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P2008 TC

Flight Manual

5.6 Failures indicated on the annunciator panel

5.6.1 ALTERNATOR LIGHT

Alternator (ALT) light may illuminate for a faulty alternator. If the Alternator 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.

5.6.2 TCU BOOST LIGHT

If the red TCU boost lamp illuminates one of the following conditions have happened to the engine:



Maximum admissible boost pressure exceeded (red lamp will continuously illuminated);

Proceed as follows:

Reduce Throttle until RPM and manifold pressure within operating limits



Full throttle operation exceeds 5' (red lamp will blink)

Proceed as follows:

Reduce Throttle until RPM and manifold pressure at least to maximum continuous speed.

NOTE

Record the event in the aircraft logbook with the duration and exact time of exceeding limits

5.6.3 TCU CAUTION LIGHT

5.6.3.1

SUDDEN DROP OF BOOST PRESSURE AND RPM

If Amber caution lamp of TCU is blinking proceed as follows:



If LOUD NOISE or BANG is heard: a fracture of the turbo is likely



Monitor oil pressure



LAND as soon as possible

NOTE

Record the event in the aircraft logbook with the duration and exact time of exceeding limits

5.6.3.2

SUDDEN RISE OF BOOST PRESSURE AND RPM

If Amber caution lamp of TCU is blinking proceed as follows:



Immediately reduce engine speed until boost pressure and rpm are within the limits



Limited flight operations as wastegate may be fully closed and control of boost pressure is only possible via
throttle lever



LAND as soon as pratical

NOTE

Record the event in the aircraft logbook with the duration and exact time of exceeding limits

5.6.3.3

PERIODICAL RISE&DROP OF BOOST PRESSURE AND RPM

If Amber caution lamp of TCU is NOT blinking proceed as follows:



Switch OFF

the servo motor of the engine for a moment (max 5 sec). Then the operation should stabilize



If previous step does not stabilize the operations,

switch OFF

the servo motor completely and keep the engine

within the limits using throttle



Limited flight operations as boost pressure control is no more possible



LAND as soon as pratical

NOTE

Record the event in the aircraft logbook.

Содержание P2008 TC

Страница 1: ...ntroduction 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 guidelines as finalized 14 December 2007 Ed1 rev3 02 08 20...

Страница 2: ...ta 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 Log of Revisions Revision No Date released Chapters Approved By 00 12 06 2013 All TECNAM 01 25 11 2013 9 TECNAM 02 19 01 2015 8 TECNAM 03 02 08 2017 9 TECNAM ...

Страница 3: ...te 1 12 06 2013 36 71 2 37 72 3 38 73 4 39 74 19 01 2015 5 40 75 12 06 2013 6 41 76 7 42 77 02 08 2017 8 43 78 9 44 79 10 45 80 11 46 12 47 13 48 14 49 15 50 16 51 17 52 18 53 19 54 20 55 21 56 22 57 23 58 24 59 25 60 26 61 27 62 28 63 29 64 30 65 31 66 32 67 33 68 34 69 35 70 ...

Страница 4: ... 6 1 Flight Instruments 16 1 6 2 Engine instruments 16 1 6 3 Warning Lights and Indicators 16 1 6 4 Controls 16 1 6 5 Interior 17 1 6 6 Exterior 17 1 6 7 Powerplant and Accessories 17 1 7 Airframe 18 1 7 1 Wing 18 1 7 2 Fuselage 18 1 7 3 Empennage 18 1 7 4 Flight controls 18 1 7 5 Instrument Panel 19 1 7 6 Cabin Heat Defrost 19 1 7 7 Throttle Friction Lock 19 1 7 8 Seats Seatbelts and Shoulder har...

Страница 5: ...1 9 Coolant 31 2 1 10 Propellers 31 2 1 11 Fuel 31 2 1 12 Approved Fuel 32 2 1 13 Powerplant Instrument Markings 32 2 1 14 Other Instrument Markings 32 2 1 15 Weights 32 2 1 16 Center of Gravity Limits 32 2 1 17 Approved Maneuvers 33 2 1 18 Maneuvering Load Factor Limits 33 2 1 19 Flight Crew 33 2 1 20 Kinds of Operations 33 2 1 21 Day VFR 34 2 1 22 Night 34 2 1 23 IFR 34 2 1 24 Demonstrated Cross...

Страница 6: ...5 1 Engine Failures 56 5 1 1 Engine Failures on Ground 56 5 1 2 Engine Failure during Flight 56 5 2 Smoke and Fire 57 5 2 1 Engine Fire while parked 57 5 2 2 Engine Fire during Takeoff 57 5 2 3 Engine Fire in flight 58 5 2 4 Cabin Fire during Flight 58 5 3 Landing Emergency 58 5 4 Recovery from Unintentional Spin 59 5 5 Electric Power System Malfunction 59 5 6 Failures indicated on the annunciator...

Страница 7: ...Cleaning and Care 70 7 3 7 Ground anchorage 70 8 PLACARDS MARKINGS 71 8 1 1 Magnetic compass compensation table 71 8 1 2 Engine throttle friction 71 8 1 3 Cabin heat 71 8 1 4 Trim switch 72 8 1 5 Breakers 72 8 1 6 Flaps 72 8 1 7 Generator Master Starter 72 8 1 8 Choke 73 8 1 9 Generator light 73 8 1 10 Fuel selector valve 73 8 1 11 Baggage compartment 74 8 1 12 Oil tank reservoir 74 8 1 13 Cooling...

Страница 8: ...servation of the corresponding procedure leads to an immediate or important degradation of the flight safety CAUTION Means that the non observation of the corresponding procedure leads to a minor or to a more or less long term degradation of the flight safety NOTE Draws the attention to any special item not directly related to safety but which is important or unusual ...

Страница 9: ...ould 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 distance VY Best Rate of Climb Spee...

Страница 10: ...eight 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 airplane or equipment would balanc...

Страница 11: ... 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 pounds 0 1383 kilogram meters foot poun...

Страница 12: ...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 13: ...s Wing Span 9 00 m 29 5 ft Length 6 93 m 22 7 ft Tail height 2 46 m 8 1 ft Propeller ground clearance 310 40 mm 12 2 1 6 in Minimum ground steering radius 5 50 m 18 0 ft NOTE Dimensions shown refer to aircraft weight of 600 kg 1320 lbs and normal operating tire pressure ...

Страница 14: ...ea 1 06 m2 11 4 ft2 1 3 1 4 Landing Gear Wheel track 1 8 m 5 9 ft Wheel base 1 94 m 6 4 ft 1 74 m 5 7 ft steerable nose landing gear Main gear tire Air Trac 5 00 5 alternative Goodyear flight special II tire 5 00 5 6 ply can be fitted Nose Gear tire Air Trac 5 00 5 alternative Goodyear flight special II tire 5 00 5 6 ply can be fitted Wheel brakes Marc Ingegno 199 102 1 4 Powerplant 1 4 1 Engine M...

Страница 15: ...anufacturer Model Number of blades Diameter Type Spacer Sensenich 3B0R5R68C 3 1730 68 no reduction permitted Fixed ground adjustable pitch B 1805 81 TECNAM Spacer Manufacturer MT Propeller Model MTV 33 1 A 175 200 Number of blades 2 Diameter 1 75 m Type Variable pitch Spacer 1 4 3 Oil System Oil system Oil Oil Capacity Forced with external oil reservoir See Rotaxoperator s manual Max 3 0 liters 3 ...

Страница 16: ... 245 kg 540 lb 1 5 3 Specific Loadings Wing loading 59 kg m2 12 lb ft2 Power loading 6 1 kg hp 13 5 lb hp NOTE Standard weights are estimates based on standard equipment 1 6 Standard Equipment 1 6 1 Flight Instruments Airspeed Indicator Altimeter Vertical Speed Indicator Compass 1 6 2 Engine instruments Tachometer MAP indicator Oil Pressure Fuel Pressure Oil Temperature Cylinder Head Temperature H...

Страница 17: ...Windshield Defrost 12V Power Outlet Composite Instrument Panel 1 6 6 Exterior Composite structure Landing Light Strobe Light Fixed Landing Gear Nose Gear Strut Fairing Nose and Main Wheel Fairings 1 6 7 Powerplant and Accessories Rotax 914 UL Engine 114 hp Composite Covered Wood Composite Propeller with Spinner 12Volt 18 Ah Battery 18 Amp Alternator Engine Driven Fuel Pump Electric Starter Engine ...

Страница 18: ...he 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...

Страница 19: ...ide near center throttle control 1 7 8 Seats Seatbelts and Shoulder harnesses The P2008usually comes with three point safety belts with waist and diagonal straps adjustable via a sliding metal buckle Standard seats are aluminum with cushions Seats are adjustable fore and aft by using the handle located under the seat on the outboard sides Pushing the lever towards the center of the aircraft will r...

Страница 20: ...nd must be used before flight to secure door Mechanism rotates before flight to engage doorframe to cabin composite frame 1 7 10 Baggage compartment The baggage compartment is located behind the seats Baggage shall be uniformly distributed and its weight shall not exceed 20 kg 44 lbs and the c g must be computed before flight Always tie down the baggage by using the adjustable tie down net provide...

Страница 21: ...ilot The two fuel pumps are in parallel while the flow path is guaranteed via check valves Cooling system is designed for liquid cooling of the cylinders heads and ram air cooling of the cylinders The liquid system is a closed circuit with an overflow bottle and an expansion tank The coolant flow is forced by a water pump driven from the camshaft from the radiator to the cylinder heads From the to...

Страница 22: ...7 4 gal Each fuel tank is equipped with a cabin installed shutoff and selector Andair 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 two electrical pumps All fuel lines located in the engine compartment are protected with fireproof braiding to avoid possible...

Страница 23: ...ge or in the engine compartment The generator light is located on the right side of the instrument panel Fig 1 4 Electrical system schematic some fuses may not be installed on the standard equipped aircraft 1 9 1 Alternator light Alternator ALT light red illuminates for the following conditions Alternator failure Failure of regulator rectifier with consequent over voltage sensor set off NOTE The b...

Страница 24: ...E The same fuse protects all temperature instruments 1 9 5 Oil Pressure The oil pressure reads values in bars and has a green normal operating range yellow caution ranges and two red lines NOTE One bar is equal to about 14 7 pounds of pressure 1 9 6 O A T Indicator A Outside Air Temperature indicator C if provided indicates the air temperature outside the aircraft The sensor is placed on cabin top...

Страница 25: ... wing tip a red light on left wing tip and a white lamp on both wings or optionally on vertical stabilizer 1 9 9 2 Landing Light The landing light is located on the LH wing leading edge Landing light switch is located on instrument panel Light is protected by a 3 Amp breaker 1 9 9 3 Tail Strobe Light The strobe light is optionally installed on top of the vertical stabilizer Strobe light is activat...

Страница 26: ...ndicator system for the aircraft is shown below On the left wing s strut the Pitot tube 1 while on the fuselage s sides there are two static ports 2 Two flexible hoses 3 feed the airspeed indicator 4 the altimeter 5 and the VSI 6 on the instrument panel Fig 1 5 Pitot Static system ...

Страница 27: ...ads The two steel spring leaf struts are attached to the fuselage underside via the main girder Two rawhide liners are inserted between each spring leaf and the girder Two bolts and nuts secure the individual spring leaf to the edge of the girder via a light alloy clamp while a single bolt and nut secures the inboard end of the leaf spring to the girder Figure 1 6 Main landing gear ...

Страница 28: ...ot 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 Fig 1 7 Brake System C C C C FWD ...

Страница 29: ...ap extended speed 66 68 Never exceed this speed for any given flap setting VH Maximum speed 119 120 Maximum speed in level flight at max continuous power MSL VX Best Angle Climb 63 65 The speed which results in the greatest gain of altitude in a given horizontal distance VY Best Rate Climb 76 78 The speed which results in the greatest gain of altitude in a given time 2 1 2 Airspeed Indicator Marki...

Страница 30: ... 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 less than the average pressure of the E...

Страница 31: ... documents 2 1 10 Propellers Manufacturer Model Number of blades Diameter Type GT Tonini GT 2 173 VRR FW101 2 1730 mm 68 no reduction permitted Fixed pitch wood composite NO REDUCTIONS AREPERMITTED Manufacturer Sensenich Propellers Model 2A0R5R70EN 2 Blades 3B0R5R68C 3 Blades Propeller type 2 3 Blades Composite Ground Adjustable Pitch Diameter 1778 mm 70 2 Blades 1730 mm 68 3 Blades NO REDUCTIONS ...

Страница 32: ...limit Green arc Normal operating Yellow arc Caution Red line Maximum 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 0 15 Bar 2 2 5 08 0 15 0 35 Bar 5 08 0 35 Bar 2 1 14 Other Instrument Markings Instrument Red line Minimum limit Green arc Normal operating Yellow ar...

Страница 33: ...vering Speed 2 1 18 Maneuvering Load Factor Limits Maneuvering load factors are as follows Flaps 0 4 2 LND 2 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 configuration is approved only for day VFR operation with terrain visual contact Minimum equipment required is as follows Altimeter Airspeed Indicator Headin...

Страница 34: ... 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 Private Pilot certificate and a current medical to fly at night See the FARs for more information 2 1 23 IFR IFR flight is not allowed 2 1 24 Demonstrated Crosswind Safe...

Страница 35: ...ntrol surfaces in neutral position Place scales min capacity 200 kg440 pounds under each wheel Level the aircraft using baggage 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 weight 3 1 3 ...

Страница 36: ...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 100 373 1 D D Empty weight moment M D 1 567 We Kg m Maximum takeoff weight WT 600 kg Empty weight We Sign _______________ Maximum payload WT We Wu 1 Including unusable fuel NOTE The distances A and B vary from the aircraft with pivoting NLG configuration and the aircraft with steerable NLG This weighing report r...

Страница 37: ...P2008 TC Flight Manual 37 3 2 2 Distances from the datum The mean distances of the occupants baggage and fuel from the datum are Figure 3 1 ...

Страница 38: ...60 4488 310 23188 6 37 56 3267 30 2855 70 5236 320 23936 7 43 82 3811 35 3331 80 5984 330 24684 8 50 08 4355 40 3806 90 6732 340 25432 9 56 34 4900 44 4187 100 7480 350 26180 10 62 6 5444 110 8228 360 26928 11 68 86 5989 120 8976 370 27676 12 75 12 6533 130 9724 380 28424 13 81 38 7078 140 10472 390 29172 14 87 64 7622 150 11220 400 29920 15 93 9 8166 160 11968 410 30668 16 100 16 8711 170 12716 4...

Страница 39: ... Total MOMENT Total WEIGHT Distance D MOMENT WEIGHT ADD to the distance D the value 1567mm 62in C G Range Meters 1 842 2 020 Inches 72 50 79 5 Max Weight Pounds Kilograms 1320 00 600 00 Weight lbs Arm inches Moment Empty Weight 813 5 77 13 62741 99 Fuel 150 86 97 13045 50 Pilot Passenger 300 74 80 22440 00 Baggage 20 95 16 1903 20 Totals 1283 5 78 01 100130 69 Example Problem In this example the g...

Страница 40: ...iloting 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 effect of different variables such ...

Страница 41: ...ed Indicator System Calibration Graph shows calibrated airspeed VCAS as a function of indicated airspeed VIAS Fig 4 1 Calibrated vs Indicated Airspeed The following formula gives the CAS with the flaps full deflected CAS 1 0611xIAS 7 7222 ...

Страница 42: ...P2008 TC Flight Manual 42 4 3 ICAO Chart Fig 4 2 ICAO CHART ...

Страница 43: ...peeds Conditions Weight 600 kg 1320 lbs Throttle idle No ground effect NOTE Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 200ft with banking under 30 FLAPS KIAS KCAS 0 48 45 LND 44 39 ...

Страница 44: ...P2008 TC Flight Manual 44 4 5 Crosswind Maximum demonstrated crosswind velocity is 15 knots Fig 4 3 Crosswind chart ...

Страница 45: ...49 179 212 247 196 At 50 ft AGL 247 297 351 409 324 2000 Ground Roll 160 192 227 264 207 At 50 ft AGL 265 318 376 438 343 3000 Ground Roll 172 206 243 283 219 At 50 ft AGL 284 341 403 470 363 4000 Ground Roll 184 221 261 304 232 At 50 ft AGL 305 366 432 504 384 5000 Ground Roll 198 237 280 326 246 At 50 ft AGL 327 393 464 541 407 6000 Ground Roll 212 255 301 351 260 At 50 ft AGL 352 422 499 581 43...

Страница 46: ...97 156 At 50 ft AGL 197 237 280 326 259 2000 Ground Roll 128 153 181 211 165 At 50 ft AGL 211 254 300 349 274 3000 Ground Roll 137 164 194 226 175 At 50 ft AGL 227 272 321 375 290 4000 Ground Roll 147 176 208 242 185 At 50 ft AGL 243 292 345 402 307 5000 Ground Roll 158 189 223 260 196 At 50 ft AGL 261 313 370 431 325 6000 Ground Roll 169 203 240 280 208 At 50 ft AGL 280 337 398 463 344 7000 Groun...

Страница 47: ...3 122 At 50 ft AGL 154 185 218 254 202 2000 Ground Roll 100 119 141 164 129 At 50 ft AGL 165 198 234 273 214 3000 Ground Roll 107 128 151 176 136 At 50 ft AGL 177 212 251 292 226 4000 Ground Roll 115 137 162 189 144 At 50 ft AGL 190 228 269 314 239 5000 Ground Roll 123 148 174 203 153 At 50 ft AGL 204 245 289 337 253 6000 Ground Roll 132 159 187 218 162 At 50 ft AGL 219 263 310 362 268 7000 Ground...

Страница 48: ...At 50 ft AGL 349 363 377 391 371 2000 Ground Roll 145 160 175 189 166 At 50 ft AGL 354 369 384 398 375 3000 Ground Roll 151 166 181 196 171 At 50 ft AGL 360 375 390 405 380 4000 Ground Roll 156 172 188 204 177 At 50 ft AGL 365 381 397 413 386 5000 Ground Roll 162 179 195 212 182 At 50 ft AGL 371 388 404 421 391 6000 Ground Roll 169 186 203 220 188 At 50 ft AGL 378 395 412 429 397 7000 Ground Roll ...

Страница 49: ...GL 327 339 350 362 345 2000 Ground Roll 122 134 147 159 140 At 50 ft AGL 331 343 356 368 349 3000 Ground Roll 127 139 152 165 144 At 50 ft AGL 336 348 361 374 353 4000 Ground Roll 131 145 158 171 148 At 50 ft AGL 340 354 367 380 357 5000 Ground Roll 136 150 164 178 153 At 50 ft AGL 345 359 373 387 362 6000 Ground Roll 142 156 170 185 158 At 50 ft AGL 351 365 379 394 367 7000 Ground Roll 147 162 17...

Страница 50: ...L 306 316 326 336 321 2000 Ground Roll 101 111 121 131 116 At 50 ft AGL 310 320 330 340 325 3000 Ground Roll 105 115 126 136 119 At 50 ft AGL 314 324 335 345 328 4000 Ground Roll 109 120 131 142 123 At 50 ft AGL 318 329 340 351 332 5000 Ground Roll 113 124 136 147 126 At 50 ft AGL 322 333 345 356 335 6000 Ground Roll 117 129 141 153 130 At 50 ft AGL 326 338 350 362 339 7000 Ground Roll 122 134 146...

Страница 51: ... 51 4 8 Climb Performance CLIMB RATE IN CLEAN CONFIGURATION CONDITIONS Flap 0 Engine MCP VY 78 KIAS 77KCAS Fig 4 5 CLIMB Example Given Find O A T 17 C Rate of climb 1095 ft min Pressure altitude 5600 ft Weight 550 Kg 1212 lb ...

Страница 52: ...ft OAT 11 C Power setting Engine Speed RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 54 4300 93 3 2 7 5 695 64 4800 102 4 4 5 2 527 74 5000 109 5 3 4 3 466 99 5500 122 6 8 3 2 391 114 5800 129 8 5 2 5 320 Pressure altitude HP 4000ft OAT 7 C Power setting Engine Speed RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 52 4300 93 2 8 8 4 782...

Страница 53: ...P 10000ft OAT 5 C Power setting Engine Speed RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 48 4300 92 2 1 11 6 1070 58 4800 104 3 7 6 2 648 68 5000 111 4 8 4 7 524 93 5500 126 6 4 3 4 434 108 5800 134 7 7 2 8 374 Pressure altitude HP 12000ft OAT 9 C Power setting Engine Speed RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 47 4300 91 1 ...

Страница 54: ...35 Vx 15 flaps 66 KIAS 62 KCAS RC 1000 ft min NOTE During balked landing maneuver flaps should be retracted immediately after applying full power 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 ...

Страница 55: ...ore 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 Inform the Air Traffic Control if time and conditions al...

Страница 56: ...and 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 valve OFF 5 1 2 2 IRREGULAR ENGINE RPM Throttle CHECK Engine gauges CHECK Fuel quantity indicators CHECK If the engine continues to run irregularly Fue...

Страница 57: ...it 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 valve OFF Ignition Switches OFF Master switch OFF Parking brake SET Escape rapidly from the aircraft Without remove engine cowl use a CO2 or dust extinguisher to extinguish fire d...

Страница 58: ...suitable terrain for emergency landing upwind if possible Fuel selector valve OFF Ignition Switches OFF Safety belts TIGHTEN Doors UNLATCHED Landing assured Flaps AS NECESSARY Master switch OFF Touchdown Speed 45 KIAS 40KCAS POWER ON FORCED LANDING Descent ESTABLISH Establish 65 KIAS 61KCAS Flaps AS NECESSARY Select terrain area most suitable for emergency landing and flyby checking for obstacles ...

Страница 59: ...st letter in each of the four primary recovery inputs spells out the acronym PARE pronounced pair PARE is a convenient memory aid that points the way to spin recovery The PARE format mimics the most 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...

Страница 60: ...ST PRESSURE AND RPM If Amber caution lamp of TCU is blinking proceed as follows If LOUD NOISE or BANG is heard a fracture of the turbo is likely Monitor oil pressure LAND as soon as possible NOTE Record the event in the aircraft logbook with the duration and exact time of exceeding limits 5 6 3 2 SUDDEN RISE OF BOOST PRESSURE AND RPM If Amber caution lamp of TCU is blinking proceed as follows Imme...

Страница 61: ...aircraft without excessive stick force Land aircraft as soon as possible 5 8 Other Emergencies 5 8 1 UNINTENTIONAL FLIGHT INTO ICING CONDITIONS Get away from icing conditions by changing altitude or direction of flight in order to reach an area with warmer external temperature Increase rpm to avoid ice formation on propeller blades Cabin heat ON WARNING In case of ice formation on wing leading edg...

Страница 62: ... 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 disassembling upper cowling Move the propeller to a ...

Страница 63: ...N 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 CHECK NOTE Strobe lights won t work without the engine running Landing ...

Страница 64: ...g 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 40 PSI 2 7 bar tire condition alignment fuselage skin condition G Horizontal tail and tab CHECK for damage freedom of movement H Vertical tail and rudder CHECK for damage freedom of movement NO...

Страница 65: ...king 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 secure or safety wired WARNING Drain fuel with aircraft parked on level surface R Engine cowlings CLOSE S Landing Light CHECK T Tow bar and chocks REMOVE 6 2 1 3 BEFORE START Parking ...

Страница 66: ... 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 Fuel valve ON LH or RH Engine instruments CHECK Oil temperature 90 110 C Cylinder head temperature 90 135 C Oil pressure 2 5 bar Fu...

Страница 67: ...aste gate servo motor in some conditions as TAKE OFF and initial CLIMB Refer to the ROTAX Operators Manual for the description of the procedure to use the switch 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 35 bar CAUTION Normal position of the fuel se...

Страница 68: ...ne 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 Fuel valve OFF Parking brake ON Chocks INSTALL Parking b...

Страница 69: ...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 the wing attachments and anchoring shall be provided by ramp tie downs Nose gear fork can be used for front tie down location or the tail can be tied down with the optional Tiedown point Secure the flight controls to avoid possible weathervane damage to m...

Страница 70: ...oored for immovability security and protection FAA Advisory Circular AC 20 35C Tiedown Sense contains additional information regarding preparation for severeweather tiedown and related information The following proceduresshould be used for the proper mooring of the airplane 1 Head the airplane into the wind if possible 2 Retract the flaps 3 Chock the wheels 4 Lock the control stick using safety be...

Страница 71: ...r For S 210 240 W 300 330 Steer DATE RADIO ON AIRPATH 8 1 2 Engine throttle friction A throttle friction lock is located on the side of central to keep the desired throttle friction setting The following placard 23x11 upper 21x11 lower is positioned near the friction lock knob 8 1 3 Cabin heat The cabin heat if available control knob is located on central tunnel panel area just near the throttle c...

Страница 72: ...nstrument panel and each fuse is individually marked as follows Depending on the specific equipment installed on the a c the type and position of the breakers could vary from the above shown 8 1 6 Flaps The flap control switch is located on the lower portion of the instrument panel The following placards 15x10mm the upper 6x15mm the lower are just next to it 8 1 7 Generator Master Starter On the l...

Страница 73: ...ing light is located on the upper right side of the instrument panel and it is marked with the following label 8 1 10 Fuel selector valve Fuel shutoff valve is located on central section of cockpit panel It controls the fuel coming from the tanks making the pilot able to switch LEFT TANK RIGHT TANK and OFF ...

Страница 74: ...mpartment 8 1 12 Oil tank reservoir On the oil tank reservoir is present one placards 70x70 indicating the type and quantity of engine s oil stored into the reservoir see placard and its installation in par 8 1 13 8 1 13 Cooling system overflow tank Located on the overflow tank inside the engine cowling left side are located the following placards 102x10mm 60x15 Ed 1 Rev 2 19 01 2015 ...

Страница 75: ...d the following placard indicating the nose tire inflating pressure 18x6mm 8 1 16 Doors Next latch is located a placard that show the correct turn of key for open the door 30x20mm Inside the doors in the upper side is located the following placard 4x20mm 8 1 17 Identification plate The following placard is located on the pilot side of the empennage forward of the stabilator and made of stainless s...

Страница 76: ...ds Next to the airspeed indicator is the following placard 6x52mm On the pilot s panel a placard will state the following Located on the instrument panel is the following placard This aircraft was manufactured in accordance with Light Sport aircraft airworthiness standards and does not conform to standard category airworthiness requirements Maneuvering speed VA 98 KIAS NO INTENTIONAL SPINS ...

Страница 77: ... instrumentation equipping the P2008 TC and or information and limitations related to installed equipment configuration or needed to fit local national rules 9 2 Supplements list Aircraft S N Registration marks Date SUPPLEMENTS LIST Sup No Title Rev no Date APPLICABLE YES NO S1 Airspeeds increment 0 25 11 2013 S2 MTV 33 1 Variable Pitch Propeller 0 02 08 2017 ...

Страница 78: ...P2008 TC Flight Manual 78 INTENTIONALLY LEFT BLANK ...

Страница 79: ...ions to the present Manual 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 Log of Revisions Revision No Date released Chapters Approved By 00 25 11 2013 All TECNAM ...

Страница 80: ...P2008 TC Flight Manual 2 List of Effective Pages Page Date Page Date 1 25 11 2013 2 3 4 5 6 7 8 9 10 11 12 13 14 ...

Страница 81: ...UPPLEMENT No S1 AIRSPEED INCREMENT 1 Record of Revisions 1 Log of Revisions 1 List of Effective Pages 2 Table of Contents 3 Introduction 5 Section 1 General 7 Section 2 Operating Limitations 9 Section 3 Weight Balance 11 Section 4 Performance 13 ...

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Страница 83: ...ided to allow the owner for replacing the basic AFM pages containing information amended as per the Airspeeds increment in subject It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section NOTE TECNAM reminds that flights in yellow arcs should be only performed in smooth with caution ...

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Страница 85: ...P2008 TC Flight Manual 7 Section 1 General Refer to Basic AFM Section 1 Supplement S1 pages replacement instructions ...

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Страница 87: ...l 9 Section 2 Operating Limitations Apply following pages replacement procedure Supplement S1 LIMITATIONS page Basic AFM Section 2 page A29 REPLACES Page 29 A30 REPLACES Page 30 Supplement S1 pages replacement instructions ...

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Страница 89: ...ap extended speed 68 71 Never exceed this speed for any given flap setting VH Maximum speed 119 120 Maximum speed in level flight at max continuous power MSL VX Best Angle Climb 63 65 The speed which results in the greatest gain of altitude in a given horizontal distance VY Best Rate Climb 76 78 The speed which results in the greatest gain of altitude in a given time 2 1 2 Airspeed Indicator Marki...

Страница 90: ...e 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 less than the average pressure of the ...

Страница 91: ...P2008 TC Flight Manual 11 Section 3 Weight Balance Refer to Basic AFM Section 3 Supplement S1 pages replacement instructions ...

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Страница 93: ...erformance Apply following pages replacement procedure Supplement S1 Performance page Basic AFM Section 4 page A41 REPLACES Page 41 A42 REPLACES Page 42 A43 REPLACES Page 43 A44 REPLACES Page 44 Supplement S1 pages replacement instructions ...

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Страница 95: ... calibrated airspeed VCAS as a function of indicated airspeed VIAS Fig 4 1 Calibrated vs Indicated Airspeed The following formula gives the CAS with the flaps full deflected CAS 1 0611xIAS 7 7222 0 20 40 60 80 100 120 140 160 40 60 80 100 120 140 160 CAs IAS IAS CAS kts FLAP CLEAN ...

Страница 96: ...P2008 TC Flight Manual A42 4 5 ICAO Chart Fig 4 2 ICAO CHART ...

Страница 97: ...peeds Conditions Weight 600 kg 1320 lbs Throttle idle No ground effect NOTE Altitude loss during conventional stall recovery as demonstrated during test flights is approximately 200ft with banking under 30 FLAPS KIAS KCAS 0 48 45 LND 40 34 ...

Страница 98: ...P2008 TC Flight Manual A44 4 7 Crosswind Maximum demonstrated crosswind velocity is 15 knots Fig 4 3 Crosswind chart ...

Страница 99: ...Any revisions to the present Manual 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 Log of Revisions Revision No Date released Chapters Approved By 00 2 8 2017 All TECNAM ...

Страница 100: ...P2008 TC Flight Manual 2 List of Effective Pages Page Date Page Date 1 2 8 2017 2 3 4 5 6 7 8 9 10 11 12 13 14 15 ...

Страница 101: ... System 15 1 4 4 Cooling 15 1 1 8 Fuel system 22 Section 2 Operating Limitations 9 3 4 2 Lubricant 31 3 4 3 Coolant 31 3 4 4 Propellers 31 3 4 5 Fuel 31 Section 3 Weight Balance 10 Section 4 Performance 11 4 6 Takeoff Performance 45 4 7 Climb Performance 51 4 8 Cruise 52 Section 5 Emergency Procedures 12 Section 6 Normal Procedures 13 Section 7 Ground Handling Service 14 Section 8 Placards Marking...

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Страница 103: ...allow the owner for replacing the basic AFM pages containing information for the safe and efficient operability of the MTV 33 1 propeller It is the owner s responsibility to replace the mentioned pages in accordance with the instructions herein addressed section by section NOTE TECNAM reminds that flights in yellow arcs should be only performed in smooth with caution ...

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Страница 105: ... Flight Manual 7 Section 1 General Apply following pages replacement procedure Supplement S2 GENERAL pages Basic AFM Section 1 pages MT15 REPLACE 15 MT22 REPLACES 22 Supplement S2 pages replacement instructions ...

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Страница 107: ...68 1778 mm 70 2 Blades 1730 mm 68 3 Blades 1750 mm 69 Type Fixed pitch wood composite Composite Ground Adjustable Pitch Composite Variable Pitch 1 4 3 Oil System Oil system Oil Oil Capacity Forced with external oil reservoir See Rotaxoperator s manual Max 3 0 liters 3 2 qt min 2 0 liters 2 1 qt 1 4 4 Cooling Cooling system Coolant Capacity 3 0 liters 3 17 quarts Combination air and liquid cooled s...

Страница 108: ...27 4 gal Each fuel tank is equipped with a cabin installed shutoff and selector Andair 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 two electrical pumps All fuel lines located in the engine compartment are protected with fireproof braiding to avoid possibl...

Страница 109: ...Flight Manual 9 Section 2 Operating Limitations Apply following pages replacement procedure Supplement S2 LIMITATIONS pages Basic AFM Section 2 pages MT31 REPLACES 31 Supplement S2 pages replacement instructions ...

Страница 110: ...lated documents 3 4 4 Propellers Manufacturer GT Tonini Sensenich MT Propeller Model GT 2 173 VRR FW101 2A0R5R70EN 2 Blades 3B0R5R68C 3 Blades MTV 33 1 A 175 200 Number of blades 2 2 3 Blades 2 Diameter 1730 mm 68 NO REDUCTIONS ARE PERMITTED 1778 mm 70 2 Blades 1730 mm 68 3 Blades NO REDUCTIONS ARE PERMITTED 1750 mm 69 Type Fixed pitch wood composite Composite Ground Adjustable Pitch Composite Var...

Страница 111: ...P2008 TC Flight Manual 10 Section 3 Weight Balance Refer to Basic AFM Section 3 Supplement S2 pages replacement instructions ...

Страница 112: ...ction 4 Performance Apply following pages replacement procedure Supplement S1 Performance pages Basic AFM Section 4 pages A45 thru A47 REPLACE 45 thru 47 A51 thru A53 REPLACE 51 thru 53 Supplement S2 pages replacement instructions ...

Страница 113: ...39 151 161 163 157 At 50 ft AGL 244 266 280 284 274 2000 Ground Roll 148 161 169 170 166 At 50 ft AGL 261 283 297 298 291 3000 Ground Roll 159 171 178 177 175 At 50 ft AGL 278 301 314 312 309 4000 Ground Roll 168 181 187 184 185 At 50 ft AGL 296 318 328 323 326 5000 Ground Roll 179 190 195 190 195 At 50 ft AGL 315 337 344 334 344 6000 Ground Roll 190 202 205 197 205 At 50 ft AGL 336 356 361 344 36...

Страница 114: ...135 127 At 50 ft AGL 195 215 228 235 223 2000 Ground Roll 120 131 139 142 135 At 50 ft AGL 208 228 242 247 236 3000 Ground Roll 127 139 146 149 143 At 50 ft AGL 223 242 255 259 251 4000 Ground Roll 136 147 153 154 150 At 50 ft AGL 236 258 269 269 264 5000 Ground Roll 144 155 162 160 159 At 50 ft AGL 252 272 282 280 278 6000 Ground Roll 153 164 169 167 167 At 50 ft AGL 268 288 297 290 294 7000 Grou...

Страница 115: ... 100 At 50 ft AGL 152 168 178 183 173 2000 Ground Roll 94 101 108 110 106 At 50 ft AGL 163 178 189 193 184 3000 Ground Roll 99 108 114 116 111 At 50 ft AGL 174 189 199 202 195 4000 Ground Roll 106 114 120 121 117 At 50 ft AGL 184 201 210 210 205 5000 Ground Roll 112 121 125 126 124 At 50 ft AGL 197 213 220 218 217 6000 Ground Roll 119 128 132 130 130 At 50 ft AGL 210 225 231 227 229 7000 Ground Ro...

Страница 116: ...A51 4 8 Climb Performance CLIMB RATE IN CLEAN CONFIGURATION CONDITIONS Flap 0 Engine MCP VY 78 KIAS 77KCAS Fig 4 5 CLIMB Example Given Find O A T 17 C Rate of climb 1095 ft min Pressure altitude 5600 ft Weight 550 Kg 1212 lb ...

Страница 117: ...t OAT 11 C Power setting Engine Speed RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 54 4300 101 3 2 7 5 695 64 4800 112 4 4 5 2 527 74 5000 119 5 3 4 3 466 99 5500 130 6 8 3 2 391 114 5800 135 8 5 2 5 320 Pressure altitude HP 4000ft OAT 7 C Power setting Engine Speed RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 52 4300 102 2 8 8 4 78...

Страница 118: ...HP 10000ft OAT 5 C Power setting Propeller RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 48 1770 103 2 1 11 6 1195 58 1976 114 3 7 6 2 707 68 2058 122 4 8 4 7 573 93 2264 132 6 4 3 4 449 108 2388 137 7 7 2 8 384 Pressure altitude HP 12000ft OAT 9 C Power setting Propeller RPM Speed KTAS Consumption gal h Endurance hrs including 30 reserve Range N m 47 1770 104 1 9 1...

Страница 119: ...P2008 TC Flight Manual 12 Section 5 Emergency Procedures Refer to Basic AFM Section 5 Supplement S2 pages replacement instructions ...

Страница 120: ...P2008 TC Flight Manual 13 Section 6 Normal Procedures Refer to Basic AFM Section 6 Supplement S2 pages replacement instructions ...

Страница 121: ...P2008 TC Flight Manual 14 Section 7 Ground Handling Service Refer to Basic AFM Section 7 Supplement S2 pages replacement instructions ...

Страница 122: ...P2008 TC Flight Manual 15 Section 8 Placards Markings Refer to Basic AFM Section 8 Supplement S2 pages replacement instructions ...

Страница 123: ... Drive Box 8 Richmond VA 23237 1 888 359 4682 www tecnam net info tecnam net 770 309 4155 Italian Address COSTRUZIONI AERONAUTICHE TECNAM s r l www tecnam com Via Maiorise 81043 Capua CE ITALY 39 0823 620134 39 0823 622899 useful links Rotax Technical Publications Tecnam Official Website Tecnam Customer Support Contacts ...

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