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Daher TBM 850 Pilot's Information Manual

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Table of Contents

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PILOT'S INFORMATION
MANUAL
TBM 850 --- Edition 1
PIM - DO NOT USE FOR FLIGHT OPERATIONS

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Summary of Contents for Daher TBM 850

  • Page 1 PILOT’S INFORMATION MANUAL TBM 850 --- Edition 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 2 The list of effective pages in this manual corresponds to that of the basic Pilot’s Operating Handbook. The content of this document is the property of DAHER AEROSPACE It is supplied in confidence and commercial security of its contents must be maintained.
  • Page 3 T B M SECTION 0 PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS SECTION GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AIRPLANE HANDLING, SERVICING AND MAINTENANCE SUPPLEMENTS Edition 1 -- June 22, 2007 Page 0.6 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 4 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 1 of October 15, 2007 Pages Description 0.5A Update of SOCATA modifications index 0.7 thru 0.9 List of amendments -- Revision 1 0.11 thru 0.18 List of effective pages Modifications relative to Global Air System (GAS) :...
  • Page 5 Correction of circuit breakers distribution 7.8.5 thru 7.8.9 4.0.2, 4.5.26 Deletion of “Operation in RVSM conditions” paragraph due to removal of AM250 altimeters on TBM 850 airplanes equipped with G1000 system 7.8.3 Correction of description of the essential bus bars protection and supply 7.8.4...
  • Page 6 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 1 of October 15, 2007 (Cont’d) Pages Description 0.10, 2.0.1, Minor modifications 2.6.4 thru (text moving, presentation or terminology) 2.6.12, 3.0.2, 4.0.1, 4.3.19, 4.3.24, 4.3.31 thru 4.3.48,...
  • Page 7 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 2 of December 15, 2007 Pages Description 0.10 List of amendments -- Revision 2 0.11 thru 0.13 List of effective pages 0.17 Approval page 2.6.10...
  • Page 8 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 3 of January 31st, 2008 Pages Description Title Copyright update 0.11 List of amendments -- Revision 3 0.13, 0.17, 0.19 List of effective pages 7.15.5, 7.15.6 Addition of the ELT ARTEX C406--1 (OPT70 25030C) description...
  • Page 9 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 4 of March 31, 2008 Pages Description 0.5A, 0.5B Update of SOCATA modifications index 0.12, 0.13 List of amendments -- Revision 4 0.15 thru 0.20 List of effective pages 0.21...
  • Page 10 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 4 of March 31, 2008 (Cont’d) Pages Description 7.3.2, 7.3.7 thru Correction of some details according to upholstering 7.3.9, 7.3.12, new definition 7.3.13, 7.3.22, 7.3.23, 7.8.16 7.9.5, 7.9.7 thru...
  • Page 11 Edition 1 of June 22, 2007 Revision 5 of March 25, 2009 Pages Description Title, 0.1 Incorporation of DAHER--SOCATA logo instead of EADS SOCATA Approval date of Type Certificate Data Sheet deleted 0.14 List of amendments -- Revision 5 0.15 , 0.21...
  • Page 12 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 6 of September 15, 2009 Pages Description Approval page 0.15 thru 0.18 List of amendments -- Revision 6 0.19 thru 0.26 List of effective pages 1.2.1, 2.7.1, Removal of rear baggage compartment...
  • Page 13 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 6 of September 15, 2009 Pages Description 2.8.1 Modification of airspeed indicator markings 2.8.2 Modification of ITT instrument marking 3.3.5 Modification of Oil pressure drop procedure 3.3.10 Curve deleted and addition of information about illumination of ITT red warning during and after engine...
  • Page 14 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 6 of September 15, 2009 Pages Description 4.3.42, 4.4.59 Addition of red warning light condition 7.8.6 Electrical distribution of bus bars new diagram 7.9.3 Addition of bleed air system automatic load shedding feature...
  • Page 15 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 7 of September 15, 2010 Pages Description Title Copyright update Approval page 0.18 thru 0.20 List of amendments -- Revision 7 0.21 thru 0.28 List of effective pages 1.1.1, 2.1.1,...
  • Page 16 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 7 of September 15, 2010 Pages Description 5.5.1 Incorporation of TR 01 R1 Correction of OAT values with respect to the SAT values 7.6.6 Incorporation of TR 05 Fuel condition lever...
  • Page 17 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 8 of July 15, 2012 Pages Description Title Copyright update Temporary update integration table updating Approval page 0.5B, 0.5C SOCATA modifications -- Index updating 0.20 thru 0.24 List of amendments -- Revision 8 0.25 thru 0.32...
  • Page 18 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 8 of July 15, 2012 (Cont’d) Pages Description 2.9.9 Incorporation of TR 08 4--seat accommodation capability 4.3.34, 4.4.46 Incorporation of TR 09 Prop O’speed governor test 1.3.3, 2.0.1 and Incorporation of TR 11...
  • Page 19 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 8 of July 15, 2012 (Cont’d) Pages Description 1.1.1A, 2.0.2, Addition of MOD70--0335--34 (ESI 2000) 2.0.2A, 2.1.1A, 2.8.1, 2.8.2, 2.8.4, 3.9.0B, 3.9.8, 3.9.10 thru 3.9.12, 3.10.6, 4.3.14,...
  • Page 20 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 8 of July 15, 2012 (Cont’d) Pages Description 4.3.45, 4.4.64 Modification of Shut--down procedure sequence order 4.3.19, 4.4.23 Modification of 2nd Caution in Starting engine using airplane power procedure 4.3.23, 4.4.29 Modification of 2nd Caution in Starting engine using...
  • Page 21 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 8 of July 15, 2012 (Cont’d) Pages Description 3.4.5, 3.4.6, Deleted pages 4.3.47, 4.3.48, 4.4.67, 4.4.68 0.5D, 1.4.6, Minor modifications 2.7.2, 2.8.3, (text moving, presentation or terminology) 2.8.4, 3.2.1, 3.3.1, 3.3.2,...
  • Page 22 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 9 of March 01, 2013 Pages Description Title Copyright update Approval page 0.25 thru 0.26 List of amendments -- Revision 9 0.27 thru 0.34 List of effective pages 2.7.1...
  • Page 23 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 10 of March 01, 2014 Pages Description Title Copyright update Approval page 0.5C Updating of SOCATA Modifications -- Index Addition of MOD70--0402--28 Fuel sequencer evolution 0.26 thru 0.28 List of amendments -- Revision 10 0.29 thru 0.36...
  • Page 24 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 10 of March 01, 2014 (Cont’d) Pages Description 4.3.19, 4.3.20 Modification of “Starting Engine Using Airplane Power” 4.3.24, 4.3.25 “Starting Engine Using External Power”...
  • Page 25 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 10 of March 01, 2014 (Cont’d) Pages Description 1.4.7 and 1.4.8, Minor modifications 2.3.2, 2.8.3, (text moving, presentation or terminology) 2.9.1, 3.4.1, 3.6.0B, 3.6.1 thru 3.6.4, 3.8.1, 3.10.7,...
  • Page 26 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 11 of May 29, 2015 Pages Description Title New logo Updating of temporary update integration table Approval page 0.29 and 0.30 List of normal amendments 0.31 thru 0.38 List of effective pages...
  • Page 27 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 11 of May 29, 2015 (Cont’d) Pages Description 4.3.47, 4.4.66 Modification of ”Shut--down” procedure : change of power lever IDLE duration 4.4.10 Addition of operation in filter contamination indicator check...
  • Page 28 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 12 of June 15, 2016 Pages Description Title Copyright 1, 2 Updating of temporary update integration table Approval page 0.5C, 7.5.1 Modifications due to addition of MOD70--0342--52 “Lower main landing gear doors”...
  • Page 29 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 12 of June 15, 2016 (Cont’d) Pages Description 4.3.46, 4.4.65 Modification of “AFTER LANDING” procedure : “BLEED SWITCH” position deleted 4.3.47, 4.4.66 Modification of “SHUT--DOWN”...
  • Page 30 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 13 of April 8, 2019 Pages Description Title Copyright Updating of temporary update integration table Approval page 0.2, 0.4 Modification of part number structure Addition of a reference to MyTBM.aero website for consultation of the list of modifications.
  • Page 31 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 13 of April 8, 2019 (Cont’d) Pages Description 2.0.2, 2.8.1, Modification of airspeed indicator markings : addition of 2.8.2 markings for standby airspeed indicator (TR27) 2.3.2 Clarification about engine oil use, update of oil limitation chapter...
  • Page 32 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 13 of April 8, 2019 (Cont’d) Pages Description 2.3.3, 3.9.11, Terminology, text moving and/or presentation 3.9.12, 3.10.0B, 3.10.1 thru 3.10.10, 3.13.0B, 3.13.7 thru 3.13.22, 4.0.1, 4.3.30 thru...
  • Page 33 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 14 of February 14, 2020 Pages Description Title Modification of the date of the copyright Approval page 0.36 to 0.40 List of amendments 0.41 to 0.48 List of effective pages 1.4.6, 1.4.7,...
  • Page 34 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 14 of February 14, 2020 (Cont’d) Pages Description 4.0.2, 4.5.27 Addition of applicability Pre--GARMIN software 12.01 to existing ”GPS navigation” procedure 4.3.14, 4.4.16 Addition of instruction for the display backup use before starting the engine...
  • Page 35 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 14 of February 14, 2020 (Cont’d) Pages Description 5.11.2A to Integration of a fixed torque reduction instruction when 5.11.8A BLEED HI message ON with associated impacts on 5.11.10A to airspeed 5.11.16A,...
  • Page 36 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 1 of June 22, 2007 Revision 14 of February 14, 2020 (Cont’d) Pages Description 7.0.3, 7.15.3 to Addition of description for GARMIN Integrated Flight 7.15.5 Deck approaches 1.4.6 to 1.4.10, Terminology, text moving and/or presentation 2.0.1A, 2.0.2A,...
  • Page 37 T B M SECTION 0 PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 0.40 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 38 T B M SECTION 0 PILOT’S OPERATING HANDBOOK LIST OF EFFECTIVE PAGES AND VALIDITIES EDITION 1 OF JUNE 22, 2007 From S/N 434 to 999 P/N DMNFM00EE1R14EN Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. Title 1 -- 14 0.20...
  • Page 39 T B M SECTION 0 PILOT’S OPERATING HANDBOOK Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. 1.6.1 1 -- 0 2.6.3 1 -- 13 3.2.0A 1 -- blank 1.6.2 1 -- 0 2.6.4 1 -- 8 3.2.0B 1 -- 2...
  • Page 40 T B M SECTION 0 PILOT’S OPERATING HANDBOOK Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. 3.6.4 1 -- 10 3.10.3 1 -- 14 3.13.14 1 -- 13 3.7.0A 1 -- blank 3.10.4 1 -- 13 3.13.15 1 -- 13...
  • Page 41 T B M SECTION 0 PILOT’S OPERATING HANDBOOK Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. 4.3.22 1 -- 10 4.4.9 1 -- 0 4.4.46 1 -- 10 4.3.23 1 -- 11 4.4.10 1 -- 11 4.4.47 1 -- 10...
  • Page 42 T B M SECTION 0 PILOT’S OPERATING HANDBOOK Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. 4.5.15 1 -- 0 5.8.6A 1 -- 14 5.11.1A 1 -- 7 4.5.16 1 -- 8 5.8.7A 1 -- 14 5.11.2A 1 -- 14...
  • Page 43 T B M SECTION 0 PILOT’S OPERATING HANDBOOK Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. 5.11.16 1 -- 14 6.4.12 1 -- 12 7.3.4 1 -- 13 5.11.17 1 -- 14 6.4.13 1 -- 12 7.3.5 1 -- 13...
  • Page 44 T B M SECTION 0 PILOT’S OPERATING HANDBOOK Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. 7.3.41 1 -- 12 7.6.4 1 -- 0 7.8.19 1 -- 6 7.3.42 1 -- 12 7.6.5 1 -- 13 7.8.20 1 -- 8...
  • Page 45 T B M SECTION 0 PILOT’S OPERATING HANDBOOK Page Edit. - - Rev. Page Edit. - - Rev. Page Edit. - - Rev. 7.11.6 1 -- 8 8.6.2 1 -- 0 Section 9 7.11.7 1 -- 14 8.6.3 1 -- 8 (See log of 7.11.8 1 -- 8...

  • Page 46: General

    T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK SECTION 1 GENERAL TABLE OF CONTENTS Page GENERAL 1.1.1A ..........THREE VIEW DRAWING 1.2.1 .
  • Page 47 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 1.0.2A Rev. 8 POST- -GARMIN SOFTWARE VERSION 12.01 or ANY LATER PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 48 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK SECTION 1 GENERAL TABLE OF CONTENTS Page GENERAL 1.1.1 ..........THREE VIEW DRAWING 1.2.1 .
  • Page 49 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 1.0.2 Rev. 8 PRE- -GARMIN SOFTWARE VERSION 12.01 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 50 1.1 - - GENERAL This Handbook contains 9 Sections, and includes the material required by FAR Part 23 to be furnished to the pilot for operation of the TBM 850 airplane. It also contains supplemental data supplied by the manufacturer.
  • Page 51 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 1.1.2A Rev. 8 POST- -GARMIN SOFTWARE VERSION 12.01 or ANY LATER PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 52 1.1 - - GENERAL This Handbook contains 9 Sections, and includes the material required by FAR Part 23 to be furnished to the pilot for operation of the TBM 850 airplane. It also contains supplemental data supplied by the manufacturer.
  • Page 53 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 1.1.2 Rev. 8 PRE- -GARMIN SOFTWARE VERSION 12.01 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 54 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.2 - - THREE VIEW DRAWING * Airplane on level field with fully extended FWD shock--absorber Figure 1.2.1 (1/2) -- THREE VIEW DRAWING Edition 1 -- June 22, 2007 Page 1.2.1 Rev.
  • Page 55 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Figure 1.2.1 (2/2) -- THREE VIEW DRAWING Edition 1 -- June 22, 2007 Page 1.2.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 56 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.3 - - DESCRIPTIVE DATA ENGINE Number of engines : 1 Engine manufacturer : PRATT & WHITNEY CANADA Engine model number : PT6A -- 66D Engine type : Free turbine, reverse flow and 2 turbine sections Compressor type : 4 axial stages 1 centrifugal stage...
  • Page 57 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK FUEL Total capacity : 301 us gal (1140 Litres) Total capacity each tank : 150.5 us gal (570 Litres) Total usable : 292 us gal (1106 Litres) CAUTION THE USED FUEL MUST CONTAIN AN ANTI- -ICE ADDITIVE, IN ACCORDANCE WITH SPECIFICATION MIL- -I- -27686 or MIL- -I- -85470.
  • Page 58 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK ENGINE OIL System total capacity : 12.7 Quarts (12 Litres) (oil cooler included) Usable capacity : 6 Quarts (5.7 Litres) Maximum consumption in 10 hour period : 0.14 qt / hr (0.13 l / hr) [0.3 lb / hr (136 cc / hr)] Specification Nominal...
  • Page 59 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK CABIN AND ENTRY DIMENSIONS Maximum cabin width : 3’ 11.64” (1.21 m) Maximum cabin 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’...
  • Page 60 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.4 - - ABBREVIATIONS AND TERMINOLOGY METEOROLOGICAL TERMINOLOGY International standard atmosphere Outside air temperature Static air temperature Atmospheric pressure at the airport reference point. Atmospheric pressure at sea level, at aircraft position. NOTE : On the ground, the altimeter will indicate ”zero”...
  • Page 61 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended.
  • Page 62 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK POWER TERMINOLOGY Recovery altitude : Maximum altitude at which it is possible, in standard temperature, to maintain a specified power. Overheated start : Engine start or attempt to start which causes the interturbine temperature to be higher than the maximum value permissible during start .
  • Page 63 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb gradient : Is the ratio of the change in height during a portion of climb, to the horizontal distance traversed in the same time interval. Demonstrated crosswind velocity : Is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing...
  • Page 64 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK C.G. limits : Center of Gravity Limits are the extreme center of gravity locations 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).
  • Page 65 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK GENERAL ABBREVIATIONS : Ampere or Amber : Air Data Computer : Above ground level ALT. SEL. : Altitude selector ALTI : Altimeter AMP. : Ampere : Autopilot AUTO SEL : Automatic selector AUX BP : Auxiliary boost pump : Battery...
  • Page 66 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK : High pressure : Hectopascal : Hour : Heater IGNIT : Ignition : Inch INERT SEP : Inertial separator INDIC : Indicator in.Hg : Inch of mercury INT. LIGHTS : Interior lightings INSTR.
  • Page 67 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK MTOW : Maximum Takeoff Weight MXCR : Maximum Cruise MZFW : Maximum Zero Fuel Weight : Nautical mile NOCR : Normal cruise (recommended) NORM : Normal : Primary Flight Display : Plan Horizontal Fixe (Horizontal stabilizer) PRESS : Pressure PROP...
  • Page 68 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK RADIO - - NAVIGATION ABBREVIATIONS : Automatic Direction Finder System : Attitude Director Indicator AFCS : Automated Flight Control System AHRS : Attitude and Heading Reference System AIRAC : Aeronautical Information Regulation And Control : Air Traffic Control B RNAV : Basic aRea NAVigation...
  • Page 69 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK R NAV : Area NAVigation : Required Navigation Performance SBAS : Satellite Based Augmentation System STAR : Standard Terminal Arrival Route : Traffic Advisory System TAWS : Terrain Awareness Warning System : Visual Flight Rules : Very High Frequency : Visual Meteorological Conditions...
  • Page 70 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.5 - - CONVERSION FACTORS IMPERIAL AND U.S UNITS TO METRIC UNITS TO IMPERIAL AND METRIC UNITS U.S UNITS MULTIPLY TO OBTAIN MULTIPLY TO OBTAIN FEET 0.3048 METRE METRE 3.2808 FEET INCH 25.4 0.03937...
  • Page 71 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Feet 31000 30000 20000 10000 Metres 2500 5000 7500 10000 Figure 1.5.2 -- FEET VERSUS METRES Edition 1 -- June 22, 2007 Page 1.5.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 72 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1000 Figure 1.5.3 -- INCHES VERSUS MILLIMETRES Edition 1 -- June 22, 2007 Page 1.5.3 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 73 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 8000 6000 4000 2000 1000 2000 3000 4000 Figure 1.5.4 -- POUNDS VERSUS KILOGRAMS Edition 1 -- June 22, 2007 Page 1.5.4 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 74 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.6 - - PRESSURE AND STANDARD ATMOSPHERE STANDARD ATMOSPHERE Pressure Pressure altitude °C °F (hPa) (ft) 1013.2 + 15.0 + 59.0 2000 942.1 + 11.0 + 51.8 4000 875.0 + 44.6 6000 811.9 + 37.6...
  • Page 75 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK PRESSURE CONVERSION TABLE NOTE : The standard pressure of 1013.2 hPa is equal to 29.92 inches of mercury. 28.08 28.11 28.14 28.17 28.20 28.23 28.26 28.29 28.32 28.05 28.35 28.38 28.41 28.44 28.47 28.50...

  • Page 76: Limitations

    T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved SECTION 2 LIMITATIONS TABLE OF CONTENTS Page GENERAL 2.1.1A ........... AIRSPEED LIMITATIONS 2.2.1 .
  • Page 77 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page 2.6.14A ENHANCED MODE S ......... . . 2.6.14A CHARTWIEW SYSTEM OPERATING LIMITATIONS .
  • Page 78 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved SECTION 2 LIMITATIONS TABLE OF CONTENTS Page GENERAL 2.1.1 ..........AIRSPEED LIMITATIONS 2.2.1 .
  • Page 79 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page MISCELLANEOUS LIMITS 2.7.1 ....... . . 2.7.1 SEATING LIMITS C.G.
  • Page 80 EASA Approved 2.1 - - GENERAL “TBM 850” is the trade name of the TBM 700 ”N version” airplane (TBM 700 type), which is certified in the Normal Category. This airplane must be flown in compliance with the limits specified by placards or markings and with those given in this Section and throughout the Pilot’s Operating Handbook.
  • Page 81 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 2.1.2A Rev. 8 POST- -GARMIN SOFTWARE VERSION 12.01 or ANY LATER PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 82 EASA Approved 2.1 - - GENERAL “TBM 850” is the trade name of the TBM 700 ”N version” airplane (TBM 700 type), which is certified in the Normal Category. This airplane must be flown in compliance with the limits specified by placards or markings and with those given in this Section and throughout the Pilot’s Operating Handbook.
  • Page 83 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 2.1.2 Rev. 8 PRE- -GARMIN SOFTWARE VERSION 12.01 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 84 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.2 - - AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 2.2.1. KCAS KIAS SPEED REMARKS Do not intentionally exceed Maximum operating speed this speed in normal flight category Do not make abrupt or full Maneuvering speed...
  • Page 85 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 2.2.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 86 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.3 - - POWERPLANT LIMITATIONS ENGINE Number of engines : 1 Engine manufacturer : PRATT & WHITNEY CANADA Engine model number : PT6A -- 66D Maximum power : Flaps set to Flaps set to UP, TO or LDG position 850 position...
  • Page 87 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved CAUTION DO NOT MIX DIFFERENT VISCOSITIES OR SPECIFICATIONS OF OIL AS THEIR DIFFERENT CHEMICAL STRUCTURE CAN MAKE THEM INCOMPATIBLE. Maximum oil temperature : 104 °C Oil pressure : Minimum : 60 psi Maximum : 135 psi Oil capacity : System total capacity : 12.7 Quarts (12 Litres) (Oil cooler included)
  • Page 88 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved CAUTION THE FUEL USED MUST CONTAIN AN ANTI- -ICE ADDITIVE, IN ACCORDANCE WITH SPECIFICATION MIL- -I- -27686 OR MIL- -I- -85470. ADDITIVE CONCENTRATIONS (EGME OR DIEGME) SHALL BE COMPRISED BETWEEN A MINIMUM OF 0.06 % AND A MAXIMUM OF 0.15 % BY VOLUME.
  • Page 89 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 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°...
  • Page 90 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.4 - - STARTER OPERATION LIMITS Starter operation sequence is limited as follows : if Ng ≤ 30 % ......... . . 30 seconds if Ng >...
  • Page 91 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 2.4.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 92 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.5 - - WEIGHT AND C.G. LIMITS WEIGHT LIMITS Maximum ramp weight (MRW) : 7430 lbs (3370 kg) Maximum takeoff weight (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)
  • Page 93 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved C.G. LIMITS -- see Figure 6.4.2 Center of gravity range with landing gear down and flaps up, attitude 0° : Forward limits : 181.3 inches (4.604 m) aft of datum at 4409 lbs (2000 kg) or less (14 % of m.a.c) 183.6 inches (4.664 m) aft of datum at 6250 lbs (2835 kg) (18 % of m.a.c) 185.3 inches (4.707 m) aft of datum at 6579 lbs (2984 kg) (20.85 % of m.a.c)
  • Page 94 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.6 - - OPERATION LIMITS MANEUVER LIMITS This airplane is certified in the normal category. The normal category is applicable to airplanes intended for non--aerobatic operations. Non--aerobatic operations include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and steep turns in which the angle of bank is no more than 60°.
  • Page 95 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved GFC 700 AUTOPILOT LIMITS -- During autopilot operation, a pilot with seat belt fastened must be seated at the left pilot position. -- The autopilot and yaw damper must be OFF during takeoff and landing. -- Do not engage autopilot below 1000 ft (300 m) AGL in cruise or climb.
  • Page 96 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved -- is, as installed in this airplane, complying with the equipment, performance, and functional requirements to conduct RNAV and RNP operations in accordance with the applicable requirements of the reference documents listed in the following table.
  • Page 97 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ICAO Flight Plan Code Approved Approved Reference Reference Phase of flight Phase of flight Operational limitations Operational limitations Notes Notes Item Item Documents Documents Capability Capability Code PBN/ Domestic, RNP 2 GNSS FDE availability Additional com-...
  • Page 98 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ICAO Flight Plan Code Approved Approved Reference Reference Phase of flight Phase of flight Operational limitations Operational limitations Notes Notes Item Item Documents Documents Capability Capability Code PBN/ Approach At a minimum, the flight EASA RF legs may be...
  • Page 99 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved G1000 GNSS (GPS/SBAS) NAVIGATION SYSTEM LIMITATIONS Navigation database limitations The pilot must confirm at system initialization that the Navigation database is current. If the AIRAC cycle will change during flight, the pilot must ensure the accuracy of navigation data, including suitability of navigation facilities used to define the routes and procedures for flight.
  • Page 100 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Whenever possible, RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and enroute RNAV Q and RNAV T routes should be loaded into the flight plan from the database in their entirety, rather than loading route waypoints from the database into the flight plan individually.
  • Page 101 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Procedures with RF legs (Radius to Fix legs) At a minimum, the flight director must be displayed and utilized when conducting procedures containing RF legs. SEVERE ICING CONDITIONS WARNING SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIRCRAFT IS CERTIFICATED.
  • Page 102 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved FLAP OPERATING ENVELOPE The use of flaps is not authorized above 15 000 ft. The use of flap control in “850” position is prohibited for takeoff and landing. REVERSE UTILIZATION The use of control reverse BETA (β) range is prohibited : -- during flight, -- on ground, if the engine is not running.
  • Page 103 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Day VFR 8) Pilot instruments -- Airspeed indicator -- Sensitive and adjustable altimeter -- Magnetic compass with built--in compensator 9) CAS warning and caution messages -- Oil pressure -- Low fuel pressure -- Fuel selector OFF -- Fuel auxiliary pump ON -- L.H.
  • Page 104 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 12) Various indicators -- Fuel gauge indicators (2) -- Fuel pressure indicator -- Voltmeter -- Ammeter -- Outside air temperature 13) Installations -- Fuel mechanical pump (main) -- Fuel electrical pump (auxiliary) -- Fuel shut--off valve -- Fuel timer -- Starter generator...
  • Page 105 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Night VFR 1) All equipment required for day VFR 2) Attitude display indicator 3) Instrument lighting 4) Instrument panel lighting 5) Emergency lighting 6) Vertical speed indicator 7) Navigation lights (4) 8) Anticollision lights (2) 9) Landing light 1) All equipment required for day VFR...
  • Page 106 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ALTITUDE OPERATING LIMITS Maximum altitude : 31000 ft (9449 m) Maximum differential pressure : 6.2 psi Operation in RVSM area This airplane is approved for operations in Reduced Vertical Separation Minimum (RVSM) airspace when required equipment (refer to Section “List of equipment”, §...
  • Page 107 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ENHANCED MODE S The installed Mode S system satisfies the data requirements of ICAO Doc 7030/4, Regional Supplementary Procedures for SSR Mode S Enhanced Surveillance in designated European airspace. The capability to transmit data parameters is shown in column 2 : Parameter Available (A) / Not Available (NA)
  • Page 108 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.6 - - OPERATION LIMITS MANEUVER LIMITS This airplane is certified in the normal category. The normal category is applicable to airplanes intended for non--aerobatic operations. Non--aerobatic operations include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and steep turns in which the angle of bank is no more than 60°.
  • Page 109 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved GFC 700 AUTOPILOT LIMITS -- During autopilot operation, a pilot with seat belt fastened must be seated at the left pilot position. -- The autopilot and yaw damper must be OFF during takeoff and landing. -- Do not engage autopilot below 1000 ft (300 m) AGL in cruise or climb.
  • Page 110 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Procedures during flight preparation During flight preparation, the pilot must get information about GPS constellation, via aeronautical data (consultation of GPS NOTAM). When less than 24 satellites are available (or less than 23 if equipment uses pressure altitude information), the pilot must make sure that RAIM function is available on the projected route and for the flight period in B--RNAV areas.
  • Page 111 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved The check of navigation system information consistency must be regularly performed during the flight : . when reaching each waypoint or before reaching the position report point of the ATC, .
  • Page 112 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved SEVERE ICING CONDITIONS WARNING SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIRCRAFT IS CERTIFICATED. FLIGHT IN FREEZING RAIN, FREEZING DRIZZLE, OR MIXED ICING CONDITIONS (SUPERCOOLED LIQUID WATER AND ICE CRYSTALS) MAY RESULT IN ICE BUILD- -UP ON PROTECTED SURFACES EXCEEDING THE CAPABILITY OF THE ICE PROTECTION SYSTEM,...
  • Page 113 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved FLAP OPERATING ENVELOPE The use of flaps is not authorized above 15 000 ft. The use of flap control in “850” position is prohibited for takeoff and landing. REVERSE UTILIZATION The use of control reverse BETA (β) range is prohibited : -- during flight, -- on ground, if the engine is not running.
  • Page 114 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Day VFR 8) Pilot instruments -- Airspeed indicator -- Sensitive and adjustable altimeter -- Magnetic compass with built--in compensator 9) CAS warning and caution messages -- Oil pressure -- Low fuel pressure -- Fuel selector OFF -- Fuel auxiliary pump ON -- L.H.
  • Page 115 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 12) Various indicators -- Fuel gauge indicators (2) -- Fuel pressure indicator -- Voltmeter -- Ammeter -- Outside air temperature 13) Installations -- Fuel mechanical pump (main) -- Fuel electrical pump (auxiliary) -- Fuel shut--off valve -- Fuel timer -- Starter generator...
  • Page 116 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Night VFR 1) All equipment required for day VFR 2) Attitude display indicator 3) Instrument lighting 4) Instrument panel lighting 5) Emergency lighting 6) Vertical speed indicator 7) Navigation lights (4) 8) Anticollision lights (2) 9) Landing light 1) All equipment required for day VFR...
  • Page 117 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ALTITUDE OPERATING LIMITS Maximum altitude : 31000 ft (9449 m) Maximum differential pressure : 6.2 psi Operation in RVSM area This airplane is approved for operations in Reduced Vertical Separation Minimum (RVSM) airspace when required equipment (refer to Section “List of equipment”, §...
  • Page 118 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ENHANCED MODE S The installed Mode S system satisfies the data requirements of ICAO Doc 7030/4, Regional Supplementary Procedures for SSR Mode S Enhanced Surveillance in designated European airspace. The capability to transmit data parameters is shown in column 2 : Parameter Available (A) / Not Available (NA)
  • Page 119 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 2.6.12 Rev. 8 PRE- -GARMIN SOFTWARE VERSION 12.01 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 120 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.7 - - MISCELLANEOUS LIMITS SEATING LIMITS C.G. -- 2 front seats at 178.5 in. (4.534 m) Pre--MOD 70--0315--25 -- 2 intermediate seats at 222.7 in. (5.656 m) Post--MOD 70--0315--25 with 4--seat...
  • Page 121 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved CARGO NET INSTALLATION LIMITS Small cargo net : maximum loading height = 28 in (710 mm) Large cargo net : maximum loading height = 22 in (565 mm) (in cabin, out of baggage compartment).
  • Page 122 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.8 - - MARKINGS AIRSPEED INDICATOR ON PFD(s) Airspeed indicator markings and their color code significance are shown in Figure 2.8.1. KIAS MARKING SIGNIFICANCE (Value or range) Red strip Below 65 White strip 65 -- 122...
  • Page 123 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Post--MOD70--0335--34 (ESI--2000) STANDBY AIRSPEED INDICATOR Indicated airspeed markings and their color code significance are shown in Figure 2.8.1B. KIAS MARKING SIGNIFICANCE (Value or range) Red strip Below 65 White strip 65 -- 122 Full Flap Operating Range Lower limit is maximum weight...
  • Page 124 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ENGINE INSTRUMENTS Engine instrument markings and their color code significance are shown in Figure 2.8.3. Yellow Line or Green Line or Arc Line or Arc Red Line --------- --------- --------- --------- INDICATION...
  • Page 125 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved SUCTION GAGE [PRE--MOD70--0335--34 (ESI--2000)] MARKING CORRESPONDING VALUE Green Normal operating from 4.4 to 5.2 in.Hg Red lines at 4.4 and 5.2 in.Hg Figure 2.8.4 -- SUCTION GAGE MARKINGS Edition 1 -- June 22, 2007 Page 2.8.4 Rev.
  • Page 126 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.9 - - PLACARDS (1) Under L.H. front side window (2) Calibration chart on compass and on windshield post Steer 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...
  • Page 127 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Post--MOD 70--0315--25 (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 (3)c On FWD baggage compartment door frame (non pressurized) 50 kg - - 110 lbs MAXIMUM FOR LOADING INSTRUCTIONS SEE ”WEIGHT AND BALANCE DATA”...
  • Page 128 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (4) Under GCU 475 control unit on pedestal console Edition 1 -- June 22, 2007 Page 2.9.2A Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 129 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 2.9.2B Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 130 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (5) On fuel selector (6) Near fuel tank caps Edition 1 -- June 22, 2007 Page 2.9.3 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 131 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (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) On rear passenger’s table casing TABLE MUST BE STOWED DURING TAKEOFF AND LANDING (10) Under R.H.
  • Page 132 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (11) On nose gear door (12) On nose gear leg NOSE LANDING GEAR TIRE PRESSURE : 6,5 bar 94 psi (13) On main gear leg MAIN LANDING GEAR TIRE PRESSURE : 8,96 bar 130 psi (14) On engine cowling, in front of compartment door EXTERNAL POWER...
  • Page 133 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (15) On ”pilot” door -- External side (if installed) (16) On access door -- External side Edition 1 -- June 22, 2007 Page 2.9.6 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 134 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (17) On outer fuselage skin aft of access door and in the cabin forward of access door (18) On access door -- Internal side Edition 1 -- June 22, 2007 Page 2.9.7 Rev.
  • Page 135 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (19) On ”pilot” door -- Internal side (if installed) (20) On emergency exit handle Marking on cover Marking on handle Page 2.9.8 Edition 1 -- June 22, 2007 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 136 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (21) On last step of stairs STAIRS MAX LOAD : ONE PERSON (22) On R.H. access door jamb DO NOT USE HAND RAIL TO RETRACT OR STOW STAIRS (23) On R.H. side at front seat level and on the first rear passengers masks container (R.H.
  • Page 137 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (25) On internal face of the oxygen cylinder service door (26) On the oxygen service door Edition 1 -- June 22, 2007 Page 2.9.10 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 138 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (27) On emergency locator transmitter inspection door (28) On the potty seat curtain (if installed), on pilot’s side CURTAIN MUST BE STOWED FOR TAKE- -OFF AND LANDING Post--MOD70--0557--25C (29) On the L.H. rear cargo compartment panel upper edge Pre--MOD70--0336--26 and Post--MOD70--0391--26D (30) On R.H.
  • Page 139 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (31) On the lower drawer of the R.H. cabinet Edition 1 -- June 22, 2007 Page 2.9.12 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...

  • Page 140: Emergency Procedures

    T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Page GENERAL 3.1.1 ..........REJECTED TAKEOFF PROCEDURE 3.2.1 .
  • Page 141 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 3.0.2 Rev. 2 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 142 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 143 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.1 GENERAL TABLE OF CONTENTS Page GENERAL 3.1.1 ........... Edition 1 -- June 22, 2007 Page 3.1.0B Rev.
  • Page 144 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.1 - - GENERAL The recommended procedures for different failures or emergency situations are provided in this Section. Emergency procedures associated with optional or particular equipment which require pilot’s operating handbook supplements are provided in Section 9 ”Supplements”.
  • Page 145 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 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 red messages indicating failures which require an immediate action from the pilot, and amber messages indicating failures or discrepancies which require an action as soon as practical.
  • Page 146 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 147 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.2 REJECTED TAKEOFF PROCEDURE TABLE OF CONTENTS Page REJECTED TAKEOFF PROCEDURE 3.2.1 ..... . Edition 1 -- June 22, 2007 Page 3.2.0B Rev.
  • Page 148 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.2 - - REJECTED TAKEOFF PROCEDURE Following an engine failure, refer to Chapter 3.3, Paragraph ”ENGINE FAILURE AT TAKEOFF BEFORE ROTATION”. For any other reason : 1 -- Power lever .
  • Page 149 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 3.2.2 REJECTED TAKEOFF PROCEDURE Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 150 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 151 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.3 ENGINE FAILURES TABLE OF CONTENTS Page 3.3.1 ENGINE FAILURE AT TAKEOFF BEFORE ROTATION ....3.3.2 ENGINE FAILURE AFTER ROTATION .
  • Page 152 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 - - ENGINE FAILURES ENGINE FAILURE AT TAKEOFF BEFORE ROTATION 1 -- Power lever ......... IDLE 2 -- Braking .
  • Page 153 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE FAILURE AFTER ROTATION (1/2) - If altitude does not allow to choose a favourable runway or field : Land straight ahead keeping flaps at TO and without changing landing gear position.
  • Page 154 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE FAILURE AFTER ROTATION (2/2) Before touch- -down : 6 -- Condition lever ........CUT OFF 7 -- Tank selector .
  • Page 155 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE FAILURE DURING FLIGHT 1 -- If AP engaged : “AP / TRIM DISC INT” push--button ....PRESSED 2 -- Power lever .
  • Page 156 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES OIL PRESSURE DROP “OIL PRESS” RED WARNING CAS MESSAGE “OIL PRESS” AMBER CAS MESSAGE Indicates that oil pressure is below 60 psi 1 -- Oil pressure indicator .
  • Page 157 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE REGULATION DISCREPANCY, POWER LOSS, POWER LEVER CONTROL LOSS (1/2) 1 -- If circumstances allow : Power lever ......... IDLE 2 -- Confirm engine still running 3 -- Tank selector...
  • Page 158 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE REGULATION DISCREPANCY, POWER LOSS, POWER LEVER CONTROL LOSS (2/2) 7 -- Perform a normal landing WITHOUT REVERSE 8 -- Braking ........AS REQUIRED If minimum power obtained is excessive : 1 -- Reduce airspeed by setting airplane in nose--up attitude at...
  • Page 159 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES GOVERNOR REGULATION CONTROL NOT OPERATING May indicate a rupture of the linkage 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.
  • Page 160 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES EXCESSIVE PROPELLER ROTATION SPEED Indicates : a propeller governor failure In that case, the propeller overspeed limiter will limit initially the rotation speed to 2100 RPM approximately. or a propeller governor and overspeed limiter failure In that case, only the torque limiter operates to limit the power.
  • Page 161 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES RED WARNING CAS MESSAGE “ITT” ON A - - During engine start : Indicates : ITT > 1000° C 1000° C > ITT > 870° C for more than 5 seconds 870°...
  • Page 162 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES RED WARNING CAS MESSAGE “TORQUE” ON Indicates that the torque is above 124.5 %. 1 -- Reduce power according to ”Engine Operation” tables -- Chapter 5.8.
  • Page 163 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE DOES NOT STOP ON GROUND If the engine does not stop when the condition lever is set to CUT OFF, proceed as follows : 1 -- ”AP TRIMS”...
  • Page 164 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 165 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.4 AIR START TABLE OF CONTENTS Page 3.4.1 AIR START ENVELOPE ......... . 3.4.2 AIR START WITH STARTER .
  • Page 166 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 - - AIR START AIR START ENVELOPE Air start may be attempted outside of the envelope. However, above 20000 ft or with Ng < 13 %, ITT tends to increase during start and prudence is recommended.
  • Page 167 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 -- AIR START AIR START WITH STARTER (1/2) CAUTION THE STARTER CANNOT OPERATE IF THE ”GENERATOR” SELECTOR IS ON ”ST- -BY” CAUTION IGNITION IS NOT AVAILABLE IF THE ”ESS BUS TIE” SWITCH IS KEPT ”EMER”...
  • Page 168 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 -- AIR START AIR START WITH STARTER (2/2) 10 -- ”IGNITION” switch ......AUTO or ON 11 -- ”STARTER”...
  • Page 169 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 3.4.4 AIR START Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 170 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 171 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.5 FIRE AND SMOKE TABLE OF CONTENTS Page 3.5.1 ENGINE FIRE ON GROUND ........3.5.1 CABIN FIRE ON GROUND .
  • Page 172 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 - - FIRE AND SMOKE ENGINE FIRE ON GROUND “ITT” Symptoms : ITT increasing, red warning CAS message smoke, ... 1 -- Power lever ......... IDLE 2 -- Condition lever .
  • Page 173 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE ENGINE FIRE IN FLIGHT “ITT” Symptoms : ITT increasing, red warning CAS message smoke, ... 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
  • Page 174 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 FIRE AND SMOKE Page 3.5.3 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 175 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT (1/2) If the origin is known : 1 -- Oxygen and goggles ....USE AS REQUIRED (pilot and passengers) 2 -- Defective equipment...
  • Page 176 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT (2/2) If smoke or fire persists : 5 -- ”SOURCE” selector ........6 -- ”GENERATOR”...
  • Page 177 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE SMOKE ELIMINATION 1 -- Smoke origin ........IDENTIFY 2 -- Oxygen and goggles .
  • Page 178 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 179 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.6 EMERGENCY DESCENTS TABLE OF CONTENTS Page 3.6.2 MAXIMUM RATE DESCENT ........3.6.3 MAXIMUM RANGE DESCENT .
  • Page 180 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 - - EMERGENCY DESCENTS Two types of descent are considered : 1 -- Engine running, maximum descent rate, if necessary The factors to be considered are : -- Cabin altitude and oxygen duration -- Electrical power endurance -- Distance to appropriate landing area...
  • Page 181 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 -- EMERGENCY DESCENTS MAXIMUM RATE DESCENT 1 -- Power lever ......... IDLE 2 -- Oxygen .
  • Page 182 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 -- EMERGENCY DESCENTS MAXIMUM RANGE DESCENT (1/2) 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
  • Page 183 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 -- EMERGENCY DESCENTS MAXIMUM RANGE DESCENT (2/2) -- ”PITOT R & STALL HTR” switch ..... -- “L.LDG / TAXI / R.LDG / PULSE SYST”...
  • Page 184 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 185 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.7 EMERGENCY LANDINGS TABLE OF CONTENTS Page 3.7.1 FORCED LANDING (ENGINE CUT OFF) ......3.7.2 TIRE BLOWOUT DURING LANDING .
  • Page 186 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 - - EMERGENCY LANDINGS FORCED LANDING (ENGINE CUT OFF) 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
  • Page 187 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS 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 procedure (Refer to Chapter 4.3)
  • Page 188 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 EMERGENCY LANDINGS Page 3.7.3 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 189 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR (1/2) 1 -- Ask control tower or another airplane to visually check landing gear position CAUTION IF ONE MAIN LANDING GEAR IS NOT DOWN, IT IS BETTER TO LAND WITH GEAR UP.
  • Page 190 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR (2/2) 11 -- Condition lever ........CUT OFF 12 -- Engine stop procedure .
  • Page 191 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH DEFECTIVE NOSE LANDING GEAR (DOWN UNLOCKED OR NOT DOWN) 1 -- Transfer passengers to the rear, if necessary 2 -- Approach ........Flaps TO Weight <...
  • Page 192 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH GEAR UP 1 -- Final approach ........Standard 2 -- Flaps .
  • Page 193 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITHOUT ELEVATOR CONTROL 1 -- Configuration ... LANDING GEAR DN - - FLAPS LDG 2 -- Airspeed .
  • Page 194 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH FLAPS MALFUNCTION For flaps deflections from “UP” to “TO” position : Proceed as for a normal landing, maintaining approach airspeed : Weight < 6250 lbs (2835 kg) Weight 6250 lbs (2835 kg) ≥...
  • Page 195 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS DITCHING 1 -- Landing gear ......... . In heavy swell with light wind, land parallel to the swell (rollers).
  • Page 196 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 197 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.8 FUEL SYSTEM TABLE OF CONTENTS Page “FUEL PRESS” 3.8.1 RED WARNING CAS MESSAGE ... . “AUX BOOST PMP ON” 3.8.2 AMBER WARNING CAS MESSAGE “FUEL LOW L”...
  • Page 198 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 - - FUEL SYSTEM RED WARNING CAS MESSAGE “FUEL PRESS” ON Indicates a fuel pressure drop at ”HP” engine pump inlet 1 -- Remaining fuel ........CHECK 2 -- Tank selector .
  • Page 199 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 -- FUEL SYSTEM AMBER WARNING CAS MESSAGE “AUX BOOST PMP ON” ON (Indication is normal if ”AUX BP” fuel switch is in ON position) If ”AUX BP” fuel switch is in AUTO position : 1 -- Reset to .
  • Page 200 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 -- FUEL SYSTEM AMBER WARNING CAS MESSAGE “FUEL LOW L” OR “FUEL LOW R” ON Indicates level drop in the corresponding tank 1 -- Corresponding gage ......CHECK 2 -- Check the other tank has been automatically selected If not :...
  • Page 201 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 3.8.4 FUEL SYSTEM Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 202 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 203 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.9 ELECTRICAL SYSTEM TABLE OF CONTENTS Page “BAT OFF” 3.9.1 AMBER WARNING CAS MESSAGE ....“MAIN GEN”...
  • Page 204 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 - - ELECTRICAL SYSTEM AMBER WARNING CAS MESSAGE “BAT OFF” ON Indicates that : -- the ”SOURCE” selector has been positioned on OFF or GPU or -- the battery plug is disconnected 1 -- If necessary .
  • Page 205 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING CAS MESSAGE “MAIN GEN” ON Indicates that ”GENERATOR” selector has been positioned to OFF or ST--BY, or main generator is cut off 1 -- If necessary .
  • Page 206 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING CAS MESSAGE “LOW VOLTAGE” ON normal functioning on ”MAIN GEN” 1 -- Voltmeter voltage ........CHECK 2 -- If voltage is <...
  • Page 207 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING CAS MESSAGE “LOW VOLTAGE” ON functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (1/3) Amber warning CAS messages “MAIN GEN and “LOW VOLTAGE” ON with ”GENERATOR”...
  • Page 208 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING CAS MESSAGE “LOW VOLTAGE” ON functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (2/3) If conditions allow : VMC and non icing conditions 10 -- If altitude ≥...
  • Page 209 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING CAS MESSAGE “LOW VOLTAGE” ON functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (3/3) -- ADC 2 breaker ........PULL -- TAS breaker .
  • Page 210 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Figure 3.9.1 (1/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- June 22, 2007 ELECTRICAL SYSTEM Page 3.9.7 Rev. 13 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 211 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Figure 3.9.1 (2/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- June 22, 2007 Page 3.9.8 ELECTRICAL SYSTEM Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 212 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM ”AVIONICS” MASTER SWITCH FAILURE In case of ”AVIONICS” MASTER switch misfunction, leading to the impossibility of energizing the radionavigation equipment : 1 -- ”AVIONICS MASTER” circuit breaker .
  • Page 213 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM Post--MOD70--0335--34 (ESI--2000) TOTAL LOSS OF ELECTRICAL POWER 1 -- Maintain aircraft control. 2 -- Follow display instruction to “PRESS ANY KEY FOR BATTERY POWER”. 3 -- Use the ESI--2000 for attitude, airspeed and/or altitude.
  • Page 214 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM ESI- -2000 FAILURES (1/2) 1 -- Battery indicator symbol meaning BATTERY DESCRIPTION INDICATOR Not shown Normal operation -- No information needs to be conveyed Green More than one hour of operation remains Amber...
  • Page 215 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM ESI- -2000 FAILURES (2/2) 4 -- Internal Battery Failure (red X’d battery indicator) in flight -- Remain clear of IMC. -- If in visual meteorological conditions : .
  • Page 216 3.10 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 217 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.10 PRESSURIZATION AND AIR CONDITIONING TABLE OF CONTENTS Page “CABIN DIFF PRESS” 3.10.1 RED WARNING CAS MESSAGE ..“CABIN ALTITUDE” 3.10.1 RED WARNING CAS MESSAGE .
  • Page 218 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 - - PRESSURIZATION AND AIR CONDITIONING RED WARNING CAS MESSAGE “CABIN DIFF PRESS” ON 1 -- Pressurization indicator ......CHECK ∆...
  • Page 219 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Post--MOD70--0407--00D (V15.11 GARMIN software) RED WARNING CAS MESSAGE “CABIN ALTITUDE” ON AND AMBER WARNING CAS MESSAGE “USE OXYGEN MASK” ON NOTE : “CABIN ALTITUDE” warning CAS message is followed by “USE OXYGEN MASK”...
  • Page 220 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Post--MOD70--0407--00D (V15.11 GARMIN software) and Pre--MOD70--0657--34 (EDM evolution patch) RED WARNING CAS MESSAGE “CABIN ALTITUDE” AND “EDM” ON AND AMBER WARNING CAS MESSAGE “USE OXYGEN MASK” ON NOTE : “CABIN ALTITUDE”...
  • Page 221 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Post--MOD70--0657--34 (EDM evolution patch) RED WARNING CAS MESSAGE “EDM” ON NOTE : ”EDM” warning CAS message may come on 45 s after ”CABIN ALTITUDE” warning CAS message and ”USE OXYGEN MASK” amber CAS message.
  • Page 222 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING CABIN NOT DEPRESSURIZED AFTER LANDING ∆P cabin > 0 1 -- ”DUMP” switch ....... . ACTUATED 2 -- ”BLEED”...
  • Page 223 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING AMBER WARNING CAS MESSAGE “BLEED OFF” ON Possibly due to : -- system malfunction -- “BLEED” switch on “OFF” position 1 -- Oxygen .
  • Page 224 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING RED WARNING CAS MESSAGE “BLEED TEMP” ON Indicates overheat of bleed air system. Normally this leads to BLEED cutoff and to “BLEED OFF” amber warning CAS message appearance. Should automatic cutoff occur or not : 1 -- If possible .
  • Page 225 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING RED WARNING CAS MESSAGE “DOOR” ON Indicates that one of the door latches of the access door or (if installed) of the ”pilot” door is not correctly locked On ground : -- Check the correct locking, as well as the latches position of the access door and (if installed) of the pilot door...
  • Page 226 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING Pre--MOD70--0335--34 (ESI--2000) AMBER WARNING CAS MESSAGE “VACUUM LOW” ON Suction gage indicator ....... . . CHECK Low vacuum may lead to misfunctioning of leading edge deicing, pressurization and gyroscopic vacuum--operated...
  • Page 227 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING DEFOG MALFUNCTION If moisture starts to quickly cover the inside of the windscreen with the distributor already positioned on ”DEFOG” : 1 -- ”AIR FLOW” distributor .
  • Page 228 3.11 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 229 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.11 LANDING GEAR AND FLAPS TABLE OF CONTENTS Page 3.11.1 LANDING GEAR RETRACTION DISCREPANCY ....3.11.2 LANDING GEAR EXTENSION DISCREPANCY .
  • Page 230 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 - - LANDING GEAR AND FLAPS LANDING GEAR RETRACTION DISCREPANCY NOTE : Symptoms have to be considered at the end of the sequence. A - - Symptoms : Steady red warning light ON and 0 to 3 green light(s) ON.
  • Page 231 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS LANDING GEAR EXTENSION DISCREPANCY NOTE : Symptoms have to be considered at the end of the sequence. - - Symptoms Steady red warning light ON and 0 to 3 green light(s) OFF. Red warning light flashing and 0 to 3 green light(s) OFF.
  • Page 232 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS EMERGENCY GEAR EXTENSION (1/2) NOTE : This procedure has to be followed in case of any discrepancy or doubt about the gear extension or retraction. Maintain IAS ≤...
  • Page 233 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS EMERGENCY GEAR EXTENSION (2/2) If landing gear does not lock (other than 3 green indicator lights illuminated) : 6 -- ”LDG GEAR” circuit breaker .
  • Page 234 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS RED WARNING CAS MESSAGE “FLAPS ASYM” ON Indicates a dissymmetry of flap deflection. This immediately stops the flap motor and prevents further operation of the flaps 1 -- ”FLAPS”...
  • Page 235 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 3.11.6 LANDING GEAR AND FLAPS Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 236 3.12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 237 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.12 DEICING SYSTEM TABLE OF CONTENTS Page 3.12.1 LEADING EDGES DEICING FAILURE ......3.12.1 PROPELLER DEICING FAILURE .
  • Page 238 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 - - 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”...
  • Page 239 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM INERTIAL SEPARATOR FAILURE “INERT SEP FAIL” Symptoms : -- Warning may appear “INERT SEP ON” -- Warning does not appear within 30 seconds following ”INERT SEP” switch setting ON -- Neither torque drop, nor increase of ITT observed during maneuver LEAVE icing conditions as soon as possible...
  • Page 240 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM WINDSHIELD MISTING OR INTERNAL ICING Symptoms : -- Mist or ice on windshield internal face 1 -- ”CABIN TEMP/° C” selector (pilot) Set to 12 o’clock position 2 -- ”AIR FLOW”...
  • Page 241 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM AMBER WARNING CAS MESSAGES “PITOT NO HT L”, “PITOT NO HT R” OR “STALL NO HEAT” ON Indicates a heating failure of the corresponding probe “PITOT NO HT L”...
  • Page 242 3.13 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 243 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3.13 MISCELLANEOUS TABLE OF CONTENTS Page 3.13.1 RUNAWAY OF ONE OF THE THREE ELECTRICAL TRIM TABS ..3.13.1 CRACK IN COCKPIT WINDOW OR WINDOW PANEL .
  • Page 244 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 - - MISCELLANEOUS RUNAWAY OF ONE OF THE THREE ELECTRICAL TRIM TABS 1 -- ”AP / DISC TRM INT” push button ..PRESSED AND HOLD The three trim tabs are disconnected and runaway stops 2 -- ”AP TRIMS”...
  • Page 245 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS EMERGENCY EXIT USE 1 -- Check that the anti--theft safety pin has been removed Pre--MOD70--0793--25 2 -- Remove the upholstery panel of the emergency exit. Pull it firmly through the access area to the opening handle (Refer to paragraph Emergency exit in Chapter 7.3).
  • Page 246 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS 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...
  • Page 247 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS TOTAL COMMUNICATION FAILURE 1 -- Refer to PARTICULAR TRANSPONDER USES procedures 2 -- Apply air traffic control procedures in case of communications failure : -- code 7700 during 1 minute, then -- code 7600 3 -- Try to restore communications by using all possible combinations of the headset, micro and loudspeaker...
  • Page 248 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS AUTOPILOT OR ELECTRIC PITCH TRIM MALFUNCTION 1 -- ”AP / TRIMS DISC INT” push--button ....PRESSED and HELD 2 -- ”AP TRIMS”...
  • Page 249 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS INADVERTENT SPINS (Voluntary spins are prohibited) In case of inadvertent spins 1 -- Control wheel ..... NEUTRAL : PITCH AND ROLL 2 -- Rudder...
  • Page 250 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS Post--MOD70--0407--00D (V15.11 GARMIN software) RED WARNING CAS MESSAGE ”AURAL WRN FAIL” ON Indicates that no aural warning alerts are available. CAUTION NO AURAL STALL WARNING. NO AURAL OVERSPEED WARNING.
  • Page 251 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS Post--MOD70--0407--00D (V15.11 GARMIN software) RED WARNING CAS MESSAGE ”AURAL WRN 1 CHNL” ON Indicates that one aural warning alerts channel is not available. 1 -- Both sides GMA’s SPKR button .
  • Page 252 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS Pre--MOD70--0407--00D (V15.11 GARMIN software) OXYGEN USE (1/2) WARNING SMOKING IS STRICTLY PROHIBITED ANY TIME OXYGEN SYSTEM IS USED. BEFORE USING OXYGEN, REMOVE ANY TRACE OF OIL, GREASE, SOAP AND OTHER FATTY SUBSTANCES (INCLUDING LIPSTICK, MAKE UP, ETC...) Front seats...
  • Page 253 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS OXYGEN USE (2/2) Passengers 1 -- Take a mask. 2 -- Uncoil tube totally. 3 -- Pull on the lanyard cord to take out the lanyard pin. 4 -- Put the mask on the face.
  • Page 254 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS Post--MOD70--0407--00D (V15.11 GARMIN software) OXYGEN USE (1/2) NOTE : With or without amber CAS message “USE OXYGEN MASK”. WARNING SMOKING IS STRICTLY PROHIBITED ANY TIME OXYGEN SYSTEM IS USED.
  • Page 255 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS OXYGEN USE (2/2) 7 -- Perform an emergency descent to the “En route” minimum altitude and, if possible, below 10000 ft. Passengers 1 -- Take a mask. 2 -- Uncoil tube totally.
  • Page 256 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS AIRSPEED INDICATING SYSTEM FAILURE Symptoms : erroneous indication in flight 1 -- ”PITOT L HTR” switch ......CHECK ON 2 -- ”PITOT R &...
  • Page 257 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS FLIGHT INTO SEVERE ICING CONDITIONS Severe icing conditions, particularly freezing rain and freezing drizzle, can be identified by : -- 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 area.
  • Page 258 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS DUAL GPS/SBAS FAILURE (AMBER ”DR” OR ”LOI”) ON HSI (1/2) LOSS OF GPS/SBAS NAVIGATION DATA When both GPS/SBAS receivers are inoperative or GPS navigation information is not available or invalid, the G1000 system will enter one of two modes: Dead Reckoning mode (DR) or Loss Of Integrity mode (LOI).
  • Page 259 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS DUAL GPS/SBAS FAILURE (AMBER ”DR” OR ”LOI”) ON HSI (2/2) If no Alternate Navigation Sources are available : Dead Reckoning (DR) Mode - - Active when the airplane is greater than 30 NM from the destination airport : 1 -- Navigation .
  • Page 260 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS GPS APPROACH ALARM LIMITS EXCEEDED During a GPS LPV, LNAV/VNAV, or LNAV+V approach, if the Horizontal or Vertical alarm limits are exceeded, the G1000 System will downgrade the approach.
  • Page 261 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS LEFT PFD FAILURE (1/2) Symptoms : -- Left screen is black -- AUTOPILOT is disconnected Lost systems : LEFT PFD -- AUTOPILOT (AP) and FLIGHT DIRECTOR (FD) -- COM 1 -- NAV 1 -- DME 1...
  • Page 262 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS LEFT PFD FAILURE (2/2) COM and NAVAIDS (selected on RIGHT PFD) : 1 -- “COM 2” frequency SELECTED and ACTIVATED 2 -- “COM 2 MIC + COM 2” key (audio control panel) SELECTED 3 -- RADIO CHECK with ATC PERFORMED...
  • Page 263 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS AHRS FAILURE (1/2) Symptoms : Autopilot is disconnected -- On PFD(S) : COMPARATOR WINDOW (WHITE ANNUNCIATION) : “HDG NO COMP” and/or “PIT NO COMP” and/or “ROL NO COMP” -- On PFD(S) : REVERSIONARY SENSOR WINDOW (YELLOW ANNUNCIATION) : “BOTH ON AHRS1”...
  • Page 264 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS AHRS FAILURE (2/2) If pilot wishes : 3 -- “FD” (default mode : “PITCH” and ROLL”) ENGAGED 4 -- “FD” (specifics modes : “HDG”, “NAV”, “ALT”, …) ENGAGED as DESIRED 5 -- Fly the aircraft manually to follow Command Bars If ALL white annunciations, (“HDG NO COMP”...
  • Page 265 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS ADC FAILURE Symptoms : -- On PFD(S) : COMPARATOR WINDOW (WHITE ANNUNCIATION) : “IAS NO COMP” and/or “ALT NO COMP” -- On PFD(S) : REVERSIONARY SENSOR WINDOW (YELLOW ANNUNCIATION) : “BOTH ON ADC1”...
  • Page 266 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 3.13.22 MISCELLANEOUS Rev. 13 PIM - DO NOT USE FOR FLIGHT OPERATIONS...

  • Page 267: Normal Procedures

    T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS Page GENERAL 4.1.1 ........... AIRSPEEDS FOR NORMAL OPERATION 4.2.1 .
  • Page 268 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page 4.4.34 MOTORING FOLLOWED BY AN ENGINE START ....4.4.37 AFTER STARTING ENGINE .
  • Page 269 EASA Approved 4.1 - - GENERAL This Section provides procedures for the conduct of normal operation of TBM 850 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.
  • Page 270 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 4.1.2 GENERAL Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 271 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.2 - - AIRSPEEDS FOR NORMAL OPERATION CONDITIONS : -- Takeoff weight : 6579 lbs 7394 lbs (2984 kg) (3354 kg) -- Landing weight : 6250 lbs 7024 lbs (2835 kg) (3186 kg) 1 Rotation airspeed (V...
  • Page 272 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 4.2.2 AIRSPEEDS FOR NORMAL OPERATION Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 273 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.3 - - CHECK- -LIST PROCEDURES PREFLIGHT INSPECTION (See Figure 4.3.1) IMPORTANT * During outside inspection, visually check inspection doors and airplane general condition. * In cold weather, remove even small accumulations of frost, ice or snow from wing, tail and control surfaces.
  • Page 274 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) Figure 4.3.1 -- PREFLIGHT INSPECTION Edition 1 -- June 22, 2007 Page 4.3.2 CHECK--LIST PROCEDURES Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 275 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) A - - INSIDE INSPECTIONS Cockpit 1 -- DE ICE SYSTEM panel -- All switches ........2 -- ELT .
  • Page 276 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 11 -- Landing gear emergency control -- Lever ........PULLED DOWN -- By--pass selector .
  • Page 277 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 23 -- EXT LIGHTS panel -- All switches ........24 -- Pilots ”OXYGEN”...
  • Page 278 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) From outside 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...
  • Page 279 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) WARNING DO NOT TOUCH PITOTS NOR STALL WARNING VANE. THEY COULD BE HOT ENOUGH TO BURN SKIN 42 -- ”AVIONICS” MASTER switch ......43 -- ”SOURCE”...
  • Page 280 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) B - - AIRPLANE OUTSIDE L.H. wing III 1 -- Flap ..........CHECK (Condition / Play) 2 -- Aileron and trim / Spoiler...
  • Page 281 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) Fuselage forward section IV 1 -- Forward compartment -- Inside ........CONTROLLED -- Door .
  • Page 282 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 9 -- Nose gear -- Landing light / shock absorber / doors / tire / wheel well ....... . CHECK 10 -- R.H.
  • Page 283 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 11 -- Aileron / spoiler ........CHECK (Condition / Free movement / Deflection) 12 -- Flap...
  • Page 284 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 9 -- Rudder and trim ........CHECK (Condition / Trim position) 10 -- Static dischargers...
  • Page 285 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (1/3) CAUTION ”BLEED” SWITCH SET TO “AUTO” MAY CAUSE OVERTEMPERATURE OR ABNORMAL ACCELERATION AT START CAUTION MAKE SURE THAT ”MAN OVRD” CONTROL IS OFF TO AVOID OVERTEMPERATURE RISKS AT START 1 -- Preflight inspection .
  • Page 286 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (2/3) 8 -- R.H and L.H. pedals ......ADJUSTED 9 -- Belts and harnesses (Pilot and passengers) .
  • Page 287 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (3/3) 24 -- CAS display -- Access door and (if installed) ”pilot” door “DOOR” WARNING CAS MESSAGE -- Oxygen emergency system “OXYGEN” WARNING CAS MESSAGE -- Vacuum system “VACUUM LOW”...
  • Page 288 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (1/5) CAUTION BEFORE SELECTING SOURCE, CHECK : 1 - - ”IGNITION” switch ..... . . AUTO or OFF 2 - - ”STARTER”...
  • Page 289 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (2/5) 7 -- Flaps ..........WARNING IT IS PROHIBITED TO SET FLAPS CONTROL LEVER TO “850”...
  • Page 290 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (3/5) 11 -- “STARTER” switch ........Check Ng >...
  • Page 291 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (4/5) CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO ”LO / IDLE” THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE, OVERTEMPERATURE INDICATION APPEARS (MAX.
  • Page 292 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved STARTING ENGINE USING AIRPLANE POWER (5/5) ENGINE START panel -- ”IGNITION” switch ........AUTO -- ”STARTER”...
  • Page 293 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (1/5) 1 -- GPU ........CONNECTED CAUTION BEFORE SELECTING SOURCE, CHECK :...
  • Page 294 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (2/5) 8 -- Flaps ..........WARNING IT IS PROHIBITED TO SET FLAPS CONTROL LEVER TO “850”...
  • Page 295 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (3/5) 12 -- ”SOURCE” selector ........“BAT OFF”...
  • Page 296 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (4/5) CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO ”LO / IDLE” THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE, OVERTEMPERATURE INDICATION APPEARS (MAX.
  • Page 297 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved STARTING ENGINE USING EXTERNAL POWER (5/5) ENGINE START panel -- ”IGNITION” switch ........AUTO -- ”STARTER”...
  • Page 298 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING (1/2) 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”...
  • Page 299 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING (2/2) 3 -- ”IGNITION” switch ........“IGNITION”...
  • Page 300 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (1/2) Within starter operating limits (continuous max. 1 minute), it is possible to initiate a starting procedure from a motoring procedure. 1 -- Engine controls -- ”MAN OVRD”...
  • Page 301 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (2/2) 5 -- After 15 seconds : -- ”IGNITION” switch ....... AUTO -- Ng .
  • Page 302 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES AFTER STARTING ENGINE (1/3) 1 -- ”GENERATOR” selector -- On ”MAIN” ....Voltage and current checked when current ≤...
  • Page 303 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES AFTER STARTING ENGINE (2/3) 10 -- Stand--by instruments ......CHECKED -- Suction gage CHECKED...
  • Page 304 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES AFTER STARTING ENGINE (3/3) Increase power so as to get Ng ≥ 80% to check AIRFRAME DE ICE -- ”AIRFRAME DE ICE” switch ......Visually check functioning of deicer boots during 1 total cycle and illumination of the two green lights located above the switch...
  • Page 305 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES IN- -FLIGHT AVAILABLE OXYGEN QUANTITY Oxygen pressure ........Read Outside air temperature (OAT) .
  • Page 306 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAXIING 1 -- ”TAXI” light ......... . . 2 -- ”INERT SEP”...
  • Page 307 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE TAKEOFF (1/2) 1 -- Parking brake ........“PARK BRAKE”...
  • Page 308 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE TAKEOFF (2/2) 8 -- Pilot’s / Passengers’ belts ......CHECK -- Passengers’...
  • Page 309 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAKEOFF (1/2) WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.5, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS”...
  • Page 310 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAKEOFF (2/2) 7 -- Brakes ........RELEASED 8 -- Power lever .
  • Page 311 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES CLIMB 1 -- Power lever ......ADJUST according to engine operation tables - - Chapter 5.8 or to MXCL indicator on the PFDs...
  • Page 312 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES CRUISE 1 -- Power lever ......ADJUST according to engine operation tables - - Chapter 5.8 or to Cruise index on the PFDs...
  • Page 313 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES FLAP CONTROL TRANSITION FROM “UP” TO “850” 1 -- Flaps ........CHECKED UP 2 -- Propeller RPM .
  • Page 314 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES DESCENT 1 -- Flaps ..........2 -- Altimeter settings .
  • Page 315 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE LANDING Long final 1 -- Altimeters ........CHECK 2 -- Fuel -- Gages...
  • Page 316 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES LANDING 1 -- Power lever ......... IDLE After wheels touch 2 -- Reverse...
  • Page 317 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES GO- -AROUND 1 -- GO AROUND push--button ......PUSHED 2 -- Simultaneously -- Power lever...
  • Page 318 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TOUCH AND GO After wheels touch 1 -- Flaps ..........2 -- Elevator trim .
  • Page 319 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES AFTER LANDING RUNWAY CLEAR -- AIRPLANE STOPPED 1 -- DE ICE SYSTEM panel -- ”AIRFRAME DE ICE” switch ......-- ”PROP DE ICE”...
  • Page 320 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (1/2) 1 -- Parking brake ........“PARK BRAKE”...
  • Page 321 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (2/2) 13 -- Fuel -- ”AUX BP” switch ........-- ”FUEL SEL”...
  • Page 322 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 4.3.50 CHECK--LIST PROCEDURES Rev. 13 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 323 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.4 - - AMPLIFIED PROCEDURES PREFLIGHT INSPECTION A - - INSIDE INSPECTIONS Cockpit 1 -- DE ICE SYSTEM panel -- All switches ........2 -- ELT .
  • Page 324 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 9 -- Flaps control ......... . 10 -- Fuel tank selector .
  • Page 325 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 20 -- ELECTRIC POWER panel -- CRASH lever ........-- ”GENERATOR”...
  • Page 326 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 31 -- Voltage ......... . CHECK -- BAT .
  • Page 327 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 35 -- ”AVIONICS” MASTER switch ......START 36 -- CAS display .
  • Page 328 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 42 -- ”AVIONICS” MASTER switch ......43 -- ”SOURCE”...
  • Page 329 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) B - - AIRPLANE OUTSIDE The preflight inspection described in Figure 4.3.1 is recommended before each flight. NOTE : If a preflight inspection is performed, just after the engine shut- -off, be careful because the leading edge of engine air inlet, as well as exhaust stubs may be very hot.
  • Page 330 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 3 -- Trailing edge static discharger ..... CHECK (Condition / Attachment) 4 -- Wing tip / nav.
  • Page 331 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 11 -- Fuel tank drain (two on each wing) ....DRAIN (Fuel free of water and contamination) In case of water in fuel system, drain it carefully using the four drain...
  • Page 332 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 3 -- Fuel circuit drain ........DRAIN (Fuel free of water and contamination) Filter contamination indicator...
  • Page 333 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 8 -- Propeller and spinner ......CHECK (No nicks, cracks or oil leaks / Attachment) In case of operation from contaminated runways, it is necessary to...
  • Page 334 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 3 -- Wing deicer boots ....... . CHECK (Condition / Attachment) 4 -- Stall warning...
  • Page 335 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) Fuselage rear section / Empennages VI Check that outside handle of emergency exit is flush with door skin. 1 -- ELT ..........-- ELT door .
  • Page 336 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 9 -- Rudder and trim ........CHECK (Condition / Trim position) 10 -- Static dischargers...
  • Page 337 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (1/4) Check that the weight and balance are within the correct limits. Brief passengers about use of seat belts and the emergency oxygen system, as well as opening the access door and the emergency exit.
  • Page 338 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (2/4) 7 -- Pilot seat and R.H. front seat (if occupied) -- Height adjustment ......Maximum UP -- Fore and aft adjustment .
  • Page 339 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (3/4) 16 -- ”IGNITION” switch ......AUTO or OFF The ”IGNITION”...
  • Page 340 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (4/4) -- Vacuum system “VACUUM LOW” CAUTION CAS MESSAGE If not, recycle power to PFD by setting the “AVIONICS MASTER” switch to “OFF” then “START”. If “VACUUM LOW” CAS message is still not ON, then do not take off and check vacuum system.
  • Page 341 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (1/6) CAUTION BEFORE SELECTING SOURCE, CHECK : 1 - - ”IGNITION” switch ..... . . AUTO or OFF 2 - - ”STARTER”...
  • Page 342 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (2/6) 7 -- Flaps ..........WARNING IT IS PROHIBITED TO SET FLAPS CONTROL LEVER TO “850”...
  • Page 343 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (3/6) Monitor increase of : ....(max. ITT : ± 870°C for 20 seconds max. ±...
  • Page 344 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (4/6) -- Ng The start sequence must be timed to ensure starter limits are not exceeded. Lengthy operation of the starter results in excessive temperature of the engine : -- If Ng does not reach 30 % within 30 seconds, after the starter is selected ON, abort the start.
  • Page 345 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (5/6) CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO ”LO / IDLE” THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE, OVERTEMPERATURE INDICATION APPEARS (MAX.
  • Page 346 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved STARTING ENGINE USING AIRPLANE POWER (6/6) ENGINE START panel -- ”IGNITION” switch ........AUTO -- ”STARTER”...
  • Page 347 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (1/7) 1 -- GPU ........CONNECTED CAUTION BEFORE SELECTING SOURCE, CHECK :...
  • Page 348 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (2/7) 8 -- Flaps ..........WARNING IT IS PROHIBITED TO SET FLAPS CONTROL LEVER TO “850”...
  • Page 349 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (3/7) Monitor increase of : ....(max.
  • Page 350 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (4/7) -- Ng The start sequence must be timed to ensure starter limits are not exceeded. Lengthy operation of the starter results in excessive temperature of the engine : -- If Ng does not reach 30 % within 30 seconds, after the starter is selected ON, abort the start.
  • Page 351 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (5/7) 19 -- Generator “MAIN GEN” WARNING CAS MESSAGE RESET if necessary ”MAIN GEN” CAS message normally goes out, as soon as ”STARTER”...
  • Page 352 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (6/7) CAUTION IF ENGINE STAGNATES, INTERRUPT STARTING PROCEDURE : Condition lever ........CUT OFF ”IGNITION”...
  • Page 353 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (7/7) 50 % -- ”STARTER” switch ........“STARTER”...
  • Page 354 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING (1/2) To drain fuel accumulated inside the combustion chamber, a motoring procedure is required following an aborted start. A 15--second dry motoring run is sufficient to clear any fuel pooled in the engine.
  • Page 355 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING (2/2) 2 -- Fuel Tank selector ........L or R ”AUX BP”...
  • Page 356 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (1/3) Amplified procedures stated in starting engine sequences using airplane power or with GPU are also to be applied to hereunder procedure.
  • Page 357 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (2/3) 5 -- After 15 seconds : ”IGNITION” switch ....... . . AUTO .
  • Page 358 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (3/3) 10 -- FUEL panel ”AUX BP” switch ........AUTO “AUX BOOST PMP ON”...
  • Page 359 Detailed control procedures of G1000 avionics system are described in the ”GARMIN” G1000 Integrated Flight Deck Pilot’s Guide for the Socata TBM 850. Brightness ........
  • Page 360 CHECK Detailed control procedures of autopilot and electrical pitch trim are described in the ”GARMIN” G1000 Integrated Flight Deck Pilot’s Guide for the Socata TBM 850. (See next page for the other trims) Edition 1 -- June 22, 2007 Page 4.4.38 AMPLIFIED PROCEDURES Rev.
  • Page 361 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (3/4) Pitch trim ......UP / DN, then ADJUSTED Adjust the indicator in green range (graduated from 12 to 37 %).
  • Page 362 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (4/4) Increase power so as to get Ng ≥ 80% to check AIRFRAME DE ICE Theoretically, necessary air bleed to inflate wing and empennage leading edges, as well as depression necessary to their deflation are sufficient when power lever is positioned on IDLE.
  • Page 363 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES IN- -FLIGHT AVAILABLE OXYGEN QUANTITY Oxygen pressure ........Read Outside air temperature (OAT) .
  • Page 364 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAXIING (1/2) 1 -- ”TAXI” light ......... . 2 -- ”INERT SEP”...
  • Page 365 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAXIING (2/2) 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 ”INERT SEP”...
  • Page 366 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (1/3) 1 -- Parking brake ........“PARK BRAKE”...
  • Page 367 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (2/3) If icing conditions are foreseen, refer to Chapter 4.5 ”PARTICULAR PROCEDURES” of this Section, Paragraph “Flight into known icing conditions”. 6 -- Flight controls .
  • Page 368 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (3/3) 12 -- Flight instruments ......CHECKED Altimeter setting .
  • Page 369 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (1/4) WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.5, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS”...
  • Page 370 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (2/4) 6 -- PROP O’ SPEED GOVERNOR TEST Increase power until propeller RPM reaches 1900 RPM PROP O’ SPEED ....TEST : Maintain engaged Observe that propeller RPM decreases by 50 to 250 RPM PROP O’...
  • Page 371 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (3/4) 12 -- Landing gear control ..(IAS < 128 KIAS) ... . . During the sequence : The red warning light flashes ;...
  • Page 372 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (4/4) 16 -- Power lever ....... . TRQ =121.4 % 17 -- Climb speed (recommended) .
  • Page 373 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CLIMB (1/2) 1 -- Power lever ......ADJUST according to engine operation tables - - Chapter 5.8 or to MXCL indicator on the PFDs...
  • Page 374 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CLIMB (2/2) 3 -- ECS panel Cabin pressure control panel ..Cruise altitude + 1000 feet Pressurization ........CHECK ”CABIN TEMP/°...
  • Page 375 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CRUISE (1/2) 1 -- Power lever ......ADJUST according to engine operation tables - - Chapter 5.8 or to Cruise index on the PFD’s...
  • Page 376 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CRUISE (2/2) 2 -- Pressurization ........CHECK 3 -- Fuel Gages...
  • Page 377 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES FLAP CONTROL TRANSITION FROM “UP” TO “850” 1 -- Flaps ........CHECKED UP 2 -- Propeller RPM .
  • Page 378 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES FLAP CONTROL TRANSITION FROM “850” TO “UP” 1 -- Altitude ......At or above 1500 ft AGL In case of air leak between the solenoïd valve and the torque limiter, the available torque might be below 100 %.
  • Page 379 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES DESCENT (1/2) 1 -- Flaps ..........2 -- Altimeter settings .
  • Page 380 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES DESCENT (2/2) 6 -- Windshield misting protection system ... . As required Prior to descent in moist conditions, turn ”AIR FLOW” distributor in DEFOG section and set “WINDSHIELD”...
  • Page 381 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE LANDING (1/2) Long final 1 -- Altimeters ........CHECK 2 -- Fuel Gages...
  • Page 382 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE LANDING (2/2) Short final 8 -- Autopilot ........DISCONNECT 9 -- Flaps .
  • Page 383 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES LANDING 1 -- Power lever ......... IDLE Avoid three--point landings.
  • Page 384 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES GO- -AROUND (1/2) 1 -- GO AROUND push--button ......PUSHED It provides the moving up of the flight director to + 7°...
  • Page 385 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES GO- -AROUND (2/2) If IAS is at or above 115 KIAS : 8 -- Flaps ..........In case of air leak between the solenoïd valve and the torque limiter, the available torque might be below 100 %.
  • Page 386 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TOUCH AND GO After wheels touch 1 -- Flaps ..........Check that flaps have well reached the TO position before increasing power.
  • Page 387 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER LANDING RUNWAY CLEAR -- AIRPLANE STOPPED 1 -- DE ICE SYSTEM panel -- ”AIRFRAME DE ICE” switch ......-- ”PROP DE ICE”...
  • Page 388 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (1/3) 1 -- Parking brake ........“PARK BRAKE”...
  • Page 389 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (2/3) 8 -- Condition lever ........CUT OFF 9 -- ”INERT SEP”...
  • Page 390 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (3/3) Post--MOD70--0335--34 (ESI--2000) -- 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 : .
  • Page 391 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.5 - - PARTICULAR PROCEDURES REMARK : The procedures and procedure elements given in this Chapter ”PARTICULAR PROCEDURES” supplement the normal procedures or complete certain elements of the normal procedures described in Chapter(s) 4.3 and/or 4.4.
  • Page 392 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (2/5) Boots are automatically cycling at the optimum time to assure proper ice removal. Correct operation of the system can be checked observing the corresponding green advisory light illumination at each boot inflation impulse.
  • Page 393 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (3/5) CAUTION SHOULD CONDITIONS REQUIRE IT, APPLY THESE DIRECTIVES FROM BEGINNING OF TAXI ONWARDS CAUTION DO NOT OPERATE THE INERTIAL SEPARATOR IF THE AIRSPEED EXCEEDS 200 KIAS.
  • Page 394 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (4/5) 3 -- Procedures for holding, approach and landing in icing conditions : -- Minimum recommended speeds are : Weight < 6579 lbs (2984 kg) >...
  • Page 395 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (5/5) Rate of climb values with ice accumulation on the unprotected surfaces are to be decreased by 10 %. Cruise speeds may be decreased by 10 %, if cruise power is not changed, or more, if cruise power setting should be decreased due to the additional inertial separator limitations (ITT limitation).
  • Page 396 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO SEVERE ICING CONDITIONS (1/2) THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN- -FLIGHT ICING : -- Visible rain at temperatures below 0°C ambient air temperature, -- Droplets that splash or splatter on impact at temperatures below 0°C ambient air temperature.
  • Page 397 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO SEVERE ICING CONDITIONS (2/2) 6 -- Do not extend flaps when holding in icing conditions. Operation with flaps extended can result in a reduced wing angle--of--attack, with the possibility of ice forming on the upper surface further aft on the wing than normal, possibly aft of the protected area.
  • Page 398 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT UNDER HEAVY PRECIPITATIONS 1 -- ”IGNITION” switch ........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.
  • Page 399 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW (1/2) Refer if required to paragraph ”UTILIZATION BY COLD WEATHER AND VERY COLD WEATHER”. Preflight inspection 1 -- Remove any snow or ice from the wings, stabilizers and movable surfaces, landing gear wells and gear doors, as well as flap tracks,...
  • Page 400 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW (2/2) Takeoff 1 -- Lightly lift up nose wheel during takeoff run in order to reduce the forward resistance due to snow accumulation against the wheel.
  • Page 401 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS (1/2) Refer if required to paragraph ”UTILIZATION BY COLD WEATHER AND VERY COLD WEATHER”. Preflight inspection 1 -- Remove any snow or ice from the wings, stabilizers and movable surfaces, landing gear wells and gear doors, as well as flap tracks, actuators and their fairings.
  • Page 402 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS (2/2) Landing After wheel touch 1 -- Use reverse only if necessary and very progressively by monitoring the airplane behaviour.
  • Page 403 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (1/10) REMARK : The procedures hereafter supplement the normal procedures for the airplane use when operating under temperatures between 0˚C and - - 40˚C on ground.
  • Page 404 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (2/10) ENVELOPE 1 The procedures hereafter supplement the normal procedures for the airplane use when operating in the ”envelope 1”...
  • Page 405 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (3/10) Taxiing / Before takeoff / Takeoff 1 -- On ”DE--ICE SYSTEM”...
  • Page 406 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0° C TO - - 25° C) AND VERY COLD WEATHER (- - 25° C TO - - 40° C) (4/10) ENVELOPE 2 The procedures hereafter supplement or replace the normal procedures for the airplane use when operating in the ”envelope 2”...
  • Page 407 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (5/10) 5 -- Remove chocks and / or release ties from the airplane. 6 -- Check the free deflection of the flight controls and of the elevator trim.
  • Page 408 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0° C TO - - 25° C) AND VERY COLD WEATHER (- - 25° C TO - - 40° C) (6/10) 3 -- Engine controls -- ”MAN OVRD”...
  • Page 409 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0° C TO - - 25° C) AND VERY COLD WEATHER (- - 25° C TO - - 40° C) (7/10) 13 % -- Condition lever .
  • Page 410 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (8/10) After starting the engine 1 -- On ”ECS”...
  • Page 411 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (9/10) ENVELOPE 3 The procedures defined for the ”envelope 2” are also applicable for the ”envelope 3”.
  • Page 412 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (10/10) Taxiing / Before takeoff / Takeoff Apply procedures defined for Envelope 1.
  • Page 413 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES LANDING PROCEDURE WITH STRONG HEADWIND OR CROSSWIND (1/2) If landing must be performed with strong headwind or crosswind, increase approach speed by the greatest of these 2 following values : WIND DOWN −...
  • Page 414 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES LANDING PROCEDURE WITH STRONG HEADWIND OR CROSSWIND (2/2) Do not try to stabilize the airplane by pushing down the elevator control just after the touch ; this operation may provide pitch oscillations while increasing the yaw movement to the wind.
  • Page 415 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON GRASS RUNWAY CAUTION THE SMALL WHEELS OF THE AIRPLANE AND ITS WEIGHT MAY LEAD IT TO SINK IN SOPPY OR LOOSE GROUND Before planning the landing, ensure that the field is hard, smooth and dry enough.
  • Page 416 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES Post--GARMIN software version 12.01 or any later GPS NAVIGATION Set up conditions -- Verify if the data base is current. -- Verify that altitude data is valid for the GPS prior to flight. Check the systems availability requirements in the Table 2.6.1 in Section 2.6 ”GNSS (GPS/SBAS) navigation equipment approvals”, depending on the planned navigation performance.
  • Page 417 SECTION 4 T B M NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES Pre--GARMIN software version 12.01 GPS NAVIGATION (1/2) Set up conditions -- Verify if the data base is current. -- Verify that altitude data is valid for the GPS prior to flight. -- In case of B--RNAV use : During the preflight planning phase, the availability of GPS integrity (RAIM) shall be confirmed for the intended flight (route and time).
  • Page 418 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES GPS NAVIGATION (2/2) Non precision approach with coupled autopilot Coupling with autopilot may be made in “NAV” mode, except in the following cases : -- holding pattern, -- landing pattern turn, -- interrupted approach, which have to be made in “HDG”...

  • Page 419: Performance

    T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK SECTION 5 PERFORMANCE TABLE OF CONTENTS Page GENERAL 5.1.1 ..........NOISE LEVEL 5.2.1 .
  • Page 420 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page MXCL -- TIME, CONSUMPTION AND CLIMB 5.10.5 DISTANCE (IAS = 130 KIAS) ........MXCL -- TIME, CONSUMPTION AND CLIMB 5.10.8 DISTANCE (IAS = 160 KIAS)
  • Page 421 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK SECTION 5 PERFORMANCE TABLE OF CONTENTS Page GENERAL 5.1.1 ..........NOISE LEVEL 5.2.1 .
  • Page 422 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page 5.10.4 700 SHP -- CLIMB SPEEDS (IAS = 160 KIAS) ..... . MXCL -- TIME, CONSUMPTION AND CLIMB 5.10.5 DISTANCE (IAS = 130 KIAS)
  • Page 423 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 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 424 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.1.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 425 Vol. 1, 3rd edition, Amdt 8 85 dB(A) 79.2 dB(A) Chapter 10, Appendix 6 Approved noise levels for TBM 850 are stated in EASA.A.010 Type Certificate Data Sheet. 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 airport.
  • Page 426 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.2.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 427 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.3 - - AIRSPEED CALIBRATION NOTE : Indicated airspeeds (IAS) : instrument error supposed to be null (power configuration for cruise condition flight). FLAPS UP FLAPS TO FLAPS LDG LDG GR UP LDG GR DN LDG GR DN...
  • Page 428 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved FLAPS UP FLAPS TO FLAPS LDG LDG GR UP LDG GR DN LDG GR DN KIAS KCAS KIAS KCAS KIAS KCAS MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS Figure 5.3.2 -- ALTERNATE STATIC SOURCE (BLEED AUTO)
  • Page 429 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.4 - - CABIN PRESSURIZATION ENVELOPE NOTE : The cabin pressurization envelope below characterizes the cabin altitude that could be sustained by the fuselage at different flight levels. The curve shows the minimum cabin altitude as a function of flight level, corresponding to the maximum differential pressure.
  • Page 430 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.4.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 431 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.5 - - SAT - - OAT CONVERSIONS NOTE : These indicated temperatures are available for stabilized cruise at normal operating power. ISA -- 20°C ISA -- 10°C ISA + 10°C ISA + 20°C Pressure altitude...
  • Page 432 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.5.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 433 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.6 - - STALL SPEEDS CONFIG. BANK AIR-- FLIGHT 0° 30° 45° 60° PLANE IDLE WEIGHT WEIGHT Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 4850 lbs (2200 kg) 5512 lbs (2500 kg) 6579 lbs...
  • Page 434 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.6.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 435 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.7 - - WIND COMPONENTS EXAMPLE : Angle between wind direction and flight path 50 ° Headwind 8 kts Crosswind 10 kts Wind speed 13 kts Figure 5.7.1 -- WIND COMPONENTS Edition 1 -- June 22, 2007 Page 5.7.1 Rev.
  • Page 436 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.7.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 437 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.8 - - ENGINE OPERATION The following tables or/and the optimum torque indicator must be used during normal operation of the airplane. IMPORTANT It is the responsibility of the Operator to make sure that the required version of Garmin System Software is installed prior to using the hereafter Engine Operation tables.
  • Page 438 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CAUTION THE TRQ SETTING MUST NEVER EXCEED 121.4 % FOR NP = 2000 RPM. WHEN SETTING TRQ, NG MUST NEVER EXCEED 104 % REMARK : The engine ITT limit at 840°C during continuous operation may be used in case of operational need.
  • Page 439 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum climb power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 440 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum climb power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 441 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Climb at 700 SHP power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 442 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Climb at 700 SHP power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 443 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 10 % above FL 200 NOTE : Use preferably recommended engine power.
  • Page 444 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 10 % above FL 200 NOTE : Use preferably recommended engine power.
  • Page 445 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 12 % above FL 160 NOTE : This table is not valid if inertial separator and/or BLEED HI msg are ON.
  • Page 446 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 12 % above FL 160 NOTE : This table is not valid if inertial separator and/or BLEED HI msg are ON.
  • Page 447 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.8 - - ENGINE OPERATION The following tables or/and the optimum torque indicator must be used during normal operation of the airplane. The following conditions are given : -- Np = 2000 RPM, -- BLEED switch on AUTO.
  • Page 448 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum climb power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 449 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum climb power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 450 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Climb at 700 SHP power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 451 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Climb at 700 SHP power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 6 % NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed.
  • Page 452 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 10 % above FL 200 NOTE : Use preferably recommended engine power.
  • Page 453 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 10 % above FL 200 NOTE : Use preferably recommended engine power.
  • Page 454 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise power (FL ≤ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 12 % above FL 160 NOTE : This table is not valid if inertial separator and/or BLEED HI msg are ON.
  • Page 455 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise power (FL ≥ 200) Conditions : represents the ISA conditions at the flight level Landing gear and flaps UP Np = 2000 RPM -- BLEED switch on AUTO If BLEED HI msg ON, reduce TRQ by 12 % above FL 160 NOTE : This table is not valid if inertial separator and/or BLEED HI msg are ON.
  • Page 456 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 5.8.10 Edition 1 -- June 22, 2007 Rev. 7 PRE- -GARMIN SOFTWARE VERSION 9.14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 457 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.9 - - TAKEOFF DISTANCES WEIGHT : 5512 lbs (2500 kg) Associated conditions -- Landing gear DN and flaps TO -- 15° of attitude -- TRQ = 100 % -- Np = 2000 RPM -- BLEED switch on AUTO -- Hard, dry and level runway -- GR = Ground roll (in ft)
  • Page 458 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved WEIGHT : 6579 lbs (2984 kg) Associated conditions -- Landing gear DN and flaps TO -- 15° of attitude -- TRQ = 100 % -- Np = 2000 RPM -- BLEED switch on AUTO -- Hard, dry and level runway -- GR = Ground roll (in ft) -- D...
  • Page 459 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved WEIGHT : 7394 lbs (3354 kg) Associated conditions -- Landing gear DN and flaps TO -- 12°5 of attitude -- TRQ = 100 % -- Np = 2000 RPM -- BLEED switch on AUTO -- Hard, dry and level runway -- GR = Ground roll (in ft) -- D...
  • Page 460 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.9.4 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 461 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.10 - - CLIMB PERFORMANCE MXCL - - SPEEDS (IAS = 130 KIAS) Conditions : Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 130 KIAS -- BLEED switch on AUTO and BLEED HI msg OFF RATE OF CLIMB (ft/min) Pressure Airplane...
  • Page 462 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK MXCL - - SPEEDS (IAS = 160 KIAS) Conditions : Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft, then -- 2 KIAS/1000 ft BLEED switch on AUTO and BLEED HI msg OFF RATE OF CLIMB (ft/min) Pressure...
  • Page 463 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 700 SHP - - CLIMB SPEEDS (IAS = 130 KIAS) Conditions : 700 SHP climb power Landing gear and flaps UP IAS = 130 KIAS -- BLEED switch on AUTO and BLEED HI msg OFF RATE OF CLIMB (ft/min) Pressure Airplane...
  • Page 464 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 700 SHP - - CLIMB SPEEDS (IAS = 160 KIAS) Conditions : 700 SHP climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft, then -- 2 KIAS/1000 ft BLEED switch on AUTO and BLEED HI msg OFF RATE OF CLIMB (ft/min) Pressure...
  • Page 465 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK MXCL - - TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS ) Conditions : ISA - 20°C Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 466 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK MXCL - - TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS) Conditions : Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 467 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK MXCL - - TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS) Conditions : ° ISA + 20 Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 468 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK MXCL - - TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA - 20°C Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 2 KIAS / 1000 ft then Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 469 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK MXCL - - TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 2 KIAS / 1000 ft then Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 470 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK MXCL - - TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : + 20°C Maximum climb power (850 SHP) Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 2 KIAS / 1000 ft then Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 471 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TIME, CONSUMPTION CLIMB DISTANCE (IAS = 130 KIAS) Conditions : ISA - 20°C 700 SHP climb power Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 472 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TIME, CONSUMPTION CLIMB DISTANCE (IAS = 130 KIAS) Conditions : ISA 700 SHP climb power Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 473 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TIME, CONSUMPTION CLIMB DISTANCE (IAS = 130 KIAS) Conditions : + 20°C 700 SHP climb power Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 474 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TIME, CONSUMPTION CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA - 20°C 700 SHP climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 2 KIAS / 1000 ft then Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 475 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TIME, CONSUMPTION CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA 700 SHP climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 2 KIAS / 1000 ft then Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 476 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TIME, CONSUMPTION CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA + 20°C 700 SHP climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 2 KIAS / 1000 ft then Np = 2000 RPM -- BLEED switch on AUTO NOTE : Time, consumption and distance from the 50 ft If BLEED HI msg ON, reduce TRQ by 6 %.
  • Page 477 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE AFTER GO- -AROUND Conditions : 700 SHP climb power Landing gear DN and flaps LDG IAS = 90 KIAS RATE OF CLIMB (ft/min) Pressure Airplane altitude weight (feet) -- 35°C -- 20°C -- 10°C + 10°C...
  • Page 478 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE - - FLAPS TO Conditions : 700 SHP climb power Landing gear UP and flaps TO IAS = 110 KIAS RATE OF CLIMB (ft/min) Pressure Airplane altitude weight (feet) -- 35°C -- 20°C -- 10°C...
  • Page 479 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.11 - - CRUISE PERFORMANCE Figure 5.11.1 -- CRUISE PERFORMANCE (Maximum cruise) Edition 1 -- June 22, 2007 Page 5.11.1A Rev. 7 POST- -GARMIN SOFTWARE VERSION 9.14 or ANY LATER PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 480 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA - 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 481 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA - 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 482 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA - 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 483 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 484 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA + 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 485 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA + 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 486 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA + 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 487 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Figure 5.11.9 -- CRUISE PERFORMANCE (Recommended cruise) Edition 1 -- June 22, 2007 Page 5.11.9A Rev. 7 POST- -GARMIN SOFTWARE VERSION 9.14 or ANY LATER PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 488 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA - 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 489 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA - 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 490 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA - 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 491 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 492 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA + 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 493 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA + 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 494 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA + 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 495 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (5500 lbs - - 2495 kg) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 496 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (5500 lbs - - 2495 kg) (Cont’d) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 497 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (6300 lbs - - 2858 kg) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 498 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (6300 lbs - - 2858 kg) (Cont’d) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 499 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (7100 lbs - - 3220 kg) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 500 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (7100 lbs - - 3220 kg) (Cont’d) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 501 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.11 - - CRUISE PERFORMANCE Figure 5.11.1 -- CRUISE PERFORMANCE (Maximum cruise) Edition 1 -- June 22, 2007 Page 5.11.1 Rev. 7 PRE- -GARMIN SOFTWARE VERSION 9.14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 502 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA - 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 503 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA - 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 504 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA - 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 505 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 506 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA + 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 507 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA + 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 508 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Maximum cruise Conditions : ISA + 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Use preferably recommended cruise power If BLEED HI msg ON : .
  • Page 509 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Figure 5.11.9 -- CRUISE PERFORMANCE (Recommended cruise) Edition 1 -- June 22, 2007 Page 5.11.9 Rev. 7 PRE- -GARMIN SOFTWARE VERSION 9.14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 510 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA - 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 511 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA - 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 512 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA - 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 513 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 514 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA + 5°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 515 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA + 10°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 516 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Normal (recommended) cruise Conditions : ISA + 20°C Landing gear and flaps UP Np = 2000 RPM (*) -- BLEED switch on AUTO and BLEED HI msg OFF NOTE : Power recommended by PRATT & WHITNEY CANADA If BLEED HI msg ON : .
  • Page 517 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (5500 lbs - - 2495 kg) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 518 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (5500 lbs - - 2495 kg) (Cont’d) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 519 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (6300 lbs - - 2858 kg) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 520 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (6300 lbs - - 2858 kg) (Cont’d) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 521 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (7100 lbs - - 3220 kg) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 522 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Long Range Cruise (7100 lbs - - 3220 kg) (Cont’d) Conditions : Landing gear and flaps UP Np = 2000 RPM (*) BLEED switch on AUTO and BLEED HI msg OFF LEGEND : OAT : °...
  • Page 523 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.12 - - TIME, CONSUMPTION AND DESCENT DISTANCE Conditions : Power as required to maintain constant Vz Landing gear and flaps UP CAS = 230 KCAS -- 2000 RPM -- BLEED AUTO Vz = 1500 ft/min Vz = 2000 ft/min Vz = 2500 ft/min...
  • Page 524 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.12.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 525 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.13 - - HOLDING TIME Conditions : Landing gear and flaps UP IAS = 120 KIAS -- 2000 RPM -- BLEED AUTO 35 % FUEL USED DURING HOLDING TIME Weight 5500 lbs (2495 kg) Weight 6300 lbs (2858 kg) Pressure Pressure...
  • Page 526 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.13.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 527 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.14 - - LANDING DISTANCES WEIGHT : 7024 lbs (3186 kg) Associated conditions Landing gear DN and flaps LDG Approach speed IAS = 85 KIAS Touch--down speed IAS = 78 KIAS Maximum braking without reverse Hard, dry and level runway GR = Ground roll (in ft)
  • Page 528 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved LANDING DISTANCES WEIGHT : 6250 lbs (2835 kg) Associated conditions Landing gear DN and flaps LDG Approach speed IAS = 80 KIAS Touch--down speed IAS = 65 KIAS Maximum braking without reverse Hard, dry and level runway GR = Ground roll (in ft) = Landing distance (clear to 50 ft) (in ft)
  • Page 529 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved LANDING DISTANCES WEIGHT : 5071 lbs (2300 kg) Associated conditions Landing gear DN and flaps LDG Approach speed IAS = 80 KIAS Touch--down speed IAS = 60 KIAS Maximum braking without reverse Hard, dry and level runway GR = Ground roll (in ft) = Landing distance (clear to 50 ft) (in ft)
  • Page 530 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 5.14.4 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...

  • Page 531: Weight And Balance

    T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK SECTION 6 WEIGHT AND BALANCE TABLE OF CONTENTS Page GENERAL 6.1.1 ........... AIRPLANE WEIGHING PROCEDURES 6.2.1 .
  • Page 532 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.0.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 533 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.1 - - GENERAL This section is intended to provide the pilot with the procedure to determine the weight and balance of the airplane. TBM850 G1000 (Post--MOD70--0315--25) allows multiple cabin seat configurations between 2 seats and 6 seats, as required by the operator.
  • Page 534 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.1.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 535 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 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.
  • Page 536 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.2.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 537 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.3 - - BAGGAGE LOADING There are two baggage compartments : -- one in fuselage non pressurized forward section, between firewall and cockpit with maximum baggage capacity of 110 lbs (50 kg), -- one located in the rear of the pressurized cabin with following characteristics : Pre--MOD70--0315--25...
  • Page 538 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.3.1 -- Baggage limits Authorized anchoring points are identified with green self--adhesive labels affixed to the inside of the rail. A placard indicates loading limits for each securing net. Evenly distribute the load within the cargo zone and ensure that overall weight is centered.
  • Page 539 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK WARNING IT IS THE PILOT’S RESPONSIBILITY TO CHECK THAT ALL PARCELS AND BAGGAGES ARE PROPERLY SECURED IN THE CABIN TRANSPORT OF DANGEROUS PRODUCT IS NORMALLY PROHIBITED, HOWEVER IF TRANSPORT OF SUCH PRODUCT IS NECESSARY, IT MUST BE PERFORMED IN COMPLIANCE WITH REGULATIONS CONCERNING TRANSPORT OF DANGEROUS PRODUCT AND ANY OTHER APPLICABLE REGULATION...
  • Page 540 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.3.4 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 541 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.4 - - DETERMINING WEIGHT AND BALANCE GENERAL This section is intended to provide the pilot with the procedure to detemine the weight and balance of the airplane. IT IS THE PILOT’S RESPONSIBILITY TO ENSURE THAT THE AIRPLANE IS PROPERLY LOADED AND THE WEIGHT AND BALANCE LIMITS ARE ADHERED TO.
  • Page 542 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 4) Check value (3a) to be below Maximum Zero Fuel Weight. 5) Compute Zero Fuel Weight arm (5) and CG (MAC %) (5c) using given formulas. 6) Record the loaded Fuel (6a) and compute associated moment (6b). 7) Compute Ramp Weight (7a) and moment (7b) as sum of Zero Fuel Weight (3a) + loaded Fuel (6a) and moments (3b) + (6b).
  • Page 543 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK AIRPLANE LOADING FORM (m, kg) - - Pre- -MOD70- -0315- -25 ( Arm (m) − 4.392 ) Moment = Weight x Arm CG (MAC %) = × 100 1.51 Weight Moment Item...
  • Page 544 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK AIRPLANE LOADING FORM (m, kg) - - Post- -MOD70- -0315- -25 Weight Moment Item (kg) (m.kg) (% MAC) Empty Weight (kg) (1a) (1b) Baggage FWD (< 50 kg) (2a) 3.250 (2b) Front Seats...
  • Page 545 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK EXAMPLE OF AIRPLANE WEIGHT AND BALANCE REPORT NOTE : Airplane original report shall be kept with the airplane POH Figure 6.4.1 -- Example of Weight and Balance Report and basic airplane characteristics, in kg and m Edition 1 -- June 22, 2007 Page 6.4.5...
  • Page 546 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK NOTE : Airplane original report shall be kept with the airplane POH Figure 6.4.2 -- Example of Weight and Balance Report and basic airplane characteristics, in lb and in Edition 1 -- June 22, 2007 Page 6.4.6 Rev.
  • Page 547 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.4.7 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 548 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK WEIGHT BALANCE FORM DIAGRAM (m, kg) Pre- -MOD70- -0315- -25 ( Arm (m) − 4.392 ) Moment = Weight x Arm CG (MAC %) = × 100 1.51 Weight Moment Item (kg)
  • Page 549 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.3 -- Weight and Balance diagram Edition 1 -- June 22, 2007 Page 6.4.9 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 550 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK WEIGHT BALANCE FORM DIAGRAM (m, kg) Post- -MOD70- -0315- -25 ( Arm (m) − 4.392 ) Moment = Weight x Arm CG (MAC %) = × 100 1.51 Weight Moment Item (kg)
  • Page 551 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.4 -- Weight and Balance diagram Edition 1 -- June 22, 2007 Page 6.4.11 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 552 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK WEIGHT AND BALANCE FORM AND DIAGRAM (in, lbs) Pre- -MOD70- -0315- -25 ( Arm (in) − 172.93 ) Moment = Weight x Arm CG (MAC %) = × 100 59.45 Weight Moment...
  • Page 553 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.5 -- Weight and Balance diagram Edition 1 -- June 22, 2007 Page 6.4.13 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 554 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK WEIGHT AND BALANCE FORM AND DIAGRAM (in, lbs) Post- -MOD70- -0315- -25 ( Arm (in) − 172.93 ) Moment = Weight x Arm CG (MAC %) = × 100 59.45 Weight Moment...
  • Page 555 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.6 -- Weight and Balance diagram Edition 1 -- June 22, 2007 Page 6.4.15 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 556 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.4.16 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 557 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK WEIGHT AND BALANCE SAMPLES (m, kg) - - Pre- -MOD70- -0315- -25 CAUTION LOADING SAMPLES (FIGURE 6.4.7 OR 6.4.8) ARE ONLY GIVEN AS AN EXAMPLE ; FOR CALCULATION CONCERNING YOUR AIRPLANE, REFER TO THE DIAGRAM CORRESPONDING TO ITS VALIDITY Fig.
  • Page 558 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ( Arm (m) − 4.392 ) Moment = Weight x Arm CG (MAC %) = × 100 1.51 Weight Moment Item (kg) (m.kg) (MAC %) Empty Weight (kg) 2 126 4.738 10 073 22.9...
  • Page 559 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.7 -- Loading sample Edition 1 -- June 22, 2007 Page 6.4.19 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 560 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.4.20 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 561 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK WEIGHT AND BALANCE SAMPLES (in, lbs) - - Post- -MOD70- -0315- -25 Fig. 6.4.8 1 - Airplane basic characteristics : W = Empty weight 4 638 lbs Moment 864 173 in.lbs Balance Arm 186.3 in CG (MAC %)
  • Page 562 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ( Arm (in) − 172.93 ) Moment = Weight x Arm CG (MAC %) = × 100 59.45 Weight Moment Item (lbs) (in) (in.lbs) (MAC %) Empty Weight (lbs) 4 638 186.3 864 173...
  • Page 563 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.8 -- Weight and Balance diagram Edition 1 -- June 22, 2007 Page 6.4.23 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 564 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK DETERMINING EMPTY AIRPLANE CHARACTERISTICS Empty airplane characteristics (weight and balance) may vary with regard to those indicated on weighing form according to installed optional equipment and installed seats. List of equipment (refer to paragraph 6.5) contains the standard and optional equipment, as well as their characteristics (weight, arm).
  • Page 565 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Pre--MOD 70--0315--25 and Post--MOD 70--0315--25 Rear bench (2 seats)/net : 267.1 in. (6.785 m) Baggage compartment in pressurized cabin : 303.0 in. (7.695 m) Fuel : 189.8 in. (4.820 m) Edition 1 -- June 22, 2007 Page 6.4.25 Rev.
  • Page 566 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.4.26 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 567 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.5 - - LIST OF EQUIPMENT The list of equipment is available in SOCATA Report reference NAV No. 34/90--RJ--App 1, 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 568 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 6.5.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...

  • Page 569: Description

    T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SECTION 7 DESCRIPTION TABLE OF CONTENTS Page GENERAL 7.1.1A ........... AIRFRAME 7.2.1 .
  • Page 570 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page POWERPLANT 7.6.1 ..........7.6.1 TURBOPROP ENGINE OPERATION .
  • Page 571 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page AIR CONDITIONING AND PRESSURIZATION 7.9.1 ... . 7.9.1 ENGINE AIR BLEED SYSTEM ........7.9.3 CABIN PRESSURIZATION CONTROL SYSTEM .
  • Page 572 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) 7.15.5 EMERGENCY LOCATOR TRANSMITTER ......7.15.8 FLIGHT DECK INFORMATION SYSTEM (FS 210) (if installed) .
  • Page 573 SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.1 - - GENERAL This Section provides description and operation of the TBM 850 airplane and its systems. Some of the equipment described herein is optional and may not be installed in the airplane.
  • Page 574 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.1.2 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 575 PILOT’S OPERATING HANDBOOK 7.2 - - AIRFRAME (Figures 7.2.1, 7.2.1A, 7.2.1B) The TBM 850 is a six--place, low wing airplane. Post--MOD 70--0315--25 The airplane can be changed into 2, 3, 4 or 5--seat accommodation. The structure is a semi--monocoque all--metal construction and is equipped with a retractable tricycle landing gear.
  • Page 576 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.1 -- CABIN ARRANGEMENT Pre--MOD70--0315--25 and Post--MOD70--0315--25 with 6--seat accommodation Edition 1 -- June 22, 2007 Page 7.2.2 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 577 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.1A -- CABIN ARRANGEMENT Post--MOD70--0315--25 with 4--seat accommodation with large securing net Edition 1 -- June 22, 2007 Page 7.2.1A Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 578 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.1B -- CABIN ARRANGEMENT Post--MOD70--0315--25 with 4--seat accommodation with small securing net Edition 1 -- June 22, 2007 Page 7.2.2A Page Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 579 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK WINGS The wings are monocoque, bi--spar structures. Main spars of each wing are linked to the fuselage by two integral attach fittings. Each wing contains a main landing gear well and sealed casings forming the fuel tank. The wing leading edge is equipped with a deicing system.
  • Page 580 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Wings characteristics : Area ......... 193.75 sq.
  • Page 581 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Geared motor 2) Internal actuator 3) Intermediate bearings 4) Wing flap 5) External actuator 6) Rods 7) Control selector Figure 7.2.2 (1/2) -- WING FLAPS Edition 1 -- June 22, 2007 Page 7.2.5 Rev.
  • Page 582 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.2 (2/2) -- WING FLAPS Edition 1 -- June 22, 2007 Page 7.2.6 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 583 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK EMPENNAGES Empennages are composite structures. The horizontal empennage consists of a horizontal stabilizer (PHF), control surfaces and elevator trim tabs ; the vertical empennage consists of a vertical stabilizer, the rudder and the rudder trim tab.
  • Page 584 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.2.8 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 585 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.3 - - ACCOMMODATIONS INSTRUMENT PANEL The instrument panel contains instruments and controls necessary for flight monitoring. The typical instrument panel consists of all standard equipment, as well as additional optional equipment. Upper panel (Figure 7.3.2) The upper panel located at the top part of the windshield, contains electrical generation control panels, engine starting, ancillary electrical systems,...
  • Page 586 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Post--MOD70--0335--34 (ESI--2000) . on top : surmounted by the stand--by compass, AFCS control unit, . at bottom : GCU 475 control unit and outflow valve controller. -- Right area instrument panel includes (Figure 7.3.5) : .
  • Page 587 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK To cancel and reset a general alarm, press on the red or amber indicator. A pressure on the red indicator also stops red message associated aural tones. Aural warnings (Figure 7.3.2) The aural warnings are intended to alert the pilot during some configurations.
  • Page 588 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cockpit overhead panel (Figure 7.3.2) This panel includes following elements : -- the loud--speaker of GMA # 1, -- the loud--speaker of GMA # 2, -- the VMO alarm buzzer, -- the ”HORN TEST” knob, -- the emergency lighting rheostat.
  • Page 589 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK A ”MASTER WARNING” red flashing indicator and a ”MASTER CAUTION” amber indicator located on instrument panel (see Figure 7.3.8) in front of the pilot, illuminate as soon as one or several messages of same color light on. To cancel and reset a general alarm, press on the red or amber indicator.
  • Page 590 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cockpit overhead panel (Figure 7.3.2) This panel includes following elements : -- the loud--speaker of GMA # 1, -- the loud--speaker of GMA # 2, -- the ”HORN TEST” knob, -- the emergency lighting rheostat. It is attached to the cabin upper part between frames C6 and C7.
  • Page 591 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.1 -- INSTRUMENT PANEL ASSEMBLY (Typical arrangement) Edition 1 -- June 22, 2007 Page 7.3.7 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 592 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) L.H. instrument panel emergency lighting 2) Buzzer (V alarm) 3) Loud--speaker of GMA # 2 4) R.H. instrument panel emergency lighting 5) Cockpit floodlight switches (rheostats) 6) R.H. cockpit floodlight 7) MASTERs controls (”AVIONICS”...
  • Page 593 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.2 (2/2) -- UPPER PANEL AND COCKPIT OVERHEAD PANEL Edition 1 -- June 22, 2007 Page 7.3.9 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 594 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 11) Left station reception--micro 1) L.H. GMA 1347 audio panel jacks 2) General alarm red and amber 12) Electric pitch trim control indicators 13) Maps reading tablet 3) GDU 1040 PFD1 14) Electric rudder trim control 4) Stand--by airspeed indicator 15) ”AP / DISC TRM INT”...
  • Page 595 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.3 (2/2) -- LEFT INSTRUMENT PANEL (Typical arrangement) Pre--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.3.11 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 596 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 10) Left station reception--micro 1) L.H. GMA 1347 audio panel jacks 2) General alarm red and amber 11) Electric pitch trim control indicators 12) Maps reading tablet 3) GDU 1040 PFD1 13) Electric rudder trim control 4) Electronic Stand--by indicator 14) ”AP / DISC TRM INT”...
  • Page 597 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.3A (2/2) -- LEFT INSTRUMENT PANEL (Typical arrangement) Post--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.3.13 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 598 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Stand--by altimeter 2) Stand--by compass 3) GMC 710 AFCS mode controller 4) Registration 5) Cabin pressurization control panel (Figure 7.9.2) 6) GCU 475 remote controller 7) GDU 1500 MFD Figure 7.3.4 (1/2) -- CENTRAL INSTRUMENT PANEL Pre--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.3.14...
  • Page 599 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.4 (2/2) -- CENTRAL INSTRUMENT PANEL (Typical arrangement) Pre--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.3.15 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 600 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Stand--by compass 2) GMC 710 AFCS mode controller 3) Registration 4) Cabin pressurization control panel (Figure 7.9.2) 5) GCU 475 remote controller 6) GDU 1500 MFD Figure 7.3.4A (1/2) -- CENTRAL INSTRUMENT PANEL Post--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.3.16...
  • Page 601 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.4A (2/2) -- CENTRAL INSTRUMENT PANEL (Typical arrangement) Post--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.3.17 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 602 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) GDU 1040 PFD2 2) R.H. GMA 1347 audio panel 3) Right station control wheel tube 4) Crew music 5) Adjustable air outlet 6) Right station reception--micro jacks 7) Hour meter 8) R.H.
  • Page 603 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.5 (2/2) -- RIGHT INSTRUMENT PANEL (Typical arrangement) Edition 1 -- June 22, 2007 Page 7.3.19 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 604 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Propeller governor lever 2) Power lever 3) “PROP O’ SPEED TEST” push--button 4) Flaps control 5) Condition lever 6) Levers friction adjustment 7) Emergency fuel control 8) Manual fuel tank selector (Figure 7.7.2) 9) Roll trim tab control 10) Pitch trim tab control 11) Lock for access door to landing gear emergency pump (Figure 7.5.2)
  • Page 605 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.6 (2/2) -- PEDESTAL CONSOLE (Typical arrangement) Edition 1 -- June 22, 2007 Page 7.3.21 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 606 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.7 -- CIRCUIT BREAKERS PANEL Edition 1 -- June 22, 2007 Page 7.3.22 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 607 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.8 -- GENERAL ALARMS WARNING LIGHTS Edition 1 -- June 22, 2007 Page 7.3.23 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 608 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK DOORS, WINDOWS AND EMERGENCY EXIT Cabin access door (Figure 7.3.9) The cabin one--piece access door, located on the left side of fuselage aft of the wings, opens outside. The retractable stairs and hand rail make boarding easier.
  • Page 609 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.9 -- CABIN ACCESS DOOR Edition 1 -- June 22, 2007 Page 7.3.25 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 610 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK CAUTION BEFORE OPENING ACCESS DOOR, MAKE SURE DOOR DEFLECTION AREA IS CLEAR To open door from inside the cabin, unlock the handle by pressing on knob located on its left side, pull the handle toward inside and move it upwards. Open the door by pushing it upwards.
  • Page 611 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cockpit access door (Figure 7.3.9A) The cockpit access door, so--called ”pilot” door, (if installed) located on the left side of fuselage forward of the wings, opens outside. Retractable footstep makes boarding easier. WARNING AS THE ”PILOT”...
  • Page 612 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.9A -- COCKPIT ACCESS DOOR (”PILOT” DOOR) Edition 1 -- June 22, 2007 Page 7.3.28 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 613 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FWD compartment door The FWD compartment door is located on the airplane left side between the firewall and the front pressure bulkhead. It is hinged at the top. It is maintained in the up position by a compensation rod. Two interlocking--type latches ensure its closing and it is equipped with a lock [same key as for the access door and the “pilot”...
  • Page 614 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FWD compartment door The FWD compartment door is located on the airplane left side between the firewall and the front pressure bulkhead. It is hinged at the top. It is maintained in the up position by a compensation rod. Two interlocking--type latches ensure its closing and it is equipped with a lock [same key as for the access door and the “pilot”...
  • Page 615 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.10 -- EMERGENCY EXIT Edition 1 -- June 22, 2007 Page 7.3.30 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 616 ,�, . . � 1 L I . . ._ . . . ·TBM - " ' SECTION 7 " ... DESCRIPTION ... r 850= PILOTS OPERATING HANDBOOK .. " Pre-MOD?0-0793-25 Upholstery panel 1 . ., Opening handle ..
  • Page 617 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.3.30B Edition 1 -- June 22, 2007 TR29 -- July 2022 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 618 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.11) L.H. and R.H. front seats are mounted on rails attached to the structure. Longitudinal position, height and back--rest tilting of each seat can be adjusted and the arm--rest is hinged.
  • Page 619 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.11) L.H. and R.H. front seats are mounted on rails attached to the structure. Longitudinal position, height and back--rest tilting of each seat can be adjusted and the arm--rest is hinged.
  • Page 620 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Post--MOD70--0315--25 Many accommodations are possible. They are described hereafter ONLY zone B and zone C can be modified for seat configurations. This possibility is valid ONLY for Post--MOD70--0315--25. Location For all configurations, verify that For all configurations, verify that For all configurations, verify that number...
  • Page 621 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Here are all the configurations possibilities (for Post--MOD70-0315-25 airplane) : Configuration Location number name Location number Zone C Zone B (1) This configuration accepts small net or large net from MOD70--0315--25 Each cross indicates that you have a seat at the correspondent location number.
  • Page 622 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Belts and harnesses (Figure 7.3.12) WARNING INCORRECT CLOSURE OF THE SAFETY BELT MAY INTRODUCE A RISK. MAKE SURE IT IS TIGHTENED WHEN BUCKLED. TO BE MOST EFFICIENT, THE BELT MUST NOT BE TWISTED. CHECK THAT THERE IS NO CONSTRAINT WHEN OPERATED.
  • Page 623 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK BAGGAGE COMPARTMENTS Pre--MOD 70--0315--25 Post--MOD 70--0315--25 with 6--seat accommodation There are two baggage compartments : -- An AFT compartment located in the pressurized cabin between rear passenger seats and rear pressure bulkhead. -- A FWD compartment (non--pressurized) located between firewall and fwd pressure bulkhead.
  • Page 624 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Post--MOD 70--0315--25 with 4--seat accommodation Two cargo nets are available for the pilot to safely secure and transport baggage : -- the Small Cargo Net is attached through nine anchoring points on seat rails, between frame C11 and frame C13bis (Figure 7.2.1B).
  • Page 625 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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.
  • Page 626 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Damage acceptance criteria If any damage is detected, such as : -- damage or absence of 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...
  • Page 627 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Front passenger’s seat 2) L.H. pilot’s seat 3) R.H. intermediate passenger’s seat (back to flight direction) 4) L.H. intermediate passenger’s seat (back to flight direction) 5) R.H. rear passenger’s seat Rear bench 6) L.H.
  • Page 628 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.11 (2/2) -- SEATS Pre--MOD70--0315--25 Post--MOD70--0315--25 with 6--seat accommodation Edition 1 -- June 22, 2007 Page 7.3.40 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 629 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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 Figure 7.3.11A (1/2) -- SEATS...
  • Page 630 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.11A (2/2) -- SEATS Post--MOD70--0315--25 with 4--seat accommodation Edition 1 -- June 22, 2007 Page 7.3.42 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 631 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FRONT SEATS REAR SEATS Figure 7.3.12 -- FRONT AND REAR SEAT BELTS (with movable straps) AND HARNESSES Edition 1 -- June 22, 2007 Page 7.3.43 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 632 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.3.44 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 633 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.4 - - FLIGHT CONTROLS Flight controls consist of roll, pitch and rudder controls, as well as roll trim tab, pitch trim tab and rudder trim tab controls. NOTE : During airplane parking, it is recommended to lock flight controls (see Figure 8.6.2) ROLL (Figure 7.4.1) The roll control is activated by an assembly of rods and cables which links...
  • Page 634 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pedestal assembly 2) Control wheels 3) Fuselage roll lever 4) Spoiler 5) Aileron 6) Aileron control in wing 7) Spoiler control Figure 7.4.1 (1/2) -- ROLL Edition 1 -- June 22, 2007 Page 7.4.2 Rev.
  • Page 635 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.1 (2/2) -- ROLL Edition 1 -- June 22, 2007 Page 7.4.3 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 636 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Roll trim tab 2) Aileron 3) Adjustable rods 4) Actuator 5) Trim tab control wiring 6) Trim switch on pedestal console Figure 7.4.2 (1/2) -- LATERAL TRIM Edition 1 -- June 22, 2007 Page 7.4.4 Rev.
  • Page 637 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.2 (2/2) -- LATERAL TRIM Edition 1 -- June 22, 2007 Page 7.4.5 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 638 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.4.6 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 639 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ELEVATOR (Figure 7.4.3) Both elevators are activated simultaneously by the same control. Each control surface is hinged at three points to the rear part of horizontal stabilizer. The control wheel controls the two elevators through rods, bearings and bellcranks.
  • Page 640 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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 Figure 7.4.3 (1/2) -- ELEVATOR Edition 1 -- June 22, 2007 Page 7.4.8 Rev.
  • Page 641 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.3 (2/2) -- ELEVATOR Edition 1 -- June 22, 2007 Page 7.4.9 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 642 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Cables 2) Pulleys 3) Pitch trim tabs 4) Actuating rods 5) Actuator 6) Pitch trim manual control wheel 7) Electric pitch trim control Figure 7.4.4 (1/2) -- PITCH TRIM Edition 1 -- June 22, 2007 Page 7.4.10 Rev.
  • Page 643 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.4 (2/2) -- PITCH TRIM Edition 1 -- June 22, 2007 Page 7.4.11 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 644 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.4.12 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 645 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK RUDDER (Figure 7.4.5) The rudder is hinged on three fittings attached to the vertical stabilizer rear spar. The rudder pedals / rudder linkage is ensured through cables and a rod. Pilot and R.H. station rudder pedal positions are adjustable at each station. The rudder pedal adjustment mechanism (for piloting comfort purposes) includes a manual control located against the external bulkhead beneath the instrument panel and a locking device on the rudder pedals.
  • Page 646 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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 Figure 7.4.5 (1/2) -- RUDDER Edition 1 -- June 22, 2007 Page 7.4.14 Rev.
  • Page 647 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.5 (2/2) -- RUDDER Edition 1 -- June 22, 2007 Page 7.4.15 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 648 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Trim switch on control wheel 2) Actuator 3) Rudder trim tab 4) Rods 5) Rudder trim control wiring Figure 7.4.6 (1/2) -- RUDDER TRIM Edition 1 -- June 22, 2007 Page 7.4.16 Rev.
  • Page 649 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.6 (2/2) -- RUDDER TRIM Edition 1 -- June 22, 2007 Page 7.4.17 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 650 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.4.18 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 651 SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.5 - - LANDING GEAR The TBM 850 is equipped with electro--hydraulically actuated, fully retractable tricycle landing gear. Each landing gear is equipped with one wheel and an oil--air shock absorber integrated in the strut.
  • Page 652 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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.
  • Page 653 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Red warning light (LDG GR) 2) Green indicator light (LDG GR) 3) Landing gear control selector 4) Test switch 5) Test knobs Figure 7.5.1 -- CONTROL PANEL AND LANDING GEAR INDICATING Edition 1 -- June 22, 2007 Page 7.5.3 Rev.
  • Page 654 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SAFETY Safety switch (landing gear retraction) A safety switch installed on each main landing gear prevents, by detecting shock strut compression, landing gear accidental retraction when airplane is on ground. Pre--MOD70--0407--00D (V15.11 GARMIN software) Landing gear horn Landing gear horn is controlled by power lever and / or flaps.
  • Page 655 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.2 -- EMERGENCY LANDING GEAR EXTENSION CONTROL Edition 1 -- June 22, 2007 Page 7.5.5 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 656 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK GROUND MANEUVERS Nose gear steering control (Figures 7.5.3 and 7.5.4) Nose gear steering control is combined with rudder pedals and is fitted with a shimmy damper. When one of rudder pedals is fully pushed, nose wheel swivels about 20°.
  • Page 657 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.3 -- MINIMUM TURN DIAMETER (Full rudder pedals travel without using differential braking) Edition 1 -- June 22, 2007 Page 7.5.7 Rev. 10 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 658 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.4 -- MINIMUM TURN DIAMETER (Full rudder pedals travel by using differential braking) Edition 1 -- June 22, 2007 Page 7.5.8 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 659 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK BRAKE SYSTEM (Figure 7.5.5) Airplane is equipped with a hydraulically actuated disc braking system installed on the main landing gear wheels. Each toe brake at L.H. and R.H. stations is equipped with a master cylinder which sends hydraulic pressure to the corresponding disc brake : L.H.
  • Page 660 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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 Figure 7.5.5 (1/2) -- BRAKE SYSTEM Edition 1 -- June 22, 2007 Page 7.5.10...
  • Page 661 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.5 (2/2) -- BRAKE SYSTEM Edition 1 -- June 22, 2007 Page 7.5.11 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 662 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.6 -- PARKING BRAKE Edition 1 -- June 22, 2007 Page 7.5.12 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 663 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.6 - - POWERPLANT TURBOPROP ENGINE OPERATION (Figure 7.6.1) The PRATT & WHITNEY CANADA turboprop engine (PT6A--66D model) is a free turbine engine rated at 850 SHP and developing a thermodynamic power of 1825 ESHP.
  • Page 664 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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...
  • Page 665 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.6.1 (2/2) -- POWERPLANT Edition 1 -- June 22, 2007 Page 7.6.3 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 666 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ENGINE CONTROLS (LEVERS) (Figure 7.6.2) Engine operation requires use of four levers located on pedestal console in cabin : -- power lever (Item 2), and its detent for reverse (Item 6) -- propeller governor lever (Item 1), -- condition lever (Item 3), -- ”MAN OVRD”...
  • Page 667 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Power control lever The power control lever is linked to fuel control unit. It modulates engine power from full reverse to takeoff. Engine running, the power control lever rearward displacement, past the lock using the detent, allows to control : -- the engine power in the Beta range from idle to maximum reverse, -- the Beta valve to select the propeller pitch in reverse.
  • Page 668 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Condition lever The fuel condition lever is linked to FCU. It can be positioned to cutoff, idle LO / IDLE or idle HI / IDLE. Change from idle LO / IDLE to cutoff position is only possible after having overridden the idle gate.
  • Page 669 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ENGINE INSTRUMENTS Engine indicating consists of : -- engine torque expressed in percent (%), -- propeller speed in RPM, -- generator rotation speed expressed in percent (%), -- ITT expressed in °C, -- oil pressure expressed in PSI.
  • Page 670 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ENGINE STARTING (Figure 7.6.3) Ignition function Ignition system consists of an ignition unit and two spark igniter plugs in powerplant, a three--position ”IGNITION” switch OFF -- AUTO -- ON located on ”ENGINE START” panel at upper panel. Ignition unit supplies, from 28--Volt source, high voltage current necessary to spark igniter plugs.
  • Page 671 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.6.3 -- ENGINE STARTING Edition 1 -- June 22, 2007 Page 7.6.9 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 672 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ENGINE AIR INLET Engine air inlet is located at front lower section of engine cowling. Air inlet port is protected against icing by a hot air flux provided by engine. Air is driven throughout a duct in engine casing before entering engine through a protective screen.
  • Page 673 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Compressor turbine tacho- -generator (Ng) Compressor turbine tacho--generator (Ng) is attached on accessory gearbox. It supplies a voltage which is transmitted to the G1000 system for display on the MFD (under normal display conditions). Power turbine tacho- -generator (Np) Power turbine tacho--generator is attached on the right side of the reduction gearbox.
  • Page 674 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK PROPELLER Airplane is equipped with an all--metal, four--bladed, constant--speed and full--feathering propeller. Regulation Propeller governor located on engine maintains rotation speed selected by pilot with propeller governor lever. 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 low pitch (high RPM).
  • Page 675 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.7 - - FUEL SYSTEM (Figure 7.7.1) The fuel system comprises fuel tanks, fuel unit, selectors (manual and automatic), electric and mechanical boost pumps, engine fuel system, gaging installation, monitoring installation and drains. FUEL TANKS Fuel tanks are formed by sealed casings in each wing.
  • Page 676 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Flow divider 15) Fuel unit 2) Flowmeter 16) Filter drain 3) Collector tank 17) Fuel return pipe 4) Fuel regulator 18) Filling port 5) High pressure pump (HP) 19) NACA scoop 6) Oil to fuel heater 20) Tank vent valve 7) Low pressure switch...
  • Page 677 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.1 (2/2) -- FUEL SYSTEM Edition 1 -- June 22, 2007 Page 7.7.3 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 678 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK AUTOMATIC TANK SELECTOR (Figures 7.7.2 and 7.7.3) Automatic tank selection allows, without pilot’s intervention, feeding the engine from one tank or the other in predetermined sequences. These sequences depend on airplane configuration (ground, in--flight, fuel low level CAS messages appearance).
  • Page 679 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK NOTE : The manual selector is driven by the fuel unit and is positioned on R or L mark corresponding to the tank selected by the sequencer. Therefore, the pilot continuously knows the tank which is operating. Test for system proper operation ”SHIFT”...
  • Page 680 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.2 -- MANUAL SELECTOR OF FUEL TANKS Page 7.7.6 Edition 1 -- June 22, 2007 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 681 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Electric boost pump switch 2) Fuel selector 3) “SHIFT” push--knob Figure 7.7.3 -- FUEL CONTROL PANEL Edition 1 -- June 22, 2007 Page 7.7.7 Rev. 10 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 682 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK MAIN MECHANICAL BOOST PUMP The mechanical boost pump is attached to accessory gearbox and supplies fuel necessary for engine operation. ENGINE FUEL SYSTEM The engine fuel system consists of a fuel regulator, pumps, filters, a fuel divider and fuel nozzles.
  • Page 683 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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 valves on each tank, located on wing lower surface, one at wing root and the other past main landing gear well.
  • Page 684 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.4 (2/2) -- FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Edition 1 -- June 22, 2007 Page 7.7.10 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 685 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.8 - - ELECTRICAL SYSTEM (Figures 7.8.1 and 7.8.4) The airplane is fitted with a direct--current electrical system rated to 28 volts with negative pole at ground. Airplane mains supply is obtained from various power supplies : -- an engine driven starter generator -- a stand--by generator driven by the engine through a belt -- a battery located in engine compartment...
  • Page 686 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK STAND- -BY GENERATOR Stand--by generator supplies a 28--volt stand--by direct current which may be used in case of main generator failure. Generator connection with main bus bar is controlled through ”GENERATOR” selector set to ST--BY, it will be effective when connection conditions are met.
  • Page 687 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK DISTRIBUTION Airplane electrical systems are connected 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.
  • Page 688 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.1 -- ELECTRICAL DIAGRAM Page 7.8.4 Edition 1 -- June 22, 2007 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 689 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (1/3) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- June 22, 2007 Page 7.8.5 Rev. 13 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 690 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (2/3) -- ELECTRICAL DISTRIBUTION OF BUS BARS Page 7.8.6 Edition 1 -- June 22, 2007 Rev. 6 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 691 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (3/3) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- June 22, 2007 Page 7.8.7 Rev. 12 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 692 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.8.8 Edition 1 -- June 22, 2007 Rev. 6 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 693 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ESS BUS TIE Essential bus NORM & EMER switch BUS 1 AP SERVOS Autopilot servo protection FLAPS Flaps protection AIL TRIM Aileron trim protection RUD TRIM Pitch trim protection BUS 2 LDG GEAR Landing gear general supply protection ESS BUS 1...
  • Page 694 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK BUS 1 (Continued) INERT SEP DE ICE Inertial separator protection R WS DE ICE R.H. windshield deicing protection PITOT L Pitot L heating protection AUDIO 2 Audio control panel 2 protection STROBE Strobe lights protection BLUETOOTH...
  • Page 695 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK NOTE : If an additional equipment is installed, its circuit breaker is installed on a free location. Figure 7.8.3 (3/3) -- CIRCUIT BREAKER PANEL (typical arrangement) Edition 1 -- June 22, 2007 Page 7.8.11 Rev.
  • Page 696 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INDICATING Electrical system indicating consists of voltage and ampere indicating -- refer to GARMIN G1000 Pilot’s Guide for further details. Following CAS messages may appear on the MFD CAS display : ”BAT OFF”...
  • Page 697 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”MAIN” reset knob 2) ”ST--BY” reset knob 3) Crash lever 4) ”SOURCE” selector 5) ”GENERATOR” selector Figure 7.8.4 -- ELECTRICAL CONTROL Edition 1 -- June 22, 2007 Page 7.8.13 Rev. 6 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 698 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK EXTERIOR LIGHTING (Figure 7.8.5) The airplane is equipped with two navigation lights, two strobe lights, two landing lights, a taxi light, a wing leading edge icing inspection light. A ”LTS TEST” test--knob located above lights switches allows checking proper operation of warning lights ;...
  • Page 699 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Leading edge icing inspection light The leading edge icing inspection light is installed on fuselage L.H. side, its beam illuminates the wing leading edge. It is controlled by the ”ICE LIGHT” switch installed on ”DE--ICE SYSTEM”...
  • Page 700 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) L.H. landing light switch 2) Test knob (test light integrated to switches) 3) Taxi light switch 4) R.H. landing light switch 5) Navigation lights switch 6) Strobe lights switch Figure 7.8.5 (1/2) -- EXTERNAL LIGHTING CONTROLS Page 7.8.16 Edition 1 -- June 22, 2007 Rev.
  • Page 701 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.5 (2/2) -- EXTERNAL LIGHTING CONTROLS Edition 1 -- June 22, 2007 Page 7.8.17 Rev. 6 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 702 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTERIOR LIGHTING (Figure 7.8.6) Interior lighting consists of access, cabin, instrument panel, instruments, baggage compartment and emergency lighting. Access lighting Access lighting consists of two floodlights located on the ceiling upholstering (one at the level of the access door, the other at the level of the storage cabinet) and the L.H.
  • Page 703 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Emergency lighting Emergency lighting consists of two swiveling floodlights located on both sides of the cockpit overhead panel above front seats. It illuminates instrument panel assembly in case of visor lighting tubes and / or instrument integrated lighting failure.
  • Page 704 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Instrument panel lighting switch (rheostat) 2) Instrument lighting switch (rheostat) 3) “DIMMER” switch 4) Cabin lighting switch (rear seats reading light) 5) Access door, baggage compartment and FWD dome light (delayed breaker) push--button 6) Emergency lighting switch Figure 7.8.6 (1/2) -- INTERNAL LIGHTING CONTROLS...
  • Page 705 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.6 (2/2) -- INTERNAL LIGHTING CONTROLS Edition 1 -- June 22, 2007 Page 7.8.21 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 706 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.8.22 Edition 1 -- June 22, 2007 Rev. 6 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 707 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.9 - - AIR CONDITIONING AND PRESSURIZATION NOTE : A list of abbreviations used in this chapter is given in Figure 7.9.2. The airplane is equipped with a Global Air System (GAS), which ensures air conditioning and pressurization control -- see Figure 7.9.2.
  • Page 708 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK The system normaly operates on the P2.5 port as long as the pressure or temperature demands are met by this port. If one of these conditions is not met, the system automatically switches to the P3 port.
  • Page 709 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK System protection Power for the engine bleed air system is supplied by the BUS 2 bar and is protected by the CAB BLEED breaker. CABIN PRESSURIZATION CONTROL SYSTEM In flight, the GASC controls the modulation of the Outflow Valve (OFV) in order to reach the computed cabin altitude.
  • Page 710 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.1 -- Cabin altitude monitoring CAS messages are displayed in the MFD CAS window : -- ”BLEED TEMP” red CAS message indicates that an overtemperature was detected by either the Bleed Temperature Switch (BTSW) or the Overheat Thermal Switch (OTSW).
  • Page 711 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Overpressure and negative relief safety are managed by both OFV and SFV. The safety functions are ensured by independent pneumatic modules fitted on both valves, which override the GASC control when necessary. The DUMP switch allows the pilot to open the OFV in order to depressurize the cabin.
  • Page 712 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cooling circuit The VCCS is selected on only when the GASC receives a cooling request. It is composed of two independent circuits : -- one for the cockpit zone -- one for the cabin zone For each circuit, air is sucked by means of a variable speed electrical fan and then blown through an evaporator and ducted to the different zones : -- cockpit circuit, by passing through :...
  • Page 713 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK If the AIR COND switch is set to MANUAL : -- Each zone is controlled by its own control panel (depending on the CABIN CTRL selector position). CABIN CTRL selector positions : -- OVERRIDE : controls located in the cabin zone are inhibited.
  • Page 714 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Except in the case of very cold environmental conditions, this switching is inhibited below 25000 ft. Emergency air system An emergency ventilation valve allows outside air to enter the cabin when the EMERGENCY RAM AIR control knob is pulled out.
  • Page 715 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Air temperature management Cockpit and cabin heating / cooling Cockpit and cabin air temperature management is operated by selecting : For optimal air temperature management, select AIR COND switch to MANUAL and CABIN CTRL selector to CABIN : Cockpit panel selection Cabin panel selection Air temperature...
  • Page 716 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cockpit panel selection Cabin panel selection Air temperature Air temperature CABIN CABIN expectations expectations FAN SPEED FAN SPEED TEMP/°C TEMP/°C Cockpit Warm area Cabin Warm area Results Mixed Bleed Air Circuit : Warm air is distributed to both cockpit and cabin equally due to equal temperature demand.
  • Page 717 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cockpit panel selection Cabin panel selection Air temperature Air temperature CABIN CABIN expectations expectations FAN SPEED FAN SPEED TEMP/°C TEMP/°C Cockpit Cool area Cabin Cool area Results Mixed Bleed Air Circuit : With the cockpit and cabin CABIN TEMP/°C selectors set below 22°C, the Hot Air Distributor discharges the mixed bleed air below the floor towards the cold air circuit fans and evaporators to reduce the air to the desired temperature.
  • Page 718 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK NOTE : FANS selected to OFF ensures that no cool air is recirculated when trying to maximize the heating of the cockpit and / or cabin zones. Cabin override Select AIR COND switch to MANUAL and CABIN CTRL selector to OVERRIDE.
  • Page 719 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cockpit panel selection Cabin panel selection Air temperature Air temperature CABIN CABIN expectations expectations FAN SPEED FAN SPEED TEMP/°C TEMP/°C Cockpit Cool area Cabin area Results Mixed Bleed Air Circuit : With the cockpit CABIN TEMP/°C selector set below 22°C, the Hot Air Distributor discharges the mixed bleed air below the floor towards the cold air circuit fans and evaporators to reduce the air to the desired temperature.
  • Page 720 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Windshield DEFOG Windshield defog is operated by selecting : Cockpit panel selection Cabin panel selection Air temperature CABIN CABIN expectations FAN SPEED FAN SPEED TEMP/°C TEMP/°C Cockpit area Cabin area Results Mixed Bleed Air Circuit : Air is distributed to the windshields and cockpit side windows at a fixed temperature regardless of CABIN TEMP/°C selector settings.
  • Page 721 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1 -- Demisting outlets 2 -- Front vents 3 -- Cockpit ventilated temperature sensor (CKVTS) 4 -- Cabin ventilated temperature sensor (CBVTS) 5 -- Air ports 6 -- Cabin control panel 7 -- Global air system controller (GASC) 8 -- Out--flow valve (OFV) 9 -- Safety valve (SFV)
  • Page 722 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 25 -- Demisting microswitch 26 -- Hot air distributor (HAD) 27 -- (Cabin) Inlet temperature Sensor (ITS) 28 -- (Cabin) Bleed temperature switch (BTSW) 29 -- Mixing ejector (MIXEJ) 30 -- Check valve 31 -- MFD unit 32 -- Ground safety microswitch 33 -- Differential pressure switch...
  • Page 723 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.2 (3/3) -- Global Air System Edition 1 -- June 22, 2007 Page 7.9.17 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 724 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”DUMP” switch 2) “AIR COND” switch 3) “FAN SPEED” selector (cockpit) 4) “CABIN CTRL” selector 5) ”CABIN TEMP/° C” selector (cockpit) 6) ”BLEED” switch 7) “AIR FLOW” distributor 8) “FAN SPEED” selector (cabin) 9) ”CABIN TEMP/°...
  • Page 725 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.3 (2/2) -- GAS controls Edition 1 -- June 22, 2007 Page 7.9.19 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 726 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.9.20 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 727 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.10 - - EMERGENCY OXYGEN SYSTEM (Figure 7.10.1) The gaseous oxygen system will be used by the crew and the passengers, when the cabin altitude is greater than 10000 ft following a loss of pressurization or in case of cabin air contamination.
  • Page 728 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Microphone switch 2) OXYGEN switch 3) PASSENGERS OXYGEN switch Figure 7.10.1 -- EMERGENCY OXYGEN SYSTEM Edition 1 -- June 22, 2007 Page 7.10.2 Rev. 13 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 729 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK A control panel located in the cockpit overhead panel at the disposal of the pilot includes : -- a two--position valve ON/OFF (”OXYGEN” switch) to permit the supply of the front seats occupiers masks, -- a two--position valve ON/OFF (”PASSENGERS OXYGEN”...
  • Page 730 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK WARNING DO NOT SMOKE DURING OXYGEN SYSTEM USE. OIL, GREASE, SOAP, MAKE UP, LIPSTICK AND ANY OTHER GREASY SUBSTANCES CONSTITUTE A SERIOUS FIRE OR BURNING HAZARD, WHEN ON CONTACT WITH OXYGEN FLIGHT ABOVE 15000 FT WITH EMERGENCY DESCENT Number of OUTSIDE TEMPERATURE...
  • Page 731 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK WHEN REQUIRED TO REMAIN ABOVE 15000 FT DUE TO MINIMUM ”EN ROUTE” ALTITUDE Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C...
  • Page 732 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FLIGHT BETWEEN 15000 FT AND 10000 FT Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C 1333 1282 1231 1181 1131 1083...
  • Page 733 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SMART MIKE MASK (if installed) The two cockpit masks, O smart mike masks, are equipped with a system that detects when a communication is made operating one of the push--to--talk buttons. It activates a noise reduction system that attenuates the oxygen flow noise in the headsets.
  • Page 734 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.10.8 Rev. 14 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 735 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.11 - - AIR DATA SYSTEM AND INSTRUMENTS Pre--MOD70--0335--34 (ESI--2000) (Figure 7.11.1) Airplane air data system consists of : -- two separate static pressure systems supplying an altimeter, an airspeed indicator and air data computers (ADC). A part of system 1 is backed up by an alternate system which operation is controlled by a switching valve (normal / alternate) attached to instrument panel under R.H.
  • Page 736 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pitot L 2) Dynamic system drain 3) Airspeed indicator 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) Altimeter...
  • Page 737 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.11.1 (2/2) -- AIR DATA SYSTEM Pre--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.11.3 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 738 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Post--MOD70--0335--34 (ESI--2000) (Figure 7.11.2) Airplane air data system consists of : -- two separate static pressure systems supplying an electronic standby indicator and air data computers (ADC). A part of system 1 is backed up by an alternate system which operation is controlled by a switching valve (normal / alternate) attached to instrument panel under R.H.
  • Page 739 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pitot L 2) Dynamic system drain 3) Electronic 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)
  • Page 740 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.11.2 (2/2) -- AIR DATA SYSTEM Post--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.11.6 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 741 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Alternate static source The alternate static port located in the rear fuselage supplies a system routed to the switching valve (normal / alternate) in order to replace static system 1. The alternate line incorporates a drain plug located under the instrument panel on R.H.
  • Page 742 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 7.11.8 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 743 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.12 - - VACUUM SYSTEM AND INSTRUMENTS Pre--MOD70--0335--34 (ESI--2000) (Figure 7.12.1) The airplane is fitted with a vacuum system providing the suction necessary to operate the stand--by attitude indicator, the cabin pressurization and the leading edge deicing.
  • Page 744 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pressure regulator 2) Ejector 3) Valve 4) Regulating and relief valve 5) Pressure switch 6) Failure CAS message Figure 7.12.1 (1/2) -- VACUUM SYSTEM Pre--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.12.2 Rev.
  • Page 745 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.12.1 (2/2) -- VACUUM SYSTEM Pre--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.12.3 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 746 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SUCTION GAGE The suction gage is calibrated in inches of mercury and indicates the suction available for operation of the stand--by attitude indicator. The desired vacuum range is 4.4 to 5.2 in.Hg. A vacuum reading out of this range may indicate a system malfunction or improper adjustment.
  • Page 747 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pressure regulator 2) Ejector 3) Valve 4) Regulating and relief valve 5) Pressure switch 6) Failure CAS message Figure 7.12.1A (1/2) -- VACUUM SYSTEM Post--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.12.5 Rev.
  • Page 748 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.12.1A (2/2) -- VACUUM SYSTEM Post--MOD70--0335--34 (ESI--2000) Edition 1 -- June 22, 2007 Page 7.12.6 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 749 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.13 - - ICE PROTECTION EQUIPMENT (Figure 7.13.1) Ice protection equipment is as follows : -- Pneumatic deice system for inboard, central and outboard wing and for stabilizers : ”AIRFRAME DE--ICE” -- Propeller electrical deice system : ”PROP DE--ICE”...
  • Page 750 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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”...
  • Page 751 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK HEATING OF PITOTS AND STALL WARNING SENSOR (”PITOT L HTR” AND ”PITOT R & STALL HTR”) The two pitots, which supply ADCs, the airspeed indicator and the stall warning sensor are electrically heated. This deice equipment must be used even during flight into non--icing conditions.
  • Page 752 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.13.1 -- DEICING CONTROL AND CHECK PANEL Page 7.13.4 Edition 1 -- June 22, 2007 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 753 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.14 - - AVIONICS MASTER (Figure 7.14.1) The electrical supply of avionic equipment assembly is controlled by the ”AVIONICS MASTER” switch located on the upper panel. When the “AVIONICS MASTER” switch is set to START, it allows to electrically supply, from the “BATT BUS“...
  • Page 754 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”AVIONICS MASTER” switch Figure 7.14.1 -- “AVIONICS MASTER” Edition 1 -- June 22, 2007 Page 7.14.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 755 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.15 - - MISCELLANEOUS EQUIPMENT STALL WARNING SYSTEM The airplane is equipped with an electrically deiced stall sensor in the leading edge of the right wing. This sensor fitted with a vane is electrically connected to an audible warning.
  • Page 756 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK CABIN FIRE EXTINGUISHER Pre--MOD70--0336--26 The fire extinguisher is located behind FWD R.H. seat. If there is no R.H. cabinet, the fire extinguisher is located behind FWD R.H. seat, it is attached on the floor by means of a quick--disconnect support. -- Pre--MOD70--0391--26D If there is R.H.
  • Page 757 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK GARMIN INTEGRATED FLIGHT DECK (GIFD) APPROACHES The purpose of this section is to provide an overview of the GIFD capabilities and operation related to GIFD Approaches. Detailed descriptions as well as operating instructions of these approaches are provided in the applicable Pilot s Guide and Cockpit Reference Guide.
  • Page 758 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK If SBAS integrity is available, it will be used to provide vertical guidance. During execution of a GPS approach with LNAV/VNAV service levels, while the aircraft is between the FAF and MAP, excessive deviation indicators appear as white vertical lines to indicate an area where the vertical deviation exceeds 75 feet.
  • Page 759 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK If SBAS becomes unavailable on an RNAV LPV approach, LPV yellow annunciation will be shown, but the CDI and VDI will continue to be shown. At one minute to the FAF, an APR DWNGRADE advisory message will be generated.
  • Page 760 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ELT ARTEX ME 406 Operation of the emergency locator transmitter is obtained as follows : -- from the instrument panel by setting ”ON/ARM” remote control switch to ON (locator transmitter ”ON/ARM” switch set to ARM), -- from the locator transmitter by setting its ”ON/ARM”...
  • Page 761 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ELT ARTEX C406--1 Operation of the emergency locator transmitter is obtained as follows : -- from the instrument panel by setting ”ON/ARM” remote control switch to “ON” (locator transmitter ”ON/OFF” switch set to “OFF”), -- from the locator transmitter by setting its ”ON/OFF”...
  • Page 762 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 3) (Cont’d) c) On ELT, red indicator light goes off. d) Near ELT, the buzzer does no more sound. FLIGHT DECK INFORMATION SYSTEM (FS 210) (If installed) The airplane is equipped with a flight deck information system allowing portable electronics devices to stream data to and from the G1000 system.
  • Page 763 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE SECTION 8 HANDLING, SERVICING AND MAINTENANCE TABLE OF CONTENTS Page GENERAL 8.1.1 ........... . IDENTIFICATION PLATE 8.2.1 .
  • Page 764 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE TABLE OF CONTENTS (Continued) Page AIRPLANE CLEANING AND CARE 8.8.1 ......8.8.1 WINDSHIELD AND WINDOWS .
  • Page 765 8.1 - - GENERAL This section contains the procedures recommended by the manufacturer for the proper ground handling and routine care and servicing of TBM 850 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.
  • Page 766 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 8.1.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 767 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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 768 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 8.2.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 769 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.3 - - PUBLICATIONS When the airplane is delivered from the factory, it is supplied with a Pilot’s Operating Handbook, the “GARMIN G1000 Integrated Flight Deck Pilot’s Guide and supplemental data covering optional equipment installed in the airplane (refer to Section 9 “Supplements”...
  • Page 770 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 8.3.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 771 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.4 - - INSPECTION 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.
  • Page 772 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 8.4.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 773 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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.
  • Page 774 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 8.5.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 775 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.6 - - GROUND HANDLING CAUTION ONLY MOVE OR TOW THE AIRPLANE WITH SOMEONE IN THE COCKPIT TOWING CAUTION USING THE PROPELLER FOR GROUND HANDLING COULD RESULT IN SERIOUS DAMAGE, ESPECIALLY IF PRESSURE OR PULL IS EXERTED ON BLADE TIPS The airplane should be moved on the ground with a towing bar and a suitable vehicle in order not to damage the nose gear steering mechanism.
  • Page 776 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.6.1 -- TURNING ANGLE LIMITS Edition 1 -- June 22, 2007 Page 8.6.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 777 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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 bubbles in the inner layer of multilayer windshields.
  • Page 778 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.6.2 -- CONTROL LOCK DEVICE Pre--MOD70--0279--00 Edition 1 -- June 22, 2007 Page 8.6.4 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 779 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.6.2A -- CONTROL LOCK DEVICE Post--MOD70--0279--00 Edition 1 -- June 22, 2007 Page 8.6.5 Rev. 8 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 780 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE FLYABLE STORAGE Airplanes placed in storage for a maximum of 28 days are considered in flyable storage. Storage from 0 to 7 days : -- Engine : according to Maintenance Manual P & W C. Airplane fueling : -- Keep fuel tanks full to minimize condensation in the tanks.
  • Page 781 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.7 - - SERVICING MAINTENANCE In addition to the preflight inspection (refer to Section 4, ”Normal Procedures”), servicing, inspection and test requirements for the airplane are detailed in the Maintenance Manual. Maintenance Manual outlines all items which require servicing, inspection or testing or overhaul.
  • Page 782 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Oil level check : To avoid overfilling of oil tank, and high oil consumption, an oil level check is recommended within 30 minutes after engine shutdown. Ideal interval is 15 to 20 minutes.
  • Page 783 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE CAUTION DURING FUELING OPERATIONS, TAKE CARE NOT TO DAMAGE PNEUMATIC DEICER BOOTS LOCATED ON WING LEADING EDGE. THE USE OF AVIATION GASOLINE (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...
  • Page 784 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Fuel additives Fuel used must contain an anti--ice additive conforming to MIL--I--27686 or MIL--I--85470 specification. Strict adherence to recommended preflight draining instructions as called for in Section 4 will eliminate any free water accumulations from the tank sumps. While small amounts of water may still remain emulsified in the gasoline, it will normally be consumed and go unnoticed in the operation of the engine.
  • Page 785 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE CAUTION DO NOT PERMIT THE CONCENTRATE OF EGME OR DIEGME TO COME IN CONTACT WITH THE AIRPLANE FINISH OR FUEL TANK MIXING OF THE EGME OR DIEGME WITH THE FUEL IS EXTREMELY IMPORTANT.
  • Page 786 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.7.3 -- ADDITIVE MIXING RATIO (EGME or DIEGME) Edition 1 -- June 22, 2007 Page 8.7.6 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 787 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE LANDING GEAR Nose gear tire : 5.00--5 10 PR -- Inflation pressure : 98 psi (6.7 bars) * Main gear tires : 18 5.5 10 PR -- Inflating pressure : 135 psi (9.32 bars) * Nose gear shock absorber : Fill with hydraulic fluid AIR 3520 B (MIL.H5606E) ;...
  • Page 788 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE OXYGEN The replenishment device of the oxygen cylinder is installed directly on the cylinder head. It consists of a charging valve and of a pressure gage graduated from 0 to 2000 PSIG. A chart -- see Figure 8.7.4, located on the inside of the cylinder service door, gives the cylinder charge maximum pressure according to the environment temperature.
  • Page 789 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Replenishment procedure WARNING MAKE SURE THAT THE AIRPLANE IS FITTED WITH A GROUNDING CABLE AND IS PROPERLY GROUNDED. THE OXYGEN CART MUST BE ELECTRICALLY BONDED TO THE AIRPLANE. DO NOT OPERATE THE AIRPLANE ELECTRICAL SWITCHES OR CONNECT/DISCONNECT GROUND POWER DURING OXYGEN SYSTEM REPLENISHMENT.
  • Page 790 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE If the pressure on the oxygen cylinder gage is lower, fill the oxygen cylinder. Make sure the area around the oxygen cylinder charging valve is clean. Remove the cap from the charging valve. Make sure the oxygen supply hose is clean and connect it to the charging valve.
  • Page 791 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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”...
  • Page 792 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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 793 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Coil oxygen tubing inside facepiece over reservoir bag. Connect oxygen tubing to manifold oxygen fitting. WARNING MAKE SURE LANYARD 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.
  • Page 794 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 8.7.14 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 795 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.8 - - AIRPLANE CLEANING AND CARE WINDSHIELD AND WINDOWS The windshield and windows should be cleaned with an airplane windshield cleaner. NOTE : Refer to the Maintenance Manual for products and procedures to apply. Apply the cleaner sparingly with soft cloths and rub with moderate pressure until all dirt, oil scum and bug stains are removed.
  • Page 796 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE PAINTED SURFACES Refer to Maintenance Manual for the products and procedures to apply. PROPELLER CARE Preflight inspection of propeller blades for nicks and cleaning them occasionally with a cloth soaked with soapy water to clean off grass and bug stains will assure long blade life.
  • Page 797 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.9 - - UTILIZATION BY COLD WEATHER (- - 0°C TO - - 25°C) OR VERY COLD WEATHER (- - 25°C TO - - 40°C) NOTE : Check pressure values in a hangar heated at about 15°C with control equipment at room temperature.
  • Page 798 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Check pressure values and inflate, if necessary, according to following table 1 during operation in cold weather only : OAT (°C) - - 40° - - 30° - - 20° - - 10°...
  • Page 799 CAUTION REMOVED EQUIPMENT ITEMS MUST BE STOWED IN A PLACE WHICH ENSURES THEIR INTEGRITY. Many accommodations are authorized by Daher Socata. They are enumerated in Section 7. This procedure specifies how to change your 6--seat accommodation into 4--seat accommodation, and conversely. However, it can be used partly to remove or install an equipment item.
  • Page 800 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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 protective covers.
  • Page 801 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE D. Removal of intermediate seats (Figures 8.10.2 and 8.10.3) 1) To remove intermediate seats, perform the following operations a) Install protective covers. b) Pull backrest bottom upholstery (25) to remove it. c) Clear the carpet from under the seat to facilitate moving in rails.
  • Page 802 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 3) Remove blanking plugs (31) located in line with R.H. front side window -- see Figure 8.10.3 Detail C, and install them on holes located in line with card table -- see Figure 8.10.3 Detail D. G.
  • Page 803 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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 intended use. NOTE : Slide properly the carpet under doorstep. 2) If necessary, remove the baggage compartment partition net and install the small or large cargo net (refer to Section 7).
  • Page 804 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 3) Remove blanking plugs (31) located in line with card table -- see Figure 8.10.3 Detail D, and install them on holes located in line with R.H. front side window -- see Figure 8.10.3 Detail C. D.
  • Page 805 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE G. Reconditioning 1) Make sure the work area is clean and free from debris. 2) Determine weight and balance (refer to Section 6). 3. ADDITIONAL CONFIGURATIONS WARNING : REMOVED SEATS CAN ONLY BE INSTALLED AT THEIR ORIGINAL LOCATION.
  • Page 806 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 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 8.10.8 Edition 1 -- June 22, 2007 Rev.
  • Page 807 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.10.1 (2/2) -- Removal/Installation of rear seat Edition 1 -- June 22, 2007 Page 8.10.9 Rev. 9 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 808 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 21 -- Locking handle 22 -- Lock 23 -- Pad 24 -- Rail 25 -- Backrest bottom upholstery Figure 8.10.2 -- Removal/Installation of intermediate seat Page 8.10.10 Edition 1 -- June 22, 2007 Rev.
  • Page 809 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 31 -- Blanking plug 32 -- Blanking plug 33 -- Blanking device assy 34 -- Deflector Figure 8.10.3 -- Cabin comfort – Installation of blanking plugs and deflector Edition 1 -- June 22, 2007 Page 8.10.11 Rev.
  • Page 810 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 34 -- Deflector 35 -- Deflector hole 36 -- Red mark 37 -- Color mark Figure 8.10.4 -- Cabin comfort – Installation of deflector Page 8.10.12 Edition 1 -- June 22, 2007 Rev.
  • Page 811 Report NAV No. 34/90---RJ---App1 From S/N 434 to 999 The content of this document is the property of DAHER AEROSPACE. It is supplied in confidence and commercial security of its contents must be maintained. It must not be used for any purpose other than that for which it is supplied, nor may information contained in it be disclosed to unauthorized persons.
  • Page 812 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 1 of October 15, 2007 Pages Description List of amendments 4 and 5 Chapter 21 “Environmental System” modified : New global air system (including air conditioning and pressurization) installed on airplane Chapter 25 “Equipment and furnishings”...
  • Page 813 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 2 of December 15, 2007 Pages Description List of amendments Addition of the list of critical RVSM equipment Removal of modification MOD70--0160--34A (with cross--reference to SB70--120--34) Edition 1 -- June 22, 2007 Page 0B Rev.
  • Page 814 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 3 of January 31st, 2008 Pages Description List of amendments Modification of OPT70--25030 option version : OPT70 25030A replaced by OPT70 25030C valid for airplanes equipped with G1000 system Addition of option MOD70--0153--25C ELT KANNAD 406 AF Minor modifications...
  • Page 815 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 4 of March 31, 2008 Pages Description List of amendments 4, 11, 22, 24 Addition of optional equipment 9, 10, Correction of data concerning some already listed 17 thru 19, equipment 22, 23...
  • Page 816 AMENDMENTS Edition 1 of June 22, 2007 Revision 5 of March 25, 2009 Pages Description Title Incorporation of DAHER--SOCATA logo instead of EADS SOCATA List of amendments Edition 1 -- June 22, 2007 Page 0E Rev. 5 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 817 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 6 of September 15, 2010 Pages Description Title Copyright update List of amendments Addition of option OPT70--25030D ELT C406--1 Suppression option MOD70--0153--25C KANNAD 406 AF Addition of option MOD70--0270--34 radioaltimeter Addition of option MOD70--0258--00 TAS system GTS 820 Text moving...
  • Page 818 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 7 of July 15, 2012 Pages Description Title Copyright update List of amendments Addition of option OPT70--0331--23A GARMIN GSR 56 9, 10 Modifications due to incorporation of MOD70--0315--25 “TBM Elite Edition (6 pax club or 4 pax + cargo) (TR11) Relocation portable...
  • Page 819 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 8 of March 1, 2014 Pages Description Title Copyright update List of amendments Addition of variant for Stand--by ADI equipped with slip indicator Edition 1 -- June 22, 2007 Page 0H Rev.
  • Page 820 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 9 of June 15, 2016 Pages Description Title Copyright and logo update 0I, 0J List of amendments Addition of Pre--MOD70--0407--00D validity for Aural warning system Edition 1 -- June 22, 2007 Page 0I Rev.
  • Page 821 T B M EQUIPMENT LIST AMENDMENTS Edition 1 of June 22, 2007 Revision 10 of April 8, 2019 Pages Description Title Company identity name change List of amendments 1, 28 Introduction of Flight Stream 210 optional equipment (TR25) 2, 29 thru 34 Terminology, text moving and/or presentation Page 0J Edition 1 -- June 22, 2007...
  • Page 822 T B M EQUIPMENT LIST TABLE OF CONTENTS Page ATA 01 -- Specific optional equipment ......ATA 21 -- Environmental system .
  • Page 823 T B M EQUIPMENT LIST The following list contains standard equipment installed on each airplane and available optional equipment. A separate list of equipment of items installed at the factory in your specific airplane is provided in your airplane file. Columns showing weight (in pounds) and arm (in inches) provide the weight and center of gravity location for the equipment.
  • Page 824 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 01 - - SPECIFIC OPTIONAL EQUIPMENT Flight ceiling at 31000 ft Edition 1 -- June 22, 2007 Page 3 Rev.
  • Page 825 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 21 - - ENVIRONMENTAL SYSTEM General air system controller 82024A020101 1.98 311.02 (0.900) (7.900) 21- -20 - - Distribution Mixing unit 9723A010001 0.53...
  • Page 826 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) Intermediate pressure sensor 93557A010001 0.33 110.24 (0.150) (2.800) Overheat thermal switch A042010300--5 0.18 110.24 (0.080) (2.800) Main heat exchanger 81249A010001 7.72 108.27...
  • Page 827 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 22 - - AUTO FLIGHT 0176--00A G1000 AFCS GFC 700 composed of : . Pitch servo GSA 81 3.86 247.40 (1.75)
  • Page 828 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 23 - - COMMUNICATIONS Cockpit loud--speaker (Qty 2) AB 100 SC 0.77 181.10 (0.350) (4.600) 0176--00A G1000 dual audio system with integrated Marker 2.59 153.35 Beacon Receiver # 1...
  • Page 829 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 24 - - ELECTRICAL POWER 24- -30 - - DC generation Electric power center 160GC02Y05 11.02 127.95 (5.000) (3.250) Stand--by generator...
  • Page 830 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 25 - - EQUIPMENT AND FURNISHINGS Map holder 0.46 167.72 (0.210) (4.260) 28 V plugs 25026B Partition net between the cabin and the baggage 3.64 289.53 compartment...
  • Page 831 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) Leather seats - - Belts . Pilot’s seat T700C2500002000 55.12 183.90 (25.00) (4.671) . Front R.H. seat T700C2500002001 55.12 183.90...
  • Page 832 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 25- -61 - - Emergency locator transmitter 0208--25B Emergency Locator Transmitter ME--406 4.10 336.46 (installed in tail area) (1.86) (8.546) 25030C...
  • Page 833 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 27 - - FLIGHT CONTROLS 27- -10 - - Roll control Roll trim actuator 145700.02 1.54 212.60 (0.700) (5.400) 27- -20 - - Yaw control...
  • Page 834 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 28 - - FUEL SYSTEM 28- -20 - - Fuel supply Electric boost pump 2022--B 3.48 129.92 (1.580) (3.300) Electric boost pump...
  • Page 835 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 30 - - ICE AND RAIN PROTECTION Deicer, L.H. horizontal stabilizer 4.19 398.42 T700A3013003000 (1.900) (10.120) Deicer, R.H. horizontal stabilizer 4.19 398.42 T700A3013003001...
  • Page 836 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 30- -60 - - Propeller deicing Modular brush assy 3E2044--2 0.44 47.05 (0.200) (1.195) Timer 3E2311--4 0.44 200.79 (0.200) (5.100)
  • Page 837 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 31 - - INDICATING/RECORDING SYSTEMS 31- -20 - - Independent instruments 31002B Hourmeter 56457--3 0.55 156.30 (flying time) (0.250) (3.970) 31002A...
  • Page 838 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 32 - - LANDING GEARS 32- -10 - - Main landing gear L.H. main landing gear D23767000 51.59 200.39 (23.400)
  • Page 839 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) Master cylinder 010--07802 0.88 145.67 (0.400) (3.700) Nose tire P/N 071--311--1 5.00--5--10PR TL 5.60 89.57 (2.540) (2.275) Nose tire P/N 505T01--1 5.00--5--10PR TL 6.30...
  • Page 840 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 33 - - LIGHTS 33- -10 - - Instrument panel lighting L.H. tube 67135 U290 C62S Neglig. R.H.
  • Page 841 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) With LED strobe/nav lights : -- R.H. or L.H. navigation light assy 0.32 185.04 11--1100--L--SA (0.145) (4.700) 11--1100--R--SA 33002 Halogen landing lights...
  • Page 842 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 34 - - NAVIGATION 34- -11 - - Air data systems Lift transducer 799--8 0.88 173.23 (0.400) (4.400) Pitot L heated probe AN 5812--1...
  • Page 843 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 34- -24 - - ADI and standby horizon Pre--MOD70--0335--34 (ESI--2000) Stand--by ADI 1U149--019--19 4.19 152.56 (1.900) (3.875) Stand--by ADI 102--0071--003 4.44...
  • Page 844 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 34- -31 - - Marker MARKER antenna DM N27--3 0.75 129.92 (0.340) (3.300) Receiver (integrated in the GMA 1347C dual audio systems : refer to ATA 23--11) 34- -41 - - Stormscope 34056B...
  • Page 845 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 34- -44 - - Traffic advisory system 34061D TAS system KTA 870, G1000 coupled, 11.40 132.16 of which : (5.170) (3.357) .
  • Page 846 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 34- -53 - - Transponder 0176--00A Transponder # 1 GTX 33 3.87 149.65 Mode S non diversity (1.75) (3.801) Antenna...
  • Page 847 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 35 - - OXYGEN 0207--00 Gaseous oxygen system 22.73 226.77 (10.310) (5.760) Edition 1 -- June 22, 2007 Page 26 Rev.
  • Page 848 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 37 - - VACUUM Air ejector valve 19E17--5A 0.66 116.14 (0.300) (2.950) Gyro suction gage 3--310--5 0.14 157.48 (0.065) (4.000)
  • Page 849 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 46 - - INFORMATION SYSTEMS 0459--46B Flight stream transceiver FS 210 GARMIN 0.264 151.18 (0.120) (3.840) Page 28 Edition 1 -- June 22, 2007 Rev.
  • Page 850 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 52 - - DOORS 52002A ”Pilot” door 44.092 171.26 (20.000) (4.350) Edition 1 -- June 22, 2007 Page 29 Rev.
  • Page 851 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 61 - - PROPELLER 61- -10 - - Propeller assembly Propeller HC--E4N.3 / E 9083 S (K) 153.22 43.11 (69.500)
  • Page 852 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 71 - - POWERPLANT Turboprop engine PT6 A--66D 497.30 79.72 (226.000) (2.025) Silentblocks 95007--16 2.92 79.72 (1.325) (2.025) 71- -60 - - Air inlet Inertial separator actuator...
  • Page 853 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 77 - - ENGINE INDICATING Compressor turbine tacho--generator (Ng) 0.981 108.27 MIL--G--26611C GEU--7/A (0.445) (2.750) Power turbine tacho--generator 0.981 55.12 MIL--G--26611C GEU--7/A...
  • Page 854 T B M EQUIPMENT LIST ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) OR OPTIONAL per unit (A or O) EQUIPMENT MOD70 (kg) 79 - - LUBRICATION 79- -20 - - Distribution Oil cooler L8538233 10.472 90.55 (4.750) (2.300) 79- -30 - - Indicating Oil pressure transmitter 8107--400--00--10 0.441...
  • Page 855 T B M EQUIPMENT LIST INTENTIONALLY LEFT BLANK Page 34 Edition 1 -- June 22, 2007 Rev. 10 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 856 MOD70--0276--00 Version C TBM 700 or TBM 850 equipped with GARMIN flight deck ......... .
  • Page 857 MOD70--0276--00 Version F TBM 700 or TBM 850 equipped with GARMIN flight deck ......... .
  • Page 858 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK Supp. Edition Date Flight envelope protection MOD70--0423--34 and MOD70--0488--27 From S/N 434 to S/N 684 ......05.01.17 Lavatory compartment MOD70--0505--25 Version C...
  • Page 859 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Edition 1 -- June 22, 2007 Page 9.A.4 Rev. 6 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 860 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SUPPLEMENT ”BFG” WX- -500 OR WX- -950 OR WX- -1000 OR 1000+ OR 1000E STORMSCOPE TABLE OF CONTENTS Page -- GENERAL ........9.6.2 -- LIMITATIONS .
  • Page 861 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 1 GENERAL This supplement supplies information to the pilot about limitations, normal and emergency procedures when the optional ”BFG” WX--500 or WX--950 or WX--1000 or 1000+ or 1000E stormscope is installed on the TBM airplane. The stormscope must be used within limits of this supplement.
  • Page 862 -- The WX--500 Pilot’s guide, Series II, No. 009--11501--001 and the ”GARMIN” G1000 Nxi Integrated Flight Deck Cockpit Reference Guide for the TBM 850/900, P/N 190--02349--00, at their last revision, shall be readily available to the pilot, each time the ”BFG”...
  • Page 863 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 4 NORMAL PROCEDURES Normal operating procedures of the ”BFG” stormscope are outlined in : -- the Pilot’s Handbook, Series II, No. 75--0299--7690--1 at its last revision for ”BFG” stormscope model WX--1000 or 1000+ or 1000E -- the WX--950 Pilot’s Guide, Series II, No.
  • Page 864 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 6 WEIGHT AND BALANCE Informations hereafter supplement the ones given for the standard airplane in Section 6 ”Weight and balance” of the basic Pilot’s Operating Handbook. WEIGHT EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg) 34 - - NAVIGATION...
  • Page 865 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE WEIGHT EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg) Stormscope WX--500 4.94 232.28 -- shared with the GNS 530 GPS or with (2.240) (5.900) the KMD 850 or GMX 200 MFD (OPT 70 34056A) Stormscope WX--500 4.94...
  • Page 866 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 7 DESCRIPTION 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 on the screen to indicate the electrical discharge areas.
  • Page 867 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE INTENTIONALLY LEFT BLANK Page 9.6.8 Rev. 6 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 868 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SUPPLEMENT ENGINE FIRE DETECTION SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.18.2 -- LIMITATIONS .
  • Page 869 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to operation when the TBM airplane is equipped with the option ”ENGINE FIRE DETECTION SYSTEM”. The generalities hereafter supplement those of the standard airplane described in Section 1 ”General”...
  • Page 870 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook when the TBM airplane is equipped with the option ”ENGINE FIRE DETECTION SYSTEM”.
  • Page 871 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM ENGINE FIRE IN FLIGHT ”FIRE” ”FIRE” Indications : red warning ON or CAS message Try to confirm the fire warning by looking for other indications such as ITT ”ITT” ”ITT” increase, red warning ON or CAS message, smoke from engine cowls or air conditioning system.
  • Page 872 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement 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 ”ENGINE FIRE DETECTION SYSTEM”.
  • Page 873 TBM 700A & TBM 700B (with GARMIN flight deck system) Engine fire detection system L’HOTELLIER 1.455 96.06 (OPT70 26002B) (0.66) (2.440) TBM 700C & TBM 850 (without GARMIN flight deck system) Engine fire detection system L’HOTELLIER 1.455 96.06 (OPT70 26002C) (0.66) (2.440)
  • Page 874 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 7 DESCRIPTION Airplane without GARMIN flight deck The engine fire detection system enables the monitoring and indication of a fire in the engine area. The system includes : -- 7 detectors -- the control relay -- the test push--button The system also uses the advisory panel.
  • Page 875 Airplane equipped with GARMIN G1000 flight deck (MOD70- -0176- -00) Refer to the “GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for TBM 850”, P/N 190--00708--00, at its latest revision. Airplane retrofited with GARMIN G1000 flight deck (MOD70- -0276- -00) Refer to the “GARMIN G1000 Integrated Flight Deck Cockpit Reference...
  • Page 876 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SUPPLEMENT CHIP DETECTION SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.44.2 -- LIMITATIONS .
  • Page 877 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the TBM airplane is equipped with the option ”CHIP DETECTION SYSTEM”. SECTION 2 LIMITATIONS The installation and the operation of the CHIP DETECTION SYSTEM do not...
  • Page 878 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the TBM airplane is equipped with the option ”CHIP DETECTION SYSTEM”.
  • Page 879 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 4 PROCEDURES NORMALES The normal procedures hereafter supplement 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 ”CHIP DETECTION SYSTEM”.
  • Page 880 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 7 DESCRIPTION The chip detection system enables the monitoring of engine oil system. The system includes one chip detector installed on propeller reduction gear box and, if installed, a second chip detector installed on engine accessory gear box.
  • Page 881 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM INTENTIONALLY LEFT BLANK Page 9.44.6 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 882 T B M SUPPLEMENT 45 MEXICO SPECIFICS MEXICO SPECIFICS MOD70- -0212- -11 This supplement includes the general, limitations, emergency procedures, normal procedures, performance, weight and balance and description in addition to those of TBM airplane in its standard version. This Supplement includes information to be furnished to the pilot as required by the certification conditions.
  • Page 883 T B M SUPPLEMENT 45 MEXICO SPECIFICS LIST OF EFFECTIVE PAGES AND VALIDITIES ORIGINAL ISSUE OF SEPTEMBER 30, 2011 From S/N 1 to S/N 999, except S/N 687 P/N Z00.DMAFM45EE0R2MX Page Revision Page Revision 9.45A 9.45.15 9.45B 9.45.16 9.45C 9.45.17 9.45D 9.45.18 9.45.1...
  • Page 884 T B M SUPPLEMENT 45 MEXICO SPECIFICS LIST OF AMENDMENTS Revision 1 of April 29, 2016 Pages Description 9.45A Approval page 9.45B List of effective pages and validities 9.45C List of amendments 9.45.13A and Integration of TR17 ”AIR TOTAL extinguisher” 9.45.13B 9.45.17 Modification of ”OILS -- ACEITES”...
  • Page 885 T B M SUPPLEMENT 45 MEXICO SPECIFICS LIST OF AMENDMENTS Revision 2 of July 17, 2017 Pages Description 9.45A Approval page 9.45B List of effective pages and validities 9.45D List of amendments 9.45.1 Table of contents 9.45.14 to Addition of placards for MOD70--0505--25 9.45.17 9.45.14, Text moving...

  • Page 886: Table Of Contents

    T B M SUPPLEMENT 45 MEXICO SPECIFICS SUPPLEMENT MEXICO SPECIFICS TABLE OF CONTENTS Page -- GENERAL ........9.45.2 -- LIMITATIONS .
  • Page 887 T B M SUPPLEMENT 45 MEXICO SPECIFICS SECTION 1 GENERAL This supplement is intended to inform the pilot about the airplane specifics, among others those required by the relevant Certification Authorities (limitations, description and operations necessary to the operation of the TBM airplane).
  • Page 888 T B M SUPPLEMENT 45 MEXICO SPECIFICS e) On partition wall TBM 700C1, TBM 850 TBM 700C2 (Refer to POH Supplement 41) With partition net version A (refer to Section 6 of TBM 700C1 Pilot’s Operating Handbook) Rev. 0 Page 9.45.3...
  • Page 889 With partition net version B (refer to Section 6 of TBM 700C1 Pilot’s Operating Handbook) 2) Non pressurized FWD baggage compartment a) On baggage compartment door frame TBM 700A, TBM 700B and TBM 850 S/N 269 and from S/N 434 Page 9.45.4 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 890 3) Non pressurized rear baggage compartment a) On internal face of the baggage compartment door TBM 700C, TBM 850 up to S/N 433 except S/N 269 4) On cockpit R.H. side, at front seat level TBM 700A, TBM 700B (chemical oxygen) Rev.
  • Page 891 6) On R.H. side at front seat level and on the first rear passengers masks container (R.H. side on the ceiling) TBM 700C, TBM 850 (standard definition) 7) On rear passengers masks containers (on R.H. side on the ceiling) TBM 700C, TBM 850 (standard definition) Page 9.45.6...
  • Page 892 T B M SUPPLEMENT 45 MEXICO SPECIFICS 8) On rear passenger’s table casing 9) Door internal side a) On access door -- TBM 700A from S/N 1 to S/N 49, except airplanes equipped as a retrofit with modification No. MOD70--019--25 b) On access door -- TBM 700A from S/N 50 to S/N 125, plus airplanes equipped as a retrofit with modification No.
  • Page 893 MEXICO SPECIFICS c) On access door -- TBM 700A S/N 30, 35 and from S/N 50 to S/N 125 d) On access door -- TBM 700B, TBM 700C, TBM 850 up to S/N 433 except S/N 269 e) On access door -- TBM 850 S/N 269 and from S/N 434 Page 9.45.8...
  • Page 894 T B M SUPPLEMENT 45 MEXICO SPECIFICS f) On ”pilot” door (if installed) TBM 700B, TBM 700C, TBM 850 up to S/N 433 except S/N 269 g) On ”pilot” door (if installed) TBM 850 S/N 269 and from S/N 434 Rev. 0 Page 9.45.9...
  • Page 895 T B M SUPPLEMENT 45 MEXICO SPECIFICS 10) On emergency exit handle a) TBM 700A From S/N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification No. MOD 70--019--25 Page 9.45.10 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 896 T B M SUPPLEMENT 45 MEXICO SPECIFICS b) ALL From S/N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification No. MOD 70--019--25 Marking on cover Marking on handle Rev. 0 Page 9.45.11 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 897 SUPPLEMENT 45 MEXICO SPECIFICS 11) On landing gear emergency control access door a) TBM 700A, 700B, TBM 700C, TBM 850 not equipped with MOD70- -0189- -53 b) TBM 850 equipped with MOD70- -0189- -53 12) At the upper corner of the window on each side of the cockpit Page 9.45.12...
  • Page 898 T B M SUPPLEMENT 45 MEXICO SPECIFICS 13) On cabinet drawer 14) On aisle side of rear seats TBM 700A - - PRE- -MOD70- -019- -25 Rev. 0 Page 9.45.13 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 899 Pre--MOD70--0336--26 and Post--MOD70--0391--26D 14A) On R.H. side at front seat level 14B) On the lower drawer of the R.H. cabinet TBM 850 Airplanes from S/N 434 and equipped with MOD70--0505--25 “Lavatory compartment” -- On fixed panel, cabin side Page 9.45.14 Rev.
  • Page 900 T B M SUPPLEMENT 45 MEXICO SPECIFICS -- On fixed panel, toilet side -- On access door, cabin side and toilet side Rev. 2 Page 9.45.15 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 901 T B M SUPPLEMENT 45 MEXICO SPECIFICS -- Behind access door, cabin side -- Behind access door, toilet side -- Front face of lavatory compartment, near opening / closing switches Page 9.45.16 Rev. 2 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 902 T B M SUPPLEMENT 45 MEXICO SPECIFICS -- On the magazine rack and on side wall of storage volume Rev. 2 Page 9.45.17 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 903 T B M SUPPLEMENT 45 MEXICO SPECIFICS External placards 22) Under engine cowling and under each wing 23) Near fuel tank caps a) ALL up to S/N 433 except S/N 269 Page 9.45.18 Rev. 2 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 904 T B M SUPPLEMENT 45 MEXICO SPECIFICS b) TBM 850 S/N 269 and from S/N 434 c) ALL Rev. 2 Page 9.45.19 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 905 T B M SUPPLEMENT 45 MEXICO SPECIFICS 24) Above brakes hydraulic fluid reservoir against firewall 25) On langing gear hydraulic fluid reservoir 26) On fuse box in engine cowling Page 9.45.20 Rev. 2 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 906 T B M SUPPLEMENT 45 MEXICO SPECIFICS 27) On internal face of L.H. engine cowling a) ALL b) TBM 700A, 700B, TBM 700C Rev. 2 Page 9.45.21 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 907 T B M SUPPLEMENT 45 MEXICO SPECIFICS 28) On front lower portion of firewall L.H. side 29) On engine cowling, in front of compartment door 30) On nose gear door Page 9.45.22 Rev. 2 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 908 T B M SUPPLEMENT 45 MEXICO SPECIFICS 31) On nose gear leg 32) On main gear leg TBM 700A, TBM 700B, TBM 700C1 TBM 700C2, TBM 850 Rev. 2 Page 9.45.23 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 909 T B M SUPPLEMENT 45 MEXICO SPECIFICS 33) On internal face of the oxygen cylinder service door TBM 700C, TBM 850 (standard definition) 34) On the oxygen service door TBM 700C, TBM 850 (standard definition) 35) Near air data system port Page 9.45.24...
  • Page 910 T B M SUPPLEMENT 45 MEXICO SPECIFICS 36) On external side of emergency locator transmitter inspection door 37) On emergency exit external side Rev. 2 Page 9.45.25 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 911 MEXICO SPECIFICS 38) Door external side a) TBM 700A -- On access door TBM 700B, TBM 700C, TBM 850 -- On ”pilot” door (if installed) b) TBM 700B, TBM 700C, TBM 850 -- On access door Page 9.45.26 Rev. 2...
  • Page 912 T B M SUPPLEMENT 45 MEXICO SPECIFICS c) TBM 700B, TBM 700C, TBM 850 -- On outer fuselage skin aft of access door and in the cabin forward of access door 39) ALL -- On last step of stairs 40) On R.H. access door jamb TBM 700B, TBM 700C, TBM 850 Rev.
  • Page 913 T B M SUPPLEMENT 45 MEXICO SPECIFICS Placards relative to optional equipment 41) Airplanes equipped with option OPT70 25002 : “7--place accomodation” (refer to POH Supplement 7) a) Specific for S/N 7 -- On cockpit R.H. side, at front seat level -- Under seating of intermediate and R.H.
  • Page 914 T B M SUPPLEMENT 45 MEXICO SPECIFICS -- On the rear divan middle seating b) From S/N 68 to S/N 243, except S/N 72 to 75 and S/N 205 and 240 -- On cockpit R.H. side, at front seat level -- Under seating of L.H.
  • Page 915 T B M SUPPLEMENT 45 MEXICO SPECIFICS c) S/N 7 and from S/N 68 to S/N 243, except S/N 72 to 75 and S/N 205 and 240 -- On bottom bulkhead of rear pressurized baggage compartment (in cabin) -- On L.H. side, under R.H and L.H intermediate seat seatings or on L.H.
  • Page 916 T B M SUPPLEMENT 45 MEXICO SPECIFICS 42) TBM 700B & TBM 700C1 with pilot door Airplanes equipped with option OPT70 25027 : “Cargo transportation capability” (refer to POH Supplement 30) -- On the raiser at frame 13bis, inside the cabin -- Under L.H.
  • Page 917 T B M SUPPLEMENT 45 MEXICO SPECIFICS 43) TBM 700B without pilot door Airplanes equipped with option OPT70 25031 : “Cargo transportation capability without pilot door” (refer to POH Supplement 40) -- On the raiser at frame 13bis, inside the cabin 44) TBM 700B Airplanes equipped with option OPT70 35001 : “”EROS/INTERTECHNIQUE”...
  • Page 918 T B M SUPPLEMENT 45 MEXICO SPECIFICS -- On internal face of the oxygen cylinder service door SECTION 3 EMERGENCY PROCEDURES No specifics SECTION 4 PROCEDURES NORMALES No specifics SECTION 5 PERFORMANCE No specifics SECTION 6 WEIGHT AND BALANCE No specifics Rev.
  • Page 919 T B M SUPPLEMENT 45 MEXICO SPECIFICS SECTION 7 DESCRIPTION No specifics Page 9.45.34 Rev. 2 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 920 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SUPPLEMENT ”AIRBORNE” GWX 68 COLOR WEATHER RADAR TABLE OF CONTENTS Page -- GENERAL 9.47.2 ..........-- LIMITATIONS 9.47.2 .
  • Page 921 Airplane retrofited with GARMIN G1000 NXi flight deck (MOD70--0539--00) The ”GARMIN” G1000 NXi Integrated Flight Deck Cockpit Reference Guide for the TBM 850/900 P/N 190--02349--00 at its latest revision shall be readily available to the pilot whenever the operation of the radar system is predicted.
  • Page 922 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SECTION 3 EMERGENCY PROCEDURES Installation and operation of ”AIRBORNE” GWX 68 color weather radar system do not change the basic emergency procedures of the airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook.
  • Page 923 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook. Normal operating procedures for “AIRBORNE” GWX 68 color weather radar system are outlined in the Pilot’s Guide, the references of which are given in Section 2 “Limitations”...
  • Page 924 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR BEFORE LANDING -- Radar Mode Softkey STANDBY ........ENGINE SHUT- -DOWN -- Radar Mode Softkey .
  • Page 925 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SECTION 7 DESCRITION The weather information are displayed only on the MFD. The controls for the MFD are located on both the MFD bezel and the MFD control unit. 1) MFD 2) Radar mode 3) Area of weather display...
  • Page 926 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR Figure 9.47.1 (2/2) -- GWX 68 weather radar display and controls Rev. 1 Page 9.47.7 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 927 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR INTENTIONALLY LEFT BLANK Page 9.47.8 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 928 T B M SUPPLEMENT 48 ”HONEYWELL” KTA 870 TAS SYSTEM SUPPLEMENT ”HONEYWELL” KTA 870 TAS SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.48.3 -- LIMITATIONS .
  • Page 929 T B M SUPPLEMENT 48 ”HONEYWELL” KTA 870 TAS SYSTEM INTENTIONALLY LEFT BLANK Page 9.48.2 Rev. 0 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 930 This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the TBM 850 airplane is equipped with the option ”HONEYWELL” KTA 870 TAS SYSTEM. The KTA 870 TAS function enables to monitor the traffic by relying on information obtained from nearby airplane transponders.
  • Page 931 T B M SUPPLEMENT 48 ”HONEYWELL” KTA 870 TAS SYSTEM SECTION 3 EMERGENCY PROCEDURES The installation and the operation of ”HONEYWELL” KTA 870 TAS system do not change the basic emergency procedures of the airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook. SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane...
  • Page 932 T B M SUPPLEMENT 48 ”HONEYWELL” KTA 870 TAS SYSTEM SECTION 5 PERFORMANCE The installation and the operation of the ”HONEYWELL” KTA 870 TAS SYSTEM do not change the basic performance of the airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook. SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in...
  • Page 933 T B M SUPPLEMENT 48 ”HONEYWELL” KTA 870 TAS SYSTEM SECTION 7 DESCRIPTION 7.1 COMPONENTS OF THE OPTION The KTA 870 option is constituted of the following components : -- a KTA 810 computer, -- two KA 815 antennas. Traffic information can be displayed on a dedicated screen (MFD) and traffic annunciation is displayed on both MFD and PFD.
  • Page 934 T B M SUPPLEMENT 48 ”HONEYWELL” KTA 870 TAS SYSTEM Traffic is displayed according to TCAS symbology, however track vector information is not displayed. The KTA 870 TAS system uses the following symbols : Airplanes equipped with the radio altimeter When the airplane is at a ground height lower than 2000 ft, Traffic Advisory (TA) criteria, which initiate a visual and/or an aural alert, are (sensitivity level A) :...
  • Page 935 T B M SUPPLEMENT 48 ”HONEYWELL” KTA 870 TAS SYSTEM 1) MFD 2) TAS altitude mode 3) TAS operating mode 4) Aera of TAS display Figure 9.48.1 -- KTA 870 System display and controls Page 9.48.8 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 936 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM SUPPLEMENT ”GARMIN” TAWS SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.49.3 -- LIMITATIONS .
  • Page 937 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM INTENTIONALLY LEFT BLANK Page 9.49.2 Rev. 2 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 938 TBM 700 P/N 190--01247--00. Airplane retrofited with GARMIN G1000 NXi flight deck (MOD70--0539--00) -- ”GARMIN” G1000 NXi Integrated Flight Deck Cockpit Reference Guide for the TBM 850/900 P/N 190--02349--00. Rev. 2 Page 9.49.3 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 939 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”GARMIN”...
  • Page 940 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM 4.1 - - WARNINGS OF THE TAWS FUNCTION “PULL UP” AURAL WARNING The red “PULL--UP” PFD/MFD annunciation and MFD pop--up alert light on. 1 -- Level the wings. 2 -- Display the maximum power. 3 -- Choose the optimum rate of climb adapted to airplane configuration and speed, until the warning disappears.
  • Page 941 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM “Don’t sink” AURAL WARNING The amber “TERRAIN” PFD/MFD annunciation and “DON’T SINK” pop--up alert light on. Re--establish a positive rate of climb. “Sink rate” AURAL WARNING The amber “TERRAIN” PFD/MFD annunciation and “SINK RATE” pop--up alert light on.
  • Page 942 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in Section 6 ”Weight and balance” of the basic Pilot’s Operating Handbook. WEIGHT per unit EQUIPMENT OPTIONAL EQUIPMENT SUPPLIER (kg) 34 - - NAVIGATION...
  • Page 943 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM SECTION 7 DESCRIPTION The TAWS function has 7 modes. FORWARD LOOKING TERRAIN AVOIDANCE ALERT The Forward Looking Terrain Avoidance (FLTA) alert is used by TAWS and is composed of : -- Reduced Required Terrain Clearance and Reduced Required Obstacle Clearance Reduced Required Terrain Clearance (RTC) and Reduced Required Obstacle Clearance (ROC) alerts are issued when the airplane flight path...
  • Page 944 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM During the final approach phase of flight, FLTA alerts are automatically inhibited when the airplane is below 200 feet AGL while within 0.5 Nm of the approach runway or below 125 feet AGL while within 1.0 Nm of the runway threshold.
  • Page 945 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM PREMATURE DESCENT ALERTING A Premature Descent Alert (PDA) is issued when the system detects that the airplane is significantly below the normal approach path to a runway (Figure 9.49.1). PDA alerting begins when the airplane is within 15 Nm of the destination airport.
  • Page 946 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM EXCESSIVE DESCENT RATE ALERT The purpose of the Excessive Descent Rate (EDR) alert is to provide suitable notification when the airplane is determined to be closing (descending) upon terrain at an excessive speed. Figure 9.49.2 shows the parameters for the alert as defined by TSO--C151b.
  • Page 947 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM The aural/displayed messages associated with the EDR function are described in the table 7.4. PFD/MFD MFD Map Page TAWS Page Alert Type Aural Message Annuncia-- Pop--Up Alert tion Excessive Descent Rate Warning (EDR) PULL UP “Pull up”...
  • Page 948 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM The NCR alert is issued when the altitude loss and height are within the range in the first figure, or when the sink rate (negative vertical speed) and height are within the range in the second figure. Figure 9.49.3 -- Negative Climb Rate (NCR) Alert Criteria The aural/displayed messages associated with the NCR function are described in the table 7.5.
  • Page 949 T B M SUPPLEMENT 49 ”GARMIN” TAWS SYSTEM “FIVE- -HUNDRED” AURAL ALERT The purpose of the aural alert message “Five--Hundred” is to provide an advisory alert to the pilot that the airplane is 500 feet above terrain. When the airplane descends within 500 feet of terrain, the aural message “Five--Hundred”...
  • Page 950 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM SUPPLEMENT ”GARMIN” SYNTHETIC VISION SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.50.3 -- LIMITATIONS .
  • Page 951 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM INTENTIONALLY LEFT BLANK Page 9.50.2 Rev. 3 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 952 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the airplane is equipped with the option ”GARMIN” SYNTHETIC VISION SYSTEM (SVS).
  • Page 953 Airplane equipped with GARMIN G1000 flight deck (MOD70--0176--00) -- ”GARMIN” G1000 Integrated Flight Deck Cockpit Pilot’s Guide for the TBM 850 P/N 190--00709--01 or any later revision as applicable. Airplane retrofited with GARMIN G1000 flight deck (MOD70--0276--00) -- ”GARMIN” G1000 Integrated Flight Deck Cockpit Pilot’s Guide for the TBM 700 P/N 190--01247--00 or any later revision as applicable.
  • Page 954 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM SECTION 3 EMERGENCY PROCEDURES The procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”GARMIN” SYNTHETIC VISION SYSTEM.
  • Page 955 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”GARMIN” SYNTHETIC VISION SYSTEM.
  • Page 956 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM SVS ACTIVATION (2/2) (b) If Horizon Heading is desired : -- “HRZN HDG” key ......Press The horizon heading display will cycle on or off with each press of the “HRZN HDG”...
  • Page 957 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM SECTION 5 PERFORMANCE The installation and the operation of the ”GARMIN” SYNTHETIC VISION SYSTEM do not change the basic performance of the airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook. SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in...
  • Page 958 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM SECTION 7 DESCRIPTION SVS provides additional features on the primary flight display (PFD) which display the following information : Synthetic Terrain : an artificial, database derived, three dimensional view of the terrain ahead of the aircraft within a field of view of approximately 30 degrees left and 35 degrees right of the aircraft heading.
  • Page 959 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM USE OF PATHWAY Refer to GARMIN Integrated Flight Deck Pilot’s Guide, as applicable, listed in Section 2 Limitations of this supplement for further information. If Synthetic Terrain is displayed on the PFD, the Pathway may be used to assist the pilot’s awareness of the programmed lateral and vertical navigation path.
  • Page 960 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM -- Enroute When enroute, the Pathway will be displayed along the lateral path defined by the flight plan, at the altitude selected on the altitude selector. Flight plan changes in altitude that require a climb will be indicated by the Pathway being displayed as a level path at the altitude entered for the current flight plan leg.
  • Page 961 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM If the altitude selector is left at an altitude above the current airplane altitude, the airplane will intercept the final approach course below the extended VPTH or GP, such that the Pathway will be displayed above the airplane until the aircraft intercepts the VPTH or GP.
  • Page 962 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM -- Missed approach When the missed approach is selected on the FMS, the Pathway to the Missed Approach Holding Point will be displayed just as described for the departure segment. The pilot must assure that the aircraft path will, at all times, comply with the requirements of the published missed approach procedure.
  • Page 963 T B M SUPPLEMENT 50 ”GARMIN” SYNTHETIC VISION SYSTEM INTENTIONALLY LEFT BLANK Page 9.50.14 Rev. 3 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 964 Supplement 54 Argentina specifics Pilot's Operating Handbook Supplement Argentina specifics Table of contents Page General ..........9.54.2 Limitations .

  • Page 965: General

    Supplement 54 Argentina specifics Pilot's Operating Handbook Section 1 General This supplement is intended to inform the pilot about the airplane specifics, among others those required by the relevant Certification Authorities (limitations, description and operations necessary to the operation of the TBM airplane). Refer to Supplement A at the beginning of section 9 of the POH for the list of available supplements with their respective applicability.
  • Page 966 Supplement 54 Argentina specifics Pilot's Operating Handbook b) On partition wall TBM 700C1 TBM 700C2 - refer to POH Supplement 41 With partition net version A - refer to section 6 of TBM 700C1 POH Edition 0 - August 31, 2010 Page 9.54.3 Rev.
  • Page 967 With partition net version B - refer to Section 6 of TBM 700C1 POH TBM 850 (up to S/N 433 TBM 850 (from S/N 434), TBM 900, TBM 910 (up to S/N 1269), TBM 930 Page 9.54.4 Edition 0 - August 31, 2010 Rev.
  • Page 968 On the left-side rear cargo compartment panel upper edge Airplane equipped with coat hanger TBM 910 (up to S/N 1269), TBM 930 - MOD70-0557-25B TBM 850, TBM 900, TBM 910 (from S/N 1270), TBM 930 - MOD70-0557-25C or MOD70-0641-25A Airplane equipped with coat and headset hanger...
  • Page 969 Pilot's Operating Handbook 2) Post-MOD70-0315-25, as a retrofit or as standard equipment (from S/N 609) TBM 850 (from S/N 609), TBM 900, TBM 910, TBM 930 a) For the large cargo net, on the right-side upholstery panel, in the rear bagage...
  • Page 970 Pilot's Operating Handbook 3) Non pressurized FWD baggage compartment a) On baggage compartment door frame TBM 700A, TBM 700B, TBM 850 (from S/N 434), TBM 900, TBM 910, TBM 930 4) Non pressurized rear baggage compartment a) On internal face of the baggage compartment door...
  • Page 971 7) On the right side of the cockpit, at front seat level, and on the first rear passenger masks container (right side on the ceiling) TBM 700C, TBM 850, TBM 900, TBM 910 (up to S/N 1269), TBM 930 Page 9.54.8 Edition 0 - August 31, 2010 Rev.
  • Page 972 Argentina specifics Pilot's Operating Handbook 8) On rear passenger masks containers (right side on the ceiling) TBM 700C, TBM 850, TBM 900, TBM 910 (up to S/N 1269), TBM 930 9) On rear passenger masks containers TBM 910 (from S/N 1270)
  • Page 973 Supplement 54 Argentina specifics Pilot's Operating Handbook 12) Above passenger's table TBM 910 (from S/N 1270) 13) On cabinet drawer (optional) 14) Door internal side a) On access door TBM 700A from S/N 1 to S/N 49, except airplanes equipped as a retrofit with modification No.
  • Page 974 TBM 700A from S/N 50 to S/N 125, plus airplanes equipped as a retrofit with modification No. MOD70-019-25 TBM 700B, TBM 700C, TBM 850 (Up to S/N 433) TBM 850 (From S/N 434), TBM 900, TBM 910 (up to S/N 1269), TBM 930 Edition 0 - August 31, 2010 Page 9.54.11 Rev.
  • Page 975 Argentina specifics Pilot's Operating Handbook TBM 910 (from S/N 1270) b) In the cabin, forward of access door TBM 700B, TBM 700C, TBM 850, TBM 900, TBM 910 (up to S/N 1269), TBM 930 TBM 910 (from S/N 1270) Page 9.54.12 Edition 0 - August 31, 2010 Rev.
  • Page 976 On pilot's door, if installed TBM 700B, TBM 700C, TBM 850 (Up to s/n 433) TBM 850 (From S/N 434), TBM 900, TBM 910 (up to S/N 1269), TBM 930 TBM 910 (from S/N 1270) Edition 0 - August 31, 2010 Page 9.54.13...
  • Page 977 Supplement 54 Argentina specifics Pilot's Operating Handbook 15) On emergency exit handle TBM 700A S/N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification No. MOD 70-019-25 Page 9.54.14 Edition 0 - August 31, 2010 Rev.
  • Page 978 Supplement 54 Argentina specifics Pilot's Operating Handbook S/N 24, 26, 27, 29 to 32, 34, 36 to 1269, plus airplanes equipped as a retrofit with modification No. MOD 70-019-25 Marking on cover Marking on handle Edition 0 - August 31, 2010 Page 9.54.15 Rev.
  • Page 979 Supplement 54 Argentina specifics Pilot's Operating Handbook From S/N 1270 Marking on cover Marking on handle 16) Above emergency exit Page 9.54.16 Edition 0 - August 31, 2010 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 980 Argentina specifics Pilot's Operating Handbook 17) On landing gear emergency control access door TBM 700A, TBM 700B, TBM 700C, TBM 850 not equipped with MOD70-0189-53 TBM 850 equipped with MOD70-0189-53, TBM 900, TBM 910 (up to S/N 1269), TBM 930...
  • Page 981 Supplement 54 Argentina specifics Pilot's Operating Handbook 18) On aisle side of rear seats TBM 700A - Pre-MOD70-019-25 Page 9.54.18 Edition 0 - August 31, 2010 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...

  • Page 982: External Placards

    Pilot's Operating Handbook External placards 19) Near fuel tank caps TBM 700A, TBM 700B, TBM 700C, TBM 850 (Up to S/N 433) TBM 850 (From S/N 434), TBM 900, TBM 910, TBM 930 Edition 0 - August 31, 2010 Page 9.54.19 Rev.
  • Page 983 21) On internal face of the left-side engine cowling TBM 700A, TBM 700B, TBM 700C 22) On engine cowling, in front of compartment door TBM 700A, TBM 700B, TBM 700C, TBM 850 Page 9.54.20 Edition 0 - August 31, 2010 Rev.
  • Page 984 Supplement 54 Argentina specifics Pilot's Operating Handbook TBM 900, TBM 910, TBM 930 23) On nose gear door 24) On nose gear leg Edition 0 - August 31, 2010 Page 9.54.21 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 985 25) On main gear leg TBM 700A, TBM 700B, TBM 700C1 TBM 700C2, TBM 850, TBM 900, TBM 910, TBM 930 26) On internal face of the oxygen cylinder service door TBM 700C, TBM 850, TBM 900, TBM 910, TBM 930 Page 9.54.22...
  • Page 986 Argentina specifics Pilot's Operating Handbook 27) On the oxygen service door TBM 700C, TBM 850, TBM 900, TBM 910, TBM 930 28) Near air data system port 29) On external side of emergency locator transmitter inspection door Edition 0 - August 31, 2010 Page 9.54.23...
  • Page 987 30) On emergency exit external side 31) Door external side a) TBM 700A - On access door TBM 700B, TBM 700C, TBM 850, TBM 900, TBM 910, TBM 930 - On pilot's door, if installed Page 9.54.24 Edition 0 - August 31, 2010 Rev.
  • Page 988 Supplement 54 Argentina specifics Pilot's Operating Handbook b) TBM 700B, TBM 700C, TBM 850, TBM 900, TBM 910, TBM 930 - On access door c) TBM 700B, TBM 700C, TBM 850, TBM 900, TBM 910, TBM 930 - On outer...
  • Page 989 Supplement 54 Argentina specifics Pilot's Operating Handbook 33) On the right-side access door jamb TBM 700B, TBM 700C, TBM 850, TBM 900, TBM 910 (up to S/N 1269), TBM 930 Page 9.54.26 Edition 0 - August 31, 2010 Rev. 1...

  • Page 990: Placards Relative To Optional Equipment

    Supplement 54 Argentina specifics Pilot's Operating Handbook Placards relative to optional equipment 34) Airplanes equipped with option OPT70 25002 : “7-place accomodation" - refer to POH Supplement 7 a) Specific for S/N 7 - On the right side of the cockpit, at front seat level - Under seating of intermediate and right-side rear seats (on FWD side) equipped with oxygen - On FWD side of the rear divan seating...
  • Page 991 Supplement 54 Argentina specifics Pilot's Operating Handbook - On the rear divan middle seating b) From S/N 68 to S/N 243, except S/N 72 to 75 and S/N 205 and 240 - On the right side of the cockpit, at front seat level, and under seating of left-side intermediate seat, right-side rear seat and rear seats (on FWD side) S/N 7 and from S/N 68 to S/N 243, except S/N 72 to 75 and S/N 205...
  • Page 992 Supplement 54 Argentina specifics Pilot's Operating Handbook - On left side, under the right-side and left-side intermediate seat seatings or on the left-side intermediate seat back-rest 35) TBM 700B & TBM 700C1 with pilot door Airplanes equipped with option OPT70 25027 : “Cargo transportation capability" - refer to POH Supplement 30 - On the raiser at frame 13bis, inside the cabin Edition 0 - August 31, 2010 Page 9.54.29...
  • Page 993 Supplement 54 Argentina specifics Pilot's Operating Handbook - Under the left front side window 36) TBM 700B without pilot door Airplanes equipped with option OPT70 25031 : “Cargo transportation capability without pilot door" - refer to POH Supplement 40 - On the raiser at frame 13bis, inside the cabin Page 9.54.30 Edition 0 - August 31, 2010 Rev.
  • Page 994 Supplement 54 Argentina specifics Pilot's Operating Handbook 37) TBM 700A with MOD70-019-25 and TBM 700B Airplanes equipped with option OPT70 35001 : “"EROS/INTERTECHNIQUE" gaseous oxygen system" - refer to POH Supplement 29 or 37 - On the right side of the cockpit, at front seat level, and on the first rear passenger masks container (right side on the ceiling) - On rear passenger masks containers (right side on the ceiling) - On internal face of the oxygen cylinder service door...
  • Page 995 Supplement 54 Argentina specifics Pilot's Operating Handbook 38) Airplanes equipped with optional MOD70-0505-25C ”Cabinet installation : Lavatory compartment” - On fixed panel, cabin side - On fixed panel, toilet side Page 9.54.32 Edition 0 - August 31, 2010 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 996 Supplement 54 Argentina specifics Pilot's Operating Handbook - On access door, cabin side and toilet side - Behind access door, cabin side and toilet side Edition 0 - August 31, 2010 Page 9.54.33 Rev. 1 PIM - DO NOT USE FOR FLIGHT OPERATIONS...
  • Page 997 Supplement 54 Argentina specifics Pilot's Operating Handbook - Front face of lavatory compartment, near opening / closing switches - On the magazine rack 39) Airplanes equipped with optional MOD70-0684-25 ”Extended large storage cabinet” - On the upper surface of the cabinet Page 9.54.34 Edition 0 - August 31, 2010 Rev.

  • Page 998: Emergency Procedures

    Supplement 54 Argentina specifics Pilot's Operating Handbook - Inside large drawers, on side wall - Inside small internal drawer, on side wall Section 3 Emergency procedures No specifics Section 4 Normal procedures No specifics Section 5 Performance No specifics Edition 0 - August 31, 2010 Page 9.54.35 Rev.

  • Page 999: Weight And Balance

    Supplement 54 Argentina specifics Pilot's Operating Handbook Section 6 Weight and balance The information in this section supplements and/or replaces the information in section 6: Weight and Balance of the standard POH. Item Weight per OPT70 Required (R) or Standard (S) or Optional (A or O) unit equipment MOD70...
  • Page 1000 T B M SUPPLEMENT 55 IAC AR CERTIFIED AIRPLANES SUPPLEMENT IAC AR CERTIFIED AIRPLANES TABLE OF CONTENTS Page -- GENERAL ........9.55.3 -- LIMITATIONS .

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