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Daher-Socata TBM 900, Pilot'S Information Manual

The Daher-Socata TBM 900 Pilot's Information Manual is a comprehensive and essential resource for pilots. Packed with all the necessary details and instructions, this manual provides valuable insights for the operation and maintenance of the TBM 900 aircraft. Download this user manual for free from our website.

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PILOT’S OPERATING HANDBOOK

SECTION 2

LIMITATIONS

EASA Approved

Edition 0 -- October 31, 2013
Rev. 1

Page 2.6.7

4) Engine instruments

-

Torquemeter

-

Propeller tachometer

-

Interturbine temperature indicator (ITT)

-

Gas generator tachometer (Ng)

-

Oil pressure indicator

-

Oil temperature indicator

5) Various indicators

-

Fuel gauge indicators (2)

-

Voltmeter

-

Ammeter

-

Outside air temperature

6) Installations

-

Fuel mechanical pump (main)

-

Fuel electrical pump (auxiliary)

-

Fuel shut-off valve

-

Fuel timer

-

Starter generator

-

Inertial separator

-

Stall warning

-

Electrical aileron trim

-

Electrical rudder trim

-

Manual elevator pitch trim

-

Engine ignition

-

Landing gear electro-hydraulic unit

-

Landing gear emergency hydraulic pump (manual)

-

Flaps

-

Overspeed regulator

-

Electrical feathering

-

Battery

7) Miscellaneous

-

Seats (each occupant)

-

Belts (each occupant)

-

Straps (each occupant)

-

Pilot's operating handbook

Summary of Contents for TBM 900

Page 1: ...thout permission in writing from the owners of the Copyright Information in this document is subject to change without notice 2014 socata All rights reserved DAHER SOCATA Customer support 65921 TARBES CEDEX 9 FRANCE Printed in FRANCE From S N 1000 P N T00 DMHPIPYEE0 EDITION 0 REVISION 1 CAUTION THIS INFORMATION MANUAL IS A NON OFFICIAL COPY OF THE PILOT S OPERATING HANDBOOK AND MAY BE USED FOR GEN...

Page 2: ...nor 70 0357 71 Takeoff and landing at 850shp Increase of takeoff power Major 70 0359 71 Air inlet inertial separator actuator minor 70 0361 32 Landing gear wide washer minor 70 0364 25 Modified pylon upholstery minor 70 0369 25 Obsolescence of cabin lighting LED and lenses minor 70 0370 52 Wide door motor obsolescence minor 70 0372 33 Back lighted panels minor 70 0373 33 PL1 Circuit breaker panel ...

Page 3: ...oval of MT40 transducer minor 70 0401 92 Illuminated push buttons minor 70 0402 28 Fuel sequencer evolution minor 70 0403 24 Battery firewall modification minor 70 0404 57 Aileron trimming minor NOTE Optional modifications are integrated in the list of equipment refer to the list of equipment available in SOCATA Report reference NAV No 34 90 RJ App 2 located at the end of this POH ...

Page 4: ...ition 0 October 31 2013 Rev 1 Page 0 6 TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE 6 DESCRIPTION 7 AIRPLANE HANDLING SERVICING AND MAINTENANCE 8 SUPPLEMENTS 9 ...

Page 5: ...E WEIGHTS 1 3 3 CABIN AND ENTRY DIMENSIONS 1 3 4 SPECIFIC LOADINGS 1 3 4 1 4 ABBREVIATIONS AND TERMINOLOGY 1 4 1 METEOROLOGICAL TERMINOLOGY 1 4 1 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 1 4 1 POWER TERMINOLOGY 1 4 2 AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 1 4 2 WEIGHT AND BALANCE TERMINOLOGY 1 4 2 GENERAL ABBREVIATIONS 1 4 4 RADIO NAVIGATION ABBREVIATIONS 1 4 7 1 5 CONVERSION FACTORS...

Page 6: ... s Operating Handbook The Pilot s Guide for the Electronic Standby Indicator MODEL ESI 2000 P N 0040 32500 01 Rev E or any later version as applicable must be permanently kept in the airplane with the Pilot s Operating Handbook Departure into IMC is not authorized if the battery symbol is present with an amber battery symbol less than 1 hour remaining or an amber or red X over the battery symbol o...

Page 7: ...T S OPERATING HANDBOOK SECTION 1 GENERAL Edition 0 October 31 2013 Rev 1 Page 1 2 1 1 2 THREE VIEW DRAWING Figure 1 2 1 1 2 THREE VIEW DRAWING Airplane on level field with fully extended FWD shock absorber ...

Page 8: ...PILOT S OPERATING HANDBOOK SECTION 1 GENERAL Edition 0 October 31 2013 Rev 1 Page 1 2 2 Figure 1 2 1 2 2 THREE VIEW DRAWING ...

Page 9: ...Annular Turbine type 1 gas generator turbine stage 2 power turbines stages Horsepower rating and propeller speed 850 SHP at 2000 RPM PROPELLER Number of propellers 1 Propeller manufacturer HARTZELL Propeller model number HC E4N 3 E9083S K Number of blades 4 Propeller diameter Minimum 90 inches 2 286 m Maximum 91 inches 2 311 m Propeller type Adjustable constant speed with feathering and hydraulic ...

Page 10: ...ERGENCY PURPOSES ONLY AVGAS SHALL NOT BE USED FOR MORE THAN 150 CUMULATIVE HOURS DURING ANY PERIOD BETWEEN ENGINE OVERHAUL PERIODS NOTE Use of AVGAS to be recorded in engine module logbook US Specification US French Specification FR English Specification UK NATO Code ASTM D1655 JET A ASTM D1655 JET A1 ASTM D1655 JET B AIR 3405C Grade F35 DERD 2494 Issue 9 F35 without additive MIL DTL 5624 Grade JP...

Page 11: ...S French Specification FR English Specification UK NATO Code Type 5cSt MIL L 23699C Amdt1 MIL L 23699C Amdt1 DERD 2499 Issue 1 O 156 Figure 1 3 2 RECOMMENDED ENGINE OIL TYPES Reference Service Bulletin P W C No 14001 MAXIMUM CERTIFICATED WEIGHTS Ramp 7430 lbs 3370 kg Takeoff 7394 lbs 3354 kg Landing 7024 lbs 3186 kg Baggage weight refer to Section 2 Paragraph 2 5 for weight and C G limits refer to...

Page 12: ...abin length 13 3 45 4 05 m Maximum cabin height 4 1 22 m Number of cabin entries 1 standard 1 pilot door if installed Entry width standard 3 6 52 1 08 m Entry height standard 3 10 85 1 19 m Pilot entry mean width 2 3 6 0 70 m Pilot entry mean height 3 2 16 0 97 m SPECIFIC LOADINGS Wing loading 38 16 lbs sq ft 186 3 kg m2 Power loading 8 7 lbs SHP 3 95 kg SHP ...

Page 13: ...ere at sea level KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature VA Maneuvering Speed is the maximum speed at which full or abrupt control movements may be used VFE Maximum Flap Extended Speed is the highest s...

Page 14: ... minimal drag Maximum Cruise Power Power developed corresponding to outside Flight Level and Temperature conditions Refer to Chapter 5 PERFORMANCE Ng Gas generator RPM Np Propeller rotation speed Reverse Drag produced when the propeller blade setting is negative RPM Revolutions per minute SHP Shaft Horsepower TRQ Torque AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb gradient Is the rat...

Page 15: ...enter of gravitylocations within which the airplane must be operated at a given weight Standard empty weight Weight of a standard airplane including unusable fuel and full operating fluids oil and hydraulic fluids Basic empty weight Standard empty weight plus optional equipment Useful load Is the difference between maximum ramp weight and the basic empty weight Maximum ramp weight Is the maximum w...

Page 16: ...col monomethyl ether DISC Disconnect DN Down ECS Environmental control system EGME Ethylene glycol monomethyl ether EMER Emergency ENCOD ALTI Encoding altimeter ESHP Estimated shaft horsepower ESS BUS TIE Essential BUS tie EXT LIGHTS Exterior lightings F Fahrenheit degree FCU Fuel control unit FIRE EXTING Fire extinguisher FL Flight level FOB Fuel On Board FPL Flight Plan ft Feet ft min Feet per m...

Page 17: ...MFD Multi function Display MIN Minimum min Minute mm Millimetre MLW Maximum Landing Weight MRW Maximum Ramp Weight MTOW Maximum Takeoff Weight MXCR Maximum Cruise MZFW Maximum Zero Fuel Weight NM Nautical mile NOCR Normal cruise recommended NORM Normal PFD Primary Flight Display PHF Plan Horizontal Fixe Horizontal stabilizer PRESS Pressure PROP Propeller psi Pounds per square inch qt Quart USG QTY...

Page 18: ...PILOT S OPERATING HANDBOOK SECTION 1 GENERAL Edition 0 October 31 2013 Rev 1 Page 1 4 6 USG Gallon U S V Volt or Voltage WARN Warning W S Windshield ...

Page 19: ... System GPS Ground Positioning System HF High Frequency IFR Instrument Flight Rules ILS Instrument Landing System IMC Instrument Meteorological Conditions L NAV Lateral NAVigation LPV Localizer Precision Vertical MKR Marker Radio Beacon NAV Navigation Indicators or Receivers P RNAV Precision aRea NAVigation R NAV Area NAVigation RNP Required Navigation Performance TAS Traffic Advisory System TAWS ...

Page 20: ... U S UNITS TO METRIC UNITS METRIC UNITS TO IMPERIAL AND U S UNITS MULTIPLY BY TO OBTAIN MULTIPLY BY TO OBTAIN FEET 0 3048 METRE METRE 3 2808 FEET INCH 25 4 mm mm 0 03937 INCH Imp Gal 4 546 Litre Litre 0 220 Imp Gal USG 3 785 Litre Litre 0 264 USG lb 0 45359 kg kg 2 2046 lb Figure 1 5 1 IMPERIAL AND U S UNITS TO METRIC UNITS ...

Page 21: ...PILOT S OPERATING HANDBOOK SECTION 1 GENERAL Edition 0 October 31 2013 Rev 1 Page 1 5 2 Figure 1 5 2 FEET VERSUS METRES Metres 30000 20000 10000 0 Feet 2500 5000 7500 10000 31000 ...

Page 22: ...PILOT S OPERATING HANDBOOK SECTION 1 GENERAL Edition 0 October 31 2013 Rev 1 Page 1 5 3 Figure 1 5 3 INCHES VERSUS MILLIMETRES mm 10 0 In 250 500 750 1000 20 30 40 ...

Page 23: ...PILOT S OPERATING HANDBOOK SECTION 1 GENERAL Edition 0 October 31 2013 Rev 1 Page 1 5 4 Figure 1 5 4 POUNDS VERSUS KILOGRAMS 1000 2000 3000 2000 6000 4000 0 Kg Lb 4000 8000 ...

Page 24: ...013 2 15 0 59 0 2000 942 1 11 0 51 8 4000 875 0 7 0 44 6 6000 811 9 3 1 37 6 8000 752 6 0 8 30 5 10000 696 8 4 8 23 4 12000 644 3 8 7 16 2 14000 595 2 12 7 9 2 16000 549 1 16 6 2 2 18000 505 9 20 6 5 0 20000 465 6 24 6 12 4 22000 427 8 28 5 19 3 24000 392 6 32 5 26 5 26000 359 8 36 5 33 6 28000 329 3 40 4 40 7 30000 300 8 44 4 47 8 31000 287 4 46 4 51 6 Figure 1 6 1 STANDARD ATMOSPHERE ...

Page 25: ...6 985 29 09 986 29 12 987 29 15 988 29 18 989 29 20 990 29 23 991 29 26 992 29 29 993 29 32 994 29 35 995 29 38 996 29 41 997 29 44 998 29 47 999 29 50 1000 29 53 1001 29 56 1002 29 59 1003 29 62 1004 29 65 1005 29 68 1006 29 71 1007 29 74 1008 29 77 1009 29 80 1010 29 83 1011 29 85 1012 29 88 1013 29 91 1014 29 94 1015 29 97 1016 30 00 1017 30 03 1018 30 06 1019 30 09 1020 30 12 1021 30 15 1022 3...

Page 26: ... LIMITS 2 6 1 GFC 700 AUTOPILOT LIMITS 2 6 2 G1000 GNSS GPS SBAS NAVIGATION EQUIPMENT APPROVALS 2 6 2 G1000 GNSS GPS SBAS NAVIGATION SYSTEM LIMITATIONS 2 6 2 SID STAR 2 6 4 ICING CONDITIONS 2 6 5 SEVERE ICING CONDITIONS 2 6 5 FLAP OPERATING ENVELOPE 2 6 5 REVERSE UTILIZATION 2 6 5 EQUIPMENT REQUIRED DEPENDING ON TYPE OF OPERATION 2 6 6 ALTITUDE OPERATING LIMITS 2 6 9 IN FLIGHT CIRCUIT BREAKER USE ...

Page 27: ...S OPERATING HANDBOOK SECTION 2 LIMITATIONS EASA Approved Edition 0 October 31 2013 Rev 1 Page 2 0 2 2 8 MARKINGS 2 8 1 INDICATED AIRSPEED 2 8 1 PRESSURIZATION 2 8 1 ENGINE INSTRUMENTS 2 8 2 2 9 PLACARDS 2 9 1 ...

Page 28: ...able must be permanently kept in the airplane with the Pilot s Operating Handbook Departure into IMC is not authorized if the ESI 2000 battery symbol is present with an amber battery symbol less than 1 hour remaining or an amber or red X over the battery symbol or a CAL DUE message by the battery symbol This Section of the airplane Pilot s Operating Handbook presents the various operating limitati...

Page 29: ...ry VA Maneuvering speed 160 158 Do not make abrupt or full control movements above this speed VFE Maximum flaps extended speed landing configuration takeoff configuration 120 180 122 178 Do not exceed these speeds depending on flaps position VLO Maximum landing gear operating speed extension retraction emergency extension 180 151 151 178 150 150 Do not extend or retract landing gear above this spe...

Page 30: ...nufacturer PRATT WHITNEY CANADA Engine model number PT6A 66D Maximum power 100 at Np 2000 RPM Ng limitation 104 1 Np limitation 2000 RPM 40 RPM ITT limitations Take off 850 C Maximum climb cruise 840 C During start 850 C no duration limitation 870 C for 20 seconds max 1000 C for 5 seconds max CAUTION WHEN NORMALLY OPERATING REFER TO CHAPTER 5 8 ENGINE OPERATION TABLES ...

Page 31: ...t reduced power level not exceeding 80 torque Oil pressures below 60 psi are unsafe and require that either the engine be shut down or a landing be made as soon as possible using the minimum power required to sustain flight Oil capacity System total capacity 12 7 Quarts 12 Litres Oil cooler included Usable capacity 6 Quarts 5 7 Litres Oil grade Specification Nominal viscosity US specification US F...

Page 32: ...ONAL INFORMATION THE USE OF AVIATION GASOLINE AVGAS MUST BE RESTRICTED TO EMERGENCY PURPOSES ONLY AVGAS SHALL NOT BE USED FOR MORE THAN 150 CUMULATIVE HOURS DURING ANY PERIOD BETWEEN ENGINE OVERHAUL PERIODS NOTE Use of AVGAS to be recorded in engine module logbook US Specification US French Specification FR English Specification UK NATO Code ASTM D1655 JET A ASTM D1655 JET A1 ASTM D1655 JET B AIR ...

Page 33: ...13 Rev 1 Page 2 3 4 PROPELLER Number of propellers 1 Propeller manufacturer HARTZELL Propeller model number HC E4N 3 E9083S K Propeller diameter Minimum 90 inches 2 286 m Maximum 91 inches 2 311 m Propeller blade setting at 30 inches station Low pitch 21 Feathering 86 Maximum reverse 11 ...

Page 34: ...v 1 Page 2 4 1 2 4 STARTER OPERATION LIMITS Starter operation sequence is limited as follows if Ng 30 30 seconds if Ng 30 60 seconds Should several sequences be necessary respect following spacing 1st sequence wait 1 minute 2nd sequence wait 5 minutes 3rd sequence wait 30 minutes 4th sequence ...

Page 35: ...ght MTOW 7394 lbs 3354 kg Maximum landing weight MLW 7024 lbs 3186 kg Maximum zero fuel weight MZFW 6032 lbs 2736 kg Maximum baggage weight in FWD compartment non pressurized 110 lbs 50 kg With 6 seat accommodation in rear part of pressurized cabin 220 lbs 100 kg With 4 seat accommodation in rear part of pressurized cabin 396 lbs 180 kg with small or large net see sketch below Figure 2 5 1 Baggage...

Page 36: ... datum at 6579 lbs 2984 kg 20 85 of m a c 187 inches 4 752 m aft of datum at all weights above 7024 lbs 3186 kg 23 8 of m a c Aft limits 193 65 inches 4 921 m aft of datum at 7394 lbs 3354 kg 35 of m a c 194 inches 4 928 m aft of datum at 6986 lbs 3169 kg 35 5 of m a c Reference datum 118 1 inches 3 m in front of the firewall front face Straight line variation between points Leveling point Cabin f...

Page 37: ...k is no more than 60 Aerobatic maneuvers including spins are not approved TEMPERATURE LIMITS Minimum temperature at start and takeoff 40 C 40 F Maximum temperature at start and takeoff ISA 37 C 67 F from 0 to 8000 ft pressure altitude Maximum temperature in flight ISA 37 C 67 F from 0 to 8000 ft pressure altitude ISA 30 C 54 F above 8000 ft pressure altitude FLIGHT LOAD FACTOR LIMITS Flaps up Weig...

Page 38: ...th vertical guidance including LPV within the coverage of a Satellite Based Augmentation System complying with ICAO Annex 10 and LNAV VNAV within the U S National Airspace System The airplane is approved for Enroute and Terminal operations including RNAV5 BRNAV and RNAV1 PRNAV in accordance with JAA TGL 10 provided the FMS is receiving usable navigation information from one or more GPS receivers G...

Page 39: ...ould be delayed cancelled or re routed on a track where RAIM requirements can be met For flight planning purposes operations where the route requires Class II navigation the airplane s operator or pilot in command must use the G1000 WFDE Prediction program to demonstrate that there are no outages on the specified route that would prevent the G1000 to provide primary means of Class II navigation in...

Page 40: ...he procedure and notes on the IAP chart Use of the GARMIN G1000 GPS SBAS receivers to provide navigation guidance during the final approach segment of an ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for or GPS navigation is prohibited When using the G1000 VOR LOC GS receivers to fly the final approach segment VOR LOC GS navigation data must be selected and presented on the...

Page 41: ...ed by the following visual cues If one or more of these visual cues exists immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice Accumulation of ice on the upper surface of the wing aft of the protected a...

Page 42: ...TION COUNTRY DEPENDING ON THE TYPE OF OPERATION CAUTION SYSTEMS AND EQUIPMENT MENTIONED HEREAFTER DO NOT INCLUDE SPECIFIC FLIGHT AND RADIO NAVIGATION INSTRUMENTS REQUIRED BY DECREE CONCERNING OPERATION CONDITIONS FOR CIVIL AIRPLANES IN GENERAL AVIATION OR OTHER FOREIGN REGULATIONS FOR EXAMPLE FAR PART 91 AND 135 Day VFR 1 Pilot instruments Airspeed indicator Sensitive and adjustable altimeter Magn...

Page 43: ...ltmeter Ammeter Outside air temperature 6 Installations Fuel mechanical pump main Fuel electrical pump auxiliary Fuel shut off valve Fuel timer Starter generator Inertial separator Stall warning Electrical aileron trim Electrical rudder trim Manual elevator pitch trim Engine ignition Landing gear electro hydraulic unit Landing gear emergency hydraulic pump manual Flaps Overspeed regulator Electric...

Page 44: ...ollision lights 2 9 Landing light IFR 1 All equipment required for day VFR 2 All equipment required for night VFR if flight is performed during night 3 Taxi light if flight is performed during night 4 Clock 5 2nd altimeter 6 Emergency static source 7 Pitot static tube deicing Pressurized flight 1 Cabin altimeter 2 Cabin vertical speed indication 3 Cabin differential pressure indication 4 Pressuriz...

Page 45: ...th the airplane Maintenance Manual This does not constitute operational approval Individual airplane and operational approval must be obtained in accordance with applicable operating rules Each operator must ensure compliance with required crew training and operating practices and procedures Moreover the following equipment must be installed and operating normally upon entering RVSM airspace Pilot...

Page 46: ...W SYSTEM OPERATING LIMITATIONS The geographic referenced airplane symbol on some charts must not be used for navigation NOTE The airplane symbol displayed on some charts provides supplemental airplane situational awareness information It is not intended as a means for navigation or flight guidance The airplane symbol is not to be used for conducting instrument approaches or departures and it shoul...

Page 47: ...lot MAXIMUM OCCUPANCY The number of persons on board is limited by approved seating configuration installed but must not exceed six including the pilot The number of persons must be less than or equal to the number of seats USE OF DOORS Flight with door open or ajar is prohibited CHEMICAL TOILET CABINET if installed The cabinet must be stowed during take off and landing No baggage on the top of th...

Page 48: ...Figure 2 8 1 MARKING KIAS Value or range SIGNIFICANCE Red line White line Below 65 65 122 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Green line Above 122 Normal operating airspeed range Hatched Red White Sector Above 266 266 VMO Figure 2 8 1 IAS AWARENESS BAR CUES PRESSURIZATION MARKING VALUE SIGNIFICANCE Red line 6 2 psi Cabin P limit Figure 2 8 2 PRESSUR...

Page 49: ...ture 40 C 40 F 40 to 0 C 40 to 32 F 104 to 110 C 219 2 to 230 F 0 to 104 C 32 to 219 2 F 110 C 230 F Oil pressure 60 psi 60 to 100 psi 100 to 135 psi 135 psi Generator RPM Ng 51 to 104 104 Propeller RPM Np 450 to 1000 RPM 1950 to 2050 RPM 2050 RPM ITT Engine start or off 840 to 1090 C 1544 to 1994 F 400 to 840 C 752 to 1544 F 840 C 1544 F normal limit 870 C 1598 F 20 seconds limit 1090 C 1994 F re...

Page 50: ...tion chart on compass and on windshield post For N 30 60 E 120 150 Steer For S 210 240 W 300 330 Steer DATE RADIO ON 3 On pressurized baggage compartment partition wall 100 kg 220 lbs MAXIMUM IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT ALL THE BAGGAGES ARE PROPERLY SECURED FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA IN PILOT S OPERATING HANDBOOK ...

Page 51: ...9 2 3 a For the small cargo net on frame C13bis 3 b For the large cargo net on R H side upholstery panel in the rear baggage compartment All 3 c On FWD baggage compartment door frame non pressurized 50 kg 110 lbs MAXIMUM FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA IN PILOT S OPERATING HANDBOOK ...

Page 52: ...PILOT S OPERATING HANDBOOK SECTION 2 LIMITATIONS EASA Approved Edition 0 October 31 2013 Rev 1 Page 2 9 3 4 Under GCU 475 control unit on pedestal console 5 On fuel selector 6 Near fuel tank caps ...

Page 53: ...4 7 On internal face of L H engine cowling Oil system capacity 12 l 12 7 qt 8 On landing gear emergency control access door LDG GEAR EMERGENCY ACCESS PULL 9 Under window at L H Intermediate seat 10 On rear passenger s table casing TABLE MUST BE STOWED DURING TAKEOFF AND LANDING 11 Under R H control wheel ...

Page 54: ... 9 5 12 On nose gear door 13 On nose gear leg NOSE LANDING GEAR TIRE PRESSURE 6 5 bar 94 psi 14 On main gear leg MAIN LANDING GEAR TIRE PRESSURE 8 96 bar 130 psi 15 On engine cowling in front of compartment door EXTERNAL POWER 28 VOLTS D C NOMINAL 800 AMPS STARTING CAPACITY MIN DO NOT EXCEED 1000 AMPS ...

Page 55: ...ON 2 LIMITATIONS EASA Approved Edition 0 October 31 2013 Rev 1 Page 2 9 6 16 On pilot door External side if installed 17 On access door External side 18 On outer fuselage skin aft of access door and in the cabin forward of access door ...

Page 56: ...DBOOK SECTION 2 LIMITATIONS EASA Approved Edition 0 October 31 2013 Rev 1 Page 2 9 7 19 On access door Internal side 20 On pilot door Internal side if installed 21 On emergency exit handle Marking on cover Marking on handle ...

Page 57: ...ition 0 October 31 2013 Rev 1 Page 2 9 8 22 On last step of stairs STAIRS MAX LOAD ONE PERSON 23 On R H access door jamb 24 On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling 25 On rear passengers masks containers ...

Page 58: ...ctober 31 2013 Rev 1 Page 2 9 9 26 On internal face of the oxygen cylinder service door 27 On the oxygen service door 28 On emergency locator transmitter inspection door 29 On the potty seat curtain if installed on pilot s side CURTAIN MUST BE STOWED FOR TAKE OFF AND LANDING ...

Page 59: ...CRACK IN COCKPIT WINDOW OR WINDOW PANEL 3 2 10 RUNAWAY OF TRIM 3 2 11 EMERGENCY DESCENTS 3 2 12 MAXIMUM RATE DESCENT 3 2 12 MAXIMUM RANGE DESCENT 3 2 13 EMERGENCY DESCENT PROFILES 3 2 15 INADVERTENT SPINS 3 2 16 STALL WARNING SOUND 3 2 16 LEFT PFD FAILURE 3 2 17 TIRE BLOWOUT DURING LANDING 3 2 18 SMOKE ELIMINATION 3 2 19 TOTAL LOSS OF ELECTRICAL POWER 3 2 20 RED WARNING CAS MESSAGE BLEED TEMP 3 2 ...

Page 60: ...AIN GEN and LOW VOLTAGE 3 3 16 AMBER WARNING CAS MESSAGE OIL TEMP 3 3 18 AMBER WARNING CAS MESSAGE PITOT NO HT L R 3 3 19 AMBER WARNING CAS MESSAGE PROP DEICE FAIL 3 3 20 AMBER WARNING CAS MESSAGE STALL NO HEAT 3 3 21 AMBER WARNING CAS MESSAGE VACUUM LOW 3 3 22 3 4 ENGINE MISCELLANEOUS 3 4 1 ENGINE REGULATION DISCREPANCY POWER LOSS THROTTLE CONTROL LOSS 3 4 1 GOVERNOR REGULATION CONTROL NOT OPERAT...

Page 61: ...USE 3 9 3 EMERGENCY BEACON ELT USE 3 9 4 AUTOPILOT OR ELECTRIC PITCH TRIM MALFUNCTION 3 9 5 OXYGEN USE 3 9 6 AIRSPEED INDICATING SYSTEM FAILURE 3 9 7 FLIGHT INTO SEVERE ICING CONDITIONS 3 9 8 DUAL GPS SBAS FAILURE AMBER DR OR LOI ON HSI 3 9 9 GPS APPROACH ALARM LIMITS EXCEEDED 3 9 11 AHRS FAILURE 3 9 12 ADC FAILURE 3 9 13 3 10 ANNEX 3 10 1 AIR START ENVELOPE 3 10 1 AIR START 3 10 2 BUS BAR 3 10 3 ...

Page 62: ...provides failure procedures which are not the same for all airplanes It is important for the pilot to be familiar with standard emergency procedures to be at the optimum efficacy if necessary Alarm system recall Main failure or state modification of the different systems are provided by warning or caution messages appearing on CAS display The CAS includes redmessages indicating failures which requ...

Page 63: ... WITH IMMEDIATE ACTION REQUIRED AND RED CAS MESSAGES ENGINE FIRE ON GROUND Symptoms ITT increasing red warning CAS message ITT ON smoke 1 Throttle CUT OFF 2 BLEED switch OFF RST 3 A C switch OFF 4 Brakes AS REQUIRED 5 Tank selector OFF 6 Warn ground assistance if necessary 7 Crash lever PULL DOWN 8 EVACUATE as soon as possible ...

Page 64: ...DURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 2 2 CABIN FIRE ON GROUND 1 Throttle CUT OFF 2 Brakes AS REQUIRED 3 Warn for ground assistance if necessary 4 Crash lever PULL DOWN 5 Cabin extinguisher AS REQUIRED 6 EVACUATE as soon as possible ...

Page 65: ...ymptoms ITT increasing red warning CAS message ITT ON smoke FLY THE AIRPLANE 1 Throttle CUT OFF 2 AUX BP fuel switch OFF 3 Tank selector OFF 4 BLEED switch OFF RST 5 A C switch OFF 6 If necessary Set oxygen mask 7 If necessary EMERGENCY DESCENT 8 Perform a FORCED LANDING ENGINE CUT OFF WARNING AFTER ENGINE FIRE DO NOT ATTEMPT AN AIR START ...

Page 66: ... DURING FLIGHT FLY THE AIRPLANE 1 OXYGEN and GOGGLES USE AS REQUIRED If the origin is known 2 CIRCUIT BREAKER Defective equipment PULL 3 Using the on board EXTINGUISHER extinguish fire If the origin is unknown 2 A C switch OFF 3 Not necessary equipment OFF EMERGENCY DESCENT at 10000 ft 4 If necessary SMOKE ELIMINATION 5 LAND as soon as possible ...

Page 67: ...ed Edition 0 October 31 2013 Rev 1 Page 3 2 5 ENGINE FAILURE AT TAKE OFF FLY THE AIRPLANE BEFORE ROTATION 1 Throttle Flight IDLE 2 Braking AS REQUIRED If the airplane cannot be stopped on the remaining runway 3 Throttle CUT OFF 4 Tank selector OFF 5 Crash lever PULL DOWN ...

Page 68: ...If unsuccessful MAN OVRD control FULL BACKWARD If HEIGHT does not allow to choose a favourable runway or field Land straight ahead without changing landing gear position 1 Flaps TO Maintain IAS 100 KIAS 2 Throttle CUT OFF 3 Tank selector OFF 4 Just before touch down Flaps LDG 5 Crash lever PULL DOWN If HEIGHT allows to reach a favourable runway 1 Landing gear control DN 2 Flaps AS REQUIRED 3 Maint...

Page 69: ...LOT DISCONNECT 2 Throttle CUT OFF 3 Remaining fuel CHECK 4 Tank selector SWITCH TANKS 5 AUX BP switch CHECK CORRECT 6 Air start ENVELOPE CHECKED AIR START ENVELOPE AIR START ENVELOPE Air start may be attempted outside of the envelope However above 20000 ft or at lower speeds ITT tends to increase during start and prudence is recommended Figure 3 2 1 AIR START ENVELOPE ...

Page 70: ...e CUT OFF 8 STARTER switch ON take a time CAUTION IF 5 SECONDS AFTER HAVING POSITIONED THE STARTER SWITCH IN ON POSITION THERE IS NO START INTERRUPT STARTING ATTEMPT USING THE ABORT POSITION OF THE STARTER SWITCH When Ng around 13 9 Throttle LO IDLE 10 ITT and Ng Monitor When Ng higher than 52 11 Check starter is OFF automatically CAUTION IF THE STARTER DOES NOT GO OFF AUTOMATICALLY DO IT USING TH...

Page 71: ...MP switch ACTUATED 7 Glide speed 120 KIAS maintained until favourable ground approach If ground allows it 8 ESS BUS TIE switch NORM in order to have GEAR and FLAPS available 9 Landing gear control DN If night conditions 10 OFF TAXI LDG switch LDG If ground does not allow it 11 Keep landing gear UP 12 When chosen ground is assured FLAPS LDG 13 Crash lever PULL DOWN 14 Final approach IAS 85 KIAS 15 ...

Page 72: ... SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 2 10 CRACK IN COCKPIT WINDOW OR WINDOW PANEL FLY THE AIRPLANE 1 DESCEND SLOWLY 2 Reduce cabin ΔP by setting Landing Field Elevation to 10000 ft ...

Page 73: ...AP TRIMS switch OFF 3 AP TRIMS DISC push button RELEASED 4 Pitch trim may be used manually 5 Reduce airspeed if necessary to reduce control forces If pitch trim runaway 6 AP TRIMS switch AP OFF The pitch trim may be used manually the two other trim tabs may be used again electrically If rudder or aileron trim runaway 6 PULL circuit breaker corresponding to the defective trim tab 7 AP TRIMS switch ...

Page 74: ...UM RATE DESCENT FLY THE AIRPLANE 1 Throttle Flight IDLE 2 OXYGEN USE if necessary 3 DESCENT attitude from 10 to 20 Procedure in smooth air 4 Flaps UP 5 Landing gear control UP 6 Speed VMO 266 KIAS Procedure in rough air or in case of structure problem 7 Reduce speed IAS 178 KIAS 8 Landing gear control DN 9 Flaps UP 10 Maintain IAS 178 KIAS ...

Page 75: ...ntrol knob PULLED If conditions allow VMC and non icing conditions 8 ESS BUS TIE reverse switch Cover up then EMER position 9 Prepare a forced landing Refer to Chapter 3 2 If conditions do not allow 10 ESS BUS TIE reverse switch NORMAL 11 Manually disconnect ancillary systems as follows AIRFRAME DE ICE switch OFF ICE LIGHT switch OFF PROP DE ICE switch OFF WINDSHIELD switch OFF PITOT R STALL HTR s...

Page 76: ...IN ACCESS controls OFF XPDR 2 breaker PULL If icing conditions PITOT L HTR switch Checked ON WINDSHIELD switch ON Maintain minimum recommended speeds into known icing conditions Flaps UP 135 KIAS Flaps TO 110 KIAS Flaps LDG 90 KIAS If time permits SVC PLUGS breaker PULL AIR COND breaker PULL 12 Prepare a forced landing Refer to Chapter 3 2 ...

Page 77: ...PILOT S OPERATING HANDBOOK SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 2 15 EMERGENCY DESCENT PROFILES Figure 3 2 2 EMERGENCY DESCENT PROFILES ...

Page 78: ...ONTROL WHEEL NEUTRAL PITCH ROLL 2 RUDDER FULLY OPPOSED TO THE SPIN 3 THROTTLE FLIGHT IDLE 4 Flaps UP When rotation is stopped 5 Level the wings and ease out of the dive 6 THEN FLY THE AIRPLANE STALL WARNING SOUND 1 AP TRIMS switch PRESS twice 2 Fly the aircraft wings level and nose down until stall warning stops 3 Power as required 4 Return to the desired flight path ...

Page 79: ...IMS DISC push button PRESS to mute aural tone 3 DISPLAY BACKUP mode ENGAGED on PFD2 4 PFD 1 circuit breaker CHECKED IN 5 XFR on AFCS PRESS to right side 6 Autopilot NORMAL USE Lost systems AUTOPILOT AP and FLIGHT DIRECTOR FD COM 1 NAV 1 DME 1 XPDR 1 7 Land as soon as possible 8 USE COM 2 NAV 2 DME 2 XPDR 2 SELECT COM 2 MIC CAUTION 1 IN CASE OF ILS APPROACH DON T FORGET TO SELECT LOC2 ON CDI SOURCE...

Page 80: ...GENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 2 18 TIRE BLOWOUT DURING LANDING 1 Control direction with brakes and nose wheel steering 2 REVERSE AS REQUIRED 3 Stop airplane to minimize damages 4 Perform ENGINE SHUT DOWN ...

Page 81: ...NATION 1 Smoke origin IDENTIFY 2 Oxygen and goggles USE AS REQUIRED 3 If smoke persists undertake an EMERGENCY DESCENT FLY THE AIRPLANE 4 BLEED switch OFF RST 5 A C switch OFF 6 DUMP switch ACTUATE Wait until the differential pressure drops 7 EMERGENCY RAM AIR control knob PULL If smoke increases PUSH 8 LAND as soon as possible ...

Page 82: ...r altitude FLY THE AIRPLANE 4 Land as soon as possible NOTE Aircraft power is provided to the ESI 2000 display for normal operation Operation of the basic ESI system is automatic the system is powered ON while airplane power is ON The internal battery will provide power to the ESI 2000 if airplane power is lost Press any key to allow the ESI 2000 to continue operation using the internal battery CA...

Page 83: ...amber warning CAS message appearance FLY THE AIRPLANE Should automatic cut off occur or not 1 If possible REDUCE POWER 2 HOT AIR FLOW distributor turn to the right 3 CONTROL selector COCKPIT 4 TEMP C selector MINI 5 BLEED switch OFF RST 6 As soon as warning BLEED TEMP OFF BLEED switch AUTO If BLEED TEMP and BLEED OFF warnings still ON 7 If necessary EMERGENCY DESCENT 8 Continue FLY THE AIRPLANE at...

Page 84: ...ary FLY THE AIRPLANE 3 BLEED switch CHECK AUTO 4 DUMP switch CHECK UNDER GUARD 5 EMERGENCY RAM AIR control knob CHECK PUSHED 6 Limit flight altitude to maintain cabin altitude 10000 ft 7 If necessary EMERGENCY DESCENT CABIN DIFF PRESS Indicates a cabin pressure differential over 6 4 PSI 0 2 PSI 1 Pressurization indicator CHECK If ΔP 6 4 PSI 0 2 PSI 2 BLEED switch OFF RST 3 OXYGEN USE if necessary ...

Page 85: ...k the correct locking as well as the latches position of the access door and if installed of the pilot door DO NOT TAKE OFF if warning CAS message DOOR is ON In flight FLY THE AIRPLANE 1 START a SLOW DESCENT 2 Decrease cabin pressure differential by selecting a higher cabin altitude and maximum cabin rate If a real failure of one of the doors is noted 3 BLEED switch OFF RST 4 DUMP switch ACTUATED ...

Page 86: ...NDBOOK SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 2 24 ELEC FEATH FAULT Indicates a propeller feathering system malfunction 1 FEATHER circuit breaker PULL 2 LAND AS SOON AS POSSIBLE ...

Page 87: ...flection This immediately stops the flap motor and prevents further operation of the flaps 1 FLAPS circuit breaker PULL 2 FLAPS control lever UP 3 LAND as soon as possible maintaining AIRSPEED IAS 178 KIAS for deflections between UP and TO positions IAS 122 KIAS for deflections greater than TO position 4 FOR LANDING refer to LANDING WITH FLAPS MALFUNCTION BY FLYING THE AIRPLANE ...

Page 88: ...Warning CAS message AUX BOOST PMP ON ON If pressure is normal again and warning light is off mechanical pump has failed 5 Maintain AUX BP fuel switch ON LAND AS SOON AS PRACTICAL If FUEL PRESS remains ON 6 Tank selector SWITCH TANKS FUEL PRESS CAS message is OFF a supply problem may have occurred from the tank selected first air vent fuel icing etc If FUEL PRESS remains ON 7 Fullest tank SELECT 8 ...

Page 89: ...ITT 840 C for more than 20 seconds 2 Record the engine parameters displayed and OAT conditions 3 Cancel the flight inform maintenance department B After engine start In flight FLY THE AIRPLANE 1 REDUCE POWER If ITT remains higher than 840 C 1 REDUCE POWER to maintain ITT 840 C 2 LAND AS SOON AS POSSIBLE 3 Record the airplane and engine parameters displayed in case of overtemperature 4 Inform maint...

Page 90: ...onfirmed Due to the oil pressure drop the propeller blade angle may go towards high pitch and therefore lead to a Np propeller rotation speed decrease CAUTION PREPARE FOR AN ENGINE STOP SHORTLY REDUCE POWER TO THE MINIMUM NECESSARY LAND AS SOON AS PRACTICAL If engine looses power 2 Throttle CUT OFF Perform a FORCED LANDING OIL PRESS 1 Oil pressure indicator CHECK If the indicated pressure is in th...

Page 91: ...31 2013 Rev 1 Page 3 3 1 3 3 AMBER CAS MESSAGES AUTO SEL Indicates that there is no more automatic control mode running FLY THE AIRPLANE 1 FUEL SEL switch AUTO If it is on AUTO failure is confirmed 2 FUEL SEL switch MAN 3 Select tanks manually as required CAUTION MAXIMUM IMBALANCE IS 15 USG ...

Page 92: ...ormal if AUX BP fuel switch is in ON position FLY THE AIRPLANE If AUX BP fuel switch is in AUTO position 1 RESET to ON 2 THEN to AUTO If AUX BOOST PMP ON warning CAS message GOES OFF continue the flight normally If AUX BOOST PMP ON warning CAS message remains ON mechanical booster pump has failed 3 AUX BP fuel switch ON 4 LAND AS SOON AS POSSIBLE ...

Page 93: ...age 3 3 3 BAT AMP BATTERY current over 50A while on ground After starting the engine with airplane power a battery charge above 50 amperes is normal CAUTION DO NOT TAKE OFF IF BATTERY CHARGE 50 AMPERES If this indication remains steady at a high value it may be due to a battery or generation system failure ...

Page 94: ...0 October 31 2013 Rev 1 Page 3 3 4 BAT OFF Indicates that the SOURCE selector has been positioned on OFF or the battery plug is disconnected FLY THE AIRPLANE 1 SOURCE selector OFF 2 SOURCE selector BAT 3 If warning persists LAND AS SOON AS POSSIBLE 4 Monitor airplane mains voltage ...

Page 95: ...is not running possibly due to failure or BLEED switch on OFF RST position 1 CHECK BLEED switch position and CORRECT 2 If possible reduce power FLY THE AIRPLANE 3 BLEED switch OFF RST 4 BLEED switch AUTO 5 If warning BLEED OFF displayed 6 Limit flight altitude to maintain cabin altitude 10000 ft 7 If necessary no oxygen available EMERGENCY DESCENT 8 Continue flight ...

Page 96: ...ON 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 3 6 CHIP Indicates an oil chip detection 1 LAND AS SOON AS PRACTICAL FLY THE AIRPLANE 2 Or DO NOT TAKE OFF airplane is grounded 3 INFORM maintenance center ...

Page 97: ...3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 3 7 FRONT CARGO DOOR FORWARD BAGGAGE DOOR OPEN 1 On the ground CORRECT 2 IN THE AIR FLY THE AIRPLANE REDUCE to minimum speed available LAND AS SOON AS PRACTICAL ...

Page 98: ...es fuel tanks imbalanced by more than 15 USG for more than 30 seconds If FUEL SEL on AUTO mode SELECT the fullest Tank by pressing the SHIFT push button If FUEL SEL on MAN mode SELECT the fullest Tank by Shifting the Tank Selector manually FLY THE AIRPLANE Manage the fuel by selecting the fullest tank until fuel imbalance is below 15 USG ...

Page 99: ...age 3 3 9 FUEL LOW L R Indicates a level drop in the corresponding tank 1 Corresponding gage CHECK 2 Check the other tank has been automatically selected If not 3 FUEL SEL switch MAN 4 Select tank manually as required FLY THE AIRPLANE CHECK MINIMUM FUEL TAKE DECISION land as soon as practical if necessary ...

Page 100: ...K SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 3 10 GPU DOOR GPU DOOR OPEN 1 On the ground CORRECT 2 IN THE AIR FLY THE AIRPLANE REDUCE to minimum speed available LAND AS SOON AS PRACTICAL ...

Page 101: ...CEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 3 11 IGNITION IGNITION EXCITER IS RUNNING 1 CHECK IGNITION switch position 2 If weather permits correct by switching to AUTO FLY THE AIRPLANE IGNITION switch may be left ON for a long period ...

Page 102: ... 3 12 INERT SEP FAIL Symptoms Warning INERT SEP ON does not appear within 50 seconds following INERT SEP switch setting ON Inertial separator not retracted after 50 seconds following INERT SEP switch setting OFF Circuit breaker INERT DE ICE triggered 1 LEAVE icing conditions as soon as possible FLY THE AIRPLANE ...

Page 103: ...EDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 3 13 LOW LVL FAIL L R FUEL LOW LEVEL SENSOR FAILURE CHECK Fuel Remaining in Tanks TAKE DECISION If any doubt LAND AS SOON AS PRACTICAL FLY THE AIRPLANE On the ground contact Maintenance Center ...

Page 104: ... any indication of battery discharge In that case FLY THE AIRPLANE 3 Disconnect following ancillary electrical systems A C switch OFF STROBE switch OFF CABIN lights switch OFF AP TRIMS switch AP OFF Not necessary equipment OFF WINDSHIELD switch above 15 000 ft OFF BLEED switch before landing and on ground OFF RST Only use landing lights briefly and if necessary 4 GENERATOR selector RESET if necess...

Page 105: ...rmed 3 MAIN GENERATOR RESET push button PUSH In case of failure FLY THE AIRPLANE and 4 Disconnect following ancillary electrical systems to reduce battery loads below 80A A C switch OFF STROBE switch OFF CABIN lights switch OFF AP TRIMS switch AP OFF Not necessary equipment OFF WINDSHIELD switch above 15 000 ft OFF BLEED switch before landing and on ground OFF RST Only use landing lights briefly a...

Page 106: ... selector ST BY 6 ST BY GENERATOR RESET push button PRESS If successful 7 Disconnect ancillary electrical systems not essential 8 Monitor voltmeter and ammeter Prepare to LAND AS SOON AS POSSIBLE If not successful both generators failure is confirmed If possible return to VMC conditions 9 GENERATOR selector OFF If conditions allow VMC and non icing conditions 10 If altitude 10000 ft OXYGEN switch ...

Page 107: ...SE SYST switches OFF STROBE switch OFF BLEED A C switches OFF AUX BP switch OFF FUEL SEL switch MAN AP TRIMS switch OFF PFD 2 breaker PULL ADC 2 breaker PULL TAS breaker PULL DATA LINK breaker PULL CD player OFF INSTR CABIN ACCESS controls OFF XPDR 2 breaker PULL If icing conditions PITOT L HTR switch Checked ON WINDSHIELD switch ON Maintain minimum recommended speeds into known icing conditions F...

Page 108: ...e green sector 2 Land as soon as possible FLY THE AIRPLANE 3 MONITOR If the indicated temperature is not in the green sector 4 Failure is confirmed you can expect an OIL PRESSURE failure shortly Due to the oil pressure drop the propeller blade angle may go towards high pitch and therefore lead to a Np propeller rotation speed decrease CAUTION PREPARE FOR AN ENGINE STOP SHORTLY REDUCE POWER TO THE ...

Page 109: ...ing probe PITOT NO HT L LEFT Icing conditions may alter L H airspeed indications 1 AVOID icing conditions FLY THE AIRPLANE If it is not possible 2 Perform moderate descent or climb attitudes VMO overshoot and stall warning system are always operating PITOT NO HT R RIGHT VMO overshoot warning may be altered by icing conditions FLY THE AIRPLANE Monitor maximum airspeed 266 KIAS ...

Page 110: ...roved Edition 0 October 31 2013 Rev 1 Page 3 3 20 PROP DEICE FAIL Symptoms Propeller deicing green light is not lit Propeller vibrations 1 REDUCE power FLY THE AIRPLANE 2 ACTUATE Throttle to vary RPM within operating range 3 LEAVE icing conditions as soon as possible ...

Page 111: ...pproved Edition 0 October 31 2013 Rev 1 Page 3 3 21 STALL NO HEAT Correct operation of the aural stall warning may be altered by severe or prolonged icing MONITOR and MAINTAIN minimum airspeed according to airplane configuration and icing conditions FLY THE AIRPLANE ...

Page 112: ... Edition 0 October 31 2013 Rev 1 Page 3 3 22 VACUUM LOW Low vacuum may lead to malfunctioning of LEADING EDGE DEICING and PRESSURIZATION MONITOR If necessary fly to an altitude 10000 ft and return to VMC conditions as soon as possible FLY THE AIRPLANE BLEED switch OFF RST ...

Page 113: ... If the available power is weak extend the landing gear only on a glide path in final approach and extend full flaps only in short final Do not perform a go around CAUTION IN MANUAL OVERRIDE ENGINE IS NEITHER PROTECTED AGAINST SLAM ACCELERATIONS NOR AGAINST MAXIMUM SPEED OVERSHOOTING AVOID RAPID CONTROL MOVEMENTS AND MANAGE ENGINE PARAMETERS CAUTION IN SOME CASES WHEN MANUAL OVERRIDE CONTROL IS US...

Page 114: ...speed by setting airplane in nose up attitude at IAS 178 KIAS 2 INERT SEP switch ON 3 If ITT 840 C INERT SEP switch OFF 4 Landing gear control DN 5 Flaps TO 6 Establish a long final or an ILS approach respecting IAS 178 KIAS 7 When runway is assured Fuel tank selector OFF 8 Throttle FEATHER If available and necessary to extend trajectory 9 Flaps LDG as required at IAS 122 KIAS 10 Land normally WIT...

Page 115: ... REGULATION CONTROL NOT OPERATING May indicate a failure of the governor control 1 Continue the flight 2 If Np 2000 RPM do not perform a go around and do not use the reverse In that case the go around performance and the reverse efficiency might be lower than expected The airplane repair is mandatory before any other flight ...

Page 116: ... propeller governor and overspeed limiter failure In that case only the torque limiter operates to limit the power However the pilot intervention is necessary to maintain Np 2000 RPM The propeller reducer is designed for a max Np of 2200 RPM 1 Reduce the power and the airplane speed to avoid propeller rotation speeds higher than 2000 RPM 2 Land as soon as possible 3 Do not perform a go around A go...

Page 117: ...s not stop when the Throttle is set to CUT OFF proceed as follows 1 AP TRIMS switch OFF 2 INT LIGHTS panel All switches OFF 3 EXT LIGHTS panel All switches OFF 4 ECS panel All switches OFF 5 Tank selector OFF Wait for engine stop due to lack of fuel in the pipes 6 GENERATOR selector OFF 7 SOURCE selector OFF 8 Crash lever PULL DOWN 9 Inform maintenance department ...

Page 118: ...ms GEAR UNSAFE CAS message and GEAR UNSAFE red warning light ON Or Amber light flashing and 3 green lights OFF Actions Maintain IAS 150 KIAS 1 LDG GEAR circuit breaker PULL If the GEAR UNSAFE red warning light is off The flight may be continued without any restriction Before extending the landing gear refer to EMERGENCY GEAR EXTENSION If the GEAR UNSAFE red warning light is steady ON LDG GEAR circ...

Page 119: ...ev 1 Page 3 5 2 LANDING GEAR EXTENSION DISCREPANCY NOTE Symptoms have to be considered at the end of the sequence Symptoms GEAR UNSAFE CAS message and GEAR UNSAFE red warning light ON Or Amber light flashing and 0 to 3 green light s OFF Actions Maintain IAS 150 KIAS Refer to EMERGENCY GEAR EXTENSION ...

Page 120: ...MANUAL CONTROL AT THE END OF THE MANEUVER 5 Hand pump ACTUATE with maximum amplitude Press the CAS MASTER WARNING push button to reset the GEAR UNSAFE CAS message If GEAR UNSAFE red warning light is not illuminated and 3 green lights are illuminated Continue flight if necessary at a speed BELOW 178 KIAS exit and or remain outside icing conditions Land CAUTION DO NOT ENTER ICING CONDITIONS THIS COU...

Page 121: ...ND If manual extension bar remains soft or if one or more green indicator light s does do not illuminate upon pressing CHECK DOWN then a gear unlock condition is confirmed Recycle the landing gear as follows 9 By pass selector UNLOCK PUSH 10 Wait one minute 11 Landing gear control IAS 150 KIAS UP Perform landing gear extension attempts in the NORMAL mode while applying positive load factors during...

Page 122: ...ance 15 USG 57 litres 5 Choose a runway with headwind or crosswind blowing from defective gear side 6 Align the airplane to land on the runway edge opposite to the defective landing gear 7 Do a normal approach at 90 KIAS flaps on LDG 8 Land and set nose gear immediately on ground to assure lateral control 9 Use full aileron during roll out to lift the wing with the defective landing gear 10 Prefer...

Page 123: ...OSE LANDING GEAR DOWN UNLOCKED OR NOT DOWN 1 Transfer passengers to the rear if necessary 2 Approach Flaps LDG IAS 90 KIAS 3 Land with nose up attitude keep nose high 4 Throttle CUT OFF 5 Touch down slowly with nose wheel and keep elevator at nose up stop 6 Moderate braking 7 Crash lever PULL DOWN 8 EVACUATE after airplane comes to a stop ...

Page 124: ...2013 Rev 1 Page 3 5 7 LANDING WITH GEAR UP 1 Final approach Standard 2 Flaps LDG IAS 85 KIAS 3 BLEED switch OFF RST 4 DUMP switch ACTUATED When runway is assured 5 Throttle CUT OFF 6 Tank selector OFF 7 Flare out 8 After touch down crash lever PULL DOWN 9 EVACUATE after airplane comes to a stop ...

Page 125: ... inoperant flap control lever between UP and TO positions with no flaps warning light illumination 1 FLAPS circuit breaker PULL 2 Flap control lever UP 3 LAND as soon as possible maintaining airspeeds IAS 178 KIAS for deflections between UP and TO positions IAS 122 KIAS for deflections greater than TO position 4 For landing refer to LANDING WITH FLAPS MALFUNCTION ...

Page 126: ... flaps deflections from UP to TO position Proceed as for a normal landing maintaining approach airspeed IAS 105 KIAS Provide for a landing distance increased up to about 60 For flaps deflections greater than TO position Proceed as for a normal landing maintaining approach airspeed IAS 100 KIAS Provide for a landing distance increased up to about 50 ...

Page 127: ...00 will initiate the alignment process When a normal attitude display is available resume normal flight If attitude information remains unvalid use attitude information from the primary attitude display 3 Internal Battery Failure red X d battery indicator in flight Remain clear of IMC If in visual meteorological conditions Cycle power on ESI 2000 including internal power Maintain straight and leve...

Page 128: ... Maintain control of the airplane using airplane primary instruments Remove all airplane power to the ESI 2000 by opening the 3 Amps STBY INSTR circuit breaker Press any key button as stated by the on screen message Press the M Menu button repeatedly until Shutdown menu is shown Press and hold the Hold button until SHUTTING DN message is shown in the upper left corner of the screen ...

Page 129: ... 7 1 3 7 DEICING SYSTEM LEADING EDGES DEICING FAILURE Symptoms Failure on one of the two pneumatic deicing pulses Ice on wing outboard sections Or ice on wing inboard sections and stabilizers One of the two cycling green lights is not lit 1 LEAVE icing conditions as soon as possible 2 AIRFRAME DE ICE switch OFF ...

Page 130: ...ld being covered uniformly by ice No perception of heat when touching deiced section Windshield deicing green light is not lit Symptoms may result from overheat In that case 1 WINDSHIELD switch OFF ON when necessary In case of total failure 1 TEMP C selector Maxi warm 2 HOT AIR FLOW distributor turn to the left Before landing wait for a sufficient visibility ...

Page 131: ...n to the left 3 WINDSHIELD switch ON If not successful to gain sufficient visibility 4 HOT AIR FLOW distributor fully turn to the left 5 Manually clean a sufficient visibility area 6 If necessary clean L H side window and conduct a sideslip approach rudder pedals to the right in order to get sufficient landing visual references 7 For landing with flaps LDG maintain IAS 95 KIAS CAUTION IN CASE OF S...

Page 132: ...n 0 October 31 2013 Rev 1 Page 3 8 1 3 8 PRESSURIZATION MISCELLANEOUS CABIN NOT DEPRESSURIZED AFTER LANDING ΔP cabin 0 1 DUMP switch ACTUATED 2 BLEED switch OFF 3 EMERGENCY RAM AIR control knob PULLED if necessary 4 Wait for complete cabin depressurization before opening the door ...

Page 133: ...T AIR FLOW distributor Set to around a 10 o clock position If moisture continues 2 HOT AIR FLOW distributor turn to the left 3 WINDSHIELD switch ON If there is no improvement and if the flight safety is engaged 4 Altitude 10000 ft 5 BLEED switch OFF RST NOTE If in flight the cabin will quickly be depressurized Therefore the cabin vertical speed indicator and altimeter indications will rapidly meet...

Page 134: ... heavy swell with light wind land parallel to the swell rollers In heavy wind land facing wind 2 Flaps LDG 3 Maintain a descent rate as low as possible when approaching the water 4 Airspeed IAS 85 KIAS 5 BLEED switch OFF RST 6 DUMP switch ACTUATED 7 Crash lever PULL DOWN 8 Maintain attitude without rounding off until touch down 9 EVACUATE through EMERGENCY EXIT ...

Page 135: ...G WITHOUT ELEVATOR CONTROL 1 Configuration LANDING GEAR DN FLAPS LDG 2 Airspeed Maintain IAS 95 KIAS 3 Power as necessary to maintain airspeed according to an easy approach slope 300 ft min 4 Adjust elevator by using manual pitch trim wheel 5 When ground approaches decrease slope progressively 6 Reduce power progressively ...

Page 136: ...e 3 9 3 EMERGENCY EXIT USE 1 Check that the anti theft safety pin has been removed 2 Lift up the opening handle 3 Pull emergency exit assembly toward oneself to release it from its recess 4 Put the emergency exit door inside fuselage or throw it away from the fuselage through the opening 5 EVACUATE airplane ...

Page 137: ...dition 0 October 31 2013 Rev 1 Page 3 9 4 EMERGENCY BEACON ELT USE Before a forced landing 1 On COM VHF 121 5 MHZ or on a known air traffic control frequency transmit the MAY DAY signal if possible After landing 2 ELT remote control switch ON maintain it ON until aid arrives ...

Page 138: ...IM MALFUNCTION 1 AP TRIMS DISC push button PRESSED and HELD 2 AP TRIMS switch OFF 3 AP TRIMS DISC push button RELEASED 4 If necessary control wheel RETRIM CAUTION WHEN DISCONNECTING THE AUTOPILOT AFTER A PITCH TRIM MALFUNCTION HOLD THE CONTROL WHEEL FIRMLY UP TO 30 POUNDS OF FORCE ON THE CONTROL WHEEL MAY BE NECESSARY TO HOLD THE AIRPLANE LEVEL ...

Page 139: ...l tube totally Press on the red side vanes to inflate the harness Put the mask on the face 2 No smokes 3 position selector NORMAL 100 as required 3 In case of smokes 3 position selector EMERGENCY Don the smoke goggles onto the face 4 PASSENGERS OXYGEN switch ON 5 Check the oxygen flow indicator for the front seats the blinker is transparent and for the rear passengers the blinker is green 6 MICRO ...

Page 140: ...ILURE Symptoms erroneous indication in flight 1 PITOT L HTR switch CHECK ON 2 PITOT R STALL HTR switch CHECK ON If symptoms persist 3 ALTERNATE STATIC selector PULL THOROUGHLY If symptoms persist as well as on the electronic standby instrument ESI 2000 of the L H instrument panel carry out a precautionary approach maintaining an adequate speed ...

Page 141: ...Inform Air Traffic Control to exit severe icing conditions by changing the route or the altitude 2 Avoid any sudden maneuver on flight controls 3 Do not engage the autopilot 4 If the autopilot is engaged hold the control wheel firmly and disengage the autopilot 5 If an unusual roll response or uncommanded roll control movement is observed reduce the angle of attack 6 Do not extend flaps when holdi...

Page 142: ...P will continue to be displayed with a ghosted airplane icon in the center and an amber DR overwriting the icon Airplane position will be based upon the last valid GPS position then estimated by Dead Reckoning methods Changes in true airspeed altitude or winds aloft can affect the estimated position substantially Dead Reckoning is only available in Enroute mode Terminal and Approach modes do not s...

Page 143: ...st known wind data and the last known GPS position to estimate the airplane s current position DR information will be available for a maximum of 20 minutes MAP TRAFFIC MAP display is not dependent on GPS information The position of displayed traffic relative to the airplane symbol on the map is still accurate Loss Of Integrity LOI Mode Active when the airplane is within 30 NM or departure airport ...

Page 144: ...V GPS glide path vertical guidance will be removed from the PFD The approach may be continued using the LNAV only minimums During any GPS approach in which both precision and non precision alarm limits are exceeded the G1000 System will flag the lateral guidance and display a system message ABORT APPROACH loss of navigation Immediately upon viewing the message the unit will revert to Terminal navi...

Page 145: ... BOTH ON AHRS2 is associated to white annunciation HDG NO COMP and or PIT NO COMP and or ROL NO COMP 1 Fly the airplane manually 2 AHRS1 and or AHRS2 circuit breaker CHECKED IN If pilot wishes 3 FD default mode PITCH and ROLL ENGAGED 4 FD specifics modes HDG NAV ALT ENGAGED as DESIRED 5 Fly the airplane manually to follow Command Bars If ALL white annunciations HDG NO COMP and or PIT NO COMP and o...

Page 146: ...nd or ADC2 circuit breaker CHECKED IN A If yellow annunciation BOTH ON ADC1 or BOTH ON ADC2 is associated to white annunciation IAS NO COMP and or ALT NO COMP 1 NO action required If ALL white annunciations IAS NO COMP and or ALT NO COMP go OFF refer to following B procedure B If yellow annunciation BOTH ON ADC1 or BOTH ON ADC2 ONLY not associated to white annunciation IAS NO COMP and or ALT NO CO...

Page 147: ...roved Edition 0 October 31 2013 Rev 1 Page 3 10 1 3 10 ANNEX AIR START ENVELOPE Air start may be attempted outside of the envelope However above 20000 ft ITT tends to increase during start and prudence is recommended Figure 3 10 1 AIR START ENVELOPE AIR START ENVELOPE ...

Page 148: ...e CUT OFF 8 STARTER switch ON take a time CAUTION IF 5 SECONDS AFTER HAVING POSITIONED THE STARTER SWITCH IN ON POSITION THERE IS NO START INTERRUPT STARTING ATTEMPT USING THE ABORT POSITION OF THE STARTER SWITCH When Ng around 13 9 Throttle LO IDLE 10 ITT and Ng Monitor When Ng higher than 52 11 Check starter is OFF automatically CAUTION IF THE STARTER DOES NOT GO OFF AUTOMATICALLY DO IT USING TH...

Page 149: ...PILOT S OPERATING HANDBOOK SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 10 3 BUS BAR Figure 3 10 2 1 3 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 150: ...PILOT S OPERATING HANDBOOK SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 10 4 BUS BAR Figure 3 10 2 2 3 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 151: ...PILOT S OPERATING HANDBOOK SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 10 5 ESS BUS BAR Figure 3 10 2 3 3 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 152: ...1 Determine the usable oxygen percent using the chart Figure 3 10 3 Figure 3 10 3 Usable oxygen 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 3 10 4 by the percent obtained with the chart Figure 3 10 3 Number of passengers Duration Passengers plus 1 pilot Duration Passengers plus 2 pilots 0 226 113 1 162 94 2 127 81 3 104 71 4 88 65 Figure 3 10 4 Oxygen ...

Page 153: ...PILOT S OPERATING HANDBOOK SECTION 3 EMERGENCY PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 3 10 7 EMERGENCY DESCENT PROFILES Figure 3 10 5 EMERGENCY DESCENT PROFILES ...

Page 154: ...UMP switch ACTUATED 7 Glide speed 120 KIAS maintained until favourable ground approach If ground allows it 8 ESS BUS TIE switch NORM in order to have GEAR and FLAPS available 9 Landing gear control DN If night conditions 10 OFF TAXI LDG switch LDG If ground does not allow it 11 Keep landing gear UP 12 When chosen ground is assured FLAPS LDG 13 Crash lever PULL DOWN 14 Final approach IAS 85 KIAS 15...

Page 155: ...E TAKEOFF 4 3 19 TAKEOFF 4 3 21 CLIMB 4 3 22 CRUISE 4 3 23 DESCENT 4 3 24 BEFORE LANDING 4 3 25 LANDING 4 3 26 GO AROUND 4 3 27 TOUCH AND GO 4 3 28 AFTER LANDING 4 3 29 SHUT DOWN 4 3 30 4 4 AMPLIFIED PROCEDURES 4 4 1 PREFLIGHT INSPECTION 4 4 1 BEFORE STARTING ENGINE 4 4 10 STARTING ENGINE 4 4 14 MOTORING 4 4 16 MOTORING FOLLOWED BY AN ENGINE START 4 4 18 AFTER STARTING ENGINE 4 4 20 IN FLIGHT AVAI...

Page 156: ... 5 4 FLIGHT UNDER HEAVY PRECIPITATIONS 4 5 5 UTILIZATION ON RUNWAYS COVERED WITH WATER 4 5 5 UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW 4 5 6 UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS 4 5 7 UTILIZATION BY COLD WEATHER 0 C TO 25 C AND VERY COLD WEATHER 25 C TO 40 C 4 5 9 LANDING PROCEDURE WITH STRONG HEADWIND OR CROSSWIND 4 5 18 UTILIZATION ON GRASS RUNWAY 4 5 19 GP...

Page 157: ...vides procedures for the conduct of normal operation of TBM 900 airplane The first part of this Section lists the normal procedures required as a check list The amplified procedures are developed in the second part of the Section The normal procedures for optional systems are given in Section 9 Supplements of the Pilot s Operating Handbook ...

Page 158: ... VR Flaps TO 90 KIAS 2 Best rate of climb speed VY Landing gear UP flaps UP 124 KIAS 3 Best angle of climb speed Vx 100 KIAS 4 Maximum speed Flaps TO 178 KIAS Flaps LDG 122 KIAS 5 Maximum speed with landing gear down 178 KIAS 6 Maximum landing gear operating speed Extension 178 KIAS Retraction 150 KIAS 7 Approach speed Flaps LDG 85 KIAS 8 Maximum operating speed VMO 266 KIAS 9 Glide speed maximum ...

Page 159: ... and control surfaces In case of night flight check good operation of all navigation lights landing lights strobe lights and make sure that an emergency lamp is on board If icing conditions are foreseen particularly check good functioning of all electrical and pneumatic ice protection systems Check that type and quantity of fuel used for refueling are correct Remove covers on pitots 2 static ports...

Page 160: ...PILOT S OPERATING HANDBOOK SECTION 4 NORMAL PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 4 3 2 PREFLIGHT INSPECTION 2 9 Figure 4 3 1 PREFLIGHT INSPECTION ...

Page 161: ...tions checked 6 Park brake ON 7 Landing gear control DN 8 Engine controls MAN OVRD control Backward CAUTION WHEN THE ENGINE IS SHUTDOWN THE THROTTLE MUST NOT BE MOVED INTO THE REVERSE AREA Throttle CUT OFF 9 Flaps control UP 10 Fuel tank selector L or R 11 Landing gear emergency control Lever Pulled down By pass selector Pushed Door In place 12 ECS panel BLEED switch OFF RST A C switch OFF DUMP sw...

Page 162: ...CTRIC POWER panel Crash lever UP GENERATOR selector MAIN SOURCE selector OFF 20 Access lighting Checked 21 INT LIGHTS panel OFF 22 EXT LIGHTS panel All switches OFF 23 Pilot s OXYGEN switch OFF 24 PASSENGERS OXYGEN switch OFF 25 Emergency lighting Checked CAUTION BEFORE SELECTING SOURCE CHECK 26 IGNITION switch AUTO or OFF 27 STARTER switch OFF 28 Landing gear control DN 29 SOURCE selector BATT or...

Page 163: ...e the airplane check operation of all lights and the stall warning horn Reentering the airplane 33 EXT LIGHTS panel All switches OFF 34 DE ICE SYSTEM panel All switches OFF ICE LIGHT ON 35 CAS display Checked 36 Left and right fuel quantities Checked 37 Flaps control LDG 38 Landing gear panel Warning lights 3 GREEN ON Light Test all lights red green FLASHING 39 DE ICE SYSTEM panel PITOT L HTR swit...

Page 164: ...l net if 4 seat accommodation and if baggage transportation In place Check general condition 8 Doors operation Checked 9 Stairs condition Checked Condition Play AIRPLANE OUTSIDE L H wing III 1 Flap Checked Condition Play 2 Aileron and trim Spoiler Checked Condition Free movement Deflection 3 Trailing edge static discharger Checked Condition Attachment 4 Winglet nav lights strobe landing light reco...

Page 165: ...t used 3 Fuel circuit drain Drained Fuel free of water and contamination Filter contamination indicator Checked 4 L H exhaust stub Checked Condition No crack 5 Upper engine cowls OPEN For the first flight of the day Oil cap Closed Locked Engine oil level Checked Fuel pipes Checked No leak deterioration wear 6 Engine cowls Condition Checked Closed Locked 7 Air inlets Main No crack Unobsctruted Late...

Page 166: ...Closed Locked 7 Fuel tank air vent Unobstructed Checked 8 Right pitot Condition Checked 9 Winglet nav light strobe landing light recognition light taxi light Condition Checked 10 Trailing edge static discharger Checked Condition Number Attachment 11 Aileron spoiler Checked Condition Free movement Deflection 12 Flap Checked Condition Play 13 Rear R H karman Oxygen cylinder OPEN Oxygen quantity Chec...

Page 167: ...ecked Condition Attachments 6 Elevator and trim Checked Condition Deflection free movement Trim position 7 Static dischargers Checked Condition 8 Vertical stabilizer deicer boots Checked Condition Attachments 9 Rudder and trim Checked Condition Trim position 10 Static dischargers Checked Condition 11 Tail cone nav lights strobe Condition Checked 12 Static pressure ports Clean Checked ...

Page 168: ...NEL AND SEAT HOUSING IN LOW AND INTERMEDIATE POSITIONS 6 L H and R H pedals Adjusted 7 Belts and harnesses Pilot and passengers Fastened 8 Crash lever Down 9 ELT ARM 10 MICRO MASK micro inverter MICRO 11 De ice systems All OFF 12 Park brake ON 13 Landing gear control DN 14 Pitch trim wheel Checked 15 MAN OVRD control Backward CAUTION MAKE SURE THAT MAN OVRD CONTROL IS BACKWARD TO AVOID OVERTEMPERA...

Page 169: ...N 28 AUX BP switch OFF 29 IGNITION switch AUTO 30 STARTER switch OFF 31 DIMMER switch OFF 32 CABIN switch OFF 33 ACCESS switch OFF 34 PANEL rheostat Fully turned to the left 35 All lights OFF 36 Crash lever UP 37 GENERATOR selector MAIN 38 Battery voltage Checked 39 SOURCE selector BATT battery start GPU GPU start 40 Park Brake ON 41 PASSENGERS OXYGEN switch OFF 42 Pilot s OXYGEN switch ON 43 Fron...

Page 170: ... STARTER SWITCH THE UTILISATION OF THE STARTER IS BOUND BY LIMITATIONS MENTIONED IN CHAPTER 2 4 STARTER OPERATING LIMITS When Ng 13 and ITT below 150 C and time below 20 s 6 Throttle LO IDLE When Ng 52 2 7 Check Starter is automatically OFF CAUTION IF THE STARTER DOES NOT GO OFF AUTOMATICALLY DO IT USING THE ABORT POSITION OF THE STARTER SWITCH 8 Engine parameters Checked If GPU start 9 SOURCE sel...

Page 171: ... MORE THAN 5 SECONDS NG 30 AFTER 30 SECONDS OF STARTER USE NG 50 AFTER 60 SECONDS OF STARTER USE ABORT STARTING PROCEDURE THROTTLE CUT OFF IGNITION SWITCH AUTO WHEN ITT 850 C STARTER SWITCH ABORT PILOT S OPERATING HANDBOOK SECTION 4 NORMAL PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 4 3 13 STARTING ENGINE 2 2 15 GENERATOR selector Checked MAIN ...

Page 172: ...OVRD control Backward CAUTION WHEN THE ENGINE IS SHUTDOWN THE THROTTLE MUST NOT BE MOVED INTO THE REVERSE AREA Throttle CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON 3 IGNITION switch OFF To clear fuel and vapor internally trapped 4 STARTER switch ON take a time during 15 sec maxi 5 STARTER switch ABORT To cool engine following shut down in high temperature environment 4 STARTER switch ON t...

Page 173: ...LE MUST NOT BE MOVED INTO THE REVERSE AREA Throttle CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON 3 IGNITION switch OFF 4 STARTER switch ON take a time 5 After 20 seconds and ITT 150 C IGNITION switch AUTO Ng Check 13 Throttle LO IDLE 6 Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure When Ng 52 2 7 Check Starter is automatically OFF CAUTION ...

Page 174: ... MUST NOT BE MOVED INTO THE REVERSE AREA Throttle CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON 3 IGNITION switch OFF 4 STARTER switch ON take a time 5 After 20 seconds and ITT 150 C IGNITION switch AUTO Ng Check 13 Throttle LO IDLE 6 Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure When Ng 52 2 7 Check Starter is automatically OFF CAUTION IF...

Page 175: ...v 1 Page 4 3 16 MOTORING FOLLOWED BY AN ENGINE START 2 2 10 Engine instruments Check Ng 69 2 Oil pressure Oil temperature ITT green sector 11 FUEL panel AUX BP switch AUTO 12 Generator RESET if necessary Generator and battery ammeters Charge checked BAT and ESS voltmeters Voltage checked V 28 Volts ...

Page 176: ...ailable for the planned flight see tables of paragraph IN FLIGHT AVAILABLE OXYGEN QUANTITY in Chapter 4 4 and Chapter 7 10 for a FAR 135 type operation 5 PFD 1 MFD and PFD 2 Brightness Adjust if necessary DISPLAY BACKUP button Check then return to NORMAL mode When ammeter 100 A 6 ECS panel BLEED switch AUTO A C switch AUTO PRES MODE AUTO CONTROL selector As required TEMP C selectors Adjust HOT AIR...

Page 177: ... Rev 1 Page 4 3 18 TAXIING CAUTION GENERATOR LOAD 200 AMPS 1 TAXI light ON 2 Passenger briefing As required 3 Park brake OFF 4 L H brakes Checked 5 Nose wheel steering Checked 6 Throttle As required CAUTION AVOID USING REVERSE DURING TAXIING 7 Flight instruments Check 8 CAS Checked 9 LFE Checked ...

Page 178: ...switch As required PITOT L HTR switch ON PITOT R STALL HTR switch ON 6 Flight controls Deflections checked 7 Trims SET 8 Pilot s Passengers belts Check Passengers table Stowed 9 STROBE switch ON 10 CAS display Checked 11 Fuel Gages quantity symmetry Checked FUEL SEL switch Check AUTO AUX BP fuel switch Check AUTO 12 Flight instruments Checked Altimeter setting Adjusted Checked LFE Adjusted Checked...

Page 179: ...MAL PROCEDURES EASA Approved Edition 0 October 31 2013 Rev 1 Page 4 3 20 BEFORE TAKEOFF 2 2 15 Engine instruments Check 16 Battery charge 50 Amperes CAUTION DO NOT TAKE OFF IF BATTERY CHARGE 50 Amperes CAS MESSAGE BAT AMP ON 17 Park brake OFF ...

Page 180: ...3 Lights OFF TAXI LDG switch LDG 4 Engine instruments CHECK ITT green sector 5 CAS display Check All messages OFF except INERT SEP ON if used except IGNITION if used 6 Apply brakes and increase power up to RPM in green range 7 Brakes Released 8 Throttle TRQ 100 9 Takeoff attitudes Normal takeoff Attitude 10 Short takeoff Weight 6579 lbs 2984 kg Attitude 15 Weight 6579 lbs 2984 kg Attitude 12 5 10 ...

Page 181: ...push button ON 3 Lights OFF TAXI LDG switch As required 4 Throttle Adjust CAUTION OBSERVE TRQ Ng Np ITT T AND OIL PRESSURE LIMITATIONS USE OPTIMUM TORQUE AND OR REFER TO TABLES IN CHAPTER 5 8 5 Climb speed As required 6 ECS panel TEMP C selectors Adjust 7 Fuel tank gages Check correct Quantity Symmetry 8 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPIT...

Page 182: ...HAPTER 5 8 2 Pressurization Check 3 Fuel Gages Check REGULARLY CHECK consumption expected fuel at destination Pre MOD70 0402 28 tank automatic change every 10 minutes Post MOD70 0402 28 tank automatic change every 5 minutes All symmetry max dissymmetry 15 USG 57 Litres 4 Cruise parameters engine data Check Record 5 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEA...

Page 183: ...s Done 2 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNITION AND INERT SEP ON 3 Windshield misting protection system As required 4 Fuel Gages Check Quantity Symmetry Fullest tank Select 5 Passengers briefing As required 6 Seats belts and harnesses Locked 7 Passengers table Stowed ...

Page 184: ...Gages Check Quantity Symmetry Fullest tank Select 3 INERT SEP switch ON 4 Landing gear control IAS 178 KIAS DN then 3 green ON 5 Flaps IAS 178 KIAS TO 6 Lights OFF TAXI LDG switch LDG Stabilized approach 7 Flaps IAS 122 KIAS LDG 8 Approach speed Flaps LDG Without AP engaged 85 KIAS With AP engaged 85 KIAS 9 Autopilot 200 ft Disconnect 10 YAW DAMPER push button OFF ...

Page 185: ... After wheels touch 2 Reverse As required Reverse may be applied as soon as the wheels touch the ground To avoid ingestion of foreign objects come out of the reverse range as speed reduces and use the brakes if necessary for further deceleration CAUTION ON SNOWY OR DIRTY RUNWAY IT IS BETTER NOT TO USE REVERSE BELOW 40 KIAS 3 Brakes As required ...

Page 186: ...84 kg When the vertical speed is positive and when IAS is at or above 85 KIAS 4 Landing gear control UP All warning lights OFF When IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed As required Weight above 6579 lbs 2984 kg When the vertical speed is positive and when IAS is at or above 90 KIAS 7 Landing gear control UP All warning lights OFF When IAS is at or above 115 KIAS 8 Flaps UP 9 Climb ...

Page 187: ...O Before wheels touch 1 Takeoff distances Checked See Takeoff distances Chapter 5 9 2 Rotation speed VR Checked After wheels touch 1 Flaps TO 2 Elevator trim Green sector 3 Throttle T O power 4 Takeoff attitudes Normal takeoff ATTITUDE 10 Short takeoff Weight 6579 lbs 2984 kg ATTITUDE 15 Weight 6579 lbs 2984 kg ATTITUDE 12 5 ...

Page 188: ...PLANE STOPPED 1 DE ICE SYSTEM panel AIRFRAME DE ICE switch OFF PROP DE ICE switch OFF INERT SEP switch Checked ON WINDSHIELD switch As required PITOT L HTR switch OFF PITOT R STALL HTR switch OFF BLEED switch As required 2 Radar if installed Checked Standby 3 Transponder Checked Standby 4 Flaps UP 5 STROBE switch OFF 6 Lights OFF TAXI LDG switch TAXI 7 Trims TAKEOFF position ...

Page 189: ...OFF 3 Throttle Flight IDLE for 1 minute minimum 4 TAXI light OFF 5 AP TRIMS switch OFF 6 Throttle LO IDLE for 15 seconds 7 Throttle CUT OFF 8 INERT SEP switch OFF 9 EXT LIGHTS panel All switches OFF 10 INT LIGHTS panel All switches OFF 11 Fuel AUX BP switch OFF FUEL SEL switch MAN Tank selector OFF 12 OXYGEN switch OFF 13 GENERATOR selector OFF 14 SOURCE selector OFF 15 Crash lever Pulled down 16 ...

Page 190: ...O PARAGRAPH MOTORING ESI 2000 NORMAL PROCEDURE No pilot action required for normal shutdown The ESI 2000 will shut down within 5 minutes ESI 2000 MANUAL PROCEDURE The ESI 2000 can be manually shut down when in the discharge mode to conserve battery power Remove all airplane power from the ESI Press any key button as stated by the on screen message Press the M Menu button repeatedly until shutdown ...

Page 191: ... Flight controls Deflections checked 6 Park brake ON 7 Landing gear control DN 8 Engine controls MAN OVRD control Backward CAUTION WHEN THE ENGINE IS SHUTDOWN THE THROTTLE MUST NOT BE MOVED INTO THE REVERSE AREA When engine is shut off a lack of hydraulic pressure prevents movement into reverse range Trying to force the mechanism will cause damage Throttle CUT OFF 9 Flaps control UP 10 Fuel tank s...

Page 192: ...BP switch OFF 18 ENGINE START panel IGNITION switch AUTO or OFF The IGNITION switch is normally selected to AUTO This ensures ignition whenever the STARTER switch is set to ON STARTER switch OFF If not starter is going to operate as soon as SOURCE selector is moved to BATT or GPU if connected 19 ELECTRIC POWER panel Crash lever UP GENERATOR selector MAIN SOURCE selector OFF 20 Access lighting Chec...

Page 193: ...e is not an absolute guarantee for a correctly charged battery It is recommended to use a GPU in cold weather when airplane has been stopped more than 3 hours at a temperature below 10 C 14 F If GPU source 28 Volts If using a GPU ensure that it provides a 28 volt regulated voltage with negative on earth as well as it supplies 800 amperes minimum and 1000 amperes maximum See placard located near gr...

Page 194: ... indicated by display of corresponding CAS message when control switches are ON WARNING CAS MESSAGE PITOT HT ON L R ON WARNING CAS MESSAGE STALL HEAT ON ON PITOT L HTR switch OFF PITOT R STALL HTR switch OFF WARNING DO NOT TOUCH PITOTS NOR STALL WARNING VANE THEY COULD BE HOT ENOUGH TO BURN SKIN 40 Crash lever Down Cabin II 1 Cabin fire extinguisher Checked Pressure Attachment 2 Seats belts Checke...

Page 195: ...ntion should be paid to possible blockages in airspeed sensing lines foreign objects in engine intake and exhaust stubs and water contamination of the fuel system L H wing III 1 Flap Checked Condition Play Also inspect the lower surface as well as flap fairing where pebbles and even ice in case of slush on the runway may have accumulated 2 Aileron and trim Spoiler Checked Condition Free movement D...

Page 196: ...mulates in fuel tanksumps Refer to Section 8 for servicing operations relative to fuel additives 12 L H main landing gear Shock absorber doors tire wheel well Checked If airplane has been used from muddy airfields or in snow check wheel wells to make sure they are clean and not obstructed Check frequently all landing gear retraction mechanism components shock absorbers tires and brakes This is par...

Page 197: ...e case for upper air inlets of RAM AIR system circular grille located in front of R H windshield and of vapor cycle cooling system two rectangular grilles located forward of the circular grille 8 Propeller and spinner Checked No nicks cracks or oil leaks Attachment In case of operation from contaminated runways it is necessary to carefully examine propeller blades where traces of abrasion may be f...

Page 198: ...sed Locked 7 Fuel tank air vent Unobstructed Checked 8 Right pitot Condition Checked 9 Winglet nav light strobe landing light recognition light taxi light Condition Checked 10 Trailing edge static discharger Checked Condition Number Attachment 11 Aileron spoiler Checked Condition Free movement Deflection 12 Flap Checked Condition Play 13 Rear R H karman Oxygen cylinder OPEN Oxygen quantity Checked...

Page 199: ...elage Closed Checked Attachments 5 Horizontal stabilizer deicer boots R H side Checked Condition Attachments 6 Elevator and trim Checked Condition Deflection free movement Trim position To check the deflection hold the two half elevators near fuselage inside both elevator trims to avoid stresses 7 Static dischargers Checked Condition 8 Vertical stabilizer deicer boots Checked Condition Attachments...

Page 200: ...OVEMENT WHEN SEAT IS IN MAXIMUM HIGH PERMISSIBLE POSITION TO AVOID INTERFERENCE BETWEEN SIDE UPHOLSTERY PANEL AND SEAT HOUSING IN LOW AND INTERMEDIATE POSITIONS Adjust pilot s and R H front station seats and harnesses so as to permit access to flight controls The pilot at L H station must be able to easily reach ECS panel 6 L H and R H pedals Adjusted 7 Belts and harnesses Pilot and passengers Fas...

Page 201: ...FF RST 20 DUMP switch Guarded 21 A C switch OFF 22 ALTERNATE STATIC selector Pushed 23 EMERGENCY RAM AIR control knob Pushed 24 Circuit breakers All pushed 25 ESS BUS TIE switch Guarded 26 AP TRIMS switch OFF 27 FUEL SEL selector MAN 28 AUX BP switch OFF 29 IGNITION switch AUTO The IGNITION switch is normally selected to AUTO This ensures ignition whenever the starter is activated 30 STARTER switc...

Page 202: ... pedals before turning brake selector to the right 41 PASSENGERS OXYGEN switch OFF 42 Pilot s OXYGEN switch ON Set ON the pilot s OXYGEN switch after the PASSENGERS Oxygen switch position check to avoid passengers mask deployment Check the OXYGEN CAS message is off If not open isolation valve of the oxygen cylinder in R H Karman 43 Front oxygen masks Checked Press push button PRESS TO TEST the bli...

Page 203: ...ion 0 October 31 2013 Rev 1 Page 4 4 13 BEFORE STARTING ENGINE 4 4 46 LFE selection Done Landing Field Elevation selection is done using destination airport of the flight plan pressing SYSTEM and then FMS LFE on the MFD a manual entry pressing SYSTEM then MAN LFE on the MFD ...

Page 204: ...HE ABORT POSITION OF THE STARTER SWITCH THE UTILISATION OF THE STARTER IS BOUND BY LIMITATIONS MENTIONED IN CHAPTER 2 4 STARTER OPERATING LIMITS When Ng 13 and ITT below 150 C and time below 20 s In case of starting with hot engine an ITT decrease below 150 C within starter operation limits may allow to stay within the allowed ITT enveloppe 6 Throttle LO IDLE When throttle is positioned on LO IDLE...

Page 205: ... Approved Edition 0 October 31 2013 Rev 1 Page 4 4 15 STARTING ENGINE 2 2 10 Electrical network Checked 11 GPU disconnection done by ground team Check GPU DOOR CAS message is OFF When Ground team is cleared from propeller 12 Throttle Flight IDLE 13 Engine parameters Checked Check Ng 6 9 2 oil pressure and ITT in green sector 14 AUX BP switch AUTO 15 GENERATOR selector Checked MAIN Check MAIN GEN C...

Page 206: ...is possible that no trace of drainage be observed under engine due to the drainage collector intended to prevent parking area from contamination CAUTION AFTER ANY STARTING INTERRUPT PROCEDURE WAIT FOR ENGINE TOTAL SHUT DOWN WAIT AT LEAST 30 SECONDS BEFORE INITIATING A MOTORING 1 Engine controls MAN OVRD control Backward CAUTION WHEN THE ENGINE IS SHUTDOWN THE THROTTLE MUST NOT BE MOVED INTO THE RE...

Page 207: ...ure environment 4 STARTER switch ON take a time during 30 sec WARNING CAS MESSAGE STARTER ON If ignition symptoms occur ITT increasing check that IGNITION switch is OFF that throttle is on CUT OFF and continue motoring 5 STARTER switch ABORT WARNING CAS MESSAGE STARTER OFF 6 FUEL panel AUX BP switch OFF WARNING CAS MESSAGE AUX BOOST PMP ON OFF WARNING CAS MESSAGE FUEL PRESS ON ...

Page 208: ...eleration 1 Engine controls MAN OVRD control Backward CAUTION WHEN THE ENGINE IS SHUTDOWN THE THROTTLE MUST NOT BE MOVED INTO THE REVERSE AREA Throttle CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON WARNING CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAGE FUEL PRESS OFF 3 IGNITION switch OFF 4 STARTER switch ON take a time 5 After 20 seconds and ITT 150 C IGNITION switch AUTO Ng Check 13 ...

Page 209: ...ER SWITCH 8 Engine instruments CHECK Ng 52 Oil pressure ITT green sector 9 Throttle Flight IDLE 10 Engine instruments Check Ng 69 2 Oil pressure Oil temperature ITT green sector 11 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF 12 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary MAIN GEN CAS message normally goes out as soon as STARTER CAS message goes out If n...

Page 210: ... SWITCH 8 Engine instruments CHECK Ng 52 Oil pressure ITT green sector 9 Throttle HI IDLE 10 Engine instruments Check Ng 69 2 Oil pressure Oil temperature ITT green sector 11 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF 12 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary MAIN GEN CAS message normally goes out as soon as STARTER CAS message goes out If not inc...

Page 211: ...RIMS switch ON 4 Oxygen supply Available for the planned flight see tables of paragraph IN FLIGHT AVAILABLE OXYGEN QUANTITY in this Chapter and Chapter 7 10 for a FAR 135 type operation 5 PFD 1 MFD and PFD 2 Detailed control procedures of G1000 avionics system are described in the GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the Socata TBM 900 Brightness Adjust if necessary DISP...

Page 212: ...Yaw trim L R then adjusted Adjust the indicator in green range TO TAKEOFF Roll trim L R then adjusted Adjust the indicator first at neutral position horizontal marker 13 DE ICE SYSTEM panel Checked Flight into known icing conditions is authorized only when all ice protection equipment are operating correctly This equipment may be activated before takeoff even during taxiing in case of icing condit...

Page 213: ...eck to choose a Ng power 80 in order to obtain operation design pressure which enables illuminating surely the two green lights and avoiding VACUUM LOW untimely alarms AIRFRAME DE ICE switch ON Visually check functioning of deicer boots during 1 total cycle and illumination of the two green lights located above the switch The cycle lasts 67 seconds Check both inflation impulses and illumination of...

Page 214: ... 1 Determine the usable oxygen percent using the chart Figure 4 4 1 Figure 4 4 1 Usable oxygen 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 4 4 2 by the percent obtained with the chart Figure 4 4 1 Number of passengers Duration Passengers plus 1 pilot Duration Passengers plus 2 pilots 0 226 113 1 162 94 2 127 81 3 104 71 4 88 65 Figure 4 4 2 Oxygen dura...

Page 215: ...6 Throttle As required After initial acceleration throttle may be in the TAXI RANGE sector avoiding excessive movements in order to keep a constant ground speed CAUTION AVOID USING REVERSE DURING TAXIING Operation in the Beta β range reverse is not restricted during ground operations However foreign particles dust sand grass gravel etc may be blown into the air ingested by the engine above all if ...

Page 216: ...RAME DE ICE switch As required PROP DE ICE switch As required If runway is in good condition without icing conditions INERT SEP switch As required WARNING CAS MESSAGE INERT SEP ON As required CAS message goes out immediately but it takes 30 seconds to retract the separator If there is standing water or other contamination on the runway INERT SEP switch Leave ON WARNING CAS MESSAGE INERT SEP ON ON ...

Page 217: ...owed 9 STROBE switch ON 10 CAS display Checked All messages OFF EXCEPT PARK BRAKE ON and if used INERT SEP ON ON 11 Fuel Gages quantity symmetry Checked Maximum dissymmetry is 15 USG 57 litres It is recommended to select the fullest tank by pushing the SHIFT push button if the lift off is expected within 1 minute and 15 seconds FUEL SEL switch Check AUTO AUX BP fuel switch Check AUTO 12 Flight ins...

Page 218: ...CHECKED Transponder code ADJUSTED CHECKED 16 Engine instruments Check All engine parameters must be in green range except propeller RPM which will be about 1000 RPM or more with throttle at Flight IDLE 17 Battery charge 50 Amperes CAUTION DO NOT TAKE OFF IF BATTERY CHARGE 50 Amperes CAS MESSAGE BAT AMP ON After starting engine with airplane power a battery charge above 50 amperes is normal If this...

Page 219: ...when windshield deice systems are activated Altimeter setting on PFDs 1 2 Check 3 Lights OFF TAXI LDG switch LDG 4 Engine instruments CHECK ITT green sector 5 CAS display Check All messages OFF except INERT SEP ON if used except IGNITION if used 6 Apply brakes and increase power up to RPM in green range 7 Brakes Released Torque will be about 40 to 60 before brake release For a normal takeoff maxim...

Page 220: ...oes off when the 3 landing gears are up locked GEAR UNSAFE red warning light ON and GEAR UNSAFE CAS message indicate an anomaly refer to EMERGENCY PROCEDURES It is possible that the 3 landing gear position green indicator lights flash unevenly then go off at the end of the sequence At sequence end check All warning lights OFF 13 Initial climb speed 115 KIAS In case of initial climb at Vx it is rec...

Page 221: ...a particular value of ITT For a simplified engine operation during climb power may be set first of all by torque using 100 then when the ITT typical value for climb is reached by indicated ITT using this particular value The margin between this indicated ITT and 790 C recommended ITT limit during continuous operation will gradually reduce as flight time is performed 5 Climb speed 124 KIAS Performa...

Page 222: ...m power When INERT SEP switch is OFF a more accurate setting of power must then be performed according to cruise performance tables presented in Chapter 5 11 2 Pressurization Check 3 Fuel Gages Check REGULARLY CHECK consumption expected fuel at destination Pre MOD70 0402 28 tank automatic change every 10 minutes Post MOD70 0402 28 tank automatic change every 5 minutes All symmetry max dissymmetry ...

Page 223: ... Windshield misting protection system As required Prior to descent in moist conditions turn HOT AIR FLOW distributor to 12 o clock position and set WINDSHIELD switch to ON to avoid canopy misting If misting continues turn HOT AIR FLOW distributor to the left or refer to Chapter 3 12 Paragraph WINDSHIELD MISTING OR INTERNAL ICING 4 Fuel Gages Check Quantity Symmetry Fullest tank Select 5 Passengers...

Page 224: ...ht ON and GEAR UNSAFE CAS message indicates an anomaly refer to EMERGENCY PROCEDURES It is possible that the 3 landing gear position green indicator lights flash unevenly then come on at the end of the sequence 5 Flaps IAS 178 KIAS TO 6 Lights OFF TAXI LDG switch LDG Stabilized approach 7 Flaps IAS 122 KIAS LDG However when autopilot is engaged in APR mode with coupled GS flaps must be extended in...

Page 225: ...tion 0 October 31 2013 Rev 1 Page 4 4 34 BEFORE LANDING 2 2 9 Autopilot 200 ft Disconnect 10 YAW DAMPER push button OFF The pilot effort required to use the rudder pedals is reduced if the yaw damper is turned off This is particularly significant when landing in a crosswind ...

Page 226: ...ingestion of foreign objects come out of the reverse range as speed reduces and use the brakes if necessary for further deceleration High power reverse at low speed can throw loose material into the air and can cause control problems and decrease the comfort of crew and passengers If permitted by the runway length it is better to adopt a moderate reverse CAUTION ON SNOWY OR DIRTY RUNWAY IT IS BETT...

Page 227: ...kg If speed has been maintained at 80 KIAS or more and TRQ 100 select TO flaps as soon as the 10 attitude has been attained When the vertical speed is positive and when IAS is at or above 85 KIAS 4 Landing gear control UP All warning lights OFF When IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed As required Weight above 6579 lbs 2984 kg If speed has been maintained at 85 KIAS or more and TRQ...

Page 228: ...not increase power with full flaps as airplane may lift off prematurely at low speed 2 Elevator trim Green sector To use elevator trim manual control is faster than to use electric control Ensure that runway length is sufficient to complete this sequence 3 Throttle T O power 4 Takeoff attitudes Normal takeoff ATTITUDE 10 Short takeoff Weight 6579 lbs 2984 kg ATTITUDE 15 Weight 6579 lbs 2984 kg ATT...

Page 229: ...ed Taxiing with BLEED OFF may slightly help reduce the ITT thus reducing the required stabilization time before shut down This should be applied only for short taxi duration and is left to the pilot judgement 2 Radar if installed Checked STANDBY Maintain radar if installed on STANDBY in order not to generate radiations prejudicial to outside persons The radar is automatically set to STANDBY after ...

Page 230: ...ons are less than 5 C If BLEED was selected to OFF after landing and taxi was performed at Flight IDLE power the taxi time is considered as cooling time Therefore the above stabilization time can be reduced accordingly 4 TAXI light OFF 5 AP TRIMS switch OFF 6 Throttle LO IDLE for 15 seconds Keep throttle on LO IDLE position for 15 seconds minimum before shutting down engine 7 Throttle CUT OFF 8 IN...

Page 231: ...OKING REFER TO PARAGRAPH MOTORING ESI 2000 NORMAL PROCEDURE No pilot action required for normal shutdown The ESI 2000 will shut down within 5 minutes ESI 2000 MANUAL PROCEDURE The ESI 2000 can be manually shut down when in the discharge mode to conserve battery power Remove all airplane power from the ESI Press any key button as stated by the on screen message Press the M Menu button repeatedly un...

Page 232: ...ng water or slush may be ingested by the engine or freeze on engine or cowlings NOTE Refer to Figure 5 5 1 to convert OAT to SAT in flight SAT OAT 2 C on the ground 3 Flight into known icing conditions is authorized when all airplane equipment provided for ice protection is operating correctly This includes Pneumatic deice system for inboard and outboard wing for stabilizers and for elevator horns...

Page 233: ...water or slush may be ingested by the engine or freeze on engine or cowlings NOTE Refer to Figure 5 5 1 to convert OAT to SAT in flight SAT OAT 2 C on the ground 3 Flight into known icing conditions is authorized when all airplane equipment provided for ice protection is operating correctly This includes Pneumatic deice system for inboard and outboard wing for stabilizers and for elevator horns Pr...

Page 234: ...e boots could be damaged The INERT SEP switch must be left ON while the airplane remains in icing conditions CAUTION SHOULD CONDITIONS REQUIRE IT APPLY THESE DIRECTIVES FROM BEGINNING OF TAXI ONWARDS IF AIRPLANE LEAVES ICING CONDITIONS MAINTAIN INERT SEP ON AS LONG AS ICE THICKNESS ON NON DEICED VISIBLE PARTS EXCEEDS 15 mm OR INCH This will avoid ice fragments coming from propeller spinner and bei...

Page 235: ...speeds may increase by up to Flaps UP 20 KIAS Flaps TO 15 KIAS Flaps LDG 10 KIAS In case of severe or prolonged icing an ice concretion due to refreezing around the heated stall warning may appear Above recommended speeds take into account on one side the stall speed increase due to profile shape deterioration and on the other side the weight increase of the iced up airplane taking as a basis the ...

Page 236: ...observed accomplish the following 1 Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid extended exposure to flight conditions more severe than those for which the airplane has been certificated 2 Avoid abrupt and excessive maneuvering that may exacerbate control difficulties 3 Do not engag...

Page 237: ...ON switch ON This action is intended in highly improbable case of an engine flame out further to an important ingestion to ensure immediate restarting without action of the pilot 2 INERT SEP switch ON UTILIZATION ON RUNWAYS COVERED WITH WATER If takeoff or landing must be performed on a runway covered with water 1 IGNITION switch ON 2 INERT SEP switch ON ...

Page 238: ...uent locking due to freezing after takeoff Before takeoff 1 If the runway is long enough takeoff should be performed with the flaps in the up position In that case rotation speed must be increased by 5 KIAS NOTE Takeoff distances must be increased to take into account the flap position 15 compared to the takeoff position and the runway condition The ground roll may be multiplied by 3 in some melti...

Page 239: ... 5 KIAS Use β area of throttle to adjust speed Apply very smooth variations using throttle 3 Steer the airplane using the rudder Make turns at a very low speed engine torque tends to make the airplane turn to the left 4 Use brakes only at very low speed and progressively Before takeoff 1 IGNITION switch ON 2 INERT SEP switch ON Takeoff 1 After takeoff normally retract the landing gear then perform...

Page 240: ... WITH TAMPED SNOW RUNWAYS 2 2 3 Steer the airplane using the rudder Make turns at a very low speed engine torque tends to make the airplane turn to the left 4 Use brakes only at very low speed and progressively On the ramp after landing or taxiing 1 Do not use the parking brake to prevent brake lock 2 Use chocks and or tie down the airplane ...

Page 241: ...ATION BY COLD WEATHER 0 C TO 25 C AND VERY COLD WEATHER 25 C TO 40 C 1 9 REMARK The procedures hereafter supplement the normal procedures for the airplane use when operating under temperatures between 0 C and 40 C on ground Figure 4 5 1 OPERATING ENVELOPES BY COLD WEATHER 0 C to 25 C AND VERY COLD WEATHER 25 C to 40 C ...

Page 242: ...after having parked the airplane in a heated hangar 4 Remove chocks and or release ties from the airplane 5 Check the free deflection of the flight controls and of the elevator trim 6 Check the free deflection of throttle Before starting the engine Starting the engine After starting the engine Apply normal procedures defined in Chapter s 4 3 and or 4 4 Taxiing Before takeoff Takeoff 1 On DE ICE SY...

Page 243: ...ut down 1 Park brake OFF WARNING CAS MESSAGE PARK BRAKE OFF It is recommended not to use the parking brake by cold or very cold weather so that the brakes do not stick when cooling 2 Apply normal procedures defined in Chapter s 4 3 and or 4 4 3 Use chocks and or tie down the airplane using anchor points on ground 4 Put blanking caps and plugs on air inlets exhaust stubs pitots and static ports ...

Page 244: ... or the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Spray anti icing fluid on the wings stabilizers and movable surfaces upper and lower surfaces shortly before takeoff 3 Carry out a complete rotation of the propeller to check its free rotation 4 Do not perform a fuel draining If the airplane is operating permanently under negative temperatures drainings will have to be perfo...

Page 245: ... IS SHUTDOWN THE THROTTLE MUST NOT BE MOVED INTO THE REVERSE AREA Throttle CUT OFF 4 Fuel panel AUX BP switch ON WARNING CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAGE FUEL PRESS OFF 5 Propeller AREA CLEAR 6 G1000 Composite mode 7 ENGINE START panel IGNITION switch ON WARNING CAS MESSAGE IGNITION ON STARTER switch ON take a time WARNING CAS MESSAGE STARTER ON When Ng 13 Throttle HI IDLE Move ...

Page 246: ... SOURCE selector BAT WARNING CAS MESSAGE BAT OFF OFF 11 IGNITION switch AUTO WARNING CAS MESSAGE IGNITION OFF 12 Ground power unit HAVE IT DISCONNECTED WARNING CAS MESSAGE GPU DOOR OFF 13 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF 14 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary After starting the engine 1 On ECS panel As soon as the current flow is lowe...

Page 247: ...ed Edition 0 October 31 2013 Rev 1 Page 4 5 15 UTILIZATION BY COLD WEATHER 0 C TO 25 C AND VERY COLD WEATHER 25 C TO 40 C 7 9 Taxiing Before takeoff Takeoff Apply procedures defined for Envelope 1 Landing After landing Shut down Apply procedures defined for Envelope 1 ...

Page 248: ...ng the engine Apply the procedures defined for the Envelope 2 After starting the engine 1 On ECS panel As soon as the current flow is lower than 100 A BLEED switch AUTO CONTROL selector COCKPIT TEMP C selector FULL HOT Preheat the cabin respecting time defined in Figure 4 5 2 before switching on the navigation and monitoring systems This allows to respect minimum temperatures necessary for the equ...

Page 249: ... UTILIZATION BY COLD WEATHER 0 C TO 25 C AND VERY COLD WEATHER 25 C TO 40 C 9 9 Complement If landing is foreseen by cold or very cold weather or in case of prolonged operation of the airplane in such conditions it is recommended to prepare the airplane as specified in Chapter 8 9 Figure 4 5 2 PREHEATING DURATION ...

Page 250: ...r to avoid an excessive speed Indeed in this case landing distance indicated in Chapter 5 14 would not be respected Before touch down generate a slideslip with the rudder in order to align fuselage with the runway ie left crosswind left wing low Do not use or select the fuel tank on the low wing side during prolonged sideslips with a fuel low warning or gage indicating low Retract flaps immediatel...

Page 251: ... SEP switch ON 2 Reverse Do not use In fact on a flat runway with grass it is necessary to adopt a power greater than the one obtained when the throttle is set to Flight IDLE so the pilot will not be tempted to use the reverse LANDING 1 INERT SEP switch ON After wheel touch down 2 Reverse Only if necessary Do not maintain reverse at speeds below 40 KIAS to avoid ingestion of foreign matter Indeed ...

Page 252: ...n is available on the projected route and for the flight period in B RNAV areas An alarm is provided by G1000 system in that case When 23 or more satellites are available the prediction of satellite position is valid for 7 days Their predicted availability is ensured for 48 hours by EUROCONTROL When less than 23 satellites are available the predicted availability of RAIM shall be confirmed short b...

Page 253: ...L 200 ISA 170 KIAS M 0 40 5 8 4 MAXIMUM CLIMB POWER FL 200 ISA 170 KIAS M 0 40 5 8 5 MAXIMUM CRUISE POWER FL 200 5 8 6 MAXIMUM CRUISE POWER FL 200 5 8 7 NORMAL RECOMMENDED CLIMB POWER FL 200 5 8 8 NORMAL RECOMMENDED CLIMB POWER FL 200 5 8 9 5 9 TAKEOFF DISTANCES 5 9 1 WEIGHT 5512 lbs 2500 kg 5 9 1 WEIGHT 6579 lbs 2984 kg 5 9 2 WEIGHT 7394 lbs 3354 kg 5 9 3 5 10 CLIMB PERFORMANCE 5 10 1 MXCL SPEEDS...

Page 254: ... kg Altitude 24000 ft 5 11 18 LONG RANGE CRUISE 6300 lbs 2858 kg Altitude 24000 ft 5 11 19 LONG RANGE CRUISE 6300 lbs 2858 kg Altitude 24000 ft 5 11 20 LONG RANGE CRUISE 7100 lbs 3220 kg Altitude 24000 ft 5 11 21 LONG RANGE CRUISE 7100 lbs 3220 kg Altitude 24000 ft 5 11 22 5 12 TIME CONSUMPTION AND DESCENT DISTANCE 5 12 1 5 13 HOLDING TIME 5 13 1 5 14 LANDING DISTANCES 5 14 1 WEIGHT 7024 lbs 3186 ...

Page 255: ... 31 2013 Rev 1 Page 5 1 1 5 1 GENERAL This Section provides all of the required and additional performance data for airplane operations The Section 9 Supplements of the Pilot s Operating Handbook provides specific airplane performance associated with optional equipment and systems ...

Page 256: ...mdt 28 88 dB A 77 8 dB A ICAO Annex 16 Vol 1 6th edition Amdt 8 Chapter 10 Appendix 6 85 dB A 77 8 dB A Approved noise levels for TBM airplanes are stated in EASA Noise Type Certificate Data Sheet A 010 NOTE No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at into or out of any air...

Page 257: ...P FLAPS TO LDG GR DN FLAPS LDG LDG GR DN KIAS KCAS KIAS KCAS KIAS KCAS 125 150 175 200 225 250 266 128 154 179 205 230 255 271 70 80 90 100 120 140 160 69 80 90 101 121 141 162 60 70 80 90 100 110 120 58 68 78 88 98 108 118 MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS 144 173 201 230 259 288 307 147 177 206 236 264 293 312 81 92 104 115 138 161 184 79 92 104 116 139 162 187 69 81 92 104 115 127...

Page 258: ...0 175 200 225 250 271 124 149 174 199 224 249 270 70 80 90 100 120 140 160 70 80 90 100 120 139 159 60 70 80 90 100 110 120 59 69 79 90 100 110 120 MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS 144 173 201 230 259 288 312 142 171 200 229 258 287 311 81 92 104 115 138 161 184 81 92 104 115 138 160 183 69 81 92 104 115 127 138 68 79 91 104 115 127 138 Figure 5 3 2 ALTERNATE STATIC SOURCE BLEED AUT...

Page 259: ...3 Rev 1 Page 5 4 1 5 4 CABIN PRESSURIZATION ENVELOPE Figure 5 4 1 CABIN PRESSURIZATION ENVELOPE 260 240 220 180 140 160 200 280 300 1000 2000 3000 4000 5000 6000 7000 8000 Cabin altitude feet PRESSURIZATION USEFUL ENVELOPE 9350 ft cabin P 6 2 PSI max 9000 310 Flight level FL ...

Page 260: ...2 31 32 4000 13 12 03 02 07 08 17 18 27 28 6000 17 16 07 06 03 04 13 14 23 24 8000 21 20 11 10 01 00 09 10 19 20 10000 25 24 15 14 05 04 05 06 15 16 12000 29 28 19 18 09 08 01 02 11 12 14000 33 32 23 22 13 12 03 02 07 08 16000 37 36 27 26 17 16 07 06 03 04 18000 41 40 31 30 21 20 11 10 01 00 20000 45 44 35 34 25 24 15 14 05 04 22000 49 48 39 38 29 28 19 18 09 08 24000 53 52 43 42 33 32 23 22 13 12...

Page 261: ...81 77 66 78 73 63 79 75 63 90 84 73 91 87 75 93 89 75 105 100 86 5512 lbs 2500 kg UP DN DN UP TO LDG 70 66 57 71 67 57 81 76 66 75 71 61 76 72 61 86 82 70 82 78 68 84 80 68 94 90 78 98 93 81 100 95 81 113 107 93 6579 lbs 2984 kg UP DN DN UP TO LDG 75 71 61 76 72 61 86 82 70 80 75 66 82 77 66 92 86 76 88 84 73 90 86 73 101 97 84 105 100 86 107 102 86 121 115 99 7394 lbs 3354 kg UP DN DN UP TO LDG 8...

Page 262: ...BOOK SECTION 5 PERFORMANCE Edition 0 October 31 2013 Rev 1 Page 5 7 1 5 7 WIND COMPONENTS Figure 5 7 1 WIND COMPONENTS EXAMPLE Angle between wind direction and flight path 50 Headwind 8 kts Crosswind 10 kts Wind speed 13 kts ...

Page 263: ...n system start The following conditions are given BLEED AUTO The torque must be set at or below the value corresponding to the local conditions of flight level and temperature NOTE Inertial separator must be OFF and BLEED HI MSG OFF Example for FL 260 and OAT 22 C the following tables give the maximum torque to be set Maximum climb power TRQ 82 for IAS 124 KIAS Add 0 5 of TRQ for each additional 1...

Page 264: ...C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 Recommended NG 103 18 16 14 12 100 10 99 8 97 6 100 95 4 98 94 2 100 97 92 0 99 94 90 2 100 97 92 87 4 99 94 89 84 6 100 96 91 86 81 8 99 93 88 84 79 10 100 96 91 86 81 77 12 98 93 88 83 79 74 14 100 96 90 85 81 76 71 16 100 97 93 87 83 78 73 18 99 94 90 85 80 75 20 100 96 91 87 82 77 22 98 93 88 84 79 24 100 95 90 85 81 26...

Page 265: ... 99 95 90 86 82 78 74 40 98 94 89 85 81 77 73 38 97 92 88 84 80 76 72 36 100 96 91 87 83 79 75 71 34 98 94 90 86 81 77 74 70 32 97 93 89 84 80 76 72 69 30 100 96 92 87 83 79 75 71 68 28 99 95 91 86 82 78 74 70 67 26 97 93 89 85 81 77 73 69 65 24 100 96 92 88 84 79 75 72 68 64 22 99 95 91 87 82 78 74 70 66 63 20 98 94 89 85 81 77 73 69 65 61 18 100 96 92 88 84 80 76 71 67 63 59 16 99 95 91 87 82 78...

Page 266: ...r BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 Recommended NG 103 20 18 16 14 12 10 8 100 6 99 4 97 2 100 94 0 100 97 91 2 99 94 89 4 100 96 91 86 6 98 93 89 84 8 100 96 91 86 81 10 98 93 88 83 78 12 100 95 90 85 80 76 14 100 97 92 87 82 78 73 16 99 94 89 84 80 75 18 100 96 91 86 81 77 20 98 93 88 84 79 22 100 95 90 85 81 24 100 97 92 87 83 26 98 94 89 ...

Page 267: ... 85 81 77 42 98 93 89 84 80 76 40 97 92 87 83 79 75 38 100 96 91 86 82 78 74 36 99 94 90 85 81 77 72 34 98 93 88 84 80 75 71 32 96 92 87 83 78 74 70 30 100 95 90 86 81 77 73 69 28 98 94 89 85 80 76 72 68 26 97 93 88 83 79 75 71 67 24 100 96 91 87 82 78 74 70 65 22 99 95 90 85 81 76 72 68 64 20 98 93 89 84 79 75 71 66 62 18 100 96 92 87 82 78 73 69 64 60 16 99 95 90 85 81 76 71 67 63 59 14 97 93 88...

Page 268: ...able is not valid if INERTIAL SEPARATOR ON and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 Recommended NG 103 18 16 14 12 10 8 6 4 2 0 2 100 4 97 6 100 94 8 100 97 91 10 99 94 88 12 100 96 91 86 14 99 93 88 83 16 100 96 90 85 18 98 93 87 20 100 95 90 22 100 97 92 24 99 94 26 100 96 28 98 30 100 32 100 34 100 CAUTION THE TRQ SETTING MUST NEVER EXC...

Page 269: ...2 87 42 100 96 91 86 40 99 94 89 85 38 98 93 88 83 36 96 92 87 82 34 100 95 90 85 81 32 99 94 89 84 79 30 97 92 87 82 78 28 100 96 91 86 81 76 26 99 94 89 84 80 75 24 98 93 88 83 78 73 22 96 91 86 81 76 71 20 100 94 89 84 79 74 69 18 98 93 87 82 77 72 67 16 100 96 90 85 80 75 70 65 14 99 94 88 83 78 73 68 63 12 97 92 86 81 76 71 66 61 10 100 94 89 84 79 73 68 63 59 8 97 92 87 81 76 71 66 61 57 6 1...

Page 270: ...N T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 Recommended NG 103 18 16 14 12 10 8 6 4 100 2 98 0 100 95 2 98 93 4 100 95 90 6 98 92 87 8 100 94 89 84 10 100 97 91 86 81 12 99 94 88 83 78 14 100 96 91 85 80 75 16 98 93 88 82 78 18 100 95 90 85 80 20 100 97 92 87 82 22 99 94 89 84 24 100 96 91 86 26 100 98 92 88 28 99 94 89 30 100 96 91 32 98 93 34 95 CAUTION THE TRQ...

Page 271: ...5 80 38 98 93 88 84 79 36 97 92 87 82 78 34 100 95 90 86 81 76 32 99 94 89 84 80 75 30 97 92 88 83 78 74 28 96 91 86 81 77 72 26 100 94 90 84 80 75 71 24 98 93 88 83 78 73 69 22 100 96 91 86 81 76 71 67 20 99 94 89 84 79 74 69 65 18 97 92 87 82 77 72 67 62 16 100 95 90 85 80 75 70 65 60 14 98 93 88 83 78 72 67 62 58 12 100 96 91 86 80 75 70 65 60 56 10 99 94 88 83 77 72 67 63 58 54 8 100 96 91 85 ...

Page 272: ...LEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 TRQ 100 18 16 14 12 100 10 99 8 97 6 100 95 4 98 94 2 100 97 92 0 99 94 90 2 100 97 92 87 4 99 94 89 84 6 100 96 91 86 81 8 99 93 88 84 79 10 100 96 91 86 81 77 12 98 93 88 83 79 74 14 100 96 90 85 81 76 71 16 100 97 93 87 83 78 73 18 99 94 90 85 80 75 20 100 96 91 87 82 77 22 98 93 88 84 79 24 100 95 90 85...

Page 273: ... 76 42 99 95 90 86 82 78 74 40 98 94 89 85 81 77 73 38 97 92 88 84 80 76 72 36 100 96 91 87 83 79 75 71 34 98 94 90 86 81 77 74 70 32 97 93 89 84 80 76 72 69 30 100 96 92 87 83 79 75 71 68 28 99 95 91 86 82 78 74 70 67 26 97 93 89 85 81 77 73 69 65 24 100 96 92 88 84 79 75 72 68 64 22 99 95 91 87 82 78 74 70 66 63 20 98 94 89 85 81 77 73 69 65 61 18 100 96 92 88 84 80 76 71 67 63 59 16 99 95 91 87...

Page 274: ...EPARATOR ON and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 TRQ 100 20 18 16 14 12 10 8 100 6 99 4 97 2 100 94 0 100 97 91 2 99 94 89 4 100 96 91 86 6 98 93 89 84 8 100 96 91 86 81 10 98 93 88 83 78 12 100 95 90 85 80 76 14 100 97 92 87 82 78 73 16 99 94 89 84 80 75 18 100 96 91 86 81 77 20 98 93 88 84 79 22 100 95 90 85 81 24 100 97 92 87 83 26 98 ...

Page 275: ... 95 90 85 81 77 42 98 93 89 84 80 76 40 97 92 87 83 79 75 38 100 96 91 86 82 78 74 36 99 94 90 85 81 77 72 34 98 93 88 84 80 75 71 32 96 92 87 83 78 74 70 30 100 95 90 86 81 77 73 69 28 98 94 89 85 80 76 72 68 26 97 93 88 83 79 75 71 67 24 100 96 91 87 82 78 74 70 65 22 99 95 90 85 81 76 72 68 64 20 98 93 89 84 79 75 71 66 62 18 100 96 92 87 82 78 73 69 64 60 16 99 95 90 85 81 76 71 67 63 59 14 97...

Page 276: ...is not valid if INERTIAL SEPARATOR ON and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 TRQ 100 18 16 14 12 10 8 6 4 2 0 2 100 4 97 6 100 94 8 100 97 91 10 99 94 88 12 100 96 91 86 14 99 93 88 83 16 100 96 90 85 18 98 93 87 20 100 95 90 22 100 97 92 24 99 94 26 100 96 28 98 30 100 32 100 34 100 CAUTION THE TRQ SETTING MUST NEVER EXCEED 100 WHEN SET...

Page 277: ...91 86 40 99 94 89 85 38 98 93 88 83 36 96 92 87 82 34 100 95 90 85 81 32 99 94 89 84 79 30 97 92 87 82 78 28 100 96 91 86 81 76 26 99 94 89 84 80 75 24 98 93 88 83 78 73 22 96 91 86 81 76 71 20 100 94 89 84 79 74 69 18 98 93 87 82 77 72 67 16 100 96 90 85 80 75 70 65 14 99 94 88 83 78 73 68 63 12 97 92 86 81 76 71 66 61 10 100 94 89 84 79 73 68 63 59 8 97 92 87 81 76 71 66 61 57 6 100 95 89 84 79 ...

Page 278: ...or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 TRQ 100 18 16 14 12 10 8 6 4 100 2 98 0 100 95 2 98 93 4 100 95 90 6 98 92 87 8 100 94 89 84 10 100 97 91 86 81 12 99 94 88 83 78 14 100 96 91 85 80 75 16 98 93 88 82 78 18 100 95 90 85 80 20 100 97 92 87 82 22 99 94 89 84 24 100 96 91 86 26 100 98 92 88 28 99 94 89 30 100 96 91 32 98 93 34 95 CAUTION T...

Page 279: ...5 90 85 80 38 98 93 88 84 79 36 97 92 87 82 78 34 100 95 90 86 81 76 32 99 94 89 84 80 75 30 97 92 88 83 78 74 28 96 91 86 81 77 72 26 100 94 90 84 80 75 71 24 98 93 88 83 78 73 69 22 100 96 91 86 81 76 71 67 20 99 94 89 84 79 74 69 65 18 97 92 87 82 77 72 67 62 16 100 95 90 85 80 75 70 65 60 14 98 93 88 83 78 72 67 62 58 12 100 96 91 86 80 75 70 65 60 56 10 99 94 88 83 77 72 67 63 58 54 8 100 96 ...

Page 280: ... 1795 1255 1925 8000 1 070 1665 1210 1865 1315 2010 1440 2160 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 935 1475 995 1570 1075 1665 1120 1735 2000 1060 1645 1130 1750 1205 1860 1265 1940 4000 1190 1835 1280 1960 1390 2090 1455 2180 6000 1370 2060 1470 2200 1580 2345 1660 2445 8000 1560 2315 1675 2470 1800 2630 1890 2745 Figure 5 9 1 TAKEOFF DISTANCES 55...

Page 281: ...1925 2650 8000 1620 2275 1860 2565 2025 2770 2190 2980 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 1420 2015 1520 2145 1625 2280 1710 2375 2000 1600 2250 1730 2400 1855 2560 1945 2670 4000 1830 2525 1965 2700 2110 2880 2215 3005 6000 2080 2840 2255 3035 2415 3235 2535 3375 8000 2380 3190 2565 3405 2750 3625 2880 3780 Figure 5 9 2 TAKEOFF DISTANCES 6579 lb...

Page 282: ...0 2715 3620 8000 2285 3095 2620 3505 2850 3785 3115 4075 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 1985 2730 2125 2915 2290 3100 2405 3240 2000 2260 3060 2430 3275 2610 3495 2740 3655 4000 2570 3450 2770 3690 2995 3935 3145 4110 6000 2950 3885 3180 4150 3415 4425 3580 4615 8000 3365 4365 3620 4660 3880 4960 4070 5170 Figure 5 9 3 TAKEOFF DISTANCES 7394 ...

Page 283: ...2480 2000 3025 2890 2765 2655 2545 2445 4000 2995 2860 2735 2615 2505 2405 6000 2960 2820 2695 2575 2465 2360 8000 2930 2790 2655 2535 2425 2320 6594 lbs 2991 kg SL 2585 2470 2365 2270 2175 2090 2000 2560 2445 2335 2240 2145 2055 4000 2530 2415 2305 2205 2110 2020 6000 2500 2380 2265 2165 2070 1980 8000 2465 2345 2230 2125 2035 1945 7394 lbs 3354 kg SL 2195 2095 2005 1920 1840 1765 2000 2170 2070 ...

Page 284: ...0 2370 2335 2305 2275 2245 2210 4000 2325 2295 2260 2225 2190 2160 6000 2285 2250 2210 2175 2140 2105 8000 2235 2200 2165 2125 2085 2050 6594 lbs 2991 kg SL 2070 2040 2015 1985 1960 1935 2000 2030 2000 1970 1945 1915 1885 4000 1990 1965 1935 1900 1870 1840 6000 1955 1920 1885 1855 1825 1790 8000 1910 1875 1845 1805 1775 1740 7394 lbs 3354 kg SL 1795 1765 1740 1715 1695 1670 2000 1760 1730 1705 168...

Page 285: ...14 11 3 6 5 03 00 16 13 4 2 6 8000 03 00 15 12 4 0 6 03 30 18 14 4 7 7 04 00 21 17 5 6 9 10000 03 45 19 15 5 0 8 04 30 22 17 5 9 9 05 15 26 21 6 9 11 12000 04 30 22 18 5 9 10 05 15 26 21 7 0 11 06 15 31 25 8 3 14 14000 05 15 26 20 6 9 11 06 15 31 24 8 1 14 07 15 36 29 9 6 16 16000 06 00 30 23 7 8 13 07 15 35 27 9 2 16 08 30 41 33 11 0 19 18000 06 45 33 26 8 7 15 08 00 39 31 10 4 18 09 30 47 37 12 ...

Page 286: ... 15 12 9 3 2 5 02 45 14 11 3 7 6 03 15 17 13 4 4 7 8000 03 00 16 12 4 2 6 03 30 19 15 4 9 8 04 15 22 17 5 8 9 10000 03 45 20 15 5 2 8 04 30 23 18 6 1 10 05 15 27 22 7 2 12 12000 04 30 23 18 6 2 10 05 30 28 22 7 3 12 06 30 33 26 8 6 14 14000 05 15 27 21 7 1 12 06 15 32 25 8 5 14 07 30 38 30 10 1 17 16000 06 15 31 24 8 1 14 07 15 36 29 9 6 17 08 45 43 34 11 5 20 18000 07 00 34 27 9 1 16 08 15 41 32 ...

Page 287: ...4 02 00 12 9 3 1 5 6000 02 15 12 10 3 3 5 02 45 15 12 3 9 6 03 15 17 14 4 6 7 8000 03 00 16 13 4 3 7 03 30 19 15 5 1 8 04 15 23 18 6 1 10 10000 03 45 20 16 5 4 9 04 30 24 19 6 4 10 05 30 29 22 7 6 12 12000 04 45 24 19 6 4 11 05 30 29 23 7 6 13 06 30 34 27 9 0 15 14000 05 30 28 22 7 4 13 06 30 33 26 8 8 15 07 45 40 31 10 5 18 16000 06 15 32 25 8 5 15 07 30 38 30 10 1 18 09 00 45 36 12 0 22 18000 07...

Page 288: ...5 12 4 1 8 03 30 18 14 4 7 10 8000 03 30 18 14 4 6 10 04 00 20 16 5 4 11 04 30 24 19 6 3 13 10000 04 15 22 17 5 8 13 05 00 25 20 6 7 15 05 45 29 23 7 8 17 12000 05 15 26 20 6 9 16 06 00 30 24 8 0 18 07 00 35 28 9 3 21 14000 06 15 30 24 8 0 19 07 15 35 28 9 4 22 08 15 41 32 10 9 25 16000 07 15 35 27 9 2 22 08 15 40 32 10 7 26 09 45 47 37 12 4 30 18000 08 00 39 31 10 3 25 09 30 46 36 12 0 30 11 00 5...

Page 289: ... 30 14 11 3 7 8 03 00 16 13 4 3 9 03 30 19 15 5 0 10 8000 03 30 18 14 4 9 11 04 00 22 17 5 7 12 04 45 25 20 6 6 14 10000 04 30 23 18 6 1 14 05 15 27 21 7 1 16 06 00 31 24 8 2 18 12000 05 30 27 22 7 3 17 06 15 32 25 8 5 19 07 15 37 29 9 9 23 14000 06 30 32 25 8 5 20 07 30 37 29 9 9 23 08 45 44 34 11 5 27 16000 07 30 37 29 9 7 24 08 45 43 34 11 3 28 10 00 50 39 13 2 32 18000 08 30 41 32 10 9 27 09 4...

Page 290: ...13 10 3 5 7 6000 02 45 15 11 3 9 8 03 15 17 13 4 5 10 03 45 20 16 5 2 11 8000 03 45 19 15 5 1 11 04 15 23 18 6 0 13 05 00 26 21 7 0 15 10000 04 30 24 19 6 4 14 05 15 28 22 7 5 17 06 15 33 26 8 7 20 12000 05 30 29 23 7 7 18 06 30 34 27 9 0 21 07 45 40 31 10 5 24 14000 06 30 34 27 8 9 21 07 45 40 31 10 5 25 09 00 46 36 12 2 30 16000 07 45 39 30 10 2 25 09 00 45 36 12 0 30 10 30 53 42 14 1 35 18000 0...

Page 291: ...5 2000 1525 1485 1455 1425 1395 1370 1340 4000 1490 1440 1410 1380 1350 1320 1290 6000 1450 1400 1365 1335 1305 1270 1240 8000 1410 1355 1320 1285 1255 1215 1180 Conditions Landing gear DN and flaps LDG IAS 95 KIAS Airplane weight Pressure altitude feet RATE OF CLIMB ft min ISA 35 C ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 7394 lbs 3354 kg SL 1285 1245 1220 1195 1165 1140 1115 2000 1250 12...

Page 292: ... 2150 2135 2115 2095 4000 2195 2165 2145 2125 2105 2080 2060 6000 2170 2140 2120 2095 2070 2050 2025 8000 2150 2115 2085 2060 2035 2010 1985 Conditions Landing gear UP and flaps TO IAS 115 KIAS Airplane weight Pressure altitude feet RATE OF CLIMB ft min ISA 35 C ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 7394 lbs 3354 kg SL 1940 1915 1895 1880 1865 1850 1830 2000 1920 1890 1875 1860 1840 181...

Page 293: ...PILOT S OPERATING HANDBOOK SECTION 5 PERFORMANCE Edition 0 October 31 2013 Rev 1 Page 5 11 1 5 11 CRUISE PERFORMANCE MAXIMUM CRUISE Figure 5 11 1 CRUISE PERFORMANCE Maximum cruise 7100 lbs 6300 lbs ...

Page 294: ... 100 278 218 73 3 230 262 230 261 229 260 15000 34 100 265 208 70 1 225 276 225 275 224 274 18000 40 100 256 201 67 7 222 285 221 284 220 283 20000 44 100 251 197 66 2 220 291 219 290 218 289 21000 46 100 248 195 65 6 219 294 218 293 217 292 22000 48 100 246 193 65 1 218 297 217 296 216 295 23000 50 100 244 192 64 5 217 300 216 299 215 298 24000 52 100 243 191 64 1 215 303 214 302 213 301 25000 54...

Page 295: ... 238 239 5000 4 100 302 237 79 7 234 252 233 251 233 251 10000 14 100 281 220 74 2 229 265 228 264 227 264 15000 24 100 268 210 70 8 224 279 223 279 222 278 18000 30 100 259 203 68 4 220 289 220 288 219 286 20000 34 100 253 199 66 9 218 295 217 294 216 293 21000 36 100 251 197 66 2 217 298 216 297 215 296 22000 38 100 249 195 65 7 216 301 215 300 214 299 23000 40 100 247 194 65 2 215 305 214 304 2...

Page 296: ...1 237 240 5000 1 100 304 238 80 2 233 253 232 253 232 252 10000 9 100 282 221 74 5 228 267 227 266 227 265 15000 19 100 269 211 71 2 223 281 222 280 221 279 18000 25 100 260 204 68 7 219 290 219 290 218 288 20000 29 100 255 200 67 2 217 297 216 296 215 294 21000 31 100 252 198 66 6 216 300 215 299 214 298 22000 33 100 250 196 66 0 215 303 214 302 213 301 23000 35 100 248 195 65 5 214 307 213 306 2...

Page 297: ...42 236 241 5000 6 100 305 240 80 7 232 255 232 254 231 254 10000 4 100 284 223 74 9 227 268 226 268 226 267 15000 14 100 271 213 71 5 222 283 221 282 220 281 18000 20 100 261 205 69 0 219 292 218 291 217 290 20000 24 100 256 201 67 6 216 299 216 298 215 296 21000 26 100 253 199 66 9 215 302 215 301 213 300 22000 28 100 251 197 66 4 214 305 213 304 212 303 23000 30 100 249 196 65 8 213 309 212 308 ...

Page 298: ...43 236 243 5000 11 100 307 241 81 1 231 256 231 256 230 255 10000 1 100 285 224 75 3 226 270 226 269 225 268 15000 9 100 272 214 71 9 221 285 220 284 219 283 18000 15 100 263 206 69 4 218 294 217 293 216 292 20000 19 100 257 202 67 9 216 301 215 300 214 298 21000 21 100 255 200 67 2 215 304 214 303 213 301 22000 23 100 252 198 66 7 213 307 212 306 211 305 23000 25 100 250 197 66 1 212 311 211 310 ...

Page 299: ...45 235 244 5000 16 100 309 242 81 6 231 258 230 257 230 256 10000 6 100 287 225 75 7 225 271 225 271 224 270 15000 4 100 274 215 72 3 220 286 219 285 219 284 18000 10 100 264 207 69 8 217 296 216 295 215 293 20000 14 100 259 203 68 3 215 302 214 301 213 300 21000 16 100 256 201 67 6 214 306 213 305 212 303 22000 18 100 254 199 67 0 213 309 212 308 210 306 23000 20 100 252 198 66 5 211 313 211 312 ...

Page 300: ...4 247 233 247 5000 26 100 312 245 82 5 229 260 229 260 228 259 10000 16 100 290 227 76 5 224 274 223 274 223 273 15000 6 100 276 217 73 0 219 289 218 289 217 287 18000 0 100 267 209 70 4 215 299 214 298 213 297 20000 4 100 261 205 69 0 213 306 212 305 211 303 21000 6 100 259 203 68 3 212 309 211 308 210 306 22000 8 100 256 201 67 7 211 313 210 312 209 310 23000 10 100 254 199 67 1 210 317 209 315 ...

Page 301: ...PILOT S OPERATING HANDBOOK SECTION 5 PERFORMANCE Edition 0 October 31 2013 Rev 1 Page 5 11 9 NORMAL CRUISE Recommended Figure 5 11 9 CRUISE PERFORMANCE Recommended cruise 7100 lbs 6300 lbs ...

Page 302: ...6 239 236 5000 14 100 299 234 78 9 235 249 235 248 234 248 10000 24 100 278 218 73 3 230 262 230 261 229 260 15000 34 100 265 208 70 1 225 276 225 275 224 274 18000 40 100 256 201 67 7 222 285 221 284 220 283 20000 44 100 251 197 66 2 220 291 219 290 218 289 21000 46 100 248 195 65 6 219 294 218 293 217 292 22000 48 100 246 193 65 1 218 297 217 296 216 295 23000 50 100 244 192 64 5 217 300 216 299...

Page 303: ...238 239 238 239 5000 4 100 302 237 79 7 234 252 233 251 233 251 10000 14 100 281 220 74 2 229 265 228 264 227 264 15000 24 100 268 210 70 8 224 279 223 279 222 278 18000 30 100 259 203 68 4 220 289 220 288 219 286 20000 34 100 253 199 66 9 218 295 217 294 216 293 21000 36 100 251 197 66 2 217 298 216 297 215 296 22000 38 100 249 195 65 7 216 301 215 300 214 299 23000 40 100 247 194 65 2 215 305 21...

Page 304: ...1 238 241 237 240 5000 1 100 304 238 80 2 233 253 232 253 232 252 10000 9 100 282 221 74 5 228 267 227 266 227 265 15000 19 100 269 211 71 2 223 281 222 280 221 279 18000 25 100 260 204 68 7 219 290 219 290 218 288 20000 29 100 255 200 67 2 217 297 216 296 215 294 21000 31 100 252 198 66 6 216 300 215 299 214 298 22000 33 100 250 196 66 0 215 303 214 302 213 301 23000 35 100 248 195 65 5 214 307 2...

Page 305: ...2 23 7 242 236 241 5000 6 100 305 240 80 7 232 255 232 254 231 254 10000 4 100 284 223 74 9 227 268 226 268 226 267 15000 14 100 271 213 71 5 222 283 221 282 220 281 18000 20 100 261 205 69 0 219 292 218 291 217 290 20000 24 100 256 201 67 6 216 299 216 298 215 296 21000 26 100 253 199 66 9 215 302 215 301 213 300 22000 28 100 251 197 66 4 214 305 213 304 212 303 23000 30 100 249 196 65 8 213 309 ...

Page 306: ...44 236 243 236 243 5000 11 100 307 241 81 1 231 256 231 256 230 255 10000 1 100 285 224 75 3 226 270 226 269 225 268 15000 9 100 272 214 71 9 221 284 220 284 219 283 18000 15 100 263 206 69 4 218 294 217 293 216 292 20000 19 100 257 202 67 9 216 301 215 300 214 298 21000 21 100 255 200 67 2 215 304 214 303 213 301 22000 23 100 252 198 66 7 213 307 212 306 211 305 23000 25 100 250 197 66 1 212 311 ...

Page 307: ...45 235 245 235 244 5000 16 100 309 242 81 6 231 258 230 257 230 256 10000 6 100 287 225 75 7 225 271 225 271 224 270 15000 4 100 274 215 72 3 220 286 219 285 219 284 18000 10 100 264 207 69 8 217 296 216 295 215 293 20000 14 100 259 203 68 3 215 302 214 301 213 300 21000 16 100 256 201 67 6 214 306 213 305 212 303 22000 18 100 254 199 67 0 213 309 212 308 210 306 23000 20 100 252 198 66 5 211 313 ...

Page 308: ...34 248 234 247 233 247 5000 26 100 312 245 82 5 229 260 229 260 228 259 10000 16 100 290 227 76 5 224 274 223 274 223 273 15000 6 100 276 217 73 0 219 289 218 289 217 287 18000 0 100 267 209 70 4 215 299 214 298 213 297 20000 4 100 261 205 69 0 213 306 212 305 211 303 21000 6 99 256 201 67 6 211 308 210 307 209 305 22000 8 96 248 195 65 6 208 309 207 307 205 305 23000 10 94 241 189 63 8 205 309 20...

Page 309: ...19000 37 42 149 32 147 22 146 12 145 2 143 37 1 37 4 37 9 38 4 38 7 110 196 111 198 113 201 114 203 115 204 20000 37 44 147 34 146 24 145 14 144 4 142 36 1 36 6 37 2 37 7 38 0 107 197 109 200 111 203 112 205 113 206 21000 37 46 148 36 147 26 145 16 143 6 141 35 8 36 4 36 7 37 0 37 2 107 201 108 204 109 206 110 207 111 209 22000 37 48 146 38 145 28 143 18 142 8 141 34 9 35 4 35 7 36 3 36 8 104 202 ...

Page 310: ... 26 000 42 56 151 46 150 36 148 26 146 16 144 34 5 35 0 35 3 35 6 35 9 102 223 104 226 105 228 106 230 107 232 27 000 44 57 153 47 151 37 150 27 148 17 147 34 7 35 1 35 7 35 9 36 5 103 229 104 232 106 235 107 237 108 241 28 000 45 59 154 49 153 39 151 29 149 19 147 34 8 35 4 35 7 36 0 36 3 103 235 105 239 106 241 107 243 108 245 29 000 45 61 154 51 152 41 150 31 149 21 147 34 6 34 9 35 2 35 8 36 1...

Page 311: ... 000 42 42 155 32 154 22 153 12 151 2 149 39 5 40 1 40 7 41 1 41 5 117 204 119 207 121 210 122 211 123 213 20 000 42 44 153 34 152 24 151 14 150 4 149 38 5 39 1 39 7 40 4 41 0 114 205 116 208 118 211 120 214 122 216 21 000 42 46 153 36 151 26 150 16 149 6 148 38 0 38 3 39 0 39 6 40 2 113 208 114 210 116 213 118 216 119 218 22 000 42 48 151 38 150 28 149 18 148 8 147 37 0 37 6 38 2 38 9 39 5 110 20...

Page 312: ... 26 000 45 56 152 46 151 36 149 26 147 16 145 35 8 36 5 36 8 37 2 37 5 106 224 108 228 109 230 111 232 112 233 27 000 46 57 154 47 152 37 150 27 149 17 147 36 1 36 5 36 9 37 5 37 9 107 231 108 233 110 235 111 239 113 241 28 000 48 59 156 49 154 39 152 29 150 19 148 36 5 36 9 37 2 37 6 38 0 109 238 110 240 111 243 112 245 113 246 29 000 48 61 155 51 153 41 151 31 149 21 147 36 1 36 5 36 8 37 2 37 5...

Page 313: ... 000 47 42 159 32 158 22 157 12 156 2 155 41 5 42 2 43 0 43 6 44 3 123 209 125 212 128 215 130 218 132 221 20 000 47 44 159 34 157 24 156 14 155 4 154 41 0 41 5 42 2 42 8 43 5 122 212 123 214 125 217 127 220 129 223 21 000 47 46 157 36 156 26 155 16 154 6 153 40 0 40 7 41 4 42 1 42 8 119 213 121 216 123 220 125 223 127 226 22 000 47 48 155 38 154 28 153 18 152 8 151 39 1 39 8 40 4 41 1 41 8 116 21...

Page 314: ... 26 000 49 56 153 46 152 36 151 26 149 16 147 37 3 38 1 38 8 39 2 39 6 111 226 113 229 115 233 117 235 118 236 27 000 50 57 155 47 153 37 151 27 149 17 147 37 7 38 1 38 6 39 0 39 5 112 232 113 235 115 237 116 239 117 241 28 000 52 59 158 49 155 39 153 29 151 19 149 38 4 38 6 39 1 39 5 39 9 114 241 115 242 116 244 117 246 119 248 29 000 52 61 156 51 154 41 152 31 150 21 148 37 8 38 2 38 7 39 1 39 6...

Page 315: ... 00 40 32 10 6 61 10 25 30 23 7 9 48 24000 16 00 55 43 14 6 74 12 00 37 29 9 9 55 09 35 28 22 7 4 44 22000 14 40 51 40 13 4 66 11 00 35 27 9 2 50 08 50 26 20 6 9 40 20000 13 20 47 37 12 3 59 10 00 32 25 8 4 44 08 00 24 19 6 4 35 18000 12 00 42 33 11 2 53 09 00 29 23 7 7 39 07 10 22 17 5 9 31 16000 10 40 38 30 10 0 46 08 00 26 21 6 9 34 06 25 20 16 5 3 27 14000 09 20 33 26 8 8 40 07 00 23 18 6 1 30...

Page 316: ... altitude feet FUEL USED DURING HOLDING TIME Weight 5500 lbs 2495 kg Weight 6300 lbs 2858 kg 10 min 30 min 10 min 30 min l kg USG l kg USG l kg USG l kg USG SL 29 23 7 7 88 69 23 2 30 23 7 9 89 70 23 6 5000 26 20 6 8 77 61 20 5 27 21 7 0 80 63 21 1 10000 23 18 6 1 70 55 18 4 24 19 6 4 72 57 19 2 15000 22 17 5 7 65 51 17 1 23 18 6 0 68 53 17 9 20000 20 16 5 3 60 47 15 8 21 16 5 5 63 49 16 6 Figure ...

Page 317: ...95 1940 2560 2035 2660 2135 2790 6000 1940 2560 2100 2725 2200 2855 2300 2955 8000 2100 2725 2265 2920 2360 3020 2495 3180 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 1905 2530 2000 2625 2070 2690 2135 2790 2000 2070 2690 2135 2790 2230 2890 2300 2955 4000 2230 2890 2330 2985 2430 3085 2495 3185 6000 2395 3050 2530 3215 2625 3315 2690 3380 8000 2590 3280 ...

Page 318: ... 1345 2330 1410 2395 6000 1280 2230 1380 2360 1445 2460 1510 2525 8000 1380 2360 1475 2490 1540 2590 1610 2690 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 1280 2200 1310 2300 1380 2360 1445 2430 2000 1345 2330 1410 2430 1475 2495 1540 2560 4000 1445 2460 1510 2560 1575 2655 1640 2755 6000 1575 2645 1640 2720 1705 2820 1770 2920 8000 1705 2790 1770 2885 18...

Page 319: ...1150 2330 1200 2395 6000 1080 2230 1180 2360 1230 2460 1280 2525 8000 1180 2360 1245 2490 1310 2590 1360 2690 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 1080 2200 1115 2300 1180 2360 1230 2430 2000 1150 2330 1200 2430 1245 2495 1310 2560 4000 1230 2460 1280 2560 1345 2655 1395 2755 6000 1345 2645 1395 2720 1445 2820 1510 2920 8000 1445 2790 1510 2885 156...

Page 320: ...ION 6 WEIGHT AND BALANCE TABLE OF CONTENTS 6 1 GENERAL 6 1 1 6 2 AIRPLANE WEIGHING PROCEDURES 6 2 1 6 3 BAGGAGE LOADING 6 3 1 6 4 DETERMINING WEIGHT AND BALANCE 6 4 1 GENERAL 6 4 1 UTILIZATION OF WEIGHT AND BALANCE GRAPH 6 4 1 DETERMINING EMPTY AIRPLANE CHARACTERISTICS 6 4 11 6 5 LIST OF EQUIPMENT 6 5 1 ...

Page 321: ... balance for various flight operations are also provided A list of equipment available for this airplane is referenced at the end of this Pilot s Operating Handbook refer to Chapter 6 5 It should be noted that the list of specific optional equipment installed on your airplane as delivered from the factory can be found in the records carried in the airplane IT IS THE PILOT S RESPONSIBILITY TO ENSUR...

Page 322: ...Page 6 2 1 6 2 AIRPLANE WEIGHING PROCEDURES Refer to Maintenance Manual for the procedures to use NOTE Weighing carried out at the factory takes into account all equipment installed on the airplane The list of this equipment and the total weight is noted in the Individual Inspection Record ...

Page 323: ... attached through nine anchoring points on seat rails between frame C11 and frame C13bis Figure 7 2 1B The Large Cargo Net is attached through seven anchoring points on seat rails between frame C11 and frame C13bis and six anchoring points on fuselage sides at frame C14 Figure 7 2 1A Authorized anchoring points are identified with green self adhesive labels affixed to the inside of the rail A plac...

Page 324: ...ally if rear seats are not used or removed in 4 seat accommodation first load aft compartment then if required FWD compartment If rear seats are used first load FWD compartment then if required aft compartment Weight and balance graph should be checked to ensure the airplane is within the allowable limits ...

Page 325: ... aerodynamic chord Empty weight and the corresponding balance allow to calculate the airplane basic index If airplane empty weight has varied since last weighing form refer to paragraph DETERMINING EMPTY AIRPLANE CHARACTERISTICS to determine new empty weight and the corresponding balance for instance optional equipment installation UTILIZATION OF WEIGHT AND BALANCE GRAPH FIGURES 6 4 1 6 4 1A AND 6...

Page 326: ... October 31 2013 Rev 1 Page 6 4 2 3 Utilization of weight and balance graph Record airplane basic characteristics in Compute basic index with the formula described in and record the result in Record foreseen loading in and compute total weight of the loaded airplane ...

Page 327: ...1 Configuration 6 seats standard Basic Index and Basic Empty Weight 2 Configuration Modified Basic Index Modified and Empty Weight Modified 1 Mid Seat is equal to 1 7 point of Index and 37 47 lbs 17 Kg 1 Rear Seat is equal to 6 points of Index and 52 91 lbs 24 Kg Remove or add the number of index point for each item removed or added Remove or add the weight for each item removed or added 3 From th...

Page 328: ...3 X X X 6 52 91 lbs 24 kg C4 1 X X 12 105 82 lbs 48 kg C5 X X X 6 52 91 lbs 24 kg C6 X X X 1 7 37 47 lbs 17 kg C7 X X 7 7 90 38 lbs 41 kg C8 X X 7 7 90 38 lbs 41 kg C9 X X 7 7 90 38 lbs 41 kg C10 1 X 13 7 143 29 lbs 65 kg C11 X X X 1 7 37 47 lbs 17 kg C12 X X 7 7 90 38 lbs 41 kg C13 X X 7 7 90 38 lbs 41 kg C14 X X 7 7 90 38 lbs 41 kg C15 1 X 13 7 143 29 lbs 65 kg C16 X X 3 4 74 94 lbs 34 kg C17 X ...

Page 329: ...ght 4409 62 lbs Perform the weight and balance graph with Index 57 3 and Empty Weight 4409 62 lbs Example 2 Basic Airplane Configuration 6 Seats Standard no cabinet Basic Index 65 Basic Empty Weight 4500 lbs If you remove 1 Mid Seat and 2 Rear Seats you have config C15 from table New Basic Index Basic Index Mid Seat Index 2 Rear Seats Index New Basic Index 65 1 7 2 x 6 New Basic Index 51 3 New Emp...

Page 330: ...ng to indicated value of loading 400 lbs or 200 kg in example the weight indicated in the arrow gives pitch value between two oblique lines c Then continue the line vertically downwards up to interception of oblique lines of second heading and work in the same way as before procedure described in b d Proceed in the same way for remaining headings Draw then a vertical line corresponding to final in...

Page 331: ...PILOT S OPERATING HANDBOOK SECTION 6 WEIGHT AND BALANCE Edition 0 October 31 2013 Rev 1 Page 6 4 7 Figure 6 4 1 LOADING SAMPLE In Kg and Litres ...

Page 332: ...PILOT S OPERATING HANDBOOK SECTION 6 WEIGHT AND BALANCE Edition 0 October 31 2013 Rev 1 Page 6 4 8 Figure 6 4 1A LOADING SAMPLE In lbs and USG ...

Page 333: ...PILOT S OPERATING HANDBOOK SECTION 6 WEIGHT AND BALANCE Edition 0 October 31 2013 Rev 1 Page 6 4 9 Figure 6 4 2 WEIGHT AND BALANCE GRAPH In Kg and Litres ...

Page 334: ...PILOT S OPERATING HANDBOOK SECTION 6 WEIGHT AND BALANCE Edition 0 October 31 2013 Rev 1 Page 6 4 10 Figure 6 4 2A WEIGHT AND BALANCE GRAPH In lbs and USG ...

Page 335: ...eristics weight arm except those listed in this Chapter Use the chart below to compute new empty weight and corresponding balance if necessary DATE EQUIPMENT OR MODIFICATION DESCRIPTION WEIGHT MODIFICATION BASIC EMPTY WEIGHT Weight lb Arm in Moment lb in 1000 Weight W Arm do Moment According to delivery Figure 6 4 3 SAMPLE WEIGHT AND BALANCE RECORD CG m a c do 172 93 59 45 100 Use the above formul...

Page 336: ...ets Version A L H low cabinet 9 48 4 300 203 74 5 175 Version B R H low cabinet 9 48 4 300 203 74 5 175 Version C Removable low insulated picnic bag 9 48 4 300 203 74 5 175 Version D L H top storage cabinet 7 72 3 500 203 74 5 175 Version E R H top storage cabinet 7 72 3 500 203 74 5 175 Version F R H top storage cabinet audio 7 94 3 600 203 74 5 175 Version G L H top baggage cabinet 3 09 1 400 20...

Page 337: ...rection T700G2500005000 37 48 17 00 224 80 5 710 S R H Intermediate seat back to flight direction T700G2500005001 37 48 17 00 224 80 5 710 S Double chair L H Seat T700C2500005012 52 91 24 00 278 19 7 066 R H Seat T700C2500005013 52 91 24 00 278 19 7 066 Nets S 0315 25 Small cargo net GP SOCT704CC 10 15 00 7 00 S 0315 25 Large cargo net GP SOCT704CS 10 13 00 6 00 S Partition net at Frame 14 T700B25...

Page 338: ...013 Rev 1 Page 6 5 1 6 5 LIST OF EQUIPMENT The list of equipment is available in SOCATA Report reference NAV No 34 90 RJ App 2 located at the end of this POH A separate list of equipment of items installed at the factory in your specific airplane is provided in your airplane file ...

Page 339: ...OMPARTMENTS 7 3 27 USE OF CARGO NETS 7 3 29 7 4 FLIGHT CONTROLS 7 4 1 ROLL 7 4 1 ROLL TRIM 7 4 1 ELEVATOR 7 4 6 PITCH TRIM 7 4 6 RUDDER 7 4 11 RUDDER TRIM 7 4 11 7 5 LANDING GEAR 7 5 1 HYDRAULIC PRESSURE 7 5 1 LANDING GEAR CONTROL 7 5 1 LANDING GEAR POSITION INDICATOR 7 5 1 SAFETY 7 5 4 GROUND MANEUVERS 7 5 6 BRAKE SYSTEM 7 5 9 PARKING BRAKE 7 5 9 7 6 POWERPLANT 7 6 1 TURBOPROP ENGINE OPERATION 7 ...

Page 340: ...ING 7 8 15 7 9 AIR CONDITIONING AND PRESSURIZATION 7 9 1 ENGINE BLEED AIR SYSTEM 7 9 1 DUAL ZONES ENVIRONMENTAL CONTROL SYSTEM 7 9 2 CABIN PRESSURIZATION CONTROL SYSTEM 7 9 4 7 10 EMERGENCY OXYGEN SYSTEM 7 10 1 FLIGHT ABOVE 15000 FT WITH EMERGENCY DESCENT 7 10 4 WHEN REQUIRED TO REMAIN ABOVE 15000 FT DUE TO MINIMUM EN ROUTE ALTITUDE 7 10 5 FLIGHT BETWEEN 15000 FT AND 10000 FT 7 10 6 7 11 AIR DATA ...

Page 341: ...ition 0 October 31 2013 Rev 1 Page 7 0 3 7 14 MISCELLANEOUS EQUIPMENT 7 14 1 STALL WARNING SYSTEM 7 14 1 STATIC DISCHARGERS 7 14 1 CABIN FIRE EXTINGUISHER 7 14 1 AUTOPILOT 7 14 1 GPS 7 14 1 EMERGENCY LOCATOR TRANSMITTER 7 14 2 OPTIONAL EQUIPMENT 7 14 3 ...

Page 342: ...in the airplane Complete description and operation of the GARMIN G1000 integrated flight deck are detailed in the GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the Socata TBM 900 No 190 00708 05 or any later version as applicable References to this Guide are often made all along this Section to get more details about some systems Details of other optional systems and equipment ar...

Page 343: ...onstruction and is equipped with a retractable tricycle landing gear The pressurized cabin is equipped on the left side of fuselage with a one piece access door and folding stairs comprising a hand rail allowing pilot and passengers boarding The occupants have access to cockpit and to rear seats through a central aisle An optional pilot door located forward of the cabin on the left side allows acc...

Page 344: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 2 2 Figure 7 2 1 CABIN ARRANGEMENT 6 seat accommodation ...

Page 345: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 2 3 Figure 7 2 1A CABIN ARRANGEMENT 4 seat accommodation with large securing net ...

Page 346: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 2 4 Figure 7 2 1B CABIN ARRANGEMENT 4 seat accommodation with small securing net ...

Page 347: ...he ailerons Trim tab attached on the trailing edge of L H aileron is electrically activated by a trim knob through an actuator WING FLAPS Figure 7 2 2 The wing flaps are large span slotted flaps with a single rotation point They are activated by actuating rod controlled screw jacks linked to an electric motor located under the floor inside the fuselage A preselection control located on the right s...

Page 348: ... HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 2 6 Figure 7 2 2 1 2 WING FLAPS 1 Geared motor 2 Internal actuator 3 Intermediate bearings 4 Wing flap 5 External actuator 6 Rods 7 Control selector ...

Page 349: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 2 7 Figure 7 2 2 2 2 WING FLAPS ...

Page 350: ...e 7 3 3 on top ESI 2000 MASTER CAUTION and MASTER WARNING at bottom deicing controls and indicators NORMAL MASK inverter landing gear control panel parking brake control and left station control wheel Central area instrument panel includes Figure 7 3 4 on top surmounted by the stand by compass AFCS control unit at bottom GCU 475 control unit and ECS control panel Right area instrument panel includ...

Page 351: ...ed to alert the pilot during some configurations The aural signals are heard through the loud speakers or the buzzer installed in cockpit overhead panel The aural warnings consist of the aural warning box the buzzer and loud speakers The system uses the stall warning horn the VMO alarm the landing gear control unit the flap geared motor Aural warning box The aural warning box consists of a box inc...

Page 352: ...cted by AURAL WARN circuit breaker and the emergency lighting rheostat is electrically supplied by BATT BUS bar and protected by PANEL EMER circuit breaker Aural warning operation The GMA 1 and 2 audio control panels receive signals from the aural warning box According to the airplane configuration these signals are low pitched and or high pitched The HORN TEST knob allows to test the correct oper...

Page 353: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 4 Figure 7 3 1 INSTRUMENT PANEL ASSEMBLY Typical arrangement ...

Page 354: ...l emergency lighting 5 Instrument panel emergency lighting switches rheostats 6 R H cockpit floodlight 7 ELT remote control switch 8 AP TRIMS switch 9 FUEL control panel Figure 7 7 3 10 ENGINE START switches Figure 7 6 4 11 ELECTRIC POWER switches Figure 7 8 4 12 INT LIGHTS internal lighting switches Figure 7 8 6 13 EXT LIGHTS external lighting switches Figure 7 8 5 14 L H cockpit floodlight 15 HO...

Page 355: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 7 Figure 7 3 2 2 2 UPPER PANEL AND COCKPIT OVERHEAD PANEL ...

Page 356: ...tation control wheel tube 8 Deicing control and check panel Figure 7 13 1 9 L H station rudder pedals adjusting handle 10 Left station reception micro jacks 11 Pitch Yaw trim setting management 12 Push To Talk button PTT 13 AP TRIMS DISC red push button 14 CWS 15 Paper clip 16 Chonometer management 17 Transponder Ident sequence 18 Stormscope clear 19 COM 2 Stand by active 20 Flight conditions and ...

Page 357: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 9 Figure 7 3 3 2 2 LEFT INSTRUMENT PANEL Typical arrangement ...

Page 358: ...ION Edition 0 October 31 2013 Rev 1 Page 7 3 10 Figure 7 3 4 1 2 CENTRAL INSTRUMENT PANEL 1 Stand by compass 2 GMC 710 AFCS mode controller 3 Registration 4 ECS air conditioning control panel Figure 7 9 2 5 GCU 475 remote controller 6 GDU 1500 MFD ...

Page 359: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 11 Figure 7 3 4 2 2 CENTRAL INSTRUMENT PANEL Typical arrangement ...

Page 360: ...reception micro jacks 7 Hour meter 8 R H station rudder pedals adjusting handle 9 Circuit breakers panel postlight 10 Cigar lighter and two USB servicing plugs 11 Cabin emergency air control EMERGENCY RAM AIR control knob 12 Static source selector 13 COM 2 Stand by active 14 Stormscope clear 15 Tansponder Ident sequence 16 Chronometer management 17 Paper clip 18 CWS 19 AP TRIMS DISC red push butto...

Page 361: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 13 Figure 7 3 5 2 2 RIGHT INSTRUMENT PANEL Typical arrangement ...

Page 362: ...age 7 3 14 Figure 7 3 6 1 2 PEDESTAL CONSOLE 1 Throttle 2 Flaps control 3 Throttle friction adjustment 4 Manual fuel tank selector Figure 7 7 2 5 Roll trim tab control 6 Emergency fuel control 7 Pitch trim tab control 8 Lock for access door to landing gear emergency pump Figure 7 5 2 ...

Page 363: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 15 Figure 7 3 6 2 2 PEDESTAL CONSOLE Typical arrangement ...

Page 364: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 16 Figure 7 3 7 CIRCUIT BREAKERS PANEL ...

Page 365: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 17 Figure 7 3 8 GENERAL ALARMS WARNING LIGHTS ...

Page 366: ...position near the complete closing Pull the door until it aligns with fuselage and lock it by moving inside handle downwards Check that all latch pins and hooks are correctly engaged visible green marks The DOOR CAS message lights on as long as the door is not correctly locked CAUTION BEFORE OPENING ACCESS DOOR MAKE SURE DOOR DEFLECTION AREA IS CLEAR To open door from inside the cabin unlock the h...

Page 367: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 19 Figure 7 3 9 CABIN ACCESS DOOR ...

Page 368: ...s The DOOR CAS message lights on as long as cabin access door and pilot access door if installed are not correctly locked To open door from inside the cockpit unlock the handle by pressing onknob locatedon itsright side pull thehandle inwards and move it upwards Open the door helping it to open until it reaches its maximum opening position After door opening tilt and unfold footstep CAUTION RETRAC...

Page 369: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 21 Figure 7 3 9A COCKPIT ACCESS DOOR PILOT DOOR ...

Page 370: ...pped with two handles one inside and the other outside each located on the upper frame When the airplane is parked the closing system may be locked by a safety pin provided with a flag marker The handle is then inoperable WARNING TAXIING AND FLYING WITH THIEF PROOF SAFETY PIN INSTALLED IS FORBIDDEN To open the emergency exit pull one of the two handles and tilt the emergency exit from top to botto...

Page 371: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 23 Figure 7 3 10 EMERGENCY EXIT ...

Page 372: ...nd 7 3 11A With 6 seat accommodation The accommodation consists of two individual seats installed back to the flight direction mounted on the same rails as the front seats The seat back angle is adjusted by pulling up side handle two rear seats arranged as a bench mounted on the same rails as the front seats The seat back rests tilt forward by pulling up the handle located forward on L H side of e...

Page 373: ...ibility of seat configuration Cargo zone ONLY zone B and zone C can be modified for seat configurations For the MID Seat zone B ONLY the Middle Seats can be installed in MID Seat Zone This zone accepts Fwd and Aft Facing Mid Seat when rear seats are installed The zone B accepts zero or 1 or 2 seats The zone B is not a luggage area For the REAR Seat zone C ONLY the Rear Seat can be installed in Rea...

Page 374: ...iguration name Location number 1 2 3 4 5 C1 X X X X C2 X X X C3 X X X C4 1 X X C5 X X X C6 X X X C7 X X C8 X X C9 X X C10 1 X C11 X X X C12 X X C13 X X C14 X X C15 1 X C16 X X C17 X C18 X C19 X C20 1 Zone B Zone C 1 This configuration accepts small net or large net Each cross indicates that you have a seat at the correspondent location number ...

Page 375: ...he cabin by tilting forward the L H rear seat and or L H or R H rear seat back rests Rings fitted with lashing straps are provided for securing parcels and baggage on compartment floor The FWD compartment is accessible by opening the external door located on the left side of the airplane These locations are designed for the carrying of low density loads loading and unloading must be carried out wi...

Page 376: ...nd placed on the floor Authorized anchoring points are identified with green self adhesive labels affixed to the inside of the seat rail A placard indicates loading limits for each cargo net for the Small Cargo Net it is affixed on frame C13bis for the Large Cargo Net it is affixed on R H side upholstery panel in the rear baggage compartment Maximum loads allowable in the baggage compartments depe...

Page 377: ...f hook buckle or stud on tensioning strap strap must mandatorily be discarded and replaced webbing frayed or cut on less than 30 of its surface reduce maximum load by 50 seam of vertical net tensioning straps damaged on less than 30 of its length reduce maximum load by 50 seam of tensioning straps attached on the rails damaged on less than 30 of its length reduce maximum load by 50 beyond 30 damag...

Page 378: ...dinal shift control 8 Front seat s height control 9 Front seat s back rest tilt control 10 Drawer for pilot s piddle pak if installed front side new bags rear side used bags 11 Intermediate seat s back rest tilt control 12 Rear bench seat s back rest tilt control 13 Rear bench L H seat tilt control 14 Rear bench seat s adjustment control handle NOTE To have access to the baggage compartment pull f...

Page 379: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 31 Figure 7 3 11 2 2 SEATS With 6 seat accommodation ...

Page 380: ...accommodation 1 Front passenger s seat 2 L H pilot s seat 3 R H intermediate passenger s seat facing flight direction 4 L H intermediate passenger s seat facing flight direction 5 Front seat s longitudinal shift control 6 Front seat s height control 7 Front seat s back rest tilt control 8 Intermediate seat s back rest tilt control ...

Page 381: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 33 Figure 7 3 11A 2 2 SEATS With 4 seat accommodation ...

Page 382: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 3 34 Figure 7 3 12 FRONT AND REAR SEAT BELTS with movable straps AND HARNESSES ...

Page 383: ...when the aileron is deflected upwards and remains in wing profile when the aileron is deflected downwards Control wheel movement is transmitted through rods to fuselage roll lever located under the floor The movement is then transmitted through cables to the spoiler mechanism and from the spoiler mechanism to wing roll lever which activates the aileron through a rod A rudder roll combination sprin...

Page 384: ... HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 2 Figure 7 4 1 1 2 ROLL 1 Pedestal assembly 2 Control wheels 3 Fuselage roll lever 4 Spoiler 5 Aileron 6 Aileron control in wing 7 Spoiler control ...

Page 385: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 3 Figure 7 4 1 2 2 ROLL ...

Page 386: ... HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 4 Figure 7 4 2 1 2 LATERAL TRIM 1 Roll trim tab 2 Aileron 3 Adjustable rods 4 Actuator 5 Trim tab control wiring 6 Trim switch on pedestal console ...

Page 387: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 5 Figure 7 4 2 2 2 LATERAL TRIM ...

Page 388: ...rovided with an automatic anti tab automaticity about 0 3 which is also used as trim tab PITCH TRIM Figure 7 4 4 The pitch trim is accomplished through the two anti tabs located on left and right elevators The trim tab can be controlled electrically or manually It is activated through cables and a chain on two screw actuators attached to the horizontal empennage The electrical control consists of ...

Page 389: ...dition 0 October 31 2013 Rev 1 Page 7 4 7 Figure 7 4 3 1 2 ELEVATOR 1 Control wheel assembly 2 Elevators 3 Lever assembly fuselage rear part 4 Elevator bellcrank 5 Rod with presseal connection 6 Lever assembly under floor 7 Pedestal assembly 8 Actuator ...

Page 390: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 8 Figure 7 4 3 2 2 ELEVATOR ...

Page 391: ...OOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 9 Figure 7 4 4 1 2 PITCH TRIM 1 Cables 2 Pulleys 3 Pitch trim tabs 4 Actuating rods 5 Actuator 6 Pitch trim manual control wheel 7 Electric pitch trim control ...

Page 392: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 10 Figure 7 4 4 2 2 PITCH TRIM ...

Page 393: ... beneath the instrument panel and a locking device on the rudder pedals This ball locking device allows selecting six different positions When landing gear is down rudder pedals are linked to nose gear steering system Spring system of rudder roll combination induces aileron deflection at the time of pedal displacement and vice versa RUDDER TRIM Figure 7 4 6 A trim tab hinged at two points located ...

Page 394: ...CRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 12 Figure 7 4 5 1 2 RUDDER 1 Roll rudder combination bellcrank installation 2 Rudder pedals assembly 3 Control cables 4 Pulleys 5 Rudder lever assembly 6 Rod 7 Rudder 8 Nose gear steering rod ...

Page 395: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 13 Figure 7 4 5 2 2 RUDDER ...

Page 396: ...OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 14 Figure 7 4 6 1 2 RUDDER TRIM 1 Trim switch on control wheel 2 Actuator 3 Rudder trim tab 4 Rods 5 Rudder trim control wiring ...

Page 397: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 15 Figure 7 4 6 2 2 RUDDER TRIM ...

Page 398: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 4 16 INTENTIONALLY LEFT BLANK ...

Page 399: ...e on each main landing gear are driven and kept in UP position by the landing gear itself All doors are mechanically kept in down position HYDRAULIC PRESSURE Hydraulic pressure required for landing gear operation is provided during normal operation by an electro hydraulic generator with integrated reservoir during emergency extension operation by a hand pump supplied with an auxiliary reservoir LA...

Page 400: ...ases mean the gear is not down locked In case of doubt about landing gear down locked position an independent electrical circuit provides a countercheck capability of the indication system Pressing the CHECK DOWN push button located on the landing gear panel checks the down lock of the gear making twinkle at 16 hertz the green indicator lights corresponding to the down locked gear Pressing the LIG...

Page 401: ...ION Edition 0 October 31 2013 Rev 1 Page 7 5 3 Figure 7 5 1 CONTROL PANEL AND LANDING GEAR INDICATING 1 Green indicator light 2 Red warning light 3 Landing gear control selector 4 Check down test push button 5 Light test push button 6 Amber light ...

Page 402: ...ng gear is not down locked flaps are beyond TO position Takeoff and landing gear is not down locked NOTE If one of above conditions exists and airplane is in stall configuration the audio warning signal becomes alternated high pitched sound low pitched sound Emergency landing gear extension control Figure 7 5 2 Emergency landing gear extension control consists of a hand pump and a by pass selector...

Page 403: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 5 5 Figure 7 5 2 EMERGENCY LANDING GEAR EXTENSION CONTROL ...

Page 404: ...e wheel swivels about 20 Steering may be increased up to 28 by applying differential braking to each side Airplane may be towed by attaching a steering or towing bar on nose gear Refer to Chapter 8 6 for operation In that case nose wheel steering angle is limited to 28 Minimum turn diameter Minimum turn diameter Figure 7 5 4 is obtained by using nose gear steering and differential braking Since ti...

Page 405: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 5 7 Figure 7 5 3 MINIMUM TURN DIAMETER Full rudder pedals travel without using differential braking ...

Page 406: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 5 8 Figure 7 5 4 MINIMUM TURN DIAMETER Full rudder pedals travel by using differential braking ...

Page 407: ...g during taxiing PARKING BRAKE Figures 7 5 5 and 7 5 6 Parking brake control consists of a control knob located on pilot s side lower instrument panel and a valve which regulates brake pressure To apply parking brake press on toe brake of rudder pedals and position control knob on ON PARK BRAKE CAS message lights on when control knob is positioned on ON NOTE Operating the parking brake knob withou...

Page 408: ...ion 0 October 31 2013 Rev 1 Page 7 5 10 Figure 7 5 5 1 2 BRAKE SYSTEM 1 Reservoir 2 Vent 3 R H station master cylinders 4 Parking brake control knob 5 Parking brake valve 6 Drain 7 Pilot s station master cylinders 8 L H brake assembly 9 R H brake assembly ...

Page 409: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 5 11 Figure 7 5 5 2 2 BRAKE SYSTEM ...

Page 410: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 5 12 Figure 7 5 6 PARKING BRAKE ...

Page 411: ...re mixed and sprayed into combustion chamber by fuel nozzles The mixture is first ignited by two spark igniter plugs then combustion continues as a result of air fuel mixture flow Gases resulting from combustion expand through a series of turbines The first one gas generator turbine drives compressor assembly and accessories the two other ones power turbines independant from the first one drive pr...

Page 412: ...POWERPLANT 1 Propeller governor 2 Exhaust stub 3 Axial compressors 4 Accessory gearbox 5 FCU Fuel control unit 6 Oil to fuel heater 7 Input coupling shaft 8 Air intake 9 Centrifugal impeller 10 Combustion chamber 11 Compressor turbine 12 Power turbine 1st stage 13 Power turbine 2nd stage 14 Power turbine shaft ...

Page 413: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 6 3 Figure 7 6 1 2 2 POWERPLANT ...

Page 414: ... ENGINE CONTROLS LEVERS Figure 7 6 2 Engine operation requires use of two levers located on pedestal console in cabin Throttle Item 1 and its detent for reverse Item 4 MAN OVRD emergency fuel regulation lever Item 3 NOTE Thumbwheel for lever friction Item 2 Figure 7 6 2 ENGINE CONTROLS LEVERS ...

Page 415: ...HE LINKAGE WILL RESULT REVERSE MAY ONLY BE SELECTED WITH ENGINE RUNNING AND PROPELLER TURNING When engine is shutdown there is no oil pressure in the propeller and the feathering spring locks the Beta ring and the propeller reversing interconnect linkage on the engine All rearward effort on the throttle past the idle stop may damage or break the flexible control cable Condition mode The throttle i...

Page 416: ...TE Engine monitoring is ensured by CAS messages ITT and OIL PRESS Refer to the GARMIN G1000 Cockpit Reference Guide for further details ENGINE LUBRICATION Engine oil is in a tank incorporated into the powerplant It ensures lubrication and engine cooling A cooler located on left side in engine compartment maintains oil temperature within limits Oil flow into the cooler is metered by a thermostatic ...

Page 417: ...ter function Starting system consists of STARTER switch located on ENGINE START panel starter generator and ignition circuit Refer to Paragraph Ignition function Starting procedure is semi automatic Setting STARTER switch to ON connects the starter generator which drives powerplant STARTER CAS message lights on indicating that the starter generator is operating Starter operation is stopped automat...

Page 418: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 6 8 Figure 7 6 4 ENGINE STARTING ...

Page 419: ...NE ACCESSORIES All engine driven accessories except power turbine tacho generator Np propeller governor and overspeed governor are installed on accessory gearbox located rearwards of engine Oil pump Oil pump is a self controlled gear pump located at the bottom of oil casing Fuel high pressure pump HP Fuel high pressure pump is installed on accessory gearbox It supplies fuel nozzles flow being cont...

Page 420: ...ER Airplane is equipped with an all metal four bladed constant speed and full feathering propeller Regulation Propeller governor located on engine maintains rotation speed to the nominal value of 2000 RPM Regulation is obtained through propeller blade pitch variation counterweights drive propeller blades toward high pitch low RPM whereas oil pressure delivered by governor drives back blades toward...

Page 421: ... on the lower surface a suction strainer and three level gages FUEL UNIT The fuel unit combines shut off valve tank selector and filter functions It is connected to the manual selector through a mechanical control The fuel filter is located in a bowl at the lower part of the unit It is fitted with a by pass valve a clogging indicator and a drain valve TANK MANUAL SELECTOR Figure 7 7 2 The tank man...

Page 422: ...6 Oil to fuel heater 7 Low pressure switch 8 Fuel jet 9 Main mechanical boost pump 10 Electric boost pump 11 Fuel filter 12 Filter clogging by pass valve 13 Filter clogging indicator 14 Fuel unit 15 Filter drain 16 Fuel return pipe 17 Filling port 18 NACA scoop 19 Tank vent valve 20 Fuel level gages 21 Tank drain valve 22 Check valve 23 Low level detector 24 Suction strainer 25 Fuel amplifier 26 S...

Page 423: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 7 3 Figure 7 7 1 2 2 FUEL SYSTEM ...

Page 424: ...essage lights on When both low level FUEL LOW L R CAS messages are visible the sequencer changes tanks every minute and 15 seconds Post MOD70 0402 28 Airplane in flight tank is changed every five minutes as long as a fuel low level FUEL LOW L or FUEL LOW R CAS message does not appear When the first low level CAS message lights on the sequencer immediately selects the other tank The selected tank w...

Page 425: ...ed between fuel unit and main mechanical boost pump It is controlled through AUX BP switch located on FUEL panel This switch allows stopping or selecting the two pump operating modes when set to ON electric boost pump operates permanently when set to AUTO electric boost pump is automatically operated in case of fuel pressure drop at the mechanical boost pump outlet ...

Page 426: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 7 6 Figure 7 7 2 MANUAL SELECTOR OF FUEL TANKS ...

Page 427: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 7 7 Figure 7 7 3 FUEL CONTROL PANEL 1 Electric boost pump switch 2 Fuel selector 3 SHIFT push knob ...

Page 428: ... or equal to 9 USG 34 Litres of usable fuel in specified tank AUTO SEL Sequencer inactive or operating defect FUEL IMBALANCE Fuel tanks imbalanced by more than 15 USG 57 Litres for more than 30 seconds Only affected side L R or L R displayed in CAS message FUEL SYSTEM DRAINING AND CLOGGING INDICATOR Figure 7 7 4 The fuel system comprises five drain points a drain on the filter bowl two drain valve...

Page 429: ...7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 7 9 Figure 7 7 4 FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR 1 Lighting switch 2 Mirror door 3 Clogging indicator 4 Central access door 5 Filter drain 6 Tank drain 7 Drain bowl ...

Page 430: ...mpleted Generator connection with main bus bar is controlled through GENERATOR selector set to MAIN position It will be effective when connection conditions are met Generator connection is indicated by MAIN GEN CAS message disappearance NOTE STARTER GENERATOR will not supply airplane if source switch is on GPU On ground generator load should be maintained below 200 amps STAND BY GENERATOR Stand by...

Page 431: ...d to BUS bars and protected by pull off type circuit breakers located on R H side panel See Figure 7 8 3 In case of overload of a system the circuit breaker triggers and switches the system off If a circuit breaker corresponding to a non essential system trips do not reset in flight If a circuit breaker corresponding to an essential system trips allow it to cool for about three minutes then the ci...

Page 432: ...e systems maintaining SOURCE selector on BATT position In order to save battery power it is possible to shed the charges which are not essential for flight safety for that set ESS BUS TIE switch to EMER position In this configuration only ESS BUS 1 ESS BUS 2 and BATT BUS bars are supplied NOTE Supplying BUS 1 BUS 2 BUS 3 and BUS 4 bars is always possible resetting temporarily ESS BUS TIE switch to...

Page 433: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 8 4 Figure 7 8 1 ELECTRICAL DIAGRAM ...

Page 434: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 8 5 Figure 7 8 2 1 3 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 435: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 8 6 Figure 7 8 2 2 3 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 436: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 8 7 Figure 7 8 2 3 3 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 437: ... 1 protection AHRS 1 Attitude and Heading Reference System 1 protection XPDR 1 Transponder 1 protection LDG SIG Landing gear indicating system protection AURAL WARN Aural warnings protection FEATHER Propeller feather protection TORQUE Torque control protection IGNITION Powerplant iginition protection NP NG Tachometer signal conditioner protection STBY INSTR Electronic Standby Indicator ESI 2000 pr...

Page 438: ...onal protection LDG CONT Landing gear control protection SATCOM SATCOM protection if installed SATCOM HEATER SATCOM heater protection if installed BUS 3 OXYGEN PRESS Oxygen Pressure indication protection L WS DE ICE L H windshield deicing protection PITOT R STALL Pitot R and stall warning heating protection FUEL SEL Tank selector timer protection AUX BP Electrical fuel pump protection XPDR 2 Trans...

Page 439: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 8 10 Figure 7 8 3 3 3 CIRCUIT BREAKER PANEL Typical arrangement ...

Page 440: ...he electrical power system provides systems protection in case of overvoltage short circuits In case of disconnection of starter generator or stand by generator following a failure MAIN or ST BY reset can be done by pressing corresponding MAIN or ST BY knob A battery reset is done by setting the SOURCE selector to OFF and back to BATT In case of disconnection of ground power unit following a failu...

Page 441: ...S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 8 12 Figure 7 8 4 ELECTRICAL CONTROL 1 MAIN reset knob 2 ST BY reset knob 3 Crash lever 4 SOURCE selector 5 GENERATOR selector ...

Page 442: ...re embedded in the winglets Two strobe lights are installed in the winglets and one on the tail cone They are controlled by NAV and STROBE switches located on upper panel NOTE By night do not use anticollision lights in fog clouds or mist as light beam reflexion may lead to dizziness and loss of sense of orientation Recognition lights Recongnition lights are embedded in the winglets They are autom...

Page 443: ... HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 8 14 Figure 7 8 5 EXTERNAL LIGHTING CONTROLS 1 Taxi and landing light switch 2 Pulse system switch 3 Navigation lights switch 4 Strobe lights switch ...

Page 444: ...H dome light Each floodlight is controlled by a push button located near The floodlight above the table is controlled by two switches which are two way type switches The pilot can switch off the cabin floodlights and the baggage compartment dome light with the CABIN switch Instrument panel lighting Instrument panel lighting is controlled by the PANEL rheostat located on INT LIGHTS panel This light...

Page 445: ...igure 7 8 6 INTERNAL LIGHTING CONTROLS 1 Instrument panel lighting switch rheostat 2 DIMMER switch 3 Cabin lighting switch rear seats reading light 4 Access door baggage compartment and FWD dome light delayed breaker push button 5 Emergency lighting switch 6 Circuit breaker panel lighting switch ...

Page 446: ...s and indication or warning elements ENGINE BLEED AIR SYSTEM The Engine Bleed Air System is designed to ensure the following functions to bleed air from the engine to ensure a controlled airflow in the cabin to adjust the temperature of the bleed air at a compatible level in order to control the cabin temperature in heating and cooling modes The BLEED switch allows to switch on the Engine Bleed Ai...

Page 447: ...sociation with the Main Heat Exchanger MHX The temperature measurement loop given by the Inlet Temperature Sensor ITS and the 2 Ventilated Temperature Sensors CKVTS CBVTS sends the value to the GASC which compares them with the set temperature and manages the BPV position The BPV derives a part of the bleed air through the MHX to cool it and mix it to the remaining air The Engine Air Bleed System ...

Page 448: ... The compressor clutch and the condenser fan are controlled by the GASC In automatic mode the temperature of each zone is controlled independently by the system according to the settings of the TEMP C and CABIN TEMP C selectors which can vary from 17 C to 27 C In this mode the speed of each fan is automatically controlled In manual mode the blown air temperature is controlled by the system accordi...

Page 449: ... altitudes that could be as low as 0 ft Above 13500 ft the cabin altitude is minimized while maintaining P 6 0 PSI The GDU 1500 MFD shows landing field altitude cabin climb speed in Sea Level ft min and cabin atmosphere differential pressure P in PSI Cabin is automatically depressurized as soon as the airplane is on ground through landing gear switch airplane on ground or if necessary by actuating...

Page 450: ...8 Low pressure switch 19 ECS panel 20 Cockpit thermostatic valve 21 Cockpit fan 22 Cockpit evaporator 23 Cockpit blown temperature sensor CKBTS 24 Demisting microswitch 25 Hot air distributor HAD 26 Cabin Inlet temperature Sensor ITS 27 Cabin Bleed temperature switch BTSW 28 Mixing ejector MIXEJ 29 Check valve 30 MFD unit 31 Ground safety microswitch 32 Differential pressure switch 33 By pass valv...

Page 451: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 9 7 Figure 7 9 1 2 2 Global Air System ...

Page 452: ...3 Rev 1 Page 7 9 8 Figure 7 9 2 1 2 GAS controls 1 A C switch 2 BLEED switch 3 PRES MODE switch 4 DUMP switch 5 HOT AIR FLOW distributor 6 TEMP C selector cockpit cabin 7 CONTROL selector 8 FAN SPEED selector cockpit 9 FAN SPEED selector cabin 10 CABIN TEMP C selector cabin ...

Page 453: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 9 9 Figure 7 9 2 2 2 GAS controls ...

Page 454: ...sure according to the outside temperature is given in Section 8 Figure 8 7 1 as well as on a placard on the inside of the cylinder service door minimum pressure 217 PSIG 15 bars The oxygen cylinder head is equipped with a hand controlled isolation valve to permit cylinder installation and removal a microswitch causing the OXYGEN CAS message to light on This message lights on when the isolation val...

Page 455: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 10 2 Figure 7 10 1 EMERGENCY OXYGEN SYSTEM 1 Microphone switch ...

Page 456: ... on the cabin walls aft of the front seats Permanently connected to the oxygen system they are equipped with a micro controlled by the switch MICRO MASK micro inverter under cover located on the instrument panel near the pilot s control wheel The cockpit masks are equipped with a microphone a three position selector NORMAL 100 and EMERGENCY and with a push button PRESS TO TEST The proper flow is s...

Page 457: ...14 597 580 563 546 529 1 1 759 736 713 691 668 646 623 1 2 885 856 828 799 771 743 715 1 3 1010 976 941 907 873 839 806 1 4 1137 1096 1056 1015 975 935 897 2 0 1037 1001 965 930 894 859 825 2 1 1164 1122 1080 1038 997 956 916 2 2 1289 1241 1192 1144 1097 1050 1004 2 3 1416 1361 1306 1252 1198 1145 1093 2 4 1541 1480 1418 1357 1297 1238 1180 Values in PSIG Conditions 1 4 minutes from 31000 to 15000...

Page 458: ...1067 1029 992 955 918 882 846 1 3 1513 1240 1192 1144 1097 1050 1004 1 4 1513 1452 1392 1333 1275 1217 1161 2 0 992 958 925 891 858 825 793 2 1 1215 1170 1125 1081 1037 994 952 2 2 1439 1382 1326 1270 1215 1161 1108 2 3 1662 1593 1525 1457 1391 1326 1262 2 4 1888 1807 1725 1645 1567 1490 1415 Values in PSIG Conditions 1 Flight above 15000 ft All equipment used 2 1 hour usage by each pilot and pass...

Page 459: ...9 896 864 833 801 770 1 3 961 929 896 864 833 801 770 1 4 961 929 896 864 833 801 770 2 0 992 958 925 891 858 825 793 2 1 1333 1282 1231 1181 1131 1083 1035 2 2 1333 1282 1231 1181 1131 1083 1035 2 3 1333 1282 1231 1181 1131 1083 1035 2 4 1333 1282 1231 1181 1131 1083 1035 Values in PSIG Conditions 1 Flight under 15000 ft 2 90 minutes usage by each pilot and one passenger 3 Plus 30 minutes usage b...

Page 460: ...tem 1 part which is connected to the switching valve normal alternate supplies the P cabin and the electronic standby indicator The system remainder directly supplies one of the air data computers System 2 is directly connected to the second ADC Systems feature a drain valve located under the instrument panel on R H side Alternate static source The alternate static port located in the rear fuselag...

Page 461: ...ectronic Standby Indicator ESI 2000 4 GDC 74B ADC 5 GDC 74B ADC 6 FWD pressure bulkhead 7 Static system drain 8 Static system drain 9 Static system drain 10 Emergency static system drain 11 Emergency static valve Normal Alternate 12 Instrument panel 13 Dynamic system drain 14 Pitot R 15 Rear pressure bulkhead 16 Static port 17 Emergency static port 18 Static port ...

Page 462: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 11 3 Figure 7 11 1 2 2 AIR DATA SYSTEM ...

Page 463: ... the vacuum for pressurization system In case of pressure drop a pressure switch installed in the system indicates the failure by causing the VACUUM LOW CAS message to light on ELECTRONIC STANDBY INDICATOR ESI 2000 The L 3 Communications Avionics Systems ESI 2000 Electronic Standby Instrument System consists of an AMLCD display An air data sensor is integral to the ESI 2000 housing A replaceable b...

Page 464: ...G HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 12 2 Figure 7 12 1 1 2 VACUUM SYSTEM 1 Pressure regulator 2 Ejector 3 Valve 4 Regulating and relief valve 5 Pressure switch 6 Failure CAS message ...

Page 465: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 12 3 Figure 7 12 1 2 2 VACUUM SYSTEM ...

Page 466: ...ng leading edge icing inspection light see Chapter 7 8 Paragraph EXTERIOR LIGHTING PROPELLER DEICING Propeller deicing is accomplished through electrical heating of blade roots This system operates cyclically and alternately on two opposite blades at the same time Each cycle is 180 seconds long The system operation is correct when green warning light located above PROP DE ICE switch illuminates Th...

Page 467: ...must be used even during flight into non icing conditions The system condition messages PITOT NO HT L or PITOT NO HT R PITOT HT ON L or PITOT HT ON R STALL HEAT ON or STALL NO HEAT are displayed on the GDU 1500 MFD CAS window Refer to the GARMIN G1000 Cockpit Reference Guide for further details NOTE Correct operation of the audible stall warning may be altered by severe or prolonged icing TURBINE ...

Page 468: ...PILOT S OPERATING HANDBOOK SECTION 7 DESCRIPTION Edition 0 October 31 2013 Rev 1 Page 7 13 3 Figure 7 13 1 DEICING CONTROL AND CHECK PANEL ...

Page 469: ...he trailing edges of the wings flaps and ailerons rudder stabilator propeller tips and radio antennas can result in loss of usable radio signals on all communications and navigation radio equipment Usually the ADF is first and VHF communication equipment is the last to be affected Installation of static dischargers reduces interference from precipitation static but it is possible to encounter seve...

Page 470: ... switch to ON automatically in case of shock when remote control switch is set to ARM and locator transmitter switch is set to OFF A red indicator light located on ELT remote control switch in the cockpit indicates to the pilot the emergency locator transmitter is transmitting A red indicator light located above locator transmitter switch and a buzzer located in the fuselage rear section indicate ...

Page 471: ... emergency locator transmitter is transmitting Reset after an inadvertent activation 1 Set remote control switch or ELT switch to ON a The ELT keeps on transmitting emergency signal b On remote control box red indicator light flashes c On ELT red indicator light flashes d Near ELT the buzzer sounds 2 Wait approximately for 1 second 3 Set remote control switch to ARM or ELT switch to ARM a The ELT ...

Page 472: ...ANDLING 8 6 1 TOWING 8 6 1 PARKING 8 6 1 JACKING 8 6 3 LEVELING 8 6 3 FLYABLE STORAGE 8 6 3 LONG TERM STORAGE WITHOUT FLYING 8 6 3 8 7 SERVICING 8 7 1 MAINTENANCE 8 7 1 ENGINE OIL 8 7 1 FUEL 8 7 2 LANDING GEAR 8 7 5 OXYGEN 8 7 5 8 8 AIRPLANE CLEANING AND CARE 8 8 1 WINDSHIELD AND WINDOWS 8 8 1 PAINTED SURFACES 8 8 1 PROPELLER CARE 8 8 1 ENGINE CARE 8 8 1 INTERIOR CARE 8 8 1 8 9 UTILIZATION BY COLD...

Page 473: ...nd servicing of TBM 900 airplane Also included in this section are the inspection and maintenance requirements which must be followed if your airplane is to retain its performance and dependability It is recommended that a planned schedule of lubrication and preventive maintenance be followed and that this schedule be tailored to the climatic or flying conditions to which the airplane is subjected...

Page 474: ...8 2 IDENTIFICATION PLATE Any correspondence regarding your airplane should include its serial number This number together with the model number type certificate number and production certificate number are stamped on the identification plate attached to the left side of the fuselage beneath the horizontal stabilizer ...

Page 475: ...Cockpit Reference Guide for the Socata TBM 900 No 190 00708 05 or any later version as applicable and supplemental data covering optional equipment installed in the airplane refer to Section 9 Supplements and pilot s guides In addition the owner may purchase the following Maintenance Manual Illustrated Parts Catalog Bilingual Catalog of Service Bulletins Service Letters and Service Information Let...

Page 476: ...ION PERIODS Refer to regulations in force in the certification country for information concerning preventive maintenance to be carried out A maintenance Manual must be obtained prior to performing any preventive maintenance to make sure that proper procedures are followed Maintenance must be accomplished by licensed personnel ...

Page 477: ...2013 Rev 1 Page 8 5 1 8 5 ALTERATIONS OR REPAIRS It is essential that the Airworthiness authorities be contacted prior to any alterations or repairs on the airplane to make sure that airworthiness of the airplane is not violated Alterations or repairs must be accomplished by licensed personnel ...

Page 478: ...ficulty in releasing the parking brake or damage the brake system Make sure that the fuel selector is set to OFF NOTE Do not use solar screens or shields installed on the airplane inside or leave sun visors down against windshield when airplane on ground The reflected heat from these items causes a temperature increase which accelerates the crack growth or crazing and may cause the formation of bu...

Page 479: ...PILOT S OPERATING HANDBOOK SECTION 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 6 2 Figure 8 6 1 TURNING ANGLE LIMITS ...

Page 480: ...l P W C Airplane fueling Keep fuel tanks full to minimize condensation in the tanks Keep the battery fully charged to prevent the electrolyte from freezing in cold weather Close oxygen cylinder isolation valve Storage from 8 to 28 days Engine according to Maintenance Manual P W C Airplane fueling Keep fuel tanks full to minimize condensation in the tanks Keep the battery fully charged to prevent t...

Page 481: ...PILOT S OPERATING HANDBOOK SECTION 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 6 4 Figure 8 6 2 CONTROL LOCK DEVICE ...

Page 482: ...y 6 Quarts 5 7 Litres The engine oil should be changed and the oil filter cleaned at intervals recommended in Pratt Whitney Canada Service Bulletin No 14001 which has been updated with revisions and or Supplements Refill through the system filling inlet which is located on the engine upper rear part A gage located on the filling cap indicates oil level and is calibrated in quarts to maximum level ...

Page 483: ...ASOLINE AVGAS MUST BE RESTRICTED TO EMERGENCIES ONLY AVGAS WILL NOT BE USED FOR MORE THAN 150 CUMULATIVE HOURS DURING ANY PERIOD BETWEEN ENGINE OVERHAUL WARNING DURING ALL FUELING OPERATIONS FIRE FIGHTING EQUIPMENT MUST BE AVAILABLE ATTACH GROUNDING WIRE TO AN UNPAINTED METALLIC PART OF THE AIRPLANE DO NOT OPERATE ANY AVIONICS OR ELECTRICAL EQUIPMENT ON THE AIRPLANE DURING FUELING DO NOT ALLOW OPE...

Page 484: ...nto the fuel provides two distinct effects it absorbs the dissolved water from the fuel alcohol has a freezing temperature depressant effect EGME or DIEGME must be carefully mixed with the fuel in concentration it must be between a minimum of 0 06 and a maximum of 0 15 by volume Figure 8 7 3 provides EGME or DIEGME fuel mixing ratio information CAUTION DO NOT PERMIT THE CONCENTRATE OF EGME OR DIEG...

Page 485: ...PILOT S OPERATING HANDBOOK SECTION 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 7 4 Figure 8 7 3 ADDITIVE MIXING RATIO EGME or DIEGME ...

Page 486: ...B MIL H5606E hydraulic fluid Brakes Service as required with AIR 3520 B MIL H5606E hydraulic fluid NOTE A higher inflation pressure has to be applied to tires and shock absorbers when in very cold conditions refer to Chapter 8 9 Tire inflation pressures are given for an airplane on ground at 21 C An ambient temperature change of 3 C produces approximately 1 pressure change OXYGEN The replenishment...

Page 487: ...a pressure of 1850 PSIG 127 bars at a temperature of 70 F 21 C If the cylinder temperature differs from 70 F 21 C refer to Figure 8 7 4 which lists the required pressures according to the cylinder temperature Open the oxygen service door on the R H rear karman Measure the oxygen cylinder temperature Make sure the thermometer indication is constant Note the indication Refer to the temperature press...

Page 488: ...ESULT IN FAILURE OF THE MASKS TO DEPLOY WARNING MASKS SHALL BE REPACKED IN AN AREA FREE OF OIL GREASE FLAMMABLE SOLVENTS OR OTHER CONTAMINANTS Inspect and disinfect mask and deployment container with an aqueous solution of Zephiran Chloride Scott Aviation P N 00 2572 or with disinfection cleaners EROS P N SAN50 After disinfecting and thoroughly drying the mask lightly dust the outside of the facep...

Page 489: ...CE Edition 0 October 31 2013 Rev 1 Page 8 7 8 Gently fold reservoir bag lengthwise into thirds outside edges folded inward over center of bag Do not crease bag Fold reservoir bag away from breathing valves and into facepiece Make sure bag does not cover breathing valves ...

Page 490: ...NYARD PIN IS INSERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyard pin into corresponding check valve Place mask facepiece first in deployment container Make sure that oxygen tubing and lanyard cord are free to deploy and are not caught between the container and lid...

Page 491: ...TORY DEFECTS Follow by carefully washing with a mild detergent and plenty of water Rinse thoroughly then dry with a clean moist chamois Do not rub the plastic with a dry cloth since this builds up an electrostatic charge which attracts dust Waxing will finish the cleaning operation A thin even coat of wax polished out by hand with clean soft flannel cloth will fill in minor scratches and help prev...

Page 492: ...e of 15 C 4 Position a 0 59 in 15 mm shim at the bottom of the piston tube and against forward landing gear half fork to reduce shock absorber travel Refill with hydraulic liquid Remove the shim and inflate shock absorber to 138 psi 9 5 bars at a room temperature of 15 C 5 Inflate main landing gear tires to 130 psi 8 96 bars and nose tire to 102 psi 7 bars at a room temperature of 15 C NOTE See Ta...

Page 493: ...ACCOMMODATION Figures 8 10 1 8 10 2 8 10 3 and 8 10 4 A Tools and consumable materials Seat protective covers B Preparation 1 Make sure the SOURCE selector is set to OFF and the crash lever is down C Removal of rear seats Figure 8 10 1 1 To remove rear seats perform the following operations CAUTION IN ORDER TO PREVENT CUSHION COVERING DAMAGE PROTECTIVE COVERS SHOULD BE PUT ON SEATS a Install prote...

Page 494: ... Remove deflector 34 maintained with Velcro type strap 3 If necessary remove the cabin central carpet NOTE If one of two cargo nets must be installed it is necessary to use the carpet with appropriate cuttings E Removal of a cabinet NOTE This operation must be carried out by a service center F Cabin comfort Figure 8 10 3 1 Blank off the hot air outlet located forward the large door with blanking d...

Page 495: ...1 to lock the seat WARNING VERIFY THAT LOCK 22 AND ALL PADS 23 ARE ENGAGED AND LOCKED INTO RAILS TRYING TO MOVE SEAT FORWARD AND BACKWARD f Install backrest bottom upholstery 25 NOTE Adjust it properly make sure not to obstruct deflector 34 outlet g Slide properly the carpet under the seat h Remove protective covers H Final operations 1 If removed install cabin central carpet suited to the intende...

Page 496: ... E Installation of intermediate seats 1 Install intermediate seats refer to Paragraph 1 G 2 If removed install the baggage compartment partition net 3 If removed install cabin central carpet F Installation of rear seats Figure 8 10 1 1 Make sure the work area is clean and free from debris 2 Clear the carpet from seat area to facilitate moving in rails 3 Check that knobs 8 maintain locks 3 in up po...

Page 497: ...ECTION 7 NOTE Many combinations of accommodations are authorized with seats rear and intermediate by pilot or service centers and cabinet s by service centers only However the pilot must ensure that he gets all necessary authorizations from his regulatory authority NOTE To remove or install these elements use Paragraph 1 or 2 refer to Table 1 NOTE After these operations determine weight and balanc...

Page 498: ... 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 10 6 1 Seat tilting handle 2 Ring 3 Lock 4 Pad 5 Rail 6 Backrest tilting handle 7 Quick link 8 Knob 9 Strap Figure 8 10 1 1 2 Removal Installation of rear seat ...

Page 499: ...PILOT S OPERATING HANDBOOK SECTION 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 10 7 Figure 8 10 1 2 2 Removal Installation of rear seat ...

Page 500: ...NDBOOK SECTION 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 10 8 Figure 8 10 2 Removal Installation of intermediate seat 21 Locking handle 22 Lock 23 Pad 24 Rail 25 Backrest bottom upholstery ...

Page 501: ...CTION 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 10 9 Figure 8 10 3 Cabin comfort Installation of blanking plugs and deflector 31 Blanking plug 32 Blanking plug 33 Blanking device assy 34 Deflector ...

Page 502: ...TING HANDBOOK SECTION 8 HANDLING SERVICING AND MAINTENANCE Edition 0 October 31 2013 Rev 1 Page 8 10 10 Figure 8 10 4 Cabin comfort Installation of deflector 34 Deflector 35 Deflector hole 36 Red mark 37 Color mark ...

Page 503: ...ndling servicing and maintenance information The supplements are arranged numerically See List of Supplements and Validities to make it easier to locate a particular supplement Some installed items of optional equipment whose function and operational procedures do not require detailed instructions are discussed in Section 7 Limitations contained in the following supplements are Airworthiness Autho...

Page 504: ...1 Page 9 A B LIST OF EFFECTIVE PAGES AND VALIDITIES ORIGINAL ISSUE OF OCTOBER 31 2013 From S N 1000 P N Z00 DMHFM0AEE3R1EN Page No Edit Rev No Rev Date Page No Edit Rev No Rev Date 9 A A 3 1 FEB 14 9 A B 3 1 FEB 14 9 A C 3 1 FEB 14 9 A D 3 1 FEB 14 9 A 1 3 1 FEB 14 9 A 2 3 1 FEB 14 ...

Page 505: ...IST OF AMENDMENTS Revision 1 dated February 2014 Pages Description All pages Page heading change to introduce the TBM700 trade name associated to the airplane serial numbers concerning the content of this POH TBM850 becomes TBM900 9 A 1 Modification of Engine fire detection system option number ...

Page 506: ...1000 31 10 13 47 AIRBORNE GWX 68 or GWX 70 color weather radar MOD70 0176 00 Version C GWX 68 MOD70 0394 34 GWX 70 From S N 1000 31 10 13 49 GARMIN G1000 TAWS SYSTEM MOD70 0176 00 Version F From S N 1000 31 10 13 50 GARMIN G1000 SYNTHETIC VISION SYSTEM MOD70 0226 00 From S N 1000 31 10 13 56 GARMIN GSR 56 weather datalink and satellite phone MOD70 0331 23 From S N 1000 31 10 13 57 Public transport...

Page 507: ...31 2013 Rev 0 Page 9 6 1 SUPPLEMENT BFG WX 500 STORMSCOPE TABLE OF CONTENTS Page 1 GENERAL 9 6 2 2 LIMITATIONS 9 6 2 3 EMERGENCY PROCEDURES 9 6 2 4 NORMAL PROCEDURES 9 6 2 5 PERFORMANCE 9 6 2 6 WEIGHT AND BALANCE 9 6 3 7 DESCRIPTION 9 6 3 8 HANDLING SERVICING AND MAINTENANCE 9 6 3 ...

Page 508: ... strength and is not to be used for accurate determination of thunderstorm location CAUTION THE STORMSCOPE MUST NOT BE USED FOR THUNDERSTORM PENETRATION The WX 500 Pilot s guide Series II No 009 11501 001 and the GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the Socata TBM 850 No 190 00708 05 at their latest revision shall be readily available to the pilot whenever the operation ...

Page 509: ...t s Operating Handbook when the airplane is equipped with the option BFG WX 500 STORMSCOPE The BFG Series II stormscope weather mapping system provides a visual screen readout of the electrical discharges associated with thunderstorms This information with proper interpretation will allow the pilot to detect severe thunderstorm activity A series of green dots or of strike points will be displayed ...

Page 510: ...013 Rev 0 Page 9 18 1 SUPPLEMENT ENGINE FIRE DETECTION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 18 2 2 LIMITATIONS 9 18 2 3 EMERGENCY PROCEDURES 9 18 3 4 NORMAL PROCEDURES 9 18 5 5 PERFORMANCE 9 18 5 6 WEIGHT AND BALANCE 9 18 6 7 DESCRIPTION 9 18 7 8 HANDLING SERVICING AND MAINTENANCE 9 18 7 ...

Page 511: ...RE DETECTION SYSTEM The general hereafter supplement or replace those of the standard airplane described in Section 1 General of the basic Pilot s Operating Handbook when the airplane is equipped with the option ENGINE FIRE DETECTION SYSTEM The fire detection system allows engine fire monitoring and indicating SECTION 2 LIMITATIONS Installation and operation of ENGINE FIRE DETECTION SYSTEM do not ...

Page 512: ...escribed in Section 3 Emergency procedures of the basic Pilot s Operating Handbook when the airplane is equipped with the option ENGINE FIRE DETECTION SYSTEM ENGINE FIRE ON GROUND Symptoms ITT increasing ITT CAS message FIRE CAS message smoke 1 Throttle CUT OFF 2 BLEED switch OFF RST 3 A C switch OFF 4 Brakes AS REQUIRED 5 Tank selector OFF 6 Warn ground assistance if necessary 7 Crash lever PULL ...

Page 513: ... system FLY THE AIRPLANE If the fire warning is not confirmed 1 Monitor the engine parameters ITT in particular 2 Look for smoke coming from engine cowls or from air conditioning system 3 Land as soon as possible If the fire warning is confirmed 1 Throttle CUT OFF 2 AUX BP fuel switch OFF 3 Tank selector OFF 4 BLEED switch OFF RST 5 A C switch OFF 6 If necessary Set oxygen mask 7 If necessary EMER...

Page 514: ...s of the basic Pilot s Operating Handbook when the airplane is equipped with the option ENGINE FIRE DETECTION SYSTEM Before starting the engine FIRE TEST push button DEPRESS The FIRE CAS message lights on and causes the illumination of the MASTER WARNING light SECTION 5 PERFORMANCE Installation and operation of ENGINE FIRE DETECTION SYSTEM do not change the basic performance of the airplane descri...

Page 515: ...ace those of the standard airplane described in Section 6 Weight and balance of the basic Pilot s Operating Handbook when the airplane is equipped with the option ENGINE FIRE DETECTION SYSTEM S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 26 FIRE PROTECTION A 26002F Engine fire detection system L HOTELLIER 1 455 0 66 96 06 2 440 ...

Page 516: ...ned in the most sensitive engine areas They consist of thermal switches detecting a temperature greater than 200 C PUSH BUTTON The push button enables the pilot to test the detection system by opening the grounding circuit It is connected in series with the 7 detectors The push button is located on the L H side instrument panel near the FIRE TEST indication DISPLAY Refer to the GARMIN G1000 Integr...

Page 517: ...013 Rev 0 Page 9 47 1 SUPPLEMENT GARMIN GWX 68 OR GWX 70 COLOR WEATHER RADAR TABLE OF CONTENTS Page 1 GENERAL 9 47 2 2 LIMITATIONS 9 47 2 3 EMERGENCY PROCEDURES 9 47 2 4 NORMAL PROCEDURES 9 47 3 5 PERFORMANCE 9 47 3 6 WEIGHT AND BALANCE 9 47 4 7 DESCRIPTION 9 47 4 8 HANDLING SERVICING AND MAINTENANCE 9 47 6 ...

Page 518: ...rictions Do not operate the radar during refueling operations or in the vicinity of trucks or containers containing flammables or explosives Do not allow personel within 12 feet of area being scanned by antenna when system is transmitting The GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the Socata TBM 850 No 190 00708 05 at its latest revision shall be readily available to the p...

Page 519: ...RY MODE THE WEATHER RADAR SYSTEM AUTOMATICALLY SWITCHES TO STANDBY MODE THE SYSTEM REMAINS IN STANDBY MODE UNTIL BOTH DISPLAYS ARE RESTORED IN REVERSIONARY MODE THE WEATHER RADAR SYSTEM CANNOT BE CONTROLLED AFTER STARTING ENGINE Radar Mode Softkey STANDBY A one minute warm up period is initiated The count down is displayed on the screen AFTER TAKE OFF Radar Mode Softkey As required BEFORE LANDING ...

Page 520: ... GARMIN 9 36 4 246 173 46 4 406 A 0394 34 Weather radar GWX 70 GARMIN 9 85 4 468 172 55 4 383 SECTION 7 DESCRIPTION Information hereafter supplement or replace those of the standard airplane described in Section 7 Description of the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option GARMIN GWX 68 OR GWX 70 COLOR WEATHER RADAR The weather information are displayed on...

Page 521: ...PILOT S OPERATING HANDBOOK SUPPLEMENT 47 GARMIN GWX 68 OR GWX 70 COLOR WEATHER RADAR Edition 1 October 31 2013 Rev 0 Page 9 47 5 Figure 9 47 1 2 2 GWX 68 or GWX 70 weather radar display and controls ...

Page 522: ...0 Page 9 47 6 SECTION 8 HANDLING SERVICING AND MAINTENANCE Installation and operation of GARMIN GWX 68 OR GWX 70 COLOR WEATHER RADAR do not change the basic handling servicing and maintenance procedures of the airplane described in Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook ...

Page 523: ...013 Rev 0 Page 9 49 1 SUPPLEMENT GARMIN G1000 TAWS SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 49 2 2 LIMITATIONS 9 49 2 3 EMERGENCY PROCEDURES 9 49 2 4 NORMAL PROCEDURES 9 49 3 5 PERFORMANCE 9 49 4 6 WEIGHT AND BALANCE 9 49 4 7 DESCRIPTION 9 49 5 8 HANDLING SERVICING AND MAINTENANCE 9 49 10 ...

Page 524: ...It must not be used for airplane vertical and horizontal navigation AC 2318 recommendation in order to avoid unwillingly warnings TAWS function must be inhibited for any landing on a terrain which is not mentioned in the data base The use of the terrain awareness warning and terrain display functions is prohibited during QFE atmospheric pressure at airport elevation operations The following docume...

Page 525: ...dapted to airplane configuration and speed until the warning disappears Terrain Terrain Pull up Pull up Obstacle Obstacle Pull up Pull up AURAL WARNINGS The red PULL UP PFD MFD alert annunciation and TERRAIN OBSTACLE PULL UP pop up alerts light on Adjust airplane path in order to make the warning disappear 4 2 CAUTIONS OF THE TAWS FUNCTION Caution terrain Caution obstacle Too low terrain AURAL WAR...

Page 526: ... the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE The weight and balance hereafter supplement or replace those of the standard airplane described in Section 6 Weight and balance of the basic Pilot s Operating Handbook when the airplane is equipped with the option GARMIN G1000 TAWS SYSTEM S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per u...

Page 527: ... an RTC or ROC alert is issued a potential impact point is displayed on the TAWS Page Imminent Terrain Impact and Imminent Obstacle Impact Imminent Terrain Impact ITI and Imminent Obstacle Impact IOI alerts are issued when the airplane is below the elevation of a terrain or obstacle cell in the airplane s projected path ITI and IOI alerts are accompanied by a potential impact point displayed on th...

Page 528: ...p Terrain Ahead Pull up Reduced Required Obstacle Clearance Warning ROC Red PULL UP OBSTACLE PULL UP Obstacle Obstacle Pull up Pull up Imminent Obstacle Impact Warning IOI Red PULL UP OBSTACLE AHEAD PULL UP Obstacle Ahead Pull up Obstacle Ahead Pull up Reduced Required Terrain Clearance Caution RTC Amber TERRAIN CAUTION TERRAIN Caution Terrain Caution Terrain Imminent Terrain Impact Caution ITI Am...

Page 529: ... is within 15 Nm of the destination airport PDA alerting ends when the airplane is either 0 5 Nm from the runway threshold or at an altitude of 125 feet AGL while within 1 0 Nm of the threshold Figure 9 49 1 PDA alerting threshold PDA Alerting Area The aural displayed messages associated with the PDA function are described in the table 9 49 3 Alert Type PFD MFD TAWS Page Annunciation MFD Map Page ...

Page 530: ... terrain at an excessive speed Figure 9 49 2 shows the parameters for the alert as defined by TSO C151b Figure 9 49 2 Excessive Descent Rate Alert Criteria The aural displayed messages associated with the EDR function are described in the table 9 49 4 Alert Type PFD MFD TAWS Page Annunciation MFD Map Page Pop Up Alert Aural Message Excessive Descent Rate Warning EDR Red PULL UP PULL UP Pull up Exc...

Page 531: ...on and a pop up terrain alert on the display NCR alerting is only active when departing from an airport and when the following conditions are met The height above the terrain is less than 700 feet The distance from the departure airport is 2 Nm or less The heading change from the heading at the time of departure is less than 110 degrees Figure 9 49 3 shows two figures which illustrate the NCR aler...

Page 532: ...ion solution along with specific vertical accuracy minimums Should the navigation solution become degraded or if the airplane is out of the database coverage area the annunciation TAWS N A is generated in the annunciation window and on the TAWS Page The aural message TAWS Not Available is generated When the GPS signal is re established and the airplane is within the database coverage area the aura...

Page 533: ...013 Rev 0 Page 9 50 1 SUPPLEMENT GARMIN G1000 SYNTHETIC VISION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 50 2 2 LIMITATIONS 9 50 2 3 EMERGENCY PROCEDURES 9 50 3 4 NORMAL PROCEDURES 9 50 3 5 PERFORMANCE 9 50 4 6 WEIGHT AND BALANCE 9 50 4 7 DESCRIPTION 9 50 5 8 HANDLING SERVICING AND MAINTENANCE 9 50 7 ...

Page 534: ... the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option GARMIN G1000 SYNTHETIC VISION SYSTEM The following document or any further edition applicable to the latter shall be readily available to the pilot whenever operation of the SVS is predicted GARMIN G1000 Integrated Flight Deck Pilot s Guide for the Socata TBM 850 No 190 00709 05 The use of the Synthetic Vision ...

Page 535: ...on and aircraft control SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement or replace those of the standard airplane described in Section 4 Normal Procedures of the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option GARMIN G1000 SYNTHETIC VISION SYSTEM CAUTION SVS INFORMATION IS NOT A SUBSITUTE FOR STANDARD COURSE AND ALTITUDE DEVIATION INFORMATI...

Page 536: ...th each press of the APTSIGNS key NOTE For PATHWAY HRZN HDG and APTSIGNS SYN TERR must be activated first When display backup mode is selected the display of the SVS is active within 1 minute after SVS selection SECTION 5 PERFORMANCE Installation and operation of GARMIN G1000 SYNTHETIC VISION SYSTEM do not change the basic performance of the airplane described in Section 5 Performance of the basic...

Page 537: ... SVS display Horizon Heading a pilot selectable display of heading marks displayed just above the horizon line on the PFD Airport Signs pilot selectable signposts displayed on the synthetic terrain display indicating the position of nearby airports that are in the G1000 database Runway Highlight a highlighted presentation of the location and orientation of the runway s at the departure and destina...

Page 538: ...be displayed by the Pathway as published in the approach procedure If Vectors To Final is selected as the approach transition the Pathway will display the final approach course inbound to the Missed Approach Point MAP The Pathway will be shown level at the altitude set in the G1000 altitude selector or the Final Approach Fix FAF crossing altitude whichever is higher up to the point along the final...

Page 539: ...ial missed approach leg is heading to altitude or a leg defined by other than a GPS course the Pathway will not be displayed for that segment If the course to the Missed Approach Holding Point is out of the SVS field of view during the initial missed approach climb the Pathway will not be visible on the PFD until the aircraft is turned toward the course The Pathway will be displayed at the publish...

Page 540: ...013 Rev 0 Page 9 56 1 SUPPLEMENT GARMIN GSR 56 WEATHER DATALINK AND SATELLITE PHONE TABLE OF CONTENTS Page 1 GENERAL 9 56 2 2 LIMITATIONS 9 56 2 3 EMERGENCY PROCEDURES 9 56 3 4 NORMAL PROCEDURES 9 56 3 5 PERFORMANCE 9 56 4 6 WEIGHT AND BALANCE 9 56 4 7 DESCRIPTION 9 56 4 8 HANDLING SERVICING AND MAINTENANCE 9 56 5 ...

Page 541: ...sengers to have the GSR 56 telephone audio functions USE OF PHONE BY PIC PROHIBITED DURING ALL AIRCRAFT OPERATIONS WEATHER DATALINK functions The GSR 56 weather datalink is only an advisory weather source it does not relieve the pilot to comply with the applicable operational regulation in terms of flight preparation especially with regard to the use of an approved weather and NOTAM sources during...

Page 542: ... basic Pilot s Operating Handbook when the TBM airplane is equipped with the option GARMIN GSR 56 WEATHER DATALINK AND SATELLITE PHONE Normal operating procedures of the GARMIN GSR 56 WEATHER DATALINK AND SATELLITE PHONE system are outlined in the Pilot s Guide the references of which are given in Section 2 Limitations of this Supplement BEFORE STARTING ENGINE On L H GMA 1347 audio panel 1 TEL but...

Page 543: ...Pilot s Operating Handbook when the airplane is equipped with the option GARMIN GSR 56 WEATHER DATALINK AND SATELLITE PHONE GARMIN GSR 56 weather datalink and satellite phone system provides airborne low speed datalink and voice communication capability to GARMIN G1000 system excluding any voice mail function GSR 56 weather datalink and satellite phone system contains a transceiver that operates o...

Page 544: ...0 Page 9 56 5 SECTION 8 HANDLING SERVICING AND MAINTENANCE Installation and operation of GARMIN GSR 56 WEATHER DATALINK AND SATELLITE PHONE do not change the basic handling servicing and maintenance procedures of the airplane described in Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook ...

Page 545: ...013 Rev 0 Page 9 57 1 SUPPLEMENT PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES TABLE OF CONTENTS Page 1 GENERAL 9 57 2 2 LIMITATIONS 9 57 2 3 EMERGENCY PROCEDURES 9 57 5 4 NORMAL PROCEDURES 9 57 5 5 PERFORMANCE 9 57 5 6 WEIGHT AND BALANCE 9 57 6 7 DESCRIPTION 9 57 6 8 HANDLING SERVICING AND MAINTENANCE 9 57 6 ...

Page 546: ...f the TBM airplane when used for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES SECTION 2 LIMITATIONS The limitations hereafter supplement or replace those of the standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the TBM airplane is used for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES 2 9 PLACARDS 1 On access door Internal side 2 On ...

Page 547: ...ANES Edition 1 October 31 2013 Rev 0 Page 9 57 3 3 On pilot door External side if installed 4 On outer fuselage skin aft of access door and in the cabin forward of access door 5 On emergency exit handle Internal side Marking on handle Marking on cover 6 On emergency exit handle External side ...

Page 548: ...RPLANES Edition 1 October 31 2013 Rev 0 Page 9 57 4 7 On R H access door jamb 8 On last step of stairs 9 On rear passengers masks containers 10 On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling 11 Under window at L H intermediate seat ...

Page 549: ...es of the airplane described in Section 3 Emergency procedures of the basic Pilot s Operating Handbook SECTION 4 NORMAL PROCEDURES Use of TBM 850 airplane for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES does not change the basic normal procedures of the airplane described in Section 4 Normal procedures of the basic Pilot s Operating Handbook SECTION 5 PERFORMANCE Use of TBM 850 airplane ...

Page 550: ...lot s Operating Handbook SECTION 7 DESCRIPTION Use of TBM 850 airplane for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES does not change the description of the airplane described in Section 7 Description of the basic Pilot s Operating Handbook SECTION 8 HANDLING SERVICING AND MAINTENANCE Use of TBM 850 airplane for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES does not change the b...

Page 551: ...13 Rev 1 Page 9 58 1 SUPPLEMENT FIVE BLADED PROPELLER TABLE OF CONTENTS Page 1 GENERAL 9 58 2 2 LIMITATIONS 9 58 3 3 EMERGENCY PROCEDURES 9 58 3 4 NORMAL PROCEDURES 9 58 4 5 PERFORMANCE 9 58 6 6 WEIGHT AND BALANCE 9 58 51 7 DESCRIPTION 9 58 54 8 HANDLING SERVICING AND MAINTENANCE 9 58 54 ...

Page 552: ...tandard airplane described in Section 1 General of the basic Pilot s Operating Handbook when the airplane is equipped with the option FIVE BLADED PROPELLER 1 3 DESCRIPTIVE DATA PROPELLER Number of propellers 1 Propeller manufacturer HARTZELL Propeller model number HC E5N 3C NC8834K Number of blades 5 Propeller diameter Minimum 90 inches 2 286 m Maximum 91 inches 2 311 m Propeller type Adjustable c...

Page 553: ...BLADED PROPELLER 2 3 POWER LIMITATIONS PROPELLER Number of propellers 1 Propeller manufacturer HARTZELL Propeller model number HC E5N 3C NC8834K Propeller diameter Minimum 90 inches 2 286 m Maximum 91 inches 2 311 m Propeller blade setting at 30 inches station Low pitch 19 5 Feathering 85 Maximum reverse 9 SECTION 3 EMERGENGY PROCEDURES Installation and operation of FIVE BLADED PROPELLER do not ch...

Page 554: ...ICH MAY LEAD TO A DROP DOWN OF THE AIRCRAFT REDUCE POWER SMOOTHLY TOUCH AND GO WARNING QUICKLY REDUCING THE POWER TO IDLE DURING THE FLARE MAY INDUCE A MORE PRONONCED DECELERATION THAN WITH THE 4 BLADES PROPELLER WHICH MAY LEAD TO A DROP DOWN OF THE AIRCRAFT REDUCE POWER SMOOTHLY 4 4 AMPLIFIED PROCEDURES PREFLIGHT INSPECTION CAUTION WHEN ENGINE IS SHUTDOWN DO NOT SET THE PROP DE ICE SWITCH TO ON D...

Page 555: ...OOK SUPPLEMENT 58 FIVE BLADED PROPELLER Edition 0 October 31 2013 Rev 1 Page 9 58 5 4 5 PARTICULAR PROCEDURES CAUTION WHEN ENGINE IS SHUTDOWN DO NOT SET THE PROP DE ICE SWITCH TO ON DAMAGE TO THE PROPELLER BLADES COULD RESULT ...

Page 556: ...tion FIVE BLADED PROPELLER 5 2 NOISE LEVEL Maximum noise level permissible Demonstrated noise level FAR PART 36 Appendix G Amdt 28 88 dB A 76 4 dB A ICAO Annex 16 Vol 1 6th edition Amdt 8 Chapter 10 Appendix 6 85 dB A 76 4 dB A Approved noise levels for TBM airplane are stated in EASA A 010 Type Certificate Data Sheet NOTE No determination has been made by the Federal Aviation Administration that ...

Page 557: ...age upon system start The following conditions are given BLEED AUTO The torque must be set at or below the value corresponding to the local conditions of flight level and temperature NOTE Inertial separator must be OFF and BLEED HI MSG OFF Example for FL 260 and OAT 22 C the following tables give the maximum torque to be set Maximum climb power TRQ 82 for IAS 124 KIAS Add 0 5 of TRQ for each addit...

Page 558: ... T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 Recommended NG 103 20 18 16 14 12 100 10 99 8 97 6 100 95 4 98 94 2 100 97 92 0 99 94 90 2 100 97 92 87 4 99 94 89 84 6 100 96 91 86 81 8 99 93 88 84 79 10 100 96 91 86 81 77 12 98 93 88 83 79 74 14 100 96 90 85 81 76 71 16 100 97 93 87 83 78 73 18 99 94 90 85 80 75 20 100 96 91 87 82 77 22 98 93 88 84 79 24 100 95 90 85 81...

Page 559: ... 42 99 95 90 86 82 78 74 40 98 94 89 85 81 77 73 38 97 92 88 84 80 76 72 36 100 96 91 87 83 79 75 71 34 98 94 90 86 81 77 74 70 32 97 93 89 84 80 76 72 69 30 100 96 92 87 83 79 75 71 68 28 99 95 91 86 82 78 74 70 67 26 97 93 89 85 81 77 73 69 65 24 100 96 92 88 84 79 75 72 68 64 22 99 95 91 87 82 78 74 70 66 63 20 98 94 89 85 81 77 73 69 65 61 18 100 96 92 88 84 80 76 71 67 63 59 16 99 95 91 87 82...

Page 560: ...d or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 Recommended NG 103 20 18 16 14 12 10 8 100 6 99 4 97 2 100 94 0 100 97 91 2 99 94 89 4 100 96 91 86 6 98 93 89 84 8 100 96 91 86 81 10 98 93 88 83 78 12 100 95 90 85 80 76 14 100 97 92 87 82 78 73 16 99 94 89 84 80 75 18 100 96 91 86 81 77 20 98 93 88 84 79 22 100 95 90 85 81 24 100 97 92 87 83 26 98 94 ...

Page 561: ... 90 85 81 77 42 98 93 89 84 80 76 40 97 92 87 83 79 75 38 100 96 91 86 82 78 74 36 99 94 90 85 81 77 72 34 98 93 88 84 80 75 71 32 96 92 87 83 78 74 70 30 100 95 90 86 81 77 73 69 28 98 94 89 85 80 76 72 68 26 97 93 88 83 79 75 71 67 24 100 96 91 87 82 78 74 70 65 22 99 95 90 85 81 76 72 68 64 20 98 93 89 84 79 75 71 66 62 18 100 96 92 87 82 78 73 69 64 60 16 99 95 90 85 81 76 71 67 63 59 14 97 93...

Page 562: ...This table is not valid if INERTIAL SEPARATOR ON and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 Recommended NG 103 18 16 14 12 10 8 6 4 2 0 2 100 4 97 6 100 94 8 97 91 10 100 94 88 12 100 96 91 86 14 98 93 88 83 16 100 96 90 85 18 98 93 87 20 100 95 90 22 97 92 24 100 94 26 100 96 28 98 30 100 32 100 34 100 CAUTION THE TRQ SETTING MUST NEVER EXC...

Page 563: ...4 98 93 88 42 96 91 86 40 100 95 90 85 38 98 93 88 84 36 97 92 87 82 34 100 95 90 85 81 32 99 94 89 84 79 30 97 92 87 83 78 28 96 91 86 81 77 26 100 94 89 84 80 75 24 98 93 88 83 78 73 22 96 91 86 81 76 71 20 100 95 89 84 79 74 69 18 98 93 87 82 77 72 67 16 100 96 91 85 80 75 70 66 14 99 94 88 83 78 73 68 63 12 97 92 86 81 76 71 66 61 10 100 95 89 84 79 73 68 63 59 8 98 92 87 81 76 71 66 61 57 6 1...

Page 564: ...G ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 Recommended NG 103 18 16 14 12 10 8 6 4 100 2 98 0 100 95 2 98 93 4 100 95 90 6 98 92 87 8 100 94 89 84 10 100 97 91 86 81 12 99 94 88 83 78 14 100 96 91 85 80 76 16 98 93 88 83 78 18 100 95 90 85 80 20 100 97 92 87 82 22 99 94 89 84 24 100 96 91 86 26 100 98 92 88 28 99 94 89 30 100 96 91 32 98 93 34 95 CAUTION THE ...

Page 565: ... 85 81 38 98 93 89 84 79 36 97 92 87 82 78 34 100 95 91 86 81 77 32 99 94 89 84 80 75 30 98 93 88 83 78 74 28 96 91 86 81 77 72 26 100 95 90 85 80 75 71 24 98 93 88 83 78 73 69 22 100 96 91 86 81 76 71 67 20 99 94 89 84 79 74 69 65 18 97 92 87 82 77 72 67 63 16 100 95 90 85 80 75 70 65 60 14 98 93 88 83 78 72 67 62 58 12 100 96 91 86 80 75 70 65 60 56 10 99 94 88 83 77 72 67 63 58 54 8 100 96 91 8...

Page 566: ... and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 TRQ 100 20 18 16 14 12 100 10 99 8 97 6 100 95 4 98 94 2 100 97 92 0 99 94 90 2 100 97 92 87 4 99 94 89 84 6 100 96 91 86 81 8 99 93 88 84 79 10 100 96 91 86 81 77 12 98 93 88 83 79 74 14 100 96 90 85 81 76 71 16 100 97 93 87 83 78 73 18 99 94 90 85 80 75 20 100 96 91 87 82 77 22 98 93 88 84 79 24 100...

Page 567: ... 87 83 79 76 42 99 95 90 86 82 78 74 40 98 94 89 85 81 77 73 38 97 92 88 84 80 76 72 36 100 96 91 87 83 79 75 71 34 98 94 90 86 81 77 74 70 32 97 93 89 84 80 76 72 69 30 100 96 92 87 83 79 75 71 68 28 99 95 91 86 82 78 74 70 67 26 97 93 89 85 81 77 73 69 65 24 100 96 92 88 84 79 75 72 68 64 22 99 95 91 87 82 78 74 70 66 63 20 98 94 89 85 81 77 73 69 65 61 18 100 96 92 88 84 80 76 71 67 63 59 16 99...

Page 568: ...INERTIAL SEPARATOR ON and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 TRQ 100 20 18 16 14 12 10 8 100 6 99 4 97 2 100 94 0 100 97 91 2 99 94 89 4 100 96 91 86 6 98 93 89 84 8 100 96 91 86 81 10 98 93 88 83 78 12 100 95 90 85 80 76 14 100 97 92 87 82 78 73 16 99 94 89 84 80 75 18 100 96 91 86 81 77 20 98 93 88 84 79 22 100 95 90 85 81 24 100 97 92 87...

Page 569: ...2 78 44 99 95 90 85 81 77 42 98 93 89 84 80 76 40 97 92 87 83 79 75 38 100 96 91 86 82 78 74 36 99 94 90 85 81 77 72 34 98 93 88 84 80 75 71 32 96 92 87 83 78 74 70 30 100 95 90 86 81 77 73 69 28 98 94 89 85 80 76 72 68 26 97 93 88 83 79 75 71 67 24 100 96 91 87 82 78 74 70 65 22 99 95 90 85 81 76 72 68 64 20 98 93 89 84 79 75 71 66 62 18 100 96 92 87 82 78 73 69 64 60 16 99 95 90 85 81 76 71 67 6...

Page 570: ...This table is not valid if INERTIAL SEPARATOR ON and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 TRQ 100 18 16 14 12 10 8 6 4 2 0 2 100 4 97 6 100 94 8 97 91 10 100 94 88 12 100 96 91 86 14 98 93 88 83 16 100 96 90 85 18 98 93 87 20 100 95 90 22 97 92 24 100 94 26 100 96 28 98 30 100 32 100 34 100 CAUTION THE TRQ SETTING MUST NEVER EXCEED 100 WHE...

Page 571: ... 42 96 91 86 40 100 95 90 85 38 98 93 88 84 36 97 92 87 82 34 100 95 90 85 81 32 99 94 89 84 79 30 97 92 87 83 78 28 96 91 86 81 77 26 100 94 89 84 80 75 24 98 93 88 83 78 73 22 96 91 86 81 76 71 20 100 95 89 84 79 74 69 18 98 93 87 82 77 72 67 16 100 96 91 85 80 75 70 66 14 99 94 88 83 78 73 68 63 12 97 92 86 81 76 71 66 61 10 100 95 89 84 79 73 68 63 59 8 98 92 87 81 76 71 66 61 57 6 100 95 89 8...

Page 572: ... ON and or BLEED HI MSG ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 TRQ 100 18 16 14 12 10 8 6 4 100 2 98 0 100 95 2 98 93 4 100 95 90 6 98 92 87 8 100 94 89 84 10 100 97 91 86 81 12 99 94 88 83 78 14 100 96 91 85 80 76 16 98 93 88 83 78 18 100 95 90 85 80 20 100 97 92 87 82 22 99 94 89 84 24 100 96 91 86 26 100 98 92 88 28 99 94 89 30 100 96 91 32 98 93 34 95 C...

Page 573: ... 100 95 90 85 81 38 98 93 89 84 79 36 97 92 87 82 78 34 100 95 91 86 81 77 32 99 94 89 84 80 75 30 98 93 88 83 78 74 28 96 91 86 81 77 72 26 100 95 90 85 80 75 71 24 98 93 88 83 78 73 69 22 100 96 91 86 81 76 71 67 20 99 94 89 84 79 74 69 65 18 97 92 87 82 77 72 67 63 16 100 95 90 85 80 75 70 65 60 14 98 93 88 83 78 72 67 62 58 12 100 96 91 86 80 75 70 65 60 56 10 99 94 88 83 77 72 67 63 58 54 8 1...

Page 574: ...5 1595 1090 1690 8000 965 1500 1060 1645 1140 1765 1220 1880 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 865 1365 920 1435 965 1505 1000 1555 2000 955 1490 1005 1565 1060 1645 1100 1705 4000 1050 1625 1110 1720 1180 1825 1230 1895 6000 1165 1800 1240 1910 1320 2020 1380 2100 8000 1305 2000 1390 2120 1480 2245 1565 2330 Figure 5 9 1 TAKEOFF DISTANCES 5512 ...

Page 575: ... 1645 2305 8000 1435 2020 1600 2240 1715 2400 1850 2570 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 1310 1855 1375 1940 1440 2030 1490 2090 2000 1425 2010 1500 2110 1595 2235 1660 2320 4000 1580 2205 1675 2345 1790 2485 1865 2590 6000 1755 2455 1880 2615 2005 2780 2095 2895 8000 1980 2745 2115 2925 2275 3110 2380 3245 Figure 5 9 2 TAKEOFF DISTANCES 6579 l...

Page 576: ...30 2290 3135 8000 1960 2695 2220 3045 2410 3265 2590 3490 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 1800 2485 1880 2595 1965 2705 2060 2810 2000 1945 2675 2080 2865 2215 3040 2325 3160 4000 2185 3000 2355 3200 2500 3385 2610 3520 6000 2470 3340 2640 3550 2810 3765 2935 3915 8000 2775 3720 2965 3950 3180 4185 3315 4350 Figure 5 9 3 TAKEOFF DISTANCES 7394...

Page 577: ...5 2830 2810 2000 2860 2845 2830 2810 2795 2775 4000 2840 2820 2805 2785 2765 2750 6000 2810 2790 2770 2750 2735 2710 8000 2775 2755 2735 2710 2690 2665 6594 lbs 2991 kg SL 2440 2425 2410 2400 2380 2365 2000 2415 2400 2385 2365 2350 2330 4000 2395 2375 2360 2340 2325 2305 6000 2365 2345 2330 2310 2290 2270 8000 2335 2315 2290 2270 2250 2230 7394 lbs 3354 kg SL 2080 2065 2050 2040 2020 2005 2000 205...

Page 578: ...2 235 4000 2 345 2 315 2 280 2 250 2 220 2 190 6000 2 305 2 270 2 235 2 205 2 170 2 140 8000 2 260 2 225 2 190 2 155 2 120 2 085 6594 lbs 2991 kg SL 2 075 2 050 2 025 2 000 1 975 1 955 2000 2 045 2 015 1 990 1 965 1 935 1 910 4000 2 010 1 985 1 950 1 920 1 895 1 865 6000 1 975 1 940 1 910 1 880 1 850 1 820 8000 1 930 1 900 1 870 1 835 1 805 1 770 7394 lbs 3354 kg SL 1 800 1 775 1 755 1 730 1 710 1...

Page 579: ... 30 13 10 3 5 5 03 00 16 12 4 1 6 8000 03 00 15 12 3 9 6 03 30 18 14 4 6 7 04 00 21 16 5 5 8 10000 03 30 18 14 4 9 8 04 15 22 17 5 7 9 05 00 26 20 6 8 11 12000 04 15 22 17 5 8 9 05 15 26 20 6 8 11 06 00 30 24 8 0 13 14000 05 00 25 20 6 7 11 06 00 30 23 7 9 13 07 15 35 28 9 3 16 16000 05 45 29 23 7 6 13 07 00 34 27 9 0 15 08 15 40 32 10 6 18 18000 06 30 32 25 8 5 15 07 45 38 30 10 0 18 09 15 45 35 ...

Page 580: ...00 02 15 12 9 3 1 5 02 30 14 11 3 6 5 03 00 16 13 4 3 6 8000 03 00 15 12 4 1 6 03 30 18 14 4 8 7 04 00 21 17 5 7 9 10000 03 45 19 15 5 0 8 04 15 22 18 5 9 10 05 15 27 21 7 0 11 12000 04 30 23 18 6 0 10 05 15 27 21 7 1 12 06 15 32 25 8 4 14 14000 05 15 26 21 6 9 12 06 15 31 24 8 2 14 07 15 37 29 9 7 17 16000 06 00 30 23 7 9 14 07 00 35 28 9 3 16 08 15 42 33 11 0 19 18000 06 45 33 26 8 8 16 08 00 39...

Page 581: ...4 02 00 11 9 3 0 4 6000 02 15 12 9 3 2 5 02 30 14 11 3 8 6 03 00 17 13 4 5 7 8000 03 00 16 12 4 2 7 03 30 19 15 5 0 8 04 15 22 17 5 9 9 10000 03 45 20 15 5 2 8 04 30 23 18 6 2 10 05 15 28 22 7 3 12 12000 04 30 23 18 6 2 10 05 15 28 22 7 3 12 06 15 33 26 8 7 15 14000 05 15 27 21 7 2 12 06 15 32 25 8 5 15 07 30 38 30 10 1 18 16000 06 00 31 24 8 1 14 07 15 37 29 9 7 17 08 30 44 34 11 5 21 18000 06 45...

Page 582: ...00 15 12 4 0 8 03 30 18 14 4 7 10 8000 03 30 17 14 4 6 10 04 00 20 16 5 4 11 04 30 23 18 6 2 13 10000 04 15 22 17 5 7 12 05 00 25 20 6 7 15 05 45 29 23 7 7 17 12000 05 15 26 20 6 8 15 06 00 30 24 7 9 18 07 00 35 27 9 2 21 14000 06 00 30 24 7 9 18 07 00 35 27 9 3 22 08 15 41 32 10 8 25 16000 07 00 34 27 9 1 22 08 15 40 31 10 6 25 09 30 47 37 12 3 29 18000 08 00 39 30 10 2 25 09 15 45 35 11 9 29 11 ...

Page 583: ...0 02 30 14 11 3 6 8 03 00 16 13 4 2 9 03 30 19 15 4 9 10 8000 03 30 18 14 4 8 10 04 00 21 17 5 6 12 04 45 25 19 6 5 14 10000 04 30 23 18 6 0 13 05 15 26 21 7 0 16 06 00 31 24 8 1 18 12000 05 15 27 21 7 2 16 06 15 32 25 8 4 19 07 15 37 29 9 7 22 14000 06 15 32 25 8 4 20 07 15 37 29 9 8 23 08 30 43 34 11 4 27 16000 07 15 36 28 9 5 23 08 30 42 33 11 2 27 10 00 49 39 13 0 32 18000 08 15 41 32 10 7 27 ...

Page 584: ...2 30 13 10 3 5 7 6000 02 45 14 11 3 8 8 03 00 17 13 4 5 9 03 30 20 15 5 2 11 8000 03 30 19 15 5 1 11 04 15 22 18 5 9 13 05 00 26 20 6 9 15 10000 04 30 24 19 6 3 14 05 15 28 22 7 4 17 06 15 33 26 8 6 19 12000 05 30 29 22 7 5 18 06 30 33 26 8 8 21 07 30 39 31 10 3 24 14000 06 30 33 26 8 8 21 07 30 39 31 10 3 25 09 00 46 36 12 0 29 16000 07 30 38 30 10 1 25 08 45 45 35 11 8 29 10 15 52 41 13 8 34 180...

Page 585: ...80 1555 1535 1510 1490 1470 4000 1585 1545 1525 1500 1480 1455 1435 6000 1555 1515 1490 1465 1440 1420 1395 8000 1520 1480 1455 1430 1400 1375 1345 Conditions Landing gear DN and flaps LDG IAS 95 KIAS Airplane weight Pressure altitude feet RATE OF CLIMB ft min ISA 35 C ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 7394 lbs 3354 kg SL 1350 1320 1295 1275 1255 1235 1215 2000 1325 1290 1265 1245 1...

Page 586: ...60 2245 2230 2220 2210 2190 4000 2265 2245 2230 2215 2200 2180 2165 6000 2250 2225 2210 2190 2175 2155 2135 8000 2235 2205 2185 2165 2145 2130 2110 Conditions Landing gear UP and flaps TO IAS 115 KIAS Airplane weight Pressure altitude feet RATE OF CLIMB ft min ISA 35 C ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 7394 lbs 3354 kg SL 1985 1965 1955 1940 1930 1915 1900 2000 1970 1950 1940 1925 1...

Page 587: ... S OPERATING HANDBOOK SUPPLEMENT 58 FIVE BLADED PROPELLER Edition 0 October 31 2013 Rev 1 Page 9 58 29 5 11 CRUISE PERFORMANCE MAXIMUM CRUISE Figure 5 11 1 CRUISE PERFORMANCE Maximum cruise 7100 lbs 6300 lbs ...

Page 588: ...0000 24 100 278 218 73 3 230 262 230 261 229 260 15000 34 100 265 208 70 1 226 276 225 275 224 275 18000 40 100 256 201 67 7 223 285 222 285 221 284 20000 44 100 251 197 66 2 221 292 220 291 219 290 21000 46 100 248 195 65 6 220 295 219 294 218 293 22000 48 100 246 193 65 0 219 299 218 298 217 296 23000 50 100 244 192 64 5 218 302 217 301 216 300 24000 52 100 243 190 64 1 217 306 216 304 215 303 2...

Page 589: ...238 239 237 238 5000 4 100 302 237 79 7 234 252 233 251 233 250 10000 14 100 281 220 74 2 229 265 228 265 228 264 15000 24 100 268 210 70 8 224 280 223 279 222 278 18000 30 100 259 203 68 4 221 289 220 288 219 287 20000 34 100 253 199 66 9 219 296 218 295 217 294 21000 36 100 251 197 66 2 218 299 217 298 216 297 22000 38 100 249 195 65 7 217 303 216 302 215 300 23000 40 100 247 194 65 1 216 306 21...

Page 590: ... 237 240 237 240 5000 1 100 304 238 80 2 233 253 232 253 232 252 10000 9 100 282 221 74 5 228 267 227 266 227 265 15000 19 100 269 211 71 2 223 282 222 281 222 280 18000 25 100 260 204 68 7 220 291 219 290 218 289 20000 29 100 254 200 67 2 218 298 217 297 216 296 21000 31 100 252 198 66 5 217 301 216 300 215 299 22000 33 100 250 196 66 0 216 305 215 304 214 302 23000 35 100 248 195 65 5 215 308 21...

Page 591: ...2 237 242 236 241 5000 6 100 305 240 80 7 232 255 232 254 231 253 10000 4 100 284 223 74 9 227 268 227 268 226 267 15000 14 100 271 213 71 5 222 283 222 283 221 282 18000 20 100 261 205 69 0 219 293 219 292 218 291 20000 24 100 256 201 67 6 217 300 216 299 215 297 21000 26 100 253 199 66 9 216 303 215 302 214 301 22000 28 100 251 197 66 3 215 307 214 306 213 304 23000 30 100 249 195 65 8 214 310 2...

Page 592: ...3 236 243 235 242 5000 11 100 307 241 81 1 231 256 231 256 230 255 10000 1 100 285 224 75 3 226 270 226 269 225 269 15000 9 100 272 214 72 0 221 285 221 284 220 283 18000 15 100 263 206 69 4 218 295 218 294 217 293 20000 19 100 257 202 67 9 216 302 216 301 215 299 21000 21 100 254 200 67 2 215 305 215 304 213 303 22000 23 100 252 198 66 6 214 309 214 308 212 306 23000 25 100 250 196 66 1 213 312 2...

Page 593: ...45 235 244 235 244 5000 16 100 309 242 81 6 231 258 230 257 230 256 10000 6 100 287 225 75 7 226 272 225 271 224 270 15000 4 100 274 215 72 3 221 287 220 286 219 285 18000 10 100 264 207 69 7 218 297 217 296 216 294 20000 14 100 258 203 68 3 216 303 215 302 214 301 21000 16 100 256 201 67 6 215 307 214 306 213 304 22000 18 100 254 199 67 0 214 311 213 309 211 308 23000 20 100 252 197 66 5 212 314 ...

Page 594: ...4 247 234 247 233 246 5000 26 100 312 245 82 5 229 261 229 260 228 259 10000 16 100 290 227 76 5 224 275 224 274 223 273 15000 6 100 276 217 73 0 219 290 218 289 217 288 18000 0 100 266 209 70 4 216 300 215 299 214 298 20000 4 100 261 205 69 0 214 307 213 306 212 304 21000 6 100 258 203 68 3 213 311 212 309 211 308 22000 8 100 256 201 67 6 212 314 211 313 210 311 23000 10 100 254 200 67 1 211 318 ...

Page 595: ...ILOT S OPERATING HANDBOOK SUPPLEMENT 58 FIVE BLADED PROPELLER Edition 0 October 31 2013 Rev 1 Page 9 58 37 NORMAL CRUISE Recommended Figure 5 11 9 CRUISE PERFORMANCE Recommended cruise 7100 lbs 6300 lbs ...

Page 596: ...239 236 239 235 5000 14 100 299 234 78 9 235 248 235 248 234 247 10000 24 100 278 218 73 3 230 262 230 261 229 260 15000 34 100 265 208 70 1 226 276 225 275 224 275 18000 40 100 256 201 67 7 223 285 222 285 221 284 20000 44 100 251 197 66 2 221 292 220 291 219 290 21000 46 100 248 195 65 6 220 295 219 294 218 293 22000 48 100 246 193 65 0 219 299 218 298 217 296 23000 50 100 244 192 64 5 218 302 2...

Page 597: ...38 239 238 239 237 238 5000 4 100 302 237 79 7 234 252 233 251 233 250 10000 14 100 281 220 74 2 229 265 228 265 228 264 15000 24 100 268 210 70 8 224 280 223 279 222 278 18000 30 100 259 203 68 4 221 289 220 288 219 287 20000 34 100 253 199 66 9 219 296 218 295 217 294 21000 36 100 251 197 66 2 218 299 217 298 216 297 22000 38 100 249 195 65 7 217 303 216 302 215 300 23000 40 100 247 194 65 1 216...

Page 598: ... 238 240 237 240 237 240 5000 1 100 304 238 80 2 233 253 232 253 232 252 10000 9 100 282 221 74 5 228 267 227 266 227 265 15000 19 100 269 211 71 2 223 282 222 281 222 280 18000 25 100 260 204 68 7 220 291 219 290 218 289 20000 29 100 254 200 67 2 218 298 217 297 216 296 21000 31 100 252 198 66 5 217 301 216 300 215 299 22000 33 100 250 196 66 0 216 305 215 304 214 302 23000 35 100 248 195 65 5 21...

Page 599: ... 237 242 237 242 236 241 5000 6 100 305 240 80 7 232 255 232 254 231 253 10000 4 100 284 223 74 9 227 268 227 268 226 267 15000 14 100 271 213 71 5 222 283 222 283 221 282 18000 20 100 261 205 69 0 219 293 219 292 218 291 20000 24 100 256 201 67 6 217 300 216 299 215 297 21000 26 100 253 199 66 9 216 303 215 302 214 301 22000 28 100 251 197 66 3 215 307 214 306 213 304 23000 30 100 249 195 65 8 21...

Page 600: ...4 236 243 236 243 235 242 5000 11 100 307 241 81 1 231 256 231 256 230 255 10000 1 100 285 224 75 3 226 270 226 269 225 269 15000 9 100 272 214 72 0 221 285 221 284 220 283 18000 15 100 263 206 69 4 218 295 218 294 217 293 20000 19 100 257 202 67 9 216 302 216 301 215 299 21000 21 100 254 200 67 2 215 305 215 304 213 303 22000 23 100 252 198 66 6 214 309 214 308 212 306 23000 25 100 250 196 66 1 2...

Page 601: ...9 236 245 235 244 235 244 5000 16 100 309 242 81 6 231 258 230 257 230 256 10000 6 100 287 225 75 7 226 272 225 271 224 270 15000 4 100 274 215 72 3 221 287 220 286 219 285 18000 10 100 264 207 69 7 218 297 217 296 216 294 20000 14 100 258 203 68 3 216 303 215 302 214 301 21000 16 100 256 201 67 6 215 307 214 306 213 304 22000 18 100 254 199 67 0 214 311 213 309 211 308 23000 20 100 252 197 66 5 2...

Page 602: ... 89 8 234 247 234 247 233 246 5000 26 100 312 245 82 5 229 261 229 260 228 259 10000 16 100 290 227 76 5 224 275 224 274 223 273 15000 6 100 276 217 73 0 219 290 218 289 217 288 18000 0 100 266 209 70 4 216 300 215 299 214 298 20000 4 100 261 205 69 0 214 307 213 306 212 304 21000 6 99 256 201 67 6 212 309 211 308 210 306 22000 8 96 248 195 65 6 209 310 208 309 206 307 23000 10 94 241 189 63 7 206...

Page 603: ...19 205 19000 38 42 149 32 148 22 147 12 145 2 143 37 4 37 9 38 4 38 7 38 9 111 196 113 199 114 202 115 203 116 204 20000 38 44 150 34 148 24 147 14 146 4 144 37 0 37 3 37 9 38 4 38 7 110 201 111 202 112 205 114 208 115 209 21000 38 46 148 36 147 26 146 16 145 6 144 36 0 36 6 37 1 37 6 38 2 107 201 109 204 110 207 112 210 113 213 22000 38 48 147 38 146 28 145 18 143 8 142 35 3 35 8 36 4 36 6 37 2 1...

Page 604: ...106 225 26 000 42 56 151 46 150 36 148 26 146 16 145 34 6 35 1 35 4 35 6 36 2 103 223 104 226 105 228 106 230 108 233 27 000 44 57 152 47 151 37 150 27 148 17 147 34 6 35 1 35 7 36 0 36 5 103 228 104 232 106 235 107 237 108 241 28 000 45 59 153 49 152 39 151 29 149 19 147 34 5 35 1 35 7 36 0 36 3 103 233 104 237 106 241 107 243 108 245 29 000 45 61 153 51 151 41 150 31 148 21 146 34 3 34 6 35 2 35...

Page 605: ... 209 19 000 42 42 156 32 154 22 152 12 151 2 150 40 0 40 3 40 7 41 3 41 9 119 205 120 207 121 209 123 211 124 214 20 000 42 44 154 34 153 24 151 14 150 4 149 38 9 39 5 39 9 40 5 41 1 116 206 117 209 118 211 120 214 122 216 21 000 43 46 153 36 152 26 151 16 150 6 149 38 2 38 7 39 4 39 9 40 6 113 208 115 211 117 214 119 217 121 220 22 000 43 48 152 38 151 28 150 18 149 8 148 37 4 38 0 38 6 39 2 39 8...

Page 606: ...111 226 26 000 44 56 152 46 150 36 148 26 147 16 146 35 9 36 2 36 6 37 2 37 8 107 224 108 226 109 228 111 232 112 235 27 000 46 57 154 47 152 37 150 27 148 17 147 36 2 36 5 36 9 37 2 37 8 107 231 108 233 109 235 111 237 112 241 28 000 48 59 156 49 154 39 152 29 151 19 149 36 5 36 8 37 2 37 8 38 2 108 238 109 240 111 243 112 246 113 248 29 000 48 61 155 51 153 41 151 31 149 21 147 36 1 36 4 36 8 37...

Page 607: ... 220 19 000 48 42 160 32 159 22 158 12 157 2 156 42 0 42 6 43 3 44 0 44 6 125 210 127 213 129 217 131 219 133 222 20 000 48 44 160 34 159 24 157 14 156 4 155 41 4 42 1 42 5 43 2 43 9 123 214 125 217 126 219 128 222 130 225 21 000 48 46 158 36 157 26 156 16 155 6 154 40 4 41 1 41 8 42 4 43 1 120 214 122 218 124 221 126 224 128 227 22 000 48 48 157 38 156 28 155 18 153 8 152 39 8 40 4 41 0 41 4 42 1...

Page 608: ...118 232 26 000 48 56 153 46 151 36 150 26 149 16 148 37 4 37 9 38 5 39 2 39 8 111 226 113 228 114 231 117 235 118 238 27 000 50 57 155 47 153 37 151 27 149 17 148 37 7 38 1 38 5 39 0 39 6 112 232 113 235 114 237 116 239 118 242 28 000 51 59 157 49 154 39 152 29 150 19 149 38 1 38 2 38 7 39 1 39 8 113 239 114 240 115 243 116 245 118 248 29 000 52 61 156 51 154 41 152 31 150 21 148 37 7 38 1 38 6 39...

Page 609: ... 40 31 10 6 61 10 25 29 23 7 8 48 24000 16 00 55 43 14 5 73 12 00 37 29 9 8 55 09 35 28 22 7 3 44 22000 14 40 51 40 13 4 66 11 00 34 27 9 1 50 08 50 26 20 6 8 40 20000 13 20 47 37 12 3 59 10 00 32 25 8 4 44 08 00 24 19 6 3 35 18000 12 00 42 33 11 1 53 09 00 29 23 7 6 39 07 10 22 17 5 8 31 16000 10 40 38 30 10 0 46 08 00 26 20 6 8 34 06 25 20 15 5 2 27 14000 09 20 33 26 8 8 40 07 00 23 18 6 1 30 05...

Page 610: ...titude feet FUEL USED DURING HOLDING TIME Weight 5500 lbs 2495 kg Weight 6300 lbs 2858 kg 10 min 30 min 10 min 30 min l kg USG l kg USG l kg USG l kg USG SL 30 23 7 8 89 70 23 5 30 24 8 0 91 71 24 1 5000 26 21 6 9 79 62 20 8 27 21 7 1 81 64 21 4 10000 24 18 6 2 71 55 18 7 24 19 6 5 73 58 19 4 15000 22 17 5 8 66 51 17 3 23 18 6 0 69 54 18 1 20000 20 16 5 3 60 47 15 9 21 17 5 6 63 50 16 7 Figure 5 1...

Page 611: ... the standard airplane described in Section 6 Weight and balance of the basic Pilot s Operating Handbook when the airplane is equipped with the option FIVE BLADED PROPELLER S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 61 PROPELLER 61 10 Propeller assembly O 0345 61 Propeller HC E5N 3C NC8834K spinner 104552P 171 08 77 60 43 11 1 0...

Page 612: ...ng The system operation is correct when green warning light located above PROP DE ICE switch illuminates The cycles continue as long as the switch remains set to ON CAUTION WHEN ENGINE IS SHUTDOWN DO NOT SET THE PROP DE ICE SWITCH TO ON DAMAGE TO THE PROPELLER BLADES COULD RESULT SECTION 8 HANDLING SERVICING AND MAINTENANCE Information hereafter supplement or replace those of the standard airplane...

Page 613: ...14 Rev 0 Page 9 59 1 SUPPLEMENT BRAZIL SPECIFICS TABLE OF CONTENTS Page 1 GENERAL 9 59 2 2 LIMITATIONS 9 59 2 3 EMERGENCY PROCEDURES 9 59 9 4 NORMAL PROCEDURES 9 59 9 5 PERFORMANCE 9 59 9 6 WEIGHT AND BALANCE 9 59 9 7 DESCRIPTION 9 59 9 8 HANDLING SERVICING AND MAINTENANCE 9 59 9 ...

Page 614: ...uthorities limitations description and operations necessary to the operation of the TBM airplane SECTION 2 LIMITATIONS The limitations hereafter supplement or replace those of the standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook 2 5 WEIGHT AND C G LIMITS WEIGHT LIMITS With 4 seat accommodation in rear part of pressurized cabin 396 lbs 180 kg with small o...

Page 615: ...compartment partition wall 100 kg MÁXIMO É DE RESPONSABILIDADE DO PILOTO CHECAR SE TODA BAGAGEM ESTÁ ADEQUADAMENTE SEGURA PARA INSTRUÇÕES DE CARREGAMENTO CONSULTAR A SEÇÃO DE PESO E BALANCEAMENTO DO MANUAL DE VÔO For the small cargo net on frame C13bis For the large cargo net on R H side upholstery panel in the rear baggage compartment ...

Page 616: ...ge 9 59 4 On FWD baggage compartment door frame non pressurized 50 kg MÁXIMO PARA INSTRUÇÓES DE CARREGAMENTO CONSULTAR A SEÇÃO DE PESO E BALANCEAMENTO DO MANUAL DE VÔO Near fuel tank caps On rear passenger s table casing A MESA DEVERÁ ESTAR RECOLHIDA PARA DECOLAGEM E POUSO On nose gear door ...

Page 617: ...S Edition 0 March 31 2014 Rev 0 Page 9 59 5 On engine cowling in front of compartment door TOMADA EXTERNA 28 VOLTS D C NOMINAL 800 AMPS CAPACIDADE MÍNIMA PARA PARTIDA NÃO EXCEDA 1000 AMPS On pilot door External side if installed On access door External side ...

Page 618: ...K SUPPLEMENT 59 BRAZIL SPECIFICS Edition 0 March 31 2014 Rev 0 Page 9 59 6 On outer fuselage skin aft of access door and in the cabin forward of access door On access door Internal side On pilot door Internal side if installed ...

Page 619: ...NG HANDBOOK SUPPLEMENT 59 BRAZIL SPECIFICS Edition 0 March 31 2014 Rev 0 Page 9 59 7 On emergency exit handle Marking on cover Marking on handle On last step of stairs MAX UMA PESSOA NA ESCADA On R H access door jamb ...

Page 620: ...MENT 59 BRAZIL SPECIFICS Edition 0 March 31 2014 Rev 0 Page 9 59 8 On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling On rear passengers masks containers On the oxygen service door ...

Page 621: ...CE The weight and balance hereafter supplement or replace those of the standard airplane described in Section 6 Weight and balance of the basic Pilot s Operating Handbook S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 01 SPECIFIC OPTIONAL EQUIPMENT S 01004 Brazil certification markings SOCATA SECTION 7 DESCRIPTION No specifics SECTI...

Page 622: ...is supplied nor may information contained in it be disclosed to unauthorized persons It must not be reproduced nor transmitted in any form in whole or in part without permission in writing from the owners of the Copyright Information in this document is subject to change without notice 2014 socata All rights reserved DAHER SOCATA Customer support 65921 TARBES CEDEX 9 FRANCE Printed in FRANCE Repor...

Page 623: ...ICAL POWER 10 ATA 25 EQUIPMENT AND FURNISHINGS 11 ATA 26 FIRE PROTECTION 14 ATA 27 FLIGHT CONTROLS 15 ATA 28 FUEL SYSTEM 16 ATA 30 ICE AND RAIN PROTECTION 17 ATA 31 INDICATING RECORDING SYSTEMS 18 ATA 32 LANDING GEARS 19 ATA 33 LIGHTS 21 ATA 34 NAVIGATION 22 ATA 35 OXYGEN 27 ATA 37 VACUUM 28 ATA 52 DOORS 29 ATA 56 WINDOWS 30 ATA 57 WINGS 31 ATA 61 PROPELLER 32 ATA 71 POWER PLANT 33 ATA 77 ENGINE I...

Page 624: ...ying the equipment R equipment items required for certification S standard equipment items A optional equipment items which are in addition to required or standard items O optional equipment items replacing required or standard items LIST OF CRITICAL RVSM EQUIPMENT Equipment listed hereafter or later approved versions is required for RVSM operation Equipment P N Barometric altimeter GDC74B Air dat...

Page 625: ... EQUIPMENT Edition 0 October 31 2013 Rev 1 Page 3 S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 01 SPECIFIC OPTIONAL EQUIPMENT S 01026A Flight ceiling at 31000 ft SOCATA ...

Page 626: ...ization control S Cabin altitude warn switch 214 C40 3 261 CONDEC EATON 0 077 0 035 153 94 3 910 S Cabin aP warn switch 17 600 01 UMA 0 143 0 065 139 76 3 550 S Outflow valve 81146A010101 LIEBHERR 3 97 1 800 317 32 8 060 S Safety valve 81147A010101 LIEBHERR 3 31 1 500 317 32 8 060 21 50 Temperature conditioning system S Flow control shut off valve 6784A010001 LIEBHERR 4 74 2 500 114 17 2 900 S Non...

Page 627: ... Cockpit Evaporator Assembly 14720A010001 LIEBHERR 9 06 4 111 200 79 5 100 S Cabin Evaporator Assembly 14719A010001 LIEBHERR 12 90 5 850 311 02 7 900 S Condenser Assembly 81250A010001 LIEBHERR 24 80 11 250 330 71 8 400 21 60 Temperature regulation S By pass valve 6043A010001 LIEBHERR 3 31 1 500 106 30 2 700 S Bleed differential pressure sensor 93558A010001 LIEBHERR 0 44 0 200 114 17 2 900 S Inlet ...

Page 628: ...Upgrading of AFCS GFC 700 composed of GARMIN Pitch servo GSA 81 Servo mount GSM 86 GARMIN 4 08 1 85 247 40 6 284 Roll servo GSA 81 Servo mount GSM 86 GARMIN 4 08 1 85 231 10 5 870 Yaw servo GSA 81 Servo mount GSM 86 GARMIN 4 08 1 85 253 70 6 444 Pitch trim servo GSA 81 Servo mount GSM 86 GARMIN 4 14 1 88 157 87 4 010 Trim adapter GTA 82 GARMIN 1 30 0 59 240 87 6 118 AFCS Control Unit GMC 710 GARMI...

Page 629: ...6 21B P3 CHELTON 0 86 0 390 271 65 6 900 S 0176 00A G1000 COM 2 system GARMIN Transceiver integrated in GIA 63W Integrated Avionics Unit 2 refer to ATA 34 28 GARMIN VHF antenna above fuselage 16 21B P3 CHELTON 0 86 0 390 271 65 6 900 S Static dischargers DSC 740049 Qty 4 DAYTON GRANGER Neglig S Static dischargers 2 5 SCY Qty 2 CHELTON Neglig S Static dischargers 2 9 SCY Qty 3 CHELTON Neglig O 0287...

Page 630: ...728 125 59 3 190 Version A capability already installed GDR 66 transceiver rack GARMIN 4 85 2 200 121 77 3 093 CPDLC antenna VF10 605 DAYTON GRANGER 0 79 0 360 145 59 3 698 A 0410 23 HF Communication System KHF1050 of which HONEYWELL 38 03 17 250 302 70 7 689 Control Display unit 1 56 0 707 155 43 3 948 Receiver Exciter 5 90 2 676 123 07 3 126 Antenna coupler 16 20 7 348 342 28 8 694 Power amplifi...

Page 631: ...kg REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O A 0353 23 GDR 66 for CPDLC using of which GARMIN 6 01 2 728 125 59 3 190 Version A capability already installed GDR 66 transceiver rack GARMIN 4 85 2 200 121 77 3 093 CPDLC antenna VF10 605 DAYTON GRANGER 0 79 0 360 145 59 3 698 ...

Page 632: ... 1 ASTRONICS 14 330 6 500 128 15 3 255 R Stand by alternator ES10024B 5 HARTZELL ENGINEERING TECHNOLOGY HET 13 000 5 897 104 84 2 663 R Starter generator MG94K 1 ADVANCED INDUSTRIES 31 989 14 510 118 83 2 815 S 24002A Lead acid battery RG 380E 44 CONCORDE 85 979 39 000 112 20 2 850 A 0303 24 Charger Maintainer for lead acid battery 0 220 0 100 114 17 2 900 24 40 External power supply S Ground powe...

Page 633: ...151 25 CD reader PCD 7100 PS ENGINEERING 2 20 1 00 205 04 5 208 A 0304 25 Cabin fitting out Autolux leather upholstering variants SOCATA Version A Heather leather light blue coloured seats Version B Blue jeans coloured carpets Version C Sateen Chocolate coloured seats and cabinets Version D Carbon coloured Finishing Version E Grey coloured seats and cabinets S 0374 25 Servicing plugs unit of which...

Page 634: ...S Pilot s seat T700C2500002012 SOCATA 55 12 25 00 183 90 4 671 S Front R H seat T700C2500002013 SOCATA 55 12 25 00 183 90 4 671 25 61 Emergency locator transmitter A 25030F Three frequency emergency locator transmitter C406 1 with base with G1000 system GPS source airplanes equipped with reinforcement of which ARTEX 7 77 3 523 349 92 8 888 ELT C406 1 ARTEX 3 36 1 525 354 72 9 010 ELT NAV interface...

Page 635: ...ED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 26 FIRE PROTECTION S 26002E Engine fire detection system capability installation L HOTELLIER A 26002F Engine fire detection system L HOTELLIER 1 455 0 660 96 06 2 440 A 0391 26 Portable fire extinguisher unit 74 00 AIR TOTAL 4 85 2 200 170 11 4 321 ...

Page 636: ... R Rudder trim actuator 145700 02 LPMI 1 543 0 700 395 27 10 040 S 0348 27 New control wheels CROUZET S L H equipped control wheel 83912112 CROUZET 2 535 1 150 157 98 4 000 S RH equipped control wheel 83912113 CROUZET 2 535 1 150 157 98 4 000 27 30 Pitch control S Pitch trim actuator 145400 02 LPMI 1 213 0 550 425 20 10 800 27 50 Wing flaps control R Flap control including AVIAC 15 520 7 040 218 5...

Page 637: ...it L88A15 651 INTERTECHNIQUE 4 586 2 080 133 07 3 380 R A35 fuel sequencer unit TFE 1 102 0 500 125 98 3 200 28 40 Fuel indication R 0158 28C Fuel gage amplifier in us gal 738574 1 0 INTERTECHNIQUE 1 08 0 49 278 74 7 080 R Inboard L H gage 762 438 1 0 INTERTECHNIQUE 0 331 0 150 183 07 4 650 R Inboard R H gage 762 439 1 0 INTERTECHNIQUE 0 331 0 150 183 07 4 650 R Intermediate gage 762 440 1 0 INTER...

Page 638: ...001002 inboard L H wing SOCATA 5 732 2 600 173 23 4 400 S Deicer T700A3010001003 inboard R H wing SOCATA 5 732 2 600 173 23 4 400 S Deicer T700A3010001004 middle L H wing SOCATA 3 748 1 700 173 23 4 400 S Deicer T700A3010001005 middle R H wing SOCATA 3 748 1 700 173 23 4 400 S Deicer T700A3010012000 outboard L H wing SOCATA 2 65 1 200 173 23 4 400 S Deicer T700A3010001007 outboard R H wing SOCATA ...

Page 639: ...TIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 31 INDICATING RECORDING SYSTEMS 31 20 Independent instruments O 31002A Hourmeter 56457 3 engine running time DATCON 0 551 0 250 156 30 3 970 S Hourmeter 56457 3 flying time DATCON 0 551 0 250 156 30 3 970 31 50 Aural warning R Aural warning system T700A3155011000 SOCATA 0 661 0 300 183 07 4 650 ...

Page 640: ... 24 300 93 70 2 380 32 30 Extension and retraction R Door actuator EC 6230 HRL 1 345 0 610 192 91 4 900 O 0334 32 Main locking actuator VSTS 083560 HL 13 228 6 000 208 07 5 285 O 0334 32 Nose locking actuator VSTS 083560 HL 13 228 6 000 110 24 2 800 R Hand pump 914 8D27 TELEDYNE 2 326 1 055 181 10 4 600 S 0342 52 Lower main landing gear doors R H and L H 6 614 3 000 204 33 5 190 32 35 Hydraulic ge...

Page 641: ...OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O R Nose tire 5 00 5 10PR TL MICHELIN 5 600 2 540 89 57 2 275 GOOD YEAR 6 300 2 858 89 57 2 275 O Nose wheel 40 262A PARKER 2 976 1 350 89 57 2 275 O Main wheel Model 40 434 PARKER 11 28 5 120 204 33 5 190 R Parking brake valve T700A3240010 or T700B3240001 SOCATA 0 331 0 150 157 48 4 000 ...

Page 642: ...H taxi and landing lights 01 0771674 01 WHELEN 1 400 0 635 181 10 4 600 S 0322 00 R H taxi and landing lights 01 0771674 01 WHELEN 1 400 0 635 181 10 4 600 S 0322 00 NAV Anticollision system LED lights S Central units S L H strobe light power supply 01 0771234 07 WHELEN 0 609 0 277 191 38 4 861 S R H strobe light power supply 01 0771234 07 WHELEN 0 609 0 277 191 38 4 861 S Rear strobe light power ...

Page 643: ...8 4 000 S 0160 34A Autorisation to operate in RVSM area S 0176 00A Air Data Computer 1 GDC 74B GARMIN 2 31 1 05 150 24 3 816 S 0176 00A Air Data Computer 2 GDC 74B GARMIN 2 31 1 05 150 24 3 816 O 0335 34 Electronic Standby Instrument ESI 2000 replacing altimeter airspeed indicator and stand by horizon L 3 Communication Avionics Systems S Version A refer to 34 24 2 75 1 250 154 29 3 919 34 21 Headi...

Page 644: ...d of PFD1 GDU 1040A GARMIN 6 53 2 96 155 71 3 955 PFD2 GDU 1040A GARMIN 6 53 2 96 155 71 3 955 MFD GDU 1500A GARMIN 8 66 3 93 155 20 3 942 Engine Airframe Interface Unit 1 GEA 71 GARMIN 2 53 1 15 150 63 3 826 Engine Airframe Interface Unit 2 GEA 71 GARMIN 2 53 1 15 150 63 3 826 Integrated Avionics Unit 1 GIA 63W GARMIN 7 21 3 27 149 37 3 794 Integrated Avionics Unit 2 GIA 63W GARMIN 7 21 3 27 149 ...

Page 645: ...dar GWX 70 GARMIN 10 35 4 47 169 1 4 295 34 43 Radioaltimeter A 0270 34A Radioaltimeter RA4500 G1000 coupled of which 2 500 1 134 220 47 5 600 Transceiver RA4500 FREEFLIGHT 1 900 0 862 228 82 5 812 Antennas S67 2002 SENSOR SYSTEMS 0 300 0 136 182 09 and 205 83 4 625 and 5 228 34 44 Traffic advisory system A 0176 00F G1000 TAWS system GARMIN A 0258 00B TAS system GTS 820 G1000 coupled of which GARM...

Page 646: ...eceiver integrated in the GIA 63W Integrated Avionics Unit 2 refer to ATA 34 28 34 53 Transponder S 0176 00D Transponder 1 GTX 33D Mode S diversity GARMIN 4 12 1 87 149 65 3 801 Antenna KA 61 under fuselage 0 40 0 18 150 08 3 812 Antenna KA 61 above fuselage 0 40 0 18 193 22 4 908 A 0176 00E Transponder 2 GTX 33 Mode S non diversity GARMIN 3 87 1 75 149 65 3 801 Antenna KA 61 0 40 0 18 193 22 4 90...

Page 647: ... RA3502 P N 0505 757 912 BECKER 2 205 1 000 Antenna AN3500 P N 0832 601 912 BECKER 3 594 1 630 RMI converter AC3504 P N 0856 010 912 BECKER 1 323 0 600 34 55 DME installation A 34014E DME KN63 G1000 coupled HONEYWELL 2 80 1 27 232 28 5 900 Antenna KA 61 0 40 0 18 238 82 6 066 34 57 Global Positioning System GPS S 0176 00A GPS WAAS Antenna GA 36 GARMIN 0 46 0 21 204 84 5 203 S 0176 00A GPS WAAS XM ...

Page 648: ...NT Edition 0 October 31 2013 Rev 1 Page 25 ARM in m WEIGHT per unit lb kg REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 35 OXYGEN S 0207 00 Gaseous oxygen system EROS INTERTECHNIQUE 22 73 10 310 226 77 5 760 ...

Page 649: ...ED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 37 VACUUM S Air ejector valve 19E17 5A LUCAS 0 661 0 300 116 14 2 950 S Regulator and relief valve 38E 96 2D LUCAS 1 323 0 600 116 14 2 950 S Vacuum relief valve 691 21A LUCAS 0 331 0 150 139 76 3 550 S Valve 557 18 E LUCAS 0 353 0 160 118 11 3 000 ...

Page 650: ...EIGHT per unit lb kg REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 52 DOORS A 52002A Pilot door SOCATA 44 092 20 000 171 26 4 350 O 0320 52 New Pilot door SOCATA 44 864 20 350 173 23 4 400 S 0342 52 Additional landing gear doors SOCATA 6 613 3 000 204 33 5 190 ...

Page 651: ...EQUIPMENT Edition 0 October 31 2013 Rev 1 Page 28 ARM in m WEIGHT per unit lb kg REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 56 WINDOWS S 56001A Deiced R H windshield SPS a1 764 a 0 800 158 27 4 020 ...

Page 652: ...ion 0 October 31 2013 Rev 1 Page 29 ARM in m WEIGHT per unit lb kg REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 57 WINGS S 57001A Utilization on runways covered with melting snow SOCATA a 7 716 a 3 500 200 00 5 080 ...

Page 653: ...M OPT70 or MOD70 S R A O 61 PROPELLER 61 10 Propeller assembly S Propeller 4 blade HC E4N 3 E 9083 S K spinner HARTZELL 154 76 70 20 43 11 1 095 A Propeller 5 blade HC E5N 3C NC 8834 K spinner 104552P HARTZELL 171 08 77 60 43 11 1 095 61 20 Controls S Propeller governor 8210 007 WOODWARD 2 646 1 200 59 06 1 500 R Overspeed governor 1439230 JIHOSTROJ 2 535 1 150 59 06 1 500 ...

Page 654: ...OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 71 POWER PLANT R Turboprop engine PT6 A 66D P W CANADA 497 30 226 00 79 72 2 025 S Silentblocks 95007 16 BARRY 2 92 1 325 79 72 2 025 S Silentblocks 95007 19 BARRY 2 92 1 325 79 72 2 025 71 60 Air inlet R 0359 71 Inertial separator actuator JA23372 1000 2 BEAVER 2 156 0 978 62 99 1 600 ...

Page 655: ...NGINE INDICATING R Compressor turbine tacho generator Ng MIL G 26611C GEU 7 A AIRCRAFT APPLIANCES AND EQUI LTD 0 981 0 445 108 27 2 750 R Propeller turbine tacho generator Np MIL G 26611 GEU 7 A AIRCRAFT APPLIANCES AND EQUI LTD 0 981 0 445 55 12 1 400 R Torque transducer 8107 200 00 10 THALES 0 463 0 210 53 54 1 360 77 12 Fuel management S Fuel flow transmitter 660 526A SHADIN 1 000 0 454 110 20 2...

Page 656: ... STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 79 LUBRICATION 79 20 Distribution R Oil cooler L8538233 LORI 10 472 4 750 90 55 2 300 79 30 Indicating R Oil pressure transmitter 8107 400 00 10 SEXTANT 0 441 0 200 106 30 2 700 S 0169 79 Chip detection system 2 detectors interfaced with G1000 system PWC Neglig ...

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