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Daher-Socata TBM 700 Series, Pilot Operating Handbook


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PILOT’S INFORMATION

MANUAL

TBM 700 --- Edition 1

Summary of Contents for TBM 700 Series

Page 1: ...PILOT S INFORMATION MANUAL TBM 700 Edition 1...

Page 2: ...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 f...

Page 3: ...el replacement Major 010 24 Increase of the inboard generators ratings minor 011 56 Installation of a bonding plate on de iced windshield minor 012 30 Pitch control horn de icing Major 013 34 VOR LOC...

Page 4: ...reinforcement Major 037 21 Cabin air conditioning Ground ventilation improvement minor 038 28 Fuel unit INTERTECHNIQUE L88A15 651 minor 039 27 Installation of pitch trim position transmitter minor 04...

Page 5: ...N LHC 1118 04 minor 061 27 Elevator trim jack minor 062 24 Strengthening of AUXILEC starter generator mounting flange Major 063 32 Main gear tires minor 065 32 Removal of the main landing gear inboard...

Page 6: ...1 52 TBM700B Access door widening incorporation of modifications and increase of maximum zero fuel weight Major 095 71 Engine plenum chamber minor 096 30 Modification of R H wing de icing hose routing...

Page 7: ...7 55 Horizontal stabilizer reinforcement Major 119 71 Change of location of the oil pump breather outlet Major 120 55 Horizontal stabilizer outboard hinge fittings Major 121 76 Thermal protection of J...

Page 8: ...ERTECHNIQUE minor 0161 27 Aileron control emergency stop minor 0163 77 Torque transducer static port tube minor 0166 53 Change of glass fiber fabric type on TBM 700 composite floors minor 0168 57 Modi...

Page 9: ...cement of fin expansion pins minor 0209 57 Reinforcement of trailing edge omega at rib 7 minor 0213 27 Pitch trim union connector at rear pressure bulkhead minor 0216 52 TBM 700A door upper mechanism...

Page 10: ...Page 0 6 Edition 1 November 30 2010 Rev 0 TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE 6 DESCRIPTION 7 AIRPLANE HANDLI...

Page 11: ...N AND ENTRY DIMENSIONS 1 3 4 BAGGAGE SPACE ENTRY DIMENSIONS NON PRESSURIZED 1 3 4 SPECIFIC LOADINGS 1 3 4 1 4 ABBREVIATIONS AND TERMINOLOGY 1 4 1 METEOROLOGICAL TERMINOLOGY 1 4 1 GENERAL AIRSPEED TERM...

Page 12: ...l data supplied by the manufacturer The GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for SOCATA TBM 700 P N 190 01247 00 or any later version as applicable must be permanently kept in t...

Page 13: ...NERAL TBM 700 PILOT S OPERATING HANDBOOK Page 1 2 1 Edition 1 November 30 2010 Rev 0 1 2 THREE VIEW DRAWING Figure 1 2 1 1 2 THREE VIEW DRAWING TBM700A Airplane on line of flight with extended FWD sho...

Page 14: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 2 2 Edition 1 November 30 2010 Rev 0 Figure 1 2 1 2 2 THREE VIEW DRAWING TBM700A...

Page 15: ...ECTION 1 GENERAL TBM 700 PILOT S OPERATING HANDBOOK Page 1 2 3 Edition 1 November 30 2010 Rev 0 Figure 1 2 1A 1 2 THREE VIEW DRAWING TBM700B Airplane on line of flight with extended FWD shock absorber...

Page 16: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 2 4 Edition 1 November 30 2010 Rev 0 Figure 1 2 1A 2 2 THREE VIEW DRAWING TBM700B...

Page 17: ...pe Annular Turbine type 1 gas generator turbine stage 2 power turbines stages Horsepower rating and propeller speed 700 SHP at 2000 RPM PROPELLER Number of propellers 1 Propeller manufacturer HARTZELL...

Page 18: ...CTED TO EMERGENCY PURPOSES ONLY AVGAS SHALL NOT BE USED FOR MORE THAN 150 CUMULATIVE HOURS DURING ANY PERIOD BETWEEN ENGINE OVERHAUL PERIODS NOTE Use of AVGAS to be recorded in engine module logbook U...

Page 19: ...tion FR English Specification UK NATO Code Type 5cSt MIL L 23699C Amdt1 MIL L 23699C Amdt1 DERD 2499 Issue 1 O 156 Figure 1 3 2 RECOMMENDED ENGINE OIL TYPES Reference Service Bulletin P W C No 14001 M...

Page 20: ...cabin length 13 3 45 4 05 m Maximum cabin height 4 1 22 m TBM700A Number of cabin entries 1 Entry width 2 1 59 0 65 m Entry height 3 10 85 1 19 m TBM700B Number of cabin entries 1 Entry width 3 6 52 1...

Page 21: ...e if it is set to QNH Standard Temperature Is 15 C 59 F at sea level pressure altitude and decreases by 2 C 3 6 F for each 1000 ft of altitude Pressure altitude Is the altitude read from an altimeter...

Page 22: ...safely extended or retracted VMO Maximum Operating Speed is the speed limit that may not be deliberately exceeded in normal flight operations VR Rotation Speed is the speed at which rotation is initi...

Page 23: ...ue permissible during start Flame out Involuntary loss of the combustion chamber flame during operation GPU Ground power unit Feathering Action which reduces the drag of a propeller by positioning bla...

Page 24: ...ed during certification tests The value shown is not considered to be limiting g Is acceleration due to gravity Usable fuel Total fuel which can be effectively consumed by the engine WEIGHT AND BALANC...

Page 25: ...usable fuel and full operating fluids oil and hydraulic fluids Basic empty weight Standard empty weight plus optional equipment Useful load Is the difference between maximum ramp weight and the basic...

Page 26: ...BRT Brightness CAS Crew Alerting System C Celsius degree CHiPS Cable Harness Protection System CONT Control DIEGME Diethylene glycol monomethyl ether DISC Disconnect DN Down ECS Environmental control...

Page 27: ...l Litre L Left l h Litre hour lb or lbs Pound s L D Lift to drag LDG Landing LDG GR Landing gear LRCR Long Range Cruise LO Low LP Low pressure LRN Long range navigation LTS TEST Lightings test m Metr...

Page 28: ...izontal stabilizer PRESS Pressure PROP Propeller psi Pounds per square inch qt Quart us gal QTY Quantity R Red or Right RUD Rudder s or sec Second SEL Selector SIG Signalization SL Sea level S N Seria...

Page 29: ...cations Transceivers DME Distance Measuring Equipment ELT Emergency Locator Transmitter FMS Flight Management System GPS Ground Positioning System HF High Frequency IFR Instrument Flight Rules ILS Ins...

Page 30: ...n 1 November 30 2010 Rev 0 VHF Very High Frequency VMC Visual Meteorological Conditions V NAV Vertical NAVigation VOR VHF Omnidirectional Range VOR LOC VHF Omnidirectional Range LOCalizer WAAS Wide Ar...

Page 31: ...U S UNITS TO METRIC UNITS METRIC UNITS TO IMPERIAL AND U S UNITS MULTIPLY BY TO OBTAIN MULTIPLY BY TO OBTAIN FEET 0 3048 METRE METRE 3 2808 FEET INCH 25 4 mm mm 0 03937 INCH Imp Gal 4 546 Litre Litre...

Page 32: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 5 2 Edition 1 November 30 2010 Rev 0 Figure 1 5 2 FEET VERSUS METRES M tres 30000 20000 10000 0 Feet 2500 5000 7500 10000...

Page 33: ...SECTION 1 GENERAL TBM 700 PILOT S OPERATING HANDBOOK Page 1 5 3 Edition 1 November 30 2010 Rev 0 Figure 1 5 3 INCHES VERSUS MILLIMETRES mm 10 0 In 250 500 750 1000 20 30 40...

Page 34: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 5 4 Edition 1 November 30 2010 Rev 0 Figure 1 5 4 POUNDS VERSUS KILOGRAMS 1000 2000 3000 2000 6000 4000 0 Kg Lb 4000 8000...

Page 35: ...re hPa C F 0 1013 2 15 0 59 0 2000 942 1 11 0 51 8 4000 875 0 7 0 44 6 6000 811 9 3 1 37 6 8000 752 6 0 8 30 5 10000 696 8 4 8 23 4 12000 644 3 8 7 16 2 14000 595 2 12 7 9 2 16000 549 1 16 6 2 2 18000...

Page 36: ...29 06 985 29 09 986 29 12 987 29 15 988 29 18 989 29 20 990 29 23 991 29 26 992 29 29 993 29 32 994 29 35 995 29 38 996 29 41 997 29 44 998 29 47 999 29 50 1000 29 53 1001 29 56 1002 29 59 1003 29 62...

Page 37: ...LIMITS 2 4 1 2 5 WEIGHT AND C G LIMITS 2 5 1 WEIGHT LIMITS 2 5 1 C G LIMITS 2 5 1 FLIGHT LOAD FACTOR LIMITS 2 5 2 2 6 OPERATION LIMITS 2 6 1 MANEUVER LIMITS 2 6 1 TEMPERATURE LIMITS 2 6 1 GFC 700 AUTO...

Page 38: ...0 Rev 0 TABLE OF CONTENTS Continued Page 2 7 MISCELLANEOUS LIMITS 2 7 1 SEATING LIMITS C G 2 7 1 BAGGAGE LIMITS 2 7 1 MINIMUM CREW 2 7 1 MAXIMUM OCCUPANCY 2 7 1 USE OF DOORS 2 7 1 2 8 MARKINGS 2 8 1 A...

Page 39: ...The GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the Socata TBM 700 No 190 01247 00 or any later version as applicable must be readily available to the pilot This Section of the air...

Page 40: ...later version as applicable must be readily available to the pilot This Section of the airplane Pilot s Operating Handbook presents the various operating limitations the significance of such limitatio...

Page 41: ...t make abrupt or full control movements above this speed VFE Maximum flaps extended speed landing configuration takeoff configuration 120 180 122 178 Do not exceed these speeds depending on flaps posi...

Page 42: ...AX TRQ 100 at Np 2000 RPM MAX TRQ 110 at Np 1800 RPM Maximum power Ng 104 1 Np 2000 RPM ITT Anytime during engine operation continuous 800 C During start 870 C for 20 seconds max 1000 C for 5 seconds...

Page 43: ...s gal 1100 Litres Usable fuel 281 6 us gal 1066 Litres Unusable fuel 9 us gal 34 Litres Maximum fuel imbalance 25 us gal 95 Litres NOTE Usable fuel can be safely used during all normal airplane maneuv...

Page 44: ...F40 with additive MIL DTL 5624 Grade JP 5 AIR 3404C Grade F44 DERD 2452 Issue 2 Amdt 1 F44 with additive when utilization MIL DTL 83133 Grade JP 8 AIR 3405C Grade F34 DERD 2453 Issue 4 Amdt 1 F34 wit...

Page 45: ...ber 30 2010 Rev 0 2 4 STARTER OPERATION LIMITS Starter operation sequence is limited as follows if Ng 30 30 seconds if Ng 30 60 seconds Should several sequences be necessary respect following spacing...

Page 46: ...th landing gear down and flaps up attitude 0 Forward limits 181 3 inches 4 604 m aft of datum at 4409 lbs 2000 kg or less 14 of m a c 183 6 inches 4 664 m aft of datum at 6250 lbs 2835 kg 18 of m a c...

Page 47: ...ING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 5 2 Edition 1 November 30 2010 Rev 0 FLIGHT LOAD FACTOR LIMITS Flaps up 1 5 n 3 8 g Flaps down 0 n 2 0 g CAUTION INTENTIONAL NEGATIVE LOAD F...

Page 48: ...eoff ISA 37 C 67 F from 0 to 8000 ft pressure altitude Maximum temperature in flight ISA 37 C 67 F from 0 to 8000 ft pressure altitude ISA 30 C 54 F at 30000 ft pressure altitude Linear decrease betwe...

Page 49: ...n shown to meet the accuracy requirements for Enroute Terminal non precision instrument approach operations using GPS and WAAS including GPS or GPS and RNAV approaches and approach procedures with ver...

Page 50: ...must be done in compliance with equipment User s Manual For every navigation into areas reserved for B RNAV or P RNAV the pilot must be provided with a predicted availability of RAIM on the route if t...

Page 51: ...coordinates are referenced with regard to WGS 84 system or an equivalent system SEVERE ICING CONDITIONS WARNING SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIR...

Page 52: ...escribed in Chapter 3 13 FLAPS OPERATING ENVELOPE The use of flaps is not authorized above 15 000 ft REVERSE UTILIZATION The use of control reverse BETA range is prohibited during flight EQUIPMENT REQ...

Page 53: ...ctor OFF Fuel auxiliary pump ON L H and R H fuel tank low level Non functioning of fuel timer Battery overheat only with cadmium nickel battery Battery stop Main generator OFF Low voltage Ground power...

Page 54: ...cal pump main Fuel electrical pump auxiliary Fuel shut off valve Fuel timer Starter generator Inertial separator Stall warning Electrical aileron trim Electrical rudder trim Manual elevator pitch trim...

Page 55: ...4 8 Anticollision lights 2 9 Landing light IFR 1 All equipment required for day VFR 2 All equipment required for night VFR if flight is performed during night 3 Taxi light if flight is performed duri...

Page 56: ...equipment List of critical RVSM equipment is maintained in accordance with the airplane Maintenance Manual This does not constitute operational approval Individual airplane and operational approval mu...

Page 57: ...Available A Not Available NA Magnetic Heading A Indicated Airspeed A Mach No A Vertical Rate A Roll Angle A True Airspeed A True Track Angle A Groundspeed A Selected Altitude A Barometric Pressure Set...

Page 58: ...e 2 6 11 Edition 1 November 30 2010 Rev 0 Operators must have back up charts available to the flight crew Database currency must be verified prior to use via database effectivity page The flight crew...

Page 59: ...ont baggage at 128 inches 3 250 m Rear baggage at 297 6 inches 7 560 m see NOTE 1 Rear baggage at 303 inches 7 695 m see NOTE 2 NOTE 1 Valid S N 1 to 23 25 28 33 and 35 except airplanes equipped as a...

Page 60: ...or code significance are shown in Figure 2 8 1 MARKING KIAS Value or range SIGNIFICANCE Red line White line Below 60 60 122 Full Flap Operating Range Lower limit is maximum weight VSO in landing confi...

Page 61: ...to 230 F 0 to 104 C 32 to 219 2 F 110 C 230 F Oil pressure 60 psi 60 to 100 psi 100 to 135 psi 135 psi Fuel pressure 0 to 5 psi 10 to 50 psi 50 psi Generator RPM Ng 51 to 104 104 Propeller RPM Np 450...

Page 62: ...front side window Valid S N 1 to 23 25 28 33 and 35 except airplanes equipped as a retrofit with modification Nr MOD 70 019 25 ICING CONDITIONS ALLOWED FLIGHT CONDITIONS DAY AND NIGHT VFR AND IFR 1 Un...

Page 63: ...compartment bottom bulkhead pressurized 100 kg 220 lbs MAXIMUM IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT ALL THE BAGGAGES ARE PROPERLY SECURED FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DAT...

Page 64: ...SECTION 2 LIMITATIONS EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 2 9 3 Edition 1 November 30 2010 Rev 0 5 Under GCU 475 control unit on pedestal console...

Page 65: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 4 Edition 1 November 30 2010 Rev 0 6 On fuel selector 7 Near fuel tank caps...

Page 66: ...d under seating of intermediate and rear passenger seats which are fitted with oxygen EMERGENCY OXYGEN IN DRAWER UNDER SEAT PULL FULLY THE MASK OUT OF DRAWER AT FULL EXTENSION GIVE CORD A TUG MAXIMUM...

Page 67: ...RATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 6 Edition 1 November 30 2010 Rev 0 12 Under R H control wheel 13 On nose gear door 14 On nose gear leg NOSE LANDING GEAR TIRE PRESSURE...

Page 68: ...v 0 15 On main gear leg MAIN LANDING GEAR TIRE PRESSURE 8 25 bar 120 psi 16 On engine cowling in front of baggage compartment door EXTERNAL POWER 28 VOLTS D C NOMINAL 800 AMPS STARTING CAPACITY MIN DO...

Page 69: ...NDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 8 Edition 1 November 30 2010 Rev 0 17 TBM700B On access door External side 18 TBM700B On outer fuselage skin aft of access door and in the cabin...

Page 70: ...on 1 November 30 2010 Rev 0 19 TBM700A from S N 1 to S N 49 except airplanes equipped as a retrofit with modification No MOD70 019 25 On access door Internal side 19 TBM700A from S N 50 plus airplanes...

Page 71: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 10 Edition 1 November 30 2010 Rev 0 19 TBM700B On access door Internal side...

Page 72: ...Approved TBM 700 PILOT S OPERATING HANDBOOK Page 2 9 11 Edition 1 November 30 2010 Rev 0 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...

Page 73: ...IMITATIONS EASA Approved Page 2 9 12 Edition 1 November 30 2010 Rev 0 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...

Page 74: ...Page 2 9 13 Edition 1 November 30 2010 Rev 0 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...

Page 75: ...R CONTROL LOSS 3 3 5 GOVERNOR REGULATION CONTROL NOT OPERATING 3 3 7 EXCESSIVE PROPELLER ROTATION SPEED 3 3 8 RED CAS MESSAGE ITT ON 3 3 9 ENGINE DOES NOT STOP ON GROUND 3 3 10 3 4 AIR START 3 4 1 AIR...

Page 76: ...L OR FUEL LOW R ON 3 8 3 AMBER CAS MESSAGE AUTO SEL ON 3 8 3 3 9 ELECTRICAL SYSTEM 3 9 1 RED CAS MESSAGE BAT OVERHEAT ON if Cadmium Nickel battery installed 3 9 1 AMBER CAS MESSAGE BAT OFF ON 3 9 1 AM...

Page 77: ...URE 3 12 2 WINDSHIELD DEICING FAILURE 3 12 2 WINDSHIELD MISTING OR INTERNAL ICING 3 12 3 AMBER CAS MESSAGES PITOT NO HT 1 PITOT NO HT 2 OR STALL NO HEAT ON 3 12 4 3 13 MISCELLANEOUS 3 13 1 RUNAWAY OF...

Page 78: ...in Section 9 Supplements Pilot must know procedures given in this section and be prepared to take appropriate actions should an emergency arise Some emergency procedures are a part of basic pilot trai...

Page 79: ...nd amber messages indicating failures or discrepancies which require an action as soon as practical Red or amber failure warnings are coupled with the lighting of a flashing red indicator aural warnin...

Page 80: ...ine failure refer to Chapter 3 3 Paragraph ENGINE FAILURE AT TAKEOFF BEFORE ROTATION For any other reason 1 Power lever IDLE 2 Reverse AS REQUIRED 3 Braking AS REQUIRED If the airplane cannot be stopp...

Page 81: ...BOOK Page 3 3 1 Edition 1 November 30 2010 Rev 0 3 3 ENGINE FAILURES ENGINE FAILURE AT TAKEOFF BEFORE ROTATION 1 Power lever IDLE 2 Braking AS REQUIRED If the airplane cannot be stopped on the remaini...

Page 82: ...flaps at TO and without changing landing gear position Before touch down 1 Maintain IAS 80 KIAS 2 Power lever IDLE 3 Condition lever CUT OFF 4 Tank selector OFF 5 CRASH lever PUSH If altitude allows...

Page 83: ...er lever IDLE 2 Propeller governor lever FEATHER 3 Condition lever CUT OFF 4 Remaining fuel CHECK 5 Tank selector SWITCH TANKS 6 AUX BP switch and fuel pressure CHECK CORRECT 7 Air start in flight Ref...

Page 84: ...in the green sector 2 Shorten the flight and monitor If the indicated pressure is not in the green sector 3 Failure is confirmed Due to the oil pressure drop the propeller blade angle may go towards...

Page 85: ...ry to continue flight If the available power is weak extend the landing gear only on a glide path in final approach and extend full flaps only in short final Do not perform a go around CAUTION IN MANU...

Page 86: ...nimum power obtained is excessive 1 Reduce airspeed by setting airplane in nose up attitude at IAS 178 KIAS 2 INERT SEP switch ON 3 If ITT 800 C INERT SEP switch OFF 4 Landing gear control DN 5 Flaps...

Page 87: ...NOR REGULATION CONTROL NOT OPERATING May indicate a rupture of the linkage of the governor control 1 Continue the flight 2 If Np 2000 RPM do not perform a go around and do not use the reverse In that...

Page 88: ...rotation speed to 2100 RPM approximately or a propeller governor and overspeed limiter failure In that case only the torque limiter operates to limit the power However the pilot intervention is necess...

Page 89: ...T 800 C for more than 20 seconds If the limits previously mentioned are exceeded 1 Stop the starting procedure 2 Cancel the flight inform maintenance department B After engine start Indicates that ITT...

Page 90: ...op when the condition lever is set to CUT OFF proceed as follows 1 AP TRIMS MASTER switch OFF 2 AVIONICS MASTER switch OFF 3 INT LIGHTS panel All switches OFF 4 EXT LIGHTS panel All switches OFF 5 ECS...

Page 91: ...ENVELOPE Pressure altitude ft 140 190 61 266 STARTER ASSIST MANDATORY PROPELLER WINDMILLING FEATHERED PROPELLER 20000 STARTER ASSIST NOT MANDATORY IAS KIAS Air start may be attempted at all speeds an...

Page 92: ...ILABLE IF THE ESS BUS TIE SWITCH IS KEPT EMER NOTE The AVIONICS MASTER switch may be ON 1 BLEED VALVE switch OFF CAUTION BLEED VALVE SWITCH ON MAY CAUSE OVERTEMPERATURE OR ABNORMAL ACCELERATION 2 FREO...

Page 93: ...2 2 11 IGNITION switch AUTO or ON 12 STARTER switch ON 13 Condition lever LO IDLE when Ng 13 14 ITT and Ng MONITOR 15 When Ng 50 steady STARTER OFF IGNITION AUTO 16 Condition lever HI IDLE 17 Propell...

Page 94: ...AILABLE IF THE ESS BUS TIE SWITCH IS KEPT EMER NOTE The AVIONICS MASTER switch may be ON 1 BLEED VALVE switch OFF CAUTION BLEED VALVE SWITCH ON MAY CAUSE OVERTEMPERATURE OR ABNORMAL ACCELERATION 2 FRE...

Page 95: ...RTER ASSIST NOT MANDATORY 2 2 9 AUX BP fuel switch ON 10 IGNITION switch ON 11 Condition lever LO IDLE 12 ITT and Ng MONITOR 13 When Ng 50 steady IGNITION switch AUTO 14 Condition lever HI IDLE 15 Pro...

Page 96: ...ondition lever CUT OFF 3 BLEED VALVE switch OFF 4 FREON or AIR COND switch if installed OFF 5 Brakes AS REQUIRED 6 Tank selector OFF 7 Ask for ground assistance if necessary 8 CRASH lever PUSH 9 EVACU...

Page 97: ...T ON smoke 1 Power lever IDLE 2 Propeller governor lever FEATHER 3 Condition lever CUT OFF 4 AUX BP fuel switch OFF 5 Tank selector OFF 6 BLEED VALVE switch OFF 7 FREON or AIR COND switch if installed...

Page 98: ...gin is known 2 Defective equipment OFF Descend quickly below 12000 ft 3 Using the on board extinguisher if installed EXTINGUISH fire if necessary 4 Smoke elimination if necessary UNDERTAKE PROCEDURE R...

Page 99: ...ISH if necessary with the on board extinguisher if installed 7 All pull off type circuit breakers PULL 8 All electrical equipment CUT OFF 9 SOURCE selector BAT 10 GENERATOR selector MAIN 11 Necessary...

Page 100: ...ON 1 Smoke origin IDENTIFY 2 Oxygen USE AS REQUIRED pilot and passengers 3 If smoke persists undertake an EMERGENCY DESCENT Refer to Chapter 3 6 4 BLEED VALVE switch OFF 5 FREON or AIR COND switch if...

Page 101: ...DURE IN SMOOTH AIR 1 Power lever IDLE 2 Oxygen If necessary 3 Propeller governor lever MAX RPM 4 Flaps UP 5 Landing gear UP 6 Speed VMO 266 KIAS PROCEDURE IN ROUGH AIR OR IN CASE OF STRUCTURE PROBLEM...

Page 102: ...EASA Approved Page 3 6 2 Edition 1 November 30 2010 Rev 0 3 6 EMERGENCY DESCENTS GLIDE DISTANCE AND OPTIMUM SPEED Configuration 1 Flaps UP 2 Landing gear UP 3 Propeller governor lever FEATHER 4 Optimu...

Page 103: ...er CUT OFF 4 Tank selector OFF 5 AUX BP fuel switch OFF 6 BLEED VALVE switch OFF 7 FREON or AIR COND switch if installed OFF 8 DUMP switch ACTUATED 9 Glide speed 110 KIAS maintained until favourable g...

Page 104: ...proved Page 3 7 2 Edition 1 November 30 2010 Rev 0 3 7 EMERGENCY LANDINGS TIRE BLOWOUT DURING LANDING 1 Control direction with brakes and nose wheel steering 2 REVERSE AS REQUIRED 3 Stop airplane to m...

Page 105: ...ED VALVE switch OFF 3 DUMP switch ACTUATED 4 Maintain tank selector on defective landing gear side to lighten corresponding wing maximum fuel unbalance 25 us gal 95 litres 5 Choose a runway with headw...

Page 106: ...r 30 2010 Rev 0 3 7 EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR 2 2 11 Condition lever CUT OFF 12 Engine stop procedure COMPLETE 13 EVACUATE If landing gear drags during landing 14 Cond...

Page 107: ...LANDING GEAR DOWN UNLOCKED OR NOT DOWN 1 Transfer passengers to the rear if necessary 2 Approach Flaps TO IAS 90 KIAS 3 Land with nose up attitude keep nose high 4 Condition lever CUT OFF 5 Propeller...

Page 108: ...ANDINGS LANDING WITH GEAR UP 1 Final approach Standard Flaps LDG IAS 85 KIAS 2 BLEED VALVE switch OFF 3 DUMP switch ACTUATED When runway is assured 4 Power lever IDLE 5 Propeller governor lever FEATHE...

Page 109: ...LANDINGS LANDING WITHOUT ELEVATOR CONTROL 1 Configuration LANDING GEAR DN FLAPS LDG 2 Airspeed Maintain IAS 95 KIAS 3 Power as necessary to maintain airspeed according to an easy approach slope 300 ft...

Page 110: ...ALFUNCTION For flaps deflections from UP to TO position 1 Proceed as for a normal landing maintaining approach airspeed IAS 100 KIAS Provide for a landing distance increased up to about 60 For flaps d...

Page 111: ...arallel to the swell rollers In heavy wind land facing wind 2 Flaps LDG 3 Maintain a descent rate as low as possible when approaching the water 4 Airspeed IAS 80 KIAS 5 BLEED VALVE switch OFF 6 DUMP s...

Page 112: ...P ON ON CHECK 6 Fuel pressure CHECK If pressure is normal again and warning light is off mechanical pump has failed 7 Maintain AUX BP fuel switch ON If pressure remains at 0 or drops to 0 after AUX BP...

Page 113: ...AS MESSAGE AUX BOOST PMP ON ON Indication is normal if AUX BP fuel switch is in ON position If AUX BP fuel switch is in AUTO position 1 Reset to ON 2 Then to AUTO If AUX BOOST PMP ON CAS message goes...

Page 114: ...he corresponding tank 1 Corresponding gage CHECK 2 Check the other tank has been automatically selected If not 3 FUEL SEL switch MAN 4 Select tank manually as required AMBER CAS MESSAGE AUTO SEL ON In...

Page 115: ...LAND AS SOON AS POSSIBLE REMARK In case of subsequent electrical generator failure the battery can be used again by selecting 4 GENERATOR selector OFF CAS MESSAGE MAIN GEN ON 5 SOURCE selector BAT 6 R...

Page 116: ...ning persists MAIN GEN switching confirmed 3 MAIN GENERATOR RESET push button PUSH In case of failure 4 Disconnect following ancillary electrical systems FREON or AIR COND switch if installed OFF STRO...

Page 117: ...or any indication of battery run down In that case 3 Disconnect following ancillary electrical systems FREON or AIR COND switch if installed OFF STROBE switch OFF CABIN lights switch OFF CABIN FAN sw...

Page 118: ...ERATOR selector MAIN 2 MAIN GENERATOR RESET push button PRESS If successful 3 Disconnect ancillary electrical systems not essential 4 Monitor voltmeter and ammeter Prepare to SHORTEN FLIGHT If not suc...

Page 119: ...S BAT bar are directly supplied by the battery Available ancillary systems see Figure 3 9 1 12 LAND as soon as possible If necessary it is always possible to use other ancillary systems by selecting E...

Page 120: ...MAIN GEN failure 3 3 TAS breaker PULL DATA LINK breaker PULL CD player OFF INSTR CABIN ACCESS controls OFF XPDR 2 breaker PULL If icing conditions PITOT 1 HTR switch Checked ON WINDSHIELD switch ON M...

Page 121: ...SECTION 3 EMERGENCY PROCEDURES EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 3 9 7 Edition 1 November 30 2010 Rev 0 Figure 3 9 1 1 2 ELECTRICAL DISTRIBUTION OF BUS BARS...

Page 122: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 9 8 Edition 1 November 30 2010 Rev 0 Figure 3 9 1 2 2 ELECTRICAL DISTRIBUTION OF BUS BARS...

Page 123: ...ONICS MASTER switch misfunction leading to the impossibility of energizing the radionavigation equipment 1 AVIONICS MASTER circuit breaker PULL The radionavigation equipment are supplied again and the...

Page 124: ...tor CHECK If P 6 2 psi 2 BLEED VALVE switch OFF 3 EMERGENCY DESCENT Refer to Chapter 3 6 RED CAS MESSAGE CABIN ALTITUDE ON 1 Pressurization indicator CHECK If cabin altitude 10000 ft 2 Oxygen Refer to...

Page 125: ...ULLED if necessary 4 Wait for complete cabin depressurization before opening the door AMBER CAS MESSAGE BLEED OFF ON Indicates the pressurization system is not running possibly due to failure or BLEED...

Page 126: ...ED OFF amber CAS message appearance Should automatic cutoff occur or not 1 BLEED VALVE switch OFF 2 If necessary EMERGENCY DESCENT Refer to Chapter 3 6 or continue flight at an altitude 12000 ft REMAR...

Page 127: ...e access door have not been correctly locked On ground check the correct locking as well as the latches position of the access door During flight 1 Start a slow descent 2 Decrease cabin P by selecting...

Page 128: ...Rev 0 3 10 PRESSURIZATION AND AIR CONDITIONING AMBER CAS MESSAGE VACUUM LOW ON Suction gage indicator CHECK Low vacuum may lead to misfunctioning of leading edge deicing pressurization and gyroscopic...

Page 129: ...stributor already positioned on DEFOG 1 DEFOG NORMAL distributor NORMAL 2 CABIN TEMP selector Set to around a 10 o clock position 3 WINDSHIELD switch ON If there is no improvement and if the flight sa...

Page 130: ...r PUSH If landing gear is down and locked correct indication Continue flight if necessary at a speed below 178 KIAS without icing conditions or land If landing gear does not lock incorrect indication...

Page 131: ...ing gear is down and locked correct indication Continue flight if necessary at a speed below 178 KIAS without icing conditions or land If landing gear does not lock incorrect indication refer to parag...

Page 132: ...circuit breaker PULL If the red warning light goes off The flight may be continued without any restriction The electrohydraulic pump starting will be manually controlled with the LDG GR circuit breake...

Page 133: ...below 178 KIAS without icing conditions or land If landing gear does not lock incorrect indication refer to paragraph DISCREPANCY WHEN LANDING GEAR GOES DOWN CAUTION DO NOT ENTER ICING CONDITIONS THIS...

Page 134: ...issing Perform a MANUAL EXTENSION 1 LDG GR circuit breaker PULL 2 Floor hatch OPEN 3 By pass selector FULLY PULL LOCK 4 Landing gear control DN 5 Hand pump ACTUATE with maximum amplitude CAUTION THE E...

Page 135: ...UNLOCK PUSH BACK 10 Wait a minute 11 Landing gear control IAS 128 KIAS UP Try to extend landing gear in NORMAL mode with positive load factors during maneuver as well as drifting If not successful Ref...

Page 136: ...d warning light goes off 2 LAND If the red warning light remains fixed ON apply the following procedure Red warning light on LANDING GEAR control panel remains fixed ON whatever the condition of the g...

Page 137: ...on the normal indicating and on the CHECK DN indicating the bad locking of a landing gear in down position is confirmed Recycle the landing gear as follows 9 By pass selector UNLOCK PUSH 10 Wait a mi...

Page 138: ...AND FLAPS RED CAS MESSAGE FLAPS ASYM ON Indicates a dissymmetry of flap deflection This immediately stops the flap motor and prevents further operation of the flaps 1 FLAPS circuit breaker PULL 2 SHOR...

Page 139: ...lses Ice on wing outboard sections Or ice on wing inboard sections and stabilizers One of the two cycling green lights is not lit 1 LEAVE icing conditions as soon as possible 2 AIRFRAME DE ICE switch...

Page 140: ...p nor increase of ITT observed during maneuver LEAVE icing conditions as soon as possible WINDSHIELD DEICING FAILURE Symptoms Windshield being covered uniformly by ice No perception of heat when touch...

Page 141: ...elector Max HOT 2 DEFOG NORMAL distributor Max DEFOG 3 WINDSHIELD switch ON If not successful to gain sufficient visibility 4 Manually clean a sufficient visibility area 5 If necessary clean L H side...

Page 142: ...s may alter L H airspeed indications 1 AVOID icing conditions If it is not possible 2 Perform moderate descent or climb attitudes VMO overshooting and stall warning lights are always operating PITOT N...

Page 143: ...LEASED 4 Pitch trim may be used manually 5 Reduce airspeed if necessary to reduce control forces If pitch trim runaway 6 AP TRIMS MASTER switch AP OFF The pitch trim may be used manually the two other...

Page 144: ...g handle 3 Pull emergency exit assembly toward oneself to release it from its recess 4 Put the emergency exit door inside fuselage or throw it away from the fuselage through the opening 5 EVACUATE air...

Page 145: ...SPONDER USES procedures 2 Apply air traffic control procedures in case of communications failure code 7700 during 1 minute then code 7600 3 Try to restore communications by using all possible combinat...

Page 146: ...ion 1 November 30 2010 Rev 0 3 13 MISCELLANEOUS ACCIDENTAL SPINS Voluntary spins are prohibited In case of accidental spins 1 Control wheel NEUTRAL PITCH AND ROLL 2 Rudder FULLY OPPOSED TO THE SPIN 3...

Page 147: ...O ACTIVATE PULL ON THE OTHER LANYARD Front seats 1 Open drawer located in R H seat seating 2 Take a mask uncoil tube totally 3 Fully extend the lanyard 4 Tug to activate the generator when the oxygen...

Page 148: ...ated the CAS message OXYGEN appears on the MFD unit The CAS message will remain ON as long as the used generator is not replaced AIRSPEED INDICATING SYSTEM FAILURE Symptoms erroneous indication in fli...

Page 149: ...conditions 1 Inform Air Traffic Control to exit severe icing conditions by changing the route or the altitude 2 Avoid any sudden maneuver on flight controls 3 Do not engage the autopilot 4 If the aut...

Page 150: ...ventional means VOR DME NDB and dead reckoning elements enable making sure that B RNAV accuracy criteria are observed When this condition is not met the Air Traffic Control must be contacted to return...

Page 151: ...POWER 4 3 14 STARTING ENGINE USING EXTERNAL POWER GPU 4 3 19 MOTORING 4 3 24 MOTORING FOLLOWED BY AN ENGINE START 4 3 26 AFTER STARTING ENGINE 4 3 28 TAXIING 4 3 30 BEFORE TAKEOFF 4 3 31 TAKEOFF 4 3 3...

Page 152: ...4 4 59 SHUT DOWN 4 4 60 4 5 PARTICULAR PROCEDURES 4 5 1 FLIGHT INTO KNOWN ICING CONDITIONS 4 5 1 FLIGHT INTO SEVERE ICING CONDITIONS 4 5 6 FLIGHT UNDER HEAVY PRECIPITATIONS 4 5 8 UTILIZATION ON RUNWAY...

Page 153: ...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...

Page 154: ...s Chapter 5 8 2 Best rate of climb speed VY Landing gear UP flaps UP 123 KIAS 3 Best angle of climb speed Vx 95 KIAS 4 Maximum speed Flaps TO 178 KIAS Flaps LDG 122 KIAS 5 Maximum speed with landing g...

Page 155: ...il and control surfaces In case of night flight check good operation of all navigation lights landing lights strobe lights and make sure that an emergency lamp is on board If icing conditions are fore...

Page 156: ...M PILOT S OPERATING HANDBOOK 700 SECTION 4 NORMAL PROCEDURES EASA Approved Page 4 3 2 Edition 1 November 30 2010 Rev 0 CHECK LIST PROCEDURES PREFLIGHT INSPECTION Cont d Figure 4 3 1 PREFLIGHT INSPECTI...

Page 157: ...panel All switches OFF 2 ELECTRIC POWER panel SOURCE selector OFF GENERATOR selector OFF 3 ENGINE START panel IGNITION switch AUTO STARTER switch OFF 4 INT LIGHTS panel All switches OFF 5 EXT LIGHTS p...

Page 158: ...RAM AIR control knob PUSHED 13 Fuel FUEL SEL selector MAN AUX BP switch OFF Tank selector L or R 14 Flight control lock REMOVED STOWED 15 Flight controls Deflections checked 16 Parking brake SET 17 En...

Page 159: ...ector BAT or GPU 23 AVIONICS MASTER switch START 24 PFD1 DISPLAY BACKUP button OUT 25 EXT LIGHTS panel LTS TEST push button PRESS 3 green lamps L LDG TAXI R LDG ON red and amber MASTER warnings ON L L...

Page 160: ...N Test 1 then 2 RED ON 3 GREEN ON 34 DE ICE SYSTEM panel PITOT 1 HTR switch ON WARNING CAS MESSAGE PITOT HT 1 ON PITOT 2 STALL HTR switch ON WARNING CAS MESSAGE PITOT HT ON 1 2 ON WARNING CAS MESSAGE...

Page 161: ...TEM panel ALL SWITCHES OFF 37 AVIONICS MASTER switch OFF 38 SOURCE selector OFF Cabin II 1 Cabin fire extinguisher if installed CHECK Pressure Attachment 2 Seats belts CHECK 3 Windows CHECK General co...

Page 162: ...e movement Deflection 3 Trailing edge static discharger CHECK Condition Attachment 4 Wing tip nav lights Strobe landing light Condition CHECK 5 OAT probe Condition CHECK 6 Fuel tank CAP CLOSED LOCKED...

Page 163: ...SED LOCKED 2 GPU door CLOSED If not used 3 Fuel circuit drain DRAIN Fuel free of water and contamination Filter contamination indicator CHECK 4 L H exhaust stub CHECK Condition No crack 5 Upper engine...

Page 164: ...ch wing DRAIN Fuel free of water and contamination 2 Main landing gear Shock absorber doors tire wheel well CHECK 3 Wing deicer boots CHECK Condition Attachment 4 Stall warning CHECK Condition Deflect...

Page 165: ...fin CHECK Attachment condition 4 Inspection door under fuselage CLOSED CHECK Attachments 5 Horizontal stabilizer deicer boots R H side CHECK Condition Attachments 6 Elevator and trim CHECK Condition D...

Page 166: ...ID OVERTEMPERATURE RISKS AT START 1 Preflight inspection COMPLETED 2 Cabin access door CLOSED LOCKED 3 Baggage STOWED 4 Parking brake SET 5 Weight and balance COMPUTED CHECKED 6 Pilot and R H station...

Page 167: ...ARNING CAS MESSAGE OXYGEN OFF 18 Fuel Quantity CHECKED Tank selector L or R CHECKED FUEL SEL switch AUTO WARNING CAS MESSAGE AUTO SEL OFF SHIFT push button PRESS The selector changes tank On ground ob...

Page 168: ...CTING SOURCE CHECK 1 IGNITION switch AUTO 2 STARTER switch OFF 3 INERT SEP switch OFF 4 Landing gear control DN 5 ELECTRIC POWER panel SOURCE selector BAT Voltage CHECKED 24 5Volts 6 Engine controls M...

Page 169: ...WARNING CAS MESSAGE FUEL PRESS OFF 8 Propeller AREA CLEAR 9 ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON NOTE The utilizati...

Page 170: ...N APPEARS MAX ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF Wait ITT 800 C then STARTER switch OFF BEFORE A...

Page 171: ...13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF Ng 50 STARTER switch OFF WARNING CAS MES...

Page 172: ...ING ENGINE USING AIRPLANE POWER 5 5 10 Condition lever HI IDLE 11 Engine instruments CHECK Ng 69 2 Oil pressure Oil temperature ITT green sector 12 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AU...

Page 173: ...ECK 2 IGNITION switch AUTO 3 STARTER switch OFF 4 INERT SEP switch OFF 5 Landing gear control DN 6 SOURCE selector GPU WARNING CAS MESSAGE GPU DOOR ON WARNING CAS MESSAGE BAT OFF ON Battery voltage CH...

Page 174: ...MESSAGE FUEL PRESS OFF Fuel pressure indicator CHECK 9 Propeller AREA CLEAR 10 ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON...

Page 175: ...ION APPEARS MAX ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF Wait ITT 800 C then STARTER switch OFF BEFORE...

Page 176: ...ondition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF Ng 50 STARTER switch OFF WARNING CAS MESSAGE...

Page 177: ...2 Propeller governor lever FEATHER 13 GPU HAVE IT DISCONNECTED WARNING CAS MESSAGE GPU DOOR OFF 14 Condition lever HI IDLE 15 Propeller governor lever MAX RPM 16 Engine instruments CHECK Ng 69 2 Oil p...

Page 178: ...INE TOTAL SHUT DOWN WAIT AT LEAST 30 SECONDS BEFORE INITIATING A MOTORING 1 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND TH...

Page 179: ...OFF To clear fuel and vapor internally trapped 4 STARTER switch ON during 15 sec maxi WARNING CAS MESSAGE STARTER ON To cool engine following shut down in high temperature environment 4 STARTER switch...

Page 180: ...oring procedure 1 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Propeller governor...

Page 181: ...S MESSAGE STARTER OFF WARNING CAS MESSAGE IGNITION OFF if IGNITION switch AUTO WARNING CAS MESSAGE IGNITION ON if IGNITION switch ON then switch to AUTO WARNING CAS MESSAGE IGNITION Off 7 Engine instr...

Page 182: ...AP TRIMS MASTER switch ON 4 PFD 1 MFD and PFD 2 Brightness ADJUST If necessary DISPLAY BACKUP button CHECK then return to NORMAL mode If battery current 100 A 5 ECS panel BLEED VALVE switch ON LO or H...

Page 183: ...en ADJUSTED Roll trim L R then ADJUSTED 12 DE ICE SYSTEM panel MFD on system page PROP DE ICE switch ON Check illumination of the green light located above the switch PROP DE ICE switch OFF WINDSHIELD...

Page 184: ...I light ON 2 INERT SEP switch CHECKED ON CHECK WARNING CAS MESSAGE INERT SEP ON ON 3 Passenger briefing AS REQUIRED 4 Parking brake RELEASED WARNING CAS MESSAGE PARK BRAKE OFF 5 L H and R H seats brak...

Page 185: ...Flaps TO 5 DE ICE SYSTEM panel AIRFRAME DE ICE switch As required PROP DE ICE switch As required If runway is in good condition without icing conditions INERT SEP switch OFF WARNING CAS MESSAGE INERT...

Page 186: ...sed INERT SEP ON ON 11 Fuel Gages quantity symmetry CHECKED FUEL SEL switch CHECK AUTO AUX BP fuel switch CHECK AUTO 12 Flight instruments CHECKED Altimeter setting ADJUSTED ALT SEL ADJUSTED 13 VHF VO...

Page 187: ...HECK attitude 2 2 Heading HSI Stand by compass CHECK Altimeter setting CHECK 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ITT green sector 5 CAS display CHECK All messages OFF except INERT...

Page 188: ...TIONS 1 Horizon CHECK attitude 2 2 Heading HSI Stand by compass CHECK Altimeter setting CHECK 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ITT green sector 5 CAS display CHECK All messages...

Page 189: ...TION See Takeoff distances Chapter 5 8 Normal take off ATTITUDE 7 5 Short take off ATTITUDE 15 10 Vertical speed indicator POSITIVE 11 Brakes APPLY Briefly 12 Landing gear control IAS 128 KIAS UP At s...

Page 190: ...N OBSERVE TRQ Ng Np ITT T AND OIL PRESSURE LIMITATIONS USE OPTIMUM TORQUE AND OR REFER TO TABLES IN CHAPTER 5 7 2 Climb speed AS REQUIRED 3 ECS panel Cabin altitude selector Cruise altitude 1000 feet...

Page 191: ...the PFDs CAUTION OBSERVE TRQ Ng Np ITT T AND OIL PRESSURE LIMITATIONS USE OPTIMUM TORQUE AND OR REFER TO TABLES IN CHAPTER 5 7 2 Pressurization CHECK 3 Fuel Gages CHECK REGULARLY CHECK consumption exp...

Page 192: ...bin rate selector Adjusted 4 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNITION AND INERT SEP ON CAUTION USE OF CONTROL REVERSE BETA RANG...

Page 193: ...ers CHECK 2 Fuel Gages CHECK Quantity Symmetry Fullest tank SELECT 3 INERT SEP switch IAS 200 KIAS ON 4 Propeller lever MAX RPM 5 Landing gear control IAS 178 KIAS DN 3 Green lights ON Red warning lig...

Page 194: ...e As required Reverse may be applied as soon as the wheels touch the ground To avoid ingestion of foreign objects come out the reverse as speed reduces and use the brakes if necessary for further dece...

Page 195: ...November 30 2010 Rev 0 CHECK LIST PROCEDURES GO AROUND 1 Simultaneously Power lever TRQ 100 Attitude 7 5 2 Flaps TO If the vertical speed is positive and if IAS is at or above 85 kt 3 Landing gear co...

Page 196: ...Power lever Display TRQ 100 4 Takeoff ROTATION See Takeoff distances Chapter 5 8 ATTITUDE 7 5 AFTER LANDING RUNWAY CLEAR AIRPLANE STOPPED 1 DE ICE SYSTEM panel AIRFRAME DE ICE switch OFF PROP DE ICE...

Page 197: ...imum 4 TAXI light OFF 5 AP TRIMS MASTER switch OFF 6 AVIONICS MASTER switch START 7 Pressurization BLEED VALVE switch OFF Check for cabin depressurization 8 FAN FLOW switch if installed As required 9...

Page 198: ...TS panel All switches OFF 16 Fuel AUX BP switch OFF FUEL SEL switch MAN Tank selector OFF 17 GENERATOR selector OFF 18 SOURCE selector OFF 19 CRASH lever PUSHED DOWN 20 Parking brake As required CAUTI...

Page 199: ...ECTRIC POWER panel SOURCE selector OFF GENERATOR selector OFF 3 ENGINE START panel IGNITION switch AUTO The IGNITION switch is normally selected to AUTO This ensures ignition whenever the STARTER swit...

Page 200: ...o have the door in place 9 AVIONICS MASTER switch OFF 10 AP TRIMS MASTER switch OFF 11 ECS panel BLEED VALVE switch OFF CABIN FAN switch OFF FREON or AIR COND switch if installed OFF DUMP switch GUARD...

Page 201: ...ure prevents movement into reverse range Trying to force the mechanism will cause damage Power lever IDLE Propeller governor lever MAX RPM Condition lever CUT OFF 18 BAT BUS power supply Access lighti...

Page 202: ...been stopped more than 3 hours at a temperature below 10 C 14 F GPU 28 Volts If using a GPU ensure that it provides a 28 volt regulated voltage with negative on earth as well as it supplies 800 amper...

Page 203: ...orated microphones pilot only are correctly connected in oxygen drawer to radio system Oxygen emergency system in good operation condition must be imperatively taken on board during all flights even a...

Page 204: ...is indicated by display of corresponding CAS message when control switches are ON WARNING CAS MESSAGE PITOT HT ON 1 2 ON WARNING CAS MESSAGE STALL HEAT ON ON PITOT 1 HTR switch OFF PITOT 2 STALL HTR...

Page 205: ...s CHECK 3 Windows CHECK General condition No cracks 4 Emergency exit CLOSED LOCKED Anti theft safety REMOVE STOW 5 Baggage compartment STRAPS IN PLACE 6 Partition net if installed IN PLACE 7 Emergency...

Page 206: ...ored outside the use of the flight control lock and blanking covers is recommended Propeller should be tied down to prevent rotation without oil pressure When the airplane is stored for extended perio...

Page 207: ...tank air vent UNOBSTRUCTED CHECK Air vent is not likely to be obstructed by ice or water as it is located in a wing lower surface recess 8 External pitot IAS Condition CHECK 9 Internal pitot VMO Cond...

Page 208: ...airfields or in snow check wheel wells to make sure they are clean and not obstructed Check frequently all landing gear retraction mechanism components shock absorbers tires and brakes This is particu...

Page 209: ...No leak deterioration wear 6 Engine cowls Condition CHECK CLOSED LOCKED 7 Air inlets Main No crack UNOBSTRUCTED Check for no cracks which are sometimes put in evidence by traces of soot resulting fro...

Page 210: ...6 in of minimum height with half tank NOTE Crush or relieve the shock absorber one time or twice before the inspection to remove possible sticking In case of doubt request a check of the shock absorbe...

Page 211: ...ck that outside handle of emergency exit is flush with door skin 1 Static pressure ports Clean CHECK 2 Ventral fins CHECK Attachment condition Ventral fins are made of two parts one fixed part and one...

Page 212: ...tion 1 November 30 2010 Rev 0 AMPLIFIED PROCEDURES PREFLIGHT INSPECTION Cont d 7 Vertical stabilizer deicer boots CHECK Condition Attachments 8 Rudder and trim CHECK Condition Trim position 9 Static d...

Page 213: ...E SURE THAT MAN OVRD CONTROL IS OFF TO AVOID OVERTEMPERATURE RISKS AT START 1 Preflight inspection COMPLETED 2 Cabin access door CLOSED LOCKED 3 Baggage STOWED 4 Parking brake SET PARK BRAKE CAS messa...

Page 214: ...KUP button OUT 12 IGNITION switch AUTO The IGNITION switch is normally selected to AUTO This ensures ignition whenever the starter is activated 13 STARTER switch OFF If not starter is going to operate...

Page 215: ...tank On ground observe a tank change every minute and 15 seconds 19 Fire detection TEST if installed CARRY OUT 20 EXT LIGHTS panel STROBE AS REQUIRED The use of strobe lights may generate discomfort...

Page 216: ...CHECK 1 IGNITION switch AUTO 2 STARTER switch OFF 3 INERT SEP switch OFF 4 Landing gear control DN 5 ELECTRIC POWER panel SOURCE selector BAT Mains voltage CHECKED 24 5 Volts 6 Engine controls MAN OV...

Page 217: ...pter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE When condition lever is positioned on LO IDLE before having obtained 13 of Ng there is a risk of overtemperature further to an excessive...

Page 218: ...y ventilating combustion chamber NOTE No action is required for the following conditions ITT from 800 C to 870 C limited to 20 seconds ITT from 870 C to 1000 C limited to 5 seconds CAUTION IF 10 SECON...

Page 219: ...is selected ON abort the start If Ng does not reach 50 within 1 minute abort the start Before starting a new test respect delays indicated in Chapter 2 4 STARTER OPERATION LIMITS Oil pressure WARNING...

Page 220: ...STARTER OFF WARNING CAS MESSAGE IGNITION OFF Engine instruments CHECK Ng increasing to 69 2 Oil pressure ITT green sector NOTE This behaviour should only be observed with outside low temperature OAT 0...

Page 221: ...AMPLIFIED PROCEDURES STARTING ENGINE USING AIRPLANE POWER 6 6 13 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary MAIN GEN CAS message normally goes out as soon as STARTER CAS message goe...

Page 222: ...CHECK 2 IGNITION switch AUTO 3 STARTER switch OFF 4 INERT SEP switch OFF 5 Landing gear control DN 6 SOURCE selector GPU WARNING CAS MESSAGE GPU DOOR ON WARNING CAS MESSAGE BAT OFF ON Battery voltage...

Page 223: ...opeller AREA CLEAR 10 ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING CAS MESSAGE STARTER ON WARNING CAS MESSAGE IGNITION ON NOTE The utilization of the starter is bound by limitatio...

Page 224: ...ime stop immediately the starting procedure as indicated in the following caution and inform the maintenance department This starting engine procedure must be also applied in case of drop in voltage s...

Page 225: ...Condition lever CUT OFF IGNITION switch OFF Wait ITT 800 C then STARTER switch OFF BEFORE ANY RESTARTING ATTEMPT CARRY OUT A MOTORING Refer to paragraph MOTORING CONTINUE WITH NORMAL PROCEDURE HEREAFT...

Page 226: ...TING PROCEDURE Condition lever CUT OFF IGNITION switch OFF STARTER switch OFF WAIT FOR 1 MINUTE Refer to Chapter 2 4 STARTER OPERATION LIMITS THEN TRY TO RESTART ENGINE START panel IGNITION switch AUT...

Page 227: ...rved with outside low temperature OAT 0 C cold engine This procedure may be used for the first starting of the day CONTINUE WITH NORMAL PROCEDURE HEREAFTER 11 SOURCE selector BAT WARNING CAS MESSAGE B...

Page 228: ...L panel AUX BP switch AUTO At this time observing a drop in the fuel pressure is normal WARNING CAS MESSAGE AUX BOOST PMP ON OFF 18 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary MAIN G...

Page 229: ...is collected and not drained under the engine To improve cooling of the bearing cavities and prevent oil coking after shut down in high OAT above 35 C 95 F environment it is recommended to perform a 3...

Page 230: ...ING CAS MESSAGE IGNITION OFF To clear fuel and vapor internally trapped 4 STARTER switch ON for 15 sec maxi WARNING CAS MESSAGE STARTER ON To cool engine following shut down in high temperature enviro...

Page 231: ...1 minute it is possible to initiate a starting procedure from a motoring procedure This procedure will conserve the battery by taking advantage of first Ng acceleration 1 Engine controls MAN OVRD cont...

Page 232: ...for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING CAS MESSAGE OIL PRESS OFF NOTE No action is required for the following conditions ITT from 800 C to 870 C limited to 20 seconds ITT...

Page 233: ...panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF At this time observing a drop in the fuel pressure is normal 11 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessary MAIN GEN...

Page 234: ...icated voltage on the ST BY generator is low close to 27 volts reset the ST BY generator and recheck the voltage The indicated voltage should be in the green range then again on MAIN 4 PFD 1 MFD and P...

Page 235: ...ly selected to NORMAL However if canopy misting is evident select DEFOG and increase a little the cabin temperature thanks to the CABIN TEMP selector Cabin altitude selector Airfield altitude 500 feet...

Page 236: ...or in green range TO TAKEOFF Roll trim L R then ADJUSTED Adjust the indicator first at neutral position horizontal marker 12 DE ICE SYSTEM panel Flight into known icing conditions is authorized only w...

Page 237: ...eflation are sufficient when power lever is positioned on IDLE However it is advised for check to choose a Ng power 80 in order to obtain operation design pressure which enables illuminating surely th...

Page 238: ...s selected with the power lever 3 Passenger briefing AS REQUIRED 4 Parking brake RELEASED Make sure that chocks are removed if used WARNING CAS MESSAGE PARK BRAKE OFF 5 L H and R H seat brakes CHECKED...

Page 239: ...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 switch is turned...

Page 240: ...spent with the propeller RPM in the caution yellow range at a minimum 4 Flaps TO 5 DE ICE SYSTEM panel AIRFRAME DE ICE switch As required PROP DE ICE switch As required If runway is in good condition...

Page 241: ...ED Adjust at neutral position 8 Pilot s Passengers belts CHECK Passengers table REMOVED 9 STROBE switch ON 10 CAS display CHECK All messages OFF except PARK BRAKE ON and if used INERT SEP ON ON 11 Fue...

Page 242: ...if installed ADJUSTED Transponder code ADJUSTED 14 Engine instruments CHECK All engine parameters must be in green range except propeller RPM which will be about 1000 RPM or more with power lever at...

Page 243: ...as to indicate a 2 nose up attitude when airplane center of gravity is at a middle average 2 Heading HSI Stand by compass CHECK The indication of the stand by compass is disturbed when windshield s d...

Page 244: ...to indicate a 2 nose up attitude when airplane center of gravity is at a middle average 2 Heading HSI Stand by compass CHECK The indication of the stand by compass is disturbed when windshield s deic...

Page 245: ...keoff maximum torque 100 will be applied after brake release On short runway maximum torque will be applied before brake release 8 Power lever TRQ 100 9 Takeoff ROTATION See Takeoff distances Chapter...

Page 246: ...applied after brake release On short runway maximum torque will be applied before brake release 8 Power lever TRQ 100 9 Takeoff ROTATION See Takeoff distances Chapter 5 8 Normal take off ATTITUDE 7 5...

Page 247: ...are locked If the red warning light is fixed ON there is a discrepancy refer to EMERGENCY PROCEDURES It is possible that the 3 landing gear position green indicator lights flash uncertainly then go of...

Page 248: ...ording to engine operation tables in Chapter 5 7 These tables give the max climb power torque setting MXCL For each engine when torque is reduced below 100 at high altitude according to the tables the...

Page 249: ...position during climb Do not wait a fresh sensation to perform this setting Desired temperature will be as longer to obtain as setting is made later 4 Fuel tank gages CHECK CORRECT Quantity Symmetry I...

Page 250: ...limiter may be reached This limit is 110 at sea level and drops to about 100 at 30000 ft Therefore any propeller RPM reducing performed in altitude from a torque close to 100 if ITT limit permits it...

Page 251: ...LARLY CHECK consumption expected fuel at destination tank automatic change every 10 minutes symmetry max dissymmetry 25 us gal 95 Litres When the cruise parameters are stabilized after 4 min minimum 4...

Page 252: ...out 500 ft min 5 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNITION AND INERT SEP ON The maximum speed for changing the position of the i...

Page 253: ...py misting in moist conditions turn DEFOG NORMAL distributor to 12 o clock position turn CABIN TEMP selector in hot section and turn windshield heat ON prior to descent 7 Fuel Gages CHECK Quantity Sym...

Page 254: ...gear control IAS 178 KIAS DN Green warning lights ON Red warning light OFF Post MOD70 021 32 5 Landing gear control IAS 178 KIAS DN Green indicator lights ON Red warning light OFF During the sequence...

Page 255: ...S LDG However when autopilot is engaged in APR mode with coupled GS flaps must be extended in landing position before crossing the OUTER MARKER or 1000 ft AGL 10 Approach speed Flaps LDG 80 KIAS To en...

Page 256: ...ects come out the reverse as speed reduces and use the brakes if necessary for further deceleration High power reverse at low speed can throw loose material into the air and can cause control problems...

Page 257: ...power is applied Right rudder pressure will be required to maintain coordinated straight flight until the rudder trim can be adjusted 2 Flaps TO If speed has been maintained at 80 KIAS or more and TR...

Page 258: ...e power with full flaps as airplane may lift off prematurely at low speed 2 Elevator trim Green sector To use elevator trim manual control is faster than to use electric control Ensure that runway len...

Page 259: ...ECKED ON It is highly recommended to use inertial separator during all ground operations WINDSHIELD switch As required PITOT 1 HTR switch OFF PITOT 2 STALL HTR switch OFF BLEED VALVE switch As require...

Page 260: ...ring area ITT is considered stabilized when variations are less than 5 C If BLEED VALVE was selected to OFF after landing and taxi was performed at IDLE power the taxi time is considered as cooling ti...

Page 261: ...OFF 13 AVIONICS MASTER switch OFF 14 EXT LIGHTS panel All switches OFF 15 INT LIGHTS panel All switches OFF 16 Fuel When fuel pressure is below 10 psi check AUX BP pump is operating AUX BP switch OFF...

Page 262: ...erating on ramps taxiways or runways where surface snow ice standing water or slush may be ingested by the engine or freeze on engine or cowlings NOTE Refer to Figure 5 4 1 to convert OAT to SAT in fl...

Page 263: ...t enter or leave as soon as possible icing conditions Apply LEADING EDGES DEICING FAILURE emergency procedure Ice protection procedures 1 Prior to entering IMC as a preventive If 0 C OAT 13 C PROP DE...

Page 264: ...ATOR IS IN FIXED POSITION If a high speed descent 200 KIAS is anticipated into known icing conditions position INERT SEP switch to ON before accelerating This will avoid reducing speed below 200 KIAS...

Page 265: ...Standby compass indications are altered when windshield deicing system s operate s 3 Procedures for holding approach and landing in icing conditions Minimum recommended speeds are Flaps UP 130 KIAS F...

Page 266: ...eezing around the heated stall warning may appear Above recommended speeds take into account on one side the stall speed increase due to profile shape deterioration and on the other side the weight in...

Page 267: ...tures as cold as 18 C increased vigilance is warranted at temperatures around freezing with visible moisture present If the visual cues specified in Section 2 Limitations for identifying severe icing...

Page 268: ...t 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 w...

Page 269: ...N switch ON 2 INERT SEP switch ON UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW 1 2 Refer if required to paragraph UTILIZATION BY COLD WEATHER AND VERY COLD WEATHER Preflight inspecti...

Page 270: ...5 compared to the takeoff position and the runway condition The ground roll may be multiplied by 3 in some melting or not tamped snow cases 2 IGNITION switch ON 3 INERT SEP switch ON Takeoff 1 Lightly...

Page 271: ...ing fluid on the wings stabilizers and movable surfaces upper and lower surfaces shortly before takeoff Taxiing 1 INERT SEP switch ON 2 Taxi at very slow speed max 5 KIAS Use area of power lever to ad...

Page 272: ...behaviour The engine torque tends to make the airplane turn to the left 2 Taxi at very slow speed max 5 KIAS Use area of power lever to adjust speed Apply very smooth variations using power lever 3 S...

Page 273: ...the normal procedures for the airplane use when operating under temperatures between 0 C and 40 C on ground Figure 4 5 1 OPERATING ENVELOPES BY COLD WEATHER 0 C to 25 C AND VERY COLD WEATHER 25 C to...

Page 274: ...ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS 2 Carry out a complete rotation of the propeller to check its free rotation...

Page 275: ...r the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Landing After landing 1 Apply normal procedures defined in Chapter s 4 3 and or 4 4 2 Apply according to the condition of runway...

Page 276: ...e is modified as follows Preflight inspection Before starting the engine Starting the engine Apply the procedures defined for the Envelope 3 After starting the engine 1 ECS panel As soon as the curren...

Page 277: ...THER 25 C to 40 C 10 10 Taxiing Before takeoff Takeoff Apply procedures defined for Envelope 1 Landing After landing Shut down Apply procedures defined for Envelope 1 Complement If landing is foreseen...

Page 278: ...nd movable surfaces Apply according to the condition of runways and taxiways the procedures UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVER...

Page 279: ...This enables to preheat spark igniters before starting the engine Before starting the engine Apply normal procedures defined in Chapter s 4 3 and or 4 4 Starting the engine The starting must be manda...

Page 280: ...ON WARNING CAS MESSAGE AUX BOOST PMP ON ON WARNING CAS MESSAGE FUEL PRESS OFF Fuel pressure indicator Check 5 Propeller AREA CLEAR 6 ENGINE START panel IGNITION switch ON WARNING CAS MESSAGE IGNITION...

Page 281: ...wer unit HAVE IT DISCONNECTED WARNING CAS MESSAGE GPU DOOR OFF 11 FUEL panel AUX BP switch AUTO WARNING CAS MESSAGE AUX BOOST PMP ON OFF 12 Generator WARNING CAS MESSAGE MAIN GEN OFF RESET if necessar...

Page 282: ...5 21 Edition 1 November 30 2010 Rev 0 PARTICULAR PROCEDURES UTILIZATION BY COLD WEATHER 0 C to 25 C AND VERY COLD WEATHER 25 C to 40 C 8 10 Taxiing Before takeoff Takeoff Apply procedures defined for...

Page 283: ...in distance with increase of piloting difficulties and landing performance During approach with crosswind maintain airplane in drift correction at the latest until the beginning of flare In short fin...

Page 284: ...h this operation may provide pitch oscillations while increasing the yaw movement to the wind Do not deflect ailerons into wind while taxiing This will raise spoilers and have a detrimental effect A g...

Page 285: ...TAXI TAKEOFF 1 INERT SEP switch ON 2 Reverse Do not use In fact on a flat runway with grass it is necessary to adopt a power greater than the one obtained when the power lever is set to IDLE so the p...

Page 286: ...n any part of the intended flight When less than 24 satellites are available or less than 23 if equipment uses pressure altitude information the pilot must make sure that RAIM function is available on...

Page 287: ...NAVIGATION 2 2 Non precision approach with coupled autopilot Coupling with autopilot may be made in NAV mode except in the following cases holding pattern landing pattern turn interrupted approach whi...

Page 288: ...CONVERSIONS 5 4 1 5 5 STALL SPEEDS 5 5 1 5 6 WIND COMPONENTS 5 6 1 5 7 ENGINE OPERATION 5 7 1 Maximum climb power 5 7 2 Maximum cruise power 5 7 4 Normal recommended cruise power 5 7 6 5 8 TAKEOFF DI...

Page 289: ...2010 Rev 0 TABLE OF CONTENTS Continued Page 5 10 CRUISE PERFORMANCE 5 10 1 Maximum cruise 5 10 2 Normal recommended cruise 5 10 9 Intermediate cruise 5 10 16 Long Range cruise 5 10 23 5 11 TIME CONSU...

Page 290: ...Maximum noise level permissible Demonstrated noise level ICAO Annex 16 Chapter 6 Appendix 3 80 dB A 73 3 dB A ICAO Annex 16 Chapter 10 Appendix 6 88 dB A 80 4 dB A TBM 700 airplane has received the n...

Page 291: ...FLYOVER NOISE LEVEL Flyover noise level measured in accordance with 14 CFR Part 36 Appendix F 77 4 dB A NOTE No determination has been made by the Federal Aviation Administration that the noise level...

Page 292: ...GR UP FLAPS TO LDG GR DN FLAPS LDG LDG GR DN KIAS KCAS KIAS KCAS KIAS KCAS 125 150 175 200 225 250 266 127 152 177 203 228 253 270 70 80 90 100 120 140 160 69 80 90 101 121 141 162 60 70 80 90 100 110...

Page 293: ...25 150 175 200 225 250 271 124 149 174 199 224 249 270 70 80 90 100 120 140 160 70 80 90 100 120 139 159 60 70 80 90 100 110 120 59 69 79 90 100 110 120 MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS...

Page 294: ...n 1 November 30 2010 Rev 0 5 3 CABIN PRESSURIZATION ENVELOPE Figure 5 3 1 CABIN PRESSURIZATION ENVELOPE 260 240 220 180 140 160 200 280 300 1000 2000 3000 4000 5000 6000 7000 8000 Cabin altitude feet...

Page 295: ...12 21 22 31 32 4000 13 12 03 02 07 08 17 18 27 28 6000 17 16 07 06 03 04 13 14 23 24 8000 21 20 11 10 01 00 09 10 19 20 10000 25 24 15 14 05 04 05 06 15 16 12000 29 28 19 18 09 08 01 02 11 12 14000 3...

Page 296: ...AS 4850 lbs 2200 kg UP DN DN UP TO LDG 65 62 53 66 63 53 75 71 61 70 67 57 71 68 57 81 77 66 78 73 63 79 75 63 90 84 73 91 87 75 93 89 75 105 100 86 5512 lbs 2500 kg UP DN DN UP TO LDG 70 66 57 71 67...

Page 297: ...H H E A D W I N D C O M P O N E N T S kt 20 10 0 10 20 30 40 25 kt DEMONSTRATED CROSSWIND 0 10 20 30 40 50 40 30 160 20 10 50 60 70 80 90 100 110 120 CROSSWIND COMPONENTS kt 10 20 30 40 0 180 Figure 5...

Page 298: ...ng tables give the maximum torque to be set Maximum climb power TRQ 84 for IAS 130 KIAS Add 1 of TRQ for each additional 15 KIAS on climb airspeed cf tables Figures 5 7 1A and 5 7 1B Maximum cruise po...

Page 299: ...24 22 20 18 TRQ 100 100 16 TRQ 100 99 14 97 12 100 95 10 98 93 08 100 96 91 06 99 94 89 04 100 97 92 87 02 99 95 90 85 0 97 93 87 82 02 100 95 90 85 80 04 98 93 88 82 78 06 100 95 91 86 80 75 08 98 9...

Page 300: ...90 85 81 76 72 36 98 94 89 84 79 74 70 34 97 92 87 82 77 73 68 32 100 95 91 86 81 76 71 66 30 99 94 89 84 79 74 69 65 28 97 92 87 82 77 72 68 63 26 100 95 90 85 80 75 70 66 61 24 98 93 88 83 78 73 69...

Page 301: ...FL OAT C 100 110 120 130 140 150 160 170 180 190 200 24 22 20 18 TRQ 100 16 TRQ 100 14 12 10 08 100 06 99 04 97 02 100 95 0 98 93 02 100 95 91 04 98 93 88 06 100 96 91 85 08 98 93 88 82 10 100 96 91...

Page 302: ...34 97 91 86 81 75 32 100 95 89 84 79 73 30 98 93 88 82 77 71 28 96 91 86 80 75 69 26 100 94 89 84 78 73 67 24 98 92 87 82 76 71 66 22 100 96 90 85 80 74 69 64 20 98 94 88 83 78 72 67 62 18 97 92 86 8...

Page 303: ...Q 100 16 TRQ 100 14 100 12 98 10 96 08 100 94 06 98 92 04 100 96 90 02 99 93 87 0 100 96 91 85 02 98 93 88 82 04 100 95 90 85 79 06 98 93 88 83 76 08 100 95 90 85 81 74 10 98 93 88 83 78 71 12 100 95...

Page 304: ...0 75 69 32 100 95 90 83 78 73 67 30 98 93 88 81 76 71 66 28 100 96 91 86 79 74 69 64 26 98 94 89 83 77 72 67 62 24 96 92 87 81 75 70 65 60 22 100 94 90 85 79 73 68 63 58 20 98 92 87 83 76 71 66 61 57...

Page 305: ...51 1066 1181 1329 1526 1493 1657 1837 2051 2329 1017 1132 1280 1444 1657 1591 1772 1968 2215 2510 PRESSURE ALTITUDE ISA 10 C ISA 20 C ISA 30 C ISA 37 C ALTITUDE ft GR D50 GR D50 GR D50 GR D50 0 2000 4...

Page 306: ...280 1444 1640 1837 2067 2001 2198 2461 2723 3051 1378 1542 1739 1968 2231 2133 2362 2625 2920 3281 PRESSURE ALTITUDE ISA 10 C ISA 20 C ISA 30 C ISA 37 C ALTITUDE ft GR D50 GR D50 GR D50 GR D50 0 2000...

Page 307: ...2000 4000 6000 8000 3060 3030 3000 2970 2930 2920 2890 2860 2830 2800 2800 2770 2740 2700 2660 2690 2660 2630 2590 2550 2590 2550 2520 2480 2440 2480 2455 2415 2380 2340 5512 lbs 2500 kg SL 2000 4000...

Page 308: ...00 4000 6000 8000 2680 2640 2590 2550 2500 2560 2500 2460 2420 2360 2440 2390 2340 2290 2240 2330 2280 2230 2180 2130 2220 2180 2130 2080 2030 2120 2080 2030 1980 1925 5512 lbs 2500 kg SL 2000 4000 60...

Page 309: ...3 02 00 10 8 2 6 4 6000 02 00 10 7 2 6 4 02 15 11 9 2 9 5 03 00 14 11 3 7 6 8000 02 45 12 10 3 2 6 03 00 15 12 4 0 7 04 00 19 15 5 9 10000 03 15 15 12 4 0 7 04 00 18 14 4 8 9 05 00 23 18 6 11 12000 04...

Page 310: ...5 11 9 2 9 5 6000 02 15 11 8 2 9 5 02 30 12 10 3 2 6 03 15 16 13 4 2 7 8000 03 00 14 11 3 7 7 03 30 16 13 4 2 8 04 30 21 17 5 5 10 10000 03 45 17 14 4 5 8 04 15 20 16 5 3 10 05 30 26 20 6 9 13 12000 0...

Page 311: ...12 10 3 2 5 6000 02 15 12 9 3 2 5 02 45 14 11 3 7 6 03 30 18 14 4 8 8 8000 03 00 16 12 4 2 7 03 45 18 14 4 8 9 04 45 24 19 6 3 11 10000 04 00 19 15 5 0 9 04 45 23 18 6 1 11 06 00 29 23 7 7 15 12000 05...

Page 312: ...5 9 7 2 4 5 02 15 11 9 2 9 6 6000 02 15 11 9 2 9 6 02 45 13 10 3 4 7 03 30 16 13 4 2 9 8000 03 00 14 11 3 7 8 03 30 17 13 4 5 10 04 30 21 17 5 5 12 10000 04 00 18 14 4 8 11 04 30 21 16 5 5 13 05 45 27...

Page 313: ...8 2 6 5 02 30 12 10 3 2 7 6000 02 30 12 10 3 2 7 03 00 14 11 3 7 8 03 45 18 15 4 8 10 8000 03 30 16 13 4 2 10 04 00 19 15 5 0 11 05 00 24 19 6 3 14 10000 04 30 20 16 5 3 12 05 00 24 19 6 3 14 06 30 30...

Page 314: ...6 02 45 14 11 3 7 8 6000 02 45 14 11 3 7 8 03 15 16 13 4 2 9 04 15 21 16 5 5 12 8000 03 45 18 14 4 8 11 04 30 21 17 5 5 13 05 30 28 22 7 4 16 10000 04 45 23 18 6 1 14 05 30 27 21 7 1 17 07 15 34 27 9...

Page 315: ...2120 2100 2070 2030 1980 1940 2000 1960 1920 1880 1830 1910 1870 1830 1780 1730 1820 1780 1730 1690 1630 1740 1695 1650 1600 1545 1650 1620 1570 1520 1465 5512 lbs 2500 kg SL 2000 4000 6000 8000 1900...

Page 316: ...2970 2950 2920 2900 2870 2850 2820 2800 2760 2740 2730 2700 2670 2650 2610 2620 2600 2570 2540 2500 2520 2490 2460 2430 2395 2410 2395 2365 2330 2295 5512 lbs 2500 kg SL 2000 4000 6000 8000 2710 2700...

Page 317: ...OT S OPERATING HANDBOOK Page 5 10 1 Edition 1 November 30 2010 Rev 0 5 10 CRUISE PERFORMANCE Conditions ISA Weight 5512 lbs 2500 kg Figure 5 10 1 CRUISE PERFORMANCE TAS KTAS Flight level FL 100 200 30...

Page 318: ...67 20000 44 100 218 171 57 6 211 277 209 275 208 273 21000 46 100 216 170 57 1 210 280 208 278 207 276 22000 48 100 214 168 56 5 209 283 207 281 206 279 23000 50 100 212 166 56 0 208 286 206 284 205 2...

Page 319: ...270 20000 34 100 220 173 58 2 209 281 207 278 206 276 21000 36 100 218 171 57 6 208 284 206 281 205 279 22000 38 100 216 170 57 1 207 287 205 285 204 282 23000 40 100 215 168 56 7 206 290 204 288 202...

Page 320: ...272 20000 29 100 222 174 58 6 208 282 206 280 205 278 21000 31 100 220 173 58 1 207 285 205 283 204 281 22000 33 100 218 171 57 5 206 289 204 286 203 284 23000 35 100 216 170 57 1 205 292 203 289 202...

Page 321: ...273 20000 24 100 223 175 58 9 207 284 205 281 204 279 21000 26 100 221 174 58 5 206 287 204 285 203 282 22000 28 100 220 172 58 0 205 290 203 288 202 285 23000 30 100 218 171 57 5 204 293 202 291 201...

Page 322: ...5 275 20000 19 100 224 176 59 3 206 285 204 283 203 281 21000 21 100 223 175 58 9 205 288 203 286 202 284 22000 23 100 221 174 58 5 204 291 202 289 201 287 23000 25 100 220 172 58 0 203 295 201 292 20...

Page 323: ...284 202 283 21000 16 100 224 176 59 2 205 291 202 287 201 286 22000 18 100 223 175 58 9 203 294 201 291 200 289 23000 20 98 218 171 57 6 201 295 200 294 197 290 24000 22 96 211 166 55 7 198 296 196 29...

Page 324: ...1 202 279 20000 4 97 225 177 59 4 202 288 201 287 199 284 21000 6 94 218 171 57 5 198 288 198 286 196 283 22000 8 92 211 166 55 7 196 288 193 285 191 282 23000 10 88 204 160 53 9 195 292 190 284 188 2...

Page 325: ...9 210 267 20000 44 100 218 171 57 6 211 277 209 275 208 273 21000 46 100 216 170 57 1 210 280 208 278 207 276 22000 48 100 214 168 56 5 209 283 207 281 206 279 23000 50 100 212 166 56 0 208 286 206 28...

Page 326: ...272 208 270 20000 34 100 220 173 58 2 209 281 207 278 206 276 21000 36 100 218 171 57 6 208 284 206 281 205 279 22000 38 100 216 170 57 1 207 287 205 285 204 282 23000 40 100 215 168 56 7 206 290 204...

Page 327: ...274 207 272 20000 29 100 222 174 58 6 208 282 206 280 205 278 21000 31 100 220 173 58 1 207 285 205 283 204 281 22000 33 100 218 171 57 5 206 289 204 286 203 284 23000 35 100 216 170 57 1 205 292 203...

Page 328: ...275 206 273 20000 24 100 223 175 58 9 207 284 205 281 204 279 21000 26 100 221 174 58 5 206 287 204 285 203 282 22000 28 100 220 172 58 0 205 290 203 288 202 285 23000 30 100 218 171 57 5 204 293 202...

Page 329: ...7 277 205 275 20000 19 100 224 176 59 3 206 286 204 283 203 281 21000 21 100 223 175 58 9 205 288 203 286 202 284 22000 23 100 221 174 58 5 204 291 202 289 201 287 23000 25 97 216 170 57 1 201 292 199...

Page 330: ...06 278 204 277 20000 14 100 226 177 59 7 206 287 203 284 202 283 21000 16 98 220 173 58 1 203 288 202 286 199 283 22000 18 96 214 168 56 5 200 289 198 286 196 284 23000 20 92 207 162 54 7 197 289 195...

Page 331: ...201 278 199 275 20000 4 90 213 167 56 3 196 280 194 277 193 275 21000 6 87 206 162 54 4 193 279 191 277 189 274 22000 8 84 200 157 52 8 189 279 187 276 185 274 23000 10 81 193 152 51 0 185 278 184 275...

Page 332: ...157 52 8 201 264 199 262 197 259 21000 46 88 198 155 52 2 200 267 198 265 196 262 22000 48 88 195 153 51 6 199 270 197 268 195 265 23000 50 88 193 152 51 1 198 273 196 271 194 268 24000 52 88 192 151...

Page 333: ...59 53 4 199 268 198 265 196 263 21000 36 88 199 157 52 7 198 271 196 268 195 266 22000 38 88 198 155 52 2 197 274 196 271 193 268 23000 40 88 195 153 51 6 196 277 195 274 192 271 24000 42 88 194 152 5...

Page 334: ...53 7 198 269 197 267 195 264 21000 31 88 201 158 53 1 197 272 196 270 194 267 22000 33 88 199 156 52 5 196 275 195 273 193 270 23000 35 88 197 155 52 0 195 278 194 276 191 273 24000 37 88 195 153 51 5...

Page 335: ...54 0 197 271 196 269 194 266 21000 26 88 202 159 53 5 196 273 195 272 193 269 22000 28 88 200 157 52 8 195 277 194 275 192 272 23000 30 88 198 156 52 4 194 280 193 278 191 275 24000 32 87 3 195 153 51...

Page 336: ...4 196 272 195 270 193 268 21000 21 88 204 160 53 9 195 275 194 273 192 270 22000 23 88 201 158 53 1 194 278 193 276 190 272 23000 25 85 6 195 153 51 5 191 279 189 276 187 272 24000 27 82 7 189 148 49...

Page 337: ...54 6 196 274 194 272 192 269 21000 16 86 5 201 158 53 1 194 275 191 272 189 269 22000 18 84 195 153 51 5 190 275 188 272 186 269 23000 20 81 190 149 50 1 187 275 185 271 182 268 24000 22 78 183 144 4...

Page 338: ...1 9 186 266 185 263 182 260 21000 6 76 4 190 150 50 3 183 266 181 263 179 259 22000 8 74 184 144 48 6 180 265 178 262 175 258 23000 10 71 2 178 140 47 0 176 264 174 262 171 257 24000 12 69 172 135 45...

Page 339: ...234 23000 56 5 50 163 38 7 254 226 40 161 39 1 256 228 30 159 39 7 260 231 20 158 40 3 265 233 10 156 40 9 267 235 24000 56 52 161 37 9 249 227 42 159 38 3 251 230 32 158 38 8 254 232 22 156 39 4 258...

Page 340: ...238 23000 61 5 50 165 40 6 267 229 40 164 41 1 269 232 30 162 41 7 273 235 20 161 42 3 278 237 10 159 42 9 280 239 24000 61 52 164 39 8 260 230 42 162 40 3 265 233 32 161 40 8 267 236 22 159 41 5 271...

Page 341: ...0 10 25 32 25 8 4 48 24000 16 00 58 45 15 3 72 12 00 41 32 10 8 55 09 35 29 23 7 7 43 22000 14 40 54 42 14 3 65 11 00 37 29 9 8 50 08 50 27 21 7 1 39 20000 13 20 49 39 12 9 58 10 00 34 27 9 45 08 00 2...

Page 342: ...Pressure Weight 4850 lbs 2200 kg Weight 5512 lbs 2500 kg Pressure altitude feet 10 min 30 min 10 min 30 min feet l kg us gal l kg us gal l kg us gal l kg us gal SL 29 23 7 7 87 69 23 0 31 24 8 2 93 7...

Page 343: ...0 2100 2230 2360 2490 1180 1245 1345 1445 1540 2070 2200 2330 2460 2590 1215 1310 1410 1510 1610 2135 2265 2395 2525 2690 PRESSURE ALTITUDE ISA 10 C ISA 20 C ISA 30 C ISA 37 C ALTITUDE ft GR D50 GR D5...

Page 344: ...00 2230 2360 2490 1000 1065 1150 1230 1310 2070 2200 2330 2460 2590 1030 1115 1200 1280 1360 2135 2265 2395 2525 2690 PRESSURE ALTITUDE ISA 10 C ISA 20 C ISA 30 C ISA 37 C ALTITUDE ft GR D50 GR D50 GR...

Page 345: ...CTION 6 WEIGHT AND BALANCE TABLE OF CONTENTS Page 6 1 GENERAL 6 1 1 6 2 AIRPLANE WEIGHING PROCEDURES 6 2 1 6 3 BAGGAGE LOADING 6 3 1 6 4 DETERMINING WEIGHT AND BALANCE 6 4 1 GENERAL 6 4 1 UTILIZATION...

Page 346: ...ating the weight and the balance for various flight operations are also provided A list of equipment available for this airplane is included at the end of this section It should be noted that the list...

Page 347: ...30 2010 Rev 0 6 2 AIRPLANE WEIGHING PROCEDURES Refer to Maintenance Manual for the procedures to use NOTE Weighing carried out at the factory takes into account all equipment installed on the airplane...

Page 348: ...OPERLY SECURED IN THE CABIN TRANSPORT OF DANGEROUS PRODUCT IS NORMALLY PROHIBITED HOWEVER IF TRANSPORT OF SUCH PRODUCT IS NECESSARY IT WILL BE PERFORMED IN COMPLIANCE WITH REGULATIONS CONCERNING TRANS...

Page 349: ...rplane basic index If airplane empty weight has varied since last weighing form refer to paragraph DETERMINING EMPTY AIRPLANE CHARACTERISTICS to determine new empty weight and the corresponding balanc...

Page 350: ...ue lines of first heading Front seats b Then continue the line horizontally following direction given by arrow according to indicated value of loading 400 lbs or 150 kg in example the weight indicated...

Page 351: ...SECTION 6 WEIGHT AND BALANCE TBM 700 PILOT S OPERATING HANDBOOK Page 6 4 3 Edition 1 November 30 2010 Rev 0 Figure 6 4 1 LOADING SAMPLE in Kg and Litres...

Page 352: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 4 4 Edition 1 November 30 2010 Rev 0 Figure 6 4 1A LOADING SAMPLE in lbs and us gal...

Page 353: ...PILOT S OPERATING HANDBOOK Page 6 4 5 Edition 1 November 30 2010 Rev 0 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...

Page 354: ...CTION 6 WEIGHT AND BALANCE Page 6 4 6 Edition 1 November 30 2010 Rev 0 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 retrofi...

Page 355: ...LOT S OPERATING HANDBOOK Page 6 4 7 Edition 1 November 30 2010 Rev 0 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 retro...

Page 356: ...ON 6 WEIGHT AND BALANCE Page 6 4 8 Edition 1 November 30 2010 Rev 0 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 retr...

Page 357: ...ccording to installed optional equipment List of equipment paragraph 6 5 contains the standard and optional equipment as well as their characteristics weight arm Use the chart below to compute new emp...

Page 358: ...219 1 in 5 565 m 28 33 and 35 except Rear seats 259 3 in 6 585 m airplanes equipped as FWD cargo compart 128 0 in 3 250 m a retrofit with Aft bagg compart 297 6 in 7 560 m modification Fuel 189 8 in 4...

Page 359: ...O or A allows classifying the equipment R equipment items required for certification S standard equipment items A optional equipment items which are in addition to required or standard items O optiona...

Page 360: ...ND BALANCE Page 6 5 2 Edition 1 November 30 2010 Rev 0 S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 01 SPECIFIC O...

Page 361: ...n switch 214 C40 3 261 CONDEC 0 077 0 035 153 94 3 910 S Cabin pressurization dump soleno d valve 5112 1 AEROSPACE 0 441 0 200 181 10 4 600 S Cabin P warn switch 17 600 1 or 17 600 01 UMA 0 143 0 065...

Page 362: ...116 14 2 950 S Pressure regulating and shut off valve 3213876 9 GARRETT 4 564 2 070 114 17 2 900 S Temperature control sensor 622446 1 GARRETT 0 628 0 285 133 86 3 400 S Temperature control valve 9794...

Page 363: ...TO FLIGHT S G1000 AFCS GFC 700 composed of GARMIN Pitch servo GSA 81 and Servo mount GMS 85 GARMIN 3 86 1 75 247 40 6 284 Roll servo GSA 81 and Servo mount GMS 85 GARMIN 3 86 1 75 231 10 5 870 Yaw ser...

Page 364: ...nte grated Marker Beacon Receiver 2 GMA 1347C GARMIN 2 59 1 71 153 35 3 895 S 0276 00A G1000 COM 1 system Transceiver integrated in the GIA 63W Integra ted Avionics Unit 1 refer to ATA 34 28 GARMIN VH...

Page 365: ...or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m O 23011A Radio headset H10 13 4 DAVID CLARK O 23011B Radio headset 7001 PELTOR O 23011C Radio headset HMEC 25 KA SENNHEISER O 23011D R...

Page 366: ...7 95 3 250 R Electric power center 160GC02Y04 Freon ignition priority ECE 11 023 5 000 127 95 3 250 R Electric power center 160GC02Y05 Freon ignition priority contact splitting S N 92 9999 and S N 1 9...

Page 367: ...olstering version B SOCATA 6 614 3 000 212 60 5 400 A 25004C Leather upholstering version C SOCATA 6 614 3 000 212 60 5 400 A 25004D Leather upholstering version D SOCATA 6 614 3 000 212 60 5 400 A 25...

Page 368: ...lder SOCATA 0 463 0 210 167 72 4 260 O 25017A Window panel blinds and upper door locking safety device TBM700A SOCATA Negli gible A 25018A Smoke goggles PURITAN 0 573 0 260 200 00 5 080 A 25021A Coat...

Page 369: ...20 393 9 250 289 53 7 354 A 25032 Front seats ease covers SOCATA 2 756 1 250 183 78 4 668 Seats Belts Standard equipment S Seats 6 places without oxygen equipment Valid S N 24 26 27 29 to 32 34 36 to...

Page 370: ...except S N 72 to 75 plus airplanes equipped as a retrofit with MOD70 023 25 S Belt and harness T700A2510007 ANJOU AERONAUTIQ UE 1 786 0 810 192 91 or 287 40 4 900 or 7 300 25 60 Emergency equipment A...

Page 371: ...PMENT SUPPLIER WEIGHT per unit lb kg ARM in m 26 FIRE PROTECTION A 26001A Portable fire extinguisher unit FH 15 N or H1 10 AIR AREOFEU MAIP 4 696 2 130 4 266 1 935 176 38 4 480 176 38 4 480 A 26001B P...

Page 372: ...aw control R Rudder trim actuator 145700 01 or 145700 02 LPMI 1 543 0 700 395 27 10 040 A 27001A AFC and electric trim control on R H control wheel SOCATA 0 882 0 400 157 48 4 000 27 30 Pitch control...

Page 373: ...iven fuel pump 1127 01 LHC 1 543 0 700 110 24 2 800 R Engine driven fuel pump1127 01A LHC 1 543 0 700 110 24 2 800 R Fuel sequencer unit E3 003 00 STPI 1 764 0 800 125 98 3 200 R Fuel unit 35001C14 1...

Page 374: ...vember 30 2010 Rev 0 ARM in m WEIGHT per unit lb kg EQUIPMENT SUPPLIER REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O R Low level probe 722 447 INTER TECHNIQUE 0 110...

Page 375: ...900 398 42 10 120 S Deicer vertical stabilizer T700A3014003000 SOCATA 3 968 1 800 374 02 9 500 S Deicer inboard L H wing T700A3010001002 SOCATA 5 732 2 600 173 23 4 400 S Deicer inboard R H wing T700A...

Page 376: ...O Deicer outboard L H wing T700A3010012000 with radar MOD70 0276 00C SOCATA 2 646 1 200 173 23 4 400 30 40 Windshield deicing S Windshield heater controller WH 89 10 AIR SYSTEMS 0 992 0 450 149 61 3...

Page 377: ...L A or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 31 INDICATING RECORDING SYSTEMS 31 20 Independent instruments O 31002A Hourmeter 56457 3 engine running time DATCON 0 551 0 250 156...

Page 378: ...main landing gear 21136 001 00 ERAM 50 044 22 700 200 39 5 090 R R H main landing gear 21136 002 00 ERAM 50 044 22 700 200 39 5 090 32 20 Nose landing gear R Nose gear 21130 001 00 ERAM 52 910 24 000...

Page 379: ...tire 18x5 5 8 190T MICHELIN 12 200 5 534 204 33 5 190 R Main tire 18x5 5 8PR FLE GOOD YEAR 13 450 6 101 204 33 5 190 R Master cylinder 010 07801 PARKER 0 882 0 400 145 67 3 700 R Master cylinder 010...

Page 380: ...wing inspection light icing detection 01 0790093 00 WHELEN 0 198 0 090 151 57 3 850 S Landing lights 4596 GE 0 794 0 360 179 13 4 550 S Taxi light assembly A715 1 4587 WHELEN 1 102 0 500 93 70 2 380...

Page 381: ...22 0 100 157 48 4 000 R Stand by altimeter 3A43 22 35F 28 1 THOMMEN 1 10 0 500 154 45 3 923 R Stand by airspeed indicator 5A58 22 30K 28 1 THOMMEN 0 57 0 260 155 20 3 942 34 21 Heading reference syste...

Page 382: ...t instrumentation system S 0276 00A Integrated Flight Deck System G1000 composed of PFD1 GDU 1040A 6 53 2 96 155 71 3 955 PFD2 GDU 1040A 6 53 2 96 155 71 3 955 MFD GDU 1500A 8 66 3 93 155 20 3 942 Eng...

Page 383: ...oupled 4 94 2 240 232 28 5 900 Antenna NY163 0 84 0 380 311 02 7 900 Processor WX500 2 27 1 030 255 91 6 500 34 42 Weather radar A 0276 00C Weather radar G1000 coupled GWX 68 9 36 4 25 173 46 4 406 34...

Page 384: ...90 4 500 143 00 3 635 Power amplifier low noise amplifier GPA 65 1 89 0 860 221 00 5 624 Antenna upper fuselage GA 58 0 79 0 360 230 00 5 860 Antenna under fuselage GA 58 0 79 0 360 260 00 6 620 34 5...

Page 385: ...selage KA 61 0 40 0 18 193 22 4 908 A 0276 00E Transponder 2 GTX 33 Mode S non diversity 3 87 1 75 149 65 3 801 Antenna KA 61 0 40 0 18 193 22 4 908 34 54 Automatic Direction Finder ADF A 0276 00H ADF...

Page 386: ...IPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 35 OXYGEN S Generator 117024 02 PURITAN 0 948 0 430 180 31 4 580 209 84 5 330 257 09 6 530 S Mask 174554 174555 PURITAN 0 441 0 200 180 31 4 580 209 84 5...

Page 387: ...IER WEIGHT per unit lb kg ARM in m 37 VACUUM S Air ejector valve 19E17 5A LUCAS 0 661 0 300 116 14 2 950 S Gyro suction gage 3 310 5 UMA 0 143 0 065 157 48 4 000 S Gyro vacuum air filter 1J7 2 AIRBORN...

Page 388: ...ED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 61 PROPELLER 61 10 Propeller assembly S Propeller HC E4N 3 E 9083 S K HARTZELL 153 220 69 500 43 11 1...

Page 389: ...IONAL A or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 71 POWER PLANT R Turbogenerator PT6 A 64 P W CANADA 471 784 214 000 79 72 2 025 S Silentblocks 95007 16 BARRY 2 921 1 325 79 72...

Page 390: ...Compressor turbine tacho generator Ng MIL G 26611C GEU 7 A QPL AIRCRAFT APPLIANCES AND EQUI LTD 0 981 0 445 108 27 2 750 R Power turbine tacho generator P N 32005 007 MIL G 26611 GEU 7 A or P N 32005...

Page 391: ...QUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 79 LUBRICATION 79 20 Distribution R Oil cooler L8538233 LORI 10 472 4 750 90 55 2 300 79 30 Indica...

Page 392: ...ES 7 2 7 7 3 ACCOMMODATIONS 7 3 1 INSTRUMENT PANEL 7 3 1 DOORS WINDOWS AND EMERGENCY EXIT 7 3 18 BAGGAGE COMPARTMENTS 7 3 27 SEATS BELTS AND HARNESSES 7 3 28 7 4 FLIGHT CONTROLS 7 4 1 ROLL 7 4 1 ROLL...

Page 393: ...R 7 6 12 7 7 FUEL SYSTEM 7 7 1 FUEL TANKS 7 7 1 FUEL UNIT 7 7 1 TANK MANUAL SELECTOR 7 7 1 TANK AUTOMATIC SELECTOR 7 7 4 ELECTRIC BOOST PUMP 7 7 5 MAIN MECHANICAL BOOST PUMP 7 7 8 ENGINE FUEL SYSTEM 7...

Page 394: ...NAMIC PRESSURE SYSTEM 7 11 4 7 12 VACUUM SYSTEM AND INSTRUMENTS 7 12 1 STAND BY ATTITUDE INDICATOR 7 12 1 SUCTION GAGE 7 12 4 7 13 ICE PROTECTION EQUIPMENT 7 13 1 WING AND EMPENNAGE DEICING 7 13 1 PRO...

Page 395: ...ed in the airplane Complete description and operation of the GARMIN G1000 integrated flight deck are detailed in the GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the Socata TBM 700...

Page 396: ...t and to rear seats through a central aisle TBM700B The pressurized cabin is equipped on the left side of fuselage with a wide one piece door and folding stairs comprising a hand rail allowing pilot a...

Page 397: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 2 2 Edition 1 November 30 2010 Rev 0 Figure 7 2 1 CABIN ARRANGEMENT...

Page 398: ...otation The spoilers located in front of flaps on top skin side are mechanically linked to the ailerons Trim tab knob attached on the trailing edge of L H aileron is electrically activated by a trim k...

Page 399: ...t 1 510 m Rigging angle to fuselage horizontal datum 2 Sweep angle at 25 chord 0 Dihedral at datum plane 6 5 Aspect ratio platform reference 8 216 Taper ratio 0 608 Airfoil section at wing root RA 16...

Page 400: ...BM 700 PILOT S OPERATING HANDBOOK Page 7 2 5 Edition 1 November 30 2010 Rev 0 Figure 7 2 2 1 2 WING FLAPS 1 Geared motor 2 Internal actuator 3 Intermediate bearings 4 Wing flap 5 External actuator 6 R...

Page 401: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 2 6 Edition 1 November 30 2010 Rev 0 Figure 7 2 2 2 2 WING FLAPS...

Page 402: ...d 3 89 ft 1 186 m Tip chord 2 60 ft 0 795 m Mean aerodynamic chord at y 3 76 ft 1 147 m 3 26 ft 0 995 m Airfoil section NACA 642 A415 modified Dihedral 6 5 Rigging angle leading edge up 0 5 Aspect rat...

Page 403: ...ns two Primary Flight Displays PFD and one Multi Function Display MFD refer to the GARMIN G1000 Cockpit Reference Guide for detailed description Apart from the G1000 system equipment listed below comp...

Page 404: ...General alarms warning lights and CAS messages Warning red and Caution yellow messages appear on the GDU 1500 MFD CAS display to alert crew about monitored systems discrepancies As a message appears a...

Page 405: ...ound gear up and extended flaps high pitched sound stall low pitched sound gear up idle and stall alternate high pitched and g p g p low pitched sounds gear up extended flaps and stall alternate high...

Page 406: ...t breaker Aural warning operation The GMA 1 and 2 audio control panels receive signals from the aural warning box According to the airplane configuration these signals are low pitched and or high pitc...

Page 407: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 5 Edition 1 November 30 2010 Rev 0 Figure 7 3 1 INSTRUMENT PANEL ASSEMBLY Typical arrangement...

Page 408: ...ud speaker of GMA 2 4 R H instrument panel emergency lighting 5 Cockpit floodlight switches rheostats 6 R H air outlet up to S N 87 7 R H cockpit floodlight 8 MASTERs controls AVIONICS and AP TRIMS 9...

Page 409: ...S OPERATING HANDBOOK Page 7 3 7 Edition 1 November 30 2010 Rev 0 Figure 7 3 2 2 2 UPPER PANEL AND COCKPIT OVERHEAD PANEL Valid S N 24 26 27 29 to 32 34 36 to 9999 plus airplanes equipped as a retrofit...

Page 410: ...control panel Figure 7 5 1 7 Parking brake control Figure 7 5 6 8 Left station control wheel tube 9 Deicing control and check panel Figure 7 13 1 10 L H station rudder pedals adjusting handle 11 Left...

Page 411: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 9 Edition 1 November 30 2010 Rev 0 Figure 7 3 3 2 2 LEFT INSTRUMENT PANEL Typical arrangement...

Page 412: ...7 3 10 Edition 1 November 30 2010 Rev 0 Figure 7 3 4 1 2 CENTRAL INSTRUMENT PANEL 1 Stand by altimeter 2 Stand by compass 3 GMC 710 AFCS mode controller 4 Registration 5 Cabin pressurization control...

Page 413: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 11 Edition 1 November 30 2010 Rev 0 Figure 7 3 4 2 2 CENTRAL INSTRUMENT PANEL Typical arrangement...

Page 414: ...usic 5 Adjustable air outlet 6 Right station reception micro jacks 7 Hour meter 8 R H station rudder pedals adjusting handle 9 Circuit breakers panel postlight 10 Servicing plug 11 Cabin emergency air...

Page 415: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 13 Edition 1 November 30 2010 Rev 0 Figure 7 3 5 2 2 RIGHT INSTRUMENT PANEL Typical arrangement...

Page 416: ...CONSOLE 1 Propeller governor lever 2 Power lever 3 PROP O SPEED TEST push button 4 Flaps control 5 Condition lever 6 Levers friction adjustment 7 Emergency fuel control 8 Manual fuel tank selector Fig...

Page 417: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 15 Edition 1 November 30 2010 Rev 0 Figure 7 3 6 2 2 PEDESTAL CONSOLE Typical arrangement...

Page 418: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 16 Edition 1 November 30 2010 Rev 0 Figure 7 3 7 CIRCUIT BREAKERS PANEL...

Page 419: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 17 Edition 1 November 30 2010 Rev 0 Figure 7 3 8 GENERAL ALARMS WARNING LIGHTS...

Page 420: ...located on door upper edge and move it forward to free the latch pin Lower the door carefully until it is sustained by the cable To close the door from inside the airplane raise lower door by pulling...

Page 421: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 19 Edition 1 November 30 2010 Rev 0 Figure 7 3 9 CABIN ACCESS DOOR TBM 700A Door equipped with one cable...

Page 422: ...r upper edge and move it forward to free the latch pins Lower the door carefully until it is sustained by the cables To close the door from inside the airplane raise lower door by pulling on the handl...

Page 423: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 21 Edition 1 November 30 2010 Rev 0 Figure 7 3 1A CABIN ACCESS DOOR TBM 700A Door equipped with two cables...

Page 424: ...or opening tilt stairs downwards Stairs down movement is damped by means of two gas struts and leads the hand rail to extend CAUTION RETRACT STAIRS BEFORE CLOSING ACCESS DOOR AND MAKE SURE DOOR DEFLEC...

Page 425: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 23 Edition 1 November 30 2010 Rev 0 Figure 7 3 1B CABIN ACCESS DOOR TBM 700B...

Page 426: ...R To retract stairs from outside the airplane raise stairs by pushing them upwards from the lower part and fold them inside cabin While stairs are retracted the hand rail folds up To close the door fr...

Page 427: ...rofile Windows Windows do not open The windshield consists of two parts the pilot s one being electrically deiced The R H one may be optionally deiced Emergency exit Figure 7 3 2 The emergency exit is...

Page 428: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 26 Edition 1 November 30 2010 Rev 0 Figure 7 3 2 EMERGENCY EXIT...

Page 429: ...ng must be carried out with caution to avoid any damage to airplane The cabin may be separated from the rear baggage compartment by a partition net if installed intended to protect the passengers from...

Page 430: ...ont seats The back rest tilting of the seats can be modified The L H rear seat back tilts forward to ease baggage loading in aft baggage compartment Belts and harnesses Figure 7 3 4 WARNING INCORRECT...

Page 431: ...seats and two rear seats arranged as a bench The back rest tilting of these seats can be modified The rear seat back rests tilt forward to ease baggage loading in aft baggage compartment Belts and har...

Page 432: ...ed on the same rails as the front seats and two rear seats arranged as a bench The back rest tilting of these seats can be modified The rear seat back rests tilt forward and the rear L H seat may tilt...

Page 433: ...irection 4 L H intermediate passenger s seat back to flight direction 5 R H rear passenger s seat 6 L H rear passenger s seat 7 Front seat s longitudinal shift control 8 Oxygen masks 2 drawer R H fron...

Page 434: ...TING HANDBOOK Page 7 3 33 Edition 1 November 30 2010 Rev 0 Figure 7 3 3 2 2 SEATS TBM 700A S N 1 to 23 25 28 33 and 35 except airplanes equipped as a retrofit with modification No MOD 70 019 25 Oxygen...

Page 435: ...intermediate passenger s seat back to flight direction 5 R H rear passenger s seat 6 L H rear passenger s seat 7 Front seat s longitudinal shift control 8 Oxygen masks 2 drawer intermediate seats 9 F...

Page 436: ...NG HANDBOOK Page 7 3 35 Edition 1 November 30 2010 Rev 0 Figure 7 3 3A 2 2 SEATS TBM700A S N 24 26 27 29 to 32 34 36 to 9999 plus airplanes equipped as a retrofit with modification No MOD 70 019 25 Va...

Page 437: ...shift control 8 Oxygen masks 2 drawer intermediate seats 9 Front seat s height control 10 Front seat s back rest tilt control 11 Drawer for pilot s piddle pak if installed front side new bags rear sid...

Page 438: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 37 Edition 1 November 30 2010 Rev 0 Figure 7 3 3B 2 2 SEATS TBM 700B...

Page 439: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 38 Edition 1 November 30 2010 Rev 0 Figure 7 3 4 FRONT OR REAR SEAT BELT with movable straps AND HARNESSES...

Page 440: ...ile when the aileron is deflected upwards and remains in wing profile when the aileron is deflected downwards Control wheel movement is transmitted through rods to fuselage roll lever located under th...

Page 441: ...ANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 2 Edition 1 November 30 2010 Rev 0 Figure 7 4 1 1 2 ROLL 1 Pedestal assembly 2 Control wheels 3 Fuselage roll lever 4 Spoiler 5 Aileron 6 Aileron control in...

Page 442: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 3 Edition 1 November 30 2010 Rev 0 Figure 7 4 1 2 2 ROLL...

Page 443: ...ANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 4 Edition 1 November 30 2010 Rev 0 1 Roll trim tab 2 Aileron 3 Adjustable rods 4 Actuator 5 Trim tab control wiring 6 Trim switch on pedestal console Figure...

Page 444: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 5 Edition 1 November 30 2010 Rev 0 Figure 7 4 2 2 2 LATERAL TRIM...

Page 445: ...l surface is provided with an automatic anti tab automaticity about 0 3 which is also used as trim tab PITCH TRIM Figure 7 4 4 The pitch trim is accomplished through the two anti tabs located on left...

Page 446: ...Page 7 4 7 Edition 1 November 30 2010 Rev 0 Figure 7 4 3 1 2 ELEVATOR 1 Control wheel assembly 2 Elevators 3 Lever assembly fuselage rear part 4 Elevator bellcrank 5 Rod with presseal connection 6 Le...

Page 447: ...K 700 SECTION 7 DESCRIPTION Page 7 4 8 Edition 1 November 30 2010 Rev 0 Figure 7 4 4 1 2 PITCH TRIM 1 Cables 2 Pulleys 3 Pitch trim tabs 4 Actuating rods 5 Actuator 6 Pitch trim manual control wheel 7...

Page 448: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 9 Edition 1 November 30 2010 Rev 0 Figure 7 4 4 2 2 PITCH TRIM...

Page 449: ...khead beneath the instrument panel and a locking device on the rudder pedals This ball locking device allows selecting six different positions When landing gear is down rudder pedals are linked to nos...

Page 450: ...NG HANDBOOK Page 7 4 11 Edition 1 November 30 2010 Rev 0 Figure 7 4 5 1 2 RUDDER 1 Roll rudder combination bellcrank installation 2 Rudder pedals assembly 3 Control cables 4 Pulleys 5 Rudder lever ass...

Page 451: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 12 Edition 1 November 30 2010 Rev 0 Figure 7 4 5 2 2 RUDDER...

Page 452: ...CRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 13 Edition 1 November 30 2010 Rev 0 Figure 7 4 6 1 2 RUDDER TRIM 1 Trim switch on control wheel 2 Actuator 3 Rudder trim tab 4 Rods 5 Rudder trim c...

Page 453: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 14 Edition 1 November 30 2010 Rev 0 Figure 7 4 6 2 2 RUDDER TRIM...

Page 454: ...nder which also provides up and down locking Nose gear swivels on two ball joints installed on a tubular steel mount frame Its operation is accomplished by a hydraulic actuating cylinder which also pr...

Page 455: ...ION INDICATOR Figure 7 5 1 Landing gear position indication is accomplished by 4 warning lights 3 green indicator lights one per landing gear 1 red warning light NOTE The red warning light flashes as...

Page 456: ...S OPERATING HANDBOOK Page 7 5 3 Edition 1 November 30 2010 Rev 0 Figure 7 5 1 CONTROL PANEL AND LANDING GEAR INDICATING 1 Red warning light LDG GR 2 Green indicator light LDG GR 3 Landing gear control...

Page 457: ...ion and landing gear is not down locked flaps are beyond TO position Takeoff and landing gear is not down locked NOTE If one of above conditions exists and airplane is in stall configuration the audio...

Page 458: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 5 5 Edition 1 November 30 2010 Rev 0 Figure 7 5 2 EMERGENCY LANDING GEAR EXTENSION CONTROL...

Page 459: ...nose wheel swivels about 20 Steering may be increased up to 28 by applying differential braking to each side Airplane may be towed by attaching a steering or towing bar on nose gear Refer to Chapter...

Page 460: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 5 7 Edition 1 November 30 2010 Rev 0 Figure 7 5 3 MINIMUM TURN DIAMETER Full rudder pedals travel without using differential braking...

Page 461: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 5 8 Edition 1 November 30 2010 Rev 0 Figure 7 5 4 MINIMUM TURN DIAMETER Full rudder pedals travel by using differential braking...

Page 462: ...vering during taxiing PARKING BRAKE Figures 7 5 5 and 7 5 6 Parking brake control consists of a control knob located on pilot s side lower instrument panel a valve which regulates brake pressure To ap...

Page 463: ...ge 7 5 10 Edition 1 November 30 2010 Rev 0 Figure 7 5 5 1 2 BRAKE SYSTEM 1 Reservoir 2 Vent 3 R H station master cylinders 4 Parking brake control knob 5 Parking brake valve 6 Drain 7 Pilot s station...

Page 464: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 5 11 Edition 1 November 30 2010 Rev 0 Figure 7 5 5 2 2 BRAKE SYSTEM...

Page 465: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 5 12 Edition 1 November 30 2010 Rev 0 Figure 7 5 6 PARKING BRAKE...

Page 466: ...continues as a result of air fuel mixture flow Gases resulting from combustion expand through a series of turbines The first one gas generator turbine drives compressor assembly and accessories the t...

Page 467: ...2 POWER PLANT 1 Propeller governor 2 Exhaust stub 3 Axial compressors 4 Accessory gearbox 5 FCU Fuel control unit 6 Oil to fuel heater 7 Compressor stubshaft 8 Air intake 9 Centrifugal impeller 10 Co...

Page 468: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 6 3 Edition 1 November 30 2010 Rev 0 Figure 7 6 1 2 2 POWER PLANT...

Page 469: ...gure 7 6 2 Engine operation requires use of four levers located on pedestal console in cabin power lever Item 2 and its detent for reverse Item 6 propeller governor lever Item 1 condition lever Item 3...

Page 470: ...ng spring locks the Beta ring and the propeller reversing interconnect linkage on the engine All rearward effort on the power control lever past the idle stop may damage or break the flexible control...

Page 471: ...erformed by pulling lever knob up NOTE The power available if the power lever fails will be limited by the position of the lever Lever friction Figure 7 6 2 A thumbwheel Item 4 located on right side o...

Page 472: ...and oil filling up refer to Section 8 ENGINE STARTING Figure 7 6 3 Ignition function Ignition system consists of an ignition unit and two spark igniter plugs in power plant a three position IGNITION...

Page 473: ...Air is driven throughout a duct in engine casing before entering engine through a protective screen An inertial separator system inside the air duct protects the engine from ingesting dense particles...

Page 474: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 6 9 Edition 1 November 30 2010 Rev 0 Figure 7 6 3 ENGINE STARTING...

Page 475: ...gulator FCU through a second filter In case of contamination of this second filter a by pass valve allows fuel to go directly from high pressure pump to the regulator Compressor turbine tacho generato...

Page 476: ...ase of main propeller governor failure Propeller overspeed limiter is equipped with a test soleno d which allows performing ground tests by arming limiter under normal overspeed power PROP O SPEED TES...

Page 477: ...d low pitch high RPM Propeller governor allows feathering either by voluntary pilot action via the propeller governor lever or automatically in case of engine failure or shutdown Propeller reverse pit...

Page 478: ...ated on the lower surface a suction strainer and three level gages FUEL UNIT The fuel unit combines shut off valve tank selector and filter functions It is connected to the manual selector through a m...

Page 479: ...fuel heater 7 Low pressure switch 8 Pressure transmitter 9 Fuel jet 10 Main mechanical boost pump 11 Electric boost pump 12 Fuel filter 13 Filter clogging by pass valve 14 Filter clogging indicator 1...

Page 480: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 7 3 Edition 1 November 30 2010 Rev 0 Figure 7 7 1A 2 2 FUEL SYSTEM...

Page 481: ...O SEL CAS message disappears the sequencer chooses a tank R or L and through the actuator positions the fuel unit selector on the selected tank The sequencer controls the time during which the selecte...

Page 482: ...ystem operation is indicated by rotation of the manual selector Setting FUEL SEL switch to MAN position or setting manual selector to OFF position leads to system de activating and appearance of AUTO...

Page 483: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 7 6 Edition 1 November 30 2010 Rev 0 Figure 7 7 2A MANUAL SELECTOR OF FUEL TANKS...

Page 484: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 7 7 Edition 1 November 30 2010 Rev 0 Figure 7 7 3A FUEL CONTROL PANEL...

Page 485: ...g installation is a capacitive type Fuel data are displayed in us gallons Three fuel level gages are installed in each tank The wing root side fuel level gage is equipped with a low level detector whi...

Page 486: ...g them with a screwdriver Fuel system draining shall be performed prior to the first flight of the day and after each tank refueling using a sampler to pick off fuel at the two drain valves of each ta...

Page 487: ...ERATING HANDBOOK Page 7 7 11 Edition 1 November 30 2010 Rev 0 Figure 7 7 4A FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Valid from S N 1 to 92 1 Clogging indicator 2 Lens 3 Central access door...

Page 488: ...ormed prior to the first flight of the day and after each tank refueling using a sampler to pick off fuel at the two drain valves of each tank and at the filter vent valve A red filter bypass flag on...

Page 489: ...OK Page 7 7 13 Edition 1 November 30 2010 Rev 0 Figure 7 7 4A FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR Valid from S N 93 to 9999 1 Lighting switch 2 Mirror door 3 Clogging indicator 4 Centra...

Page 490: ...t is accessible from outside through a door Connection relays main bus bar generator regulation and protection systems and control logic systems are grouped in electrical power center attached to fron...

Page 491: ...is available and is a power supply source when engine driven generators are stopped The battery is always connected to BAT BUS bus bar except when CRASH lever is pulled down Battery connection to main...

Page 492: ...to circuit breaker panel NORM position is protected and locked by a cover Common power supply to both essential bus bars is protected by a fuse each bar being individually protected by a circuit brea...

Page 493: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 8 4 Edition 1 November 30 2010 Rev 0 Figure 7 8 1 ELECTRICAL DIAGRAM...

Page 494: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 5 Edition 1 November 30 2010 Rev 0 Figure 7 8 2 1 3 ELECTRICAL DISTRIBUTION OF BUS BARS...

Page 495: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 8 6 Edition 1 November 30 2010 Rev 0 Figure 7 8 2 2 3 ELECTRICAL DISTRIBUTION OF BUS BARS...

Page 496: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 7 Edition 1 November 30 2010 Rev 0 Figure 7 8 2 3 3 ELECTRICAL DISTRIBUTION OF BUS BARS...

Page 497: ...protection AUDIO 1 Audio control panel 1 protection AHRS 1 Attitude and Heading Reference System 1 protection XPDR 1 Transponder 1 protection ELT Emergency Locator Transmitter protection AURAL Aural...

Page 498: ...S 1 Continued INERT DE ICE Inertial separator protection R WS DE ICE R H windshield deicing protection if installed PITOT 1 Pitot 1 heating protection AUDIO 2 Audio control panel 2 protection STROBE S...

Page 499: ...K 700 SECTION 7 DESCRIPTION Page 7 8 10 Edition 1 November 30 2010 Rev 0 Figure 7 8 3 3 3 CIRCUIT BREAKER PANEL typical arrangement NOTE If an additional equipment is installed its circuit breaker is...

Page 500: ...bus bar is supplied GPU DOOR Ground power receptacle access door is not closed PROTECTION SAFETY Figure 7 8 4 The electrical power center provides systems protection in case of overvoltage coming fro...

Page 501: ...OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 8 12 Edition 1 November 30 2010 Rev 0 Figure 7 8 4 ELECTRICAL CONTROL 1 MAIN reset knob 2 ST BY reset knob 3 Crash lever 4 SOURCE selector 5 GENERAT...

Page 502: ...in leading edges Lights illumination is controlled by L LDG and R LDG switches located on upper panel A warning light is incorporated in each switch to indicate proper operation of used landing light...

Page 503: ...panel Figure 7 13 1 Front baggage compartment light if installed The dome light of the front baggage compartment has two positions the first allows automatic illumination via the switch located in th...

Page 504: ...age 7 8 15 Edition 1 November 30 2010 Rev 0 Figure 7 8 5 1 2 EXTERNAL LIGHTING CONTROLS 1 L H landing light switch 2 Test knob test light integrated to switches 3 Taxi light switch 4 R H landing light...

Page 505: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 8 16 Edition 1 November 30 2010 Rev 0 Figure 7 8 5 2 2 EXTERNAL LIGHTING CONTROLS...

Page 506: ...strip The floodlight above the table is controlled by two switches which are two way switches type The pilot can switch off the cabin floodlights and the dome light of rear baggage compartment with th...

Page 507: ...10 Rev 0 Map reading light illumination The illumination of the map reading light located on L H station control wheel is controlled by the switch rheostat located on this light Valid S N 24 26 27 29...

Page 508: ...26 27 29 to 32 34 36 to 9999 plus airplanes equipped as a retrofit with modification Nr MOD 70 019 25 1 Instrument panel lighting switch rheostat 2 Instrument lighting switch rheostat 3 DIMMER switch...

Page 509: ...700 SECTION 7 DESCRIPTION Page 7 8 20 Edition 1 November 30 2010 Rev 0 Figure 7 8 6 2 2 INTERNAL LIGHTING CONTROLS Valid S N 24 26 27 29 to 32 34 36 to 9999 plus airplanes equipped as a retrofit with...

Page 510: ...eated by a fan which if BLEED VALVE switch is set to ON starts automatically Temperature regulation Temperature regulation is accomplished by adding hot air to the air coming from cooling turbine A pr...

Page 511: ...er 4 Water separator 5 Temperature control valve 6 Pressure regulator of temperature control valve 7 Check valve 8 Temperature control sensor 9 Cabin emergency air inlet 10 Defogging outlets 11 Adjust...

Page 512: ...TBM 700 PILOT S OPERATING HANDBOOK Page 7 9 3 Edition 1 November 30 2010 Rev 0 Figure 7 9 1 2 2 AIR CONDITIONING Valid S N 24 26 27 29 to 32 34 36 to 85 87 90 S N 1 to 23 25 28 33 and 35 with modific...

Page 513: ...reactivated as long as BLEED TEMP CAS message is displayed After BLEED TEMP CAS message has disappeared set BLEED VALVE switch to OFF then to ON to reactivate the system CABIN FAN switch controls the...

Page 514: ...tside by the NACA scoop located on L H FWD engine cowling When the airplane is on ground air flow is created by a fan which if BLEED VALVE switch is set to ON starts automatically Temperature regulati...

Page 515: ...trol valve 6 Pressure regulator of temperature control valve 7 Check valve 8 Temperature control sensor 9 Cabin emergency air inlet 10 Defogging outlets 11 Adjustable air outlets 12 Air conditioning f...

Page 516: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 9 4C Edition 1 November 30 2010 Rev 0 Figure 7 9 1A 2 2 AIR CONDITIONING Valid S N 86 88 89 91 to 9999...

Page 517: ...System cannot be reactivated as long as BLEED TEMP CAS message is displayed After BLEED TEMP CAS message has disappeared set BLEED VALVE switch to OFF then to ON to reactivate the system CABIN FAN sw...

Page 518: ...ead and each one is connected to a static port located on rear cone for the outflow valve and under rear baggage compartment for safety valve Cabin is automatically depressurized as soon as the airpla...

Page 519: ...0 2010 Rev 0 Figure 7 9 2 1 2 PRESSURIZATION 1 Check valve 2 Cabin atmosphere P microswitch 3 G1000 system CAS messages 4 Outflow valve 5 Safety valve 6 Depressurization valve 7 Landing gear switch ai...

Page 520: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 9 7 Edition 1 November 30 2010 Rev 0 Figure 7 9 2 2 2 PRESSURIZATION...

Page 521: ...ON Page 7 9 8 Edition 1 November 30 2010 Rev 0 Figure 7 9 3 1 2 ECS CONTROL AND CHECK PANEL 1 BLEED VALVE switch ON OFF 2 BLEED VALVE switch HI LO 3 CABIN FAN switch 4 DUMP switch 5 CABIN TEMP selecto...

Page 522: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 9 9 Edition 1 November 30 2010 Rev 0 Figure 7 9 3 2 2 ECS CONTROL AND CHECK PANEL...

Page 523: ...uipped with a microphone A transparent flexible tube and a lanyard connect both masks to a generator When one of the lanyards is pulled priming mechanism leads to a chemical reaction inside the genera...

Page 524: ...G HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 10 2 Edition 1 November 30 2010 Rev 0 Figure 7 10 1 1 2 EMERGENCY OXYGEN SYSTEM 1 Generator 2 Supply tubes 3 Masks 4 Drawer 5 Microswitch 6 Dimpled support...

Page 525: ...message remains displayed as long as used generator is not replaced Condition of the coloured band located around the generators provides activated generator identification Originally amber turning t...

Page 526: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 10 4 Edition 1 November 30 2010 Rev 0 Figure 7 10 1 2 2 EMERGENCY OXYGEN SYSTEM...

Page 527: ...rplane normal static system When selector is on alternate position pulled rearwards static pressure is picked from a port located in airplane rear fuselage two separate dynamic pressure systems supply...

Page 528: ...d indicator 4 GDC 74B ADC 5 GDC 74B ADC 6 FWD pressure bulkhead 7 Static system drain 8 Static system drain 9 Static system drain 10 Emergency static system drain 11 Emergency static valve Normal Alte...

Page 529: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 11 3 Edition 1 November 30 2010 Rev 0 Figure 7 11 1 2 2 AIR DATA SYSTEM...

Page 530: ...STEM Two heated pitot probes are installed under the L H wing The first one supplies the airspeed indicator and the Air Data Computer ADC The second one supplies the other ADC Both lines incorporate a...

Page 531: ...venturi effect A relief valve fixed in cabin to frame C2 maintains the vacuum for pressurization and instrument systems In case of pressure drop a microswitch installed in the system indicates the fa...

Page 532: ...HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 12 2 Edition 1 November 30 2010 Rev 0 Figure 7 12 1 1 2 VACUUM SYSTEM 1 Pressure regulator 2 Ejector 3 Valve 4 Regulating and relief valve 5 Pressure switch...

Page 533: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 12 3 Edition 1 November 30 2010 Rev 0 Figure 7 12 1 2 2 VACUUM SYSTEM...

Page 534: ...ercury and indicates the suction available for operation of the attitude indicator The desired vacuum range is 4 4 to 5 2 in Hg A vacuum reading out of this range may indicate a system malfunction or...

Page 535: ...on the lower L H side of the instrument panel WING AND EMPENNAGE DEICING A pneumatic deice system assures protection of wing leading edges horizontal stabilizer elevator horns and vertical stabilizer...

Page 536: ...D When the switch is positioned to ON the controller supplies the heating resistors the windshield temperature is monitored by probe 1 When the temperature reaches 45 C 113 F the controller cuts the e...

Page 537: ...all warning sensor are electrically heated This deice equipment must be used even during flight into non icing conditions The system condition messages PITOT NO HT 1 or 2 PITOT HT ON 1 or 2 STALL HEAT...

Page 538: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 13 4 Edition 1 November 30 2010 Rev 0 Figure 7 13 1 DEICING CONTROL AND CHECK PANEL...

Page 539: ...quipment assembly is controlled by the AVIONICS MASTER switch located on the upper panel When the AVIONICS MASTER switch is set to START it allows to electrically supply from the BATT BUS bar a limite...

Page 540: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 14 2 Edition 1 November 30 2010 Rev 0 Figure 7 14 1 AVIONICS MASTER 1 AVIONICS MASTER switch...

Page 541: ...y severe or prolonged icing STATIC DISCHARGERS As an aid in flight static dischargers are installed to improve radio communications during flight by reducing interference from dust or various forms of...

Page 542: ...tter assembly is constituted of a transmitter supplied by a battery of a retractable antenna integrated in the locator transmitter and allowing use of the latter outside the airplane and of a remote c...

Page 543: ...PILOT S OPERATING HANDBOOK Page 7 15 3 Edition 1 November 30 2010 Rev 0 Reset after an inadvertent activation On ON ARMED RESET TEST remote control switch press on RESET TEST or set locator transmitt...

Page 544: ...8 1 GENERAL 8 1 1 8 2 IDENTIFICATION PLATE 8 2 1 8 3 PUBLICATIONS 8 3 1 8 4 INSPECTION PERIODS 8 4 1 8 5 ALTERATIONS OR REPAIRS 8 5 1 8 6 GROUND HANDLING 8 6 1 TOWING 8 6 1 PARKING 8 6 1 TIE DOWN 8 6...

Page 545: ...tion 1 November 30 2010 Rev 0 TABLE OF CONTENTS Continued Page 8 8 AIRPLANE CLEANING AND CARE 8 8 1 WINDSHIELD AND WINDOWS 8 8 1 PAINTED SURFACES 8 8 2 PROPELLER CARE 8 8 2 ENGINE CARE 8 8 2 INTERIOR...

Page 546: ...e and servicing of TBM 700 airplane Also included in this section are the inspection and maintenance requirements which must be followed if your airplane is to retain its performance and dependability...

Page 547: ...0 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 nu...

Page 548: ...e for SOCATA TBM 700 P N 190 01247 00 or any later version as applicable and supplemental data covering optional equipment installed in the airplane refer to Section 9 Supplements and to pilot s guide...

Page 549: ...PECTION 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...

Page 550: ...1 November 30 2010 Rev 0 8 5 ALTERATIONS OR REPAIRS It is essential that the Airworthiness authorities be contacted prior to any alterations or repairs on the airplane to make sure that airworthiness...

Page 551: ...se gear fork is equipped with an integrated towing fitting CAUTION DO NOT TOW THE AIRPLANE WHEN CONTROLS ARE SECURED WHEN TOWING WITH A VEHICLE DO NOT EXCEED THE NOSE GEAR TURNING ANGLE AS THIS MAY RE...

Page 552: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 6 2 Edition 1 November 30 2010 Rev 0 Figure 8 6 1 TURNING ANGLE LIMITS...

Page 553: ...s wheel chocks and control lock are recommended In severe weather and high wind conditions tie the airplane down as outlined in the following paragraph TIE DOWN Proper tie down procedure is the best p...

Page 554: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 6 4 Edition 1 November 30 2010 Rev 0 Figure 8 6 2 CONTROL LOCK DEVICE...

Page 555: ...ndensation in the tanks Keep the battery fully charged to prevent the electrolyte from freezing in cold weather Storage from 8 to 28 days Engine according to Maintenance Manual P W C Airplane fueling...

Page 556: ...spection or testing at special intervals first 100 flight hours and yearly inspection ENGINE OIL Type of oil CAUTION DO NOT MIX DIFFERENT BRANDS OR TYPES Nominal viscosity US specification US French s...

Page 557: ...g cycle and reverify level before adding oil If more than 30 minutes have passed and the dipstick indicates that oil is needed start the engine and run at ground idle low idle for 5 minutes Reverify o...

Page 558: ...CTRICAL EQUIPMENT ON THE AIRPLANE DURING FUELING DO NOT ALLOW OPEN FLAME OR SMOKING IN THE VICINITY OF THE AIRPLANE WHILE FUELING NOTE Use of AVGAS must be recorded in engine module logbook US Specifi...

Page 559: ...unusual conditions small amounts of water emulsified can precipitate from the fuel stream and freeze in sufficient quantities to induce partial icing of the engine fuel system While these conditions...

Page 560: ...ult in a water buildup in the fuel which leeches out the additive An indication of this is when an excessive amount of water accumulates in the fuel tank sumps The concentration can be checked using a...

Page 561: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 7 6 Edition 1 November 30 2010 Rev 0 Figure 8 7 3 ADDITIVE MIXING RATIO EGME or DIEGME...

Page 562: ...Inflating pressure 120 psi 8 25 bar Nose gear shock absorber Fill with hydraulic fluid AIR 3520 B MIL H5606E inflate with nitrogen to 87 psi 6 bar Main gear shock absorbers Fill with hydraulic fluid...

Page 563: ...entification Amber turning to black indicates an used generator which will require removal according maintenance manual instructions in order to replace it with a new one WARNING GENERATOR CHEMICAL RE...

Page 564: ...NG SPRAYS IN CASE OF DOUBT CONCERNING A PRODUCT DO NOT USE IT DURING CLEANING OPERATION AVOID WEARING OBJECTS SUCH AS RING WATCH BRACELET AND EXERCISE CARE TO PREVENT BUTTONS BUCKLES AND ANY HARD OBJE...

Page 565: ...bug stains will assure long blade life Small nicks on the propeller particularly near the tips and on the leading edges should be dressed out as soon as possible since these nicks produce stress conce...

Page 566: ...the seals of the door and engine cowlings as well as the leading edge deicers 2 Apply engine oil on the engine cowling latches 3 Inflate tires and shock absorbers according to following table 1 NOTE C...

Page 567: ...ranged numerically See List of Supplements and Validities to make it easier to locate a particular supplement Some installed items of optional equipment whose function and operational procedures do no...

Page 568: ...er 30 2010 Rev 0 LIST OF EFFECTIVE PAGES AND VALIDITIES ORIGINAL ISSUE OF NOVEMBER 30 2010 S N 1 to S N 433 except S N 269 equipped with MOD70 276 00 Page Edit Rev Page Edit Rev Page Edit Rev No No No...

Page 569: ...TBM 700 PILOT S OPERATING HANDBOOK 850 SECTION 9 SUPPLEMENT A Page 9 AC Edition 2 November 30 2010 Rev 0 LIST OF NORMAL AMENDMENTS Edition 2 of November 30 2010 Revision of Pages Description...

Page 570: ...0A and TBM 700B From S N 96 equipped with MOD70 0276 00 30 11 10 18 L HOTELLIER Engine fire detection system All From S N 1 except S N 205 and 249 equipped with MOD70 0276 00 30 11 10 29 EROS INTERTEC...

Page 571: ...10 Rev 0 44 Chip detection system All From S N 1 equipped with MOD70 276 00 30 11 10 47 AIRBORNE GWX 68 color weather radar All equipped with MOD70 176 00 or MOD70 276 00 22 06 07 49 GARMIN G1000 TAWS...

Page 572: ...1 Edition 1 November 30 2010 Rev 0 SUPPLEMENT BFG WX 500 STORMSCOPE TABLE OF CONTENTS Page 1 GENERAL 9 6 2 2 LIMITATIONS 9 6 2 3 EMERGENCY PROCEDURES 9 6 3 4 NORMAL PROCEDURES 9 6 3 5 PERFORMANCE 9 6...

Page 573: ...pe systems signal displays are not intended for the purpose of penetrating thunderstorm areas or areas of severe turbulence such intentional use is prohibited NOTE Range selection determines receiver...

Page 574: ...procedures of the basic Pilot s Operating Handbook SECTION 4 NORMAL PROCEDURES Normal operating procedures of the BFG stormscope are outlined in the WX 500 Pilot s Guide Series II No 009 11501 001 at...

Page 575: ...94 2 240 232 28 5 900 SECTION 7 DESCRIPTION The BFG Series II stormscope weather mapping system provides a visual screen readout of the electrical discharges associated with thunderstorms This inform...

Page 576: ...Edition 1 November 30 2010 Rev 0 SUPPLEMENT KEITH VAPOR CYCLE COOLING SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 15 2 2 LIMITATIONS 9 15 2 3 EMERGENCY PROCEDURES 9 15 2 4 NORMAL PROCEDURES 9 15 3 5 PE...

Page 577: ...ribed in Section 2 Limitations of the basic Pilot s Operating Handbook The vapor cycle cooling system can be operated with a Ground Power Unit engine running with GENERATOR selector on MAIN The system...

Page 578: ...struct the evaporator lattice orifice located according to the evaporator installation either above the cabin floor or in the baggage compartment NOTE 2 The standby compass may be disturbed when the v...

Page 579: ...f valve rated to open at 425 psi 29 bars a binary pressure switch monitoring low and high pressures 30 P 300 psi 2 P 20 bars a relay The components are installed on a pallet and enclosed in a housing...

Page 580: ...l expansion valve is screwed on the evaporator inlet Two service valves for the refrigerant The low pressure LP service valve and the high pressure HP service valve are installed on a Tee bulkhead uni...

Page 581: ...the thermal expansion valve located at the evaporator inlet A temperature control sensor monitoring the refrigerant temperature at the evaporator heat exchanger outlet pilots the thermal expansion val...

Page 582: ...nsion valve 3 HP service valve 4 Sight glass 5 Binary pressure switch 6 Receiver drier 7 Condenser air outlet 8 Condenser heat exchanger 9 Compressor condenser fan motor 10 Compressor condenser assemb...

Page 583: ...SUPPLEMENT 15 KEITH VAPOR CYCLE COOLING SYSTEM TBM 700 Page 9 15 9 Edition 1 November 30 2010 Rev 0 Figure 9 15 1 2 2 Schematic diagram...

Page 584: ...TBM 700 SUPPLEMENT 15 KEITH VAPOR CYCLE COOLING SYSTEM Page 9 15 10 Edition 1 November 30 2010 Rev 0 Figure 9 15 2 1 2 ECS panel 1 Green light 2 Operation switch 3 Light test 4 Fan speed selector...

Page 585: ...SUPPLEMENT 15 KEITH VAPOR CYCLE COOLING SYSTEM TBM 700 Page 9 15 11 Edition 1 November 30 2010 Rev 0 Figure 9 15 2 2 2 ECS panel...

Page 586: ...850 Page 9 18 1 Rev 2 SUPPLEMENT ENGINE FIRE DETECTION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 18 2 2 LIMITATIONS 9 18 2 3 EMERGENCY PROCEDURES 9 18 3 4 NORMAL PROCEDURES 9 18 5 5 PERFORMANCE 9 18...

Page 587: ...e generalities hereafter supplement those of the standard airplane described in Section 1 General of the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option ENGINE FIRE...

Page 588: ...n the TBM airplane is equipped with the option ENGINE FIRE DETECTION SYSTEM ENGINE FIRE ON GROUND Indications ITT increasing red warning ITT ON or ITT CAS message red warning FIRE ON or FIRE CAS messa...

Page 589: ...k for smoke coming through engine cowls or from air conditioning system 3 Land as soon as possible If the fire alarm is confirmed 1 Power lever IDLE 2 Propeller governer lever FEATHER 3 Condition leve...

Page 590: ...he TBM airplane is equipped with the option ENGINE FIRE DETECTION SYSTEM Before starting the engine FIRE DETECT TEST push button DEPRESS The FIRE red warning goes on or the FIRE CAS message lights on...

Page 591: ...per unit lb kg ARM in m 34 FIRE PROTECTION A Engine fire detection system OPT70 26002A TBM 700A TBM 700B without G1000 system L HOTELLIER 1 455 0 66 96 06 2 440 A Engine fire detection system OPT70 2...

Page 592: ...ISORY2 circuit breaker DETECTORS The 7 detectors are secured on supports positioned in the most sensitive engine areas They consist of thermal switches detecting a temperature greater than 200 C RELAY...

Page 593: ...s detecting a temperature greater than 200 C PUSH BUTTON The push button enables the pilot to test the detection system by opening the grounding circuit It is connected in series with the 7 detectors...

Page 594: ...2010 Rev 0 SUPPLEMENT EROS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 30000 FT TABLE OF CONTENTS Page 1 GENERAL 9 29 2 2 LIMITATIONS 9 29 3 3 EMERGENCY PROCEDURES 9 29 4 4 NORMAL PROCEDURES 9 29 6 5 PERFOR...

Page 595: ...OS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 30000 FT and with MOD70 0276 00 This system replaces the standard oxygen system described in Section 7 Description Chapter Emergency oxygen of the basic Pilot s...

Page 596: ...rd airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the TBM 700 airplane is equipped with the option EROS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 30000 FT and with...

Page 597: ...e of the basic Pilot s Operating Handbook If circumstances require that the depressurized airplane remains at 10000 ft or above tables located in Section 7 give minimum oxygen pressure values required...

Page 598: ...e 4 PASSENGERS OXYGEN switch ON 5 Check the oxygen flow indicator for the front seats the blinker is transparent and for the rear passengers the blinker is green 6 NORMAL MASK micro inverter MASK 7 Pe...

Page 599: ...OS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 30000 FT and with MOD70 0276 00 External Rear R H karman Oxygen cylinder open Oxygen pressure CHECK Internal Oxygen supply Available for the planned flight see...

Page 600: ...ne the usable oxygen percent using the chart Figure 9 29 1 Figure 9 29 1 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 9 29 2 by the percent obtained with t...

Page 601: ...mance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane i...

Page 602: ...ution of this pressure according to the outside temperature is given in Section 8 Figure 9 29 3 as well as on a placard on the inside of the cylinder service door minimum pressure 217 PSIG 15 bars The...

Page 603: ...are equipped with a micro controlled by the switch NORMAL MASK micro inverter under cover located on the instrument panel near the pilot s control wheel with a three position selector NORMAL 100 and...

Page 604: ...5 578 550 522 1 3 802 770 740 707 674 642 608 1 4 920 882 847 809 772 734 696 2 0 937 898 864 824 783 745 709 2 1 1056 1009 971 925 881 837 792 2 2 1175 1123 1078 1027 977 928 875 2 3 1293 1234 1186 1...

Page 605: ...567 539 513 1 2 880 843 811 773 738 702 665 1 3 1091 1044 1001 955 910 864 817 1 4 1300 1242 1191 1134 1077 1022 966 2 0 912 873 839 801 763 728 689 2 1 1122 1072 1029 980 934 885 840 2 2 1333 1271 1...

Page 606: ...2 590 1 2 776 745 716 683 653 622 590 1 3 776 745 716 683 653 622 590 1 4 776 745 716 683 653 622 590 2 0 912 873 839 801 763 728 689 2 1 1228 1172 1125 1073 1016 966 913 2 2 1228 1172 1125 1073 1016...

Page 607: ...option EROS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 30000 FT and with MOD70 0276 00 These directives replace the one described in Chapter Servicing Paragraph Oxygen of the basic Pilot s Operating Handbo...

Page 608: ...ES A SERIOUS FIRE HAZARD USE NO OIL OR GREASE WITH THE OXYGEN REPLENISHMENT EQUIPMENT ALWAYS OPEN SHUT OFF VALVE SLOWLY TO AVOID GENERATING HEAT AND REPLENISH THE SYSTEM SLOWLY AT A RATE NOT EXCEEDING...

Page 609: ...ssure on the gage and fill to the correct pressure if necessary Release the pressure in the oxygen supply hose and disconnect from the charging valve Install the cap on the charging valve Make sure al...

Page 610: ...us solution of Zephiran Chloride Scott Aviation P N 00 2572 or with disinfection cleaners EROS P N SAN50 After disinfecting and thoroughly drying the mask lightly dust the outside of the facepiece wit...

Page 611: ...Page 9 29 18 Edition 1 November 30 2010 Rev 0 Gently fold reservoir bag lengthwise into thirds outside edges folded inward over center of bag Do not crease bag Fold reservoir bag away from breathing...

Page 612: ...ANYARD PIN IS INSERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyar...

Page 613: ...2010 Rev 0 SUPPLEMENT EROS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 31000 FT TABLE OF CONTENTS Page 1 GENERAL 9 37 2 2 LIMITATIONS 9 37 3 3 EMERGENCY PROCEDURES 9 37 4 4 NORMAL PROCEDURES 9 37 6 5 PERFOR...

Page 614: ...OS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 31000 FT and with MOD70 0276 00 This system replaces the standard oxygen system described in Section 7 Description Chapter Emergency oxygen of the basic Pilot s...

Page 615: ...rd airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the TBM 700 airplane is equipped with the option EROS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 31000 FT and with...

Page 616: ...e of the basic Pilot s Operating Handbook If circumstances require that the depressurized airplane remains at 10000 ft or above tables located in Section 7 give minimum oxygen pressure values required...

Page 617: ...e 4 PASSENGERS OXYGEN switch ON 5 Check the oxygen flow indicator for the front seats the blinker is transparent and for the rear passengers the blinker is green 6 NORMAL MASK micro inverter MASK 7 Pe...

Page 618: ...OS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 31000 FT and with MOD70 0276 00 External Rear R H karman Oxygen cylinder open Oxygen pressure CHECK Internal Oxygen supply Available for the planned flight see...

Page 619: ...ne the usable oxygen percent using the chart Figure 9 37 1 Figure 9 37 1 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 9 37 2 by the percent obtained with t...

Page 620: ...mance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane i...

Page 621: ...ution of this pressure according to the outside temperature is given in Section 8 Figure 9 37 3 as well as on a placard on the inside of the cylinder service door minimum pressure 217 PSIG 15 bars The...

Page 622: ...en system they are equipped with a micro controlled by the switch NORMAL MASK micro inverter under cover located on the instrument panel near the pilot s control wheel with a three position selector N...

Page 623: ...743 715 1 3 1010 976 941 907 873 839 806 1 4 1137 1096 1056 1015 975 935 897 2 0 1037 1001 965 930 894 859 825 2 1 1164 1122 1080 1038 997 956 916 2 2 1289 1241 1192 1144 1097 1050 1004 2 3 1416 1361...

Page 624: ...710 685 1 2 1067 1029 992 955 918 882 846 1 3 1513 1240 1192 1144 1097 1050 1004 1 4 1513 1452 1392 1333 1275 1217 1161 2 0 992 958 925 891 858 825 793 2 1 1215 1170 1125 1081 1037 994 952 2 2 1439 13...

Page 625: ...0 1 2 961 929 896 864 833 801 770 1 3 961 929 896 864 833 801 770 1 4 961 929 896 864 833 801 770 2 0 992 958 925 891 858 825 793 2 1 1333 1282 1231 1181 1131 1083 1035 2 2 1333 1282 1231 1181 1131 10...

Page 626: ...option EROS INTERTECHNIQUE GASEOUS OXYGEN SYSTEM 31000 FT and with MOD70 0276 00 These directives replace the one described in Chapter Servicing Paragraph Oxygen of the basic Pilot s Operating Handbo...

Page 627: ...ES A SERIOUS FIRE HAZARD USE NO OIL OR GREASE WITH THE OXYGEN REPLENISHMENT EQUIPMENT ALWAYS OPEN SHUT OFF VALVE SLOWLY TO AVOID GENERATING HEAT AND REPLENISH THE SYSTEM SLOWLY AT A RATE NOT EXCEEDING...

Page 628: ...ssure on the gage and fill to the correct pressure if necessary Release the pressure in the oxygen supply hose and disconnect from the charging valve Install the cap on the charging valve Make sure al...

Page 629: ...us solution of Zephiran Chloride Scott Aviation P N 00 2572 or with disinfection cleaners EROS P N SAN50 After disinfecting and thoroughly drying the mask lightly dust the outside of the facepiece wit...

Page 630: ...Page 9 37 18 Edition 1 November 30 2010 Rev 0 Gently fold reservoir bag lengthwise into thirds outside edges folded inward over center of bag Do not crease bag Fold reservoir bag away from breathing...

Page 631: ...ANYARD PIN IS INSERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyar...

Page 632: ...Edition 1 November 30 2010 Rev 0 SUPPLEMENT OPERATION AT 31000 FT TABLE OF CONTENTS Page 1 GENERAL 9 38 2 2 LIMITATIONS 9 38 2 3 EMERGENCY PROCEDURES 9 38 2 4 NORMAL PROCEDURES 9 38 2 5 PERFORMANCE 9...

Page 633: ...rplane at 31000 ft is subjected to the application of the PRATT WHITNEY Service Bulletins No 14261 and 14308 Flight at 31000 ft is authorized if the option OPT70 35001D EROS INTERTECHNIQUE Gaseous oxy...

Page 634: ...one given for the standard airplane in Section 5 Performance of the basic Pilot s Operating Handbook 5 1 CABIN PRESSURIZATION ENVELOPE Figure 9 38 1 CABIN PRESSURIZATION ENVELOPE 260 240 220 180 140 1...

Page 635: ...wer IAS 130 kt TRQ Normal recommended Cruise Power TRQ Maximum Cruise Power TRQ 66 91 95 100 64 89 93 99 62 86 91 97 60 85 89 95 58 83 87 93 56 81 85 91 54 79 83 89 52 77 81 87 50 75 79 85 48 74 77 83...

Page 636: ...obtain the values for 31000 ft refer to Section 5 Performance Chapter 5 10 Cruise performance of the basic Pilot s Operating Handbook and decrease the values given for 30000 ft in the tables Maximum...

Page 637: ...and balance given in Section 6 Weight and balance of the basic Pilot s Operating Handbook SECTION 7 DESCRIPTION In order to be able to fly at 31000 ft the PRATT WHITNEY Service Bulletins No 14261 and...

Page 638: ...1 Edition 1 November 30 2010 Rev 0 SUPPLEMENT CHIP DETECTION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 44 2 2 LIMITATIONS 9 44 2 3 EMERGENCY PROCEDURES 9 44 3 4 NORMAL PROCEDURES 9 44 4 5 PERFORMANCE...

Page 639: ...pment limitations description and operations necessary to the operation when the TBM airplane is equipped with the option CHIP DETECTION SYSTEM and with MOD70 0276 00 SECTION 2 LIMITATIONS The install...

Page 640: ...hen the TBM airplane is equipped with the option CHIP DETECTION SYSTEM and with MOD70 0276 00 Indication CHIP amber CAS message lights on On ground Before engine start 1 Do not start engine After engi...

Page 641: ...f the basic Pilot s Operating Handbook when the TBM airplane is equipped with the option CHIP DETECTION SYSTEM and with MOD70 0276 00 When CHIP amber CAS message lights on it causes the illumination o...

Page 642: ...NAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 79 LUBRICATION A Chip detection system 1 or 2 detectors MOD70 0169 79D Negligible SECTION 7 DESCRIPTION The chip detection system enable...

Page 643: ...850 Page 9 47 1 Rev 1 SUPPLEMENT AIRBORNE GWX 68 COLOR WEATHER RADAR TABLE OF CONTENTS Page 1 GENERAL 9 47 2 2 LIMITATIONS 9 47 2 3 EMERGENCY PROCEDURES 9 47 3 4 NORMAL PROCEDURES 9 47 4 5 PERFORMANC...

Page 644: ...portant to obey the following restrictions Do not operate the radar during refueling operations or in the vicinity of trucks or containers containing flammables or explosives Do not allow personel wit...

Page 645: ...ystem do not change the basic emergency procedures of the airplane described in Section 3 Emergency procedures of the basic Pilot s Operating Handbook CAUTION IN REVERSIONARY MODE THE WEATHER RADAR SY...

Page 646: ...ar system are outlined in the Pilot s Guide the references of which are given in Section 2 Limitations of this Supplement CAUTION IN REVERSIONARY MODE THE WEATHER RADAR SYSTEM AUTOMATICALLY SWITCHES T...

Page 647: ...e and a 3 KIAS decrease in Long Range cruise performance described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the on...

Page 648: ...1500 The controls for the MFD are located on both the MFD bezel and the MFD control unit keyboard GCU 475 Figure 9 47 1 1 2 GWX 68 weather radar display and controls 1 GDU 1500 MFD 2 Radar mode 3 Are...

Page 649: ...SUPPLEMENT 47 AIRBORNE GWX 68 COLOR WEATHER RADAR TBM 700 850 Page 9 47 7 Rev 1 Figure 9 47 1 2 2 GWX 68 weather radar display and controls...

Page 650: ...850 Page 9 49 1 Rev 1 SUPPLEMENT GARMIN G1000 TAWS SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 49 3 2 LIMITATIONS 9 49 3 3 EMERGENCY PROCEDURES 9 49 4 4 NORMAL PROCEDURES 9 49 4 5 PERFORMANCE 9 49 6 6...

Page 651: ...ides terrain proximity alerting and detection to the pilot It must not be used for airplane vertical and horizontal navigation AC 2318 recommendation in order to avoid unwillingly warnings TAWS functi...

Page 652: ...g Handbook when the airplane is equipped with the option GARMIN G1000 TAWS SYSTEM The TAWS function is not operational TAWS FAIL ANNUNCIATION SECTION 4 NORMAL PROCEDURES The normal procedures hereafte...

Page 653: ...s PULL UP AURAL WARNING Terrain Terrain Pull up Pull up Obstacle Obstacle Pull up Pull up AURAL WARNINGS The red PULL UP PFD MFD annunciation and TERRAIN OBSTACLE PULL UP pop up alerts light on Adjust...

Page 654: ...of climb Don t sink AURAL WARNING The amber TERRAIN PFD MFD annunciation and SINK RATE pop up alert light on Reduce rate of descent Sink rate AURAL WARNING SECTION 5 PERFORMANCE The installation and...

Page 655: ...ation hereafter supplement the one given for the standard airplane in Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit...

Page 656: ...ert is issued a potential impact point is displayed on the TAWS Page Imminent Terrain Impact and Imminent Obstacle Impact Imminent Terrain Impact ITI and Imminent Obstacle Impact IOI alerts are issued...

Page 657: ...l up Imminent Terrain Impact Warning ITI Red PULL UP TERRAIN AHEAD PULL UP Terrain Ahead Pull up Terrain Ahead Pull up Reduced Required Obstacle Clearance Warning ROC Red PULL UP OBSTACLE PULL UP Obst...

Page 658: ...15 Nm of the destination airport PDA alerting ends when the airplane is either 0 5 Nm from the runway threshold OR at an altitude of 125 feet AGL while within 1 0 Nm of the threshold Figure 9 49 1 PD...

Page 659: ...purpose of the Excessive Descent Rate EDR alert is to provide suitable notification when the airplane is determined to be closing descending upon terrain at an excessive speed Figure 9 49 2 shows the...

Page 660: ...so referred to as Altitude Loss After Takeoff is to provide suitable alerts to the pilot when the system determines that the airplane is losing altitude closing upon terrain after takeoff The aural me...

Page 661: ...egative vertical speed and height are within the range in the second figure Figure 9 49 3 Negative Climb Rate NCR Alert Criteria The aural displayed messages associated with the NCR function are descr...

Page 662: ...ong with specific vertical accuracy minimums Should the navigation solution become degraded or if the airplane is out of the database coverage area the annunciation TAWS N A is generated in the annunc...

Page 663: ...850 Page 9 50 1 Rev 2 SUPPLEMENT GARMIN G1000 SYNTHETIC VISION SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 50 3 2 LIMITATIONS 9 50 4 3 EMERGENCY PROCEDURES 9 50 5 4 NORMAL PROCEDURES 9 50 6 5 PERFORMAN...

Page 664: ...plane is equipped with the option GARMIN G1000 SYNTHETIC VISION SYSTEM SVS The SVS does not replace and is not intended to be used independently of the TAS and or TAWS system s The SVS does not replac...

Page 665: ...h MOD70 0276 00 GARMIN G1000 Integrated Flight Deck Cockpit Pilot s Guide for the Daher Socata TBM 700 No 190 01247 00 or any later revision as applicable The use of the Synthetic Vision system displa...

Page 666: ...cribed in Section 3 Emergency procedures of the basic Pilot s Operating Handbook when the airplane is equipped with the option GARMIN G1000 SYNTHETIC VISION SYSTEM INCONSISTENT DISPLAY BETWEEN SVS AND...

Page 667: ...HE PRIMARY FLIGHT INSTRUMENTS AS WELL AS FOR THE TRAFFIC ADVISORY SYSTEM TAS OR THE TERRAIN AWARENESS WARNING SYSTEM TAWS SVS ACTIVATION 1 2 1 If SVS is desired PFD key Press SYN VIS key Press SYN TER...

Page 668: ...splay will cycle on or off with each press of the HRZN HDG key c If Airport Signs are desired APTSIGNS key Press The airport signs display will cycle on or off with each press of the APTSIGNS key NOTE...

Page 669: ...performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airp...

Page 670: ...ays displayed when synthetic terrain is selected for display Pathway a pilot selectable three dimensional representation of the programmed flight plan path that can be selected for display alone or wi...

Page 671: ...gment displayed will be the first GPS course leg The Pathway must be within the SVS field of view of 30 degrees left and 35 degrees right If the programmed path is outside that field of view the Pathw...

Page 672: ...y displays should only be used to maintain awareness with regard to the surrounding terrain and the programmed flight path Primary aircraft control must be accomplished by reference to the primary fli...

Page 673: ...to the Missed Approach Point MAP The Pathway will be shown level at the altitude set in the G1000 altitude selector or the Final Approach Fix FAF crossing altitude whichever is higher up to the point...

Page 674: ...or a leg defined by other than a GPS course the Pathway will not be displayed for that segment If the course to the Missed Approach Holding Point is out of the SVS field of view during the initial mi...

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