Download Print this page

Daher TBM 700 Pilot's Manual

Daher TBM 700 Pilot's Manual

Hide thumbs Also See for TBM 700:

Pilot's information manual (1532 pages)

page of 991

/ 991
Contents
Table of Contents
Bookmarks

Table of Contents

Advertisement

Quick Links

Download this manual

INFORMATION MANUAL

THIS INFORMATION MANUAL IS A NON---OFFICIAL COPY OF THE PILOT'S

OPERATING HANDBOOK AND MAY BE USED FOR GENERAL INFORMATION

IT IS NOT KEPT CURRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE

FOR AIRWORTHINESS AUTHORITIES APPROVED MANUAL WHICH IS THE ONLY ONE

The content of this document is the property of

confidence and commercial security of its contents must be maintained.

It must not be used for any purpose other than that for which it is supplied, nor may

information contained in it be disclosed to unauthorized persons. It must not be

reproduced nor transmitted in any form in whole or in part without permission in

Information in this document is subject to change without notice.

 2002 thru 2012, 2014 ---

For any information concerning this document, please contact :

SOCATA SAS

CUSTOMER SUPPORT

65921 TARBES CEDEX 9

FRANCE

October 31, 2014 --- Rev. 8

TBM 700

Version C

PILOT'S

PURPOSES ONLY.

INTENDED FOR OPERATION OF THE AIRPLANE.

writing from the owners of the Copyright.

CAUTION

SOCATA SAS

SOCATA SAS

--- All rights reserved

TELEPHONE : 33 (0)5 62.41.73.00

TELEFAX

P/N : T00.DMCPIPYE

. It is supplied in

: 33 (0)5 62.41.76.54

Printed in FRANCE

Table of Contents

Advertisement

Chapters

Table of Contents

Need help?

Need help?

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

Questions and answers

Summary of Contents for Daher TBM 700

Page 1 TBM 700 Version C PILOT’S INFORMATION MANUAL CAUTION THIS INFORMATION MANUAL IS A NON---OFFICIAL COPY OF THE PILOT’S OPERATING HANDBOOK AND MAY BE USED FOR GENERAL INFORMATION PURPOSES ONLY. IT IS NOT KEPT CURRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE FOR AIRWORTHINESS AUTHORITIES APPROVED MANUAL WHICH IS THE ONLY ONE INTENDED FOR OPERATION OF THE AIRPLANE.
Page 2 New A14 landing gear control panel Major 124--71 Engine drains minor 138--53 ELT housing minor 139--00 TBM 700 takeoff max. weight increase Major 140--00 Evolutions from TBM 700B to TBM 700C1 : Major MTOW 6579 lbs (2984 kg) 142--21 Air cycle system (ACS) Major...
Page 3 (external flap carriages are processed by amendment) 0170--23 Separation of audio circuit low points (GMA minor 340) -- TBM 700 equipped with option OPT70 23023 0172--57 Replacement on flaps of SHUR LOCK nuts minor by machined bushings 0173--28 New fuel gauging probes...
Page 4 T B M SECTION 0 PILOT’S OPERATING HANDBOOK MOD70 No. SUBJECT CLASSIF. 0195--56 Rear cabin window (same as front cabine minor window) 0201--32 Landing gear actuating cylinder minor modification 0205--55 Replacement of fin expansion pins minor 0209--57 Reinforcement of trailing edge omega at rib 7 minor 0213--27 Pitch trim union connector at rear pressure...
Page 5 T B M SECTION 0 PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Rev. 6 Page 0.5D...
Page 6 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 Rev. 0 Page 0.6...
Page 7: 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 8 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 1.0.2 Rev. 0...
Page 9: General
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. It also contains supplemental data supplied by the manufacturer.
Page 10 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 1.1.2 Rev. 0...
Page 11: Three View Drawing
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1.2 - - THREE VIEW DRAWING Figure 1.2.1 (1/2) -- THREE VIEW DRAWING Rev. 0 Page 1.2.1...
Page 12 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Figure 1.2.1 (2/2) -- THREE VIEW DRAWING Rev. 7 Page 1.2.2...
Page 13: 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 14: 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 15: 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 : 0.14 qt / hr (0.13 l / hr) [0.3 lb/hr (0.136 kg/h)] CAUTION DO NOT MIX DIFFERENT BRANDS OR TYPES...
Page 16: Cabin And Entry Dimensions
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK CABIN AND ENTRY DIMENSIONS Maximum cabin width : 3’ 11.64” (1.21 m) Maximum cabin length : 13’ 3.45” (4.05 m) Maximum cabin height : 4’ (1.22 m) Number of cabin entries : 1 (standard) + 1 ”pilot” door (if installed) Entry width (standard) : 3’...
Page 17: 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 IOAT Indicated outside air temperature Atmospheric pressure at the airport reference point.
Page 18 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 19: 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 20: 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 21 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 22: General Abbreviations
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK GENERAL ABBREVIATIONS : Ampere or Amber : Air Data Computer AIL TRIM : Aileron trim ALT. SEL. : Altitude selector ALTI : Altimeter AMP. : Ampere : Autopilot AUTO SEL : Automatic selector AUX BP : Auxiliary boost pump : Battery...
Page 23 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK INERT SEP : Inertial separator INDIC : Indicator in.Hg : Inch of mercury INT. LIGHTS : Interior lightings INSTR. : Instrument IRCR : Intermediate range cruise : Interturbine temperature : Kilogram : Knot (1 nautical mile/hr -- 1852 m/hr) : Kilowatt : Litre...
Page 24 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK : Quart (¼ us gal) : Quantity : Red or Right : Rudder s or sec : Second : Selector : Signalization : Sea level : Serial number SPKR : Speaker ST - - BY : Stand--by STALL HTR...
Page 25: Radio -- Navigation Abbreviations
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK RADIO - - NAVIGATION ABBREVIATIONS : Automatic Direction Finder System : Attitude Director Indicator : Transponder : Course Deviation Indicator : Communications Transceivers : Distance Measuring Equipment EGPWS : Enhanced Ground Proximity Warning System : Emergency Locator Transmitter : Ground Positioning System : High Frequency...
Page 26: Efis Abbreviations
T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK EFIS ABBREVIATIONS ATTITUDE FAIL: Attitude failure CMPST : Composite (EFIS composite mode ) : Control Panel : Course : Display Unit : Flight director EADI : Electronic Attitude Deviation Indicator EFIS : Electronic Flight Instrument System EHSI : Electronic Horizontal Situation Indicator...
Page 27: 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 28 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK Feet 31000 30000 20000 10000 Mètres 2500 5000 7500 10000 Figure 1.5.2 -- FEET VERSUS METRES Page 1.5.2 Rev. 0...
Page 29 T B M SECTION 1 GENERAL PILOT’S OPERATING HANDBOOK 1000 Figure 1.5.3 -- INCHES VERSUS MILLIMETRES Rev. 0 Page 1.5.3...
Page 30 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 Page 1.5.4 Rev. 0...
Page 31: 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 32: 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 33: 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 ........... AIRSPEED LIMITATIONS 2.2.1 .
Page 34 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 35: General
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 36 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.1.2...
Page 37: 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 this speed in normal flight Maximum operating speed category Do not make abrupt or full...
Page 38 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.2.2...
Page 39: Powerplant Limitations
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.3 - - POWERPLANT LIMITATIONS ENGINE Number of engines : 1 Engine manufacturer : PRATT & WHITNEY CANADA Engine model number : PT6A -- 64 Engine operating limits for takeoff and continous operations : Maximum power : -- 700 SHP : MAX TRQ 100 % at Np = 2000 RPM...
Page 40: 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 41: 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 42 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.3.4...
Page 43: 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 44 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.4.2...
Page 45: Weight And C.g. Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.5 - - WEIGHT AND C.G. LIMITS (Refer to Supplement 41 for TBM 700C2 airplane) WEIGHT LIMITS Maximum ramp weight (MRW) : 6614 lbs (3000 kg) Maximum takeoff weight (MTOW) : 6579 lbs (2984 kg) Maximum landing weight (MLW) : 6250 lbs (2835 kg) Maximum zero fuel weight (MZFW) : 6001 lbs (2722 kg) Maximum baggage weight in pressurized compartment : 220 lbs (100 kg)
Page 46 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.5.2...
Page 47: 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--aerobatic operations. Non--aerobatic operations include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and steep turns in which the angle of bank is no more than 60°.
Page 48: Severe Icing Conditions
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved SEVERE ICING CONDITIONS WARNING SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIRCRAFT IS CERTIFICATED. FLIGHT IN FREEZING RAIN, FREEZING DRIZZLE, OR MIXED ICING CONDITIONS (SUPERCOOLED LIQUID WATER AND ICE CRYSTALS) MAY RESULT IN ICE BUILD- -UP ON PROTECTED SURFACES EXCEEDING THE CAPABILITY OF THE ICE PROTECTION SYSTEM,...
Page 49: Flap Operating Envelope
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved FLAP OPERATING ENVELOPE The use of flaps is not authorized above 15 000 ft. REVERSE UTILIZATION The use of control reverse BETA (β) range is prohibited : -- during flight, -- on ground, if the engine is not running.
Page 50 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) Warning lights -- Oil pressure -- Low fuel pressure -- Fuel selector OFF -- Fuel auxiliary pump ON -- L.H.
Page 51 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 52 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 53 RVSM Operational Approval is required by an ICAO Regional Navigation Agreement. NOTE : Only altimeters AM250 are compliant with TBM 700 operation in RVSM area. 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.
Page 54 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.6.8...
Page 55: Miscellaneous Limits
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.7 - - MISCELLANEOUS LIMITS SEATING LIMITS C.G. -- 2 seats at 180.5 inches (4.585 m) -- 2 seats at 222.1 inches (5.641 m) -- 2 seats at 272.3 inches (6.916 m) BAGGAGE LIMITS -- Baggage in pressurized cabin at 303 inches (7.695 m) -- Rear baggage at 329.4 inches (8.366 m)
Page 56 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.7.2...
Page 57: Markings
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.8 - - MARKINGS AIRSPEED INDICATOR (Refer to Supplement 41 for TBM 700C2 airplane) Airspeed indicator markings and their color code significance are shown in Figure 2.8.1. KIAS MARKING SIGNIFICANCE (Value or range) White arc...
Page 58: 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 59: Placards
T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved 2.9 - - PLACARDS (1) Under L.H. front side window * (2) Calibration chart on compass and on windshield post WARNING Steer TURN L AND R WINDSHIELD DE- -ICE OFF BEFORE Steer COMPASS READING DATE :...
Page 60 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (3) On pressurized baggage compartment partition wall * (*) Refer to Supplement 41 for TBM 700C2 airplane Rev. 7 Page 2.9.2...
Page 61 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (4) Under radio rack, in front of pedestal Rev. 7 Page 2.9.3...
Page 62 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (5) On fuel selector (6) Near fuel tank caps Rev. 7 Page 2.9.4...
Page 63 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (7) On internal face of L.H. engine cowling Oil system capacity 12 l 12.7 qt (8) On landing gear emergency control access door LDG GEAR EMERGENCY UNDER HATCH (9) On rear passenger’s table casing TABLE MUST BE STOWED DURING TAKEOFF AND LANDING (10) Under R.H.
Page 64 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (11) On nose gear door (12) On nose gear leg NOSE LANDING GEAR TIRE PRESSURE : 6,5 bar 94 psi (13) On main gear leg * MAIN LANDING GEAR TIRE PRESSURE : 8,25 bar 120 psi (14) On engine cowling, in front of compartment door...
Page 65 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (15) On ”pilot” door -- External side (if installed) (16) On access door -- External side Rev. 7 Page 2.9.7...
Page 66 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (17) On outer fuselage skin aft of access door and in the cabin forward of access door (18) On access door -- Internal side Rev. 7 Page 2.9.8...
Page 67 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (19) On ”pilot” door -- Internal side (if installed) (20) On emergency exit handle Marking on cover Marking on handle Rev. 7 Page 2.9.9...
Page 68 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (21) On last step of stairs STAIRS MAX LOAD : ONE PERSON (22) On R.H. access door jamb DO NOT USE HAND RAIL TO RETRACT OR STOW STAIRS (23) On R.H. side at front seat level and on the first rear passengers masks container (R.H.
Page 69 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (25) On internal face of the oxygen cylinder service door (26) On the oxygen service door Rev. 7 Page 2.9.11...
Page 70 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (27) On internal face of L.H. engine cowl (28) On internal face of the door of the rear baggage compartment (non pressurized) Rev. 7 Page 2.9.12...
Page 71 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (29) On emergency locator transmitter inspection door (30) On the potty seat curtain (if installed), on pilot’s side CURTAIN MUST BE STOWED FOR TAKE- -OFF AND LANDING Post--MOD70--0391--26D (31) On R.H. side at front seat level (32) On the lower drawer of the R.H.
Page 72 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved (29) On emergency locator transmitter inspection door (30) On the potty seat curtain (if installed), on pilot’s side CURTAIN MUST BE STOWED FOR TAKE- -OFF AND LANDING Rev. 7 Page 2.9.13...
Page 73 T B M SECTION 2 LIMITATIONS PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 2.9.14...
Page 74 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 75 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page EMERGENCY DESCENTS 3.6.1 ....... . 3.6.2 MAXIMUM RATE DESCENT .
Page 76 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page AMBER WARNING LIGHT LO VOLT 3.9.3 normal functioning on ”MAIN GEN” ........AMBER WARNING LIGHT LO VOLT 3.9.4...
Page 77 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page 3.12 DEICING SYSTEM 3.12.1 ......... 3.12.1 LEADING EDGES DEICING FAILURE .
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 an advisory panel. This panel includes red warning lights indicating a failure which requires an immediate action from the pilot, and amber warning lights indicating failures or discrepancies which require an action as soon as practical.
Page 80 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 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 3.2.2...
Page 82 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 83 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE FAILURE AFTER ROTATION (Refer to Supplement 41 for TBM 700C2 airplane) - 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 84 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE FAILURE DURING FLIGHT 1 -- If AP engaged : “AP / TRIM DISC INT” push--button ....PRESSED 2 -- Power lever .
Page 85: Engine Failures
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES OIL PRESSURE DROP OIL PRESS RED WARNING LIGHT 1 -- Oil pressure indicator ......CHECK 2 -- If the indicated pressure is correct .
Page 86: 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 -- Tank selector...
Page 87 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES ENGINE REGULATION DISCREPANCY, POWER LOSS, POWER LEVER CONTROL LOSS (2/2) 7 -- Perform a normal landing WITHOUT REVERSE 8 -- Braking ........AS REQUIRED If minimum power obtained is excessive : 1 -- Reduce airspeed by setting airplane in nose--up attitude at...
Page 88: 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 89: 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 90: Red Warning Light
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES RED WARNING LIGHT ON (1/2) Indicates that ITT exceeds 800°C During an engine start Intertubine temperature °C 1000 Inform the maintenance department No action required Time (seconds)
Page 91 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.3 -- ENGINE FAILURES RED WARNING LIGHT ON (2/2) 3 -- Record the engine parameters read as well as ground conditions. 4 -- Inform maintenance department. During flight 1 -- ITT indicator .
Page 92: 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 MASTER”...
Page 93 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 3.3.12...
Page 94: Air Start
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 - - AIR START AIR START ENVELOPE AIR START ENVELOPE Air start may be attempted outside of the envelope. However, above 20000 ft or with Ng < 13 %, ITT tends to increase during start and prudence is recommended.
Page 95: 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 96 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.4 -- AIR START AIR START WITH STARTER (2/2) 12 -- Condition lever ........LO / IDLE when Ng μ...
Page 97 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 3.4.4...
Page 98: 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 Symptoms : ITT increasing, red warning light smoke, ... 1 -- Power lever ......... IDLE 2 -- Condition lever .
Page 99: Engine Fire In Flight
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK D.G.A.C. Approved 3.5 -- FIRE AND SMOKE ENGINE FIRE IN FLIGHT Symptoms : ITT increasing, red warning light smoke, ... 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
Page 100: 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) If the origin is known : 1 -- Oxygen and goggles (if installed) ..USE AS REQUIRED (pilot and passengers) 2 -- Defective equipment...
Page 101 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK D.G.A.C. Approved 3.5 -- FIRE AND SMOKE CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT (2/2) If smoke or fire persists : 5 -- ”SOURCE” selector ........6 -- ”GENERATOR”...
Page 102: 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 and goggles (if installed) .
Page 103 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK D.G.A.C. Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 3.5.6...
Page 104: Emergency Descents
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 - - EMERGENCY DESCENTS Two types of descent are considered : 1 -- Engine running, maximum descent rate, if necessary The factors to be considered are : -- Cabin altitude and oxygen duration -- Electrical power endurance -- Distance to appropriate landing area...
Page 105: Maximum Rate Descent
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 -- EMERGENCY DESCENTS MAXIMUM RATE DESCENT 1 -- Power lever ......... IDLE 2 -- Oxygen .
Page 106 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 -- EMERGENCY DESCENTS MAXIMUM RANGE DESCENT (2/3) 7 -- Oxygen ........If necessary Check oxygen duration before reaching 12000 ft and check flow to passengers...
Page 107 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.6 -- EMERGENCY DESCENTS MAXIMUM RANGE DESCENT (3/3) -- “CD” player ........-- “INSTR / CABIN / ACCESS”...
Page 108: Emergency Landings
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 - - EMERGENCY LANDINGS FORCED LANDING (ENGINE CUT OFF) (Refer to Supplement 41 for TBM 700C2 airplane) 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
Page 109: 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 110: 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 111 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 112: 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) (Refer to Supplement 41 for TBM 700C2 airplane) 1 -- Transfer passengers to the rear, if necessary 2 -- Approach .
Page 113: 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 (Refer to Supplement 41 for TBM 700C2 airplane) 1 -- Final approach ........Standard (Flaps LDG, IAS = 80 KIAS) 2 -- ”BLEED”...
Page 114: 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 115: 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 (Refer to Supplement 41 for TBM 700C2 airplane) For flaps deflections from “UP” to “TO” position : Proceed as for a normal landing, maintaining approach airspeed : -- Weight ±...
Page 116: Ditching
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.7 -- EMERGENCY LANDINGS DITCHING (Refer to Supplement 41 for TBM 700C2 airplane) 1 -- Landing gear ......... . In heavy swell with light wind, land parallel to the swell (rollers).
Page 117 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 3.7.10...
Page 118: Fuel System
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 - - FUEL SYSTEM RED WARNING LIGHT ON (1/2) FUEL PRESS Indicates a fuel pressure drop at ”HP” engine pump inlet 1 -- Remaining fuel ........CHECK 2 -- Tank selector .
Page 119 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 -- FUEL SYSTEM RED WARNING LIGHT ON (2/2) FUEL PRESS If pressure remains at 0 and if warning remains on : FUEL PRESS 9 -- Selection of the fullest tank .
Page 120: Amber Warning Light
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 -- FUEL SYSTEM AMBER WARNING LIGHT AUX BP 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 121: Amber Warning Light
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.8 -- FUEL SYSTEM AMBER WARNING LIGHT FUEL L. LO FUEL R. LO Indicates level drop in the corresponding tank 1 -- Corresponding gage ......CHECK 2 -- Check the other tank has been automatically selected If not :...
Page 122: Electrical System
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 - - ELECTRICAL SYSTEM RED WARNING LIGHT BAT OVHT (if Cadmium- -Nickel battery installed) Indicates a battery overheat 1 -- ”SOURCE” selector ........WARNING LIGHT BAT OVHT 2 -- Monitor airplane mains battery voltage...
Page 123 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING LIGHT MAIN GEN Indicates that ”GENERATOR” selector has been positioned to OFF or ST--BY, or main generator is cut off 1 -- If necessary .
Page 124 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING LIGHT LO VOLT normal functioning on ”MAIN GEN” 1 -- Voltmeter voltage ....... . . CHECK 2 -- If voltage is <...
Page 125 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING LIGHT LO VOLT functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (1/3) Amber warning lights MAIN GEN LO VOLT with ”GENERATOR” selector on ”ST--BY” 1 -- ”GENERATOR”...
Page 126 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING LIGHT LO VOLT functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (2/3) 9 -- ”GENERATOR” selector ......If conditions allow : VMC and non icing conditions 10 -- If altitude ≥...
Page 127 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM AMBER WARNING LIGHT LO VOLT functioning on ”ST- -BY GENERATOR” (after ”MAIN GEN” failure) (3/3) -- VHF 1 / NAV 1 / GPS 1 .
Page 128 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Figure 3.9.1 (1/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Rev. 7 Page 3.9.7...
Page 129 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved Figure 3.9.1 (2/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Rev. 7 Page 3.9.8...
Page 130 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.9 -- ELECTRICAL SYSTEM ”RADIO MASTER” SWITCH FAILURE In case of ”RADIO MASTER” switch misfunction, leading to the impossibility of energizing the radionavigation equipment : 1 -- ”RADIO FAN” circuit breaker .
Page 131 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 3.9.10...
Page 132 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 - - PRESSURIZATION AND AIR CONDITIONING RED WARNING LIGHT CAB PRESS 1 -- Pressurization indicator ......CHECK ∆...
Page 133 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING AMBER WARNING LIGHT BLEED OFF Indicates an overpressure at air conditioning pack inlet or a malfunction of the pressure stop and regulating valve (Normal signal if ”BLEED”...
Page 134 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING RED WARNING LIGHT BLEED TEMP Indicates overheat of air conditioning pack. Normally this leads to BLEED cutoff and to amber warning light illumination. BLEED OFF Should automatic cutoff occur or not : 1 -- If possible, reduce power...
Page 135 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING RED WARNING LIGHT DOOR Indicates that one of the door latches of the access door and (if installed) of the ”pilot” door has not been correctly locked On ground, check the correct locking, as well as the latches position of the access door and (if installed) of the ”pilot”...
Page 136 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING AMBER WARNING LIGHT VACUUM LO Suction gage indicator ....... . CHECK Low vacuum may lead to misfunctioning of leading edge deicing, pressurization and gyroscopic vacuum--operated...
Page 137 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.10 -- PRESSURIZATION AND AIR CONDITIONING DEFOG MALFUNCTION If moisture starts to quickly cover the inside of the windscreen with the distributor already positioned on ”DEFOG” : 1 -- ”AIR FLOW” distributor .
Page 138 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 - - LANDING GEAR AND FLAPS LANDING GEAR RETRACTION DISCREPANCY NOTE : Symptoms have to be considered at the end of the sequence. A - - Symptoms : Steady red warning light ON and 0 to 3 green light(s) ON.
Page 139 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS LANDING GEAR EXTENSION DISCREPANCY NOTE : Symptoms have to be considered at the end of the sequence. - - Symptoms Steady red warning light ON and 0 to 3 green light(s) OFF. Red warning light flashing and 0 to 3 green light(s) OFF.
Page 140 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS EMERGENCY GEAR EXTENSION (1/2) NOTE : This procedure has to be followed in case of any discrepancy or doubt about the gear extension or retraction. Maintain IAS ≤...
Page 141 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS EMERGENCY GEAR EXTENSION (2/2) If landing gear does not lock (other than 3 green indicator lights illuminated) : 6 -- ”LDG GR” circuit breaker .
Page 142 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.11 -- LANDING GEAR AND FLAPS RED WARNING LIGHT FLAPS Indicates a dissymmetry of flap deflection. This immediately stops the flap motor and prevents further operation of the flaps 1 -- ”FLAPS”...
Page 143 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 3.11.6...
Page 144: 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 145: Inertial Separator Failure
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM INERTIAL SEPARATOR FAILURE Symptoms : -- Warning light is not lit 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 146: 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 (Refer to Supplement 41 for TBM 700C2 airplane) Symptoms : -- Mist or ice on windshield internal face 1 -- ”CABIN TEMP/° C” selector .
Page 147: Amber Warning Light
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.12 -- DEICING SYSTEM AMBER WARNING LIGHT PITOT 1 PITOT 2 STALL HTR Indicates a heating failure of the corresponding probe Icing conditions may alter airspeed indications on the PITOT 1 airspeed indicator 1 -- AVOID icing conditions...
Page 148: 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 149: 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 150: 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 151: Particular Transponder Uses
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS PARTICULAR TRANSPONDER USES 1 -- Check transponder mode selector ....ON or ALT 2 -- Codes selector : 7700...
Page 152: 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...) Front seats 1 -- Take a mask on the opposite seat side (pilot : R.H.
Page 153 T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS OXYGEN USE (2/2) Passengers 1 -- Take a mask. 2 -- Uncoil tube totally. 3 -- Pull on the lanyard cord to take out the lanyard pin. 4 -- Put the mask on the face.
Page 154: Airspeed Indicating System Failure
T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 3.13 -- MISCELLANEOUS AIRSPEED INDICATING SYSTEM FAILURE Symptoms : erroneous indication in flight 1 -- ”PITOT 1 HTR” switch ......CHECK ON 2 -- ”PITOT 2 &...
Page 155: 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 156 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 157 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved TABLE OF CONTENTS (Continued) Page 4.4.37 MOTORING FOLLOWED BY AN ENGINE START ....4.4.40 AFTER STARTING ENGINE .
Page 158: General
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. The amplified procedures are developed in the second part of the Section.
Page 159 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 4.1.2...
Page 160: Airspeeds For Normal Operation
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved 4.2 - - AIRSPEEDS FOR NORMAL OPERATION (Refer to Supplement 41 for TBM 700C2 airplane) CONDITIONS : - Takeoff weight 6579 lbs (2984 kg) - Landing weight : 6250 lbs (2835 kg) Rotation airspeed (V -- Flaps TO...
Page 161 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 4.2.2...
Page 162: 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 163 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 Rev. 7 Page 4.3.2...
Page 164 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 -- ELECTRIC POWER panel -- ”SOURCE”...
Page 165 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 11 -- ECS panel -- ”BLEED” switch ........-- “AIR COND”...
Page 166 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 20 -- BAT BUS power supply -- Stop watch ........CHECKED -- Access lighting .
Page 167 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 30 -- INT LIGHTS panel ....... . . CHECK 31 -- ECS panel -- ”LT TEST”...
Page 168 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 37 -- EXT LIGHTS panel -- ”STROBE” ........-- ”NAV”...
Page 169 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 170 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 -- Forward compartment...
Page 171 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 8 -- Propeller and spinner ......CHECK (No nicks, cracks or oil leaks / Attachment) 9 -- Nose gear...
Page 172 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 10 -- Aileron / spoiler ........CHECK (Condition / Free movement / Deflection) 11 -- Flap...
Page 173 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 10 -- Static dischargers ....... . CHECK (Condition) 11 -- Tail cone...
Page 174: Before Starting Engine
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (1/3) (Refer to Supplement 41 for TBM 700C2 airplane) CAUTION ”BLEED” SWITCH “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 175 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (2/3) 9 -- Belts and harnesses (Pilot and passengers) ..FASTENED 10 -- Crash lever ......... . . 11 -- Oxygen supply .
Page 176 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (3/3) 26 -- Access door and (if installed) ”pilot” door WARNING LIGHT DOOR 27 -- Fuel -- Gages ........CHECKED -- Tank selector .
Page 177: 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 or OFF 2 - - ”STARTER”...
Page 178 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 ........WARNING LIGHT AUX BP ON FUEL PRESS...
Page 179 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (3/5) 11 -- Condition lever ........HI / IDLE 12 -- Engine instruments .
Page 180 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (4/5) CAUTION IF ENGINE STAGNATES, INTERRUPT STARTING PROCEDURE : Condition lever ........CUT OFF ”IGNITION”...
Page 181 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (5/5) 50 % -- ”STARTER” switch ........STARTER WARNING LIGHTS IGNITION...
Page 182: 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 183 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 ........WARNING LIGHTS AUX BP ON FUEL PRESS...
Page 184 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (3/5) 11 -- ”SOURCE” selector ........WARNING LIGHT BAT OFF 12 -- Propeller governor lever...
Page 185 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (4/5) CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO ”LO / IDLE” THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE, OVERTEMPERATURE INDICATION APPEARS (MAX.
Page 186 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (5/5) ENGINE START panel -- ”IGNITION” switch ........AUTO -- ”STARTER”...
Page 187: 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 188 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES MOTORING (2/2) 3 -- ”IGNITION” switch ........WARNING LIGHT IGNITION To clear fuel and vapor internally trapped :...
Page 189: 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 190 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 191: 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 -- GYRO INST panel -- All switches ........Pull on the caging knobs when starting the ADI(s).
Page 192 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES AFTER STARTING ENGINE (2/2) 5 -- ”GENERATOR” selector -- On ”MAIN” ....Voltage and current checked when current ≤...
Page 193: In--Flight Available Oxygen Quantity
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES IN- -FLIGHT AVAILABLE OXYGEN QUANTITY Oxygen pressure ........Read Outside air temperature (IOAT) .
Page 194: 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 195: 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 ........WARNING LIGHT PARK BRAKE 2 -- Condition lever...
Page 196 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE TAKEOFF (2/2) -- ”PITOT 1 HTR” switch ....... -- ”PITOT 2 &...
Page 197: Takeoff
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAKEOFF (1/2) (Refer to Supplement 41 for TBM 700C2 airplane) 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 198 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TAKEOFF (2/2) 7 -- PROP O’ SPEED GOVERNOR TEST -- Increase power until propeller RPM reaches 1900 RPM -- PROP O’ SPEED ....TEST : Maintain engaged -- Observe that propeller RPM decreases by 50 to 250 RPM -- PROP O’...
Page 199: 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 CAUTION...
Page 200: 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 CAUTION...
Page 201: Descent
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES DESCENT 1 -- Altimeter settings ......COMPLETE 2 -- ECS panel -- Cabin altitude selector...
Page 202: Before Landing
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES BEFORE LANDING (Refer to Supplement 41 for TBM 700C2 airplane) Long final 1 -- Altimeters ........CHECK 2 -- Fuel -- Gages...
Page 203 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 204: Go--Around
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES GO- -AROUND (Refer to Supplement 41 for TBM 700C2 airplane) 1 -- Simultaneously -- Power lever ......TRQ = 100 % -- Attitude .
Page 205 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES TOUCH AND GO (Refer to Supplement 41 for TBM 700C2 airplane) After wheel touch 1 -- Flaps ..........2 -- Elevator trim .
Page 206 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (1/2) 1 -- Parking brake ........WARNING LIGHT PARK BRAKE 2 -- ”TAXI”...
Page 207 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (1/2) 1 -- Parking brake ........WARNING LIGHT PARK BRAKE 2 -- ”TAXI”...
Page 208: Motoring
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (2/2) 14 -- Fuel -- ”AUX BP” switch ........-- ”FUEL SEL”...
Page 209: Shut--Down
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved CHECK--LIST PROCEDURES SHUT- -DOWN (2/2) 14 -- Fuel -- ”AUX BP” switch ........-- ”FUEL SEL”...
Page 210 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 -- ELECTRIC POWER panel -- ”SOURCE”...
Page 211 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 212 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 213 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 25 -- Voltage ......... . CHECK -- BAT .
Page 214 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 29 -- Oxygen emergency system ... OXYGEN WARNING LIGHT If not, open isolation valve of the oxygen cylinder in R.H. karman. Oxygen emergency system in good operation condition must be imperatively taken on board during all flights, even at low altitude in order to be used in case of smoke in the cabin.
Page 215 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 35 -- ”PITOT 2 & STALL HTR” switch ......PITOT 2 WARNING LIGHTS STALL HTR...
Page 216 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 ......CHECK (Pressure / Attachment) The fire extinguisher is provided with a pressure gage.
Page 217 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 218 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 219 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 12 -- Fuel tank drain (two on each wing) ....DRAIN (Fuel free of water and contamination) In case of water in fuel system, drain it carefully using the four drain...
Page 220 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) Fuselage forward section IV 1 -- Forward compartment -- Inside ........CONTROLLED -- Door .
Page 221: Performance
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 7 -- Air inlets -- Main ..... . No crack - - UNOBSTRUCTED Check for no cracks, which are sometimes put in evidence by traces of soot resulting from exhaust gases.
Page 222 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) R.H. wing V Additional remarks are identical to those of L.H. wing. 1 -- Fuel tank drain (two on each wing) ....DRAIN (Fuel free of water and contamination) 2 -- Main landing gear...
Page 223 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) Fuselage rear section / Empennages VI Check that outside handle of emergency exit is flush with door skin. 1 -- ELT ..........Access to ELT is possible through an inspection door located on R.H.
Page 224 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 10 -- Static dischargers ....... . CHECK (Condition) 11 -- Tail cone...
Page 225: Weight And Balance
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (1/5) (Refer to Supplement 41 for TBM 700C2 airplane) 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 226 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (2/5) If the airplane is equipped with option OPT70 01029 “Provision for TBM 700C2” : -- Pilot seat and R.H. front seat (if occupied) .
Page 227 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (3/5) 15 -- ”NORMAL/MASK” micro inverter ....NORMAL 16 -- ”IGNITION”...
Page 228 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (4/5) 26 -- Access door and (if installed) ”pilot” door WARNING LIGHT DOOR If ”DOOR” warning light is not OFF, open the access door and (if installed) the ”pilot”...
Page 229 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (5/5) 32 -- In case of night flight -- INT LIGHTS panel : ”INSTR” + ”PANEL” ..ADJUSTED -- Navigation lights .
Page 230 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (1/6) CAUTION BEFORE SELECTING SOURCE, CHECK : 1 - - ”IGNITION” switch ..... . . AUTO or OFF 2 - - ”STARTER”...
Page 231 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (2/6) 8 -- Propeller ........AREA CLEAR 9 -- ENGINE START panel -- ”IGNITION”...
Page 232 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (3/6) In case of higher temperature and longer time, stop immediately the starting procedure as indicated in the following caution and inform the maintenance department.
Page 233 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (4/6) Wait ITT < 800°C, then : ”STARTER” switch ....... . BEFORE ANY RESTARTING ATTEMPT, CARRY OUT A MOTORING (Refer to paragraph ”MOTORING”)
Page 234 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (5/6) ENGINE START panel -- ”IGNITION” switch ........AUTO -- ”STARTER”...
Page 235 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (6/6) Engine instruments ..CHECK Ng increasing to 68 % (± 1 %) (Oil pressure / ITT = green sector) NOTE : This behaviour should only be observed with outside low temperature (IOAT <...
Page 236 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 237 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (2/7) 8 -- FUEL panel -- ”AUX BP” switch ........WARNING LIGHTS AUX BP ON FUEL PRESS...
Page 238 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 239 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 240 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 STAGNATES, INTERRUPT STARTING PROCEDURE : Condition lever ........CUT OFF ”IGNITION”...
Page 241 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (6/7) 50 % -- ”STARTER” switch ........STARTER WARNING LIGHTS IGNITION...
Page 242 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (7/7) 16 -- Engine instruments ... CHECK : Ng 68 % (± 1 %) (Oil pressure / Oil temperature / ITT = green sector) 17 -- FUEL panel -- ”AUX BP”...
Page 243 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING (1/3) 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.The fuel is removed in liquid or vapor form, through an airflow intended to dry combustion chamber, turbines and exhaust nozzles.
Page 244 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING (2/3) 2 -- FUEL panel -- Tank selector ........L or R -- ”AUX BP”...
Page 245 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES MOTORING (3/3) 6 -- FUEL panel -- ”AUX BP” switch ........AUX BP ON WARNING LIGHTS FUEL PRESS...
Page 246: 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. Within starter operating limits (continuous max.
Page 247 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 -- Ng .
Page 248 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 WARNING LIGHT AUX BP ON...
Page 249: After Starting Engine
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (1/4) 1 -- GYRO INST panel -- All switches ........Pull on the caging knobs when starting the ADI(s).
Page 250 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (2/4) -- ”R.WINDSHIELD” switch ......Check illumination of the green light located above the switch (except if hot conditions)
Page 251 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (3/4) 5 -- ”GENERATOR” selector For these tests, ”BLEED” switch must be left OFF, to unload the generator circuit. -- On ”MAIN” ....Voltage and current checked when current ≤...
Page 252 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (4/4) 8 -- “RADIO MASTER” switch ......-- VHF/VOR/GPS/TAS/ EGPWS/WX means (if installed) .
Page 253: In--Flight Available Oxygen Quantity
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES IN- -FLIGHT AVAILABLE OXYGEN QUANTITY Oxygen pressure ........Read Outside air temperature (IOAT) .
Page 254: 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 255 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 256: Before Takeoff
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (1/3) 1 -- Parking brake ........WARNING LIGHT PARK BRAKE 2 -- Condition lever...
Page 257 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (2/3) If there is standing water or other contamination on the runway : -- ”INERT SEP” switch ......Left ON WARNING LIGHT INERT SEP...
Page 258 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (3/3) 12 -- Trims -- Pitch ........ADJUSTED -- Yaw .
Page 259 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (1/3) (Refer to Supplement 41 for TBM 700C2 airplane) 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 260 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (2/3) 6 -- Radar switch ....... . . As required 7 -- PROP O’...
Page 261 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TAKEOFF (3/3) 13 -- Landing gear control ..(IAS < 128 KIAS) ... . During the sequence : -- The red warning light flashes ;...
Page 262 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES CLIMB (1/2) (Refer to Supplement 41 for TBM 700C2 airplane) 1 -- Power lever ......ADJUST according to engine operation table - - Chapter 5.7 CAUTION...
Page 263 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 264 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 As indicated in lower part of these tables, reducing propeller RPM is...
Page 265 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 266 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES DESCENT (1/2) 1 -- Altimeter settings ......COMPLETE 2 -- ECS panel -- Cabin altitude selector...
Page 267 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES DESCENT (2/2) 4 -- Windshield misting protection system ... . As required Prior to descent in moist conditions, turn ”AIR FLOW” distributor in DEFOG section and set WINDSHIELD switches to “ON”...
Page 268 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE LANDING (1/2) (Refer to Supplement 41 for TBM 700C2 airplane) Long final 1 -- Altimeters ........CHECK 2 -- Fuel -- Gages...
Page 269 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES BEFORE LANDING (2/2) 7 -- 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 270 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 271 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES GO- -AROUND (Refer to Supplement 41 for TBM 700C2 airplane) 1 -- Simultaneously -- Power lever ......TRQ = 100 % -- Attitude .
Page 272: Touch And Go
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES TOUCH AND GO (Refer to Supplement 41 for TBM 700C2 airplane) After wheels touch 1 -- Flaps ..........Check that flaps have well reached the TO position before increasing power.
Page 273: 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 274 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (1/2) 1 -- Parking brake ........WARNING LIGHT PARK BRAKE 2 -- ”TAXI”...
Page 275 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (1/2) 1 -- Parking brake ........WARNING LIGHT PARK BRAKE 2 -- ”TAXI”...
Page 276 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (2/2) 13 -- Condition lever ........CUT OFF CAUTION IN CASE OF SHUT- -DOWN ON A CONTAMINATED...
Page 277 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved AMPLIFIED PROCEDURES SHUT- -DOWN (2/2) 13 -- Condition lever ........CUT OFF CAUTION IN CASE OF SHUT- -DOWN ON A CONTAMINATED...
Page 278: Description
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 279 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 280 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (3/5) CAUTION SHOULD CONDITIONS REQUIRE IT, APPLY THESE DIRECTIVES FROM BEGINNING OF TAXI ONWARDS CAUTION DO NOT OPERATE THE INERTIAL SEPARATOR IF THE AIRSPEED EXCEEDS 200 KIAS.
Page 281 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (4/5) 3 -- Procedures for holding, approach and landing in icing conditions : -- Minimum recommended speeds are : . Flaps UP 130 KIAS .
Page 282 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (5/5) Cruise speeds may be decreased by 10 %, if cruise power is not changed, or more, if cruise power setting should be decreased due to the additional inertial separator limitations (ITT limitation).
Page 283 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 284 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 285 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 286: Utilization On Runways Covered With Melting Or Not Tamped Snow
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW (1/2) Refer if required to paragraph ”UTILIZATION BY COLD WEATHER AND VERY COLD WEATHER”. Preflight inspection 1 -- Remove any snow or ice from the wings, stabilizers and movable surfaces, landing gear wells and gear doors, as well as flap tracks,...
Page 287 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW (2/2) Takeoff 1 -- Lightly lift up nose wheel during takeoff run in order to reduce the forward resistance due to snow accumulation against the wheel.
Page 288: 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 ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS (1/2) Refer if required to paragraph ”UTILIZATION BY COLD WEATHER AND VERY COLD WEATHER”. Preflight inspection 1 -- Remove any snow or ice from the wings, stabilizers and movable surfaces, landing gear wells and gear doors, as well as flap tracks, actuators and their fairings.
Page 289 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 290: 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°...
Page 291: 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 292 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 293: 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) (4/10) ENVELOPE 2 The procedures hereafter supplement or replace the normal procedures for the airplane use when operating in the ”envelope 2”...
Page 294 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) 6 -- Remove chocks and / or release ties from the airplane.
Page 295 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0° C TO - - 25° C) AND VERY COLD WEATHER (- - 25° C TO - - 40° C) (6/10) 3 -- Engine controls -- ”MAN OVRD”...
Page 296 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0° C TO - - 25° C) AND VERY COLD WEATHER (- - 25° C TO - - 40° C) (7/10) 13 % -- Condition lever .
Page 297 T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0° C TO - - 25° C) AND VERY COLD WEATHER (- - 25° C TO - - 40° C) (8/10) After starting the engine 1 -- On ”ECS”...
Page 298: Envelope 3
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (- - 0° C TO - - 25° C) AND VERY COLD WEATHER (- - 25° C TO - - 40° C) (9/10) ENVELOPE 3 The procedures defined for the ”envelope 2”...
Page 299 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 300: 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 (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 301 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 302: 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 planning the landing, ensure that the field is hard, smooth and dry enough.
Page 303: Operation In Rvsm Conditions
T B M SECTION 4 NORMAL PROCEDURES PILOT’S OPERATING HANDBOOK EASA Approved PARTICULAR PROCEDURES OPERATION IN RVSM CONDITIONS After altitude capture, in altitude hold mode of the autopilot, discrepancy between desired altitude and held altitude must be adjusted using the vertical trim control in order not to exceed ¦...
Page 304 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK SECTION 5 PERFORMANCE TABLE OF CONTENTS Page ACOUSTIC LIMITATION 5.1.1 ........AIRSPEED CALIBRATION 5.2.1 .
Page 305 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 306: Acoustic Limitation
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 EASA.A.010 on 14th July 2004. Rev. 7...
Page 307 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 5.1.2...
Page 308: 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 309 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 ON)
Page 310: Cabin Pressurization Envelope
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.3 - - CABIN PRESSURIZATION ENVELOPE Cabin altitude (feet) 9350 ft cabin 9000 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 Rev.
Page 311 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 5.3.2 Rev. 0...
Page 312: Sat -- Ioat Conversions
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.4 - - SAT - - IOAT 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 313 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 5.4.2 Rev. 0...
Page 314: Stall Speeds
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.5 - - STALL SPEEDS (Refer to Supplement 41 for TBM 700C2 airplane) CONFIG. BANK AIR-- FLIGHT 0° 30° 45° 60° PLANE IDLE WEIGHT Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 4850 lbs...
Page 315 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved INTENTIONALLY LEFT BLANK Rev. 7 Page 5.5.2...
Page 316: 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 Figure 5.6.1 -- WIND COMPONENTS Rev.
Page 317 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 5.6.2 Rev. 0...
Page 318: 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 ON. The torque must be set at or below the value corresponding to the local conditions of flight level and temperature.
Page 319: Maximum Climb Power (Fl ± 200)
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 ON NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed T°...
Page 320: Maximum Climb Power (Fl ² 200)
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 ON NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed T°...
Page 321: Maximum Cruise Power (Fl 200)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Figure 5.7.2 -- ENGINE OPERATION Conditions : Maximum cruise power (FL 200) ≤ Landing gear and flaps UP Np = 2000 RPM -- BLEED ON NOTE : Use preferably recommended cruise power T°...
Page 322 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 ON NOTE : Use preferably recommended cruise power T° (°C) FLIGHT LEVEL (FL) SAT IOAT -- 67...
Page 323: Normal (Recommended) Cruise Power (Fl ± 200)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK Figure 5.7.3 -- ENGINE OPERATION Conditions : Normal (recommended) cruise power (FL ≤ 200) Landing gear and flaps UP Np = 2000 RPM -- BLEED ON T° (°C) FLIGHT LEVEL (FL) IOAT -- 25 -- 15...
Page 324 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 ON T° (°C) FLIGHT LEVEL (FL) SAT IOAT -- 67 -- 56 -- 65 -- 54...
Page 325 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 5.7.8 Rev. 0...
Page 326: Takeoff Distances
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.8 - - TAKEOFF DISTANCES (Refer to Supplement 41 for TBM 700C2 airplane) WEIGHT : 5512 lbs (2500 kg) Associated conditions -- Landing gear DN and flaps TO -- 15° of attitude -- TRQ = 100 % -- Np = 2000 RPM -- BLEED ON -- Hard, dry and level runway -- GR = Ground roll (in ft)
Page 327 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 ON -- Hard, dry and level runway -- GR = Ground roll (in ft) -- D...
Page 328: Climb Performance
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.9 - - CLIMB PERFORMANCE (Refer to Supplement 41 for TBM 700C2 airplane) CLIMB SPEEDS (IAS = 130 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 130 KIAS -- BLEED ON RATE OF CLIMB (ft/min) Pressure...
Page 329: 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 ON RATE OF CLIMB (ft/min) Pressure Airplane altitude...
Page 330: Time, Consumption And Climb
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 ON NOTE : Time, consumption and distance from the 50 ft WEIGHT...
Page 331 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 ON NOTE : Time, consumption and distance from the 50 ft WEIGHT...
Page 332 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 ON NOTE : Time, consumption and distance from the 50 ft WEIGHT...
Page 333: Time, Consumption And Climb
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 ; -- 2 KIAS / 1000 ft then 2000 RPM -- BLEED ON NOTE : Time, consumption and distance from the 50 ft...
Page 334 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 ; -- 2 KIAS / 1000 ft then 2000 RPM -- BLEED ON NOTE : Time, consumption and distance from the 50 ft...
Page 335 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 ; -- 2 KIAS / 1000 ft then 2000 RPM -- BLEED ON NOTE : Time, consumption and distance from the 50 ft...
Page 336: 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 337: 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 338: Cruise Performance
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK 5.10 - - CRUISE PERFORMANCE (Refer to Supplement 41 for TBM 700C2 airplane) Conditions : ISA Weight 5512 lbs (2500 kg) Flight level (FL) IRCR NOCR MXCR LRCR (KTAS) Figure 5.10.1 -- CRUISE PERFORMANCE Rev.
Page 339: 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 ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 340 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 ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 341 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 ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 342 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Maximum cruise Conditions : ISA Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure...
Page 343 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 ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 344 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 ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 345 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 ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 346: 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 ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 347 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 ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 348 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 ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 349 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 ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 350 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 ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 351 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 ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 352 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 ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 353: 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 ON AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg)
Page 354 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 ON AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg)
Page 355 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 ON AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg)
Page 356 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Intermediate cruise Conditions : ISA Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg) (2500 kg) (2800 kg)
Page 357 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 ON AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg)
Page 358 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 ON AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg)
Page 359 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 ON AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg)
Page 360: Long Range Cruise (5512 Lbs -- 2500 Kg) (Altitude ± 24000 Ft)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Long Range Cruise (5512 lbs - 2500 kg) IOAT : ˚C LEGEND : IAS : KIAS Conditions : Landing gear and flaps UP : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Presssure...
Page 361: Long Range Cruise (5512 Lbs -- 2500 Kg) (Altitude ² 24000 Ft)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Long Range Cruise (5512 lbs - 2500 kg) (Cont’d) IOAT : ˚C LEGEND : IAS : KIAS Conditions : Landing gear and flaps UP : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Altitude...
Page 362: Long Range Cruise (6173 Lbs -- 2800 Kg) (Altitude ± 24000 Ft)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Long Range Cruise (6173 lbs - 2800 kg) IOAT : ˚C LEGEND : IAS : KIAS Conditions : Landing gear and flaps UP : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Altitude...
Page 363: Long Range Cruise (6173 Lbs -- 2800 Kg) (Altitude ² 24000 Ft)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK CRUISE PERFORMANCE Long Range Cruise (6173 lbs - 2800 kg) (Cont’d) IOAT : ˚C LEGEND : IAS : KIAS Conditions : Landing gear and flaps UP : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Altitude...
Page 364: 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 ON Vz = 1500 ft/min Vz = 2000 ft/min Vz = 2500 ft/min...
Page 365 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 5.11.2 Rev. 0...
Page 366: 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 ON 30 % FUEL USED DURING HOLDING TIME Weight 4850 lbs (2200 kg) Weight 5512 lbs (2500 kg) Pressure Pressure...
Page 367 T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 5.12.2 Rev. 0...
Page 368: Landing Distances
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved 5.13 - - LANDING DISTANCES (Refer to Supplement 41 for TBM 700C2 airplane) WEIGHT : 6250 lbs (2835 kg) Associated conditions Landing gear DN and flaps LDG Approach speed IAS = 80 KIAS Touch--down speed IAS = 65 KIAS...
Page 369: Weight : 5071 Lbs (2300 Kg)
T B M SECTION 5 PERFORMANCE PILOT’S OPERATING HANDBOOK EASA Approved LANDING DISTANCES WEIGHT : 5071 lbs (2300 kg) Associated conditions Landing gear DN and flaps LDG Approach speed IAS = 80 KIAS Touch--down speed IAS = 60 KIAS Maximum braking without reverse Hard, dry and level runway GR = Ground roll (in ft) = Landing distance (clear to 50 ft) (in ft)
Page 370: General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
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 371 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 6.0.2 Rev. 0...
Page 372 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. A list of equipment available for this airplane is included at the end of this section.
Page 373 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 6.1.2 Rev. 0...
Page 374: 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 375 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 6.2.2 Rev. 0...
Page 376: Baggage Loading
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.3 - - BAGGAGE LOADING There are two baggage compartments : -- one located in the rear of the pressurized cabin provides a maximum baggage capacity between 187 lbs (85 kg) and 220 lbs (100 kg), -- the other one located in the rear fuselage section, non pressurized, between the rear pressure bulkhead at frame C17 and the frame C18 provides a maximum baggage capacity between 55 lbs (25 kg) and 77 lbs...
Page 377 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.3.1 -- BAGGAGE LOADING GRAPH Rev. 7 Page 6.3.2...
Page 378: 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 379 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 380 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.1 -- LOADING SAMPLE (in Kg and Litres) Rev. 7 Page 6.4.3...
Page 381 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.1A -- LOADING SAMPLE (in lbs and us gal) Rev. 7 Page 6.4.4...
Page 382 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK Figure 6.4.2 -- WEIGHT AND BALANCE GRAPH (in Kg and Litres) Rev. 7 Page 6.4.5...
Page 383 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) Page 6.4.6 Rev. 5...
Page 384: Determining Empty Airplane Characteristics
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK DETERMINING EMPTY AIRPLANE CHARACTERISTICS (Refer to Supplement 41 for TBM 700C2 airplane) 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 385 T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 6.4.8 Rev. 0...
Page 386: List Of Equipment
T B M SECTION 6 WEIGHT AND BALANCE PILOT’S OPERATING HANDBOOK 6.5 - - LIST OF EQUIPMENT (Refer to Supplement 41 for equipment specific for TBM 700C2 airplane) 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 387 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) 01 - - SPECIFIC OPTIONAL EQUIPMENT 01019 DME KN63 shield case SOCATA 0.33 231.50...
Page 388 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) 21 - - ENVIRONMENTAL SYSTEM 21- -20 - - Distribution Cabin fan 11--93364 HONEYWELL...
Page 389 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) Overtemperature switch NORMALAIR 0.14 107.95 6083C000--001 GARRETT (0.065) (2.742) Pressure regulator and shut--off NORMALAIR 3.09...
Page 390 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) 22 - - AUTO FLIGHT NOTE : KFC 325 autopilot is included in EFIS equipment (ATA 34) AFC air data computer KDC 222...
Page 391 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 Antenna 16--21B--P3 CHELTON 1.04 272.28 (under fuselage) (0.470) (6.916)
Page 392 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) 23024 Version A (Cont’d) (Cont’d) . GPS antenna KA 92 HONEYWELL 0.26 196.85...
Page 393 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) 23025 . CDI GI 106A 1.46 155.51 (Cont’d) CONTINENT (0.660) (3.950) Version B (antenna on R.H.
Page 394 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) 23026 VHF Data Link KDR510 HONEYWELL . Version A (antenna under wing) 2.45 191.69 (1.113)
Page 395 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) 24 - - ELECTRICAL POWER 24- -30 - - DC generation Ammeter AM99--05 FALGAYRAS...
Page 396 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 25004D Leather upholstering -- version D SOCATA 6.614 212.60...
Page 397 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) 25024B Carpet protecting mat SOCATA 5.73 246.10 (2.600) (6.250) 25024C Carpet protecting mat SOCATA...
Page 398 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) Seats - - Belts (Standard equipment) Seats (6 places with or without oxygen equipment) -- Post--MOD70--019--25 .
Page 399 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- -61 - - Emergency locator transmitter 25030A Three--frequency emergency ARTEX 7.63 350.39...
Page 400 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) O 0153--25C Emergency beacon SERPE--IESM 2.45 347.09 KANNAD 406AF (1.110) (8.816) (installed in tail area) (with...
Page 401 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) 26 - - FIRE PROTECTION 26001B Portable fire extinguisher unit L’HOTELLIER 3.64 192.16...
Page 402 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) 27 - - FLIGHT CONTROLS 27- -10 - - Roll control Roll trim actuator 145700.02 LPMI...
Page 403 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 2022--B WELDON...
Page 404 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) 30 - - ICE AND RAIN PROTECTION Deicer, L.H. horizontal stabilizer SOCATA 4.19 398.42...
Page 405 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) 30- -60 - - Propeller deicing Modular brush assy 3E2044--2 BF GOODRICH 0.44...
Page 406 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) 31 - - INDICATING/RECORDING SYSTEMS 31- -20 - - Independent instruments Chronometer 420000...
Page 407 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 408 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- -35 - - Hydraulic generation Hydraulic power pack : -- from S/N 11 to S/N 227 : 1118--03 6.548 84.65...
Page 409 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) Main wheel 040--27000 PARKER 11.02 204.33 (5.000) (5.190) Parking brake valve T700A3240010 SOCATA 0.33 157.48...
Page 410 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) 33 - - LIGHTS 33- -10 - - Instrument panel lighting L.H.
Page 411 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 Altimeter # 1 UNITED 0.90...
Page 412 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) 34053 Encoding altimeter # 2 KEA 130A KING 0.79 156.89 (R.H.
Page 413 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 34002E Additional horizon 1100--28LS (7F) 2.65 153.54...
Page 414 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) 34056A . Processor WX500 BF GOODRICH 2.27 255.91 (Cont’d) (1.030) (6.500) 34- -42 - - Weather radar...
Page 415 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) 34037I . Antennas (Qty 2) DM 19--2--1 DORNE & 0.40 182.09 (Cont’d)
Page 416 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) 34061B TAS + TAWS system KMH 880 HONEYWELL 15.89 166.02 with indicator on MFD KMD 850 or (7.21)
Page 417 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- -51 - - NAV 1 installation GS--NAV VHF antenna DORNE &...
Page 418 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) 0152--34 Transponder # 1 GTX330D GARMIN 7.50 152.60 Mode S (3.400) (3.876) (European countries only)
Page 419 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) 34014C DME KN63 system, of which : 4.32 209.84 (through NAV1 KN53 and NAV2 (1.960) (5.330)
Page 420 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) 35 - - OXYGEN 35001B Gaseous oxygen system EROS/INTER 24.69 178.19 TECHNIQUE...
Page 421 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) 37 - - VACUUM Air ejector valve 19E17--5A LUCAS 0.66 116.14 (0.300)
Page 422 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) 52 - - DOORS 52002A ”Pilot” door SOCATA 44.092 171.26 (20.000) (4.350)
Page 423 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) 57 - - WINGS 57001A Utilization on runways covered SOCATA 200.00 --7.716...
Page 424 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) 61 - - PROPELLER 61- -10 - - Propeller assembly Propeller (4--blade) HARTZELL 153.22...
Page 425 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 Turboprop engine PT6 A--64 P &...
Page 426 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 427 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 428 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 429 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK TABLE OF CONTENTS (Continued) Page POWERPLANT 7.6.1 ..........7.6.1 TURBOPROP ENGINE OPERATION .
Page 430 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 ..........7.9.9 PRESSURIZATION .
Page 431 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.0.4 Rev. 0...
Page 432 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. Details of other optional systems and equipment are presented in Section 9 ”Supplements”...
Page 433 T B M SECTION 0 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.1.2 Rev. 0...
Page 434 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.2 - - AIRFRAME The TBM 700 is a six--place, low wing airplane. The structure is a semi--monocoque all--metal construction and is equipped with a retractable tricycle landing gear. The pressurized cabin is equipped, on the left side of fuselage, with a ”wide”...
Page 435 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.1 -- CABIN ARRANGEMENT Page 7.2.2 Rev. 0...
Page 436: Ailerons, Spoilers And Pitch Trim Tab
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 437 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Wings characteristics : Area ......... 193.75 sq.
Page 438 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) Position indicator 8) Control selector Figure 7.2.2 (1/2) -- WING FLAPS Rev. 0 Page 7.2.5...
Page 439 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.2.2 (2/2) -- WING FLAPS Page 7.2.6 Rev. 0...
Page 440 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 441 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.2.8 Rev. 0...
Page 442: Instrument Panel
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.3 - - ACCOMODATIONS INSTRUMENT PANEL (Figure 7.3.1) 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 and ancillary electrical systems.
Page 443 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Central pedestal (Figure 7.3.6) The central pedestal under the radio rack, comprises position indicators and trim tabs controls, flaps, engine controls and fuel tank selector. Circuit breakers panel (Figures 7.3.7 and 7.8.2) Circuit breakers for all electrical equipment supplied by bus bars are located on a separate panel installed on the left side of cockpit, near the pilot or on right side when the airplane is equipped with a ”pilot”...
Page 444 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK The system uses : -- the stall warning horn, -- the VMO alarm, -- AP alarms, -- the landing gear control unit, -- the flap geared motor, -- the radar altimeter aural warning. Aural warning box The aural warning box consists of a box including logic circuits, which create the signals heard in the aural warning loud--speaker.
Page 445 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Upper panel (Figure 7.3.2) The upper panel includes following elements : -- the alarm loud--speaker (landing gear up with flaps extended and / or idle, stall), -- the altitude preselection indicating buzzer, -- the autopilot disconnection indicating buzzer, -- the VMO alarm buzzer, -- the ”HORN TEST”...
Page 446 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK The ”HORN TEST” knob allows to test the correct operation of aural warnings : -- Set the ”SOURCE” selector to ”BAT” or to ”GPU”. -- Push and hold the ”HORN TEST” knob : .
Page 447 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.1 -- INSTRUMENT PANEL ASSEMBLY (Typical arrangement) Page 7.3.6 Rev. 0...
Page 448 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Rev. 0 Page 7.3.7...
Page 449 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) L.H. instrument panel emergency lighting 2) Buzzers (AP, landing gear not extended and V alarms) 3) Loud--speakers (radio and stall warning horn) 4) R.H. instrument panel emergency lighting 5) Cockpit floodlight switches (rheostats) 6) R.
Page 450 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.2 (2/2) -- UPPER PANEL AND COCKPIT OVERHEAD PANEL Rev. 0 Page 7.3.9...
Page 451 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 22) ”AP / DISC TRM INT” red 1) Altitude preselection indicator push--button 2) GPS indicator lights 23) Electric pitch trim control 3) Encoding altimeter 1 24) Maps reading tablet 4) Torquemeter 25) Electric rudder trim control 5) Propeller RPM indicator 26) Left station reception--micro...
Page 452 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.3 (2/2) -- LEFT INSTRUMENT PANEL (Typical arrangement) Rev. 7 Page 7.3.11...
Page 453 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Stand--by compass 2) AP mode controller (see Section 9) 3) Advisory panel (Figure 7.3.8) 4) Audio control box 5) COM/NAV/GPS 1 6) COM/NAV/GPS 2 7) Cabin interior lighting rheostats and switches (Figure 7.8.7) 8) ”RADIO MASTER”...
Page 454 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.4 (2/2) -- CENTRAL INSTRUMENT PANEL (Typical arrangement) Rev. 0 Page 7.3.13...
Page 455 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”FUEL” check and control panel (fuel pressure and quantity indicators, ”FUEL SEL” and ”AUX BP” switches) (Figure 7.7.3) 2) ELT remote control switch 3) ”GYRO 2 mode” indicator 4) Airspeed indicator 2 5) ADI 2 indicator 6) Encoding altimeter 2 7) HSI 2 indicator...
Page 456 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.5 (2/2) -- RIGHT INSTRUMENT PANEL (Typical arrangement) Rev. 0 Page 7.3.15...
Page 457 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Trim tabs indicators 2) Flaps position indicator 3) Propeller governor lever 4) Power lever 5) Flaps control 6) Condition lever 7) Levers friction adjustment 8) Emergency fuel control 9) Manual fuel tank selector (Figure 7.7.2) 10) Roll trim tab control 11) Pitch trim tab control 12) Lock for access door to landing gear emergency pump (Figure 7.5.2)
Page 458 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.6 (2/2) -- PEDESTAL CONSOLE (Typical arrangement) Rev. 0 Page 7.3.17...
Page 459 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.7 -- CIRCUIT BREAKERS PANEL -- Without ”pilot” door Page 7.3.18 Rev. 0...
Page 460 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.7A -- CIRCUIT BREAKERS PANEL -- With ”pilot” door Rev. 0 Page 7.3.19...
Page 461 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK MASTER General warning WARNING upon illumination of red warning light MASTER General warning CAUTION upon illumination of amber warning light Inter turbine temperature ≥ 800°C OIL PRESS Engine oil low pressure ≤ 4.1 bar (60 psi) STARTER Starter generator running (flashing) IGNITION...
Page 462 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.8 (2/2) -- ADVISORY PANEL AND GENERAL ALARMS WARNING LIGHTS Rev. 0 Page 7.3.21...
Page 463: 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 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 464 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.9 -- CABIN ACCESS DOOR Rev. 0 Page 7.3.23...
Page 465 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 466 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Cockpit access door (Figure 7.3.9A) The cockpit access door, so--called ”pilot” door, (if installed) located on the left side of fuselage forward of the wings, opens outside. Retractable footstep makes boarding easier. WARNING AS THE ”PILOT”...
Page 467 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.9A -- COCKPIT ACCESS DOOR (”PILOT” DOOR) Page 7.3.26 Rev. 0...
Page 468 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FWD compartment door The FWD compartment door is located on the airplane left side between the firewall and the front pressure bulkhead. It is hinged at the top. It is maintained in the up position by a compensation rod. Two interlocking--type latches ensure its closing and it is equipped with a lock (same key as for the access door, “pilot”...
Page 469 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.10 -- EMERGENCY EXIT Page 7.3.28 Rev. 0...
Page 470 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Rev. 0 Page 7.3.29...
Page 471: Seats, Belts And Harnesses
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK SEATS, BELTS AND HARNESSES (Refer to Supplement 41 for TBM 700C2 airplane) Cockpit seats (Figure 7.3.11) L.H. and R.H. front seats are mounted on rails attached to the structure. Longitudinal position, height and back--rest tilting of each seat can be adjusted and the arm--rest is hinged.
Page 472: Baggage Compartments
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK BAGGAGE COMPARTMENTS There are two baggage compartments : -- a compartment located in the pressurized cabin between rear passenger seats and rear pressure bulkhead, -- an AFT compartment (non--pressurized) located between the rear pressure bulkhead at frame C17 and the frame C18.
Page 473 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 474 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.11 (2/2) -- SEATS Rev. 0 Page 7.3.33...
Page 475 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.3.12 -- FRONT OR REAR SEAT BELT (with movable straps) AND HARNESSES Page 7.3.34 Rev. 0...
Page 476: 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 477 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 Page 7.4.2 Rev. 0...
Page 478 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.1 (2/2) -- ROLL Rev. 0 Page 7.4.3...
Page 479 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) Aileron trim tab position indicator 7) Trim switch on pedestal console Figure 7.4.2 (1/2) -- LATERAL TRIM Page 7.4.4 Rev.
Page 480 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.2 (2/2) -- LATERAL TRIM Rev. 0 Page 7.4.5...
Page 481 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.4.6 Rev. 0...
Page 482: Pitch Trim
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 483 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 Page 7.4.8 Rev.
Page 484 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.3 (2/2) -- ELEVATOR Rev. 0 Page 7.4.9...
Page 485 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 tab position indicator 7) Pitch trim manual control wheel 8) Pitch trim electrical control Figure 7.4.4 (1/2) -- PITCH TRIM Rev.
Page 486 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.4 (2/2) -- PITCH TRIM Rev. 0 Page 7.4.11...
Page 487 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.4.12 Rev. 0...
Page 488: Rudder Trim
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK RUDDER (Figure 7.4.5) The rudder is hinged on three fittings attached to the vertical stabilizer rear spar. The rudder pedals / rudder linkage is ensured through cables and a rod. Pilot and R.H. station rudder pedal positions are adjustable at each station. The rudder pedal adjustment mechanism (for piloting comfort purposes) includes a manual control located against the external bulkhead beneath the instrument panel and a locking device on the rudder pedals.
Page 489 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 Page 7.4.14 Rev.
Page 490 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.5 (2/2) -- RUDDER Rev. 0 Page 7.4.15...
Page 491 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 6) Rudder trim tab position indicator Figure 7.4.6 (1/2) -- RUDDER TRIM Page 7.4.16 Rev.
Page 492 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.4.6 (2/2) -- RUDDER TRIM Rev. 0 Page 7.4.17...
Page 493 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.4.18 Rev. 0...
Page 494: Landing Gear
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 495: Hydraulic Pressure
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK HYDRAULIC PRESSURE Hydraulic pressure required for landing gear operation is accomplished : -- 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 496 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 Rev.
Page 497 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 498 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.2 -- EMERGENCY LANDING GEAR EXTENSION CONTROL Rev. 7 Page 7.5.5...
Page 499: 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 500 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) Rev. 8 Page 7.5.7...
Page 501 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) Page 7.5.8 Rev. 0...
Page 502: 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 503 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 Page 7.5.10 Rev.
Page 504 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.5 (2/2) -- BRAKE SYSTEM Rev. 0 Page 7.5.11...
Page 505 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.5.6 -- PARKING BRAKE Page 7.5.12 Rev. 0...
Page 506: Turboprop Engine Operation
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.6 - - POWERPLANT TURBOPROP ENGINE OPERATION (Figure 7.6.1) The PRATT & WHITNEY CANADA turboprop engine (PT6A--64 type) is a free turbine engine developing thermodynamic power of 1580 SHP, derated to 700 SHP. Intake air enters engine through an annular casing and is then ducted toward compressor.
Page 507 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 508 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.6.1 (2/2) -- POWER PLANT Rev. 0 Page 7.6.3...
Page 509: 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 510 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 511 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 512: Engine Instruments
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ENGINE INSTRUMENTS (Figure 7.6.3) Engine indicating panel consists of the following instruments : a torquemeter, a propeller speed indicator, an ITT indicator, a gas generator speed indicator, an oil pressure and temperature indicator, an Engine Trend Monitoring (ETM) indicator/computer.
Page 513 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK The most important information can be recorded anytime in the ETM system. Once analyzed, these records make it possible to immediately detect any deviations of the operating parameters and thus schedule appropriate maintenance operations.
Page 514 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Torque indicator 2) ”PROP O’SPEED TEST” knob 3) Propeller indicator 4) ITT indicator 5) ITT test knob 6) Ng indicator 7) Oil pressure and temperature indicator 8) ETM indicator/computer Figure 7.6.3 -- ENGINE INSTRUMENTS Rev.
Page 515 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1 -- DISPLAY The window display of the ETM. It contains two lines, with 12 characters per line. 2 -- RECORD BUTTON This button is used to manually generate an output report 3 -- STOPWATCH START / STOP SWITCH When the stopwatch is activated, this switch starts and stops it...
Page 516 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.6.4 (2/2) -- ETM INDICATOR/COMPUTER Rev. 0 Page 7.6.11...
Page 517: 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 518 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.6.5 -- ENGINE STARTING Rev. 0 Page 7.6.13...
Page 519: 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, ”STARTER” warning light in advisory panel 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 520: 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 521 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Torque transmitter Torque transmitter is attached on the torque limiter, it measures torque produced by the power turbine by comparing oil pressures (reduction gear and power turbine) and converts pressure difference into a voltage which is applied to torquemeter.
Page 522 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 523 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.6.18 Rev. 0...
Page 524: Fuel System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.7 - - FUEL SYSTEM (Figure 7.7.1) The fuel system comprises fuel tanks, fuel unit, selectors (manual and automatic), electric and mechanical boost pumps, engine fuel system, gaging installation, monitoring installation and drains. FUEL TANKS Fuel tanks are formed by sealed casings in each wing.
Page 525: Electric Boost Pump
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Flow divider 2) Flowmeter 3) Collector tank 4) Fuel regulator 5) High pressure pump (HP) 6) Oil to fuel heater 7) Low pressure switch 8) Pressure transmitter 9) Fuel jet 10) Main mechanical boost pump 11) Electric boost pump 12) Fuel filter...
Page 526 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.1 (2/2) -- FUEL SYSTEM Rev. 0 Page 7.7.3...
Page 527 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK AUTOMATIC TANK SELECTOR (Figures 7.7.2 and 7.7.3) Automatic tank selection allows, without pilot’s intervention, feeding the engine from one tank to the other in predetermined sequences. These sequences depend on airplane configuration (ground, in--flight, fuel low level warning lights illuminated).
Page 528 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK NOTE : The manual selector is driven by the fuel unit and is positioned on ”R ” or ”L” mark corresponding to the tank selected by the sequencer. Therefore, the pilot continuously knows the tank which is operating. Test for system proper operation ”SHIFT”...
Page 529 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.2 -- MANUAL SELECTOR OF FUEL TANKS Page 7.7.6 Rev. 0...
Page 530 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.3 -- FUEL CONTROL PANEL Rev. 0 Page 7.7.7...
Page 531: 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 532: Fuel Monitoring Installation
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FUEL MONITORING INSTALLATION (Figure 7.7.3) Monitoring installation comprises pressure indicator and warning lights grouped on advisory panel. Pressure indicator is attached on ”FUEL” panel ; it indicates fuel pressure at main booster pump outlet. Indications provided by illumination of warning lights on advisory panel : -- ”FUEL OFF”...
Page 533: Fuel System Draining And Clogging Indicator
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FUEL SYSTEM DRAINING AND CLOGGING INDICATOR (Figure 7.7.4) The fuel system comprises five drain points, a drain on the filter bowl, two drain valves on each tank, located on wing lower surface, one at wing root and the other past main landing gear well.
Page 534 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.7.4 (2/2) -- FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Rev. 0 Page 7.7.11...
Page 535 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.7.12 Rev. 0...
Page 536: Electrical System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.8 - - ELECTRICAL SYSTEM (Figures 7.8.1 and 7.8.5) 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 537: 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 538 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Rev. 0 Page 7.8.3...
Page 539: Emergency Use
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK DISTRIBUTION Airplane electrical systems are connected to ”BUS” bars and protected by circuit breakers located on L.H. side panel, near the pilot (See Figure 7.8.3) or on R.H. side panel, if ”pilot” door installed (See Figure 7.8.3A). In case of overload of a system, the circuit breaker triggers and switches the system off.
Page 540 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.1 -- ELECTRICAL DIAGRAM Rev. 0 Page 7.8.5...
Page 541 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (1/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Page 7.8.6 Rev. 0...
Page 542 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.2 (2/2) -- ELECTRICAL DISTRIBUTION OF BUS BARS Rev. 0 Page 7.8.7...
Page 543 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK AP / TRIMS AP & trims general protec. FUEL GAGE 1 L.H gage protection RUD TRIM Rudder trim protection FUEL GAGE 2 R.H gage protection AIL TRIM Aileron trim protection FUEL SEL Timer protection PITCH TRIM Pitch trim protection...
Page 544 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 (2/3) -- CIRCUIT BREAKER PANEL (”HONEYWELL” typical arrangement) Rev. 0 Without ”pilot” door Page 7.8.9...
Page 545 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 (”GARMIN” typical arrangement) Page 7.8.10 Without ”pilot” door Rev.
Page 546 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Rev. 0 Page 7.8.11...
Page 547 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ESS BUS TIE Essential bus NORM & PULSE Pulse lite system (if installed) EMER switch SYST protection LDG GR LDG general protection L.H. wing leading edge lighting LIGHT and lighting test protection FLAPS Flaps protection STROBE...
Page 548 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 7.8.3A (2/3) -- CIRCUIT BREAKER PANEL (”HONEYWELL” typical arrangement) Rev. 0 With ”pilot” door Page 7.8.13...
Page 549 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 7.8.3A (3/3) -- CIRCUIT BREAKER PANEL (”GARMIN” typical arrangement) Page 7.8.14 With ”pilot” door Rev.
Page 550 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INDICATING (Figure 7.8.4) Electrical system indicating consists of a voltmeter and an ammeter located on the upper panel, as well as warning lights grouped on advisory panel. The voltmeter indicates the voltage with generator connected to main bus bar.
Page 551 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK PROTECTION - - SAFETY (Figure 7.8.5) The electrical power center provides systems protection in case of : -- overvoltage coming from the starter generator, the stand--by generator or the ground power receptacle -- short--circuit in starter generator feeder -- starter generator undervoltage In case of disconnection of starter generator or stand--by generator following...
Page 552 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Ammeter 2) Voltmeter 3) General flashing red and amber warning lights 4) Electric system warning lights on the ”ADVISORY PANEL” 5) Battery temperature indicator (if installed) 6) ”BAT TEMP TEST” push--button (if installed) Figure 7.8.4 (1/2) -- INDICATING Rev.
Page 553 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.4 (2/2) -- INDICATING Page 7.8.18 Rev. 0...
Page 554 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 7.8.5 -- ELECTRICAL CONTROL Rev. 0 Page 7.8.19...
Page 555: Exterior Lighting
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK EXTERIOR LIGHTING (Figure 7.8.6) 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 556 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 557 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 7) Pulse lite system switch (if installed) Figure 7.8.6 (1/2) -- EXTERNAL LIGHTING CONTROLS Page 7.8.22 Rev.
Page 558 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.6 (2/2) -- EXTERNAL LIGHTING CONTROLS Rev. 0 Page 7.8.23...
Page 559: Interior Lighting
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTERIOR LIGHTING (Figure 7.8.7) Interior lighting consists of access, cabin, instrument panel, instruments, baggage compartment and emergency lighting. Access lighting Access lighting consists of two floodlights located on the ceiling upholstering (one at the level of the access door, the other at the level of the storage cabinet) and the L.H.
Page 560 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Emergency lighting Emergency lighting consists of two swiveling floodlights located on the upper duct above front seats. It illuminates instrument panel assembly in case of visor lighting and / or instrument integrated lighting failure. The rheostat located near R.H.
Page 561 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Instrument lighting switch (rheostat) 2) Instrument panel lighting switch (rheostat) 3) Cabin lighting switch (rear seats reading light) 4) Access door, baggage compartment and FWD dome light (delayed breaker) push--button 5) Emergency lighting switch (rheostat) Figure 7.8.7 (1/2) -- INTERNAL LIGHTING CONTROLS Page 7.8.26...
Page 562 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.8.7 (2/2) -- INTERNAL LIGHTING CONTROLS Rev. 0 Page 7.8.27...
Page 563 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.8.28 Rev. 0...
Page 564: 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 the temperature and flow--pressure regulation system (ACS), the vapor cycle cooling system (VCCS), control and check systems and distribution. Temperature and flow- -pressure regulation system Air necessary for conditioning is picked up from the engine.
Page 565 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Vapor cycle cooling system The 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 comprises : -- A high pressure pack consisting of : .
Page 566 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK The fan provides air circulation in the cabin through the evaporator. It is attached under the floor, on R.H. side, between frames C14 and C15. The fan is supplied by the “BUS 4” bar and protected by the CB 111 ”FAN” circuit breaker.
Page 567 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Heat exchanger/cooling turbine 21) Cabin differential pressure pack switch 2) Water separator 22) Auxiliary volume tank 3) Check valve 23) Emergency air supply 4) Duct overtemperature switch 24) Controller 5) Duct temperature sensor 25) Compressor/condenser pack 6) Demisting outlets 26) Pressure...
Page 568 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.1 (2/2) -- AIR CONDITIONING Rev. 2 Page 7.9.5...
Page 569 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK When vapor cycle cooling system operation is requested by the controller, the compressor pressurizes the refrigerant and discharges it to the condenser heat exchanger through the HP pressure switch. At the condenser heat exchanger outlet, refrigerant cooled by the condenser fan flows through the receiver drier to the thermal expansion valve located at the evaporator heat exchanger inlet.
Page 570 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Distribution Conditioned air enters the distribution box from where it is dispatched either into the cabin through two outlets located at the level of rudder pedals, through a row of ports located on the lower section of the L.H. and R.H. side upholstery or through the demisting outlets.
Page 571 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK VAPOR CYCLE COOLING SYSTEM The “AIR COND” switch has three positions : -- “OFF” No automatic regulation of cabin temperature. -- “FAN ONLY” : Controls only cabin fan operation. -- “ON” Controls operation of the cabin fan and automatic regulation of cabin temperature.
Page 572 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 573 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Check valve 2) Cabin differential pressure switch 3) Advisory panel 4) Outflow valve 5) Safety valve 6) Depressurization valve 7) Landing gear switch (airplane on ground) 8) Pressure controller 9) Cabin altitude switch 10) Auxiliary volume tank Figure 7.9.2 (1/2) -- PRESSURIZATION Page 7.9.10...
Page 574 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.2 (2/2) -- PRESSURIZATION Rev. 0 Page 7.9.11...
Page 575 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Amber warning light 2) Warning light test push--button 3) ”BLEED” switch -- “ON/OFF/RST” 4) “AIR COND” switch -- “ON/FAN ONLY/OFF” 5) “FAN FLOW” switch -- “AUTO/LO” 6) ”DUMP” switch 7) “AIR FLOW” distributor -- “HOT/DEFOG/CABIN” 8) ”CABIN TEMP/˚C”...
Page 576 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.9.3 (2/2) -- ”ECS” CONTROL AND CHECK PANEL Rev. 5 Page 7.9.13...
Page 577 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.9.14 Rev. 0...
Page 578: Emergency Oxygen System
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.10 - - EMERGENCY OXYGEN SYSTEM (Figure 7.10.1) The gaseous oxygen system will be used by the crew and the passengers, when the cabin altitude is greater than 10000 ft following a loss of pressurization or in case of cabin air contamination.
Page 579 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Microphone switch Figure 7.10.1 -- EMERGENCY OXYGEN SYSTEM Page 7.10.2 Rev. 0...
Page 580 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 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” switch) to permit the supply of the front seats occupiers masks, -- a two--position valve “ON/OFF”...
Page 581: Flight Above 15000 Ft With Emergency Descent
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK WARNING DO NOT SMOKE DURING OXYGEN SYSTEM USE. OIL, GREASE, SOAP, MAKE UP, LIPSTICK AND ANY OTHER GREASY SUBSTANCES CONSTITUTE A SERIOUS FIRE OR BURNING HAZARD, WHEN ON CONTACT WITH OXYGEN FLIGHT ABOVE 15000 FT WITH EMERGENCY DESCENT Number of OUTSIDE TEMPERATURE...
Page 582: When Required To Remain Above 15000 Ft Due To Minimum "En Route" Altitude
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK WHEN REQUIRED TO REMAIN ABOVE 15000 FT DUE TO MINIMUM ”EN ROUTE” ALTITUDE Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C...
Page 583: Flight Between 15000 Ft And 10000 Ft
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK FLIGHT BETWEEN 15000 FT AND 10000 FT Number of OUTSIDE TEMPERATURE occupants 110˚F/ 90˚F/ 70˚F/ 50˚F/ 30˚F/ 10˚F/ --10˚F/ Cockpit Cabin 43˚C 32˚C 21˚C 10˚C --1˚C --12˚C --23˚C 1333 1282 1231 1181 1131 1083...
Page 584: 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 the altimeters, airspeed and vertical speed indicators. They also provide a static pressure reference to the ∆P cabin and to the Autopilot system Air Data Computer (ADC).
Page 585 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) Pitot 1 2) Pitot 2 3) Pitot 2 dynamic drain 4) Pitot 1 dynamic drain 5) V detector 6) Static drain 7) Emergency static drain 8) Static drain 9) FWD pressure bulkhead 10) Airspeed indicator 1 11) Encoding altimeter 1 12) Vertical speed indicator 1...
Page 586 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.11.1 (2/2) -- AIR DATA SYSTEM Rev. 0 Page 7.11.3...
Page 587: 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 and also supplies the V warning.
Page 588: 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 stand--by attitude indicator, the cabin pressurization and the leading edge deicing.
Page 589 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 warning light (Figure 7.3.8) Figure 7.12.1 (1/2) -- VACUUM SYSTEM Page 7.12.2 Rev. 0...
Page 590 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.12.1 (2/2) -- VACUUM SYSTEM Rev. 0 Page 7.12.3...
Page 591: Gyroscopic Instruments Control
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.12.2 -- GYROSCOPIC INSTRUMENTS CONTROL Page 7.12.4 Rev. 0...
Page 592: Suction Gage
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK GYROSCOPIC INSTRUMENTS CONTROL (Figure 7.12.2) Gyroscopic instruments : electrical attitude gyros, HSI, RMI, ADI, etc... are controlled by switches located on instrument panel upper strip. SUCTION GAGE The suction gage is calibrated in inches of mercury and indicates the suction available for operation of the attitude indicator.
Page 593 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK INTENTIONALLY LEFT BLANK Page 7.12.6 Rev. 0...
Page 594: 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 595: 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 596: 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 airspeed indicators and the stall warning sensor are electrically heated. This deice equipment must be used even during flight into non--icing conditions ;...
Page 597 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Figure 7.13.1 -- DEICING CONTROL AND CHECK PANEL Page 7.13.4 Rev. 0...
Page 598: Radio Master And Ground Communication
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 7.14 - - RADIO MASTER AND GROUND COMMUNICATION (Figure 7.14.1) The electrical supply of radio communication and radio navigation equipment assembly is controlled by the ”RADIO MASTER” switch located on the ”INT LIGHTS”...
Page 599 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK 1) ”RADIO MASTER” switch 2) ”GND CLR” (ground clearance) ground communication indicator light Figure 7.14.1 -- RADIO MASTER AND GROUND COMMUNICATION Page 7.14.2 Rev. 0...
Page 600: 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 601: Cabin Fire Extinguisher
T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK CABIN FIRE EXTINGUISHER The fire extinguisher is located behind FWD R.H. seat. It is attached on the floor by means of a quick--disconnect support. A pressure gage allows checking the fire extinguisher condition. Follow the recommendations indicated on the extinguisher.
Page 602 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK A red indicator light located above locator transmitter switch and a buzzer located in the fuselage rear section indicate the emergency locator transmitter is transmitting. Reset after an inadvertent activation a) The keeps 1) Set remote control switch or ELT transmitting...
Page 603 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK CABIN FIRE EXTINGUISHER The fire extinguisher is located behind FWD R.H. seat. It is attached on the floor by means of a quick--disconnect support. A pressure gage allows checking the fire extinguisher condition. Follow the recommendations indicated on the extinguisher.
Page 604 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK Reset after an inadvertent activation a) The keeps 1) Set remote control switch or ELT switch to “ON”. transmitting emergency signal. b) On remote control box, red indicator light flashes. c) On ELT, red indicator light flashes.
Page 605 T B M SECTION 7 DESCRIPTION PILOT’S OPERATING HANDBOOK ELT KANNAD 406 AF Operation of the emergency locator transmitter is obtained as follows : -- from the instrument panel by setting ”ON/ARMED/RESET--TEST” remote control switch to “ON” (locator transmitter ”ARM/ON/OFF” switch set to “ARM”), -- from the locator transmitter by setting its ”ARM/ON/OFF”...
Page 606 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 607 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 608 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 609 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.1.2 Rev. 0...
Page 610: 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 611 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.2.2 Rev. 0...
Page 612 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 and supplemental data covering optional equipment installed in the airplane (refer to Section 9 “Supplements” and pilot’s guides). In addition, the owner may purchase the following : -- Maintenance Manual -- Wiring Manual...
Page 613 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.3.2 Rev. 0...
Page 614: 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 615 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.4.2 Rev. 0...
Page 616: 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 617 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.5.2 Rev. 0...
Page 618: 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 619 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.6.1 -- TURNING ANGLE LIMITS Page 8.6.2 Rev. 0...
Page 620: 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 airplane inside, or leave sun visors down against windshield when airplane on ground. The reflected heat from these items causes a temperature increase which accelerates the crack growth or crazing and may cause the formation of bubbles in the inner layer of multilayer windshields.
Page 621 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.6.2 -- CONTROL LOCK DEVICE Page 8.6.4 Rev. 0...
Page 622: 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 623 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.6.6 Rev. 0...
Page 624: Engine Oil
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE 8.7 - - SERVICING MAINTENANCE In addition to the preflight inspection (refer to Section 4, ”Normal Procedures”), servicing, inspection and test requirements for the airplane are detailed in the Maintenance Manual. Maintenance Manual outlines all items which require servicing, inspection, testing or overhaul.
Page 625 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Refill through the system filling inlet which is located on the engine upper rear part. A gage located on the filling cap indicates oil level and is calibrated in quarts to maximum level under cold conditions ”MAX COLD”...
Page 626 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 627 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 628 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 629 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Figure 8.7.3 -- ADDITIVE MIXING RATIO (EGME or DIEGME) Page 8.7.6 Rev. 0...
Page 630: Landing Gear
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE LANDING GEAR (Refer to Supplement 41 for TBM 700C2 airplane) Nose gear tire : 5.00--5 10 PR -- Inflation pressure : 98 psi (6.7 bars) * Main gear tires : 18 5.5 8 PR -- Inflation pressure : 125 psi (8.6 bars) * Nose gear shock absorber : Fill with hydraulic fluid AIR 3520 B (MIL.H5606E) ;...
Page 631 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE OXYGEN The replenishment device of the oxygen cylinder is installed directly on the cylinder head. It consists of a charging valve and of a pressure gage graduated from 0 to 2000 PSIG. A chart -- see Figure 8.7.4, located on the inside of the cylinder service door, gives the cylinder charge maximum pressure according to the environment temperature.
Page 632 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Replenishment procedure WARNING MAKE SURE THAT THE AIRPLANE IS FITTED WITH A 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 633 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE If the pressure on the oxygen cylinder gage is lower, fill the oxygen cylinder. Make sure the area around the oxygen cylinder charging valve is clean. Remove the cap from the charging valve. Make sure the oxygen supply hose is clean and connect it to the charging valve.
Page 634 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE WARNING MASKS SHALL BE REPACKED IN AN AREA FREE OF OIL, GREASE, FLAMMABLE SOLVENTS OR OTHER CONTAMINANTS Inspect and disinfect mask and deployment container with an aqueous solution of Zephiran Chloride (”Scott Aviation” P/N 00--2572) or with disinfection cleaners (”EROS”...
Page 635 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Gently fold reservoir bag lengthwise into thirds (outside edges folded inward over center of bag). Do not crease bag. Fold reservoir bag away from breathing valves and into facepiece. Make sure bag does not cover breathing valves.
Page 636 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE Coil oxygen tubing inside facepiece over reservoir bag. Connect oxygen tubing to manifold oxygen fitting. WARNING MAKE SURE LANYARD PIN IS INSERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED. CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyard pin into corresponding check valve.
Page 637: Etm Datakey Operation
T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE ETM DATAKEY OPERATION The key is inserted into its receptacle in the airplane prior to turning power on and removed after power is turned off. While inserted the reports which are recorded during the flight are electronically written to a memory chip in the key.
Page 638: 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 639: 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 640: 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) (Refer to Supplement 41 for TBM 700C2 airplane) 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 :...
Page 641 T B M SECTION 8 HANDLING, SERVICING PILOT’S OPERATING HANDBOOK AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.9.2 Rev. 0...
Page 642 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF SUPPLEMENTS AND VALIDITIES Supp. Edition Date A -- General From S/N 1 to S/N 433, except S/N 269 31.01.90 ..... . 1 -- ”BENDIX / KING”...
Page 643 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 8 -- ”BENDIX / KING” GC 381A radar graphics interface TBM 700A and TBM 700B From S/N 1 28.02.91 ............. . . 9 -- ”BENDIX / KING”...
Page 644 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 16 -- ”BENDIX / KING” KRA 405 radar altimeter From S/N 1 to S/N 433, except S/N 269 30.09.95 ..... . 17 -- ”BENDIX / KING”...
Page 645 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 24 -- ”NAVCAL” flight inspection system capability TBM 700A From S/N 1 31.07.96 ............. . . 25 -- ”EVENTIDE”...
Page 646 ..... . 40 -- Cargo transportation capability without pilot door TBM 700 airplanes equipped with the large door 15.11.01 ..
Page 647 T B M SECTION 9 SUPPLEMENT A PILOT’S OPERATING HANDBOOK LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 41 -- TBM 700C2 TBM 700C2 From S/N 244, plus S/N 205 and S/N 240 15.02.03 ....42 -- “HONEYWELL”...
Page 660 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SUPPLEMENT ”BFG” WX- -500 OR WX- -950 OR WX- -1000 OR 1000+ OR 1000E STORMSCOPE TABLE OF CONTENTS Page -- GENERAL ........9.6.2 -- LIMITATIONS .
Page 661 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 1 GENERAL This supplement supplies information to the pilot about limitations, normal and emergency procedures when the optional ”BFG” WX--500 or WX--950 or WX--1000 or 1000+ or 1000E stormscope is installed on the TBM airplane. The stormscope must be used within limits of this supplement.
Page 662 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE -- The Stormscope ”BFG” Pilot’s Handbook, Series II, No. 75--0299--7690--1 (WX--1000 or 1000+ or 1000E), -- The WX--950 Pilot’s guide, Series II, No. 009--10951--001, -- The WX--500 Pilot’s guide, Series II, No. 009--11501--001 and the ”GARMIN”...
Page 663 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 4 NORMAL PROCEDURES Normal operating procedures of the ”BFG” stormscope are outlined in : -- the Pilot’s Handbook, Series II, No. 75--0299--7690--1 at its last revision for ”BFG” stormscope model WX--1000 or 1000+ or 1000E -- the WX--950 Pilot’s Guide, Series II, No.
Page 664 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 6 WEIGHT AND BALANCE Informations hereafter supplement the ones given for the standard airplane in Section 6 ”Weight and balance” of the basic Pilot’s Operating Handbook. WEIGHT EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg) 34 - - NAVIGATION...
Page 665 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE WEIGHT EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg) Stormscope WX--500 4.94 232.28 -- shared with the GNS 530 GPS or with (2.240) (5.900) the KMD 850 or GMX 200 MFD (OPT 70 34056A) Stormscope WX--500 4.94...
Page 666 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE SECTION 7 DESCRIPTION The ”BFG” (Series II) stormscope, weather mapping system provides a visual screen readout of the electrical discharges associated with thunderstorms. This information with proper interpretation, will allow the pilot to detect severe thunderstorm activity. A series of green dots or of strike points will be displayed on the screen to indicate the electrical discharge areas.
Page 667 T B M SUPPLEMENT 6 ”BFG” STORMSCOPE INTENTIONALLY LEFT BLANK Rev. 6 Page 9.6.8...
Page 738 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER SUPPLEMENT ”BENDIX / KING” KRA 405 RADAR ALTIMETER TABLE OF CONTENTS Page -- GENERAL ........9.16.2 -- LIMITATIONS .
Page 739 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER SECTION 1 GENERAL This supplement provides information necessary for airplane utilization when the ”BENDIX / KING” KRA 405 radar altimeter is installed on TBM airplane not equipped with “GARMIN” G1000 system. The radar altimeter provides the pilot with altitude information within --20 ft and 2500 ft.
Page 740 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER SECTION 4 NORMAL PROCEDURES The normal procedures given hereafter complete those of the standard airplane described in Section 4 ”Normal procedures” of the basic Pilot’s Operating Handbook. After engine starting : 1.
Page 741 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER SECTION 5 PERFORMANCE The installation of the ”BENDIX / KING” KRA 405 radar altimeter does not change the basic performance of the airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook. SECTION 6 WEIGHT AND BALANCE Weight and balance corresponding to the ”BENDIX / KING”...
Page 742 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER INTENTIONALLY LEFT BLANK Rev. 3 Page 9.16.5...
Page 743 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER SECTION 7 DESCRIPTION STANDARD VERSION : KNI 415 INDICATOR (Figure 9.16.1) The DH lamp can be disabled by depressing it and rearmed by depressing it once again. 1) DH lamp 2) Flag 3) Indicator pointer 4) Altitude scale...
Page 744 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER Figure 9.16.1 (2 / 2) -- KNI 415 INDICATOR Rev. 3 Page 9.16.7...
Page 745 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER EFIS VERSION (Figure 9.16.2) 1) Radar altimeter altitude display 2) DH annunciator 3) Selected decision height 4) DH selection pull--knob 5) TEST button Figure 9.16.2 (1 / 2) -- RADAR ALTIMETER : EFIS VERSION WITHOUT KNI 415 INDICATOR Rev.
Page 746 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER Figure 9.16.2 (2 / 2) -- RADAR ALTIMETER : EFIS VERSION WITHOUT KNI 415 INDICATOR Rev. 3 Page 9.16.9...
Page 747 T B M SUPPLEMENT 16 ”BENDIX / KING” KRA 405 RADAR ALTIMETER COMBINED VERSION The radar altimeter information given in the EADI system are a recopy of the indications and selections made on the KNI 415 indicator. Rev. 3 Page 9.16.10...
Page 748 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR SUPPLEMENT ”BENDIX/KING” RDR 2000 VERTICAL PROFILE WEATHER RADAR TABLE OF CONTENTS Page -- GENERAL 9.22.2 ..........-- LIMITATIONS 9.22.2 .
Page 749 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR SECTION 1 GENERAL This supplement supplies information necessary for the operation of the airplane when the optional ”BENDIX/KING” RDR 2000 vertical profile color weather radar system is installed in the TBM airplane. SECTION 2 LIMITATIONS These limitations supplement those of standard airplane described in...
Page 750 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR 2.3 - - RDR 2000 weather radar interfaced with GMX 200 multi- -function display The ”BENDIX/KING” RDR 2000 Pilot’s Guide P/N 006--08755--0000 and the “GARMIN” GMX 200 Pilot’s Guide P/N 190--00607--02 at their latest revision shall be readily available to the pilot whenever the operation of the radar system is predicted.
Page 751 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR TAKE OFF -- Radar As required ..........If the radar is switched ”ON”...
Page 752: Bendix/King" Rdr 2000
T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR SECTION 5 PERFORMANCE Installation of ”BENDIX/KING” RDR 2000 vertical profile weather radar system results in a 5 KIAS decrease in maximum cruise performance and a 3 KIAS decrease in Long Range cruise performance described in Section 5 ”Performance”...
Page 753 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR SECTION 7 DESCRITION 7.1 - - RDR 2000 weather radar not interfaced with multi- -function display (KMD 850 or GMX 200) All modes and controls, as well as radar clutter display are arranged on a specific screen.
Page 754 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR Figure 9.22.1 (2/2) -- Indicator Rev. 2 Page 9.22.7...
Page 755 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR OPERATIONAL CONTROLS Controls brightness of the indicator display. Alternately selects between weather (Wx) and ”weather--alert” (WxA) modes of operation. ”Wx” or ”WxA” will appear on the lower left of the display.
Page 756 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR Radar switch--on/off. The test pattern is displayed on the indicator, no transmission occurs. After 30 seconds in this mode, the system is in a state of readiness. No radar transmission occurs, and the antenna is parked in the down position.
Page 757 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR 7.2 - - RDR 2000 weather radar interfaced with KMD 850 multi- -function display : KMD 850 radar function selection Figure 9.22.2 -- KMD 850 Multi--function display When the KMD 850 is set to radar function, equivalences between KMD 850 and radar standard operational controls described in chapter 7.1 are as follows : RDR 2000 STANDARD...
Page 758 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR 7.3 - - RDR 2000 weather radar interfaced with GMX 200 multi- -function display (1) “WX” : GMX 200 radar function selection Figure 9.22.3 -- GMX 200 Multi--function display When the GMX 200 is set to radar function, equivalences between GMX 200 and radar standard operational controls described in chapter 7.1 are as follows : RDR 2000 STANDARD...
Page 759 T B M SUPPLEMENT 22 “BENDIX/KING” RDR 2000 WEATHER RADAR Post- -MOD70- -125- -23 Radar setting to ON or OFF is performed by using the “RADIO MASTER” switch. Page 9.22.12 Rev. 2...
Page 776 T B M SUPPLEMENT 28 ”BFG” SKYWATCH TRAFFIC ADVISORY SYSTEM SUPPLEMENT ”BFG” SKYWATCH SKY 497 OR SKY 899 TRAFFIC ADVISORY SYSTEM TABLE OF CONTENTS Page -- GENERAL ........9.28.3 -- LIMITATIONS .
Page 777 T B M SUPPLEMENT 28 ”BFG” SKYWATCH TRAFFIC ADVISORY SYSTEM INTENTIONALLY LEFT BLANK Rev. 1 Page 9.28.2...
Page 778: 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 ”BFG” SKYWATCH SKY 497 OR SKY 899 TRAFFIC ADVISORY SYSTEM. The SKYWATCH traffic advisory system relies on information obtained from nearby aircraft transponders.
Page 779: Normal Procedures
T B M SUPPLEMENT 28 ”BFG” SKYWATCH TRAFFIC ADVISORY SYSTEM SECTION 4 NORMAL PROCEDURES Normal operating procedures of the ”BFG” SKYWATCH traffic advisory system are outlined in : -- the Pilot’s Guide for the ”BFG” SKYWATCH traffic advisory system, Model SKY 497 P/N 009--10801--001 Rev. B dated 06/00 or any applicable following edition -- the Pilot’s Guide for the ”BFG”...
Page 780: Weight And Balance
T B M SUPPLEMENT 28 ”BFG” SKYWATCH TRAFFIC ADVISORY 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...
Page 781: Description
T B M SUPPLEMENT 28 ”BFG” SKYWATCH TRAFFIC ADVISORY SYSTEM SECTION 7 DESCRIPTION The SKYWATCH is an airborne Traffic Advisory System (TAS). It monitors the airspace around your aircraft and advises the flight crew where to look for transponder equipped aircraft that may pose a collision threat. SKYWATCH SKY 497 The traffic can be displayed on the stormscope display, whether a stormscope system is installed or not.
Page 782 T B M SUPPLEMENT 28 ”BFG” SKYWATCH TRAFFIC ADVISORY SYSTEM The Traffic Advisory (TA) criteria, which initiates a visual and/or an aural alert, are (sensitivity level B) : -- detection of an intruder aircraft within a 0.55 NM horizontal radius and a ±...
Page 783 T B M SUPPLEMENT 28 ”BFG” SKYWATCH TRAFFIC ADVISORY SYSTEM TEST : Held position for test ST--BY/OPR : 1st press : Skywatch stand--by 2nd press : OPR selection Figure 9.28.1 -- SKYWATCH SKY 899 remote control : EFS 40 display impossible ST--BY/OPR : Skywatch stand--by TEST/MODE : 1st case : When the SKY 899 is in stand--by, tests the Skywatch...
Page 784: General
T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY SUPPLEMENT CARGO TRANSPORTATION CAPABILITY TABLE OF CONTENTS Page -- GENERAL 9.30.3 ..........-- LIMITATIONS 9.30.3 .
Page 785 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY INTENTIONALLY LEFT BLANK Page 9.30.2 Rev. 0...
Page 786: Limitations
T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY SECTION 1 GENERAL This supplement is intended to inform the pilot about the limitations, description and operations necessary to load the airplane in order to perform cargo transportation. For this utilization, the freight is installed in the cabin aft of the front seats. SECTION 2 LIMITATIONS The limitations hereafter supplement those of the standard airplane...
Page 787 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY FREIGHT WEIGHT LIMITATIONS Bulk freight [max. density 6.24 lb/cu.ft (100 kg/m )] : -- between the two partition nets 441 lbs (200 kg) ....-- aft of the rear partition net 220 lbs (100 kg) .
Page 788 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY PLACARDS (1) On the raiser at frame 13bis, inside the cabin (2) Under L.H. front side window Rev. 2 Page 9.30.5...
Page 789: Emergency Procedures
T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY SECTION 3 EMERGENCY PROCEDURES The installation of the option ”CARGO TRANSPORTATION CAPABILITY” does not change the basic emergency procedures of the airplane described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook.
Page 790: Weight And Balance
T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the information given for the standard airplane in Section 6 ”Weight and Balance” of the basic Pilot’s Operating Handbook, when the airplane is equipped with the option ”CARGO TRANSPORTATION CAPABILITY”.
Page 791 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY WEIGHT per unit STANDARD OR EQUIPMENT OPTIONAL EQUIPMENT SUPPLIER (kg) Stairway SOCATA 9.921 252.36 (4.500) (6.410) Cabin and baggage compartment SOCATA 23.369 234.02 carpets (10.600) (5.944) JEPPESEN cabinet -- Composite SOCATA 14.991 202.76 (OPT70 25005C) (6.800)
Page 792 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY WEIGHT AND BALANCE DETERMINATION Enter the basic empty weight of the airplane in normal configuration and the moment in the appropriate block on the Loading Form, Figure 9.30.2 (1/3). Use Figure 9.30.1 to determine the weight and moment difference for the conversion to the cargo version.
Page 793 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Enter the characteristics of the loaded airplane in blocks for the zero fuel and weight with fuel configurations, Figure 9.30.3. Calculate the basic index using the formula described in and enter the results in , Figure 9.30.3.
Page 794 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Measure the cargo CG position (x dimension) from the anchor plates at frame 7. Express the cargo CG arm according to the following formula : do = 208.31 + x (in) do = 5.291 + x Figure 9.30.1 -- CG arm calculation Rev.
Page 795 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY LOADING FORM WEIGHT C.G. MOMENT ITEM lb.in (kg) (m.kg) 1. Basic empty weight 2. Cargo conversion 180.5 3. Pilot (4.585) 180.5 4. R.H. seat passenger (4.585) 128.0 5. Front baggage (3.250) 6. Cargo 7.
Page 796 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY = (d -- 172.93) x 100 m.a.c. % 59.45 WEIGHT ITEM m.a.c. % 14. Zero fuel weight 15. Weight with fuel Figure 9.30.2 (2/3) -- Loading Form (lbs and in) = (d -- 4.3925) x 100 % cam 1.51...
Page 797 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Figure 9.30.3 -- Weight and balance graph (in lbs) Page 9.30.14 Rev. 2...
Page 798 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Figure 9.30.3A -- Weight and balance graph (in kg) Rev. 2 Page 9.30.15...
Page 799 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY SECTION 7 DESCRIPTION DESCRIPTION For transport of goods in bulk (cargo of low density), two partition nets are available : -- one net at frame 7 for cargo installed in the cabin with only a pilot on board or one net at frames 7/10 with a pilot and a R.H.
Page 800 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Figure 9.30.4 -- Partition nets (version with a pilot) Rev. 2 Page 9.30.17...
Page 801 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Figure 9.30.4A -- Partition nets (version with a pilot and a R.H. passenger) Page 9.30.18 Rev. 2...
Page 802 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Figure 9.30.5 (1/2) -- Stowing of front container, pallet or heavy box (pilot alone on board) Rev. 2 Page 9.30.19...
Page 803 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Figure 9.30.5 (2/2) -- Stowing of rear container, pallet or heavy box (pilot alone on board) Page 9.30.20 Rev. 2...
Page 804 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY SECTION 8 HANDLING, SERVICING AND MAINTENANCE A - - CONVERSION PASSENGERS ACCOMMODATION INTO CARGO TRANSPORTATION VERSION 1) Remove the rear double chair and the intermediate passengers’ seats. 2) If the airplane is equipped with the gaseous oxygen option, optionally remove the R.H.
Page 805 T B M SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY B - - CONVERSION OF CARGO TRANSPORTATION VERSION INTO PASSENGERS ACCOMMODATION 1) If removed, install the stairs. 2) Remove and put away : -- the stowing nets, P/N T700B259001300000, -- the retaining angles, P/N T700B259003100000, -- the front partition...
Page 806 T B M SUPPLEMENT 35 “HONEYWELL” KMD 850 MULTI--FUNCTION DISPLAY SUPPLEMENT ”HONEYWELL” KMD 850 MULTI- -FUNCTION DISPLAY TABLE OF CONTENTS Page -- GENERAL 9.35.2 ..........-- LIMITATIONS 9.35.3 .
Page 807 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 ””HONEYWELL” KMD 850 MULTI--FUNCTION DISPLAY”. The generalities hereafter supplement those of the standard airplane described in Section 1 ”General”...
Page 808 The limitations hereafter supplement those of the standard airplane described in Section 2 ”Limitations” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””HONEYWELL” KMD 850 MULTI--FUNCTION DISPLAY”. KMD 550/850 Multi--function Display Pilot’s Guide, P/N 006--18222--0000, Revision 0 dated Oct/2000 or any applicable following edition, shall be readily available to the pilot.
Page 809 T B M SUPPLEMENT 35 “HONEYWELL” KMD 850 MULTI--FUNCTION DISPLAY SECTION 3 EMERGENCY PROCEDURES Installation and operation of the ”HONEYWELL” KMD 850 Multi--function Display do not change the emergency procedures described in Section 3 ”Emergency procedures” of the basic Pilot’s Operating Handbook. SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard aircraft...
Page 810 T B M SUPPLEMENT 35 “HONEYWELL” KMD 850 MULTI--FUNCTION DISPLAY SECTION 5 PERFORMANCE The installation and the operation of the ”HONEYWELL” KMD 850 Multi--function Display do not change the basic performance of the airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook.
Page 811 T B M SUPPLEMENT 35 “HONEYWELL” KMD 850 MULTI--FUNCTION DISPLAY SECTION 7 DESCRIPTION 1 -- Brightness control 8 -- Control knobs (inner and outer) 2 -- Data card 9 -- Power key labels 3 -- LCD display 10 -- Soft labels 4 -- Available function 11 -- Joystick 5 -- ON/OFF control...
Page 812 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 SUPPLEMENT ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- -RNAV) INTERFACED WITH EHSI OF EFS 40 TABLE OF CONTENTS Page -- GENERAL .
Page 813: General
The generalities hereafter supplement those of the standard airplane described in Section 1 ”General” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””GARMIN GNS 530” GPS NAVIGATION SYSTEM (B--RNAV) INTERFACED WITH EHSI OF EFS 40”.
Page 814: Limitations
The limitations hereafter supplement those of the standard airplane described in Section 2 ”Limitations” of the basic Pilot’s Operating Handbook, when the TBM 700 airplane is equipped with the option ””GARMIN GNS 530” GPS NAVIGATION SYSTEM (B--RNAV) INTERFACED WITH EHSI OF EFS 40”.
Page 815 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 Procedures during flight preparation During flight preparation, the pilot must get information about GPS constellation, via aeronautical data (consultation of GPS NOTAM). When less than 24 satellites are available (or less than 23 if equipment uses pressure altitude information), the pilot must make sure that RAIM function is available on the projected route and for the flight period in B--RNAV areas.
Page 816 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 The check of navigation system information consistency must be regularly performed during the flight : . when reaching each waypoint or before reaching the position report point of the ATC, .
Page 817: Emergency Procedures
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 700 airplane is equipped with the option ””GARMIN 530” NAVIGATION SYSTEM (B--RNAV) INTERFACED WITH EHSI OF EFS 40”.
Page 818 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 ”MSG” ANNUNCIATOR ILLUMINATION In navigation with GPS associated to the warning : ”MSG” push--button of associated GPS PRESS ....Check the message.
Page 819: Normal Procedures
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 ””GARMIN 530” NAVIGATION SYSTEM (B--RNAV) INTERFACED WITH EHSI OF EFS 40”.
Page 820 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 SYSTEM ANNUNCIATORS / SWITCHES / CONTROLS ”CDI” push- -button of the GPS This push--button may be used to select data to be displayed on electromechanical instruments (CDI or HSI).
Page 821 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 ”MSG” message annunciator CAUTION ”MSG” ANNUNCIATOR MAY BE PERMANENTLY ILLUMINATED IF THERE EXISTS A PERMANENT MESSAGE. WHEN A NEW MESSAGE APPEARS, ”MSG” ANNUNCIATOR JUST FLASHES. ”MSG”...
Page 822 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 NOTE : When the EHSI is selected on GPS navigation source, the RMI remains selected on NAV 1 source (VOR or RNAV). REMARK : The change of steering source for the autopilot, when the latter is set to “NAV”...
Page 823: Performance
T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 SECTION 5 PERFORMANCE The installation and the operation of the ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B--RNAV) INTERFACED WITH EHSI OF EFS 40 do not change the basic performance of the airplane described in Section 5 ”Performance”...
Page 824: Description
T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 SECTION 7 DESCRIPTION Normal operating procedures of the ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B--RNAV) INTERFACED WITH EHSI OF EFS 40 are described in the ”GARMIN”...
Page 825 T B M SUPPLEMENT 36 ”GARMIN GNS 530” GPS NAVIGATION SYSTEM (B- RNAV) INTERFACED WITH EHSI OF EFS 40 Figure 9.36.1 -- ”GARMIN GNS 530” GPS SYSTEMS Page 9.36.14 Rev. 1...
Page 838 T B M SUPPLEMENT 41 TBM 700C2 SUPPLEMENT TBM 700C2 TABLE OF CONTENTS Page -- GENERAL ........9.41.2A Descriptive data .
Page 839 T B M SUPPLEMENT 41 TBM 700C2 TABLE OF CONTENTS (Continued) -- HANDLING, SERVICING AND MAINTENANCE ..9.41.78 Servicing ........9.41.78 Utilization by cold weather (-- 0˚C to -- 25˚C) or very cold weather (-- 25˚C to -- 40˚C)
Page 840: General
T B M SUPPLEMENT 41 TBM 700C2 SECTION 1 GENERAL This supplement is intended to inform the pilot about the limitations and procedures necessary to use the TBM 700C2 airplane : -- between 6579 lbs (2984 kg) and 7394 lbs (3354 kg) for takeoff weight, and/or -- between 6250 lbs (2835 kg) and 7024 lbs (3186 kg) for landing weight.
Page 841: Operation Limits
T B M SUPPLEMENT 41 TBM 700C2 C.G. LIMITS (Figures 9.41.34 and 9.41.34A -- Section 6 of this Supplement) Center of gravity range with landing gear down and flaps up, attitude 0° : Forward limits : 183.6 inches (4.664 m) aft of datum at 6250 lbs (2835 kg) (18 % of m.a.c) 185.3 inches (4.707 m) aft of datum at 6579 lbs (2984 kg) (20.85 % of m.a.c) 187 inches (4.752 m) aft of datum at all weights above 7024 lbs (3186 kg) (23.8 % of m.a.c)
Page 842 T B M SUPPLEMENT 41 TBM 700C2 2.3 - - MARKINGS AIRSPEED INDICATOR Airspeed indicator markings and their color code significance are shown in Figure 9.41.1. KIAS MARKING SIGNIFICANCE (Value or range) White arc 65 -- 122 Full Flap Operating Range Lower limit is maximum weight in landing configuration.
Page 843 T B M SUPPLEMENT 41 TBM 700C2 INTENTIONALLY LEFT BLANK Page 9.41.2D Rev. 5...
Page 844 T B M SUPPLEMENT 41 TBM 700C2 2.4 - - PLACARDS Under L.H. front side window On main gear leg MAIN LANDING GEAR TIRE PRESSURE : 8,96 bar 130 psi On pressurized baggage compartment partition wall With partition net version A (refer to Section 6 of TBM 700C1 Pilot’s Operating Handbook) Rev.
Page 845 T B M SUPPLEMENT 41 TBM 700C2 With partition net version B (refer to Section 6 of TBM 700C1 Pilot’s Operating Handbook) Page 9.41.4 Rev. 1...
Page 846: Emergency Procedures
T B M SUPPLEMENT 41 TBM 700C2 SECTION 3 EMERGENCY PROCEDURES The emergency procedures hereafter supplement or replace those of the TBM 700C1 airplane described in Section 3 ”Emergency procedures” of the TBM 700C1 Pilot’s Operating Handbook, when using the TBM 700C2 airplane : -- between 6579 lbs (2984 kg) and 7394 lbs (3354 kg) for takeoff weight, and/or...
Page 847: Emergency Landings
T B M SUPPLEMENT 41 TBM 700C2 3.2 - - EMERGENCY LANDINGS FORCED LANDING (ENGINE CUT OFF) 1 -- Power lever ......... IDLE 2 -- Propeller governor lever .
Page 848 T B M SUPPLEMENT 41 TBM 700C2 3.2 -- 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 = 95 KIAS 3 -- Land with nose--up attitude, keep nose high...
Page 849 T B M SUPPLEMENT 41 TBM 700C2 3.2 -- EMERGENCY LANDINGS LANDING WITH GEAR UP 1 -- Final approach ........Standard (Flaps LDG, IAS = 85 KIAS) 2 -- ”BLEED”...
Page 850 T B M SUPPLEMENT 41 TBM 700C2 3.2 -- EMERGENCY LANDINGS LANDING WITH FLAPS MALFUNCTION For flaps deflections from “UP” to “TO” position : Proceed as for a normal landing, maintaining approach airspeed : Weight < 6250 lbs (2835 kg) Weight >...
Page 851 T B M SUPPLEMENT 41 TBM 700C2 INTENTIONALLY LEFT BLANK Page 9.41.8B Rev. 5...
Page 852 T B M SUPPLEMENT 41 TBM 700C2 3.2 -- EMERGENCY LANDINGS DITCHING 1 -- Landing gear ......... . In heavy swell with light wind, land parallel to the swell (rollers).
Page 853: Deicing System
T B M SUPPLEMENT 41 TBM 700C2 3.3 - - DEICING SYSTEM WINDSHIELD MISTING OR INTERNAL ICING Symptoms : -- Mist or ice on windshield internal face 1 -- ”CABIN TEMP/˚C” selector ..... . . Max HOT 2 -- ”AIR FLOW”...
Page 854: Normal Procedures
T B M SUPPLEMENT 41 TBM 700C2 SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement or replace those of the TBM 700C1 airplane described in Section 4 ”Normal procedures” of the TBM 700C1 Pilot’s Operating Handbook, when using the TBM 700C2 airplane : -- between 6579 lbs (2984 kg) and 7394 lbs (3354 kg) for takeoff weight, and/or...
Page 855: Check--List Procedures
T B M SUPPLEMENT 41 TBM 700C2 4.2 - - CHECK- -LIST PROCEDURES BEFORE STARTING ENGINE CAUTION ”BLEED” SWITCH “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 856 T B M SUPPLEMENT 41 TBM 700C2 CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (Cont’d) 11 -- ”OXYGEN” switch ........12 -- ”PASSENGERS OXYGEN”...
Page 857 T B M SUPPLEMENT 41 TBM 700C2 CHECK--LIST PROCEDURES BEFORE STARTING ENGINE (Cont’d) 26 -- Fuel -- Gages ........CHECKED -- Tank selector .
Page 858 T B M SUPPLEMENT 41 TBM 700C2 INTENTIONALLY LEFT BLANK Rev. 5 Page 9.41.11D...
Page 859 T B M SUPPLEMENT 41 TBM 700C2 CHECK--LIST PROCEDURES TAKEOFF WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.4 OF THIS SUPPLEMENT, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS” 1 -- Heading -- HSI -- Stand--by compass .
Page 860 T B M SUPPLEMENT 41 TBM 700C2 CHECK--LIST PROCEDURES TAKEOFF (Cont’d) 8 -- Brakes ........RELEASED 9 -- Power lever .
Page 861 T B M SUPPLEMENT 41 TBM 700C2 CHECK--LIST PROCEDURES BEFORE LANDING Long final 1 -- Altimeters ........CHECK 2 -- Fuel gages .
Page 862 T B M SUPPLEMENT 41 TBM 700C2 CHECK--LIST PROCEDURES GO- -AROUND 1 -- Simultaneously -- Power lever ......TRQ = 100 % -- Attitude .
Page 863: Amplified Procedures
T B M SUPPLEMENT 41 TBM 700C2 4.3 - - AMPLIFIED PROCEDURES BEFORE STARTING ENGINE 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. CAUTION ”BLEED”...
Page 864 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (Cont’d) 7 -- Pilot seat and R.H. front seat (if occupied) -- Height adjustment ......Maximum UP -- Fore and aft adjustment .
Page 865 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (Cont’d) 14 -- ”NORMAL/MASK” micro inverter ....NORMAL 15 -- ”IGNITION” switch .
Page 866 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (Cont’d) 25 -- Access door and (if installed) ”pilot” door DOOR WARNING LIGHT If ”DOOR” warning light is not OFF, open the access door and (if installed) the ”pilot” door and reclose it (them). Check locking pins are in place (green band is visible).
Page 867 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (Cont’d) 31 -- In case of night flight -- INT LIGHTS panel : ”INSTR” + ”PANEL” ..ADJUSTED -- Navigation lights .
Page 868 T B M SUPPLEMENT 41 TBM 700C2 INTENTIONALLY LEFT BLANK Rev. 5 Page 9.41.15F...
Page 869 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES TAKEOFF WHEN LINED UP CAUTION - - IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP - - IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.4 OF THIS SUPPLEMENT, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS” 1 -- Heading -- HSI -- Stand--by compass .
Page 870 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES TAKEOFF (Cont’d) 6 -- Radar switch ....... . . As required 7 -- PROP O’...
Page 871 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES TAKEOFF (Cont’d) 13 -- Landing gear control ..(IAS < 128 KIAS) ... . . During the sequence : -- The red warning light flashes ;...
Page 872 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES CLIMB 1 -- Power lever ......ADJUST according to engine operation table - - Chapter 5.7 of the TBM 700C1 Pilot’s Operating Handbook CAUTION...
Page 873 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES CLIMB (Cont’d) 3 -- ECS panel -- Cabin altitude selector ..Cruise altitude + 1000 feet -- Cabin rate selector ....ADJUST so as to obtain a cabin climb rate of about 500 ft/min...
Page 874 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES BEFORE LANDING Long final 1 -- Altimeters ........CHECK 2 -- Fuel gages .
Page 875 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES BEFORE LANDING (Cont’d) 7 -- 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 876: Go--Around
T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES GO- -AROUND 1 -- Simultaneously -- Power lever ......TRQ = 100 % -- Attitude .
Page 877 T B M SUPPLEMENT 41 TBM 700C2 AMPLIFIED PROCEDURES TOUCH AND GO After wheel touch 1 -- Flaps ..........Check that flaps have well reached the TO position before increasing power.
Page 878: Particular Procedures
T B M SUPPLEMENT 41 TBM 700C2 4.4 - - PARTICULAR PROCEDURES REMARK : The procedures and procedure elements given in this Chapter ”PARTICULAR PROCEDURES” supplement the normal procedures. FLIGHT INTO KNOWN ICING CONDITIONS General 1 -- Icing conditions exist when the IOAT on the ground or in flight is + 13°C or below, and visible moisture in any form is present (clouds, fog with visibility of one mile (1.6 km) or less, rain, snow, sleed or ice crystals).
Page 879 T B M SUPPLEMENT 41 TBM 700C2 PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (Cont’d) 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 880 T B M SUPPLEMENT 41 TBM 700C2 PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (Cont’d) 2 -- When operating under IMC : -- All ”DE ICE SYSTEM” switches ......-- ”IGNITION”...
Page 881 T B M SUPPLEMENT 41 TBM 700C2 PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (Cont’d) NOTE : ”IGNITION” switch may be left ON for a long period. Standby compass indications are altered when windshield deicing system(s) operate(s). 3 -- Procedures for holding, approach and landing in icing conditions : -- Minimum recommended speeds are : .
Page 882 T B M SUPPLEMENT 41 TBM 700C2 PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (Cont’d) 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 883: Performance
T B M SUPPLEMENT 41 TBM 700C2 SECTION 5 PERFORMANCE TABLE OF CONTENTS Page 5.1 -- ACOUSTIC LIMITATION ......9.41.32 5.2 -- STALL SPEEDS .
Page 884 T B M SUPPLEMENT 41 TBM 700C2 TABLE OF CONTENTS (Cont’d) Page ........9.41.54 Intermediate cruise .
Page 885 88 dB(A) 79.6 dB(A) OACI, Annex 16, Chapter 10, Appendix 6 TBM 700 airplane has received the noise limitation type certificate Nr N181 dated 31st January 1990, as well as Type Certificate Data Sheet EASA.A.010 dated 14 July 2004. Page 9.41.32...
Page 886: Demonstrated Crosswind
T B M SUPPLEMENT 41 TBM 700C2 5.2 - - STALL SPEEDS CONFIG. BANK AIR-- FLIGHT 0° 30° 45° 60° PLANE IDLE WEIGHT WEIGHT Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 7394 lbs (3354 kg) Figure 9.41.2 -- STALL SPEEDS 5.3 - - DEMONSTRATED CROSSWIND 20 kts Rev.
Page 887: Takeoff Distances
T B M SUPPLEMENT 41 TBM 700C2 5.4 - - TAKEOFF DISTANCES WEIGHT : 7394 lbs (3354 kg) Associated conditions -- Landing gear DN and flaps TO -- 12°5 of attitude -- TRQ = 100 % -- Np = 2000 RPM -- BLEED ON -- Hard, dry and level runway -- GR = Ground roll (in ft) -- D...
Page 888 T B M SUPPLEMENT 41 TBM 700C2 5.5 - - CLIMB PERFORMANCE [7394 Lbs (3354 Kg)] CLIMB SPEEDS (IAS = 130/160 KIAS) Conditions : Maximum climb power Landing gear and flaps UP BLEED ON RATE OF CLIMB (ft/min) Pressure Pressure altitude (KIAS) (feet)
Page 889: Climb Performance
T B M SUPPLEMENT 41 TBM 700C2 CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE [7394 Lbs (3354 Kg)] Conditions : ISA - 20°C Maximum climb power Landing gear and flaps UP 2000 RPM -- BLEED ON NOTE : Time, consumption and distance from the 50 ft 160 KIAS up to 20000 ft 130 KIAS then -- 2 KIAS/1000 ft...
Page 890 T B M SUPPLEMENT 41 TBM 700C2 CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE [7394 Lbs (3354 Kg)] Conditions : Maximum climb power Landing gear and flaps UP 2000 RPM -- BLEED ON NOTE : Time, consumption and distance from the 50 ft 160 KIAS up to 20000 ft 130 KIAS then -- 2 KIAS/1000 ft...
Page 891 T B M SUPPLEMENT 41 TBM 700C2 CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE [7394 Lbs (3354 Kg)] Conditions : ISA + 20 ° Maximum climb power Landing gear and flaps UP 2000 RPM -- BLEED ON NOTE : Time, consumption and distance from the 50 ft 160 KIAS up to 20000 ft 130 KIAS then -- 2 KIAS/1000 ft...
Page 892 T B M SUPPLEMENT 41 TBM 700C2 CLIMB PERFORMANCE CLIMB PERFORMANCE AFTER GO- -AROUND Conditions : Maximum climb power Landing gear DN and flaps LDG IAS = 95 KIAS RATE OF CLIMB (ft/min) Pressure Pressure Airplane Airplane altitude weight (feet) -- 35°C -- 20°C -- 10°C...
Page 893 T B M SUPPLEMENT 41 TBM 700C2 5.6 - - CRUISE PERFORMANCE Maximum cruise Conditions : ISA - 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure...
Page 894: Cruise Performance
T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Maximum cruise Conditions : ISA - 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT...
Page 895 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Maximum cruise Conditions : ISA - 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT...
Page 896 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Maximum cruise Conditions : Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg)
Page 897 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT...
Page 898 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT...
Page 899 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT...
Page 900 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA - 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure...
Page 901 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA - 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure...
Page 902 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA - 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure...
Page 903 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Normal (recommended) cruise Conditions : Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT...
Page 904 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure...
Page 905 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure...
Page 906 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure...
Page 907 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Intermediate cruise Conditions : ISA - 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg) (3300 kg) (°C) ( C)
Page 908 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Intermediate cruise Conditions : ISA - 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg) (3300 kg) (°C) ( C)
Page 909 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Intermediate cruise Conditions : ISA - 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg) (3300 kg) (°C) ( C)
Page 910 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Intermediate cruise Conditions : Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg) (3300 kg) (°C) ( C) (feet) (feet)
Page 911 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 5°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg) (3300 kg) (°C) ( C)
Page 912 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 10°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg) (3300 kg) (°C) ( C)
Page 913 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 20°C Landing gear and flaps UP 2000 RPM (*) -- BLEED ON AIRSPEEDS (kt) Fuel flow 6614 lbs 7275 lbs Pressure IOAT altitude (3000 kg) (3300 kg) (°C) ( C)
Page 914 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Long Range Cruise (6614 lbs - 3000 kg) Conditions : Landing gear and flaps UP LEGEND : IOAT : °C IAS : KIAS : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Presssure...
Page 915 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Long Range Cruise (6614 lbs - 3000 kg) (Cont’d) Conditions : Landing gear and flaps UP LEGEND : IOAT : °C IAS : KIAS : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Presssure...
Page 916 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Long Range Cruise (7275 lbs - 3300 kg) Conditions : Landing gear and flaps UP LEGEND : IOAT : °C IAS : KIAS : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Presssure...
Page 917 T B M SUPPLEMENT 41 TBM 700C2 CRUISE PERFORMANCE Long Range Cruise (7275 lbs - 3300 kg) (Cont’d) Conditions : Landing gear and flaps UP LEGEND : IOAT : °C IAS : KIAS : us gal/h 2000 RPM (*) -- BLEED ON : lbs/h TAS : KTAS Presssure...
Page 918: Landing Distances
T B M SUPPLEMENT 41 TBM 700C2 5.7 - - LANDING DISTANCES WEIGHT : 7024 lbs (3186 kg) Landing gear DN and flaps LDG Associated conditions Approach speed IAS = 85 KIAS Touch--down speed IAS = 78 KIAS Maximum braking without reverse Hard, dry and level runway GR = Ground roll (in ft) = Landing distance (clear to 50 ft) (in ft)
Page 919: Weight And Balance
T B M SUPPLEMENT 41 TBM 700C2 SECTION 6 WEIGHT AND BALANCE Information hereafter supplement or replace the one given for the TBM 700C1 airplane in Section 6 ”Weight and balance” of the TBM 700C1 Pilot’s Operating Handbook. GENERAL IT IS THE PILOT’S RESPONSIBILITY TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY AND THE WEIGHT AND BALANCE LIMITS ARE ADHERED TO.
Page 920 T B M SUPPLEMENT 41 TBM 700C2 Figure 9.41.34 -- WEIGHT AND BALANCE GRAPH (in Kg and Litres) Rev. 5 Page 9.41.67...
Page 921 T B M SUPPLEMENT 41 TBM 700C2 Figure 9.41.34A -- WEIGHT AND BALANCE GRAPH (in lbs and us gal) Page 9.41.68 Rev. 5...
Page 922: Determining Empty Airplane Characteristics
T B M SUPPLEMENT 41 TBM 700C2 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 contains the standard and optional equipment, as well as their characteristics (weight, arm).
Page 923: List Of Equipment
T B M SUPPLEMENT 41 TBM 700C2 LIST OF EQUIPMENT WEIGHT per unit STANDARD OR EQUIPMENT OPTIONAL EQUIPMENT SUPPLIER (kg) 25 - - EQUIPMENT - - FURNISHINGS JEPPESEN filing cabinet (OPT70 25005D) SOCATA 16.09 203.74 (7.300) (5.175) Storage box -- Compositie (wood and leather) SOCATA 17.64 203.74...
Page 924 T B M SUPPLEMENT 41 TBM 700C2 WEIGHT STANDARD OR EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg) 26 - - FIRE PROTECTION Portable fire extinguisher unit 863520--00 L’HOTELLIER 3.64 194.17 (OPT70 26001B) (1.650) (4.932) 32 - - LANDING GEARS 32- -10 - - Main landing gear L.H.
Page 925 T B M SUPPLEMENT 41 TBM 700C2 WEIGHT STANDARD OR EQUIPMENT per unit OPTIONAL EQUIPMENT SUPPLIER (kg) 34 - - NAVIGATION 34- -11 - - Air data systems Airspeed indicator # 1 8040 Code B.850 UNITED 0.75 157.48 INSTRUMENTS (0.340) (4.000) Airspeed indicator # 1 8140 Code B.851 UNITED...
Page 926 T B M SUPPLEMENT 41 TBM 700C2 INTENTIONALLY LEFT BLANK Rev. 5 Page 9.41.73...
Page 927 T B M SUPPLEMENT 41 TBM 700C2 SECTION 7 DESCRIPTION SEATS, BELTS AND HARNESSES (Figures 9.41.36 and 9.41.37) Cockpit seats 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 928 T B M SUPPLEMENT 41 TBM 700C2 FRONT SEATS REAR SEATS Figure 9.41.36 -- FRONT AND REAR SEAT BELTS (with movable straps) AND HARNESSES Rev. 5 Page 9.41.75...
Page 929 T B M SUPPLEMENT 41 TBM 700C2 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 930 T B M SUPPLEMENT 41 TBM 700C2 Figure 9.41.37 (2/2) -- SEATS Rev. 5 Page 9.41.77...
Page 931 T B M SUPPLEMENT 41 TBM 700C2 SECTION 8 HANDLING, SERVICING AND MAINTENANCE 8.1 - - SERVICING LANDING GEAR Main gear tires : 18 5.5 10 PR -- Inflating pressure : 135 psi (9.32 bars) * (*) Tire inflation pressures are given for an airplane on ground at 21˚C. An ambient temperature change of 3˚C produces approximately 1 % pressure change.
Page 950 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 SUPPLEMENT PROVISION FOR TBM 700C2 TABLE OF CONTENTS Page -- GENERAL ........9.43.3 -- LIMITATIONS .
Page 951 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 INTENTIONALLY LEFT BLANK Page 9.43.2 Rev. 0...
Page 952 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 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 700C1 airplane is equipped with the option ”PROVISION FOR TBM 700C2”.
Page 953 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 SECTION 3 EMERGENCY PROCEDURES The installation of the option ”PROVISION FOR TBM 700C2” does not change the basic emergency procedures of the airplane described in Section 3 ”Emergency procedures” of the TBM 700C1 Pilot’s Operating Handbook.
Page 954 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the TBM 700C1 airplane in Section 6 ”Weight and balance” of the TBM 700C1 Pilot’s Operating Handbook. WEIGHT per unit STANDARD OR EQUIPMENT OPTIONAL EQUIPMENT...
Page 955 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 SECTION 7 DESCRIPTION SEATS, BELTS AND HARNESSES Cockpit seats 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 956 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 SECTION 8 HANDLING, SERVICING AND MAINTENANCE 8.1 - - SERVICING LANDING GEAR Main gear tires : 18 5.5 10 PR -- Inflating pressure : 135 psi (9.32 bars) NOTE : Tire inflation pressures are given for an airplane on ground at 21˚C. An ambient temperature change of 3˚C produces approximately 1 % pressure change.
Page 957 T B M SUPPLEMENT 43 PROVISION FOR TBM 700C2 INTENTIONALLY LEFT BLANK Page 9.43.8 Rev. 0...
Page 960 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 961 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 962 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM SECTION 7 DESCRIPTION The chip detection system enables the monitoring of engine oil system. The system includes one chip detector installed on propeller reduction gear box and, if installed, a second chip detector installed on engine accessory gear box.
Page 963 T B M SUPPLEMENT 44 CHIP DETECTION SYSTEM INTENTIONALLY LEFT BLANK Rev. 1 Page 9.44.6...
Page 972 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT SUPPLEMENT MULTI- -MISSION AIRCRAFT TABLE OF CONTENTS Page -- GENERAL ........9.53.3 -- LIMITATIONS .
Page 973 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT INTENTIONALLY LEFT BLANK Page 9.53.2 Rev. 0...
Page 974 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, procedures and description necessary to the operation when the TBM700 airplane is equipped with ”MULTI--MISSION AIRCRAFT” (MMA) option : The MMA consists in different versions, provided in the table hereafter : VERSION EQUIPMENT...
Page 975 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT SECTION 2 LIMITATIONS 2.1 - - GENERAL The limitations hereafter supplement those of the standard airplane described in Section 2 ”Limitations” of the basic Pilot’s Operating Handbook when the TBM700 airplane is equipped with the ”MULTI--MISSION AIRCRAFT”...
Page 976 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT 2.4 - - FLIGHT OPERATING LIMITS VERSION CONFIGURATION Maximum altitude Sphere is totally or partially extended 20000 ft (6096 m) 2.5 - - MISCELLANEOUS LIMITS Only cabin standard or mission lay out is allowed to fly. 2.6 - - LABELS EXTENDED SPHERE IAS ±...
Page 977 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT 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 TBM700 airplane is equipped with the ”MULTI--MISSION AIRCRAFT”...
Page 978: Before Taxiing
T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT 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 TBM700 airplane equipped with ”MULTI--MISSION AIRCRAFT” option. BEFORE TAXIING 1 -- Extension/retraction switch CHECK UNDER GUARD...
Page 979 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT RETRACT THE SPHERE 1 -- Airspeed below 160 KIAS ........2 -- Extension/retraction switch .
Page 980 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT SECTION 5 PERFORMANCE The performance hereafter supplement those of the standard airplane described in Section 5 ”Performance” of the basic Pilot’s Operating Handbook, when TBM700 airplane equipped with ”MULTI--MISSION AIRCRAFT” option. 5.1 - - LONG RANGE CRUISE When the sphere is extended : at iso torque, the airspeed is decreased by 4 KIAS, at iso airspeed, the fuel flow is increased by 2 US.Gal/h.
Page 981 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT 5.2 - - WIND COMPONENTS EXAMPLE : Angle between wind direction and flight path 50 ° Headwind 8 kts Crosswind 10 kts Wind speed 13 kts Figure 9.53.1 -- WIND COMPONENTS Page 9.53.10 Rev.
Page 982 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT SECTION 6 WEIGHT AND BALANCE The weight and balance hereafter supplement those of the standard airplane described in Section 6 ”Weight and Balance” of the basic Pilot’s Operating Handbook, when TBM700 airplane equipped with ”MULTI--MISSION AIRCRAFT”...
Page 983 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT SECTION 7 DESCRIPTION The description hereafter supplement those of the standard airplane described in Section 7 ”Description” of the basic Pilot’s Operating Handbook, when the TBM700 airplane is equipped with the ”MULTI--MISSION AIRCRAFT” option. The main components of the Multi--mission aircraft are : 1) One extension/retraction control panel (pilot control only), 2) One console in order to operate the sphere when extended,...
Page 984 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT 7.1 - - CABIN LAYOUTS Aircraft equipped with gazeous oxygen Either L.H. intermediate seat (Item 1) or L.H. rear seat (Item 2) can be removed if necessary. Aircraft equipped with chemical oxygen Either L.H. intermediate seat (Item 1) or L.H. rear seat (Item 2) can be removed if necessary, provided that access to oxygen masks is possible for every passenger aboard during all flight phases.
Page 985 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT Figure 9.53.3 -- CABIN LAYOUTS Page 9.53.14 Rev. 0...
Page 986 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT 7.2 - - EXTENSION/RETRACTION CONTROL PANEL 1) STOP : Emergency stop -- when actuated stops the sphere maneuver. 2) Under guard switch : sphere maneuver control. 3) Blue indicator light : light is ON if the sphere is extended. 4) Red warning light : flashes during sphere maneuver, is ON if a failure is detected.
Page 987 T B M SUPPLEMENT 53 MULTI--MISSION AIRCRAFT INTENTIONALLY LEFT BLANK Page 9.53.16 Rev. 0...
Page 988 T B M SUPPLEMENT 60 ADS--B OUT FUNCTION SUPPLEMENT ADS- -B OUT FUNCTION TABLE OF CONTENTS Page -- GENERAL 9.60.2 ..........-- LIMITATIONS 9.60.2 .
Page 989 T B M SUPPLEMENT 60 ADS--B OUT FUNCTION SECTION 1 GENERAL This supplement is intended to inform the pilot about the equipment limitations, description and operations necessary for operation when the airplane is equipped with “ADS--B OUT function”. The ADS--B OUT function is integrated in the optional modification MOD70-0494-34A : Garmin GTX 330 Diversity Mode S transponder # 1 with the extended squitter functionality.
Page 990 T B M SUPPLEMENT 60 ADS--B OUT FUNCTION SECTION 4 NORMAL PROCEDURES Operation of “ADS--B OUT function” does not change the normal procedures of the airplane described in Section 4 “Normal Procedures” of the basic Pilot’s Operating Handbook. SECTION 5 PERFORMANCE Operation of “ADS--B OUT function”...
Page 991 T B M SUPPLEMENT 60 ADS--B OUT FUNCTION SECTION 7 DESCRIPTION Information hereafter supplement or replace those of the standard airplane described in Section 7 ”Description” of the basic Pilot’s Operating Handbook when the airplane is equipped with the “ADS--B OUT function”. The “ADS--B OUT function”...

Save PDF