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Tecnam P2010tdi Flight Manual

Tecnam P2010tdi Flight Manual

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TECNAM P2010tdi
M
ANUFACTURER
A
IRCRAFT MODEL
S
ERIAL NUMBER
: ...............................................
B
UILD YEAR
R
EGISTRATION MARKINGS
This manual must be carried in the airplane at all times.
The airplane has to be operated in compliance with procedures and limitations
contained herein.
This manual also constitutes the FAA Approved Airplane Flight Manual for
U.S. operations in accordance with FAR 21.29.
Costruzioni Aeronautiche TECNAM S.p.A.
Via Maiorise
CAPUA (CE) – Italy
Tel. +39 0823 99.75.38
WEB:
www.tecnam.com
Thisdocument and the information thereon is the property of Costruzioni Aeronautiche Tecnam S.p.A., and may only be used
for the purpose for which Tecnam products are supplied, and/or use and maintenance of Tecnam Aircraft.
Reproduction or use of the data, information, drawings thereon, in whole or in part, is strictly Prohibited without
the express written permission of Costruzioni Aeronautiche Tecnam S.p.A.
P2010tdi – Aircraft Flight Manual
Aircraft Flight Manual
Doc. No. 2010/552
Ed.2 Rev.4
2022, November 21
: COSTRUZIONI AERONAUTICHE TECNAM
: P2010tdi
:.....................................
: ........................
S.p.A.

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  • Page 1 WEB: www.tecnam.com Thisdocument and the information thereon is the property of Costruzioni Aeronautiche Tecnam S.p.A., and may only be used for the purpose for which Tecnam products are supplied, and/or use and maintenance of Tecnam Aircraft. Reproduction or use of the data, information, drawings thereon, in whole or in part, is strictly Prohibited without...
  • Page 3 P2010tdi – Aircraft Flight Manual Page i INDEX FOREWORD .....................III SECTIONS LIST ..................IV RECORD OF REVISIONS ..............ROR-1 LIST OF EFFECTIVE PAGES ............LOEP-2 Edition - Rev. 0 Aircraft Flight Manual INDEX...
  • Page 4 P2010tdi – Aircraft Flight Manual Page ii Intentionally left blank Edition - Rev. 0 Aircraft Flight Manual INDEX...
  • Page 5 P2010tdi – Aircraft Flight Manual Page iii FOREWORD Before using the airplane, you are recommended to read carefully this manual: a deep knowledge of airplane features and limitations will allow you for operating the airplane safely. For further information, please contact: COSTRUZIONI AERONAUTICHE TECNAM S.p.A.

  • Page 6: Section List

    P2010tdi – Aircraft Flight Manual Page iv SECTIONS LIST General (*) Section 1 Limitations (**) Section 2 Emergency Procedures (*) Section 3 Normal Procedures (*) Section 4 Performances (*) Section 5 Weight and Balance (*) Section 6 Airframe and Systems description (*)

  • Page 7: Record Of Revisions

    P2010tdi – Aircraft Flight Manual Page RoR-1 RECORD OF REVISIONS Any revision to the present Manual, except actual weighing data, is recorded: a Record of Revisions is provided at the front of this manual and the operator is advised to make sure that the record is kept up-to-date.
  • Page 8 P2010tdi – Aircraft Flight Manual Page RoR-2 Ed / Description of Revised pages Approval Revision Ed. 2 EASA approval No. First issue 10076578 Rev. 0 Updates for: RoR-2 - MOD2010/221 LoEP-1, 2 - MOD2010/227; 2 - 9, 13, 14, 21 thru 23, - MOD2010/228;...

  • Page 9: List Of Effective Pages

    P2010tdi – Aircraft Flight Manual Page LoEP-1 LIST OF EFFECTIVE PAGES The List of Effective Pages (LOEP), applicable to manuals of every operator, lists all the basic AFM pages: each manual could contain either basic pages or one variant of these pages when the pages of some Supplements are embodied.
  • Page 10 P2010tdi – Aircraft Flight Manual Page LoEP-2 Section Pages Revision i, ii, iii, iv; RoR-1 Rev. 0 LoEP-4 Section 0 Rev. 3 RoR-2, LoEP-1 thru 3 Rev. 4 Rev. 0 1 thru 5, 7 thru 14 Section 1 Rev. 4 1 thru 6, 8, 10 thru 12, 15 thru 20, 24 thru 29 Rev.
  • Page 11 P2010tdi – Aircraft Flight Manual Page LoEP-3 1 thru 4, 7, 12 ,13 Rev. 0 Section 6 5, 6, 8 thru 11 Rev. 1 14, 15, 16 Rev. 3 1 thru 6, 8, 10, 13 thru 21, 23 thru 26, 28, 29, 32, 34 thru 41, 43 thru 55, 57 thru 61, 63, 64, 65, 67, 69, 70, Rev.
  • Page 12 P2010tdi – Aircraft Flight Manual Page LoEP-4 Intentionally left blank Edition - Rev. 3 Aircraft Flight Manual LIST OF EFFECTIVE PAGES...

  • Page 13: Section 1 General

    P2010tdi – Aircraft Flight Manual Page 1 - 0 SECTION 1 GENERAL Edition - Rev. 0 Section 1 - GENERAL...
  • Page 15 P2010tdi – Aircraft Flight Manual Page 1 - 1 INDEX INTRODUCTION ...................3 WARNING – CAUTION – NOTE ............3 THREE VIEW AND DIMENSIONS ............4 3.1. Dimensions ..................5 ENGINE ....................6 PROPELLER ..................6 MAXIMUM WEIGHTS AND SPECIFIC LOADINGS .......7 6.1. Maximum Weights ................7 6.2.
  • Page 16 P2010tdi – Aircraft Flight Manual Page 1 - 2 Intentionally left blank Edition - Rev. 0 Section 1 – GENERAL INDEX...

  • Page 17: Section 1 - General Introduction

    P2010tdi – Aircraft Flight Manual Page 1 - 3 Introduction The Aircraft Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this aeroplane. This manual also contains supplemental data supplied by the aeroplane manufacturer.
  • Page 18 P2010tdi – Aircraft Flight Manual Page 1 - 4 Three view and Dimensions Figure 1-1 - General View Edition - Rev. 0 Section 1 – GENERAL THREE VIEW AND DIMENSIONS...
  • Page 19 P2010tdi – Aircraft Flight Manual Page 1 - 5 3.1. Dimensions Overall dimensions Wing Span…………………………………… 10.30m / 33.79ft Overall Length………………………………. 7.91m / 25.95ft Overall Height……………………………….. 2.84m / 9.32ft Stabilator span……………………………… 3.35m / 10.99ft Wing Wing surface………………………………… 13.9 m / 149.6 ft Mean Geometric Chord……………………..
  • Page 20 P2010tdi – Aircraft Flight Manual Page 1 - 6 Engine Manufacturer.…………………….… Continental Aerospace Technologies GmbH Model……….………………………. TAE 125-02-125 Type Certificate.…………………..EASA.E.055 Engine type.…...…………………… Liquid cooled 4 cylinder in-line four-stroke diesel engine with DOHC (double overhead camshaft), turbo charged, engine equipped with an electric starter and one alternator and optional auxiliary drive.
  • Page 21 P2010tdi – Aircraft Flight Manual Page 1 - 7 Maximum Weights and Specific Loadings 6.1. Maximum Weights Maximum Take-Off Weight…………... 1160 kg (2557 lb) Maximum Landing Weight…………... 1160 kg (2557 lb) For Aircraft embodying MOD2010/207: Maximum Take-Off Weight…………... 1200 kg (2645 lb) Maximum Landing Weight…………...
  • Page 22 P2010tdi – Aircraft Flight Manual Page 1 - 8 Fuel, Lubricant and Coolant 7.1. Fuel Fuel Specification..........JET A-1 (ASTM D 1655) Diesel (EN 590) 7.2. Lubricant Engine Oil Specification........Aero Shell Oil Diesel Ultra Shell Helix Ultra 5W-30 Gearbox Oil Specification………………….……...
  • Page 23 P2010tdi – Aircraft Flight Manual Page 1 - 9 Acronyms and Terminology 8.1. Velocity terminology KCAS Calibrated Airspeed is the indicated airspeed expressed in knots, corrected taking into account the errors related to the instrument itself and its installation. Indicated Airspeed is the speed shown on the airspeed indicator KIAS and it is expressed in knots.
  • Page 24 P2010tdi – Aircraft Flight Manual Page 1 - 10 8.2. Meteorological terminology International Standard Atmosphere: is the air atmospheric standard condition at sea level, at 15°C (59°F) and at 1013.25hPa (29.92 inHg). Official atmospheric pressure at airport level: it indicates the aircraft absolute altitude with respect to the official airport level.
  • Page 25 P2010tdi – Aircraft Flight Manual Page 1 - 11 8.4. Aircraft performance and flight planning terminology Crosswind Velocity is the velocity of the crosswind component for the which adequate control of the airplane during take-off and landing is assured. Usable fuel is the total fuel minus unusable fuel.
  • Page 26 P2010tdi – Aircraft Flight Manual Page 1 - 12 8.5. Weight and balance terminology Datum “Reference datum” is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. is the horizontal distance of an item measured from the reference datum.
  • Page 27 P2010tdi – Aircraft Flight Manual Page 1 - 13 Unit Conversion Chart Table 1-1 - Unit Conversion Chart  MOLTIPLYING YIELDS EMPERATURE Fahrenheit [°F] Celsius [°C] ⋅ −     + Celsius [°C] ⋅ Fahrenheit [°F]  ...
  • Page 28 P2010tdi – Aircraft Flight Manual Page 1 - 14 10. Litres / US Gallons Conversion Chart Table 1-2 - Litres/US Gallons Conversion Chart Litres US Gallons US Gallons Litres 11.4 15.1 22.7 30.3 37.9 10.6 45.4 11.9 53.0 13.2 60.6 15.9...
  • Page 29 P2010tdi – Aircraft Flight Manual Page 2 - 0 SECTION 2 LIMITATIONS Edition - Rev. 0 Section 2 - LIMITATIONS...
  • Page 31 P2010tdi – Aircraft Flight Manual Page 2 - 1 INDEX INTRODUCTION ..................3 SPEED .......................4 2.1. Speed limitations ................4 2.2. Airspeed Indicator Markings ..............6 POWERPLANT ..................7 3.1. Engine....................7 3.2. Propeller ...................7 3.3. Powerplant Limitations ..............7 INSTRUMENTATION MARKINGS ............10 FUEL ......................11 OIL ......................
  • Page 32 P2010tdi – Aircraft Flight Manual Page 2 - 2 12.4. Baggage compartment placard ........... 17 KINDS OF OPERATION ..............18 PBN (RNAV & RNP) OPERATIONAL CAPABILITY ......24 14.1. General GNSS Navigation Equipment Approvals ....... 24 AVIONIC SYSTEM LIMITATIONS ............25 15.1.

  • Page 33: Section 2 - Limitations

    P2010tdi – Aircraft Flight Manual Page 2 - 3 Introduction Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of P2010tdi aircraft, its engines, standard systems and equipment. Edition - Rev. 0 EASA Approved Section 2 – LIMITATIONS...
  • Page 34 P2010tdi – Aircraft Flight Manual Page 2 - 4 Speed 2.1. Speed limitations The following table addresses the airspeed limitations and their operational significance: Table 2-1 - Speeds Limitations SPEED KCAS KIAS REMARKS Never exceed Do not exceed this speed in any Speed operation.
  • Page 35 P2010tdi – Aircraft Flight Manual Page 2 - 5 For Aircraft embodying MOD2010/207: Table 2-2a - Speeds Limitations (MOD 2010/207) SPEED KCAS KIAS REMARKS Never exceed Do not exceed this speed in any Speed operation. Maximum Structural Do not exceed this speed except in Cruising smooth air and only with caution.
  • Page 36 P2010tdi – Aircraft Flight Manual Page 2 - 6 2.2. Airspeed Indicator Markings Table 2-3 - Airspeed Indicator Markings MARKING KIAS EXPLANATION Positive Flap Operating Range (lower limit is V , at specified maximum weight and 48-90 White arc upper limit is the maximum speed permissible with landing flaps extension).

  • Page 37: Power Plant

    P2010tdi – Aircraft Flight Manual Page 2 - 7 Powerplant 3.1. Engine MANUFACTURER………………………... Continental Aerospace Technologies GmbH MODEL……………………………………... TAE 125-02-125 TYPE………………………………………... Liquid cooled 4 cylinder in-line four-stroke diesel engine with DOHC (double overhead camshaft), turbo charged, engine equipped with an electric starter and one alternator and optional auxiliary drive.
  • Page 38 P2010tdi – Aircraft Flight Manual Page 2 - 8 Oil temperature Operating temperature………..…  min. 50°C (122°F) max. 120°C (248°F) Coolant temperature Operating temperature………..…  min. 60°C (140°F) max. 105°C (221°F) Gearbox temperature  Operating temperature………..… min. 0°C (32°F) max. 120°C (248°F) Fuel temperature ...
  • Page 39 Page 2 - 9 Cold Weather Operation* P2010tdi is equipped with a sensor monitoring intercooler temperature. In case of both intercooler temperature equal or lower than 15°C (59°F) and altitude/Outside Air Temperature envelope within red area, a CAS message (“INTRCLR TEMP LO”) alerts the pilot.
  • Page 40 P2010tdi – Aircraft Flight Manual Page 2 - 10 Instrumentation Markings Table 2-5 – Avionics System Instrument Markings WHITE GREEN YELLOW ARC/LINE INSTRUMENT Minimum Advisory Safe Caution Maximum limit operation limit 2251 -> PROPELLER 0 -> 2250 2301 -> 2500...
  • Page 41 P2010tdi – Aircraft Flight Manual Page 2 - 11 Fuel 2 TANKS 120 litres each one (32 gallons) MAXIMUM CAPACITY 240 litres (63 gallons) MAXIMUM USABLE FUEL 231 litres (61 gallons) APPROVED FUEL JET A-1 (ASTM D 1655) Diesel (EN 590)
  • Page 42 P2010tdi – Aircraft Flight Manual Page 2 - 12 Operative and additional limitations 8.1. Maximum Operating Altitude Maximum operating altitude is 18000 ft (5846 m) MSL Flight crew and passengers are required to use supplemental oxygen according to applicable Air Operation Rules.
  • Page 43 P2010tdi – Aircraft Flight Manual Page 2 - 13 Weights and center of gravity limits Table 2-6 – Weight Limits Condition Weight Maximum Take-off Weight 1160 kg 2557 lb Maximum Landing Weight 1160 kg 2557 lb Datum Vertical plane tangent to the wing leading edge (the...
  • Page 44 P2010tdi – Aircraft Flight Manual Page 2 - 14 For aircraft embodying MOD2010/207: Table 2-7 – Weight Limits(MOD2010/207) Condition Weight Maximum Take-off Weight 1200 kg 2645 lb Maximum Landing Weight 1200 kg 2645 lb Datum Vertical plane tangent to the wing leading edge (the...

  • Page 45: Approved Maneuvers

    P2010tdi – Aircraft Flight Manual Page 2 - 15 10. Maneuvers and Load Factor Limits 10.1. Load Factor Limits Maneuver load factors limits are as follows: Positive Negative + 3.8 g -1.52 g Maneuver load factors limits with flaps extended are as follows:...
  • Page 46 P2010tdi – Aircraft Flight Manual Page 2 - 16 11. Seats and Baggage 11.1. Maximum Passenger Seating Configuration Maximum passenger seating configuration is 3. 11.2. Baggage Loading Limit Table 2-8 – Baggage Weight Limits Max Loading Max Loading Intensity 40 kg / 88 lb 0.72 kg/dm...

  • Page 47: Limitation Placards

    P2010tdi – Aircraft Flight Manual Page 2 - 17 12. Limitation Placards Hereinafter limitation placards, related to the operating limitations, are placed in plain view on the pilot. 12.1. Speed limitations On the left side instrument panel, above on the left, it is placed the following placard...

  • Page 48: Kinds Of Operation

    P2010tdi – Aircraft Flight Manual Page 2 - 18 13. Kinds of operation The airplane is approved for single pilot, VFR and IFR (day/night) operations, provided the appropriate equipment is installed and operable. Flights in icing conditions are prohibited. The following list identifies the systems and equipment upon which type certification for each kind of operation was predicated.
  • Page 49 P2010tdi – Aircraft Flight Manual Page 2 - 19 Table 2-9 – Kinds of Operation Equipment List Number of items installed VFR Day VFR Night System, Instrument, and/or Equipment IFR Day IFR Night Remarks and/or Exceptions Autoflight (ATA-22) A/P system...
  • Page 50 P2010tdi – Aircraft Flight Manual Page 2 - 20 Number of items installed VFR Day VFR Night System, Instrument, IFR Day and/or Equipment IFR Night Remarks and/or Exceptions Equipment/ Furnishings (ATA-25) Safety belt One safety belt and one seat for each occupant must be operative.
  • Page 51 P2010tdi – Aircraft Flight Manual Page 2 - 21 Number of items installed VFR Day VFR Night System, Instrument, IFR Day and/or Equipment IFR Night Remarks and/or Exceptions Fuel System (ATA-28) Electrical fuel pump Fuel temperature indicator Fuel quantity indicator...
  • Page 52 P2010tdi – Aircraft Flight Manual Page 2 - 22 Number of items installed VFR Day VFR Night System, Instrument, IFR Day and/or Equipment IFR Night Remarks and/or Exceptions Strobe lights Map light Navigation Instruments (ATA-34) Primary flight display (PFD) Multifunction...
  • Page 53 P2010tdi – Aircraft Flight Manual Page 2 - 23 Number of items installed VFR Day VFR Night System, Instrument, IFR Day and/or Equipment IFR Night Remarks and/or Exceptions Engine Indicating System (ATA-77) PWR indicator RPM indicator CT indicator Fuel flow indicator...
  • Page 54 P2010tdi – Aircraft Flight Manual Page 2 - 24 14. PBN (RNAV & RNP) Operational Capability 14.1. General GNSS Navigation Equipment Approvals The Garmin GNSS navigation system as installed in this airplane complies with the requirements of AC 20-138D, JAA TGL-10 and AMCs 20-4A. 20-27A and 20-28.
  • Page 55 The following document, at the latest revision, must be carried on board the airplane at all times: - The “Garmin G1000Nxi Pilot’s Guide for the Tecnam P2010tdi” (last issue) must be carried in the aircraft and made available to the pilot at all time.
  • Page 56 P2010tdi – Aircraft Flight Manual Page 2 - 26 RNAV OPERATIONS In general terms, RNAV equipment operates by automatically determining aircraft position from one, or a combination, of the following together with the means to establish and follow a desired path:...
  • Page 57 P2010tdi – Aircraft Flight Manual Page 2 - 27 15.2. G1000Nxi GNSS (GPS/SBAS) Navigation System Limitations The pilot must confirm at system initialization that the Navigation database is current. Navigation database is expected to be current for the duration of the flight.
  • Page 58 P2010tdi – Aircraft Flight Manual Page 2 - 28 Both GPS navigation receivers must be operating and providing GPS navigation guidance to the PFD for operations requiring RNP-4 (long range navigation) performance. Whenever possible, RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and en-route RNAV “Q”...
  • Page 59 P2010tdi – Aircraft Flight Manual Page 2 - 29 DEAD RECKONING MODE Dead Reckoning Mode only functions in En-route (ENR) or Oceanic (OCN) phase of flight. In all other phases, an invalid GPS solution produces a “NO GPS POSITION” annunciation on the map and the G1000Nxi stops using GPS.
  • Page 60 Page 2 - 30 16. Autopilot System Limitations The “Garmin G1000Nxi Pilot’s Guide for the Tecnam P2010tdi” (last issue) must be carried in the aircraft NOTE and made available to the pilot at all time. Following operating limitations shall apply when the aircraft is equipped with Garmin GFC700 Autopilot: The Autopilot is certified for Category I –...

  • Page 61: Section 3 Emergency Procedures

    P2010tdi – Aircraft Flight Manual Page 3 - 0 SECTION 3 EMERGENCY PROCEDURES Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES...
  • Page 63 P2010tdi – Aircraft Flight Manual Page 3 - 1 INDEX INTRODUCTION ................... 3 1.1. Reference Airspeeds for Emergency Procedures ........4 1.2. Annunciator and Alerts ................4 1.3. Alert Level Definition ................5 1.4. CAS Messages Summary ..............6 ELECTRICAL SYSTEM ................. 8 2.1.
  • Page 64 P2010tdi – Aircraft Flight Manual Page 3 - 2 7.7.1. High Gearbox Temperature ............26 7.8. Intercooler Temperature Limit Exceedance .......... 27 7.8.1. Low Intercooler Temperature ............27 7.8.2. High Intercooler Temperature ............. 27 7.9. Oil Temperature Limits Exceedance ............ 28 7.9.1.
  • Page 65 P2010tdi – Aircraft Flight Manual Page 3 - 3 Introduction Section 3 includes checklists and detailed procedures for coping with various types of emergency conditions that could arise. Before operating the aircraft, the pilot should become thoroughly familiar with the present manual and, in particular, with the present Section.
  • Page 66 Text color is based on alert levels described in the following section. The Annunciation Window is located to the right of the Altimeter and Vertical Speed Indicator. All P2010tdi annunciations can be displayed simultaneously in the Annunciation Window. A white horizontal line separates annunciations that are acknowledged from annunciations that are not yet acknowledged.
  • Page 67 P2010tdi – Aircraft Flight Manual Page 3 - 5 1.3. Alert Level Definition Warning: This level of alert requires immediate attention. A warning alert appears in the Annunciation Window. Text appearing in the Annunciation Window is red. A warning alert is also accompanied by a flashing Warning Softkey annunciation. Pressing the Warning Softkey acknowledges the warning alert and stops the aural tone, if applicable.
  • Page 68 1.4. CAS Messages Summary The following table shows a summary of all Crew Alerting Message (CAS), divided for System or Function. For CAS message related to avionics system refer to Garmin P2010tdi Pilot’s Guide. Table 3-1 -CAS Messages Summary System...
  • Page 69 P2010tdi – Aircraft Flight Manual Page 3 - 7 LH FUEL Fuel LH FUEL LOW Low fuel quantity detected QTY LOW RH FUEL Fuel LH FUEL LOW Low fuel quantity detected QTY LOW LH-RH Fuel RH-LH FUEL LH and RH FUEL QTY LOW...
  • Page 70 P2010tdi – Aircraft Flight Manual Page 3 - 8 ELECTRICAL SYSTEM 2.1. Alternator Failure Annunciation window Alert window ALT FAIL Alternator failure If ALT FAIL caution is ON: Circuit breaker(s)…………………………. CHECK Generator Switch…………………………. Generator Switch…………………………. If ALT FAIL caution remains on: Generator Switch………………………….
  • Page 71 P2010tdi – Aircraft Flight Manual Page 3 - 9 2.2. Loss of Essential Bus Land as soon as practical In case of loss of essential bus, the following equipment will be lost: Table 3-2 – Loss of Essential Bus FIELD...
  • Page 72 P2010tdi – Aircraft Flight Manual Page 3 - 10 2.3. Loss of Main Bus Land as soon as practical The following will be lost: Table 3-3 – Loss of Main Bus INSTRUMENT STARTER CABIN LIGHT CONVERTER LIGHT 28/12V NAV LIGHT...
  • Page 73 P2010tdi – Aircraft Flight Manual Page 3 - 11 2.5. Electrical system overall failure In case of electrical system overall failure, apply following procedure: Master Switch…………………………... Generator Switch………………………. Master Switch…………………………... Generator Switch………………………. If failure persists, land as soon as possible...

  • Page 74: Pitot Heat

    P2010tdi – Aircraft Flight Manual Page 3 - 12 PITOT-STATIC SYSTEM 3.1. Pitot heating system failure Annunciation window Alert window PITOT HEAT ON Pitot heat on PITOT HEAT Pitot heat off or fail When the Pitot Heating system is active, the green PITOT...
  • Page 75 P2010tdi – Aircraft Flight Manual Page 3 - 13 3.2. Static source malfunction The alternate source valve is located on the left side of the central pedestal. If static source malfunction is suspected and/or abnormal fluctuations of indicated airspeed and/or altitude are detected in relationship with yawing: 1.
  • Page 76 P2010tdi – Aircraft Flight Manual Page 3 - 14 AVIONIC SYSTEM 4.1. Loss of information displayed When a LRU or a LRU function fails, a large red “X” is typically displayed on the display field associated with the failed data.

  • Page 77: Attitude Fail

    P2010tdi – Aircraft Flight Manual Page 3 - 15 4.3. Loss of attitude information ATTITUDE FAIL (red X on display field) Display system is not receiving attitude information from AHRS. INSTRUCTION: revert to standby instrument 4.4. Loss of altitude information...

  • Page 78: Vert Speed Fail

    P2010tdi – Aircraft Flight Manual Page 3 - 16 4.5. Loss of vertical speed information VERT SPEED FAIL (red X on display field) Display system is not receiving vertical speed input from Air Data Computer. INSTRUCTION: determine vertical speed on the basis of altitude information 4.6.
  • Page 79 P2010tdi – Aircraft Flight Manual Page 3 - 17 4.7. Display failure In the event of a display failure, the G1000 Nxi phase III System automatically switches to reversionary (backup) mode. In reversionary mode, all important flight information is presented on the remaining display in the same format as in normal operating mode.
  • Page 80 P2010tdi – Aircraft Flight Manual Page 3 - 18 Engine Securing Following procedure is applicable to shut down the engine in flight: Thrust Lever……………………………………… IDLE Engine Master……………………………………. Fuel Selector valve.……………………………... Electrical fuel pump……………………………… Generator switch………………………………… Edition - Rev. 0 Section 3 – EMERGENCY PROCEDURES...
  • Page 81 P2010tdi – Aircraft Flight Manual Page 3 - 19 Aircraft Evacuation With the engine secured and propeller stopped: Parking brakes…………………………………… ENGAGED Seat Belts…...……………………………………. UNSTRAP Headphones.……………………………………... REMOVE Doors…....……………………………… OPEN Master switch…..………………………………… Escape away from flames/hot engine compartment/spilling fuel tanks/hot brakes Edition - Rev. 0 Section 3 –...

  • Page 82: Power Plant

    P2010tdi – Aircraft Flight Manual Page 3 - 20 POWERPLANT 7.1. Engine Failure during Take-off run If engine fails before rotation: ABORT TAKE OFF Thrust Lever…………………………….. IDLE Brakes…………………………………… AS REQUIRED With aircraft stopped Engine Master………………………….. Fuel Selector valve.……………………. Electrical fuel pump…………………….
  • Page 83 P2010tdi – Aircraft Flight Manual Page 3 - 21 7.2. Engine Failure after Take-off If engine fails immediately after becoming airborne:  Abort on the runway if possible. In case low altitude precludes a runway stop and/or engine restart: =79 kts...
  • Page 84 P2010tdi – Aircraft Flight Manual Page 3 - 22 7.3. Abnormal engine or propeller behaviour during the flight In normal conditions, FADEC switch must be in "AUTO" position, as this will allow the FADEC system to choose automatically the healthiest channel. If the engine acts...
  • Page 85 P2010tdi – Aircraft Flight Manual Page 3 - 23 7.4. Propeller Overspeed In case of propeller overspeeding, apply following procedure: Thrust Lever…………………………………... REDUCE power Airspeed……………………………………….. REDUCE to prevent propeller overspeed RPM indicator…………………………………. CHECK If it is not possible to decrease propeller RPM, land as soon as possible applying Forced landing procedure.
  • Page 86 P2010tdi – Aircraft Flight Manual Page 3 - 24 7.5. Coolant Temperature (CT) Limit Exceedance 7.5.1. H OOLANT EMPERATURE Annunciation window Alert window CT HIGH Coolant Temp High If CT exceeds maximum limit: Thrust lever…………………………… REDUCE power as practical Airspeed……………………………….
  • Page 87 P2010tdi – Aircraft Flight Manual Page 3 - 25 7.6. Coolant Level Limit Exceedance Annunciation window Alert window COOLANT LVL LOW Coolant Level Low Coolant Temperature……………... Monitor If CT rises: Refer to CT Limits Exceedance procedure (§7.6). Edition - Rev. 0 Section 3 –...
  • Page 88 P2010tdi – Aircraft Flight Manual Page 3 - 26 7.7. Gearbox Temperature Limit Exceedance 7.7.1. H EARBOX EMPERATURE Annunciation window Alert window Gearbox Temp High GEARBOX TEMP HI POWER……………………...... REDUCE AIRSPEED…………………...... INCREASE as required extinguish message. If CAS message doesn’t extinguish: Land as soon as possible Edition - Rev.
  • Page 89 P2010tdi – Aircraft Flight Manual Page 3 - 27 7.8. Intercooler Temperature Limit Exceedance 7.8.1. L NTERCOOLER EMPERATURE Annunciation window Alert window Intercooler Temp Low INTRCLR TEMP LO POWER……………………...... INCREASE as required extinguish message If CAS message doesn’t extinguish: Fly immediately away from engine red zone (see Sect.2) (changing altitude and direction of flight, out and below of clouds, visible moisture, precipitation) to allow to increase outside air temperature.
  • Page 90 P2010tdi – Aircraft Flight Manual Page 3 - 28 7.9. Oil Temperature Limits Exceedance 7.9.1. H EMPERATURE Annunciation window Alert window Oil Temp High OIL TEMP HI Maximum oil temperature limit exceedance can be the final effect of different causes: excessive friction between moving engine components, oil leakage from the circuit (with related pressure reduction) etc.
  • Page 91 P2010tdi – Aircraft Flight Manual Page 3 - 29 7.10. Oil Pressure Limits Exceedance 7.10.1. L RESSURE Annunciation window Alert window Oil Press Low OIL PRESS LO If the oil pressure is under the lower limit Thrust Lever…………………… REDUCE to minimum practical OIL TEMP………………………...
  • Page 92 P2010tdi – Aircraft Flight Manual Page 3 - 30 7.11. Alternate Air Caution Light ON Land as soon as practical. Check the air filter before next flight. 7.12. Glow Plug System Failure* Annunciation window Alert window GLOWSYS FAIL GLOWSYS Fail...
  • Page 93 P2010tdi – Aircraft Flight Manual Page 3 - 31 FUEL SYSTEM 8.1. Fuel Temperature Limits Exceedance 8.1.1. L EMPERATURE CAS message will be provided only when fuel temperature is below or equal to -31°C. For Diesel, operation with fuel temperature equal or below -5°C are not allowed.
  • Page 94 P2010tdi – Aircraft Flight Manual Page 3 - 32 8.2. Fuel Filter Clogged Annunciation window Alert window FUEL FLTR CLGD Fuel Filter Clogged Land as soon as practical. Replace the fuel filter before next flight. Edition - Rev. 0 Section 3 – EMERGENCY PROCEDURES...
  • Page 95 P2010tdi – Aircraft Flight Manual Page 3 - 33 Inflight Engine Restart Engine inflight restart must be performed without using the starter as long as propeller is windmilling in order to avoid possible engine damages. The propeller will normally continue to turn as long as the airspeed is above 65 KIAS.
  • Page 96 P2010tdi – Aircraft Flight Manual Page 3 - 34 10. FADEC Warning Annunciation window Alert window Fadec A Fail FADEC A Fadec B Fail FADEC B In case of both FADEC warnings come ON, consider that a monitoring of intercooler temperature is not available. Avoid operating aircraft in the engine red zone (see Sect.2).
  • Page 97 P2010tdi – Aircraft Flight Manual Page 3 - 35 11. Smoke and Fire 11.1. Engine fire on the ground Fuel Selector valve.……………………………... Engine Master……………………………………. Electric Fuel pump………………………………. Cabin heat and defrost………………………….. Master and Generator Switches.………………. Parking Brake……………………………………. ENGAGED Aircraft Evacuation……………………………….
  • Page 98 P2010tdi – Aircraft Flight Manual Page 3 - 36 11.3. Engine fire in flight Fuel Selector valve.……………………………... Engine Master……………………………………. Electric Fuel pump………………………………. Cabin heat and defrost………………………….. Thrust Lever……………………………………… FULL FORWARD Master and Generator Switches.………………. Cabin ventilation…………………………………. OPEN Land as soon as possible applying Forced landing procedure 11.4.
  • Page 99 P2010tdi – Aircraft Flight Manual Page 3 - 37 11.5. Electrical smoke or fire in cabin during flight Cabin heat………………………….. Cabin ventilation…………………… OPEN In case of fire, direct the fire extinguisher toward the base of flame Initiate an emergency descent: Flaps ...........

  • Page 100: Press And Hold

    P2010tdi – Aircraft Flight Manual Page 3 - 38 12. FLIGHT CONTROLS 12.1. Electrical pitch trim control failure Trim Runaway In event of trim runaway: AP DISC switch……..………... PRESS and HOLD TRIM DISC switch…..………... AP DISC switch……………….. RELEASE Pitch trim………………………..
  • Page 101 P2010tdi – Aircraft Flight Manual Page 3 - 39 12.2. Electrical rudder trim control failure Trim Runaway In event of trim runaway: Airspeed and flaps...…………... ADJUST to control aircraft without excessive force Rudder………………………….. As required Land aircraft as soon as practical...
  • Page 102 P2010tdi – Aircraft Flight Manual Page 3 - 40 12.3. Flaps control failure 1. Flaps position ............. Visually check position 2. Airspeed .......Maintain according to observed flap position 3. Flaps position ......Visually check movement while operating the flaps switch in all positions If flaps are stuck: 4.
  • Page 103 P2010tdi – Aircraft Flight Manual Page 3 - 41 13. RECOVERY FROM UNINTENTIONAL SPIN If unintentional spin occurs: Flap………..………………….. Thrust Lever………………… IDLE Ailerons……………………... Neutral Rudder………………………. Fully opposite to the direction of spin Control Wheel……………… Forward When rotation stops: Rudder………………………. NEUTRAL Attitude……………………….

  • Page 104: Unintentional Flight Into Icing Conditions

    P2010tdi – Aircraft Flight Manual Page 3 - 42 14. UNINTENTIONAL FLIGHT INTO ICING CONDITIONS Pitot heat…………………….. CHECK ON Fly immediately away from icing conditions (changing altitude and direction of flight, out and below of clouds, visible moisture, precipitation) Control surfaces…………….
  • Page 105 P2010tdi – Aircraft Flight Manual Page 3 - 43 15. Emergency Landing 15.1. Forced Landing without Engine Power Preparation: Flaps………………………………………. Airspeed…………………………………... ESTABLISH V GLIDE (79 KIAS) Glide ratio is about 11.5, therefore in zero wind conditions for every 1000 ft it is possible to cover about 2 NM.
  • Page 106 P2010tdi – Aircraft Flight Manual Page 3 - 44 15.2. Power on forced landing Flaps………………………………………….. Airspeed……………………………………… ESTABLISH V GLIDE (79 KIAS) Glide ratio is about 11.5, therefore in zero wind conditions for every 1000 ft it is possible to cover about 2 NM.
  • Page 107 P2010tdi – Aircraft Flight Manual Page 3 - 45 16. Oxygen System 16.1. Oxygen pressure loss Cabin Ventilation………………………….OPEN Initiate an emergency descent: Flaps ........... UP Thrust lever ......... IDLE Airspeed ..........as required When passing 10,000 ft or at an altitude where oxygen is no longer required, whichever comes first: Oxygen………………………….…………OFF...
  • Page 108 P2010tdi – Aircraft Flight Manual Page 3 - 46 Intentionally left blank Edition - Rev. 0 Section 3 – EMERGENCY PROCEDURES EMERGENCY LANDING...

  • Page 109: Section 4 Normal Procedures

    P2010tdi – Aircraft Flight Manual Page 4 - 0 SECTION 4 NORMAL PROCEDURES Edition - Rev. 0 Section 4 – NORMAL PROCEDURES...
  • Page 111 P2010tdi – Aircraft Flight Manual Page 4 - 1 INDEX INTRODUCTION ..................3 AIRSPEEDS FOR NORMAL OPERATIONS..........4 PRE-FLIGHT INSPECTION ...............5 3.1. Cabin Inspection ................5 3.2. Aircraft Walk-Around .................7 CHECKLIST ..................... 11 4.1. Before Starting Engine ..............11 4.2. Engine Starting ................13 4.3.
  • Page 112 P2010tdi – Aircraft Flight Manual Page 4 - 2 Intentionally left blank Edition - Rev. 0 Section 4 – NORMAL PROCEDURES INDEX...
  • Page 113 P2010tdi – Aircraft Flight Manual Page 4 - 3 Introduction Section 4 describes checklists and recommended procedures for the conduct of normal operations for P2010tdi aircraft. Edition - Rev. 0 Section 4 – NORMAL PROCEDURES INTRODUCTION...
  • Page 114 P2010tdi – Aircraft Flight Manual Page 4 - 4 Airspeeds for normal operations. The following airspeeds are those which are significant for normal operations. MTOW (MOD MTOW 2010/207) SPEEDS FLAPS 1160 kg 1200 kg (2557 lb) (2645 lb) Rotation Speed (V...
  • Page 115 P2010tdi – Aircraft Flight Manual Page 4 - 5 Pre-Flight Inspection Before each flight, it is necessary to carry out a complete aircraft check including a cabin inspection followed by an external inspection, as below detailed. 3.1. Cabin Inspection Aircraft documents …….…………..
  • Page 116 P2010tdi – Aircraft Flight Manual Page 4 - 6 If oxygen system is planned or anticipated to be used for flight: Cannulas …………………………. visual inspection Masks …………………………. visual inspection There must be at least one cannula or mask for each occupant on board.
  • Page 117 P2010tdi – Aircraft Flight Manual Page 4 - 7 3.2. Aircraft Walk-Around To perform the aircraft walk around, carry out the checklists according to the pattern shown in Visual inspection is defined as follows: check for defects, cracks, detachments, excessive play, unsafe or improper installation as well as for general condition.
  • Page 118 P2010tdi – Aircraft Flight Manual Page 4 - 8 Figure 4-1 - Aircraft Walk-around Left fuel filler cap CHECK desired fuel level (use graduated dipstick). Drain the left fuel tank sump by quick drain valve using a cup to collect fuel (drainage operation must be carried with the aircraft parked on a level surface).
  • Page 119 P2010tdi – Aircraft Flight Manual Page 4 - 9 Left main landing CHECK inflation, tire condition, alignment, gear fuselage skin condition. Check fuselage skin status, tire status (cuts, bruises, cracks and excessive wear), slippage markers integrity, gear structure and brakes hoses: there should be no sign of hydraulic fluid leakage.
  • Page 120 P2010tdi – Aircraft Flight Manual Page 4 - 10 Check the engine cowling surface conditions, then open engine inspection doors and perform the following checks: Nacelle inlets and exhausts openings must be free of obstructions. Check connection and integrity of air intake system, visually inspect that ram air intake is unobstructed.

  • Page 121: Section 4 - Normal Procedures Checklists

    P2010tdi – Aircraft Flight Manual Page 4 - 11 Checklist 4.1. Before Starting Engine Pre-flight inspection………….. Complete Seat position safety Adjust belts…………………………… Flight controls………………… Operate full stroke checking for movement smoothness, free of play and friction Parking brake…………………. Engage Thrust Lever…………………...
  • Page 122 P2010tdi – Aircraft Flight Manual Page 4 - 12 14. Fuel quantity…………………………… compare the fuel quantity indicators with fuel quantity visually checked into the tanks 15. Fuel temperature………………………. Check within limits. Refer to Instrumentation Markings (Par. 4) in Section 2.
  • Page 123 P2010tdi – Aircraft Flight Manual Page 4 - 13 4.2. Engine Starting Thrust IDLE Lever…………………………… Fuel selector valve………………..….. Select the tank with less fuel Electric fuel pump………….…………. Propeller area…………………………. Check that area is clear of persons / objects Check to ensure no person or object is present in the area close to the propeller.
  • Page 124 P2010tdi – Aircraft Flight Manual Page 4 - 14 11. Check oil pressure rises and OIL PRESS LOW warning extinguish. If after 3 seconds the minimum oil pressure of 1 bar is not indicated: shut down the engine immediately. 12. Electric fuel pump………………………...
  • Page 125 P2010tdi – Aircraft Flight Manual Page 4 - 15 4.4. Before taxing Flight instruments and avionics…………. Set, TEST functions Altimeters…………………………….…… Pitot Heat…………………………..……... CHECK message “Pitot heat ON”, then OFF, CHECK CAS message “Pitot heat” 4.5. Taxiing Parking brake…………………………… Release Brakes……………………………………...
  • Page 126 P2010tdi – Aircraft Flight Manual Page 4 - 16 4.6. Before Take-off Parking brake………………………………..Brake pedal press, ON Engine parameters.…………………………... Check within limits ALT FAIL warning...………………………….. OFF (check) Electric Fuel pump………………………..Fuel selector valve……………………………. Select the fullest tank Fuel Temperature……………………………..
  • Page 127 P2010tdi – Aircraft Flight Manual Page 4 - 17 During the test, verify the following: FADEC TEST CAS message comes ON and propeller speed increases. Propeller speed target 1100-1300 RPM. If the CAS messages do not appear at this time, a take-off must not be attempted with the aircraft.
  • Page 128 P2010tdi – Aircraft Flight Manual Page 4 - 18 13. FADEC Switch………………………... Switch to FADEC B (FADEC B FORCED and FADEC B ACTIVE messages come ON) Engine check (running without a change) 14. Thrust Lever…………………………………... FULL FORWARD a. Propeller RPM…..……......
  • Page 129 P2010tdi – Aircraft Flight Manual Page 4 - 19 4.7. Take-off Parking brake…………………………. Release Brakes…………………………………. Apply Thrust Lever…………………………... FULL and check 2240 to 2300 RPM, power indicator must show more than 95%. Engine proper performance at full throttle shall be checked early in the ground roll in order to abandon take-off if necessary.
  • Page 130 P2010tdi – Aircraft Flight Manual Page 4 - 20 4.8. Climb Thrust Lever...……………………………... As required Engine parameters………………………... In the allowed range Normal climbs are performed flaps UP and maximum continuous power at speeds 5 to 10 knots higher than best rate of climb speeds.
  • Page 131 P2010tdi – Aircraft Flight Manual Page 4 - 21 Check each occupant’s oxygen cannula adjustment and NOTE flowmeter setting. Recheck oxygen pressure indication from time to time. Always place the flowmeter in a position where it is in the normal scan area of the user.
  • Page 132 P2010tdi – Aircraft Flight Manual Page 4 - 22 4.10. Descent Thrust Lever……………………..……….. As required 4.11. Before Landing Electric fuel pump…...…………………. Fuel selector valve…………………...… Select the fullest tank Landing Light…………...…………….… On downwind, leg abeam touch down point Flaps……………………...……………... Set T/O (below 100 KIAS,...
  • Page 133 P2010tdi – Aircraft Flight Manual Page 4 - 23 4.13. Landing Thrust Lever……………………………………... IDLE at touchdown Brakes……………………………………………. Apply Flaps……………………………………………… Electric Fuel Pump……………………………… Pitot Heat………………………………………… OFF (if ON) External lights……………………….…………... As required Transponder…………………………………….. As required 4.14. Engine Shutdown Parking brake………………………………….. Thrust Lever……………………………………...
  • Page 134 P2010tdi – Aircraft Flight Manual Page 4 - 24 4.15. Post-flight checks Wheel chocks and wing mooring lines…….. Parking brake………………………………... Release Doors…………………………………………. Close and Lock Protection covers………………………….. Install Edition - Rev. 0 Section 4 – NORMAL PROCEDURES CHECKLISTS...

  • Page 135: Section 5 Performance

    P2010tdi – Aircraft Flight Manual Page 5 - 0 SECTION 5 PERFORMANCE Edition - Rev. 0 Section 5 - PERFORMANCE...
  • Page 137 P2010tdi – Aircraft Flight Manual Page 5 - 1 INDEX INTRODUCTION ..................3 USE OF PERFORMANCE CHARTS ............3 DEMONSTRATED OPERATING TEMPERATURE ........3 GRADIENT / RATE (FT/MIN) OF CLIMB / DESCENT .......4 AIRSPEED INDICATOR SYSTEM CALIBRATION ........5 ICAO STANDARD ATMOSPHERE ............6 STALL SPEED ...................7 CROSSWIND .....................8...
  • Page 138 P2010tdi – Aircraft Flight Manual Page 5 - 2 Intentionally left blank Edition - Rev. 0 Section 5 – PERFORMANCE INDEX...
  • Page 139 P2010tdi – Aircraft Flight Manual Page 5 - 3 Introduction This section provides all necessary data for an accurate and comprehensive planning of flight activity from take-off to landing. Data reported in graphs and/or in tables were determined using: “Flight Test Data” under conditions prescribed by EASA CS-23...
  • Page 140 P2010tdi – Aircraft Flight Manual Page 5 - 4 Gradient / Rate (ft/min) of climb / descent GRADIENT GROUND SPEED (kts) DEG ft/NM 1001 1057 1031 1092 1152 1051 1117 1182 1248 1061 1131 1202 1273 1344 1060 1136 1212...
  • Page 141 P2010tdi – Aircraft Flight Manual Page 5 - 5 Airspeed Indicator System Calibration Indicated airspeeds provided in this flight manual assume zero instrument error for all flap configurations. Normal Static Source Graph shows calibrated airspeed V as a function of indicated airspeed V .
  • Page 142 P2010tdi – Aircraft Flight Manual Page 5 - 6 ICAO Standard Atmosphere Figure 5-1 - ICAO Chart Examples: Scope Given Find Density A: Pressure altitude = 1600ft → C: Density Altitude = 2550ft Altitude: B: Temperature = 20°C → E: ISA Air Temperature = 12°C...

  • Page 143: Stall Speed

    P2010tdi – Aircraft Flight Manual Page 5 - 7 Stall Speed Weight: 1160 kg (2557 lb) Thrust Lever: IDLE CG: Most Forward (23%) TALL PEED EIGHT 0° NGLE LAPS LAPS LAPS [kg] [deg] KIAS KCAS KIAS KCAS KIAS KCAS ([lb])
  • Page 144 P2010tdi – Aircraft Flight Manual Page 5 - 8 Crosswind Maximum demonstrated crosswind is 17 kts.  Example: Given Find Wind direction (with respect to aircraft Headwind = 17.5 kts longitudinal axis) = 30° Wind speed = 20 kts Crosswind = 10 kts Figure 5-2 - Crosswind Chart Edition - Rev.

  • Page 145: Take-Off Performance

    P2010tdi – Aircraft Flight Manual Page 5 - 9 Take-Off Performance Corrections Weight = 1160 kg (2557 lbs) Flaps: Take-off Headwind: - 10 m (33 ft) for each kts Thrust lever: MTOP/2300 RPM Tailwind: +20 m (66 ft) for each kts...
  • Page 146 P2010tdi – Aircraft Flight Manual Page 5 - 10 Corrections Weight = 1200 kg (2645 lbs) (*) Flaps: Take-off Headwind: - 10 m (33 ft) for each kts Thrust lever: MTOP/2300 RPM Tailwind: +20 m (66 ft) for each kts...

  • Page 147: Take-Off Rate Of Climb

    P2010tdi – Aircraft Flight Manual Page 5 - 11 10. Take-Off Rate of Climb Thrust lever: MCP/2250 RPM Flaps: Take-off Vy=67 kts (IAS) Rate of Climb [ft/min] Pressure Weight Temperature [°C/°F] Altitude [kg/lbs] [ft] -25/-13 -15/5 0/32 15/59 30/86 50/122...
  • Page 148 P2010tdi – Aircraft Flight Manual Page 5 - 12 Thrust lever: MCP/2250 RPM Flaps: Take-off Vy=67 kts (IAS) Rate of Climb [ft/min] Pressure Weight Temperature [°C/°F] Altitude [kg/lbs] [ft] -25/-13 -15/5 0/32 15/59 30/86 50/122 2000 4000 6000 8000 1200 /...

  • Page 149: En-Route Rate Of Climb

    P2010tdi – Aircraft Flight Manual Page 5 - 13 11. En-Route Rate of Climb Thrust Lever: MCP/2250 RPM Flaps: UP Vy=79 kts (IAS) Rate of Climb [ft/min] Pressure Weight Temperature [°C/°F] Altitude [kg/lbs] [ft] -25/-13 -15/5 0/32 15/59 30/86 50/122...
  • Page 150 P2010tdi – Aircraft Flight Manual Page 5 - 14 Thrust Lever: MCP/2250 RPM Flaps: UP Vy=79 kts (IAS) Rate of Climb [ft/min] Pressure Weight Temperature [°C/°F] Altitude [kg/lbs] [ft] -25/-13 -15/5 0/32 15/59 30/86 50/122 2000 4000 6000 8000 1200 /...

  • Page 151: Cruise Performance

    P2010tdi – Aircraft Flight Manual Page 5 - 15 12. Cruise Performance MTOW ISA-30°C ISA+30°C Pressure altitude: 0 feet F.C. [ktas] [ktas] [ktas] [l/h]/ [USg/h] 33 / 8.7 26 / 6.8 22 / 5.8 18 / 4.7 MTOW ISA-30°C ISA+30°C Pressure altitude: 5000 feet F.C.

  • Page 152: Landing Performance

    P2010tdi – Aircraft Flight Manual Page 5 - 16 13. Landing Performance Weight = 1160 kg (2557 lbs) Corrections Flaps: Landing Headwind: - 4 m (-13 ft) for each kts Thrust lever: Idle Tailwind: +13 m (+43 ft) for each kts...
  • Page 153 P2010tdi – Aircraft Flight Manual Page 5 - 17 Weight = 1200 kg (2645 lbs) (*) Corrections Flaps: Landing Headwind: - 4 m (-13 ft) for each kts Thrust lever: Idle Tailwind: +13 m (+43 ft) for each kts = 66 kts (IAS)
  • Page 154 P2010tdi – Aircraft Flight Manual Page 5 - 18 14. Balked Landing Performance Thrust Lever: Full Forward Flaps: LAND =65 kts (IAS) Steady Gradient of Climb [%] Pressure Weight Temperature [°C/°F] Altitude [kg/lbs] [ft] -25/-13 -15/5 0/32 15/59 30/86 50/122...
  • Page 155 P2010tdi – Aircraft Flight Manual Page 5 - 19 Thrust Lever: Full Forward Flaps: LAND =66 kts (IAS) Steady Gradient of Climb [%] Pressure Weight Temperature [°C/°F] Altitude [kg/lbs] [ft] -25/-13 -15/5 0/32 15/59 30/86 50/122 2000 4000 1200 /...

  • Page 156: Oxygen System

    P2010tdi – Aircraft Flight Manual Page 5 - 20 15. Oxygen System XYGEN FLOW DURATION PER ALTITUDE AND PER USERS WITH MAXIMUM (165 CYLINDER CAPACITY LITERS Altitude 1 user time 2 user time 3 user time 4 user time [ft]...
  • Page 157 P2010tdi – Aircraft Flight Manual Page 5 - 21 Capacity 2218 Full tank 1680 1140 Middle tank Empty MH-4 XYGEN FLOW RATE WITH FLUXOMETER Edition - Rev. 0 Section 5 – PERFORMANCE OXYGEN SYSTEM...

  • Page 158: Noise Data

    P2010tdi – Aircraft Flight Manual Page 5 - 22 16. Noise Data Noise level, determined in accordance with ICAO/Annex 16 6 Ed., July 2011, Vol. I°, Chapter 10 and 14 CFR Part 36, is 74.85 dB(A). For A/C embodying MOD2010/207, Noise level, determined in accordance with ICAO/Annex 16 6 Ed., July 2011, Vol.

  • Page 159: Section 6 Weight And Balance

    P2010tdi – Aircraft Flight Manual Page 6 - 0 SECTION 6 WEIGHT AND BALANCE Edition - Rev. 0 Section 6 – WEIGHT AND BALANCE...
  • Page 161 P2010tdi – Aircraft Flight Manual Page 6 - 1 INDEX INTRODUCTION ..................3 WEIGHING PROCEDURES ...............4 2.1. PREPARATION ................4 2.2. LEVELLING ..................4 2.3. WEIGHING ..................4 2.4. DETERMINATION OF C.G. LOCATION ...........4 2.5. Weighing Record ................5 2.6. Weighing Record (II) .................6 WEIGHT AND BALANCE DETERMINATION FOR FLIGHT ......7 BAGGAGE LOADING ................
  • Page 162 P2010tdi – Aircraft Flight Manual Page 6 - 2 Intentionally left blank Edition - Rev. 0 Section 6 – WEIGHT AND BALANCE INDEX...
  • Page 163 P2010tdi – Aircraft Flight Manual Page 6 - 3 Introduction This section describes the procedure for establishing the basic empty weight and the moment of the aircraft. Loading procedure information is also provided. Aircraft must be operated in accordance with the limits concerning the maximum take-off weight and CG excursion as re- ported in Flight Manual Section 2.

  • Page 164: Determination Of C.g. Location

    P2010tdi – Aircraft Flight Manual Page 6 - 4 Weighing Procedures 2.1. PREPARATION Carry out weighing procedure inside closed hangar Remove from cabin any object unintentionally left Make sure Flight Manual and mandatory documents are on board Align nose wheel...

  • Page 165: Weighing Procedures

    P2010tdi – Aircraft Flight Manual Page 6 - 5 2.5. Weighing Record P2010TDI ���� = ���� ( %������������ ) = ∙ 100 = ______ ���� 2 ∙A−���� 1 ∙���� ����−0.013 �������� 1.378 = _____ ���� = ���� ( %������������ ) = ∙...
  • Page 166 P2010tdi – Aircraft Flight Manual Page 6 - 6 2.6. Weighing Record (II) P2010TDI ���� = ���� ( %������������ ) = ∙ 100 = ______ ���� 2 ∙A−���� 1 ∙���� ����−0.013 �������� 1.378 = _____ ���� = ���� ( %������������ ) = ∙...
  • Page 167 P2010tdi – Aircraft Flight Manual Page 6 - 7 Weight and Balance determination for flight The pilot is responsible for ensuring the correct useful load loading. In this subsection, the procedure to be used for the determination of aircraft weight and balance in flight is described.
  • Page 168 P2010tdi – Aircraft Flight Manual Page 6 - 8 Table 6-1 - Weight and C.G. – Form Moment (M) = [kg] or (lb) [m] or (ft) W * Arm [kg*m] or (lb*ft) Empty weight USEFUL LOAD 0.293 (0,96 ft) Pilot 0.293 (0,96 ft)
  • Page 169 P2010tdi – Aircraft Flight Manual Page 6 - 9 Table 6-2 - Weight and C.G. – Example Moment (M) = [kg] or (lb) [m] or (ft) W * Arm [kg*m] or (lb*ft) Empty weight 765 (1687 lb) 0.245 (0,80 ft) 187.4 (1350 lb*ft)
  • Page 170 P2010tdi – Aircraft Flight Manual Page 6 - 10 Figure 6-3 - Loading Diagram Edition - Rev. 1 Section 6 – WEIGHT AND BALANCE WEIGHING AND BALANCE DETERMINATION FOR FLIGHT...
  • Page 171 P2010tdi – Aircraft Flight Manual Page 6 - 11 Figure 6-4 – Weight Moment Envelope Edition - Rev. 1 Section 6 – WEIGHT AND BALANCE WEIGHING AND BALANCE DETERMINATION FOR FLIGHT...
  • Page 172 P2010tdi – Aircraft Flight Manual Page 6 - 12 Baggage Loading The baggage loading in the dedicated compartments must be carried out in accordance with diagram addressed and with C.G. excursion and weight limitations reported in Section 2. Pilot is provided with tie-down nets and snap fasteners allowing for securing the loads.
  • Page 173 This paragraph contains a list of equipment which may be installed on TECNAM P2010tdi. The items that have been installed on the aircraft at the time of its registration are marked with an “X” in the column “As deliv.”. It is an operator’s responsibility made on the airplane.

  • Page 174: Baggage Loading

    P2010tdi – Aircraft Flight Manual Page 6 - 14 Weight (each) Inst. / Rem. Description Model/PN deliv. (I/R) & Date [kg] [lbs] [ft] ATA 22 – Auto Flight 17.4 22-10-1 Servo Pitch GSA 80 011-00877-20 1.44 3.17 3.17 2.05 6.73...
  • Page 175 P2010tdi – Aircraft Flight Manual Page 6 - 15 Weight (each) Inst. / Rem. Description Model/PN deliv. (I/R) & Date [kg] [lbs] [ft] ATA 31 – Indicating / Reporting Systems 31-20-1 Compass C2400L4P or 0.88 -0.69 -2.26 C2400L4P-SF 31-40-1 COM/NAV/GPS Garmin GIA 64W 7.19...
  • Page 176 P2010tdi – Aircraft Flight Manual Page 6 - 16 Weight (each) Inst. / Rem. Description Model/PN deliv. (I/R) & Date [kg] [lbs] [ft] Becker Avionics RA -0.69 -2.26 3502 0505.757-912 ADF System 34-50-1 Becker Avionics RA (Receiver Controller) 3502 (02) 0506.133-912...

  • Page 177: Section 7 Airframe And System Description

    P2010tdi – Aircraft Flight Manual Page 7 - 0 SECTION 7 AIRFRAME AND SYSTEM DESCRIPTION Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION...
  • Page 179 P2010tdi – Aircraft Flight Manual Page 7 - 1 INDEX INTRODUCTION ...................3 AIRFRAME ....................3 2.1. Wing ....................3 2.2. Fuselage ...................4 2.3. Empennages ..................4 2.3.1. Horizontal Tail ................4 2.3.2. Rudder Surface ................5 2.4. Main Landing Gear ................6 2.5. Nose Landing Gear ................8 FLIGHT CONTROLS ................9...
  • Page 180 P2010tdi – Aircraft Flight Manual Page 7 - 2 10.1.1. GDU 1050/GDU 1054 (PFD/MFD) ..........31 10.1.2. GMA 1360 (Audio Panel) ............34 10.1.3. GIA 64W (IAU Integrated Avionics Unit) ........35 10.1.4. GDC 72 (Air Data Computer) ............35 10.1.5.
  • Page 181 P2010tdi – Aircraft Flight Manual Page 7 - 3 NTRODUCTION This section provides description and operation of the its system IRFRAME P2010tdi’s airframe can be divided in the following main groups: Wing Fuselage Empennage Landing gear 2.1. W Each wing is connected to the fuselage by means of two bolt attachments and a single strut brace per side.
  • Page 182 2.2. F USELAGE The P2010tdi fuselage is mainly made by carbon fibres composite materials. The fuselage is made by two main shells that are later assembled bonding the two main bodies and the floor (composite) and adding aluminium parts that allow the connection of the main landing gear, seats, wing and instrument panel.
  • Page 183 P2010tdi – Aircraft Flight Manual Page 7 - 5 2.3.2. R UDDER URFACE The rudder structure is made-up by a single aluminium spar (1) and ribs (2). Aluminium skin panels (3) are riveted to the above elements. It is connected to the fin through two hinges;...

  • Page 184: Main Landing Gear

    Wheels are cantilevered on gear struts and feature hydraulically actuated disc brakes controlled by toe. Main gear wheels install type 6.00-6 tyres. P2010tdi is provided with an independent hydraulically actuated brake system for each main wheel. A master cylinder is attached to each pilot’s rudder pedal.
  • Page 185 P2010tdi – Aircraft Flight Manual Page 7 - 7 Figure 7-4 - Rudder Pedals and Brake Master Cylinders (Pilot and Co-pilot Side) Figure 7-5 - Brake System Schematic Edition - Rev. 1 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION AIRFRAME...

  • Page 186: Nose Landing Gear

    P2010tdi – Aircraft Flight Manual Page 7 - 8 2.5. N ANDING A Pivoting nose gear is attached to the firewall reinforcement plate. The shock absorber is fitted on the upper machined component and directly on the nose landing gear structure.
  • Page 187 P2010tdi – Aircraft Flight Manual Page 7 - 9 LIGHT ONTROLS Aircraft flight controls are operated through control wheel and rudder pedals. Longitudinal control acts through a system of push-rods and is equipped with a trim tab. A cable control circuit is confined within the cabin and it is connected to a pair of push-pull rod systems positioned in each main wing which control ailerons differentially.

  • Page 188: Instrument Panel

    P2010tdi – Aircraft Flight Manual Page 7 - 10 NSTRUMENT ANEL The instrument panel is divided in three areas: • The left area holds Garmin G1000 Nxi phase III PFD, FADEC test button, Engine Starter and FADEC switches; • The Central area holds the standby unit MD 302 suite, audio panel and the ELT button;...
  • Page 189 P2010tdi – Aircraft Flight Manual Page 7 - 11 Figure 7-7 - Instrument Panel 4.1. E NGINE CONTROL LEVER Engine handling is via one lever: Thrust Lever. It is situated on the centre control and it is used to control power and RPM.
  • Page 190 P2010tdi – Aircraft Flight Manual Page 7 - 12 For aircraft embodying MOD2010/257 the two knobs are replaced by a single rotating knob with which is possible to regulate the intensity of hot air, indeed is not provided a mechanism for the partition of air between defrost and cabin heat.

  • Page 191: Seats And Safety Harness

    P2010tdi – Aircraft Flight Manual Page 7 - 13 EATS AND SAFETY HARNESS In correspondence of the seats, three fitting points safety belts are provided; belt adjustment is via the sliding buckle located on the belt metal hook. Seats are built with light alloy tube structure and synthetic material cushioning. It is possible to perform following seat adjustments: Horizontal –...
  • Page 192 P2010tdi – Aircraft Flight Manual Page 7 - 14 OORS P2010tdi features three doors. The main door is placed on the left side of the cabin, while on the right side there are two secondary doors, one on the front side and the other on the rear, used as an emergency exit.
  • Page 193 P2010tdi – Aircraft Flight Manual Page 7 - 15 The internal handle can be locked, to avoid any chance of inadvertent opening, by means of a hook located nearby the handle itself and upper safety block, following pictures show the functioning.

  • Page 194: Power Plant

    P2010tdi – Aircraft Flight Manual Page 7 - 16 OWERPLANT 7.1. E NGINE The CD-170 is an engine build by: Continental Aerospace Technologies GMBH Platanenstr. 14 09356 St. Egidien Germany The CD-170 (TAE 125 series) is a liquid-cooled 4-cylinder in-line four-stroke diesel engine with DOHC (double overhead camshaft).
  • Page 195 P2010tdi – Aircraft Flight Manual Page 7 - 17 7.2. P ROPELLER The engine is equipped with a MT propeller MTV-6-R/190-69 manufactured. It is a three blade constant speed variable pitch propeller. Blades are made of laminated wood composite structure. Epoxy fiberglass covers the entire blade surface and it is painted with acryl lacquer.
  • Page 196 P2010tdi – Aircraft Flight Manual Page 7 - 18 7.3. G EARBOX OIL SYSTEM The gearbox oil system is a wet oil sump system. Gearbox oil is used for lubrication and cooling of the gearbox and for operation of the propeller regulation by the Constant Speed Unit.

  • Page 197: Fuel System

    P2010tdi – Aircraft Flight Manual Page 7 - 19 UEL SYSTEM The P2010tdi fuel system provides to the following function: fuel storage, fuel distribution and fuel indicating, Figure 7-12. Fuel system and relative components are designed in accordance to Continental motors specification and requirements.
  • Page 198 P2010tdi – Aircraft Flight Manual Page 7 - 20 Figure 7-12 - Fuel System Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION FUEL SYSTEM...
  • Page 199 Figure 7-13 - Fuel selector valve control location The fuel approved and tested by Tecnam for feeding the CD-170 engine are Jet A- 1 or Diesel EN590. Edition - Rev. 0...

  • Page 200: Electrical System

    The Main battery installed is a lead type 12 cells battery. The MAIN battery is used to start the engine and to power the units when the P2010TDI A/C is on the ground while the engine and therefore the alternator are switched off.
  • Page 201 P2010tdi – Aircraft Flight Manual Page 7 - 23 The electric system is composed of three distribution busses: • Essential bus; • Main bus; • Avionic bus. A dedicated switch, named Avionic Master Switch, allow the selection of active/inactive Avionic bus, Figure 7-15.
  • Page 202 P2010tdi – Aircraft Flight Manual Page 7 - 24 Figure 7-14 - Electric System 9.1. S TALL ARNING YSTEM The aircraft is equipped with a stall warning system consisting of a sensor located on the right wing leading edge connected to a warning horn located near the instrument panel.
  • Page 203 P2010tdi – Aircraft Flight Manual Page 7 - 25 9.2. M ASTER SWITCH ARRANGEMENT The master switches group is located in the lower left area. The “Master” switch is put in the ON position it enables the master relay and connects the battery to the bus Bar.
  • Page 204 P2010tdi – Aircraft Flight Manual Page 7 - 26 9.3. E XTERNAL OWER UPPLY An external power socket, Military Standard P/N MS3506-1 provided by Adams Aviation, is installed in order to allow engine starting and the possibility of feeding electric system during ground operations without depleting the batteries. The external power plug is made in such a way that the polarity cannot be inadvertently reversed and is located near Main Battery.
  • Page 205 9.4. I GNITION CONTROL PANEL In the P2010tdi A/C there is a Fadec Unit (Full Authority Digital Engine) located in the central pedestal under Thrust Lever compartment; this Fadec unit is enabled by means of “Engine Master” switch located in the upper left side of cockpit panel.
  • Page 206 VIONIC YSTEM P2010tdi avionic suite is based on G1000 Nxi. Garmin G1000 Nxi suite is an integrated flight deck whose modular layout allows to extend it in order to add new features. It provides the pilot with primary flight information, presenting navigation moving map and engine parameters.
  • Page 207 P2010tdi – Aircraft Flight Manual Page 7 - 29 The installed configuration is based on a two-screens layout. Primary flight information are displayed on the LH screen, namely PFD (Primary Flight Display). Primary Engine and moving map information are displayed on the RH display, namely MFD (Multi-Function Display).
  • Page 208 P2010tdi – Aircraft Flight Manual Page 7 - 30 Additional items that may be installed as optional equipment at customer request are listed in table below. Table 7-4 – Optional equipment LRU Model Description Type Qty. KN 63 Remote RA-3502/AC-3504...
  • Page 209 10.1.1. GDU 1050/GDU 1054 (PFD/MFD) GDU 1050/1054 units display flight and engine parameters and moving map information and act as the user interface for P2010tdi avionics suite. GDU 1050 units placed on instrument panel LH side are identified as Primary Flight Display (PFD), while GDU 1054 placed on instrument panel RH side are identified as Multifunction Display (MFD).
  • Page 210 P2010tdi – Aircraft Flight Manual Page 7 - 32 This feature provides the pilot with an automatic dimming of both display and keys in accordance with the lighting conditions sensed by the two external light sensors positioned in the upper right and lower left corners of each display. Furthermore, the pilot can easily access a manual dimming mode for both displays and keys.
  • Page 211 P2010tdi – Aircraft Flight Manual Page 7 - 33 GDU 1054 provides the following functions: Flight instruments functions (Reversionary mode only) Display of attitude (pitch and roll) rate of turn, slip/skid, directional, airspeed, altitude and vertical speed; display of Outside Air...
  • Page 212 P2010tdi – Aircraft Flight Manual Page 7 - 34 10.1.2. GMA 1360 (A UDIO ANEL The Garmin GMA1360 is a vertically oriented panel mounted audio control and marker beacon system. The system delivers reliability and versatility for all audio controlling functions. LED-illuminated push-buttons and logical panel layout allow audio selection of NAV, COM, DME, ADF, MKR, TEL, AUX and automatic warning audio in voice or tone annunciation.
  • Page 213 GIA 64W unit is a microprocessor-based unit linked to GDU 1050 via Ethernet High speed Data Bus (HSDB). P2010tdi is equipped with two GIA 64W units, each one connected to a GDU 1050 unit through a HSDB link. Each GIA 64W is interfaced with the following antennas: GPS antenna;...
  • Page 214 P2010tdi – Aircraft Flight Manual Page 7 - 36 10.1.5. GTP 59 (T EMPERATURE PROBE The Garmin GTP 59 is an outside mounted temperature probe that provides raw air temperature data. One GTP are installed, interfaced with the GDC 72, and provide them with temperature data in order to allow the evaluation of temperature influenced air data parameters.
  • Page 215 P2010tdi – Aircraft Flight Manual Page 7 - 37 10.1.8. GEA 71B (E NGINE IRFRAME NTERFACE The GEA 71B is a microprocessor based input/output Line Replaceable Unit (LRU) used to monitor sensor inputs and drive annunciator outputs for aircraft engine systems. It interfaces with all engine sensors on the aircraft and communicates engine information via RS-485 digital interface to both GIA 64W Integrated Avionics Units.
  • Page 216 P2010tdi – Aircraft Flight Manual Page 7 - 38 10.1.10. F LIGHT TREAM IRELESS VIONICS NTERFACE (MOD2010/206) The Flight Stream 510 Wireless Avionics Interface allows the connection of a compatible mobile electronic device to the avionics. The Flight Stream 510 utilizes a Bluetooth connection for pairing up to 4 devices as well as a WI-FI connection for wireless database transfer.

  • Page 217: Autopilot System

    11. A UTOPILOT YSTEM P2010tdi aircraft is equipped, as an optional equipment, with an integrated 2-axis autopilot suite manufactured by Garmin and identified as GFC 700. This autopilot suite was designed as an option for the G1000Nxi integrated flight deck. The autopilot is controlled via dedicated keys grouped in a control panel located on the MFD.
  • Page 218 P2010tdi – Aircraft Flight Manual Page 7 - 40 Figure 7-24 – Avionic Scheme with Auto-pilot The multifunction display (MFD) provides the pilot with a dedicated set of keys for autopilot control (see red frame in the below picture). The roll servo is located under the pilot seat and is fixed to a/c structure using a dedicated mount.
  • Page 219 P2010tdi – Aircraft Flight Manual Page 7 - 41 11.1. A UTOPILOT ONTROL ANEL The GDU1054 includes a set of additional soft-keys dedicated to the control of Autopilot system. The following dedicated AFCS keys are located on the bezel of the MFD (refer...
  • Page 220 P2010tdi – Aircraft Flight Manual Page 7 - 42 11.2. P ILOT CONTROL WHEEL AND THROTTLE BUTTONS On the left side of pilot’s and copilot’s control wheels there are two PTT switches (the one on pilot control wheel is shown below as (1)) that, when pushed, allow radio transmission.
  • Page 221 P2010tdi – Aircraft Flight Manual Page 7 - 43 The above mentioned AFCS controls are depicted in the below figures. where: PTT switch AP DISC Switch AP Trim Switch CWS Button Figure 7-26 – Autopilot Control Wheel Switches/Buttons Edition - Rev. 0...
  • Page 222 P2010tdi – Aircraft Flight Manual Page 7 - 44 11.3. A UTOPILOT UNCTIONS AND EATURES GFC 700 autopilot suite is deeply integrated with Garmin G1000Nxi avionics suite which integrates both the a/p controls and the sensors providing the required data to the servos.
  • Page 223 P2010tdi – Aircraft Flight Manual Page 7 - 45 11.3.1 ESP Garmin GFC 700 is equipped with an envelope protection feature referred as ESP (Electronic Stability & Protection). Electronic Stability and Protection continuously monitors the aircraft. The system works by applying a correcting force to the controls in order to nudge pilot to avoid extreme attitudes that may bring the aircraft, if not corrected, to exceed normal flying envelope.
  • Page 224 P2010tdi – Aircraft Flight Manual Page 7 - 46 To enable or disable ESP: Turn the large FMS Knob to select the AUX Page Group. Turn the small FMS Knob to select the System Setup Page. If necessary, select the SETUP 2 Softkey to display the AUX-SYSTEM SETUP 2 Page.
  • Page 225 P2010tdi – Aircraft Flight Manual Page 7 - 47 11.3.1.1 Pitch Mode Pitch attitude boundaries are set based on P2010tdi aircraft performances. Since pitch ESP augments the natural aircraft longitudinal stability, no special simbology is required. Value that have been set-up for the P2010 are as follows: Nose above the horizon: Engagement low threshold: + 15°...
  • Page 226 P2010tdi – Aircraft Flight Manual Page 7 - 48 11.3.1.2 Roll Mode Roll mode is similar to pitch mode and also utilizes configurable gain file parameters to define engagement and disengagement limits as well as the speed and torque curves.
  • Page 227 P2010tdi – Aircraft Flight Manual Page 7 - 49 When ESP is inactive (roll attitude within nominal limits) only the engagement limits are displayed in order to reduce clutter on the roll indicator. As the bank angle is increased, a region of an increasing force as a function of bank angle is entered.
  • Page 228 P2010tdi – Aircraft Flight Manual Page 7 - 50 11.3.2 USP Underspeed Protection (USP) is a flight director function that reacts to underspeed conditions, designed to discourage aircraft operation below minimum established airspeeds. USP has to be intended as a feature that will work to...
  • Page 229 P2010tdi – Aircraft Flight Manual Page 7 - 51 How Underspeed Protection functions depends on which vertical flight director mode is selected. For the purpose of this discussion, the vertical flight director modes can be divided into two categories: It is important to maintain altitude for as long as possible (altitude-critical modes).
  • Page 230 P2010tdi – Aircraft Flight Manual Page 7 - 52 11.3.2.1 Altitude critical modes (ALT, GS, GP, TO, GA) This mode allows the airplane to slow as much as possible but still protect against a stall as USP is triggered by stall warning. In these modes when stall protection is triggered, the airplane responds more abruptly and aggressively attempts to minimize flight path deviation while preventing a stall.
  • Page 231 P2010tdi – Aircraft Flight Manual Page 7 - 53 11.3.2.2 Non Altitude critical modes (VS, VNAV, PIT, LVL, FLC) USP in these modes is triggered by airspeed and is just a transition from following the selected reference to following a minimum airspeed. This provides for smooth transition to USP and also can provide a larger stall protection margin.
  • Page 232 P2010tdi – Aircraft Flight Manual Page 7 - 54 Another mode related to USP is the coupled go-around. This mode allows the pilot to perform coupled missed approaches by pressing a button located on the throttle lever. With this feature, the AP will remain engaged and fly the missed approach attempting to capture and track the Flight Director command bars (6°...

  • Page 233: Pitot-Static Pressure System

    ITOT STATIC PRESSURE SYSTEMS The P2010tdi airspeed/altitude indicating systems are connected with a Pitot-Static system based on a total pressure/Pitot probe (simple Pitot tube, heated for icing protection) mounted on left wing strut and two static pressure ports connected in parallel and located in correspondence of engine firewall on left and right side of fuselage.
  • Page 234 Page 7 - 56 13. L IGHTS 13.1. E XTERNAL LIGHTS P2010tdi is equipped with the following external lights: • 2 combined LED NAV/POS/Strobe integrated lights located on RH and LH wing; • 1 POS/strobe combined light located on the rear (fixed on the rudder);...

  • Page 235: Oxygen System

    P2010tdi – Aircraft Flight Manual Page 7 - 57 14. O XYGEN YSTEM The oxygen system is composed by a cylinder AL-180, a regulator for the inlet of up to 4 lines with cannulas or mask (one for each cabin occupant). Each line presents a flowmeter for the monitoring and the adjustment of oxygen flow.
  • Page 236 P2010tdi – Aircraft Flight Manual Page 7 - 58 The cylinder specification are shown in the following table. Cylinder Maximum Maximum Diameter Length Empty Model Cylinder Cylinder [in]/[cm] [in]/[cm] Weight Number Pressure Capacity [lb]/[kg]] [psi] [Cu.Ft.]/[lt] AL-180 2216 5.8/165 3.2/8.1 11.8/30...
  • Page 237 P2010tdi – Aircraft Flight Manual Page 7 - 59 14.1. U SE OF CANNULAS The cannula can be readily placed into position on the face of the user through the following passages: Slide the loop adjustment collar (bola) down to...
  • Page 238 P2010tdi – Aircraft Flight Manual Page 7 - 60 14.2. U SE OF MASK The mask allows the pilot to use both the installed dispending unit and radio equipment. The mask presents a connector, that is fixed by lining up the two pins on the cable connector to the receptacle on the mask and pushing in.
  • Page 239 P2010tdi – Aircraft Flight Manual Page 7 - 61 15. P LACARDS Here in the overview of the placard installed on the aircraft in addition to the limitation placards reported in Section 2. Additionally, nearby the placards listed below (English...
  • Page 240 P2010tdi – Aircraft Flight Manual Page 7 - 62 External placards Aircraft Registration Placard: Baggage compartment placards: Edition - Rev. 3 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 241 P2010tdi – Aircraft Flight Manual Page 7 - 63 Static Port: Lift Point: Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 242 P2010tdi – Aircraft Flight Manual Page 7 - 64 Wheel Fairing “No Step”: Allowed Fuel Placard: Tire Pressure placard: Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 243 P2010tdi – Aircraft Flight Manual Page 7 - 65 Stabilator degrees placard: Emergency exit placards: Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 244 P2010tdi – Aircraft Flight Manual Page 7 - 66 15.1. INTERNAL PLACARD Safety equipment placards: Edition - Rev. 3 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 245 P2010tdi – Aircraft Flight Manual Page 7 - 67 ELT unit position placard: Breaker Panel placards: Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 246 P2010tdi – Aircraft Flight Manual Page 7 - 68 Magnetic Compass placard: Battery Placard: (installed on the LH side of fuselage cone) Edition - Rev. 3 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 247 P2010tdi – Aircraft Flight Manual Page 7 - 69 Engine Oil filler placard: Gearbox Oil level check placard: Coolant tank placard: Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 248 P2010tdi – Aircraft Flight Manual Page 7 - 70 Emergency exit placards: Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 249 P2010tdi – Aircraft Flight Manual Page 7 - 71 Baggage Door opening knob: Edition - Rev. 1 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 250 P2010tdi – Aircraft Flight Manual Page 7 - 72 Pedestal placards: Edition - Rev. 0 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 251 P2010tdi – Aircraft Flight Manual Page 7 - 73 Cabin air system (instrument panel)*: *) for aircraft NOT embodying MOD2010/257 Power lever placard: Edition - Rev. 3 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...
  • Page 252 P2010tdi – Aircraft Flight Manual Page 7 - 74 Fuel selector control knob: Edition - Rev. 3 Section 7 - AIRFRAME AND SYSTEMS DESCRIPTION PLACARDS...

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