Daher TBM 850 Pilot'S Information Manual Download

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TBM

PILOT’S OPERATING HANDBOOK

850

SECTION 7

DESCRIPTION

Page 7.5.6

Edition 1 -- June 22, 2007

Rev. 0

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

. Steering may be increased up to 28

by applying

differential braking to each side.
Airplane may be towed by attaching a steering or towing bar on nose gear

(Refer to Chapter 8.6 for operation). In that case nose wheel steering angle is

limited to

Minimum turn diameter

Minimum turn diameter, Figure 7.5.4, is obtained by using nose gear steering

and differential braking. Since tight turns lead to untimely tire wear, turns

should be made using the largest possible turning radius.

PIM - DO NOT USE FOR FLIGHT OPERATIONS

Summary of Contents for TBM 850

Page 1: ...PILOT S INFORMATION MANUAL TBM 850 Edition 1 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 2: ...book 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 It must not be reproduced nor transmitted in any form in whole or in part without permission ...

Page 3: ...n 1 June 22 2007 Rev 0 TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE 6 DESCRIPTION 7 AIRPLANE HANDLING SERVICING AND MAINTENANCE 8 SUPPLEMENTS 9 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 4: ...2 2 3 12 3 4 3 30 4 3 47 4 4 38 4 4 66 4 5 20 4 5 21 7 3 13 Modifications of ECS panel controls 4 3 30 4 3 38 4 3 41 4 4 38 4 4 52 4 4 57 7 3 10 7 3 11 Cabin rate selector deleted 4 3 30 4 3 33 4 3 38 4 3 41 4 4 43 4 4 52 4 4 57 7 3 10 7 3 11 Cabin altitude selector replaced by cabin pressure control panel associated to new adjustments 5 8 1 thru 5 8 9 Engine operation performance tables addition ...

Page 5: ... 11 4 3 12 4 4 14 6 3 1 6 3 2 6 4 3 thru 6 4 7 7 3 27 Deletion of rear baggage compartment Addition of FWD baggage compartment 3 9 7 3 9 8 7 8 5 thru 7 8 9 Correction of circuit breakers distribution 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 ...

Page 6: ...7 Revision 1 of October 15 2007 Cont d Pages Description 0 10 2 0 1 2 6 4 thru 2 6 12 3 0 2 4 0 1 4 3 19 4 3 24 4 3 31 thru 4 3 48 4 4 24 4 4 30 4 4 39 4 4 40 4 4 48 4 4 49 4 4 60 7 3 1 7 3 3 7 3 4 7 8 2 7 8 3 7 8 10 7 10 2 7 13 4 7 14 1 Minor modifications text moving presentation or terminology PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 7: ...d addition of data required for RVSM operational approval 3 0 1 3 0 2 Table of contents of Section 3 simplified due to creation of sub dividers for each chapter with their own table of contents 3 1 0B 3 2 0B 3 3 0B 3 4 0B 3 5 0B 3 6 0B 3 7 0B 3 8 0B 3 9 0B 3 10 0B 3 11 0B 3 12 0B 3 13 0B Creation of sub dividers for each Section 3 chapter with table of contents containing chapter sub titles at the...

Page 8: ...nuary 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 0 12 0 14 thru 0 16 0 18 0 20 7 0 3 7 15 2 7 15 3 Minor modifications terminology text moving and or presentation PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 9: ...5 Modification of Starting engine using airplane power and Starting engine using external power GPU normal procedures to limit maximum start up ITT 4 3 46 4 4 65 Modification of After landing normal procedure to improve occupants comfort during taxi maneuver 4 3 27 4 3 47 4 3 48 4 4 32 4 4 33 4 4 66 4 4 67 Modification of Shut down and Motoring normal procedures as regards to high temperature 4 3 ...

Page 10: ...ction of some details according to upholstering new definition 7 9 5 7 9 7 thru 7 9 9 7 9 11 Correction of some details of components relative to Global Air System 0 14 thru 0 22 4 3 16 4 3 17 4 3 20 to 4 3 22 4 3 25 4 3 47 4 3 48 4 4 19 4 4 20 4 4 24 to 4 4 26 4 4 30 4 4 31 4 4 66 4 4 67 7 0 3 7 3 3 7 3 10 7 3 12 7 3 13 7 9 1 7 9 5 7 9 7 thru 7 9 10 Minor modifications terminology text moving and...

Page 11: ...DMENTS 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 List of effective pages PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 12: ... 1 4 1 1 4 3 1 4 7 1 4 9 1 4 10 Modification of abbreviations and terminology 2 0 1 2 6 10 Addition of in flight circuit breaker use limits 2 2 1 Modification of VMO and maximum inertial separator operating speeds 2 6 2 Modification of NOTE about autopilot use in descent Addition of Enroute and Terminal operations instructions 2 6 4 Sub paragraph c deleted in Instrument approach paragraph 2 6 6 Mo...

Page 13: ...tion of information about illumination of ITT red warning during and after engine start 3 3 11 Curve deleted 3 3 13 3 3 14 Deleted pages 3 8 1 Modification of red warning CAS message FUEL PRESS ON procedure 3 8 3 Addition of a CAUTION about maximum imbalance 3 10 5 Addition of information related to on ground red warning CAS message DOOR ON 3 11 1 3 11 2 3 11 3 3 11 4 Rewording of landing gear ret...

Page 14: ...stribution of bus bars new diagram 7 9 3 Addition of bleed air system automatic load shedding feature 7 15 3 ELT KANNAD data deleted 1 2 1 1 4 2 1 4 8 2 5 1 2 6 1 2 6 3 2 6 4 3 3 0B 3 3 11 3 3 12 3 8 2 3 8 3 3 9 1 3 10 3 3 10 5 4 3 11 0B 3 11 4 3 33 4 4 43 4 4 49 4 4 59 5 14 2 5 14 3 7 0 1 7 0 2 7 2 1 7 4 7 7 4 10 7 5 2 7 7 4 7 8 5 7 8 7 thru 7 8 22 7 9 4 7 13 2 Minor modifications text moving pre...

Page 15: ...ndments Revision 7 0 21 thru 0 28 List of effective pages 1 1 1 2 1 1 5 8 1A thru 5 8 10A 5 8 1 thru 5 8 10 5 11 1A thru 5 11 22A 5 11 1 thru 5 11 22 7 1 1 8 3 1 Incorporation of TR 01 R1 Garmin software evolution 1 3 3 Modification of standard empty weight and maximum useful load 2 9 1 Incorporation of TR 03 Windshield de ice placard 2 9 11 Incorporation of TR 02 Addition of a placard related to ...

Page 16: ...eptember 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 5 11 2A thru 5 11 8A 5 11 10A thru 5 11 16A 5 11 2 thru 5 11 8 5 11 10 thru 5 11 16 Minor modifications text moving presentation or terminology PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 17: ...page 0 5B 0 5C SOCATA modifications Index updating 0 20 thru 0 24 List of amendments Revision 8 0 25 thru 0 32 List of effective pages 8 6 4 thru 8 6 6 Incorporation of TR 06 Control lock device 1 1 1A and 1 1 2A 1 1 1 and 1 1 2 2 0 1A and 2 0 2A 2 0 1 and 2 0 2 2 1 1A and 2 1 2A 2 1 1 and 2 1 2 2 6 1A thru 2 6 14A 2 6 1 thru 2 6 12 3 13 0B 3 13 10 thru 3 13 18 7 1 1A and 7 1 2A 7 1 1 and 7 1 2 In...

Page 18: ... capability 4 3 34 4 4 46 Incorporation of TR 09 Prop O speed governor test 1 3 3 2 0 1 and 2 0 2 2 0 1A and 2 0 2A 2 5 1 and 2 5 2 2 7 1 2 9 1 and 2 9 2 2 9 2A and 2 9 2B 4 3 7 4 4 6 6 0 1 6 3 1 and 6 3 2 6 4 1 thru 6 4 10 7 0 1 7 2 1 and 7 2 2 7 2 1A and 7 2 2A 7 3 26 thru 7 3 36 7 15 2 Incorporation of TR 11 4 seat accommodation MOD70 0315 25 1 0 1A 1 0 2A 1 0 1 1 0 2 Section 1 Table of content...

Page 19: ... 4 3 28 4 3 46 4 4 18 4 4 36 4 4 66 7 0 3 7 3 1 7 3 2 7 3 8 thru 7 3 11 7 3 11A thru 7 3 11D 7 8 7 7 8 9 7 8 11 7 11 1 thru 7 11 8 7 12 1 thru 7 12 6 Addition of MOD70 0335 34 ESI 2000 1 3 3 Modification of oil consumption value 2 0 2A 2 0 2 2 7 1 Addition of chemical toilet cabinet 2 9 7 Modification of access door placard internal side 2 9 8 Modification of pilot door placard internal side 3 4 0...

Page 20: ... 2nd Caution in Starting engine using external power GPU procedure 4 4 30 Modification of Motoring procedure 4 5 16 Modification of Utilization by cold weather and very cold weather procedure Preflight Inspection 4 5 26 Modification of GPS navigation procedure 7 3 23 Addition of indications about FRONT CARGO DOOR CAS message illumination 7 8 20 7 8 21 Modification of Internal lighting controls key...

Page 21: ...3 4 5 3 4 6 4 3 47 4 3 48 4 4 67 4 4 68 Deleted pages 0 5D 1 4 6 2 7 2 2 8 3 2 8 4 3 2 1 3 3 1 3 3 2 3 3 3 3 3 12 3 4 4 3 5 1 3 7 1 3 7 5 thru 3 7 7 3 7 10 3 8 3 3 13 8 4 0 1 4 0 2 4 3 6 4 3 16 thru 4 3 46 4 4 5 4 4 19 thru 4 4 66 4 5 18 5 0 1A 5 0 2A 5 0 1 5 0 2 7 0 2 7 3 1 7 3 3 7 3 4 7 5 4 Minor modifications text moving presentation or terminology PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 22: ...cedure Addition of Passenger s seat backrest position 4 3 33 4 4 43 Modification of Before Takeoff procedure Passenger s table and passenger s seat backrest 4 3 39 4 4 56 Modification of Descent procedure Passenger s table and passenger s seat backrest 0 5B 6 4 2A thru 6 4 2D 7 2 1 7 3 26A 7 3 26B Addition of Post MOD70 0315 25 multi configuration possibilities 8 0 2 8 10 1 thru 8 10 12 Addition o...

Page 23: ...ages 1 4 6 Addition of abbreviation FPL 3 7 1 Modification of Forced landing engine cut off procedure Final approach speed modified for both weights 3 9 10 Modification of Total loss of electrical power procedure Modification of NOTE 3 11 3 Modification of Emergency gear extension procedure Precise details added in NOTE about the use of procedure 3 12 2 Modification of Inertial Separator failure p...

Page 24: ...f Cruise procedure Addition of specific data following installation of new fuel sequencer as per MOD70 0402 28 4 5 1 Modification of OAT value to be consistent with that of Ice protection procedures 4 5 2 Modification of Ice protection procedures new wording and new data 7 0 1A thru 7 0 4A 7 0 1 thru 7 0 4 Section 7 Table of contents modified to be consistent with other sections due to GARMIN V12 ...

Page 25: ...d Pages Description 1 4 7 and 1 4 8 2 3 2 2 8 3 2 9 1 3 4 1 3 6 0B 3 6 1 thru 3 6 4 3 8 1 3 10 7 3 12 2 3 13 8 4 3 16 thru 4 3 48 4 4 19 thru 4 4 68 4 5 1 4 5 19 4 5 25 5 0 1 and 5 0 2 7 3 2 7 3 20 7 3 26A 7 4 13 7 5 7 7 6 8 7 8 9 7 15 2 8 7 2 8 8 1 Minor modifications text moving presentation or terminology 3 6 5 3 6 6 Deleted pages PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 26: ...Air start with starter procedure modification of IGNITION position when Ng μ 50 steady 3 11 5 Flaps malfunction procedure modification of flap control lever position 4 3 6 4 4 5 Landing gear panel addition of 3 green lights ON 4 3 18 4 3 23 4 3 29 4 4 22 4 4 28 4 4 35 4 5 19 Modification of Ng Value 70 2 instead of 69 2 4 3 20 4 3 25 4 4 24 4 4 31 Modification of Ng Value 70 2 instead of 52 4 3 31...

Page 27: ...etry 4 4 52 Deletion of POST MOD70 0402 28 paragraph 4 4 67 7 7 8 Addition of tolerance of 2 psi for the fuel pressure 7 5 4 Emergency landing gear extension control modfication of the number of cycles 7 9 11 Modification of cabin pressurization control panel Figure 7 9 2 7 13 1 Modfication of Wing and empennage deicing procedure parts deiced through 1st and 2nd cycles have been reversed 3 3 10 3 ...

Page 28: ... 1 3 10 2 thru 3 10 4 3 13 6 3 13 8 thru 3 13 10 7 3 2 7 3 4 thru 7 3 7 7 5 4 7 8 7 7 8 9 7 10 1 7 15 1 Modifications due to addition of MOD70 0407 00D Aural warning evolution and software G1000 integrated Flight Deck V15 11 0 31 and 0 32 List of normal amendments Revision 12 0 33 thru 0 40 List of effective pages 1 3 3 8 7 1 and 8 7 2 Clarification about engine oil use 1 4 6 Addition of abbreviat...

Page 29: ...CH position deleted 4 3 47 4 4 66 Modification of SHUT DOWN procedure TR19 6 0 1 6 1 1 6 3 1 thru 6 3 4 6 4 1 thru 6 4 26 Modification of WEIGHT AND BALANCE procedure 7 3 2 Modification of hour meter location 7 15 3 Modification of optional equipment 1 4 7 1 4 8 3 10 7 thru 3 10 10 3 13 0B 3 13 11 thru 3 13 20 4 4 31 7 0 1A 7 0 3A 7 0 1 7 0 3 7 3 3 7 3 8 thru 7 3 44 7 15 2 Terminology text moving ...

Page 30: ... of modifications 0 5A thru 0 5D Removal of the list of modifications from the POH 0 33 thru 0 36 List of amendments 0 37 thru 0 44 List of effective pages 1 1 1A 1 1 1 2 1 1A 2 1 1 2 6 3 3 13 14 4 4 37 4 4 38 7 1 1A 7 1 1 7 3 1 7 3 2 7 3 4 7 3 5 7 6 7 7 8 12 7 13 3 7 15 2 7 15 3 7 15 6 8 3 1 Replacement of the reference to the Cockpit Reference Guide by the reference to the Pilot s Guide 1 1 1A 1...

Page 31: ...ondition 3 9 2 3 9 3 Deletion of right windshield restriction for deicing systems 3 9 7 7 0 4A 7 8 5 7 8 10 7 8 11 7 15 6 Introduction of Flight Stream 210 optional equipment TR25 3 10 3 Addition of Pre MOD70 0657 34 validity 3 10 4 Addition of EDM procedure Post MOD70 0657 34 3 13 6 Addition of AURAL WRN FAIL procedure 3 13 7 Addition of AURAL WRN 1 CHNL procedure 4 3 33 Modification of Oxygen gr...

Page 32: ...on 13 of April 8 2019 Cont d Pages Description 2 3 3 3 9 11 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 4 3 50 4 4 18 4 4 37 thru 4 4 39 4 3 40 4 4 52 4 4 54 7 0 1A 7 0 1 7 3 2 7 3 4 7 5 1 7 5 4 7 6 5 7 7 4 7 10 1 7 15 1 8 7 9 Terminology text moving and or presentation PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 33: ... 1A 2 6 8A Deletion of paragraph SID STAR following rewording of paragraphs GNSS SBAS navigation equipment approvals and GNSS SBAS navigation system limitations 2 3 1 Correction of ITT limitation during start 2 6 2A to 2 6 5A Rewording of paragraph GNSS SBAS navigation equipment approvals 2 9 11 Addition of placard for coat hanger retrofit MOD70 0557 25C 3 10 1 to 3 10 3 Addition of instruction to...

Page 34: ... engine 4 4 41 Correction of usable oxygen graph 4 4 62 Correction of attitude at which it is required to set flaps TO 5 0 2A Correction of pages numbering for Cruise performance paragraph 5 4 1 Addition of a note explaining the curve for pressurization envelope 5 8 3A to 5 8 10A 5 8 2 to 5 8 9 Integration of a fixed torque reduction instruction when BLEED HI message ON 5 9 1 to 5 9 3 Modification...

Page 35: ...to 7 0 4 7 1 1 7 1 2 Applicability removed in footer 7 0 4 Addition of Flight Deck Information System paragraph in the Table of content was previously only on page 7 0 4A 7 5 9 Addition of CAUTION and instructions related to parking brake release 7 5 11 Correction of brake system diagram pipe between park brake valve and right wing 7 9 1 to 7 9 14 Air conditioning and pressurization system Rewordi...

Page 36: ...Integrated Flight Deck approaches 1 4 6 to 1 4 10 2 0 1A 2 0 2A 2 6 2A 2 6 2 2 6 8A to 2 6 14A 2 9 11 2 9 12 3 1 1 3 9 4 3 9 5 4 3 14 4 3 15 4 3 30 4 3 31 4 4 16 to 4 4 18 4 4 37 to 4 4 39 4 5 28 5 8 1A 5 8 3A to 5 8 10A 5 8 1 5 8 2 to 5 8 9 5 9 1 to 5 9 3 5 10 12 to 5 10 18 5 11 2A to 5 11 22A 5 11 2 to 5 11 22 7 0 3 7 0 4 7 5 9 7 9 15 to 7 9 20 7 10 8 7 15 6 to 7 15 8 Terminology text moving and...

Page 37: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 0 Page 0 40 Edition 1 June 22 2007 Rev 14 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 38: ... 1 13 0 35 1 13 0 36 1 14 0 37 1 14 0 38 1 14 0 39 1 14 0 40 1 14 0 41 1 14 0 42 1 14 0 43 1 14 0 44 1 14 0 45 1 14 0 46 1 14 0 47 1 14 0 48 1 14 1 0 1A 1 8 1 0 2A 1 8 1 0 1 1 8 1 0 2 1 8 1 1 1A 1 13 1 1 2A 1 8 1 1 1 1 13 1 1 2 1 8 1 2 1 1 6 1 2 2 1 0 1 3 1 1 0 1 3 2 1 0 1 3 3 1 12 1 3 4 1 0 1 4 1 1 6 1 4 2 1 6 1 4 3 1 6 1 4 4 1 0 1 4 5 1 0 1 4 6 1 14 1 4 7 1 14 1 4 8 1 14 1 4 9 1 14 1 4 10 1 14 1...

Page 39: ... 8 2 6 7 1 8 2 6 8 1 8 2 6 9 1 8 2 6 10 1 8 2 6 11 1 8 2 6 12 1 8 2 7 1 1 9 2 7 2 1 8 2 8 1 1 13 2 8 2 1 13 2 8 3 1 10 2 8 4 1 8 2 9 1 1 10 2 9 2 1 8 2 9 2A 1 8 2 9 2B 1 8 2 9 3 1 0 2 9 4 1 4 2 9 5 1 0 2 9 6 1 0 2 9 7 1 8 2 9 8 1 8 2 9 9 1 8 2 9 10 1 0 2 9 11 1 14 2 9 12 1 14 3 0 1 1 2 3 0 2 1 2 3 1 0A 1 blank 3 1 0B 1 2 3 1 1 1 14 3 1 2 1 0 3 2 0A 1 blank 3 2 0B 1 2 3 2 1 1 8 3 2 2 1 0 3 3 0A 1 b...

Page 40: ...1 14 3 10 9 1 13 3 10 10 1 13 3 11 0A 1 blank 3 11 0B 1 6 3 11 1 1 6 3 11 2 1 6 3 11 3 1 11 3 11 4 1 6 3 11 5 1 11 3 11 6 1 0 3 12 0A 1 blank 3 12 0B 1 2 3 12 1 1 0 3 12 2 1 10 3 12 3 1 12 3 12 4 1 0 3 13 0A 1 blank 3 13 0B 1 13 3 13 1 1 0 3 13 2 1 0 3 13 3 1 0 3 13 4 1 0 3 13 5 1 0 3 13 6 1 13 3 13 7 1 13 3 13 8 1 13 3 13 9 1 13 3 13 10 1 13 3 13 11 1 13 3 13 12 1 14 3 13 13 1 13 3 13 14 1 13 3 1...

Page 41: ...4 1 1 4 4 15 1 0 4 4 16 1 14 4 4 17 1 14 4 4 18 1 14 4 4 19 1 10 4 4 20 1 10 4 4 21 1 10 4 4 22 1 11 4 4 23 1 10 4 4 24 1 11 4 4 25 1 10 4 4 26 1 10 4 4 27 1 10 4 4 28 1 11 4 4 29 1 10 4 4 30 1 10 4 4 31 1 12 4 4 32 1 10 4 4 33 1 10 4 4 34 1 10 4 4 35 1 11 4 4 36 1 10 4 4 37 1 14 4 4 38 1 14 4 4 39 1 14 4 4 40 1 10 4 4 41 1 14 4 4 42 1 10 4 4 43 1 10 4 4 44 1 10 4 4 45 1 11 4 4 46 1 10 4 4 47 1 10...

Page 42: ...14 5 8 5 1 14 5 8 6 1 14 5 8 7 1 14 5 8 8 1 14 5 8 9 1 14 5 8 10 1 7 5 9 1 1 14 5 9 2 1 14 5 9 3 1 14 5 9 4 1 0 5 10 1 1 14 5 10 2 1 14 5 10 3 1 14 5 10 4 1 14 5 10 5 1 14 5 10 6 1 14 5 10 7 1 14 5 10 8 1 14 5 10 9 1 14 5 10 10 1 14 5 10 11 1 14 5 10 12 1 14 5 10 13 1 14 5 10 14 1 14 5 10 15 1 14 5 10 16 1 14 5 10 17 1 14 5 10 18 1 14 5 11 1A 1 7 5 11 2A 1 14 5 11 3A 1 14 5 11 4A 1 14 5 11 5A 1 14...

Page 43: ... 6 4 17 1 12 6 4 18 1 12 6 4 19 1 12 6 4 20 1 12 6 4 21 1 12 6 4 22 1 12 6 4 23 1 12 6 4 24 1 12 6 4 25 1 12 6 4 26 1 12 6 5 1 1 0 6 5 2 1 0 7 0 1 1 14 7 0 2 1 14 7 0 3 1 14 7 0 4 1 14 7 1 1 1 14 7 1 2 1 14 7 2 1 1 9 7 2 2 1 8 7 2 1A 1 8 7 2 2A 1 8 7 2 3 1 0 7 2 4 1 0 7 2 5 1 0 7 2 6 1 0 7 2 7 1 0 7 2 8 1 0 7 3 1 1 13 7 3 2 1 13 7 3 3 1 12 7 3 4 1 13 7 3 5 1 13 7 3 6 1 12 7 3 7 1 12 7 3 8 1 12 7 3...

Page 44: ... 9 1 0 7 6 10 1 0 7 6 11 1 0 7 6 12 1 0 7 7 1 1 0 7 7 2 1 0 7 7 3 1 0 7 7 4 1 13 7 7 5 1 10 7 7 6 1 0 7 7 7 1 10 7 7 8 1 11 7 7 9 1 0 7 7 10 1 0 7 8 1 1 0 7 8 2 1 1 7 8 3 1 1 7 8 4 1 1 7 8 5 1 13 7 8 6 1 6 7 8 7 1 12 7 8 8 1 6 7 8 9 1 12 7 8 10 1 13 7 8 11 1 13 7 8 12 1 13 7 8 13 1 6 7 8 14 1 6 7 8 15 1 6 7 8 16 1 6 7 8 17 1 6 7 8 18 1 6 7 8 19 1 6 7 8 20 1 8 7 8 21 1 8 7 8 22 1 6 7 9 1 1 14 7 9 2...

Page 45: ... 1 14 7 15 8 1 14 8 0 1 1 0 8 0 2 1 9 8 1 1 1 0 8 1 2 1 0 8 2 1 1 0 8 2 2 1 0 8 3 1 1 13 8 3 2 1 0 8 4 1 1 0 8 4 2 1 0 8 5 1 1 0 8 5 2 1 0 8 6 1 1 0 8 6 2 1 0 8 6 3 1 8 8 6 4 1 8 8 6 5 1 8 8 6 6 1 8 8 7 1 1 12 8 7 2 1 12 8 7 3 1 0 8 7 4 1 0 8 7 5 1 0 8 7 6 1 0 8 7 7 1 0 8 7 8 1 0 8 7 9 1 13 8 7 10 1 0 8 7 11 1 0 8 7 12 1 0 8 7 13 1 0 8 7 14 1 0 8 8 1 1 10 8 8 2 1 0 8 9 1 1 0 8 9 2 1 0 8 10 1 1 9 8...

Page 46: ...DARD AIRPLANE WEIGHTS 1 3 3 CABIN AND ENTRY DIMENSIONS 1 3 4 SPECIFIC LOADINGS 1 3 4 1 4 ABBREVIATIONS AND TERMINOLOGY 1 4 1 METEOROLOGICAL TERMINOLOGY 1 4 1 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 1 4 1 POWER TERMINOLOGY 1 4 3 AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 1 4 4 WEIGHT AND BALANCE TERMINOLOGY 1 4 4 GENERAL ABBREVIATIONS 1 4 6 RADIO NAVIGATION ABBREVIATIONS 1 4 9 1 5 CONVER...

Page 47: ...BM PILOT S OPERATING HANDBOOK 850 SECTION 1 GENERAL Page 1 0 2A Edition 1 June 22 2007 Rev 8 POST GARMIN SOFTWARE VERSION 12 01 or ANY LATER INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 48: ...PLANE WEIGHTS 1 3 3 CABIN AND ENTRY DIMENSIONS 1 3 4 SPECIFIC LOADINGS 1 3 4 1 4 ABBREVIATIONS AND TERMINOLOGY 1 4 1 METEOROLOGICAL TERMINOLOGY 1 4 1 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 1 4 1 POWER TERMINOLOGY 1 4 3 AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 1 4 4 WEIGHT AND BALANCE TERMINOLOGY 1 4 4 GENERAL ABBREVIATIONS 1 4 6 RADIO NAVIGATION ABBREVIATIONS 1 4 9 1 5 CONVERSION FAC...

Page 49: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 1 GENERAL Page 1 0 2 Edition 1 June 22 2007 Rev 8 PRE GARMIN SOFTWARE VERSION 12 01 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 50: ...k Pilot s Guide it states the one described in section 2 1 Post MOD70 0335 34 ESI 2000 Whenever this POH refers to the Electronic Standby Indicator MODEL ESI 2000 Pilot s Guide it states the one described in section 2 1 All The general for complex optional systems are given in Section 9 Supplements of the Pilot s Operating Handbook PART 135 OPERATIONS For 14 CFR 135 operations TBM aircraft alterna...

Page 51: ...BM PILOT S OPERATING HANDBOOK 850 SECTION 1 GENERAL Page 1 1 2A Edition 1 June 22 2007 Rev 8 POST GARMIN SOFTWARE VERSION 12 01 or ANY LATER INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 52: ... commonly used Whenever this POH refers to the GARMIN integrated Flight Deck Pilot s Guide it states the one described in section 2 1 The general for complex optional systems are given in Section 9 Supplements of the Pilot s Operating Handbook PART 135 OPERATIONS For 14 CFR 135 operations TBM aircraft alternative source of electric power is able to supply 150 percent of the electrical loads of all...

Page 53: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 1 GENERAL Page 1 1 2 Edition 1 June 22 2007 Rev 8 PRE GARMIN SOFTWARE VERSION 12 01 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 54: ... PILOT S OPERATING HANDBOOK Page 1 2 1 Edition 1 June 22 2007 Rev 6 1 2 THREE VIEW DRAWING Figure 1 2 1 1 2 THREE VIEW DRAWING Airplane on level field with fully extended FWD shock absorber PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 55: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 1 GENERAL Page 1 2 2 Edition 1 June 22 2007 Rev 0 Figure 1 2 1 2 2 THREE VIEW DRAWING PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 56: ...type 1 gas generator turbine stage 2 power turbines stages Horsepower rating and propeller speed 850 SHP at 2000 RPM PROPELLER Number of propellers 1 Propeller manufacturer HARTZELL Propeller model number HC E4N 3 E9083S K Number of blades 4 Propeller diameter Minimum 90 inches 2 286 m Maximum 91 inches 2 311 m Propeller type Adjustable constant speed with feathering and hydraulic control reverse ...

Page 57: ...OSES ONLY AVGAS SHALL NOT BE USED FOR MORE THAN 150 CUMULATIVE HOURS DURING ANY PERIOD BETWEEN ENGINE OVERHAUL PERIODS NOTE Use of AVGAS to be recorded in engine module logbook US Specification US French Specification FR English Specification UK NATO Code ASTM D1655 JET A ASTM D1655 JET A1 ASTM D1655 JET B AIR 3405C Grade F35 DERD 2494 Issue 9 F35 without additive MIL DTL 5624 Grade JP 4 AIR 3407B...

Page 58: ...9G O 156 STD O 154 HTS Figure 1 3 2 RECOMMENDED ENGINE OIL TYPES Reference Service Bulletin P W C No 14001 at the latest revision MAXIMUM CERTIFICATED WEIGHTS Ramp 7430 lbs 3370 kg Takeoff 7394 lbs 3354 kg Landing 7024 lbs 3186 kg Baggage weight refer to Section 2 Paragraph 2 5 for weight and C G limits refer to Section 6 for cargo loading instructions STANDARD AIRPLANE WEIGHTS Standard empty weig...

Page 59: ... 45 4 05 m Maximum cabin height 4 1 22 m Number of cabin entries 1 standard 1 pilot door if installed Entry width standard 3 6 52 1 08 m Entry height standard 3 10 85 1 19 m Pilot entry mean width 2 3 6 0 70 m Pilot entry mean height 3 2 16 0 97 m SPECIFIC LOADINGS Wing loading 38 16 lbs sq ft 186 3 kg m2 Power loading 8 7 lbs SHP 3 95 kg SHP PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 60: ...r each 1000 ft of altitude Pressure altitude Is the altitude read from an altimeter when the altimeter s barometric scale has been set to 29 92 inches of mercury 1013 2 hPa GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is the indicated airspeed expressed in knots corrected for position and instrument error Knots calibrated airspeed is equal to KTAS in standard atmosphere ...

Page 61: ...eed limit that may not be deliberately exceeded in normal flight operations VR Rotation Speed is the speed at which rotation is initiated during takeoff to achieve takeoff safety speed at screen height VSO Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration VS1 Stalling Speed or the minimum steady flight speed obtained in a specific ...

Page 62: ...ng start Flame out Involuntary loss of the combustion chamber flame during operation GPU Ground power unit Feathering Action which reduces the drag of a propeller by positioning blades at the pitch angle allowing minimal drag Maximum Cruise Power Power developed corresponding to outside Flight Level and Temperature conditions Refer to Chapter 5 PERFORMANCE Ng Gas generator RPM Np Propeller rotatio...

Page 63: ...tion tests The value shown is not considered to be limiting g Is acceleration due to gravity Usable fuel Total fuel which can be effectively consumed by the engine WEIGHT AND BALANCE TERMINOLOGY Reference datum Datum perpendicular to the longitudinal airplane centerline from which all distances are measured for balance purpose Arm Is the distance from the reference datum to the center of gravity C...

Page 64: ... operating fluids oil and hydraulic fluids Basic empty weight Standard empty weight plus optional equipment Useful load Is the difference between maximum ramp weight and the basic empty weight Maximum ramp weight Is the maximum weight approved for ground maneuver It includes the weight of start taxi and run up fuel Maximum takeoff weight Is the maximum weight approved at the beginning of the takeo...

Page 65: ...em C Celsius degree CHiPS Cable Harness Protection System CONT Control DIEGME Diethylene glycol monomethyl ether DISC Disconnect DN Down ECS Environmental control system EDM Emergency Descent Mode EGME Ethylene glycol monomethyl ether EMER Emergency ENCOD ALTI Encoding altimeter ESHP Estimated shaft horsepower ESS BUS TIE Essential BUS tie EXT LIGHTS Exterior lightings F Fahrenheit degree FCU Fuel...

Page 66: ...l mile hr 1852 m hr kW Kilowatt l Litre L Left l h Litre hour lb or lbs Pound s L D Lift to drag LDG Landing LDG GR Landing gear LRCR Long Range Cruise LO Low LP Low pressure LRN Long range navigation LTS TEST Lightings test m Metre m a c Mean aerodynamic chord MAIN GEN Main generation MAN Manual MAN OVRD Manual override MAX RPM Maximum revolutions per minute MDA Minimum Descent Altitude MFD Multi...

Page 67: ...lan Horizontal Fixe Horizontal stabilizer PRESS Pressure PROP Propeller psi Pounds per square inch qt Quart us gal QTY Quantity R Red or Right RUD Rudder s or sec Second SEL Selector SIG Signalization SL Sea level S N Serial number SPKR Speaker ST BY Stand by STALL HTR Stall heater Std Standard T Temperature TEMP Temperature TO Takeoff TURN COORD Turn coordinator us gal Gallon U S V Volt or Voltag...

Page 68: ...COM Communications Transceivers DME Distance Measuring Equipment ELT Emergency Locator Transmitter FDE Fault Detection and Exclusion FMS Flight Management System GNSS Global Navigation Satellite System GPS Ground Positioning System HF High Frequency IFR Instrument Flight Rules ILS Instrument Landing System IMC Instrument Meteorological Conditions L NAV Lateral NAVigation LPV Localizer Precision Ve...

Page 69: ...S Traffic Advisory System TAWS Terrain Awareness Warning System VFR Visual Flight Rules VHF Very High Frequency VMC Visual Meteorological Conditions V NAV Vertical NAVigation VOR VHF Omnidirectional Range VOR LOC VHF Omnidirectional Range LOCalizer WAAS Wide Area Augmentation System WFDE WAAS Fault Detection and Exclusion WGS World Geodetic System WXR Weather surveillance radar XPDR Transponder PI...

Page 70: ...C UNITS METRIC UNITS TO IMPERIAL AND U S UNITS MULTIPLY BY TO OBTAIN MULTIPLY BY TO OBTAIN FEET 0 3048 METRE METRE 3 2808 FEET INCH 25 4 mm mm 0 03937 INCH Imp Gal 4 546 Litre Litre 0 220 Imp Gal us gal 3 785 Litre Litre 0 264 us gal lb 0 45359 kg kg 2 2046 lb Figure 1 5 1 IMPERIAL AND U S UNITS TO METRIC UNITS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 71: ... S OPERATING HANDBOOK 850 SECTION 1 GENERAL Page 1 5 2 Edition 1 June 22 2007 Rev 0 Figure 1 5 2 FEET VERSUS METRES Metres 30000 20000 10000 0 Feet 2500 5000 7500 10000 31000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 72: ...CTION 1 GENERAL TBM 850 PILOT S OPERATING HANDBOOK Page 1 5 3 Edition 1 June 22 2007 Rev 0 Figure 1 5 3 INCHES VERSUS MILLIMETRES mm 10 0 In 250 500 750 1000 20 30 40 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 73: ...LOT S OPERATING HANDBOOK 850 SECTION 1 GENERAL Page 1 5 4 Edition 1 June 22 2007 Rev 0 Figure 1 5 4 POUNDS VERSUS KILOGRAMS 1000 2000 3000 2000 6000 4000 0 Kg Lb 4000 8000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 74: ...2000 942 1 11 0 51 8 4000 875 0 7 0 44 6 6000 811 9 3 1 37 6 8000 752 6 0 8 30 5 10000 696 8 4 8 23 4 12000 644 3 8 7 16 2 14000 595 2 12 7 9 2 16000 549 1 16 6 2 2 18000 505 9 20 6 5 0 20000 465 6 24 6 12 4 22000 427 8 28 5 19 3 24000 392 6 32 5 26 5 26000 359 8 36 5 33 6 28000 329 3 40 4 40 7 30000 300 8 44 4 47 8 31000 287 4 46 4 51 6 Figure 1 6 1 STANDARD ATMOSPHERE PIM DO NOT USE FOR FLIGHT O...

Page 75: ...29 12 987 29 15 988 29 18 989 29 20 990 29 23 991 29 26 992 29 29 993 29 32 994 29 35 995 29 38 996 29 41 997 29 44 998 29 47 999 29 50 1000 29 53 1001 29 56 1002 29 59 1003 29 62 1004 29 65 1005 29 68 1006 29 71 1007 29 74 1008 29 77 1009 29 80 1010 29 83 1011 29 85 1012 29 88 1013 29 91 1014 29 94 1015 29 97 1016 30 00 1017 30 03 1018 30 06 1019 30 09 1020 30 12 1021 30 15 1022 30 18 1023 30 21 ...

Page 76: ...IGHT AND C G LIMITS 2 5 1 WEIGHT LIMITS 2 5 1 C G LIMITS 2 5 2 2 6 OPERATION LIMITS 2 6 1A MANEUVER LIMITS 2 6 1A TEMPERATURE LIMITS 2 6 1A FLIGHT LOAD FACTOR LIMITS 2 6 1A GFC 700 AUTOPILOT LIMITS 2 6 2A G1000 GNSS GPS SBAS NAVIGATION EQUIPMENT APPROVALS 2 6 2A G1000 GNSS GPS SBAS NAVIGATION SYSTEM LIMITATIONS 2 6 6A SEVERE ICING CONDITIONS 2 6 8A FLAP OPERATING ENVELOPE 2 6 9A REVERSE UTILIZATIO...

Page 77: ...TIONS 2 6 14A 2 7 MISCELLANEOUS LIMITS 2 7 1 SEATING LIMITS C G 2 7 1 BAGGAGE LIMITS 2 7 1 MINIMUM CREW 2 7 1 MAXIMUM OCCUPANCY 2 7 1 USE OF DOORS 2 7 1 CHEMICAL TOILET CABINET 2 7 1 CARGO NET INSTALLATION LIMITS 2 7 2 2 8 MARKINGS 2 8 1 AIRSPEED INDICATOR ON PFD s 2 8 1 STANDBY AIRSPEED INDICATOR 2 8 1 PRESSURIZATION 2 8 2 ENGINE INSTRUMENTS 2 8 3 SUCTION GAGE PRE MOD70 0335 34 ESI 2000 2 8 4 2 9...

Page 78: ...GHT AND C G LIMITS 2 5 1 WEIGHT LIMITS 2 5 1 C G LIMITS 2 5 2 2 6 OPERATION LIMITS 2 6 1 MANEUVER LIMITS 2 6 1 TEMPERATURE LIMITS 2 6 1 FLIGHT LOAD FACTOR LIMITS 2 6 1 GFC 700 AUTOPILOT LIMITS 2 6 2 GPS NAVIGATION LIMITS 2 6 2 SID STAR 2 6 4 SEVERE ICING CONDITIONS 2 6 5 FLAP OPERATING ENVELOPE 2 6 6 REVERSE UTILIZATION 2 6 6 EQUIPMENT REQUIRED DEPENDING ON TYPE OF OPERATION 2 6 6 ALTITUDE OPERATI...

Page 79: ...1 SEATING LIMITS C G 2 7 1 BAGGAGE LIMITS 2 7 1 MINIMUM CREW 2 7 1 MAXIMUM OCCUPANCY 2 7 1 USE OF DOORS 2 7 1 CHEMICAL TOILET CABINET 2 7 1 CARGO NET INSTALLATION LIMITS 2 7 2 2 8 MARKINGS 2 8 1 AIRSPEED INDICATOR ON PFD s 2 8 1 STANDBY AIRSPEED INDICATOR 2 8 1 PRESSURIZATION 2 8 2 ENGINE INSTRUMENTS 2 8 3 SUCTION GAGE PRE MOD70 0335 34 ESI 2000 2 8 4 2 9 PLACARDS 2 9 1 PIM DO NOT USE FOR FLIGHT O...

Page 80: ...er version as applicable must be permanently kept in the airplane with the Pilot s Operating Handbook Departure into IMC is not authorized if the battery symbol is present with an amber battery symbol less than 1 hour remaining or an amber or red X over the battery symbol or a CAL DUE message by the battery symbol All This Section of the airplane Pilot s Operating Handbook presents the various ope...

Page 81: ...S OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 1 2A Edition 1 June 22 2007 Rev 8 POST GARMIN SOFTWARE VERSION 12 01 or ANY LATER INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 82: ...190 00709 07 or any later version as applicable must be readily available to the pilot This Section of the airplane Pilot s Operating Handbook presents the various operating limitations the significance of such limitations instrument markings color coding and basic placards necessary for the safe operation of the airplane its powerplant and installed equipment The limitations included in this Sect...

Page 83: ...M PILOT S OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 1 2 Edition 1 June 22 2007 Rev 8 PRE GARMIN SOFTWARE VERSION 12 01 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 84: ...l control movements above this speed VFE Maximum flaps extended speed landing configuration takeoff configuration 120 180 122 178 Do not exceed these speeds depending on flaps position VLO Maximum landing gear operating speed extension retraction 180 130 178 128 Do not extend or retract landing gear above this speed VLE Maximum landing gear extended speed 180 178 Do not exceed this speed with land...

Page 85: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 2 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 86: ...aximum power Flaps set to UP TO or LDG position Flaps set to 850 position 100 at Np 2000 RPM 121 4 at Np 2000 RPM 110 at Np 1800 RPM Ng limitation 104 1 Np limitation 2000 RPM ITT limitations Take off 850 C Maximum climb cruise 840 C During start 840 C no duration limitation 870 C for 20 seconds max 1000 C for 5 seconds max CAUTION WHEN NORMALLY OPERATING REFER TO CHAPTER 5 8 ENGINE OPERATION TABL...

Page 87: ...um 60 psi Maximum 135 psi Oil capacity System total capacity 12 7 Quarts 12 Litres Oil cooler included Usable capacity 6 Quarts 5 7 Litres FUEL Fuel pressure Minimum 10 psi Maximum 50 psi Fuel limitations 2 tanks 150 5 us gal 570 Litres each Total fuel 301 us gal 1140 Litres Usable fuel 292 us gal 1106 Litres Unusable fuel 9 us gal 34 Litres Maximum fuel unbalance 15 us gal 57 Litres NOTE Usable f...

Page 88: ...BETWEEN ENGINE OVERHAUL PERIODS NOTE Use of AVGAS to be recorded in engine module logbook CAUTION MAXIMUM TIME FOR SIDESLIP CONDITION IS 30 SECONDS US Specification US French Specification FR English Specification UK NATO Code ASTM D1655 JET A ASTM D1655 JET A1 ASTM D1655 JET B AIR 3405C Grade F35 DERD 2494 Issue 9 F35 without additive MIL DTL 5624 Grade JP 4 AIR 3407B DERD 2454 Issue 4 Amdt 1 F40...

Page 89: ...v 0 PROPELLER Number of propellers 1 Propeller manufacturer HARTZELL Propeller model number HC E4N 3 E9083S K Propeller diameter Minimum 90 inches 2 286 m Maximum 91 inches 2 311 m Propeller blade setting at 30 inches station Low pitch 21 Feathering 86 Maximum reverse 11 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 90: ... 4 STARTER OPERATION LIMITS Starter operation sequence is limited as follows if Ng 30 30 seconds if Ng 30 60 seconds Should several sequences be necessary respect following spacing 1st sequence wait 1 minute 2nd sequence wait 5 minutes 3rd sequence wait 30 minutes 4th sequence PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 91: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 4 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 92: ...um 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 Pre MOD 70 0315 25 Post MOD 70 0315 25 with 6 seat accommodation in rear part of pressurized cabin 220 lbs 100 kg Post MOD 70 0315 25 with 4 seat accommodation in rear part of pressurized cabin 396 lbs 180 kg with small or large net see sketc...

Page 93: ...inches 4 752 m aft of datum at all weights above 7024 lbs 3186 kg 23 8 of m a c Aft limits 194 9 inches 4 951 m aft of datum at all weights below 6250 lbs 2835 kg 37 of m a c 194 3 inches 4 936 m aft of datum at 6579 lbs 2984 kg 36 of m a c 193 65 inches 4 921 m aft of datum at 7394 lbs 3354 kg 35 of m a c Reference datum 118 1 inches 3 m in front of the firewall front face Straight line variation...

Page 94: ...ep turns in which the angle of bank is no more than 60 Aerobatic maneuvers including spins are not approved TEMPERATURE LIMITS Minimum temperature at start and takeoff 40 C 40 F Maximum temperature at start and takeoff ISA 37 C 67 F from 0 to 8000 ft pressure altitude Maximum temperature in flight ISA 37 C 67 F from 0 to 8000 ft pressure altitude ISA 30 C 54 F at 31000 ft pressure altitude Linear ...

Page 95: ...below 2000 ft 600 m AGL with a vertical speed in excess of 2000 ft min G1000 GNSS GPS SBAS NAVIGATION EQUIPMENT APPROVALS The GARMIN GNSS navigation system installed in this airplane is a GPS system with a Satellite Based Augmentation System SBAS comprised of two TSO C145a or later Class 3 approved GARMIN GIAs TSO C146a Class 3 approved GARMIN GDUs Display Units GARMIN GA36 and GA37 antennas GPS s...

Page 96: ...anic and Remote continental Class II Navigation RNAV 10 RNP 10 GNSS FDE availability must be verified prior to flight Maximum predicted FDE unavailability is 34 minutes 1 Two GNSS systems requi red to be operational 2 FAA AC 90 105A R A1 Additional com munication and surveillance equipment may be required to obtain ope rational approval to utilize RNP 10 RNAV 10 perfor mance En route continental A...

Page 97: ...veillance equipment may be required to obtain ope rational approval to utilize RNP 2 performance Departure Arrival RNP 1 with and without RF legs At a minimum the flight director must be displayed and utilized when conducting procedures containing RF legs FAA AC 90 105A R O2 Includes RNP terminal departure and arrival pro cedures This includes pro cedures with Radius to Fix legs RF legs Approach R...

Page 98: ... terminal RAIM prediction website www raimprediction net or by contacting a Flight Service Station Within Europe using Europe s AUGUR GPS RAIM Prediction Tool at http augur ecacnav com augur app home Note 2 A BOTH ON GPS1 or BOTH ON GPS2 system annunciation does not necessarily mean that one GPS has failed Refer to the MFD GPS STATUS page to determine the state of the unused GPS General considerat...

Page 99: ...lidate a procedure must be reported to Garmin International The affected procedure is prohibited from being flown using data from the Navigation database until a new Navigation database is installed in the airplane and verified that the discrepancy has been corrected Contact information to report Navigation database discrepancies can be found at www Garmin com Support Contact Garmin Support Aviati...

Page 100: ...ended route of flight the flight should be delayed cancelled or re routed on a track where RAIM requirements can be met For flight planning purposes in Remote Continental and Oceanic areas the pilot must check FDE availability Referto the Table 2 6 1 GNSS operational requirements to check maximum authorized FDE unavailability and WFDE Prediction program references Approach operations limitations L...

Page 101: ...the aircraft is certificated shall be determined by the following visual cues If one or more of these visual cues exists immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice Accumulation of ice on the up...

Page 102: ...operations when appropriate equipment is installed and operating correctly The type certification for each use requires the following equipment The equipment must be installed and operate perfectly according to the indicated type of use CAUTION IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT THE FOLLOWING EQUIPMENT LISTS ARE IN ACCORDANCE WITH THE SPECIFIC NATIONAL OPERATION RULES OF THE AIRPLANE R...

Page 103: ...uel pressure Fuel selector OFF Fuel auxiliary pump ON L H and R H fuel tank low level Non functioning of fuel timer Battery overheat Battery stop Main generator OFF Low voltage Ground power unit connected Inertial separator Starter Ignition Flaps Landing gears and doors 10 Aural warning VMO warning Landing gear warning Stall warning 11 Engine instruments Torquemeter Propeller tachometer Interturbi...

Page 104: ...mechanical pump main Fuel electrical pump auxiliary Fuel shut off valve Fuel timer Starter generator Inertial separator Stall warning Electrical aileron trim Electrical rudder trim Manual elevator pitch trim Engine ignition Landing gear electro hydraulic unit Landing gear emergency hydraulic pump manual Flaps Overspeed regulator Manual feathering Battery 14 Miscellaneous Seats each occupant Belts ...

Page 105: ...ht VFR if flight is performed during night 3 Taxi light if flight is performed during night 4 Clock 5 2nd altimeter 6 Emergency static source 7 Pitot static tube deicing Pressurized flight Cabin altimeter Cabin vertical speed indication Cabin differential pressure indication Pressurization control valve Safety valve Pressurization control Maximum cabin altitude and pressure warning light Flight in...

Page 106: ...ed in accordance with applicable operating rules Each operator must ensure compliance with required crew training and operating practices and procedures Moreover the following equipment must be installed and operating normally upon entering RVSM airspace Pilot and R H station primary altimeters Autopilot Altitude Alerter ATC transponder NOTE Any changes to the pitot static air data computer autopi...

Page 107: ... CHARTVIEW SYSTEM OPERATING LIMITATIONS The geographic referenced airplane symbol on some charts must not be used for navigation NOTE The airplane symbol displayed on some charts provides supplemental airplane situational awareness information It is not intended as a means for navigation or flight guidance The airplane symbol is not to be used for conducting instrument approaches or departures and...

Page 108: ...s in which the angle of bank is no more than 60 Aerobatic maneuvers including spins are not approved TEMPERATURE LIMITS Minimum temperature at start and takeoff 40 C 40 F Maximum temperature at start and takeoff ISA 37 C 67 F from 0 to 8000 ft pressure altitude Maximum temperature in flight ISA 37 C 67 F from 0 to 8000 ft pressure altitude ISA 30 C 54 F at 31000 ft pressure altitude Linear decreas...

Page 109: ...d check on available ground aids or shall allow to return to primary navigation sources in case of GPS navigation loss Use of GPS as a navigation source is PROHIBITED unless the pilot verifies the currency of the data base and the coordinates of each selected waypoint The aircraft is approved for Enroute and Terminal operations including RNAV5 BRNAV and RNAV1 PRNAV in accordance with JAA TGL 10 pr...

Page 110: ...nnot be done In that case the flight will either be postponed or another route will be chosen The prediction software must then be used again Preflight procedures During preflight checks it is necessary to verify data base validity updating of the last AIRAC cycle The onboard equipment must be initialized in compliance with manufacturer procedures refer to the GARMIN G1000 Integrated Flight Deck P...

Page 111: ...he official documentation coordinates of various points and paths between points Instrument approach Non precision approach Use of the GPS to perform an instrument approach is possible as long as this use is approved by the air navigation local authority for the approach in question Instrument approaches performed with the GPS must be executed according to approved approach procedures given in the...

Page 112: ...or more of these visual cues exists immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice Accumulation of ice on the upper surface of the wing aft of the protected area Since the autopilot when operating ...

Page 113: ...ns when appropriate equipment is installed and operating correctly The type certification for each use requires the following equipment The equipment must be installed and operate perfectly according to the indicated type of use CAUTION IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT THE FOLLOWING EQUIPMENT LISTS ARE IN ACCORDANCE WITH THE SPECIFIC NATIONAL OPERATION RULES OF THE AIRPLANE REGISTRAT...

Page 114: ...ure Fuel selector OFF Fuel auxiliary pump ON L H and R H fuel tank low level Non functioning of fuel timer Battery overheat Battery stop Main generator OFF Low voltage Ground power unit connected Inertial separator Starter Ignition Flaps Landing gears and doors 10 Aural warning VMO warning Landing gear warning Stall warning 11 Engine instruments Torquemeter Propeller tachometer Interturbine temper...

Page 115: ...l pump main Fuel electrical pump auxiliary Fuel shut off valve Fuel timer Starter generator Inertial separator Stall warning Electrical aileron trim Electrical rudder trim Manual elevator pitch trim Engine ignition Landing gear electro hydraulic unit Landing gear emergency hydraulic pump manual Flaps Overspeed regulator Manual feathering Battery 14 Miscellaneous Seats each occupant Belts each occu...

Page 116: ...f flight is performed during night 3 Taxi light if flight is performed during night 4 Clock 5 2nd altimeter 6 Emergency static source 7 Pitot static tube deicing Pressurized flight Cabin altimeter Cabin vertical speed indication Cabin differential pressure indication Pressurization control valve Safety valve Pressurization control Maximum cabin altitude and pressure warning light Flight into icing...

Page 117: ...cordance with applicable operating rules Each operator must ensure compliance with required crew training and operating practices and procedures Moreover the following equipment must be installed and operating normally upon entering RVSM airspace Pilot and R H station primary altimeters Autopilot Altitude Alerter ATC transponder NOTE Any changes to the pitot static air data computer autopilot alti...

Page 118: ...EW SYSTEM OPERATING LIMITATIONS The geographic referenced airplane symbol on some charts must not be used for navigation NOTE The airplane symbol displayed on some charts provides supplemental airplane situational awareness information It is not intended as a means for navigation or flight guidance The airplane symbol is not to be used for conducting instrument approaches or departures and it shou...

Page 119: ... PILOT S OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 6 12 Edition 1 June 22 2007 Rev 8 PRE GARMIN SOFTWARE VERSION 12 01 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 120: ...seats at 267 1 in 6 785 m BAGGAGE LIMITS Baggage in pressurized cabin at 303 inches 7 695 m Baggage in non pressurized forward section at 128 inches 3 250 m MINIMUM CREW One pilot MAXIMUM OCCUPANCY The number of persons on board is limited by approved seating configuration installed but must not exceed six including the pilot The number of persons must be less than or equal to the number of seats ...

Page 121: ... Rev 8 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 CAUTION NO ITEM MAY EXTEND FORWARD OF THE CARGO NET SYSTEM TO PROTECT DOOR FROM OBSTRUCTION PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 122: ...nge Red white barber pole strip Above 266 266 VMO Figure 2 8 1 AIRSPEED INDICATOR MARKINGS Pre MOD70 0335 34 ESI 2000 STANDBY AIRSPEED INDICATOR Indicated airspeed markings and their color code significance are shown in Figure 2 8 1A MARKING KIAS Value or range SIGNIFICANCE White arc 65 122 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Wide 65 81 Transition p...

Page 123: ...RKING KIAS Value or range SIGNIFICANCE Red strip Below 65 White strip 65 122 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Green strip 122 266 Normal operating airspeed range Red strip 266 Maximum speed for all operations Figure 2 8 1B STANDBY AIRSPEED INDICATOR MARKINGS All PRESSURIZATION MARKING VALUE SIGNIFICANCE Red line 6 2 psi Cabin P limit Figure 2 8 2...

Page 124: ...um Limit Oil temperature 40 C 40 to 0 C 104 to 110 C 0 to 104 C 110 C Oil pressure 60 psi 60 to 100 psi 100 to 135 psi 135 psi Fuel pressure 0 to 5 psi 10 to 50 psi 50 psi Generator RPM Ng 51 to 104 104 Propeller RPM Np 450 to 1000 RPM 1600 to 2000 RPM 2000 RPM ITT Engine start or off 840 to 1090 C 400 to 840 C 840 C normal limit 870 C 20 seconds limit 1090 C red line absolute limit Engine running...

Page 125: ...Approved Page 2 8 4 Edition 1 June 22 2007 Rev 8 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 126: ...ompass and on windshield post For N 30 60 E 120 150 Steer For S 210 240 W 300 330 Steer DATE RADIO ON 3 On pressurized baggage compartment partition wall 100 kg 220 lbs MAXIMUM IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT ALL THE BAGGAGES ARE PROPERLY SECURED FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA IN PILOT S OPERATING HANDBOOK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 127: ...a For the small cargo net on frame C13bis 3 b For the large cargo net on R H side upholstery panel in the rear baggage compartment All 3 c On FWD baggage compartment door frame non pressurized 50 kg 110 lbs MAXIMUM FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA IN PILOT S OPERATING HANDBOOK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 128: ...SECTION 2 LIMITATIONS EASA Approved TBM 850 PILOT S OPERATING HANDBOOK Page 2 9 2A Edition 1 June 22 2007 Rev 8 4 Under GCU 475 control unit on pedestal console PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 129: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 9 2B Edition 1 June 22 2007 Rev 8 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 130: ...SECTION 2 LIMITATIONS EASA Approved TBM 850 PILOT S OPERATING HANDBOOK Page 2 9 3 Edition 1 June 22 2007 Rev 0 5 On fuel selector 6 Near fuel tank caps PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 131: ... Rev 4 7 On internal face of L H engine cowling Oil system capacity 12 l 12 7 qt 8 On landing gear emergency control access door LDG GEAR EMERGENCY ACCESS PULL 9 On rear passenger s table casing TABLE MUST BE STOWED DURING TAKEOFF AND LANDING 10 Under R H control wheel PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 132: ...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 28 VOLTS D C NOMINAL 800 AMPS STARTING CAPACITY MIN DO NOT EXCEED 1400 AMPS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 133: ... OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 9 6 Edition 1 June 22 2007 Rev 0 15 On pilot door External side if installed 16 On access door External side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 134: ...oved TBM 850 PILOT S OPERATING HANDBOOK Page 2 9 7 Edition 1 June 22 2007 Rev 8 17 On outer fuselage skin aft of access door and in the cabin forward of access door 18 On access door Internal side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 135: ...BOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 9 8 Edition 1 June 22 2007 Rev 8 19 On pilot door Internal side if installed 20 On emergency exit handle Marking on cover Marking on handle PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 136: ... 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 side on the ceiling 24 On rear passengers masks containers PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 137: ...ATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 9 10 Edition 1 June 22 2007 Rev 0 25 On internal face of the oxygen cylinder service door 26 On the oxygen service door PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 138: ... 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 side at front seat level PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 139: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 2 LIMITATIONS EASA Approved Page 2 9 12 Edition 1 June 22 2007 Rev 14 31 On the lower drawer of the R H cabinet PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 140: ...FAILURES 3 3 1 3 4 AIR START 3 4 1 3 5 FIRE AND SMOKE 3 5 1 3 6 EMERGENCY DESCENTS 3 6 1 3 7 EMERGENCY LANDINGS 3 7 1 3 8 FUEL SYSTEM 3 8 1 3 9 ELECTRICAL SYSTEM 3 9 1 3 10 PRESSURIZATION AND AIR CONDITIONING 3 10 1 3 11 LANDING GEAR AND FLAPS 3 11 1 3 12 DEICING SYSTEM 3 12 1 3 13 MISCELLANEOUS 3 13 1 NOTE Sub title for each Section 3 chapter is given at the back of their respective divider herea...

Page 141: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 0 2 Edition 1 June 22 2007 Rev 2 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 142: ...3 1 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 143: ...T S OPERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 1 0B Edition 1 June 22 2007 Rev 2 SECTION 3 1 GENERAL TABLE OF CONTENTS Page 3 1 GENERAL 3 1 1 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 144: ...lot s operating handbook supplements are provided in Section 9 Supplements The pilot must know procedures given in this section and be prepared to take appropriate action should an emergency arise Some emergency procedures are a part of pilot basic training Although these emergencies are discussed here this information is not intended to replace such training but only to provide a source of refere...

Page 145: ... amber messages indicating failures or discrepancies which require an action as soon as practical Red or amber failure warnings are coupled with the lighting of a flashing red indicator or a fixed amber indicator Both indicators are located on the upper part of the L H instrument panel When either one lights up press it once to reactivate It will go out and is ready to signal in the event of anoth...

Page 146: ...3 2 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 147: ...OOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 2 0B Edition 1 June 22 2007 Rev 2 SECTION 3 2 REJECTED TAKEOFF PROCEDURE TABLE OF CONTENTS Page 3 2 REJECTED TAKEOFF PROCEDURE 3 2 1 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 148: ...ure refer to Chapter 3 3 Paragraph ENGINE FAILURE AT TAKEOFF BEFORE ROTATION For any other reason 1 Power lever IDLE 2 Reverse AS REQUIRED 3 Braking AS REQUIRED If the airplane cannot be stopped on the remaining runway 4 Power lever IDLE 5 Condition lever CUT OFF 6 Tank selector OFF 7 CRASH lever PULL DOWN Evacuate if necessary after the airplane has come to a stop PIM DO NOT USE FOR FLIGHT OPERAT...

Page 149: ... PILOT S OPERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 2 2 Edition 1 June 22 2007 Rev 0 REJECTED TAKEOFF PROCEDURE INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 150: ...3 3 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 151: ...3 3 1 ENGINE FAILURE AFTER ROTATION 3 3 2 ENGINE FAILURE DURING FLIGHT 3 3 4 OIL PRESSURE DROP 3 3 5 ENGINE REGULATION DISCREPANCY POWER LOSS POWER LEVER CONTROL LOSS 3 3 6 GOVERNOR REGULATION CONTROL NOT OPERATING 3 3 8 EXCESSIVE PROPELLER ROTATION SPEED 3 3 9 RED WARNING CAS MESSAGE ITT ON 3 3 10 RED WARNING CAS MESSAGE TORQUE ON 3 3 11 ENGINE DOES NOT STOP ON GROUND 3 3 12 PIM DO NOT USE FOR FL...

Page 152: ...3 3 1 Edition 1 June 22 2007 Rev 8 3 3 ENGINE FAILURES ENGINE FAILURE AT TAKEOFF BEFORE ROTATION 1 Power lever IDLE 2 Braking AS REQUIRED If the airplane cannot be stopped on the remaining runway 3 Condition lever CUT OFF 4 Tank selector OFF 5 CRASH lever PULL DOWN PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 153: ...gear position Before touch down 1 Maintain Weight 6579 lbs 2984 kg Weight 6579 lbs 2984 kg IAS 80 KIAS IAS 85 KIAS 2 Power lever IDLE 3 Condition lever CUT OFF 4 Tank selector OFF 5 CRASH lever PULL DOWN If altitude allows to reach a favourable runway or ground 1 LDG DN 2 Flaps AS REQUIRED 3 Maintain Weight 6579 lbs 2984 kg Weight 6579 lbs 2984 kg IAS 100 KIAS Flaps UP IAS 105 KIAS Flaps UP IAS 90...

Page 154: ...OT S OPERATING HANDBOOK ENGINE FAILURES Page 3 3 3 Edition 1 June 22 2007 Rev 8 3 3 ENGINE FAILURES ENGINE FAILURE AFTER ROTATION 2 2 Before touch down 6 Condition lever CUT OFF 7 Tank selector OFF 8 CRASH lever PULL DOWN PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 155: ...n PRESSED 2 Power lever IDLE 3 Propeller governor lever FEATHER 4 Condition lever CUT OFF 5 Remaining fuel CHECK 6 Tank selector SWITCH TANKS 7 AUX BP switch and fuel pressure CHECK CORRECT 8 Air start Refer to Chapter 3 4 9 In case of high altitude above 12000 ft undertake an EMERGENCY DESCENT Refer to Chapter 3 6 10 If air start not successful perform a FORCED LANDING Refer to Chapter 3 7 PIM DO...

Page 156: ... green sector 2 Shorten the flight and monitor If the indicated pressure is not in the green sector 3 Failure is confirmed Due to the oil pressure drop the propeller blade angle may go towards high pitch and therefore lead to a Np propeller rotation speed decrease CAUTION PREPARE FOR AN ENGINE STOP SHORTLY REDUCE POWER TO THE MINIMUM NECESSARY LAND AS SOON AS PRACTICAL If engine looses power 4 Pow...

Page 157: ...ssary to continue flight If the available power is weak extend the landing gear only on a glide path in final approach and extend full flaps only in short final Do not perform a go around CAUTION IN MANUAL OVERRIDE ENGINE IS NEITHER PROTECTED AGAINST SLAM ACCELERATIONS NOR AGAINST MAXIMUM SPEED OVERSHOOTING AVOID RAPID CONTROL MOVEMENTS AND MANAGE ENGINE PARAMETERS CAUTION IN SOME CASES WHEN MANUA...

Page 158: ...obtained is excessive 1 Reduce airspeed by setting airplane in nose up attitude at IAS 178 KIAS 2 INERT SEP switch ON 3 If ITT 840 C INERT SEP switch OFF 4 Landing gear control DN 5 Flaps TO 6 Establish a long final or an ILS approach respecting IAS 178 KIAS 7 When runway is assured Condition lever CUT OFF 8 Propeller governor lever FEATHER if necessary to extend trajectory 9 Flaps LDG as required...

Page 159: ...ATION 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 In that case the go around performance and the reverse efficiency might be lower than expected The airplane repair is mandatory before any other flight PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 160: ... a propeller governor and overspeed limiter failure In that case only the torque limiter operates to limit the power However the pilot intervention is necessary to maintain Np 2000 RPM The propeller reducer is designed for a max Np of 2200 RPM 1 Reduce the power and the aircraft speed to avoid propeller rotation speeds higher than 2000 RPM 2 Land as soon as possible 3 Do not perform a go around A ...

Page 161: ...1 Stop the starting procedure 2 Record the engine parameters displayed as well as OAT conditions 3 Cancel the flight inform maintenance department B After engine start Indicates that ITT has been higher than 840 C more than 2 seconds 1 Reduce power according to Engine Operation tables Chapter 5 8 If ITT remains higher than 840 C 1 Reduce power to maintain ITT 840 C 2 Shorten the flight 3 Record th...

Page 162: ... 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 2 Shorten the flight 3 Record the airplane and engine parameters read in case of overtorque 4 Inform maintenance department at the end of the flight PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 163: ...ndition lever is set to CUT OFF proceed as follows 1 AP TRIMS MASTER switch OFF 2 AVIONICS MASTER switch OFF 3 INT LIGHTS panel All switches OFF 4 EXT LIGHTS panel All switches OFF 5 ECS panel All switches OFF 6 Tank selector OFF Wait for engine stop due to lack of fuel in the pipes 7 GENERATOR selector OFF 8 SOURCE selector OFF 9 CRASH lever PULL DOWN 10 Inform the maintenance department PIM DO N...

Page 164: ...3 4 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 165: ...OOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 4 0B Edition 1 June 22 2007 Rev 8 SECTION 3 4 AIR START TABLE OF CONTENTS Page AIR START ENVELOPE 3 4 1 AIR START WITH STARTER 3 4 2 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 166: ...age 3 4 1 Edition 1 June 22 2007 Rev 10 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 Figure 3 4 1 AIR START ENVELOPE PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 167: ...IGNITION IS NOT AVAILABLE IF THE ESS BUS TIE SWITCH IS KEPT EMER NOTE The AVIONICS MASTER switch may be ON 1 BLEED switch OFF CAUTION BLEED SWITCH SET TO AUTO MAY CAUSE OVERTEMPERATURE OR ABNORMAL ACCELERATION 2 AIR COND switch OFF 3 Air start envelope CHECKED 4 Electric consumption REDUCE 5 Power lever IDLE 6 Propeller governor lever FEATHER 7 Condition lever CUT OFF 8 Tank selector CHECK 9 AUX B...

Page 168: ...IGNITION switch AUTO or ON 11 STARTER switch ON 12 Condition lever LO IDLE when Ng μ 13 13 ITT and Ng MONITOR 14 When Ng μ 50 steady STARTER OFF IGNITION AUTO 15 Condition lever HI IDLE 16 Propeller governor lever MAX RPM 17 Power lever AS REQUIRED 18 Electrical equipment AS REQUIRED 19 AUX BP fuel switch AUTO 20 BLEED switch AS REQUIRED PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 169: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved AIR START Page 3 4 4 Edition 1 June 22 2007 Rev 8 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 170: ...3 5 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 171: ...ge 3 5 0B Edition 1 June 22 2007 Rev 2 SECTION 3 5 FIRE AND SMOKE TABLE OF CONTENTS Page ENGINE FIRE ON GROUND 3 5 1 CABIN FIRE ON GROUND 3 5 1 ENGINE FIRE IN FLIGHT 3 5 2 CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT 3 5 4 SMOKE ELIMINATION 3 5 6 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 172: ...DLE 2 Condition lever CUT OFF 3 BLEED switch OFF 4 AIR COND switch OFF 5 Brakes AS REQUIRED 6 Tank selector OFF 7 Warn ground assistance if necessary 8 CRASH lever PULL DOWN 9 EVACUATE as soon as possible CABIN FIRE ON GROUND 1 Power lever IDLE 2 Condition lever CUT OFF 3 Brakes AS REQUIRED 4 Warn ground assistance if necessary 5 CRASH lever PULL DOWN 6 Cabin extinguisher AS REQUIRED 7 EVACUATE as...

Page 173: ...ITT ON smoke 1 Power lever IDLE 2 Propeller governor lever FEATHER 3 Condition lever CUT OFF 4 AUX BP fuel switch OFF 5 Tank selector OFF 6 BLEED switch OFF 7 AIR COND switch OFF 8 In case of high altitude above 12000 ft undertake an EMERGENCY DESCENT Refer to Chapter 3 6 9 Perform a FORCED LANDING ENGINE CUT OFF Refer to Chapter 3 7 WARNING AFTER ENGINE FIRE DO NOT ATTEMPT AN AIR START PIM DO NOT...

Page 174: ...SECTION 3 EMERGENCY PROCEDURES EASA Approved TBM 850 PILOT S OPERATING HANDBOOK FIRE AND SMOKE Page 3 5 3 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 175: ...ding circuit breaker PULL Descend quickly below 12000 ft 3 Using the on board extinguisher EXTINGUISH fire if necessary 4 Smoke elimination if necessary UNDERTAKE PROCEDURE Refer to this chapter 5 LAND as soon as possible If the origin is unknown 1 Oxygen and goggles USE AS REQUIRED pilot and passengers 2 AIR COND switch OFF 3 Not necessary equipment OFF 4 Smoke elimination if necessary UNDERTAKE ...

Page 176: ...ry with the on board extinguisher 8 All circuit breakers PULL 9 All electrical equipment CUT OFF 10 SOURCE selector BAT 11 GENERATOR selector MAIN 12 Necessary circuit breakers ENGAGE one after the other checking for possible fire or smoke 13 Necessary electrical equipment ON one after the other checking for possible fire or smoke 14 Defective equipment Corresponding circuit breaker PULL 15 Not af...

Page 177: ... Smoke origin IDENTIFY 2 Oxygen and goggles USE AS REQUIRED pilot and passengers 3 If smoke persists undertake an EMERGENCY DESCENT Refer to Chapter 3 6 4 BLEED switch OFF 5 AIR COND switch OFF 6 DUMP switch ACTUATE Wait until the differential pressure drops 7 RAM AIR control knob PULL If smoke increases PUSH 8 LAND as soon as possible PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 178: ...3 6 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 179: ...0 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 6 0B Edition 1 June 22 2007 Rev 10 SECTION 3 6 EMERGENCY DESCENTS TABLE OF CONTENTS Page MAXIMUM RATE DESCENT 3 6 2 MAXIMUM RANGE DESCENT 3 6 3 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 180: ...sary The factors to be considered are Cabin altitude and oxygen duration Electrical power endurance Distance to appropriate landing area Flight conditions IMC VMC ICING Minimum safe altitude Fuel reserves 2 Engine failure aircraft flown for maximum range The pilot is in charge of evaluating the situation and priorities Refer to Figure 3 6 1 EMERGENCY DESCENT PROFILES Figure 3 6 1 EMERGENCY DESCENT...

Page 181: ...CY DESCENTS MAXIMUM RATE DESCENT 1 Power lever IDLE 2 Oxygen If necessary 3 Propeller governor lever MAX RPM Procedure in smooth air 4 Flaps UP 5 Landing gear UP 6 Speed VMO 266 KIAS Procedure in rough air or in case of structure problem 7 Reduce speed IAS 178 KIAS 8 Landing gear DN 9 Flaps UP 10 Keep IAS 178 KIAS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 182: ...sary Check oxygen duration before reaching 12000 ft and check flow to passengers 8 DUMP switch ACTUATED 9 RAM AIR control knob PULLED If conditions allow VMC and non icing conditions 10 ESS BUS TIE reverse switch Cover up EMER position 11 Prepare a forced landing Refer to Chapter 3 7 If flight conditions do not allow 12 ESS BUS TIE reverse switch NORMAL 13 Manually disconnect ancillary systems as ...

Page 183: ... BP switch OFF FUEL SEL switch MAN AP TRIMS MASTER switch OFF PFD 2 breaker PULL ADC 2 breaker PULL CD player OFF INSTR CABIN ACCESS controls OFF XPDR 2 breaker PULL If icing conditions PITOT L HTR switch Checked ON WINDSHIELD switch ON Maintain minimum recommended speeds Chapter 4 5 Flight into known icing conditions Paragraph Ice protection procedures Point 3 If time permits SVC PLUGS breaker PU...

Page 184: ...3 7 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 185: ...F CONTENTS Page FORCED LANDING ENGINE CUT OFF 3 7 1 TIRE BLOWOUT DURING LANDING 3 7 2 LANDING WITH UNLOCKED MAIN LANDING GEAR 3 7 4 LANDING WITH DEFECTIVE NOSE LANDING GEAR DOWN UNLOCKED OR NOT DOWN 3 7 6 LANDING WITH GEAR UP 3 7 7 LANDING WITHOUT ELEVATOR CONTROL 3 7 8 LANDING WITH FLAPS MALFUNCTION 3 7 9 DITCHING 3 7 10 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 186: ...D switch OFF 8 DUMP switch ACTUATED 9 Glide speed 120 KIAS maintained until favourable ground approach If ground allows it 10 ESS BUS TIE reverse switch NORMAL in order to have GEAR and FLAPS available 11 Landing gear DN If night conditions 12 L LDG R LDG ON If ground does not allow it 13 Keep landing gear UP 14 When chosen ground is assured FLAPS LDG 15 CRASH lever PULL DOWN 16 Final approach Wei...

Page 187: ... Page 3 7 2 Edition 1 June 22 2007 Rev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 188: ...SECTION 3 EMERGENCY PROCEDURES EASA Approved TBM 850 PILOT S OPERATING HANDBOOK EMERGENCY LANDINGS Page 3 7 3 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 189: ...ch OFF 3 DUMP switch ACTUATED 4 Maintain tank selector on defective landing gear side to lighten corresponding wing maximum fuel unbalance 15 us gal 57 litres 5 Choose a runway with headwind or crosswind blowing from defective gear side 6 Align the airplane to land on the runway edge opposite to the defective landing gear 7 Land and set nose gear immediately on ground to assure lateral control 8 U...

Page 190: ...Rev 8 3 7 EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR 2 2 11 Condition lever CUT OFF 12 Engine stop procedure COMPLETE 13 EVACUATE If landing gear drags during landing 14 Condition lever CUT OFF 15 CRASH lever PULL DOWN 16 Tank selector OFF 17 EVACUATE after airplane comes to a stop PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 191: ...Transfer passengers to the rear if necessary 2 Approach Flaps TO Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 90 KIAS IAS 95 KIAS 3 Land with nose up attitude keep nose high 4 Condition lever CUT OFF 5 Propeller governor lever FEATHER 6 Touch down slowly with nose wheel and keep elevator at nose up stop 7 Moderate braking 8 CRASH lever PULL DOWN 9 EVACUATE after airplane comes to a stop PIM...

Page 192: ...oach Standard 2 Flaps LDG Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 80 KIAS IAS 85 KIAS 3 BLEED switch OFF 4 DUMP switch ACTUATED When runway is assured 5 Power lever IDLE 6 Propeller governor lever FEATHER 7 Condition lever CUT OFF 8 Tank selector OFF 9 Flare out 10 After touch down CRASH lever PULL DOWN 11 EVACUATE after airplane comes to a stop PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 193: ...ANDING WITHOUT ELEVATOR CONTROL 1 Configuration LANDING GEAR DN FLAPS LDG 2 Airspeed Maintain IAS 95 KIAS 3 Power as necessary to maintain airspeed according to an easy approach slope 300 ft min 4 Adjust elevator by using manual pitch trim wheel 5 When ground approaches decrease slope progressively 6 Reduce power progressively PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 194: ...r a normal landing maintaining approach airspeed Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 100 KIAS IAS 105 KIAS Provide for a landing distance increased up to about 60 For flaps deflections greater than TO position Proceed as for a normal landing maintaining approach airspeed Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 95 KIAS IAS 100 KIAS Provide for a landing distance increase...

Page 195: ...nd parallel to the swell rollers In heavy wind land facing wind 2 Flaps LDG 3 Maintain a descent rate as low as possible when approaching the water 4 Airspeed Weight 6579 lbs 2984 kg Weight 6579 lbs 2984 kg IAS 80 KIAS IAS 85 KIAS 5 BLEED switch OFF 6 DUMP switch ACTUATED 7 CRASH lever PULL DOWN 8 Maintain attitude without rounding off until touch down 9 EVACUATE through EMERGENCY EXIT PIM DO NOT ...

Page 196: ...3 8 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 197: ... June 22 2007 Rev 2 SECTION 3 8 FUEL SYSTEM TABLE OF CONTENTS Page RED WARNING CAS MESSAGE FUEL PRESS ON 3 8 1 AMBER WARNING CAS MESSAGE AUX BOOST PMP ON ON 3 8 2 AMBER WARNING CAS MESSAGE FUEL LOW L OR FUEL LOW R ON 3 8 3 AMBER WARNING CAS MESSAGE AUTO SEL ON 3 8 3 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 198: ...HECK 6 Fuel pressure CHECK If pressure is normal again and warning light is off mechanical pump has failed 7 Maintain AUX BP fuel switch ON If pressure remains at 0 or drops to 0 after AUX BP pump operation and if warning FUEL PRESS remains ON 8 Tank selector SWITCH TANKS If pressure is normal again a supply problem may have occurred from the tank selected first air vent fuel icing etc If pressure...

Page 199: ...ST 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 ON 2 Then to AUTO If AUX BOOST PMP ON warning CAS message goes out continue flight normally If AUX BOOST PMP ON warning CAS message remains ON mechanical booster pump has failed 3 AUX BP fuel switch ON 4 Shorten flight PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 200: ...ing tank 1 Corresponding gage CHECK 2 Check the other tank has been automatically selected If not 3 FUEL SEL switch MAN 4 Select tank manually as required AMBER WARNING CAS MESSAGE AUTO SEL ON Indicates there is no more automatic control mode running 1 FUEL SEL switch AUTO If it is on AUTO failure is confirmed 2 FUEL SEL switch MAN 3 Select tanks manually as required CAUTION MAXIMUM UNBALANCE IS 1...

Page 201: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved FUEL SYSTEM Page 3 8 4 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 202: ...3 9 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 203: ... WARNING CAS MESSAGE MAIN GEN ON 3 9 2 AMBER WARNING CAS MESSAGE LOW VOLTAGE ON normal functioning on MAIN GEN 3 9 3 AMBER WARNING CAS MESSAGE LOW VOLTAGE ON functioning on ST BY GENERATOR after MAIN GEN failure 3 9 4 ELECTRICAL DISTRIBUTION OF BUS BARS 3 9 7 AVIONICS MASTER SWITCH FAILURE 3 9 9 Post MOD70 0335 34 ESI 2000 TOTAL LOSS OF ELECTRICAL POWER 3 9 10 ESI 2000 FAILURES 3 9 11 PIM DO NOT U...

Page 204: ...n 1 June 22 2007 Rev 6 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 CORRECT 2 If warning persists SHORTEN FLIGHT 3 Monitor airplane mains voltage PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 205: ...ecessary CORRECT 2 If warning persists MAIN GEN switching confirmed 3 MAIN GENERATOR RESET push button PUSH In case of failure 4 Keep the following systems connected A P system Deicing systems STROBE and NAV lights Cockpit emergency lights VHF 1 NAV GPS 1 BLEED Landing lights on short final This will allow keeping electrical consumption below maximum standby capacity All other not necessary equipm...

Page 206: ...itor a possible drop or any indication of battery run down In that case 3 Keep the following systems connected A P system Deicing systems STROBE and NAV lights Cockpit emergency lights VHF 1 NAV GPS 1 BLEED Landing lights on short final This will allow keeping electrical consumption below maximum standby capacity All other not necessary equipment can be disconnected 4 GENERATOR selector ST BY RESE...

Page 207: ...BY 1 GENERATOR selector MAIN 2 MAIN GENERATOR RESET push button PRESS If successful 3 Disconnect electrical systems not essential 4 Monitor voltmeter and ammeter Prepare to SHORTEN FLIGHT If not successful 5 GENERATOR selector ST BY 6 ST BY GENERATOR RESET push button PRESS If successful 7 Disconnect electrical systems not essential 8 Monitor voltmeter and ammeter Prepare to SHORTEN FLIGHT If not ...

Page 208: ...ation only both ESS BUS bars and BUS BAT bar are directly supplied by the battery Available systems see Figure 3 9 1 12 LAND as soon as possible If use of other systems is required ESS BUS TIE reverse switch NORMAL If flight conditions do not allow 13 Manually disconnect systems as follows AIRFRAME DE ICE switch OFF ICE LIGHT switch OFF PROP DE ICE switch OFF WINDSHIELD switch OFF PITOT R STALL HT...

Page 209: ...e 3 3 ADC 2 breaker PULL TAS breaker PULL DATA LINK breaker PULL CD player OFF INSTR CABIN ACCESS controls OFF XPDR 2 breaker PULL If icing conditions PITOT L HTR switch Checked ON WINDSHIELD switch ON Maintain minimum recommended speeds Chapter 4 5 Flight into known icing conditions Paragraph Ice protection procedures Point 3 If time permits SVC PLUGS breaker PULL AIR COND breaker PULL 14 LAND as...

Page 210: ...RGENCY PROCEDURES EASA Approved TBM 850 PILOT S OPERATING HANDBOOK ELECTRICAL SYSTEM Page 3 9 7 Edition 1 June 22 2007 Rev 13 Figure 3 9 1 1 2 ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 211: ...PERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved ELECTRICAL SYSTEM Page 3 9 8 Edition 1 June 22 2007 Rev 12 Figure 3 9 1 2 2 ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 212: ...7 Rev 0 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 PULL The radionavigation equipment are supplied again and the flight can continue PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 213: ...000 for attitude airspeed and or altitude 4 Land as soon as possible NOTE Aircraft power is provided to the ESI 2000 display for normal operation Operation of the basic ESI system is automatic the system is powered ON anytime aircraft power is ON The internal battery will provide power to the ESI 2000 if aircraft power is lost Press any key to allow the ESI 2000 to continue operation using the int...

Page 214: ... low battery voltage condition exists Red X Battery has failed Service is required 2 ESI 2000 Attitude invalid in flight Maintain straight and level flight at a constant airspeed Press the M button twice Press the S button once The ESI 2000 will initiate the alignment process When a normal attitude display is available resume normal flight If attitude information remains unvalid use attitude infor...

Page 215: ...nment Remain clear of IMC until amber X is removed from the display 6 Internal Battery state of charge low amber battery symbol displayed in flight Remain clear of IMC until amber battery symbol is removed from display signifying battery is charged sufficiently to have one hour of discharge abilitiy 7 ESI 2000 in flight shutdown Manual Procedure Maintain control of the aircraft using aircraft prim...

Page 216: ...3 10 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 217: ... MESSAGE CABIN ALTITUDE ON AND AMBER WARNING CAS MESSAGE USE OXYGEN MASK ON 3 10 2 RED WARNING CAS MESSAGE CABIN ALTITUDE AND EDM ON AND AMBER WARNING CAS MESSAGE USE OXYGEN MASK ON 3 10 3 RED WARNING CAS MESSAGE EDM ON 3 10 4 CABIN NOT DEPRESSURIZED AFTER LANDING 3 10 5 AMBER WARNING CAS MESSAGE BLEED OFF ON 3 10 6 RED WARNING CAS MESSAGE BLEED TEMP ON 3 10 7 RED WARNING CAS MESSAGE DOOR ON 3 10 ...

Page 218: ...itch OFF 3 EMERGENCY DESCENT Refer to Chapter 3 6 Pre MOD70 0407 00D V15 11 GARMIN software RED WARNING CAS MESSAGE CABIN ALTITUDE ON 1 Pressurization indicator CHECK If cabin altitude 10000 ft 2 Oxygen USE 3 BLEED switch CHECK AUTO 4 DUMP switch CHECK UNDER GUARD 5 RAM AIR control knob CHECK PUSHED 6 Limit flight altitude to maintain cabin altitude 12000 ft 7 If necessary EMERGENCY DESCENT Refer ...

Page 219: ...BIN ALTITUDE warning CAS message is followed by USE OXYGEN MASK amber CAS message and 3 voice messages USE OXYGEN MASK USE OXYGEN MASK 1 Pressurization indicator CHECK If cabin altitude 10000 ft 2 Oxygen USE 3 BLEED switch CHECK AUTO 4 DUMP switch CHECK UNDER GUARD 5 RAM AIR control knob CHECK PUSHED 6 Limit flight altitude to maintain cabin altitude 12000 ft 7 If necessary EMERGENCY DESCENT Refer...

Page 220: ...and 3 voice messages USE OXYGEN MASK USE OXYGEN MASK 1 Pressurization indicator CHECK If cabin altitude 10000 ft 2 Oxygen USE 3 BLEED switch CHECK AUTO 4 DUMP switch CHECK UNDER GUARD 5 RAM AIR control knob CHECK PUSHED 6 Limit flight altitude to maintain cabin altitude 12000 ft 7 If necessary EMERGENCY DESCENT Refer to Chapter 3 6 Inform maintenance department before next flight NOTE EDM makes a ...

Page 221: ...CAS message 1 Pressurization indicator CHECK If cabin altitude 10000 ft 2 Oxygen USE 3 BLEED switch CHECK AUTO 4 DUMP switch CHECK UNDER GUARD 5 RAM AIR control knob CHECK PUSHED 6 Limit flight altitude to maintain cabin altitude 12000 ft 7 If necessary EMERGENCY DESCENT Refer to Chapter 3 6 NOTE EDM makes a 90 left heading change and descent to 15000 ft EDM override is possible by pressing twice ...

Page 222: ...1 June 22 2007 Rev 13 AIR CONDITIONING 3 10 PRESSURIZATION AND AIR CONDITIONING All CABIN NOT DEPRESSURIZED AFTER LANDING P cabin 0 1 DUMP switch ACTUATED 2 BLEED switch OFF 3 RAM AIR control knob PULLED if necessary 4 Wait for complete cabin depressurization before opening the door PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 223: ...n BLEED switch on OFF position 1 Oxygen USE 2 If necessary CORRECT 3 If possible reduce power 4 BLEED switch OFF RST 5 BLEED switch AUTO If in flight 6 If warning BLEED OFF still displayed and if EMERGENCY DESCENT is required refer to Chapter 3 6 or continue flight at an altitude below 12000 ft 7 Continue flight If on the ground 6 BLEED switch OFF RST 7 Taxi back to the apron 8 Normal engine shut ...

Page 224: ...OFF amber warning CAS message appearance Should automatic cutoff occur or not 1 If possible REDUCE POWER 2 AIR FLOW distributor CABIN 3 CABIN CTRL selector OVERRIDE 4 CABIN TEMP C selector MINI 5 BLEED switch OFF RST 6 BLEED switch AUTO If BLEED TEMP and BLEED OFF warnings still ON 7 If necessary EMERGENCY DESCENT refer to Chapter 3 6 or continue flight at an altitude 12000 ft 8 Continue flight If...

Page 225: ...or 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 Do not take off if warning CAS message DOOR is ON In flight 1 Start a slow descent 2 Decrease cabin pressure differential by selecting a higher cabin altitude If a real failure of one of the doors is noted 3 BLEED switch OFF 4 DUMP switch ACTUATED 5 I...

Page 226: ...ad to misfunctioning of leading edge deicing pressurization and gyroscopic vacuum operated instruments MONITOR If necessary fly to an altitude 12000 ft and return to VMC conditions as soon as possible BLEED switch OFF Post MOD70 0335 34 ESI 2000 AMBER WARNING CAS MESSAGE VACUUM LOW ON Low vacuum may lead to misfunctioning of leading edge deicing pressurization MONITOR If necessary fly to an altitu...

Page 227: ...tor already positioned on DEFOG 1 AIR FLOW distributor Set to around a 10 o clock position If moisture continues 2 AIR FLOW distributor HOT 3 WINDSHIELD switch ON If there is no improvement and if the flight safety is engaged 4 Altitude 12000 ft 5 BLEED switch OFF NOTE If in flight the cabin will quickly be depressurized Therefore the cabin vertical speed indicator and altimeter indications will r...

Page 228: ...3 11 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 229: ...1 June 22 2007 Rev 6 SECTION 3 11 LANDING GEAR AND FLAPS TABLE OF CONTENTS Page LANDING GEAR RETRACTION DISCREPANCY 3 11 1 LANDING GEAR EXTENSION DISCREPANCY 3 11 2 EMERGENCY GEAR EXTENSION 3 11 3 RED WARNING CAS MESSAGE FLAPS ASYM ON 3 11 5 FLAPS MALFUNCTION 3 11 5 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 230: ... red warning light ON and 0 to 3 green light s ON Actions Refer to EMERGENCY GEAR EXTENSION B Symptoms Red warning light flashing and 3 green lights OFF Actions 1 LDG GEAR circuit breaker PULL If the red warning light goes off The flight may be continued without any restriction Before extending the landing gear refer to EMERGENCY GEAR EXTENSION If the red warning light becomes steady ON LDG GEAR c...

Page 231: ...D FLAPS 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 or Red warning light flashing and 0 to 3 green light s OFF Actions Refer to EMERGENCY GEAR EXTENSION PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 232: ...O 110 CYCLES IT IS MANDATORY TO HAVE A CLEAR HARDENING OF THE MANUAL CONTROL AT THE END OF THE MANEUVER 5 Hand pump ACTUATE with maximum amplitude If landing gear is down and locked red light not illuminated three green lights illuminated Continue flight if necessary at a speed BELOW 178 KIAS exit and or remain outside icing conditions Land CAUTION DO NOT ENTER ICING CONDITIONS THIS COULD ADVERSEL...

Page 233: ...ne or more green indicator light s does do not illuminate and upon pressing CHECK DN then a gear unlock condition is confirmed Recycle the landing gear as follows 9 By pass selector UNLOCK PUSH 10 Wait one minute 11 Landing gear control IAS 128 KIAS UP Perform landing gear extension attempts in the NORMAL mode while applying positive load factors during the maneuver as well as skidding In case of ...

Page 234: ...S for deflections between UP and TO positions IAS 122 KIAS for deflections greater than TO position 4 For landing refer to Chapter 3 7 Paragraph LANDING WITH FLAPS MALFUNCTION FLAPS MALFUNCTION In case of blockage of flaps or inoperant flap control lever between UP and LDG positions with no flaps warning light illumination 1 FLAPS circuit breaker PULL 2 Flap control lever UP 3 SHORTEN flight maint...

Page 235: ...M PILOT S OPERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 11 6 Edition 1 June 22 2007 Rev 0 LANDING GEAR AND FLAPS INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 236: ...3 12 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 237: ...EICING SYSTEM TABLE OF CONTENTS Page LEADING EDGES DEICING FAILURE 3 12 1 PROPELLER DEICING FAILURE 3 12 1 INERTIAL SEPARATOR FAILURE 3 12 2 WINDSHIELD DEICING FAILURE 3 12 2 WINDSHIELD MISTING OR INTERNAL ICING 3 12 3 AMBER WARNING CAS MESSAGES PITOT NO HT L PITOT NO HT R OR STALL NO HEAT ON 3 12 4 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 238: ...wing outboard sections Or ice on wing inboard sections and stabilizers One of the two cycling green lights is not lit 1 LEAVE icing conditions as soon as possible 2 AIRFRAME DE ICE switch OFF PROPELLER DEICING FAILURE Symptoms Propeller deicing green light is not lit Propeller vibrations 1 REDUCE power 2 ACTUATE propeller governor lever to vary RPM within operating range 3 LEAVE icing conditions a...

Page 239: ...que drop nor increase of ITT observed during maneuver LEAVE icing conditions as soon as possible WINDSHIELD DEICING FAILURE Symptoms Windshield being covered uniformly by ice No perception of heat when touching deiced section Windshield deicing green light is not lit Symptoms may result from overheat In that case 1 WINDSHIELD switch OFF ON when necessary In case of total failure 1 CABIN TEMP C sel...

Page 240: ...SHIELD switch ON If not successful to gain sufficient visibility 4 AIR FLOW distributor HOT 5 Manually clean a sufficient visibility area 6 If necessary clean L H side window and conduct a sideslip approach rudder pedals to the right in order to get sufficient landing visual references 7 For landing with flaps LDG maintain Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 90 KIAS IAS 95 KIAS CAU...

Page 241: ...ter L H airspeed indications 1 AVOID icing conditions If it is not possible 2 Perform moderate descent or climb attitudes VMO overshooting and stall warning lights are always operating PITOT NO HT R VMO overshoot warning may be altered by icing conditions Monitor maximum airspeed 266 KIAS STALL NO HEAT Correct operation of the aural stall warning may be altered by severe or prolonged icing MONITOR...

Page 242: ...3 13 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 243: ...OMMUNICATION FAILURE 3 13 3 PARTICULAR TRANSPONDER USES 3 13 3 AUTOPILOT OR ELECTRIC PITCH TRIM MALFUNCTION 3 13 4 INADVERTENT SPINS 3 13 5 RED WARNING CAS MESSAGE AURAL WRN FAIL ON 3 13 6 RED WARNING CAS MESSAGE AURAL WRN 1 CHNL ON 3 13 7 OXYGEN USE 3 13 8 AIRSPEED INDICATING SYSTEM FAILURE 3 13 12 FLIGHT INTO SEVERE ICING CONDITIONS 3 13 13 DUAL GPS SBAS FAILURE AMBER DR or LOI ON HSI 3 13 14 GP...

Page 244: ...ch trim may be used manually 5 Reduce airspeed if necessary to reduce control forces If pitch trim runaway 6 AP TRIMS MASTER switch AP OFF The pitch trim may be used manually the two other trim tabs may be used again electrically If rudder or aileron trim runaway 7 PULL circuit breaker corresponding to the defective trim tab 8 AP TRIMS MASTER switch ON Two other trim tabs may be used again electri...

Page 245: ...ing handle Refer to paragraph Emergency exit in Chapter 7 3 All 3 Lift up the opening handle 4 Pull emergency exit assembly toward oneself to release it from its recess 5 Put the emergency exit door inside fuselage or throw it away from the fuselage through the opening 6 EVACUATE airplane EMERGENCY BEACON USE ELT Before a forced landing 1 On COM VHF 121 5 MHZ or on a known air traffic control freq...

Page 246: ...ll emergency exit assembly toward oneself to release it from its recess 4 Put the emergency exit door inside fuselage or throw it away from the fuselage through the opening 5 EVACUATE airplane EMERGENCY BEACON USE ELT Before a forced landing 1 On COM VHF 121 5 MHZ or on a known air traffic control frequency transmit the MAY DAY signal if possible After landing 2 ELT remote control switch ON mainta...

Page 247: ... 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 PARTICULAR TRANSPONDER USES 1 Check transponder mode selector ON or ALT 2 Codes selector 7700 EMERGENCY DISTRESS 7600 COMMUNICATIONS FAILURE 7500 HIJACKING PIM DO NOT USE...

Page 248: ...FUNCTION 1 AP TRIMS DISC INT push button PRESSED and HELD 2 AP TRIMS MASTER switch OFF 3 AP TRIMS DISC INT push button RELEASED 4 If necessary control wheel RETRIM CAUTION WHEN DISCONNECTING THE AUTOPILOT AFTER A PITCH TRIM MALFUNCTION HOLD THE CONTROL WHEEL FIRMLY UP TO 30 POUNDS OF FORCE ON THE CONTROL WHEEL MAY BE NECESSARY TO HOLD THE AIRPLANE LEVEL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 249: ...e 22 2007 Rev 0 3 13 MISCELLANEOUS INADVERTENT SPINS Voluntary spins are prohibited In case of inadvertent spins 1 Control wheel NEUTRAL PITCH AND ROLL 2 Rudder FULLY OPPOSED TO THE SPIN 3 Power lever IDLE 4 Flaps UP when rotation is stopped 5 Level the wings and ease out of the dive PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 250: ...ANEOUS 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 NO LANDING GEAR WARNING 1 Maintain airspeeds Flaps UP 105 KIAS 266 Flaps TO 100 KIAS 178 Flaps LDG 85 IAS 122 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 251: ...22 2007 Rev 13 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 PRESS SPKR led ON on available GMA s 2 Volume ADJUST TO LOUDER LEVEL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 252: ...ide pilot R H side R H front passenger L H side draw it out of the stowage cup and uncoil tube totally Press on the red side vanes to inflate the harness Put the mask on the face 2 No smokes 3 position selector NORMAL 100 as required 3 In case of smokes 3 position selector EMERGENCY Don the smoke goggles onto the face 4 PASSENGERS OXYGEN switch ON 5 Check the oxygen flow indicator for the front se...

Page 253: ...ING HANDBOOK MISCELLANEOUS Page 3 13 9 Edition 1 June 22 2007 Rev 13 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 254: ...LUDING LIPSTICK MAKE UP ETC Front seats 1 Take a mask on the opposite seat side pilot R H side R H front passenger L H side draw it out of the stowage cup and uncoil tube totally Press on the red side vanes to inflate the harness Put the mask on the face 2 No smokes 3 position selector NORMAL 100 as required 3 In case of smokes 3 position selector EMERGENCY Don the smoke goggles onto the face 4 PA...

Page 255: ...1 June 22 2007 Rev 13 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 3 Pull on the lanyard cord to take out the lanyard pin 4 Put the mask on the face PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 256: ...LURE Symptoms erroneous indication in flight 1 PITOT L HTR switch CHECK ON 2 PITOT R STALL HTR switch CHECK ON If symptoms persist 3 ALTERNATE STATIC selector PULL THOROUGHLY 4 Use standby instrument only If symptoms persist as well as on the airspeed indicator of the L H instrument panel carry out a precautionary approach maintaining an adequate speed PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 257: ...1 Inform Air Traffic Control to exit severe icing conditions by changing the route or the altitude 2 Avoid any sudden maneuver on flight controls 3 Do not engage the autopilot 4 If the autopilot is engaged hold the control wheel firmly and disengage the autopilot 5 If an unusual roll response or uncommanded roll control movement is observed reduce the angle of attack 6 Do not extend flaps when hol...

Page 258: ...TION MAP will continue to be displayed with a ghosted aircraft icon in the center and an amber DR overwriting the icon Aircraft position will be based upon the last valid GPS position then estimated by Dead Reckoning methods Changes in true airspeed altitude or winds aloft can affect the estimated position substantially Dead Reckoning is only available in Enroute mode Terminal and Approach modes d...

Page 259: ...ast known wind data and the last known GPS position to estimate the airplane s current position DR information will be available for a maximum of 20 minutes MAP TRAFFIC MAP display is not dependent on GPS information The position of displayed traffic relative to the airplane symbol on the map is still accurate Loss Of Integrity LOI Mode Active when the airplane is within 30 NM or departure airport...

Page 260: ...NAV GPS glide path vertical guidance will be removed from the PFD The approach may becontinued using the LNAV only minimums During any GPS approach in which both precision and non precision alarm limits are exceeded the G1000 System will flag the lateral guidance and display a system message ABORT APPROACH loss of navigation Immediately upon viewing the message the unit will revert to Terminal nav...

Page 261: ... FD COM 1 NAV 1 DME 1 XPDR 1 Actions TRAJECTORY 1 AP DISC switch on control wheel PRESS to mute aural tone associated to Auto pilot disconnection 2 Fly the aircraft manually using stand by instruments information 3 PFD 1 CIRCUIT BREAKER CHECKED IN 4 RIGHT PFD REVERSIONARY mode ENGAGED DISPLAY BACK UP button OUT 5 XFR on AFCS control unit PRESS Check green arrow to right side to connect AFCS to RIG...

Page 262: ...o control panel SELECTED 3 RADIO CHECK with ATC PERFORMED 4 NAV 2 frequency SELECTED and ACTIVATED 5 DME 2 source SELECTED 6 XPDR 2 SELECTED check squawk and mode 7 CDI source NAV LOC or GPS SELECTED as desired 8 Shorten flight CAUTION 1 In case of ILS approach don t forget to select LOC2 on CDI source on RIGHT PFD 2 Use of reversionary mode will report LEFT PFD information on MFD and disable supp...

Page 263: ...VERSIONARY SENSOR WINDOW YELLOW ANNUNCIATION BOTH ON AHRS1 or BOTH ON AHRS2 Lost systems AHRS1 or AHRS2 AUTOPILOT AP Systems still operative FLIGHT DIRECTOR FD when engaged again Actions AUTOPILOT IS NOT OPERATIVE 1 AHRS1 and or AHRS2 circuit breaker CHECKED IN A If yellow annunciation BOTH ON AHRS1 or BOTH ON AHRS2 is associated to white annunciation HDG NO COMP and or PIT NO COMP and or ROL NO C...

Page 264: ...ually to follow Command Bars If ALL white annunciations HDG NO COMP and or PIT NO COMP and or ROL NO COMP GO OFF refer to following B procedure B If yellow annunciation BOTH ON AHRS1 or BOTH ON AHRS2 ONLY not associated to white annunciation HDG NO COMP and or PIT NO COMP and or ROL NO COMP 1 PFD1 and PFD2 SENSOR softkey s PRESSED 2 AHRS1 on PFD1 and or AHRS2 on PFD2 RESET 3 BOTH ON AHRS1 or BOTH ...

Page 265: ...and or ADC2 circuit breaker CHECKED IN A If yellow annunciation BOTH ON ADC1 or BOTH ON ADC2 is associated to white annunciation IAS NO COMP and or ALT NO COMP 1 NO action required If ALL white annunciations IAS NO COMP and or ALT NO COMP GO OFF refer to following B procedure B If yellow annunciation BOTH ON ADC1 or BOTH ON ADC2 ONLY not associated to white annunciation IAS NO COMP and or ALT NO C...

Page 266: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 3 EMERGENCY PROCEDURES EASA Approved MISCELLANEOUS Page 3 13 22 Edition 1 June 22 2007 Rev 13 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 267: ...OLLOWED BY AN ENGINE START 4 3 28 AFTER STARTING ENGINE 4 3 30 IN FLIGHT AVAILABLE OXYGEN QUANTITY 4 3 33 TAXIING 4 3 34 BEFORE TAKEOFF 4 3 35 TAKEOFF 4 3 37 CLIMB 4 3 39 CRUISE 4 3 40 FLAP CONTROL TRANSITION FROM UP TO 850 4 3 41 FLAP CONTROL TRANSITION FROM 850 TO UP 4 3 41 DESCENT 4 3 42 BEFORE LANDING 4 3 43 LANDING 4 3 44 GO AROUND 4 3 45 TOUCH AND GO 4 3 46 AFTER LANDING 4 3 47 SHUT DOWN 4 3...

Page 268: ...65 SHUT DOWN 4 4 66 4 5 PARTICULAR PROCEDURES 4 5 1 FLIGHT INTO KNOWN ICING CONDITIONS 4 5 1 FLIGHT INTO SEVERE ICING CONDITIONS 4 5 6 FLIGHT UNDER HEAVY PRECIPITATIONS 4 5 8 UTILIZATION ON RUNWAYS COVERED WITH WATER 4 5 8 UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW 4 5 9 UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS 4 5 11 UTILIZATION BY COLD WEATHER 0 C to 25 C AND VE...

Page 269: ...ures 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 The normal procedures for optional systems are given in Section 9 Supplements of the Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 270: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 4 NORMAL PROCEDURES EASA Approved GENERAL Page 4 1 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 271: ...limb speed VY Landing gear UP flaps UP 123 KIAS 124 KIAS 3 Best angle of climb speed Vx 95 KIAS 100 KIAS 4 Maximum speed Flaps TO 178 KIAS Flaps LDG 122 KIAS 178 KIAS 122 KIAS 5 Maximum speed with landing gear down 178 KIAS 178 KIAS 6 Maximum landing gear operating speed Extension 178 KIAS Retraction 128 KIAS 178 KIAS 128 KIAS 7 Approach speed Flaps LDG 80 KIAS 85 KIAS 8 Maximum operating speed VM...

Page 272: ...PILOT S OPERATING HANDBOOK 850 SECTION 4 NORMAL PROCEDURES EASA Approved Page 4 2 2 Edition 1 June 22 2007 Rev 0 AIRSPEEDS FOR NORMAL OPERATION INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 273: ...ntrol surfaces In case of night flight check good operation of all navigation lights landing lights strobe lights and make sure that an emergency lamp is on board If icing conditions are foreseen particularly check good functioning of all electrical and pneumatic ice protection systems Check that type and quantity of fuel used for refueling are correct Remove covers on pitots 2 static ports 3 engi...

Page 274: ...K 850 SECTION 4 NORMAL PROCEDURES EASA Approved CHECK LIST PROCEDURES Page 4 3 2 Edition 1 June 22 2007 Rev 0 CHECK LIST PROCEDURES PREFLIGHT INSPECTION Cont d Figure 4 3 1 PREFLIGHT INSPECTION PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 275: ...MAL MASK micro inverter NORMAL 4 Flight control lock REMOVED STOWED 5 Flight controls Deflections checked 6 Parking brake SET 7 Landing gear control DN 8 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 9 Flaps ...

Page 276: ...witch OFF AIR COND switch OFF DUMP switch GUARDED 13 Static Air control knob PUSHED 14 RAM AIR control knob PUSHED 15 Breakers panel All breakers ENGAGED 16 AVIONICS MASTER switch OFF 17 AP TRIMS MASTER switch OFF 18 Fuel FUEL SEL selector MAN AUX BP switch OFF 19 ENGINE START panel IGNITION switch AUTO or OFF STARTER switch OFF 20 ELECTRIC POWER panel CRASH lever UP GENERATOR selector MAIN SOURCE...

Page 277: ...switch OFF 26 Emergency lighting CHECKED CAUTION BEFORE SELECTING SOURCE CHECK 27 IGNITION switch AUTO or OFF 28 STARTER switch OFF 29 Landing gear control DN 30 SOURCE selector BAT or GPU 31 Voltage CHECK BAT 24 5 Volts GPU 28 Volts 32 EXT LIGHTS panel LTS TEST push button PRESS All instrument panel lamps ON except on landing gear control panel L LDG TAXI R LDG switches ON 3 green lamps ON L LDG ...

Page 278: ...tches OFF ICE LIGHT ON 35 AVIONICS MASTER switch START 36 CAS display CHECK 37 Left and right fuel quantities CHECK 38 EXT LIGHTS panel LTS TEST push button PRESS red and amber MASTER warnings ON 39 Flaps LDG 40 Landing gear panel Warning lights 3 GREEN ON Test 1 then 2 RED FLASHING 3 GREEN ON 41 DE ICE SYSTEM panel PITOT L HTR switch ON WARNING CAS MESSAGE PITOT HT L ON PITOT R STALL HTR switch O...

Page 279: ... 44 ESI 2000 battery indicator symbol NOT DISPLAYED Cabin II 1 Cabin fire extinguisher CHECK Pressure Attachment 2 Seats belts CHECK 3 Windows CHECK General condition No crack 4 Emergency exit CLOSED LOCKED Anti theft safety REMOVE STOW 5 Baggage compartment STRAPS IN PLACE 6 Partition net if 6 seat accommodation IN PLACE CHECK general condition 7 Large net or small net if 4 seat accommodation and...

Page 280: ...on 3 Trailing edge static discharger CHECK Condition Attachment 4 Wing tip nav lights Strobe landing light Condition CHECK 5 OAT probe Condition CHECK 6 Fuel tank CAP CLOSED LOCKED 7 Fuel tank air vent Unobstructed CHECK 8 Left pitot Condition CHECK 9 Wing lower surface CHECK No leak 10 Wing deicer boots CHECK Condition Attachment 11 Fuel tank drain two on each wing DRAIN Fuel free of water and co...

Page 281: ... Fuel circuit drain DRAIN Fuel free of water and contamination Filter contamination indicator CHECK 4 L H exhaust stub CHECK Condition No crack 5 Upper engine cowls OPEN For the first flight of the day Oil cap CLOSED LOCKED Engine oil level CHECK Fuel pipes CHECK No leak deterioration wear 6 Engine cowls Condition CHECK CLOSED LOCKED 7 Air inlets Main No crack UNOBSTRUCTED Lateral upper UNOBSTRUCT...

Page 282: ... tank drain two on each wing DRAIN Fuel free of water and contamination 2 Main landing gear Shock absorber doors tire wheel well CHECK 3 Wing deicer boots CHECK Condition Attachment 4 Stall warning CHECK Condition Deflection 5 Wing lower surface CHECK No leaks 6 Fuel tank CAP CLOSED LOCKED 7 Fuel tank air vent Unobstructed CHECK 8 Right pitot Condition CHECK 9 Wing tip nav light strobe landing lig...

Page 283: ...ntity CHECKED 14 Oxygen pressure CHECK Fuselage rear section Empennages VI 1 ELT OFF ELT door CLOSED LOCKED 2 Static pressure ports CLEAN CHECK 3 Ventral fins CHECK Condition Attachments 4 Inspection door under fuselage CLOSED CHECK Attachments 5 Horizontal stabilizer deicer boots R H side CHECK Condition Attachments 6 Elevator and trim CHECK Condition Deflection free movement Trim position 7 Stat...

Page 284: ...PROCEDURES Page 4 3 12 Edition 1 June 22 2007 Rev 1 CHECK LIST PROCEDURES PREFLIGHT INSPECTION Cont d 9 Rudder and trim CHECK Condition Trim position 10 Static dischargers CHECK Condition 11 Tail cone Condition CHECK 12 Static pressure ports Clean CHECK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 285: ...eflight inspection COMPLETED 2 Cabin access door CLOSED LOCKED 3 Pilot door if installed CLOSED LOCKED 4 Baggage STOWED 5 Parking brake SET 6 Weight and balance COMPUTED CHECKED 7 Pilot seat and R H front seat if occupied Height adjustment Maximum UP Fore and aft adjustment ADJUST and CHECK LOCKING Height adjustment ADJUST CAUTION IT IS MANDATORY TO ADJUST SEAT IN FORE AFT MOVEMENT WHEN SEAT IS IN...

Page 286: ...er NORMAL 12 Landing gear control DN 13 AVIONICS MASTER switch START 14 LEFT PFD REVERSIONARY mode ENGAGED DISPLAY BACK UP button OUT 15 RADIO VHF ON ADJUSTED 16 IGNITION switch AUTO or OFF 17 STARTER switch OFF 18 SOURCE selector BAT or GPU 19 Authorization for engine starting ASKED 20 Pilots OXYGEN switch ON 21 PASSENGERS OXYGEN switch OFF 22 Copilot and pilot masks Press push button PRESS TO TE...

Page 287: ...door and if installed pilot door WARNING CAS MESSAGE DOOR OFF Oxygen emergency system WARNING CAS MESSAGE OXYGEN OFF Vacuum system CAUTION CAS MESSAGE VACUUM LOW ON 25 Fuel Quantity CHECKED Tank selector L or R CHECKED 26 EXT LIGHTS panel STROBE AS REQUIRED 27 In case of night flight INT LIGHTS panel INSTR PANEL ADJUSTED Navigation lights ON Flashlight if necessary IN PLACE PIM DO NOT USE FOR FLIG...

Page 288: ... IGNITION switch AUTO or OFF 2 STARTER switch OFF 3 INERT SEP switch OFF 4 Landing gear control DN 5 ELECTRIC POWER panel SOURCE selector BAT Voltage CHECKED 24 5 Volts 6 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever...

Page 289: ...h ON WARNING CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAGE FUEL PRESS OFF 9 Propeller AREA CLEAR 10 ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON NOTE The utilization of the starter is bound by limitations mentioned in Chapter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE Monitor increase of ITT max ITT 8...

Page 290: ...NE POWER 3 5 11 STARTER switch OFF Check Ng 52 12 Condition lever HI IDLE 13 Engine instruments CHECK Ng 70 2 Oil pressure Oil temperature ITT green sector 14 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF 15 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary Ammeters CHARGE CHECKED Voltmeters VOLTAGE CHECKED V 28 Volts PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 291: ...TURE INDICATION APPEARS MAX ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or AUTO Wait ITT 850 C then STARTER switch OFF BEFORE ANY RESTARTING ATTEMPT CARRY OUT A MOTORING Refer to paragraph MOTORING CAUTION IF ENGINE STAGNATES INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or AUT...

Page 292: ...Ng 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF Ng 50 STARTER switch OFF WARNING CAS MESSAGE STARTER OFF WARNING CAS MESSAGE IGNITION OFF Engine instruments CHECK Ng 70 2 Oil pressure ITT green sector NOTE This behaviour should only be observed with outside low temperature OAT 0 C cold...

Page 293: ... AUTO or OFF 3 STARTER switch OFF 4 INERT SEP switch OFF 5 Landing gear control DN 6 SOURCE selector GPU WARNING CAS MESSAGE GPU DOOR ON WARNING CAS MESSAGE BAT OFF ON Voltmeter VOLTAGE CHECKED V 28 Volts 7 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller go...

Page 294: ...CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAGE FUEL PRESS OFF Fuel pressure indicator CHECK 10 Propeller AREA CLEAR 11 ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON NOTE The utilization of the starter is bound by limitations mentioned in Chapter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE Monitor increas...

Page 295: ...eller governor lever FEATHER 14 GPU HAVE IT DISCONNECTED WARNING CAS MESSAGE GPU DOOR OFF 15 Condition lever HI IDLE 16 Propeller governor lever MAX RPM 17 Engine instruments CHECK Ng 70 2 Oil pressure Oil temperature ITT green sector 18 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF 19 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary Ammeters CHARGE CHECKED Vo...

Page 296: ...RATURE INDICATION APPEARS MAX ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or AUTO Wait ITT 850 C then STARTER switch OFF BEFORE ANY RESTARTING ATTEMPT CARRY OUT A MOTORING Refer to paragraph MOTORING CAUTION IF ENGINE STAGNATES INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or A...

Page 297: ...Ng 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF Ng 50 STARTER switch OFF WARNING CAS MESSAGE STARTER OFF WARNING CAS MESSAGE IGNITION OFF Engine instruments CHECK Ng 70 2 Oil pressure ITT green sector NOTE This behaviour should only be observed with outside low temperature OAT 0 C cold...

Page 298: ...WN WAIT AT LEAST 30 SECONDS BEFORE INITIATING A MOTORING 1 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON WARNING CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAG...

Page 299: ...lear fuel and vapor internally trapped 4 STARTER switch ON during 15 sec maxi WARNING CAS MESSAGE STARTER ON To cool engine following shut down in high temperature environment 4 STARTER switch ON during 30 sec WARNING CAS MESSAGE STARTER ON 5 STARTER switch OFF WARNING CAS MESSAGE STARTER OFF 6 FUEL panel AUX BP switch OFF WARNING CAS MESSAGE AUX BOOST PMP ON OFF WARNING CAS MESSAGE FUEL PRESS ON ...

Page 300: ...rting procedure from a motoring procedure 1 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON WARNING CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAGE FUEL PRESS OF...

Page 301: ...ds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF Ng 50 stable STARTER switch OFF WARNING CAS MESSAGE STARTER OFF WARNING CAS MESSAGE IGNITION OFF 7 Engine instruments CHECK Ng 52 Oil pressure ITT green sector 8 Condition lever HI IDLE 9 Engine instruments CHECK Ng 70 2 Oil pressure Oil temperature ITT green sector 10 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF 11...

Page 302: ...on PRESS Verify rotation of FUEL TANK SELECTOR 6 Oxygen supply Available for the planned flight see tables of paragraph IN FLIGHT AVAILABLE OXYGEN QUANTITY in this Chapter and Chapter 7 10 for a FAR 135 type operation 7 LEFT PFD REVERSIONARY mode DISENGAGED DISPLAY BACK UP button IN 8 PFD 1 MFD and PFD 2 Brightness ADJUST if necessary DISPLAY BACKUP button CHECK then return to NORMAL mode When amm...

Page 303: ...S Radio altimeter if installed ADJUSTED TESTED 14 MFD flight management Weight computing SET CHECKED FOB synchro SET FPL if requested SET 15 AP TRIMS AP TRIMS MASTER operation CHECK Pitch trim UP DN then ADJUSTED Yaw trim L R then ADJUSTED Roll trim L R then ADJUSTED 16 DE ICE SYSTEM panel MFD on system page PROP DE ICE switch ON Check illumination of the green light located above the switch PROP ...

Page 304: ...STARTING ENGINE 3 3 Increase power so as to get Ng 80 to check AIRFRAME DE ICE AIRFRAME DE ICE switch ON Visually check functioning of deicer boots during 1 total cycle and illumination of the two green lights located above the switch AIRFRAME DE ICE switch OFF INERT SEP switch ON WARNING CAS MESSAGE INERT SEP ON ON after 30 seconds PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 305: ... temperature OAT Read 1 Determine the usable oxygen percent using the chart Figure 4 3 5 Figure 4 3 5 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 4 3 6 by the percent obtained with the chart Figure 4 3 5 Number of passengers Duration Passengers plus 1 pilot Duration Passengers plus 2 pilots 0 226 113 1 162 94 2 127 81 3 104 71 4 88 65 Figure 4 3 6 PIM ...

Page 306: ... CHECK WARNING CAS MESSAGE INERT SEP ON ON 3 Passenger briefing AS REQUIRED 4 Parking brake RELEASED WARNING CAS MESSAGE PARK BRAKE OFF 5 L H and R H seats brakes CHECKED 6 Nose wheel steering CHECKED 7 Power lever AS REQUIRED CAUTION AVOID USING REVERSE DURING TAXIING 8 Flight instruments CHECK 9 CAS display CHECK 10 Cabin pressurization control panel Cruise altitude 1000 feet PIM DO NOT USE FOR ...

Page 307: ...O 5 DE ICE SYSTEM panel AIRFRAME DE ICE switch As required PROP DE ICE switch As required If runway is in good condition without icing conditions INERT SEP switch OFF WARNING CAS MESSAGE INERT SEP ON OFF If there is standing water or other contamination on the runway INERT SEP switch Leave ON WARNING CAS MESSAGE INERT SEP ON ON WINDSHIELD switch As required PITOT L HTR switch ON PITOT R STALL HTR ...

Page 308: ...ON 11 Fuel Gages quantity symmetry CHECKED FUEL SEL switch CHECK AUTO AUX BP fuel switch CHECK AUTO 12 Flight instruments CHECKED Altimeter setting ADJUSTED CHECKED ALT SEL ADJUSTED CHECKED 13 VHF VOR GPS XPDR ADJUSTED CHECKED Radar Stormscope TAS TAWS ADF if installed ADJUSTED CHECKED Radio altimeter if installed ADJUSTED CHECKED Transponder code ADJUSTED CHECKED 14 Engine instruments CHECK 15 Ba...

Page 309: ...de 2 2 Heading HSI Stand by compass CHECK Altimeter setting CHECK 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ITT green sector 5 CAS display CHECK All messages OFF except INERT SEP ON if used except IGNITION if used 6 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 PR...

Page 310: ...15 Weight 6579 lbs 2984 kg ATTITUDE 12 5 10 Vertical speed indicator POSITIVE 11 Brakes APPLY Briefly 12 Landing gear control IAS 128 KIAS UP At sequence end check All warning lights OFF 13 Initial climb speed Weight 6579 lbs 2984 kg 110 KIAS Weight 6579 lbs 2984 kg 115 KIAS 14 Flaps UP Only when flaps are confirmed UP 15 Flap control 850 16 Power lever TRQ 121 4 17 Climb speed recommended 130 KIA...

Page 311: ...ION OBSERVE TRQ Ng Np ITT T AND OIL PRESSURE LIMITATIONS USE OPTIMUM TORQUE AND OR REFER TO TABLES IN CHAPTER 5 8 2 Climb speed AS REQUIRED 3 ECS panel Cabin pressure control panel Cruise altitude 1000 feet Pressurization CHECK CABIN TEMP C selectors ADJUST 4 Fuel tank gages CHECK CORRECT Quantity Symmetry 5 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PREC...

Page 312: ... REFER TO TABLES IN CHAPTER 5 8 2 Pressurization CHECK 3 Fuel Gages CHECK REGULARLY CHECK consumption Pre MOD70 0402 28 Fuel sequencer evolution tank automatic change every 10 minutes Post MOD70 0402 28 Fuel sequencer evolution tank automatic change every 5 minutes All expected fuel at destination symmetry max dissymmetry 15 us gal 57 Litres 4 Cruise parameters engine data CHECK RECORD 5 DE ICE SY...

Page 313: ...P TO 850 1 Flaps CHECKED UP 2 Propeller RPM 2000 3 Power lever TRQ 100 4 Flap control lever From UP to 850 5 Power lever As required TRQ less than 121 4 FLAP CONTROL TRANSITION FROM 850 TO UP 1 Altitude At or above 1500 ft AGL 2 Propeller RPM 2000 3 Power lever TRQ 100 4 Flap control lever From 850 to UP 5 Power lever As required TRQ less than 100 2000 RPM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 314: ...YSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNITION AND INERT SEP ON CAUTION USE OF CONTROL REVERSE BETA β RANGE BEHIND THE FLIGHT IDLE POSITION IS PROHIBITED DURING FLIGHT 6 Windshield misting protection system As required 7 Fuel Gages CHECK Quantity Symmetry Fullest tank SELECT 8 Passengers briefing As required 9 Seats belts and harnesses LOC...

Page 315: ...SELECT 3 INERT SEP switch IAS 200 KIAS ON 4 Propeller lever MAX RPM 5 Landing gear control IAS 178 KIAS DN Green indicator lights ON Red warning light OFF 6 Flaps IAS 178 KIAS TO 7 Lights L LDG TAXI R LDG ON Short final 8 Autopilot DISCONNECT 9 Flaps IAS 122 KIAS LDG 10 Approach speed Flaps LDG Weight 6250 lbs 2835 kg 80 KIAS Weight 6250 lbs 2835 kg 85 KIAS Flaps LDG With AP engaged 85 KIAS 11 YAW...

Page 316: ...ever IDLE After wheels touch 2 Reverse As required Reverse may be applied as soon as the wheels touch the ground To avoid ingestion of foreign objects come out the reverse as speed reduces and use the brakes if necessary for further deceleration CAUTION ON SNOWY OR DIRTY RUNWAY IT IS BETTER NOT TO USE REVERSE BELOW 40 KIAS 3 Brakes As required PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 317: ...ow 6579 lbs 2984 kg If the vertical speed is positive and if IAS is at or above 85 KIAS 4 Landing gear control UP All warning lights OFF If IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed AS REQUIRED Weight above 6579 lbs 2984 kg If the vertical speed is positive and if IAS is at or above 90 KIAS 7 Landing gear control UP All warning lights OFF If IAS is at or above 115 KIAS 8 Flaps UP 9 Clim...

Page 318: ...Rev 13 CHECK LIST PROCEDURES TOUCH AND GO After wheels touch 1 Flaps TO 2 Elevator trim Green sector 3 Power lever Display TRQ 100 4 Takeoff ROTATION See Takeoff distances Chapter 5 9 Normal takeoff ATTITUDE 7 5 Short takeoff Weight 6579 lbs 2984 kg ATTITUDE 15 Weight 6579 lbs 2984 kg ATTITUDE 12 5 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 319: ...LEAR AIRPLANE STOPPED 1 DE ICE SYSTEM panel AIRFRAME DE ICE switch OFF PROP DE ICE switch OFF INERT SEP switch CHECKED ON WINDSHIELD switch As required PITOT L HTR switch OFF PITOT R STALL HTR switch OFF 2 Radar if installed CHECKED STANDBY 3 Transponder CHECKED SBY 4 Flaps UP 5 STROBE switch OFF 6 Lights L LDG R LDG OFF TAXI ON 7 OXYGEN switch OFF PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 320: ...surization AIR COND switch OFF 3 Condition lever HI IDLE 4 Power lever IDLE for 2 minutes 5 TAXI light OFF 6 AP TRIMS MASTER switch OFF CAUTION IN CASE OF SHUT DOWN ON A CONTAMINATED AREA Condition lever CUT OFF Propeller governor lever FEATHER 7 Propeller governor lever FEATHER for 15 seconds 8 Condition lever CUT OFF 9 INERT SEP switch OFF 10 AVIONICS MASTER switch OFF 11 EXT LIGHTS panel All sw...

Page 321: ... TO IMPROVE COOLING OF THE BEARING CAVITIES AND MINIMIZE OIL COKING REFER TO PARAGRAPH MOTORING 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 Remove all aircraft power from the ESI Pre...

Page 322: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 4 NORMAL PROCEDURES EASA Approved CHECK LIST PROCEDURES Page 4 3 50 Edition 1 June 22 2007 Rev 13 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 323: ...wed in the front cargo compartment with the towing bar and the blanking covers 5 Flight controls Deflections checked 6 Parking brake SET 7 Landing gear control DN 8 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION When engine is shut off a lack of hydraulic pressure prevents movement into reverse rang...

Page 324: ...s to have the door in place 12 ECS panel BLEED switch OFF AIR COND switch OFF DUMP switch GUARDED 13 Static Air control knob PUSHED 14 RAM AIR control knob PUSHED 15 Breakers panel All breakers ENGAGED 16 AVIONICS MASTER switch OFF 17 AP TRIMS MASTER switch OFF 18 Fuel FUEL SEL selector MAN AUX BP switch OFF 19 ENGINE START panel IGNITION switch AUTO or OFF The IGNITION switch is normally selected...

Page 325: ...RCE selector OFF 21 Access lighting CHECKED This check allows to ensure that the fuse of the BAT BUS operates correctly 22 INT LIGHTS panel OFF 23 EXT LIGHTS panel All switches OFF 24 Pilots OXYGEN switch OFF 25 PASSENGERS OXYGEN switch OFF 26 Emergency lighting CHECKED CAUTION BEFORE SELECTING SOURCE CHECK 27 IGNITION switch AUTO or OFF 28 STARTER switch OFF 29 Landing gear control DN 30 SOURCE s...

Page 326: ...28 volt regulated voltage with negative on earth as well as it supplies 800 amperes minimum and 1400 amperes maximum See placard located near ground power receptacle door 32 EXT LIGHTS panel LTS TEST push button PRESS All instrument panel lamps ON except on landing gear control panel L LDG TAXI R LDG switches ON 3 green lamps ON The illuminated three green lamps located on switches prove the corre...

Page 327: ...FLASHING 3 GREEN ON Test 1 and 2 correspond to BUS bars 1 or 2 which feed them respectively 41 DE ICE SYSTEM panel PITOT L HTR switch ON WARNING CAS MESSAGE PITOT HT L ON PITOT R STALL HTR switch ON Correct operation of pitot PITOT L and R tube heating elements and of stall aural warning system STALL HTR is indicated by display of corresponding CAS message when control switches are ON WARNING CAS ...

Page 328: ...PLAYED Cabin II 1 Cabin fire extinguisher CHECK Pressure Attachment 2 Seats belts CHECK 3 Windows CHECK General condition No crack 4 Emergency exit CLOSED LOCKED Anti theft safety REMOVE STOW 5 Baggage compartment STRAPS IN PLACE 6 Partition net if 6 seat accommodation IN PLACE CHECK general condition 7 Large net or small net if 4 seat accommodation and if baggage transportation IN PLACE CHECK gen...

Page 329: ...ide the use of the flight control lock and blanking covers is recommended Propeller should be tied down to prevent rotation without oil pressure When the airplane is stored for extended periods of time a thorough preflight inspection is recommended Particular attention should be paid to possible blockages in airspeed sensing lines foreign objects in engine intake and exhaust stubs and water contam...

Page 330: ... consequent exertion to lock and unlock them to avoid water infiltration in case of rain on ground and to avoid fuel loss in flight 7 Fuel tank air vent Unobstructed CHECK Air vent is not likely to be obstructed by ice or water as it is located in a wing lower surface recess 8 Left pitot Condition CHECK 9 Wing lower surface CHECK No leak Check fuel tank access doors for leaks Check for surface dam...

Page 331: ...uel additives 12 L H main landing gear Shock absorber doors tire wheel well CHECK If airplane has been used from muddy airfields or in snow check wheel wells to make sure they are clean and not obstructed Check frequently all landing gear retraction mechanism components shock absorbers tires and brakes This is particularly important for airplanes used from hilly fields Improperly serviced or worn ...

Page 332: ...tinuous heating of air inlet lip 5 Upper engine cowls OPEN For the first flight of the day Oil cap CLOSED LOCKED Engine oil level CHECK Fuel pipes CHECK No leak deterioration wear 6 Engine cowls Condition CHECK CLOSED LOCKED 7 Air inlets Main No crack UNOBSTRUCTED Check for no cracks which are sometimes put in evidence by traces of soot resulting from exhaust gases Lateral upper UNOBSTRUCTED Later...

Page 333: ...ear Landing light shock absorber doors tire wheel well CHECK Without passengers and baggages on board the unpainted surface of the nose gear shock absorber tube must be visible about 57 mm 2 22 in of minimum height with full tanks 63 mm 2 46 in of minimum height with half tank NOTE Crush or relieve the shock absorber one time or twice before the inspection to remove possible sticking In case of do...

Page 334: ... 5 Wing lower surface CHECK No leaks 6 Fuel tank CAP CLOSED LOCKED 7 Fuel tank air vent Unobstructed CHECK 8 Right pitot Condition CHECK 9 Wing tip nav light strobe landing light Condition CHECK 10 Trailing edge static discharger CHECK Condition Number Attachment 11 Aileron spoiler CHECK Condition Free movement Deflection 12 Flap CHECK Condition Play 13 Rear R H karman Oxygen cylinder OPEN Oxygen ...

Page 335: ...Ventral fins CHECK Attachment condition Ventral fins are made of two parts one fixed part and one removable part with rear lower inspection door Check that these two parts are connected by the locking roller 4 Inspection door under fuselage CLOSED CHECK Attachments 5 Horizontal stabilizer deicer boots R H side CHECK Condition Attachments 6 Elevator and trim CHECK Condition Deflection free movement...

Page 336: ...PROCEDURES Page 4 4 14 Edition 1 June 22 2007 Rev 1 AMPLIFIED PROCEDURES PREFLIGHT INSPECTION Cont d 9 Rudder and trim CHECK Condition Trim position 10 Static dischargers CHECK Condition 11 Tail cone Condition CHECK 12 Static pressure ports Clean CHECK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 337: ...CH 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 COMPLETED 2 Cabin access door CLOSED LOCKED 3 Pilot door if installed CLOSED LOCKED 4 Baggage STOWED 5 Parking brake SET PARK BRAKE CAS message appearance does not indicate that parking brake is set For that press o...

Page 338: ...station seats and harnesses so as to permit access to all flight controls The pilot at L H station must be able to easily reach ECS panel 8 R H and L H pedals ADJUSTED 9 Belts and harnesses Pilot and passengers FASTENED Check belt buckles for correct locking as well as automatic locking of shoulder harness by exerting a rapid pull on the latter 10 Passengers seat backrest UPRIGHT 11 NORMAL MASK mi...

Page 339: ... switch OFF 22 Copilot and pilot masks Press push button PRESS TO TEST the blinker shall turn red momentarily then turns transparent 23 Passengers briefing AS REQUIRED 24 CAS display Access door and if installed pilot door WARNING CAS MESSAGE DOOR OFF If DOOR CAS message is not OFF open the access door and if installed the pilot door and reclose it them Check locking pins are in place green band i...

Page 340: ...e of strobe lightsmay generate discomfort to personnel on ground particularly by night 27 In case of night flight INT LIGHTS panel INSTR PANEL ADJUSTED Navigation lights ON Flashlight if necessary IN PLACE To maintain battery power for starting and only when GND CLR ground clearance is available on airplane VHF1 can be operated by setting SOURCE selector to OFF and AVIONICS MASTER switch to ON If ...

Page 341: ...IGNITION switch AUTO or OFF 2 STARTER switch OFF 3 INERT SEP switch OFF 4 Landing gear control DN 5 ELECTRIC POWER panel SOURCE selector BAT Voltage CHECKED 24 5 Volts 6 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever ...

Page 342: ...MP ON ON WARNING CAS MESSAGE FUEL PRESS OFF 9 Propeller AREA CLEAR 10 ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON NOTE The utilization of the starter is bound by limitations mentioned in Chapter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE When condition lever is positioned on LO IDLE before having obtained ...

Page 343: ... 170 C within starter operation limits before opening of the condition lever may allow to stay within above mentioned ITT limits In case of higher temperature and longer time stop immediately the starting procedure as indicated in the following caution and inform the maintenance department If starting engine procedure is aborted further to overtemperature indications max ITT 870 C for more than 20...

Page 344: ...efore starting a new test respect delays indicated in Chapter 2 4 STARTER OPERATION LIMITS Oil pressure WARNING CAS MESSAGE OIL PRESS OFF 11 STARTER switch OFF Check Ng 52 12 Condition lever HI IDLE 13 Engine instruments CHECK Ng 70 2 Oil pressure Oil temperature ITT green sector 14 FUEL panel AUX BP switch AUTO At this time observing a drop in the fuel pressure is normal WARNING CAS MESSAGE AUX B...

Page 345: ...URE INDICATION APPEARS MAX ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or AUTO Wait ITT 850 C then STARTER switch OFF BEFORE ANY RESTARTING ATTEMPT CARRY OUT A MOTORING Refer to paragraph MOTORING CAUTION IF ENGINE STAGNATES INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or AUTO...

Page 346: ...g 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF Ng 50 STARTER switch OFF WARNING CAS MESSAGE STARTER OFF WARNING CAS MESSAGE IGNITION OFF Engine instruments CHECK Ng 70 2 Oil pressure ITT green sector NOTE This behaviour should only be observed with outside low temperature OAT 0 C cold ...

Page 347: ... gear control DN 6 SOURCE selector GPU WARNING CAS MESSAGE GPU DOOR ON WARNING CAS MESSAGE BAT OFF ON Voltmeter VOLTAGE CHECKED V 28 Volts If voltage is 30 volts immediately turn SOURCE selector to OFF Radio navigation equipment may be damaged before main fuse failure 7 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLI...

Page 348: ...ator CHECK 10 Propeller AREA CLEAR 11 ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON NOTE The utilization of the starter is bound by limitations mentioned in Chapter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE When condition lever is positioned on LO IDLE before having obtained 13 of Ng there is a risk of over...

Page 349: ... may allow to stay within above mentioned ITT limits In case of higher temperature and longer time stop immediately the starting procedure as indicated in the following caution and inform the maintenance department This starting engine procedure must be also applied in case of drop in voltage supplied by GPU This drop will be shown by a low or zero Ng acceleration If starting engine procedure is a...

Page 350: ... abort the start Before starting a new test respect delays indicated in Chapter 2 4 STARTER OPERATION LIMITS Oil pressure WARNING CAS MESSAGE OIL PRESS OFF 12 SOURCE selector BAT WARNING CAS MESSAGE BAT OFF OFF 13 Propeller governor lever FEATHER 14 GPU HAVE IT DISCONNECTED WARNING CAS MESSAGE GPU DOOR OFF This means that ground power receptacle door has been correctly locked 15 Condition lever HI...

Page 351: ...se Ng over 70 to start main generator Ammeters CHARGE CHECKED Voltmeters VOLTAGE CHECKED V 28 Volts 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 ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch O...

Page 352: ...tion lever CUT OFF IGNITION switch OFF or AUTO STARTER switch OFF WAIT FOR 1 MINUTE Refer to Chapter 2 4 STARTER OPERATION LIMITS THEN TRY TO RESTART ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON Ng 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure W...

Page 353: ...NE USING EXTERNAL POWER GPU 7 7 Ng 50 STARTER switch OFF WARNING CAS MESSAGE STARTER OFF WARNING CAS MESSAGE IGNITION OFF Engine instruments CHECK Ng 70 2 Oil pressure ITT green sector NOTE This behaviour should only be observed with outside low temperature OAT 0 C cold engine This procedure may be used for the first starting of the day PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 354: ... of the bearing cavities and prevent oil coking after shut down in high OAT above 35 C 95 F environment it is recommended to perform a 30 second dry motoring run It is possible that no trace of drainage be observed under engine due to the drainage collector intended to prevent parking area from contamination CAUTION AFTER ANY STARTING INTERRUPT PROCEDURE WAIT FOR ENGINE TOTAL SHUT DOWN WAIT AT LEA...

Page 355: ...GE IGNITION OFF To clear fuel and vapor internally trapped 4 STARTER switch ON during 15 sec maxi WARNING CAS MESSAGE STARTER ON To cool engine following shut down in high temperature environment 4 STARTER switch ON during 30 sec WARNING CAS MESSAGE STARTER ON If ignition symptoms occur ITT increasing check that IGNITION switch is OFF that condition lever is on CUT OFF and continue motoring 5 STAR...

Page 356: ...ssible to initiate a starting procedure from a motoring procedure This procedure will conserve the battery by taking advantage of first Ng acceleration 1 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 2 Fuel T...

Page 357: ...nds max 1000 C for 5 seconds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF NOTE No action is required for the following conditions ITT from 850 C to 870 C limited to 20 seconds ITT from 870 C to 1000 C limited to 5 seconds Ng 50 stable STARTER switch OFF WARNING CAS MESSAGE STARTER OFF WARNING CAS MESSAGE IGNITION OFF 7 Engine instruments CHECK Ng 52 Oil pressure ITT green sector 8 Conditi...

Page 358: ...l AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF At this time observing a drop in the fuel pressure is normal 11 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary MAIN GEN CAS message normally goes out as soon as STARTER CAS message goes out If not increase Ng over 70 to start main generator Ammeters CHARGE CHECKED Voltmeters VOLTAGE CHECKED V 28 Volts PIM DO NOT USE FOR F...

Page 359: ...ated voltage should be in the green range then again on MAIN 2 AVIONICS MASTER switch ON 3 AP TRIMS MASTER switch ON 4 FUEL SEL switch AUTO 5 SHIFT push button PRESS Verify rotation of FUEL TANK SELECTOR 6 Oxygen supply Available for the planned flight see tables of paragraph IN FLIGHT AVAILABLE OXYGEN QUANTITY in this Chapter and Chapter 7 10 for a FAR 135 type operation 7 LEFT PFD REVERSIONARY m...

Page 360: ...select DEFOG or HOT to increase demisting efficiency Cabin pressure control panel Airfield altitude 10 Stand by instruments CHECKED Suction gage PRE MOD70 0335 34 ESI 2000 CHECKED 11 ADI HSI on PFD1 PFD2 CHECKED 12 Altimeter setting 13 VHF VOR GPS ADJUSTED TESTED Radar Stormscope TAS TAWS CHECKED Radio altimeter if installed ADJUSTED TESTED 14 MFD flight management Weight computing SET CHECKED FOB...

Page 361: ...fore takeoff even during taxiing in case of icing conditions on ground Refer to Chapter 4 5 PARTICULAR PROCEDURES of this Section MFD on system page PROP DE ICE switch ON Check illumination of the green light located above the switch Illumination of the green light shows that power supplied to blade root electric resistors is between 8 and 10 amperes It is advised to wait at least a whole half cyc...

Page 362: ...s illuminating surely the two green lights and avoiding VACUUM LOW untimely alarms AIRFRAME DE ICE switch ON Visually check functioning of deicer boots during 1 total cycle and illumination of the two green lights located above the switch The cycle lasts 67 seconds Check both inflation impulses and illumination of each corresponding green light the first impulse inflates the external and middle wi...

Page 363: ...temperature OAT Read 1 Determine the usable oxygen percent using the chart Figure 4 4 1 Figure 4 4 1 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 4 4 2 by the percent obtained with the chart Figure 4 4 1 Number of passengers Duration Passengers plus 1 pilot Duration Passengers plus 2 pilots 0 226 113 1 162 94 2 127 81 3 104 71 4 88 65 Figure 4 4 2 PIM D...

Page 364: ...ed with the power lever 3 Passenger briefing AS REQUIRED 4 Parking brake RELEASED Make sure that chocks are removed if used WARNING CAS MESSAGE PARK BRAKE OFF 5 L H and R H seats brakes CHECKED 6 Nose wheel steering CHECKED Check the control wheel move roll in the same direction as the rudder pedals due to the rudder aileron interconnect 7 Power lever AS REQUIRED After initial acceleration power l...

Page 365: ...d operations However foreign particles dust sand grass gravel etc may be blown into the air ingested by the engine above all if INERT SEP switch is turned OFF and cause damage to the propeller 8 Flight instruments CHECK Check navigation and communication systems before or during taxiing check gyroscopic instruments on PFDs 1 2 and stand by ADI during ground turns 9 CAS display CHECK 10 Cabin press...

Page 366: ...ith the propeller RPM in the caution yellow range at a minimum 4 Flaps TO 5 DE ICE SYSTEM panel AIRFRAME DE ICE switch As required PROP DE ICE switch As required If runway is in good condition without icing conditions INERT SEP switch OFF WARNING CAS MESSAGE INERT SEP ON OFF CAS message goes out immediately but it takes 30 seconds to retract the separator If there is standing water or other contam...

Page 367: ...ntrols DEFLECTIONS CHECKED 7 Trims Pitch ADJUSTED Adjust inside green index sector depending on the current balance condition Yaw ADJUSTED Adjust abeam TO index Roll ADJUSTED Adjust at neutral position 8 Pilot s Passengers belts CHECK Passengers table STOWED Passengers seat backrest CHECK 9 STROBE switch ON 10 CAS display CHECK All messages OFF except PARK BRAKE ON and if used INERT SEP ON ON 11 F...

Page 368: ...al to outside persons Radio altimeter if installed ADJUSTED CHECKED Transponder code ADJUSTED CHECKED 14 Engine instruments CHECK All engine parameters must be in green range except propeller RPM which will be about 1000 RPM or more with power lever at IDLE 15 Battery charge 50 Amperes CAUTION DO NOT TAKE OFF IF BATTERY CHARGE 50 Amperes After starting engine with airplane power a battery charge a...

Page 369: ...WN ICING CONDITIONS 1 Horizon CHECK attitude 2 Horizon has been set so as to indicate a 2 nose up attitude when airplane center of gravity is at a middle average 2 Heading HSI Stand by compass CHECK The indication of the stand by compass is disturbed when windshield deice systems are activated Altimeter setting on PFDs 1 2 CHECK 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ITT green sec...

Page 370: ...g PROP O SPEED test 7 Brakes RELEASED It is not necessary to reduce power at the end of OVERSPEED test torque will be about 40 before brake release For a normal takeoff maximum torque 100 will be applied after brake release On short runway maximum torque will be applied before brake release 8 Power lever TRQ 100 9 Takeoff ROTATION See Takeoff distances Chapter 5 9 Normal takeoff ATTITUDE 7 5 Short...

Page 371: ...tor lights flash unevenly then go off at the end of the sequence At sequence end check All warning lights OFF 13 Initial climb speed Weight 6579 lbs 2984 kg 110 KIAS Weight 6579 lbs 2984 kg 115 KIAS In case of initial climb at Vx it is recommended not to retract flaps to UP before 500 ft AGL Weight 6579 lbs 2984 kg 95 KIAS Weight 6579 lbs 2984 kg 100 KIAS 14 Flaps UP Only when flaps are confirmed ...

Page 372: ...PROCEDURES Page 4 4 50 Edition 1 June 22 2007 Rev 10 AMPLIFIED PROCEDURES TAKEOFF 4 4 16 Power lever TRQ 121 4 17 Climb speed recommended 130 KIAS Trims Pitch Roll and Yaw ADJUSTED 18 YAW DAMPER push button ON 19 Lights TAXI OFF L LDG R LDG AS REQUIRED PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 373: ...gh altitude according to the tables during the final climb reaching the maximum permitted Ng 104 is possible and the ITT will be approximately constant giving a particular value of ITT For a simplified engine operation during climb power may be set first of all by torque using 121 4 then when the ITT typical value for climb is reached by indicated ITT using this particular value The margin between...

Page 374: ...Fuel sequencer evolution In spite of fuel selector automatic operation a non negligible dissymmetry may be observed at the end of climb for example when 10 minutes of climb have been performed on the same fuel tank Consequently it is recommended to select the fullest tank by pushing the SHIFT push button at the beginning of the climb Tolerated maximum dissymmetry is 15 us gal 57 Litres 5 DE ICE SY...

Page 375: ... sea level and drops to about 100 at 31000 ft Therefore any propeller RPM reducing performed in altitude from a torque close to 100 if ITT limit permits it will be followed by a non negligible power and performance decrease owing to torque limiter FLAPS set to 850 position Not active torque limiter Propeller RPM reducing is possible until 121 4 maximum torque is reached red line on indicator CAUTI...

Page 376: ...0 0402 28 Fuel sequencer evolution tank automatic change every 10 minutes Post MOD70 0402 28 Fuel sequencer evolution tank automatic change every 5 minutes All symmetry max dissymmetry 15 us gal 57 Litres When the cruise parameters are stabilized after 4 min minimum 4 Cruise parameters engine data CHECK RECORD 5 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY ...

Page 377: ...to 850 The torque limiter is deactivated CAUTION OBSERVE TRQ Ng Np ITT T AND OIL PRESSURE LIMITATIONS Refer to tables in Chapter 5 8 Engine operation tables Chapter 5 8 give torque to be applied according to OAT in order not to exceed authorized maximum power When INERT SEP switch is OFF a more accurate setting of power must then be performed according to cruise performance tables presented in Cha...

Page 378: ... case of air leak between the solenoïd valve and the torque limiter the available torque might be below 100 Consequently it is strongly recommended not to operate the flap control from 850 to UP below 1500 ft AGL 2 Propeller RPM 2000 3 Power lever TRQ 100 4 Flap control lever From 850 to UP The torque limiter is activated and limits torque to 110 5 Power lever As required TRQ less than 100 2000 RP...

Page 379: ... 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNITION AND INERT SEP ON The maximum speed for changing the position of the inertial separator is 200 KIAS Prior to descending into or through known or suspected icing conditions select INERT SEP switch ON prior to accelerating beyond 200 KIAS There are no special speed limitations with the inertial separator secured in either position ...

Page 380: ...ditions turn AIR FLOW distributor in DEFOG section and set WINDSHIELD switch to ON to avoid canopy misting If misting continues set AIR FLOW distributor to HOT or refer to Chapter 3 12 Paragraph WINDSHIELD MISTING OR INTERNAL ICING 7 Fuel Gages CHECK Quantity Symmetry Fullest tank SELECT 8 Passengers briefing As required 9 Seats belts and harnesses LOCKED 10 Passengers table STOWED 11 Passengers s...

Page 381: ...4 Propeller lever MAX RPM 5 Landing gear control IAS 178 KIAS DN Green indicator lights ON Red warning light OFF During the sequence The red warning light flashes it indicates that the landing gear motor is running It goes off when the 3 landing gears are locked Steady ON red warning light indicates an anomaly refer to EMERGENCY PROCEDURES It is possible that the 3 landing gear position green indi...

Page 382: ...aps LDG Weight 6250 lbs 2835 kg 80 KIAS Weight 6250 lbs 2835 kg 85 KIAS Flaps LDG With AP engaged 85 KIAS This is to avoid any vertical deviation in case of late flaps extension to LDG position in short final To ensure positive and rapid engine response to throttle movement it is recommended that a minimum of 10 torque be maintained on final approach until landing is assured 11 YAW DAMPER push but...

Page 383: ...o avoid ingestion of foreign objects come out the reverse as speed reduces and use the brakes if necessary for further deceleration High power reverse at low speed can throw loose material into the air and can cause control problems and decrease the comfort of crew and passengers If permitted by the runway length it is better to adopt a moderate reverse CAUTION ON SNOWY OR DIRTY RUNWAY IT IS BETTE...

Page 384: ...trim can be adjusted 3 Flaps TO Weight below 6579 lbs 2984 kg If speed has been maintained at 80 KIAS or more and TRQ 100 select TO flaps as soon as the 7 5 attitude has been attained If the vertical speed is positive and if IAS is at or above 85 KIAS 4 Landing gear control UP All warning lights OFF If IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed AS REQUIRED Weight above 6579 lbs 2984 kg I...

Page 385: ...UND 2 2 If IAS is at or above 115 KIAS 8 Flaps UP In case of air leak between the solenoïd valve and the torque limiter the available torque might be below 100 Consequently it is strongly recommended not to select 850 for a new approach or visual circuit for staying below 1500 ft AGL 9 Climb speed AS REQUIRED 10 Power AS REQUIRED PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 386: ...quence 3 Power lever Display TRQ 100 4 Takeoff ROTATION See Takeoff distances Chapter 5 9 Normal takeoff ATTITUDE 7 5 Short takeoff Weight 6579 lbs 2984 kg ATTITUDE 15 Weight 6579 lbs 2984 kg ATTITUDE 12 5 Rotation speed at takeoff according to airplane weight is also given in Chapter 5 9 However the pilot s operating handbook does not supply distances concerning touch and go These distances are l...

Page 387: ... ON WINDSHIELD switch As required PITOT L HTR switch OFF PITOT R STALL HTR switch OFF 2 Radar if installed CHECKED STANDBY Maintain radar if installed on STANDBY in order not to generate radiations prejudicial to outside persons The radar is automatically set to STANDBY after the touch down 3 Transponder CHECKED SBY The transponder is automatically set to SBY after the touch down 4 Flaps UP 5 STRO...

Page 388: ... lever HI IDLE 4 Power lever IDLE for 2 minutes This allows the engine to stabilize at minimum obtainable ITT in order to minimize the likelihood of oil coking in the 3 bearing area 5 TAXI light OFF 6 AP TRIMS MASTER switch OFF CAUTION IN CASE OF SHUT DOWN ON A CONTAMINATED AREA Condition lever CUT OFF Propeller governor lever FEATHER 7 Propeller governor lever FEATHER for 15 seconds Keep propelle...

Page 389: ...panel All switches OFF 13 Fuel When fuel pressure is below 10 psi 2 psi check AUX BP pump is operating AUX BP switch OFF FUEL SEL switch MAN Tank selector OFF 14 GENERATOR selector OFF 15 SOURCE selector OFF 16 CRASH lever PULL DOWN 17 Parking brake As required CAUTION IN CASE OF HIGH OAT ABOVE 35 C 95 F IT IS REQUIRED TO PERFORM 30 SECONDS DRY MOTORING RUN AFTER SHUT DOWN TO IMPROVE COOLING OF TH...

Page 390: ...tdown The ESI 2000 will shut down within 5 minutes ESI 2000 MANUAL PROCEDURE The ESI 2000 can be manually shut down when in the discharge mode to conserve battery power Remove all aircraft power from the ESI Press any key button as stated by the on screen message Press the M Menu button repeatedly until shutdown menu is shown Press and hold the Hold button until SHUTTING DN message is shown in the...

Page 391: ...n ramps taxiways or runways where surface snow ice standing water or slush may be ingested by the engine or freeze on engine or cowlings NOTE Refer to Figure 5 5 1 to convert OAT to SAT in flight SAT OAT 2 C on the ground 3 Flight into known icing conditions is authorized when all airplane equipment provided for ice protection is operating correctly This includes Pneumatic deice system for inboard...

Page 392: ...ave as soon as possible icing conditions Apply LEADING EDGES DEICING FAILURE emergency procedure Ice protection procedures 1 Prior to entering IMC as a preventive If OAT 5 C INERT SEP switch ON IGNITION switch ON PROP DE ICE switch ON AIRFRAME DE ICE switch ON WINDSHIELD DE ICE switch ON 2 When operating under IMC INERT SEP switch ON IGNITION switch ON PROP DE ICE switch ON AIRFRAME DE ICE switch ...

Page 393: ...ch to ON before accelerating This will avoid reducing speed below 200 KIAS during descent to set the inertial separator IF AIRPLANE LEAVES ICING CONDITIONS MAINTAIN INERT SEP ON AS LONG AS ICE THICKNESS ON NON DEICED VISIBLE PARTS EXCEEDS 15 mm OR INCH This will avoid ice fragments coming from propeller spinner and being ingested by engine INERTIAL SEPARATOR POSITION AFFECTS ENGINE PARAMETERS PART...

Page 394: ...ach and landing at minimum speeds noted above Ice accumulation effects When ice has accumulated on the unprotected surfaces of the airplane aerodynamic characteristics may be changed Particularly stall speeds may increase by up to Flaps UP 20 KIAS Flaps TO 15 KIAS Flaps LDG 10 KIAS Correct operation of the aural stall warning may be altered by severe or prolonged icing Indeed in case of severe or ...

Page 395: ... 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 Because of the higher landing speed landing distances will be increased In the landing configuration using 90 KIAS approach speed increases landing distance by 20 refer to Chap...

Page 396: ... cold as 18 C increased vigilance is warranted at temperatures around freezing with visible moisture present If the visual cues specified in Section 2 Limitations for identifying severe icing conditions are observed accomplish the following 1 Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to av...

Page 397: ...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 7 If the flaps are extended do not retract them until the airframe is clear of ice 8 Report these weather conditions to Air Traffic Control PIM DO NOT USE FOR...

Page 398: ...IGNITION switch ON This action is intended in highly improbable case of an engine flame out further to an important ingestion to ensure immediate restarting without action of the pilot 2 INERT SEP switch ON UTILIZATION ON RUNWAYS COVERED WITH WATER If takeoff or landing must be performed on a runway covered with water 1 IGNITION switch ON 2 INERT SEP switch ON PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 399: ...e surfaces upper and lower surfaces and in the landing gear wells shortly before takeoff Taxiing 1 INERT SEP switch ON 2 Taxi at very slow speed max 5 KIAS flaps up brake occasionally to maintain the brake pads warm this will prevent any subsequent locking due to freezing after takeoff Before takeoff 1 If the runway is long enough takeoff should be performed with the flaps in the up position In th...

Page 400: ...ring takeoff run in order to reduce the forward resistance due to snow accumulation against the wheel 2 After takeoff normally retract the landing gear then perform a complete cycle extension retraction at IAS 128 KIAS Before landing 1 IGNITION switch ON 2 INERT SEP switch ON Touch and Go Prohibited On the ramp after landing or taxiing 1 Do not use the parking brake to prevent brake lock 2 Use cho...

Page 401: ...on the wings stabilizers and movable surfaces upper and lower surfaces shortly before takeoff Taxiing 1 INERT SEP switch ON 2 Taxi at very slow speed max 5 KIAS Use β area of power lever to adjust speed Apply very smooth variations using power lever 3 Steer the airplane using the rudder Make turns at a very low speed engine torque tends to make the airplane turn to the left 4 Use brakes only at ve...

Page 402: ...r The engine torque tends to make the airplane turn to the left 2 Taxi at very slow speed max 5 KIAS Use β area of power lever to adjust speed Apply very smooth variations using power lever 3 Steer the airplane using the rudder Make turns at a very low speed engine torque tends to make the airplane turn to the left 4 Use brakes only at very low speed and progressively On the ramp after landing or ...

Page 403: ...al procedures for the airplane use when operating under temperatures between 0 C and 40 C on ground Figure 4 5 1 OPERATING ENVELOPES BY COLD WEATHER 0 C to 25 C AND VERY COLD WEATHER 25 C to 40 C 40 30 20 10 0 10 OPERATING ENVELOPES Transit time hours O A T C 10 9 8 7 6 5 4 3 2 1 0 ENVELOPE 2 Hot air preheating GPU starting Feather Hi Idle Normal procedures ENVELOPE 1 Normal procedures BAT startin...

Page 404: ...YS COVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS 2 Carry out a complete rotation of the propeller to check its free rotation 3 Do not perform a fuel draining If the airplane is operating permanently under negative temperatures drainings will have to be performed once a week after having parked the airplane in a heated hangar 4 Remo...

Page 405: ...cedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Landing After landing 1 Apply normal procedures defined in Chapter s 4 3 and or 4 4 2 Apply according to the condition of runways and taxiways the procedures UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Shut down 1 Parking brake RELEASED WARNING ...

Page 406: ...let on engine rear table by opening the upper cowling in the cabin by half opening the door 2 Remove any snow or ice from the wings stabilizers and movable surfaces Apply according to the condition of runways and taxiways the procedures UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Spray anti icing fluid on t...

Page 407: ...r lever and of the propeller governor lever 8 IGNITION switch ON during 30 seconds WARNING CAS MESSAGE IGNITION ON then IGNITION switch AUTO WARNING CAS MESSAGE IGNITION OFF This enables to preheat spark igniters before starting the engine Before starting the engine Apply normal procedures defined in Chapter s 4 3 and or 4 4 Starting the engine The starting must be mandatorily performed using an e...

Page 408: ...CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Propeller governor lever Feather Condition lever CUT OFF 4 Fuel panel AUX BP switch ON WARNING CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAGE FUEL PRESS OFF Fuel pressure indicator Check 5 Propeller AREA CLEAR 6 ENGINE START panel IGNITION switch ON WARNING CAS MESSAGE IGNITI...

Page 409: ...rature is low the more the selector is hard to move Starter limits and checks of starting sequence are unchanged 7 Engine instruments Check NG 70 2 Oil pressure ITT green sector 8 SOURCE selector BAT WARNING CAS MESSAGE BAT OFF OFF 9 IGNITION switch AUTO WARNING CAS MESSAGE IGNITION OFF 10 Ground power unit HAVE IT DISCONNECTED WARNING CAS MESSAGE GPU DOOR OFF 11 FUEL panel AUX BP switch AUTO WARN...

Page 410: ...e current flow is lower than 100 A BLEED switch AUTO CABIN CTRL selector OVERRIDE CABIN TEMP C selector FULL HOT 2 Propeller governor lever As soon as the oil temperature is greater than 0 C Propeller governor lever MAX RPM Perform 2 propeller regulations 3 Apply normal procedures defined in Chapter s 4 3 and or 4 4 Taxiing Before takeoff Takeoff Apply procedures defined for Envelope 1 Landing Aft...

Page 411: ...s Preflight inspection Before starting the engine Starting the engine Apply the procedures defined for the Envelope 2 After starting the engine 1 On ECS panel As soon as the current flow is lower than 100 A BLEED switch AUTO CABIN CTRL selector OVERRIDE CABIN TEMP C selector FULL HOT Preheat the cabin respecting time defined in Figure 4 5 2 before switching on the navigation and monitoring systems...

Page 412: ... TO 40 C 10 10 Taxiing Before takeoff Takeoff Apply procedures defined for Envelope 1 Landing After landing Shut down Apply procedures defined for Envelope 1 Complement If landing is foreseen by cold or very cold weather or in case of prolonged operation of the airplane in such conditions it is recommended to prepare the airplane as specified in Chapter 8 9 Figure 4 5 2 PREHEATING DURATION PIM DO ...

Page 413: ...g difficulties and landing performance During approach with crosswind maintain airplane in drift correction at the latest until the beginning of flare CAUTION MAXIMUM TIME FOR SIDESLIP CONDITION IS 30 SECONDS In short final on a short runway it is necessary to use normal approach speed 80 KIAS with flaps LDG in order to avoid an excessive speed Indeed in this case landing distance indicated in Cha...

Page 414: ...eration may provide pitch oscillations while increasing the yaw movement to the wind Do not deflect ailerons into wind while taxiing This will raise spoilers and have a detrimental effect A good solution is to maintain ailerons to neutral position during second taxi phase after landing and during first taxi phase before takeoff Maximum demonstrated crosswind for landing is 20 kt The most restricti...

Page 415: ...KEOFF 1 INERT SEP switch ON 2 Reverse Do not use In fact on a flat runway with grass it is necessary to adopt a power greater than the one obtained when the power lever is set to IDLE so the pilot will not be tempted to use the reverse LANDING 1 INERT SEP switch ON After wheel touch down 2 Reverse Only if necessary Do not maintain reverse at speeds below 40 KIAS to avoid ingestion of foreign matte...

Page 416: ...t 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 GPS flight plan In the active flight plan addition of a STAR or an approach is always made at the end of the flight plan In the scope of these additions the pilot m...

Page 417: ...edicted in any part of the intended flight 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 An alarm is provided by G1000 system in that case When 23 or more satellites are available the prediction of satellite position ...

Page 418: ...ON 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 mode For memory the approach particular point name in the GARMIN system is as follows IA IAF FA FAF ou FAP MA MAP MH MAHP PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 419: ...b power FL 200 5 8 3A Maximum climb power FL 200 5 8 4A Climb at 700 SHP power FL 200 5 8 5A Climb at 700 SHP power FL 200 5 8 6A Maximum cruise power FL 200 5 8 7A Maximum cruise power FL 200 5 8 8A Normal recommended cruise power FL 200 5 8 9A Normal recommended cruise power FL 200 5 8 10A 5 9 TAKEOFF DISTANCES 5 9 1 Weight 5512 lbs 2500 kg 5 9 1 Weight 6579 lbs 2984 kg 5 9 2 Weight 7394 lbs 335...

Page 420: ... 10 18 5 11 CRUISE PERFORMANCE 5 11 1A Maximum cruise 5 11 1A Normal recommended cruise 5 11 9A Long Range cruise 5500 lbs 2495 kg Altitude 24000 ft 5 11 17A Long Range cruise 5500 lbs 2495 kg Altitude 24000 ft 5 11 18A Long Range cruise 6300 lbs 2858 kg Altitude 24000 ft 5 11 19A Long Range cruise 6300 lbs 2858 kg Altitude 24000 ft 5 11 20A Long Range cruise 7100 lbs 3220 kg Altitude 24000 ft 5 1...

Page 421: ... 8 1 Maximum climb power FL 200 5 8 2 Maximum climb power FL 200 5 8 3 Climb at 700 SHP power FL 200 5 8 4 Climb at 700 SHP power FL 200 5 8 5 Maximum cruise power FL 200 5 8 6 Maximum cruise power FL 200 5 8 7 Normal recommended cruise power FL 200 5 8 8 Normal recommended cruise power FL 200 5 8 9 5 9 TAKEOFF DISTANCES 5 9 1 Weight 5512 lbs 2500 kg 5 9 1 Weight 6579 lbs 2984 kg 5 9 2 Weight 7394...

Page 422: ...ORMANCE FLAPS TO 5 10 18 5 11 CRUISE PERFORMANCE 5 11 1 Maximum cruise 5 11 1 Normal recommended cruise 5 11 9 Long Range cruise 5500 lbs 2495 kg Altitude 24000 ft 5 11 17 Long Range cruise 5500 lbs 2495 kg Altitude 24000 ft 5 11 18 Long Range cruise 6300 lbs 2858 kg Altitude 24000 ft 5 11 19 Long Range cruise 6300 lbs 2858 kg Altitude 24000 ft 5 11 20 Long Range cruise 7100 lbs 3220 kg Altitude 2...

Page 423: ...007 Rev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 424: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE EASA Approved Page 5 1 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 425: ...dB A 79 6 dB A ICAO Annex 16 Vol 1 3rd edition Amdt 8 Chapter 10 Appendix 6 85 dB A 79 2 dB A 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 PIM DO NOT USE FO...

Page 426: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE EASA Approved Page 5 2 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 427: ...R DN FLAPS LDG LDG GR DN KIAS KCAS KIAS KCAS KIAS KCAS 125 150 175 200 225 250 266 128 154 179 205 230 255 271 70 80 90 100 120 140 160 69 80 90 101 121 141 162 60 70 80 90 100 110 120 58 68 78 88 98 108 118 MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS 144 173 201 230 259 288 307 147 177 206 236 264 293 312 81 92 104 115 138 161 184 79 92 104 116 139 162 187 69 81 92 104 115 127 138 67 78 90 10...

Page 428: ...0 271 124 149 174 199 224 249 270 70 80 90 100 120 140 160 70 80 90 100 120 139 159 60 70 80 90 100 110 120 59 69 79 90 100 110 120 MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS 144 173 201 230 259 288 312 142 171 200 229 258 287 311 81 92 104 115 138 161 184 81 92 104 115 138 160 183 69 81 92 104 115 127 138 68 79 91 104 115 127 138 Figure 5 3 2 ALTERNATE STATIC SOURCE BLEED AUTO PIM DO NOT USE...

Page 429: ...The curve shows the minimum cabin altitude as a function of flight level corresponding to the maximum differential pressure The maximum differential pressure is limited by the pressurization system protection function Figure 5 4 1 CABIN PRESSURIZATION ENVELOPE 260 240 220 180 140 160 200 280 300 1000 2000 3000 4000 5000 6000 7000 8000 Cabin altitude feet Pressurization useful envelope 9350 ft cabi...

Page 430: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE Page 5 4 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 431: ... 13 12 03 02 07 08 17 18 27 28 6000 17 16 07 06 03 04 13 14 23 24 8000 21 20 11 10 01 00 09 10 19 20 10000 25 24 15 14 05 04 05 06 15 16 12000 29 28 19 18 09 08 01 02 11 12 14000 33 32 23 22 13 12 03 02 07 08 16000 37 36 27 26 17 16 07 06 03 04 18000 41 40 31 30 21 20 11 10 01 00 20000 45 44 35 34 25 24 15 14 05 04 22000 49 48 39 38 29 28 19 18 09 08 24000 53 52 43 42 33 32 23 22 13 12 26000 57 56...

Page 432: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE Page 5 5 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 433: ...73 63 79 75 63 90 84 73 91 87 75 93 89 75 105 100 86 5512 lbs 2500 kg UP DN DN UP TO LDG 70 66 57 71 67 57 81 76 66 75 71 61 76 72 61 86 82 70 82 78 68 84 80 68 94 90 78 98 93 81 100 95 81 113 107 93 6579 lbs 2984 kg UP DN DN UP TO LDG 75 71 61 76 72 61 86 82 70 80 75 66 82 77 66 92 86 76 88 84 73 90 86 73 101 97 84 105 100 86 107 102 86 121 115 99 7394 lbs 3354 kg UP DN DN UP TO LDG 81 77 65 83 7...

Page 434: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE EASA Approved Page 5 6 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 435: ...TING HANDBOOK Page 5 7 1 Edition 1 June 22 2007 Rev 0 5 7 WIND COMPONENTS Figure 5 7 1 WIND COMPONENTS EXAMPLE Angle between wind direction and flight path 50 Headwind 8 kts Crosswind 10 kts Wind speed 13 kts PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 436: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE Page 5 7 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 437: ...e MFD Power up page upon system start The following conditions are given Np 2000 RPM BLEED switch on AUTO The torque must be set at or below the value corresponding to the local conditions of flight level and temperature NOTE Inertial separator must be OFF and BLEED HI msg OFF Example for FL 260 and OAT 22 C the following tables give the maximum torque to be set Maximum climb power TRQ 92 for IAS ...

Page 438: ... 7 POST GARMIN SOFTWARE VERSION 9 14 or ANY LATER 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 439: ...L OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 121 20 120 18 118 16 121 117 14 120 115 12 118 114 10 121 117 112 08 120 115 109 06 118 113 108 04 121 116 111 106 02 119 114 109 104 0 121 117 112 106 101 02 120 115 109 103 97 04 118 112 106 100 95 06 121 115 109 103 97 92 08 121 117 112 106 100 95 89 10 120 114 108 103 97 92 87 12 121 117 111 106 100 94 89 84 14 119 114 108 102 97 91 86 16...

Page 440: ...112 107 102 97 93 88 84 42 121 116 111 106 101 96 92 87 83 40 120 115 110 105 100 95 90 86 82 38 118 113 108 103 98 94 89 85 80 36 121 117 112 107 102 97 92 88 83 79 34 120 115 110 106 101 96 91 87 82 78 32 119 114 109 104 99 95 90 86 81 77 30 121 117 112 107 103 98 93 89 84 80 76 28 120 115 111 106 102 97 92 87 83 79 75 26 119 114 109 105 100 95 91 86 82 77 73 24 118 113 108 103 99 94 89 85 80 76...

Page 441: ... msg ON reduce TRQ by 6 NOTE Add 1 of TRQ for each additional 10 KCAS on climb airspeed This table is not valid if inertial separator and or BLEED HI msg are ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 18 16 14 12 10 08 06 04 02 0 100 02 97 04 100 95 06 97 92 08 100 95 89 10 97 92 87 12 100 94 89 84 14 100 97 91 86 16 99 94 88 18 100 96 91 20 98 93 22 100 95 24 ...

Page 442: ...00 96 91 56 99 94 90 54 98 93 89 52 97 92 88 50 96 91 87 48 100 95 90 86 46 99 94 89 85 44 97 93 88 84 42 96 92 87 83 40 100 95 90 86 82 38 98 94 89 85 80 36 97 92 88 83 79 34 100 96 91 87 82 78 32 99 95 90 86 81 77 30 98 93 89 84 80 76 28 97 92 87 83 79 75 26 100 95 91 86 82 77 73 24 99 94 89 85 80 76 72 22 98 92 88 83 79 74 70 20 100 96 91 87 82 77 72 68 18 99 95 89 85 80 75 71 66 16 98 93 88 83...

Page 443: ...engine power This table is not valid if inertial separator and or BLEED HI msg are ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 18 16 14 12 10 08 06 04 02 121 0 120 02 121 116 04 119 113 06 121 116 110 08 119 113 107 10 121 116 110 104 12 119 113 106 100 14 121 115 109 103 97 16 118 112 106 100 18 121 115 108 103 20 121 118 111 105 22 120 114 108 24 121 117 111 2...

Page 444: ...112 106 101 96 42 121 116 111 105 100 95 40 120 115 110 104 99 93 38 119 114 109 102 97 92 36 118 112 107 101 96 91 34 121 116 111 106 100 95 89 32 120 115 110 105 99 93 88 30 119 114 109 103 97 92 86 28 118 113 108 101 96 90 85 26 117 112 106 100 94 89 84 24 121 116 110 104 98 93 87 82 22 120 114 108 102 96 91 85 80 20 118 112 106 100 95 89 83 78 18 121 116 110 104 99 93 87 81 76 16 120 114 108 1...

Page 445: ...LEED HI msg are ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 24 22 20 18 16 14 12 10 08 121 06 120 04 121 117 02 120 114 0 117 111 02 121 114 108 04 121 117 111 105 06 120 114 108 101 08 121 117 110 104 98 10 120 113 107 101 95 12 121 116 110 104 98 92 14 119 113 106 100 95 89 16 121 115 109 103 97 91 18 121 118 112 106 99 94 20 120 114 108 102 96 22 121 117 111 105 99 24...

Page 446: ...2 42 120 115 110 105 100 95 91 40 118 114 109 104 99 94 89 38 117 113 108 103 97 93 88 36 116 112 106 101 96 92 86 34 115 110 105 100 95 90 85 32 121 114 109 104 99 94 89 84 30 120 113 108 103 98 93 87 82 28 118 112 107 102 97 91 86 81 26 116 111 106 101 95 89 84 79 24 121 115 110 105 99 93 88 82 77 22 119 114 108 103 97 91 86 80 75 20 117 112 107 101 95 89 84 78 73 18 121 115 110 105 99 93 87 81 ...

Page 447: ...d OAT 21 C the following tables give the maximum torque to be set Maximum climb power TRQ 92 for IAS 130 KIAS Add 1 of TRQ for each additional 10 KIAS on climb airspeed cf tables Figures 5 8 1 and 5 8 1A Climb at 700 SHP power TRQ 92 for IAS 130 KIAS Add 1 of TRQ for each additional 10 KIAS on climb airspeed cf tables Figures 5 8 2 and 5 8 2A Maximum cruise power TRQ 106 cf tables Figures 5 8 3 an...

Page 448: ...0 110 120 130 140 150 160 170 180 190 200 23 21 121 19 120 17 118 15 121 117 13 120 115 11 118 114 09 121 117 112 07 120 115 109 05 118 113 108 03 121 116 111 106 01 119 114 109 104 01 121 117 112 106 101 03 120 115 109 103 97 05 118 112 106 100 95 07 121 115 109 103 97 92 09 121 117 112 106 100 95 89 11 120 114 108 103 97 92 87 13 121 117 111 106 100 94 89 84 15 119 114 108 102 97 91 86 17 121 11...

Page 449: ...102 97 93 88 84 41 121 116 111 106 101 96 92 87 83 39 120 115 110 105 100 95 90 86 82 37 118 113 108 103 98 94 89 85 80 35 121 117 112 107 102 97 92 88 83 79 33 120 115 110 106 101 96 91 87 82 78 31 119 114 109 104 99 95 90 86 81 77 29 121 117 112 107 103 98 93 89 84 80 76 27 120 115 111 106 102 97 92 87 83 79 75 25 119 114 109 105 100 95 91 86 82 77 73 23 118 113 108 103 99 94 89 85 80 76 72 21 1...

Page 450: ...reduce TRQ by 6 NOTE Add 1 of TRQ for each additional 10 KCAS on climb airspeed This table is not valid if inertial separator and or BLEED HI msg are ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 23 21 19 17 15 13 11 09 07 05 03 01 01 100 03 97 05 100 95 07 97 92 09 100 95 89 11 97 92 87 13 100 94 89 84 15 100 97 91 86 17 99 94 88 19 100 96 91 21 98 93 23 100 95 25 100 97 ...

Page 451: ... 55 99 94 90 53 98 93 89 51 97 92 88 49 96 91 87 47 100 95 90 86 45 99 94 89 85 43 97 93 88 84 41 96 92 87 83 39 100 95 90 86 82 37 98 94 89 85 80 35 97 92 88 83 79 33 100 96 91 87 82 78 31 99 95 90 86 81 77 29 98 93 89 84 80 76 27 97 92 87 83 79 75 25 100 95 91 86 82 77 73 23 99 94 89 85 80 76 72 21 98 92 88 83 79 74 70 19 100 96 91 87 82 77 72 68 17 99 95 89 85 80 75 71 66 15 98 93 88 83 78 73 6...

Page 452: ...ower This table is not valid if inertial separator and or BLEED HI msg are ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 23 21 19 17 15 13 11 09 07 05 03 01 121 02 120 03 121 117 05 120 114 07 121 117 111 09 120 114 107 11 121 117 110 104 13 119 113 107 101 15 121 115 110 104 97 17 118 112 106 100 19 121 115 108 103 21 121 118 111 105 23 120 114 108 25 121 117 111 27 119 1...

Page 453: ...6 101 97 41 121 116 111 105 100 96 39 120 115 110 104 99 95 37 119 114 109 102 98 94 35 118 112 107 101 97 93 33 121 116 111 106 100 96 91 31 120 115 110 105 99 95 90 29 119 114 109 103 98 94 89 27 118 113 108 101 97 93 87 25 117 112 106 100 95 92 86 23 121 116 110 104 99 94 90 84 21 120 114 108 102 97 92 88 83 19 118 112 106 100 96 91 86 81 17 121 116 110 104 99 95 89 84 79 15 120 114 108 102 98 ...

Page 454: ...msg are ON T C FLIGHT LEVEL FL OAT 100 110 120 130 140 150 160 170 180 190 200 23 21 19 17 15 13 11 09 07 121 05 120 03 121 117 01 120 114 01 117 111 03 121 114 108 05 121 118 111 105 07 120 114 108 101 09 121 117 110 104 98 11 120 113 107 101 95 13 121 116 110 104 98 92 15 119 113 106 100 95 89 17 121 115 109 103 97 91 19 121 118 112 106 99 94 21 120 114 108 102 96 23 121 117 111 105 99 25 119 11...

Page 455: ...1 120 115 110 105 100 95 91 39 118 114 109 104 99 94 90 37 117 113 108 103 97 93 89 35 116 112 106 101 96 92 88 33 115 110 105 100 95 91 87 31 121 114 109 104 99 94 90 86 29 120 113 108 103 98 93 89 85 27 118 112 107 102 97 92 88 83 25 116 111 106 101 96 91 87 81 23 121 115 110 105 100 95 89 85 80 21 119 114 108 103 98 94 87 83 78 19 117 112 107 101 95 91 86 81 76 17 121 115 110 105 99 94 89 84 78...

Page 456: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE Page 5 8 10 Edition 1 June 22 2007 Rev 7 PRE GARMIN SOFTWARE VERSION 9 14 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 457: ...17 1132 1280 1444 1657 1591 1772 1968 2215 2510 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1083 1214 1363 1575 1804 1690 1870 2100 2379 2707 1148 1296 1476 1690 1968 1788 1985 2247 2559 2920 1214 1378 1575 1837 2100 1903 2133 2411 2756 3133 1247 1444 1640 1919 2198 1969 2231 2526 2887 3281 Figure 5 9 1 TAKEOFF DISTANCES 5512 lbs 2500 ...

Page 458: ...1739 1968 2231 2133 2362 2625 2920 3281 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1476 1673 1870 2100 2428 2264 2493 2789 3117 3543 1575 1772 2001 2297 2657 2395 2657 2953 3346 3839 1690 1903 2149 2461 2854 2559 2854 3182 3609 4134 1755 1969 2231 2543 2969 2657 2953 3314 3740 4298 Figure 5 9 2 TAKEOFF DISTANCES 6579 lbs 2984 kg Corre...

Page 459: ... 2545 2890 3315 2840 3150 3510 3955 4445 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 2165 2445 2740 3135 3560 3020 3365 3760 4235 4760 2315 2595 2955 3380 3855 3200 3580 4035 4530 5105 2480 2780 3185 3625 4170 3415 3805 4300 4825 5450 2560 2920 3330 3805 4380 3530 3990 4480 5055 5710 Figure 5 9 3 TAKEOFF DISTANCES 7394 lbs 3354 kg Corr...

Page 460: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE EASA Approved Page 5 9 4 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 461: ... 8000 3050 3025 2995 2960 2930 2915 2890 2860 2820 2790 2800 2765 2735 2695 2655 2685 2655 2615 2575 2535 2580 2545 2505 2465 2425 2480 2445 2405 2360 2320 6594 lbs 2991 kg SL 2000 4000 6000 8000 2585 2560 2530 2500 2465 2470 2445 2415 2380 2345 2365 2335 2305 2265 2230 2270 2240 2205 2165 2125 2175 2145 2110 2070 2035 2090 2055 2020 1980 1945 7394 lbs 3354 kg SL 2000 4000 6000 8000 2195 2170 2140...

Page 462: ...0 6000 8000 2850 2815 2770 2725 2680 2720 2680 2635 2590 2540 2600 2560 2510 2460 2405 2490 2445 2395 2340 2290 2385 2335 2285 2230 2180 2285 2235 2180 2130 2080 6594 lbs 2991 kg SL 2000 4000 6000 8000 2430 2395 2355 2315 2270 2320 2280 2240 2195 2150 2215 2175 2130 2085 2035 2115 2075 2030 1980 1935 2025 1985 1935 1885 1840 1940 1895 1845 1800 1755 7394 lbs 3354 kg SL 2000 4000 6000 8000 2080 204...

Page 463: ...45 2420 2390 2360 2330 2335 2310 2280 2245 2215 2235 2210 2175 2145 2110 2145 2115 2085 2050 2015 2060 2030 1995 1960 1925 1980 1945 1910 1875 1845 6594 lbs 2991 kg SL 2000 4000 6000 8000 2050 2025 1995 1970 1935 1955 1925 1900 1870 1840 1875 1840 1815 1780 1745 1795 1765 1735 1700 1665 1720 1690 1660 1625 1590 1640 1620 1585 1555 1520 7394 lbs 3354 kg SL 2000 4000 6000 8000 1725 1700 1670 1640 16...

Page 464: ...4000 6000 8000 2160 2120 2075 2035 1995 2055 2010 1970 1925 1880 1955 1915 1875 1830 1785 1865 1825 1780 1735 1690 1785 1740 1695 1650 1605 1705 1665 1620 1570 1515 6594 lbs 2991 kg SL 2000 4000 6000 8000 1820 1780 1740 1700 1660 1730 1690 1650 1610 1570 1650 1600 1560 1520 1480 1570 1530 1490 1450 1400 1490 1460 1410 1370 1330 1415 1380 1345 1305 1255 7394 lbs 3354 kg SL 2000 4000 6000 8000 1540 ...

Page 465: ... 2 3 01 45 10 8 2 6 4 6000 02 00 10 8 2 8 4 02 30 12 10 3 3 5 02 45 15 11 3 9 6 8000 02 45 14 11 3 6 6 03 15 16 13 4 3 7 03 45 19 15 5 1 8 10000 03 15 17 13 4 5 7 04 00 20 16 5 3 9 04 45 24 19 6 3 10 12000 04 00 20 16 5 4 9 04 45 24 19 6 4 11 05 45 29 22 7 5 13 14000 04 45 24 19 6 2 11 05 45 28 22 7 4 13 06 45 33 26 8 8 15 16000 05 30 27 21 7 1 13 06 30 32 25 8 4 15 07 45 38 30 10 0 18 18000 06 15...

Page 466: ...01 30 8 6 2 1 3 01 45 9 7 2 5 4 02 00 11 9 2 9 4 6000 02 15 12 9 3 1 5 02 30 14 11 3 7 6 03 00 16 13 4 3 7 8000 03 00 15 12 4 1 7 03 30 18 14 4 8 8 04 00 22 17 5 7 9 10000 03 45 19 15 5 1 8 04 30 23 18 6 0 10 05 15 27 21 7 1 12 12000 04 30 23 18 6 0 10 05 15 27 21 7 2 12 06 15 32 25 8 5 15 14000 05 15 26 21 7 0 12 06 15 31 25 8 3 15 07 30 37 29 9 9 18 16000 06 00 30 24 8 0 15 07 15 36 28 9 5 17 08...

Page 467: ... 9 7 2 3 4 02 00 10 8 2 7 4 02 15 12 10 3 2 5 6000 02 30 13 10 3 4 5 02 45 15 12 4 1 7 03 15 18 14 4 8 8 8000 03 15 17 13 4 5 7 03 45 20 16 5 4 9 04 30 24 19 6 4 11 10000 04 00 21 17 5 6 10 04 45 25 20 6 7 11 05 45 30 24 8 0 14 12000 04 45 25 20 6 7 12 05 45 30 24 8 0 14 07 00 36 28 9 5 17 14000 05 45 30 23 7 8 14 06 45 35 28 9 3 17 08 15 42 33 11 1 20 16000 06 30 34 26 8 9 17 08 00 40 32 10 6 20 ...

Page 468: ...0 4 01 45 9 7 2 3 4 02 00 10 8 2 7 5 6000 02 15 11 9 3 0 6 02 30 13 10 3 5 7 03 00 15 12 4 1 8 8000 03 00 15 12 3 9 8 03 30 17 14 4 6 9 04 00 20 16 5 4 11 10000 03 45 18 15 4 9 10 04 15 22 17 5 7 12 05 00 26 20 6 7 14 12000 04 30 22 17 5 8 12 05 15 26 20 6 9 14 06 00 31 24 8 1 17 14000 05 15 26 20 6 8 15 06 15 30 24 8 0 17 07 15 36 28 9 4 20 16000 06 00 29 23 7 7 17 07 00 35 27 9 1 20 08 15 41 32 ...

Page 469: ... 5 1 6 3 4000 01 45 8 7 2 2 4 01 45 10 8 2 6 5 02 15 12 9 3 1 6 6000 02 30 13 10 3 3 7 02 45 15 12 3 9 8 03 15 17 14 4 6 9 8000 03 15 17 13 4 4 9 03 45 20 16 5 2 11 04 30 23 18 6 1 12 10000 04 00 21 16 5 5 11 04 45 25 19 6 5 14 05 45 29 23 7 6 16 12000 05 00 25 20 6 6 14 05 45 29 23 7 8 17 06 45 35 27 9 2 20 14000 05 45 29 23 7 7 17 06 45 34 27 9 1 20 08 00 40 32 10 7 24 16000 06 45 33 26 8 8 20 0...

Page 470: ...7 3 4000 01 45 9 7 2 5 5 02 00 11 9 3 0 6 02 30 13 10 3 5 7 6000 02 45 14 11 3 7 7 03 00 17 13 4 4 9 03 45 20 15 5 2 10 8000 03 30 19 15 5 0 10 04 00 22 17 5 9 12 05 00 26 21 6 9 14 10000 04 30 23 18 6 2 13 05 15 28 22 7 3 15 06 15 33 26 8 6 18 12000 05 30 28 22 7 4 16 06 15 33 26 8 7 19 07 30 39 31 10 3 23 14000 06 15 33 26 8 6 19 07 30 39 30 10 2 23 09 00 46 36 12 1 27 16000 07 15 37 29 9 9 23 0...

Page 471: ...2 15 11 9 3 0 5 6000 02 30 12 9 3 1 5 03 00 14 11 3 7 6 03 30 17 13 4 4 8 8000 03 15 15 12 4 1 7 04 00 18 14 4 9 9 04 45 22 17 5 8 10 10000 04 15 19 15 5 0 9 05 00 23 18 6 0 11 06 00 27 21 7 2 13 12000 05 15 23 18 6 0 11 06 00 27 21 7 2 14 07 15 33 26 8 6 17 14000 06 00 26 21 6 9 14 07 15 31 25 8 3 16 08 45 38 30 10 0 20 16000 06 45 30 23 7 9 16 08 15 36 28 9 5 19 10 00 43 34 11 4 23 18000 07 45 3...

Page 472: ...9 7 2 3 4 02 15 11 8 2 8 5 02 30 13 10 3 4 6 6000 02 45 13 10 3 5 6 03 15 16 12 4 1 7 04 00 19 15 5 0 9 8000 03 45 17 14 4 6 8 04 30 21 16 5 5 10 05 20 25 20 6 6 12 10000 04 45 21 17 5 7 11 05 30 26 20 6 8 13 06 40 31 24 8 2 15 12000 05 45 25 20 6 7 13 06 45 31 24 8 1 16 08 00 37 29 9 7 19 14000 06 30 30 23 7 8 16 08 00 36 28 9 4 19 09 30 43 34 11 3 23 16000 07 30 34 26 8 9 18 09 00 40 32 10 7 22 ...

Page 473: ... 2 6 4 02 15 12 9 3 1 5 02 45 14 11 3 8 7 6000 03 00 15 11 3 9 7 03 30 18 14 4 6 8 04 15 21 17 5 6 10 8000 04 00 19 15 5 1 9 04 45 23 18 6 1 11 05 45 28 22 7 4 14 10000 05 00 24 19 6 3 12 06 00 29 23 7 6 15 07 15 35 27 9 2 18 12000 06 00 28 22 7 5 15 07 30 34 27 9 1 18 09 00 42 33 11 0 22 14000 07 15 33 26 8 7 18 08 45 40 31 10 5 21 10 30 48 38 12 8 26 16000 08 15 38 30 9 9 21 10 00 45 36 12 0 25 ...

Page 474: ...5 11 8 2 8 6 02 30 13 10 3 3 7 6000 02 45 13 11 3 5 8 03 30 16 12 4 2 9 04 00 19 15 5 0 11 8000 03 45 18 14 4 7 10 04 30 21 17 5 6 12 05 20 25 20 6 6 15 10000 04 45 22 17 5 8 13 05 45 26 21 6 9 16 07 00 31 24 8 2 19 12000 06 00 26 21 6 9 16 07 00 31 25 8 3 20 08 30 37 29 9 9 23 14000 07 00 31 24 8 1 20 08 15 36 29 9 6 24 10 00 43 34 11 5 28 16000 08 00 35 27 9 2 23 09 30 42 33 11 0 28 11 30 50 39 ...

Page 475: ...4 4000 02 00 10 8 2 7 6 02 30 12 10 3 2 7 03 00 14 11 3 8 8 6000 03 15 15 12 4 0 9 03 45 18 14 4 8 10 04 30 22 17 5 7 12 8000 04 15 20 16 5 3 12 05 00 24 19 6 3 14 06 00 29 22 7 6 17 10000 05 30 25 20 6 6 15 06 30 30 23 7 9 18 07 45 36 28 9 4 22 12000 06 30 30 23 7 9 19 08 00 36 28 9 4 23 09 30 43 34 11 3 27 14000 07 45 35 27 9 2 23 09 15 42 33 11 0 27 11 00 50 39 13 2 33 16000 09 00 40 31 10 5 27...

Page 476: ...02 15 11 9 3 0 6 02 45 14 11 3 6 8 03 15 16 13 4 3 9 6000 03 30 17 13 4 5 10 04 15 20 16 5 4 12 05 00 24 19 6 4 14 8000 04 45 23 18 6 0 14 05 30 27 21 7 2 16 06 45 32 25 8 6 20 10000 06 00 28 22 7 4 18 07 15 34 27 8 9 21 08 30 41 32 10 7 25 12000 07 15 34 27 8 9 22 08 45 40 32 10 7 26 10 30 49 38 12 9 32 14000 08 30 39 31 10 4 26 10 15 47 37 12 5 32 12 30 57 45 15 1 38 16000 10 00 45 35 11 9 31 12...

Page 477: ...1265 1230 1190 1145 1230 1195 1155 1115 1070 1165 1130 1090 1050 1000 1105 1065 1025 985 940 1045 1010 970 925 880 985 955 915 870 825 Conditions 700 SHP climb power Landing gear DN and flaps LDG IAS 95 KIAS Airplane weight Pressure altitude feet RATE OF CLIMB ft min ISA 35 C ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 7394 lbs 3354 kg SL 2000 4000 6000 8000 1120 1085 1045 1010 965 1025 985 9...

Page 478: ...1910 1880 1860 1830 1805 1830 1800 1775 1750 1720 1750 1720 1700 1670 1640 1680 1650 1620 1595 1565 1600 1585 1555 1525 1495 Conditions 700 SHP climb power Landing gear UP and flaps TO IAS 115 KIAS Airplane weight Pressure altitude feet RATE OF CLIMB ft min ISA 35 C ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 7394 lbs 3354 kg SL 2000 4000 6000 8000 1825 1800 1775 1750 1720 1695 1670 1640 1620...

Page 479: ...850 PILOT S OPERATING HANDBOOK Page 5 11 1A Edition 1 June 22 2007 Rev 7 POST GARMIN SOFTWARE VERSION 9 14 or ANY LATER 5 11 CRUISE PERFORMANCE Figure 5 11 1 CRUISE PERFORMANCE Maximum cruise PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 480: ...36 265 234 264 233 262 15000 34 121 270 212 71 4 230 280 229 278 227 276 18000 40 121 262 205 69 1 227 289 226 287 224 285 20000 44 121 256 201 67 7 225 295 224 293 222 291 21000 46 121 254 200 67 2 224 298 222 296 221 294 22000 48 121 252 198 66 7 223 302 221 299 219 297 23000 50 121 251 197 66 2 222 305 220 303 218 300 24000 52 121 249 196 65 9 221 308 219 306 217 303 25000 54 121 248 195 65 6 2...

Page 481: ...34 269 232 267 231 265 15000 24 121 273 214 72 1 229 283 227 281 225 279 18000 30 121 264 207 69 8 225 292 224 290 222 288 20000 34 121 259 203 68 4 223 299 221 297 219 294 21000 36 121 257 201 67 8 222 302 220 300 218 297 22000 38 121 255 200 67 3 221 305 219 303 217 300 23000 40 121 253 198 66 8 220 309 218 306 216 304 24000 42 121 252 198 66 5 219 312 217 310 215 307 25000 44 121 251 197 66 2 2...

Page 482: ...233 270 232 269 230 267 15000 19 121 274 215 72 5 228 285 226 283 224 281 18000 25 121 265 208 70 1 224 294 223 292 221 290 20000 29 121 260 204 68 7 222 301 220 298 218 296 21000 31 121 258 203 68 2 221 304 219 302 217 299 22000 33 121 256 201 67 6 220 307 218 305 216 302 23000 35 121 254 200 67 2 219 311 217 308 215 305 24000 37 121 253 198 66 8 217 314 216 312 213 309 25000 39 121 252 198 66 5 ...

Page 483: ...232 272 231 270 229 269 15000 14 121 276 216 72 8 227 287 225 285 223 283 18000 20 121 267 209 70 5 223 296 222 294 220 291 20000 24 121 261 205 69 0 221 302 219 300 217 298 21000 26 121 259 203 68 4 220 306 218 303 216 301 22000 28 121 257 202 68 0 219 309 217 307 215 304 23000 30 121 256 201 67 5 218 312 216 310 214 307 24000 32 121 254 199 67 1 216 316 215 313 212 310 25000 34 121 253 198 66 8 ...

Page 484: ... 231 273 230 272 228 270 15000 09 121 277 218 73 2 226 288 224 286 222 284 18000 15 121 268 210 70 8 222 297 221 295 219 293 20000 19 121 263 206 69 4 220 304 218 302 216 299 21000 21 121 260 204 68 8 219 307 217 305 215 302 22000 23 121 259 203 68 3 218 311 216 308 214 305 23000 25 121 257 201 67 8 216 314 215 312 213 309 24000 27 121 255 200 67 4 215 317 213 316 211 313 25000 29 119 254 199 67 1...

Page 485: ... 230 275 229 273 227 272 15000 04 121 279 219 73 6 225 290 223 288 221 286 18000 10 121 269 211 71 1 221 299 220 297 218 295 20000 14 121 264 207 69 7 219 306 217 304 215 301 21000 16 121 262 205 69 1 218 309 216 307 214 304 22000 18 121 260 204 68 6 217 312 215 310 213 307 23000 20 121 258 202 68 1 215 316 214 313 212 310 24000 22 120 256 201 67 7 214 319 212 317 210 314 25000 24 116 249 196 65 9...

Page 486: ...6 229 278 227 276 226 274 15000 06 121 281 221 74 3 223 293 221 291 220 289 18000 00 121 272 213 71 8 220 302 218 300 216 298 20000 04 121 266 209 70 4 217 309 215 307 213 304 21000 06 120 264 207 69 8 216 312 214 310 212 307 22000 08 117 257 202 67 9 213 313 211 310 208 307 23000 10 114 249 195 65 7 209 313 207 310 204 306 24000 12 110 241 189 63 6 205 313 203 310 200 305 25000 14 106 233 183 61 ...

Page 487: ...MANCE TBM 850 PILOT S OPERATING HANDBOOK Page 5 11 9A Edition 1 June 22 2007 Rev 7 POST GARMIN SOFTWARE VERSION 9 14 or ANY LATER Figure 5 11 9 CRUISE PERFORMANCE Recommended cruise PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 488: ...1 74 5 236 265 234 264 233 262 15000 34 121 270 212 71 4 230 280 229 278 227 276 18000 40 121 262 205 69 1 227 289 226 287 224 285 20000 44 121 256 201 67 7 225 295 224 293 222 291 21000 46 121 254 200 67 2 224 298 222 296 221 294 22000 48 121 252 198 66 7 223 302 221 299 219 297 23000 50 121 251 197 66 2 222 305 220 303 218 300 24000 52 121 249 196 65 9 221 308 219 306 217 303 25000 54 121 248 19...

Page 489: ...3 75 2 234 269 232 267 231 265 15000 24 121 273 214 72 1 229 283 227 281 225 279 18000 30 121 264 207 69 8 225 292 224 290 222 288 20000 34 121 259 203 68 4 223 299 221 297 219 294 21000 36 121 257 201 67 8 222 302 220 300 218 297 22000 38 121 255 200 67 3 221 305 219 303 217 300 23000 40 121 253 198 66 8 220 309 218 306 216 304 24000 42 121 252 198 66 5 219 312 217 310 215 307 25000 44 121 251 19...

Page 490: ...25 75 6 233 270 232 269 230 267 15000 19 121 274 215 72 5 228 285 226 283 224 281 18000 25 121 265 208 70 1 224 294 223 292 221 290 20000 29 121 260 204 68 7 222 301 220 298 218 296 21000 31 121 258 203 68 2 221 304 219 302 217 299 22000 33 121 256 201 67 6 220 307 218 305 216 302 23000 35 121 254 200 67 2 219 311 217 308 215 305 24000 37 121 253 198 66 8 217 314 216 312 213 309 25000 39 118 252 1...

Page 491: ...26 76 0 232 272 231 270 229 269 15000 14 121 276 216 72 8 227 287 225 285 223 283 18000 20 121 267 209 70 5 223 296 222 294 220 291 20000 24 121 261 205 69 0 221 302 219 300 217 298 21000 26 121 259 203 68 4 220 306 218 303 216 301 22000 28 121 257 202 68 0 219 309 217 307 215 304 23000 30 121 256 201 67 5 218 312 216 310 214 307 24000 32 121 254 199 67 1 216 316 215 313 212 310 25000 34 115 252 1...

Page 492: ...27 76 4 231 273 230 272 228 270 15000 09 121 277 218 73 2 226 288 224 286 222 284 18000 15 121 268 210 70 8 222 297 221 295 219 293 20000 19 121 263 206 69 4 220 304 218 302 216 299 21000 21 121 260 204 68 8 219 307 217 305 215 302 22000 23 121 259 203 68 3 218 311 216 308 214 305 23000 25 121 257 201 67 8 216 314 215 312 213 309 24000 27 117 253 199 66 9 215 317 213 315 210 311 25000 29 113 245 1...

Page 493: ...228 76 8 230 275 229 273 227 272 15000 04 121 279 219 73 6 225 290 223 288 221 286 18000 10 121 269 211 71 1 221 299 220 297 218 295 20000 14 121 264 207 69 7 219 306 217 304 215 301 21000 16 121 262 205 69 1 218 309 216 307 214 304 22000 18 121 260 204 68 6 217 312 215 310 213 307 23000 20 117 254 200 67 2 214 314 212 311 210 308 24000 22 114 246 193 65 1 211 314 208 311 206 307 25000 24 110 239 ...

Page 494: ... 231 77 6 229 278 227 276 226 274 15000 06 121 281 221 74 3 223 293 221 291 220 289 18000 00 121 272 213 71 8 220 302 218 300 216 298 20000 04 117 259 203 68 4 214 305 212 302 210 299 21000 06 114 251 197 66 4 211 305 209 302 207 299 22000 08 111 244 191 64 4 207 306 205 303 203 299 23000 10 108 237 186 62 5 204 306 202 303 199 299 24000 12 104 229 180 60 5 201 306 198 302 196 298 25000 14 101 222...

Page 495: ...149 197 34 38 7 115 147 199 24 39 1 116 146 201 14 39 6 118 144 203 4 40 1 119 143 205 21000 45 46 37 4 111 148 198 36 37 9 112 146 201 26 38 4 114 145 203 16 38 8 115 143 205 6 39 3 117 142 207 22000 45 48 36 7 109 147 200 38 37 1 110 145 202 28 37 5 112 144 205 18 38 1 113 142 207 8 38 6 115 140 208 23000 45 50 35 9 107 146 202 40 36 4 108 144 205 30 36 8 109 142 206 20 37 3 111 141 208 10 37 8 ...

Page 496: ...9 155 230 48 37 3 111 153 232 38 37 8 112 152 235 28 38 2 114 150 237 18 38 8 115 148 240 28000 55 5 60 36 9 110 156 235 50 37 4 111 154 238 40 37 9 113 153 241 30 38 3 114 151 243 20 38 8 115 149 245 29000 56 62 36 6 109 156 238 52 37 1 110 154 241 42 37 5 111 152 244 32 38 0 113 150 246 22 38 5 114 148 248 30000 56 5 64 36 4 108 155 242 54 36 9 110 154 245 44 37 3 111 152 247 34 37 8 112 150 250...

Page 497: ...152 201 34 40 8 121 150 203 24 41 2 122 149 205 14 41 7 124 147 206 4 42 2 125 145 208 21000 50 46 39 4 117 151 202 36 39 9 119 149 204 26 40 5 120 147 206 16 40 9 121 145 208 6 41 4 123 143 209 22000 50 48 38 7 115 149 204 38 39 1 116 148 206 28 39 6 118 146 208 18 40 1 119 144 209 8 40 6 121 142 210 23000 50 50 38 0 113 148 206 40 38 4 114 146 207 30 38 9 116 144 209 20 39 3 117 142 210 10 39 8 ...

Page 498: ...15 157 232 48 39 1 116 155 234 38 39 6 118 153 236 28 40 1 119 151 238 18 40 6 121 148 240 28000 60 5 60 39 0 116 158 238 50 39 5 117 156 241 40 40 0 119 154 243 30 40 5 120 152 244 20 41 0 122 150 246 29000 61 62 38 7 115 157 241 52 39 1 116 155 243 42 39 7 118 153 245 32 40 1 119 151 247 22 40 7 121 149 249 30000 61 5 64 38 5 114 157 244 54 39 0 116 155 247 44 39 4 117 153 249 34 39 9 119 150 25...

Page 499: ...154 203 34 42 7 127 152 205 24 43 3 129 150 206 14 43 8 130 148 208 4 44 3 132 146 209 21000 55 46 41 5 123 153 205 36 41 9 125 150 206 26 42 4 126 148 208 16 43 0 128 146 209 6 43 5 129 144 210 22000 55 48 40 8 121 151 206 38 41 2 122 149 208 28 41 7 124 147 209 18 42 1 125 145 211 8 42 6 127 143 212 23000 55 50 40 0 119 150 208 40 40 6 121 147 209 30 41 0 122 145 211 20 41 5 123 143 212 10 41 9 ...

Page 500: ...21 158 234 48 41 2 122 155 235 38 41 7 124 153 237 28 42 3 126 151 239 18 42 8 127 149 240 28000 65 5 60 41 1 122 159 240 50 41 6 124 157 241 40 42 0 125 154 243 30 42 6 127 152 245 20 43 1 128 150 246 29000 66 62 40 8 121 158 242 52 41 3 123 156 244 42 41 8 124 153 246 32 42 2 125 151 248 22 42 8 127 149 249 30000 66 5 64 40 6 121 158 245 54 41 1 122 155 247 44 41 6 124 153 249 34 42 1 125 150 25...

Page 501: ...CE TBM 850 PILOT S OPERATING HANDBOOK Page 5 11 1 Edition 1 June 22 2007 Rev 7 PRE GARMIN SOFTWARE VERSION 9 14 5 11 CRUISE PERFORMANCE Figure 5 11 1 CRUISE PERFORMANCE Maximum cruise PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 502: ...234 264 233 262 15000 33 121 270 212 71 4 230 280 229 278 227 276 18000 39 121 262 205 69 1 227 289 226 287 224 285 20000 43 121 256 201 67 7 225 295 224 293 222 291 21000 45 121 254 200 67 2 224 298 222 296 221 294 22000 46 121 252 198 66 7 223 302 221 299 219 297 23000 48 121 251 197 66 2 222 305 220 303 218 300 24000 50 121 249 196 65 9 221 308 219 306 217 303 25000 52 121 248 195 65 6 220 312 ...

Page 503: ...232 267 231 265 15000 23 121 273 214 72 1 229 283 227 281 225 279 18000 29 121 264 207 69 8 225 292 224 290 222 288 20000 33 121 259 203 68 4 223 299 221 297 219 294 21000 35 121 257 201 67 8 222 302 220 300 218 297 22000 36 121 255 200 67 3 221 305 219 303 217 300 23000 38 121 253 198 66 8 220 309 218 306 216 304 24000 40 121 252 198 66 5 219 312 217 310 215 307 25000 42 121 251 197 66 2 217 316 ...

Page 504: ...232 269 230 267 15000 18 121 274 215 72 5 228 285 226 283 224 281 18000 24 121 265 208 70 1 224 294 223 292 221 290 20000 28 121 260 204 68 7 222 301 220 298 218 296 21000 30 121 258 203 68 2 221 304 219 302 217 299 22000 31 121 256 201 67 6 220 307 218 305 216 302 23000 33 121 254 200 67 2 219 311 217 308 215 305 24000 35 121 253 198 66 8 217 314 216 312 213 309 25000 37 121 252 198 66 5 216 317 ...

Page 505: ... 231 270 229 269 15000 13 121 276 216 72 8 227 287 225 285 223 283 18000 19 121 267 209 70 5 223 296 222 294 220 291 20000 23 121 261 205 69 0 221 302 219 300 217 298 21000 25 121 259 203 68 4 220 306 218 303 216 301 22000 26 121 257 202 68 0 219 309 217 307 215 304 23000 28 121 256 201 67 5 218 312 216 310 214 307 24000 30 121 254 199 67 1 216 316 215 313 212 310 25000 32 120 253 198 66 8 215 319...

Page 506: ... 230 272 228 270 15000 08 121 277 218 73 2 226 288 224 286 222 284 18000 14 121 268 210 70 8 222 297 221 295 219 293 20000 18 121 263 206 69 4 220 304 218 302 216 299 21000 20 121 260 204 68 8 219 307 217 305 215 302 22000 21 121 259 203 68 3 218 311 216 308 214 305 23000 23 121 257 201 67 8 216 314 215 312 213 309 24000 25 121 255 200 67 4 215 317 213 316 211 313 25000 27 118 254 199 67 1 214 321...

Page 507: ...5 229 273 227 272 15000 03 121 279 219 73 6 225 290 223 288 221 286 18000 09 121 269 211 71 1 221 299 220 297 218 295 20000 13 121 264 207 69 7 219 306 217 304 215 301 21000 15 121 262 205 69 1 218 309 216 307 214 304 22000 16 121 260 204 68 6 217 312 215 310 213 307 23000 18 121 258 202 68 1 215 316 214 313 212 310 24000 20 119 256 201 67 7 214 319 212 317 210 314 25000 22 115 249 196 65 9 211 32...

Page 508: ...78 227 276 226 274 15000 07 121 281 221 74 3 223 293 221 291 220 289 18000 01 121 272 213 71 8 220 302 218 300 216 298 20000 03 121 266 209 70 4 217 309 215 307 213 304 21000 05 120 264 207 69 8 216 312 214 310 212 307 22000 06 117 257 202 67 9 213 313 211 310 208 307 23000 08 113 249 195 65 7 209 313 207 310 204 306 24000 10 109 241 189 63 6 205 313 203 310 200 305 25000 12 106 233 183 61 5 202 3...

Page 509: ... PERFORMANCE TBM 850 PILOT S OPERATING HANDBOOK Page 5 11 9 Edition 1 June 22 2007 Rev 7 PRE GARMIN SOFTWARE VERSION 9 14 Figure 5 11 9 CRUISE PERFORMANCE Recommended cruise PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 510: ...36 265 234 264 233 262 15000 33 121 270 212 71 4 230 280 229 278 227 276 18000 39 121 262 205 69 1 227 289 226 287 224 285 20000 43 121 256 201 67 7 225 295 224 293 222 291 21000 45 121 254 200 67 2 224 298 222 296 221 294 22000 46 121 252 198 66 7 223 302 221 299 219 297 23000 48 121 251 197 66 2 222 305 220 303 218 300 24000 50 121 249 196 65 9 221 308 219 306 217 303 25000 52 121 248 195 65 6 2...

Page 511: ...234 269 232 267 231 265 15000 23 121 273 214 72 1 229 283 227 281 225 279 18000 29 121 264 207 69 8 225 292 224 290 222 288 20000 33 121 259 203 68 4 223 299 221 297 219 294 21000 35 121 257 201 67 8 222 302 220 300 218 297 22000 36 121 255 200 67 3 221 305 219 303 217 300 23000 38 121 253 198 66 8 220 309 218 306 216 304 24000 40 121 252 198 66 5 219 312 217 310 215 307 25000 42 120 251 197 66 2 ...

Page 512: ...233 270 232 269 230 267 15000 18 121 274 215 72 5 228 285 226 283 224 281 18000 24 121 265 208 70 1 224 294 223 292 221 290 20000 28 121 260 204 68 7 222 301 220 298 218 296 21000 30 121 258 203 68 2 221 304 219 302 217 299 22000 31 121 256 201 67 6 220 307 218 305 216 302 23000 33 121 254 200 67 2 219 311 217 308 215 305 24000 35 121 253 198 66 8 217 314 216 312 213 309 25000 37 117 252 198 66 5 ...

Page 513: ... 232 272 231 270 229 269 15000 13 121 276 216 72 8 227 287 225 285 223 283 18000 19 121 267 209 70 5 223 296 222 294 220 291 20000 23 121 261 205 69 0 221 302 219 300 217 298 21000 25 121 259 203 68 4 220 306 218 303 216 301 22000 26 121 257 202 68 0 219 309 217 307 215 304 23000 28 121 256 201 67 5 218 312 216 310 214 307 24000 30 121 254 199 67 1 216 316 215 313 212 310 25000 32 114 252 198 66 5...

Page 514: ... 231 273 230 272 228 270 15000 08 121 277 218 73 2 226 288 224 286 222 284 18000 14 121 268 210 70 8 222 297 221 295 219 293 20000 18 121 263 206 69 4 220 304 218 302 216 299 21000 20 121 260 204 68 8 219 307 217 305 215 302 22000 21 121 259 203 68 3 218 311 216 308 214 305 23000 23 121 257 201 67 8 216 314 215 312 213 309 24000 25 116 253 199 66 9 215 317 213 315 210 311 25000 27 112 245 193 64 8...

Page 515: ... 230 275 229 273 227 272 15000 03 121 279 219 73 6 225 290 223 288 221 286 18000 09 121 269 211 71 1 221 299 220 297 218 295 20000 13 121 264 207 69 7 219 306 217 304 215 301 21000 15 121 262 205 69 1 218 309 216 307 214 304 22000 16 121 260 204 68 6 217 312 215 310 213 307 23000 18 116 254 200 67 2 214 314 212 311 210 308 24000 20 113 246 193 65 1 211 314 208 311 206 307 25000 22 108 239 188 63 1...

Page 516: ...6 229 278 227 276 226 274 15000 07 121 281 221 74 3 223 293 221 291 220 289 18000 01 121 272 213 71 8 220 302 218 300 216 298 20000 03 117 259 203 68 4 214 305 212 302 210 299 21000 05 114 251 197 66 4 211 305 209 302 207 299 22000 06 111 244 191 64 4 207 306 205 303 203 299 23000 08 108 237 186 62 5 204 306 202 303 199 299 24000 10 105 229 180 60 5 201 306 198 302 196 298 25000 12 101 222 174 58 ...

Page 517: ...33 38 7 115 147 199 23 39 1 116 146 201 13 39 6 118 144 203 3 40 1 119 143 205 21000 45 45 37 4 111 148 198 35 37 9 112 146 201 25 38 4 114 145 203 15 38 8 115 143 205 5 39 3 117 142 207 22000 45 46 36 7 109 147 200 36 37 1 110 145 202 26 37 5 112 144 205 16 38 1 113 142 207 6 38 6 115 140 208 23000 45 48 35 9 107 146 202 38 36 4 108 144 205 28 36 8 109 142 206 18 37 3 111 141 208 8 37 8 112 139 2...

Page 518: ...0 46 37 3 111 153 232 36 37 8 112 152 235 26 38 2 114 150 237 16 38 8 115 148 240 28000 55 5 58 36 9 110 156 235 48 37 4 111 154 238 38 37 9 113 153 241 28 38 3 114 151 243 18 38 8 115 149 245 29000 56 60 36 6 109 156 238 50 37 1 110 154 241 40 37 5 111 152 244 30 38 0 113 150 246 20 38 5 114 148 248 30000 56 5 62 36 4 108 155 242 52 36 9 110 154 245 42 37 3 111 152 247 32 37 8 112 150 250 22 38 3...

Page 519: ...33 40 8 121 150 203 23 41 2 122 149 205 13 41 7 124 147 206 3 42 2 125 145 208 21000 50 45 39 4 117 151 202 35 39 9 119 149 204 25 40 5 120 147 206 15 40 9 121 145 208 5 41 4 123 143 209 22000 50 46 38 7 115 149 204 36 39 1 116 148 206 26 39 6 118 146 208 16 40 1 119 144 209 6 40 6 121 142 210 23000 50 48 38 0 113 148 206 38 38 4 114 146 207 28 38 9 116 144 209 18 39 3 117 142 210 8 39 8 118 140 2...

Page 520: ...32 46 39 1 116 155 234 36 39 6 118 153 236 26 40 1 119 151 238 16 40 6 121 148 240 28000 60 5 58 39 0 116 158 238 48 39 5 117 156 241 38 40 0 119 154 243 28 40 5 120 152 244 18 41 0 122 150 246 29000 61 60 38 7 115 157 241 50 39 1 116 155 243 40 39 7 118 153 245 30 40 1 119 151 247 20 40 7 121 149 249 30000 61 5 62 38 5 114 157 244 52 39 0 116 155 247 42 39 4 117 153 249 32 39 9 119 150 251 22 40 ...

Page 521: ...33 42 7 127 152 205 23 43 3 129 150 206 13 43 8 130 148 208 3 44 3 132 146 209 21000 55 45 41 5 123 153 205 35 41 9 125 150 206 25 42 4 126 148 208 15 43 0 128 146 209 5 43 5 129 144 210 22000 55 46 40 8 121 151 206 36 41 2 122 149 208 26 41 7 124 147 209 16 42 1 125 145 211 6 42 6 127 143 212 23000 55 48 40 0 119 150 208 38 40 6 121 147 209 28 41 0 122 145 211 18 41 5 123 143 212 8 41 9 125 141 2...

Page 522: ...34 46 41 2 122 155 235 36 41 7 124 153 237 26 42 3 126 151 239 16 42 8 127 149 240 28000 65 5 58 41 1 122 159 240 48 41 6 124 157 241 38 42 0 125 154 243 28 42 6 127 152 245 18 43 1 128 150 246 29000 66 60 40 8 121 158 242 50 41 3 123 156 244 40 41 8 124 153 246 30 42 2 125 151 248 20 42 8 127 149 249 30000 66 5 62 40 6 121 158 245 52 41 1 122 155 247 42 41 6 124 153 249 32 42 1 125 150 251 22 42 ...

Page 523: ... 42 33 11 0 61 10 25 30 24 7 9 49 24000 16 00 57 45 15 1 74 12 00 39 30 10 2 55 09 35 28 22 7 4 44 22000 14 40 52 41 13 8 66 11 00 36 28 9 5 50 08 50 26 20 6 8 40 20000 13 20 48 38 12 8 59 10 00 33 26 8 6 44 08 00 24 19 6 2 36 18000 12 00 44 34 11 5 53 09 00 30 23 7 8 39 07 10 21 17 5 7 31 16000 10 40 39 31 10 3 46 08 00 27 21 7 0 34 06 25 19 15 5 0 28 14000 09 20 35 27 9 1 40 07 00 23 18 6 2 30 0...

Page 524: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE Page 5 12 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 525: ...00 lbs 2495 kg Weight 6300 lbs 2858 kg Pressure altitude feet 10 min 30 min 10 min 30 min feet l kg us gal l kg us gal l kg us gal l kg us gal SL 32 25 8 4 95 75 25 1 32 25 8 4 96 75 25 3 5000 28 22 7 3 83 65 22 0 29 23 7 6 86 68 22 7 10000 25 20 6 6 75 59 19 8 26 20 6 8 77 61 20 4 15000 23 18 6 1 69 54 18 3 24 19 6 3 72 57 19 0 20000 21 17 5 6 63 50 16 8 22 17 5 9 66 52 17 6 Figure 5 13 1 HOLDING...

Page 526: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE Page 5 13 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 527: ...5 2920 1740 1870 2035 2200 2360 2330 2495 2660 2855 3020 1840 1970 2135 2300 2495 2430 2590 2790 2955 3180 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1905 2070 2230 2395 2590 2530 2690 2890 3050 3280 2000 2135 2330 2530 2725 2625 2790 2985 3215 3410 2070 2230 2430 2625 2855 2690 2890 3085 3315 3570 2135 2300 2495 2690 2920 2790 2955 3...

Page 528: ...2490 1180 1245 1345 1445 1540 2070 2200 2330 2460 2590 1215 1310 1410 1510 1610 2135 2265 2395 2525 2690 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1280 1345 1445 1575 1705 2200 2330 2460 2645 2790 1310 1410 1510 1640 1770 2300 2430 2560 2720 2885 1380 1475 1575 1705 1835 2360 2495 2655 2820 2985 1445 1540 1640 1770 1900 2430 2560 275...

Page 529: ...90 1000 1065 1150 1230 1310 2070 2200 2330 2460 2590 1030 1115 1200 1280 1360 2135 2265 2395 2525 2690 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1080 1150 1230 1345 1445 2200 2330 2460 2645 2790 1115 1200 1280 1395 1510 2300 2430 2560 2720 2885 1180 1245 1345 1445 1560 2360 2495 2655 2820 2985 1230 1310 1395 1510 1610 2430 2560 2755 ...

Page 530: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 5 PERFORMANCE EASA Approved Page 5 14 4 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 531: ...6 2 1 6 3 BAGGAGE LOADING 6 3 1 6 4 DETERMINING WEIGHT AND BALANCE 6 4 1 GENERAL 6 4 1 USING THE WEIGHT AND BALANCE FORM AND DIAGRAM 6 4 1 AIRPLANE LOADING FORM 6 4 3 EXAMPLE OF AIRPLANE WEIGHT AND BALANCE REPORT 6 4 5 WEIGHT AND BALANCE FORM AND DIAGRAM 6 4 8 WEIGHT AND BALANCE SAMPLES 6 4 17 DETERMINING EMPTY AIRPLANE CHARACTERISTICS 6 4 24 6 5 LIST OF EQUIPMENT 6 5 1 PIM DO NOT USE FOR FLIGHT O...

Page 532: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 0 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 533: ...ns between 2 seats and 6 seats as required by the operator All A list of equipment available for this airplane is referenced at the end of this Pilot s Operating Handbook refer to Chapter 6 5 The list of specific optional equipment installed on your airplane as delivered from the factory can be found in the records carried in the airplane IT IS THE PILOT S RESPONSIBILITY TO ENSURE THAT THE AIRPLAN...

Page 534: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 1 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 535: ...IRPLANE WEIGHING PROCEDURES Refer to Maintenance Manual for the procedures to use NOTE Weighing carried out at the factory takes into account all equipment installed on the airplane The list of this equipment and the total weight is noted in the Individual Inspection Record PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 536: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 2 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 537: ... net separating the cabin from the baggage compartment is attached to frame C14 Post MOD70 0315 25 with other allowed seat accommodation There are two loading areas One in place of the two removed rear seats with maximum loading capacity of 176 lbs 80 kg One in the baggage compartment behind the rear seats area with maximum loading capacity of 220 lbs 100 kg Two types of baggage securing nets can ...

Page 538: ... 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 When using the large net distribute the weight in each zone delineated by the step in the floor according to the zone limits PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 539: ...WITH REGULATIONS CONCERNING TRANSPORT OF DANGEROUS PRODUCT AND ANY OTHER APPLICABLE REGULATION Baggage compartments loading must be done in accordance with the weight and balance limits of the airplane refer to Section 2 for limitations Generally if rear seats are not used or removed first load AFT compartment then if required FWD compartment If rear seats are used first load FWD compartment then ...

Page 540: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 3 4 Edition 1 June 22 2007 Rev 12 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 541: ...ERMINING EMPTY AIRPLANE CHARACTERISTICS to determine the new empty weight and the corresponding moment USING THE WEIGHT AND BALANCE FORM AND DIAGRAM This procedure determines the airplane weight and balance characteristics for flight Select the units for the Weight and Balance determination either m and kg or lb and in and use the dedicated form Figures 6 4 3 or 6 4 4 or 6 4 5 or 6 4 6 appropriate...

Page 542: ...keoff Weight 11a and moment 11b as sum of Ramp Weight 7a Taxi Fuel 10a and moments 7b 10b 12 Check value 11a to be below Maximum Takeoff Weight 13 Compute Takeoff Weight arm 13 and CG MAC 13c using given formulas 14 Record the expected Trip Fuel negative value 14a and compute associated moment 14b 15 Compute Landing Weight 15a and moment 15b as sum of Takeoff Weight 11a Trip Fuel 14a and moments 1...

Page 543: ... CG MAC Empty Weight kg 1a 1b 1c Baggage FWD 50 kg 2a 3 250 2b Front Seats kg 2a 4 534 2b Inter Seats kg 2a 5 656 2b Rear bench kg 2a 6 785 2b Baggage AFT 100 kg 2a 7 695 2b Zero Fuel Weight 2 736 kg 3a 5 3b 5c Fuel kg 6a 4 820 6b Ramp Weight 3 370 kg 7a 9 7b 9c Taxi Fuel kg 10a 4 820 10b Takeoff Weight 3 354 kg 11a 13 11b 13c Trip Fuel kg 14a 4 820 14b Landing Weight 3 186 kg 15a 17 15b 17c PIM D...

Page 544: ...kg per seat removed 2a 6 785 2b Pax 2a 2b Cargo 80 kg 2a 2b Baggage AFT 100 kg 2a 7 695 2b Zero Fuel Weight 2 736 kg 3a 5 3b 5c Fuel kg 6a 4 820 6b Ramp Weight 3 370 kg 7a 9 7b 9c Taxi Fuel kg 10a 4 820 10b Takeoff Weight 3 354 kg 11a 13 11b 13c Trip Fuel kg 14a 4 820 14b Landing Weight 3 186 kg 15a 17 15b 17c Item Weight kg Empty Weight 1a Baggage FWD 50 kg 2a Front Seats 2a Inter Seats 17 kg per...

Page 545: ... Edition 1 June 22 2007 Rev 12 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 546: ...AND BALANCE Page 6 4 6 Edition 1 June 22 2007 Rev 12 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 547: ...SECTION 6 WEIGHT AND BALANCE TBM 850 PILOT S OPERATING HANDBOOK Page 6 4 7 Edition 1 June 22 2007 Rev 12 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 548: ...Arm CG MAC Arm m 4 392 1 51 100 Item Weight kg Arm m Moment m kg CG MAC Empty Weight kg Baggage FWD 50 kg 3 250 Front Seats kg 4 534 Inter Seats kg 5 656 Rear bench kg 6 785 Baggage AFT 100 kg 7 695 Zero Fuel Weight 2 736 kg Fuel kg 4 820 Ramp Weight 3 370 kg Taxi Fuel kg 4 820 Takeoff Weight 2 354 kg Trip Fuel kg 4 820 Landing Weight 3 186 kg PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 549: ...SECTION 6 WEIGHT AND BALANCE TBM 850 PILOT S OPERATING HANDBOOK Page 6 4 9 Edition 1 June 22 2007 Rev 12 Figure 6 4 3 Weight and Balance diagram PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 550: ...00 Item Weight kg Arm m Moment m kg CG MAC Empty Weight kg Baggage FWD 50 kg 3 250 Front Seats kg 4 534 Inter Seats 17 kg per seat removed 5 710 Pax Rear bench 24 kg per seat removed 6 785 Pax Cargo 80 kg Baggage AFT 100 kg 7 695 Zero Fuel Weight 2 736 kg Fuel kg 4 820 Ramp Weight 3 370 kg Taxi Fuel kg 4 820 Takeoff Weight 3 354 kg Trip Fuel kg 4 820 Landing Weight 3 186 kg PIM DO NOT USE FOR FLIG...

Page 551: ...SECTION 6 WEIGHT AND BALANCE TBM 850 PILOT S OPERATING HANDBOOK Page 6 4 11 Edition 1 June 22 2007 Rev 12 Figure 6 4 4 Weight and Balance diagram PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 552: ...C Arm in 172 93 59 45 100 Item Weight lbs Arm in Moment in lbs CG MAC Empty Weight lbs Baggage FWD 110 lbs 128 0 Front Seats lbs 178 5 Inter Seats lbs 222 7 Rear bench lbs 267 1 Baggage AFT 220 lbs 303 0 Zero Fuel Weight 6 032 lbs Fuel lbs 189 8 Ramp Weight 7 430 lbs Taxi Fuel lbs 189 8 Takeoff Weight 7 394 lbs Trip Fuel lbs 189 8 Landing Weight 7 024 lbs PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 553: ...SECTION 6 WEIGHT AND BALANCE TBM 850 PILOT S OPERATING HANDBOOK Page 6 4 13 Edition 1 June 22 2007 Rev 12 Figure 6 4 5 Weight and Balance diagram PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 554: ...ight lbs Arm in Moment in lbs CG MAC Empty Weight lbs Baggage FWD 110 lbs 128 0 Front Seats lbs 178 5 Inter Seats 37 5 lbs per seat removed 224 8 Pax Rear bench 52 9 lbs per seat removed 267 1 Pax Cargo 176 lbs Baggage AFT 220 lbs 303 0 Zero Fuel Weight 6 032 lbs Fuel lbs 189 8 Ramp Weight 7 430 lbs Taxi Fuel lbs 189 8 Takeoff Weight 7 394 lbs Trip Fuel lbs 189 8 Landing Weight 7 024 lbs PIM DO NO...

Page 555: ...SECTION 6 WEIGHT AND BALANCE TBM 850 PILOT S OPERATING HANDBOOK Page 6 4 15 Edition 1 June 22 2007 Rev 12 Figure 6 4 6 Weight and Balance diagram PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 556: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 4 16 Edition 1 June 22 2007 Rev 12 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 557: ...LE FOR CALCULATION CONCERNING YOUR AIRPLANE REFER TO THE DIAGRAM CORRESPONDING TO ITS VALIDITY Fig 6 4 7 1 Airplane basic characteristics W Empty weight Moment Balance Arm CG MAC 2 126 kg 10 073 m kg 4 738 m 22 9 2 Foreseen loading 1 Pilot and 1 front Passenger 2 Rear Passengers AFT Cargo in baggage compartment Fuel 200 kg 160 kg 50 kg 820 kg 3 Foreseen fuel Taxi Fuel Trip Fuel 16 kg 600 kg PIM DO...

Page 558: ... FWD 50 kg 0 3 250 0 Front Seats kg 200 4 534 907 Inter Seats kg 0 5 656 0 Rear bench kg 160 6 785 1 086 Baggage AFT 100 kg 50 7 695 385 Zero Fuel Weight 2 736 kg 2 536 4 910 12 451 34 3 Fuel kg 820 4 820 3 952 Ramp Weight 3 370 kg 3 356 4 888 16 403 32 8 Taxi Fuel kg 16 4 820 77 Takeoff Weight 3 354 kg 3 340 4 888 16 326 32 8 Trip Fuel kg 600 4 820 2 892 Landing Weight 3 186 kg 2 740 4 903 13 434...

Page 559: ...SECTION 6 WEIGHT AND BALANCE TBM 850 PILOT S OPERATING HANDBOOK Page 6 4 19 Edition 1 June 22 2007 Rev 12 Figure 6 4 7 Loading sample PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 560: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 4 20 Edition 1 June 22 2007 Rev 12 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 561: ...istics W Empty weight Moment Balance Arm CG MAC 4 638 lbs 864 173 in lbs 186 3 in 22 6 2 Foreseen loading FWD compartment 1 Pilot and 1 front Passenger 1 Intermediate Passenger 2 Rear seats removed Rear cargo AFT Cargo in baggage compartment Fuel 100 lbs 400 lbs 220 lbs 105 8 lbs 176 lbs 120 lbs 1 850 lbs 3 Foreseen fuel Taxi Fuel Trip Fuel 36 lbs 1 400 lbs PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 562: ...er Seats 37 5 lbs per seat removed 0 224 8 0 Pax 220 49 456 Rear bench 52 9 lbs per seat removed 105 8 267 1 28 259 Pax 0 0 Cargo 176 lbs 100 26 710 Baggage AFT 220 lbs 120 303 0 36 360 Zero Fuel Weight 6 032 lbs 5 472 188 7 1 032 640 26 5 Fuel lbs 1 850 189 8 351 130 Ramp Weight 7 430 lbs 7 322 189 0 1 383 770 27 Taxi Fuel lbs 36 189 8 6 831 Takeoff Weight 7 394 lbs 7 286 189 0 1 397 237 27 Trip ...

Page 563: ...SECTION 6 WEIGHT AND BALANCE TBM 850 PILOT S OPERATING HANDBOOK Page 6 4 23 Edition 1 June 22 2007 Rev 12 Figure 6 4 8 Weight and Balance diagram PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 564: ...ew empty weight and corresponding balance if necessary DATE EQUIPMENT OR MODIFICATION DESCRIPTION WEIGHT MODIFICATION BASIC EMPTY WEIGHT Weight lb Arm in Moment lb in 1000 Weight W Arm do Moment According to delivery Figure 6 4 9 SAMPLE WEIGHT AND BALANCE RECORD CG m a c do 172 93 59 45 100 Use the above formula to express arm do in of mean aerodynamic chord NOTE Arm expressed in inches with regar...

Page 565: ... HANDBOOK Page 6 4 25 Edition 1 June 22 2007 Rev 12 Pre MOD 70 0315 25 and Post MOD 70 0315 25 Rear bench 2 seats net 267 1 in 6 785 m All Baggage compartment in pressurized cabin 303 0 in 7 695 m Fuel 189 8 in 4 820 m PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 566: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 4 26 Edition 1 June 22 2007 Rev 12 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 567: ...ev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 568: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 6 WEIGHT AND BALANCE Page 6 5 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 569: ...ODATIONS 7 3 1 INSTRUMENT PANEL 7 3 1 DOORS WINDOWS AND EMERGENCY EXIT 7 3 24 SEATS BELTS AND HARNESSES 7 3 31 BAGGAGE COMPARTMENTS 7 3 35 7 4 FLIGHT CONTROLS 7 4 1 ROLL 7 4 1 ROLL TRIM 7 4 1 ELEVATOR 7 4 7 PITCH TRIM 7 4 7 RUDDER 7 4 13 RUDDER TRIM 7 4 13 7 5 LANDING GEAR 7 5 1 HYDRAULIC PRESSURE 7 5 2 LANDING GEAR CONTROL 7 5 2 LANDING GEAR POSITION INDICATOR 7 5 2 SAFETY 7 5 4 GROUND MANEUVERS ...

Page 570: ...SYSTEM 7 7 1 FUEL TANKS 7 7 1 FUEL UNIT 7 7 1 TANK MANUAL SELECTOR 7 7 1 AUTOMATIC TANK SELECTOR 7 7 4 ELECTRIC BOOST PUMP 7 7 5 MAIN MECHANICAL BOOST PUMP 7 7 8 ENGINE FUEL SYSTEM 7 7 8 FUEL GAGING INSTALLATION 7 7 8 FUEL SYSTEM MONITORING 7 7 8 FUEL SYSTEM DRAINING AND CLOGGING INDICATOR 7 7 9 7 8 ELECTRICAL SYSTEM 7 8 1 STARTER GENERATOR 7 8 1 STAND BY GENERATOR 7 8 2 BATTERY 7 8 2 GROUND POWER...

Page 571: ... INSTRUMENTS 7 11 1 STATIC PRESSURE SYSTEMS 7 11 1 DYNAMIC PRESSURE SYSTEM 7 11 7 7 12 VACUUM SYSTEM AND INSTRUMENTS 7 12 1 STAND BY ATTITUDE INDICATOR 7 12 1 SUCTION GAGE 7 12 4 ELECTRONIC STANDBY INDICATOR ESI 2000 7 12 4 7 13 ICE PROTECTION EQUIPMENT 7 13 1 WING AND EMPENNAGE DEICING 7 13 1 PROPELLER DEICING 7 13 2 WINDSHIELD DEICING 7 13 2 HEATING OF PITOTS AND STALL WARNING SENSOR 7 13 3 TURB...

Page 572: ...OK 850 SECTION 7 DESCRIPTION Page 7 0 4 Edition 1 June 22 2007 Rev 14 TABLE OF CONTENTS Continued EMERGENCY LOCATOR TRANSMITTER 7 15 5 FLIGHT DECK INFORMATION SYSTEM FS 210 if installed 7 15 8 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 573: ... and may not be installed in the airplane Complete description and operation of the GARMIN G1000 integrated flight deck are detailed in the GARMIN G1000 Integrated Flight Deck Pilot s Guide References to this Guide are often made all along this Section to get more details about some systems Details of other optional systems and equipment are presented in Section 9 Supplements of the Pilot s Operat...

Page 574: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 1 2 Edition 1 June 22 2007 Rev 14 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 575: ...ction and is equipped with a retractable tricycle landing gear The pressurized cabin is equipped on the left side of fuselage with a one piece access door and folding stairs comprising a hand rail allowing pilot and passengers boarding The occupants have access to cockpit and to rear seats through a central aisle An optional pilot door located forward of the cabin on the left side allows access to...

Page 576: ...RATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 2 2 Edition 1 June 22 2007 Rev 8 Figure 7 2 1 CABIN ARRANGEMENT Pre MOD70 0315 25 and Post MOD70 0315 25 with 6 seat accommodation PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 577: ...TION TBM 850 PILOT S OPERATING HANDBOOK Page 7 2 1A Edition 1 June 22 2007 Rev 8 Figure 7 2 1A CABIN ARRANGEMENT Post MOD70 0315 25 with 4 seat accommodation with large securing net PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 578: ...NG HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 2 2A Page Edition 1 June 22 2007 Rev 8 Figure 7 2 1B CABIN ARRANGEMENT Post MOD70 0315 25 with 4 seat accommodation with small securing net PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 579: ... located in front of flaps on top skin side are mechanically linked to the ailerons Trim tab knob attached on the trailing edge of L H aileron is electrically activated by a trim knob through an actuator WING FLAPS Figure 7 2 2 The wing flaps are large span slotted flaps with a single rotation point They are activated by actuating rod controlled screw jacks linked to an electric motor located unde...

Page 580: ...angle to fuselage horizontal datum 2 Sweep angle at 25 chord 0 Dihedral at datum plane 6 5 Aspect ratio platform reference 8 216 Taper ratio 0 608 Airfoil section at wing root RA 16 43 Airfoil section at wing tip RA 13 3 43 Twist 0 Aileron spoilers characteristics Global aileron area including trim tab 9 65 sq ft 0 897 m2 Aileron trim tab area 0 78 sq ft 0 072 m2 Spoiler area 1 80 sq ft 0 167 m2 F...

Page 581: ...OPERATING HANDBOOK Page 7 2 5 Edition 1 June 22 2007 Rev 0 Figure 7 2 2 1 2 WING FLAPS 1 Geared motor 2 Internal actuator 3 Intermediate bearings 4 Wing flap 5 External actuator 6 Rods 7 Control selector PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 582: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 2 6 Edition 1 June 22 2007 Rev 0 Figure 7 2 2 2 2 WING FLAPS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 583: ...ip chord 2 60 ft 0 795 m Mean aerodynamic chord at y 3 76 ft 1 147 m 3 26 ft 0 995 m Airfoil section NACA 642 A415 modified Dihedral 6 5 Rigging angle leading edge up 0 5 Aspect ratio 5 034 Elevator global area including trim tabs 21 76 sq ft 2 022 m2 Elevator trim tab area right datum plane 3 47 sq ft 0 322 m2 Vertical stabilizer characteristics Global area 33 28 sq ft 3 092 m2 Construction root ...

Page 584: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 2 8 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 585: ...s two Primary Flight Displays PFD and one Multi Function Display MFD refer to the GARMIN G1000 Pilot s Guide for detailed description Apart from the G1000 system equipment listed below complete the instrument panel Left area instrument panel includes Figures 7 3 3 or 7 3 3A Pre MOD70 0335 34 ESI 2000 on top stand by airspeed indicator and stand by attitude indicator at bottom deicing controls and ...

Page 586: ... and on the arm rest of rear R H passenger s seat Pedestal console Figure 7 3 6 The pedestal console under the GCU 475 control unit comprises flaps controls pitch trim tab control wheel aileron trim switch engine controls and fuel tank selector Circuit breakers panel Figures 7 3 7 and 7 8 3 Circuit breakers for all electrical equipment supplied by bus bars are located on a separate panel installed...

Page 587: ...rn the VMO alarm the landing gear control unit the flap geared motor Aural warning box The aural warning box consists of a box including logic circuits which create the signals heard in the aural warning loud speakers According to the airplane configuration different signals are produced by the logic circuits gear up and idle high pitched sound gear up and extended flaps high pitched sound stall l...

Page 588: ...o control panels receive signals from the aural warning box According to the airplane configuration these signals are low pitched and or high pitched The HORN TEST knob allows to test the correct operation of aural warnings Set the SOURCE selector to BAT or to GPU Set the AVIONICS MASTER switch to ON Push and hold the HORN TEST knob the VMO buzzer emits bips the loud speakers emit alternate low pi...

Page 589: ...through the loud speakers installed in cockpit overhead panel and through the pilot s and R H station headsets The aural warnings consist of the G1000 system GIA and GMA the loud speakers The system uses the stall warning system the airspeed indicator the landing gear control unit the flap geared motor the idle position sensor Aural warning alerts According to the airplane configuration different ...

Page 590: ...stat It is attached to the cabin upper part between frames C6 and C7 The emergency lighting rheostat is electrically supplied by BATT BUS bar and protected by PANEL EMER circuit breaker The HORN TEST push button allows to test the correct operation of aural warnings set the SOURCE selector to BATT or GPU push and hold the HORN TEST push button The loud speakers emit stall stall aural warning alert...

Page 591: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 7 Edition 1 June 22 2007 Rev 12 All Figure 7 3 1 INSTRUMENT PANEL ASSEMBLY Typical arrangement PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 592: ...ergency lighting 5 Cockpit floodlight switches rheostats 6 R H cockpit floodlight 7 MASTERs controls AVIONICS and AP TRIMS 8 FUEL control panel Figure 7 7 3 9 ENGINE START switches Figure 7 6 3 10 ELECTRIC POWER switches Figure 7 8 4 11 INT LIGHTS internal lighting switches Figure 7 8 6 12 EXT LIGHTS external lighting switches Figure 7 8 5 13 L H cockpit floodlight 14 HORN TEST aural warning test ...

Page 593: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 9 Edition 1 June 22 2007 Rev 12 Figure 7 3 2 2 2 UPPER PANEL AND COCKPIT OVERHEAD PANEL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 594: ...ol panel Figure 7 5 1 7 Parking brake control Figure 7 5 6 8 Left station control wheel tube 9 Deicing control and check panel Figure 7 13 1 10 L H station rudder pedals adjusting handle 11 Left station reception micro jacks 12 Electric pitch trim control 13 Maps reading tablet 14 Electric rudder trim control 15 AP DISC TRM INT red push button 16 Flight conditions and instruction placard 17 Adjust...

Page 595: ...DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 11 Edition 1 June 22 2007 Rev 12 Figure 7 3 3 2 2 LEFT INSTRUMENT PANEL Typical arrangement Pre MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 596: ... panel Figure 7 5 1 6 Parking brake control Figure 7 5 6 7 Left station control wheel tube 8 Deicing control and check panel Figure 7 13 1 9 L H station rudder pedals adjusting handle 10 Left station reception micro jacks 11 Electric pitch trim control 12 Maps reading tablet 13 Electric rudder trim control 14 AP DISC TRM INT red push button 15 Flight conditions and instruction placard 16 Adjustabl...

Page 597: ...ESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 13 Edition 1 June 22 2007 Rev 12 Figure 7 3 3A 2 2 LEFT INSTRUMENT PANEL Typical arrangement Post MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 598: ... Rev 12 Figure 7 3 4 1 2 CENTRAL INSTRUMENT PANEL Pre MOD70 0335 34 ESI 2000 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 599: ...ESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 15 Edition 1 June 22 2007 Rev 12 Figure 7 3 4 2 2 CENTRAL INSTRUMENT PANEL Typical arrangement Pre MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 600: ...ne 22 2007 Rev 12 Figure 7 3 4A 1 2 CENTRAL INSTRUMENT PANEL Post MOD70 0335 34 ESI 2000 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 601: ...SCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 17 Edition 1 June 22 2007 Rev 12 Figure 7 3 4A 2 2 CENTRAL INSTRUMENT PANEL Typical arrangement Post MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 602: ...ir outlet 6 Right station reception micro jacks 7 Hour meter 8 R H station rudder pedals adjusting handle 9 Circuit breakers panel postlight 10 Servicing plug 11 Cabin emergency air control RAM AIR control knob 12 Static source selector 13 ECS air conditioning control panel Figure 7 9 2 14 Electric pitch trim control 15 Electric rudder trim control 16 Maps reading tablet 17 AP DISC TRM INT red pus...

Page 603: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 19 Edition 1 June 22 2007 Rev 12 Figure 7 3 5 2 2 RIGHT INSTRUMENT PANEL Typical arrangement PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 604: ... 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 605: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 21 Edition 1 June 22 2007 Rev 12 Figure 7 3 6 2 2 PEDESTAL CONSOLE Typical arrangement PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 606: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 3 22 Edition 1 June 22 2007 Rev 12 Figure 7 3 7 CIRCUIT BREAKERS PANEL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 607: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 23 Edition 1 June 22 2007 Rev 12 Figure 7 3 8 GENERAL ALARMS WARNING LIGHTS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 608: ... stairs downwards Stairs down movement is damped by means of two gas struts and leads the hand rail to extend CAUTION RETRACT STAIRS BEFORE CLOSING ACCESS DOOR AND MAKE SURE DOOR DEFLECTION AREA IS CLEAR To retract stairs press on locking pin located on stairs front string board see detail 1 raise retractable handle see detail 2 and pull stairs inside cabin While stairs are retracted the hand rail...

Page 609: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 25 Edition 1 June 22 2007 Rev 12 Figure 7 3 9 CABIN ACCESS DOOR PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 610: ...tairs from outside the airplane raise stairs by pushing them upwards from the lower part and fold them inside cabin While stairs are retracted the hand rail folds up To close the door from outside the airplane press on knob on outside fuselage at the right side of the door The door driven by a geared motor tilts downwards up to a position near the complete closing Push the door until it aligns wit...

Page 611: ...N RETRACT FOOTSTEP BEFORE CLOSING ACCESS DOOR Fold and tilt footstep upwards To close the door from inside the airplane pull the door until it aligns with fuselage and lock it by moving inside handle downwards Check that each latch is correctly engaged in its recess visible green marks The DOOR CAS message lights on as long as cabin access door and pilot access door if installed are not correctly ...

Page 612: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 3 28 Edition 1 June 22 2007 Rev 12 Figure 7 3 9A COCKPIT ACCESS DOOR PILOT DOOR PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 613: ...arts electrically deiced Emergency exit Figure 7 3 10 The emergency exit is installed on the right side of the fuselage and opens towards the inside It is equipped with two handles one inside and the other outside each located on the upper frame When the airplane is parked the closing system may be locked by a safety pin provided with a flag marker The handle is then inoperable WARNING TAXIING AND...

Page 614: ...CAS message lights on as long as FWD compartment door is not locked Windows Windows do not open The windshield consists of two parts electrically deiced Emergency exit Figure 7 3 10 The emergency exit is installed on the right side of the fuselage and opens towards the inside It is equipped with two handles one inside and the other outside each located on the upper frame When the airplane is parke...

Page 615: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 3 30 Edition 1 June 22 2007 Rev 12 Figure 7 3 10 EMERGENCY EXIT PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 616: ...Step 1 I 0 0 0 00 N ü i t f_ z n 1 l t t 1 Step 2 1 1 1 1 1 J J 1 1 1 lt T J SECTION 7 r DESCRIPTION Â 1 1 Upholstery panel 2 Opening handle 1 f J T T LO 1 A À a I 1 1 1 _ 1 1 1 _11 À 1 _ 1 T t Il f Figure 7 3 10A REMOVAL OF THE UPHOLSTERY PANEL OF THE EMERGENCY EXIT 1 T Edition 1 June 22 2007 TR29 July 2022 __ _ 1 T Page 7 3 30A PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 617: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 3 30B Edition 1 June 22 2007 TR29 July 2022 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 618: ... 70 0315 25 with 6 seat accommodation The accommodation consists of two individual seats installed back to the flight direction mounted on the same rails as the front seats The seat back angle is adjusted by pulling up side handle two rear seats arranged as a bench mounted on the same rails as the front seats The seat back rests tilt forward by pulling up the handle located forward on L H side of ...

Page 619: ...15 25 with 6 seat accommodation The accommodation consists of two individual seats installed back to the flight direction mounted on the same rails as the front seats The seat back angle is adjusted by pulling up side handle two rear seats arranged as a bench mounted on the same rails as the front seats The seat back rests tilt forward by pulling up the handle located forward on L H side of each s...

Page 620: ...gurations This possibility is valid ONLY for Post MOD70 0315 25 For the MID Seat zone B ONLY the Middle Seats can be installed in MID Seat Zone This zone accepts Fwd and Aft Facing Mid Seat when rear seats are installed ONLY per MOD 70 0315 25 The zone B accepts zero or 1 or 2 seats The zone B is not a luggage area For the REAR Seat zone C ONLY the Rear Seat can be installed in Rear Seat Zone The ...

Page 621: ...cation number 1 2 3 4 5 C1 X X X X C2 X X X C3 X X X C4 1 X X C5 X X X C6 X X X C7 X X C8 X X C9 X X C10 1 X C11 X X X C12 X X C13 X X C14 X X C15 1 X C16 X X C17 X C18 X C19 X C20 1 Zone B Zone C 1 This configuration accepts small net or large net from MOD70 0315 25 Each cross indicates that you have a seat at the correspondent location number Location number PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 622: ...T THE BELT MUST NOT BE TWISTED CHECK THAT THERE IS NO CONSTRAINT WHEN OPERATED AFTER A SERIOUS ACCIDENT REPLACE ALL BELTS Each cockpit seat is equipped with a four point restraint system consisting of an adjustable lap belt and a dual strap inertia reel type shoulder harness Each passenger seat is equipped with a three point restraint system consisting of an adjustable lap belt and an inertia reel...

Page 623: ...irplane Theselocationsaredesignedforthecarryingoflowdensityloads loadingand unloading must be carried out with caution to avoid any damage to airplane The cabin is separated from the baggage compartment by a partition net intended to protect the passengers from injuries that could be caused by improper tie down of a content The partition net is mounted at frame C14 Figure 7 2 1 it is secured at th...

Page 624: ...e Small Cargo Net is attached through nine anchoring points on seat rails between frame C11 and frame C13bis Figure 7 2 1B the Large Cargo Net is attached through seven anchoring points on seat rails between frame C11 and frame C13bis and six anchoring points on fuselage sides at frame C14 Figure 7 2 1A NOTE Original Partition Net must be disconnected from side walls and placed on the floor PIM DO...

Page 625: ...ection 6 Weight and balance WARNING ANY PARCEL OR BAGGAGE IN CABIN MUST BE STOWED BY CARGO NET AND STRAPS IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT ALL THE PARCELS AND BAGGAGE ARE PROPERLY SECURED IN CASE OF TRANSPORT OF DANGEROUS MATERIALS RESPECT THE LAW CONCERNING TRANSPORT OF DANGEROUS MATERIALS AND ANY OTHER APPLICABLE REGULATION USE OF CARGO NETS Net inspection Before each use visually ...

Page 626: ...cal net tensioning straps damaged on less than 30 of its length reduce maximum load by 50 seam of tensioning straps attached on the rails damaged on less than 30 of its length reduce maximum load by 50 beyond 30 damage for above mentioned cases defective element must mandatorily be discarded and replaced netting cut or torn on less than 3 9 in 100 mm still serviceable no impact netting cut or torn...

Page 627: ...itudinal shift control 8 Front seat s height control 9 Front seat s back rest tilt control 10 Drawer for pilot s piddle pak if installed front side new bags rear side used bags 11 Intermediate seat s back rest tilt control 12 Rear bench seat s back rest tilt control 13 Rear bench L H seat tilt control 14 Rear bench seat s adjustment control handle NOTE To have access to the baggage compartment pul...

Page 628: ...S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 3 40 Edition 1 June 22 2007 Rev 12 Figure 7 3 11 2 2 SEATS Pre MOD70 0315 25 Post MOD70 0315 25 with 6 seat accommodation PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 629: ...odation 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 630: ...M PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 3 42 Edition 1 June 22 2007 Rev 12 Figure 7 3 11A 2 2 SEATS Post MOD70 0315 25 with 4 seat accommodation PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 631: ...IPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 3 43 Edition 1 June 22 2007 Rev 12 Figure 7 3 12 FRONT AND REAR SEAT BELTS with movable straps AND HARNESSES FRONT SEATS REAR SEATS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 632: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 3 44 Edition 1 June 22 2007 Rev 12 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 633: ... is deflected upwards and remains in wing profile when the aileron is deflected downwards Control wheel movement is transmitted through rods to fuselage roll lever located under the floor The movement is then transmitted through cables to the spoiler mechanism and from the spoiler mechanism to wing roll lever which activates the aileron through a rod A rudder roll combination spring type system in...

Page 634: ...TION 7 DESCRIPTION Page 7 4 2 Edition 1 June 22 2007 Rev 0 Figure 7 4 1 1 2 ROLL 1 Pedestal assembly 2 Control wheels 3 Fuselage roll lever 4 Spoiler 5 Aileron 6 Aileron control in wing 7 Spoiler control PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 635: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 4 3 Edition 1 June 22 2007 Rev 0 Figure 7 4 1 2 2 ROLL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 636: ...TION 7 DESCRIPTION Page 7 4 4 Edition 1 June 22 2007 Rev 0 Figure 7 4 2 1 2 LATERAL TRIM 1 Roll trim tab 2 Aileron 3 Adjustable rods 4 Actuator 5 Trim tab control wiring 6 Trim switch on pedestal console PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 637: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 4 5 Edition 1 June 22 2007 Rev 0 Figure 7 4 2 2 2 LATERAL TRIM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 638: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 4 6 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 639: ... with an automatic anti tab automaticity about 0 3 which is also used as trim tab PITCH TRIM Figure 7 4 4 The pitch trim is accomplished through the two anti tabs located on left and right elevators The trim tab can be controlled electrically or manually It is activated through cables and a chain on two screw actuators attached to the horizontal empennage The electrical control consists of a switc...

Page 640: ...tion 1 June 22 2007 Rev 0 Figure 7 4 3 1 2 ELEVATOR 1 Control wheel assembly 2 Elevators 3 Lever assembly fuselage rear part 4 Elevator bellcrank 5 Rod with presseal connection 6 Lever assembly under floor 7 Pedestal assembly 8 Actuator PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 641: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 4 9 Edition 1 June 22 2007 Rev 0 Figure 7 4 3 2 2 ELEVATOR PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 642: ...DESCRIPTION Page 7 4 10 Edition 1 June 22 2007 Rev 6 Figure 7 4 4 1 2 PITCH TRIM 1 Cables 2 Pulleys 3 Pitch trim tabs 4 Actuating rods 5 Actuator 6 Pitch trim manual control wheel 7 Electric pitch trim control PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 643: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 4 11 Edition 1 June 22 2007 Rev 0 Figure 7 4 4 2 2 PITCH TRIM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 644: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 4 12 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 645: ...the instrument panel and a locking device on the rudder pedals This ball locking device allows selecting six different positions When landing gear is down rudder pedals are linked to nose gear steering system Spring system of rudder roll combination induces aileron deflection at the time of pedal displacement and vice versa RUDDER TRIM Figure 7 4 6 A trim tab hinged at two points located at rudder...

Page 646: ... 7 4 14 Edition 1 June 22 2007 Rev 0 Figure 7 4 5 1 2 RUDDER 1 Roll rudder combination bellcrank installation 2 Rudder pedals assembly 3 Control cables 4 Pulleys 5 Rudder lever assembly 6 Rod 7 Rudder 8 Nose gear steering rod PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 647: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 4 15 Edition 1 June 22 2007 Rev 0 Figure 7 4 5 2 2 RUDDER PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 648: ...K 850 SECTION 7 DESCRIPTION Page 7 4 16 Edition 1 June 22 2007 Rev 0 Figure 7 4 6 1 2 RUDDER TRIM 1 Trim switch on control wheel 2 Actuator 3 Rudder trim tab 4 Rods 5 Rudder trim control wiring PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 649: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 4 17 Edition 1 June 22 2007 Rev 0 Figure 7 4 6 2 2 RUDDER TRIM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 650: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 4 18 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 651: ... is accomplished by a hydraulic actuating cylinder which also provides up and down locking The nose wheel is steerable It is connected to pedals through a spring rod and is provided with a shimmy damper In UP position nose wheel is automatically disconnected Actuating cylinders have a locking device integrated at both ends This device maintains landing gear in up or down position Pre MOD70 0342 52...

Page 652: ...e 7 5 1 Landing gear position indication is accomplished by 4 warning lights 3 green indicator lights one per landing gear 1 red warning light NOTE The red warning light flashes as soon as landing gears are operating and remains continuously on in case of locking problem When landing gear is correctly retracted all warning lights are OFF Down locked correct indication is when there are 3 green ind...

Page 653: ...BOOK Page 7 5 3 Edition 1 June 22 2007 Rev 0 Figure 7 5 1 CONTROL PANEL AND LANDING GEAR INDICATING 1 Red warning light LDG GR 2 Green indicator light LDG GR 3 Landing gear control selector 4 Test switch 5 Test knobs PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 654: ...ning signal becomes alternated high pitched sound low pitched sound Post MOD70 0407 00D V15 11 GARMIN software Landing gear aural warning Landing gear Landing gear aural warning alert sounds when throttle is on IDLE position and landing gear is not down locked flaps are beyond TO position Takeoff and landing gear is not down locked NOTE If one of above conditions exists and airplane is in stall co...

Page 655: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 5 5 Edition 1 June 22 2007 Rev 0 Figure 7 5 2 EMERGENCY LANDING GEAR EXTENSION CONTROL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 656: ...about 20 Steering may be increased up to 28 by applying differential braking to each side Airplane may be towed by attaching a steering or towing bar on nose gear Refer to Chapter 8 6 for operation In that case nose wheel steering angle is limited to 28 Minimum turn diameter Minimum turn diameter Figure 7 5 4 is obtained by using nose gear steering and differential braking Since tight turns lead t...

Page 657: ...RIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 5 7 Edition 1 June 22 2007 Rev 10 Figure 7 5 3 MINIMUM TURN DIAMETER Full rudder pedals travel without using differential braking PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 658: ... OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 5 8 Edition 1 June 22 2007 Rev 0 Figure 7 5 4 MINIMUM TURN DIAMETER Full rudder pedals travel by using differential braking PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 659: ...l knob located on pilot s side lower instrument panel and a valve which regulates brake pressure To apply the parking brake press on toe brake of rudder pedals and set the control knob to ON PARK BRAKE CAS message lights on when the control knob is set to ON NOTE Operating the parking brake knob without applying pressure on rudder pedals does not cause the wheels to be braked CAUTION FAILURE TO AP...

Page 660: ...on 1 June 22 2007 Rev 0 Figure 7 5 5 1 2 BRAKE SYSTEM 1 Reservoir 2 Vent 3 R H station master cylinders 4 Parking brake control knob 5 Parking brake valve 6 Drain 7 Pilot s station master cylinders 8 L H brake assembly 9 R H brake assembly PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 661: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 5 11 Edition 1 June 22 2007 Rev 14 Figure 7 5 5 2 2 BRAKE SYSTEM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 662: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 5 12 Edition 1 June 22 2007 Rev 0 Figure 7 5 6 PARKING BRAKE PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 663: ...entrifugal stage assembly to form a whole assembly Compressed air and fuel are mixed and sprayed into combustion chamber by fuel nozzles The mixture is first ignited by two spark igniter plugs then combustion continues as a result of air fuel mixture flow Gases resulting from combustion expand through a series of turbines The first one gas generator turbine drives compressor assembly and accessori...

Page 664: ...peller governor 2 Exhaust stub 3 Axial compressors 4 Accessory gearbox 5 FCU Fuel control unit 6 Oil to fuel heater 7 Input coupling shaft 8 Air intake 9 Centrifugal impeller 10 Combustion chamber 11 Compressor turbine 12 Power turbine 1st stage 13 Power turbine 2nd stage 14 Power turbine shaft PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 665: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 6 3 Edition 1 June 22 2007 Rev 0 Figure 7 6 1 2 2 POWERPLANT PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 666: ...eration 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 emergency fuel regulation lever Item 5 NOTE Thumbwheel for lever friction Item 4 Figure 7 6 2 ENGINE CONTROLS LEVERS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 667: ...KAGE WILL RESULT REVERSE MAY ONLY BE SELECTED WITH ENGINE RUNNING AND PROPELLER TURNING When engine is shutdown there is no oil pressure in the propeller and the feathering spring locks the Beta ring and the propeller reversing interconnect linkage on the engine Any rearward effort on the power control lever past the idle stop may damage or break the flexible control cable Propeller governor lever...

Page 668: ... gate To override idle gate raise lever and move it rearwards MAN OVRD emergency fuel regulation lever Emergency fuel regulation lever is normally in locked position In case of FCU or power lever failure it allows setting engine power manually Unlocking and locking are performed by pulling lever knob up NOTE The power available if the power lever fails will be limited by the position of the lever ...

Page 669: ...ws checking the overspeed valve for correct operation ENGINE LUBRICATION Engine oil is in a tank incorporated into the powerplant It ensures lubrication and engine cooling A cooler located on left side in engine compartment maintains oil temperature within limits Oil flow into the cooler is metered by a thermostatic valve Engine oil also supplies propeller governor and engine torquemeter Lubricati...

Page 670: ...d starting or flight air start with starter ON position for IGNITION switch is used in case of flight air start without starter In this configuration ignition unit is supplied permanently In any case IGNITION CAS message lights on as long as ignition unit is supplied Starter function Starting system consists of STARTER switch located on ENGINE START panel starter generator and ignition circuit Ref...

Page 671: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 6 9 Edition 1 June 22 2007 Rev 0 Figure 7 6 3 ENGINE STARTING PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 672: ... INERT SEP inverter located on DE ICE SYSTEM panel When inverter is set to ON an electric actuator activates vanes INERT SEP ON CAS message lights on when vanes have reached their maximum deflection and remains visible as long as switch remains ON Full deflection takes about 30 seconds EXHAUST SYSTEM Exhaust gases are evacuated through exhaust stubs located on sides of engine cowlings ENGINE ACCES...

Page 673: ...es reduction gear and power turbine and converts pressure difference into a voltage This voltage is transmitted to the G1000 system for display on the MFD under normal display conditions Propeller overspeed limiter Propeller overspeed limiter is installed on left side of the reduction gear box It prevents a propeller overspeed in case of main propeller governor failure Propeller overspeed limiter ...

Page 674: ... RPM Propeller governor allows feathering either by voluntary pilot action via the propeller governor lever or automatically in case of engine failure or shutdown Propeller reverse pitch allows reduced taxiing speed or landing roll Change from idle to reverse position is performed with power lever Refer to Paragraph ENGINE CONTROLS Propeller overspeed regulator tests Figure 7 3 6 PROP O SPEED TEST...

Page 675: ...rface a suction strainer and three level gages FUEL UNIT The fuel unit combines shut off valve tank selector and filter functions It is connected to the manual selector through a mechanical control The fuel filter is located in a bowl at the lower part of the unit It is fitted with a by pass valve a clogging indicator and a drain valve TANK MANUAL SELECTOR Figure 7 7 2 The tank manual selector is ...

Page 676: ...ressure switch 8 Pressure transmitter 9 Fuel jet 10 Main mechanical boost pump 11 Electric boost pump 12 Fuel filter 13 Filter clogging by pass valve 14 Filter clogging indicator 15 Fuel unit 16 Filter drain 17 Fuel return pipe 18 Filling port 19 NACA scoop 20 Tank vent valve 21 Fuel level gages 22 Tank drain valve 23 Check valve 24 Low level detector 25 Suction strainer 26 Fuel amplifier 27 Seque...

Page 677: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 7 3 Edition 1 June 22 2007 Rev 0 Figure 7 7 1 2 2 FUEL SYSTEM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 678: ...er controls the time during which the selected tank will operate This time varies depending on airplane conditions Airplane on ground tank is changed every minute and 15 seconds Pre MOD70 0402 28 Fuel sequencer evolution Airplane in flight tank is changed every ten minutes as long as a fuel low level CAS message does not appear When the first low level CAS message lights on the sequencer immediate...

Page 679: ... preferably choose the tank from which he wants to take fuel In all cases proper system operation is indicated by rotation of the manual selector Setting FUEL SEL switch to MAN position or setting manual selector to OFF position leads to system de activating and appearance of AUTO SEL CAS message AUTO SEL CAS message also lights on when order given by the sequencer has not been executed after 12 s...

Page 680: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 7 6 Edition 1 June 22 2007 Rev 0 Figure 7 7 2 MANUAL SELECTOR OF FUEL TANKS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 681: ...RIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 7 7 Edition 1 June 22 2007 Rev 10 Figure 7 7 3 FUEL CONTROL PANEL 1 Electric boost pump switch 2 Fuel selector 3 SHIFT push knob PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 682: ...pacitive type Fuel data are displayed in us gallons Three fuel level gages are installed in each tank The wing root side fuel level gage is equipped with a low level detector which leads to fuel low level CAS messages appearance when usable fuel quantity remaining in the concerned fuel tank is under about 9 us gal 34 Litres FUEL SYSTEM MONITORING Fuel system monitoring is ensured by CAS messages F...

Page 683: ...f fuel at the two drain valves of each tank and at the filter vent valve A red filter bypass flag on the fuel unit and visible from outside when an inspection door located on L H side under front baggage compartment is open indicates filter clogging A push button adjacent to the inspection door controls the illumination of a light provided to improve visibility of the clogging indicator This indic...

Page 684: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 7 10 Edition 1 June 22 2007 Rev 0 Figure 7 7 4 2 2 FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 685: ... outside through a door Connection relays main bus bar generator regulation and protection systems and control logic systems are grouped in electrical power center attached to front baggage compartment upper section Electrical system indicating is displayed on the GDU 1500 MFD and monitoring is ensured by CAS messages STARTER GENERATOR The starter generator is the main electrical power source It o...

Page 686: ...a power supply source when engine driven generators are stopped The battery is always connected to BATT BUS bus bar except when CRASH lever is pulled down Battery connection to main bus bar is controlled through SOURCE selector set to BAT position BAT OFF CAS message lights on when battery is isolated from the main bus and when main bus is supplied through another source GROUND POWER RECEPTACLE Th...

Page 687: ...aker panel NORM position is protected and locked by a cover Common power supply to both essential bus bars is protected by a fuse each bar being individually protected by a circuit breaker BATT BUS bar is directly connected to the battery it is protected by a fuse located in electrical power center NOTE The electrical distribution of bus bars is described in Figure 7 8 2 EMERGENCY USE With both ge...

Page 688: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 8 4 Edition 1 June 22 2007 Rev 1 Figure 7 8 1 ELECTRICAL DIAGRAM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 689: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 8 5 Edition 1 June 22 2007 Rev 13 Figure 7 8 2 1 3 ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 690: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 8 6 Edition 1 June 22 2007 Rev 6 Figure 7 8 2 2 3 ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 691: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 8 7 Edition 1 June 22 2007 Rev 12 Figure 7 8 2 3 3 ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 692: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 8 8 Edition 1 June 22 2007 Rev 6 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 693: ...us 2 circuit protection PANEL Instrument panel normal lighting protection LDG SIG Landing gear indicating system protection KEYBOARD Keyboard protection AUDIO 1 Audio control panel 1 protection AHRS 1 Attitude and Heading Reference System 1 protection XPDR 1 Transponder 1 protection ELT Emergency Locator Transmitter protection AURAL WARN Aural warnings protection Pre MOD70 0407 00D NP NG Tachomete...

Page 694: ...BIN Passenger s reading lamps protection INSTR Instruments lighting protection TORQUE Torque control protection IGNITION Powerplant ignition protection TAS TAS if installed protection WXR Weather radar if installed protection DATA LINK Data Link if installed protection BUS 3 OXYGEN PRESS Oxygen Pressure indication protection L WS DE ICE L H windshield deicing protection PITOT R STALL Pitot R and s...

Page 695: ...NG HANDBOOK Page 7 8 11 Edition 1 June 22 2007 Rev 13 Figure 7 8 3 3 3 CIRCUIT BREAKER PANEL typical arrangement NOTE If an additional equipment is installed its circuit breaker is installed on a free location PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 696: ...DOOR Ground power receptacle access door is not closed PROTECTION SAFETY Figure 7 8 4 The electrical power center provides systems protection in case of overvoltage coming from the starter generator the stand by generator or the ground power receptacle short circuit in starter generator feeder starter generator undervoltage In case of disconnection of starter generator or stand by generator follow...

Page 697: ...50 PILOT S OPERATING HANDBOOK Page 7 8 13 Edition 1 June 22 2007 Rev 6 Figure 7 8 4 ELECTRICAL CONTROL 1 MAIN reset knob 2 ST BY reset knob 3 Crash lever 4 SOURCE selector 5 GENERATOR selector PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 698: ...per panel A warning light is incorporated in each switch to indicate proper operation of used landing light The Pulse lite system if installed enables the pilot to control landing light flashing to be seen by the control tower or in heavy traffic areas Taxi light The taxi light is attached to the nose gear it is controlled by TAXI switch located on upper panel A warning light is incorporated in th...

Page 699: ...TEM panel Figure 7 13 1 FWD compartment light The dome light of the FWD compartment has two positions the first allows automatic illumination via the switch located in the upper section of the door frame the second maintains the dome light permanently off regardless of the door position Fuel unit compartment light The lighting of the fuel unit compartment allows improving the visibility of the clo...

Page 700: ...ion 1 June 22 2007 Rev 6 Figure 7 8 5 1 2 EXTERNAL LIGHTING CONTROLS 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 701: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 8 17 Edition 1 June 22 2007 Rev 6 Figure 7 8 5 2 2 EXTERNAL LIGHTING CONTROLS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 702: ...out after 3 minutes If the CRASH lever is up there is no access lighting automatic cut out Cabin lighting Cabin lighting consists of two swiveling floodlights for front seats six individual floodlights for rear passenger seats and the baggage compartment R H dome light Each floodlight is controlled by a push button located near The floodlight above the table is controlled by two switches which are...

Page 703: ... visor lighting tubes and or instrument integrated lighting failure A rheostat located on the cockpit overhead panel controls emergencylighting operation and intensity Forward rotation of control knob allows changing from OFF position to minimum lighting then increasing lighting to maximum brightness Map reading light illumination The illumination of the map reading lights located on control wheel...

Page 704: ...NTERNAL LIGHTING CONTROLS 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 705: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 8 21 Edition 1 June 22 2007 Rev 8 Figure 7 8 6 2 2 INTERNAL LIGHTING CONTROLS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 706: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 8 22 Edition 1 June 22 2007 Rev 6 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 707: ...ller the GASC which receives information from the sensors within the sub systems the human interfaces set in the airplane The GASC elaborates the proper commands to the sub systems actuators and indication or warning elements GAS controls are located on the ECS panel on the left side of the right control wheel a control panel above the arm rest of the L H side passenger s seat The pilot monitorsth...

Page 708: ... the GASC To adjust the temperature of the bleed air The bleed air outlet temperature control is ensured by the By Pass Valve BPV in association with the Main Heat Exchanger MHX Based on pilot s or passengers CABIN TEMP C selector position the GASC computes the appropriate cabin air inlet temperature target and compares it to the actual measured inlet temperature in order to set the BPV position T...

Page 709: ...t cabin altitude is reported in the information display on the MFD as ALT SEL FT The GASC controls the OFV through a torque motor on the valve Cabin altitude management In order to maximize comfort during all phases of flight the cabin altitude is automatically computed by the GASC using flight parameters such as aircraft altitude altitude rate of change sent by the avionics The cabin altitude rat...

Page 710: ...inlet overtemperature or a BDPS or FCSOV failure is detected BLEED OFF amber CAS message is displayed 45 seconds after landing if a fault on the Overheat Thermal Switch was detected by the GASC during flight CABIN ALTITUDE red CAS message indicates that the cabin altitude is over 10000 ft CABIN DIFF PRESS red CAS message indicates that the cabin differential pressure is over 6 4 psi 441 mb The DUM...

Page 711: ...heating and cooling functions The ECS consists of two independent air circuits Heating circuit controlled by Temperature Conditioning System TCS Cooling circuit controlled by Vapor Cycle Cooling System VCCS Heating circuit The TCS regulates hot air coming from the bleed air system also used for pressurization and mixes it with the recirculating cabin air at the Mixing Ejector MIXEJ in order to low...

Page 712: ...t equipped with swivelling and adjustable air outlets ports located on the floor between the cabinets and the intermediate passenger s seats System operation See Figure 7 9 3 and paragraph Air temperature management ECS control panel selection If the AIR COND switch is set to OFF Before GASC software evolution Pre MOD70 0689 21 Temperature is set by default by the GASC to 23 C After GASC software ...

Page 713: ...itches from the P2 5 to the P3 bleed port to increase the temperature and flow rate of the incoming bleed air Except in the case of very cold environmental conditions this switching is inhibited below 25000 ft All ECS Service required advisory message appears on the MFD when the GASC detects a faulty operation of ECS system NOTE If ECS Service required advisory message appears Inform maintenance d...

Page 714: ... knob and pull out NOTE Reduce the cabin differential pressure if necessary by depressurizing the cabin to be able to operate the EMERGENCY RAM AIR control knob System protection Power for the ECS is supplied by the BUS 2 bar and is protected by the AIR COND breaker Three fans are supplied by BUS 4 bar and protected respectively by following breakers COND FAN CABIN FAN and COCKPIT FAN The ground f...

Page 715: ...L selector to CABIN and Air temperature expectations Cockpit panel selection Cabin panel selection CABIN TEMP C FAN SPEED CABIN TEMP C FAN SPEED Cockpit area Warm Cabin area Hot Results Mixed Bleed Air Circuit Warm air is distributed to both cockpit and cabin More warm air is directed to cabin due to the greater temperature demand Cold Air Circuit Not active as no CABIN TEMP C selector is set belo...

Page 716: ...erature demand Cold Air Circuit Not active as no CABIN TEMP C selector is set below 22 C FANS select OFF Selecting a FAN speed will reduce cabin air temperature Cockpit area Warm Cabin area Cool Results Mixed Bleed Air Circuit Warm air is distributed to both cockpit andcabin Morewarm air is directedto cockpit duetothe greater temperature demand Cold Air Circuit Cabin CABIN TEMP C selector is set b...

Page 717: ... air to the desired temperature Cold Air Circuit Both cockpit and cabin CABIN TEMP C selectors are set below 22 C resulting in both cockpit and cabin air conditioning systems supplying their respective area Cockpit and cabin FANS Select 1 or more to circulate the cooled air Cockpit area Cool Cabin area Warm Results Mixed Bleed Air Circuit Warm air is distributed to both cockpit and cabin More warm...

Page 718: ...ually to the cockpit and cabin Only the cockpit CABIN TEMP C and FAN SPEED selectors inputs are used by the GASC for air temperature management Air temperature expectations Cockpit panel selection Cabin panel selection CABIN TEMP C FAN SPEED CABIN TEMP C FAN SPEED Cockpit area Warm Cabin area Results Mixed Bleed Air Circuit Warm air is distributed equally to both cockpit and cabin The temperature ...

Page 719: ...e 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 Cold Air Circuit Cockpit CABIN TEMP C selector is set below 22 C resulting in both cockpit and cabin air conditioning systems to supply their respective area Cockpit FAN select 1 or more ...

Page 720: ...abin panel selection CABIN TEMP C FAN SPEED CABIN TEMP C FAN SPEED Cockpit area Cabin area Results Mixed Bleed Air Circuit Air is distributedto thewindshields and cockpit side windows at a fixed temperature regardless of CABIN TEMP C selector settings Cold Air Circuit Inhibited when DEFOG is selected FANS will continue to operate if selected to 1 or more for air circulation PIM DO NOT USE FOR FLIG...

Page 721: ...Out flow valve OFV 9 Safety valve SFV 10 Condenser fan 11 Condenser 12 High pressure switch 13 Drier filter 14 Cabin fan 15 Cabin evaporator 16 Cabin blown temperature sensor CBBTS 17 Cabin thermostatic valve 18 Low pressure switch 19 Cabin pressurization control panel CPCP 20 ECS panel 21 Cockpit thermostatic valve 22 Cockpit fan 23 Cockpit evaporator 24 Cockpit blown temperature sensor CKBTS Fig...

Page 722: ...h 33 Differential pressure switch 34 By pass valve BPV 35 Cabin altitude alarm switch 36 Emergency air supply system RAM AIR 37 Main heat exchanger MHX 38 Ground fan GF 39 Flow control shut off valve FCSOV 40 Bleed differential pressure sensor BDPS 41 Compressor 42 Shut off valve SOV 43 Overheat thermal switch OTSW 44 Non return valve NRV 45 Intermediate port pressure sensor IPPS 46 Cabin pressure...

Page 723: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 9 17 Edition 1 June 22 2007 Rev 14 Figure 7 9 2 3 3 Global Air System PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 724: ...7 9 3 1 2 GAS controls 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 C selector cabin 10 Cabin pressurization control panel PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 725: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 9 19 Edition 1 June 22 2007 Rev 14 Figure 7 9 3 2 2 GAS controls PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 726: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 9 20 Edition 1 June 22 2007 Rev 14 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 727: ...ature Pressure Dry and use limit pressures are maximum pressure 1850 PSIG 127 bars at 70 F 21 C Evolution of this pressure according to the outside temperature is given in Section 8 Figure 8 7 4 as well as on a placard on the inside of the cylinder service door minimum pressure 217 PSIG 15 bars The oxygen cylinder head is equipped with a hand controlled isolation valve to permit cylinder installat...

Page 728: ...TING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 10 2 Edition 1 June 22 2007 Rev 13 Figure 7 10 1 EMERGENCY OXYGEN SYSTEM 1 Microphone switch 2 OXYGEN switch 3 PASSENGERS OXYGEN switch PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 729: ...n walls aft of the front seats Permanently connected to the oxygen system they are equipped with a micro controlled by the switch NORMAL MASK micro inverter under cover located on the instrument panel near the pilot s control wheel with a three position selector NORMAL 100 and EMERGENCY and with a push button PRESS TO TEST The proper flow is signaled by a flow indicator blinker into the oxygen tub...

Page 730: ...46 529 1 1 759 736 713 691 668 646 623 1 2 885 856 828 799 771 743 715 1 3 1010 976 941 907 873 839 806 1 4 1137 1096 1056 1015 975 935 897 2 0 1037 1001 965 930 894 859 825 2 1 1164 1122 1080 1038 997 956 916 2 2 1289 1241 1192 1144 1097 1050 1004 2 3 1416 1361 1306 1252 1198 1145 1093 2 4 1541 1480 1418 1357 1297 1238 1180 Values in PSIG Conditions 1 4 minutes from 31000 to 15000 ft All equipmen...

Page 731: ...5 918 882 846 1 3 1513 1240 1192 1144 1097 1050 1004 1 4 1513 1452 1392 1333 1275 1217 1161 2 0 992 958 925 891 858 825 793 2 1 1215 1170 1125 1081 1037 994 952 2 2 1439 1382 1326 1270 1215 1161 1108 2 3 1662 1593 1525 1457 1391 1326 1262 2 4 1888 1807 1725 1645 1567 1490 1415 Values in PSIG Conditions 1 Flight above 15000 ft All equipment used 2 1 hour usage by each pilot and passenger 3 Plus 1 h...

Page 732: ...1 770 1 3 961 929 896 864 833 801 770 1 4 961 929 896 864 833 801 770 2 0 992 958 925 891 858 825 793 2 1 1333 1282 1231 1181 1131 1083 1035 2 2 1333 1282 1231 1181 1131 1083 1035 2 3 1333 1282 1231 1181 1131 1083 1035 2 4 1333 1282 1231 1181 1131 1083 1035 Values in PSIG Conditions 1 Flight under 15000 ft 2 90 minutes usage by each pilot and one passenger 3 Plus 30 minutes usage by each pilot at ...

Page 733: ...ks 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 Noise reduction function operates when the switch located on O2 connecting line is set to ON Figure 7 10 1 Noise reduction switch PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 734: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 10 8 Edition 1 June 22 2007 Rev 14 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 735: ... normal static system When selector is on alternate position pulled rearwards static pressure is picked from a port located in airplane rear fuselage two separate dynamic pressure systems supplying the airspeed indicator system and air data computers STATIC PRESSURE SYSTEMS Primary systems Two dual static ports one on either side of the fuselage tail part supply a dual system routed towards the co...

Page 736: ...irspeed 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 13 Instrument panel 14 Dynamic system drain 15 Pitot R 16 Rear pressure bulkhead 17 Static port 18 Emergency static port 19 Static port PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 737: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 11 3 Edition 1 June 22 2007 Rev 8 Figure 7 11 1 2 2 AIR DATA SYSTEM Pre MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 738: ...em When selector is on alternate position pulled rearwards static pressure is picked from a port located in airplane rear fuselage two separate dynamic pressure systems supplying the electronic standby indicator and air data computers STATIC PRESSURE SYSTEMS Primary systems Two dual static ports one on either side of the fuselage tail part supply a dual system routed towards the cockpit System 1 p...

Page 739: ...tronic Standby Indicator ESI 2000 4 GDC 74B ADC 5 GDC 74B ADC 6 FWD pressure bulkhead 7 Static system drain 8 Static system drain 9 Static system drain 10 Emergency static system drain 11 Emergency static valve Normal Alternate 12 Instrument panel 13 Dynamic system drain 14 Pitot R 15 Rear pressure bulkhead 16 Static port 17 Emergency static port 18 Static port PIM DO NOT USE FOR FLIGHT OPERATIONS...

Page 740: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 11 6 Edition 1 June 22 2007 Rev 8 Figure 7 11 2 2 2 AIR DATA SYSTEM Post MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 741: ...stalled under the L H wing The second one is installed under the R H wing The first one supplies the airspeed indicator and one ADC Post MOD70 0335 34 ESI 2000 One heated pitot probe is installed under the L H wing The second one is installed under the R H wing The first one supplies the electronic standby indicator and one ADC All The second one supplies the other ADC Both lines incorporate a dra...

Page 742: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 11 8 Edition 1 June 22 2007 Rev 8 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 743: ...effect A relief valve fixed in cabin to frame C2 maintains the vacuum for pressurization and instrument systems In case of pressure drop a pressure switch installed in the system indicates the failure by causing the VACUUM LOW CAS message to light on STAND BY ATTITUDE INDICATOR The stand by attitude indicator equipped with a slip indicator provides a visual reference of actual airplane flight atti...

Page 744: ...IPTION Page 7 12 2 Edition 1 June 22 2007 Rev 8 Figure 7 12 1 1 2 VACUUM SYSTEM Pre MOD70 0335 34 ESI 2000 1 Pressure regulator 2 Ejector 3 Valve 4 Regulating and relief valve 5 Pressure switch 6 Failure CAS message PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 745: ...SECTION 7 DESCRIPTION TBM 850 PILOT S OPERATING HANDBOOK Page 7 12 3 Edition 1 June 22 2007 Rev 8 Figure 7 12 1 2 2 VACUUM SYSTEM Pre MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 746: ...essed air is taken from the powerplant The air flow is regulated before going into the ejector which creates necessary vacuum by venturi effect A relief valve fixed in cabin to frame C2 maintains the vacuum for pressurization system In case of pressure drop a pressure switch installed in the system indicates the failure by causing the VACUUM LOW CAS message to light on ELECTRONIC STANDBY INDICATOR...

Page 747: ...DBOOK Page 7 12 5 Edition 1 June 22 2007 Rev 8 Figure 7 12 1A 1 2 VACUUM SYSTEM Post MOD70 0335 34 ESI 2000 1 Pressure regulator 2 Ejector 3 Valve 4 Regulating and relief valve 5 Pressure switch 6 Failure CAS message PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 748: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 12 6 Edition 1 June 22 2007 Rev 8 Figure 7 12 1A 2 2 VACUUM SYSTEM Post MOD70 0335 34 ESI 2000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 749: ...strument panel WING AND EMPENNAGE DEICING A pneumatic deice system assures protection of wing leading edges horizontal stabilizer elevator horns and vertical stabilizer The system automatically cycles when AIRFRAME DE ICE switch is set to ON The 67 second cycle breaks down in two inflation cycles a first cycle induces inflation of leading edges deicer boots in wing central and outboard sections th...

Page 750: ...ed by the WINDSHIELD switch When the switch is positioned to ON the controller supplies the heating resistors the windshield temperature is monitored by probe 1 When the temperature reaches 45 C 113 F the controller cuts the electrical supply to the heating resistors and resumes supply when the temperature falls below 30 C 86 F The cycle continues as long as the switch remains set to ON In the eve...

Page 751: ... must be used even during flight into non icing conditions The system condition messages PITOT NO HT L or R PITOT HT ON L or R STALL HEAT ON or STALL NO HEAT are displayed on the GDU 1500 MFD CAS window Refer to the GARMIN G1000 Pilot s Guide for further details NOTE Correct operation of the audible stall warning may be altered by severe or prolonged icing TURBINE AIR INLET PROTECTION Operation an...

Page 752: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 13 4 Edition 1 June 22 2007 Rev 1 Figure 7 13 1 DEICING CONTROL AND CHECK PANEL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 753: ... 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 bar a limited number of equipment One single COM engine monitoring data and fuel indicating functions are available The L H station PFD only displays a reduced quantity of information PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 754: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 7 DESCRIPTION Page 7 14 2 Edition 1 June 22 2007 Rev 0 Figure 7 14 1 AVIONICS MASTER 1 AVIONICS MASTER switch PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 755: ...the alarms speaker All NOTE The audible stall warning may be altered by severe or prolonged icing STATIC DISCHARGERS As an aid in flight static dischargers are installed to improve radio communications during flight by reducing interference from dust or various forms of precipitations rain snow or ice crystals Under these conditions the build up and discharge of static electricity from the trailin...

Page 756: ...er drawer of the R H cabinet inserted in foam Post MOD70 0336 26 The fire extinguisher is located on R H front station side panel All A pressure gage allows checking the fire extinguisher condition Follow the recommendations indicated on the extinguisher AUTOPILOT Autopilot control panel is located above the GDU 1500 MFD Refer to Section 2 Limitations of this Pilot s Operating Handbook and to GARM...

Page 757: ...ches is strictly advisory There is no guarantee that stepdown fix altitudes will be honored and the crew must level off at the MDA if the runway is not visible LNAV approaches may be executed with or without SBAS and advisory vertical guidance is dependent on sufficient GPS vertical error estimates rather than SBAS vertical integrity LNAV V approaches do not downgrade in general because they do no...

Page 758: ...d automatically upon loss of SBAS or GPS approach alarm limits being exceeded depending on the approach service level that has been loaded in the flight plan and activated This automatic downgrade is annunciated to the pilot through an APR DWNGRADE advisory message and a change in the annunciated service level in the HSI As the APR DWNGRADE advisory message may not be triggered under certain circu...

Page 759: ...TAS or SVS system refer to Section 9 Supplements Other optional equipment such as radio altimeter or chartview system are described in the GARMIN G1000 Pilot s Guide NOTE Refer to Section 2 Limitations for chartview system operating limitations EMERGENCY LOCATOR TRANSMITTER The airplane is equipped with an emergency locator transmitter which enables to locate it in case of distress It is located i...

Page 760: ...ransmitter is transmitting A red indicator light located on R H side of locator transmitter switch and a buzzer located in the fuselage rear section indicate the emergency locator transmitter is transmitting Reset after an inadvertent activation 1 Set remote control switch or ELT switch to ON a The ELT keeps on transmitting emergency signal b On remote control box red indicator light flashes c On ...

Page 761: ... the pilot the emergency locator transmitter is transmitting A red indicator light located above locator transmitter switch and a buzzer located in the fuselage rear section indicate the emergency locator transmitter is transmitting Reset after an inadvertent activation 1 Set remote control switch or ELT switch to ON a The ELT keeps on transmitting emergency signal b On remote control box red indi...

Page 762: ...ar 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 For the system description and its utilization refer to GARMIN G1000 Pilot s Guide PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 763: ...8 2 IDENTIFICATION PLATE 8 2 1 8 3 PUBLICATIONS 8 3 1 8 4 INSPECTION PERIODS 8 4 1 8 5 ALTERATIONS OR REPAIRS 8 5 1 8 6 GROUND HANDLING 8 6 1 TOWING 8 6 1 PARKING 8 6 1 TIE DOWN 8 6 3 JACKING 8 6 3 LEVELING 8 6 3 FLYABLE STORAGE 8 6 5 LONG TERM STORAGE WITHOUT FLYING 8 6 5 8 7 SERVICING 8 7 1 MAINTENANCE 8 7 1 ENGINE OIL 8 7 1 FUEL 8 7 2 LANDING GEAR 8 7 7 OXYGEN 8 7 8 PIM DO NOT USE FOR FLIGHT OP...

Page 764: ... 8 2 PROPELLER CARE 8 8 2 ENGINE CARE 8 8 2 INTERIOR CARE 8 8 2 8 9 UTILIZATION BY COLD WEATHER 0 C to 25 C OR VERY COLD WEATHER 25 C to 40 C 8 9 1 Post MOD 70 0315 25 8 10 PREPARATION OF THE AIRPLANE EQUIPMENT AND FURNISHINGS 8 10 1 CONVERSION OF 6 SEAT ACCOMMODATION INTO 4 SEAT ACCOMMODATION 8 10 1 CONVERSION OF 4 SEAT ACCOMMODATION INTO 6 SEAT ACCOMMODATION 8 10 5 ADDITIONAL CONFIGURATIONS 8 10...

Page 765: ...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 It is recommended that a planned schedule of lubrication and preventive maintenance be followed and that this schedule be tailored to the climatic or flying conditions to which the airplane is subjected For this see Ma...

Page 766: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 1 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 767: ...ON 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 768: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 2 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 769: ... Pilot s Guide and supplemental data covering optional equipment installed in the airplane refer to Section 9 Supplements and pilot s guides In addition the owner may purchase the following Maintenance Manual Wiring Manual Illustrated Parts Catalog Bilingual Illustrated Tool and Equipment Manual Catalog of Service Bulletins Service Letters and Service Information Letters CAUTION PILOT S OPERATING ...

Page 770: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 3 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 771: ...r to regulations in force in the certification country for information concerning preventive maintenance to be carried out A maintenance Manual must be obtained prior to performing any preventive maintenance to make sure that proper procedures are followed Maintenance must be accomplished by licensed personnel PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 772: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 4 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 773: ...Rev 0 8 5 ALTERATIONS OR REPAIRS It is essential that the Airworthiness authorities be contacted prior to any alterations or repairs on the airplane to make sure that airworthiness of the airplane is not violated Alterations or repairs must be accomplished by licensed personnel PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 774: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 5 2 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 775: ... with an integrated towing fitting CAUTION DO NOT TOW THE AIRPLANE WHEN CONTROLS ARE SECURED WHEN TOWING WITH A VEHICLE DO NOT EXCEED THE NOSE GEAR TURNING ANGLE AS THIS MAY RESULT IN DAMAGE TO THE GEAR AND STEERING MECHANISM see Figure 8 6 1 PARKING When parking the airplane head it into the wind Do not set the parking brake when brakes are overheated or during cold weather when accumulated moist...

Page 776: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 6 2 Edition 1 June 22 2007 Rev 0 Figure 8 6 1 TURNING ANGLE LIMITS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 777: ...over tie downs wheel chocks and control lock are recommended In severe weather and high wind conditions tie the airplane down as outlined in the following paragraph TIE DOWN Proper tie down procedure is the best protection against damage to the airplane by gusty or strong winds To tiedown the airplane securely proceed as follows Install control lock see Figure 8 6 2 Chock all wheels Tie sufficient...

Page 778: ... PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 6 4 Edition 1 June 22 2007 Rev 8 Figure 8 6 2 CONTROL LOCK DEVICE Pre MOD70 0279 00 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 779: ...ION 8 HANDLING SERVICING AND MAINTENANCE TBM 850 PILOT S OPERATING HANDBOOK Page 8 6 5 Edition 1 June 22 2007 Rev 8 Figure 8 6 2A CONTROL LOCK DEVICE Post MOD70 0279 00 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 780: ... prevent the electrolyte from freezing in cold weather Close oxygen cylinder isolation valve Storage from 8 to 28 days Engine according to Maintenance Manual P W C Airplane fueling Keep fuel tanks full to minimize condensation in the tanks Keep the battery fully charged to prevent the electrolyte from freezing in cold weather Close oxygen cylinder isolation valve Battery remaining in the airplane ...

Page 781: ...NT VISCOSITIES OR SPECIFICATIONS OF OIL AS THEIR DIFFERENT CHEMICAL STRUCTURE CAN MAKE THEM INCOMPATIBLE Specification Nominal Viscosity Specification NATO Code 5cSt MIL PRF 23699G O 156 STD O 154 HTS Figure 8 7 1 RECOMMENDED ENGINE OIL TYPES Reference Service Bulletin P W C No 14001 at the latest revision Oil capacity System total capacity 12 7 Quarts 12 Litres oil cooler included Usable capacity...

Page 782: ...vel may result in high consumption rate with the oil exiting through the accessory gearbox breather CAUTION WHEN FILLER CAP ASSEMBLY IS INSTALLED AND LOCKED NO MOVEMENT IS ALLOWED FUEL Total capacity each tank 150 5 us gal 570 l NOTE To minimize condensation it is recommended that airplane be refueled after each flight respecting weight and balance limits CAUTION NEVER FLY THE AIRPLANE WITH CONTAM...

Page 783: ... THE AIRPLANE DURING FUELING DO NOT ALLOW OPEN FLAME OR SMOKING IN THE VICINITY OF THE AIRPLANE WHILE FUELING NOTE Use of AVGAS must be recorded in engine module logbook US Specification US French Specification FR English Specification UK NATO Code ASTM D1655 JET A ASTM D1655 JET A1 ASTM D1655 JET B AIR 3405C Grade F35 DERD 2494 Issue 9 F35 without additive MIL DTL 5624 Grade JP 4 AIR 3407B DERD 2...

Page 784: ...small amounts of water emulsified can precipitate from the fuel stream and freeze in sufficient quantities to induce partial icing of the engine fuel system While these conditions are quite rare and will not normally be a problem to owners and operators they do exist in certain areas of the world and consequently must be dealt with when encountered Therefore to alleviate the possibility of fuel ic...

Page 785: ...TIONING Prolonged storage of the airplane will result in a water buildup in the fuel which leeches out the additive An indication of this is when an excessive amount of water accumulates in the fuel tank sumps The concentration can be checked using a differential refractometer It is imperative that the technical manual for the differential refractometer be followed explicitly when checking the add...

Page 786: ...M PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 7 6 Edition 1 June 22 2007 Rev 0 Figure 8 7 3 ADDITIVE MIXING RATIO EGME or DIEGME PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 787: ...r shock absorbers Fill with hydraulic fluid AIR 3520 B MIL H5606E inflate with nitrogen to 160 psi 11 bars Hydraulic system Check every 100 hours and service with AIR 3520 B MIL H5606E hydraulic fluid Brakes Service as required with AIR 3520 B MIL H5606E hydraulic fluid NOTE A higher inflation pressure has to be applied to tires and shock absorbers when in very cold conditions refer to Chapter 8 9...

Page 788: ...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 Figure 8 7 4 Charge pressure chart PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 789: ...RE HAZARD USE NO OIL OR GREASE WITH THE OXYGEN REPLENISHMENT EQUIPMENT ALWAYS OPEN SHUT OFF VALVE SLOWLY TO AVOID GENERATING HEAT AND REPLENISH THE SYSTEM SLOWLY AT A RATE NOT EXCEEDING 200 PSIG 13 7 BARS PER MINUTE CAUTION REPLENISHMENT OF THE OXYGEN SYSTEM SHOULD ONLY BE CARRIED OUT BY QUALIFIED PERSONNEL NOTE The cylinder full charge isassured for a pressure of 1850 PSIG 127 bars at a temperatu...

Page 790: ... and fill to the correct pressure if necessary Release the pressure in the oxygen supply hose and disconnect from the charging valve Install the cap on the charging valve Make sure all the tools and materials are removed and the work area is clean and free from debris Close the oxygen service door Passengers masks repacking instructions WARNING DO NOT USE OIL OR OTHER PETROLEUM BASED LUBRICANTS ON...

Page 791: ...ephiran Chloride Scott Aviation P N 00 2572 or with disinfection cleaners EROS P N SAN50 After disinfecting and thoroughly drying the mask lightly dust the outside of the facepiece with Neo Novacite powder Scott Aviation P N 00 736 Contamination can be removed with mild soap and water solution Fold headstrap into facepiece Pull lanyard cord out to side of facepiece so that it does not interfere wi...

Page 792: ...2 Edition 1 June 22 2007 Rev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 793: ...ERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyard pin into corresponding check valve Place mask facepiece first in deployment container Make sure that oxygen tubing and lanyard cord are free to deploy and are not caught between the container and lid Close and latch...

Page 794: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 7 14 Edition 1 June 22 2007 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 795: ...BT CONCERNING A PRODUCT DO NOT USE IT DURING CLEANING OPERATION AVOID WEARING OBJECTS SUCH AS RING WATCH BRACELET AND EXERCISE CARE TO PREVENT BUTTONS BUCKLES AND ANY HARD OBJECTS FROM TOUCHING THE WINDSHIELD AND THE WINDOWS ADHESIVE TAPES OTHER THAN MINNESOTA 3M TYPE 670 SHALL NOT BE USED ON ACRYLIC SURFACES NEVER USE BUFFING MACHINES AS EXCESSIVE FORCES OR SPEEDS MIGHT PRODUCE REDHIBITORY DEFECT...

Page 796: ...ure long blade life Small nicks on the propeller particularly near the tips and on the leading edges should be dressed out as soon as possible since these nicks produce stress concentrations and if not removed may result in cracks Never use an alkaline cleaner on the blades remove grease and dirt ENGINE CARE Refer to Maintenance Manual for the procedures to follow INTERIOR CARE To remove dust and ...

Page 797: ...nd engine cowlings seals as well as the leading edge deicers 2 Apply engine oil on the engine cowling latches 3 Inflate main landing gear shock absorbers to 247 psi 17 bars at a room temperature of 15 C 4 Position a 0 59 in 15 mm shim at the bottom of the piston tube and against forward landing gear half fork to reduce shock absorber travel Refill with hydraulic liquid Remove the shim and inflate ...

Page 798: ...g table 1 during operation in cold weather only OAT C 40 30 20 10 15 P R E Main landing gear shock absorber 189 13 196 13 5 203 14 218 15 247 17 E S S U R Nose gear shock absorber 102 7 109 7 5 116 8 123 8 5 138 9 5 R E S Main landing gear tire 144 9 96 144 9 96 130 8 96 130 8 96 130 8 96 psi bars Nose gear tire 94 6 5 94 6 5 102 7 102 7 102 7 Table 1 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 799: ...horized 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 However the pilot must ensure that he gets all necessary authorizations from his regulatory authority 1 CONVERSION OF 6 SEAT ACCOMMODATION INTO 4 SEAT ACCOMMODATION Fig...

Page 800: ...krest tilting handle is located behind backrest c Clear the carpet from under the seat to facilitate moving in rails d Unlock seat using seat tilting handle 1 and tilt it forward e Hold the seat in tilted position and unscrew quick links 7 of strap 9 located under L H seatpan NOTE This operation is specific to L H seat f Pull up and hold L H and R H rings 2 and turn knobs 8 by 90 in order to relea...

Page 801: ...Remove the seat g Install backrest bottom upholstery 25 CAUTION IN ORDER TO PREVENT DEFLECTORS DAMAGE IT IS NECESSARY TO REMOVE THEM 2 Remove deflector 34 maintained with Velcro type strap 3 If necessary remove the cabin central carpet NOTE If one of two cargo nets must be installed it is necessary to use the carpet with appropriate cuttings E Removal of a cabinet NOTE This operation must be carri...

Page 802: ... direction frontwards the L H seat must be installed on the right and the R H seat on the left in order to have the armrest on aisle side a Pull backrest bottom upholstery 25 to remove it b Clear the carpet from seat area to facilitate moving in rails c Position the seat and put lock 22 near the color mark 37 made on rail bottom on aisle side NOTE The color mark 37 in the rail is aligned with red ...

Page 803: ...ONVERSION OF 4 SEAT ACCOMMODATION INTO 6 SEAT ACCOMMODATION Figures 8 10 1 8 10 2 8 10 3 and 8 10 4 A Tools and consumable materials Seat protective covers B Preparation 1 Make sure the SOURCE selector is set to OFF 2 If installed remove the cargo net 3 Remove intermediate seats refer to Paragraph 1 D 4 Remove the deflectors 34 maintained with Velcro type strap 5 If necessary remove the cabin cent...

Page 804: ...work area is clean and free from debris 2 Clear the carpet from seat area to facilitate moving in rails 3 Check that knobs 8 maintain locks 3 in up position 4 Position the seat fold it forward refer to Detail B and insert pads 4 into rail 5 apertures 5 Move the seat so that locks 3 are in front of the color mark made on rail bottom 6 Pull up and hold L H and R H rings 2 and turn knobs 8 by 90 in o...

Page 805: ...ny combinations of accommodations are authorized with seats rear and intermediate by pilot or service centers and cabinet s by service centers only However the pilot must ensure that he gets all necessary authorizations from his regulatory authority NOTE To remove or install these elements use Paragraph 1 or 2 refer to Table 1 NOTE After these operations determine weight and balance with the new i...

Page 806: ...ERVICING AND MAINTENANCE Page 8 10 8 Edition 1 June 22 2007 Rev 9 Figure 8 10 1 1 2 Removal Installation of rear seat 1 Seat tilting handle 2 Ring 3 Lock 4 Pad 5 Rail 6 Backrest tilting handle 7 Quick link 8 Knob 9 Strap PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 807: ...ION 8 HANDLING SERVICING AND MAINTENANCE TBM 850 PILOT S OPERATING HANDBOOK Page 8 10 9 Edition 1 June 22 2007 Rev 9 Figure 8 10 1 2 2 Removal Installation of rear seat PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 808: ... 8 HANDLING SERVICING AND MAINTENANCE Page 8 10 10 Edition 1 June 22 2007 Rev 9 Figure 8 10 2 Removal Installation of intermediate seat 21 Locking handle 22 Lock 23 Pad 24 Rail 25 Backrest bottom upholstery PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 809: ...50 PILOT S OPERATING HANDBOOK Page 8 10 11 Edition 1 June 22 2007 Rev 9 Figure 8 10 3 Cabin comfort Installation of blanking plugs and deflector 31 Blanking plug 32 Blanking plug 33 Blanking device assy 34 Deflector PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 810: ... SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 10 12 Edition 1 June 22 2007 Rev 9 Figure 8 10 4 Cabin comfort Installation of deflector 34 Deflector 35 Deflector hole 36 Red mark 37 Color mark PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 811: ...other than that for which it is supplied nor may information contained in it be disclosed to unauthorized persons It must not be reproduced nor transmitted in any form in whole or in part without permission in writing from the owners of the Copyright Information in this document is subject to change without notice 2019 AEROSPACE All rights reserved DAHER AEROSPACE Customer care 65921 TARBES CEDEX ...

Page 812: ...luding air conditioning and pressurization installed on airplane 9 Chapter 25 Equipment and furnishings modified New cabin furnishings and carpet installed on airplane 16 Addition of sub chapter Aural warning 25 Chapter 35 Oxygen modified New oxygen system installed on airplane 20 21 Correction or addition of weights and arms 1 10 to 15 17 to 19 22 to 24 26 to 32 Presentation terminology or text m...

Page 813: ...MENTS Edition 1 of June 22 2007 Revision 2 of December 15 2007 Pages Description 0B List of amendments 2 Addition of the list of critical RVSM equipment 20 Removal of modification MOD70 0160 34A with cross reference to SB70 120 34 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 814: ...08 Pages Description 0C List of amendments 10 Modification of OPT70 25030 option version OPT70 25030A replaced by OPT70 25030C valid for airplanes equipped with G1000 system 11 Addition of option MOD70 0153 25C ELT KANNAD 406 AF 0D Minor modifications text moving presentation or terminology PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 815: ...ENDMENTS Edition 1 of June 22 2007 Revision 4 of March 31 2008 Pages Description 0D List of amendments 4 11 22 24 Addition of optional equipment 9 10 17 thru 19 22 23 Correction of data concerning some already listed equipment PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 816: ...dition 1 June 22 2007 Rev 5 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 0E List of amendments PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 817: ...10 Pages Description Title Copyright update 0F List of amendments 10 Addition of option OPT70 25030D ELT C406 1 11 Suppression of option MOD70 0153 25C ELT KANNAD 406 AF 22 Addition of option MOD70 0270 34 radioaltimeter 23 Addition of option MOD70 0258 00 TAS system GTS 820 24 Text moving PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 818: ... due to incorporation of MOD70 0315 25 TBM Elite Edition 6 pax club or 4 pax cargo TR11 11 Relocation of portable fire extinguisher unit MOD70 336 26 12 Suppression of Trim and Flap indicator equipment 19 20 Modification due to validity for bulb strobe nav lights and led strobe nav lights 21 22 Addition of validities due to incorporation of MOD70 0335 34 ESI 2000 9 23 to 32 Minor modifications ter...

Page 819: ... 22 2007 Rev 8 AMENDMENTS Edition 1 of June 22 2007 Revision 8 of March 1 2014 Pages Description Title Copyright update 0H List of amendments 22 Addition of variant for Stand by ADI equipped with slip indicator PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 820: ...07 Rev 9 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 16 Addition of Pre MOD70 0407 00D validity for Aural warning system PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 821: ...n 1 of June 22 2007 Revision 10 of April 8 2019 Pages Description Title Company identity name change 0J List of amendments 1 28 Introduction of Flight Stream 210 optional equipment TR25 2 29 thru 34 Terminology text moving and or presentation PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 822: ...nt and furnishings 9 ATA 26 Fire protection 11 ATA 27 Flight controls 12 ATA 28 Fuel system 13 ATA 30 Ice and rain protection 14 ATA 31 Indicating recording systems 16 ATA 32 Landing gears 17 ATA 33 Lights 19 ATA 34 Navigation 21 ATA 35 Oxygen 26 ATA 37 Vacuum 27 ATA 46 Information systems 28 ATA 52 Doors 29 ATA 61 Propeller 30 ATA 71 Powerplant 31 ATA 77 Engine indicating 32 ATA 79 Lubrication 33...

Page 823: ...required for certification S standard equipment items A optional equipment items which are in addition to required or standard items O optional equipment items replacing required or standard items LIST OF CRITICAL RVSM EQUIPMENT Equipment listed hereafter or later approved versions is required for RVSM operation Equipment P N Barometric altimeter GDC74B Air data computer GDU1XXX Display 2 3 2 2 P ...

Page 824: ...tion 1 June 22 2007 Rev 0 S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 01 SPECIFIC OPTIONAL EQUIPMENT S Flight ceiling at 31000 ft PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 825: ... 21 30 Pressurization control S Cabin altitude warn switch 214 C40 3 261 0 08 0 035 153 94 3 910 S Cabin pressure control panel 22297A010001 0 66 0 300 167 32 4 250 S Cabin differential pressure switch 17 600 01 0 14 0 065 139 76 3 550 S Outflow valve 81146A010101 3 97 1 800 317 32 8 060 S Safety valve 81147A010101 3 31 1 500 317 32 8 060 A 0176 00I Selected cabin altitude repeater potentiometer i...

Page 826: ...ystem S Compressor 1377A010001 14 77 6 700 98 43 2 500 S Cockpit Evaporator Assembly 14720A010001 9 06 4 111 200 79 5 100 S Cabin Evaporator Assembly 14719A010001 12 90 5 850 311 02 7 900 S Condenser Assembly 81250A010001 24 80 11 250 330 71 8 400 21 60 Temperature regulation S By pass valve 6043A010001 3 31 1 500 106 30 2 700 S Bleed differential pressure sensor 93558A010001 0 44 0 200 114 17 2 9...

Page 827: ...GFC 700 composed of Pitch servo GSA 81 and Servo mount GMS 85 3 86 1 75 247 40 6 284 Roll servo GSA 81 and Servo mount GMS 85 3 86 1 75 231 10 5 870 Yaw servo GSA 81 and Servo mount GMS 85 3 86 1 75 253 70 6 444 Pitch trim servo GSA 81 and Servo mount GMS 85 4 04 1 83 157 87 4 010 Trim adapter GTA 82 1 30 0 59 240 87 6 118 AFCS Control Unit GMC 710 0 91 0 41 156 61 3 978 PIM DO NOT USE FOR FLIGHT ...

Page 828: ... 1 system Transceiver integrated in the GIA 63W Integrated Avionics Unit 1 refer to ATA 34 28 VHF antenna under fuselage 16 21B P3 0 86 0 390 271 65 6 900 S 0176 00A G1000 COM 2 system Transceiver integrated in the GIA 63W Integrated Avionics Unit 2 refer to ATA 34 28 VHF antenna upper fuselage 16 21B P3 0 86 0 390 271 65 6 900 S 23011G Radio stereo headset HMEC 25 6A S Static dischargers Type 2 1...

Page 829: ...OWER 24 30 DC generation R Electric power center 160GC02Y05 11 02 5 000 127 95 3 250 R Stand by generator T700A243008000601 12 13 5 500 102 36 2 600 R Starter generator 8012F 24 47 11 100 110 24 2 800 S 24002 Lead Acid battery RG 380E 44 85 98 39 000 112 20 2 850 24 40 External power supply S Ground power receptacle MS 3506 1 0 79 0 360 114 17 2 900 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 830: ...orage cabinet Vers E R H top storage cabinet Vers F R H top storage cabinet audio Vers G L H top baggage cabinet Vers H R H top baggage cabinet 9 48 4 300 9 48 4 300 9 48 4 300 7 72 3 500 7 72 3 500 7 94 3 600 3 09 1 400 3 09 1 400 203 74 5 175 203 74 5 175 203 74 5 175 203 74 5 175 203 74 5 175 203 74 5 175 203 74 5 175 203 74 5 175 S 0207 00 Carpet Cabin furnishings 35 27 16 000 302 45 137 19 21...

Page 831: ...seat back to flight direction T700C2500003003 35 27 16 00 35 27 16 00 220 94 5 612 220 94 5 612 Post MOD70 0315 25 S L H Intermediate seat T700G2500005000 R H Intermediate seat T700G2500005001 37 48 17 00 37 48 17 00 224 80 5 710 224 80 5 710 All S Double chair L H seat T700C2500005002 R H seat T700C2500005003 52 91 24 00 52 91 24 00 278 19 7 066 278 19 7 066 S Reels 1 79 0 810 192 91 or 287 40 4 ...

Page 832: ...53 6500 2 69 1 220 353 15 8 970 Antenna 21 41 0 31 0 140 318 70 8 095 O 25030D Emergency Locator Transmitter C406 1 with base 4 46 2 021 354 72 9 010 Antenna 21 41 0 31 0 140 318 70 8 095 S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 26 FIRE PROTECTION Pre MOD70 0336 26 S 26001B Portable fire extinguisher unit 863520 00 3 64 1 650 ...

Page 833: ...0 Yaw control R Rudder trim actuator 145700 02 1 54 0 700 395 27 10 040 S AFC and electric trim control on R H control wheel 0 88 0 400 157 48 4 000 27 30 Pitch control S Pitch trim actuator 145400 02 1 21 0 550 425 20 10 800 27 50 Wing flaps control R Flap control including 15 52 7 040 218 50 5 550 Flap motor 6157 1 2 87 1 300 216 54 5 500 Flap actuator 1 5295 2 5295 or 1 5297 2 5297 1 92 0 870 1...

Page 834: ...0 700 110 24 2 800 R Fuel sequencer unit 1 10 0 500 125 98 3 200 R Fuel unit L88A15 651 4 59 2 080 133 07 3 380 28 40 Fuel indication R 0158 28 Fuel gage amplifier in us gal 1 08 0 49 278 74 7 080 R Inboard L H probe 768 403 or 762 438 1 0 0 33 0 150 183 07 4 650 R Inboard R H probe 768 404 or 762 439 1 0 0 33 0 150 183 07 4 650 R Intermediate probe 766 976 1 or 762 440 1 0 0 22 0 100 190 94 4 850...

Page 835: ...01002 5 73 2 600 173 23 4 400 S Deicer inboard R H wing T700A3010001003 5 73 2 600 173 23 4 400 S Deicer middle L H wing T700A3010001004 3 75 1 700 173 23 4 400 S Deicer middle R H wing T700A3010001005 3 75 1 700 173 23 4 400 S Deicer outboard L H wing T700A3010012000 2 65 1 200 173 23 4 400 S Deicer outboard R H wing T700A3010001007 3 31 1 500 173 23 4 400 S Dual port distribution valve 1532 10C ...

Page 836: ... in m WEIGHT per unit lb kg REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O 30 60 Propeller deicing S Modular brush assy 3E2044 2 0 44 0 200 47 05 1 195 S Timer 3E2311 4 0 44 0 200 200 79 5 100 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 837: ...unit lb kg ARM in m 31 INDICATING RECORDING SYSTEMS 31 20 Independent instruments S 31002B Hourmeter 56457 3 flying time 0 55 0 250 156 30 3 970 O 31002A Hourmeter 56457 3 engine running time 0 55 0 250 156 30 3 970 31 50 Aural warning R Aural warning system T700A3155011000 Pre MOD70 0407 00D 0 66 0 300 183 07 4 650 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 838: ... 93 70 2 380 32 30 Extension and retraction R Door actuator EC 6230 1 35 0 610 192 91 4 900 R Main locking actuator 08 1480 13 23 6 000 208 07 5 285 R Nose locking actuator 08 1480 13 23 6 000 110 24 2 800 R Hand pump 914 8D27 2 33 1 055 181 10 4 600 32 35 Hydraulic generation R Hydraulic power pack assy 1118 04 10 36 4 700 84 65 2 150 32 40 Wheels and brakes R Brake assembly 030 19100 14 99 6 800...

Page 839: ...ter cylinder 010 07802 0 88 0 400 145 67 3 700 R Nose tire P N 071 311 1 5 00 5 10PR TL 5 60 2 540 89 57 2 275 R Nose tire P N 505T01 1 5 00 5 10PR TL 6 30 2 858 89 57 2 275 R Nose wheel 40 262A 2 98 1 350 89 57 2 275 R Main wheel Model 40 434 11 28 5 120 204 33 5 190 R Parking brake valve T700A3240010 or T700B3240001 0 33 0 150 157 48 4 000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 840: ... 0 100 157 48 4 000 S Instruments emergency lighting 2240 3 0 11 0 050 181 10 4 600 A 33001B PULSELITE control 1 27 0 574 202 60 5 146 33 40 External lighting S L H wing inspection light icing detection T700A3340012 0 20 0 090 151 57 3 850 S Landing lights 4596 0 79 0 360 179 13 4 550 S Taxi light assy T700A3340006 1 10 0 500 93 70 2 380 S NAV Anticollision system With bulb strobe nav lights S Ant...

Page 841: ...R OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O With LED strobe nav lights S R H or L H navigation light assy 11 1100 L SA 11 1100 R SA 0 32 0 145 185 04 4 700 All A 33002 Halogen landing lights Q5596 Halogen taxi lights Q5587 0 79 0 360 1 10 0 500 179 13 4 550 93 70 2 380 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 842: ...10000 0 22 0 100 157 48 4 000 Pre MOD70 0335 34 ESI 2000 R Stand by altimeter 3A43 22 35F 28 1 1 10 0 500 154 45 3 923 R Stand by airspeed indicator 5A58 22 30K 28 1 0 57 0 260 155 20 3 942 34 21 Heading reference system S 0176 00A Attitude and Heading Reference System 1 GRS 77 3 46 1 57 171 77 4 363 S 0176 00A Attitude and Heading Reference System 2 GRS 77 3 46 1 57 171 77 4 363 S 0176 00A Magnet...

Page 843: ...R Electronic Standby Indicator 2 75 1 250 154 29 3 919 34 28 Electronic flight instrumentation system S 0176 00A Integrated Flight Deck System G1000 composed of PFD1 GDU 1040A 6 53 2 96 155 71 3 955 PFD2 GDU 1040A 6 53 2 96 155 71 3 955 MFD GDU 1500A 8 66 3 93 155 20 3 942 Engine Airframe Interface Unit 1 GEA 71 2 53 1 15 150 63 3 826 Engine Airframe Interface Unit 2 GEA 71 2 53 1 15 150 63 3 826 ...

Page 844: ...scope G1000 coupled 4 94 2 240 232 28 5 900 Antenna NY163 0 84 0 380 311 02 7 900 Processor WX500 2 27 1 030 255 91 6 500 34 42 Weather radar A 0176 00C Weather radar G1000 coupled GWX 68 9 36 4 25 173 46 4 406 34 43 Radioaltimeter A 34037L Radioaltimeter EFIS coupled Transceiver KRA 405B 2 80 1 270 231 18 5 872 Antenna DM 19 2 1 0 20 0 090 181 10 and 204 72 4 600 and 5 200 A 0270 34 Radioaltimete...

Page 845: ...A 0176 00F G1000 TAWS system A 0258 00 TAS system GTS 820 G1000 coupled of which 22 05 10 220 177 00 4 513 Processor GTS 820 9 90 4 500 143 00 3 635 Power amplifier low noise amplifier GPA 65 1 89 0 860 221 00 5 624 Antenna upper fuselage GA 58 0 79 0 360 230 00 5 860 Antenna under fuselage GA 58 0 79 0 360 260 00 6 620 34 51 NAV 1 installation S GS NAV VHF antenna DM N4 17N 3 31 1 500 401 57 10 2...

Page 846: ...tenna upper fuselage KA 61 0 40 0 18 193 22 4 908 A 0176 00E Transponder 2 GTX 33 Mode S non diversity 3 87 1 75 149 65 3 801 Antenna KA 61 0 40 0 18 193 22 4 908 34 54 Automatic Direction Finder ADF A 0176 00H ADF RA 3500 system European countries only 7 61 3 45 214 65 5 452 34 55 DME installation A 34014E DME KN63 G1000 coupled 2 80 1 27 232 28 5 900 Antenna KA 61 0 40 0 18 238 82 6 066 34 57 Gl...

Page 847: ... 1 June 22 2007 Rev 7 S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 35 OXYGEN S 0207 00 Gaseous oxygen system 22 73 10 310 226 77 5 760 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 848: ...in m 37 VACUUM S Air ejector valve 19E17 5A 0 66 0 300 116 14 2 950 S Gyro suction gage 3 310 5 0 14 0 065 157 48 4 000 S Gyro vacuum air filter 1J7 2 0 38 0 170 139 76 3 550 S Regulator and relief valve 38E 96 2D 1 32 0 600 116 14 2 950 S Vacuum relief valve 691 21A 0 33 0 150 139 76 3 550 S Valve 557 18 E 0 35 0 160 118 11 3 000 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 849: ...Rev 10 S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 46 INFORMATION SYSTEMS O 0459 46B Flight stream transceiver FS 210 GARMIN 0 264 0 120 151 18 3 840 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 850: ...dition 1 June 22 2007 Rev 10 S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 52 DOORS A 52002A Pilot door 44 092 20 000 171 26 4 350 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 851: ...S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 61 PROPELLER 61 10 Propeller assembly S Propeller HC E4N 3 E 9083 S K 153 22 69 500 43 11 1 095 61 20 Controls R Overspeed governor A210632 2 73 1 240 59 06 1 500 S Propeller governor 8210 007 2 65 1 200 59 06 1 500 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 852: ...STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 71 POWERPLANT R Turboprop engine PT6 A 66D 497 30 226 000 79 72 2 025 S Silentblocks 95007 16 2 92 1 325 79 72 2 025 71 60 Air inlet R Inertial separator actuator 148600 09A 1 72 0 780 62 99 1 600 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 853: ...in m 77 ENGINE INDICATING R Compressor turbine tacho generator Ng MIL G 26611C GEU 7 A 0 981 0 445 108 27 2 750 R Power turbine tacho generator MIL G 26611C GEU 7 A 0 981 0 445 55 12 1 400 R Torque transducer 8107 200 00 10 or CZ52E8 G 0 463 0 210 53 54 1 360 77 12 Fuel management S Fuel transmitter 660 526A 1 000 0 454 110 20 2 799 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 854: ...0 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 79 LUBRICATION 79 20 Distribution R Oil cooler L8538233 10 472 4 750 90 55 2 300 79 30 Indicating R Oil pressure transmitter 8107 400 00 10 0 441 0 200 106 30 2 700 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 855: ...TBM 850 EQUIPMENT LIST Page 34 Edition 1 June 22 2007 Rev 10 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 856: ... N 684 30 11 90 18 L HOTELLIER Engine fire detection system OPT70 26002 From S N 1 up to S N 684 except S N 205 and 249 31 01 96 44 Chip detection system MOD70 0169 79 From S N 1 up to S N 684 10 02 05 45 Mexico Specifics MOD70 0212 11 From S N 1 to S N 999 except S N 687 30 11 11 47 AIRBORNE GWX 68 color weather radar MOD70 0176 00 Version C MOD70 0276 00 Version C TBM 700 or TBM 850 equipped wit...

Page 857: ...1 12 01 11 55 IAC AR Certified airplanes MOD70 332 00 TBM700 or TBM850 equipped with MOD70 0176 00 or MOD70 0276 00 30 09 11 56 GARMIN GSR 56 weather data link and satellite phone MOD70 0331 23 From S N 434 15 11 11 57 Public transportation for French registered airplanes MOD70 0352 11 From S N 148 to S N 999 plus S N 137 and S N 143 to S N 145 30 10 12 59 Brazil specifics OPT70 01004 From S N 434...

Page 858: ...0 0315 25 20 03 17 64 Stick shaker MOD70 0510 27 Version C From S N 434 22 05 17 65 MD302 standby attitude module MOD70 0462 34 Version C From S N 434 to S N 644 without MOD70 0335 34 ESI 2000 18 09 17 66 GARMIN G1000 NXi retrofit MOD70 0539 00 From S N 434 to S N 684 30 10 17 69 Baro VNAV approaches MOD70 0636 34 Airplane from S N 434 to S N 684 equipped with G1000 system MOD70 0176 00 or G1000 N...

Page 859: ...TBM PILOT S OPERATING HANDBOOK 850 SECTION 9 SUPPLEMENT A Page 9 A 4 Edition 1 June 22 2007 Rev 6 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 860: ...WX 500 OR WX 950 OR WX 1000 OR 1000 OR 1000E STORMSCOPE TABLE OF CONTENTS Page 1 GENERAL 9 6 2 2 LIMITATIONS 9 6 2 3 EMERGENCY PROCEDURES 9 6 3 4 NORMAL PROCEDURES 9 6 4 5 PERFORMANCE 9 6 4 6 WEIGHT AND BALANCE 9 6 5 7 DESCRIPTION 9 6 7 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 861: ...in Section 2 Limitations of the basic Pilot s Operating Handbook The BFG stormscope systems signal displays are not intended for the purpose of penetrating thunderstorm areas or areas of severe turbulence such intentional use is prohibited NOTE Range selection determines receiver sensitivity and therefore relative range Displayed range is based on signal strength and is not to be used for accurate...

Page 862: ...ght deck MOD70 0176 00 The WX 500 Pilot s guide Series II No 009 11501 001 and the GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the TBM 850 P N 190 00708 00 or Airplane retrofited with GARMIN G1000 NXi flight deck MOD70 0539 00 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 0...

Page 863: ...or 1000E or the WX 950 Pilot s Guide Series II No 009 10951 001 at its last revision for BFG stormscope model WX 950 or the WX 500 Pilot s Guide Series II No 009 11501 001 at its last revision for BFG stormscope model WX 500 SECTION 5 PERFORMANCE Installation and operation of BFG stormscope do not change the basic emergency procedures of the airplane described in Section 5 Performance of the basic...

Page 864: ...scope WX 1000 OPT 70 34009B BFG 15 432 7 000 230 71 5 860 A Stormscope WX 1000 EFIS coupled OPT 70 34009C BFG 15 432 7 000 230 71 5 860 A Stormscope WX 1000E EFIS coupled Remote installed control OPT 70 34009D BFG 9 502 4 310 269 09 6 835 A Stormscope WX 1000E EFIS coupled OPT 70 34009E BFG 15 939 7 230 230 94 5 866 A Stormscope WX 1000E shared with the SKYWATCH OPT 70 34009F BFG 15 939 7 230 230 ...

Page 865: ...IPMENT SUPPLIER OPTIONAL EQUIPMENT A Stormscope WX 500 shared with the GNS 530 GPS or with the KMD 850 or GMX 200 MFD OPT 70 34056A BFG 4 94 2 240 232 28 5 900 A Stormscope WX 500 shared with the GARMIN flight deck system OPT 70 34056B BFG 4 94 2 240 232 28 5 900 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 866: ...tivity A series of green dots or of strike points will be displayed on the screen to indicate the electrical discharge areas Dots or strike points may be displayed on two selectable wiews 360 view of surrounding airspace and 120 view of forward airspace only The display scope provides full scale selectable ranges of 200 100 50 and 25 NM Post MOD70 125 23 and without GARMIN G1000 or G1000 NXi fligh...

Page 867: ...TBM 700 850 SUPPLEMENT 6 BFG STORMSCOPE Page 9 6 8 Rev 6 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 868: ...ev 2 SUPPLEMENT ENGINE FIRE DETECTION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 18 2 2 LIMITATIONS 9 18 2 3 EMERGENCY PROCEDURES 9 18 3 4 NORMAL PROCEDURES 9 18 5 5 PERFORMANCE 9 18 5 6 WEIGHT AND BALANCE 9 18 6 7 DESCRIPTION 9 18 7 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 869: ...eafter supplement those of the standard airplane described in Section 1 General of the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option ENGINE FIRE DETECTION SYSTEM The fire detection system allows engine fire monitoring and indicating SECTION 2 LIMITATIONS The limitations of the TBM airplane equipped with the engine fire detection system are those of the standard...

Page 870: ... is equipped with the option ENGINE FIRE DETECTION SYSTEM ENGINE FIRE ON GROUND Indications ITT increasing red warning ITT ON or ITT CAS message red warning FIRE ON or FIRE CAS message smoke 1 Power lever IDLE 2 Condition lever CUT OFF 3 BLEED VALVE or BLEED switch OFF 4 FREON or AIR COND switch if installed OFF 5 Brakes AS REQUIRED 6 Tank selector OFF 7 Ask for ground assistance if necessary 8 CR...

Page 871: ...through engine cowls or from air conditioning system 3 Land as soon as possible If the fire alarm is confirmed 1 Power lever IDLE 2 Propeller governer lever FEATHER 3 Condition lever CUT OFF 4 AUX BP fuel switch OFF 5 Tank selector OFF 6 BLEED VALVE or BLEED switch OFF 7 FREON or AIR COND switch if installed OFF 8 At high altitude above 12000 ft undertake an EMERGENCY DESCENT Refer to Chapter 3 6 ...

Page 872: ...sequipped with the option ENGINE FIRE DETECTION SYSTEM Before starting the engine FIRE DETECT TEST push button DEPRESS The FIRE red warning goes on or the FIRE CAS message lights on and causes the illumination of the MASTER WARNING light SECTION 5 PERFORMANCE Installation and operation of the engine fire detection system do not modify the performance of the airplane described in Section 5 Performa...

Page 873: ...A Engine fire detection system OPT70 26002A TBM 700A TBM 700B without GARMIN flight deck system L HOTELLIER 1 455 0 66 96 06 2 440 A Engine fire detection system OPT70 26002D TBM 700A TBM 700B with GARMIN flight deck system L HOTELLIER 1 455 0 66 96 06 2 440 A Engine fire detection system OPT70 26002B TBM 700C TBM 850 without GARMIN flight deck system L HOTELLIER 1 455 0 66 96 06 2 440 A Engine fi...

Page 874: ...sist of thermal switches detecting a temperature greater than 200 C RELAY The relay controls the illumination of the FIRE warning light located on the advisory panel It is positioned on a base plate secured under the floorboard PUSH BUTTON The push button enables the pilot to test the detection system by opening the grounding circuit supplying the relay It is connected in series with the 7 detecto...

Page 875: ...ircuit It is connected in series with the 7 detectors The push button is located on the L H side instrument panel the FIRE DETECT TEST placard DISPLAY 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 0...

Page 876: ...ev 1 SUPPLEMENT CHIP DETECTION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 44 2 2 LIMITATIONS 9 44 2 3 EMERGENCY PROCEDURES 9 44 3 4 NORMAL PROCEDURES 9 44 4 5 PERFORMANCE 9 44 4 6 WEIGHT AND BALANCE 9 44 4 7 DESCRIPTION 9 44 5 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 877: ...scription 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 change the limitations of the airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 878: ...rplane is equipped with the option CHIP DETECTION SYSTEM Indication CHIP amber warning on On ground Before engine start 1 Do not start engine After engine start or after landing 1 Return to parking area 2 Shut down engine 3 Inspect chip detector s and engine if required In flight 1 Check and monitor engine parameters 2 Land as soon as practical 3 Shut down engine 4 Inspect chip detector s and engi...

Page 879: ...f the CHIP DETECTION 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 those given for the standard aircraft in Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in...

Page 880: ...e 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 In case of chip detection amber warning light CHIP on advisory panel or amber CAS message CHIP on GARMIN flight deck system screen goes on PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 881: ...TBM 700 850 SUPPLEMENT 44 CHIP DETECTION SYSTEM Page 9 44 6 Rev 1 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 882: ... its standard version This Supplement includes information to be furnished to the pilot as required by the certification conditions This Supplement Revision 2 meeting the Mexico DGAC requirements is approved under the authority of DOA EASA 21J 013 Approval Number EASA 21J 013 17275 T N DOA Date September28 2017 THIS DOCUMENT MUST BE EMBODIED IN SECTION 9 OF THE PILOT S OPERATING HANDBOOK AND BE PE...

Page 883: ... 0 9 45 7 0 9 45 8 0 9 45 9 0 9 45 10 0 9 45 11 0 9 45 12 0 9 45 13 0 9 25 13A 1 9 25 13B 1 9 45 14 2 9 45 15 2 9 45 16 2 9 45 17 2 9 45 18 2 9 45 19 2 9 45 20 2 9 45 21 2 9 45 22 2 9 45 23 2 9 45 24 2 9 45 25 2 9 45 26 2 9 45 27 2 9 45 28 2 9 45 29 2 9 45 30 2 9 45 31 2 9 45 32 2 9 45 33 2 9 45 34 2 This Supplement Revision 2 meeting the Mexico DGAC requirements is approved under the authority of...

Page 884: ...scription 9 45A Approval page 9 45B List of effective pages and validities 9 45C List of amendments 9 45 13A and 9 45 13B Integration of TR17 AIR TOTAL extinguisher 9 45 17 Modification of OILS ACEITES placard addition of AEROSHELL 560 9 45 15 9 45 16 9 45 18 9 45 20 Terminology PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 885: ...n 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 9 45 17 Addition of placards for MOD70 0505 25 9 45 14 9 45 18 thru 9 45 34 Text moving PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 886: ...age 1 GENERAL 9 45 2 2 LIMITATIONS 9 45 2 Internal placards 9 45 2 External placards 9 45 18 Placards relative to optional equipment 9 45 28 3 EMERGENCY PROCEDURES 9 45 33 4 NORMAL PROCEDURES 9 45 33 5 PERFORMANCE 9 45 33 6 WEIGHT AND BALANCE 9 45 33 7 DESCRIPTION 9 45 34 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 887: ...orities limitations description and operations necessary to the operation of the TBM airplane SECTION 2 LIMITATIONS The limitations hereafter supplement or replace those of the standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook PLACARDS Internal placards 1 Rear pressurized baggage compartment in cabin d On bottom bulkhead TBM 700A TBM 700B PIM DO NOT USE F...

Page 888: ...TBM 700 850 Page 9 45 3 Rev 0 e On partition wall TBM 700C1 TBM 850 or TBM 700C2 Refer to POH Supplement 41 With partition net version A refer to Section 6 of TBM 700C1 Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 889: ... 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 890: ...v 0 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 or 4 On cockpit R H side at front seat level TBM 700A TBM 700B chemical oxygen PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 891: ...re fitted with oxygen TBM 700A TBM 700B chemical oxygen 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 892: ... 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 MOD70 019 25 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 893: ...CS Page 9 45 8 Rev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 894: ...SPECIFICS TBM 700 850 Page 9 45 9 Rev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 895: ... 45 MEXICO SPECIFICS Page 9 45 10 Rev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 896: ...FICS TBM 700 850 Page 9 45 11 Rev 0 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 897: ... 0 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 ALL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 898: ...SUPPLEMENT 45 MEXICO SPECIFICS TBM 700 850 Page 9 45 13 Rev 0 13 On cabinet drawer ALL 14 On aisle side of rear seats TBM 700A PRE MOD70 019 25 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 899: ... 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 15 On fixed panel cabin side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 900: ...SUPPLEMENT 45 MEXICO SPECIFICS TBM 700 850 Page 9 45 15 Rev 2 16 On fixed panel toilet side 17 On access door cabin side and toilet side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 901: ...LEMENT 45 MEXICO SPECIFICS Page 9 45 16 Rev 2 18 Behind access door cabin side 19 Behind access door toilet side 20 Front face of lavatory compartment near opening closing switches PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 902: ...SUPPLEMENT 45 MEXICO SPECIFICS TBM 700 850 Page 9 45 17 Rev 2 21 On the magazine rack and on side wall of storage volume PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 903: ...0 SUPPLEMENT 45 MEXICO SPECIFICS Page 9 45 18 Rev 2 ALL 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 904: ...SUPPLEMENT 45 MEXICO SPECIFICS TBM 700 850 Page 9 45 19 Rev 2 b TBM 850 S N 269 and from S N 434 c ALL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 905: ...ENT 45 MEXICO SPECIFICS Page 9 45 20 Rev 2 ALL 24 Above brakes hydraulic fluid reservoir against firewall 25 On langing gear hydraulic fluid reservoir 26 On fuse box in engine cowling PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 906: ...SUPPLEMENT 45 MEXICO SPECIFICS TBM 700 850 Page 9 45 21 Rev 2 27 On internal face of L H engine cowling a ALL b TBM 700A 700B TBM 700C PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 907: ...50 SUPPLEMENT 45 MEXICO SPECIFICS Page 9 45 22 Rev 2 ALL 28 On front lower portion of firewall L H side 29 On engine cowling in front of compartment door 30 On nose gear door PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 908: ...SUPPLEMENT 45 MEXICO SPECIFICS TBM 700 850 Page 9 45 23 Rev 2 31 On nose gear leg ALL 32 On main gear leg TBM 700A TBM 700B TBM 700C1 TBM 700C2 TBM 850 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 909: ...ge 9 45 24 Rev 2 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 ALL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 910: ...LEMENT 45 MEXICO SPECIFICS TBM 700 850 Page 9 45 25 Rev 2 36 On external side of emergency locator transmitter inspection door ALL 37 On emergency exit external side ALL PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 911: ...NT 45 MEXICO SPECIFICS Page 9 45 26 Rev 2 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 912: ...ge 9 45 27 Rev 2 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 913: ...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 rear seats on FWD side equipped with oxygen On FWD side of the rear divan seating PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 914: ...ev 2 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 intermediate seat R H rear seat and rear seats on FWD side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 915: ... 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 intermediate seat back rest PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 916: ... Rev 2 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 front side window PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 917: ...POH Supplement 40 On the raiser at frame 13bis inside the cabin 44 TBM 700B Airplanes equipped with option OPT70 35001 EROS INTERTECHNIQUE gaseous oxygen system refer to POH Supplement 29 or 37 On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling On rear passengers masks containers on R H side on the ceiling PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 918: ...ev 2 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 919: ...TBM 700 850 SUPPLEMENT 45 MEXICO SPECIFICS Page 9 45 34 Rev 2 SECTION 7 DESCRIPTION No specifics PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 920: ...ev 1 SUPPLEMENT AIRBORNE GWX 68 COLOR WEATHER RADAR TABLE OF CONTENTS Page 1 GENERAL 9 47 2 2 LIMITATIONS 9 47 2 3 EMERGENCY PROCEDURES 9 47 3 4 NORMAL PROCEDURES 9 47 4 5 PERFORMANCE 9 47 5 6 WEIGHT AND BALANCE 9 47 5 7 DESCRIPTION 9 47 6 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 921: ...nel within 12 feet of area being scanned by antenna when system is transmitting Airplane equipped with GARMIN G1000 flight deck MOD70 0176 00 The GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the TBM 850 P N 190 00708 00 at its latest revision shall be readily available to the pilot whenever the operation of the radar system is predicted Airplane retrofited with GARMIN G1000 flig...

Page 922: ...ge the basic emergency procedures of the airplane described in Section 3 Emergency procedures of the basic Pilot sOperating Handbook CAUTION IN REVERSIONARY MODE THE WEATHER RADAR SYSTEM AUTOMATICALLY SWITCHES TO STANDBY MODE THE SYSTEM REMAINS IN STANDBY MODE UNTIL BOTH DISPLAYS ARE RESTORED IN REVERSIONARY MODE THE WEATHER RADAR SYSTEM CANNOT BE CONTROLLED PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 923: ...lined in the Pilot s Guide the references of which are given in Section 2 Limitations of this Supplement CAUTION IN REVERSIONARY MODE THE WEATHER RADAR SYSTEM AUTOMATICALLY SWITCHES TO STANDBY MODE THE SYSTEM REMAINS IN STANDBY MODE UNTIL BOTH DISPLAYS ARE RESTORED IN REVERSIONARY MODE THE WEATHER RADAR SYSTEM CANNOT BE CONTROLLED AFTER ENGINE STARTING Radar Mode Softkey STANDBY A one minute warm ...

Page 924: ...crease in Long Range cruise performance 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 Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 34 NAVIGATION A Weather radar GWX 6...

Page 925: ... The controls for the MFD are located on both the MFD bezel and the MFD control unit Figure 9 47 1 1 2 GWX 68 weather radar display and controls 1 MFD 2 Radar mode 3 Area of weather display 4 Antenna stabilization status 5 MFD bezels 6 MFD control unit 7 Changes radar range TILT and bearing 8 Scale for weather display PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 926: ...SUPPLEMENT 47 AIRBORNE GWX 68 COLOR WEATHER RADAR TBM 700 850 Page 9 47 7 Rev 1 Figure 9 47 1 2 2 GWX 68 weather radar display and controls PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 927: ...TBM 700 850 SUPPLEMENT 47 AIRBORNE GWX 68 COLOR WEATHER RADAR Page 9 47 8 Rev 1 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 928: ... 0 SUPPLEMENT HONEYWELL KTA 870 TAS SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 48 3 2 LIMITATIONS 9 48 3 3 EMERGENCY PROCEDURES 9 48 4 4 NORMAL PROCEDURES 9 48 4 5 PERFORMANCE 9 48 5 6 WEIGHT AND BALANCE 9 48 5 7 DESCRIPTION 9 48 6 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 929: ...TBM 850 SUPPLEMENT 48 HONEYWELL KTA 870 TAS SYSTEM Page 9 48 2 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 930: ...n Section 2 Limitations of the basic Pilot s Operating Handbook when the TBM 850 airplane is equipped with the option HONEYWELL KTA 870 TAS SYSTEM REMARK The KTA 870 TAS function is an advisory means not a TCAS Following documents or any further edition applicable to the latter shall be readily available to the pilot each time the KTA 870 system is used KTA 870 KMH 880 Traffic Advisory System Mult...

Page 931: ...book when the TBM airplane is equipped with the option HONEYWELL KTA 870 TAS SYSTEM BEFORE TAKEOFF Traffic Page TEST Softkey PUSH TAS system test OK voice alert HEARD WARNING DO NOT ATTEMPT EVASIVE MANEUVERS BASED SOLELY ON TRAFFIC INFORMATION SHOWN ON DISPLAY ASSOCIATED TO THE KTA 870 TAS FUNCTION INFORMATION ON THE DISPLAY IS PROVIDED TO THE FLIGHT CREW AS AN AID IN VISUALLY ACQUIRING TRAFFIC IT...

Page 932: ...nce of the basic Pilot s Operating Handbook 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 A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 34 NAVIGATION A TAS system KTA 870 coupled with GARMIN G1000 system OPT70 034 061D HONEYWELL 9 17 4 160 13...

Page 933: ...is displayed when the vertical separation between your own airplane altitude and the intruder altitude ranges MODE From Up to ABOVE Look up 2700 ft 9000 ft NORMAL Normal 2700 ft 2700 ft Below Below 9000 ft 2700 ft UNREST Unrestricted 9000 ft 9000 ft Traffic Advisory TA criteria which initiate a visual and or an aural alert are sensitivity level B detection of an intruder airplane within a 0 55 NM ...

Page 934: ... a visual and or an aural alert are sensitivity level A detection of an intruder airplane within a 0 2 NM horizontal radius and a 600 ft relative altitude approach of an intruder airplane on a course that will intercept your course within 15 to 20 seconds The aural traffic alert is inhibited when the height detected by the radio altimeter is below 600 ft TAS function will be automatically activate...

Page 935: ...PLEMENT 48 HONEYWELL KTA 870 TAS SYSTEM Page 9 48 8 Rev 1 Figure 9 48 1 KTA 870 System display and controls 1 MFD 2 TAS altitude mode 3 TAS operating mode 4 Aera of TAS display PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 936: ...ev 2 SUPPLEMENT GARMIN TAWS SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 49 3 2 LIMITATIONS 9 49 3 3 EMERGENCY PROCEDURES 9 49 4 4 NORMAL PROCEDURES 9 49 4 5 PERFORMANCE 9 49 6 6 WEIGHT AND BALANCE 9 49 7 7 DESCRIPTION 9 49 8 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 937: ...TBM 700 850 SUPPLEMENT 49 GARMIN TAWS SYSTEM Page 9 49 2 Rev 2 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 938: ...2318 recommendation in order to avoid unwillingly warnings TAWS function must be inhibited for any landing on a terrain which is not mentioned in the data base The use of the terrain awareness warning and terrain display functions is prohibited during QFE atmospheric pressure at airport elevation operations The following document or any further edition applicable to the latter shall be readily ava...

Page 939: ... the airplane is equipped with the option GARMIN TAWS SYSTEM The TAWS function is not operational TAWS FAIL ANNUNCIATION 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 TAWS SYSTEM TAWS System Test OK voice messa...

Page 940: ...ING Terrain Terrain Pull up Pull up Obstacle Obstacle Pull up Pull up AURAL WARNINGS The red PULL UP PFD MFD annunciation and TERRAIN OBSTACLE PULL UP pop up alerts light on Adjust airplane path in order to make the warning disappear 4 2 CAUTIONS OF THE TAWS FUNCTION Caution terrain Caution obstacle Too low terrain AURAL WARNINGS The amber TERRAIN PFD MFD annunciation and CAUTION TERRAIN OBSTACLE ...

Page 941: ...ink AURAL WARNING The amber TERRAIN PFD MFD annunciation and SINK RATE pop up alert light on Reduce rate of descent Sink rate AURAL WARNING SECTION 5 PERFORMANCE The installation and the operation of the GARMIN TAWS SYSTEM do not change the basic performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 942: ...upplement the one given for the standard airplane in Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 34 NAVIGATION A TAWS system MOD70 0176 00 Version F MOD70 0276 00 Version F GARMIN PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 943: ...l impact point is displayed on the TAWS Page Imminent Terrain Impact and Imminent Obstacle Impact Imminent Terrain Impact ITI and Imminent Obstacle Impact IOI alerts are issued when the airplane is below the elevation of a terrain or obstacle cell in the airplane s projected path ITI and IOI alerts are accompanied by a potential impact point displayed on the TAWS Page The alert is annunciated when...

Page 944: ... Impact Warning ITI Red PULL UP TERRAIN AHEAD PULL UP Terrain Ahead Pull up Terrain Ahead Pull up Reduced Required Obstacle Clearance Warning ROC Red PULL UP OBSTACLE PULL UP Obstacle Obstacle Pull up Pull up Imminent Obstacle Impact Warning IOI Red PULL UP OBSTACLE AHEAD PULL UP Obstacle Ahead Pull up Obstacle Ahead Pull up Reduced Required Terrain Clearance Caution RTC Amber TERRAIN CAUTION TERR...

Page 945: ...ation airport PDA alerting ends when the airplane is either 0 5 Nm from the runway threshold OR at an altitude of 125 feet AGL while within 1 0 Nm of the threshold Figure 9 49 1 PDA alerting threshold The aural displayed messages associated with the PDA function are described in the table 7 3 Alert Type PFD MFD TAWS Page Annuncia tion MFD Map Page Pop Up Alert Aural Message Premature Descent Alert...

Page 946: ...ssive 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 Figure 9 49 2 Excessive Descent Rate Alert Criteria PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 947: ...itude Loss After Takeoff is to provide suitable alerts to the pilot when the system determines that the airplane is losing altitude closing upon terrain after takeoff The aural message Don t sink is given for NCR alerts accompanied by an annunciation and a pop up terrain alert on the display NCR alerting is only active when departing from an airport and when the following conditions are met The he...

Page 948: ...d 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 Alert Type PFD MFD TAWS Page Annuncia tion MFD Map Page Pop Up Alert Aural Message Negative Climb Rate Caution NCR Amber TERRAIN DON T SINK Don t sink Table 7 5 NCR alert PIM DO NOT USE FOR FLIGHT OP...

Page 949: ...rtical accuracy minimums Should the navigation solution become degraded or if the airplane is out of the database coverage area the annunciation TAWS N A is generated in the annunciation window and on the TAWS Page The aural message TAWS Not Available is generated When the GPS signal is re established and the airplane is within the database coverage area tne aural message TAWS Available is generat...

Page 950: ...ev 3 SUPPLEMENT GARMIN SYNTHETIC VISION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 50 3 2 LIMITATIONS 9 50 4 3 EMERGENCY PROCEDURES 9 50 5 4 NORMAL PROCEDURES 9 50 6 5 PERFORMANCE 9 50 8 6 WEIGHT AND BALANCE 9 50 8 7 DESCRIPTION 9 50 9 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 951: ...TBM 700 850 SUPPLEMENT 50 GARMIN SYNTHETIC VISION SYSTEM Page 9 50 2 Rev 3 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 952: ...with the option GARMIN SYNTHETIC VISION SYSTEM SVS The SVS does not replace and is not intended to be used independently of the TAS and or TAWS system s The SVS does not replace and is not intended to be used independently of the horizontal and vertical primary flight instruments The SVS does not replace and is not intended to be used independently of the Course Deviation Indicator and the Vertica...

Page 953: ...90 01247 00 or any later revision as applicable Airplane retrofited with GARMIN G1000 NXi flight deck MOD70 0539 00 GARMIN G1000 NXi Integrated Flight Deck Cockpit Pilot s Guide for the TBM 850 900 P N 190 02348 00 or any later revision as applicable The use of the Synthetic Vision system display elements alone for aircraft control without reference to the primary flight instruments is prohibited ...

Page 954: ...ane retrofited with GARMIN G1000 flight deck MOD70 0276 00 INCONSISTENT DISPLAY BETWEEN SVS AND PRIMARY FLIGHT INSTRUMENTS PFD key Press SYN VIS key Press SYN TERR key Press SVS is removed from the PFD Verify Use GARMIN system primary displays for navigation and aircraft control Airplane retrofited with GARMIN G1000 NXi flight deck MOD70 0539 00 INCONSISTENT DISPLAY BETWEEN SVS AND PRIMARY FLIGHT ...

Page 955: ...AIN AWARENESS WARNING SYSTEM TAWS Airplane equipped with GARMIN G1000 flight deck MOD70 0176 00 or airplane retrofited with GARMIN G1000 flight deck MOD70 0276 00 SVS ACTIVATION 1 2 4 If SVS is desired PFD key Press SYN VIS key Press SYN TERR key Press The synthetic vision system will cycle on or off with each press of the SYN TERR key The Flight Path Marker is displayed anytime SYN TERR is select...

Page 956: ...splay will cycle on or off with each press of the APTSIGNS key NOTE For PATHWAY HRZN HDG and APTSIGNS SYN TERR must be activated first When display backup mode is selected the display of the SVS is active within 1 minute after SVS selection Airplane retrofited with GARMIN G1000 NXi flight deck MOD70 0539 00 SVS ACTIVATION Refer to GARMIN Integrated Flight Deck Pilot s Guide as applicable listed in...

Page 957: ...ane 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 Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 34 NAVIGATION A GARMIN Synthetic Vision System GARMIN PIM DO NOT USE FO...

Page 958: ...errain is selected for display Pathway a pilot selectable three dimensional representation of the programmed flight plan path that can be selected for display alone or with the flight director anytime synthetic terrain is selected for display Traffic a display on the PFD indicating the position of other aircraft detected by the Traffic Information System TIS component of the GARMIN flight deck sys...

Page 959: ...displayed for that segment The first Pathway segment displayed will be the first GPS course leg The Pathway must be within the SVS field of view of 30 degrees left and 35 degrees right If the programmed path is outside that field of view the Pathway will not be visible on the display until the aircraft has turned toward the course The Pathway will be displayed at either the altitude selected on th...

Page 960: ... only be used to maintain awareness with regard to the surrounding terrain and the programmed flight path Primary aircraft control must be accomplished by reference to the primary flight instruments and if desired the flight director GPS approach During a GPS approach the lateral path and altitude will be displayed by the Pathway in magenta along each segment including the path required to track c...

Page 961: ...Approach Point MAP The Pathway will be shown level at the altitude set in the altitude selector or the Final Approach Fix FAF crossing altitude whichever is higher up to the point along the final approach course where that altitude intercepts the extended GS If the altitude selector indicates an altitude below the airplane s current altitude the Pathway will appear below the airplane altitude and ...

Page 962: ... by other than a GPS course the Pathway will not be displayed for that segment If the course to the Missed Approach Holding Point is out of the SVS field of view during the initial missed approach climb the Pathway will not be visible on the PFD until the aircraft is turned toward the course The Pathway will be displayed at the published missed approach altitude OR the altitude set on the altitude...

Page 963: ...TBM 700 850 SUPPLEMENT 50 GARMIN SYNTHETIC VISION SYSTEM Page 9 50 14 Rev 3 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 964: ...Page 1 General 9 54 2 2 Limitations 9 54 2 Internal placards 9 54 2 External placards 9 54 19 Placards relative to optional equipment 9 54 27 3 Emergency procedures 9 54 35 4 Normal procedures 9 54 35 5 Performance 9 54 35 6 Weight and balance 9 54 36 7 Description 9 54 36 8 Handling servicing and maintenance 9 54 36 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 965: ... 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 Section 2 Limitations The information in this section supplements and or replaces the information in section 2 Limitations of the standard POH Placards Internal placards 1 Rear pressurized baggage com...

Page 966: ... 54 Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 3 b On partition wall TBM 700C1 or TBM 700C2 refer to POH Supplement 41 With partition net version A refer to section 6 of TBM 700C1 POH PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 967: ...gentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 4 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 968: ...eft 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 TBM 910 from S N 1336 TBM 930 MOD70 0683 25F PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 969: ...0 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 compartment b For the small cargo net on frame C13bis or on the right lower upholstery panel PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 970: ...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 TBM 700C TBM 850 up to S N 433 or PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 971: ...700B chemical oxygen 6 Under seating of intermediate and rear passenger seats on FWD side which are fitted with oxygen TBM 700A TBM 700B chemical oxygen 7 On the right side of the cockpit at front seatlevel 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 972: ...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 10 On internal face of rear passenger masks containers doors TBM 910 from S N 1270 11 On rear passenger s table casing TBM 700A TBM 700B TBM 700C TBM 850 TBM 900 TBM 910 up to S N 1269 TBM 930 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 973: ...10 Rev 1 Page 9 54 10 12 Above passenger s table TBM 910 from S N 1270 13 On cabinet drawer optional All 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 MOD70 019 25 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 974: ...ugust 31 2010 Rev 1 Page 9 54 11 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 975: ...gentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 12 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 976: ...tina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 13 c 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 977: ... Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 14 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 978: ...rgentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 15 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 979: ...Operating Handbook Supplement 54 Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 16 From S N 1270 Marking on cover Marking on handle 16 Above emergency exit All PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 980: ...t 31 2010 Rev 1 Page 9 54 17 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 TBM 910 from S N 1270 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 981: ...Pilot s Operating Handbook Supplement 54 Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 18 18 On aisle side of rear seats TBM 700A Pre MOD70 019 25 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 982: ... 54 Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 19 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 983: ... 2010 Rev 1 Page 9 54 20 All 20 On internal face of the left side engine cowling 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 984: ...t s Operating Handbook Supplement 54 Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 21 TBM 900 TBM 910 TBM 930 All 23 On nose gear door 24 On nose gear leg PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 985: ...ition 0 August 31 2010 Rev 1 Page 9 54 22 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 986: ...fics Edition 0 August 31 2010 Rev 1 Page 9 54 23 27 On the oxygen service door TBM 700C TBM 850 TBM 900 TBM 910 TBM 930 All 28 Near air data system port 29 On external side of emergency locator transmitter inspection door PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 987: ...specifics Edition 0 August 31 2010 Rev 1 Page 9 54 24 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 988: ...900 TBM910 TBM930 Onaccess door c TBM 700B TBM 700C TBM 850 TBM 900 TBM 910 TBM 930 On outer fuselage skin aft of access door and in the cabin forward of access door 32 TBM 700A On external side of lower half door TBM 700B TBM 700C TBM 850 TBM 900 TBM 910 Up to S N 1269 TBM 930 On last step of stairs PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 989: ...dbook Supplement 54 Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 26 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 990: ...uipment 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 991: ...cept 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 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 992: ...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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 993: ... Rev 1 Page 9 54 30 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 994: ... 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 995: ...gentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 32 38 Airplanes equipped with optional MOD70 0505 25C Cabinet installation Lavatory compartment On fixed panel cabin side On fixed panel toilet side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 996: ...ing Handbook Supplement 54 Argentina specifics Edition 0 August 31 2010 Rev 1 Page 9 54 33 On access door cabin side and toilet side Behind access door cabin side and toilet side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 997: ...August 31 2010 Rev 1 Page 9 54 34 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 998: ... 0 August 31 2010 Rev 1 Page 9 54 35 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 999: ...and Balance of the standard POH S R A O Item OPT70 or MOD70 Required R or Standard S or Optional A or O equipment Weight per unit lb kg Arm in m 01 Specific optional equipment A 0289 11 Argentina markings A 0619 11F Argentina markings 34 Navigation A 0176 00H ADF RA 3500 system 7 61 3 45 214 65 5 452 Section 7 Description No specifics Section 8 Handling servicing and maintenance No specifics PIM D...

Page 1000: ... 9 55 18 3 1 GENERAL 9 55 18 3 2 EMERGENCY LANDINGS 9 55 19 Landing without elevator control 9 55 19 Landing without rudder control 9 55 20 Landing without ailerons 9 55 20 3 3 DEICING SYSTEM 9 55 21 Leading edges deicing failure 9 55 21 4 NORMAL PROCEDURES 9 55 22 4 3 CHECK LIST PROCEDURES 9 55 22 Touch and go 9 55 22 4 4 AMPLIFIED PROCEDURES 9 55 23 Touch and go 9 55 23 4 5 PARTICULAR PROCEDURES...

Page 1001: ...FORMANCE 9 55 29 5 1 WIND COMPONENTS 9 55 29 5 2 TAKEOFF DISTANCES 9 55 30 5 3 LANDING DISTANCES 9 55 33 6 WEIGHT AND BALANCE 9 55 36 RUSSIAN TBM700 LIST OF REQUIRED AND STANDARD EQUIPMENT 9 55 37 RUSSIAN TBM700 LIST OF OPTIONAL EQUIPMENT 9 55 66 7 DESCRIPTION 9 55 81 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1002: ...PERATING LIMITS The airplane is only allowed to operate on paved runways VFR NIGHT OPERATION LIMITS The aircraft VFR night operation without ATC communications is prohibited MISCELLANEOUS LIMITS In case of single pilot operations the right crew seat must not be occupied by a passenger The aircraft may be operated in CIS airspace on routes covered by ATC ground facilities using RBS mode and VHF rad...

Page 1003: ...gage compartment in cabin a On bottom bulkhead TBM 700A TBM 700B and TBM 850 100 kg 220 lbs MAXIMUM IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT ALL THE BAGGAGES ARE PROPERLY SECURED FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA IN PILOT S OPERATING HANDBOOK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1004: ... 50 kg 110 lbs MAXIMUM FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA IN PILOT S OPERATING HANDBOOK 3 On cockpit R H side at front seat level TBM 700A TBM 700B chemical oxygen EMERGENCY OXYGEN IN DRAWER UNDER SEAT PULL FULLY THE MASK OUT OF DRAWER AT FULL EXTENSION GIVE CORD A TUG MAXIMUM DURATION 12 min SEE POH NO SMOKING WHILE IN USE PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1005: ... and rear passenger seats on FWD side which are fitted with oxygen TBM 700A TBM 700B chemical oxygen 5 On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling TBM 850 gazeous oxygen TBM 700B gazeous oxygen if installed PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1006: ...ntainers on R H side on the ceiling TBM 850 gazeous oxygen TBM 700B gazeous oxygen if installed 7 On rear passenger s table casing TBM 700A TBM 700B and TBM 850 TABLE MUST BE STOWED DURING TAKEOFF AND LANDING 8 On rear passenger s table casing TBM 850 PUSH TO OPEN PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1007: ...On access door Internal side a TBM700A from S N 1 to S N 49 except airplanes equipped as a retrofit with modification No MOD70 019 25 b TBM700A from S N 50 to S N 125 plus airplanes equipped as a retrofit with modification No MOD70 019 25 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1008: ...SUPPLEMENT 55 IAC AR CERTIFIED AIRPLANES TBM 700 850 Page 9 55 9 Rev 0 c TBM700A S N 30 35 and from S N 50 to 125 d TBM700B e TBM850 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1009: ...TBM 700 850 SUPPLEMENT 55 IAC AR CERTIFIED AIRPLANES Page 9 55 10 Rev 0 10 On pilot door if installed a TBM700B b TBM850 11 TBM700A On access door External side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1010: ...MENT 55 IAC AR CERTIFIED AIRPLANES TBM 700 850 Page 9 55 11 Rev 0 12 TBM700B TBM850 On pilot door if installed External side 13 On access door External side TBM700B TBM850 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1011: ...NT 55 IAC AR CERTIFIED AIRPLANES Page 9 55 12 Rev 0 14 Under the window on L H side at the level of intermediate seats TBM700A TBM700B TBM850 15 On cabinet drawer TBM700A TBM700B TBM850 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1012: ... CERTIFIED AIRPLANES TBM 700 850 Page 9 55 13 Rev 0 16 On aisle side of rear seats TBM700A PRE MOD70 019 25 17 Under seating of L H intermediate seat on FWD side TBM700A TBM700B TBM850 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1013: ...TBM 700 850 SUPPLEMENT 55 IAC AR CERTIFIED AIRPLANES Page 9 55 14 Rev 0 18 On emergency exit handle TBM700A TBM700B TBM850 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1014: ...C AR CERTIFIED AIRPLANES TBM 700 850 Page 9 55 15 Rev 0 19 On emergency exit handle external side TBM700A TBM700B TBM850 20 TBM700B TBM850 On outer fuselage skin aft of access door PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1015: ...MENT 55 IAC AR CERTIFIED AIRPLANES Page 9 55 16 Rev 0 21 TBM700B TBM850 In the cabin forward of access door 22 TBM700A TBM700B TBM850 On last step of stairs STAIRS MAX LOAD ONE PERSON PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1016: ...SUPPLEMENT 55 IAC AR CERTIFIED AIRPLANES TBM 700 850 Page 9 55 17 Rev 0 23 TBM700B TBM850 On R H access door jamb DO NOT USE HAND RAIL TO RETRACT OR STOW STAIRS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1017: ...s 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 Red or amber failure warnings are coupled with the lighting of a flashing red indicator or a fixed amber indicator Both indicators are located on the upper part of the instrument panel When either one lights up press it once to ...

Page 1018: ...AS 100 KIAS IAS 105 KIAS 3 Power as necessary to maintain airspeed according to an easy approach slope 300 ft min 4 Adjust aircraft pitch using manual pitch trim wheel and engine thrust 5 When ground approaches decrease slope progressively 6 Reduce power just before touchdown CAUTION ENGINE POWER INCREASE EFFECT IS NOSING UP DECREASE EFFECT IS NOSING DOWN CAUTION IN CASE OF CONTROL DISCONNECTION A...

Page 1019: ... LDG 2 Normal landing CAUTION CONTROL AIRCRAFT DIRECTION BY MEANS OF AILERONS LANDING WITHOUT AILERONS 1 Configuration LANDING GEAR DN FLAPS TO 2 Airspeed Maintain IAS as below Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 100 KIAS IAS 105 KIAS CAUTION CONTROL AIRCRAFT DIRECTION BY MEANS OF RUDDER PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1020: ...ILURE Symptoms Propeller de icing green light is not lit Propeller vibrations Intensive ice accumulation on the windshield Abnormal airplane behaviour 1 REDUCE power 2 ACTUATE propeller governor lever to vary RPM within operating range 3 LEAVE icing conditions as soon as possible PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1021: ...ed in Section 4 Normal Procedures of the basic Pilot s Operating Handbook 4 3 CHECK LIST PROCEDURES TOUCH AND GO After wheels touch 1 Flaps TO 2 Power lever Display TRQ 100 3 Takeoff ROTATION See Takeoff distances Chapter 5 9 Normal takeoff ATTITUDE 7 5 Short takeoff Weight 6579 lbs 2984 kg ATTITUDE 15 Weight 6579 lbs 2984 kg ATTITUDE 12 5 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1022: ... Short takeoff Weight 6579 lbs 2984 kg ATTITUDE 15 Weight 6579 lbs 2984 kg ATTITUDE 12 5 Rotation speed at takeoff according to airplane weight is also given in Chapter 5 9 However the pilot s operating handbook does not supply distances concerning touch and go These distances are let to pilot s initiative In case of air leak between the solenoï d valve and the torque limiter the available torque ...

Page 1023: ... with visibility of one mile 1 6 km or less rain snow sleed or ice crystals 2 Icing conditions also exist when the OAT on the ground is 13 C or below and when operating on ramps taxiways or runways where surface snow ice standing water or slush may be ingested by the engine or freeze on engine or cowlings NOTE Refer to Figure 5 5 1 to convert OAT to SAT in flight SAT OAT 2 C on the ground 3 Flight...

Page 1024: ...t enter or leave as soon as possible icing conditions Apply LEADING EDGES DEICING FAILURE emergency procedure Ice protection procedures 1 Prior to entering IMC as a preventive If 0 C OAT 13 C PROP DE ICE switch ON INERT SEP switch ON If 15 C OAT 0 C All DE ICE SYSTEM switches ON IGNITION switch ON INERT SEP switch ON If 25 C OAT 15 C All DE ICE SYSTEM switches ON INERT SEP switch ON If OAT 25 C PR...

Page 1025: ...scent 200 KIAS is anticipated into known icing conditions position INERT SEP switch to ON before accelerating This will avoid reducing speed below 200 KIAS during descent to set the inertial separator IF AIRPLANE LEAVES ICING CONDITIONS MAINTAIN INERT SEP ON AS LONG AS ICE THICKNESS ON NON DEICED VISIBLE PARTS EXCEEDS 15 mm OR INCH This will avoid ice fragments coming from propeller spinner and be...

Page 1026: ...e flaps as required for final approach and landing at minimum speeds noted above Ice accumulation effects When ice has accumulated on the unprotected surfaces of the airplane aerodynamic characteristics may be changed Particularly stall speeds may increase by up to Flaps UP 20 KIAS Flaps TO 15 KIAS Flaps LDG 10 KIAS Correct operation of the aural stall warning may be altered by severe or prolonged...

Page 1027: ...nertial separator limitations ITT limitation Because of the higher landing speed landing distances will be increased In the landing configuration using 90 KIAS approach speed increases landing distance by 20 refer to Chapter 5 14 LANDING DISTANCES STALL The characteristics are conventional An aural warning is provided by stall warning horn which sounds between 6 and 10 knots above the stall in all...

Page 1028: ...after supplement those of standard airplane described in Section 5 Performance of the basic Pilot s Operating Handbook 5 1 WIND COMPONENTS The runway condition changes the full crosswind limits as follows Dry runway μ 0 6 20 kts Wet runway μ 0 45 15 kts Iced runway μ 0 3 10 kts PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1029: ...1329 1526 1493 1657 1837 2051 2329 1017 1132 1280 1444 1657 1591 1772 1968 2215 2510 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1083 1214 1363 1575 1804 1690 1870 2100 2379 2707 1148 1296 1476 1690 1968 1788 1985 2247 2559 2920 1214 1378 1575 1837 2100 1903 2133 2411 2756 3133 1247 1444 1640 1919 2198 1969 2231 2526 2887 3281 Figure 5...

Page 1030: ... 1837 2067 2001 2198 2461 2723 3051 1378 1542 1739 1968 2231 2133 2362 2625 2920 3281 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1476 1673 1870 2100 2428 2264 2493 2789 3117 3543 1575 1772 2001 2297 2657 2395 2657 2953 3346 3839 1690 1903 2149 2461 2854 2559 2854 3182 3609 4134 1755 1969 2231 2543 2969 2657 2953 3314 3740 4298 Figure ...

Page 1031: ...675 3055 2675 2955 3285 3675 4135 2035 2280 2545 2890 3315 2840 3150 3510 3955 4445 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 2165 2445 2740 3135 3560 3020 3365 3760 4235 4760 2315 2595 2955 3380 3855 3200 3580 4035 4530 5105 2480 2780 3185 3625 4170 3415 3805 4300 4825 5450 2560 2920 3330 3805 4380 3530 3990 4480 5055 5710 Figure 5 ...

Page 1032: ... 2725 2920 1740 1870 2035 2200 2360 2330 2495 2660 2855 3020 1840 1970 2135 2300 2495 2430 2590 2790 2955 3180 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1905 2070 2230 2395 2590 2530 2690 2890 3050 3280 2000 2135 2330 2530 2725 2625 2790 2985 3215 3410 2070 2230 2430 2625 2855 2690 2890 3085 3315 3570 2135 2300 2495 2690 2920 2790 29...

Page 1033: ...30 2360 2490 1180 1245 1345 1445 1540 2070 2200 2330 2460 2590 1215 1310 1410 1510 1610 2135 2265 2395 2525 2690 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1280 1345 1445 1575 1705 2200 2330 2460 2645 2790 1310 1410 1510 1640 1770 2300 2430 2560 2720 2885 1380 1475 1575 1705 1835 2360 2495 2655 2820 2985 1445 1540 1640 1770 1900 2430 ...

Page 1034: ...0 2360 2490 1000 1065 1150 1230 1310 2070 2200 2330 2460 2590 1030 1115 1200 1280 1360 2135 2265 2395 2525 2690 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1080 1150 1230 1345 1445 2200 2330 2460 2645 2790 1115 1200 1280 1395 1510 2300 2430 2560 2720 2885 1180 1245 1345 1445 1560 2360 2495 2655 2820 2985 1230 1310 1395 1510 1610 2430 2...

Page 1035: ...IED AIRPLANES Page 9 55 36 Rev 0 SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard airplane in Section 6 Weight and Balance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1036: ... Russian certification SOCATA X X X 21 ENVIRONMENTAL SYSTEM S General Air System Controller GASC 82024A020 LIEBHERR 0 900 7 900 Post MOD70 0207 X S General Air System Controller GASC 82024A030 LIEBHERR 0 900 7 900 Post MOD70 0207 X 21 20 Distribution S Cabin fan AVVC 00244 VETUS 1 500 6 400 X X S Mixing unit 9723A010001 LIEBHERR 0 240 3 850 Post MOD70 0207 X S Hot Air Distributor 6044A010001 LIEBH...

Page 1037: ...X S Check valve 985C 63 3 LE BOZEC 0 090 3 000 X X S Outflow valve controller 130618 1 GARRETT 0 750 4 000 X X S Outflow valve 103760 1 GARRETT 0 700 8 060 X X S Outflow valve 81146A010101 LIEBHERR 1 800 8 060 Post MOD70 0207 X S Safety valve 103760 2 GARRETT 0 700 8 060 X X S Safety valve 81147A010101 LIEBHERR 1 500 8 060 Post MOD70 0207 X S 0176 00I Selected cabin altitude repeater potentio mete...

Page 1038: ...10002 LIEBHERR 0 050 2 600 Post MOD70 0207 X S Shut off valve 4589A010001 LIEBHERR 1 075 2 900 Post MOD70 0207 X S Intermediate pressure sensor 93557A010001 LIEBHERR 0 150 2 800 Post MOD70 0207 X S Overheat thermal switch A042010300 5 LIEBHERR 0 080 2 800 Post MOD70 0207 X S Main heat exchanger 81249A010001 LIEBHERR 3 500 2 750 Post MOD70 0207 X S Ground Fan 8031A010 LIEBHERR 1 790 2 300 Post MOD7...

Page 1039: ...ated sensor 92279A010002 LIEBHERR 0 080 4 625 Post MOD70 0207 X S Cabin ventilated sensor 92279A010002 LIEBHERR 0 080 6 350 Post MOD70 0207 X 22 AUTO FLIGHT S 0176 00A AFCS GFC 700 composed of GARMIN From S N 434 plus S N 269 X Pitch servo GSA 81 Servo mount GMS 85 GARMIN 1 750 6 284 X Roll servo GSA 81 Servo mount GMS 85 GARMIN 1 750 5 870 X Yaw servo GSA 81 Servo mount GMS 85 GARMIN 1 750 6 444 ...

Page 1040: ...ker Qty 2 AB 100 SC ALPINE ELEC TRONICS 0 350 4 600 X X X S 0176 00A Dual audio system with integrated Marker Beacon Receiver 1 GMA 1347C GARMIN 1 170 3 895 From S N 434 plus S N 269 X S 0176 00A Dual audio system with integrated Marker Beacon Receiver 2 GMA 1347C GARMIN 1 170 3 895 From S N 434 plus S N 269 X S 0176 00A G1000 COM 1 system GARMIN From S N 434 plus S N 269 X Transceiver integrated ...

Page 1041: ...cept S N 205 and 240 X X S 0276 00A G1000 COM 1 system GARMIN From S N 14 to 243 X X Transceiver integrated in GIA 63W Integrated Avionics Unit 1 refer to ATA 34 28 GARMIN except S N 205 and 240 X X VHF antenna under fuselage 16 21B P3 CHELTON 0 390 6 900 X X S 0276 00A G1000 COM 2 system GARMIN From S N 14 to 243 X X Transceiver integrated in GIA 63W Integrated Avionics Unit 2 refer to ATA 34 28 ...

Page 1042: ...0GC02Y04 Freon ignition priority ECE 5 000 3 250 X X R Electric power center 160GC02Y05 Freon ignition priority contact splitting ECE 5 000 3 250 S N 92 9999 and S N 1 92 after SB70 031 24 X X X R Stand by generator T700A2430045900 SOCATA 5 500 2 600 X X R Stand by generator T700A2430080900 SOCATA 5 500 2 600 X X R Stand by generator T700A243008000601 SOCATA 5 500 2 600 X R Starter generator 8012F...

Page 1043: ...om S N 434 plus S N 269 X Carpet furnishings SOCATA 137 19 5 370 X S 25026B Partition net between the cabin and the bag gage compartment SOCATA 1 650 7 354 X S 25018A Smoke goggles PURITAN 0 260 5 080 X Seats Belts Standard equipment S Seats 6 places without oxygen equipment Valid S N 1 to 23 25 28 33 and 35 except airplanes equipped as a retrofit with MOD70 019 25 X Pilot s seat T700A2512000 SOCA...

Page 1044: ...Pilot s seat PPI 13 470 4 640 X X Front R H seat PPI 13 470 4 640 X X Intermediate seat back to flight direction PPI 11 570 5 545 X X Rear divan Model 3028 P N 303437 3 Valid up to S N 67 plus S N 72 to 75 except airplanes equipped as a retrofit with MOD70 023 25 ERDA 34 000 6 891 X X Rear divan T700A252123000 Valid from S N 68 except S N 72 to 75 plus airplanes equipped as a retrofit with MOD70 0...

Page 1045: ...ck to flight direc tion T700C2500003003 SOCATA 16 000 5 612 X S Double chair X L H seat T700C2500005002 SOCATA 24 000 7 066 X R H seat T700C2500005003 SOCATA 24 000 7 066 X 25 61 Emergency locator transmitter S 0273 25B Emergency beacon KANNAD 406 AF Com pact automatic fixed installed in cabin under seat of which ELT 406 AF compact Antenna ANT300 SERPE IESM 1 040 0 850 0 150 6 933 6 890 7 960 Post...

Page 1046: ...0 5 400 X X R Roll trim actuator 145700 02 LPMI 0 700 5 400 X X X 27 20 Yaw control R Rudder trim actuator 145700 01 LPMI 0 700 10 040 X X R Rudder trim actuator 145700 02 LPMI 0 700 10 040 X X X S AFC and electric trim control on R H control wheel SOCATA 0 400 4 000 X 27 30 Pitch control S Pitch trim actuator 145400 01 LPMI 0 550 10 800 X X S Pitch trim actuator 145400 02 LPMI 0 550 10 800 X X X ...

Page 1047: ...R Engine driven fuel pump 1127 01 IN LHC 0 700 2 800 X X R Engine driven fuel pump 1127 01A IN LHC 0 700 2 800 X X X R Engine driven fuel pump 1127 02A IN LHC 0 700 2 800 Post MOD70 0237 08 X X X R Fuel sequencer unit E3 003 00 STPI 0 800 3 200 X X R Fuel unit 35001C14 1 LE BOZEC 2 500 3 380 X X R Fuel unit L88A15 651 INTER TECHNIQUE 2 080 3 380 X X X R Fuel sequencer unit TFE 0 500 3 200 X 28 40 ...

Page 1048: ...0 150 4 650 X X X R Inboard R H probe 762 439 1 0 INTER TECHNIQUE 0 150 4 650 X R Intermediate probe 766 976 1 or 762 440 1 0 INTER TECHNIQUE 0 100 4 850 X X X R Intermediate probe 762 440 1 0 INTER TECHNIQUE 0 100 4 850 X R Low level probe 722 447 INTER TECHNIQUE 0 050 4 650 X X X R Outboard probe 766 977 1 or 762 441 1 0 INTER TECHNIQUE 0 100 4 850 X X X R Outboard probe 762 441 1 0 INTER TECHNI...

Page 1049: ...g SOCATA 2 600 4 400 X X X S Deicer T700A3010001004 middle L H wing SOCATA 1 700 4 400 X X X S Deicer T700A3010001005 middle R H wing SOCATA 1 700 4 400 X X X S Deicer Std T700A3010001006 outboard L H wing SOCATA 1 500 4 400 X X S Deicer T700A3010012000 outboard L H wing SOCATA 1 200 4 400 X S Deicer T700A3010001007 outboard R H wing SOCATA 1 500 4 400 X X X S Dual port distribution valve 1532 10C...

Page 1050: ... controller Qty 2 L H R H TWH 93 01 AIR SYSTEMS 0 450 3 800 From S N 434 plus S N 269 X 30 60 Propeller deicing S Deicing kit 67 600 2 GOODRICH 0 800 1 230 X X S Modular brush assy 3E2044 2 BF GOODRICH 0 200 1 195 X S Timer 3E2311 4 BF GOODRICH 0 200 5 100 X 31 INDICATING RECORDING SYSTEMS 31 20 Independent instruments S Hourmeter 56457 3 flying time DATCON 0 250 3 970 X 31 50 Aural warning R Aura...

Page 1051: ...landing gear 21135 002 00 ERAM 22 700 5 090 X X R R H main landing gear 21136 001 00 ERAM 22 700 5 090 X X R R H main landing gear 21136 002 00 ERAM 22 700 5 090 X X R L H main landing gear D23767000 MESSIER DOWTY 23 400 5 090 X O L H main landing gear D23767000 MESSIER DOWTY 23 400 5 090 Post MOD70 0141 32 X X R R H main landing gear D23768000 MESSIER DOWTY 23 400 5 090 X O R H main landing gear ...

Page 1052: ...and pump 914 8D27 TELEDYNE 1 055 4 600 X X X 32 35 Hydraulic generation R Hydraulic power pack LHC X X up to S N 10 1118 02 or 03 2 970 2 150 X X from S N 11 1118 03 2 970 2 150 X X from S N 1 1118 04 4 700 2 150 From S N 1 retrofit X X X 32 40 Wheels and brakes R Brake assembly 030 19100 PARKER 6 800 5 190 X X X R Main tire 18x5 5 8PR TL DUNLOP 6 000 5 190 X X R Main tire 18x5 5 8 190T MICHELIN 5...

Page 1053: ...ATOR 2 540 2 275 X X R Nose wheel 40 262A PARKER 1 350 2 275 X X X R Main wheel Model 40 270 040 27000 PARKER 5 000 5 190 X X R Main wheel Model 40 434 PARKER 5 120 5 190 X R Parking brake valve 060 01600 PARKER 0 150 4 000 X X R Parking brake valve T700A3240010 or T700B3240001 SOCATA 0 150 4 000 X 33 LIGHTS 33 10 Instrument panel lighting S Panel lights regulator T700A3310025 SOCATA X X X S Instr...

Page 1054: ...S Taxi light assembly T700A3340006 SOCATA 0 500 2 380 X S NAV Anticollision system WHELEN X X S Anticollision power supply A413A HDA DF 28 WHELEN 1 360 5 200 X X S Anticollision power supply A413A HDA DF 14 28 WHELEN 1 360 5 200 X X S Anticollision power supply A413A HDA CF 14 28 WHELEN 1 360 5 200 X X S R H navigation light assy A600 PG 28 WHELEN 0 230 4 700 X X S R H navigation light assy A600 P...

Page 1055: ...onment data 34 11 Air data systems R Lift transducer 799 5 SAFE FLIGHT INSTRUMENTS 0 400 4 400 X X R Lift transducer 799 8 S AFE FLIGHT INSTRUMENTS 0 400 4 400 X X X S Pitot heated probe AN 5812 1 QPL AIR CRAFT APPLIANCES AND EQUI LTD 0 340 5 100 Up to S N 433 except S N 269 X X S Pitot L heated probe AN 5812 1 QPL AIR CRAFT APPLIANCES AND EQUI LTD 0 340 5 100 From S N 434 plus S N 269 X S Pitot R...

Page 1056: ...Data Computer 2 GDC 74B GARMIN 1 050 3 816 From S N 434 plus S N 269 X S 0276 00A Air Data Computer 1 GDC 74B GARMIN 1 050 3 816 From S N 14 to 243 except S N 205 and 240 X X S 0276 00A Air Data Computer 2 GDC 74B GARMIN 1 050 3 816 From S N 14 to 243 except S N 205 and 240 X X 34 20 Attitude and direction 34 21 Heading reference system S 0176 00A Attitude and Heading Reference System 1 GRS 77 GAR...

Page 1057: ...MU 44 GARMIN 0 220 4 597 From S N 14 to 243 except S N 205 and 240 X X S 0276 00A Magnetometer 2 GMU 44 GARMIN 0 220 4 597 From S N 14 to 243 except S N 205 and 240 X X 34 23 Magnetic compass R Stand by compass C2350 DL4CM AIRPATH 0 250 4 150 X X R Stand by compass C2350 L4CM23 AIRPATH 0 250 4 150 X X X 34 24 ADI and standby horizon S Stand by ADI 1U149 019 19 SIGMATEK 1 900 3 875 X X X 34 28 Elec...

Page 1058: ...U 475 GARMIN 0 370 4 009 X S 0276 00A Integrated Flight Deck System G1000 com posed of From S N 14 to 243 except S N 205 and 240 X X PFD1 GDU 1040A GARMIN 2 960 3 955 X X PFD2 GDU 1040A GARMIN 2 960 3 955 X X MFD GDU 1500A GARMIN 3 930 3 942 X X Engine Airframe Interface Unit 1 GEA 71 GARMIN 1 150 3 826 X X Engine Airframe Interface Unit 2 GEA 71 GARMIN 1 150 3 826 X X Integrated Avionics Unit 1 G...

Page 1059: ...7D dual audio systems refer to ATA 23 Post MOD70 0276 00 From S N 14 to 243 except S N 205 and 240 X X 34 50 Dependent position determining 34 51 NAV 1 installation S VHF GS NAV antenna DM N4 17N DORNE MARGOLIN 1 500 10 200 X X X S Receiver integrated in the GIA 63W Integrated Avionics Unit 1 refer to ATA 34 28 X X X 34 52 NAV 2 installation S Receiver integrated in the GIA 63W Integrated Avionics...

Page 1060: ...rom S N 14 to 243 except S N 205 and 240 X X Antenna KA 61 0 180 4 908 X X 34 57 Global Positioning System GPS S 0176 00A GPS WAAS Antenna GA 36 GARMIN 0 210 5 203 From S N 434 plus S N 269 X S 0176 00A GPS WAAS XM Antenna GA 37 GARMIN 0 230 5 203 From S N 434 plus S N 269 X S 0276 00A GPS WAAS Antenna GA 36 GARMIN 0 21 5 203 From S N 14 to 243 except S N 205 and 240 X X S 0276 00A GPS WAAS XM Ant...

Page 1061: ...ith OPT70 35001 X X 5 330 X X 6 530 X X S 0207 00 Gaseous oxygen system EROS INTER TECHNIQUE 10 310 5 760 Post MOD70 0220 00 X 37 VACUUM S Air ejector valve 19E17 5A LUCAS 0 300 2 950 X X X S Gyro suction gage 3 310 5 UMA 0 065 4 000 X X X S Gyro vacuum air filter 1J7 2 AIRBORNE 0 170 3 550 X X X S Regulator and relief valve 38E 96 2D LUCAS 0 600 2 950 X X X S Vacuum relief valve 691 21A LUCAS 0 1...

Page 1062: ...or MOD70 57 WINGS S 57001A Utilization on runways covered with melting snow SOCATA a 3 500 5 080 X X 61 PROPELLER 61 10 Propeller assembly S Propeller HC E4N 3 E 9083 S K HARTZELL 69 500 1 095 X X X 61 20 Controls R Overspeed governor A210632 WOODWARD 1 240 1 500 X X X S Propeller governor 8210 007 WOODWARD 1 200 1 500 X X X 71 POWER PLANT R Turboprop engine PT6 A 64 P W CANADA 225 000 2 025 Pre M...

Page 1063: ...00 09 LPMI 0 780 1 600 X X R Inertia ice separator actuator 148600 09A LPMI 0 780 1 600 X X X 77 ENGINE INDICATING R Compressor turbine tacho generator Ng MIL G 26611C GEU 7 A QPL AIR CRAFT APPLIANCES AND EQUI LTD 0 445 2 750 X X X R Power turbine tacho generator MIL G 26611 GEU 7 A P N 32005 007 QPL AIR CRAFT APPLIANCES AND EQUI LTD 0 445 1 400 Pre MOD70 0188 X X R Power turbine tacho generator M...

Page 1064: ... A APPLICABILITY OR EFFECTIVITY ARM m WEIGHT per unit kg EQUIPMENT SUPPLIER REQUIRED R OR STANDARD S OR SPARES O EQUIPMENT ITEM OPT70 or MOD70 77 12 Fuel management S Fuel flow transducer 660 526A SHADIN 0 454 2 799 X X X 79 LUBRICATION 79 20 Distribution R Oil cooler L8538233 LORI 4 750 2 300 X X X 79 30 Indicating R 79001A Oil pressure transmitter 8107 400 00 10 MORS SEX TANT 0 200 2 700 X X X P...

Page 1065: ...eglig X X X A 0176 00B Data link GDL 69A interfaced with G1000 system GARMIN 1 160 3 827 From S N 434 plus S N 269 X A 0276 00B Data link GDL 69A interfaced with G1000 system GARMIN 1 160 3 827 From S N 14 to 243 except S N 205 and 240 X X O 23011A Radio headset H10 13 4 DAVID CLARK X X O 23011B Radio headset 7001 PELTOR X X O 23011C Radio headset HMEC 25 KA SENNHEISER X X O 23011D Radio stereo he...

Page 1066: ...4A Leather upholstering version A SOCATA 3 000 5 400 X X A 25004B Leather upholstering version B SOCATA 3 000 5 400 X X A 25004C Leather upholstering version C SOCATA 3 000 5 400 X X A 25004D Leather upholstering version D SOCATA 3 000 5 400 X X X A 25005A JEPPESEN filing cabinet SOCATA 5 580 5 107 S N 1 to 39 X A 25005B JEPPESEN filing cabinet PPI SOCATA 8 500 5 150 S N 40 to 9999 plus 24 and 36 ...

Page 1067: ... 40 to 244 except 205 X X A 0171 25 Generation 2005 cabinets SOCATA From S N 328 X Version A L H low cabinet SOCATA 4 300 5 175 X Version B R H low cabinet SOCATA 4 300 5 175 X Version C Removable low insulated picnic bag SOCATA 4 300 5 175 X Version D L H tall storage cabinet SOCATA 3 500 5 175 X Version E R H tall storage cabinet SOCATA 3 500 5 175 X Version F R H tall storage cabinet audio SOCA...

Page 1068: ...TA 16 000 5 370 From S N 434 plus S N 269 X O 25025A Cabin furnishings LUXE SOCATA 3 500 7 325 S N 137 to 243 except 205 and 240 X O 25025B Cabin furnishings VIP SOCATA 3 500 7 325 S N 137 to 243 except 205 and 240 X A 25026A Partition net between the cabin and the baggage compartment SOCATA 1 250 7 354 Post MOD70 019 25 X X OPT70 25026B S A 25028A 28V plugs lighter SOCATA X X A 25032 Front seats ...

Page 1069: ...id kit SOCATA 1 800 7 250 X X 25 61 Emergency locator transmitter O 25030C Three frequency emergency locator transmitter C406 1 with base NAV interfaced with G1000 system GPS source airplanes equipped with reinforcement of which ARTEX 3 459 8 900 Post MOD70 0176 00 X ELT C406 1 ARTEX 1 525 9 010 X ELT NAV interface box 453 6500 ARTEX 1 220 8 970 X Antenna 21 41 CHELTON 0 140 8 095 X O 25030D Three...

Page 1070: ... 1 525 9 010 X Antenna 110 338 ARTEX 0 204 8 095 X O 25030F Three frequency emergency locator transmitter C406 1 with base NAV interfaced with G1000 system GPS source airplanes equipped with reinforcement of which ARTEX 3 523 8 888 Post MOD70 0176 00 X ELT C406 1 ARTEX 1 525 9 010 X ELT NAV interface box 453 6500 ARTEX 1 220 8 970 X Antenna 110 338 ARTEX 0 204 8 095 X 26 FIRE PROTECTION A 26001A P...

Page 1071: ...70 A 26002C Engine fire detection system L HOTELLIER 0 660 2 440 From S N 434 plus S N 269 X A 26002D Engine fire detection system L HOTELLIER 0 660 2 440 Post MOD70 0276 00 From S N 14 to 243 except S N 205 and 240 X X 27 FLIGHT CONTROLS 27 20 Yaw control A 27001A AFC and electric trim control on R H control wheel SOCATA 0 400 4 000 X X S 27 50 Wing flaps control O 27002A Flap control LPMI 7 910 ...

Page 1072: ...TA 1 200 4 400 TBM700A B equipped with optional MOD70 0276 00C Weather radar X X 31 INDICATING RECORDING SYSTEMS 31 20 Independent instruments O 31002A Hourmeter 56457 3 engine running time DATCON 0 250 3 970 X X X O 31002B Hourmeter 56457 3 flying time DATCON 0 250 3 970 X X S 33 LIGHTS 33 10 Instrument panel lighting A 33001B PULSELITE control Ref 1NC P N 1220 2410 2 PRECISE FLIGHT 0 574 5 146 F...

Page 1073: ...X X 34 NAVIGATION 34 28 Electronic flight instrumentation system A 0226 00 G1000 Synthetic Vision System GARMIN Post MOD70 0176 00 and MOD70 0225 00 X A 0222 00 Electronic checklists technical content TBM850 Checklist V1 0 GARMIN Post MOD70 0176 00 X 34 41 Stormscope A 34056B Stormscope WX 500 G1000 coupled of which BFG 2 240 5 900 From S N 434 plus S N 269 X Antenna NY163 BFG 0 380 7 900 X Proces...

Page 1074: ...radar GWX 68 GARMIN 4 250 4 406 From S N 14 to 243 except S N 205 and 240 X X 34 43 Radioaltimeter A 34037L Radioaltimeter KRA 405B G1000 coupled without KNI 415 or aural warning of which 2 600 5 318 Post MOD70 0176 00 X Transceiver KRA 405B HONEYWELL 1 270 5 872 X Antennas DM 19 2 1 DORNE MARGOLIN 0 090 and 0 090 4 625 5 228 X X A 34037M Radioaltimeter KRA 405B G1000 coupled without KNI 415 or au...

Page 1075: ... 625 5 228 X X A 0270 34B Radioaltimeter RA4500 G1000 coupled of which 1 134 5 600 Post MOD70 0276 00 From S N 14 to 243 except S N 205 and 240 X X Transceiver RA4500 FREEFLIGHT 0 862 5 812 X X Antennas S67 2002 SENSOR SYSTEMS 0 136 and 0 136 4 625 5 228 X X X X 34 44 Traffic advisory system A 34061D TAS system KTA 870 G1000 coupled of which HONEYWELL 5 17 3 357 Post MOD70 0176 00 X Processor KTA ...

Page 1076: ...58 under fuselage GARMIN 0 360 6 620 X A 0258 00C TAS system GTS 820 G1000 coupled of which GARMIN 10 220 4 513 Post MOD70 0276 00 From S N 14 to 243 except S N 205 and 240 X X Processor GTS 820 GARMIN 4 500 3 635 X X Power amplifier low noise amplifier GPA 65 GARMIN 0 860 5 624 X X Antenna GA 58 upper fuselage GARMIN 0 360 5 860 X X Antenna GA 58 under fuselage GARMIN 0 360 6 620 X X 34 50 Depend...

Page 1077: ...3 Mode S non diversity GARMIN 1 750 3 801 From S N 14 to 243 except S N 205 and 240 X X Antenna KA 61 0 180 4 908 X X A 0264 34 Transponder 1 GTX 33D Mode S diversity with extended squitter GARMIN 1 870 3 801 From S N 434 plus S N 269 X Antenna KA 61 under fuselage 0 180 3 812 X Antenna KA 61 upper fuselage 0 180 4 908 X 34 54 Automatic Direction Finder ADF A 0176 00H ADF RA 3500 system BECKER 3 4...

Page 1078: ... N 205 and 240 X X Antenna KA 61 0 180 6 066 X X 34 62 Multifunction display A 0176 00G G1000 Chartwiew function GARMIN From S N 434 plus S N 269 X A 0276 00G G1000 Chartwiew function GARMIN From S N 14 to 243 except S N 205 and 240 X X 35 OXYGEN O 35001C Gaseous oxygen system 30000 ft EROS INTER TECHNIQUE 10 400 4 526 Post MOD70 0276 00 From S N 14 to 243 except S N 205 and 240 X X O 35001D Gaseo...

Page 1079: ...NT SUPPLIER OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 57 WINGS O 57001A Utilization on runways covered with melting snow SOCATA a 3 500 5 080 From S N 1 to 110 Standard from S N 111 X 79 LUBRICATION 79 30 Indicating A 0169 79C Chip detection system 2 detectors interfaced with G1000 system PWC Neglig Post MOD70 0176 00 X A 0169 79D Chip detection system 1 or 2 detectors interfaced with G1000 sy...

Page 1080: ...age 9 55 81 Rev 0 SECTION 7 DESCRIPTION Information hereafter supplement those given for the standard airplane in Section 7 Description of the basic Pilot s Operating Handbook Figure 9 55 1 GENERAL ALARMS WARNING LIGHTS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1081: ...TBM 700 850 SUPPLEMENT 55 IAC AR CERTIFIED AIRPLANES Page 9 55 82 Rev 0 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1082: ...tation rudder pedals adjusting handle 9 Circuit breakers panel postlight 10 Servicing plug 11 Cabin emergency air control RAM AIR control knob 12 Static source selector 13 ECS air conditioning control panel 14 Electric pitch trim control 15 Electric rudder trim control 16 Maps reading tablet 17 AP DISC TRM INT red push button 18 General alarm red and amber indicators Figure 9 55 2 1 2 RIGHT INSTRU...

Page 1083: ...TBM 700 850 SUPPLEMENT 55 IAC AR CERTIFIED AIRPLANES Page 9 55 84 Rev 0 Figure 9 55 2 2 2 RIGHT INSTRUMENT PANEL Typical arrangement PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1084: ... 0 SUPPLEMENT GARMIN GSR 56 WEATHER DATALINK AND SATELLITE PHONE TABLE OF CONTENTS Page 1 GENERAL 9 56 2 2 LIMITATIONS 9 56 2 3 EMERGENCY PROCEDURES 9 56 3 4 NORMAL PROCEDURES 9 56 4 5 PERFORMANCE 9 56 5 6 WEIGHT AND BALANCE 9 56 5 7 DESCRIPTION 9 56 5 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1085: ...e GMA TEL input can be activated at all time of flight for the front passenger and passengers to have the GSR56 telephone audio functions USE OF PHONE BY PIC PROHIBITED DURING ALL AIRCRAFT OPERATIONS WEATHER DATALINK functions The GSR 56 weather datalink is only an advisory weather source it does not relieve the pilot to comply with the applicable operational regulation in terms of flight preparat...

Page 1086: ...e approved under FCC ID Q639522B and registered by the ITU International Telecommunication Union for international use according to the GMPCS MoU The receiver transmitter RF module embedded in the GSR 56 is a 9522 B manufactured by Iridium Satellite LLC Terms of use are subject to changes and are available from the ITU website 2 1 PLACARDS Under L H front side window under instruction plate SECTIO...

Page 1087: ...in Section 2 Limitations of this Supplement BEFORE STARTING ENGINE On L H GMA audio panel 1 TEL button OFF BEFORE STARTING A PHONE CALL IN FLIGHT On L H GMA audio panel 1 TEL button OFF If passengers intend to take part into a phone call 2 CABIN button OFF If front passenger intends to take part into a phone call 3 INTRCOM button OFF On R H GMA audio panel 4 TEL button ON If passengers intend to t...

Page 1088: ...t s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 23 COMMUNICATIONS A Weather datalink and satellite phone system GSR 56 coupled with GARMIN system MOD70 0331 23 GARMIN 3 82 1 736 58 03 1 474 SECTION 7 DESCRIPTION GARMIN GSR 56 weather datalink and satellite phone system provides airborne low speed datalink and voice communication capability to GARM...

Page 1089: ... not supported by the GSR 56 it is not possible to access the GSR 56 voice mail from the aircraft there is no indication on the GARMIN integrated flight deck system when a new message has been left on the GSR 56 voice mail The controls for the MFD are located on both the MFD bezel and the MFD control unit keyboard The telephone audio including the incoming call ringing is controlled by the TEL but...

Page 1090: ... TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES TABLE OF CONTENTS Page 1 GENERAL 9 57 2 2 LIMITATIONS 9 57 2 3 EMERGENCY PROCEDURES 9 57 7 4 NORMAL PROCEDURES 9 57 7 5 PERFORMANCE 9 57 7 6 WEIGHT AND BALANCE 9 57 7 7 DESCRIPTION 9 57 8 8 HANDLING SERVICING AND MAINTENANCE 9 25 8 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1091: ...rplane when used for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES SECTION 2 LIMITATIONS These limitations supplement those of standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the TBM airplane is used for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES 2 1 PLACARDS 1 On access door Internal side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1092: ...H REGISTERED AIRPLANES TBM 700 850 Page 9 57 3 Rev 1 2 On access door External side 3 On pilot door External side if installed 4 On outer fuselage skin aft of access door and in the cabin forward of access door PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1093: ... PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES Page 9 57 4 Rev 1 5 On emergency exit handle Internal side Marking on cover Marking on handle 6 On emergency exit handle External side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1094: ...ES TBM 700 850 Page 9 57 5 Rev 1 7 On R H access door jamb 8 On last step of stairs 9 On rear passengers masks containers 10 On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1095: ...C TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES Page 9 57 6 Rev 1 11 Under window at L H intermediate seat 12 On rear passenger s table edge 13 On the chemical toilet cabinet curtain if installed PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1096: ...FOR FRENCH REGISTERED AIRPLANES does not change the basic normal procedures of the airplane described in Section 4 Normal procedures of the basic Pilot s Operating Handbook SECTION 5 PERFORMANCE Use of TBM airplane for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES does not change the basic performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handboo...

Page 1097: ...OR FRENCH REGISTERED AIRPLANES does not change Section 7 Description of the basic Pilot s Operating Handbook SECTION 8 HANDLING SERVICING AND MAINTENANCE Use of TBM airplane for PUBLIC TRANSPORTATION FOR FRENCH REGISTERED AIRPLANES does not change Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1098: ...ement and the basic POH it is attached to together with its further applicable Supplements are EASA approved on behalf of the Brazilian Aviation Authority ANAC The original version of this Supplement is meeting the ANAC requirements and is approved by EASA on behalf of the Brazilian Aviation Authority ANAC Approval number EASA letter DRO ana CT 2 2017 D 5550 Date November 16 2017 This airplane mus...

Page 1099: ...age Edit Rev Rev Date No No No No 9 59A 2 0 JUL 17 9 59B 2 0 JUL 17 9 59C 2 0 JUL 17 9 59D 2 0 JUL 17 9 59 1 2 0 JUL 17 9 59 2 2 0 JUL 17 9 59 3 2 0 JUL 17 9 59 4 2 0 JUL 17 9 59 5 2 0 JUL 17 9 59 6 2 0 JUL 17 9 59 7 2 0 JUL 17 9 59 8 2 0 JUL 17 9 59 9 2 0 JUL 17 9 59 10 2 0 JUL 17 9 59 11 2 0 JUL 17 9 59 12 2 0 JUL 17 9 59 13 2 0 JUL 17 9 59 14 2 0 JUL 17 9 59 15 2 0 JUL 17 9 59 16 2 0 JUL 17 PIM...

Page 1100: ... 20 2017 Pages Description All pages Supplement creation Approval The original version of this Supplement is an English version meeting the ANAC requirements It is EASA approved on behalf of the Brazilian Aviation Authority ANAC Approval number EASA letter DRO ana CT 2 2017 D 5550 Date November 16 2017 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1101: ...PILOT S OPERATING HANDBOOK SUPPLEMENT 59 BRAZIL SPECIFICS Edition 2 July 20 2017 Rev 0 Page 9 59 D INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1102: ...UPPLEMENT BRAZIL SPECIFICS TABLE OF CONTENTS Page 1 GENERAL 9 59 2 2 LIMITATIONS 9 59 3 3 EMERGENCY PROCEDURES 9 59 14 4 NORMAL PROCEDURES 9 59 14 5 PERFORMANCE 9 59 14 6 WEIGHT AND BALANCE 9 59 15 7 DESCRIPTION 9 59 15 8 HANDLING SERVICING AND MAINTENANCE 9 59 15 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1103: ...9 59 2 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 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1104: ...plane described in Section 2 Limitations of the basic Pilot s Operating Handbook 2 1 GENERAL TBM 700 airplane is certified under EASA A 010 and ANAC No 9307 Type Certificates 2 5 WEIGHT AND C G LIMITS WEIGHT LIMITS With 4 seat accommodation in rear part of pressurized cabin 396 lbs 180 kg with small or large net see sketch below Figure 2 5 1 Baggage limits PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1105: ...h Brazilian IS 21 013A use of GNSS GPS is prohibited under IFR unless other means of navigation suitable and approved for the intended route are installed and operational It must be possible at any point along the route to navigate to the destination or alternate using such means The SBAS functionality is not available in Brazil therefore operations that require such functionality such as GNSS ver...

Page 1106: ...or the small cargo net on frame C13bis For the large cargo net on R H side upholstery panel in the rear baggage compartment All On FWD baggage compartment door frame non pressurized 50 KG MÁXIMO PARA INSTRUÇÕES DE CARREGAMENTO CONSULTAR A SEÇÃO DE PESO E BALANCEAMENTO DO MANUAL DE VÔO PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1107: ...CS Edition 2 July 20 2017 Rev 0 Page 9 59 6 Near fuel tank caps On internal face of L H engine cowling Capacidade de óleo 12 l 12 7 qt On rear passenger s table casing A MESA DEVERÁ ESTAR RECOLHIDA PARA DECOLAGEM E POUSO PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1108: ...NDBOOK SUPPLEMENT 59 BRAZIL SPECIFICS Edition 2 July 20 2017 Rev 0 Page 9 59 7 On nose gear door On engine cowling in front of compartment door On pilot door External side if installed PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1109: ... 59 BRAZIL SPECIFICS Edition 2 July 20 2017 Rev 0 Page 9 59 8 On access door External side On outer fuselage skin aft of access door and in the cabin forward of access door On access door Internal side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1110: ... HANDBOOK SUPPLEMENT 59 BRAZIL SPECIFICS Edition 2 July 20 2017 Rev 0 Page 9 59 9 On pilot door Internal side if installed On emergency exit handle Marking on cover Marking on handle PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1111: ...tion 2 July 20 2017 Rev 0 Page 9 59 10 On last step of stairs On R H access door jamb On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling On rear passengers masks containers PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1112: ...ev 0 Page 9 59 11 On the oxygen service door Pre MOD70 0336 26 and Post MOD70 0391 26D On R H side at front seat level On the lower drawer of the R H cabinet All Airplanes equipped with MOD70 0505 25 Lavatory compartment On fixed panel cabin side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1113: ...LOT S OPERATING HANDBOOK SUPPLEMENT 59 BRAZIL SPECIFICS Edition 2 July 20 2017 Rev 0 Page 9 59 12 On fixed panel toilet side On access door cabin side and toilet side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1114: ...OOK SUPPLEMENT 59 BRAZIL SPECIFICS Edition 2 July 20 2017 Rev 0 Page 9 59 13 Behind access door cabin side and toilet side Front face of lavatory compartment near opening closing switches PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1115: ...S Edition 2 July 20 2017 Rev 0 Page 9 59 14 On the magazine rack and on side wall of storage volume SECTION 3 EMERGENCY PROCEDURES No specifics SECTION 4 PROCEDURES NORMALES No specifics SECTION 5 PERFORMANCE No specifics PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1116: ...irplane described in Section 6 Weight and balance of the basic Pilot s Operating Handbook S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 01 SPECIFIC OPTIONAL EQUIPMENT S 01004 Brazil certification markings SOCATA SECTION 7 DESCRIPTION No specifics SECTION 8 HANDLING SERVICING AND MAINTENANCE No specifics PIM DO NOT USE FOR FLIGHT OP...

Page 1117: ...PILOT S OPERATING HANDBOOK SUPPLEMENT 59 BRAZIL SPECIFICS Edition 2 July 20 2017 Rev 0 Page 9 59 16 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1118: ...OUT FUNCTION TABLE OF CONTENTS Page 1 GENERAL 9 60 2 2 LIMITATIONS 9 60 2 3 EMERGENCY PROCEDURES 9 60 3 4 NORMAL PROCEDURES 9 60 3 5 PERFORMANCE 9 60 3 6 WEIGHT AND BALANCE 9 60 3 7 DESCRIPTION 9 60 4 8 HANDLING SERVICING AND MAINTENANCE 9 60 5 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1119: ...T system has been shown to meet the equipment requirements of 14 CFR 91 227 The installed transponder system is able to respond to interrogations in Modes A C and S and is fully compliant with the requirements of CS ACNS D ELS EHS Mode S Elementary Enhanced Surveillance The installed ADS B OUT system is fully compliant with the requirements of CS ACNS D ADSB 1090 MHz Extended Squitter ADS B OUT 1 ...

Page 1120: ...change the normal procedures of the airplane described in Section 4 Normal Procedures of the basic Pilot s Operating Handbook SECTION 5 PERFORMANCE Operation of ADS B OUT function does not change the performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Operation of ADS B OUT function does not change the weight and balan...

Page 1121: ...nsponder ADS B OUT data is only transmitted via transponder 1 Use of transponder 2 results in a loss of the ADS B OUT data transmission If the transponder 1 detects any internal fault or failure with the ADS B OUT functionality the XPDR1 ADS B FAIL message will be displayed After being informed of ADS B OUT failure either by the XPDR1 ADS B FAIL message or by Air Traffic Control it is possible to ...

Page 1122: ... HANDLING SERVICING AND MAINTENANCE Operation of ADS B OUT function does not change the handling servicing and maintenance of the airplane described in Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1123: ...TBM 700 850 SUPPLEMENT 60 ADS B OUT FUNCTION Rev 4 Page 9 60 6 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1124: ...NT FLIGHT ENVELOPE PROTECTION TABLE OF CONTENTS Page 1 GENERAL 9 62 2 2 LIMITATIONS 9 62 2 3 EMERGENCY PROCEDURES 9 62 3 4 NORMAL PROCEDURES 9 62 7 5 PERFORMANCE 9 62 14 6 WEIGHT AND BALANCE 9 62 14 7 DESCRIPTION 9 62 15 8 HANDLING SERVICING AND MAINTENANCE 9 62 18 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1125: ...ATIONS AND TERMINOLOGY GENERAL ABBREVIATIONS AoA Angle of Attack ESP Electronic Stability Protection USP UnderSpeed Protection SECTION 2 LIMITATIONS Information hereafter supplement those of the standard airplane described in Section 2 Limitations of the Pilot s Operating Handbook Airplane equipped with GARMIN G1000 flight deck MOD70 0176 00 The GARMIN G1000 Integrated Flight Deck Cockpit Referenc...

Page 1126: ...ation hereafter supplement or replace those of the standard airplane described in Section 3 Emergency Procedures of the basic Pilot s Operating Handbook when the airplane is equipped with FLIGHT ENVELOPE PROTECTION 3 9 ELECTRICAL SYSTEM Figure 3 9 1 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1127: ... pushbutton PRESS and HOLD until recovery 2 Control wheel NEUTRAL PITCH ROLL 3 Rudder FULLY OPPOSED TO THE SPIN 4 Power lever IDLE 5 Flaps UP When rotation is stopped 6 Level the wings and ease out of the dive AP OFF AND STALL WARNING SOUND 1 Fly the airplane wings level and nose down until stall warning stops 2 Power as required 3 Return to the desired flight path PIM DO NOT USE FOR FLIGHT OPERAT...

Page 1128: ... may be triggered but AP will remain ON Airplane retrofited with GARMIN G1000 NXi flight deck MOD70 0539 00 AMBER WARNING CAS MESSAGE ESP FAIL Indicates pitch roll high speed and AoA protections are inoperative 1 Maintain the airplane inside the flight envelope FLAPS UP 105 IAS 266 KIAS FLAPS TO 100 IAS 178 KIAS FLAPS LDG 85 IAS 122 KIAS 2 Continue flight 3 Inform maintenance department PIM DO NOT...

Page 1129: ...tive 1 Maintain IAS below 266 KIAS 2 Continue flight 3 Inform maintenance department AMBER WARNING CAS MESSAGE ESP DEGRADED AOA Indicates AoA protection at low speed is inoperative 1 Maintain airspeed above 1 3 Vs FLAPS UP 105 IAS 266 KIAS FLAPS TO 100 IAS 178 KIAS FLAPS LDG 85 IAS 122 KIAS 2 Continue flight 3 Inform maintenance department PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1130: ...n 1 January 5 2017 Rev 1 Page 9 62 7 SECTION 4 NORMAL PROCEDURES Information hereafter supplement or replace those of the standard airplane described in Section 4 Normal Procedures of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1131: ...kg If the vertical speed is positive and if IAS is at or above 85 KIAS 4 Landing gear control UP All warning lights OFF If IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed AS REQUIRED Weight above 6579 lbs 2984 kg If the vertical speed is positive and if IAS is at or above 90 KIAS 7 Landing gear control UP All warning lights OFF If IAS is at or above 115 KIAS 8 Flaps UP 9 Climb speed AS REQUIR...

Page 1132: ...peed is positive and if IAS is at or above 85 KIAS 4 Landing gear control UP All warning lights OFF If IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed AS REQUIRED Weight above 6579 lbs 2984 kg If the vertical speed is positive and if IAS is at or above 90 KIAS 7 Landing gear control UP All warning lights OFF If IAS is at or above 115 KIAS 8 Flaps UP 9 Climb speed AS REQUIRED 10 Power AS REQUI...

Page 1133: ...usted 3 Flaps TO Weight below 6579 lbs 2984 kg If speed has been maintained at 80 KIAS or more and TRQ 100 select TO flaps as soon as the 8 attitude has been attained If the vertical speed is positive and if IAS is at or above 85 KIAS 4 Landing gear control UP All warning lights OFF If IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed AS REQUIRED Weight above 6579 lbs 2984 kg If speed has been ...

Page 1134: ...e 115 KIAS 8 Flaps UP In case of air leak between the solenoïd valve and the torque limiter the available torque might be below 100 Consequently it is strongly recommended not to select 850 for a new approach or visual circuit for staying below 1500 ft AGL 9 Climb speed AS REQUIRED 10 Power AS REQUIRED PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1135: ...trol UP All warning lights OFF If IAS is at or above 110 KIAS 5 Flaps UP 6 Climb speed AS REQUIRED Weight above 6579 lbs 2984 kg If speed has been maintained at 85 KIAS or more and TRQ 100 select TO flaps as soon as the 7 5 attitude has been attained If the vertical speed is positive and if IAS is at or above 90 KIAS 7 Landing gear control UP All warning lights OFF If IAS is at or above 115 KIAS 8...

Page 1136: ...CONDITIONS CAUTION THE STALL WARNING SYSTEM DOES NOT FUNCTION PROPERLY IN ICING CONDITIONS AND SHOULD NOT BE RELIED UPON TO PROVIDE ADEQUATE STALL WARNING IN ICING CONDITIONS AND AFTER LEAVING ICING CONDITIONS IF ICE ACCRETION REMAINS ON THE AIRPLANE THEREFORE THE USP AND ESP IF INSTALLED FUNCTIONS RECEIVING INFORMATION FROM THE STALL WARNING SYSTEM MAY NOT BE CORRECTLY ENGAGED PIM DO NOT USE FOR ...

Page 1137: ...rd airplane described in Section 6 Weight and Balance of the basic Pilot s Operating Handbook when the airplane is equipped with the FLIGHT ENVELOPE PROTECTION S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 34 NAVIGATION A 0423 34 Lift transducer and AoA computer installation of which SAFE FLIGHT INSTRUMENTS 1 66 0 752 242 01 6 147 ...

Page 1138: ...tion hereafter supplement or replace those of the standard airplane described in Section 7 Description of the basic Pilot s Operating Handbook when the airplane is equipped with the FLIGHT ENVELOPE PROTECTION 7 8 ELECTRICAL SYSTEM Figure 7 8 1 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1139: ...TBM 850 SUPPLEMENT 62 FLIGHT ENVELOPE PROTECTION Edition 1 January 5 2017 Rev 1 Page 9 62 16 Figure 7 8 2 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1140: ...f attack value is sent to the GARMIN Integrated Flight Deck system for display The AoA computer also triggers the stall aural warning alert that begins no later than 5 knots above the stall in all configurations The stall warning system should be ckecked during the preflight inspection by momentarily turning on the SOURCE selector and by manipulating the vane of the lift transducer at the wing lea...

Page 1141: ...se of system and its controls refer to GARMIN Pilot s Guide at the latest issue SECTION 8 HANDLING SERVICING AND MAINTENANCE Operation of FLIGHT ENVELOPE PROTECTION does not change the handling servicing and maintenance of the airplane described in Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1142: ...NT LAVATORY COMPARTMENT TABLE OF CONTENTS Page 1 GENERAL 9 63 2 2 LIMITATIONS 9 63 2 3 EMERGENCY PROCEDURES 9 63 5 4 NORMAL PROCEDURES 9 63 5 5 PERFORMANCE 9 63 6 6 WEIGHT AND BALANCE 9 63 7 7 DESCRIPTION 9 63 14 8 HANDLING SERVICING AND MAINTENANCE 9 63 18 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1143: ...ARTMENT SECTION 2 LIMITATIONS The limitations hereafter supplement or replace those of the standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option LAVATORY COMPARTMENT TOILET SEAT MUST NOT BE OCCUPIED DURING TAKE OFF AND LANDING DIVIDER MUST BE STOWED DURING TAKE OFF AND LANDING HEADSET SHALL BE WORN AT ALL TIME...

Page 1144: ...ATORY COMPARTMENT TBM 850 Edition 3 March 20 2017 Rev 0 Page 9 63 3 On fixed panel toilet side On access door cabin side and toilet side Behind access door cabin side and toilet side PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1145: ...VATORY COMPARTMENT TBM 850 Edition 3 March 20 2017 Rev 0 Page 9 63 4 Inner face of toilet cover Front face of lavatory compartment near opening closing switches On the magazine rack PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1146: ...message and 3 voice messages USE OXYGEN MASK USE OXYGEN MASK Inform passengers to use emergency stowing of the divider and oxygen mask SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement or replace those of the standard airplane described in Section 4 Normal Procedures of the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option LAVATORY COMPARTMENT ...

Page 1147: ...0 2017 Rev 0 Page 9 63 6 SECTION 5 PERFORMANCE Installation and operation of LAVATORY COMPARTMENT do not change the basic performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1148: ...D BALANCE AFTER THE APPLICATION OF THE LAVATORY COMPARTMENT OPTION NOTE The new empty weight determination after lavatory compartment installation shall be performed from the 6 seat configuration airplane characteristics 1 Record the basic empty weight 1a and moment 1b and CG MAC 1c from the last Weight and Balance Report in 6 seat configuration see samples Figures 6 4 1 and 6 4 2 of the basic Pil...

Page 1149: ... Variation after LAVATORY COMPARTMENT option installation 12 87 New empty weight ready for cargo preparation 2a 3 2b 3c Moment Weight x Arm CG MAC Arm in 172 93 59 45 100 Item Weight lbs Arm in Moment in lbs CG MAC Empty Weight lbs 1a 1b 1c Weight and Moment Variation after LAVATORY COMPARTMENT option installation 27 7529 New empty weight ready for cargo preparation 2a 3 2b 3c PIM DO NOT USE FOR F...

Page 1150: ...fer to POH Section 6 4 using the weight and balance form procedure to determine the weight and balance of the airplane equipped with the lavatory compartment option together with the use of the loading form hereafter S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 25 EQUIPMENT AND FURNISHINGS O 0505 25C Lavatory compartment 138 9 63 ...

Page 1151: ...ght x Arm CG MAC Arm m 4 392 1 51 100 Item Weight kg Arm m Moment m kg CG MAC Empty Weight kg Baggage FWD 50 kg 3 250 Front Seats kg 4 534 Inter Seats 17 kg per seat removed 5 710 Pax Baggage AFT 100 kg 7 695 Zero Fuel Weight 2 736 kg Fuel kg 4 820 Ramp Weight 3 370 kg Taxi Fuel kg 4 820 Takeoff Weight 3 354 kg Trip Fuel kg 4 820 Landing Weight 3 186 kg PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1152: ...SUPPLEMENT 63 LAVATORY COMPARTMENT TBM 850 Edition 3 March 20 2017 Rev 0 Page 9 63 11 Figure 9 63 1 Weight and Balance diagram PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1153: ...CG MAC Arm in 172 93 59 45 100 Item Weight lbs Arm in Moment in lbs CG MAC Empty Weight lbs Baggage FWD 110 lbs 128 0 Front Seats lbs 178 5 Inter Seats 37 5 lbs per seat removed 224 8 Pax Baggage AFT 220 lbs 303 0 Zero Fuel Weight 6 032 lbs Fuel lbs 189 8 Ramp Weight 7 430 lbs Taxi Fuel lbs 189 8 Takeoff Weight 7 394 lbs Trip Fuel kg 189 8 Landing Weight 7 024 lbs PIM DO NOT USE FOR FLIGHT OPERATI...

Page 1154: ...SUPPLEMENT 63 LAVATORY COMPARTMENT TBM 850 Edition 3 March 20 2017 Rev 0 Page 9 63 13 Figure 9 63 2 Weight and Balance diagram PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1155: ...cture is made of composite panels The lavatory compartment assembly is composed of A chemical toilet Electrically deployable separating panels divider Two 2 actuating switches DEPLOY STOW Two 2 emergency stowing buttons PUSH TO STOW accessible from inside or outside the lavatory compartment One 1 mirror One 1 electric power plug One 1 headset allowing communication between the passenger and the cr...

Page 1156: ...ction is only accessible when the lavatory compartment structure is unscrewed from the floor and moved slightly aside to access the plug Mirror is automatically illuminated during the deployment of the divider A safety anti pinching sensor stops the deployment of the divider in case an interference is detected To remove the chemical toilet system from the lavatory compartment structure it is neces...

Page 1157: ...SUPPLEMENT 63 LAVATORY COMPARTMENT TBM 850 Edition 3 March 20 2017 Rev 0 Page 9 63 16 Figure 9 63 3 1 2 Lavatory compartment PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1158: ...SUPPLEMENT 63 LAVATORY COMPARTMENT TBM 850 Edition 3 March 20 2017 Rev 0 Page 9 63 17 Figure 9 63 3 2 2 Lavatory compartment PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1159: ...LING SERVICING AND MAINTENANCE Installation and operation of LAVATORY COMPARTMENT do not change the basic handling servicing and maintenance procedures of the airplane described in Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1160: ...NT STICK SHAKER TABLE OF CONTENTS Page 1 GENERAL 9 64 2 2 LIMITATIONS 9 64 2 3 EMERGENCY PROCEDURES 9 64 3 4 NORMAL PROCEDURES 9 64 5 5 PERFORMANCE 9 64 5 6 WEIGHT AND BALANCE 9 64 6 7 DESCRIPTION 9 64 7 8 HANDLING SERVICING AND MAINTENANCE 9 64 13 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1161: ...out the equipment limitations description and operations necessary for operation when the airplane is equipped with the STICK SHAKER SECTION 2 LIMITATIONS Operation of the STICK SHAKER does not change the limitations of the airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1162: ...on hereafter supplement or replace 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 STICK SHAKER 3 9 ELECTRICAL SYSTEM Figure 3 9 1 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1163: ... as required 4 Return to the desired flight path Aircraft equipped with AoA system MOD70 0423 34 AP OFF AND STALL WARNING SOUND NOTE Shaker will vibrate simultaneously with stall warning sound 1 Fly the airplane wings level and nose down until stall warning stops 2 Power as required 3 Return to the desired flight path RED WARNING CAS MESSAGE USP ACTIVE ON 1 Do not disconnect AP 2 Increase power up...

Page 1164: ...ot change the normal procedures of the airplane described in Section 4 Normal Procedures of the basic Pilot s Operating Handbook SECTION 5 PERFORMANCE Operation of the STICK SHAKER does not change the performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1165: ...ght and Balance of the basic Pilot s Operating Handbook when the airplane is equipped with the STICK SHAKER S R A O ITEM OPT70 or MOD70 OPTIONAL EQUIPMENT WEIGHT per unit lb kg ARM in m 27 FLIGHT CONTROLS O 0510 27C Stick shaker of which 1 053 0 477 144 0 3 658 Support T700J2730008100 0 053 0 024 143 0 3 631 Stick shaker C 101702 1 1 000 0 453 144 1 3 661 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1166: ...these signals are low pitched and or high pitched The HORN TEST knob allows to test the correct operation of aural warnings Set the SOURCE selector to BAT or to GPU Set the AVIONICS MASTER switch to ON Push and hold the HORN TEST knob the VMO buzzer emits bips the loud speakers emit alternate low pitched and high pitched sounds the shaker vibrates Release the knob to stop the alarms Post MOD70 040...

Page 1167: ...VATOR 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 The stick shaker is fixed on the pitch lever linked to the pilot control column lever This is a mechanical device to vibrate the control wheel to ...

Page 1168: ...e 9 64 9 Figure 7 4 3 ELEVATOR 1 Control wheel assembly 2 Elevators 3 Lever assembly fuselage rear part 4 Elevator bellcrank 5 Rod with presseal connection 6 Lever assembly under floor 7 Pedestal assembly 8 Actuator 9 Stick shaker PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1169: ...TBM 850 SUPPLEMENT 64 STICK SHAKER Edition 0 May 22 2017 Rev 0 Page 9 64 10 7 8 ELECTRICAL SYSTEM Figure 7 8 1 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1170: ...SUPPLEMENT 64 STICK SHAKER TBM 850 Edition 0 May 22 2017 Rev 0 Page 9 64 11 Figure 7 8 2 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1171: ...begins between 5 and 10 knots above the stall in all configurations The stall warning system should be checked during the preflight inspection by momentarily turning on the SOURCE selector and by manipulating the vane in the wing Pre MOD70 0407 00D The system is operational if a continous tone low pitched sound is heard on the alarms speaker and the stick shaker simultaneously vibrates Post MOD70 ...

Page 1172: ...ECTION 8 HANDLING SERVICING AND MAINTENANCE Operation of the STICK SHAKER does not change the handling servicing and maintenance of the airplane described in Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1173: ...TBM 850 SUPPLEMENT 64 STICK SHAKER Edition 0 May 22 2017 Rev 0 Page 9 64 14 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1174: ...EMENT MD302 STANDBY ATTITUDE MODULE TABLE OF CONTENTS Page 1 GENERAL 9 65 2 2 LIMITATIONS 9 65 2 3 EMERGENCY PROCEDURES 9 65 4 4 NORMAL PROCEDURES 9 65 6 5 PERFORMANCE 9 65 7 6 WEIGHT AND BALANCE 9 65 7 7 DESCRIPTION 9 65 8 8 HANDLING SERVICING AND MAINTENANCE 9 65 16 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1175: ...ndby Attitude Module SECTION 2 LIMITATIONS Information hereafter supplement or replace those of the standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the airplane is equipped with MD302 STANDBY ATTITUDE MODULE 2 1 GENERAL The Pilot s Guide for the MD302 Standby Attitude Module P N 9017846 Rev E or any later version as applicable must be permanently k...

Page 1176: ... code significance are shown in Figure 2 8 1 MARKING KIAS Value or range SIGNIFICANCE Red line Below 65 White line 65 122 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Green line Above 122 Normal operating airspeed range Hatched Red White Sector Above 266 266 VMO Figure 2 8 1 IAS AWARENESS BAR CUES PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1177: ...TANDBY ATTITUDE MODULE 3 9 ELECTRICAL SYSTEM Figure 3 9 1 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS TOTAL LOSS OF ELECTRICAL POWER 1 Maintain airplane control 2 Use the MD302 for attitude airspeed and altitude 3 Land as soon as possible NOTE Airplane power is provided to the MD 302 display for normal operation Operation of the basic MD 302system is automatic the system is powered ON while airpla...

Page 1178: ...PRESSURIZATION AND AIR CONDITIONING AMBER WARNING CAS MESSAGE VACUUM LOW ON Low vacuum may lead to misfunctioning of leading edge deicing pressurization MONITOR If necessary fly to an altitude 12000 ft and return to VMC conditions as soon as possible BLEED switch OFF PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1179: ...r symbol Not displayed If a battery symbol appears on the MD302 display airplane take off is not allowed until the situation is resolved Refer to the battery details in the MD302 Pilot s guide for further information SHUT DOWN Standby attitude module OFF MD302 NORMAL PROCEDURE No pilot action required for normal shutdown The MD302 will shut down automatically within 60 seconds following electrical...

Page 1180: ... AND BALANCE Information hereafter supplement or replace those of the standard airplane described in Section 6 Weight and Balance of the basic Pilot s Operating Handbook when the airplane is equipped with the MD302 STANDBY ATTITUDE MODULE S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 34 NAVIGATION 34 11 Air data systems O 0462 34C ...

Page 1181: ...age 9 65 8 SECTION 7 DESCRIPTION Information hereafter supplement or replace those of the standard airplane described in Section 7 Description of the basic Pilot s Operating Handbook when the airplane is equipped with the MD302 STANDBY ATTITUDE MODULE PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1182: ...v 0 Page 9 65 9 7 3 ACCOMMODATIONS Instrument panel Figure 7 3 1 includes Standby Attitude Module MD302 Figure 7 3 1 LEFT INSTRUMENT PANEL 1 Airspeed readout 2 Barometric pressure window 3 Altimeter digital readout 4 Slip skid indicator 5 Horizon PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1183: ... ATTITUDE MODULE Edition 0 September 18 2017 Rev 0 Page 9 65 10 7 8 ELECTRICAL SYSTEM Figure 7 8 1 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS Figure 7 8 2 PARTIAL ELECTRICAL DISTRIBUTION OF BUS BARS PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1184: ...rts one on either side of the fuselage tail part supply a dual system routed towards the cockpit System 1 part which is connected to the switching valve normal alternate supplies the P cabin and the standby attitude module The system remainder directly supplies one of the air data computers System 2 is directly connected to the second ADC Systems feature a drain valve located under the instrument ...

Page 1185: ...ttitude Module MD302 4 GDC ADC 5 GDC ADC 6 FWD pressure bulkhead 7 Static system drain 8 Static system drain 9 Static system drain 10 Emergency static system drain 11 Emergency static valve Normal Alternate 12 Instrument panel 13 Dynamic system drain 14 Pitot R 15 Rear pressure bulkhead 16 Static port 17 Emergency static port 18 Static port PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1186: ...SUPPLEMENT 65 MD302 STANDBY ATTITUDE MODULE TBM 850 Edition 0 September 18 2017 Rev 0 Page 9 65 13 Figure 7 11 1 2 2 AIR DATA SYSTEM PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1187: ...em indicates the failure by causing the VACUUM LOW CAS message to light on STANDBY ATTITUDE MODULE MD302 The Mid Continent Instrument and Avionics MD302 Standby Attitude Module consists of two LCD screens The first screen displays the airplane attitude pitch and roll and the second screen displays the airplane altitude and airspeed The MD302 is powered from the ESSENTIAL BUS 2 or internal replacea...

Page 1188: ...E MODULE TBM 850 Edition 0 September 18 2017 Rev 0 Page 9 65 15 Figure 7 12 1 VACUUM SYSTEM 1 Pressure regulator 2 Ejector 3 Valve 4 Regulating and relief valve 5 Pressure switch 6 Failure CAS message PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1189: ... 16 SECTION 8 HANDLING SERVICING AND MAINTENANCE Operation of MD302 STANDBY ATTITUDE MODULE does not change the handling servicing and maintenance of the airplane described in Section 8 Handling Servicing and Maintenance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1190: ...NT GARMIN G1000 NXi RETROFIT TABLE OF CONTENTS Page 1 GENERAL 9 66 2 2 LIMITATIONS 9 66 2 3 EMERGENCY PROCEDURES 9 66 3 4 NORMAL PROCEDURES 9 66 11 5 PERFORMANCE 9 66 11 6 WEIGHT AND BALANCE 9 66 12 7 DESCRIPTION 9 66 13 8 HANDLING SERVICING AND MAINTENANCE 9 66 15 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1191: ...ibed in Section 2 Limitations of the basic Pilot s Operating Handbook when the airplane is equipped with GARMIN G1000 NXi RETROFIT 2 1 GENERAL The GARMIN G1000 NXi Integrated Flight Deck Pilot s Guide No 190 02348 00 or any later version as applicable must be readilyavailable to the pilot and permanently kept in the airplane with the Pilot s Operating Handbook 2 6 OPERATION LIMITS GNSS GPS SBAS NA...

Page 1192: ...N G1000 NXi RETROFIT TABLE OF CONTENTS NOTE CAS MESSAGES are in alphabetical order by either Chapter Section Paragraph Advisiry or Supplement Page ABORT APR 9 66 8 APR DWNGRADE 9 66 8 CARGO DOOR 9 66 4 ESP DEGRADED AOA Sup 62 Flight Envelope Protection ESP DEGRADED IAS Sup 62 Flight Envelope Protection ESP FAIL Sup 62 Flight Envelope Protection GWX FAIL 9 66 11 TCAS FAIL 9 66 9 TRAFFIC FAIL 9 66 1...

Page 1193: ...ADE and by an annunciation change on the HSI from LPV L VNAV or LNAV V to LNAV GPS glide path vertical guidance will be removed from the PFD The approach may becontinued using the LNAV only minimums During any GPS approach in which both precision and non precision alarm limits are exceeded the G1000 System will flag the lateral guidance and display a red CAS message ABORT APR loss of navigation Im...

Page 1194: ...FD when engaged again Actions AUTOPILOT IS NOT OPERATIVE 1 AHRS1 and or AHRS2 circuit breaker CHECKED IN A If yellow annunciation BOTH ON AHRS1 or BOTH ON AHRS2 is associated to white annunciation HDG and or PIT and or ROL 1 Fly the aircraft manually 2 AHRS1 and or AHRS2 circuit breaker CHECKED IN If pilot wishes 3 FD default mode PITCH and ROLL ENGAGED 4 FD specifics modes HDG NAV ALT ENGAGED as ...

Page 1195: ...nunciation BOTH ON AHRS1 or BOTH ON AHRS2 ONLY not associated to white annunciation HDG and or PIT and or ROL 1 PFD1 and PFD2 SENSOR softkey s PRESSED 2 AHRS1 on PFD1 and or AHRS2 on PFD2 RESET 3 BOTH ON AHRS1 or BOTH ON AHRS2 annunciation s OFF CHECKED 4 Autopilot NORMAL USE as desired PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1196: ...uit breaker CHECKED IN A If yellow annunciation BOTH ON ADC1 or BOTH ON ADC2 is associated to white annunciation IAS and or ALT 1 NO action required If ALL white annunciations IAS and or ALT GO OFF refer to following B procedure B If yellow annunciation BOTH ON ADC1 or BOTH ON ADC2 ONLY not associated to white annunciation IAS and or ALT pilot may do following actions 1 PFD1 and PFD2 SENSOR softke...

Page 1197: ...ndicates a loss of GPS navigation Perform a GO AROUND AMBER CAS MESSAGE APR DWNGRADE Indicates Vertical guidance generated by SBAS is unavailable If LNAV minimums available 1 Approach Downgrade to LNAV If LNAV minimums not available Perform a GO AROUND 2 Inform maintenance department PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1198: ...form maintenance department If transponder 2 or transponder 1 is unavailable 1 Inform Air Traffic Control of the loss of the second XPDR 2 Leave controlled airspace 3 Continue flight 4 Inform maintenance department Aircraft equipped with GTS820 Traffic Advisory System MOD70 0258 00 AMBER CAS MESSAGE TCAS FAIL Indicates that Traffic Advisory System is inoperative NOTE No active traffic available bu...

Page 1199: ...t equipped with ADS B OUT function MOD70 0264 34 AMBER CAS MESSAGE XPDR1 ADS B FAIL or XPDR2 ADS B FAIL Indicates ADS B OUT function of transponder 1 or transponder 2 is inoperative Other functions may remain available If transponder 2 or transponder 1 is available 1 Restore ADS B OUT function by setting transponder 2 or transponder 1 as active 2 Continue flight 3 Inform maintenance department If ...

Page 1200: ... using other weather data source and adjust flight route 3 Inform maintenance department SECTION 4 NORMAL PROCEDURES Operation of the GARMIN G1000 NXi RETROFIT does not change the normal procedures of the airplane described in Section 4 Normal Procedures of the basic Pilot s Operating Handbook SECTION 5 PERFORMANCE Operation of GARMIN G1000 NXi RETROFIT does not change the performance of the airpl...

Page 1201: ...he airplane is equipped with the GARMIN G1000 NXi RETROFIT S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT WEIGHT per unit lb kg ARM in m 34 NAVIGATION 34 28 Electronic Flight Instrumentation system O 0539 00 Version D Integrated Flight Deck System G1000 NXi of which PFD1 GDU 1050A 6 31 2 04 155 63 3 953 PFD2 GDU 1050A 6 31 2 04 155 63 3 953 MFD GDU 1550 5 49 2 49...

Page 1202: ...s are flush with the fuselage profile The CARGO DOOR CAS message lights on as long as FWD compartment door is not locked 7 15 MISCELLANEOUS EQUIPMENT FLIGHT DECK INFORMATION SYSTEM FS 510 if installed The airplane is equipped with a flight deck information system allowing portable electronics devices to stream data to and from the GARMIN integrated flight deck system For the system description and...

Page 1203: ...entifier Description Distance to runway RWxxx Runway fix defined in the navigation database xxx is the runway number and suffix e g RW19L N A FINAL The roll out from the turn to the final approach course is accomplished as this fix is sequenced 3 5 Nm STRGHT Initial fix for the straight in transition 6 Nm The waypoints created by the FMS to define a VISUAL approach are fixes stored in the flight p...

Page 1204: ...fore the visual approach is loaded into the flight plan The TAWS function normally provides some suppression of terrain alerts when flying an approach with vertical guidance The TAWS logic is adjusted to ensure that there is no suppression of terrain alerts while flying a VISUAL approach Visual approaches are intended to be used as an aid to situational awareness Visual approaches are advisory in ...

Page 1205: ...TBM 850 SUPPLEMENT 66 GARMIN G1000 NXI RETROFIT Edition 0 October 30 2017 Rev 1 Page 9 66 16 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1206: ...ENT BARO VNAV APPROACHES TABLE OF CONTENTS Page 1 GENERAL 9 69 2 2 LIMITATIONS 9 69 2 3 EMERGENCY PROCEDURES 9 69 9 4 NORMAL PROCEDURES 9 69 12 5 PERFORMANCE 9 69 13 6 WEIGHT AND BALANCE 9 69 13 7 DESCRIPTION 9 69 13 8 HANDLING SERVICING AND MAINTENANCE 9 69 19 PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1207: ...RMIN Integrated Flight Deck Pilot s Guides as applicable must be readily available to the pilot and permanently kept in the airplane with the POH G1000 850 P N 190 00709 00 Rev C or any later revision G1000 NXi retrofitted 850 P N 190 02348 Rev B or any later revision 2 6 OPERATION LIMITS GNSS GPS SBAS NAVIGATION EQUIPMENT APPROVALS The GARMIN GNSS navigation system installed in this airplane is a...

Page 1208: ...f flight Approved PBN Capability Operational limitations Reference Documents ICAO Flight Plan Code Notes Item 10a Code Item 18 PBN En route Oceanic and Remote continental Class II Navigation RNAV 10 RNP 10 GNSS FDE availability must be verified prior to flight Maximum predicted FDE unavailability is 34 minutes 1 Two GNSS systems requi red to be operational 2 FAA AC 90 105A R A1 Additional com muni...

Page 1209: ...y must be verified prior to oceanic or remote continental flight Maxi mum predicted FDE una vailability is 5 minutes Two GNSS systems requi red to be operational 2 Only one operational GNSS system required for domestic and offshore operations areas FAA AC 90 105A R Additional com munication and surveillance equipment may be required to obtain ope rational approval to utilize RNP 2 performance Depa...

Page 1210: ... in the initial and intermediate legs of the approach pro cedure or the final leg of the missed approach procedure only Approach RNP APCH LNAV VNAV minima with and without RF legs At a minimum the flight director must be displayed and utilized when conducting procedures containing RF legs QNH shall be available at the destination airport when conducting a Baro VNAV approach Use of remote altimeter...

Page 1211: ...al leg of the missed approach procedure only 1 and 2 see Note 1 and Note 2 hereafter Table 2 6 1 GNSS operational requirements Note 1 FDE RAIM availability worldwide can be determined using the WFDE Prediction program part number 006 A0154 01 or later approved version with GARMIN GA36 and GA37 antennas selected or Within the United States using the FAA s en route and terminal RAIM prediction websi...

Page 1212: ...nfirm 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 If an amended chart affecting navigation data is published for the procedure the database must not be used to conduct the procedure...

Page 1213: ... fixes from the database is permitted provided all fixes along the published route to be flown are inserted GNSS integrity limitations For flight planning purposes in areas where SBAS coverage is not available the pilot must check RAIM availability The availability of GPS integrity RAIM shall be confirmed for the intended route of flight In the event of a predicted continuous loss of RAIM of more ...

Page 1214: ...g A current altimeter setting for the landing airport is required When using remote altimeter minima the baro VNAV function may be used to the published LNAV MDA 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 SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement or repla...

Page 1215: ...m will automatically downgrade to LNAV VNAV or LNAV 2 Update minimums as appropriate NOTE In some cases the approach may be downgraded without AMBER WARNING CAS MESSAGE APR DWNGRADE being displayed to the crew Please consider the HSI approach annunciation as the primary mean to identify the current mode of operation NOTE Refer to the section 7 to get details on the approach downgrading process GPS...

Page 1216: ...NAV This may be indicated by an annunciation change on the HSI Symptoms AP mode from GP flashing 5 seconds to PIT VDI is flagged and indicates NO GP If automatic downgrade to LNAV 1 Update minimums as appropriate If not Perform a GO AROUND VDI WHITE or VDI AMBER ON APPROACH Symptoms VDI white or VDI amber at bottom of VDI window If possible 1 Use LNAV minimums If not Perform a GO AROUND PIM DO NOT...

Page 1217: ...ailability requirements in the table 2 6 1 in section 2 GNSS GPS SBAS navigation equipment approvals depending on the planned navigation performance GPS flight plan In the active flight plan addition of a STAR or an approach is always made at the end of the flight plan In the scope of these additions the pilot must pay attention not to duplicate points Non precision approach with coupled autopilot...

Page 1218: ...ook SECTION 7 DESCRIPTION Description hereafter supplement or replace those of the standard airplane described in Section 7 Description of the basic Pilot s Operating Handbook when the airplane is equipped with the Baro VNAV approaches capability 7 15 MISCELLANEOUS EQUIPMENT GARMIN INTEGRATED FLIGHT DECK GIFD APPROACHES The purpose of this section is to provide an overview of the GIFD capabilities...

Page 1219: ...anomalies could result in loss of advisory vertical guidance If GPS is lost the LNAV approach will be aborted RNAV GPS or RNAV GNSS L VNAV LNAV VNAV approaches add published vertical guidance in addition to LNAV guidance They are different from LNAV V in that the vertical deviations are not advisory but rather published guidance The minimums of an LNAV VNAV approach represent a DA rather than an M...

Page 1220: ...ublished or on some approaches that are not authorized for SBAS No pilot action is required to receive the temperature compensated glide path when SBAS is not available or allowed Final Approach Segment FAS Altimeter systems assume an ISA temperature model When actual atmosphere deviates from the ISA model it results in altitude errors For example performing a Baro VNAV during a hot day would resu...

Page 1221: ...itude The temperature compensation required depends on the temperature profile over the altitude range between the point at which the barometric setting is measured presumed to be the approach airport and the present altitude of the aircraft This temperature profile is estimated by using the air data system static air temperature SAT and applying the standard temperature lapse rate to determine th...

Page 1222: ... temperature compensation of both the published approach waypoint altitudes on the active flight plan page and the minimum altitude The minimum altitude selection type changes to BARO if it was previously set to TEMP COMP Temperature compensation of the minimum altitude is not dependent on use of barometric altitude for vertical guidance on the FAS and is therefore available for any type of approa...

Page 1223: ...CAS message and the service level annunciation being removed from the HSI If SBAS becomes unavailable on an RNAV LNAV VNAV approach L VNAV is shown in yellow the system switches to LNAV VNAV Baro VNAV service level and the APR DWNGRADE amber CAS message will be generated the VDI will be flagged NO GP until the APR DWNGRADE amber CAS message has been acknowledged If the APR DWNGRADE amber CAS messa...

Page 1224: ...ERVICING AND MAINTENANCE Operation of the airplane equipped with the Baro VNAV approaches capability does not change the basic handling servicing and maintenance of the airplane described in section 8 Handling servicing and maintenance of the basic Pilot s Operating Handbook PIM DO NOT USE FOR FLIGHT OPERATIONS ...

Page 1225: ...TBM 850 SUPPLEMENT 69 BARO VNAV APPROACHES Edition 1 September 30 2018 Rev 0 Page 9 69 20 INTENTIONALLY LEFT BLANK PIM DO NOT USE FOR FLIGHT OPERATIONS ...

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