Home

P92Echo-Technam-Flight Manual

1. Tu u t teste ret 41 CLIMB PERFORMAN CE 42 CRUISE esee ee eee ce ee 43 CONSEQUENCES FROM RAIN AND INSECT 43 October 98 5 36 P92 Echo COSTRUZIONI AERONAUTICHE P92 Echo 100 SE TECNAM FLIGHT MANUAL penrormance _ Introduction This section provides all necessary data for accurate and comprehensive planning of flight activity from takeoff to landing Data reported in graphs and or tables were determined using aircraft and engine in good condition average piloting techniques Each graph or table was determined according to ICAO Standard Atmosphere ISA m s 1 evaluations of the impact on performance was carried out by theoretical means for airspeed external temperature e altitude weight October 98 5 37 lt COSTRUZIONI AERONAUTICHE 45 Fai 100 AY TECNAM FLIGHT MANUAL PERFORMANCE Airspeed Calibration The difference between indicated airspeed and calibrated airspeed is within JAR VLA limits of 3 for all speeds above 1 3 Vs Stall Speeds CONDITIONS weight 450 kg engine idle no ground effect Note The table below is valid for both P92 Echo and P92 Echo 100 Lateral Banking October 98 Rev May 2002 5 38 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 MANUAL PERFORMANCE J Crosswind Maximu
2. COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 TECNAM FLIGHT MANUAL LIMITATIONS Introduction Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of the P92 ECHO its engine standard systems and standard equipment Airspeed Limitations For all models SPEED km h IAS REMARKS Never exceed speed Never exceed this speed in any operation Maximum Structural Never exceed this speed unless in smooth Cruising Speed air and then only with caution Maneuvering speed Do not make full or abrupt control movements above this speed as this may cause stress In excess of limit load factor VER Maximum flap extended 110 Never exceed this speed for any given flap speed setting October 98 2 16 Rev A date 15 01 99 P92 Echo 100 TECNAM FLIGHT MANUAL LIMITATIONS COSTRUZIONI AERONAUTICHE P92 Echo X 2 Airspeed Indicator Markings Airspeed indicator markings and their color code are explained in the following table For all models Significance White arc Flap Operating Range lower limit is Vso at maximum weight and upper limit is maximum speed permissible with flaps extended at 35 Green arc 110 200 Normal Operating Range lower limit is Vsi at maximum weight and flaps at 0 and upper limit is maximum structural speed Vyo Yellow arc 200 260 Operations must be conducted with caution and only in smooth a
3. For installation follow reverse procedure October 98 4 29 P92 Echo P92 Echo 100 COSTRUZIONI AERONAUTICHE SE TECNAM FLIGHT MANUAL noma rrocepuees Preflight Inspection Before each flight it is necessary to carry out a complete inspection of the aircraft as hereby detailed Cabin Inspection A B C Q 7m 0 Weight and balance check if within limits Safety belts used to lock controls free Flight controls activate flight controls to insure unhindered movement of control rods and surfaces Parking brake engage Master switch ON Check generator switch is illuminated and ammeter is operational Flaps control activate control to full extension checking end travel and instrument indication Trim control activate control to full scale checking end travel and instrument indication Master switch OFF Fuel level check level on the basis of flight plan External Inspection To carry out the external inspection it will be necessary to follow the checklist below with the station order outlined in fig 4 1 A B C D E F G Left side tank cap Check proper fastening Left fuel tank blow out plug check for obstructions Remove protection cap and check pitot is unobstructed do not blow inside vents place protection cap inside aircraft Leading edge and wing skin check integrity Left aileron check integrity and unhindered movement Left flap and hinges check integrity Check integrity of left s
4. GROUND HANDLING 55 CLEANING AND CARE 56 Ottobre 98 8 54 92 92 100 lt TECNAM FLIGHT MANUAL GROUND HANDLING AND SERVICE COSTRUZIONI AERONAUTICHE Introduction This section contains factory recommended procedures for proper ground handling and routine care and servicing It also identifies certain inspection and maintenance requirements which must be followed if the aircraft is to retain its new plane performance and dependability It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered locally Airplane Inspection Periods Inspection intervals occur at 50 100 hours and in accordance with special inspection schedules which are added to regularly scheduled inspections Correct maintenance procedures are described in the aircraft s Service Manual or in the engine s Service Manual Ground Handling Towing The aircraft is most easily and safely maneuvered by hand by pushing on wing struts near attachments or by pulling it by its propeller near the axle A tow bar can be fixed onto nose gear fork Aircraft may be steered by turning rudder or for steep turns by pushing lightly on tailcone to lift nose wheel Parking And Tie Down When parking airplane outdoors head it into the wind and set the parking brake If chocks or wedges are available it is preferable to use the latter In severe weather and high wind
5. P92 Echo P92 Echo 100 ME TECNAM FLIGHT MANUAL inreoouerion _ COSTRUZIONI AERONAUTICHE Flight Manual P92 EcHO P92 100 ROTAX 912UL 81Hp or ROTAX 912ULS 100Hp engine MANUFACTURER COSTRUZIONI AERONAUTICHE S r AIRCRAFT TYPE P92 ECHO amp P92 EcHO 100 Warning This manual is valid for the P92 Echo with either Rotax 912 81 Hp engine or Rotax 912S 100 Hp engine P92 Echo 100 For evident safety reasons and upon reading this manual for the first time it is necessary to underline perhaps also highlight with a colored marker any differences in charts and tables as applicable to personal aircraft The Flight Manual must always be kept on board the aircraft The aircraft described herein is to be operated in accordance with procedures and limitations described in this Flight Manual October 98 i 1 P92 Echo P92 Echo 100 K TECNAM FLIGHT MANUAL IwrODUCHON _ COSTRUZIONI AERONAUTICHE Record of Revisions All revisions to the current Manual except for actual weighing data must be recorded in the following table and in case of approved sections must be endorsed by the Responsible Airworthiness Authority New text or amendments to revised pages shall be clearly marked by a vertical black line on the left hand margin with revision N and date indicated on left side of page Record of Revisions October 98 i 2 COSTRUZIONI AERONAUTICH
6. 100 TECNAM FLIGHT MANUAL GENERAL lt Na 2 Descriptive Data P92 Echo 8 P92 Echo 100 Wing Wing span 9 6m Wing chord 1 4 Wing surface 13 2 m Wing loading 34 1kg m Aspect ratio 6 2 Taper ratio 1 0 Dihedral 1 5 Fuselage Overall length 6 3m Overall width 1 1 m Overall height 2 5m Empennage Stabilator span 2 9 m Vertical tail span 1 2 m Landing Gear Wheel track 1 8 m Wheel base 1 6 m Main gear tire Air Trac 5 00 5 Wheel hub and brake Marc Ingegno Nose gear tire Sava 4 00 6 Control Surfaces Travel Limits Ailerons Up 20 down 15 2 Stabilator Up 18 down 3 1 Trim Tab 29129 ET Rudder RS 25 LS 25 1 Flaps 09 359 1 October 98 1 7 lt Na 2 Manufacturer Model Engine type Maximum power Manufacturer Model Number of blades Diameter Type October 98 COSTRUZIONI AERONAUTICHE 92 92 100 FLIGHT MANUAL GENERAL Engine P92 Echo P92 Echo 100 Bombardier Rotax GmbH Bombardier Rotax GmbH 912 UL Four cylinder horizontally opposed twins with overall displacement of 1211 2 c c mixed cooling water cooled heads and alr cooled cylinders twin carburetors integrated reduction gear 2 273 1 with torque damper Compression ratio 9 0 1 81Hp 59 6 kW at 5800 rpm max 5 min Propeller P92 Echo Giancarlo amp Felice S n c GT ECHO 2 166 145 2 1660 mm
7. for the start of the takeoff run is the maximum weight approved for the landing touch down is the weight of chocks blocks stands etc used when weighing an airplane and is included in the scale readings Tare is deducted from the scale reading to obtain the actual net airplane weight COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 _ TECNAM FLr6HT MANUAL _ Unit Conversion Factors Multiplying Temperature Fahrenheit Celsius Weights Kilograms Pounds Speed Meters per second Feet per minute Knots Kilometers hour Pressure Atmosphere Pounds sq in Length Kilometers Nautical miles Meters Feet Centimeters Inches Volume Liters Gallons US Surface Square meters Square feet October 98 Yields Celsius Fahrenheit Pounds Kilograms Feet per minute Meters per second Kilometers hour Knots Pounds sq in Atmosphere Nautical miles Kilometers Feet Meters Inches Centimeters Gallons US Liters Square feet Square meters P92 Echo lt COSTRUZIONI AERONAUTICHE P92 Echo 100 N TECNAM FLIGHT MANUAL MITATIONS Section 2 Limitations Table Of Contents INTRODUCTION 16 AIRSPEED LIMITATIONS 16 AIRSPEED INDICATOR MARKINGS 17 POWERPLANT LIMITATIONS 18 PROPELLER 19 POWERPLANT INSTRUMENT MARKINGS 20 OTHER INSTRUMENT MARKINGS 21 WEIGHT LIMITS 21 CENTER OF GRAVITY LIMITS 21 APPROVED MANEUVERS 21 FUEL 22 October 98 2 15 N J
8. pertaining to normal flight Stalls except whip stalls e Lazy eights Chandelles Turns in which the angle of bank is not more than 60 Acrobatic maneuvers including spins are not approved October 98 2 21 lt COSTRUZIONI AERONAUTICHE P92 Echo X 2 92 100 FLIGHT MANUAL LIMITATIONS Fuel Two tanks 35 liters each Total fuel capacity 70 liters Optional Two tanks 45 1 each total 90 1 Approved Fuel High octane gasoline DIN 51600 O NORM 1103 Unleaded gasoline DIN 51603 O NORM 1101 Avgas 100LL October 98 2 22 COSTRUZIONI AERONAUTICHE P92 Echo 92 100 lt TECNAM FLIGHT MANUAL EMERGENCY PROCEDURES Section 3 Emergency Procedures Table of Contents introduCTION 24 ENGINE Failure 24 FORCED LANDING 25 SMOKE AND FIRE 25 RECOVERY FROM UNINTENTIONAL SPIN 26 deployment of emergency parachute OPTIONAL EQUIPMENT 27 October 98 3 23 lt COSTRUZIONI AERONAUTICHE Bee pe 1 00 TECNAM FLIGHT MANUAL EMERGENCY PROCEDURES Introduction Section 3 includes checklists and detailed procedures to be used in the event of emergencies Emergencies caused by a malfunction of the aircraft or engine are extremely rare if appropriate maintenance and pre flight inspections are carried out In case of emergency suggestions presented in this section should be considered and applied as necessary to correct the problem Befor
9. 77 Ground roll P92 Echo 100 DISTANCE P92 Echo DISTANCE P92 Echo 100 250 Ground roll Distance m a 2 50 400 410 420 430 440 450 460 470 480 490 500 WEIGHT Kg Fig 5 2 TAKEOFF October 98 5 40 P92 Echo COSTRUZIONI AERONAUTICHE P92 Echo 100 SE TECNAM FLIGHT MANUAL penrormance _ Landing Ground Roll Distance And Landing Distance P92 Echo amp P92 Echo 100 Conditions Flaps 35 Runway dry compact grass Engine throttle idle Slope 0 Wind zero Distance over a 15 m obstacle The graph below is valid for both P92 Echo and P92 Echo 100 300 250 Ground roll e DISTANCE Ground roll Distance m a 50 400 410 420 430 440 450 460 470 480 490 500 WEIGHT Kg Fig 5 3 LANDING October 98 5 41 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 TECNAM FLIGHT MANUAL PERFORMANCE lt Climb Performance Climb Rate In Clean Configuration Conditions ISA Flaps 0 Weight 450 kg Engine full throttle 92 Echo Echo 100 R C m sec 500 1000 1500 2000 2500 3000 Altitude m Fig 5 4 CLIMB RATE P92 Echo Vy 120 km h P92 Echo 100 Vy 120 km h NOTE For each 10 kg weight increase R C decreases by 0 15 m sec 30 fi mi
10. AM MANUAL ws _ Flaps are extended via an electric servo actuator controlled by a switch on the dashboard Flaps act in continuous mode an LED indicator shows surface position Two lighted LEDs indicate takeoff position 15 The electric circuit is protected by a breaker positioned on the right side of the dashboard Longitudinal trim is performed by a small tab positioned on the stabilator and controlled via an electric servoactuator by pushing an Up Down push button located on the control stick or on the dashboard Instrument Panel The instrument panel is of conventional type allowing space for a broad range of equipment Instruments marked with an asterisk are optional OPTIONAL SSS RPM INDICATOR CYL HEADS TEMP FLAPS INDICATOR TRIM INDICATOR GENARATOR WARNING LIGHT AIRSPEED S ads ge OIL TERM Y OIL PRESSURE CLOCK AMMETER VOLTMETER FUSE CABIN HEAT C x RADIO HOUSING IGNITION FLAP CONTROL euo THROTTLE NAV EIGHT LANDING LIGHT BANK INDICATOR PARACHUTE FIRING HANDLE STROBE LIGHT CARB HEAT Fig 7 1 INSTRUMENT PANEL October 98 7 50 P92 Echo COSTRUZIONI AERONAUTICHE P92 Echo 100 Throttle Friction Lock It is possible to adjust the engine s throttle friction by tightening appropriately the friction lock located on the dashboard near center throttle control Seats and Safety H
11. E XX TECNAM FLIGHT MANUAL Table of Contents General Limitations Emergency procedures Normal procedures Performance Weight and balance Systems description Ground handling and servicing October 98 P92 Echo P92 Echo 100 INTRODUCTION Section 1 Section 2 Section 3 Section 4 Section 5 Section 6 Section 7 Section 8 MITAD COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 TECNAM FLIGHT MANUAL GENERAL Section 1 General Table of Contents INTRODUCTION aa au AH 5 WARNINGS CAUTIONS 5 THREE VIEW DRANWMTNG 5 et ero eee ee nee oe bes RR 6 DESGRIPTIVE DATA terere teste lotte es he 7 CONTROL SURFACES TRAVEL 5 0 7 ENGINE AA AA p E EODD EOD 8 PROPELLEEBR eoe 8 WA NA tero e KIL MASELA 9 OT aasan ma ees 9 COOLING yuyuta E 9 MECH ES EE 10 SPECIEICEOADINGIS 2 4 e 10 ABBREVIATIONS AND nenne 11 UNIECONVERSION EACTORS iicet AA vea ett ae des 14 October 98 1 4 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 TECNAM FLIGHT MANUAL ENERALI lt Na 2 Introduction The P92 ECHO is a twin seat single engine aircraft with a strut braced rectangular high wing fixed main landing gear an
12. Fixed pitch wood 9125 Four cylinder horizontally opposed twins with overall displacement of 1352 c c mixed cooling water cooled heads and alr cooled cylinders twin carburetors integrated reduction gear 2 4286 1 with torque damper Compression ratio 10 3 1 100 Hp 73 5 kW at 5800 rpm max 5 min P92 Echo 100 F lli Tonini Giancarlo amp Felice S n c GT ECHO 2 172 164 2 1720 mm Fixed pitch wood 1 8 gt sae ey lt COSTRUZIONI AERONAUTICHE 92 92 100 FLIGHT MANUAL GENERAL Fuel P92 Echo E P92 Echo 100 Fuel grade Fuel tanks Capacity of each wing tank Total capacity High octane gasoline DIN 51600 O NORM 1103 red e Unleaded gasoline DIN 51603 1101 e AVGAS 100LL 2 wing tanks integrated within the wing s leading edge with drainage reservoir located in engine cowling 35 liters 70 liters Oil P92 Echo amp P92 Echo 100 Oil system Oil Oil Capacity Forced with external oil reservoir Automotive grade type oil type API SF or SG preferably synthetic or semi synthetic 2 5 liters Cooling P92 Echo amp P92 Echo 100 Cooling system Coolant Capacity October 98 Mixed air and liquid pressurized closed circuit system Antifreeze and water liquid mixture 3 liters 1 9 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 S TECNAM MANUA
13. L senema Weights P92 Echo amp P92 Echo 100 Maximum takeoff 450 kg Standard empty weight 280 kg Specific Loadings P92 Echo P92 Echo 100 Wing Loading 34 1 kg m 34 1 kg m Power Loading 5 5 kg hp 4 5 kg hp October 98 1 10 lt Na 2 92 COSTRUZIONI AERONAUTICHE P92 Echo 100 TECNAM FLIGHT MANUAL Abbreviations and Terminology Airspeed Terminology and Symbols CAS IAS TAS Vobs October 98 Calibrated Airspeed is indicated airspeed corrected for position and instrument error Indicated Airspeed is the speed shown on the on board airspeed indicator True Airspeed is calibrated airspeed corrected for altitude and temperature Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution Never Exceed Speed is the speed limit that may not be exceeded at any time Stalling Speed Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration at the most forward center of gravity Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance Best Rate of Climb Speed is the speed which results in the greatest gain in altitude in a given time Ro
14. TECNAM FLIGHT MANUAL SYSTEMS Engine gt P92 Echo ROTAX 912UL 4 stroke horizontally opposed 4 cylinder mixed air and water cooled twin electronic ignition forced lubrication Maximum rating 81Hp 59 6 kW at 5800 RPM Reduction gearbox 2 273 1 Prop GT ECHO 2 166 145 gt P92 100 ROTAX 9125 4 stroke horizontally opposed 4 cylinder mixed air and water cooled twin electronic ignition forced lubrication Maximum rating 100 Hp 73 5 kW a 5800 g min Reduction gearbox 2 4286 1 Prop GT ECHO 2 172 164 For further information refer to Engine Operating Manual Fuel System The system consists of two composite material fuel tanks that are integral part of the leading edge featuring a viewport to visually monitor fuel level of each tank Capacity is 35 liters each Each tank is equipped with cabin installed shut off valve and of a main filter located on the firewall and equipped with a drainage valve Fuel level is detected via a calibrated scale located on fuel tank walls visible from cabin The fuel system also features a mechanical pump operated by the engine and an emergency non return valve that allows gravity feed in case of main pump failure Electrical System The aircraft s electrical system consists of a 12 Volt DC circuit controlled by a Master switch located on dashboard Electricity is provided by an alternator or by a buffer battery placed in tailcone Generator light is located on the right sid
15. TION 29 RIGGING AND DERIGGING ENGINE COWLING 29 PREFLIGHT INSPECTION 30 CHECKLISTS 33 October 98 4 28 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 XX TECNAM FLIGHT MANUAL noma moeeoues Introduction Section 4 contains checklists and amplified procedures for the conduct of normal operation Rigging and Derigging Engine Cowling Upper Cowling L Parking brake ON Fuel shutoff valves OFF III IV V VI VII Master switch OFF Magnetos OFF Unlatch all four butterfly Cam locks mounted on the cowling by rotating them 90 counterclockwise while slightly pushing inwards Remove engine cowling paying attention to propeller shaft passing through nose To assemble rest cowling horizontal insuring proper fitting of nose base reference pins 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 Lower Cowling 1 II III IV After disassembling upper cowling bring propeller to horizontal position Using a standard screwdriver press and rotate 90 the two Cam locks positioned on lower cowling by the firewall Disconnect landing light wire Pull out the first hinge pin positioned on the side of the firewall then while holding cowling pull out second hinge pin remove cowling with downward motion
16. age is made up of a truss structure with special steel tubing and beginning at the cabin s rear section by an aluminum alloy semi monococgue 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 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 tubular spar connected to ribs and Jeading edge the entire structure is covered with thermoretractible synthetic material Flight Controls Aircraft flight controls consist of aileron rudder and stabilator control surfaces 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 October 98 7 49 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 S TECN
17. arness Aircraft features three point fitting safety belts with waist and diagonal straps adjustable via a sliding metal buckle Seats on the P92 can be of two types e Standard seats are fiberglass with easily removable cushions Seats may be adjusted on ground by operating on the latch mechanism located below seating cushion e Optional seats type J are built with light alloy tube structure and synthetic material cushioning A lever located on the right lower side of each seat allows adjustment of seat position according to pilot size Doors Doors available on the P92 can be of two types e Standard doors feature a light alloy tubular frame supporting a transparent or tinted panel An internal safety latch mechanism is positioned in proximity of doors upper edge and must be used before flight to secure door Mechanism rotates to engage door frame to cabin tubular framework e Optional doors can be equipped with door handles on both sides of doors and left side external door handle equipped with a door lock An internal safety latch mechanism is positioned in proximity of door s upper edge and must be used before flight to secure door Mechanism rotates to engage door frame to cabin tubular framework Baggage Compartment The baggage compartment is located behind the pilots seats Baggage shall be uniformly distributed on utility shelf October 98 7 51 COSTRUZIONI AERONAUTICHE P92 Echo 92 100
18. conditions it is wise to tie the airplane down Tie down ropes shall be fastened to the wing strut attachments and anchoring shall be provided by ramp tie downs Nose gear fork can be used for front tie down location Flight controls shall be secured to avoid possible weathervaning to end travel damage of moving surfaces For this purpose seatbelts may be used to latch control stick to prevent its movement Ottobre 98 8 55 92 92 100 lt TECNAM FLIGHT MANUAL GROUND HANDLING AND SERVICE COSTRUZIONI AERONAUTICHE Jacking Given the light empty weight lifting one of the main wheels can easily be accomplished even without the use of hydraulic jacks It is in fact sufficient that while one person lifts one half wing by acting on the spar immediately before the wingtip another person places a suitable stand below the steel spring attachment Leveling Aircraft leveling may become necessary to check wing incidence dihedral or the exact location of CG Leveling is obtained when the lower cabin edge and the main gear support beam are horizontal Road Transport It is recommended to secure tightly all aircraft components onto the cart to avoid damage during transport Minimum cart size are 7x2 5 meters It is suggested to place wings under the aircraft s bottom secured by specific clamps Secondary components such as stabilators and struts shall be protected from accidental hits using plastic or othe
19. d steerable nose wheel This Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this aircraft This Flight Manual contains 8 sections Section 1 provides basic data and information of general interest in addition to definitions and explanations of symbols abbreviations and terminology commonly used Warnings Cautions Notes The following definitions apply to warnings cautions and notes used in the Flight Manual means that the non observation of the corresponding procedure leads to an immediate or important WARNING j degradation of the flight safety means that the non observation of the corresponding p procedure leads to a minor or to a more or less long CAUTION term degradation of the flight safety draws the attention to any special item not directly NOTE related to safety but which is important or unusual October 98 1 5 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 SE TECNAM FLIGHT MANUAL Semi Three View Drawing AN SN je 4 Dimensions shown refer to aircraft weight of 450 kg and normal operating tire pressure Propeller clearance 360mm Propeller clearance with deflated front tire and compressed shock absorber 142mm e Minimum ground steering radius 5 5m October 98 1 6 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo
20. e of the instrument panel October 98 7 52 lt P92 Echo P92 Echo 100 lt TECNAM FLIGHT MANUAL SYSTEMS COSTRUZIONI AERONAUTICHE Oil and Cylinder Head Temp Oil Pressure These instruments are connected in series with their respective sensors Temperature instruments are protected by the same breaker oil pressure indicator and a second breaker protects other instruments Avionics The central part of the dashboard holds room for avionics eguipment System s manufacturer furnishes features for each system Airspeed Indicator System The aircraft s airspeed indicator system is shown below and consists of two static vents located on both sides of the aircraft forward of cabin and by a pitot tube located on left wing strut FIG 7 2 AIRSPEED INDICATOR SYSTEM Brakes The aircraft s braking system is a single system acting on both wheels of main landing gear through disk brakes the same circuit acts as parking brake via an intercept valve To activate brakes it is sufficient to verify that brake shut off valve positioned on tunnel between pilots is OFF then activate brake lever as necessary To activate parking brake pull brake lever and set brake shut valve to ON October 98 7 53 COSTRUZIONI AERONAUTICHE P92 Echo 92 100 lt TECNAM FLIGHT MANUAL GROUND HANDLING AND SERVICE Section 8 Ground Handling And Service Table of Contents INTRODUCTION 55 AIRPLANE INSPECTION PERIODS 55
21. e 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 should be provided Engine Failure Depending on the case that may apply the emergency procedure should follow the guidelines listed below Engine failure during takeoff run Throttle idle fully out Brakes apply as needed Magnetos OFF Flaps extend Master switch OFF Fuel shutoff valves OFF Engine Failure Immediately After Takeoff Locate landing area Throttle idle fully out Fuel shutoff valves OFF Magnetos OFF Flaps as needed Master switch OFF Land with wings level SR mS B S dL October 98 3 24 P92 Echo FLIGHT MANUAL Emergency PROCEDURES COSTRUZIONI AERONAUTICHE P92 Echo 100 Forced Landing Emergency Landing Without Engine Power I Setglide speed to optimal value of 110 Km h 2 Select terrain area most suitable for emergency landing possibly upwind 3 Fuel shutoff valves OFF 4 Magnetos OFF 5 Tighten safety belts release door safety lock and unlatch doors 6 Flaps as needed 7 When ready to land Master switch OFF Power On Forced Landing 1 Adjust descent slope 2 Extend flaps as needed 3 Select terrain area most suitable for emergency landing and flyby checking for obstacles and wind direction 4 Tighten safety belts release door safety lock and unlatch d
22. g is the distance measured during landing from actual touchdown to stop point is the distance measured during landing from 15m obstacle clearing to actual stop is specific range that is the distance in nautical miles which can be expected at a specific power setting and or flight configuration per kilo of fuel consumed COSTRUZIONI AERONAUTICHE TECNAM P92 Echo P92 Echo 100 FLIGHT MANUAL GENERAL Weight And Balance Terminology Datum Arm Moment C G Standard Empty Weight Basic Empty Weight Useful Load Maximum Weight Maximum Takeoff Weight Maximum Landing Weight Tare October 98 is an imaginary vertical plane from which all horizontal distances are measured for balance purposes is the horizontal distance from the reference datum to the center of gravity C G of an item is the product of the weight of an item multiplied by its arm Center of Gravity is the point at which the airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane is the weight of a standard airplane including unusable fuel full operating fuels and full engine oil is the standard empty weight plus the weight of optional equipment is the difference between takeoff weight and the basic empty weight is the maximum weight of the aircraft is the maximum weight approved
23. h fuel taps inspect fuel circuit for losses from tubing check integrity of fireproof protection braids drain circuit using a container to collect fuel activating the specific drainage tap located on the firewall shut fuel taps Check for absence of water or other contaminants WARNING Drainage operation must be carried out with aircraft parked on level surface V VI VII Check integrity of silent blocks Check firmness and integrity of air intake system check externally that ram air intake is unobstructed Check that all parts are secure or safetied U Close engine cowling V Check left side static port is unobstructed October 98 4 31 COSTRUZIONI AERONAUTICHE P92 Echo Z P92 Echo 100 lt TECNAM FLIGHT MANUAL NORMAL PROCEDURES Z Remove tow bar and chocks Avoid blowing inside left strut mounted pitot and inside airspeed indicator system s static vents as this may damage instruments FIG 4 1 October 98 4 32 92 92 100 TECNAM FLIGHT MANUAL NORMAL PROCEDURES COSTRUZIONI AERONAUTICHE Checklists Before Starting Engine after preflight inspection I Flight planning fuel consumption refueling II Aircraft loading and related inspections see section 6 III Seat and safety belts adjustment IV Doors secured V Parking brake ON Starting Engine L Master switch ON Both fuel taps ON HI Engine thro
24. ide main landing gear tire inflation 1 4 bar condition and alignment check fuselage skin condition October 98 4 30 gt tae ey lt COSTRUZIONI AERONAUTICHE TECNAM MANUAL NORMAL PROCEDURES P92 Echo P92 Echo 100 H Horizontal tail and tab check integrity and unhindered movement I L Vertical tail and rudder check integrity and unhindered movement Check integrity of right side main landing gear tire pressure 1 4 bar condition and alignment check fuselage skin condition M Right flap and hinges check integrity N Q R Right aileron check integrity and unhindered movement Leading edge and wing skin check integrity Check right side tank cap is fastened and blow out plug is unobstructed Check right side static vent is unobstructed do not blow inside vents read note Check integrity of nose landing gear strut tire inflation 1 0 bar and condition check condition of rubber shock absorbers Propeller and spinner condition check for nicks and fastening Open engine cowling and perform the following checklist I II III IV Check no foreign objects are present Check the cooling circuit for losses from tubing check coolant reservoir level insure radiator honeycomb cooling fins are unobstructed Check lubrication circuit for losses from tubing check oil reservoir level insure radiator honeycomb cooling fins are unobstructed Open bot
25. ir Red line 260 Maximum speed for all operations October 98 2 17 Rev May 2002 P92 Echo P92 Echo 100 TECNAM FLIGHT MANUAL LIMITATIONS sey lt COSTRUZIONI AERONAUTICHE amp J Powerplant Limitations The following table lists operating limitations for aircraft installed engine Engine Manufacturer Bombardier Rotax Gmbh Engine Model 912 UL 912 m mo som s s sso Temperatures Maximum Power Coolant monitored at cylinder heads Maximum Oil Minimum Oil Oil Pressure 912UL 912 Caution Admissible pressure for cold start is 7 bar maximum for short periods October 98 2 18 P92 Echo lt COSTRUZIONI AERONAUTICHE P92 Echo 100 UNS TECNAM FLIGHT MANUAL LIMITATIONS Viscosity Use viscosity grade oil as specified in the following table MONOGRADE MULTIGRADE OIL OIL TROPICAL CLIMATE CONTINENTAL CLIMATE ARCTIC CLIMATE CAUTION Use of Aviation Grade Oil with or without additives is not permitted Coolant Mixture 8096 concentrated antifreeze e g Fiat Paraflu with anticorrosion additive and 2096 demineralized water Propeller Tonini Giancarlo amp Felice Tonini Giancarlo amp Felice MODEL GT ECHO 2 166 145 GT ECHO 2 172 164 PROP TYPE Wood twin blade fixed pitch Wood twin blade fixed pitch 1660 mm 1720 mm Octobe
26. m demonstrated crosswind velocity is 15 Kts Example Given Find Wind direction 30 Headwind 17 5 Kts Crosswind 10 Kts Wind velocity 20 Kts 0 10 20 50 LL 7 30 amp pis er lt 40 4 gt 40 ia 56 na e lt gt er 2 30 5 ZONA RACCOMANDATA ZONA NON RACCOMANDATA 62 FT 2 60 F lt lt lt ES Xe 76 a 17 5 T N we fe Ll LI LU 0 gt 104 80 o ae 2 f Hr II Q ES 4 dA ud 0 90 n Wise L TT L L M i 10 Li 100 BA WA _ SI AAR Meet 20 SP 3189 150 140 130 120 110 7 0 10 20 30 40 50 COMPONENTE A TRAVERSO Kts Fig 5 1 CROSSWIND CHART October 98 5 39 P92 Echo lt COSTRUZIONI AERONAUTICHE P92 Echo 100 AY TECNAM FLIGHT MANUAL PERFORMANCE Takeoff Performance Takeoff Distance Conditions ISA Flaps 15 Engine full throttle Slope 0 Wind zero Runway dry compact grass 300 Ground roll P92 Echo
27. m takeoff weight 450 kg Wy We Woe October 98 6 46 COSTRUZIONI AERONAUTICHE P92 Echo lt P92 Echo 100 V TECNAM FLIGHT MANUAL WEIGHT amp BALANCE C G Travel Maximum admissible C G travel exceeds actual operational limits Moreover occupants and fuel impact only marginally on CG travel When on flat terrain exceeding CG travel aft limit will cause aircraft tail to lower October 98 6 47 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 S TECNAM MANUAL ss _ Section 7 Airplane and System Descriptions Table of Contents INTRODUCTION 49 AIRFRAME 2 FLIGHT CONTROLS 49 INSTRUMENT PANEL 50 SEATS AND SAFETY HARNESS 51 DOORS 51 BAGGAGE COMPARTMENT 51 ENGINE 52 FUEL SYSTEM 52 ELECTRICAL SYSTEM 52 AIRSPEED INDICATOR SYSTEM 53 BRAKES 53 October 98 7 48 lt COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 AY TECNAM FLIGHT MANUAL SYSTEMS Introduction This section provides description and operation of the aircraft and its systems Airframe Wing The wing is made up of a central light alloy torque box a composite leading edge is attached to the front spar and geometrically similar flap and aileron are hinged to rear Flaps and ailerons are both made up of an aluminum spar connected to formed sheet metal leading edge and ribs and are covered by a thermoretractible synthetic material Fuselage The front part of the fusel
28. n For each 10 kg weight decrease R C increases by 0 15 m sec 30 fi min October 98 5 42 P92 Echo P92 Echo 100 TECNAM FLIGHT MANUAL PERFORMANCE COSTRUZIONI AERONAUTICHE lt Cruise Conditions ISA A Altitude 0 Wind 0 P92 Echo P92 Echo 100 Consequences From Rain And Insect Flight tests have demonstrated that neither rain nor insect impact build up on leading edge has caused substantial variations on aircraft s flight qualities October 98 5 43 COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 XX TECNAM FLIGHT MANUAL wegura BALANCE Section 6 Weight amp Balance Table of Contents INTRODUCTION 45 aircraft weighing procedures 45 weighing report 46 C G TRAVEL 47 October 98 6 44 COSTRUZIONI AERONAUTICHE P92 Echo p P92 Echo 100 K TECNAM FLIGHT MANUAL wecnr s saiance WEIGHT amp BALANCE Introduction This section describes the procedure for establishing the basic empty weight and moment of the aircraft Loading procedure information is also provided Aircraft Weighing Procedures Preparation Carry out weighing procedure inside closed hangar Remove from cabin all objects left unintentionally Align nose wheel Drain fuel using draining reservoir Oil hydraulic fluid and coolant to operating levels Position seats to most forward position Flaps retracted 0 Control surfaces in neutral position Place scales min ca
29. ntentional spin entry follow the emergency procedure described below Adjust throttle to minimum full outward position Activate rudder bar by pushing foot opposite spin direction Push control stick full forward and keep in position until spin is halted Center rudder bar Gradually recover flight attitude easing back on the control stick avoiding to exceed Vyng and maximum load factor Readjust throttle to restore engine power BR ES d gt October 98 3 26 lt COSTRUZIONI AERONAUTICHE Bee ae TECNAM FLIGHT MANUAL Emergency PROCEDURES Deployment of Emergency Parachute optional equipment Keeping in mind that full deployment of parachute is achieved after two seconds the following procedure is recommended Try leveling aircraft as much as possible Minimum altitude for successful deployment is about 33m 100 ft Pull firing clip firmly and to end travel Shut off fuel valves magnetos and master switch Tighten safety belt and helmet chinstrap Release door safety lock and unlatch doors Assume tucked position before touch down gt gt S This altitude is only representative successful deployment depends on aircraft attitude a dtsysed s98ater deployment altitude yields better chances for successful deploymeig 27 COSTRUZIONI AERONAUTICHE P92 Echo P92 100 lt TECNAM FLIGHT MANUAL NORMAL PROCEDURES Section 4 Normal Procedures Table of Contents INTRODUC
30. oors 5 Before touchdown fuel shutoff valves OFF 6 Flaps extended Z After touchdown Magnetos OFF Master switch OFF Smoke And Fire Engine Fire While Parked Or During Takeoff 1 Fuel shutoff valves OFF 2 Abort takeoff if possible 3 If engine is running let it use up remaining fuel in carburetors 4 Magnetos and Master switch OFF 5 Warn bystanders to clear the area as fast as possible 6 Without removing the engine cowling use a CO or a powder fire extinguisher to put out flames directing spray towards cowling s air intakes October 98 3 25 COSTRUZIONI AERONAUTICHE P92 Echo ec P92 Echo 100 TECNAM FLIGHT MANUAL EMERGENCY PROCEDURES Note DO NOT USE WATER to put out fire and do not open engine cowling until absolutely certain fire is extinguished In case an appropriate fire extinguisher is not handy still keeping engine cowling closed it is possible to use a woolen blanket sand or dirt to try smothering the fire Engine Compartment Fire In Flight Fuel shutoff valves OFF Throttle fully inward Magnetos OFF Do not try airstarting engine Extend flaps as needed Carry out forced landing emergency procedure Master switch OFF NS B dL Cabin Fire During Flight Master switch OFF Door vents open 3 Extinguish fire with on board fire extinguisher Gif available directing spray towards flame base 4 Land as soon as possible N Recovery From Unintentional Spin In case of uni
31. pacity 150 kg under each wheel moe Leveling a Level the aircraft using cabin floor as datum b Center bubble on level by deflating nose tire Weighing a Record weight shown on each scale b Repeat weighing procedure three times c Calculate empty weight Determination of C G location a Drop a plumb bob tangent to the leading edge in non tapered area of one half wing approximately one meter from wing root and trace reference mark on the floor Repeat operation for other half wing Stretch a taught line between the two marks d Measure the distance between the reference line and main wheel axis e Using recorded data it is possible to determine the aircraft s C G location and moment see following table October 98 6 45 lt COSTRUZIONI AERONAUTICHE P92 Echo P92 Echo 100 ME TECNAM FLIGHT MANUAL weiout a BALANCE Weighing Report Model P92 ECHO amp P92 ECHO 100 s n Weighing n Date Datum Propeller support flange without spacer DATUM N N REFERENCE LINE PLUMB BOB www meters Plumb bob distance from LS wheel A Plumb bob distance from RS wheel Average distance A Ag 2 Bob distance from nose wheel Dru LS wheel weight RS wheel weight Deleted 1 9 Empty weight We Wi 1 Deleted 3 2 Empty weight moment M D 1 39 W Maximu
32. r 98 2 19 COSTRUZIONI AERONAUTICHE TECNAM P92 Echo P92 Echo 100 FLIGHT MANUAL LIMITATIONS Powerplant Instrument Markings Powerplant instrument markings and their color code significance are shown below P92 Echo Instrument Red Line Green Arc Yellow Arc Red Line Minimum Normal Caution Maximum Limit Limit Operating 2160 5500 5500 5800 5800 Cylinder heads and C coolant temp Fuel gage liter s P92 Echo 100 Instrument Oil Temp C Cylinder heads and C coolant temp Oil pressure 140 Red Line Red Line Green Arc Yellow Arc Minimum Normal Caution Maximum Limit Limit Operating 2160 5500 5500 5800 5800 90 100 50 90 130 100 130 50 5 5 Fuel gage October 98 2 20 COSTRUZIONI AERONAUTICHE P92 Echo X 2 92 100 FLIGHT MANUAL LIMITATIONS Note The table below is valid for both P92 models Other Instrument Markings INSTRUMENT RED LINE GREEN ARC YELLOW ARC RED LINE Minimum limit Normal operating Caution Maximum limit Weight Limits Maximum takeoff weight 450 kg Center Of Gravity Limits Forward limit 2390 MAC Aft limit 26 MAC Datum Propeller support flange w o spacer Bubble Level Cabin floor It is the pilot s responsibility to insure that airplane is properly loaded Approved Maneuvers This aircraft is intended for non aerobatic operation only Non aerobatic operation includes e Any maneuver
33. r material For correct rigging and derigging procedure refer to Service Manual Cleaning and Care To clean painted surfaces use a mild detergent such as shampoo normally used for car finish use a soft cloth for drying The plastic windshield and windows should never be dusted when dry use lukewarm soapy water and dry using chamois only It is possible to use special 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 Ottobre 98 8 56
34. ruise L Reach cruising altitude Set power and engine rpm s for cruise III Check engine parameters foitpressue ___ 15 8 18 8 IV Carburetor heat as needed see paragraph on carb heat in Section 3 Compensate unpredicted asymmetrical fuel consumption between left and right fuel tanks by shutting off appropriate fuel tap located inside cabin Landing I Turn on landing light if installed II Check runway final and establish descent and approach to final III Extend flaps gradually to maximum deflection of 35 IV Optimal touchdown speed 70 Km h V Land and taxi VI Flaps to 0 VII Parking brake ON Turn off landing light navigation lights and strobe light Engine Shut Down Keep engine running at 3000 RPM for about two minutes order to reduce latent heat II Turn off all electrical utilities III Set magnetos switch and Master switch to OFF IV Set both fuel taps to OFF V Insert hood over pitot tube on left side wing strut October 98 4 35 P92 Echo COSTRUZIONI AERONAUTICHE P92 Echo 100 lt TECNAM FLIGHT MANUAL PERFORMANCE Section 5 Performance Table of Contents INTRODUCTION SERA 37 AIRSPEED CALIBRATION eere eene nne 38 STALD SPEEDS ntt ette eoe teret eo cetero ete EQUES E SEE ERR DUNS 38 CROSSWIND esce eee ede eee ect leve tee eese hy et 39 TAKEOFF PERFORMANCE 40
35. tation speed is the speed at which the aircraft rotates about the pitch axis during takeoff Obstacle speed is the speed at which the aircraft flies over a 15m obstacle during takeoff or landing lt 2 92 92 100 COSTRUZIONI AERONAUTICHE TECNAM FLIGHT MANUAL GENERAL Meteorological Terminology OAT Ts Hp Outside Air Temperature is the free air static temperature expressed in degrees Celsius C Standard Temperature is 15 C at sea level pressure altitude and decreased by 2 C for each 1000 ft of altitude Pressure Altitude is the altitude read from an altimeter when the barometric subscale has been set to 1013 mb Engine Power Terminology RPM Revolutions Per Minute is the number of revolutions per minute of the propeller multiplied by 2 273 912UL or 2 4286 912S yields engine RPM Airplane Performance And Flight Planning Terminology Crosswind Velocity Usable fuel Unusable fuel G TOR TOD GR LD S R October 98 is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated is the fuel available for flight planning is the quantity of fuel that cannot be safely used in flight is the acceleration of gravity is the takeoff distance measured from actual start to wheel liftoff point is total takeoff distance measured from start to 15m obstacle clearin
36. ttle to idle IV Choke as needed V Magnetos switch to ON VI Prop area free VII Ignition key set to START VIII Prop RPM 2400 2600 RPM IX Choke OFF X Check engine instruments XI Check oil pressure rise maximum value cold 7 bar Before Taxing L Radio and utilities ON IL Altimeter reset HI Navigation lights as required Taxiing L Brakes check operation II Flight instruments check operation October 98 4 33 COSTRUZIONI AERONAUTICHE P92 Echo ec P92 Echo 100 TECNAM FLIGHT MANUAL NORMAL PROCEDURES Holding I Parking brake ON II Turn on navigation lights strobe light and landing light optional equipment III Check engine parameters Cylinder heads temperature 180 1850 IV Check ammeter to insure alternator is charging V Prop rpm s at 3800 RPM and test magnetos VI Visual check of fuel indicators VII Flaps at 15 takeoff VIII Stick free and zero trim IX Seat belts fastened and doors secured Takeoff And Climb I Control Tower for takeoff II Check for clear final and wind on runway III Parking brake OFF full throttle IV Carburetor heat OFF V Taxi to line up VI Rotation and takeoff VII Slight braking to stop wheel spinning Flaps retracted IX Landing light OFF X Trim adjustment XI Establish climb rate October 98 4 34 lt COSTRUZIONI AERONAUTICHE 45 E 1 00 AY TECNAM FLIGHT MANUAL NORMAL PROCEDURES C

P92Echo-Technam-Flight Manual

Contents

Download Pdf Manuals

Related Search

Related Contents