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P92 Eaglet

Flight Manual

Revision Date: 12-14-2007
Revision Number: 1.00

Doc n° 27-13-100-00

16

1.7 Airframe

1.7.1

Wing

The wing is constructed of a central light alloy torque box; an aluminum leading edge with integrated fuel tank is attached
to the front spar while flap and aileron are hinged to rear spar. Flaps are constructed of a center spar to which front and rear
ribs are joined; wrap-around aluminum skin panels cover the flap structure. The aileron is constructed of an aluminum spar
to which a formed sheet metal leading edge and metal ribs are attached; a wrap-around. Aluminium material covers aileron
structure.

1.7.2

Fuselage

The front part of the fuselage is made up of a mixed structure: a truss structure with special steel members for cabin
survival cell, and a light-alloy semi-monocoque structure for the cabin's bottom section. The aft part of the fuselage is
constructed of an aluminum alloy semi-monocoque structure. The engine housing is isolated from the cabin by a stainless
steel firewall; the steel stringers engine mount is attached to the cabin's truss structure in four points.

1.7.3

Empennage

The vertical tail is entirely metal: the vertical stabilizer is made up of a twin spar with load carrying skin while the rudder
consists of an aluminum torque stringer connected to light alloy ribs and skin. The horizontal tail is an all-moving type
(stabilator); its structure consists of an aluminum spar connected to ribs and leading edge; the entire structure is covered
with aluminum material.

1.7.4

Flight controls

The control surfaces are manually operated using a control stick for ailerons and stabilator and rudder pedals for the rudder;
longitudinal control acts through a system of push-rods and is equipped with a trim tab. Aileron control is of mixed type
with push-rods and cables; the cable control circuit is confined within the cabin and is connected to a pair of push-rods
positioned in the wings that control ailerons differentially. Aileron trimming is carried out on ground through a small tab
positioned on left aileron.
Flaps are extended via an electric servo actuator controlled by a switch on the control stick. Flaps act in a continuous mode;
a panel mounted indicator shows surface position. A fuse positioned on the right side of the panel protects the electric
circuit.
Longitudinal trim is performed by a small tab positioned on the stabilator and controlled via an electric servo actuator by
pushing an Up/Down push-button located on the control stick.

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Содержание P92 Eaglet

Страница 1: ...year ___________________ Registration __________________ Introduction This manual contains information to be furnished to the pilot as required by the FAA in addition to further information supplied by the manufacturer This manual must always be present on board the aircraft The aircraft is to be operated in compliance with information and limitations contained herein All sections follow the ASTM ...

Страница 2: ... except actual weighing data must be recorded in the following table New or amended text in the revised pages will be indicated by a black vertical line in the left hand margin Revision Number and date will be shown on the right hand side of the amended page Log of Revisions Revision No Date released Chapters Approved By 1 0 12 14 2007 All Tecnam ...

Страница 3: ... 14 2007 46 12 14 2007 12 12 14 2007 47 12 14 2007 13 12 14 2007 48 12 14 2007 14 12 14 2007 49 12 14 2007 15 12 14 2007 50 12 14 2007 16 12 14 2007 51 12 14 2007 17 12 14 2007 52 12 14 2007 18 12 14 2007 53 12 14 2007 19 12 14 2007 54 12 14 2007 20 12 14 2007 55 12 14 2007 21 12 14 2007 56 12 14 2007 22 12 14 2007 57 12 14 2007 23 12 14 2007 58 12 14 2007 24 12 14 2007 59 12 14 2007 25 12 14 2007...

Страница 4: ...nts 15 1 6 2 Engine instruments 15 1 6 3 Warning Lights and Indicators 15 1 6 4 Controls 15 1 6 5 Interior 15 1 6 6 Exterior 15 1 6 7 Powerplant and Accessories 15 1 7 Airframe 16 1 7 1 Wing 16 1 7 2 Fuselage 16 1 7 3 Empennage 16 1 7 4 Flight controls 16 1 7 5 Instrument Panel 17 1 7 6 Carburetor Heat 17 1 7 7 Cabin Heat Defrost 17 1 7 8 Throttle Friction Lock 17 1 7 9 Seats Seatbelts and Shoulde...

Страница 5: ...1 9 Coolant 28 2 1 10 Propeller 28 2 1 11 Fuel 28 2 1 12 Approved Fuel 29 2 1 13 Powerplant Instrument Markings 29 2 1 14 Other Instrument Markings 29 2 1 15 Weights 29 2 1 16 Center of Gravity Limits 29 2 1 17 Approved Maneuvers 30 2 1 18 Maneuvering Load Factor Limits 30 2 1 19 Flight Crew 30 2 1 20 Kinds of Operations 30 2 1 21 Day VFR 31 2 1 22 Night 31 2 1 23 IFR 31 2 1 24 Demonstrated Crossw...

Страница 6: ...1 Engine Failures 50 5 1 1 Engine Failures on Ground 50 5 1 2 Engine Failure during Flight 50 5 2 Smoke and Fire 51 5 2 1 Engine Fire while parked 51 5 2 2 Engine Fire during Takeoff 51 5 2 3 Engine Fire in flight 51 5 2 4 Cabin Fire during Flight 52 5 3 Landing Emergency 52 5 4 Recovery from Unintentional Spin 53 5 5 Other Emergencies 53 5 5 1 UNINTENTIONAL FLIGHT INTO ICING CONDITIONS 53 5 5 2 C...

Страница 7: ...sport 63 7 3 6 Cleaning and Care 63 7 3 7 Ground anchorage 63 8 Placards and Markings 64 WARNINGS CAUTIONS NOTES The following definitions apply to warnings cautions and notes used in the Flight Manual WARNING Means that the non observation of the corresponding procedure leads to an immediate or important degradation of the flight safety CAUTION Means that the non observation of the corresponding ...

Страница 8: ...uising Speed is the speed that should not be exceeded except in smooth air then only with caution VS Stalling Speed or minimum steady flight speed flaps retracted VS0 Stalling speed or minimum steady flight speed in landing configuration VS1 Stalling speed in clean configuration flap 0 VX Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal di...

Страница 9: ...uration per gallon of fuel used Weight and Balance Terminology Datum Reference datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes Arm is the horizontal distance from the reference datum to the center of gravity C G of an item Moment is the product of the weight of an item multiplied by its arm C G Center of Gravity is the point at which the a...

Страница 10: ...ilometers km 0 5396 Nautical miles nm Nautical miles nm 1 853 Kilometers km Meters m 3 281 Feet ft Feet ft 0 3048 Meters m Centimeters cm 0 3937 Inches in Inches in 2 540 Centimeters cm Volume Liters l 0 2642 U S Gallons US Gal U S Gallons US Gal 3 785 Liters l Area Square meters m2 10 76 Square feet sq ft Square feet sq ft 0 0929 Square meters m2 Torque foot pounds 1 3558 Newton meters foot pound...

Страница 11: ...e primary numbers are in metric and the US conversion is in parenthesis for your information This Flight Manual has been prepared to ASTM standards to provide pilots and instructors with information for the safe and efficient operation of this aircraft This Flight Manual contains the following sections 1 General Information 2 Operating Limitations 3 Weight Balance 4 Performance 5 Emergency Procedu...

Страница 12: ...0 00 12 THREE VIEW DRAWING Figure 1 1 General Views Wing Span 8 7m 28 5 Length 6 5m 21 3 Tail height 2 5m 8 2 Propeller ground clearance 320mm 12 6 Minimum ground steering radius 5 5m 18 NOTE Dimensions shown refer to aircraft weight of 600 kg 1320 lbs and normal operating tire pressure ...

Страница 13: ...abilator area 1 972 m2 21 2 ft2 1 3 1 4 Landing Gear Wheel track 1 8 m 5 9 Wheel base 1 6 m 5 2 Main gear tires Air Trac 5 00 5 Nose gear tire Sava 4 00 6 Wheel brakes Marc Ingegno 199 102 1 4 Powerplant 1 4 1 Engine Manufacturer Bombardier Rotax GmbH Model 912 ULS or 912 S2 Certification basis ASTM F2239 or FAR Part 33 Type 4 stroke carburetor engine Maximum power 73 5 kW 98 5 hp 5800 rpm max 5 m...

Страница 14: ...rade Auto fuel Avgas Min RON 95 AKI 91 Premium USA 100LL Fuel tanks 2 integral wing tanks Capacity of each wing tank 45 liters 11 9 gal Total capacity 90 liters 23 8 gal Total usable fuel 86 8 liters 22 9 gal 1 5 Weights 1 5 1 Maximum Weights Maximum take off weight 600 kg 1320 lbs Maximum landing weight 600 kg 1320 lbs Maximum baggage weight 20 kg 44 lbs 1 5 2 Standard Weights Empty weight 325 kg...

Страница 15: ...oke Electric Flaps Hydraulic Disc Brakes with Parking Brake Left and Right Fuel Selector Valves Direct Nose Wheel Steering 1 6 5 Interior Adjustable Pilot and Copilot Seats Acoustic Cabin Soundproofing Adjustable Cabin Air Ventilators Steel Roll Cage Cabin Heat and Windshield Defrost 12V Power Outlet Metal Instrument Panel 1 6 6 Exterior All Aluminum structure Landing Light Strobe Light Fixed Land...

Страница 16: ...ly metal the vertical stabilizer is made up of a twin spar with load carrying skin while the rudder consists of an aluminum torque stringer connected to light alloy ribs and skin The horizontal tail is an all moving type stabilator its structure consists of an aluminum spar connected to ribs and leading edge the entire structure is covered with aluminum material 1 7 4 Flight controls The control s...

Страница 17: ...Heat Defrost The cabin heat control knob is positioned on the lower of the instrument panel when knob is pulled fully outward cabin receives maximum hot air Vents are located by the rudder pedals and above instrument panel If necessary outside fresh air can be circulated inside cabin by opening the vents on the panel 1 7 8 Throttle Friction Lock Adjust the engine s throttle friction by tightening ...

Страница 18: ...n be run continuously at 5500 RPM The oil system is a dry sump forced lubrications system The oil tank is located on the passenger side of the engine compartment and holds 3 liters 3 2 quarts of oil The dual ignition system is a solid state breakerless capacitive discharge interference suppression system instead of a mechanical magneto system Each ignition system is powered by individual and total...

Страница 19: ...d with a cabin installed shutoff valve A strainer cup with a drainage valve Gascolator is located on the engine side of the firewall Fuel level indicators for each tank are located on instrument panel Fuel feed is through an engine driven mechanical pump All fuel lines located in the engine compartment are protected with fireproof braiding to avoid possible fire Figure 1 3 illustrates the schemati...

Страница 20: ...Right Fuel Tank Firewall Mesh filter and drain Filter M Mechanical Fuel Pump Electric Fuel Pump Left Carb Right carb Fuel Pressure gauge Balance line Fuel Selector Valves Right wing fuel tank vent Left wing fuel tank vent Left fuel quantity indicator Right fuel quantity indicator Drain Figure 1 3 Fuel System ...

Страница 21: ... right side of the instrument panel WARNING If the Ignition Switches are ON an accidental movement of the propeller may start the engine with possible danger for bystanders Fig 1 4 Electrical system schematic 1 9 1 Generator light Generator light red illuminates for the following conditions Generator failure Failure of regulator rectifier with consequent over voltage sensor set off NOTE The batter...

Страница 22: ...al Outside Air Temperature indicator C is located on the upper left side of the instrument panel The sensor is placed on cabin top 1 9 8 Stall Warning System The aircraft may be equipped with a stall warning system consisting of a sensor located on the right wing leading edge connected to a warning horn located on the instrument panel 1 9 9 Avionics The central part of the instrument panel holds r...

Страница 23: ... the instrument panel The signal reaches a strobe light trigger circuit box positioned in the tail cone just behind the baggage compartment 1 10Pitot and Static Pressure Systems The airspeed indicator system for the aircraft is shown below Below the left wing s leading edge the Pitot tube 1 while on the fuselage s sides there are two static ports 2 Two flexible hoses 3 feed the airspeed indicator ...

Страница 24: ...oard end of the leaf spring to the girder Figure 1 6 Main landing gear Wheels are cantilevered on gear struts and feature hydraulically actuated disc brakes see fig 4 13 controlled by a lever 1 located on cabin tunnel between seats Main gear wheels mount Air Trac type 5 00 5 tires inflated at 23 PSI 1 6 bar Hydraulic circuit shut off valve 2 is positioned between seats With circuit shut off pullin...

Страница 25: ...m has a reservoir 4 on the co pilot s brake pedals 1 The reservoir is directly connected to the brake master cylinders 3 Two flexible hoses connect the master cylinders on the co pilot s brake pedals to the master cylinders on the pilot s brake pedals The parking brake valve 6 is mounted on the floor of the fuselage below the seats and it s activated by lever 2 Each main wheel has a brake disc 7 F...

Страница 26: ...mit load factor VFE Maximum flap extended speed 68 Never exceed this speed for any given flap setting VH Maximum speed 120 Maximum speed in level flight at max continuous power MSL VX Best Angle Climb 60 The speed which results in the greatest gain of altitude in a given horizontal distance VY Best Rate Climb 68 The speed which results in the greatest gain of altitude in a given time 2 1 2 Airspee...

Страница 27: ...low 3500 RPM Normal 2 0 5 0 bar Above 3500 RPM 2 1 6 Operating starting temperature range OAT Min 25 C OAT Max 50 C Warning Admissible pressure for cold start is 7 bar maximum for short periods For your information Bar is a unit of measure The word comes from the Greek baros weighty We see the same root in our word barometer for an instrument measuring atmospheric pressure One bar is just a bit le...

Страница 28: ... into the Rotax Operator s Manual and in its related documents 2 1 10 Propeller Manufacturer GT Tonini Model GT 2 173 VRR SRTC FW 101 Propeller type Wood twin blade fixed pitch Diameter 1730 mm 68 no reduction permitted 2 1 11 Fuel Two tanks 45 liters 11 9 gallons Total fuel capacity 90 liters 23 8 gallons Usable fuel quantity 86 8 liters 22 9 gal NOTE During all phases of flight both tanks normal...

Страница 29: ...limit Engine Tach Rpm 1400 5500 5500 5800 5800 Oil Temp C 50 90 110 50 90 110 130 130 C Cylinder heads temp C 50 135 135 C Oil pressure Bar 0 8 2 5 0 8 2 5 7 7 Fuel Pressure PSI 2 2 2 2 5 8 5 8 2 1 14 Other Instrument Markings Instrument Red line Minimum limit Green arc Normal operating Yellow arc Caution Red line Maximum limit Voltmeter 10 Volt 12 14 Volt Suction gauge if installed 4 0 in Hg 4 5 ...

Страница 30: ...n 1 Knots sec Warning Limit load factor could be exceeded by moving the flight controls abruptly to full control deflection at a speed above VA 93 KIAS Maneuvering Speed 2 1 18 Maneuvering Load Factor Limits Maneuvering load factors are as follows Flaps 0 4 2 35 1 9 0 2 1 19 Flight Crew Minimum crew for flight is one pilot seated on the left side 2 1 20 Kinds of Operations The airplane in standard...

Страница 31: ...ompass Fuel Gauges Oil Pressure Indicator Oil Temp Indicator Cylinder Head Temp Indicator Tachometer Flight into expected and or known icing conditions is prohibited 2 1 22 Night Night flight is approved if the aircraft is equipped as per the ASTM standard F2245 06 A2 LIGHT AIRCRAFT TO BE FLOWN AT NIGHT as well as any pertinent FAR NOTE The FAA requires that the pilot possesses a minimum of a Priv...

Страница 32: ...tion 0 Place control surfaces in neutral position Place scales min capacity 200 kg 440 pounds under each wheel Level the aircraft using cabin floor as datum Center bubble on level by deflating nose tire Record weight shown on each scale Repeat weighing procedure three times 3 1 2 Calculate empty weight Weighing Record weight shown on each scale Repeat weighing procedure three times Calculate empty...

Страница 33: ...distance LH wheel AL LH wheel weight WL Plumb bob distance RH wheel AR RH wheel weight WR Average distance AL AR 2 A W2 WL WR Bob distance from nose wheel B Empty weight 1 We W1 W2 D W A W B We 2 1 m D D 14 100 Empty weight moment M D 1 430 We Kg m Maximum takeoff weight WT 600 kg Empty weight We Sign _______________ Maximum payload WT We Wu 1 Including unusable fuel 2 3 kg 3 2 1 Center of Gravity...

Страница 34: ...2 Eaglet Flight Manual Revision Date 12 14 2007 Revision Number 1 00 Doc n 27 13 100 00 34 3 2 2 Distances from the datum The mean distances of the occupants baggage and fuel from the datum are Figure 3 4 ...

Страница 35: ...7 30 2610 36 70 4850 63 320 22174 31 7 42 2745 02 35 3045 42 80 5543 58 330 22867 26 8 48 3137 16 40 3480 48 90 6236 52 340 23560 20 9 54 3529 31 44 3828 53 100 6929 47 350 24253 15 10 60 3921 45 110 7622 42 360 24946 10 11 66 4313 60 120 8315 37 370 25639 05 12 72 4705 74 130 9008 31 380 26331 99 13 78 5097 89 140 9701 26 390 27024 94 14 84 5490 03 150 10394 21 400 27717 89 15 90 5882 18 160 1108...

Страница 36: ...total weight does not exceed maximum gross weight of 1320 pounds 7 Check that the arm falls within the C G range Computation Chart Weight lbs Arm inches Moment Empty Weight Fuel 65 36 Pilot Passenger 69 29 Baggage 87 01 Totals C G Range Meters 1 7430 1 9250 Inches 68 60 75 8 Max Weight Pounds Kilograms 1320 00 600 00 Example Problem Weight lbs Arm inches Moment Empty Weight 748 9 67 79 50767 93 Fu...

Страница 37: ...item type Item description Serial number Equipment list Date Ref Description p n Weight kg Datum m Engine accessories A1 Engine Rotax 912S2 or 912ULS 61 0 0 32 A2 Propeller Tonini GT 2 173 VRR SRTC FW101 6 0 0 13 A3 Exhaust and manifolds p n 973670 4 50 0 55 A4 Heat exchanger p n 92 11 830 2 00 0 55 A5 Oil Reservoir full p n 956 137 4 00 0 64 A6 Oil radiator p n 886 025 0 40 0 07 A7 Liquid coolant...

Страница 38: ... D1 Altimeter United Instruments p n 5934PM 3 or LUN 1128 10B4 TSO C10b 0 39 1 35 D2 Airspeed Ind UMA T6 311 161 TSO C2b 0 30 1 35 D3 Compass Airpath C2300 TSO 0 29 1 35 D4 Clock Quartz Chronometer LC2 AT420100 0 15 1 35 D5 Vertical speed indicator VSI 2FM 3 0 35 1 35 D6 Turn and Bank Indicator FALCON GAUGER TC02E 3 1 0 56 1 35 D7 Attitude Indicator GH 02V 3 1 10 1 35 D8 Directional Gyro FALCON GA...

Страница 39: ...ngine in good condition Average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA MSL evaluations of the impact on performance were carried out by theoretical means for Airspeed External temperature Altitude Weight Type and condition of runway 4 1 Use of Performance Charts Performance data is presented in tabular or graphical form to illustrate the ef...

Страница 40: ...n 27 13 100 00 40 4 2 Airspeed Indicator System Calibration Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS Fig 4 1 Calibrated vs Indicated Airspeed 40 50 60 70 80 90 100 110 120 130 140 40 50 60 70 80 90 100 110 120 130 140 IAS kts CAS kts 78 75 ...

Страница 41: ...P92 Eaglet Flight Manual Revision Date 12 14 2007 Revision Number 1 00 Doc n 27 13 100 00 41 4 3 ICAO Chart Fig 4 2 ICAO CHART ...

Страница 42: ...600 kg 1320 lbs Throttle idle No ground effect NOTE Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 100ft with banking under 30 0 30 45 60 FLAP KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 0 44 52 47 54 52 58 62 65 15 42 50 45 52 50 56 59 63 35 39 38 42 50 46 53 55 60 LATERAL BANK ...

Страница 43: ...P92 Eaglet Flight Manual Revision Date 12 14 2007 Revision Number 1 00 Doc n 27 13 100 00 43 4 5 Crosswind Maximum demonstrated crosswind velocity is 15 knots Fig 4 3 Crosswind chart ...

Страница 44: ...l throttle Slope 0 Wind zero Vr 48 KIAS VLO 49 KIAS Vx flaps 15 56 KIAS R C 200 ft min Decrease distances by 10 for each 10 Knots of headwind Increase distances by 20 for each 10 Knots of tailwind For dry and paved runway operation decrease ground run by 6 Example Given Find O A T 15 C TOD 253m 830 ft Pressure altitude 2900 ft Weight 450 Kg 990 TOR 117m 383 ft Fig 5 4 Takeoff performance ...

Страница 45: ...f tailwind For dry and paved runway operation increase ground run by 10 If it becomes necessary to land without flap extension flap malfunction increase approach speed by 10 Knots increase by landing distance by 40 distance pertaining to flap setting at 35 and increase Vx to 58 KIAS Vx 15 flaps speed over obstacle is 48 KIAS Hp ft 0 1000 2000 3000 4000 5000 6000 7000 GR m GR ft 115 377 118 387 122...

Страница 46: ...n Number 1 00 Doc n 27 13 100 00 46 4 8 Climb Performance CLIMB RATE IN CLEAN CONFIGURATION CONDITIONS Flap 0 Engine Full throttle VY 68 knots Fig 5 5 CLIMB Example Given Find O A T 17 C Rate of climb 654 ft min Pressure altitude 5600 ft Weight 580 Kg 1279 lb ...

Страница 47: ... Engine RPM Speed KTAS Consumption gal h Endurance hrs Range N m 55 4600 101 4 5 8 588 60 5000 105 4 5 5 1 540 70 5200 110 4 9 4 7 520 Pressure altitude HP 6000 ft OAT 3 C Propeller RPM Speed KTAS Consumption gal h Endurance hrs Range N m 55 5000 104 4 5 8 606 60 5200 108 4 5 5 1 556 1 Range and endurance are intended approximate and referred to a zero wind condition Pressure altitude HP 8000 ft O...

Страница 48: ...balked landing maneuver flaps should be retracted immediately after applying full power Fig 5 6 BALKED LANDING 4 11Effects of Rain and Insects Flight tests have demonstrated that neither rain nor insect impact build up on leading edge has caused substantial variations on aircraft s flight qualities 4 12Noise Data Noise level was determined according to JAR 36 Sub C Ed 23 May 1997 ICAO Annex 16 Cha...

Страница 49: ... and applied as necessary to correct the problem Before operating the aircraft the pilot should become thoroughly familiar with the present manual and in particular with the present section Further a continued and appropriate training program should be provided In case of emergency the pilot should act as follows Keep control of the airplane Analyze the situation Apply the pertinent procedure Info...

Страница 50: ... on the ground to land safely The landing should be planned straight ahead with only small changes in directions not exceeding 45 to the left or 45 to the right Flaps AS REQUIRED Throttle AS REQUIRED At touch down Ignition Switches OFF Master switch OFF Fuel selector valves OFF 5 1 2 2 IRREGULAR ENGINE RPM Throttle CHECK Engine gauges CHECK Fuel quantity indicators CHECK Carburetor heat ON If the ...

Страница 51: ...se of an engine restart Land as soon as possible 5 1 2 6 ENGINE OUT GLIDE Flaps RETRACT Speed 68 KIAS Electric equipments OFF In flight engine restart If conditions permit try to restart several times NOTE Glide ratio is 12 8 therefore with 1000 ft of altitude it is possible to cover 2 nautical miles in zero wind conditions 5 2 Smoke and Fire 5 2 1 Engine Fire while parked Fuel selector valves OFF...

Страница 52: ... Locate most suitable terrain for emergency landing upwind if possible Fuel selector valves OFF Ignition Switches OFF Safety belts TIGHTEN Doors UNLATCHED Landing assured Flaps AS NECESSARY Master switch OFF Touchdown Speed 42 KIAS POWER ON FORCED LANDING Descent ESTABLISH Establish 68 KIAS Flaps AS NECESSARY Select terrain area most suitable for emergency landing and flyby checking for obstacles ...

Страница 53: ...ost docile spin configuration possible affording the greatest response to recovery inputs Errant control inputs that may aggravate the spin are avoided in the process As a mental checklist it forces you to focus on the appropriate recovery actions Calling each item out loud also tends to reinforce the physical inputs 5 5 Other Emergencies 5 5 1 UNINTENTIONAL FLIGHT INTO ICING CONDITIONS Get away f...

Страница 54: ...ERATOR LIGHT ILLUMINATES Generator light may illuminate for a faulty alternator If the generator light illuminates proceed as follows LAND as soon as possible Continue flight on battery power alone the battery is capable of supplying the electrical system for about 20 minutes with normal flight electric loads including operation of flap and trim 5 7 Trim System Failure 5 7 1 LOCKED CONTROL In case...

Страница 55: ...er shaft passing through nose To reinstall Rest cowling horizontal insuring proper fitting of nose base reference pins Reinstall the four screws Secure latches by applying light pressure check for proper assembly and fasten Cam locks WARNING Butterfly Cam locks are locked when tabs are horizontal and open when tabs are vertical Verify tab is below latch upon closing 6 1 2 Lower Cowling After disas...

Страница 56: ... Friction lock CHECK Throttle IDLE Ignition Switches OFF Master switch ON Generator light ON Aux Alternator switch if installed ON Alternator light ON Flaps EXTEND Visually check that flaps are fully extended and instrument indication is correct Trim CHECK Activate control in both directions checking for travel limits and instrument indication Stall warning CHECK Navigation lights and strobe light...

Страница 57: ...k that the pitot tube mounted on the left wing is unobstructed Do not blow inside pitot tube C Left side leading edge and wing skin CHECK for damage D Left aileron CHECK for damage freedom of movement Left tank vent CHECK for obstructions E Left flap and hinges CHECK security F Left main landing gear CHECK inflation 23 PSI 1 6 bar tire condition alignment fuselage skin condition G Horizontal tail ...

Страница 58: ... unobstructed Check fuel system Open both fuel shutoff valves and inspect fuel lines for leaks Drain Gascolator using a cup to collect fuel Make sure that valve is closed and not leaking Check for water or other contaminants Engine mounts CHECK integrity Intake system Check connection and integrity of air intake system visually inspect that ram air intake is unobstructed All parts Check they are s...

Страница 59: ... doesn t rise within 10 seconds shut down engine The maximum oil pressure for cold conditions is 7 bar Engine instruments CHECK Choke OFF Engine rpm 2000 2500 rpm Fuel pressure CHECK 6 2 1 5 BEFORE TAXI Radio and Avionics ON Altimeter SET Flight Instruments SET CHECK Parking brake OFF 6 2 1 6 TAXI Brakes CHECK Flight instruments CHECK 6 2 1 7 BEFORE TAKE OFF Parking brake ON Engine instruments CHE...

Страница 60: ...00 AGL Flaps RETRACT Establish Vy clean 68 KIAS Trim ADJUST Cruise climb 75 80 KNOTS 6 2 1 9 CRUISE Reaching cruise altitude Throttle SET 5500 RPM Max Engine instruments CHECK Oil temperature 90 110 C Cylinder head temperature 90 135 C Oil pressure 2 5 bar Fuel pressure 0 15 0 40 bar CAUTION Normal position of the fuel selectors is both on Check fuel balance and fuel pressure If necessary shut off...

Страница 61: ... 2 1 13 ENGINE SHUT DOWN Keep engine running at 2500 rpm for about one minute in order to reduce latent heat This can be accomplished during taxi NOTE Do not ride the brakes to facilitate cool down If necessary stop for one minute with parking brake on to cool the engine Electrical equipment except the Strobe Light OFF Ignition switches OFF Strobe light OFF Master switch OFF One or both fuel valve...

Страница 62: ... you can safely maneuver the aircraft Aircraft may be steered by turning rudder or for steep turns by pushing lightly on tailcone to lift nose wheel 7 3 2 Parking and Tiedown When parking airplane outdoors head it into the wind and set the parking brake It is preferable to use chocks if available Tie the airplane down in severe weather and high wind conditions Tie down ropes shall be fastened to t...

Страница 63: ... glass detergents but in any case never use products such as gasoline alcohol acetone or other solvents To clean cabin interior seats upholstery and carpet it is generally recommended to use foam type detergents 7 3 7 Ground anchorage The airplane should be moored for immovability security and protection FAA Advisory Circular AC 20 35C Tiedown Sense contains additional information regarding prepar...

Страница 64: ...wing On the right hand side of the panel a placard will state the following Near baggage compartment a placard will state the following On the doors there are the following placards For other placards see Line Maintenance Manual LIGHT SPORT Passenger Warning This aircraft was manufactured in accordance with Light Sport aircraft airworthiness standards and does not conform to standard category airw...

Страница 65: ... Aircraft Inc 1350 Churchill Way Marietta GA 30062 www tecnamaircraft com Tecnam bellsouth net 770 309 4155 Italian Address COSTRUZIONI AERONAUTICHE TECNAM s r l www tecnam com Casoria industrial plant 1a Traversa via G Pascoli n 1 80026 Casoria NA ITALY Via Maiorise 81043 Capua CE ITALY 39 081 7583210 39 081 7584528 39 0823 620134 39 0823 622899 ...

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