Daher-Socata TBM 700 Series Pilot Operating Handbook

Equipped with mod70-0276-00

page of 674

/ 674
Contents
Table of Contents
Bookmarks

Table of Contents

Quick Links

Download this manual

PILOT'S INFORMATION

MANUAL

TBM 700 --- Edition 1

Table of Contents

Chapters

Table of Contents

Need help?

Do you have a question about the TBM 700 Series and is the answer not in the manual?

Questions and answers

Summary of Contents for Daher-Socata TBM 700 Series

Page 1 PILOT’S INFORMATION MANUAL TBM 700 --- Edition 1...
Page 2 TBM 700 Versions A and B equipped with MOD70-0276-00 PILOT’S OPERATING HANDBOOK The content of this document is the property of SOCATA. It is supplied in confidence and commercial security of its contents must be maintained. It must not be used for any purpose other than that for which it is supplied, nor may information contained in it be disclosed to unauthorized persons.
Page 3 T B M SECTION 0 PILOT’S OPERATING HANDBOOK SOCATA MODIFICATIONS - - INDEX NOTE : The standardized name for SOCATA modifications is MOD70- -XXX- -XX MOD70 No. SUBJECT CLASSIF. 001--06 Increase in ramp and max. takeoff weights Major 002--24 Alternator current output increase Major 003--28 Unusable fuel updating...
Page 4: Pilot's Operating Handbook
T B M SECTION 0 PILOT’S OPERATING HANDBOOK MOD70 No. SUBJECT CLASSIF. 025--21 Cabin air cooling minor 026--28 Fuel booster pump AIRBORNE 1B9--5 minor 027--32 Modification of the landing gears attaching Major bolts 029--55 HEXCEL GENIN fibre glass P/N 1581/E536D Major as a variant 030--28...
Page 5 T B M SECTION 0 PILOT’S OPERATING HANDBOOK MOD70 No. SUBJECT CLASSIF. 051--76 Fuel emergency control lever minor 052--27 Cable guide bracket on pitch trim pulley minor 053--24 Horizontal stabilizer and elevator trim tab minor bonding 054--21 Reinforcement of the ECS exchanger air minor intake 055--37...
Page 6 T B M SECTION 0 PILOT’S OPERATING HANDBOOK MOD70 No. SUBJECT CLASSIF. 077--55 Rudder horn bonding minor 078--57 Aileron balancing weight minor 079--53 Frame 10 reinforcement Major 080--53 Frame 2 front and rear link fittings Major 083--52 Lower door handle minor 084--25 Footstep carpet...
Page 7 T B M SECTION 0 PILOT’S OPERATING HANDBOOK MOD70 No. SUBJECT CLASSIF. 110--55 External bearing/horizontal stabilizer Major 111--53 Door maneuvering mechanism minor Reinforcement of the pulley attachment at Frame 14 112--21 Cabin air conditioning minor 113--53 “FIRE--PROOF” treatment of the nose landing minor gear well 114--25...
Page 8 T B M SECTION 0 PILOT’S OPERATING HANDBOOK MOD70 No. SUBJECT CLASSIF. 135--11 Airplane without finishing paint Major 144--33 Cabin lighting telebreaker minor 146--00 Clamp type modification airspeed minor indicating system and cabin pressurization regulation system 0150--53 VHF1 antenna support reinforcement -- S/N minor 243 equipped with option OPT70 34061A 0157--21...
Page 9 T B M SECTION 0 PILOT’S OPERATING HANDBOOK MOD70 No. SUBJECT CLASSIF. 0191--71 Engine drainage breather pipe modification minor -- TBM 700A, B, C equipped with MOD70--124--71 (engine drainage) and TBM 700N (850) 0194--25 Linings Generation 2005--3 minor 0195--56 Rear cabin window (same as front cabine minor window) 0201--32...
Page 10 T B M SECTION 0 PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS SECTION GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AIRPLANE HANDLING, SERVICING AND MAINTENANCE SUPPLEMENTS Page 0.6 Edition 1 -- November 30, 2010 Rev. 0...
Page 11: Table Of Contents
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK SECTION 1 GENERAL TABLE OF CONTENTS Page GENERAL 1.1.1 ..........THREE VIEW DRAWING 1.2.1 .
Page 12: General
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.1 - - GENERAL This Handbook contains 9 Sections, and includes the material required by FAR Part 23 to be furnished to the pilot for operation of the TBM 700 airplane equipped with MOD70--276--00.
Page 13: Three View Drawing
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.2 - - THREE VIEW DRAWING * Airplane on line of flight with extended FWD shock--absorber Figure 1.2.1 (1 / 2) -- THREE VIEW DRAWING TBM700A Edition 1 -- November 30, 2010 Page 1.2.1 Rev.
Page 14 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Figure 1.2.1 (2 / 2) -- THREE VIEW DRAWING TBM700A Edition 1 -- November 30, 2010 Page 1.2.2 Rev. 0...
Page 15 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK * Airplane on line of flight with extended FWD shock--absorber Figure 1.2.1A (1 / 2 ) -- THREE VIEW DRAWING TBM700B Edition 1 -- November 30, 2010 Page 1.2.3 Rev. 0...
Page 16 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Figure 1.2.1A (2 / 2 ) -- THREE VIEW DRAWING TBM700B Edition 1 -- November 30, 2010 Page 1.2.4 Rev. 0...
Page 17: Descriptive Data
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.3 - - DESCRIPTIVE DATA ENGINE Number of engines : 1 Engine manufacturer : PRATT & WHITNEY CANADA Engine model number : PT6A -- 64 Engine type : Free turbine, reverse flow and 2 turbine sections Compressor type : 4 axial stages 1 centrifugal stage...
Page 18: Fuel
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK FUEL Total capacity : 290.6 us gal (1100 Litres) Total capacity each tank : 145.3 us gal (550 Litres) Total usable : 281.6 us gal (1066 Litres) CAUTION THE USED FUEL MUST CONTAIN AN ANTI- -ICE ADDITIVE, IN ACCORDANCE WITH SPECIFICATION MIL- -I- -27686 or MIL- -I- -85470.
Page 19: Engine Oil
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK ENGINE OIL System total capacity : 12.7 Quarts (12 Litres) (oil cooler included) Usable capacity : 6 Quarts (5.7 Litres) Maximum consumption : 0.30 qt / hr (0.29 l / hr) [0.3 lb/hr (0.136 kg/h)] CAUTION DO NOT MIX DIFFERENT BRANDS OR TYPES...
Page 20: Cabin And Entry Dimensions
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK TBM700B : Standard empty weight : 4167 lbs (1890 kg) Maximum useful load : 2447 lbs (1110 kg) CABIN AND ENTRY DIMENSIONS Maximum cabin width : 3’ 11.64” (1.21 m) Maximum cabin length : 13’ 3.45” (4.05 m) Maximum cabin height : 4’...
Page 21: Abbreviations And Terminology
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.4 - - ABBREVIATIONS AND TERMINOLOGY METEOROLOGICAL TERMINOLOGY International standard atmosphere Outside air temperature is the free air static temperature. It is expressed in either degrees Celsius or degrees Fahrenheit. Static air temperature Atmospheric pressure at the airport reference point.
Page 22 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Maneuvering Speed is the maximum speed at which full or abrupt control movements may be used. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended.
Page 23: Power Terminology
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK POWER TERMINOLOGY Recovery altitude : Maximum altitude at which it is possible, in standard temperature, to maintain a specified power. Overheated start : Engine start or attempt to start which causes the interturbine temperature to be higher than the maximum value permissible during start .
Page 24: Airplane Performance And Flight Planning Terminology
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb gradient : Is the ratio of the change in height during a portion of climb, to the horizontal distance traversed in the same time interval. Demonstrated crosswind velocity : Is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing...
Page 25 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK C.G. limits : Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. Standard empty weight : Weight of a standard airplane including unusable fuel and full operating fluids (oil and hydraulic fluids).
Page 26: General Abbreviations
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK GENERAL ABBREVIATIONS : Ampere or Amber : Air Data Computer : Above ground level ALT. SEL. : Altitude selector ALTI : Altimeter AMP. : Ampere : Autopilot AUTO SEL : Automatic selector AUX BP : Auxiliary boost pump : Battery...
Page 27 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK : Heater IGNIT : Ignition : Inch INERT SEP : Inertial separator INDIC : Indicator in.Hg : Inch of mercury INT. LIGHTS : Interior lightings INSTR. : Instrument : Interturbine temperature : Kilogram : Knot (1 nautical mile/hr -- 1852 m/hr) : Kilowatt...
Page 28 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK NOCR : Normal cruise (recommended) NORM : Normal : Primary Flight Display : Plan Horizontal Fixe (Horizontal stabilizer) PRESS : Pressure PROP : Propeller : Pounds per square inch : Quart (¼ us gal) : Quantity : Red or Right : Rudder...
Page 29: Radio -- Navigation Abbreviations
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK RADIO - - NAVIGATION ABBREVIATIONS : Automatic Direction Finder System : Attitude Director Indicator AFCS : Automated Flight Control System AHRS : Attitude and Heading Reference System : Transponder B RNAV : Basic aRea NAVigation : Course Deviation Indicator : Communications Transceivers...
Page 30 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK : Very High Frequency : Visual Meteorological Conditions V NAV : Vertical NAVigation : VHF Omnidirectional Range VOR / LOC : VHF Omnidirectional Range LOCalizer WAAS : Wide Area Augmentation System : Weather surveillance radar XPDR : Transponder...
Page 31: Conversion Factors
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.5 - - CONVERSION FACTORS IMPERIAL AND U.S UNITS TO METRIC UNITS TO IMPERIAL AND METRIC UNITS U.S UNITS MULTIPLY TO OBTAIN MULTIPLY TO OBTAIN FEET 0.3048 METRE METRE 3.2808 FEET INCH 25.4 0.03937...
Page 32 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Feet 30000 20000 10000 Mètres 2500 5000 7500 10000 Figure 1.5.2 -- FEET VERSUS METRES Edition 1 -- November 30, 2010 Page 1.5.2 Rev. 0...
Page 33 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1000 Figure 1.5.3 -- INCHES VERSUS MILLIMETRES Edition 1 -- November 30, 2010 Page 1.5.3 Rev. 0...
Page 34 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 8000 6000 4000 2000 1000 2000 3000 4000 Figure 1.5.4 -- POUNDS VERSUS KILOGRAMS Edition 1 -- November 30, 2010 Page 1.5.4 Rev. 0...
Page 35: Pressure And Standard Atmosphere
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.6 - - PRESSURE AND STANDARD ATMOSPHERE STANDARD ATMOSPHERE Pressure Pressure altitude °C °F (hPa) (ft) 1013.2 + 15.0 + 59.0 2000 942.1 + 11.0 + 51.8 4000 875.0 + 44.6 6000 811.9 + 37.6...
Page 36: Pressure Conversion Table
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK PRESSURE CONVERSION TABLE NOTE : The standard pressure of 1013.2 hPa is equal to 29.92 inches of mercury. 28.08 28.11 28.14 28.17 28.20 28.23 28.26 28.29 28.32 28.05 28.35 28.38 28.41 28.44 28.47 28.50...
Page 37: Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved SECTION 2 LIMITATIONS TABLE OF CONTENTS Page GENERAL 2.1.1 ..........2.1A GENERAL 2.1.2 .
Page 38 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page MISCELLANEOUS LIMITS 2.7.1 ....... . . 2.7.1 SEATING LIMITS C.G.
Page 39: General
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.1 - - GENERAL The TBM 700 airplane is certified in the Normal Category. This airplane must be flown in compliance with the limits specified by placards or markings and with those given in this Section and throughout the Pilot’s Operating Handbook.
Page 40: A General
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.1A - - GENERAL TBM 700 airplane is certificated in the Normal Category. This airplane must be flown in compliance with the limits specified by placards or markings and with those given in this Section and throughout the Pilot’s Operating Handbook.
Page 41: Airspeed Limitations
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.2 - - AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 2.2.1. KCAS KIAS SPEED REMARKS Do not intentionally exceed Maximum operating speed this speed in normal flight category Do not make abrupt or full Maneuvering speed...
Page 42: Power Plant Limitations
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.3 - - POWER PLANT LIMITATIONS ENGINE Number of engines : 1 Engine manufacturer : PRATT & WHITNEY CANADA Engine model number : PT6A -- 64 Engine operating limits for takeoff and continous operations : Maximum power : -- 700 SHP : MAX TRQ 100 % at Np = 2000 RPM...
Page 43: Fuel
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Oil grade (Specification) : French English Nominal US specification NATO specification specification viscosity (US) code (FR) (UK) MIL--L--23699C MIL--L--23699C DERD 2499 Type 5cSt O.156 Amdt 1 Amdt 1 Issue 1 Figure 2.3.1 -- ENGINE OIL RECOMMENDED TYPE (Reference : Service Bulletin P &...
Page 44: Propeller
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved NOTE : Use of AVGAS to be recorded in engine module logbook. English US Specification French Specification Specification NATO Code (US) (FR) (UK) ASTM--D1655 JET A F35 without ASTM--D1655 JET A1 AIR 3405C Grade F35 DERD 2494 Issue 9 additive...
Page 45: Starter Operation Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.4 - - STARTER OPERATION LIMITS Starter operation sequence is limited as follows : if Ng ≤ 30 % ......... . . 30 seconds if Ng >...
Page 46: Weight And C.g. Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.5 - - WEIGHT AND C.G. LIMITS WEIGHT LIMITS Maximum ramp weight : 6614 lbs (3000 kg) Maximum takeoff weight : 6579 lbs (2984 kg) Maximum landing weight : 6250 lbs (2835 kg) Maximum zero fuel weight in wings (MZFW) : 6001 lbs (2722 kg) Maximum baggage weight in FWD compartment (non pressurized) : 110 lbs (50 kg)
Page 47: Flight Load Factor Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved FLIGHT LOAD FACTOR LIMITS Flaps up : -- 1.5 ≤ n ≤ + 3.8 g Flaps down : -- 0 ≤ n ≤ + 2.0 g CAUTION INTENTIONAL NEGATIVE LOAD FACTORS PROHIBITED Edition 1 -- November 30, 2010 Page 2.5.2 Rev.
Page 48: Operation Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.6 - - OPERATION LIMITS MANEUVER LIMITS This airplane is certified in the normal category. The normal category is applicable to airplanes intended for non--acrobatic operations. Non--acrobatic operations include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and steep turns in which the angle of bank is no more than 60°.
Page 49: Gps Navigation Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved GPS NAVIGATION LIMITS Data base updating must be verified before each flight. The navigation sources required for the anticipated flight shall be serviceable and allow an immediate crossed check on available ground aids or shall allow to return to primary navigation sources in case of GPS navigation loss.
Page 50 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 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”...
Page 51: Severe Icing Conditions
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 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.
Page 52: Flaps Operating Envelope
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved -- Accumulation of ice on the upper surface of the wing aft of the protected area. Since the autopilot, when operating, may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when any of the visual cues specified above exist, or when unusual lateral trim requirements or autopilot trim warnings are encountered while the aircraft is in icing conditions.
Page 53: Edition 1
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Day VFR 1) Pilot instruments -- Airspeed indicator -- Sensitive and adjustable altimeter -- Magnetic compass with built--in compensator 2) CAS warning and caution messages -- Oil pressure -- Low fuel pressure -- Fuel selector OFF -- Fuel auxiliary pump ON -- L.H.
Page 54 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 5) Various indicators -- Fuel gauge indicators (2) -- Fuel pressure indicator -- Voltmeter -- Ammeter -- Outside air temperature 6) Installations -- Fuel mechanical pump (main) -- Fuel electrical pump (auxiliary) -- Fuel shut--off valve -- Fuel timer -- Starter generator...
Page 55 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Night VFR 1) All equipment required for day VFR 2) Attitude display indicator 3) Instrument lighting 4) Instrument panel lighting 5) Emergency lighting 6) Vertical speed indicator 7) Navigation lights (4) 8) Anticollision lights (2) 9) Landing light 1) All equipment required for day VFR...
Page 56: Altitude Operating Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Flight into icing conditions -- All equipment required for IFR flight -- Propeller deicing -- L.H. windshield deicing -- Airframe, stabilizer and elevator horn deicing -- Wing leading edge inspection light (if night flight) -- Stall warning deicing -- Inertial separator ALTITUDE OPERATING LIMITS...
Page 57: In--Flight Circuit Breaker Use Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved IN- -FLIGHT CIRCUIT BREAKER USE LIMITS A tripped circuit breaker should not be reset in flight unless deemed necessary for continued safe flight and landing. Only one reset should be attempted.
Page 58 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved Operators must have back--up charts available to the flight crew. Database currency must be verified prior to use via database effectivity page. The flight crew is responsible for verifying availability of charts for the planned flight.
Page 59: Seating Limits C.g
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.7 - - MISCELLANEOUS LIMITS SEATING LIMITS C.G. From 1 to 6 seats : -- 2 seats at 180.5 inches (4.585 m) -- 2 seats at 219.1 inches (5.565 m) } see NOTE 1 -- 2 seats at 259.3 inches (6.585 m) -- 2 seats at 180.5 inches (4.585 m)
Page 60: Markings
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.8 - - MARKINGS AIRSPEED INDICATOR Airspeed indicator markings and their color code significance are shown in Figure 2.8.1. KIAS MARKING SIGNIFICANCE (Value or range) Red line Below 60 White line 60 -- 122 Full Flap Operating Range...
Page 61: Engine Instruments
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved ENGINE INSTRUMENTS Engine instrument markings and their color code significance are shown in Figure 2.8.3. Yellow Line or Line or arc Green Arc Red Line INSTRUMENT --------- --------- --------- --------- Minimum Caution...
Page 62: Placards
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.9 - - PLACARDS (1) Under L.H. front side window -- Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped retrofit with modification Nr MOD 70--019--25 : ICING CONDITIONS ALLOWED FLIGHT CONDITIONS : DAY AND NIGHT VFR AND IFR...
Page 63 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (2) Calibration chart on compass and on windshield post WARNING Steer TURN L AND R WINDSHIELD DE- -ICE OFF BEFORE Steer COMPASS READING DATE : RADIO ON (3) On rear baggage compartment bottom bulkhead (pressurized) 100 kg - - 220 lbs MAXIMUM IT IS THE PILOT’S RESPONSIBILITY TO CHECK THAT ALL THE BAGGAGES ARE...
Page 64 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (5) Under GCU 475 control unit on pedestal console Edition 1 -- November 30, 2010 Page 2.9.3 Rev. 0...
Page 65 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (6) On fuel selector (7) Near fuel tank caps Edition 1 -- November 30, 2010 Page 2.9.4 Rev. 0...
Page 66 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (8) On internal face of L.H. engine cowling Oil system capacity 12 l 12.7 qt (9) On R.H. side, at front seat level and under seating of intermediate and rear passenger seats, which are fitted with oxygen EMERGENCY OXYGEN IN DRAWER UNDER SEAT ;...
Page 67 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (12) Under R.H. control wheel (13) On nose gear door (14) On nose gear leg NOSE LANDING GEAR TIRE PRESSURE : 6,5 bar 94 psi Edition 1 -- November 30, 2010 Page 2.9.6 Rev.
Page 68 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (15) On main gear leg MAIN LANDING GEAR TIRE PRESSURE : 8,25 bar 120 psi (16) On engine cowling, in front of baggage compartment door EXTERNAL POWER 28 VOLTS D.C. NOMINAL 800 AMPS STARTING CAPACITY MIN DO NOT EXCEED 1400 AMPS...
Page 69 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (17) TBM700B On access door -- External side (18) TBM700B On outer fuselage skin aft of access door and in the cabin forward of access door Edition 1 -- November 30, 2010 Page 2.9.8 Rev.
Page 70 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (19) TBM700A from S / N 1 to S / N 49, except airplanes equipped as a retrofit with modification No. MOD70--019--25 On access door -- Internal side (19) TBM700A from S / N 50, plus airplanes equipped as a retrofit with modification No.
Page 71 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (19) TBM700B On access door -- Internal side Edition 1 -- November 30, 2010 Page 2.9.10 Rev. 0...
Page 72 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (20) From S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification No. MOD 70--019--25 On emergency exit handle Edition 1 -- November 30, 2010 Page 2.9.11 Rev.
Page 73 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (20) 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 On emergency exit handle Marking on cover Marking on handle Edition 1 -- November 30, 2010...
Page 74 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (21) TBM700A On external side of lower half--door TBM700B On last step of stairs STAIRS MAX LOAD : ONE PERSON (22) TBM700B On R.H. access door jamb DO NOT USE HAND RAIL TO RETRACT OR STOW...
Page 75 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Page GENERAL 3.1.1 ..........REJECTED TAKEOFF PROCEDURE 3.2.1 .
Page 76 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page EMERGENCY LANDINGS 3.7.1 ....... . . 3.7.1 FORCED LANDING (ENGINE CUT OFF) .
Page 77 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page 3.11 LANDING GEAR AND FLAPS 3.11.1 ......3.11.1 DISCREPANCY WHEN LANDING GEAR GOES UP .
Page 78 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.1 - - GENERAL The recommended procedures for different failures or emergency situations are provided in this Section. Emergency procedures associated with optional or particular equipment which require pilot’s operating handbook supplements are provided in Section 9 ”Supplements”.
Page 79 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Alarm system recall Main failure or state modification of the different systems are provided by warning or caution messages appearing on CAS display. The CAS includes red messages indicating failures which require an immediate action from the pilot, and amber messages indicating failures or discrepancies which require an action as soon as practical.
Page 80: Rejected Takeoff Procedure
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.2 - - REJECTED TAKEOFF PROCEDURE Following an engine failure, refer to Chapter 3.3, Paragraph ”ENGINE FAILURE AT TAKEOFF BEFORE ROTATION”. For any other reason : 1 -- Power lever .
Page 81: Engine Failures
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 - - ENGINE FAILURES ENGINE FAILURE AT TAKEOFF BEFORE ROTATION 1 -- Power lever ......... IDLE 2 -- Braking .
Page 82: Engine Failure After Rotation
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE FAILURE AFTER ROTATION - - If altitude does not allow to choose a favourable runway or field : Land straight ahead keeping flaps at TO and without changing landing gear position.
Page 83: Engine Failure During Flight
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE FAILURE DURING FLIGHT 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
Page 84: Oil Pressure Drop
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES OIL PRESSURE DROP “OIL PRESS” RED CAS MESSAGE “OIL PRESS” AMBER CAS MESSAGE Indicates that oil pressure is below 60 psi 1 -- Oil pressure indicator .
Page 85: Engine Regulation Discrepancy, Power Loss, Power Lever Control Loss
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE REGULATION DISCREPANCY, POWER LOSS, POWER LEVER CONTROL LOSS (1/2) 1 -- If circumstances allow : Power lever ......... IDLE 2 -- Confirm engine still running 3 -- Check that no parameter exceeds allowed values...
Page 86 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE REGULATION DISCREPANCY, POWER LOSS, POWER LEVER CONTROL LOSS (2/2) 6 -- Perform a normal landing WITHOUT REVERSE 7 -- Braking ........AS REQUIRED If minimum power obtained is excessive : 1 -- Reduce airspeed by setting airplane in nose--up attitude at...
Page 87: Governor Regulation Control Not Operating
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES GOVERNOR REGULATION CONTROL NOT OPERATING May indicate a rupture of the linkage of the governor control. 1 -- Continue the flight. 2 -- If Np < 2000 RPM, do not perform a go--around and do not use the reverse.
Page 88: Excessive Propeller Rotation Speed
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES EXCESSIVE PROPELLER ROTATION SPEED Indicates : a propeller governor failure In that case, the propeller overspeed limiter will limit initially the rotation speed to 2100 RPM approximately. or a propeller governor and overspeed limiter failure In that case, only the torque limiter operates to limit the power.
Page 89: Red Cas Message "Itt" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES RED CAS MESSAGE “ITT” ON A - - During engine start : Indicates : ITT > 1000˚C 1000˚C > ITT > 870˚C for more than 5 seconds 870˚C >...
Page 90: Engine Does Not Stop On Ground
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE DOES NOT STOP ON GROUND If the engine does not stop when the condition lever is set to CUT OFF, proceed as follows : 1 -- ”AP TRIMS”...
Page 91: Air Start
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 - - AIR START AIR START ENVELOPE Pressure altitude (ft) 20000 STARTER STARTER ASSIST ASSIST MANDATORY NOT MANDATORY PROPELLER FEATHERED WINDMILLING PROPELLER (KIAS) Air start may be attempted at all speeds and all altitudes. However, above 20000 ft or with Ng <...
Page 92: Air Start With Starter
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 -- AIR START AIR START WITH STARTER (1/2) CAUTION THE STARTER CANNOT OPERATE IF THE ”GENERATOR” SELECTOR IS ON ”ST- -BY” CAUTION IGNITION IS NOT AVAILABLE IF THE ”ESS BUS TIE” SWITCH IS KEPT ”EMER”...
Page 93 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 -- AIR START AIR START WITH STARTER (2/2) 11 -- ”IGNITION” switch ......AUTO or ON 12 -- ”STARTER”...
Page 94: Air Start Without Starter
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 -- AIR START AIR START WITHOUT STARTER (STARTER ASSIST NOT MANDATORY) (1/2) CAUTION THE STARTER CANNOT OPERATE IF THE ”GENERATOR” SELECTOR IS ON ”ST- -BY” CAUTION IGNITION IS NOT AVAILABLE IF THE ”ESS BUS TIE” SWITCH IS KEPT ”EMER”...
Page 95 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 -- AIR START AIR START WITHOUT STARTER (STARTER ASSIST NOT MANDATORY) (2/2) 9 -- ”AUX BP” fuel switch ........10 -- ”IGNITION”...
Page 96: Fire And Smoke
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 - - FIRE AND SMOKE ENGINE FIRE ON GROUND “ITT” Symptoms : ITT increasing, red warning CAS message smoke, ... 1 -- Power lever ......... IDLE 2 -- Condition lever .
Page 97: Engine Fire In Flight
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE ENGINE FIRE IN FLIGHT “ITT” Symptoms : ITT increasing, red warning CAS message smoke, ... 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
Page 98: Cabin Electrical Fire Or Smoke During Flight
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT (1/2) 1 -- Oxygen ......USE AS REQUIRED (pilot and passengers) If the origin is known :...
Page 99 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT (2/2) If smoke or fire persists : 4 -- ”SOURCE” selector ........5 -- ”GENERATOR”...
Page 100: Smoke Elimination
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.5 -- FIRE AND SMOKE SMOKE ELIMINATION 1 -- Smoke origin ........IDENTIFY 2 -- Oxygen .
Page 101: Emergency Descents
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 - - EMERGENCY DESCENTS PROCEDURE IN SMOOTH AIR 1 -- Power lever ......... IDLE 2 -- Oxygen .
Page 102 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 -- EMERGENCY DESCENTS GLIDE DISTANCE AND OPTIMUM SPEED Configuration 1 -- Flaps ..........2 -- Landing gear .
Page 103: Emergency Landings
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 - - EMERGENCY LANDINGS FORCED LANDING (ENGINE CUT OFF) 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
Page 104: Tire Blowout During Landing
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS TIRE BLOWOUT DURING LANDING 1 -- Control direction with brakes and nose wheel steering 2 -- REVERSE ....... . . AS REQUIRED 3 -- Stop airplane to minimize damages 4 -- Perform engine SHUT--DOWN procedure (Refer to Chapter 4.3)
Page 105: Landing With Unlocked Main Landing Gear
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR (1/2) 1 -- Ask control tower or another airplane to visually check landing gear position CAUTION IF ONE MAIN LANDING GEAR IS NOT DOWN, IT IS BETTER TO LAND WITH GEAR UP.
Page 106 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR (2/2) 11 -- Condition lever ........CUT OFF 12 -- Engine stop procedure .
Page 107: Landing With Defective Nose Landing Gear
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH DEFECTIVE NOSE LANDING GEAR (DOWN UNLOCKED OR NOT DOWN) 1 -- Transfer passengers to the rear, if necessary 2 -- Approach ........Flaps TO IAS = 90 KIAS 3 -- Land with nose--up attitude, keep nose high...
Page 108: Landing With Gear Up
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH GEAR UP 1 -- Final approach ........Standard (Flaps LDG, IAS = 85 KIAS) 2 -- ”BLEED VALVE”...
Page 109: Landing Without Elevator Control
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITHOUT ELEVATOR CONTROL 1 -- Configuration ... LANDING GEAR DN - - FLAPS LDG 2 -- Airspeed .
Page 110: Landing With Flaps Malfunction
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS LANDING WITH FLAPS MALFUNCTION For flaps deflections from “UP” to “TO” position : 1 -- Proceed as for a normal landing, maintaining approach airspeed .
Page 111: Ditching
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS DITCHING 1 -- Landing gear ......... . In heavy swell with light wind, land parallel to the swell (rollers).
Page 112: Fuel System
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 - - FUEL SYSTEM RED CAS MESSAGE “FUEL PRESS” ON Indicates a fuel pressure drop at ”HP” engine pump inlet 1 -- Remaining fuel ........CHECK 2 -- Tank selector .
Page 113: Amber Cas Message "Aux Boost Pmp On" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 -- FUEL SYSTEM AMBER CAS MESSAGE “AUX BOOST PMP ON” ON (Indication is normal if ”AUX BP” fuel switch is in ON position) If ”AUX BP” fuel switch is in AUTO position : 1 -- Reset to .
Page 114: Amber Cas Message "Fuel Low L" Or "Fuel Low R" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 -- FUEL SYSTEM AMBER CAS MESSAGE “FUEL LOW L” OR “FUEL LOW R” ON Indicates level drop in the corresponding tank 1 -- Corresponding gage ......CHECK 2 -- Check the other tank has been automatically selected If not :...
Page 115: Electrical System
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 - - ELECTRICAL SYSTEM RED CAS MESSAGE ”BAT OVERHEAT” ON (if Cadmium- -Nickel battery installed) Indicates a battery overheat 1 -- ”SOURCE” selector ........CAS MESSAGE ”BAT OFF”...
Page 116: Amber Cas Message "Main Gen" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER CAS MESSAGE “MAIN GEN” ON Indicates that ”GENERATOR” selector has been positioned to OFF or ST--BY, or main generator is cut off 1 -- If necessary .
Page 117: Amber Cas Message "Low Voltage" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER CAS MESSAGE “LOW VOLTAGE” ON normal functioning on ”MAIN GEN” 1 -- Voltmeter voltage ....... . . CHECK 2 -- If battery voltage is <...
Page 118: Amber Cas Message "Low Voltage" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER CAS MESSAGE “LOW VOLTAGE” ON functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (1/3) Amber CAS messages “MAIN GEN and “LOW VOLTAGE” ON with ”GENERATOR”...
Page 119 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER CAS MESSAGE “LOW VOLTAGE” ON functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (2/3) If conditions allow : VMC and non icing conditions 10 -- If altitude ≥...
Page 120 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER CAS MESSAGE “LOW VOLTAGE” ON functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (3/3) -- TAS breaker ........PULL -- DATA LINK breaker .
Page 121: Electrical Distribution Of Bus Bars
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Figure 3.9.1 (1/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- November 30, 2010 Page 3.9.7 Rev. 0...
Page 122 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Figure 3.9.1 (2/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- November 30, 2010 Page 3.9.8 Rev. 0...
Page 123: Avionics" Master Switch Failure
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM ”AVIONICS” MASTER SWITCH FAILURE In case of ”AVIONICS” MASTER switch misfunction, leading to the impossibility of energizing the radionavigation equipment : 1 -- ”AVIONICS MASTER” circuit breaker .
Page 124: Pressurization And Air Conditioning
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 - - PRESSURIZATION AND AIR CONDITIONING RED CAS MESSAGE “CABIN DIFF PRESS” ON 1 -- Pressurization indicator ......CHECK ∆...
Page 125: Cabin Not Depressurized After Landing
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING CABIN NOT DEPRESSURIZED AFTER LANDING ∆P cabin > 0 1 -- ”DUMP” switch ....... . ACTUATED 2 -- ”BLEED VALVE”...
Page 126: Red Cas Message "Bleed Temp" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING RED CAS MESSAGE ”BLEED TEMP” ON Indicates overheat of air conditioning pack. Normally this leads to ”BLEED VALVE” cutoff and to “BLEED OFF” amber CAS message appearance Should automatic cutoff occur or not : 1 -- ”BLEED VALVE”...
Page 127: Red Cas Message "Door" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING RED CAS MESSAGE ”DOOR” ON Indicates that the door latches of the access door have not been correctly locked On ground, check the correct locking, as well as the latches position of the access door During flight : 1 -- Start a slow descent...
Page 128: Amber Cas Message "Vacuum Low" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING AMBER CAS MESSAGE ”VACUUM LOW” ON Suction gage indicator ....... . CHECK Low vacuum may lead to misfunctioning of leading edge deicing, pressurization and gyroscopic vacuum--operated...
Page 129: Defog Malfunction
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING DEFOG MALFUNCTION If moisture starts to quickly cover the inside of the windscreeen with the distributor already positioned on ”DEFOG” : 1 -- ”DEFOG / NORMAL” distributor .
Page 130: Landing Gear And Flaps
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 - - LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP (1/2) - - Red warning light on ”LANDING GEAR” control panel remains ON : 1 -- ”LDG GR” circuit--breaker .
Page 131 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP (2/2) CAUTION THE ENTIRE EXTENSION OF THE LANDING GEAR TAKES ABOUT 65 CYCLES. IT IS MANDATORY TO HAVE A CLEAN HARDENING OF THE MANUAL CONTROL AT THE END OF THE MANEUVER If landing gear is down and locked (correct indication) :...
Page 132 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 - - LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP (1/2) - - Red warning light on ”LANDING GEAR” control panel remains flashing ON : The red warning light on the landing gear control panel flashing at the end of maneuver indicates that the landing gear electrohydraulic pump still operates.
Page 133 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP (2/2) If the fixed red warning light is still on : Continue flight if necessary at a speed below 178 KIAS, without icing conditions or land.
Page 134: Discrepancy When Landing Gear Goes Down
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN (1/2) - - Incorrect indication on ”LANDING GEAR” control panel : Red warning light switched on or off, one or more green lights are missing Perform a MANUAL EXTENSION : 1 -- ”LDG GR”...
Page 135 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN (2/2) If the ”CHECK DN” indication is also incorrect, recycle landing gear as follows : 9 -- By--pass selector .
Page 136 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN (1/2) - - Red warning light on ”LANDING GEAR” control panel remains flashing ON (whatever the condition of the green lights may be) : The red warning light on the landing gear control panel flashing at the end of maneuver indicates that the landing gear electrohydraulic pump operates correctly.
Page 137 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN (2/2) 6 -- ”LDG GR” circuit breaker ......PUSH 7 -- ”CHECK DN”...
Page 138: Red Cas Message "Flaps Asym" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS RED CAS MESSAGE “FLAPS ASYM” ON Indicates a dissymmetry of flap deflection. This immediately stops the flap motor and prevents further operation of the flaps 1 -- ”FLAPS”...
Page 139: Deicing System
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 - - DEICING SYSTEM LEADING EDGES DEICING FAILURE Symptoms : Failure on one of the two pneumatic deicing pulses : -- Ice on wing outboard sections -- Or ice on wing inboard sections and stabilizers -- One of the two cycling green lights is not lit 1 -- LEAVE icing conditions as soon as possible 2 -- ”AIRFRAME DE ICE”...
Page 140: Inertial Separator Failure
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM INERTIAL SEPARATOR FAILURE “INERT SEP ON” Symptoms : -- Warning does not appear within 30 seconds following ”INERT SEP” switch setting ON -- Neither torque drop, nor increase of ITT observed during maneuver LEAVE icing conditions as soon as possible WINDSHIELD DEICING FAILURE...
Page 141: Windshield Misting Or Internal Icing
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM WINDSHIELD MISTING OR INTERNAL ICING Symptoms : -- Mist or ice on windshield internal face 1 -- ”CABIN TEMP” selector ......Max HOT 2 -- ”DEFOG / NORMAL”...
Page 142: Pitot No Ht 2"Or "Stall No Heat" On
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM AMBER CAS MESSAGES “PITOT NO HT 1”, “PITOT NO HT 2” OR “STALL NO HEAT” ON Indicates a heating failure of the corresponding probe “PITOT NO HT 1”...
Page 143: Miscellaneous
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 - - MISCELLANEOUS RUNAWAY OF ONE OF THE THREE ELECTRICAL TRIM TABS 1 -- ”AP / DISC TRM INT” push button ..PRESSED AND HOLD The three trim tabs are disconnected and runaway stops 2 -- ”AP / TRIMS MASTER”...
Page 144: Emergency Exit Use
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS EMERGENCY EXIT USE 1 -- Check that the anti--theft safety pin has been removed 2 -- Lift up the opening handle 3 -- Pull emergency exit assembly toward oneself to release it from its recess 4 -- Put the emergency exit door inside fuselage or throw it away from the fuselage through the opening...
Page 145: Total Communication Failure
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS TOTAL COMMUNICATION FAILURE 1 -- Refer to PARTICULAR TRANSPONDER USES procedures 2 -- Apply air traffic control procedures in case of communications failure : -- code 7700 during 1 minute, then -- code 7600 3 -- Try to restore communications by using all possible combinations of the headset, micro and loudspeaker...
Page 146: Accidental Spins
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS ACCIDENTAL SPINS (Voluntary spins are prohibited) In case of accidental spins 1 -- Control wheel ..... NEUTRAL : PITCH AND ROLL 2 -- Rudder...
Page 147: Oxygen Use
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS OXYGEN USE (1/2) WARNING SMOKING IS STRICTLY PROHIBITED ANY TIME OXYGEN SYSTEM IS USED. BEFORE USING OXYGEN, REMOVE ANY TRACE OF OIL, GREASE, SOAP AND OTHER FATTY SUBSTANCES (INCLUDING LIPSTICK, MAKE UP, ETC...) WARNING IN CASE GENERATOR FAILS TO ACTIVATE, PULL ON...
Page 148: Airspeed Indicating System Failure
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS OXYGEN USE (2/2) NOTE : Whenever an oxygen generator is activated, the CAS message ”OXYGEN” appears on the MFD unit. The CAS message will remain ON as long as the used generator is not replaced AIRSPEED INDICATING SYSTEM FAILURE Symptoms : erroneous indication in flight...
Page 149: Flight Into Severe Icing Conditions
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS FLIGHT INTO SEVERE ICING CONDITIONS Severe icing conditions, particularly freezing rain and freezing drizzle, can be identified by : -- unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice, -- accumulation of ice on the upper surface of the wing aft of the protected area.
Page 150: Loss Of Gps Navigation : "Loi", "Warn" Or
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS LOSS OF GPS NAVIGATION : “LOI”, “WARN” OR “DR” ANNUNCIATIONS LIGHT ON In case of loss of RAIM function, the navigation information remains available but its integrity is no longer controlled. -- If RAIM loss occurs out of B--RNAV area, the aircraft must not enter B--RNAV area.
Page 151 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS Page GENERAL 4.1.1 ..........AIRSPEEDS FOR NORMAL OPERATION 4.2.1 .
Page 152 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page 4.4.33 MOTORING FOLLOWED BY AN ENGINE START ....4.4.36 AFTER STARTING ENGINE .
Page 153 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.1 - - GENERAL This Section provides procedures for the conduct of normal operation of TBM 700 airplane. The first part of this Section lists the normal procedures required as a check list.
Page 154: Airspeeds For Normal Operation
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.2 - - AIRSPEEDS FOR NORMAL OPERATION CONDITIONS : - Takeoff weight 6579 lbs (2984 kg) - Landing weight : 6250 lbs (2835 kg) Rotation airspeed (V -- Flaps TO .
Page 155: Check--List Procedures
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.3 - - CHECK- -LIST PROCEDURES PREFLIGHT INSPECTION (See Figure 4.3.1) IMPORTANT * During outside inspection, visually check inspection doors and airplane general condition. * In cold weather, remove even small accumulations of frost, ice or snow from wing, tail and control surfaces.
Page 156 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) Figure 4.3.1 -- PREFLIGHT INSPECTION Edition 1 -- November 30, 2010 Page 4.3.2 Rev. 0...
Page 157 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) A - - INSIDE INSPECTIONS Cockpit -- CRASH lever ........1 -- DE ICE SYSTEM panel -- All switches .
Page 158 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 11 -- ECS panel -- ”BLEED VALVE” switch ......-- ”CABIN FAN”...
Page 159 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) CAUTION BEFORE SELECTING SOURCE, CHECK : 19 - - ”IGNITION” switch ....... . . AUTO 20 - - ”STARTER”...
Page 160 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 30 -- CAS display ........CHECK 31 -- Left and right fuel quantities .
Page 161 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 36 -- Reentering the airplane -- EXT LIGHTS panel ....ALL SWITCHES OFF -- DE ICE SYSTEM panel .
Page 162 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) B - - AIRPLANE OUTSIDE L.H. wing III 1 -- Flap ..........CHECK (Condition / Play) 2 -- Aileron and trim / Spoiler...
Page 163 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 13 -- L.H. main landing gear -- Shock--absorber / doors / tire / wheel well ....... . CHECK Fuselage forward section IV 1 -- Baggage compartment...
Page 164 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 9 -- Nose gear -- Landing light / shock--absorber / doors / tire / wheel well ....... . CHECK 10 -- R.H.
Page 165 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) Fuselage rear section / Empennages 1 -- Static pressure ports ..... . . Clean - - CHECK 2 -- Static pressure ports .
Page 166: Before Starting Engine
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (1/2) CAUTION ”BLEED VALVE” SWITCH ON ”ON” MAY CAUSE OVERTEMPERATURE OR ABNORMAL ACCELERATION AT START CAUTION MAKE SURE THAT ”MAN OVRD” CONTROL IS OFF TO AVOID OVERTEMPERATURE RISKS AT START 1 -- Preflight inspection .
Page 167 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (2/2) 17 -- CAS display -- Access door “DOOR” WARNING CAS MESSAGE -- Oxygen emergency system “OXYGEN” WARNING CAS MESSAGE 18 -- Fuel -- Quantity .
Page 168: Starting Engine Using Airplane Power
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (1/5) CAUTION BEFORE SELECTING SOURCE, CHECK : 1 - - ”IGNITION” switch ......AUTO 2 - - ”STARTER”...
Page 169 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (2/5) 7 -- FUEL panel -- ”AUX BP” switch ........“AUX BOOST PMP ON”...
Page 170 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (3/5) CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO ”LO / IDLE” THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE, OVERTEMPERATURE INDICATION APPEARS (MAX.
Page 171 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (4/5) ENGINE START panel -- ”IGNITION” switch ........AUTO -- ”STARTER”...
Page 172 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (5/5) 10 -- Condition lever ....... . . HI / IDLE 11 -- Engine instruments .
Page 173: Starting Engine Using External Power (Gpu)
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (1/5) 1 -- GPU ........CONNECTED CAUTION BEFORE SELECTING SOURCE, CHECK :...
Page 174 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (2/5) 8 -- FUEL panel -- ”AUX BP” switch ........“AUX BOOST PMP ON”...
Page 175 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (3/5) CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO ”LO / IDLE” THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE, OVERTEMPERATURE INDICATION APPEARS (MAX.
Page 176 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (4/5) ENGINE START panel -- ”IGNITION” switch ........AUTO -- ”STARTER”...
Page 177 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (5/5) 11 -- ”SOURCE” selector ........“BAT OFF”...
Page 178: Motoring
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING (1/2) CAUTION AFTER ANY STARTING INTERRUPT PROCEDURE : - - WAIT FOR ENGINE TOTAL SHUT- -DOWN - - WAIT AT LEAST 30 SECONDS BEFORE INITIATING A MOTORING 1 -- Engine controls -- ”MAN OVRD”...
Page 179 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING (2/2) 3 -- ”IGNITION” switch ........“IGNITION”...
Page 180: Motoring Followed By An Engine Start
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (1/2) Within starter operating limits (continuous max. 1 minute), it is possible to initiate a starting procedure from a motoring procedure. 1 -- Engine controls -- ”MAN OVRD”...
Page 181 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (2/2) 6 -- Monitor increase of : -- ITT ....(max.
Page 182: After Starting Engine
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES AFTER STARTING ENGINE (1/2) 1 -- ”GENERATOR” selector -- On ”MAIN” ....Voltage and current checked when battery current ≤...
Page 183 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES AFTER STARTING ENGINE (2/2) 9 -- VHF/VOR/GPS ....... . ADJUSTED -- Radar/Stormscope/TAS/TAWS/ Radio altimeter (if installed)
Page 184: Taxiing
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAXIING 1 -- ”TAXI” light ......... . 2 -- ”INERT SEP”...
Page 185: Before Takeoff
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE TAKEOFF (1/2) 1 -- Parking brake ........“PARK BRAKE”...
Page 186 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE TAKEOFF (2/2) 8 -- Pilot’s / Passengers’ belts ......CHECK -- Passengers’...
Page 187: Takeoff
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAKEOFF (1/2) WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.5, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS”...
Page 188 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAKEOFF (1/2) WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.5, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS”...
Page 189 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAKEOFF (2/2) 8 -- Power lever ....... . . TRQ = 100 % 9 -- Takeoff .
Page 190: Climb
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES CLIMB 1 -- Power lever ......ADJUST according to engine operation table - - Chapter 5.7 or to MXCL indicator on the PFDs...
Page 191: Cruise
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES CRUISE 1 -- Power lever ......ADJUST according to engine operation table - - Chapter 5.7 or to Cruise index on the PFDs...
Page 192: Descent
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES DESCENT 1 -- Altimeter settings ......COMPLETE 2 -- “ALT SEL”...
Page 193: Before Landing
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE LANDING Long final 1 -- Altimeters ........CHECK 2 -- Fuel -- Gages...
Page 194 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES LANDING 1 -- Power lever ......... IDLE After wheel touch 2 -- Reverse...
Page 195 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES GO- -AROUND 1 -- Simultaneously -- Power lever ......TRQ = 100 % -- Attitude .
Page 196 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TOUCH AND GO After wheel touch 1 -- Flaps ..........2 -- Elevator trim .
Page 197 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (1/2) 1 -- Parking brake ........“PARK BRAKE”...
Page 198 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (2/2) 14 -- EXT LIGHTS panel -- All switches ........15 -- INT LIGHTS panel -- All switches .
Page 199 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.4 - - AMPLIFIED PROCEDURES PREFLIGHT INSPECTION A - - INSIDE INSPECTIONS Cockpit -- CRASH lever ........1 -- DE ICE SYSTEM panel -- All switches .
Page 200 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 8 -- Landing gear emergency control Open door of emergency landing gear compartment. -- Lever ........PULLED DOWN -- By--pass selector .
Page 201 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 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 range.
Page 202 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 25 -- Voltage ......... . CHECK -- BAT .
Page 203 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 27 -- Oxygen emergency system “OXYGEN” WARNING CAS MESSAGE If not, seek which of the oxygen generators has been activated. The amber strip around each generator becomes black by thermal effect, if the generator has been operated.
Page 204 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 34 -- DE ICE SYSTEM panel -- ”PITOT 1 HTR” switch ......“PITOT HT 1”...
Page 205 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) Cabin II 1 -- Cabin fire extinguisher (if installed) ....CHECK (Pressure / Attachment) The fire extinguisher is provided with a pressure gage.
Page 206 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) B - - AIRPLANE OUTSIDE The preflight inspection described in Figure 4.3.1 is recommended before each flight. NOTE : If a preflight inspection is performed, just after the engine shut- -off, be careful because the leading edge of engine air inlet, as well as exhaust stubs may be very hot.
Page 207 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 3 -- Trailing edge static discharger ..... CHECK (Condition / Attachment) 4 -- Wing tip / nav.
Page 208 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) A long term storage of the airplane causes water accumulation in fuel, which absorbs additive. This phenomenon occurs when an excessive quantity of water accumulates in fuel tank sumps. Refer to Section 8 for servicing operations relative to fuel additives.
Page 209 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 3 -- Fuel circuit drain ........DRAIN (Fuel free of water and contamination) -- Filter contamination indicator...
Page 210 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 9 -- Nose gear -- 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...
Page 211 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 7 -- Fuel tank air vent ....Unobstructed - - CHECK 8 -- Wing tip / nav.
Page 212 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 7 -- Vertical stabilizer deicer boots ..... . CHECK (Condition / Attachments) 8 -- Rudder and trim...
Page 213 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (1/3) Check that the weight and balance are within the correct limits. Brief passengers about use of seat belts and the emergency oxygen system, as well as opening the access door and the emergency exit.
Page 214 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (2/3) 8 -- 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.
Page 215 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (3/3) 18 -- Fuel -- Gages ........CHECKED -- Tank selector .
Page 216 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (1/6) CAUTION BEFORE SELECTING SOURCE, CHECK : 1 - - ”IGNITION” switch ......AUTO 2 - - ”STARTER”...
Page 217 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (2/6) 7 -- FUEL panel -- ”AUX BP” switch ........“AUX BOOST PMP ON”...
Page 218 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (3/6) starting engine procedure aborted further overtemperature indications (max. ITT : 870°C for more than 20 seconds -- 1000°C for more than 5 seconds), maintaining during few seconds ”STARTER”...
Page 219 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (4/6) -- Ng The start sequence must be timed to ensure starter limits are not exceeded. Lengthy operation of the starter results in excessive temperature of the engine : -- If Ng does not reach 30 % within 30 seconds, after the starter is selected ON, abort the start.
Page 220 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (5/6) Monitor increase of : -- ITT ....(max.
Page 221 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (6/6) 13 -- Generator “MAIN GEN” WARNING CAS MESSAGE RESET if necessary ”MAIN GEN” CAS message normally goes out, as soon as ”STARTER”...
Page 222 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (1/7) Before connecting GPU, check that its indicated voltage is correct. 1 -- GPU ........CONNECTED CAUTION BEFORE SELECTING SOURCE, CHECK :...
Page 223 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (2/7) -- Propeller governor lever ..... . . MAX RPM -- Condition lever .
Page 224 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (3/7) Monitor increase of : -- ITT ... . . (max.
Page 225 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (4/7) CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO ”LO / IDLE” THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE, OVERTEMPERATURE INDICATION APPEARS (MAX.
Page 226 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (5/7) CAUTION IF ENGINE IS SLOW TO START OR STAGNATES. INTERRUPT STARTING PROCEDURE : Condition lever ........CUT OFF ”IGNITION”...
Page 227 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (6/7) -- ”STARTER” switch ........“STARTER”...
Page 228 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (7/7) 17 -- FUEL panel -- ”AUX BP” switch ....... . . AUTO At this time, observing a drop in the fuel pressure is normal.
Page 229 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING (1/2) To drain fuel accumulated inside the combustion chamber, a motoring procedure is required following an aborted start. A 15--second dry motoring run is sufficient to clear any fuel pooled in the engine. Fuel removed in this manner is collected and not drained under the engine.
Page 230 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING (2/2) 2 -- FUEL panel -- Tank selector ........L or R -- ”AUX BP”...
Page 231: Motoring Followed By An Engine Start
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (1/3) Amplified procedures stated in starting engine sequences using airplane power or with GPU are also to be applied to hereunder procedure.
Page 232 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (2/3) 5 -- After 15 seconds : -- ”IGNITION” switch ......AUTO or ON -- Ng .
Page 233 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (3/3) 10 -- FUEL panel -- ”AUX BP” switch ....... . . AUTO “AUX BOOST PMP ON”...
Page 234: After Starting Engine
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (1/4) 1 -- ”AVIONICS” MASTER switch ......2 -- ”AP TRIMS”...
Page 235 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (2/4) -- ”CABIN FAN” switch ..... . . As required There is no inconvenience to set ”CABIN FAN”...
Page 236 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (3/4) 11 -- AP / TRIMS -- ”AP TRIMS” MASTER operation ....CHECK Detailed control procedures of autopilot and electrical pitch trim are described in the ”GARMIN”...
Page 237 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (4/4) -- ”WINDSHIELD” switch ..ONand on the MFD Page Check illumination of the green light(s) located above the switch (except if hot conditions) This light may remain OFF, if cabin temperature is very high, for...
Page 238: Taxiing
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAXIING (1/2) 1 -- ”TAXI” light ......... . 2 -- ”INERT SEP”...
Page 239 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAXIING (2/2) CAUTION AVOID USING REVERSE DURING TAXIING Operation in the Beta (β) range / reverse is not restricted during ground operations. However, foreign particles (dust, sand, grass, gravel, etc...) may be blown into the air, ingested by the engine (above all if ”INERT SEP”...
Page 240: Before Takeoff
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (1/3) 1 -- Parking brake ........“PARK BRAKE”...
Page 241 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (2/3) 6 -- Flight controls ....DEFLECTIONS CHECKED 7 -- Trims -- Pitch...
Page 242 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (3/3) 13 -- VHF/VOR/GPS/XPDR ......ADJUSTED -- Radar/Stormscope/TAS/TAWS/ADF (if installed)
Page 243: Takeoff
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (1/3) WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.5, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS”...
Page 244 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (1/3) WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.5, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS”...
Page 245 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (2/3) -- PROP O’ SPEED ..... . . TEST : Release -- Check that propeller RPM increases by a minimum of 50 RPM when compared to minimum value during PROP O’SPEED test.
Page 246 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (2/3) -- PROP O’ SPEED ..... . . TEST : Release -- Check that propeller RPM increases again up to 1900 RPM 7 -- Brakes...
Page 247 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (3/3) Post--MOD70--021--32 12 -- Landing gear control ..(IAS < 128 KIAS) ... . . During the sequence : -- The red warning light flashes ;...
Page 248: Climb
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CLIMB (1/2) 1 -- Power lever ......ADJUST according to engine operation table - - Chapter 5.7 to MXCL indicator on the PFDs...
Page 249 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CLIMB (2/2) 3 -- ECS panel -- Cabin altitude selector ..Cruise altitude + 1000 feet -- Cabin rate selector .
Page 250: Cruise
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CRUISE (1/2) 1 -- Power lever ......ADJUST according to engine operation table - - Chapter 5.7 to Cruise index on the PFD’s...
Page 251 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CRUISE (2/2) 3 -- Fuel -- Gages ........CHECK REGULARLY CHECK : - - consumption...
Page 252: Descent
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES DESCENT (1/2) 1 -- Flaps ..........2 -- Altimeter settings .
Page 253 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES DESCENT (2/2) 6 -- Windshield misting protection system ... . As required avoid canopy misting moist conditions, turn ”DEFOG / NORMAL”...
Page 254: Before Landing
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE LANDING (1/2) Long final 1 -- Altimeters ........CHECK 2 -- Fuel -- Gages...
Page 255 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE LANDING (2/2) Short final 8 -- Autopilot ......... . . Autopilot must be disconnected at the latest at 200 ft above the ground or at decision height or before go--around, whichever is the highest.
Page 256: Landing
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES LANDING 1 -- Power lever ......... IDLE Avoid three--point landings.
Page 257 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES GO- -AROUND 1 -- Simultaneously -- Power lever ......TRQ = 100 % -- Attitude .
Page 258: Touch And Go
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TOUCH AND GO After wheel touch 1 -- Flaps ..........Check that flaps have well reached the TO position before increasing power.
Page 259: After Landing
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER LANDING RUNWAY CLEAR -- AIRPLANE STOPPED 1 -- DE ICE SYSTEM panel -- ”AIRFRAME DE ICE” switch ......-- ”PROP DE ICE”...
Page 260: Shut--Down
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (1/2) 1 -- Parking brake ........“PARK BRAKE”...
Page 261 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (2/2) 10 -- Propeller governor lever ... FEATHER for 15 seconds Keep propeller governor lever on FEATHER position for 15 seconds minimum before shutting down engine.
Page 262: Particular Procedures
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.5 - - PARTICULAR PROCEDURES REMARK : The procedures and procedure elements given in this Chapter ”PARTICULAR PROCEDURES” supplement the normal procedures or complete certain elements of the normal procedures described in Chapter(s) 4.3 and/or 4.4.
Page 263: Flight Into Known Icing Conditions
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (2/5) Boots are automatically cycling at the optimum time to assure proper ice removal. Correct operation of the system can be checked observing the corresponding green advisory light illumination at each boot inflation impulse.
Page 264 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (3/5) 2 -- When operating under IMC : -- All ”DE ICE SYSTEM” switches ......-- ”IGNITION”...
Page 265 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (4/5) NOTE : ”IGNITION” switch may be left ON for a long period. Standby compass indications are altered when windshield deicing system(s) operate(s).
Page 266 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (5/5) 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...
Page 267: Flight Into Severe Icing Conditions
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO SEVERE ICING CONDITIONS (1/2) THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN- -FLIGHT ICING : -- Visible rain at temperatures below 0°C ambient air temperature, -- Droplets that splash or splatter on impact at temperatures below 0°C ambient air temperature.
Page 268 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO SEVERE ICING CONDITIONS (2/2) 6 -- Do not extend flaps when holding in icing conditions. Operation with flaps extended can result in a reduced wing angle--of--attack, with the possibility of ice forming on the upper surface further aft on the wing than normal, possibly aft of the protected area.
Page 269: Flight Under Heavy Precipitations
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT UNDER HEAVY PRECIPITATIONS 1 -- ”IGNITION” switch ........This action is intended, in highly improbable case of an engine flame--out further to an important ingestion, to ensure immediate restarting without action of the pilot.
Page 270 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW (2/2) Before takeoff 1 -- If the runway is long enough, takeoff should be performed with the flaps in the up position.
Page 271: Utilization On Icy Or Covered With Tamped Snow Runways
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION COVERED WITH TAMPED SNOW RUNWAYS (1/2) Refer if required to paragraph ”UTILIZATION BY COLD WEATHER AND VERY COLD WEATHER”. Preflight inspection 1 -- Remove any snow or ice from the wings, stabilizers and movable surfaces, landing gear wells and gear doors, as well as flap tracks, actuators and their fairings.
Page 272 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS (2/2) Landing After wheel touch 1 -- Use reverse only if necessary and very progressively by monitoring the airplane behaviour.
Page 273: Utilization By Cold Weather (-- 0°C To -- 25°C) And Very Cold Weather (-- 25°C To -- 40°C )
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C TO - - 25˚C) AND VERY COLD WEATHER (- - 25˚C TO - - 40˚C) (1/10) REMARK : The procedures hereafter supplement the normal procedures for the airplane use when operating under temperatures between 0˚C and - - 40˚C on ground.
Page 274: Envelope 1
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (2/10) ENVELOPE 1 The procedures hereafter supplement the normal procedures for the airplane use when operating in the ”envelope 1”...
Page 275 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (3/10) Taxiing / Before takeoff / Takeoff 1 -- On ”DE--ICE SYSTEM”...
Page 276: Envelope 2
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (9/10) ENVELOPE 2 The procedures defined for the ”envelope 3” are also applicable for the ”envelope 2”.
Page 277 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (10/10) Taxiing / Before takeoff / Takeoff Apply procedures defined for Envelope 1.
Page 278: Envelope 3
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved ENVELOPE 3 The procedures hereafter supplement or replace the normal procedures for the airplane use when operating in the ”envelope 3” defined in Figure 4.5.1. Preflight inspection 1 -- Preheat the engine and the cabin.
Page 279 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (5/10) 9 -- ”IGNITION” switch .
Page 280 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (6/10) -- Power lever .
Page 281 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (7/10) 8 -- ”SOURCE” selector .
Page 282 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0˚C to - - 25˚C) AND VERY COLD WEATHER (- - 25˚C to - - 40˚C) (8/10) Taxiing / Before takeoff / Takeoff Apply procedures defined for Envelope 1.
Page 283 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES LANDING PROCEDURE WITH STRONG HEADWIND CROSSWIND (1/2) If landing must be performed with strong headwind or crosswind, increase approach speed by the greatest of these 2 following values : ( WIND DOWN −...
Page 284: Landing Procedure With Strong Headwind Or Crosswind
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES LANDING PROCEDURE WITH STRONG HEADWIND OR CROSSWIND (2/2) Do not try to stabilize the airplane by pushing down the elevator control just after the touch ; this operation may provide pitch oscillations while increasing the yaw movement to the wind.
Page 285: Utilization On Grass Runway
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON GRASS RUNWAY CAUTION THE SMALL WHEELS OF THE AIRPLANE AND ITS WEIGHT MAY LEAD IT TO SINK IN SOPPY OR LOOSE GROUND Before planing the landing, ensure that the field is hard, smooth and dry enough.
Page 286: Gps Navigation
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES GPS NAVIGATION (1/2) Set up conditions -- Verify if the data base is current. -- Verify that altitude data is valid for the GPS prior to flight. -- In case of B--RNAV use : During the preflight planning phase, the availability of GPS integrity (RAIM) shall be confirmed for the intended flight (route and time).
Page 287 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES GPS NAVIGATION (2/2) Non precision approach with coupled autopilot Coupling with autopilot may be made in “NAV” mode, except in the following cases : -- holding pattern, -- landing pattern turn, -- interrupted approach, which have to be made in “HDG”...
Page 288 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK SECTION 5 PERFORMANCE TABLE OF CONTENTS Page ACOUSTIC LIMITATION 5.1.1 ........5.1A FLYOVER NOISE LEVEL 5.1.2 .
Page 289 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page 5.10 CRUISE PERFORMANCE 5.10.1 ....... . . 5.10.2 Maximum cruise .
Page 290: Acoustic Limitation
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.1 - - ACOUSTIC LIMITATION Maximum noise Demonstrated level permissible noise level ICAO, Annex 16, 80 dB(A) 73.3 dB(A) Chapter 6, Appendix 3 ICAO, Annex 16, 88 dB(A) 80.4 dB(A) Chapter 10, Appendix 6 TBM 700 airplane has received the noise limitation type certificate Nr N181 dated 31st January 1990 replaced by the Type Certificate Data Sheet...
Page 291 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.1A - - FLYOVER NOISE LEVEL Flyover noise level measured in accordance with 14 CFR Part 36 Appendix F : 77.4 dB (A). NOTE : No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into or out of any airport.
Page 292: Airspeed Calibration
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.2 - - AIRSPEED CALIBRATION NOTE : Indicated airspeeds (IAS) : instrument error supposed to be null (power configuration for cruise condition flight). FLAPS UP FLAPS TO FLAPS LDG LDG GR UP LDG GR DN LDG GR DN...
Page 293 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA. Approved FLAPS UP FLAPS TO FLAPS LDG LDG GR UP LDG GR DN LDG GR DN KIAS KCAS KIAS KCAS KIAS KCAS MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS Figure 5.2.2 -- ALTERNATE STATIC SOURCE (BLEED LO)
Page 294: Cabin Pressurization Envelope
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.3 - - CABIN PRESSURIZATION ENVELOPE Cabin altitude (feet) 8850 ft cabin 8000 PRESSURIZATION USEFUL 7000 ENVELOPE 6000 5000 ∆ P= 6.2 PSI max 4000 3000 2000 1000 Flight level (FL) Figure 5.3.1 -- CABIN PRESSURIZATION ENVELOPE Edition 1 -- November 30, 2010 Page 5.3.1...
Page 295 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.4 - - SAT - - OAT CONVERSIONS NOTE : These indicated temperatures are available for stabilized cruise at normal operating power. ISA -- 20°C ISA -- 10°C ISA + 10°C ISA + 20°C Pressure altitude...
Page 296: Stall Speeds
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.5 - - STALL SPEEDS CONFIG. BANK AIR-- FLIGHT 0° 30° 45° 60° PLANE IDLE WEIGHT WEIGHT Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 4850 lbs (2200 kg) 5512 lbs (2500 kg) 6579 lbs...
Page 297: Wind Components
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.6 - - WIND COMPONENTS EXAMPLE : Angle between wind direction and flight path 50 ° Headwind 8 kts Crosswind 10 kts Wind speed 13 kts FLIGHT 25 kt : DEMONSTRATED CROSSWIND PATH 0˚...
Page 298: Engine Operation
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.7 - - ENGINE OPERATION The following tables must be used during normal operation of the airplane. The following conditions are given : -- Np = 2000 RPM, -- BLEED LO. The torque must be set at or below the value corresponding to the local conditions of flight level and temperature.
Page 299 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK ENGINE OPERATION Conditions : Maximum climb power (FL ≤ 200) Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED LO NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed FLIGHT LEVEL (FL) OAT (°C) OAT (°C)
Page 300 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK ENGINE OPERATION Conditions : Maximum climb power (FL 200) ≥ Landing gear and flaps UP IAS = 130 KIAS -- Np = 2000 RPM -- BLEED LO NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed FLIGHT LEVEL (FL) OAT (°C) OAT (°C)
Page 301 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK ENGINE OPERATION Conditions : Maximum cruise power (FL 200) ≤ Landing gear and flaps UP Np = 2000 RPM -- BLEED LO NOTE : Use preferably recommended cruise power FLIGHT LEVEL (FL) OAT (°C) OAT (°C) -- 24...
Page 302 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK ENGINE OPERATION Conditions : Maximum cruise power (FL 200) ≥ Landing gear and flaps UP Np = 2000 RPM -- BLEED LO NOTE : Use preferably recommended cruise power FLIGHT LEVEL (FL) OAT (°C) OAT (°C) -- 64...
Page 303 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK ENGINE OPERATION Conditions : Normal (recommended) cruise power (FL ≤ 200) Landing gear and flaps UP Np = 2000 RPM -- BLEED LO FLIGHT LEVEL (FL) OAT (°C) OAT (°C) -- 24 -- 22 -- 20 TRQ = 100 %...
Page 304 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK ENGINE OPERATION Conditions : Normal (recommended) cruise power (FL 200) ≥ Landing gear and flaps UP Np = 2000 RPM -- BLEED LO FLIGHT LEVEL (FL) OAT (°C) OAT (°C) -- 64 -- 62 -- 60 -- 58...
Page 305: Takeoff Distances
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.8 - - TAKEOFF DISTANCES WEIGHT : 5512 lbs (2500 kg) Associated conditions -- Landing gear DN and flaps TO -- 15° of attitude -- TRQ = 100 % -- Np = 2000 RPM -- BLEED LO -- Hard, dry and level runway -- GR = Ground roll (in ft)
Page 306 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved TAKEOFF DISTANCES WEIGHT : 6579 lbs (2984 kg) Associated conditions -- Landing gear DN and flaps TO -- 15° of attitude -- TRQ = 100 % -- Np = 2000 RPM -- BLEED LO -- Hard, dry and level runway -- GR = Ground roll (in ft) -- D...
Page 307: Climb Performance
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.9 - - CLIMB PERFORMANCE CLIMB SPEEDS (IAS = 130 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 130 KIAS -- BLEED LO RATE OF CLIMB (ft/min) Pressure Pressure Airplane...
Page 308: Climb Speeds (Ias = 160 Kias)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved CLIMB PERFORMANCE CLIMB SPEEDS (IAS = 160 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 160 KIAS -- BLEED LO RATE OF CLIMB (ft/min) Pressure Pressure Airplane...
Page 309: Time, Consumption And Climb Distance (Ias = 130 Kias)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS ) Conditions : ISA - 20°C Maximum climb power Landing gear and flaps UP IAS = 130 KIAS -- 2000 RPM -- BLEED LO NOTE : Time, consumption and distance from the 50 ft WEIGHT...
Page 310 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 130 KIAS -- 2000 RPM -- BLEED LO NOTE : Time, consumption and distance from the 50 ft WEIGHT...
Page 311 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS) Conditions : ISA + 20 ° Maximum climb power Landing gear and flaps UP IAS = 130 KIAS -- 2000 RPM -- BLEED LO NOTE : Time, consumption and distance from the 50 ft WEIGHT...
Page 312: Time, Consumption And Climb Distance (Ias = 160 Kias)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA - 20 ° Maximum climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 4 KIAS / 2000 ft then 2000 RPM -- BLEED LO NOTE : Time, consumption and distance from the 50 ft...
Page 313 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 4 KIAS / 2000 ft then 2000 RPM -- BLEED LO NOTE : Time, consumption and distance from the 50 ft...
Page 314 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA + 20°C Maximum climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; -- 4 KIAS / 2000 ft then 2000 RPM -- BLEED LO NOTE : Time, consumption and distance from the 50 ft...
Page 315: Climb Performance After Go--Around
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE CLIMB PERFORMANCE AFTER GO- -AROUND Conditions : Maximum climb power Landing gear DN and flaps LDG IAS = 90 KIAS RATE OF CLIMB (ft/min) Pressure Pressure Airplane Airplane altitude weight (feet) -- 35°C...
Page 316: Climb Performance -- Flaps To
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CLIMB PERFORMANCE CLIMB PERFORMANCE - - FLAPS TO Conditions : Climb maximum power Landing gear UP and flaps TO IAS = 110 KIAS RATE OF CLIMB (ft/min) Pressure Pressure Airplane Airplane altitude weight (feet)
Page 317: Cruise Performance
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.10 - - CRUISE PERFORMANCE Conditions : ISA Weight 5512 lbs (2500 kg) Flight level (FL) IRCR NOCR MXCR LRCR (KTAS) Figure 5.10.1 -- CRUISE PERFORMANCE Edition 1 -- November 30, 2010 Page 5.10.1 Rev.
Page 318: Maximum Cruise
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA - 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 319 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA - 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 320 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA - 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 321 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure...
Page 322 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 323 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg)
Page 324 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 325: Normal (Recommended) Cruise
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA - 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 326 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA - 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 327 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA - 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 328 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 329 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 330 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 331 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 332: Intermediate Cruise
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA - 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg)
Page 333 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA - 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg)
Page 334 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA - 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg)
Page 335 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg) (2800 kg) (°C)
Page 336 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg)
Page 337 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg)
Page 338 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure altitude (2200 kg) (2500 kg)
Page 339: Long Range Cruise
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Long Range Cruise (5512 lbs - 2500 kg) OAT : ˚C LEGEND : IAS : KIAS Conditions : Landing gear and flaps UP : us gal/h 2000 RPM (*) -- BLEED LO : lbs/h TAS : KTAS Presssure...
Page 340 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Long Range Cruise (6173 lbs - 2800 kg) OAT : ˚C LEGEND : IAS : KIAS Conditions : Landing gear and flaps UP : us gal/h : lbs/h TAS : KTAS 2000 RPM (*) -- BLEED LO Presssure altitude...
Page 341: Time, Consumption And Descent Distance
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.11 - - TIME, CONSUMPTION AND DESCENT DISTANCE Conditions : Power as required to maintain constant Vz Landing gear and flaps UP CAS = 230 KCAS -- 2000 RPM -- BLEED LO Vz = 1500 ft/min Vz = 2000 ft/min Vz = 2500 ft/min...
Page 342: Holding Time
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.12 - - HOLDING TIME Conditions : Landing gear and flaps UP IAS = 120 KIAS -- 2000 RPM -- BLEED LO 30 % FUEL USED DURING HOLDING TIME Weight 4850 lbs (2200 kg) Weight 5512 lbs (2500 kg) Pressure Pressure...
Page 343: Landing Distances
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.13 - - LANDING DISTANCES WEIGHT : 6250 lbs (2835 kg) Associated conditions Landing gear DN and flaps LDG Approach speed 80 KIAS Touch--down speed 65 KIAS Maximum braking without reverse Hard, dry and level runway GR = Ground roll (in ft) = Landing distance (clear to 50 ft) (in ft)
Page 344 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved LANDING DISTANCES WEIGHT : 5071 lbs (2300 kg) Associated conditions Landing gear DN and flaps LDG Approach speed 80 KIAS Touch--down speed 60 KIAS Maximum braking without reverse Hard, dry and level runway GR = Ground roll (in ft) = Landing distance (clear to 50 ft) (in ft) PRESSURE...
Page 345 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK SECTION 6 WEIGHT AND BALANCE TABLE OF CONTENTS Page GENERAL 6.1.1 ..........AIRPLANE WEIGHING PROCEDURES 6.2.1 .
Page 346: General
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.1 - - GENERAL This section contains the procedure for determining the basic empty weight and the balance corresponding to the TBM 700 airplane. Procedures for calculating the weight and the balance for various flight operations are also provided.
Page 347: Airplane Weighing Procedures
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.2 - - AIRPLANE WEIGHING PROCEDURES Refer to Maintenance Manual for the procedures to use. NOTE : Weighing carried out at the factory takes into account all equipment installed on the airplane.
Page 348: Baggage Loading
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.3 - - BAGGAGE LOADING There are two baggage compartments : -- one in fuselage non pressurized forward section, between firewall and cockpit with maximum baggage capacity of 110 lbs (50 kg). -- the other one is in the rear of the pressurized cabin with maximum baggage capacity of 220 lbs (100 kg).
Page 349: Determining Weight And Balance
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.4 - - DETERMINING WEIGHT AND BALANCE GENERAL This paragraph is intended to provide the pilot with a simple and rapid means of determining weight and balance of his airplane. IT IS THE PILOT’S RESPONSIBILITY TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY AND THE WEIGHT AND BALANCE LIMITS ARE ADHERED TO.
Page 350 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Utilization of weight and balance graph : -- Record airplane basic characteristics in -- Compute basic index with the formula described in and record the result in -- Record foreseen loading in and compute total weight of the loaded airplane.
Page 351 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.1 -- LOADING SAMPLE (in Kg and Litres) Edition 1 -- November 30, 2010 Page 6.4.3 Rev. 0...
Page 352 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.1A -- LOADING SAMPLE (in lbs and us gal) Edition 1 -- November 30, 2010 Page 6.4.4 Rev. 0...
Page 353 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.2 -- WEIGHT AND BALANCE GRAPH (in Kg and Litres) Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification Nr MOD 70--019--25 Edition 1 -- November 30, 2010 Page 6.4.5 Rev.
Page 354 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.2A -- WEIGHT AND BALANCE GRAPH (in lbs and us gal) Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification Nr MOD 70--019--25 Edition 1 -- November 30, 2010 Page 6.4.6...
Page 355 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.3 -- WEIGHT AND BALANCE GRAPH (in Kg and Litres) Valid S / N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70--019--25 Edition 1 -- November 30, 2010 Page 6.4.7 Rev.
Page 356 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.3A -- WEIGHT AND BALANCE GRAPH (in lbs and us gal) Valid S / N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70--019--25 Edition 1 -- November 30, 2010 Page 6.4.8...
Page 357: Determining Empty Airplane Characteristics
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK DETERMINING EMPTY AIRPLANE CHARACTERISTICS Empty airplane characteristics (weight and balance) may vary with regard to those indicated on weighing form according to installed optional equipment. List of equipment (paragraph 6.5) contains the standard and optional equipment, as well as their characteristics (weight, arm).
Page 358 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ( do − 172.93 ) CG m.a.c.% = × 100 59.45 Use the above formula to express arm ”d ” in % of mean aerodynamic chord. NOTE : Arm expressed in inches with regard to reference. Front seats : 180.5 in.
Page 359: List Of Equipment
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.5 - - LIST OF EQUIPMENT The following list contains standard equipment installed on each airplane and available optional equipment. A separate list of equipment of items installed at the factory in your specific airplane is provided in your airplane file.
Page 360 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 01 - - SPECIFIC OPTIONAL EQUIPMENT S 01026B Flight ceiling at 31000 ft Edition 1 -- November 30, 2010 Page 6.5.2 Rev.
Page 361 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 21 - - ENVIRONMENTAL SYSTEM 21- -20 - - Distribution Cabin fan AVVC 00244 VETUS...
Page 362 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) Heat exchanger 195980--1 GARRETT 12.599 114.17 (5.715) (2.900) Heat exchanger 195980--3 GARRETT 12.599...
Page 363 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 22 - - AUTO FLIGHT G1000 AFCS GFC 700 GARMIN composed of : .
Page 364 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) EQUIPMENT per unit OR OPTIONAL (A or O) EQUIPMENT SUPPLIER MOD70 (kg) 23 - - COMMUNICATIONS Cockpit loud--speaker (Qty 2) 0.77 181.10 AB 100 SC (0.350)
Page 365 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 23011A Radio headset H10--13.4 DAVID CLARK 23011B Radio headset 7001 PELTOR 23011C...
Page 366 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 24 - - ELECTRICAL POWER 24- -30 - - DC generation Electric power center 11.023 127.95...
Page 367 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 25 - - EQUIPMENT AND FURNISHINGS 25001A Toilets SOCATA 30.055 285.91 (13.633)
Page 368 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 25006F Refreshment cabinet -- Composite SOCATA 18.960 202.76 (8.600) (5.150) 25007A Retractable table...
Page 369 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 25026A Partition net between the cabin and SOCATA 2.756 289.53 the baggage compartment (1.250)
Page 370 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) -- Valid from S/N 68, except S/N 72 to 75, plus airplanes equipped as a retrofit with MOD70--023--25 Belt and harness T700A2510007...
Page 371 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 26 - - FIRE PROTECTION 26001A Portable fire extinguisher unit FH 15 N AREOFEU 4.696...
Page 372 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 27 - - FLIGHT CONTROLS 27- -10 - - Roll control Roll trim actuator 145700.01 LPMI...
Page 373 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 28 - - FUEL SYSTEM 28- -20 - - Fuel supply Electric boost pump 2003--B WELDON...
Page 374 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) Low level probe 722--447 INTER-- 0.110 183.07 TECHNIQUE (0.050) (4.650) Outboard probe 766--977--1...
Page 375 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 30 - - ICE AND RAIN PROTECTION Deicer, L.H. elevator horn SOCATA 3.307 403.15...
Page 376 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) Deicer, outboard L.H. wing SOCATA 2.646 173.23 T700A3010012000 (1.200) (4.400) (with radar MOD70--0276--00C) 30- -40 - - Windshield deicing...
Page 377 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 31 - - INDICATING/RECORDING SYSTEMS 31- -20 - - Independent instruments O 31002A Hourmeter 56457--3...
Page 378 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 32 - - LANDING GEARS 32- -10 - - Main landing gear L.H.
Page 379 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) Cont’d Hydraulic power pack : -- from S/N 1 : 1118--04 (retrofit) 10.362 84.65...
Page 380 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 33 - - LIGHTS 33- -10 - - Instrument panel lighting Instruments emergency lighting WEMAC...
Page 381 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) EQUIPMENT per unit OR OPTIONAL (A or O) EQUIPMENT SUPPLIER MOD70 (kg) 34 - - NAVIGATION 34- -11 - - Air data systems Lift transducer 799--5 0.88...
Page 382 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) EQUIPMENT per unit OR OPTIONAL (A or O) EQUIPMENT SUPPLIER MOD70 (kg) 34- -24 - - ADI and standby horizon Stand--by ADI 1U149--019--19 SIGMATEK 4.19...
Page 383 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) EQUIPMENT per unit OR OPTIONAL (A or O) EQUIPMENT SUPPLIER MOD70 (kg) 34- -41 - - Stormscope 34056C Stormscope, G1000 coupled 4.94 232.28 (2.240)
Page 384 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) EQUIPMENT per unit OR OPTIONAL (A or O) EQUIPMENT SUPPLIER MOD70 (kg) 34- -44 - - Traffic advisory system A 0276--00F G1000 TAWS system A 0258--00C TAS system GTS 820, G1000 22.05 177.00...
Page 385 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT OPT70 REQUIRED (R) OR STANDARD (S) EQUIPMENT per unit OR OPTIONAL (A or O) EQUIPMENT SUPPLIER MOD70 (kg) A 0276--00D Transponder # 1 GTX 33D 4.12 149.65 Mode S diversity (1.87) (3.801)
Page 386 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 35 - - OXYGEN 180.31 (4.580) 0.948 209.84 Generator 117024--02 PURITAN (0.430)
Page 387 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 37 - - VACUUM Air ejector valve 19E17--5A LUCAS 0.661 116.14 (0.300)
Page 388 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 61 - - PROPELLER 61- -10 - - Propeller assembly Propeller HC--E4N.3 / E 9083 S (K) HARTZELL 153.220...
Page 389 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 71 - - POWER PLANT Turbogenerator PT6 A--64 P & W CANADA 471.784 79.72 (214.000)
Page 390 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 77 - - ENGINE INDICATING Compressor turbine QPL (AIRCRAFT 0.981 108.27 tacho--generator (Ng)
Page 391 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK ITEM WEIGHT REQUIRED (R) OR STANDARD (S) OPT70 EQUIPMENT per unit OR OPTIONAL (A or O) SUPPLIER EQUIPMENT MOD70 (kg) 79 - - LUBRICATION 79- -20 - - Distribution Oil cooler L8538233 LORI...
Page 392 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SECTION 7 DESCRIPTION TABLE OF CONTENTS Page GENERAL 7.1.1 ..........AIRFRAME 7.2.1 .
Page 393 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page POWER PLANT 7.6.1 ..........7.6.1 TURBOPROP ENGINE OPERATION .
Page 394 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page AIR CONDITIONING AND PRESSURIZATION 7.9.1 ... . 7.9.1 AIR CONDITIONING ..........7.9.5 PRESSURIZATION .
Page 395: General
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.1 - - GENERAL This Section provides description and operation of the TBM 700 airplane and its systems. Some of the equipment described herein is optional and may not be installed in the airplane. Complete description and operation of the GARMIN G1000 integrated flight deck are detailed in the ”GARMIN”...
Page 396: Airframe
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.2 - - AIRFRAME The TBM 700 is a six / seven--place, low wing airplane. The structure is a semi--monocoque all--metal construction and is equipped with a retractable tricycle landing gear. TBM700A : The pressurized cabin is equipped, on the left side of fuselage, with a two--piece door comprising integrated stairs allowing pilot and passengers...
Page 397 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.1 -- CABIN ARRANGEMENT Edition 1 -- November 30, 2010 Page 7.2.2 Rev. 0...
Page 398: Wings
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK WINGS The wings are monocoque, bi--spar structures. Main spars of each wing are linked to the fuselage by two integral attach fittings. Each wing contains a main landing gear well and sealed casings forming the fuel tank. The wing leading edge is equipped with a deicing system.
Page 399 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Wings characteristics : Area ......... 193.75 sq.
Page 400 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Geared motor 2) Internal actuator 3) Intermediate bearings 4) Wing flap 5) External actuator 6) Rods 7) Control selector Figure 7.2.2 (1/2) -- WING FLAPS Edition 1 -- November 30, 2010 Page 7.2.5 Rev.
Page 401 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.2 (2/2) -- WING FLAPS Edition 1 -- November 30, 2010 Page 7.2.6 Rev. 0...
Page 402: Empennages
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK EMPENNAGES Empennages are composite structures. The horizontal empennage consists of a horizontal stabilizer (PHF), control surfaces and elevator trim tabs ; the vertical empennage consists of a vertical stabilizer, the rudder and the rudder trim tab.
Page 403: Instrument Panel
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.3 - - ACCOMODATIONS INSTRUMENT PANEL The instrument panel contains instruments and controls necessary for flight monitoring. The typical instrument panel consists of all standard equipment, as well as additional optional equipment. Upper panel (Figure 7.3.2) The upper panel located at the top part of the windshield, contains electrical generation control panels, engine starting, ancillary electrical systems,...
Page 404 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK An adjustable air outlet is located on both sides of instrument panel lower part. Reception--micro jacks are located on the arm--rest on both lateral sides of the cockpit, on R.H. side of intermediate R.H. passenger’s seat and on the arm--rest of rear R.H.
Page 405 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK The system uses : -- the stall warning horn, -- the VMO alarm, -- the landing gear control unit, -- the flap geared motor. Aural warning box The aural warning box consists of a box including logic circuits, which create the signals heard in the aural warning loud--speakers.
Page 406 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK The VMO alarm buzzer is electrically supplied by ”ESS BUS 2” bar and protected by ”AURAL WARN” circuit breaker and the emergency lighting rheostat is electrically supplied by ”BATT BUS” bar and protected by ”PANEL EMER”...
Page 407 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.1 -- INSTRUMENT PANEL ASSEMBLY (Typical arrangement) Edition 1 -- November 30, 2010 Page 7.3.5 Rev. 0...
Page 408 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) L. H. instrument panel emergency lighting 2) Buzzer (V alarm) 3) Loud--speaker of GMA # 2 4) R.H. instrument panel emergency lighting 5) Cockpit floodlight switches (rheostats) 6) R.H. air outlet (up to S/N 87) 7) R.H.
Page 409 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.2 (2/2) -- UPPER PANEL AND COCKPIT OVERHEAD PANEL Valid S / N 24, 26, 27, 29 to 32, 34, 36 to 9999 plus airplanes equipped as a retrofit with modification Nr MOD 70- -019- -25 Edition 1 -- November 30, 2010 Page 7.3.7 Rev.
Page 410 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 11) Left station reception--micro 1) L.H. GMA 1347 audio panel jacks 2) General alarm red and amber 12) Electric pitch trim control indicators 13) Maps reading tablet 3) GDU 1040 PFD1 14) Electric rudder trim control 4) Stand--by airspeed indicator 15) ”AP / DISC TRM INT”...
Page 411 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.3 (2/2) -- LEFT INSTRUMENT PANEL (Typical arrangement) Edition 1 -- November 30, 2010 Page 7.3.9 Rev. 0...
Page 412 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Stand--by altimeter 2) Stand--by compass 3) GMC 710 AFCS mode controller 4) Registration 5) Cabin pressurization control panel (Figure 7.9.2) 6) GCU 475 remote controller 7) GDU 1500 MFD Figure 7.3.4 (1/2) -- CENTRAL INSTRUMENT PANEL Edition 1 -- November 30, 2010 Page 7.3.10 Rev.
Page 413 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.4 (2/2) -- CENTRAL INSTRUMENT PANEL (Typical arrangement) Edition 1 -- November 30, 2010 Page 7.3.11 Rev. 0...
Page 414 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) GDU 1040 PFD2 2) R.H. GMA 1347 audio panel 3) Right station control wheel tube 4) Crew music 5) Adjustable air outlet 6) Right station reception--micro jacks 7) Hour meter 8) R.
Page 415 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.5 (2/2) -- RIGHT INSTRUMENT PANEL (Typical arrangement) Edition 1 -- November 30, 2010 Page 7.3.13 Rev. 0...
Page 416 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Propeller governor lever 2) Power lever 3) “PROP O’ SPEED TEST” push--button 4) Flaps control 5) Condition lever 6) Levers friction adjustment 7) Emergency fuel control 8) Manual fuel tank selector (Figure 7.7.2A) 9) Roll trim tab control 10) Pitch trim tab control 11) Lock for access door to landing gear emergency pump (Figure 7.5.2)
Page 417 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.6 (2/2) -- PEDESTAL CONSOLE (Typical arrangement) Edition 1 -- November 30, 2010 Page 7.3.15 Rev. 0...
Page 418 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.7 -- CIRCUIT BREAKERS PANEL Edition 1 -- November 30, 2010 Page 7.3.16 Rev. 0...
Page 419 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.8 -- GENERAL ALARMS WARNING LIGHTS Edition 1 -- November 30, 2010 Page 7.3.17 Rev. 0...
Page 420: Doors, Windows And Emergency Exit
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK DOORS, WINDOWS AND EMERGENCY EXIT Cabin access door (Figure 7.3.9) The cabin two--piece access door (crew and passengers), located on the left side of fuselage aft of the wings, opens outside. Stairs are incorporated in the lower door.
Page 421 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.9 -- CABIN ACCESS DOOR TBM 700A - - Door equipped with one cable Edition 1 -- November 30, 2010 Page 7.3.19 Rev. 0...
Page 422 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK DOORS, WINDOWS AND EMERGENCY EXIT Cabin access door (Figure 7.3.1A) The cabin two--piece access door (crew and passengers), located on the left side of fuselage aft of the wings, opens outside. Stairs are incorporated in the lower door.
Page 423 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.1A -- CABIN ACCESS DOOR TBM 700A - - Door equipped with two cables Edition 1 -- November 30, 2010 Page 7.3.21 Rev. 0...
Page 424 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK DOORS, WINDOWS AND EMERGENCY EXIT Cabin access door (Figure 7.3.1B) The cabin one--piece access door, located on the left side of fuselage aft of the wings, opens outside. The retractable stairs and hand rail make boarding easier.
Page 425 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.1B -- CABIN ACCESS DOOR TBM 700B Edition 1 -- November 30, 2010 Page 7.3.23 Rev. 0...
Page 426 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK CAUTION BEFORE OPENING ACCESS DOOR, MAKE SURE DOOR DEFLECTION AREA IS CLEAR To open door from inside the cabin, unlock the handle by pressing on knob located on its left side, pull the handle toward inside and move it upwards. Open the door by pushing it upwards.
Page 427 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FWD baggage compartment door The FWD baggage compartment door is located on the airplane left side between the firewall and the front pressure bulkhead. It is hinged at the top. It is maintained in the up position by a compensation rod.
Page 428 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.2 -- EMERGENCY EXIT Edition 1 -- November 30, 2010 Page 7.3.26 Rev. 0...
Page 429: Baggage Compartments
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK BAGGAGE COMPARTMENTS There are two baggage compartments : An AFT compartment located in the pressurized cabin between rear passenger seats and rear pressure bulkhead. A FWD compartment (non--pressurized) located between firewall and fwd pressure bulkhead.
Page 430: Seats, Belts And Harnesses
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.3) L.H. and R.H. front seats are mounted on rails attached to the structure. Longitudinal position, height and back--rest tilting of each seat can be adjusted and the arm--rest is hinged.
Page 431 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.3A) L.H. and R.H. front seats are mounted on rails attached to the structure. Longitudinal position, height and back--rest tilting of each seat can be adjusted and the arm--rest is hinged.
Page 432 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.3B) L.H. and R.H. front seats are mounted on rails attached to the structure. Longitudinal position, height and back--rest tilting of each seat can be adjusted and the arm--rest is hinged.
Page 433 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Front passenger’s seat 2) L. H. pilot’s seat 3) R. H. intermediate passenger’s seat (back to flight direction) 4) L. H. intermediate passenger’s seat (back to flight direction) 5) R. H. rear passenger’s seat 6) L.
Page 434 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK (*) Oxygen masks (2) drawer in variant of R.H. rear seat Figure 7.3.3 (2/2) -- SEATS TBM 700A S/N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification No.
Page 435 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Front passenger’s seat 2) L. H. pilot’s seat 3) R. H. intermediate passenger’s seat (back to flight direction) 4) L. H. intermediate passenger’s seat (back to flight direction) 5) R. H. rear passenger’s seat Rear bench 6) L.
Page 436 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK (*) Variant from S / N 68 except S / N 72, 73, 74 and 75 Figure 7.3.3A (2/2) -- SEATS TBM700A S/N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification No.
Page 437 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Front passenger’s seat 2) L. H. pilot’s seat 3) R. H. intermediate passenger’s seat (back to flight direction) 4) L. H. intermediate passenger’s seat (back to flight direction) 5) R. H. rear passenger’s seat Rear bench 6) L.
Page 438 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.3B (2/2) -- SEATS TBM 700B Edition 1 -- November 30, 2010 Page 7.3.37 Rev. 0...
Page 439 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.4 -- FRONT OR REAR SEAT BELT (with movable straps) AND HARNESSES Edition 1 -- November 30, 2010 Page 7.3.38 Rev. 0...
Page 440: Flight Controls
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.4 - - FLIGHT CONTROLS Flight controls consist of roll, pitch and rudder controls, as well as roll trim tab, pitch trim tab and rudder trim tab controls. NOTE : During airplane parking, it is recommended to lock flight controls (see Figure 8.6.2) ROLL (Figure 7.4.1) The roll control is activated by an assembly of rods and cables which links...
Page 441 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pedestal assembly 2) Control wheels 3) Fuselage roll lever 4) Spoiler 5) Aileron 6) Aileron control in wing 7) Spoiler control Figure 7.4.1 (1/2) -- ROLL Edition 1 -- November 30, 2010 Page 7.4.2 Rev.
Page 442 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.1 (2/2) -- ROLL Edition 1 -- November 30, 2010 Page 7.4.3 Rev. 0...
Page 443 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Roll trim tab 2) Aileron 3) Adjustable rods 4) Actuator 5) Trim tab control wiring 6) Trim switch on pedestal console Figure 7.4.2 (1/2) -- LATERAL TRIM Edition 1 -- November 30, 2010 Page 7.4.4 Rev.
Page 444 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.2 (2/2) -- LATERAL TRIM Edition 1 -- November 30, 2010 Page 7.4.5 Rev. 0...
Page 445: Elevator
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ELEVATOR (Figure 7.4.3) Both elevators are activated simultaneously by the same control. Each control surface is hinged at three points to the rear part of horizontal stabilizer. The control wheel controls the two elevators through rods, bearings and bellcranks.
Page 446 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Control wheel assembly 2) Elevators 3) Lever assembly, fuselage rear part 4) Elevator bellcrank 5) Rod with presseal connection 6) Lever assembly under floor 7) Pedestal assembly 8) Actuator Figure 7.4.3 (1/2) -- ELEVATOR Edition 1 -- November 30, 2010 Page 7.4.7 Rev.
Page 447 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Cables 2) Pulleys 3) Pitch trim tabs 4) Actuating rods 5) Actuator 6) Pitch trim manual control wheel 7) Electric pitch trim control Figure 7.4.4 (1/2) -- PITCH TRIM Edition 1 -- November 30, 2010 Page 7.4.8 Rev.
Page 448 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.4 (2/2) -- PITCH TRIM Edition 1 -- November 30, 2010 Page 7.4.9 Rev. 0...
Page 449: Rudder
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK RUDDER (Figure 7.4.5) The rudder is hinged on three fittings attached to the vertical stabilizer rear spar. Cables and a rod comprise the rudder pedals / rudder linkage. Pilot and R.H. station rudder pedal positions are adjustable at each station. The rudder pedal adjustment mechanism (for piloting comfort purposes) includes a manual control located against the external bulkhead beneath the instrument panel and a locking device on the rudder pedals.
Page 450 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Roll / rudder combination bellcrank installation 2) Rudder pedals assembly 3) Control cables 4) Pulleys 5) Rudder lever assembly 6) Rod 7) Rudder 8) Nose gear steering rod Figure 7.4.5 (1/2) -- RUDDER Edition 1 -- November 30, 2010 Page 7.4.11 Rev.
Page 451 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.5 (2/2) -- RUDDER Edition 1 -- November 30, 2010 Page 7.4.12 Rev. 0...
Page 452 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Trim switch on control wheel 2) Actuator 3) Rudder trim tab 4) Rods 5) Rudder trim control wiring Figure 7.4.6 (1/2) -- RUDDER TRIM Edition 1 -- November 30, 2010 Page 7.4.13 Rev.
Page 453 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.6 (2/2) -- RUDDER TRIM Edition 1 -- November 30, 2010 Page 7.4.14 Rev. 0...
Page 454: Landing Gear
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.5 - - LANDING GEAR The TBM 700 is equipped with electro--hydraulically actuated, fully retractable tricycle landing gear. Each landing gear is equipped with one wheel and an oil--air shock absorber integrated in the strut.
Page 455: Hydraulic Pressure
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK HYDRAULIC PRESSURE Hydraulic pressure required for landing gear operation is provided : -- during normal operation, by an electro--hydraulic generator with integrated reservoir, -- during emergency extension operation by a hand pump supplied with an auxiliary reservoir.
Page 456 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Red warning light (LDG GR) 2) Green indicator light (LDG GR) 3) Landing gear control selector 4) Test switch 5) Test knobs Figure 7.5.1 -- CONTROL PANEL AND LANDING GEAR INDICATING Edition 1 -- November 30, 2010 Page 7.5.3 Rev.
Page 457: Safety
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SAFETY Safety switch (landing gear retraction) : A safety switch installed on each main landing gear prevents, by detecting shock strut compression, landing gear accidental retraction when airplane is on ground. Landing gear horn : Landing gear horn is controlled by power lever and / or flaps.
Page 458 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.2 -- EMERGENCY LANDING GEAR EXTENSION CONTROL Edition 1 -- November 30, 2010 Page 7.5.5 Rev. 0...
Page 459: Ground Maneuvers
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK GROUND MANEUVERS Nose gear steering control (Figures 7.5.3 and 7.5.4) Nose gear steering control is combined with rudder pedals and is fitted with a shimmy damper. When one of rudder pedals is fully pushed, nose wheel swivels about 20°.
Page 460 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.3 -- MINIMUM TURN DIAMETER (Full rudder pedals travel without using differential braking) Edition 1 -- November 30, 2010 Page 7.5.7 Rev. 0...
Page 461 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.4 -- MINIMUM TURN DIAMETER (Full rudder pedals travel by using differential braking) Edition 1 -- November 30, 2010 Page 7.5.8 Rev. 0...
Page 462: Brake System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK BRAKE SYSTEM (Figure 7.5.5) Airplane is equipped with a hydraulically actuated disc braking system installed on the main landing gear wheels. Each toe brake at L.H. and R.H. stations is equipped with a master cylinder which sends hydraulic pressure to the corresponding disc brake : L.H.
Page 463 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Reservoir 2) Vent 3) R.H. station master cylinders 4) Parking brake control knob 5) Parking brake valve 6) Drain 7) Pilot’s station master cylinders 8) L.H. brake assembly 9) R.H. brake assembly Figure 7.5.5 (1/2) -- BRAKE SYSTEM Edition 1 -- November 30, 2010 Page 7.5.10...
Page 464 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.5 (2/2) -- BRAKE SYSTEM Edition 1 -- November 30, 2010 Page 7.5.11 Rev. 0...
Page 465 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.6 -- PARKING BRAKE Edition 1 -- November 30, 2010 Page 7.5.12 Rev. 0...
Page 466: Power Plant
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.6 - - POWER PLANT TURBOPROP ENGINE OPERATION (Figure 7.6.1) The PRATT & WHITNEY CANADA turboprop engine (PT6A--64 type) is a free turbine engine developing thermodynamic power of 1580 SHP, derated to 700 SHP.
Page 467 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Propeller governor 2) Exhaust stub 3) Axial compressors 4) Accessory gearbox 5) FCU Fuel control unit 6) Oil to fuel heater 7) Compressor stubshaft 8) Air intake 9) Centrifugal impeller 10) Combustion chamber 11) Compressor turbine 12) Power turbine 1st stage...
Page 468 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.6.1 (2/2) -- POWER PLANT Edition 1 -- November 30, 2010 Page 7.6.3 Rev. 0...
Page 469: Engine Controls (Levers)
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ENGINE CONTROLS (LEVERS) (Figure 7.6.2) Engine operation requires use of four levers located on pedestal console in cabin : -- power lever (Item 2), and its detent for reverse (Item 6) -- propeller governor lever (Item 1), -- condition lever (Item 3), -- ”MAN OVRD”...
Page 470 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Power control lever The power control lever is linked to fuel control unit. It modulates engine power from full reverse to takeoff. Engine running, the power control lever rearward displacement, past the lock using the detent, allows to control : -- the engine power in the Beta range from idle to maximum reverse, -- the Beta valve to select the propeller pitch in reverse.
Page 471: Engine Instruments
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Post--MOD70--0256--76 The fuel condition lever has a ”HI / IDLE” locked position. Change from idle ”HI / IDLE” to ”LO / IDLE” position is only possible after having overridden the idle gate. To override idle gate, raise lever and move it rearwards.
Page 472: Engine Lubrication
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ENGINE LUBRICATION Engine oil is in a tank incorporated into the power plant. 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.
Page 473: Engine Air Inlet
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Starter function Starting system consists of ”STARTER” switch located on ”ENGINE START” panel, starter generator and ignition circuit (Refer to Paragraph ”Ignition function”). Starting procedure is manual. Setting ”STARTER” switch to ”ON” connects the starter generator which drives power plant .
Page 474 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.6.3 -- ENGINE STARTING Edition 1 -- November 30, 2010 Page 7.6.9 Rev. 0...
Page 475: Exhaust System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK EXHAUST SYSTEM Exhaust gases are evacuated through exhaust stubs located on sides of engine cowlings. ENGINE ACCESSORIES All engine driven accessories [except power turbine tacho--generator (Np) and propeller governor] are installed on accessory gearbox located rearwards of engine.
Page 476 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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 is equipped with a test solenoïd which allows performing ground tests by arming limiter under normal overspeed power.
Page 477: Propeller
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK PROPELLER Airplane is equipped with an all--metal, four--bladed, constant--speed and full--feathering propeller. Regulation Propeller governor located on engine maintains rotation speed selected by pilot with propeller governor lever. Regulation is obtained through propeller blade pitch variation : counterweights drive propeller blades toward high pitch (low RPM) whereas oil pressure delivered by governor drives back blades toward low pitch (high RPM).
Page 478: Fuel System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.7 - - FUEL SYSTEM (Figure 7.7.1A) The fuel system comprises fuel tanks, fuel unit, selectors (manual and automatic), electric and mechanical boost pumps, engine fuel system, gaging installation, monitoring installation and drains. FUEL TANKS Fuel tanks are formed by sealed casings in each wing.
Page 479 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Flow divider 15) Fuel unit 2) Flowmeter 16) Filter drain 3) Collector tank 17) Fuel return pipe 4) Fuel regulator 18) Filling port 5) High pressure pump (HP) 19) NACA scoop 6) Oil to fuel heater 20) Tank vent valve 7) Low pressure switch...
Page 480 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.1A (2/2) -- FUEL SYSTEM Edition 1 -- November 30, 2010 Page 7.7.3 Rev. 0...
Page 481: Tank Automatic Selector
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK TANK AUTOMATIC SELECTOR (Figures 7.7.3A and 7.7.4A) Tank automatic selection allows, without pilot’s intervention, feeding the engine from one tank to the other in predetermined sequences. These sequences depend on airplane configuration (ground, in--flight, fuel low level CAS messages appearance).
Page 482: Electric Boost Pump
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Test for system proper operation ”SHIFT” push--knob allows the pilot to test system proper operation anytime. When the system operates, the fuel tank is changed when ”SHIFT” push--knob is pressed once. If airplane is on ground or in flight, low level warning lights not illuminated, the new selected tank remains operating and a new sequence is initiated.
Page 483 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.2A -- MANUAL SELECTOR OF FUEL TANKS Edition 1 -- November 30, 2010 Page 7.7.6 Rev. 0...
Page 484 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.3A -- FUEL CONTROL PANEL Edition 1 -- November 30, 2010 Page 7.7.7 Rev. 0...
Page 485: Main Mechanical Boost Pump
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK MAIN MECHANICAL BOOST PUMP The mechanical boost pump is attached to accessory gearbox and supplies fuel necessary for engine operation. ENGINE FUEL SYSTEM The engine fuel system consists of a fuel regulator, pumps, filters, a fuel divider and fuel nozzles.
Page 486: Fuel System Draining And Clogging Indicator
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FUEL SYSTEM DRAINING AND CLOGGING INDICATOR (Figure 7.7.4A) The fuel system comprises five drain points, a drain on the filter bowl, two drain valves on each tank, located on wing lower surface, on wing root side. These drains allow draining water or sediments contained in fuel.
Page 487 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Clogging indicator 2) Lens 3) Central access door 4) Filter drain 5) Tank drain 6) Drain bowl Figure 7.7.4A -- FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Valid from S/N 1 to 92 Edition 1 -- November 30, 2010 Page 7.7.11 Rev.
Page 488 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FUEL SYSTEM DRAINING AND CLOGGING INDICATOR (Figure 7.7.4A) The fuel system comprises five drain points, a drain on the filter bowl, two drain valves on each tank, located on wing lower surface, one at wing root and the other past main landing gear well.
Page 489 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Lighting switch 2) Mirror door 3) Clogging indicator 4) Central access door 5) Filter drain 6) Tank drain 7) Drain bowl Figure 7.7.4A -- FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Valid from S/N 93 to 9999 Edition 1 -- November 30, 2010...
Page 490: Electrical System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.8 - - ELECTRICAL SYSTEM (Figures 7.8.1 and 7.8.4) The airplane is fitted with a direct--current electrical system rated to 28 volts with negative pole at ground. Airplane mains supply is obtained from various power supplies : -- an engine driven starter generator -- a stand--by generator driven by the engine through a belt -- a battery located in engine compartment...
Page 491: Stand--By Generator
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK STAND- -BY GENERATOR Stand--by generator supplies a 28--volt stand--by direct current which may be used in case of main generator failure. Generator connection with main bus bar is controlled through ”GENERATOR” selector set to ”ST--BY”, it will be effective when connection conditions are met.
Page 492: Distribution
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK DISTRIBUTION Airplane electrical systems are connected to ”BUS” bars and protected by “pull--off” type circuit breakers located on R.H. side panel (See Figure 7.8.3). In case of overload of a system, the circuit breaker triggers and switches the system off.
Page 493 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.1 -- ELECTRICAL DIAGRAM Edition 1 -- November 30, 2010 Page 7.8.4 Rev. 0...
Page 494 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (1/3) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- November 30, 2010 Page 7.8.5 Rev. 0...
Page 495 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (2/3) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- November 30, 2010 Page 7.8.6 Rev. 0...
Page 496 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (3/3) -- ELECTRICAL DISTRIBUTION OF BUS BARS Edition 1 -- November 30, 2010 Page 7.8.7 Rev. 0...
Page 497 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ESS BUS TIE Essential bus NORM & EMER switch BUS 1 AP SERVOS Autopilot servo protection FLAPS Flaps protection AIL TRIM Aileron trim protection Pitch trim protection RUD TRIM BUS 2 LDG GEAR Landing gear general supply protection ESS BUS 1...
Page 498 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK BUS 1 (Continued) Inertial separator protection INERT DE ICE R WS DE ICE R.H. windshield deicing protection (if installed) PITOT 1 Pitot 1 heating protection AUDIO 2 Audio control panel 2 protection STROBE Strobe lights protection CAB TEMP...
Page 499 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK NOTE : If an additional equipment is installed, its circuit breaker is installed on a free location. Figure 7.8.3 (3/3) -- CIRCUIT BREAKER PANEL (typical arrangement) Edition 1 -- November 30, 2010 Page 7.8.10 Rev.
Page 500: Indicating
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INDICATING Electrical system indicating consists of voltage and ampere indicating -- refer to GARMIN G1000 Cockpit Reference Guide for further details. Following CAS messages may appear on the MFD CAS display : ”BAT OFF”...
Page 501 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”MAIN” reset knob 2) ”ST--BY” reset knob 3) Crash lever 4) ”SOURCE” selector 5) ”GENERATOR” selector Figure 7.8.4 -- ELECTRICAL CONTROL Edition 1 -- November 30, 2010 Page 7.8.12 Rev. 0...
Page 502: Exterior Lighting
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK EXTERIOR LIGHTING (Figure 7.8.5) The airplane is equipped with two navigation lights, two strobe lights, two landing lights, a taxi light, a wing leading edge icing inspection light. A ”LTS TEST” test--knob located above lights switches allows checking proper operation of warning lights ;...
Page 503 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Leading edge icing inspection light The leading edge icing inspection light is installed on fuselage L.H. side, its beam illuminates the wing leading edge. It is controlled by the ”ICE LIGHT” switch installed on ”DE--ICE SYSTEM”...
Page 504 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) L.H. landing light switch 2) Test knob (test light integrated to switches) 3) Taxi light switch 4) R.H. landing light switch 5) Navigation lights switch 6) Strobe lights switch Figure 7.8.5 (1/2) -- EXTERNAL LIGHTING CONTROLS Edition 1 -- November 30, 2010 Page 7.8.15 Rev.
Page 505 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.5 (2/2) -- EXTERNAL LIGHTING CONTROLS Edition 1 -- November 30, 2010 Page 7.8.16 Rev. 0...
Page 506: Interior Lighting
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTERIOR LIGHTING (Figure 7.8.6) Interior lighting consists of access, cabin, instrument panel, instruments, baggage compartments and emergency lighting. Access lighting Access lighting consists of two floodlights located on the ceiling upholstering (one at the level of the access door, the other at the level of the storage cabinet) and the L.H.
Page 507 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Map reading light illumination The illumination of the map reading light located on L.H. station control wheel is controlled by the switch (rheostat) located on this light. Valid S/N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70- -019- -25 Edition 1 -- November 30, 2010...
Page 508 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Instrument panel lighting switch (rheostat) 2) Instrument lighting switch (rheostat) 3) ”DIMMER” switch 4) Cabin lighting switch (rear seats reading light) 5) Access door, baggage compartment and FWD dome light (delayed breaker) push--button 6) Emergency lighting switch Figure 7.8.6 (1/2) -- INTERNAL LIGHTING CONTROLS...
Page 509 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.6 (2/2) -- INTERNAL LIGHTING CONTROLS Valid S/N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70- -019- -25 Edition 1 -- November 30, 2010 Page 7.8.20 Rev.
Page 510: Air Conditioning And Pressurization
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.9 - - AIR CONDITIONING AND PRESSURIZATION AIR CONDITIONING (Figure 7.9.1) Air conditioning system includes a flow--pressure regulation system, temperature regulation and cooling system, control and check systems and distribution. Air necessary for conditioning is picked up from the engine. A two--setting level valve regulates pressure and bleed hot air flow and may be also used as shutoff valve.
Page 511 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Overheat switch 2) Cooling turbine 3) Hot air -- cold air mixer 4) Water separator 5) Temperature control valve 6) Pressure regulator of temperature control valve 7) Check--valve 8) Temperature control sensor 9) Cabin emergency air inlet 10) Defogging outlets 11) Adjustable air outlets...
Page 512 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.1 (2/2) -- AIR CONDITIONING Valid S/N 24, 26, 27, 29 to 32, 34, 36 to 85, 87, 90 + S/N 1 to 23, 25, 28, 33 and 35 with modification No. MOD70- -019- -25 Edition 1 -- November 30, 2010 Page 7.9.3 Rev.
Page 513 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Control and check (Figure 7.9.3) Air conditioning system controls are located on ”ECS” panel, CAS messages are grouped on MFD unit. Conditioning occurs when ”BLEED VALVE” switch is set to ”ON” ; this leads to opening of pressure regulation valve and leads to ”BLEED OFF”...
Page 514 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.9 - - AIR CONDITIONING AND PRESSURIZATION AIR CONDITIONING (Figure 7.9.1A) Air conditioning system includes a flow--pressure regulation system, temperature regulation and cooling system, control and check systems and distribution. Air necessary for conditioning is picked up from the engine. A two--setting level valve regulates pressure and bleed hot air flow and may be also used as shutoff valve.
Page 515 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Overheat switch 2) Cooling turbine 3) Hot air -- cold air mixer 4) Water separator 5) Temperature control valve 6) Pressure regulator of temperature control valve 7) Check--valve 8) Temperature control sensor 9) Cabin emergency air inlet 10) Defogging outlets 11) Adjustable air outlets...
Page 516 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.1A (2/2) -- AIR CONDITIONING Valid S/N 86, 88, 89, 91 to 9999 Edition 1 -- November 30, 2010 Page 7.9.4C Rev. 0...
Page 517 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Control and check (Figure 7.9.3) Air conditioning system controls are located on ”ECS” panel, CAS messages are grouped on MFD unit. Conditioning occurs when ”BLEED VALVE” switch is set to ”ON” ; this leads to opening of pressure regulation valve and leads to ”BLEED OFF”...
Page 518: Pressurization
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK PRESSURIZATION (Figures 7.9.2 and 7.9.3) Pressurization system maintains the pressure corresponding to an altitude compatible with passengers’ safety and comfort inside the cabin. The system uses the air conditioning system to pressurize the cabin and the vacuum generation system for check and safety.
Page 519 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Check valve 2) Cabin--atmosphere ∆P microswitch 3) G1000 system (CAS messages) 4) Outflow valve 5) Safety valve 6) Depressurization valve 7) Landing gear switch (airplane on ground) 8) Pressure controller 9) Cabin altitude warn switch 10) Compensation tank Figure 7.9.2 (1/2) -- PRESSURIZATION...
Page 520 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.2 (2/2) -- PRESSURIZATION Edition 1 -- November 30, 2010 Page 7.9.7 Rev. 0...
Page 521 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”BLEED VALVE” switch -- ON/OFF 2) ”BLEED VALVE” switch -- HI/LO 3) ”CABIN FAN” switch 4) ”DUMP” switch 5) ”CABIN TEMP” selector 6) ”DEFOG / NORMAL” distributor 7) Cabin altitude selector Figure 7.9.3 (1/2) -- ”ECS”...
Page 522 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.3 (2/2) -- ”ECS” CONTROL AND CHECK PANEL Edition 1 -- November 30, 2010 Page 7.9.9 Rev. 0...
Page 523: Emergency Oxygen System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.10 - - EMERGENCY OXYGEN SYSTEM (Figure 7.10.1) Emergency oxygen system must be used following a pressurization system failure at an altitude between 12000 and 30000 ft. The three emergency oxygen systems provide enough chemical oxygen for six persons during a descent from 30000 to 12000 ft and below.
Page 524 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Generator 2) Supply tubes 3) Masks 4) Drawer 5) Microswitch 6) Dimpled support 7) Microphone switch Figure 7.10.1 (1/2) -- EMERGENCY OXYGEN SYSTEM Edition 1 -- November 30, 2010 Page 7.10.2 Rev.
Page 525: Indicating
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INDICATING When the ”SOURCE” selector is set to ”BAT” or ”GPU”, as soon as an oxygen generator is activated, the ”OXYGEN” warning CAS message is displayed. The warning CAS message remains displayed as long as used generator is not replaced.
Page 526 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.10.1 (2/2) -- EMERGENCY OXYGEN SYSTEM Edition 1 -- November 30, 2010 Page 7.10.4 Rev. 0...
Page 527: Air Data System And Instruments
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.11 - - AIR DATA SYSTEM AND INSTRUMENTS (Figure 7.11.1) Airplane air data system consists of : -- two separate static pressure systems supplying an altimeter, an airspeed indicator and air data computers (ADC). A part of system 1 is backed up by an alternate system which operation is controlled by a switching valve (normal / alternate) attached to instrument panel under R.H.
Page 528 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pitot 1 2) Dynamic system drain 3) Airspeed indicator 4) GDC 74B ADC 5) GDC 74B ADC 6) FWD pressure bulkhead 7) Static system drain 8) Static system drain 9) Static system drain 10) Emergency static system drain 11) Emergency static valve (Normal / Alternate) 12) Altimeter...
Page 529 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.11.1 (2/2) -- AIR DATA SYSTEM Edition 1 -- November 30, 2010 Page 7.11.3 Rev. 0...
Page 530: Dynamic Pressure System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Alternate static source The alternate static port located in the rear fuselage supplies a system routed to the switching valve (normal / alternate) in order to replace static system 1. The alternate line incorporates a drain plug located under the instrument panel on R.H.
Page 531: Vacuum System And Instruments
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.12 - - VACUUM SYSTEM AND INSTRUMENTS (Figure 7.12.1) The airplane is fitted with a vacuum system providing the suction necessary to operate the attitude indicator, the cabin pressurization and the leading edge deicing.
Page 532 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pressure regulator 2) Ejector 3) Valve 4) Regulating and relief valve 5) Pressure switch 6) Failure CAS message Figure 7.12.1 (1/2) -- VACUUM SYSTEM Edition 1 -- November 30, 2010 Page 7.12.2 Rev.
Page 533 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.12.1 (2/2) -- VACUUM SYSTEM Edition 1 -- November 30, 2010 Page 7.12.3 Rev. 0...
Page 534: Suction Gage
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SUCTION GAGE The suction gage is calibrated in inches of mercury and indicates the suction available for operation of the attitude indicator. The desired vacuum range is 4.4 to 5.2 in.Hg. A vacuum reading out of this range may indicate a system malfunction or improper adjustment.
Page 535: Ice Protection Equipment
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.13 - - ICE PROTECTION EQUIPMENT (Figure 7.13.1) Ice protection equipment is as follows : -- Pneumatic deice system for inboard, central and outboard wing and for stabilizers : ”AIRFRAME DE--ICE” -- Propeller electrical deice system : ”PROP DE--ICE”...
Page 536: Propeller Deicing
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK PROPELLER DEICING Propeller deicing is accomplished through electrical heating of blade roots. This system operates cyclically and alternately on two opposite blades at the same time. Each cycle is 180 seconds long. The system operation is correct when green warning light located above ”PROP DE ICE”...
Page 537: Heating Of Pitots And Stall Warning Sensor
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK HEATING OF PITOTS AND STALL WARNING SENSOR (”PITOT 1 HTR” AND ”PITOT 2 & STALL HTR”) The two pitots, which supply ADC(s), the airspeed indicator and the stall warning sensor are electrically heated. This deice equipment must be used even during flight into non--icing conditions.
Page 538 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.13.1 -- DEICING CONTROL AND CHECK PANEL Edition 1 -- November 30, 2010 Page 7.13.4 Rev. 0...
Page 539: Avionics Master
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.14 - - AVIONICS MASTER (Figure 7.14.1) The electrical supply of avionic equipment assembly is controlled by the ”AVIONICS MASTER” switch located on the upper panel. When the “AVIONICS MASTER” switch is set to START, it allows to electrically supply, from the “BATT BUS“...
Page 540 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”AVIONICS MASTER” switch Figure 7.14.1 -- “AVIONICS MASTER” Edition 1 -- November 30, 2010 Page 7.14.2 Rev. 0...
Page 541: Miscellaneous Equipment
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.15 - - MISCELLANEOUS EQUIPMENT STALL WARNING SYSTEM The airplane is equipped with an electrically deiced stall sensor in the leading edge of the right wing. This sensor fitted with a vane is electrically connected to an audible warning.
Page 542: Cabin Fire Extinguisher
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK CABIN FIRE EXTINGUISHER (if installed) The fire extinguisher is located on the pilot’s seat L.H. side. It is attached on the floor by means of a quick--disconnect support. A pressure gage allows checking the fire extinguisher condition.
Page 543 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Reset after an inadvertent activation On ”ON/ARMED/RESET--TEST” remote control switch, press on “RESET--TEST” or set locator transmitter switch to “OFF”, then to “ARM”. Edition 1 -- November 30, 2010 Page 7.15.3 Rev.
Page 544 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE SECTION 8 HANDLING, SERVICING AND MAINTENANCE TABLE OF CONTENTS Page GENERAL 8.1.1 ........... . IDENTIFICATION PLATE 8.2.1 .
Page 545 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE TABLE OF CONTENTS (Continued) Page AIRPLANE CLEANING AND CARE 8.8.1 ......8.8.1 WINDSHIELD AND WINDOWS .
Page 546: General
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.1 - - GENERAL This section contains the procedures recommended by the manufacturer for the proper ground handling and routine care and servicing of TBM 700 airplane. Also included in this section are the inspection and maintenance requirements which must be followed if your airplane is to retain its performance and dependability.
Page 547: Identification Plate
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.2 - - IDENTIFICATION PLATE Any correspondence regarding your airplane should include its serial number. This number together with the model number, type certificate number and production certificate number are stamped on the identification plate attached to the left side of the fuselage beneath the horizontal stabilizer.
Page 548: Publications
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.3 - - PUBLICATIONS When the airplane is delivered from the factory, it is supplied with a Pilot’s Operating Handbook, the “GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for SOCATA TBM 700”, P/N 190--01247--00, or any later version as applicable, and supplemental data covering optional equipment installed in the airplane (refer to Section 9 “Supplements”...
Page 549: Inspection Periods
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.4 - - INSPECTION PERIODS Refer to regulations in force in the certification country for information concerning preventive maintenance to be carried out. A maintenance Manual must be obtained prior to performing any preventive maintenance to make sure that proper procedures are followed.
Page 550: Alterations Or Repairs
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.5 - - ALTERATIONS OR REPAIRS It is essential that the Airworthiness authorities be contacted prior to any alterations or repairs on the airplane to make sure that airworthiness of the airplane is not violated.
Page 551: Ground Handling
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.6 - - GROUND HANDLING CAUTION ONLY MOVE OR TOW THE AIRPLANE WITH SOMEONE IN THE COCKPIT TOWING CAUTION USING THE PROPELLER FOR GROUND HANDLING COULD RESULT IN SERIOUS DAMAGE, ESPECIALLY IF PRESSURE OR PULL IS EXERTED ON BLADE TIPS The airplane should be moved on the ground with a towing bar and a suitable vehicle in order not to damage the nose gear steering mechanism.
Page 552 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.6.1 -- TURNING ANGLE LIMITS Edition 1 -- November 30, 2010 Page 8.6.2 Rev. 0...
Page 553: Tie--Down
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE NOTE : Do not use solar screens or shields installed on the aircraft inside, or leave sun visors down against windshield when aircraft on ground. The reflected heat from these items causes a temperature increase which accelerates the crack growth or crazing and may cause the formation of bubbles in the inner layer of multilayer windshields.
Page 554 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.6.2 -- CONTROL LOCK DEVICE Edition 1 -- November 30, 2010 Page 8.6.4 Rev. 0...
Page 555: Flyable Storage
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE FLYABLE STORAGE Airplanes placed in storage for a maximum of 28 days are considered in flyable storage. Storage from 0 to 7 days : -- Engine : according to Maintenance Manual P & W -- C Airplane fueling : -- Keep fuel tanks full to minimize condensation in the tanks.
Page 556: Servicing
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.7 - - SERVICING MAINTENANCE In addition to the preflight inspection (refer to Section 4, ”Normal Procedures”), servicing, inspection and test requirements for the airplane are detailed in the Maintenance Manual. Maintenance Manual outlines all items which require attention at 100, 300 and 600 hour intervals (for airframe), 100 and 300 hour intervals (for GTP) plus those items which require servicing, inspection or testing at special...
Page 557: Fuel
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Refill sump through the system filling inlet which is located on the engine upper rear part. A gage located on the filling cap indicates oil level and is calibrated in quarts to maximum level under cold conditions ”MAX COLD”...
Page 558 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE CAUTION DURING FUELING OPERATIONS, TAKE CARE NOT TO DAMAGE PNEUMATIC DEICER BOOTS LOCATED ON WING LEADING EDGE. THE USE OF AVIATION GASOLINE (AVGAS) MUST BE RESTRICTED TO EMERGENCIES ONLY. AVGAS WILL NOT BE USED FOR MORE THAN 150 CUMULATIVE HOURS DURING ANY PERIOD BETWEEN ENGINE OVERHAUL WARNING...
Page 559 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Fuel additives Fuel used must contain an anti--ice additive conforming to MIL--I--27686 or MIL--I--85470 specification. Strict adherence to recommended preflight draining instructions as called for in Section 4 will eliminate any free water accumulations from the tank sumps. While small amounts of water may still remain emulsified in the gasoline, it will normally be consumed and go unnoticed in the operation of the engine.
Page 560 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE CAUTION DO NOT PERMIT THE CONCENTRATE OF EGME OR DIEGME TO COME IN CONTACT WITH THE AIRPLANE FINISH OR FUEL TANK MIXING OF THE EGME OR DIEGME WITH THE FUEL IS EXTREMELY IMPORTANT.
Page 561 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.7.3 -- ADDITIVE MIXING RATIO (EGME or DIEGME) Edition 1 -- November 30, 2010 Page 8.7.6 Rev. 0...
Page 562: Landing Gear
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE LANDING GEAR Nose gear tire : 5.00--5 6 PR -- Inflating pressure : 94 psi (6.5 bar) Main gear tires : 18 5.5 8 PR -- Inflating pressure : 120 psi (8.25 bar) Nose gear shock absorber : Fill with hydraulic fluid AIR 3520 B (MIL.H5606E) ;...
Page 563: Oxygen
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE OXYGEN Indicating When the ”SOURCE” selector is set to ”BAT” or ”GPU”, as soon as an oxygen generator is activated, the ”OXYGEN” warning CAS message is displayed. The warning CAS message remains displayed as long as used generator is not replaced.
Page 564: Airplane Cleaning And Care
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.8 - - AIRPLANE CLEANING AND CARE WINDSHIELD AND WINDOWS The windshield and windows should be cleaned with an airplane windshield cleaner. NOTE : Refer to the Maintenance Manual for products and procedures to apply. Apply the cleaner sparingly with soft cloths and rub with moderate pressure until all dirt, oil scum and bug stains are removed.
Page 565: Painted Surfaces
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE PAINTED SURFACES Refer to Maintenance Manual for the products and procedures to apply. PROPELLER CARE Preflight inspection of propeller blades for nicks and cleaning them occasionally with a cloth soaked with soapy water to clean off grass and bug stains will assure long blade life.
Page 566: Utilization By Cold Weather (-- 0°C To -- 25°C) Or Very Cold Weather (-- 25°C To -- 40°C)
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.9 - - UTILIZATION BY COLD WEATHER (- - 0°C TO - - 25°C) OR VERY COLD WEATHER (- - 25°C TO - - 40°C) If a landing is foreseen by cold or very cold weather or in case of airplane prolonged operation in such conditions, it is recommended to prepare the airplane as follows : 1 -- Smear with silicone grease the seals of the door and engine...
Page 567 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK SECTION 9 SUPPLEMENTS This section consists of a series of supplements, each covering a single system which may be installed in the TBM airplanes equipped with MOD70--0276--00. Each supplement contains a brief description, and when applicable, operating limitations, emergency and normal procedures, and performance.
Page 568 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF EFFECTIVE PAGES AND VALIDITIES ORIGINAL ISSUE OF NOVEMBER 30, 2010 S / N 1 to S / N 433, except S / N 269 equipped with MOD70- -276- -00 P/N Z00.DMAFM0AEE2R0EN Page Edit.
Page 569 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF NORMAL AMENDMENTS Edition 2 of November 30, 2010 Revision ... of ..Pages Description Edition 2 -- November 30, 2010 Page 9.AC Rev. 0...
Page 570 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF SUPPLEMENTS AND VALIDITIES Supp. Edition Date A -- General S / N 1 to S / N 433, except S / N 269 equipped with MOD70--0276--00 30.11.10 ....... . 6 -- ”BFG”...
Page 571 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 44 -- Chip detection system From S / N 1 equipped with MOD70--276--00 30.11.10 ........47 -- ”AIRBORNE”...
Page 572 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SUPPLEMENT ”BFG” WX- -500 STORMSCOPE TABLE OF CONTENTS Page -- GENERAL ........9.6.2 -- LIMITATIONS .
Page 573: General
T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 1 GENERAL This supplement supplies information to the pilot about limitations, normal and emergency procedures when the optional ”BFG” WX--500 stormscope is installed on the TBM airplane. The stormscope must be used within limits of this supplement.
Page 574: Emergency Procedures
T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 3 EMERGENCY PROCEDURES Installation and operation of ”BFG” stormscope do not change the basic emergency procedures of the airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook. SECTION 4 NORMAL PROCEDURES Normal operating procedures of the ”BFG”...
Page 575: Weight And Balance
T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 6 WEIGHT AND BALANCE Informations hereafter supplement the ones given for the standard airplane in Section 6 ”Weight and balance” of the basic Pilot’s Operating Handbook. WEIGHT per unit EQUIPMENT OPTIONAL EQUIPMENT SUPPLIER (kg) 34 - - NAVIGATION...
Page 576 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM SUPPLEMENT ”KEITH” VAPOR CYCLE COOLING SYSTEM TABLE OF CONTENTS Page -- GENERAL 9.15.2 ..........-- LIMITATIONS 9.15.2 .
Page 577 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM SECTION 1 GENERAL This supplement provides information necessary for airplane utilization when the ”KEITH” vapor cycle cooling system is installed on TBM 700 airplane equipped with MOD70--0276--00. SECTION 2 LIMITATIONS These limitations supplement those of standard airplane described in Section 2 ”Limitations”...
Page 578 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM SECTION 4 NORMAL PROCEDURES The operation of the ”KEITH” vapor cycle cooling system is started thanks to the ”AIR COND” control switch integrated to the ”ECS” panel. The operation instructions are described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook.
Page 579 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM SECTION 7 DESCRIPTION The ”KEITH” vapor cycle cooling system improves the passengers and crew comfort in warm and / or humid atmospheric conditions. The refrigerant used is called R134A. The installation (Figure 9.15.1) comprises : -- A compressor/condenser assembly located in the fuselage rear section between frames C 17 and C 18 and consisting of : .
Page 580 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM -- An evaporator fan that also provides the air circulation in the cabin as the standard ventilation system. TBM700A It is installed at the same location as for the ventilation system between frames C 13 and C 14 on R.H.
Page 581 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM A second switch ”FAN FLOW” controls the cabin air HI or LO flow in either FAN ONLY or ON operating positions. A green light located next to the switches illuminates to indicate the operation of the compressor/condenser fan motor.
Page 582 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM 1) Overhead distribution duct 2) Thermal expansion valve 3) HP service valve 4) Sight glass 5) Binary pressure switch 6) Receiver drier 7) Condenser air outlet 8) Condenser heat exchanger 9) Compressor/condenser fan motor 10) Compressor/condenser assembly 11) Condenser air inlet...
Page 583 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM Figure 9.15.1 (2/2) -- Schematic diagram Edition 1 -- November 30, 2010 Page 9.15.9...
Page 584 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM 1) Green light 2) Operation switch 3) Light test 4) Fan speed selector Figure 9.15.2 (1/2) -- ”ECS” panel Edition 1 -- November 30, 2010 Page 9.15.10...
Page 585 T B M SUPPLEMENT 15 “KEITH” VAPOR CYCLE COOLING SYSTEM Figure 9.15.2 (2/2) -- ”ECS” panel Edition 1 -- November 30, 2010 Page 9.15.11...
Page 586 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SUPPLEMENT ENGINE FIRE DETECTION SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.18.2 -- LIMITATIONS .
Page 587 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to operation when the TBM airplane is equipped with the option ”ENGINE FIRE DETECTION SYSTEM”. The generalities hereafter supplement those of the standard airplane described in Section 1 ”General”...
Page 588 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook when the TBM airplane is equipped with the option ”ENGINE FIRE DETECTION SYSTEM”.
Page 589 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM ENGINE FIRE IN FLIGHT ”FIRE” ”FIRE” Indications : red warning ON or CAS message Try to confirm the fire warning by looking for other indications such as ITT ”ITT” ”ITT” increase, red warning ON or CAS message, smoke from engine cowls or air conditioning system.
Page 590 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook when the TBM airplane is equipped with the option ”ENGINE FIRE DETECTION SYSTEM”.
Page 591 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in Section 6 ”Weight and balance” of the basic Pilot’s Operating Handbook. WEIGHT per unit EQUIPMENT OPTIONAL EQUIPMENT SUPPLIER (kg)
Page 592 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM SECTION 7 DESCRIPTION Pre- -MOD70- -0176- -00 or Pre- -MOD70- -276- -00 ”G1000 Integrated Flight Deck” The engine fire detection system enables the monitoring and indication of a fire in the engine area. The system includes : -- 7 detectors -- the control relay...
Page 593 T B M SUPPLEMENT 18 ENGINE FIRE DETECTION SYSTEM Post- -MOD70- -0176- -00 or Post- -MOD70- -0276- -00 “G1000 Integrated Flight Deck” The engine fire detection system enables the monitoring and indication of a fire in the engine area. The system includes : -- 7 detectors -- the test push--button -- the G1000 system.
Page 594 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) SUPPLEMENT ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) TABLE OF CONTENTS Page ............. -- GENERAL 9.29.2 ............-- LIMITATIONS 9.29.3 ........-- EMERGENCY PROCEDURES 9.29.4 ........-- NORMAL PROCEDURES 9.29.6 ............
Page 595: General
T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT)”...
Page 596: Limitations
T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) SECTION 2 LIMITATIONS The limitations hereafter supplement those of the standard airplane described in Section 2 ”Limitations” of the basic Pilot’s Operating Handbook, when airplane equipped with option ””EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT)” and with MOD70--0276--00.
Page 597: Emergency Procedures
T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) SECTION 3 EMERGENCY PROCEDURES These emergency procedures supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE”...
Page 598 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) OXYGEN USE (Cont’d) 3 -- In case of smokes : 3--position selector EMERGENCY Don the smoke goggles onto the face 4 -- ”PASSENGERS OXYGEN” switch 5 -- Check the oxygen flow indicator for the front seats (the blinker is transparent) and for the rear passengers (the blinker is green).
Page 599: Normal Procedures
T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE”...
Page 600 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) IN--FLIGHT AVAILABLE OXYGEN QUANTITY (Cont’d) 1 -- Determine the usable oxygen percent using the chart Figure 9.29.1. Figure 9.29.1 2 -- Determine the oxygen duration in minutes by multiplying the values read on table Figure 9.29.2 by the percent obtained with the chart Figure 9.29.1.
Page 601: Performance
T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) AFTER LANDING ”OXYGEN” switch SECTION 5 PERFORMANCE The installation of the gaseous oxygen system does not change the basic performance of the airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook.
Page 602: Description
T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) SECTION 7 DESCRIPTION The TBM 700 airplane is equipped with an optional gaseous oxygen system, which will be used by the crew and the passengers, when the cabin altitude is greater than 10000 ft following a loss of pressurization or in case of cabin air contamination.
Page 603 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) An indicating and control panel located in the cockpit overhead panel at the disposal of the pilot includes : -- a graduated pressure gage to permit checking the cylinder charge, -- a two--position valve ON/OFF (”OXYGEN”...
Page 604 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) FLIGHT ABOVE 15000 FT WITH EMERGENCY DESCENT Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C 1056 1009 1175 1123...
Page 605 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) WHEN REQUIRED TO REMAIN ABOVE 15000 FT DUE TO MINIMUM ”EN ROUTE” ALTITUDE Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C...
Page 606 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) FLIGHT BETWEEN 15000 FT AND 10000 FT Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C 1228 1172 1125 1073...
Page 607 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) SECTION 8 HANDLING, SERVICING AND MAINTENANCE The operations hereafter supplement those of the standard airplane described in Section 8 ”Handling, servicing and maintenance” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE”...
Page 608 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) REPLENISHMENT PROCEDURE WARNING MAKE SURE THAT THE AIRPLANE IS FITTED WITH A GROUDING CABLE AND IS PROPERLY GROUNDED. THE OXYGEN CART MUST BE ELECTRICALLY BONDED TO THE AIRPLANE. DO NOT OPERATE THE AIRPLANE ELECTRICAL SWITCHES OR CONNECT/DISCONNECT GROUND POWER DURING OXYGEN SYSTEM REPLENISHMENT.
Page 609 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) If the pressure on the oxygen cylinder gage is lower, fill the oxygen cylinder. Make sure the area around the oxygen cylinder charging valve is clean. Remove the cap from the charging valve. Make sure the oxygen supply hose is clean and connect it to the charging valve.
Page 610 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) WARNING MASKS SHALL BE REPACKED IN AN AREA FREE OF OIL, GREASE, FLAMMABLE SOLVENTS OR OTHER CONTAMINANTS Inspect and disinfect mask and deployment container with an aqueous solution of Zephiran Chloride (”Scott Aviation” P/N 00--2572) or with disinfection cleaners (”EROS”...
Page 611 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) Gently fold reservoir bag lengthwise into thirds (outside edges folded inward over center of bag). Do not crease bag. Fold reservoir bag away from breathing valves and into facepiece. Make sure bag does not cover breathing valves.
Page 612 T B M SUPPLEMENT 29 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (30000 FT) Coil oxygen tubing inside facepiece over reservoir bag. Connect oxygen tubing to manifold oxygen fitting. WARNING MAKE SURE LANYARD PIN IS INSERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED. CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyard pin into corresponding check valve.
Page 613 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) SUPPLEMENT ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) TABLE OF CONTENTS Page -- GENERAL ........9.37.2 -- LIMITATIONS .
Page 614 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT)”...
Page 615: Limitations
T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) SECTION 2 LIMITATIONS The limitations hereafter supplement those of the standard airplane described in Section 2 ”Limitations” of the basic Pilot’s Operating Handbook, when airplane equipped with option ””EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT)” and with MOD70--0276--00.
Page 616: Emergency Procedures
T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) SECTION 3 EMERGENCY PROCEDURES These emergency procedures supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE”...
Page 617 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) OXYGEN USE (Cont’d) 3 -- In case of smokes : 3--position selector EMERGENCY Don the smoke goggles onto the face 4 -- ”PASSENGERS OXYGEN” switch 5 -- Check the oxygen flow indicator for the front seats (the blinker is transparent) and for the rear passengers (the blinker is green).
Page 618: Normal Procedures
T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE”...
Page 619 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) IN--FLIGHT AVAILABLE OXYGEN QUANTITY (Cont’d) 1 -- Determine the usable oxygen percent using the chart Figure 9.37.1. Figure 9.37.1 2 -- Determine the oxygen duration in minutes by multiplying the values read on table Figure 9.37.2 by the percent obtained with the chart Figure 9.37.1.
Page 620: Performance
T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) AFTER LANDING ”OXYGEN” switch SECTION 5 PERFORMANCE The installation of the gaseous oxygen system does not change the basic performance of the airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook.
Page 621: Description
T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) SECTION 7 DESCRIPTION The TBM 700 airplane is equipped with an optional gaseous oxygen system, which will be used by the crew and the passengers, when the cabin altitude is greater than 10000 ft following a loss of pressurization or in case of cabin air contamination.
Page 622 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) An indicating and control panel located in the cockpit overhead panel at the disposal of the pilot includes : -- a graduated pressure gage to permit checking the cylinder charge, -- a two--position valve ON/OFF (”OXYGEN”...
Page 623 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) FLIGHT ABOVE 15000 FT WITH EMERGENCY DESCENT Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C 1010 1137 1096 1056...
Page 624 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) WHEN REQUIRED TO REMAIN ABOVE 15000 FT DUE TO MINIMUM ”EN ROUTE” ALTITUDE Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C...
Page 625 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) FLIGHT BETWEEN 15000 FT AND 10000 FT Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C 1333 1282 1231 1181...
Page 626: Handling, Servicing And Maintenance
T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) SECTION 8 HANDLING, SERVICING AND MAINTENANCE The operations hereafter supplement those of the standard airplane described in Section 8 ”Handling, servicing and maintenance” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””EROS/INTERTECHNIQUE”...
Page 627 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) REPLENISHMENT PROCEDURE WARNING MAKE SURE THAT THE AIRPLANE IS FITTED WITH A GROUDING CABLE AND IS PROPERLY GROUNDED. THE OXYGEN CART MUST BE ELECTRICALLY BONDED TO THE AIRPLANE. DO NOT OPERATE THE AIRPLANE ELECTRICAL SWITCHES OR CONNECT/DISCONNECT GROUND POWER DURING OXYGEN SYSTEM REPLENISHMENT.
Page 628 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) If the pressure on the oxygen cylinder gage is lower, fill the oxygen cylinder. Make sure the area around the oxygen cylinder charging valve is clean. Remove the cap from the charging valve. Make sure the oxygen supply hose is clean and connect it to the charging valve.
Page 629 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) WARNING MASKS SHALL BE REPACKED IN AN AREA FREE OF OIL, GREASE, FLAMMABLE SOLVENTS OR OTHER CONTAMINANTS Inspect and disinfect mask and deployment container with an aqueous solution of Zephiran Chloride (”Scott Aviation” P/N 00--2572) or with disinfection cleaners (”EROS”...
Page 630 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) Gently fold reservoir bag lengthwise into thirds (outside edges folded inward over center of bag). Do not crease bag. Fold reservoir bag away from breathing valves and into facepiece. Make sure bag does not cover breathing valves.
Page 631 T B M SUPPLEMENT 37 ”EROS/INTERTECHNIQUE” GASEOUS OXYGEN SYSTEM (31000 FT) Coil oxygen tubing inside facepiece over reservoir bag. Connect oxygen tubing to manifold oxygen fitting. WARNING MAKE SURE LANYARD PIN IS INSERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED. CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyard pin into corresponding check valve.
Page 632 T B M SUPPLEMENT 38 OPERATION AT 31000 FT SUPPLEMENT OPERATION AT 31000 FT TABLE OF CONTENTS Page -- GENERAL ........9.38.2 -- LIMITATIONS .
Page 633: General
T B M SUPPLEMENT 38 OPERATION AT 31000 FT SECTION 1 GENERAL This supplement is intended to inform the pilot about the limitations and the operation of the TBM 700 airplane at 31000 ft. SECTION 2 LIMITATIONS The limitations hereafter supplement those of the standard airplane described in Section 2 ”Limitations”...
Page 634: Performance
T B M SUPPLEMENT 38 OPERATION AT 31000 FT SECTION 5 PERFORMANCE Information hereafter supplement or replace the one given for the standard airplane in Section 5 ”Performance” of the basic Pilot’s Operating Handbook. 5.1 - - CABIN PRESSURIZATION ENVELOPE Cabin altitude (feet)
Page 635 T B M SUPPLEMENT 38 OPERATION AT 31000 FT 5.2 - - ENGINE OPERATION Conditions : 31000 ft Landing gear and flaps UP Np = 2000 RPM -- BLEED LO Maximum Climb Normal Maximum Cruise Power (recommended) Power IAS = 130 kt Cruise Power (˚C) TRQ (%)
Page 636 T B M SUPPLEMENT 38 OPERATION AT 31000 FT 5.3 - - CLIMB PERFORMANCE : TIME, CONSUMPTION AND CLIMB DISTANCE To obtain the values for 31000 ft, refer to Section 5 ”Performance”, Chapter 5.9 “Climb performance”, of the basic Pilot’s Operating Handbook and add 4 % to the values given for 30000 ft in the tables “Time, consumption and climb distance”.
Page 637 T B M SUPPLEMENT 38 OPERATION AT 31000 FT SECTION 6 WEIGHT AND BALANCE The operation of the TBM 700 airplane at 31000 ft does not change the weight and balance given in Section 6 ”Weight and balance” of the basic Pilot’s Operating Handbook.
Page 638 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SUPPLEMENT CHIP DETECTION SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.44.2 -- LIMITATIONS .
Page 639: General
T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the TBM airplane is equipped with the option ”CHIP DETECTION SYSTEM” and with MOD70--0276--00.
Page 640: Emergency Procedures
T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the TBM airplane is equipped with the option ”CHIP DETECTION SYSTEM”...
Page 641: Performance
T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 4 PROCEDURES NORMALES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook, when the TBM airplane is equipped with the option ”CHIP DETECTION SYSTEM”...
Page 642: Weight And Balance
T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM 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. WEIGHT EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg) 79 - - LUBRICATION...
Page 643 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SUPPLEMENT ”AIRBORNE” GWX 68 COLOR WEATHER RADAR TABLE OF CONTENTS Page -- GENERAL 9.47.2 ..........-- LIMITATIONS 9.47.2 .
Page 644 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional ”AIRBORNE” GWX 68 color weather radar system is installed in the TBM 700 or TBM 850 airplanes equipped with MOD70--0176--00 or MOD70--276--00.
Page 645 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SECTION 3 EMERGENCY PROCEDURES Installation and operation of ”AIRBORNE” GWX 68 color weather radar system do not change the basic emergency procedures of the airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook.
Page 646 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook. Normal operating procedures for “AIRBORNE” GWX 68 color weather radar system are outlined in the Pilot’s Guide, the references of which are given in Section 2 “Limitations”...
Page 647 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR BEFORE LANDING -- Radar Mode Softkey STANDBY ....... . . ENGINE SHUT- -DOWN -- Radar Mode Softkey .
Page 648 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR SECTION 7 DESCRITION The weather information are displayed only on the MFD (GDU 1500). The controls for the MFD are located on both the MFD bezel and the MFD control unit (keyboard GCU 475).
Page 649 T B M SUPPLEMENT 47 “AIRBORNE” GWX 68 COLOR WEATHER RADAR Figure 9.47.1 (2/2) -- GWX 68 weather radar display and controls Rev. 1 Page 9.47.7...
Page 650 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM SUPPLEMENT ”GARMIN” G1000 TAWS SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.49.3 -- LIMITATIONS .
Page 651: General
T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the airplane is equipped with the option ”GARMIN” G1000 TAWS SYSTEM. The TAWS function enables to detect if the airplane path is in compliance with the overflown terrain relief.
Page 652: Emergency Procedures
T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”GARMIN”...
Page 653 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM 4.1 - - WARNINGS OF THE TAWS FUNCTION “PULL UP” AURAL WARNING The red “PULL--UP” PFD/MFD annunciation and MFD pop--up alert light on. 1 -- Level the wings. 2 -- Display the maximum power. 3 -- Choose the optimum rate of climb adapted to airplane configuration and speed, until the warning disappears.
Page 654: Performance
T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM “Don’t sink” AURAL WARNING The amber “TERRAIN” PFD/MFD annunciation and “DON’T SINK” pop--up alert light on. Re--establish a positive rate of climb. “Sink rate” AURAL WARNING The amber “TERRAIN” PFD/MFD annunciation and “SINK RATE” pop--up alert light on.
Page 655: Weight And Balance
T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in Section 6 ”Weight and balance” of the basic Pilot’s Operating Handbook. WEIGHT EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg)
Page 656: Description
T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM SECTION 7 DESCRIPTION The G1000 TAWS function has 7 modes. FORWARD LOOKING TERRAIN AVOIDANCE ALERT The Forward Looking Terrain Avoidance (FLTA) alert is used by TAWS and is composed of : -- Reduced Required Terrain Clearance and Reduced Required Obstacle Clearance Reduced Required Terrain Clearance (RTC) and Reduced Required...
Page 657 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM During the final approach phase of flight, FLTA alerts are automatically inhibited when the airplane is below 200 feet AGL while within 0.5 Nm of the approach runway or below 125 feet AGL while within 1.0 Nm of the runway threshold.
Page 658 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM PREMATURE DESCENT ALERTING A Premature Descent Alert (PDA) is issued when the system detects that the airplane is significantly below the normal approach path to a runway (Figure 9.49.1). PDA alerting begins when the airplane is within 15 Nm of the destination airport.
Page 659 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM EXCESSIVE DESCENT RATE ALERT The purpose of the Excessive Descent Rate (EDR) alert is to provide suitable notification when the airplane is determined to be closing (descending) upon terrain at an excessive speed. Figure 9.49.2 shows the parameters for the alert as defined by TSO--C151b.
Page 660 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM The aural/displayed messages associated with the EDR function are described in the table 7.4. PFD/MFD MFD Map Page TAWS Page Alert Type Aural Message Annuncia-- Pop--Up Alert tion Excessive Descent Rate Warning (EDR) PULL UP “Pull up”...
Page 661 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM The NCR alert is issued when the altitude loss and height are within the range in the first figure, or when the sink rate (negative vertical speed) and height are within the range in the second figure. Figure 9.49.3 -- Negative Climb Rate (NCR) Alert Criteria The aural/displayed messages associated with the NCR function are described in the table 7.5.
Page 662 T B M SUPPLEMENT 49 ”GARMIN” G1000 TAWS SYSTEM “FIVE- -HUNDRED” AURAL ALERT The purpose of the aural alert message “Five--Hundred” is to provide an advisory alert to the pilot that the airplane is 500 feet above terrain. When the airplane descends within 500 feet of terrain, the aural message “Five--Hundred”...
Page 663 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SUPPLEMENT ”GARMIN” G1000 SYNTHETIC VISION SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.50.3 -- LIMITATIONS .
Page 664 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary to the operation when the airplane is equipped with the option ”GARMIN” G1000 SYNTHETIC VISION SYSTEM (SVS).
Page 665 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SECTION 2 LIMITATIONS The limitations hereafter supplement those of the standard airplane described in Section 2 ”Limitations” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”GARMIN” G1000 SYNTHETIC VISION SYSTEM.
Page 666 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SECTION 3 EMERGENCY PROCEDURES The procedures hereafter supplement those of the standard airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”GARMIN” G1000 SYNTHETIC VISION SYSTEM.
Page 667 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”GARMIN” G1000 SYNTHETIC VISION SYSTEM.
Page 668 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SVS ACTIVATION (2/2) (b) If Horizon Heading is desired : -- “HRZN HDG” key ......Press The horizon heading display will cycle on or off with each press of the “HRZN HDG”...
Page 669 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SECTION 5 PERFORMANCE The installation and the operation of the ”GARMIN” G1000 SYNTHETIC VISION SYSTEM do not change the basic performance of the airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook.
Page 670 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM SECTION 7 DESCRIPTION SVS provides additional features on the G1000 primary flight display (PFD) which display the following information : Synthetic Terrain : an artificial, database derived, three dimensional view of the terrain ahead of the aircraft within a field of view of approximately 30 degrees left and 35 degrees right of the aircraft heading.
Page 671 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM USE OF PATHWAY If Synthetic Terrain is displayed on the PFD, the Pathway may be used to assist the pilot’s awareness of the programmed lateral and vertical navigation path. The following sections describe the basic use of the Pathway in various flight segments.
Page 672 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM -- Enroute When enroute, the Pathway will be displayed along the lateral path defined by the flight plan, at the altitude selected on the G1000 altitude selector. Flight plan changes in altitude that require a climb will be indicated by the Pathway being displayed as a level path at the altitude entered for the current flight plan leg.
Page 673 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM If the altitude selector is left at an altitude above the current airplane altitude, the airplane will intercept the final approach course below the extended VPTH or GP, such that the Pathway will be displayed above the airplane until the aircraft intercepts the VPTH or GP.
Page 674 T B M SUPPLEMENT 50 ”GARMIN” G1000 SYNTHETIC VISION SYSTEM -- Missed approach When the missed approach is selected on the G1000 FMS, the Pathway to the Missed Approach Holding Point will be displayed just as described for the departure segment. The pilot must assure that the aircraft path will, at all times, comply with the requirements of the published missed approach procedure.

This manual is also suitable for:

Tbm 700 a Tbm 700 b

Daher-Socata TBM 700 Series Pilot Operating Handbook

Quick Links

Chapters

Need help?

Questions and answers

Subscribe to Our Youtube Channel

Summary of Contents for Daher-Socata TBM 700 Series