Club(DAeC) engineers and SILA 450 C meets all requirements and standards according to German Airworthiness Requirements LTF – UL. Measured noise level is around 59.42 dB DAeC. SILA 450 C Take – off run Take – off with obstacle 15 m Flaps take off position 90 m 190 m OPERATION MANUAL SILA 450 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 OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 39 WEIGHT AND BALANCE 6.1 INTRODUCTION The aircraft weight and determination of aircraft weight is extremely important to be in proper balance, because maneuvering and controllability of aircraft depends on C.G. position and distribution of payload. There are some limitations about payload but for any case in this manual, for example baggage with weigh of 20 kg. 6.2 WEIGHT AND BALANCE RECORD PERMITED PAY 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 span. Figure 6 -1 Weight and balance record Figure 6 – 1 showing weight and balance record and permitted C.G. range of empty aircraft. Permitted range of C.G. for empty airplane is 23-27% of MAC or 292 – 340 mm from l.e. WARNING If C.G. isn’t in allowed range further exploitation is prohibited OPERATION MANUAL SILA 450 c AERO EAST EUROPE Date 01.09.2015. Revision 00 Page | 40 SECTION 7 – Airplane System & Description _____TABLE OF CONTENTS__________________________________________ •7.1 Introduction 41 •7.2 Airframe 41 •7.3 Flight controls 41 •7.4 Instrument Panel 42 •7.5 Landing Gear System 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 Required Flight Equipment 55 - 7.20.1 Avionics 55 - 7.20.2 Engine Gauges and Other Devices 55