P2008 TC Flight Manual 1 FLIGHT MANUAL US-LSA P2008 TC Manufacturer COSTRUZIONI AERONAUTICHE TECNAM S.r.l. Serial number: ________________ Build 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 guidelines as finalized 14 December 2007. Ed1 rev3- 02/08/2017
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P2008 TC Flight Manual
1
FLIGHT MANUAL
US-LSA
P2008 TC Manufacturer
COSTRUZIONI AERONAUTICHE TECNAM S.r.l.
Serial number: ________________
Build 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 guidelines as finalized 14 December 2007.
Ed1 rev3- 02/08/2017
P2008 TC Flight Manual
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Record of Revisions
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;
Unit Conversion Chart .................................................................................................................................................... 11
SECTION 1 GENERAL ........................................................................................................................................................12
1.9 Electrical System ..................................................................................................................................................... 23 1.9.1 Alternator light ............................................................................................................................................... 23 1.9.2 Voltmeter ....................................................................................................................................................... 24 1.9.3 Oil temperature .............................................................................................................................................. 24
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1.9.4 Cylinder head temperature ............................................................................................................................ 24 1.9.5 Oil Pressure ..................................................................................................................................................... 24 1.9.6 O.A.T. Indicator ............................................................................................................................................... 24 1.9.7 Stall Warning System ...................................................................................................................................... 24 1.9.8 Avionics........................................................................................................................................................... 24 1.9.9 External Lights ................................................................................................................................................ 25
1.10 Pitot and Static Pressure Systems ........................................................................................................................... 26
1.11 Landing Gear .......................................................................................................................................................... 27 1.11.1 Brake System .................................................................................................................................................. 28
3.2 Weighing report ..................................................................................................................................................... 36 3.2.1 Center of Gravity Limits .................................................................................................................................. 36 3.2.2 Distances from the datum .............................................................................................................................. 37
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3.3 Weight and Balance ............................................................................................................................................... 38 3.3.1 Loading ........................................................................................................................................................... 39
4.1 Use of Performance Charts ..................................................................................................................................... 40
4.2 Airspeed Indicator System Calibration .................................................................................................................... 41
4.11 Effects of Rain and Insects ...................................................................................................................................... 54
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
5.4 Recovery from Unintentional Spin .......................................................................................................................... 59
5.5 Electric Power System Malfunction ........................................................................................................................ 59
5.7 Trim System Failure ................................................................................................................................................ 61 5.7.1 LOCKED CONTROL .......................................................................................................................................... 61
5.8 Other Emergencies ................................................................................................................................................. 61 5.8.1 UNINTENTIONAL FLIGHT INTO ICING CONDITIONS ........................................................................................ 61
SECTION 6 NORMAL PROCEDURES ..................................................................................................................................62
9 SUPPLEMENT LIST ....................................................................................................................................................77
Nose wheel weight W1 = Plumb bob 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 =
DW A W B
We
2 1 m 100373.1
%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 remains valid.
3.2.1 Center of Gravity Limits
Forward limit 20% MAC for all weights
Aft limit 33% MAC for all weights
Datum Propeller support flange w/o spacer
Bubble Level Cabin floor
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3.2.2 Distances from the datum
The mean distances of the occupants, baggage and fuel from the datum are:
Figure 3-1
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3.3 Weight and Balance In order to compute the weight and balance of this aircraft, we have provided the following loading charts. This will reduce
the amount of math you need. To compute weight and balance use the formula:
Weight * Arm = Moment.
Pilot & Passenger
Fuel
Baggage
Weight
(lbs)
Moment
(lbs x in)
Weight
(lbs)
Moment
(lbs x in)
Gallons Weight
(lbs) Moment
Weight
(lbs)
Moment
(lbs x in)
10 748 260 19448
1 6,26 544
5 476
20 1496 270 20196
2 12,52 1089
10 952
30 2244 280 20944
3 18,78 1633
15 1427
40 2992 290 21692
4 25,04 2178
20 1903
50 3740 300 22440
5 31,3 2722
25 2379
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 420 31416
17 106,42 9255
180 13464 430 32164
18 112,68 9800
190 14212 440 32912
19 118,94 10344
200 14960 450 33660
20 125,2 10889
210 15708 460 34408
21 131,46 11433
220 16456 470 35156
22 137,72 11978
230 17204 480 35904
23 143,98 12522
240 17952 490 36652
24 150,24 13066
250 18700 500 37400
25 156,5 13611
26 162,76 14155
Meter Inches
PAX 1.900 74,80
FUEL 2.209 86,97
BAGGAGE 2.417 95,16
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To compute weight and balance:
1. Get moments from loading charts
2. Obtain the empty weight and moment from the most recent weight and balance
3. Insert the weights and the moments for fuel, occupants and baggage from the previous chart
4. Total the weight and the moment columns
5. Divide the total moment by the total weight to get the arm
6. Check that the total weight does not exceed maximum gross weight of 1320 pounds
7. Check that the arm falls within the C.G. range
CoG Position Computation Chart
Weight (lbs)
Arm (inches)* Moment
Empty Weight
Fuel 86.97
Pilot & Passenger 74.80
Baggage 95.16
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 gross weight is under the max gross weight of 1320 pounds and the Arm or C.G. is within the C.G.
range listed above.
3.3.1 Loading
Baggage compartment is designed for a maximum load of 44 pounds. Baggage size shall prevent excessive loading of
utility shelf (maximum pressure 12.5 kg/dm2). Maximum baggage size is: 80x45x32 cm . Baggage shall be secured using a
tie-down net to prevent any baggage movement during maneuvers.
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SECTION 4 PERFORMANCE
4 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:
“Flight test data” with conditions as prescribed by ASTM and bilateral agreements
Aircraft and engine 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 effect of different variables such as altitude,
temperature and weight. Given information is sufficient to plan journey with required precision and safety.
Additional information is provided for each table or graph.
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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
The following formula gives the CAS with the flaps full deflected:
CAS = 1.0611xIAS – 7.7222
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4.3 ICAO Chart
Fig. 4-2 ICAO CHART
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4.4 Stall Speeds
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
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4.5 Crosswind Maximum demonstrated crosswind velocity is 15 knots
Fig. 4-3 Crosswind chart
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4.6 Takeoff Performance
Weight = 600 kg
Flaps: Take-Off (15°)
Speed at Lift-Off = 48 KIAS
Speed Over 50ft Obstacle = 58 KIAS
Throttle Levers: Full Forward
Runway: Grass
Corrections
Headwind: - 5m for each kt (16 ft/kt)
Tailwind: + 15m for each kt (50ft/kt)
Paved Runway: - 6% to Ground Roll
Runway slope: + 5% to Ground Roll for each +1%
Pressure
Altitude
Distance [m]
Temperature [°C] ISA
[ft] -25 0 25 50
S.L. Ground Roll 139 167 197 230 185
At 50 ft AGL 231 277 327 381 307
1000 Ground Roll 149 179 212 247 196
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 352 422 499 581 431
7000 Ground Roll 228 274 323 377 276
At 50 ft AGL 378 454 536 624 457
8000 Ground Roll 245 294 347 405 292
At 50 ft AGL 406 488 576 671 485
9000 Ground Roll 264 316 374 436 310
At 50 ft AGL 437 525 620 722 514
10000 Ground Roll 284 341 402 469 329
At 50 ft AGL 470 565 667 777 546
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Weight = 550 kg
Flaps: Take-Off (15°)
Speed at Lift-Off = 48 KIAS
Speed Over 50ft Obstacle = 58 KIAS
Throttle Levers: Full Forward
Runway: Grass
Corrections
Headwind: - 5m for each kt (16 ft/kt)
Tailwind: + 15m for each kt (50ft/kt)
Paved Runway: - 6% to Ground Roll
Runway slope: + 5% to Ground Roll for each +1%
Pressure
Altitude
Distance [m]
Temperature [°C] ISA
[ft] -25 0 25 50
S.L. Ground Roll 111 133 157 184 148
At 50 ft AGL 184 221 261 304 245
1000 Ground Roll 119 143 169 197 156
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 Ground Roll 182 218 258 300 220
At 50 ft AGL 301 362 427 498 365
8000 Ground Roll 195 235 277 323 233
At 50 ft AGL 324 389 459 535 387
9000 Ground Roll 210 252 298 347 247
At 50 ft AGL 349 418 494 576 410
10000 Ground Roll 226 272 321 374 263
At 50 ft AGL 375 450 532 620 435
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Weight = 500 kg
Flaps: Take-Off (15°)
Speed at Lift-Off = 48 KIAS
Speed Over 50ft Obstacle = 58 KIAS
Throttle Levers: Full Forward
Runway: Grass
Corrections
Headwind: - 5m for each kt (16 ft/kt)
Tailwind: + 15m for each kt (50ft/kt)
Paved Runway: - 6% to Ground Roll
Runway slope: + 5% to Ground Roll for each +1%
Pressure
Altitude
Distance [m]
Temperature [°C] ISA
[ft] -25 0 25 50
S.L. Ground Roll 87 104 123 143 115
At 50 ft AGL 144 172 204 237 191
1000 Ground Roll 93 111 132 153 122
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 Roll 142 170 201 234 172
At 50 ft AGL 235 282 333 389 285
8000 Ground Roll 153 183 216 252 182
At 50 ft AGL 253 304 359 418 302
9000 Ground Roll 164 197 233 271 193
At 50 ft AGL 272 327 386 449 320
10000 Ground Roll 177 212 250 292 205
At 50 ft AGL 293 351 415 484 340
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4.7 Landing Distance
Weight = 600 kg
Flaps: Land (40°)
Short Final Approach Speed = 52 KIAS
Throttle Levers: Idle
Runway: Grass
Corrections
Headwind: - 5m for each kt (16 ft/kt)
Tailwind: + 15m for each kt (50ft/kt)
Paved Runway: - 2% to Ground Roll
Runway slope: - 2.5% to Ground Roll for each +1%
Pressure
Altitude
Distance [m]
Temperature [°C] ISA
[ft] -25 0 25 50
S.L. Ground Roll 135 149 162 176 157
At 50 ft AGL 344 358 371 385 366
1000 Ground Roll 140 154 168 182 162
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 175 193 210 228 194
At 50 ft AGL 384 402 419 437 403
8000 Ground Roll 182 200 219 237 200
At 50 ft AGL 391 409 428 446 409
9000 Ground Roll 189 208 227 246 206
At 50 ft AGL 398 417 436 455 415
10000 Ground Roll 197 216 236 256 213
At 50 ft AGL 406 425 445 465 422
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Weight = 550 kg
Flaps: Land (40°)
Short Final Approach Speed = 52 KIAS
Throttle Levers: Idle
Runway: Grass
Corrections
Headwind: - 5m for each kt (16 ft/kt)
Tailwind: + 15m for each kt (50ft/kt)
Paved Runway: - 2% to Ground Roll
Runway slope: - 2.5% to Ground Roll for each +1%
Pressure
Altitude
Distance [m]
Temperature [°C] ISA
[ft] -25 0 25 50
S.L. Ground Roll 114 125 136 148 132
At 50 ft AGL 323 334 345 357 341
1000 Ground Roll 118 130 141 153 136
At 50 ft AGL 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 147 162 177 192 163
At 50 ft AGL 356 371 386 401 372
8000 Ground Roll 153 168 184 199 168
At 50 ft AGL 362 377 393 408 377
9000 Ground Roll 159 175 191 207 173
At 50 ft AGL 368 384 400 416 382
10000 Ground Roll 165 182 198 215 179
At 50 ft AGL 374 391 407 424 388
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Weight = 500 kg
Flaps: Land (40°)
Short Final Approach Speed = 52 KIAS
Throttle Levers: Idle
Runway: Grass
Corrections
Headwind: - 5m for each kt (16 ft/kt)
Tailwind: + 15m for each kt (50ft/kt)
Paved Runway: - 2% to Ground Roll
Runway slope: - 2.5% to Ground Roll for each +1%
Pressure
Altitude
Distance [m]
Temperature [°C] ISA
[ft] -25 0 25 50
S.L. Ground Roll 94 103 113 122 109
At 50 ft AGL 303 312 322 331 318
1000 Ground Roll 97 107 117 127 112
At 50 ft AGL 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 122 134 146 158 134
At 50 ft AGL 331 343 355 367 343
8000 Ground Roll 126 139 152 165 139
At 50 ft AGL 335 348 361 374 348
9000 Ground Roll 131 145 158 171 143
At 50 ft AGL 340 354 367 380 352
10000 Ground Roll 136 150 164 178 148
At 50 ft AGL 345 359 373 387 357
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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)
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4.9 Cruise Maximum takeoff weight = 600 kg (1320 lbs)
During balked landing maneuver, flaps should be retracted immediately after applying full power.
4.11 Effects 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.
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SECTION 5 EMERGENCY PROCEDURES
5 Introduction Section 6 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 of the present section should be considered 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
Inform the Air Traffic Control if time and conditions allow
AIRSPEEDS FOR SAFE OPERATION IN EMERGENCY SITUATIONS KIAS KCAS
Engine failure after takeoff (15 degrees of flaps) 61 Knots 59 Knots
Engine failure during flight 65 Knots 61 Knots
Maneuvering speed 98Knots 97 Knots
Maximum glide 65 Knots 61Knots
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5.1 Engine Failures If an emergency arises, the basic guidelines described in this section should be considered and applied as necessary to
Use elevator control to recover to straight and level or a climbing attitude
NOTE
The first 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 focus on the appropriate recovery actions. Calling each item out loud
also tends to reinforce the physical inputs.
5.5 Electric Power System Malfunction Electric power supply system malfunctions may be avoided by carrying out inspections as scheduled and prescribed in the
Service Manual. Causes for malfunctions are hard to establish but, in any case, problems of this nature must be dealt with
immediately.
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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:
1. Reduce Throttle until RPM and manifold pressure within operating limits
Full throttle operation exceeds 5' (red lamp will blink)
Proceed as follows:
2. 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.
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5.7 Trim System Failure
5.7.1 LOCKED CONTROL
In case the trim control should not respond, act as follows:
LH/RH switch ........................................................................... CHECK for correct position
Airspeed .................................................................................... Adjust speed to control 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 edge, stall speed may increase.
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SECTION 6 NORMAL PROCEDURES
6 Introduction Section 6 contains checklists and the procedures for normal operation.
7 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 recommended to follow a planned schedule of lubrication and preventive maintenance
based on climatic and flying conditions encountered locally.
7.1 Aircraft Inspection Periods Inspection intervals occur at 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
Line Maintenance Manual.
7.2 Aircraft Alterations or Repairs For repairs, refer to aircraft’s Line Maintenance Manual.
7.3 Ground Handling
7.3.1 Towing
The use of a towbar is recommended. But, pulling on the propeller near the axle 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 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 moving surfaces. Seatbelts may be used to latch control
stick to prevent its movement.
7.3.3 Jacking
Given the light empty weight of the aircraft, lifting one of the main wheels can easily be accomplished even without the use
of hydraulic jacks. For an acceptable procedure please refer to the Line Maintenance Manual.
7.3.4 Leveling
Aircraft leveling may become necessary to check wing incidence, dihedral or the exact location of CG. Longitudinal
leveling verification is obtained by placing a level longitudinally, over the aft part of the baggage compartment floor. See
maintenance manual for instructions.
7.3.5 Road Transport
It is recommended to secure tightly all aircraft components onto the cart to avoid damage during transport. Minimum cart
size is 7x2.5 meters. It is suggested to place wings under the aircraft’s bottom, secured by specific clamps. Secondary
components such as stabilator and struts shall be protected from accidental hits using plastic or other material. For correct
rigging and de-rigging procedure, refer to the Line Maintenance Manual.
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7.3.6 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.
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 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 belts.
5. Secure tie-down ropes to the wing tie-down rings and to the tailring at approximately 45-degree angles to the
ground, in longitudinal direction (see Fig.8-1).
Tie Down Ring
Tie Down Anchor
Tie Down Anchor Tie Down Anchor
Tie Down AnchorTie Down Anchor
Tie Down RopeTie Down Rope
Tie Down RopeTie Down Rope
Tie Down RingTie Down Ring
Tie Down Rope
Fig. 7-1. CABLE POCITIONING
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Section 8 PLACARDS & MARKINGS
8 PLACARDS & MARKINGS
8.1.1 Magnetic compass compensation table
To compensate the deviation errors of the magnetic compass, the following correction table is located just below the
compass:
For N 30 60 E 120 150
Steer
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 control. The cabin’s
heat control is marked with this placard (20x11mm).
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8.1.4 Trim switch
The trim shunt control is located on the upper left area of the instrument panel alternatively allocating trim control to either
Rh or Lh control stick. The following placard (25x14mm) is positioned just above of it.
8.1.5 Breakers
Breakers are located on the lower/right side of the instrument 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 lower part of the instrument panel are located, in order:
The starter, marked with a placard:
For the generator and master switches:
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8.1.8 Choke
Located above the choke lever:
8.1.9 Generator light
A generator warning 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.
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8.1.11 Baggage compartment
A placard (30x50mm) indicating the maximum weight and to fasten the baggage’s retain harnesses, is present visible into
the baggage compartment.
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
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8.1.14 Brake oil reservoir
On the cap of the brake’s oil tank, is a placard indicating the type of oil that must be used.
8.1.15 Tire pressures
On each steel spring leaf is a placard indicating the main tires inflating pressure (18x6mm):
On the nose gear is located 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 steel.
Builder:
CostruzioniAeronauticheTecnam
Model: P2008
Serial number: XXX
40 PSI
32 PSI
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8.1.18 Static port
On each static port is locate a placard diam 20mm:
8.1.19 Fuel Tank
Next each fuel tank is the following placard (40x100 mm)
8.1.20 Limitation Placards
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
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Section 9 SUPPLEMENT LIST
9 SUPPLEMENT LIST
9.1 Introduction
This Section concerns the supplemental manuals of additional (or optional) 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
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INTENTIONALLY LEFT BLANK
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SUPPLEMENT No. S1
AIRSPEED INCREMENT
Record of Revisions 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;
Record of Revisions .................................................................................................................................................... 1
Log of Revisions .......................................................................................................................................................... 1
List of Effective Pages ................................................................................................................................................. 2
Table of Contents ....................................................................................................................................................... 3
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
0
20
40
60
80
100
120
140
160
40 60 80 100 120 140 160
CA
s
IAS
IAS-CAS kts FLAP CLEAN
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4.5 ICAO Chart
Fig. 4-2 ICAO CHART
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4.6 Stall Speeds
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
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4.7 Crosswind Maximum demonstrated crosswind velocity is 15 knots
Fig. 4-3 Crosswind chart
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SUPPLEMENT No. S2
MTV-33-1 VARIABLE PITCH PROPELLER
Record of Revisions 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
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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 “
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Table of Contents
Record of Revisions .................................................................................................................................................... 1
Log of Revisions .......................................................................................................................................................... 1
List of Effective Pages ................................................................................................................................................. 2
Table of Contents ....................................................................................................................................................... 3