SOCATA TBM 700 Pilot's Information Manual

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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

INTENDED FOR OPERATION OF THE AIRPLANE.

The content of this document is the property of SOCATA. It is supplied in confidence and

commercial security of its contents must be maintained.

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

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

nor transmitted in any form in whole or in part without permission in writing from the owners

Information in this document is subject to change without notice.

For any information concerning this document, please contact :

SOCATA

SUPPORT CLIENT / CUSTOMER SUPPORT

AEROPORT TARBES-OSSUN-LOURDES

B.P . 930 - 65009 TARBES CEDEX

FRANCE

January 31, 1990 - Rev. 9

TBM 700

Versions A and B

PILOT'S

CAUTION

PURPOSES ONLY.

of the Copyright.

TELEPHONE : 33 (0)5 62.41.73.00

TELEFAX

TELEX

P/N : T00.DMAPIPYE

: 33 (0)5 62.41.76.54

532 835 F

Printed in FRANCE

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Summary of Contents for SOCATA TBM 700

Page 1 FOR AIRWORTHINESS AUTHORITIES APPROVED MANUAL WHICH IS THE ONLY ONE INTENDED FOR OPERATION OF THE AIRPLANE. The content of this document is the property of SOCATA. It is supplied in confidence and commercial security of its contents must be maintained.
Page 2 Back to Contents T B M PILOT’S INFORMATION MANUAL SOCATA MODIFICATIONS – INDEX NOTE : The standardized name for SOCATA modifications is : MOD70–XXX–XX MOD70 No. SUBJECT CLASSIF. 001–06 Increase in ramp and max. takeoff weights Major 002–24 Alternator current output increase Major 003–28...
Page 3 Major 022–55 Machined parts replaced by castings or drop Major forgings (in alternate) 023–25 Replacement of the ERDA bench by the Major SOCATA bench 024–34 3 in VS indicator minor 025–21 Cabin air cooling minor 026–28 Fuel booster pump AIRBORNE 1B9–5 minor 027–32...
Page 4 Back to Contents T B M PILOT’S INFORMATION MANUAL MOD70 No. SUBJECT CLASSIF. 038–28 Fuel unit INTERTECHNIQUE L88A15–651 minor 039–27 Installation of pitch trim position transmitter minor 041–71 Reinforcement of NACA air intakes on cabin minor air conditioning system and engine oil cooling system 042–25 Cabin covering improvement (lower door)
Page 5 Back to Contents T B M PILOT’S INFORMATION MANUAL MOD70 No. SUBJECT CLASSIF. 063–32 Main gear tires minor 064–22 Adapter module/Autopilot Major 065–32 Removal of the main landing gear inboard Major doors 066–57 Wing attachment shafts minor 067–57 Simplification of the main landing gear fai- minor rings : standard configuration 068–32...
Page 6 Back to Contents T B M PILOT’S INFORMATION MANUAL MOD70 No. SUBJECT CLASSIF. 088–53 Stringer bracket riveting minor 089–25 Lowering of pilot’s and R.H. front seats minor 090–32 Landing gear retraction actuators P/N 08 minor 1480 091–52 TBM700B Access door widening, Major incorporation of modifications and increase...
Page 7 Back to Contents T B M PILOT’S INFORMATION MANUAL MOD70 No. SUBJECT CLASSIF. 113–53 “FIRE–PROOF” treatment of the nose minor landing gear well 114–25 Shoulder harnesses pilots minor passengers 115–25 FWD baggage compartment panels minor 116–52 Evolution of stairs hand rail mechanism minor 117–55 Horizontal stabilizer reinforcement...
Page 8 The content of this document is the property of SOCATA. It is supplied in confidence and commercial security of its contents must be maintained. It must not be used for any purpose other than that for which it is supplied, nor may information contained in it be disclosed to unauthorized persons.
Page 9 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL SECTION 1 GENERAL TABLE OF CONTENTS Page GENERAL 1.1.1 ........... THREE VIEW DRAWING 1.2.1 .
Page 10 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 1.0.2 Rev. 2...
Page 11 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. Section 1 provides basic data and information of general interest. It also contains definitions or explanations of abbreviations and terminology commonly used.
Page 12 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 1.1.2 Rev. 2...
Page 13 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 1.2 – THREE VIEW DRAWING * Airplane on line of flight with extended FWD shock–absorber Figure 1.2.1 (1 / 2) – THREE VIEW DRAWING – TBM700A Rev. 7 Page 1.2.1...
Page 14 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL Figure 1.2.1 (2 / 2) – THREE VIEW DRAWING – TBM700A Page 1.2.2 Rev. 7...
Page 15 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL * Airplane on line of flight with extended FWD shock–absorber Figure 1.2.1A (1 / 2 ) – THREE VIEW DRAWING – TBM700B Rev. 7 Page 1.2.3...
Page 16 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL Figure 1.2.1A (2 / 2 ) – THREE VIEW DRAWING – TBM700B Page 1.2.4 Rev. 7...
Page 17 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 1.3 – DESCRIPTIVE DATA ENGINE Number of engines : 1 Engine manufacturer : PRATT & WHITNEY CANADA Engine model number : PT6A – 64 Engine type : Free turbine, reverse flow and 2 turbine sections Compressor type : 4 axial stages 1 centrifugal stage...
Page 18 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 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–27686D or E or MIL–I85470A.
Page 19 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL ENGINE OIL System total capacity : 12.7 Quarts (12 Litres) (oil cooler included) Usable capacity : 6 Quarts (5.7 Litres) Maximum consumption : 0.30 qt / hr (0.29 l / hr) [0.3 lb/hr (0.136 kg/h)] CAUTION DO NOT MIX DIFFERENT BRANDS OR TYPES...
Page 20 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL MAXIMUM CERTIFICATED WEIGHTS Ramp : 6614 lbs (3000 kg) Takeoff : 6579 lbs (2984 kg) Landing : 6250 lbs (2835 kg) Baggage weight (refer to Section 6 for cargo loading instructions) : In FWD compartment (non pressurized) : 110 lbs (50 kg) In aft compartment (pressurized) : 220 lbs (100 kg) STANDARD AIRPLANE WEIGHTS...
Page 21 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 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...
Page 22 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL : Maneuvering Speed is the maximum speed at which full or abrupt control movements may be used. : Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. : Maximum Landing Gear Extended Speed is the maximum speed at which an airplane can be safely flown with the landing gear extended.
Page 23 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL POWER TERMINOLOGY Recovery altitude : Maximum altitude at which it is possible, in standard temperature, to maintain a specified power. Overheated start : Engine start or attempt to start which causes the interturbine temperature to be higher than the maximum value permissible during start .
Page 24 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Climb gradient : Is the ratio of the change in height during a portion of climb, to the horizontal distance traversed in the same time interval. Demonstrated crosswind velocity : Is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing...
Page 25 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL C.G. limits : Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. Standard empty weight : Weight of a standard airplane including unusable fuel and full operating fluids (oil and hydraulic fluids).
Page 26 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 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 BAT OVHT Battery overheat...
Page 27 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 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 Left Litre / hour lb or lbs...
Page 28 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL Quantity Red or Right Rudder s or sec Second Selector Signalization Sea level Serial number SPKR Speaker ST – BY Stand–by STALL HTR Stall heater Standard T° Temperature TEMP Temperature Takeoff...
Page 29 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL RADIO – NAVIGATION ABBREVIATIONS Automatic Direction Finder System Attitude Director Indicator Transponder Course Deviation Indicator Communications Transceivers Distance Measuring Equipment Emergency Locator Transmitter High Frequency Horizontal Situation Indicator Instrument Flight Rules Instrument Landing System Instrument Meteorological Conditions...
Page 30 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 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 ERMI...
Page 31 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 1.5 – CONVERSION FACTORS IMPERIAL AND U.S UNITS TO METRIC METRIC UNITS TO IMPERIAL AND U.S UNITS UNITS MULTIPLY TO OBTAIN MULTIPLY TO OBTAIN FEET 0.3048 METRE METRE 3.2808 FEET INCH...
Page 32 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL Feet 30000 20000 10000 Mètres 2500 5000 7500 10000 Figure 1.5.2 – FEET VERSUS METRES Page 1.5.2 Rev. 2...
Page 33 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 1000 Figure 1.5.3 – INCHES VERSUS MILLIMETRES Rev. 2 Page 1.5.3...
Page 34 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 8000 6000 4000 2000 1000 2000 3000 4000 Figure 1.5.4 – POUNDS VERSUS KILOGRAMS Page 1.5.4 Rev. 2...
Page 35 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 1.6 – PRESSURE AND STANDARD ATMOSPHERE STANDARD ATMOSPHERE Pressure Pressure °C °F altitude (hPa) (ft) 1013.2 + 15.0 + 59.0 2000 942.1 + 11.0 + 51.8 4000 875.0 + 44.6 6000 811.9...
Page 36 Back to Contents T B M SECTION 1 GENERAL PILOT’S INFORMATION MANUAL 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...
Page 37 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved SECTION 2 LIMITATIONS TABLE OF CONTENTS Page GENERAL 2.1.1 ........... AIRSPEED LIMITATIONS 2.2.1 .
Page 38 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved TABLE OF CONTENTS (Continued) Page MARKINGS 2.8.1 ..........2.8.1 AIRSPEED INDICATOR .
Page 39 D.G.A.C. Approved 2.1 – GENERAL The TBM 700 airplane is certified in the Normal Category. This airplane must be flown in compliance with the limits specified by placards or markings and with those given in this Section and throughout the Pilot’s Operating Handbook.
Page 40 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 2.1.2 Rev. 2...
Page 41 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.2 – AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 2.2.1. KCAS KIAS SPEED REMARKS Do not intentionally exceed Maximum operating speed this speed in normal flight category Do not make abrupt or full...
Page 42 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 2.2.2 Rev. 2...
Page 43 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.3 – POWER PLANT LIMITATIONS ENGINE Number of engines : 1 Engine manufacturer : PRATT & WHITNEY CANADA Engine model number : PT6A – 64 Engine operating limits for takeoff and continous operations : Maximum power : –...
Page 44 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 45 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. 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...
Page 46 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 2.3.4 Rev. 2...
Page 47 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.4 – STARTER OPERATION LIMITS Starter operation sequence is limited as follows : if Ng ≤ 30 % ......... . . 30 seconds if Ng >...
Page 48 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 2.4.2 Rev. 2...
Page 49 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.5 – WEIGHT AND C.G. LIMITS WEIGHT LIMITS Maximum ramp weight : 6614 lbs (3000 kg) Maximum takeoff weight : 6579 lbs (2984 kg) Maximum landing weight : 6250 lbs (2835 kg) Maximum zero fuel weight in wings (MZFW) : 6001 lbs (2722 kg) Maximum baggage weight in FWD compartment (non pressurized) : 110 lbs (50 kg)
Page 50 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved FLIGHT LOAD FACTOR LIMITS – 1.5 ≤ n ≤+ 3.8 g Flaps up : ≤ n ≤+ 2.0 g Flaps down : – 0 CAUTION INTENTIONAL NEGATIVE LOAD FACTORS PROHIBITED Page 2.5.2 Rev.
Page 51 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.6 – OPERATION LIMITS MANEUVER LIMITS This airplane is certified in the normal category. The normal category is applicable to airplanes intended for non–acrobatic operations. Non–acrobatic operations include any maneuvers incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles, and steep turns in which the angle of bank is no more than 60°.
Page 52 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. 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 53 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved FLAPS 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. Rev.
Page 54 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved EQUIPMENT REQUIRED DEPENDING ON TYPE OF OPERATION The airplane is approved for day & night VFR and day & night IFR operations when appropriate equipment is installed and operating correctly. The type certification for each use requires the following equipment.
Page 55 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 56 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 5) Various indicators – Fuel gauge indicators (2) – Fuel pressure indicator – Voltmeter – Ammeter – Outside air temperature 6) Installations – Fuel mechanical pump (main) –...
Page 57 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. 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...
Page 58 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved Flight into icing conditions – All equipment required for IFR flight – Propeller deicing – L.H. windshield deicing – Airframe, stabilizer and elevator horn deicing – Wing leading edge inspection light (if night flight) –...
Page 59 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.7 – MISCELLANEOUS LIMITS SEATING LIMITS C.G. From 1 to 6 seats : – 2 seats at 180.5 inches (4.585 m) – 2 seats at 219.1 inches (5.565 m) } see NOTE 1 –...
Page 60 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 2.7.2 Rev. 2...
Page 61 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.8 – MARKINGS AIRSPEED INDICATOR Airspeed indicator markings and their color code significance are shown in Figure 2.8.1. KIAS MARKING SIGNIFICANCE (Value or range) White arc 60 –...
Page 62 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved ENGINE INSTRUMENTS Engine instrument markings and their color code significance are shown in Figure 2.8.2. Yellow Line or Line or arc Green Arc Red Line INSTRUMENT --------- --------- ---------...
Page 63 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved 2.9 – PLACARDS (1) Under L.H. front side window – Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped retrofit with modification MOD 70–019–25...
Page 64 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (2) Calibration chart on compass and on windshield post WARNING Steer TURN L AND R WINDSHIELD DE–ICE OFF BEFORE Steer COMPASS READING DATE : RADIO ON (3) On rear baggage compartment bottom bulkhead (pressurized) 100 kg –...
Page 65 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (5) Under radio rack, in front of pedestal Rev. 5 Page 2.9.3...
Page 66 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (6) On fuel selector (7) Near fuel tank caps Page 2.9.4 Rev. 2...
Page 67 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (8) On internal face of L.H. engine cowling Oil system capacity 12 l 12.7 qt (9) On R.H. side, at front seat level and under seating of intermediate and rear passenger seats, which are fitted with oxygen EMERGENCY OXYGEN IN DRAWER UNDER SEAT ;...
Page 68 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (12) Under R.H. control wheel (13) On nose gear door (14) On nose gear leg NOSE LANDING GEAR TIRE PRESSURE : 6,5 bar 94 psi Page 2.9.6 Rev.
Page 69 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (15) On main gear leg MAIN LANDING GEAR TIRE PRESSURE : 8,25 bar 120 psi (16) On engine cowling, in front of baggage compartment door EXTERNAL POWER 28 VOLTS D.C.
Page 70 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (17) TBM700B On access door – External side (18) TBM700B On outer fuselage skin aft of access door and in the cabin forward of access door Page 2.9.8 Rev.
Page 71 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (19) TBM700A from S / N 1 to S / N 49, except airplanes equipped as a retrofit with modification No. MOD 70–019–25 On access door – Internal side (19) TBM700A from S / N 50, plus airplanes equipped as a retrofit with modification No.
Page 72 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (19) TBM700B On access door – Internal side (19) TBM700B On ”pilot” door – Internal side (if installed) Page 2.9.10 Rev. 9...
Page 73 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (20) From S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification No. MOD 70–019–25 On emergency exit handle Rev.
Page 74 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (20) From S / N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification No. MOD 70–019–25 On emergency exit handle Marking on cover Marking on handle...
Page 75 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved (21) TBM700A On external side of lower half–door TBM700B On last step of stairs STAIRS MAX LOAD : ONE PERSON (22) TBM700B On R.H. access door jamb DO NOT USE HAND RAIL TO RETRACT...
Page 76 Back to Contents T B M SECTION 2 LIMITATIONS PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 2.9.14 Rev. 7...
Page 77 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved SECTION 3 LIMITATIONS TABLE OF CONTENTS Page GENERAL 3.1.1 ........... REJECTED TAKEOFF PROCEDURE 3.2.1 .
Page 78 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved TABLE OF CONTENTS (Continued) Page EMERGENCY DESCENTS 3.6.1 ....... . . 3.6.1 PROCEDURE IN SMOOTH AIR .
Page 79 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved TABLE OF CONTENTS (Continued) Page AMBER WARNING LIGHT LO VOLT functioning on ”ST–BY GENERATOR” 3.9.4 (after ”MAIN GEN” failure) ........3.9.6 ELECTRICAL DISTRIBUTION OF BUS BARS .
Page 80 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved TABLE OF CONTENTS (Continued) Page 3.13 MISCELLANEOUS 3.13.1 ......... . 3.13.1 RUNAWAY OF ONE OF THE THREE ELECTRICAL TRIM TABS .
Page 81 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 82 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 83 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 84 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 3.2.2 Rev. 2...
Page 85 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES ENGINE FAILURE AT TAKEOFF BEFORE ROTATION 1 – Power lever ......... IDLE 2 –...
Page 86 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES ENGINE FAILURE AFTER ROTATION – If altitude does not allow to choose a favourable runway or field : Land straight ahead keeping flaps at TO and without changing landing gear position.
Page 87 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES ENGINE FAILURE DURING FLIGHT 1 – Power lever ......... IDLE 2 –...
Page 88 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES OIL PRESSURE DROP RED WARNING LIGHT OIL PRESS 1 – Oil pressure indicator ......CHECK 2 –...
Page 89 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES ENGINE REGULATION DISCREPANCY, POWER LOSS, POWER LEVER CONTROL LOSS 1 – If circumstances allow : Power lever ......... IDLE 2 –...
Page 90 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES ENGINE REGULATION DISCREPANCY, POWER LOSS, POWER LEVER CONTROL LOSS (Cont’d) 6 – Perform a normal landing WITHOUT REVERSE 7 – Braking .
Page 91 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 92 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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.
Page 93 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES RED WARNING LIGHT Indicates that ITT exceeds 800°C During an engine start Intertubine temperature °C É É É É É É É É É É É É É É É 1000 É...
Page 94 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – ENGINE FAILURES RED WARNING LIGHT ”ITT” ON (Cont’d) 3 – Record the engine parameters read in case of overtemperature, as well as ground conditions. 4 –...
Page 95 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
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Page 97 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.4 – AIR START AIR START ENVELOPE Pressure altitude (ft) 2000 STARTER STARTER ASSIST ASSIST MANDATORY NOT MANDATORY PROPELLER FEATHERED WINDMILLING PROPELLER (KIAS) Air start may be attempted at all speeds and all altitudes. However, above 20000 ft or with Ng <...
Page 98 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – AIR START AIR START WITH STARTER 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 99 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – AIR START AIR START WITH STARTER (Cont’d) 12 – Condition lever ........LO / IDLE when Ng ~ 13 % 13 –...
Page 100 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – AIR START AIR START WITHOUT STARTER (STARTER ASSIST NOT MANDATORY) CAUTION THE STARTER CANNOT OPERATE IF THE ”GENERATOR” SELECTOR IS ON ”ST–BY” CAUTION IGNITION IS NOT AVAILABLE IF THE ”ESS BUS TIE”...
Page 101 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – AIR START AIR START WITHOUT STARTER (STARTER ASSIST NOT MANDATORY) (Cont’d) 9 – ”IGNITION” switch ........10 –...
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Page 103 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.5 – FIRE AND SMOKE ENGINE FIRE ON GROUND Symptoms : ITT increasing, red warning light smoke, ... 1 – Power lever ......... IDLE 2 –...
Page 104 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – FIRE AND SMOKE ENGINE FIRE IN FLIGHT Symptoms : ITT increasing, red warning light smoke, ... 1 – Power lever ......... IDLE 2 –...
Page 105 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – FIRE AND SMOKE CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT If the origin is known : 1 – Oxygen ....... USE AS REQUIRED (pilot and passengers) 2 –...
Page 106 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – FIRE AND SMOKE CABIN ELECTRICAL FIRE OR SMOKE DURING FLIGHT (Cont’d) If smoke or fire persists : 5 – ”SOURCE” selector ........6 –...
Page 107 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.3 – FIRE AND SMOKE SMOKE ELIMINATION 1 – Smoke origin ........IDENTIFY 2 –...
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Page 109 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.6 – EMERGENCY DESCENTS PROCEDURE IN SMOOTH AIR 1 – Power lever ......... IDLE 2 –...
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Page 111 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS GLIDE DISTANCE AND OPTIMUM SPEED Configuration 1 – Flaps ..........2 –...
Page 112 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS FORCED LANDING (ENGINE CUT OFF) 1 – Power lever ......... IDLE 2 –...
Page 113 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS TIRE BLOWOUT DURING LANDING 1 – Control direction with brakes and nose wheel steering 2 – REVERSE ....... . AS REQUIRED 3 –...
Page 114 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR 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 115 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR (Cont’d) 11 – Condition lever ........CUT OFF 12 –...
Page 116 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS LANDING WITH DEFECTIVE NOSE LANDING GEAR (DOWN UNLOCKED OR NOT DOWN) 1 – Transfer passengers to the rear, if necessary 2 – Approach .
Page 117 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS LANDING WITH GEAR UP 1 – Final approach ........Standard (Flaps LDG, IAS = 80 KIAS) 2 –...
Page 118 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS LANDING WITHOUT ELEVATOR CONTROL 1 – Configuration ... . LANDING GEAR DN – FLAPS LDG 2 –...
Page 119 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.7 – EMERGENCY LANDINGS DITCHING 1 – Landing gear ......... In heavy swell with light wind, land parallel to the swell (rollers).
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Page 121 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.8 – FUEL SYSTEM RED WARNING LIGHT FUEL PRESS Indicates a fuel pressure drop at ”HP” engine pump inlet 1 – Remaining fuel ........CHECK 2 –...
Page 122 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.8 – FUEL SYSTEM RED WARNING LIGHT ”FUEL PRESS” ON (Cont’d) If pressure remains at 0 and if warning remains on : FUEL PRESS 9 – Selection of the fullest tank .
Page 123 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 124 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 125 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.9 – ELECTRICAL SYSTEM RED WARNING LIGHT BAT OVHT Indicates a battery overheat 1 – ”SOURCE” selector ........WARNING LIGHT BAT OFF 2 –...
Page 126 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 127 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.9 – ELECTRICAL SYSTEM AMBER WARNING LIGHT LO VOLT normal functioning on ”MAIN GEN” 1 – Voltmeter voltage ........CHECK 2 –...
Page 128 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.9 – ELECTRICAL SYSTEM AMBER WARNING LIGHT LO VOLT functioning on ”ST–BY GENERATOR” (after ”MAIN GEN” failure) Amber warning lights MAIN GEN LO VOLT with ”GENERATOR” selector on ”ST–BY” 1 –...
Page 129 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.9 – ELECTRICAL SYSTEM AMBER WARNING LIGHT ”LO VOLT” ON functioning on ”ST–BY GENERATOR” (after ”MAIN GEN” failure) (Cont’d) 9 – ”GENERATOR” selector ....... If conditions allow : VMC and non icing conditions Altitude 3 10 –...
Page 130 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved FLAPS (D) STROBE PITOT 1 HTR R.W / S DE ICE INERT SEP AIRFRAME DE ICE ENGINE INDIC 1 : – torquemeter, propeller & oil press+temperature IGNIT AUX BP...
Page 131 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.9 – ELECTRICAL SYSTEM ”RADIO MASTER” SWITCH FAILURE NOTE : This procedure is not valid for aircraft S/N 1 to 17 if the ”RADIO FAN” circuit breaker is not releasable manually.
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Page 133 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.10 – PRESSURIZATION AND AIR CONDITIONING RED WARNING LIGHT CAB PRESS 1 – Pressurization indicator ......CHECK P >...
Page 134 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.10 – PRESSURIZATION AND AIR CONDITIONING AMBER WARNING LIGHT BLEED OFF (Normal signal if ”BLEED VALVE” switch is OFF) 1 – If necessary ........CORRECT 2 –...
Page 135 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.10 – PRESSURIZATION AND AIR CONDITIONING RED WARNING LIGHT BLEED TEMP Indicates overheat of air conditioning pack. Normally this leads to ”BLEED VALVE” cutoff and to amber warning light BLEED OFF illumination...
Page 136 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 137 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 138 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.10 – PRESSURIZATION AND AIR CONDITIONING DEFOG MALFUNCTION If moisture starts to quickly cover the inside of the windscreeen with the distributor already positioned on ”DEFOG” : 1 –...
Page 139 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP – Red warning light on ”LANDING GEAR” control panel remains ON : 1 – ”LDG GR” circuit–breaker .
Page 140 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP (Cont’d) CAUTION THE ENTIRE EXTENSION OF THE LANDING GEAR TAKES ABOUT 65 CYCLES. IT IS MANDATORY TO HAVE A CLEAN HARDENING OF THE MANUAL CONTROL AT THE END OF THE MANEUVER If landing gear is down and locked (correct indication) :...
Page 141 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP – Red warning light on ”LANDING GEAR” control panel remains flashing ON : The red warning light on the landing gear control panel flashing at the end of maneuver indicates that the landing gear electrohydraulic pump still operates.
Page 142 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES UP (Cont’d) If the fixed red warning light is still on : Continue flight if necessary at a speed below 178 KIAS, without icing conditions or land.
Page 143 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN – Incorrect indication on ”LANDING GEAR” control panel : Red warning light switched on or off, one or more green lights are missing Perform a MANUAL EXTENSION : 1 –...
Page 144 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN (Cont’d) If the ”CHECK DN” indication is also incorrect, recycle landing gear as follows : 9 –...
Page 145 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN – Red warning light on ”LANDING GEAR” control panel remains flashing ON (whatever the condition of the green lights may be) : The red warning light on the landing gear control panel flashing at the end of maneuver indicates that the landing gear electrohydraulic pump operates correctly.
Page 146 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.11 – LANDING GEAR AND FLAPS DISCREPANCY WHEN LANDING GEAR GOES DOWN (Cont’d) 6 – ”LDG GR” circuit–breaker ......PUSH 7 –...
Page 147 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
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Page 149 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.12 – DEICING SYSTEM LEADING EDGES DEICING FAILURE Symptoms : Failure on one of the two pneumatic deicing pulses : – Ice on wing outboard sections –...
Page 150 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 151 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.12 – DEICING SYSTEM WINDSHIELD MISTING OR INTERNAL ICING Symptoms : – Mist or ice on windshield internal face 1 – ”CABIN TEMP” selector ......Max HOT 2 –...
Page 152 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 153 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 154 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 –...
Page 155 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 : –...
Page 156 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.13 – MISCELLANEOUS PARTICULAR TRANSPONDER USES 1 – Check transponder mode selector ....ON or ALT 2 –...
Page 157 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.13 – MISCELLANEOUS OXYGEN USE 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 –...
Page 158 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 3.13 – MISCELLANEOUS AIRSPEED INDICATING SYSTEM FAILURE Symptoms : erroneous indication in flight 1 – ”PITOT 1 HTR” switch ......CHECK ON 2 –...
Page 159 Back to Contents T B M SECTION 3 EMERGENCY PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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, –...
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Page 161 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS Page GENERAL 4.1.1 ........... AIRSPEEDS FOR NORMAL OPERATION 4.2.1 .
Page 162 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved TABLE OF CONTENTS (Continued) Page 4.4.32 MOTORING FOLLOWED BY AN ENGINE START ....4.4.34 AFTER STARTING ENGINE .
Page 163 D.G.A.C. 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.
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Page 165 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 4.2 – AIRSPEEDS FOR NORMAL OPERATION CONDITIONS : - Takeoff weight 6579 lbs (2984 kg) - Landing weight : 6250 lbs (2835 kg) Rotation airspeed (V –...
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Page 167 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 168 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) Figure 4.3.1 – PREFLIGHT INSPECTION Page 4.3.2 Rev. 2...
Page 169 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) A – INSIDE INSPECTIONS Cockpit – CRASH lever ........1 –...
Page 170 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 12 – ECS panel – ”BLEED VALVE” switch ......–...
Page 171 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) CAUTION BEFORE SELECTING SOURCE, CHECK : 20 – ”IGNITION” switch ......AUTO or OFF 21 –...
Page 172 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 30 – ECS panel – ”LT TEST” push button (if vapor cycle cooling system installed) ... . PRESS (green lamp ON) 31 –...
Page 173 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 36 – EXT LIGHTS panel – ”STROBE” ......... –...
Page 174 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) B – AIRPLANE OUTSIDE L.H. wing 1 – Flap ..........CHECK (Condition / Play) 2 –...
Page 175 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 13 – L.H. main landing gear – Shock–absorber / doors / tire / wheel arch ....... . CHECK Fuselage forward section 1 –...
Page 176 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 8 – Propeller and spinner ......CHECK (No nicks, cracks or oil leaks / Attachment) 9 –...
Page 177 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES PREFLIGHT INSPECTION (Cont’d) 10 – Aileron / spoiler ........CHECK (Condition / Free movement / Deflection) 11 –...
Page 178 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES BEFORE STARTING ENGINE CAUTION ”BLEED VALVE” 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 –...
Page 179 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES BEFORE STARTING ENGINE (Cont’d) 17 – ”SOURCE” selector ......BAT (or GPU) 18 –...
Page 180 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER CAUTION BEFORE SELECTING SOURCE, CHECK : 1 – ”IGNITION” switch ..... . . AUTO or OFF 2 –...
Page 181 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) 6 – FUEL panel – ”AUX BP” switch ........WARNING LIGHT AUX BP ON Î...
Page 182 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) 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 183 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) ENGINE START panel – ”IGNITION” switch ........AUTO –...
Page 184 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) 9 – Condition lever ........HI / IDLE CHECK : Ng ' 10 –...
Page 185 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) 1 – GPU ........CONNECTED 2 –...
Page 186 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) 4 – FUEL panel – ”AUX BP” switch ........WARNING LIGHTS AUX BP ON Î...
Page 187 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) 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 188 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) ENGINE START panel – ”IGNITION” switch ........AUTO –...
Page 189 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) 7 – ”SOURCE” selector ........Î...
Page 190 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES MOTORING CAUTION AFTER ANY STARTING INTERRUPT PROCEDURE : – WAIT FOR ENGINE TOTAL SHUT–DOWN – WAIT AT LEAST 30 SECONDS BEFORE INITIATING A MOTORING 1 –...
Page 191 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES MOTORING (Cont’d) 3 – ”IGNITION” switch ........Î...
Page 192 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES MOTORING FOLLOWED BY AN ENGINE START Within starter operating limits (continuous max. 1 minute), it is possible to initiate a starting procedure from a motoring procedure. 1 –...
Page 193 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (Cont’d) 5 – After 15 seconds : – ”IGNITION” switch ......AUTO or ON –...
Page 194 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES AFTER STARTING ENGINE 1 – GYRO INST panel – All switches ........Pull on the caging knobs when starting the ADI(s).
Page 195 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES AFTER STARTING ENGINE (Cont’d) 5 – ”GENERATOR” selector – On ”MAIN” ....Voltage and current checked when current ≤...
Page 196 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES TAXIING 1 – ”TAXI” light ......... . . 2 –...
Page 197 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES BEFORE TAKEOFF 1 – Parking brake ........WARNING LIGHT PARK BRAKE 2 –...
Page 198 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES BEFORE TAKEOFF (Cont’d) – ”PITOT 2 & STALL HTR” switch ..... . . 7 –...
Page 199 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES TAKEOFF WHEN LINED UP CAUTION – IF HEAVY PRECIPITATION, TURN IGNITION AND INERT SEP – IF ICING CONDITIONS ARE FORESEEN, REFER TO CHAPTER 4.5, PARAGRAPH ”FLIGHT INTO KNOWN ICING CONDITIONS”...
Page 200 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES TAKEOFF (Cont’d) 8 – Brakes ........RELEASED 9 –...
Page 201 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES CLIMB 1 – Power lever ......ADJUST according to engine operation table –...
Page 202 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES CRUISE 1 – Power lever ......ADJUST according to engine operation table –...
Page 203 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES DESCENT 1 – Altimeter settings ......COMPLETE 2 –...
Page 204 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES BEFORE LANDING Long final 1 – Altimeters ........CHECK 2 –...
Page 205 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES LANDING 1 – Power lever ......... IDLE After wheel touch 2 –...
Page 206 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES GO–AROUND 1 – Simultaneously – Power lever ....... TRQ = 100 % –...
Page 207 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES TOUCH AND GO After wheel touch 1 – Flaps ..........2 –...
Page 208 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES SHUT–DOWN 1 – Parking brake ........WARNING LIGHT PARK BRAKE 2 –...
Page 209 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved CHECK–LIST PROCEDURES SHUT–DOWN (Cont’d) 13 – INT LIGHTS panel – All switches ........14 –...
Page 210 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 4.3.44 Rev. 6...
Page 211 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 4.4 – AMPLIFIED PROCEDURES PREFLIGHT INSPECTION A – INSIDE INSPECTIONS Cockpit – CRASH lever ........1 –...
Page 212 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 8 – Landing gear emergency control Open door of emergency landing gear compartment. – Lever ........PULLED DOWN –...
Page 213 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 214 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 24 – Voltage ......... . CHECK –...
Page 215 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 28 – Oxygen emergency Î Î Î Î Î Î Î Î Î Î Î Î system ... OXYGEN WARNING LIGHT Î...
Page 216 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 33 – ”PITOT 1 HTR” switch ....... . . Î...
Page 217 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 37 – Reentering the airplane – EXT LIGHTS panel ....ALL SWITCHES OFF –...
Page 218 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 ducts may be very hot.
Page 219 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 2 – Aileron and trim / Spoiler ......CHECK (Condition / Free movement / Deflection) Ensure there are no foreign objects in the spoiler recess.
Page 220 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 11 – Wing deicer boots ....... . . CHECK (Condition / Attachment) Care must be taken when refuelling the airplane to avoid damaging...
Page 221 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) Fuselage forward section 1 – Baggage compartment – Inside ........CONTROLLED –...
Page 222 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 8 – Propeller and spinner ......CHECK (No nicks, cracks or oil leaks / Attachment) In case of operation from contaminated runways, it is necessary to...
Page 223 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 4 – Stall warning ........CHECK (Condition / Deflection) 5 –...
Page 224 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES PREFLIGHT INSPECTION (Cont’d) 4 – Horizontal stabilizer deicer boots (R.H. side) ......CHECK (Condition / Attachments) 5 –...
Page 225 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 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.
Page 226 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (Cont’d) 8 – R.H and L.H. pedals ......ADJUSTED 9 –...
Page 227 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (Cont’d) 18 – ”BAT TEMP TEST” push–button (if installed) ..PRESS Check illumination of the ”BAT OVHT”...
Page 228 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE STARTING ENGINE (Cont’d) 23 – Engine instruments ....... . CHECK 24 –...
Page 229 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER CAUTION BEFORE SELECTING SOURCE, CHECK : 1 – ”IGNITION” switch ..... . . AUTO or OFF 2 –...
Page 230 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) 7 – Propeller ........AREA CLEAR 8 –...
Page 231 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) NOTE : No action is required for the following conditions : – ITT from 8005 C to 8705 C limited to 20 seconds, –...
Page 232 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) – Ng The start sequence must be timed to ensure starter limits are not exceeded. Lengthy operation of the starter results in excessive temperature of the engine : –...
Page 233 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) Monitor increase of : – ITT ....(max.
Page 234 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER (Cont’d) Î Î Î Î Î Î Î Î Î Î Î Î 12 – Generator ..WARNING LIGHT MAIN GEN Î...
Page 235 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Rev. 8 Page 4.4.23B...
Page 236 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) Before connecting GPU, check that its indicated voltage is correct. 1 – GPU ........CONNECTED 2 –...
Page 237 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) 4 – FUEL panel – ”AUX BP” switch ........WARNING LIGHTS AUX BP ON Î...
Page 238 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) 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 239 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) Wait ITT < 8005 C, then : ”STARTER” switch ........BEFORE ANY RESTARTING ATTEMPT, CARRY OUT A MOTORING (Refer to paragraph ”MOTORING”) CONTINUE WITH NORMAL PROCEDURE HEREAFTER...
Page 240 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) ENGINE START panel – ”IGNITION” switch ........AUTO –...
Page 241 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES STARTING ENGINE USING EXTERNAL POWER (GPU) (Cont’d) 7 – ”SOURCE” selector ........Î...
Page 242 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES MOTORING To drain fuel accumulated inside the combustion chamber, a motoring procedure is required following an aborted start. A 15–second dry motoring run is sufficient to clear any fuel pooled in the engine. Fuel removed in this manner is collected and not drained under the engine.
Page 243 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES MOTORING (Cont’d) 2 – FUEL panel – Tank selector ........L or R –...
Page 244 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START Amplified procedures stated in starting engine sequences using airplane power or with GPU are also to be applied to hereunder procedure.
Page 245 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (Cont’d) 5 – After 15 seconds : – ”IGNITION” switch ......AUTO or ON –...
Page 246 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START (Cont’d) 10 – FUEL panel – ”AUX BP” switch ....... . AUTO Î...
Page 247 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Rev. 8 Page 4.4.33B...
Page 248 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE 1 – GYRO INST panel – All switches ........Pull on the caging knobs when starting the ADI(s).
Page 249 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (Cont’d) – ”R.WINDSHIELD” switch (if installed) ....Check illumination of the green light located above the switch (except if hot conditions)
Page 250 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (Cont’d) – ”AIRFRAME DE ICE” switch ......–...
Page 251 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (Cont’d) – ”BLEED VALVE” switch ....ON (LO or HI) –...
Page 252 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES AFTER STARTING ENGINE (Cont’d) 10 – ”EFIS MASTER” switch (if installed) ..... –...
Page 253 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TAXIING 1 – ”TAXI” light ......... . . 2 –...
Page 254 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TAXIING (Cont’d) 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 255 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF 1 – Parking brake ........WARNING LIGHT PARK BRAKE 2 –...
Page 256 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (Cont’d) If there is standing water or other contamination on the runway : – ”INERT SEP” switch ......Left ON WARNING LIGHT INERT SEP...
Page 257 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE TAKEOFF (Cont’d) 12 – Trims – Pitch ........ADJUSTED –...
Page 258 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TAKEOFF 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 259 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TAKEOFF (Cont’d) 6 – Radar switch (if installed) ..... . . As required 7 –...
Page 260 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TAKEOFF (Cont’d) 13 – Landing gear control ..(IAS < 128 KIAS) ... . At sequence end, check : All warning lights OFF In practice, if preconized attitude is kept, there is no difficulty to maintain a speed <...
Page 261 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TAKEOFF (Cont’d) 6 – Radar switch (if installed) ..... . . As required 7 –...
Page 262 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TAKEOFF (Cont’d) 13 – Landing gear control ..(IAS < 128 KIAS) ... . During the sequence : –...
Page 263 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES CLIMB 1 – Power lever ......ADJUST according to engine operation table –...
Page 264 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES CLIMB (Cont’d) 3 – ECS panel – Cabin altitude selector ..Cruise altitude + 1000 feet –...
Page 265 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES CRUISE 1 – Power lever ......ADJUST according to engine operation table –...
Page 266 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES CRUISE (Cont’d) 3 – Fuel – Gages ......... CHECK REGULARLY CHECK : –...
Page 267 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES DESCENT 1 – Altimeter settings ......COMPLETE 2 –...
Page 268 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE LANDING Long final 1 – Altimeters ........CHECK 2 –...
Page 269 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES DESCENT 1 – Altimeter settings ......COMPLETE 2 –...
Page 270 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE LANDING Long final 1 – Altimeters ........CHECK 2 –...
Page 271 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES BEFORE LANDING (Cont’d) 10 – 11 – Approach speed (Flaps LDG) ..... . . 80 KIAS To ensure positive and rapid engine response to throttle movement, it is recommended that a minimum of 10 % torque be maintained on...
Page 272 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES LANDING 1 – Power lever ......... IDLE Avoid three–point landings.
Page 273 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 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 274 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES LANDING 1 – Power lever ......... IDLE Avoid three–point landings.
Page 275 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES GO–AROUND 1 – Simultaneously – Power lever ....... TRQ = 100 % –...
Page 276 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES TOUCH AND GO After wheel touch 1 – Flaps ..........Check that flaps have well reached the TO position before increasing power.
Page 277 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES AFTER LANDING RUNWAY CLEAR – AIRPLANE STOPPED 1 – DE ICE SYSTEM panel – ”AIRFRAME DE ICE” switch ......–...
Page 278 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES SHUT–DOWN 1 – Parking brake ........WARNING LIGHT PARK BRAKE 2 –...
Page 279 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved AMPLIFIED PROCEDURES SHUT–DOWN (Cont’d) 9 – ”AP / TRIMS MASTER” switch ......10 –...
Page 280 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved INTENTIONALLY LEFT BLANK Page 4.4.60 Rev. 6...
Page 281 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 282 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 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 283 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES FLIGHT INTO KNOWN ICING CONDITIONS (Cont’d) 2 – When operating under IMC : – All ”DE ICE SYSTEM” switches ......–...
Page 284 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 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).
Page 285 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved 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 : –...
Page 286 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES FLIGHT INTO SEVERE ICING THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO SEVERE IN–FLIGHT ICING : – Visible rain at temperatures below 0°C ambient air temperature, –...
Page 287 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES FLIGHT INTO SEVERE ICING CONDITIONS (Cont’d) 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 288 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. 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 289 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW (Cont’d) Before takeoff 1 – If the runway is long enough, takeoff should be performed with the flaps in the up position.
Page 290 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Refer if required to paragraph ”UTILIZATION BY COLD WEATHER AND VERY COLD WEATHER”. Preflight inspection 1 –...
Page 291 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS (Cont’d) Landing After wheel touch 1 – Use reverse only if necessary and very progressively by monitoring the airplane behaviour.
Page 292 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 5 C TO – 25 5 C) AND VERY COLD WEATHER (– 25 5 C TO – 40 5 REMARK : The procedures hereafter supplement the normal procedures for the airplane use when operating under temperatures between 0 5...
Page 293 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) ENVELOPE 1 The procedures hereafter supplement the normal procedures for the airplane use when operating in the ”envelope 1”...
Page 294 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) Taxiing / Before takeoff / Takeoff 1 –...
Page 295 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) ENVELOPE 2 The procedures hereafter supplement or replace the normal procedures for the airplane use when operating in the ”envelope 2”...
Page 296 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) 6 –...
Page 297 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) 3 –...
Page 298 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) Ng ' 13 % –...
Page 299 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) After starting the engine 1 –...
Page 300 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) ENVELOPE 3 The procedures defined for the ”envelope...
Page 301 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER (– 0 °C to – 25 °C) AND VERY COLD WEATHER (– 25 °C to – 40 °C) (Cont’d) Taxiing / Before takeoff / Takeoff Apply procedures defined for Envelope...
Page 302 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES LANDING PROCEDURE WITH STRONG HEADWIND OR CROSSWIND If landing must be performed with strong headwind or crosswind, increase approach speed by the greatest of these 2 following values : ( WIND DOWN * 10 ) –...
Page 303 Back to Contents SECTION 4 T B M NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES LANDING PROCEDURE WITH STRONG HEADWIND OR CROSSWIND (Cont’d) Do not try to maintain the airplane when pushing the elevator control just after the touch ; this operation may provide pitch oscillations while increasing the yaw movement to the wind.
Page 304 Back to Contents T B M SECTION 4 NORMAL PROCEDURES PILOT’S INFORMATION MANUAL D.G.A.C. Approved PARTICULAR PROCEDURES UTILIZATION ON GRASS RUNWAY CAUTION THE SMALL WHEELS OF THE AIRPLANE AND ITS WEIGHT MAY LEAD IT TO SINK IN SOPPY OR LOOSE GROUND Before planing the landing, ensure that the field is hard, smooth and dry enough.
Page 305 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL SECTION 5 PERFORMANCE TABLE OF CONTENTS Page ACOUSTIC LIMITATION 5.1.1 ........AIRSPEED CALIBRATION 5.2.1 .
Page 306 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL TABLE OF CONTENTS (Continued) Page 5.11 TIME, CONSUMPTION AND DESCENT DISTANCE 5.11.1 ..5.12 HOLDING TIME 5.12.1 ..........5.13 LANDING DISTANCES 5.13.1...
Page 307 OACI, Annex 16, 80 dB(A) 73.3 dB(A) Chapter 6, Appendix 3 OACI, 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. Rev. 5 Page 5.1.1...
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Page 309 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. 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...
Page 310 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. 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...
Page 311 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 5.3 – CABIN PRESSURIZATION ENVELOPE Cabin altitude (feet) É É 8850 ft cabin É É É É 8000 É É É É PRESSURIZATION USEFUL 7000 ENVELOPE É É É É 6000 É...
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Page 313 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 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...
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Page 315 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. Approved 5.5 – STALL SPEEDS CONFIG. BANK AIR– FLIGHT 0° 30° 45° 60° PLANE IDLE WEIGHT Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 4850 lbs (2200 kg) 5512 lbs (2500 kg)
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Page 317 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 5.6 – WIND COMPONENTS 50 ° EXAMPLE : Angle between wind direction and flight path Headwind 8 kts Crosswind 10 kts Wind speed 13 kts FLIGHT 25 kt : DEMONSTRATED CROSSWIND PATH 0°...
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Page 319 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 5.7 – ENGINE OPERATION The following tables must be used during normal operation of the airplane. The following conditions are given : – Np = 2000 RPM, – BLEED LO. The torque must be set at or below the value corresponding to the local conditions of flight level and temperature.
Page 320 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL ENGINE OPERATION Maximum climb power (FL ≤ 200) Conditions : Landing gear and flaps UP IAS = 130 KIAS – Np = 2000 RPM – BLEED LO NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed T°...
Page 321 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL ENGINE OPERATION Maximum climb power (FL w Conditions : 200) Landing gear and flaps UP IAS = 130 KIAS – Np = 2000 RPM – BLEED LO NOTE : Add 1 % of TRQ for each additional 10 KCAS on climb airspeed T°...
Page 322 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL ENGINE OPERATION Maximum cruise power (FL v Conditions : 200) Landing gear and flaps UP Np = 2000 RPM – BLEED LO NOTE : Use preferably recommended cruise power T°...
Page 323 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL ENGINE OPERATION Maximum cruise power (FL w Conditions : 200) Landing gear and flaps UP Np = 2000 RPM – BLEED LO NOTE : Use preferably recommended cruise power T°...
Page 324 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL Figure 5.7.3 – ENGINE OPERATION Normal (recommended) cruise power (FL ≤ 200) Conditions : Landing gear and flaps UP Np = 2000 RPM – BLEED LO T° (°C) FLIGHT LEVEL (FL) IOAT –...
Page 325 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL ENGINE OPERATION Normal (recommended) cruise power (FL w Conditions : 200) Landing gear and flaps UP Np = 2000 RPM – BLEED LO T° (°C) FLIGHT LEVEL (FL) IOAT –...
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Page 327 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. Approved 5.8 – TAKEOFF DISTANCES WEIGHT : 5512 lbs (2500 kg) Associated conditions – Landing gear DN and flaps TO – 10° of attitude – TRQ = 100 % –...
Page 328 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. Approved TAKEOFF DISTANCES WEIGHT : 6579 lbs (2984 kg) Associated conditions – Landing gear DN and flaps TO – 10° of attitude – TRQ = 100 % –...
Page 329 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. Approved 5.9 – CLIMB PERFORMANCE CLIMB SPEEDS (IAS = 130 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 130 KIAS – BLEED LO RATE OF CLIMB (ft/min) Pressure Pressure...
Page 330 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. Approved CLIMB PERFORMANCE CLIMB SPEEDS (IAS = 160 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 160 KIAS – BLEED LO RATE OF CLIMB (ft/min) Pressure Pressure Airplane...
Page 331 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS ) Conditions : ISA – 205 Maximum climb power Landing gear and flaps UP IAS = 130 KIAS – 2000 RPM – BLEED LO NOTE : Time, consumption and distance from takeoff WEIGHT...
Page 332 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 130 KIAS – 2000 RPM – BLEED LO NOTE : Time, consumption and distance from takeoff WEIGHT...
Page 333 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 130 KIAS) Conditions : ISA + 20 Maximum climb power Landing gear and flaps UP IAS = 130 KIAS – 2000 RPM – BLEED LO NOTE : Time, consumption and distance from takeoff WEIGHT...
Page 334 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA – 20 Maximum climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; – 4 KIAS / 2000 ft then 2000 RPM –...
Page 335 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : Maximum climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; – 4 KIAS / 2000 ft then 2000 RPM –...
Page 336 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CLIMB PERFORMANCE TIME, CONSUMPTION AND CLIMB DISTANCE (IAS = 160 KIAS) Conditions : ISA + 205 Maximum climb power Landing gear and flaps UP IAS = 160 KIAS up to 20000 ft ; – 4 KIAS / 2000 ft then 2000 RPM –...
Page 337 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 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 altitude weight (feet)
Page 338 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 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 altitude weight...
Page 339 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 5.10 – CRUISE PERFORMANCE Conditions : Weight 5512 lbs (2500 kg) Flight level (FL) IRCR NOCR MXCR LRCR (KTAS) Figure 5.10.1 – CRUISE PERFORMANCE Rev. 2 Page 5.10.1...
Page 340 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Maximum cruise Conditions : ISA – 205 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 341 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Maximum cruise Conditions : ISA – 105 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 342 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Maximum cruise Conditions : ISA – 55 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 343 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Maximum cruise Conditions : Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs...
Page 344 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 55 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 345 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 105 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 346 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Maximum cruise Conditions : ISA + 205 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Use preferably recommended cruise power AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 347 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA – 205 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs...
Page 348 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA – 105 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs...
Page 349 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA – 55 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs...
Page 350 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Normal (recommended) cruise Conditions : Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs...
Page 351 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 55 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs...
Page 352 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 105 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs...
Page 353 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Normal (recommended) cruise Conditions : ISA + 205 Landing gear and flaps UP 2000 RPM (*) – BLEED LO NOTE : Power recommended by PRATT & WHITNEY CANADA AIRSPEEDS (kt) Fuel flow 4850 lbs...
Page 354 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Intermediate cruise Conditions : ISA – 205 Landing gear and flaps UP 2000 RPM (*) – BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT...
Page 355 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Intermediate cruise Conditions : ISA – 105 Landing gear and flaps UP 2000 RPM (*) – BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT...
Page 356 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Intermediate cruise Conditions : ISA – 55 Landing gear and flaps UP 2000 RPM (*) – BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT...
Page 357 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Intermediate cruise Conditions : Landing gear and flaps UP 2000 RPM (*) – BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT altitude (2200 kg)
Page 358 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 55 Landing gear and flaps UP 2000 RPM (*) – BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT...
Page 359 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 105 Landing gear and flaps UP 2000 RPM (*) – BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT...
Page 360 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL CRUISE PERFORMANCE Intermediate cruise Conditions : ISA + 205 Landing gear and flaps UP 2000 RPM (*) – BLEED LO AIRSPEEDS (kt) Fuel flow 4850 lbs 5512 lbs 6173 lbs Pressure IOAT...
Page 361 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 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 (*) –...
Page 362 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 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 (*) –...
Page 363 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 5.11 – TIME, CONSUMPTION AND DESCENT DISTANCE Conditions : Power as required to maintain constant Vz Landing gear and flaps UP CAS = 230 KCAS – 2000 RPM – BLEED LO Vz = 1500 ft/min Vz = 2000 ft/min Vz = 2500 ft/min...
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Page 365 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL 5.12 – HOLDING TIME Conditions : Landing gear and flaps UP IAS = 120 KIAS – 2000 RPM – BLEED LO TRQ ] 30 % FUEL USED DURING HOLDING TIME Weight 4850 lbs (2200 kg) Weight 5512 lbs (2500 kg) Pressure...
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Page 367 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. Approved 5.13 – LANDING DISTANCES WEIGHT : 6250 lbs (2835 kg) Associated conditions – Landing gear DN and flaps LDG – Approach speed 80 KIAS – Touch–down speed 65 KIAS –...
Page 368 Back to Contents T B M SECTION 5 PERFORMANCE PILOT’S INFORMATION MANUAL D.G.A.C. Approved LANDING DISTANCES WEIGHT : 5071 lbs (2300 kg) Associated conditions – Landing gear DN and flaps LDG – Approach speed 80 KIAS – Touch–down speed 60 KIAS –...
Page 369 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL SECTION 6 WEIGHT AND BALANCE TABLE OF CONTENTS Page GENERAL 6.1.1 ........... AIRPLANE WEIGHING PROCEDURES 6.2.1 .
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Page 371 PILOT’S INFORMATION MANUAL 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...
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Page 373 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL 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.
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Page 375 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL 6.3 – BAGGAGE LOADING There are two baggage compartments : – one in fuselage non pressurized forward section, between firewall and cockpit with maximum baggage capacity of 110 lbs (50 kg). –...
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Page 377 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL 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 378 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL 3 – Utilization of weight and balance graph : – Record airplane basic characteristics in ¬ – Compute basic index with the formula described in and record the result in ®...
Page 379 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL Figure 6.4.1 – LOADING SAMPLE (in Kg and Litres) Rev. 5 Page 6.4.3...
Page 380 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL Figure 6.4.1A – LOADING SAMPLE (in lbs and us gal) Page 6.4.4 Rev. 5...
Page 381 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL Figure 6.4.2 – WEIGHT AND BALANCE GRAPH (in Kg and Litres) Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Rev.
Page 382 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL Figure 6.4.2A – WEIGHT AND BALANCE GRAPH (in lbs and us gal) Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Page 6.4.6 Rev.
Page 383 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL Figure 6.4.3 – WEIGHT AND BALANCE GRAPH (in Kg and Litres) Valid S / N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Rev.
Page 384 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL Figure 6.4.3A – WEIGHT AND BALANCE GRAPH (in lbs and us gal) Valid S / N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Page 6.4.8 Rev.
Page 385 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL DETERMINING EMPTY AIRPLANE CHARACTERISTICS Empty airplane characteristics (weight and balance) may vary with regard to those indicated on weighing form according to installed optional equipment. List of equipment (paragraph 6.5) contains the standard and optional equipment, as well as their characteristics (weight, arm).
Page 386 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL ( do * 173 ) CG m.a.c.% + Use the above formula to express arm ”d ” in % of mean aerodynamic chord. NOTE : Arm expressed in inches with regard to reference. Front seats : 180.5 in.
Page 387 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL 6.5 – LIST OF EQUIPMENT The following list contains standard equipment installed on each airplane and available optional equipment. A separate list of equipment of items installed at the factory in your specific airplane is provided in your airplane file.
Page 388 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 01 – SPECIFIC OPTIONAL EQUIPMENT 01008 Flight inspection system capability NAVCAL 97.223 231.69...
Page 389 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 21 – ENVIRONMENTAL SYSTEM 21–20 – Distribution Cabin fan AVVC 00244 VETUS 3.307...
Page 390 (1.120) (2.700) Water separator 85020–8 GARRETT 2.249 94.49 (1.020) (2.400) 21–55 – Vapor cycle cooling system A 21001A Vapor cycle cooling system SOCATA 89.948 259.37 (TBM700A) (CASEY) (40.800) (6.588) A 21002A Vapor cycle cooling system – SOCATA 67.681 315.98 version A (KEITH) (30.700)
Page 391 KAS 297C (0.510) (3.950) P/N 065–00089–0004 Amplifier separator KA 25A KING 1.279 194.88 P/N 071–02008–0000 (0.580) (4.950) Amplifier separator A21 SOCATA 1.279 194.88 (0.580) (4.950) Audio alerter KAA 15 KING 0.750 171.26 P/N 071–01466–0000 (0.340) (4.350) Pitch servo KS 270A KING 2.601...
Page 392 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) Yaw rate gyro KRG 331 KING 0.750 171.26 P/N 060–00024–0000 (0.340)
Page 393 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 23 – COMMUNICATIONS Antenna 16–21B–P3 CHELTON 1.036 192.91 (0.470) 267.72...
Page 394 EFIS –1.560) (3.854) O 23005B COM1–NAV # 1 KX 165–25 with KING –3.000 152.13 EFIS –1.360) (3.864) A 23006A Passengers address system SOCATA 0.992 230.31 (0.450) (5.850) A 23007A COM1–COM2 KTR 908 KING 13.942 232.13 (6.324) (5.896) A 23008A Audio control box KMA 24H–52 KING 1.984...
Page 395 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) A 23014A VHF COM # 1 KY 196B KING 2.998 153.54...
Page 396 (3.250) priority) Electric power center 11.023 127.95 160GC02Y05 (Freon + ignition (5.000) (3.250) priority + contact splitting) S/N 92–9999 and S/N 1–92 after SB 70–031–24 Stand–by generator SOCATA 12.125 102.36 T700A2430045900 (5.500) (2.600) Stand–by generator SOCATA 12.125 102.36 T700A2430080900 (5.500) (2.600)
Page 397 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 24–40 – External power supply Ground power receptacle MS QPL (AIRCRAFT 0.794 114.17...
Page 398 REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 25 – EQUIPMENT AND FURNISHINGS A 25001A Toilets SOCATA 30.055 285.91 (13.633) (7.262) A 25003A Pilot piddle pak SOCATA 0.220 174.01 (TBM700A) (0.100) (4.420)
Page 399 PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) A 25007A Retractable table SOCATA 4.123 244.25 (1.870) (6.204) A 25009A Audio cabinet SOCATA 21.429 205.04 (TBM700A) (9.720) (5.208) A 25009B Audio cabinet –...
Page 400 REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) O 25025B Cabin furnishings ”VIP” SOCATA 7.720 288.38 (TBM700B) 3.500) (7.325) A 25026A Partition net between the cabin and SOCATA 2.756 289.53 the baggage compartment (1.250)
Page 401 (34.000) (6.891) – Valid up to S/N 67, plus S/N 72 to 75, except airplanes equipped as a retrofit with MOD70–023–25 . Rear divan T700A252123000 SOCATA 57.319 271.30 (26.000) (6.891) – Valid from S/N 68, except S/N 72 to 75, plus airplanes equipped as a retrofit with MOD70–023–25...
Page 402 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) A 25002B TBM700A 7–place accomodation : 30.137 237.76 13.670) (6.039)
Page 403 REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 25–60 – Emergency equipment A 25019A Axe SOCATA 2.425 195.28 (1.100) (4.960) A 25020A First aid kit SOCATA 3.968 285.43 (1.800) (7.250) 25–61 – Emergency locator...
Page 404 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 26 – FIRE PROTECTION A 26001A Portable fire extinguisher unit FH AREOFEU 4.850 176.38...
Page 405 395.27 (0.700) (10.040) Trim and flap indicator 4724 PEKLY S.A 1.102 159.45 (0.500) (4.050) A 27001A AFC and electric trim control on SOCATA 0.882 157.48 R.H. control wheel (0.400) (4.000) 27–30 – Pitch control Pitch trim actuator 145400–01 LPMI 1.213 425.20...
Page 406 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 28 – FUEL SYSTEM 28–20 – Fuel supply Electric boost pump 2003–B WELDON 3.483...
Page 407 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) Inboard L.H. probe 768–403 INTER– 0.331 183.07 TECHNIQUE (0.150) (4.650)
Page 408 REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 30 – ICE AND RAIN PROTECTION Deicer T700A5520015006(920), SOCATA 3.307 403.15 L.H. elevator horn (1.500) (10.240) Deicer T700A5520015007(921), SOCATA 3.307 403.15 R.H. elevator horn (1.500) (10.240)
Page 409 REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) Deicer T700A3010012000, SOCATA 2.646 173.23 outboard L.H. wing (with radar (1.200) (4.400) OPT70 34007A) 30–40 – Windshield deicing Windshield heater controller WH AIR SYSTEMS 0.992...
Page 410 (0.250) (3.970) O 31002B Hourmeter 56457–3 (flying time) DATCON 0.551 156.30 (0.250) (3.970) 31–50 – Aural warning Aural warning system SOCATA 0.661 183.07 T700A3155011000 (0.300) (4.650) 31–60 – Visual warning Advisory panel AP 89–11 AIR SYSTEMS 4.409 157.48 (2.000)
Page 411 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 32 – LANDING GEARS 32–10 – Main landing gear L.H.
Page 412 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 32–40 – Wheels and brakes Brake assembly 030–19100 PARKER 14.991 204.33...
Page 413 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 33 – LIGHTS 33–10 – Instrument panel lighting L.H.
Page 414 INSTRUMENTS (0.400) (4.400) Pitot heated probe AN 5812–1 QPL (AIRCRAFT 0.750 200.79 APPLIANCES (0.340) (5.100) AND EQUI. LTD) Static reference plug SOCATA Negligible T700A3415017 Static reference selector TB30 SOCATA 0.220 157.48 77010000 (0.100) (4.000) Vertical speed indicator 2” 7201 UNITED 1.102...
Page 415 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) VMO n P switch 32202 HYDRA 0.220 141.73 ELECTRIC (0.100)
Page 416 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) HSI KI 525A P/N 066–03046–0001 KING 3.946 157.48 (1.790) (4.000)
Page 417 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) O 34002D Electric standby horizon 3.086 153.54 505.2BSK / 7°...
Page 418 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) O 34020B RMI 1 KNI 582 (L.H. instrument KING 2.998 172.83...
Page 419 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) MARKER antenna DM N27–3 DORNE & 0.750 129.92 MARGOLIN (0.340)
Page 420 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) A 34007E Weather radar RDS 81, EFIS KING 27.998 164.17...
Page 421 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) A 34025H Weather radar RDS 82, EFIS KING 19.400 171.26...
Page 422 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 34037F Radioaltimeter KRA 405B, EFIS KING coupled –...
Page 423 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 34–51 – NAV 1 installation VHF NAV # 1 KNS 80 KING 5.952 151.57...
Page 424 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) O 34026A Transponder # 1 KT 70 KING 7.319 149.61...
Page 425 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) – 2 antennas KA 44B KING 5.600 213.03 (2.540) (5.411)
Page 426 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) A 34006A LORAN–C 604 APOLLO 4.850 170.47 (2.200) (4.330) 34–57 –...
Page 427 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 34–62 – Multifunction display (TBM700B) A 34054A MFD KMD 850 (with indicator on HONEYWELL 6.415 153.54...
Page 428 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 35 – OXYGEN 180.31 (4.580) 0.948 209.84 Generator 117024–02 PURITAN (0.430)
Page 429 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 37 – VACUUM Air ejector valve 19E17–5A LUCAS 0.661 116.14...
Page 430 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 52 – DOORS A 52002A ”Pilot” door SOCATA 44.092 171.26 (TBM700B) (20.000) (4.350) Page 6.5.44 Rev. 9...
Page 431 (kg) 56 – WINDOWS O 56001A Deiced R.H. windshield 1.764 158.27 0.800) (4.020) Window and capability of camera/observation : A 56002A – 6 Pax standard SOCATA 143.299 242.36 (65.000) (6.156) A 56002B – Camera capability SOCATA 89.132 239.96 (40.430) (6.095) A 56002C –...
Page 432 WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 57 – WINGS O 57001A Utilization on runways covered with SOCATA –7.716 200.00 melting snow –3.500) (5.080) Page 6.5.46 Rev. 9...
Page 433 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 61 – PROPELLER 61–10 – Propeller assembly Propeller HC–E4N.3 / E 9083 S (K) HARTZELL 153.220...
Page 434 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 71 – POWER PLANT Turbogenerator PT6 A–64 P &...
Page 435 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 77 – ENGINE INDICATING Compressor turbine QPL (AIRCRAFT 0.981 108.27 tacho–generator (Ng)
Page 436 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) Flowmeter 90 12 00 : – Indicator 912080–38 SHADIN 0.930...
Page 437 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL WEIGHT REQUIRED (R) OR STANDARD (S) ITEM EQUIPMENT per unit OR OPTIONAL (A or O) OPT70 SUPPLIER EQUIPMENT (kg) 79 – LUBRICATION 79–20 – Distribution Oil cooler L8538233 LORI 10.472 90.55...
Page 438 Back to Contents T B M SECTION 6 WEIGHT AND BALANCE PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 6.5.52 Rev. 9...
Page 439 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL SECTION 7 DESCRIPTION TABLE OF CONTENTS Page GENERAL 7.1.1 ........... AIRFRAME 7.2.1 .
Page 440 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL TABLE OF CONTENTS (Continued) Page POWER PLANT 7.6.1 ..........7.6.1 TURBOGENERATOR UNIT OPERATION .
Page 441 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL TABLE OF CONTENTS (Continued) Page AIR CONDITIONING AND PRESSURIZATION 7.9.1 ... . 7.9.1 AIR CONDITIONING ..........7.9.5 PRESSURIZATION .
Page 442 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.0.4 Rev. 2...
Page 443 DESCRIPTION PILOT’S INFORMATION MANUAL 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 444 Back to Contents T B M SECTION 0 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.1.2 Rev. 2...
Page 445 SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.2 – AIRFRAME The TBM 700 is a six / seven–place, low wing airplane. The structure is a semi–monocoque all–metal construction and is equipped with a retractable tricycle landing gear. TBM700A : The pressurized cabin is equipped, on the left side of fuselage, with a two–piece door comprising integrated stairs allowing pilot and passengers...
Page 446 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.2.1 – CABIN ARRANGEMENT Page 7.2.2 Rev. 7...
Page 447 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 housing and sealed casings forming the fuel tank. The wing leading edge is equipped with a deicing system.
Page 448 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Wings characteristics : Area ......... . 193.75 sq.
Page 449 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 450 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.2.2 (2/2) – WING FLAPS Page 7.2.6 Rev. 7...
Page 451 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 452 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.2.8 Rev. 7...
Page 453 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 454 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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...
Page 455 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL The system uses : – the stall warning horn, – the VMO alarm, – AP alarms, – the landing gear control unit, – the flap geared motor, – (if installed) 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 456 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Upper panel (Figures 7.3.2 and 7.3.2A) The upper panel includes following elements : – the alarm loud–speaker (landing gear up with flaps extended and / or idle, stall), –...
Page 457 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 458 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.3.2D Rev. 6...
Page 459 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.1 – INSTRUMENT PANEL ASSEMBLY (Typical arrangement) Rev. 9 Page 7.3.3...
Page 460 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) L. H. side upper panel postlight 2) Buzzers (AP, landing gear not extended and V alarms) 3) Loud–speakers (radio and stall warning horn) 4) Cockpit floodlights (instrument panel emergency lighting) 5) R.
Page 461 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.2 (2/2) – UPPER PANEL AND COCKPIT OVERHEAD PANEL Typical arrangement – Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Rev.
Page 462 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 463 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.2A (2/2) – UPPER PANEL AND COCKPIT OVERHEAD PANEL Typical arrangement – Valid S / N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Rev.
Page 464 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) ”DE SYSTEM” panel 23) Landing gear configuration postlight control panel (Figure 7.5.1) 2) OAT indicator 24) Chronometer 3) Turn coordinator 25) Microphone switch oxygen 4) VOR / ILS 2 mask (Figure 7.10.1) 5) Suction indicator 26) Parking brake control...
Page 465 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.3 (2/2) – LEFT INSTRUMENT PANEL (Typical arrangement) Rev. 6 Page 7.3.7...
Page 466 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Stand–by compass 2) AP mode controller (see Section 9) 3) Advisory panel (Figure 7.3.8) 4) KMA selection box 5) VHF 1 6) RNAV 7) VHF 2 / VOR 2 8) ADF 9) ATC 10) DME...
Page 467 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.4 (2/2) – CENTRAL INSTRUMENT PANEL (Typical arrangement) Rev. 5 Page 7.3.9...
Page 468 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) ”FUEL” check and control panel (fuel pressure and quantity indicators, ”FUEL SEL” and ”AUX BP” switches) (Figure 7.7.3) 2) ”GYRO mode” indicator 3) Emergency beacon switch (not valid for UK) 4) Altimeter 2 5) Battery temperature indicator (if installed) (Figure 7.8.4) 6) Adjustable air outlet...
Page 469 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.5 (2/2) – RIGHT INSTRUMENT PANEL (Typical arrangement) Rev. 3 Page 7.3.11...
Page 470 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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...
Page 471 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.6 (2/2) – PEDESTAL CONSOLE (Typical arrangement) Rev. 2 Page 7.3.13...
Page 472 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.7 – CIRCUIT BREAKERS PANEL – Without ”pilot” door Page 7.3.14 Rev. 7...
Page 473 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.7A – CIRCUIT BREAKERS PANEL – With ”pilot” door Rev. 7 Page 7.3.15...
Page 474 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL MASTER General warning WARNING upon illumination of red warning light MASTER MASTER General warning General warning CAUTION upon illumination of amber warning light Inter turbine temperature ≥ 800°C Engine oil low pressure ≤...
Page 475 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.8 (2/2) – ADVISORY PANEL AND GENERAL ALARMS WARNING LIGHTS Rev. 6 Page 7.3.17...
Page 476 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL DOORS, WINDOWS AND EMERGENCY EXIT Cabin access door (Figure 7.3.9) The cabin two–piece access door (crew and passengers), located on the left side of fuselage aft of the wings, opens outside. Stairs are incorporated in the lower door.
Page 477 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.9 – CABIN ACCESS DOOR Rev. 7 TBM 700A – Door equipped with one cable Page 7.3.19...
Page 478 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL DOORS, WINDOWS AND EMERGENCY EXIT Cabin access door (Figure 7.3.9A) The cabin two–piece access door (crew and passengers), located on the left side of fuselage aft of the wings, opens outside. Stairs are incorporated in the lower door.
Page 479 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.9A – CABIN ACCESS DOOR Rev. 8 TBM 700A – Door equipped with two cables Page 7.3.19B...
Page 480 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL DOORS, WINDOWS AND EMERGENCY EXIT Cabin access door (Figure 7.3.9B) 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 481 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.9B – CABIN ACCESS DOOR Rev. 9 TBM 700B Page 7.3.19D...
Page 482 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 483 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Cockpit access door (Figure 7.3.9C) 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.
Page 484 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.9C – COCKPIT ACCESS DOOR (”PILOT” DOOR) Page 7.3.19G TBM 700B Rev. 9...
Page 485 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL CAUTION RETRACT FOOTSTEP BEFORE CLOSING ACCESS DOOR Fold and tilt footstep upwards. To close the door from outside the airplane, push the door until it aligns with fuselage and lock it by moving outside handle upwards, then fold handle in its recess.
Page 486 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL FWD baggage compartment door The FWD baggage compartment door is located on the airplane left side between the firewall and the front pressure bulkhead. It is hinged at the top. It is maintained in the up position by a compensation rod.
Page 487 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.10 – EMERGENCY EXIT Rev. 2 Page 7.3.21...
Page 488 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.11) L.H. and R.H. front seats are mounted on rails attached to the structure. Longitudinal position, height and back–rest tilting of each seat can be adjusted and the arm–rest is hinged.
Page 489 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.11A) 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 490 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL SEATS, BELTS AND HARNESSES Cockpit seats (Figure 7.3.11B) 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 491 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL BAGGAGE COMPARTMENTS There are two baggage compartments : An AFT compartment located in the pressurized cabin between rear passenger seats and rear pressure bulkhead. A FWD compartment (non–pressurized) located between firewall and fwd pressure bulkhead.
Page 492 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 493 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL (*) Oxygen masks (2) drawer in variant of R.H. rear seat Figure 7.3.11 (2/2) – SEATS Valid S / N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Rev.
Page 494 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 495 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL (*) Variant from S / N 68 except S / N 72, 73, 74 and 75 Figure 7.3.11A (2/2) – SEATS Valid S / N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with modification Nr MOD 70–019–25 Rev.
Page 496 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 497 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.11B (2/2) – SEATS Rev. 7 TBM 700B Page 7.3.29...
Page 498 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.3.12 – FRONT OR REAR SEAT BELT (with movable straps) AND HARNESSES Page 7.3.30 Rev. 7...
Page 499 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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)
Page 500 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 501 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.4.1 (2/2) – ROLL Rev. 2 Page 7.4.3...
Page 502 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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) –...
Page 503 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.4.2 (2/2) – LATERAL TRIM Rev. 2 Page 7.4.5...
Page 504 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.4.6 Rev. 2...
Page 505 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 506 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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) –...
Page 507 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.4.3 (2/2) – ELEVATOR Rev. 5 Page 7.4.9...
Page 508 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Cables 2) Pulleys 3) Pitch trim tabs 4) Actuating rods 5) Actuator 6) Pitch trim tab position indicator 7) Pitch trim control wheel 8) Pitch trim manual control Figure 7.4.4 (1/2) –...
Page 509 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.4.4 (2/2) – PITCH TRIM Rev. 5 Page 7.4.11...
Page 510 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.4.12 Rev. 2...
Page 511 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL RUDDER (Figure 7.4.5) The rudder is hinged on three fittings attached to the vertical stabilizer rear spar. Cables and a rod comprise the rudder pedals / rudder linkage. Pilot and R.H.
Page 512 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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) –...
Page 513 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.4.5 (2/2) – RUDDER Rev. 2 Page 7.4.15...
Page 514 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 515 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.4.6 (2/2) – RUDDER TRIM Rev. 5 Page 7.4.17...
Page 516 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.4.18 Rev. 2...
Page 517 SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.5 – LANDING GEAR The TBM 700 is equipped with electro–hydraulically actuated, fully retractable tricycle landing gear. Each landing gear has one wheel and an oil–air shock absorber integrated in the strut. Main landing gears swivel on two ball joints installed on wing spars. Each landing gear retracts toward airplane centerline.
Page 518 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL HYDRAULIC PRESSURE Hydraulic pressure required for landing gear operation and main landing gear door operation is accomplished : – during normal operation, by an electro–hydraulic generator with integrated reservoir, –...
Page 519 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 520 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 521 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.5.2 – EMERGENCY LANDING GEAR EXTENSION CONTROL Rev. 2 Page 7.5.5...
Page 522 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 523 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.5.3 – MINIMUM TURN DIAMETER (Full rudder pedals travel without using differential braking) Rev. 2 Page 7.5.7...
Page 524 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.5.4 – MINIMUM TURN DIAMETER (Full rudder pedals travel by using differential braking) Page 7.5.8 Rev. 2...
Page 525 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 526 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 527 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.5.5 (2/2) – BRAKE SYSTEM Rev. 6 Page 7.5.11...
Page 528 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.5.6 – PARKING BRAKE Page 7.5.12 Rev. 6...
Page 529 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.6 – POWER PLANT TURBOGENERATOR UNIT OPERATION (Figure 7.6.1) PRATT & WHITNEY CANADA power plant (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 530 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Propeller governor 2) Exhaust duct 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...
Page 531 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.6.1 (2/2) – POWER PLANT Rev. 2 Page 7.6.3...
Page 532 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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) –...
Page 533 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 : –...
Page 534 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL ”MAN OVRD” emergency fuel regulation lever Emergency fuel regulation lever is normally in locked position. In case of FCU or power lever failure, it allows setting engine power manually. Unlocking and locking are performed by pulling lever knob up.
Page 535 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Engine fire detection test knob (if installed) 2) Torque indicator 3) ”PROP O’SPEED TEST” knob 4) Propeller indicator 5) ITT indicator 6) ITT test knob 7) Ng indicator 8) Oil pressure and temperature indicator 9) Fuel flow indicator...
Page 536 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Fuel flow totalizer (FLOW) is a digital display instrument which indicates : – quantity of fuel consumed since beginning of flight, – instantaneous consumption, – remaining flight time depending on fuel quantity. NOTE : Each instrument is provided with marks indicating utilization limits.
Page 537 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 538 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 539 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.6.4 – ENGINE STARTING Rev. 5 Page 7.6.11...
Page 540 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL EXHAUST SYSTEM Exhaust gases are evacuated through exhaust nozzles 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 541 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 542 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 543 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.7 – FUEL SYSTEM (Figure 7.7.1) The fuel system comprises fuel tanks, fuel unit, selectors (manual and automatic), electric boost pump and main booster pump, engine fuel system, gaging installation, checking installation and drains.
Page 544 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 boost pump 11) Electric booster pump...
Page 545 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.7.1 (2/2) – FUEL SYSTEM Rev. 5 Page 7.7.3...
Page 546 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL TANK AUTOMATIC SELECTOR (Figures 7.7.3 and 7.7.4) Tank automatic selection allows, without pilot’s intervention, feeding the engine from one tank to the other in predetermined sequences. These sequences depend on airplane configuration (ground, in–flight, fuel low level warning lights illuminated).
Page 547 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Test for system proper operation ”SHIFT” push–knob allows the pilot to test system proper operation anytime. When the system operates, the fuel tank is changed when ”SHIFT” push–knob is pressed once. If airplane is on ground or in flight, low level warning lights not illuminated, the new selected tank remains operating and a new sequence is initiated.
Page 548 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.7.2 – MANUAL SELECTOR OF FUEL TANKS Page 7.7.6 Rev. 2...
Page 549 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.7.3 – FUEL CONTROL PANEL Valid from S / N 1 to 5 Rev. 2 Page 7.7.7...
Page 550 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.7.8 Rev. 2...
Page 551 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.7.3A – FUEL CONTROL PANEL Valid from S / N 6 Rev. 2 Page 7.7.9...
Page 552 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL MAIN BOOSTER PUMP The main booster 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 553 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL FUEL CONTROL INSTALLATION (Figure 7.7.3) Control 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.
Page 554 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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, on wing root side. These drains allow draining water or sediments contained in fuel.
Page 555 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.7.4 (2/2) – FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Rev. 5 Valid from S/N 1 to 92 Page 7.7.13...
Page 556 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.7.14 Rev. 5...
Page 557 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL FUEL SYSTEM DRAINING AND CLOGGING INDICATOR (Figure 7.7.4A) The fuel system comprises five drain points, a drain on the filter bowl, two drain valves on each tank, located on wing lower surface, one at wing root and the other past main landing gear well.
Page 558 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Lighting switch 2) Mirror door 3) Clogging indicator 4) Central access door 5) Filter drain 6) Tank drain 7) Drain bowl Figure 7.7.4A (1/2) – FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Page 7.7.16 Valid from S/N 93 to 9999...
Page 559 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.7.4A (2/2) – FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Rev. 5 Valid from S/N 93 to 9999 Page 7.7.17...
Page 560 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTENTIONALLY LEFT BLANK Page 7.7.18 Rev. 5...
Page 561 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 : –...
Page 562 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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”...
Page 563 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL DISTRIBUTION Airplane electrical systems are connected to ”BUS” bars and protected by circuit breakers located on L.H. side panel, near the pilot (See Figures 7.8.3, 7.8.3A and 7.8.3B) or on R.H. side panel, if ”pilot” door installed (See Figure 7.8.3C).
Page 564 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.8.1 – ELECTRICAL DIAGRAM Page 7.8.4 Rev. 6...
Page 565 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL FLAPS (D) STROBE PITOT 1 HTR R.W / S DE ICE INERT SEP AIRFRAME DE ICE ENGINE INDIC 1 : – torquemeter, propeller & oil press+temperature PHONE IGNIT COM 1 AUX BP ADVISORY 2...
Page 566 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL AP / TRIMS AP & trims general protec. ADVISORY 1 Visual warn. protec. RUD TRIM Rudder trim protec. ADVISORY 2 Visual warn. protec. AIL TRIM Aileron trim protec. AUDIO Audio warnings protec.
Page 567 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL (*) ”Pull–off” type circuit breaker in variant Figure 7.8.3 (2/2) – CIRCUIT BREAKER PANEL (Typical arrangement) Rev. 7 TBM 700A from S/N 1 to 10 Page 7.8.7...
Page 568 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL AP / TRIMS AP & trims general protec. ADVISORY 1 Visual warn. protec. RUD TRIM Rudder trim protec. ADVISORY 2 Visual warn. protec. AIL TRIM Aileron trim protec. AUDIO Audio warnings protec.
Page 569 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL (*) Circuit breaker which cannot be pulled off up to S / N 17 NOTE 1 : If ADF 2 is installed, its circuit breaker is installed on a free location, HSI RMI becomes HSI and ADF becomes ADF 1 RMI.
Page 570 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL AP / TRIMS AP & trims general protec. FUEL GAGE 1 L.H gage protec. RUD TRIM Rudder trim protec. FUEL GAGE 2 R.H gage protec. AIL TRIM Aileron trim protec. FUEL SEL Timer protec.
Page 571 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL NOTE 1 : If an additional equipment is installed, its circuit breaker is installed on a free location. Figure 7.8.3B (2/2) – CIRCUIT BREAKER PANEL (Typical arrangement) Rev. 8 TBM 700B without ”pilot”...
Page 572 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL AP / TRIMS AP & trims general protec. L LDG L.H. landing light protec. RUD TRIM Rudder trim protec. TAXI Taxi light protec. AIL TRIM Aileron trim protec. R LDG R.H.
Page 573 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL NOTE 1 : If an additional equipment is installed, its circuit breaker is installed on a free location. Figure 7.8.3C (2/2) – CIRCUIT BREAKER PANEL (Typical arrangement) Rev. 9 TBM 700B with ”pilot”...
Page 574 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 575 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 –...
Page 576 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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) –...
Page 577 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.8.4 (2/2) – INDICATING Rev. 6 Page 7.8.13...
Page 578 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) ”MAIN” reset knob 2) ”ST–BY” reset knob 3) Crash lever 4) ”SOURCE” selector 5) ”GENERATOR” selector Figure 7.8.5 (1/2) – ELECTRICAL CONTROL Page 7.8.14 Rev. 2...
Page 579 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.8.5 (2/2) – ELECTRICAL CONTROL Rev. 2 Page 7.8.15...
Page 580 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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”...
Page 581 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 582 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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) (Free) Figure 7.8.6 (1/2) –...
Page 583 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.8.6 (2/2) – EXTERNAL LIGHTING CONTROLS Rev. 2 Page 7.8.19...
Page 584 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTERIOR LIGHTING (Figure 7.8.7) Interior lighting consists of access, cabin, instrument panel, instruments, baggage compartments and emergency lighting. Access lighting Access lighting consists of FWD dome light, rear baggage compartment, R.H.
Page 585 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Emergency lighting Emergency lighting consists of two 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 586 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INTERIOR LIGHTING (Figure 7.8.7) Interior lighting consists of access, cabin, instrument panel, instruments, baggage compartments and emergency lighting. Access lighting Access lighting consists of two floodlights located on the ceiling upholstering (one at the level of the access door, the other at the level of the storage cabinet) and the L.H.
Page 587 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 588 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Instrument lighting switch (rheostat) 2) Instrument panel lighting switch (rheostat) 3) Cabin lighting switch (rear seats reading light) 4) Access door, rear baggage compartment and FWD dome light (two–way switch with access door switch) lighting controls 5) Emergency lighting switch (rheostat) Figure 7.8.7 (1/2) –...
Page 589 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.8.7 (2/2) – INTERNAL LIGHTING CONTROLS Rev. 6 Page 7.8.23...
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Page 591 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.9 – AIR CONDITIONING AND PRESSURIZATION AIR CONDITIONING (Figure 7.9.1) Air conditioning system includes a flow–pressure regulation system, temperature regulation and cooling system, control and check systems and distribution.
Page 592 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Overheat switch 2) Cooling turbine 3) Hot air – cold air mixer 4) Water separator 5) Temperature control valve 6) Pressure regulator of temperature control valve 7) Check–valve 8) Temperature control sensor 9) Cabin emergency air inlet 10) Defogging outlets...
Page 593 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.9.1 (2/2) – AIR CONDITIONING Rev. 5 Page 7.9.3 Valid S/N 1 to 23, 25, 28, 33 and 35...
Page 594 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Control and check (Figure 7.9.3) Air conditioning system controls are located on ”ECS” panel, warning lights are grouped on advisory panel. Conditioning occurs when ”BLEED VALVE” switch is set to ”ON” ; this leads to opening of pressure regulation valve and switches off ”BLEED OFF”...
Page 595 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.9 – AIR CONDITIONING AND PRESSURIZATION AIR CONDITIONING (Figure 7.9.1A) Air conditioning system includes a flow–pressure regulation system, temperature regulation and cooling system, control and check systems and distribution.
Page 596 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Overheat switch 2) Cooling turbine 3) Hot air – cold air mixer 4) Water separator 5) Temperature control valve 6) Pressure regulator of temperature control valve 7) Check–valve 8) Temperature control sensor 9) Cabin emergency air inlet 10) Defogging outlets...
Page 597 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.9.1A (2/2) – AIR CONDITIONING Valid S/N 24, 26, 27, 29 to 32, Rev. 5 Page 7.9.4C 34, 36 to 85, 87, 90...
Page 598 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Control and check (Figure 7.9.3) Air conditioning system controls are located on ”ECS” panel, warning lights are grouped on advisory panel. Conditioning occurs when ”BLEED VALVE” switch is set to ”ON” ; this leads to opening of pressure regulation valve and switches off ”BLEED OFF”...
Page 599 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.9 – AIR CONDITIONING AND PRESSURIZATION AIR CONDITIONING (Figure 7.9.1B) Air conditioning system includes a flow–pressure regulation system, temperature regulation and cooling system, control and check systems and distribution.
Page 600 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Overheat switch 2) Cooling turbine 3) Hot air – cold air mixer 4) Water separator 5) Temperature control valve 6) Pressure regulator of temperature control valve 7) Check–valve 8) Temperature control sensor 9) Cabin emergency air inlet 10) Defogging outlets...
Page 601 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.9.1B (2/2) – AIR CONDITIONING Rev. 5 Valid S/N 86, 88, 89, 91 to 9999 Page 7.9.4G...
Page 602 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Control and check (Figure 7.9.3) Air conditioning system controls are located on ”ECS” panel, warning lights are grouped on advisory panel. Conditioning occurs when ”BLEED VALVE” switch is set to ”ON” ; this leads to opening of pressure regulation valve and switches off ”BLEED OFF”...
Page 603 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 604 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Check valve 2) Cabin–atmosphere ∆P microswitch 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 warn switch 10) Compensation tank Figure 7.9.2 (1/2) –...
Page 605 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.9.2 (2/2) – PRESSURIZATION Rev. 9 Page 7.9.7...
Page 606 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) ”BLEED VALVE” switch – ON/OFF 2) ”BLEED VALVE” switch – HI/LO 3) ”CABIN FAN” switch 4) ”DUMP” switch 5) ”CABIN TEMP” selector 6) ”DEFOG / NORMAL” distributor 7) Cabin rate selector 8) Cabin altitude selector Figure 7.9.3 (1/2) –...
Page 607 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.9.3 (2/2) – ”ECS” CONTROL AND CHECK PANEL Rev. 6 Page 7.9.9...
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Page 609 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.10 – EMERGENCY OXYGEN SYSTEM (Figure 7.10.1) Emergency oxygen system must be used following a pressurization system failure at an altitude between 12000 and 30000 ft. The three emergency oxygen systems provide enough chemical oxygen for six persons during a descent from 30000 to 12000 ft and below.
Page 610 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Generator 2) Supply tubes 3) Masks 4) Drawer 5) Microswitch 6) Dimpled support 7) Microphone switch Figure 7.10.1 (1/2) – EMERGENCY OXYGEN SYSTEM Page 7.10.2 Rev. 5...
Page 611 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL (*) Variant Figure 7.10.1 (2/2) – EMERGENCY OXYGEN SYSTEM Valid S/N 1 to 23, 25, 28, 33 and 35, except airplanes equipped as a retrofit with Rev. 5 Page 7.10.3 modification Nr MOD 70–019–25...
Page 612 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL INDICATING When the ”SOURCE” selector is set to ”BAT” or ”GPU”, as soon as an oxygen generator is activated, the ”OXYGEN” warning light located on the advisory panel illuminates. The warning light remains illuminated as long as used generator is not replaced.
Page 613 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.10.1A (2/2) – EMERGENCY OXYGEN SYSTEM Valid S/N 24, 26, 27, 29 to 32, 34, 36 to 9999, plus airplanes equipped as a retrofit with Rev. 5 Page 7.10.5 modification Nr MOD 70–019–25...
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Page 615 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 616 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) Pitot Nr 1 2) Pitot Nr 2 3) Pitot Nr 2 dynamic drain 4) Pitot Nr 1 dynamic drain 5) V detector 6) Static drain 7) Emergency static drain 8) Static drain 9) FWD pressure bulkhead 10) Airspeed indicator Nr 1...
Page 617 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.11.1 (2/2) – AIR DATA SYSTEM Rev. 5 Page 7.11.3...
Page 618 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 619 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 7.12 – VACUUM SYSTEM AND INSTRUMENTS (Figure 7.12.1) The airplane is fitted with a vacuum system providing the suction necessary to operate the attitude indicator, the cabin pressurization and the leading edge deicing.
Page 620 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 621 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.12.1 (2/2) – VACUUM SYSTEM Rev. 2 Page 7.12.3...
Page 622 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.12.2 (1/2) – GYROSCOPIC INSTRUMENTS CONTROL (Variants according to the type of installation) Page 7.12.4 Rev. 2...
Page 623 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 624 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.12.2 (2/2) – GYROSCOPIC INSTRUMENTS CONTROL (Variants according to the type of installation) Page 7.12.6 Rev. 2...
Page 625 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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” –...
Page 626 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 627 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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.
Page 628 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.13.1 – DEICING CONTROL AND CHECK PANEL Page 7.13.4 Rev. 2...
Page 629 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 630 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 1) ”RADIO MASTER” switch 2) ”GND CLR” (ground clearance) ground communication indicator Figure 7.14.1 (1/2) – RADIO MASTER AND GROUND COMMUNICATION Page 7.14.2 Rev. 2...
Page 631 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Figure 7.14.1 (2/2) – RADIO MASTER AND GROUND COMMUNICATION Rev. 2 Page 7.14.3...
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Page 633 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL 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 634 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL CABIN FIRE EXTINGUISHER (if installed) The fire extinguisher is located on the pilot’s seat L.H. side. It is attached on the floor by means of a quick–disconnect support. A pressure gage allows checking the fire extinguisher condition.
Page 635 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL Reset after an inadvertent activation ELT 90 (EUROCAE) – ELT 91 (TSO) a) The keeps 1) Set ELT switch to ”MAN/RESET” or remote control switch to ”MAN”. transmitting emergency signal.
Page 636 Back to Contents T B M SECTION 7 DESCRIPTION PILOT’S INFORMATION MANUAL JE2 or JE2NG On ELT, press on button ”RESET”. ELT 910 (export only) Set remote control switch to ”ON” position, wait 2 seconds. Set ”ON–OFF–ARM” switch to ”OFF” position, then back to ”ARM” position. Page 7.15.4 Rev.
Page 637 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE SECTION 8 HANDLING, SERVICING AND MAINTENANCE TABLE OF CONTENTS Page GENERAL 8.1.1 ........... . . IDENTIFICATION PLATE 8.2.1 .
Page 638 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE TABLE OF CONTENTS (Continued) Page AIRPLANE CLEANING AND CARE 8.8.1 ......8.8.1 WINDSHIELD AND WINDOWS .
Page 639 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 640 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.1.2 Rev. 2...
Page 641 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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 642 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.2.2 Rev. 2...
Page 643 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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.
Page 644 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.3.2 Rev. 2...
Page 645 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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 646 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.4.2 Rev. 2...
Page 647 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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.
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Page 649 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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...
Page 650 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE Figure 8.6.1 – TURNING ANGLE LIMITS Page 8.6.2 Rev. 2...
Page 651 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE NOTE : Do not use solar screens or shields installed on the aircraft inside, or leave sun visors down against windshield when aircraft on ground. The reflected heat from these items causes a temperature increase which accelerates the crack growth or crazing and may cause the formation of bubbles in the inner layer of multilayer windshields.
Page 652 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE Figure 8.6.2 – CONTROL LOCK DEVICE Page 8.6.4 Rev. 9...
Page 653 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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 : –...
Page 654 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.6.6 Rev. 9...
Page 655 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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.
Page 656 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE Refill sump through the system filling inlet which is located on the engine upper rear part. A gage located on the filling cap indicates oil level and is calibrated in quarts to maximum level under cold conditions ”MAX COLD”...
Page 657 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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.
Page 658 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE Fuel additives Fuel used must contain an anti–ice additive conforming to MIL–I–27686D or E or MIL–I–85470A specification. Strict adherence to recommended preflight draining instructions as called for in Section 4 will eliminate any free water accumulations from the tank sumps.
Page 659 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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 660 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE Figure 8.7.3 – ADDITIVE MIXING RATIO (EGME or DIEGME) Page 8.7.6 Rev. 8...
Page 661 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE LANDING GEAR Nose gear tire : 5.00–5 6 PR – Inflating pressure : 94 psi (6.5 bar) Main gear tires : 18 5.5 8 PR – Inflating pressure : 120 psi (8.25 bar) Nose gear shock absorber : Fill with hydraulic fluid AIR 3520 B (MIL.H5606E) ;...
Page 662 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE OXYGEN Indicating When the ”SOURCE” selector is set to ”BAT” or ”GPU”, as soon as an oxygen generator is activated, the ”OXYGEN” warning light located on the advisory panel illuminates.
Page 663 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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 664 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL 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 665 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE 8.9 – UTILIZATION BY COLD WEATHER (– 05 C TO – 255 OR VERY COLD WEATHER (– 255 C TO – 405 If a landing is foreseen by cold or very cold weather or in case of airplane prolonged operation in such conditions, it is recommended to prepare the airplane as follows : 1 –...
Page 666 Back to Contents T B M SECTION 8 HANDLING, SERVICING PILOT’S INFORMATION MANUAL AND MAINTENANCE INTENTIONALLY LEFT BLANK Page 8.9.2 Rev. 6...
Page 667 Back to Contents T B M SECTION 9 SUPPLEMENT A PILOT’S INFORMATION MANUAL LIST OF SUPPLEMENTS AND VALIDITIES Supp. Edition Date A – General From S / N 1 31.01.90 ............. 1 –...
Page 668 Back to Contents T B M SECTION 9 SUPPLEMENT A PILOT’S INFORMATION MANUAL LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 11 – ”CASEY COPTER” freon air conditioning From S / N 24 31.05.92 ............12 –...
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Back to Contents T B M SECTION 9 SUPPLEMENT A PILOT’S INFORMATION MANUAL LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 22 – ”BENDIX / KING” RDR 2000 vertical profile weather radar From S / N 1 30.06.96 ............. 23 –...
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Back to Contents T B M SECTION 9 SUPPLEMENT A PILOT’S INFORMATION MANUAL LIST OF SUPPLEMENTS AND VALIDITIES (cont’d) Supp. Edition Date 33 – Intentionally left free 34 – ”GARMIN GNS 430” GPS (B–RNAV) navigation system interfaced with EHSI OF EFS 40 From S / N 181 31.08.00 .

SOCATA TBM 700 Pilot's Information Manual

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