TECNAM P2010 TDI - Aircraft Flight Manual

the Caution Softkey. Pressing the Caution Softkey acknowledges all amber messages and extinguishes the softkey. Once acknowledged, caution messages are displayed until the issue is corrected. Safe Operating Advisory. This level of alert indicates crew awareness is required. It is shown in green text in the Annundation Window. System Message Advisory. This level of alert provides general Information to the pilot. Message Advisories appear in the Alerts Window and are not shown in the Annunciation Window. When a Message Advisory occurs, the System provides a white flashing Messages Softkey annunciätion. Pressing the softkey acknowledges the message advisory alert, and displays the associated text in the Alerts Window. ANNUNCIATION WINDOW SOFTKEY ANNUNCIATION Figure 3-2 - Annunciation Windows "Wärhihg Caution Figure 3-3 - Warning and Caution Softkey Annunclations 2"f Edition -Rev. 0 Section 3 - EMERGENCY PROCEDURES INTRODUCTION FT SihCE ms «^^»^k^^dB" A" ^ ^ > • TECNÄM P2010tdi-AircraftFlight Manual pages 7 16 17 18 19 20 21 22 23 24 25 26 27* 28* 29* Fuel Fuel Fuel Fuel Fuel Fuel Fuel Oil Oil Pitot Pitot Battery Battery Battery LH FUEL QTYLOW RH FUEL QTY LOW FUEL FLTR CLGD BATT MAIN FAULT LH FUEL LOW LH FUEL LOW RH-LH FUEL QTYLOW FUEL PUMP ON LHFUELTEMP LOW RH FUEL TEMP LOW FUEL FILTER CLOGGED OIL PRESS LOW OIL TEMP HIGH PITOT HEAT PITOT HEAT ON MAIN BATTERY FAIL MAIN BATTERY FAULT MAIN BATTERY RECHARGES Low fuel quantity detected Low fuel quantity detected LH and RH FUEL QTY LOW both ON Fuel pump operative LH FUEL TEMP S-31 RH FUEL TEMP S-31 Filter pressure drop out of operative limit OIL PRESS s 0.9 bar OILTEMPS121 °C Pitot Heat OFF or FAIL Pitot heater operative Main Battery Failure Main Battery Fault Main Battery Charging *) applicable foraircraft embodying MOD2010/267 y" Edition - Rev. 5 Section 3 - EMERGENCY PROCEDURES INTRODUCTION QUAUTTfAWCRAHSiNCEWS r^^^^^< •- • • r< ^i- WTECNÄM P2010tdi - Aircraft Flight Manual pages 9 2.2. Loss of Essential Bus 1. Land äs soon äs practical In case ofloss ofessential bus, the following equipmentwill be lost: Table 3-2 - Loss of Essential Bus AHRS LANDING LIGHT ADC FIELD PITOT HEAT COM#1 EIS (Garmin Engine Interface Unit) FUELPUMP STROBE LIGHT GPS/NAV#1 FLAP ACTUATOR FADEC B PFD STALL WARNING A The FADEC A, powered by Essential Bus in normal condition, continues to be powered by means of back-up batteryin case ofloss ofEssential Bus. When operating on FADEC backup battery only, the FADEC FORCE B mode MUST not be activated. This will shut down the engine. Change ormaintain flight conditions according to available equipment. •!\ CAUT10N !\ CAUTION 1\ Pilot will need to make reference to standby Instrument for primary flight Information and Parameters. Pilot will be able to use the audio panel and COM2/NA V2 via MFD. Engine and fuel Parameters and related warnings/cautions are lost. F/aps selection will be not available to the pilot. Perform visual check to determine actual position and refer to Flap Operating System Failure procedure. Strobe and landing lights will be lost, NAV and taxi lights are sft'// available. 2"" Edition - Rev. Section 3 - EMERGENCY PROCEDURES ELECTRICAL SYSTEM OUALfTT WHCRAFT SihCE *WB w^.^.^^^^»» • • ^- ^ • • ^Cj f^^^ p20l Otdi - Aircraft Flight Manual 2.5. Electrical System overall failure In case of electrical System overall failure, apply following procedure: 1. MasterSwitch................................. OFF 2. Generator Switch............................ OFF 3. Master Switch................................. 0/V 4. Generator Switch............................ ON Iffailure oersists, land äs soon äs oossible Page 3-11 If generator and main batteryare turned OFF, continued engine Operation is dependent on the remaining capacity ofthe FADEC backup battery. In this case, all electrical equipment will not operate, do not switch the FORCE-B switch, this will shut down the engine. 2.6. Battery failure* Main Battery failure OR BATT MAIN FAULT NOTE_| Light ON has to be intended äs permanently ON 1. Masterswitch ................................ OFF 2. Land äs soon äs possible *) applicable for aircraft embodying MOD2010/267 NOTE "l l.n.the event of an actual CAS message, the message will illuminate and will remain illuminated V Edition - Rev. B Section 3 - EMERGENCY PROCEDURES ELECTRICAL SYSTEM QUAUTTfAIflCRAfTSlHCEWO ^-k^^k ^ ^ < •• » - ^ r-» • [^TECNÄM P2010tdi - Aircraft Flight Manual pages 13 3.2. Static source malfunction 'HOTE l The altemate source valve is located on the left s/cte 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. Alternate static source...............................................OPEA/ 2. Cabin air System ......................................................... OFF Operation ofthe altemate static airrequires that the cabin air NOTE | system be switched off in ordernot to affect the air pressure measurement. 2"" Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES PITOT-STATIC SYSTEM QUAUTYAIRCRAFTSiMCeiM» n A A ^ »^ •- • • «^ »-• • WTECNÄM P2010tdi - Aircraft Flight Manual pages 15 4.3. Loss of attitude Information ATTITÜDE 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 ALTITUDE FAIL (red X on display field) Display System is not receiving altitude input from Air Data Computer. INSTRUCTION: revert to standby Instrument V Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES AVIONIC SYSTEM FAILURES OUAL17VAlRCR*FT5lhCE1W »^*»A ^ <k - •- • • »•< ^-• - WTECNAM P2010tdi - Aircraft Flight Manual pages 4.7. Display failure In the event of a display failure, the G1000 Nxi phase III System automatically switehes to reversionary (backup) mode. In reversionary mode, all important flight infonnation is presented on the remaining display in the same format äs in normal operating mode. The change to backup path is completely automated for all LRUs and no pilot action is required. If the svstem fails to detect a displav problem 1. REVERSIONARY MODE button PUSH REVERSIONARY MODE button is red and located on the bottom ofthe audio panel. Ifa display fails, the related Integrated Avionics Unit (IAU) is \ cut off and can no langer communicate with the remaining i \ display: subsequently the NAV and COM functions provided CAUTION to th?failed display by the associated Integrated A vionics Unit are flagged äs invalid on the remaining display. -17 2"i Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES AVIONIC SYSTEM FAILURES aUAUTYAfRCflAFTSlNCEWa n.^».^^^*»- • • ^•<r*B" ® TECNÄM P2010tdi - Aircraft Flight Manual Page 3-19 6. Aircraft Evacuation With the engine secured and propeller stopped: 1. Parking brakes.......................................... ENGAGED 2. SeatBelts................................................. UNSTRAP 3. Headphones.............................................. REMOVE 4. Doors......................................................... OPE/V 5. Masterswitch............................................ OFF 6. Escape away from flames/hot engine compartment/spilling fuel tanks/hot brakes 2"" Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES AIRCRAFT EVACUATION QUWJTVAJRCRAf-TSlhCE'W »»»»^A-«. . - ^- ^ • • [<Cj Y^^^ P2010tdi - Aircraft Flight Manual page 3 21 7.2. Engine Failure after Take-off LLenqine^faLls immediatelv after becoming airborne^ > Abort on the runway ifpossible. In case low altitude precludes a runway stop and/or engine restart: 1. Establish a glide attitude (VQUDE=79 kts) > Find a suitable place on the ground to land safely The landing should be planned straight ahead with only small changes in directions not exceeding 45° to the left and 45° to the right. CAUTION /\ny turn would reduce the glide performance. 2. Thrust Lever....................................... IDLE 3. Brakes............................................. As required With aircraft stopped 4. FuelSelectorvalve.............................. OFF 5. Electrical fuel pump............................. OFF 6. Engine Master.................................... OFF 7. Generators Master Switches................ OFF 8. Parking Brake..................................... ENGAGED 9. Aircraft Evacuation.............................. PERFORM ifnecessary 2"" Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES POWERPLANT aUAUT^AWCflAFTSIKCEWS —kA o.-• A - •• • - ^- ^•- [<C] 7.^^^' p201 Otdi - Aircraft Flight Manual page 3 - 23 7.4. Propeller Overspeed In case of propeller overspeeding, apply following procedure: 1. Thrust Lever.......................................... REDUCE power 2. Airspeed............................................... REDUCE to prevent propeller overspeed 3. RPMindicator........................................ CHECK If it is not possible to decrease propeller RPM, land äs soon äs possible applying Forced landing procedure. Maximum propeller RPM exceedance may cause engine components damage. • \ Apply caution while accelerating with power lever dose to CAUTION max 8nd inonitor RPM; RPM overspeed shall be prevented by retarding thrust lever. Forpropeller overspeeding up to 2500 RPM for maximum 20 sec., no maintenance action is required. Refer to engine/propeller manufacturer manuals. 2"'Edition -Rev. 0 Section 3 - EMERGENCY PROCEDURES POWERPLANT QUAUTrAIRCRATrSlHCEWa »^.^^.^^^ •• • • »•- —••, WTECNÄM P2010tdi-Aircraft Flight Manual page3-25 7.6. Coolant Level Limit Exceedance Annunciation window Alert window COOLANT LVL LOW Coolant Level Low 1. CoolantTemperature.......................... Monitor IfCTrises: 2. Referto CT Limits Exceedance procedure (§7.5). Z"i Edition - Rev. 6 Section 3 - EMERGENCY PROCEDURES POWERPLANT ^TWECNAM P2010tdi-AircraftFlight Manual page3-27 7.8. Intercooler Temperature Limit Exceedance 7.8.1. LOW INTERCOOLER TEMPERATURE* Annunciation window Alert window Intercooler Temp Low 1. POWER. INCREASE äs required to extinguish CAS message If CAS message doesn't extinguish: 2. 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. If CAS message doesn't extinguish: 3. Land äs soon äs possible *) applicable for aircraft NOT embodying MOD 2010/240 7.8.2. HIGH INTERCOOLER TEMPERATURE 1. POWER. REDUCE äs required to extinguish CAS message If CAS message doesn't extinguish: 2. Land äs soon äs possible 2"' Edition - Rev. 4 Section 3 - EMERGENCY PROCEDURES POWERPLANT QUAUTfAIRCRAFTSlNCEWB »^A A .a A - •• • • »•- r-• • [^TECNAM P2010tdi-Aircraft Flight Manual page3-29 7.10. Oil Pressure Limits Exceedance 7.10.1. LOW OlL PRESSURE Annunciation window Alert window Oil Press Low Ifthe oil pressure is underthe lowerlimit 1. Thrust Lever........................ REDUCE to minimum practical 2. OILTEMP........................... CHECK within limits 3. OIL PRESS......................... CHECK If oil pressure does not increase and temoerature remains within limits 4. OILand CT......................... CHECK 5. Land äs soon äs practical If oiljiressure does not increase and temperature exceeds limits 4. ENGINE......................... SECURE 5. Land äs soon äs possible applying Forced landing procedure 7.10.2. HIGH OIL PRESSURE Iftheoil oressure exceedsjipjier limlt 1. ThrustLever........................ REDUCE 2. OIL PRESS......................... CHECK If oil pressure does not decrease 3. ENGINE......................... SECURE 4. Land äs soon äs possible applying Forced landing procedure 2"d Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES POWERPLANT ^TECNAM P2010tdi - Aircraft Flight Manual pages-si 8. FUEL SYSTEM 8.1. Fuel Temperature Limits Exceedance 8.1.1. Low FUEL TEMPERATURE 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. Apply the following procedure when fuel temperatures are in red arc for JET A-1 fuel or in yellow arc for Diese! fuel: 1. FuelTank........................ SWITCH to fuel tank with higher fuel temperature, ifthis contains sufficient fuel 2. Altitude........................... CHANGEto altitude with higher OAT Ifthe temperature does not increase, land äs soon äs possible. 2°" Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES FUEL SYSTEM iiNCEwa •^^»^^^^•- • • ^d^a- [^TECNAM P2010tdi - Aircraft Flight Manual pages 33 9. Inflight Engine Restart Engine inflight restart must be performed without using the starter äs lang äs propeller is windmilling in order to avoid possible engine damages. The propeller will nonnally continue to turn äs lang äs the airspeed is above 65 KIAS. Should the propeller stop at an airspeed of 65 KCAS or more, the reason for this should be investigated before attempting a restart. If the enaine or orooeller iammina is susoected. do not use the Starter. The engine re-start can be performed in the whole aircraft NOTE | envelope. However, it is suggested to perfonn inflight engine re-start at 13000 ft or below. 1. Glide............................... Below13000n 2. Master switch.................... CHECK ON 3. Fuelquantityindicator.......... CHECK 4. FuelSelectorvalve.............. SWITCH TANK (if not empty) 5. ElectricFuel pump.............. OA/ 6. ThrustLever...................... IDLE 7. Engine Master................... OFF and then ON (if the propeller ctoes not turn, then additionally Starter ON) g-^ -j /f ?e Engine Master is in position OFF, a X w/7/ üe displayed on each engine Parameter. In case of unsuccessful enaine restart; 8. LandassoonaspossibleapplyingForced/and/ngprocedure.^^5.^ In case ofsuccessfu/ enaine restart: 9. Engine power: i. ThrustLever............... Set äs requireü il. Engine Parameters...... CHECK 2"" Edition - Rev. 1 Section 3 - EMERGENCY PROCEDURES INFLIGHT ENGINE RESTART QliAUTTfAiBCflAFTS^eSWS »^ ^ ^ ^ ^k < a- *• »•< »->•• ? TECWÄM P201 Otdi - Aircraft Flight Manual Page 3 - 35 11. Smokeand Fire 11.1. Engine fire on the ground 1. 2. 3. 4. 5. 6. 7. Fuel Selector valve. Engine Master. Electric Fuel pump. Cabin heat and defrost. Master and Generator Switches. Parking Brake. Aircraft Evacuation. OFF OFF OFF OFF OFF ENGAGED PERFORM 11.2. Engine fire during take-off Ifengine fails before rotation: ABORT TAKE-OFF 1. Engine Master.......................................... OFF 2. ThrustLever............................................. IDLE 3. Brakes..................................................... Asrequired With the aircraft under control 4. FuelSelectorvalve..................................... OFF 5. ElectricFuel pump..................................... OFF 6. Cabin heat............................................... OFF 7. Master andgeneratorSwitches..................... OFF 8. Parking Brake........................................... ENGAGED 9. Aircraft Evacuation..................................... PERFORM 2°" Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES SMOKE AND FIRE ^ ^^ p^ Q^j _ ^j^raft Flight Manual page 3 - 37 11.5. Electrical smoke orfire in cabin during flight 1. Cabinheat............................... OFF 2. Cabin ventilation........................ OPEN 3. In case of fire, direct the fire extinguisher toward the base of flame Initiale an emergency descent: 4. Flaps ................................................... UP 5. Thrust lever........................................ IDLE 6. Airspeed ............................................ äs required When passing 10,000 ft or at an altitude where oxygen is no langer required, whichever comes first: 7. OXYGEN .............................................. OFF If smoke persists: 8. Generator Switch....................... OFF If smoke persists: 9. Generator switch........................ ON 10. KeepRPMabove 1000............... OFF 11. Master switch............................ OFF If smoke oersists: 12. Generator switch........................ OFF If both generator and main battery are turned OFF, continued engine Operation is dependent on the remaining capacity ofthe wZ^^G FADEC backup battery. Turn on electrical equipment required to continue flight depending on the Situation and land äs soon äs possible ,\ If the Generator SWITCH is set to OFF, consider that flaps are supplied by battery. If the Master switch is set ta OFF, flap will l CAUTION remain in the last position. y Edition - Rev. 0 Section 3 - EMERGENCY PROCEDURES SMOKE AND FIRE QUAUTTfAIRCRAFTSlNCEWB »<k^^^A< •- *• f^ ^•- ^ ^^^ P2010tdi - Aircraft Flight Manual page 3 39 12.2. Electrical ruddertrim control failure Trim Runawav In event oftrim runaway: 1. Airspeedandflaps.................. ADJUSTto control aircraft without excess/i/e force 2. Rudder................................ Asrequired 3. Land aircraft äs soon äs practical Trim Jamming Should trim control be jammed/inoperative: 1. Breaker............................... CHECKIN 2. Airspeed andflaps.................. ADJUSTto control aircraft without axcessn/e force 3. Rudder................................ As required 4. Land aircraft äs soon äs practical 2"d Edition -Rev. 0 Section 3 - EIWERGENCY PROCEDURES FLIGHT CONTROLS ayAunAfRCRAHg^eews »^.^.^^^^ •• •" »•- •—•- ® TECN'ÄM P201 OtdJ - Aircraft Flight Manual page 3 -41 If flaps are stuck UP, plan landing using a flat approach and use power levers to control airplane speecf and rate of descent. Ifflaps are NOT stuck: NOTE Consider flaps indicator inoperative. 4. Flaps switch .........................................................................äs required 5. Flaps Position................................................................CHECK wsuaffy yi Edition - Rev. 6 Section 3 - EMERGENCY PROCEDURES FLIGHT CONTROLS QUAUTfAlRCRAFTSlNCEIMB •»<»<» ^ A - •- • • ^- ^ • • {^TECNAM P2010tdi-AircraftFlight Manual pages 43 14. UNINTENTIONAL FLIGHT INTO ICING CONDITIONS 3. Pitotheat......................... CHECK ON 4. Fly immediately away from icing conditions (changing altitude and direction of flight, out and below of clouds, visible moisture, precipitation) 5. Control surfaces................ MOVE continuously to avoid locking 6. ThrustLever..................... INCREASEtopreventicebuild-upon propeller blades In event of ice build-up in correspondence of wing leading edfires, s^a// speed increases and stall may become asymmethc. In case of stabilator ice accretion, it may lose its efficiency, leading to lack of aircraft piteh control and loss ofcontrol. 2"d Edition - Rev. 6 Section 3 - EMERGENCY PROCEDURES UNINTENTIONAL FLIGHT INTO IING CONDITIONS QUAUTfA!RCRAFrS!W£WB wn». ^ ^ ^ ^ ^ •• • • <•< ^ • • }fECNAM P2010tdi - Aircraft Flight Manual pages 45 15.2. Power on forced landing 1. Flaps.................................................. UP 2. Airspeed............................................. ESTABLISH VBUDE (79 KIAS) Glide ratio is about 11.5, therefore in zero wind conditions for every 1000 ft it is possible to cover about 2 N M. With propeller in windmilling glade ratio is about 9.3, therefore for every 1000 ft it is possible to cover about1.5NM. 3. Find a suitable place to land safely 4. SafetyBelts......................................... Tightly FASTENED When landing is assured: 5. Flaps.................................................. -Asnecessa/y 6. Fuel selectorvalve................................ OFF 7. ElectricFuel pump................................ OFF 8. Engine Master...................................... OFF 9. Generator and Master switches................ OFF Be prepared for aircraft evacuation. 2"i Edition - Rev. l Section 3 - EMERGENCY PROCEDURES EhflERGENCY LANDING