Daher TBM 700 Pilot'S Manual Download

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SECTION 5

PERFORMANCE

EASA Approved

TBM

700

PILOT’S OPERATING HANDBOOK

Page 5.9.1

Rev. 7

5.9 -- CLIMB PERFORMANCE

(Refer to Supplement 41 for TBM 700C2 airplane)

CLIMB SPEEDS (IAS = 130 KIAS)

Conditions : Maximum climb power

Landing gear and flaps UP
IAS = 130 KIAS -- BLEED ON

Airplane

weight

Pressure

altitude

(feet)

RATE OF CLIMB (ft/min)

ISA

-- 20

ISA

-- 10

ISA

+ 10

ISA

+ 20

ISA

+ 30

4850 lbs

(2200 kg)

2000

4000

6000

8000

3060

3030

3000

2970

2930

2920

2890

2860

2830

2800

2770

2740

2700

2660

2690

2660

2630

2590

2550

2590

2550

2520

2480

2440

2480

2455

2415

2380

2340

5512 lbs

(2500 kg)

2000

4000

6000

8000

2600

2570

2540

2510

2480

2485

2455

2425

2395

2350

2380

2350

2320

2290

2250

2285

2250

2220

2185

2150

2190

2160

2130

2090

2035

2105

2080

2045

2010

1975

6579 lbs

(2984 kg)

2000

4000

6000

8000

2050

2025

1995

1970

1935

1955

1925

1900

1870

1840

1875

1840

1815

1780

1745

1795

1765

1735

1700

1665

1720

1690

1660

1625

1590

1640

1620

1585

1555

1520

Figure 5.9.1 -- CLIMB SPEEDS (IAS = 130 KIAS)

Summary of Contents for TBM 700

Page 1: ...CATA SAS It is supplied in confidence and commercial security of its contents must be maintained It must not be used for any purpose other than that for which it is supplied nor may information contained in it be disclosed to unauthorized persons It must not be reproduced nor transmitted in any form in whole or in part without permission in writing from the owners of the Copyright Information in t...

Page 2: ...cycle system ACS Major 143 21 Vapor cycle cooling system VCCS Major 144 33 Cabin lighting telebreaker minor 145 53 Aft baggage compartment non pressurized Major 146 00 Clamp type modification on airspeed indicating system and cabin pressurization regulation system minor 148 25 Crash proof seat backward displacement TBM 700C2 Major 0155 21 Vapor cycle cooling system VCCS Low pressure evaporator TBM...

Page 3: ...uipped with option OPT70 23023 minor 0172 57 Replacement on flaps of SHUR LOCK nuts by machined bushings minor 0173 28 New fuel gauging probes minor 0175 23 BOSE headset wiring Front and rear minor 0177 57 Lower attachment fittings of external flap tracks minor 0183 56 Side windows generation 2006 minor 0184 56 Cabin windows generation 2006 minor 0185 21 Moving of ECS probe to the bulkhead top TBM...

Page 4: ...nding gear actuating cylinder modification minor 0205 55 Replacement of fin expansion pins minor 0209 57 Reinforcement of trailing edge omega at rib 7 minor 0213 27 Pitch trim union connector at rear pressure bulkhead minor 0217 24 Battery firewall screen minor 0256 76 Condition lever locking in HI IDLE position minor 0402 28 Fuel sequencer evolution minor ...

Page 5: ...SECTION 0 TBM 700 PILOT S OPERATING HANDBOOK Page 0 5D Rev 6 INTENTIONALLY LEFT BLANK ...

Page 6: ... 700 SECTION 0 Page 0 6 Rev 0 TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE 6 DESCRIPTION 7 AIRPLANE HANDLING SERVICING AND MAINTENANCE 8 SUPPLEMENTS 9 ...

Page 7: ...IN AND ENTRY DIMENSIONS 1 3 4 SPECIFIC LOADINGS 1 3 4 1 4 ABBREVIATIONS AND TERMINOLOGY 1 4 1 METEOROLOGICAL TERMINOLOGY 1 4 1 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 1 4 1 POWER TERMINOLOGY 1 4 3 AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY 1 4 4 WEIGHT AND BALANCE TERMINOLOGY 1 4 4 GENERAL ABBREVIATIONS 1 4 6 RADIO NAVIGATION ABBREVIATIONS 1 4 9 EFIS ABBREVIATIONS 1 4 10 1 5 CONVERSION ...

Page 8: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 0 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 9: ... to the pilot for operation of the TBM 700 airplane It also contains supplemental data supplied by the manufacturer Section 1 provides basic data and information of general interest It also contains definitions or explanations of abbreviations and terminology commonly used The general for complex optional systems are given in Section 9 Supplements of the Pilot s Operating Handbook ...

Page 10: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 1 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 11: ...SECTION 1 GENERAL TBM 700 PILOT S OPERATING HANDBOOK Page 1 2 1 Rev 0 1 2 THREE VIEW DRAWING Figure 1 2 1 1 2 THREE VIEW DRAWING ...

Page 12: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 2 2 Rev 7 Figure 1 2 1 2 2 THREE VIEW DRAWING ...

Page 13: ...urbine 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 Propeller model number HC E4N 3 E9083S K Number of blades 4 Propeller diameter Minimum 90 inches 2 286 m Maximum 91 inches 2 311 m Propeller type Adjustable constant speed with feathering and hydraulic control r...

Page 14: ...ENCY 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 US Specification US French Specification FR English Specification UK NATO Code ASTM D1655 JET A ASTM D1655 JET A1 ASTM D1655 JET B AIR 3405C Grade F35 DERD 2494 Issue 9 F35 without additive MIL DTL 5624 Grade JP 4 ...

Page 15: ... 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 MAXIMUM CERTIFICATED WEIGHTS Refer to Supplement 41 for TBM 700C2 airplane Ramp 6614 lbs 3000 kg Takeoff 6579 lbs 2984 kg Landing 6250 lbs 2835 kg Baggage weight refer to Section 6 for cargo loading instructions In rear part of pressurized cabin 220 lbs 100 k...

Page 16: ...imum cabin height 4 1 22 m Number of cabin entries 1 standard 1 pilot door if installed Entry width standard 3 6 52 1 08 m Entry height standard 3 10 85 1 19 m Pilot entry mean width 2 3 6 0 70 m Pilot entry mean height 3 2 16 0 97 m SPECIFIC LOADINGS Refer to Supplement 41 for TBM 700C2 airplane Wing loading 34 lbs sq ft 165 8 kg m2 Power loading 9 4 lbs SHP 4 26 kg SHP ...

Page 17: ...altitude 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 when the altimeter s barometric scale has been set to 29 92 inches of mercury 1013 2 hPa GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is the indicated airspeed expres...

Page 18: ...nded 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 initiated during takeoff to achieve takeoff safety speed at screen height VSO Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration VS1 Stalling Speed or ...

Page 19: ...ry loss of the combustion chamber flame during operation GPU Ground power unit Feathering Action which reduces the drag of a failed engine through propeller feathering Maximum Cruise Power Power developed at the couple limit interturbines temperature limit or gas generator RPM limit without time limitations corresponding to cruise conditions Ng Gas generator RPM Np Propeller rotation speed Reverse...

Page 20: ...rtification tests The value shown is not considered to be limiting g Is acceleration due to gravity Usable fuel Total fuel which can be effectively consumed by the engine WEIGHT AND BALANCE TERMINOLOGY Reference datum Datum perpendicular to the longitudinal airplane centerline from which all distances are measured for balance purpose Arm Is the distance from the reference datum to the center of gr...

Page 21: ...nd 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 empty weight Maximum ramp weight Is the maximum weight approved for ground maneuver It includes the weight of start taxi and run up fuel Maximum takeoff weight Is the maximum weight approved at the beginning of th...

Page 22: ...S Cabin pressure C Celsius degree CONT Control DIEGME Diethylene glycol monomethyl ether DIM Dimmer DISC Disconnect DN Down ECS Environmental control system EGME Ethylene glycol monomethyl ether EMER Emergency ENCOD ALTI Encoding altimeter ESS BUS TIE Essential BUS tie ETM Engine Trend Monitoring EXT LIGHTS Exterior lightings F Fahrenheit degree FCU Fuel control unit FIRE EXTING Fire extinguisher ...

Page 23: ...s L D Lift to drag LDG Landing LDG GR Landing gear LRCR Long Range Cruise LO Low LP Low pressure LRN Long range navigation LTS TEST Lightings test m Metre m a c Mean aerodynamic chord MAIN GEN Main generation MAN Manual MAN OVRD Manual override MAX RPM Maximum revolutions per minute MIN Minimum min Minute MLW Maximum landing weight mm Millimetre MRW Maximum ramp weight MTOW Maximum Takeoff Weight ...

Page 24: ...Second SEL Selector SIG Signalization SL Sea level S N Serial number SPKR Speaker ST BY Stand by STALL HTR Stall heater Std Standard T Temperature TEMP Temperature TO Takeoff TURN COORD Turn coordinator us gal Gallon U S V Volt or Voltage VACUUM LO Vacuum low WARN Warning W S Windshield WSR Weather surveillance radar XPDR Transponder ...

Page 25: ...Locator Transmitter GPS Ground Positioning System HF High Frequency HSI Horizontal Situation Indicator IFR Instrument Flight Rules ILS Instrument Landing System IMC Instrument Meteorological Conditions MFD Multi function Display MKR Marker Radio Beacon NAV Navigation Indicators or Receivers RMI Radio Magnetic Indicator TAS Traffic Advisory System TAWS Terrain Awareness Warning System VFR Visual Fl...

Page 26: ...e EFIS composite mode CP Control Panel CRS Course DU Display Unit FD Flight director EADI Electronic Attitude Deviation Indicator EFIS Electronic Flight Instrument System EHSI Electronic Horizontal Situation Indicator ERMI Electronic Radio Magnetic Indicator HDG Heading RCP Radar Control Panel REF Reference SG Symbol Generator TST Test ...

Page 27: ...O 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 0 220 Imp Gal us gal 3 785 Litre Litre 0 264 us gal lb 0 45359 kg kg 2 2046 lb Figure 1 5 1 IMPERIAL AND U S UNITS TO METRIC UNITS ...

Page 28: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 1 GENERAL Page 1 5 2 Rev 0 Figure 1 5 2 FEET VERSUS METRES Mètres 30000 20000 10000 0 Feet 2500 5000 7500 10000 31000 ...

Page 29: ...SECTION 1 GENERAL TBM 700 PILOT S OPERATING HANDBOOK Page 1 5 3 Rev 0 Figure 1 5 3 INCHES VERSUS MILLIMETRES mm 10 0 In 250 500 750 1000 20 30 40 ...

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

Page 31: ...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 505 9 20 6 5 0 20000 465 6 24 6 12 4 22000 427 8 28 5 19 3 24000 392 6 32 5 26 5 26000 359 8 36 5 33 6 28000 329 3 40 4 40 7 30000 300 8 44 4 47 8 31000 287 4 46 4 51 6 Figure 1 6 1 STANDARD ATMOSPHERE ...

Page 32: ...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 1004 29 65 1005 29 68 1006 29 71 1007 29 74 1008 29 77 1009 29 80 1010 29 83 1011 29 85 1012 29 88 1013 29 91 1014 29 94 1015 29 97 1016 30 00 1017 30 03 1018 30 06 1019 30 09 1020 30 12 1021 30 15 1022 30 18 1023...

Page 33: ...3 2 PROPELLER 2 3 3 2 4 STARTER OPERATION 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 2 6 OPERATION LIMITS 2 6 1 MANEUVER LIMITS 2 6 1 TEMPERATURE LIMITS 2 6 1 FLIGHT LOAD FACTOR LIMITS 2 6 1 SEVERE ICING CONDITIONS 2 6 2 FLAP OPERATING ENVELOPE 2 6 3 REVERSE UTILIZATION 2 6 3 EQUIPMENT REQUIRED DEPENDING ON TYPE OF OPERATION 2 6 3 ALTITUDE OPERATING LIMITS 2 ...

Page 34: ...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 ENGINE TREND MONITORING 2 7 1 CHEMICAL TOILET CABINET 2 7 1 2 8 MARKINGS 2 8 1 AIRSPEED INDICATOR 2 8 1 PRESSURIZATION 2 8 1 ENGINE INSTRUMENTS 2 8 2 SUCTION GAGE 2 8 2 2 9 PLACARDS 2 9 1 ...

Page 35: ...h those given in this Section and throughout the Pilot s Operating Handbook This Section of the airplane Pilot s Operating Handbook presents the various operating limitations the significance of such limitations instrument markings color coding and basic placards necessary for the safe operation of the airplane its powerplant and installed equipment The limitations for optional systems are given i...

Page 36: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 1 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 37: ... 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 position VLO Maximum landing gear operating speed extension retraction 180 130 178 128 Do not extend or retract landing gear above this speed VLE Maximum landing gear extended speed 180 178 Do not exceed this speed wi...

Page 38: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 2 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 39: ... 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 max CAUTION WHEN NORMALLY OPERATING REFER TO CHAPTER 5 7 ENGINE OPERATION TABLES OIL CAUTION DO NOT MIX DIFFERENT BRANDS OR TYPES OF OIL Maximum oil temperature 104 C Oil pressure Minimum 60 psi Maximum 135 psi Oi...

Page 40: ...tres Usable fuel 281 6 us gal 1066 Litres Unusable fuel 9 us gal 34 Litres Maximum fuel unbalance 25 us gal 95 Litres NOTE Usable fuel can be safely used during all normal airplane maneuvers CAUTION THE FUEL USED MUST CONTAIN AN ANTI ICE ADDITIVE IN ACCORDANCE WITH SPECIFICATION MIL I 27686 OR MIL I 85470 ADDITIVE CONCENTRATIONS EGME OR DIEGME SHALL BE COMPRISED BETWEEN A MINIMUM OF 0 06 AND A MAX...

Page 41: ...ditive 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 with additive S748 AIR 3404C Grade F43 DERD 2498 Issue 7 F43 without additive Figure 2 3 2 RECOMMENDED FUEL TYPES Reference Service Bulletin P W C No 14004 PROPELLER Number of propellers 1 Propeller manufacturer HAR...

Page 42: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 3 4 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 43: ...Rev 7 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 1st sequence wait 1 minute 2nd sequence wait 5 minutes 3rd sequence wait 30 minutes 4th sequence ...

Page 44: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 4 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 45: ...range with 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 184 8 inches 4 694 m aft of datum at 6579 lbs 2984 kg 20 of m a c Aft limits 194 9 inches 4 951 m aft of datum at all weights below 6250 lbs 2835 kg 37 of m a c 194 3 inches 4 936 m aft of dat...

Page 46: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 5 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 47: ...aneuvers including spins are not approved TEMPERATURE LIMITS Minimum temperature at start and takeoff 40 C 40 F Maximum temperature at start and takeoff ISA 37 C 67 F from 0 to 8000 ft pressure altitude Maximum temperature in flight ISA 37 C 67 F from 0 to 8000 ft pressure altitude ISA 30 C 54 F at 31000 ft pressure altitude Linear decrease between 8000 and 31000 ft Battery operation limit 70 C 15...

Page 48: ... these visual cues exists immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice Accumulation of ice on the upper surface of the wing aft of the protected area Since the autopilot when operating may mask t...

Page 49: ...erating correctly The type certification for each use requires the following equipment The equipment must be installed and operate perfectly according to the indicated type of use CAUTION IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT THE FOLLOWING EQUIPMENT LISTS ARE IN ACCORDANCE WITH THE SPECIFIC NATIONAL OPERATION RULES OF THE AIRPLANE REGISTRATION COUNTRY DEPENDING ON THE TYPE OF OPERATION NO...

Page 50: ...OFF Fuel auxiliary pump ON L H and R H fuel tank low level Non functioning of fuel timer Battery overheat Battery stop Main generator OFF Low voltage Ground power unit connected Inertial separator Starter Ignition Flaps Landing gears and doors 3 Aural warning VMO warning Landing gear warning Stall warning 4 Engine instruments Torquemeter Propeller tachometer Interturbine temperature indicator ITT ...

Page 51: ...n Fuel electrical pump auxiliary Fuel shut off valve Fuel timer Starter generator Inertial separator Stall warning Electrical aileron trim Electrical rudder trim Manual elevator pitch trim Engine ignition Landing gear electro hydraulic unit Landing gear emergency hydraulic pump manual Flaps Overspeed regulator Manual feathering Battery 7 Miscellaneous Seats each occupant Belts each occupant Straps...

Page 52: ...lision 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 during night 4 Clock 5 2nd altimeter 6 Emergency static source 7 Pitot static tube deicing Pressurized flight Cabin altimeter Cabin vertical speed indication Cabin differential pressure indication Pressurization cont...

Page 53: ...449 m Maximum differential pressure 6 2 psi Operation in RVSM area Reduced Vertical Separation Minima RVSM are met pending airplane compliance with SB 70 120 34 Airworthiness Approval alone does not authorize flight into airspace for which an RVSM Operational Approval is required by an ICAO Regional Navigation Agreement NOTE Only altimeters AM250 are compliant with TBM 700 operation in RVSM area I...

Page 54: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 6 8 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 55: ...s limited by approved seating configuration installed but must not exceed six including the pilot USE OF DOORS Flight with door open or ajar is prohibited ENGINE TREND MONITORING The information related to navigation and flight parameters are a recopy of the airplane instruments and must not be used as primary means of flight control The ETM Operation Manual at its latest revision must be easily a...

Page 56: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 7 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 57: ...or range SIGNIFICANCE White arc Wide Narrow 60 122 60 75 75 122 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Transition point between wide and narrow arcs is stall speed with flaps UP Upper limit is maximum speed permissible with flaps LDG Red line 266 Maximum speed for all operations Figure 2 8 1 AIRSPEED INDICATOR MARKINGS PRESSURIZATION MARKING VALUE SIGN...

Page 58: ...04 to 110 C 0 to 104 C 110 C Oil pressure 60 psi 60 to 100 psi 100 to 135 psi 135 psi Fuel pressure 0 to 5 psi 10 to 50 psi 50 psi Generator RPM Ng 51 to 104 104 Propeller RPM Np 450 to 1000 RPM 1600 to 2000 RPM 2000 RPM ITT 800 to 1090 C 400 to 800 C 800 C normal limit 1090 C red triangle absolute limit Torque TRQ 100 0 to 110 arc thick from 100 to 110 110 Figure 2 8 3 ENGINE INSTRUMENT MARKINGS ...

Page 59: ...ev 7 2 9 PLACARDS 1 Under L H front side window 2 Calibration chart on compass and on windshield post For N 30 60 E 120 150 Steer For S 210 240 W 300 330 Steer DATE RADIO ON Refer to Supplement 41 for TBM 700C2 airplane WARNING TURN L AND R WINDSHIELD DE ICE OFF BEFORE COMPASS READING ...

Page 60: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 2 Rev 7 3 On pressurized baggage compartment partition wall or Refer to Supplement 41 for TBM 700C2 airplane ...

Page 61: ...SECTION 2 LIMITATIONS EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 2 9 3 Rev 7 4 Under radio rack in front of pedestal ...

Page 62: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 4 Rev 7 5 On fuel selector 6 Near fuel tank caps ...

Page 63: ...e 2 9 5 Rev 7 7 On internal face of L H engine cowling Oil system capacity 12 l 12 7 qt 8 On landing gear emergency control access door LDG GEAR EMERGENCY UNDER HATCH 9 On rear passenger s table casing TABLE MUST BE STOWED DURING TAKEOFF AND LANDING 10 Under R H control wheel ...

Page 64: ...nose gear leg NOSE LANDING GEAR TIRE PRESSURE 6 5 bar 94 psi 13 On main gear leg MAIN LANDING GEAR TIRE PRESSURE 8 25 bar 120 psi 14 On engine cowling in front of compartment door EXTERNAL POWER 28 VOLTS D C NOMINAL 800 AMPS STARTING CAPACITY MIN DO NOT EXCEED 1400 AMPS Refer to Supplement 41 for TBM 700C2 airplane ...

Page 65: ...SECTION 2 LIMITATIONS EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 2 9 7 Rev 7 15 On pilot door External side if installed 16 On access door External side ...

Page 66: ...BM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 8 Rev 7 17 On outer fuselage skin aft of access door and in the cabin forward of access door 18 On access door Internal side ...

Page 67: ...SECTION 2 LIMITATIONS EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 2 9 9 Rev 7 19 On pilot door Internal side if installed 20 On emergency exit handle Marking on cover Marking on handle ...

Page 68: ... last step of stairs STAIRS MAX LOAD ONE PERSON 22 On R H access door jamb DO NOT USE HAND RAIL TO RETRACT OR STOW STAIRS 23 On R H side at front seat level and on the first rear passengers masks container R H side on the ceiling 24 On rear passengers masks containers on R H side on the ceiling ...

Page 69: ...SECTION 2 LIMITATIONS EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 2 9 11 Rev 7 25 On internal face of the oxygen cylinder service door 26 On the oxygen service door ...

Page 70: ...PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 12 Rev 7 27 On internal face of L H engine cowl 28 On internal face of the door of the rear baggage compartment non pressurized or ...

Page 71: ...2 9 13 TR17 March 2015 29 On emergency locator transmitter inspection door 30 On the potty seat curtain if installed on pilot s side CURTAIN MUST BE STOWED FOR TAKE OFF AND LANDING Post MOD70 0391 26D 31 On R H side at front seat level 32 On the lower drawer of the R H cabinet ...

Page 72: ...EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 2 9 13 Rev 7 29 On emergency locator transmitter inspection door 30 On the potty seat curtain if installed on pilot s side CURTAIN MUST BE STOWED FOR TAKE OFF AND LANDING ...

Page 73: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 2 LIMITATIONS EASA Approved Page 2 9 14 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 74: ... DURING FLIGHT 3 3 3 OIL PRESSURE DROP 3 3 4 ENGINE REGULATION DISCREPANCY POWER LOSS POWER LEVER CONTROL LOSS 3 3 5 GOVERNOR REGULATION CONTROL NOT OPERATING 3 3 7 EXCESSIVE PROPELLER ROTATION SPEED 3 3 8 RED WARNING LIGHT ITT ON 3 3 9 ENGINE DOES NOT STOP ON GROUND 3 3 11 3 4 AIR START 3 4 1 AIR START ENVELOPE 3 4 1 AIR START WITH STARTER 3 4 2 3 5 FIRE AND SMOKE 3 5 1 ENGINE FIRE ON GROUND 3 5 ...

Page 75: ... 3 LANDING WITH DEFECTIVE NOSE LANDING GEAR DOWN UNLOCKED OR NOT DOWN 3 7 5 LANDING WITH GEAR UP 3 7 6 LANDING WITHOUT ELEVATOR CONTROL 3 7 7 LANDING WITH FLAPS MALFUNCTION 3 7 8 DITCHING 3 7 9 3 8 FUEL SYSTEM 3 8 1 RED WARNING LIGHT FUEL PRESS ON 3 8 1 AMBER WARNING LIGHT AUX BP ON ON 3 8 3 AMBER WARNING LIGHT FUEL L LO OR FUEL R LO ON 3 8 4 AMBER WARNING LIGHT AUTO SEL ON 3 8 4 3 9 ELECTRICAL SY...

Page 76: ...ER SWITCH FAILURE 3 9 9 3 10 PRESSURIZATION AND AIR CONDITIONING 3 10 1 RED WARNING LIGHT CAB PRESS ON 3 10 1 CABIN NOT DEPRESSURIZED AFTER LANDING 3 10 1 AMBER WARNING LIGHT BLEED OFF ON 3 10 2 RED WARNING LIGHT BLEED TEMP ON 3 10 3 RED WARNING LIGHT DOOR ON 3 10 4 AMBER WARNING LIGHT VACUUM LO ON 3 10 5 DEFOG MALFUNCTION 3 10 6 3 11 LANDING GEAR AND FLAPS 3 11 1 LANDING GEAR RETRACTION DISCREPAN...

Page 77: ...MISTING OR INTERNAL ICING 3 12 3 AMBER WARNING LIGHT PITOT 1 PITOT 2 OR STALL HTR ON 3 12 4 3 13 MISCELLANEOUS 3 13 1 RUNAWAY OF ONE OF THE THREE ELECTRICAL TRIM TABS 3 13 1 CRACK IN COCKPIT WINDOW OR WINDOW PANEL 3 13 1 EMERGENCY EXIT USE 3 13 2 EMERGENCY BEACON USE ELT 3 13 2 TOTAL COMMUNICATION FAILURE 3 13 3 MAIN GYRO HEADING FAILURE 3 13 3 PARTICULAR TRANSPONDER USES 3 13 4 ACCIDENTAL SPINS 3...

Page 78: ... Supplements Pilot must know procedures given in this section and be prepared to take appropriate action should an emergency arise Some emergency procedures are a part of pilot basic training Although these emergencies are discussed here this information is not intended to replace such training but only to provide a source of reference and review This information also provides failure procedures w...

Page 79: ...dicating failures or discrepancies which require an action as soon as practical Red or amber failure warning are coupled with the lighting of a flashing red indicator or a flashing amber indicator Both indicators are located on the upper part of the L H instrument panel When either one lights up press it once to reactivate it will go out and is ready to signal in the event of another failure On th...

Page 80: ...er to Chapter 3 3 Paragraph ENGINE FAILURE AT TAKEOFF BEFORE ROTATION For any other reason 1 Power lever IDLE 2 Reverse AS REQUIRED 3 Braking AS REQUIRED If the airplane cannot be stopped on the remaining runway 4 Power lever IDLE 5 Condition lever CUT OFF 6 Tank selector OFF 7 CRASH lever PULL DOWN Evacuate if necessary after the airplane has come to a stop ...

Page 81: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 2 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 82: ...ERATING HANDBOOK Page 3 3 1 Rev 7 3 3 ENGINE FAILURES ENGINE FAILURE AT TAKEOFF BEFORE ROTATION 1 Power lever IDLE 2 Braking AS REQUIRED If the airplane cannot be stopped on the remaining runway 3 Condition lever CUT OFF 4 Tank selector OFF 5 CRASH lever PULL DOWN ...

Page 83: ...ad keeping 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 PULL DOWN If altitude allows to reach a favourable runway or ground 1 LDG DN 2 Flaps AS REQUIRED 3 Maintain IAS 100 KIAS Flaps UP IAS 90 KIAS Flaps TO 4 Power lever IDLE 5 Propeller governor lever FEATHER Before to...

Page 84: ... PRESSED 2 Power lever IDLE 3 Propeller governor lever FEATHER 4 Condition lever CUT OFF 5 Remaining fuel CHECK 6 Tank selector SWITCH TANKS 7 AUX BP switch and fuel pressure CHECK CORRECT 8 Air start Refer to Chapter 3 4 9 In case of high altitude above 12000 ft undertake an EMERGENCY DESCENT Refer to Chapter 3 6 10 If air start not successful perform a FORCED LANDING Refer to Chapter 3 7 ...

Page 85: ...If indicated pressure is below the green arc CONFIRMED FAILURE Due to the oil pressure drop the propeller blade angle may go towards high pitch and therefore lead to a Np propeller rotation speed decrease CAUTION PREPARE FOR AN ENGINE STOP SHORTLY REDUCE POWER TO THE MINIMUM NECESSARY LAND AS SOON AS PRACTICAL If engine power drops itself 4 Power lever IDLE 5 Propeller governor lever FEATHER 6 Con...

Page 86: ...sary to continue flight If the available power is weak extend the landing gear only on a glide path in final approach and extend full flaps only in short final Do not perform a go around CAUTION IN MANUAL OVERRIDE ENGINE IS NEITHER PROTECTED AGAINST SLAM ACCELERATIONS NOR AGAINST MAXIMUM SPEED OVERSHOOTING AVOID RAPID CONTROL MOVEMENTS AND MANAGE ENGINE PARAMETERS CAUTION IN SOME CASES WHEN MANUAL...

Page 87: ...btained 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 TO 6 Establish a long final or an ILS approach respecting IAS 178 KIAS 7 When runway is assured Condition lever CUT OFF 8 Propeller governor lever FEATHER if necessary to extend trajectory 9 Flaps LDG as required ...

Page 88: ...TION CONTROL NOT OPERATING May indicate a rupture of the linkage of the governor control 1 Continue the flight 2 If Np 2000 RPM do not perform a go around and do not use the reverse In that case the go around performance and the reverse efficiency might be lower than expected The airplane repair is mandatory before any other flight ...

Page 89: ... propeller governor and overspeed limiter failure In that case only the torque limiter operates to limit the power However the pilot intervention is necessary to maintain Np 2000 RPM The propeller reducer is designed for a max Np of 2200 RPM 1 Reduce the power and the aircraft speed to avoid propeller rotation speeds higher than 2000 RPM 2 Land as soon as possible 3 Do not perform a go around A go...

Page 90: ...ED WARNING LIGHT ITT ON 1 2 Indicates that ITT exceeds 800 C During an engine start 1000 870 800 Inform the maintenance department Intertubine temperature C No action required TEMPERATURE LIMITS DURING START 0 5 20 Time seconds If the above diagram limits are exceeded 1 ITT indicator CHECK 2 Stop the starting procedure ...

Page 91: ...ell as ground conditions 4 Inform maintenance department During flight 1 ITT indicator CHECK 2 Reduce power and correct display according to Engine Operation tables Chapter 5 7 If ITT remains 800 C 3 Reduce power to maintain ITT 800 C 4 Shorten the flight 5 Record the airplane and engine parameters read in case of overtemperature 6 Inform maintenance department at the end of the flight ...

Page 92: ...ndition lever is set to CUT OFF proceed as follows 1 AP TRIMS MASTER switch OFF 2 RADIO MASTER switch OFF 3 INT LIGHTS panel All switches OFF 4 EXT LIGHTS panel All switches OFF 5 ECS panel All switches OFF 6 Tank selector OFF Wait for engine stop due to lack of fuel in the pipes 7 GENERATOR selector MAIN 8 SOURCE selector OFF 9 CRASH lever PULL DOWN 10 Inform the maintenance department ...

Page 93: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 3 12 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 94: ...ATING HANDBOOK Page 3 4 1 Rev 7 3 4 AIR START AIR START ENVELOPE AIR START ENVELOPE Air start may be attempted outside of the envelope However above 20000 ft or with Ng 13 ITT tends to increase during start and prudence is recommended Figure 3 4 1 AIR START ENVELOPE ...

Page 95: ...N IGNITION IS NOT AVAILABLE IF THE ESS BUS TIE SWITCH IS KEPT EMER 1 BLEED switch OFF CAUTION BLEED SWITCH ON MAY CAUSE OVERTEMPERATURE OR ABNORMAL ACCELERATION 2 AIR COND switch OFF 3 Air start envelope CHECKED 4 Electric consumption REDUCE 5 Power lever IDLE 6 Propeller governor lever FEATHER 7 Condition lever CUT OFF 8 Tank selector CHECK 9 AUX BP fuel switch ON 10 IGNITION switch AUTO or ON 11...

Page 96: ...g μ 50 steady STARTER OFF IGNITION AUTO 15 Condition lever HI IDLE 16 Propeller governor lever MAX RPM 17 Power lever AS REQUIRED 18 Electrical equipment AS REQUIRED 19 AUX BP fuel switch AUTO 20 BLEED switch AS REQUIRED CAUTION WITH THE EFS 40 DISPLAYS ARE MOMENTARILY LOST DURING STARTER OPERATION CAUTION WITH ALTIMETERS AM250 if installed ALTITUDE INFORMATION IS MOMENTARILY CUT OFF DURING STARTE...

Page 97: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 4 4 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 98: ...2 Condition lever CUT OFF 3 BLEED switch OFF 4 AIR COND switch OFF 5 Brakes AS REQUIRED 6 Tank selector OFF 7 Warn ground assistance if necessary 8 CRASH lever PULL DOWN 9 EVACUATE as soon as possible CABIN FIRE ON GROUND 1 Power lever IDLE 2 Condition lever CUT OFF 3 Brakes AS REQUIRED 4 Warn ground assistance if necessary 5 CRASH lever PULL DOWN 6 Cabin extinguisher AS REQUIRED 7 EVACUATE as soo...

Page 99: ...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 switch OFF 7 AIR COND switch OFF 8 In case of high altitude above 12000 ft undertake an EMERGENCY DESCENT Refer to Chapter 3 6 9 Perform a FORCED LANDING ENGINE CUT OFF Refer to Chapter 3 7 WARNING AFTER ENGINE FIRE DO NOT ATTEMPT AN AIR START ...

Page 100: ...ding circuit breaker PULL Descend quickly below 12000 ft 3 Using the on board extinguisher EXTINGUISH fire if necessary 4 Smoke elimination if necessary UNDERTAKE PROCEDURE Refer to this chapter 5 LAND as soon as possible If the origin is unknown 1 Oxygen and goggles if installed USE AS REQUIRED pilot and passengers 2 AIR COND switch OFF 3 Non essential equipment OFF 4 Smoke elimination if necessa...

Page 101: ...h the on board extinguisher 8 All pull off type circuit breakers PULL 9 All electrical equipment CUT OFF 10 SOURCE selector BAT 11 GENERATOR selector MAIN 12 Necessary circuit breakers ENGAGE one after the other checking for possible fire or smoke 13 Necessary electrical equipment ON one after the other checking for possible fire or smoke 14 Defective equipment Corresponding circuit breaker PULL 1...

Page 102: ...origin IDENTIFY 2 Oxygen and goggles if installed USE AS REQUIRED pilot and passengers 3 If smoke persists undertake an EMERGENCY DESCENT Refer to Chapter 3 6 4 BLEED switch OFF 5 AIR COND switch OFF 6 DUMP control ACTUATE Wait until the differential pressure drops 7 RAM AIR control knob PULL If smoke increases PUSH 8 LAND as soon as possible ...

Page 103: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES D G A C Approved Page 3 5 6 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 104: ... descent rate if necessary The factors to be considered are Cabin altitude and oxygen duration Electrical power endurance Distance to appropriate landing area Flight conditions IMC VMC ICING Minimum safe altitude Fuel reserves 2 Engine failure aircraft flown for maximum range The pilot is in charge of evaluating the situation and priorities Figure 3 6 1 EMERGENCY DESCENT PROFILES ...

Page 105: ...ller governor lever MAX RPM Procedure in smooth air 4 Flaps UP 5 Landing gear UP 6 Speed VMO 266 KIAS Procedure in rough air or in case of structure problem 7 Reduce speed IAS 178 KIAS 8 Landing gear DN 9 Flaps UP 10 Keep IAS 178 KIAS MAXIMUM RANGE DESCENT 1 3 1 Power lever IDLE 2 Propeller governor lever FEATHER 3 Condition lever CUT OFF 4 Flaps UP 5 Landing gear UP 6 Speed IAS 120 KIAS ...

Page 106: ...e switch Cover up EMER position 11 Prepare a forced landing Refer to Chapter 3 7 If flight conditions do not allow 12 ESS BUS TIE reverse switch NORMAL 13 Manually disconnect ancillary systems as follows AIRFRAME DE ICE switch OFF ICE LIGHT switch OFF PROP DE ICE switch OFF R WINDSHIELD switch OFF PITOT 2 STALL HTR switch OFF L LDG TAXI R LDG PULSE SYST switches OFF STROBE switch OFF BLEED AIR CON...

Page 107: ... GYRO INST panel all switches OFF Transponder 2 OFF If icing conditions PITOT 1 HTR switch Checked ON L WINDSHIELD switch ON Maintain minimum recommended speeds Chapter 4 5 Flight into known icing conditions Paragraph Ice protection procedures Point 3 If time permits RADIO FAN breaker PULLED 28 VDC PLUGS breaker PULLED AIR COND breaker PULLED 14 Prepare a forced landing Refer to Chapter 3 7 ...

Page 108: ...UX BP fuel switch OFF 6 BLEED switch OFF 7 AIR COND switch OFF 8 DUMP switch ACTUATED 9 Glide speed 120 KIAS maintained until favourable ground approach If ground allows it 10 ESS BUS TIE reverse switch NORMAL in order to have GEAR and FLAPS available 11 Landing gear DN If night conditions 12 L LDG R LDG ON If ground does not allow it 13 Keep landing gear UP 14 When chosen ground is assured FLAPS ...

Page 109: ...EDURES EASA Approved Page 3 7 2 Rev 7 3 7 EMERGENCY LANDINGS TIRE BLOWOUT DURING LANDING 1 Control direction with brakes and nose wheel steering 2 REVERSE AS REQUIRED 3 Stop airplane to minimize damages 4 Perform engine SHUT DOWN procedure Refer to Chapter 4 3 ...

Page 110: ...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 headwind or crosswind blowing from defective gear side 6 Align the airplane to land on the runway edge opposite to the defective landing gear 7 Land and set nose gear immediately on ground to assure lateral control 8 Use ...

Page 111: ... 7 3 7 EMERGENCY LANDINGS LANDING WITH UNLOCKED MAIN LANDING GEAR 2 2 11 Condition lever CUT OFF 12 Engine stop procedure COMPLETE 13 EVACUATE If landing gear drags during landing 14 Condition lever CUT OFF 15 CRASH lever PULL DOWN 16 Tank selector OFF 17 EVACUATE after airplane comes to a stop ...

Page 112: ...N Refer to Supplement 41 for TBM 700C2 airplane 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 governor lever FEATHER 6 Touch down slowly with nose wheel and keep elevator at nose up stop 7 Moderate braking 8 CRASH lever PULL DOWN 9 EVACUATE after airplane comes to a stop ...

Page 113: ...to Supplement 41 for TBM 700C2 airplane 1 Final approach Standard Flaps LDG IAS 80 KIAS 2 BLEED switch OFF 3 DUMP switch ACTUATED When runway is assured 4 Power lever IDLE 5 Propeller governor lever FEATHER 6 Condition lever CUT OFF 7 Tank selector OFF 8 Flare out 9 After touch down CRASH lever PULL DOWN 10 EVACUATE after airplane comes to a stop ...

Page 114: ...ING WITHOUT ELEVATOR CONTROL 1 Configuration LANDING GEAR DN FLAPS LDG 2 Airspeed Maintain IAS 95 KIAS 3 Power as necessary to maintain airspeed according to an easy approach slope 300 ft min 4 Adjust elevator by using manual pitch trim wheel 5 When ground approaches decrease slope progressively 6 Reduce power progressively ...

Page 115: ...or flaps deflections from UP to TO position Proceed as for a normal landing maintaining approach airspeed Weight 6250 lbs 2835 kg IAS 100 KIAS Provide for a landing distance increased up to about 60 For flaps deflections greater than TO position Proceed as for a normal landing maintaining approach airspeed Weight 6250 lbs 2835 kg IAS 95 KIAS Provide for a landing distance increased up to about 50 ...

Page 116: ... Landing gear UP In heavy swell with light wind land parallel to the swell rollers In heavy wind land facing wind 2 Flaps LDG 3 Maintain a descent rate as low as possible when approaching the water 4 Airspeed IAS 80 KIAS 5 BLEED switch OFF 6 DUMP switch ACTUATED 7 CRASH lever PULL DOWN 8 Maintain attitude without rounding off until touch down 9 EVACUATE through EMERGENCY EXIT ...

Page 117: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 7 10 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 118: ...AUX BP fuel switch AUTO CHECK CORRECT If alarm persists 5 AUX BP fuel switch ON Warning light AUX BP 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 pump operation and if warning FUEL PRESS remains on 8 Tank switching PERFORM If pressure is normal a...

Page 119: ... 2 Rev 7 3 8 FUEL SYSTEM RED WARNING LIGHT FUEL PRESS ON 2 2 If pressure remains at 0 and if warning FUEL PRESS remains on 9 Selection of the fullest tank PERFORM 10 Avoid high power and rapid movements of the power lever 11 Descend to an altitude below 20000 ft 12 Land as soon as possible ...

Page 120: ... AUX BP 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 BP ON warning light goes out continue flight normally If AUX BP ON warning light remains on mechanical booster pump has failed In that case 3 AUX BP fuel switch ON 4 Shorten flight ...

Page 121: ...sponding tank 1 Corresponding gage CHECK 2 Check the other tank has been automatically selected If not 3 FUEL SEL switch MAN 4 Select tanks manually as required AMBER WARNING LIGHT AUTO SEL ON Indicates that the mode control automatic timer is off or has failed 1 FUEL SEL switch AUTO CHECK CORRECT 2 If it is on AUTO confirmed failure 3 FUEL SEL switch MAN 4 Select tanks manually as required ...

Page 122: ...SIBLE REMARK In case of subsequent electrical generator failure the battery can be used again by selecting 4 GENERATOR selector OFF WARNING LIGHT MAIN GEN ON 5 SOURCE selector BAT 6 Refer to paragraph AMBER WARNING LIGHT LO VOLT ON functioning on ST BY GENERATOR after MAIN GEN failure AMBER WARNING LIGHT BAT OFF ON Indicates that SOURCE selector has been positioned on OFF or GPU or that the batter...

Page 123: ...AIN GEN switching confirmed 3 MAIN GENERATOR RESET push button PUSH In case of failure 4 Disconnect following ancillary electrical systems AIR COND switch OFF STROBE switch OFF NAV switch OFF CABIN lights switch OFF AP TRIMS MASTER switch AP OFF All equipment not essential OFF L WINDSHIELD switch above 15 000 ft OFF R WINDSHIELD switch above 15 000 ft OFF BLEED switch before landing and on ground ...

Page 124: ...battery run down In that case 3 Disconnect following ancillary electrical systems AIR COND switch OFF STROBE switch OFF NAV switch OFF CABIN lights switch OFF AP TRIMS MASTER switch AP OFF All equipment not essential OFF L WINDSHIELD switch above 15 000 ft OFF R WINDSHIELD switch above 15 000 ft OFF BLEED switch before landing and on ground OFF Only use landing lights briefly and if necessary 4 GE...

Page 125: ...ATOR 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 successful 5 GENERATOR selector ST BY 6 ST BY GENERATOR RESET push button PRESS If successful 7 Disconnect ancillary electrical systems not essential 8 Monitor voltmeter and ammeter Prepare to SHORTEN FLIG...

Page 126: ... BUS 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 ESS BUS TIE reverse switch NORMAL If flight conditions do not allow 13 Manually disconnect ancillary systems as follows AIRFRAME DE ICE switch OFF ICE LIGHT switch OFF PROP DE ICE switch OFF R WINDS...

Page 127: ...OFF Stormscope switch OFF CD player OFF INSTR CABIN ACCESS controls OFF GYRO INST panel all switches OFF Transponder 2 OFF If icing conditions PITOT 1 HTR switch Checked ON L WINDSHIELD switch ON Maintain minimum recommended speeds Chapter 4 5 Flight into known icing conditions Paragraph Ice protection procedures Point 3 If time permits RADIO FAN breaker PULLED 28 VDC PLUGS breaker PULLED AIR COND...

Page 128: ...SECTION 3 EMERGENCY PROCEDURES EASA Approved TBM 700 PILOT S OPERATING HANDBOOK Page 3 9 7 Rev 7 Figure 3 9 1 1 2 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 129: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 9 8 Rev 7 Figure 3 9 1 2 2 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 130: ...mpossibility of energizing the radionavigation equipment 1 RADIO FAN circuit breaker PULL Circuit breaker panel L H or R H if pilot door installed lower corner The radionavigation equipment are supplied again and the flight can continue However the equipment forced ventilation is no longer available An excessive use of VHF COM transmitters may reduce their power so that transmission range will be ...

Page 131: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 9 10 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 132: ...er 3 6 If cabin altitude 10000 ft 4 Oxygen Refer to Chapter 3 13 5 BLEED switch CHECK ON 6 DUMP switch CHECK UNDER GUARD 7 RAM AIR control knob CHECK PUSHED 8 Limit flight altitude to maintain cabin altitude 12000 ft 9 If necessary EMERGENCY DESCENT Refer to Chapter 3 6 CABIN NOT DEPRESSURIZED AFTER LANDING P cabin 0 1 DUMP switch ACTUATED 2 BLEED switch OFF 3 RAM AIR control knob PULLED if necess...

Page 133: ...Indicates an overpressure at air conditioning pack inlet or a malfunction of the pressure stop and regulating valve Normal signal if BLEED switch is OFF 1 If necessary CORRECT 2 If possible reduce power 3 BLEED switch OFF 4 BLEED switch ON 5 If BLEED OFF ON and if necessary EMERGENCY DESCENT refer to Chapter 3 6 or continue flight at an altitude 12000 ft 6 Continue flight ...

Page 134: ...mally this leads to BLEED cutoff and to BLEED OFF amber warning light illumination Should automatic cutoff occur or not 1 If possible reduce power 2 AIR FLOW distributor CABIN 3 CABIN TEMP C selector 15 C 4 BLEED switch OFF 5 As soon as BLEED TEMP OFF BLEED switch ON If BLEED TEMP and BLEED OFF still ON 6 If necessary EMERGENCY DESCENT Refer to Chapter 3 6 or continue flight at an altitude 12000 f...

Page 135: ...door has not been correctly locked On ground check the correct locking as well as the latches position of the access door and if installed of the pilot door During flight 1 Start a slow descent 2 Decrease cabin P by selecting a higher cabin altitude and maximum cabin rate If real failure of one of the doors is noted 3 BLEED switch OFF 4 DUMP switch ACTUATED 5 If necessary undertake an EMERGENCY DE...

Page 136: ...TION AND AIR CONDITIONING AMBER WARNING LIGHT VACUUM LO ON Suction gage indicator CHECK Low vacuum may lead to misfunctioning of leading edge deicing pressurization and gyroscopic vacuum operated instruments MONITOR If necessary fly to an altitude 12000 ft and if possible return to VMC conditions BLEED switch OFF ...

Page 137: ... DEFOG 1 AIR FLOW distributor Set to around a 10 o clock position If moisture continues 2 AIR FLOW distributor HOT 3 L WINDSHIELD switch ON 4 R WINDSHIELD switch ON If there is no improvement and if the flight safety is engaged 5 Altitude 12000 ft 6 BLEED switch OFF NOTE If in flight the cabin will quickly be depressurized Therefore the cabin vertical speed indicator and altimeter indications will...

Page 138: ... green light s ON Actions Refer to EMERGENCY GEAR EXTENSION B Symptoms Red warning light flashing and 3 green lights OFF Actions 1 LDG GR 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 breaker for the landing gear extension If the red warning light beco...

Page 139: ...v 7 3 11 LANDING GEAR AND FLAPS LANDING GEAR EXTENSION DISCREPANCY NOTE Symptoms have to be considered at the end of the sequence Symptoms Steady red warning light ON and 0 to 3 green light s OFF or Red warning light flashing and 0 to 3 green light s OFF Actions Refer to EMERGENCY GEAR EXTENSION ...

Page 140: ...CYCLES IT IS MANDATORY TO HAVE A CLEAR HARDENING OF THE MANUAL CONTROL AT THE END OF THE MANEUVER 5 Hand pump ACTUATE with maximum amplitude If landing gear is down and locked red light not illuminated three green lights illuminated Continue flight if necessary at a speed BELOW 178 KIAS exit and or remain outside icing conditions Land CAUTION DO NOT ENTER ICING CONDITIONS THIS COULD ADVERSELY INCR...

Page 141: ...r more green indicator light s does do not illuminate and upon pressing CHECK DN then a gear unlock condition is confirmed Recycle the landing gear as follows 9 By pass selector UNLOCK PUSH 10 Wait a minute 11 Landing gear control IAS 128 KIAS UP Perform landing gear extension attempts in the NORMAL mode while applying positive load factors during the maneuver as well as skidding In case of failur...

Page 142: ...ections between UP and TO positions IAS 122 KIAS for deflections greater than TO position 4 For landing refer to Chapter 3 7 Paragraph LANDING WITH FLAPS MALFUNCTION FLAPS MALFUNCTION In case of blockage of flaps or inoperant flap control lever between UP and TO positions with no flaps warning light illumination 1 FLAPS circuit breaker PULL 2 Flap control lever UP 3 SHORTEN flight maintaining airs...

Page 143: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 11 6 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 144: ...ing outboard sections Or ice on wing inboard sections and stabilizers One of the two cycling green lights is not lit 1 LEAVE icing conditions as soon as possible 2 AIRFRAME DE ICE switch OFF PROPELLER DEICING FAILURE Symptoms Propeller deicing green light is not lit Propeller vibrations 1 REDUCE power 2 ACTUATE propeller governor lever to vary RPM within operating range 3 LEAVE icing conditions as...

Page 145: ... maneuver LEAVE icing conditions as soon as possible WINDSHIELD DEICING FAILURE Symptoms Windshield being covered uniformly by ice No perception of heat when touching deiced section Windshield deicing green light is not lit Symptoms may result from overheat In that case 1 L WINDSHIELD switch OFF ON when necessary 2 R WINDSHIELD switch OFF ON when necessary In case of total failure 1 CABIN TEMP C s...

Page 146: ...ition 2 AIR FLOW distributor Set to 10 o clock position 3 L WINDSHIELD switch ON 4 R WINDSHIELD switch ON If not successful to gain sufficient visibility 5 AIR FLOW distributor HOT 6 Manually clean a sufficient visibility area 7 If necessary clean L H side window and conduct a sideslip approach rudder pedals to the right in order to get sufficient landing visual references 8 Maintain IAS 90 KIAS C...

Page 147: ...he airspeed indicator 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 VMO overshoot warning may be altered by icing conditions Monitor maximum airspeed 266 KIAS Correct operation of the aural stall warning may be altered by severe or prolonged icing MONITOR and MAINTAIN minimum airspeed acco...

Page 148: ...ch trim may be used manually 5 Reduce airspeed if necessary to reduce control forces If pitch trim runaway 6 AP TRIMS MASTER switch AP OFF The pitch trim may be used manually the two other trim tabs may be used again electrically If rudder or aileron trim runaway 7 PULL circuit breaker corresponding to the defective trim tab 8 AP TRIMS MASTER switch ON Two other trim tabs may be used again electri...

Page 149: ...ll emergency exit assembly toward oneself to release it from its recess 4 Put the emergency exit door inside fuselage or throw it away from the fuselage through the opening 5 EVACUATE airplane EMERGENCY BEACON USE ELT Before a forced landing 1 On COM VHF 121 5 MHZ or on a known air traffic control frequency transmit the MAY DAY signal if possible After landing 2 ELT remote control switch ON mainta...

Page 150: ...ures 2 Apply air traffic control procedures in case of communications failure code 7700 during 1 minute then code 7600 3 Try to restore communications by using all possible combinations of the headset micro and loudspeaker MAIN GYRO HEADING FAILURE Use standby compass CAUTION L WINDSHIELD AND R WINDSHIELD SWITCHES AS WELL AS AIR CONDITIONING SYSTEM MUST BE SET TO OFF BEFORE COMPASS READING ...

Page 151: ...onder mode selector ON or ALT 2 Codes selector 7700 EMERGENCY DISTRESS 7600 COMMUNICATIONS FAILURE 7500 HIJACKING 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 Power lever IDLE 4 Flaps UP when rotation is stopped 5 Level the wings and ease out of the dive ...

Page 152: ...ide draw it out of the stowage cup and uncoil tube totally Press on the red side vanes to inflate the harness Put the mask on the face 2 No smokes 3 position selector NORMAL 100 as required 3 In case of smokes 3 position selector EMERGENCY Don the smoke goggles onto the face 4 PASSENGERS OXYGEN switch ON 5 Check the oxygen flow indicator for the front seats the blinker is transparent and for the r...

Page 153: ...K 700 SECTION 3 EMERGENCY PROCEDURES EASA Approved Page 3 13 6 Rev 7 3 13 MISCELLANEOUS OXYGEN USE 2 2 Passengers 1 Take a mask 2 Uncoil tube totally 3 Pull on the lanyard cord to take out the lanyard pin 4 Put the mask on the face ...

Page 154: ...G SYSTEM FAILURE Symptoms erroneous indication in flight 1 PITOT 1 HTR switch CHECK ON 2 PITOT 2 STALL HTR switch CHECK ON If symptoms persist 3 ALTERNATE STATIC selector PULL THROROUGHLY If symptoms persist as well as on the airspeed indicator of the R H instrument panel carry out a precautionary approach maintaining an adequate speed ...

Page 155: ... Inform Air Traffic Control to exit severe icing conditions by changing the route or the altitude 2 Avoid any sudden maneuver on flight controls 3 Do not engage the autopilot 4 If the autopilot is engaged hold the control wheel firmly and disengage the autopilot 5 If an unusual roll response or uncommanded roll control movement is observed reduce the angle of attack 6 Do not extend flaps when hold...

Page 156: ... EXTERNAL POWER GPU 4 3 21 MOTORING 4 3 26 MOTORING FOLLOWED BY AN ENGINE START 4 3 28 AFTER STARTING ENGINE 4 3 30 IN FLIGHT AVAILABLE OXYGEN QUANTITY 4 3 32 TAXIING 4 3 33 BEFORE TAKEOFF 4 3 34 TAKEOFF 4 3 36 CLIMB 4 3 38 CRUISE 4 3 39 DESCENT 4 3 40 BEFORE LANDING 4 3 41 LANDING 4 3 42 GO AROUND 4 3 43 TOUCH AND GO 4 3 44 AFTER LANDING 4 3 44 SHUT DOWN 4 3 45 4 4 AMPLIFIED PROCEDURES 4 4 1 PREF...

Page 157: ...G 4 4 64 SHUT DOWN 4 4 65 4 5 PARTICULAR PROCEDURES 4 5 1 FLIGHT INTO KNOWN ICING CONDITIONS 4 5 1 FLIGHT INTO SEVERE ICING CONDITIONS 4 5 6 FLIGHT UNDER HEAVY PRECIPITATIONS 4 5 8 UTILIZATION ON RUNWAYS COVERED WITH WATER 4 5 8 UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW 4 5 9 UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS 4 5 11 UTILIZATION BY COLD WEATHER 0 C to 25 C ...

Page 158: ...cedures for the conduct of normal operation of TBM 700 airplane The first part of this Section lists the normal procedures required as a check list The amplified procedures are developed in the second part of the Section The normal procedures for optional systems are given in Section 9 Supplements of the Pilot s Operating Handbook ...

Page 159: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 4 NORMAL PROCEDURES EASA Approved Page 4 1 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 160: ... Takeoff distances 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 gear down 178 KIAS 6 Maximum landing gear operating speed Extension 178 KIAS Retraction 128 KIAS 7 Approach speed Flaps LDG 80 KIAS 8 Maximum operating speed VMO 266 KIAS 9 Glide speed...

Page 161: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 4 NORMAL PROCEDURES EASA Approved Page 4 2 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 162: ...l surfaces In case of night flight check good operation of all navigation lights landing lights strobe lights and make sure that an emergency lamp is on board If icing conditions are foreseen particularly check good functioning of all electrical and pneumatic ice protection systems Check that type and quantity of fuel used for refueling are correct Remove covers on pitots 2 static ports 3 engine a...

Page 163: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 4 NORMAL PROCEDURES EASA Approved Page 4 3 2 Rev 7 CHECK LIST PROCEDURES PREFLIGHT INSPECTION Cont d Figure 4 3 1 PREFLIGHT INSPECTION ...

Page 164: ...elector OFF GENERATOR selector MAIN 2 ENGINE START panel IGNITION switch AUTO or OFF STARTER switch OFF 3 EXT LIGHTS panel All switches OFF 4 GYRO INST panel All switches OFF 5 Breakers panel All breakers ENGAGED 6 DE ICE SYSTEM panel All switches OFF 7 Landing gear control DN 8 Landing gear emergency control Lever PULLED DOWN By pass selector PUSHED Door IN PLACE 9 AP TRIMS MASTER switch OFF 10 R...

Page 165: ...HED 13 Fuel FUEL SEL selector MAN AUX BP switch OFF Tank selector L or R 14 ELT ARM 15 Flight control lock REMOVED STOWED 16 Flight controls Deflections checked 17 Parking brake SET 18 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM C...

Page 166: ... 21 IGNITION switch AUTO or OFF 22 STARTER switch OFF 23 Landing gear control DN 24 SOURCE selector BAT or GPU 25 Voltage CHECK BAT 25 Volts GPU 28 Volts 26 EXT LIGHTS panel LTS TEST push button PRESS 3 green lamps L LDG TAXI R LDG ON L LDG TAXI R LDG switches ON 3 green lamps ON L LDG TAXI R LDG switches OFF 27 Fuel gages Operation quantity CHECK 28 ADVISORY PANEL Test 1 ALL WARNING LIGHTS ON Tes...

Page 167: ...ght ON 32 Flaps LDG 33 Landing gear panel Warning lights 3 GREEN ON Test 1 then 2 RED ON 3 GREEN ON 34 PITOT 1 HTR switch ON WARNING LIGHT PITOT 1 OFF 35 PITOT 2 STALL HTR switch ON WARNING LIGHTS PITOT 2 OFF STALL HTR PITOT 1 HTR switch OFF PITOT 2 STALL HTR switch OFF 36 DE ICE SYSTEM panel LTS TEST push button PRESS All green lights ON WARNING DO NOT TOUCH PITOTS NOR STALL WARNING VANE THEY COU...

Page 168: ...the stall warning horn 38 Reentering the airplane EXT LIGHTS panel ALL SWITCHES OFF DE ICE SYSTEM panel ALL SWITCHES OFF 39 SOURCE selector OFF Cabin II 1 Cabin fire extinguisher CHECK Pressure Attachment 2 Seats belts CHECK 3 Windows CHECK General condition No crack 4 Emergency exit CLOSED LOCKED Anti theft safety REMOVE STOW 5 Baggage compartment STRAPS IN PLACE 6 Partition net IN PLACE 7 Doors ...

Page 169: ...eflection 3 Trailing edge static discharger CHECK Condition Attachment 4 Wing tip nav lights Strobe landing light Condition CHECK 5 OAT probe Condition CHECK 6 Fuel tank CAP CLOSED LOCKED 7 Fuel tank air vent Unobstructed CHECK 8 External pitot IAS Condition CHECK 9 Internal pitot VMO Condition CHECK 10 Wing lower surface CHECK No leak 11 Wing deicer boots CHECK Condition Attachment 12 Fuel tank d...

Page 170: ...ide CONTROLLED Door CLOSED 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 cowls OPEN For the first flight of the day Oil cap CLOSED LOCKED Engine oil level CHECK Fuel pipes CHECK No leak deterioration wear 6 Engine cowls Condition CHECK CLOSED LOCKED...

Page 171: ...ub CHECK Condition No cracks R H wing V 1 Fuel tank drain two on each wing DRAIN Fuel free of water and contamination 2 Main landing gear Shock absorber doors tire wheel well CHECK 3 Wing deicer boots CHECK Condition Attachment 4 Stall warning CHECK Condition Deflection 5 Wing lower surface CHECK No leaks 6 Fuel tank CAP CLOSED LOCKED 7 Fuel tank air vent Unobstructed CHECK 8 Wing tip nav light st...

Page 172: ...sure CHECK Fuselage rear section Empennages VI 1 ELT OFF 2 Static pressure ports CLEAN CHECK 3 Ventral fins 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 Deflection free movement Trim position 7 Static dischargers CHECK Condition 8 Vertical stabilizer...

Page 173: ...EDURES EASA Approved Page 4 3 12 Rev 7 CHECK LIST PROCEDURES PREFLIGHT INSPECTION Cont d 10 Static dischargers CHECK Condition 11 Tail cone Condition CHECK 12 Static pressure ports Clean CHECK 13 Rear baggage compartment Inside CONTROLLED Door CLOSED LOCKED ...

Page 174: ...eflight inspection COMPLETED 2 Cabin access door CLOSED LOCKED 3 Pilot door if installed CLOSED LOCKED 4 Baggage STOWED 5 Parking brake SET 6 Weight and balance COMPUTED CHECKED 7 Seats Pilot ADJUSTED R H front station If not occupied by a second pilot adjust seat so as not to hinder full travel of flight controls If the airplane is equipped with option OPT70 01029 Provision for TBM 700C2 Pilot se...

Page 175: ...N switch ON 13 PASSENGERS OXYGEN switch OFF 14 Copilot and pilot masks Press push button PRESS TO TEST the blinker shall turn red momentarily then turns transparent 15 NORMAL MASK micro inverter NORMAL 16 IGNITION switch AUTO or OFF 17 STARTER switch OFF 18 Landing gear control DN 19 RADIO MASTER switch ON 20 RADIO VHF1 ON ADJUSTED 21 Authorization for engine starting ASKED 22 ETM Fuel remaining C...

Page 176: ...selector L or R CHECKED FUEL SEL switch AUTO WARNING LIGHT AUTO SEL OFF SHIFT push button PRESS The selector changes tank On ground observe a tank change every minute and 15 seconds 28 ETM fuel flowmeter totalizer CHECKED ADJUSTED 29 Engine instruments CHECK 30 ITT TEST CARRY OUT 31 EXT LIGHTS panel STROBE AS REQUIRED 32 In case of night flight INT LIGHTS panel INSTR PANEL ADJUSTED Navigation ligh...

Page 177: ...ITION switch AUTO or OFF 2 STARTER switch OFF 3 INERT SEP switch OFF 4 Landing gear control DN 5 ELECTRIC POWER panel SOURCE selector BAT Voltage CHECKED 25 Volts 6 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT O...

Page 178: ...sure indicator Green sector 8 Propeller AREA CLEAR 9 ENGINE START panel IGNITION switch AUTO STARTER switch ON STARTER FLASHING IGNITION ON NOTE The utilization of the starter is bound by limitations mentioned in Chapter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING LIGHT OIL PRES...

Page 179: ... WARNING LIGHT MAIN GEN OFF RESET if necessary Battery ammeter CHARGE CHECKED Battery voltage CHECKED V 28 Volts CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO LO IDLE THERE IS NO IGNITION OR IF DURING IGNITION SEQUENCE OVERTEMPERATURE INDICATION APPEARS MAX ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNI...

Page 180: ...E Condition lever CUT OFF IGNITION switch OFF or AUTO STARTER switch OFF WAIT FOR 1 MINUTE Refer to Chapter 2 4 STARTER OPERATION LIMITS THEN TRY TO RESTART ENGINE START panel IGNITION switch AUTO STARTER switch ON STARTER FLASHING IGNITION ON Ng 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING LIGHT OIL PRESS OFF ...

Page 181: ... PROCEDURES STARTING ENGINE USING AIRPLANE POWER 5 5 Ng 50 STARTER switch OFF STARTER IGNITION Engine instruments CHECK Ng increasing to 68 1 Oil pressure ITT green sector NOTE This behaviour should only be observed with outside low temperature IOAT 0 C cold engine This procedure may be used for the first starting of the day ...

Page 182: ...itch AUTO or OFF 3 STARTER switch OFF 4 INERT SEP switch OFF 5 Landing gear control DN 6 SOURCE selector GPU WARNING LIGHT GPU ON WARNING LIGHT BAT OFF ON Voltmeter VOLTAGE CHECKED V 28 Volts 7 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever ...

Page 183: ...SS OFF Fuel pressure indicator CHECK 9 Propeller AREA CLEAR 10 ENGINE START panel IGNITION switch AUTO STARTER switch ON STARTER FLASHING IGNITION ON NOTE The utilization of the starter is bound by limitations mentioned in Chapter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING LIGH...

Page 184: ... Propeller governor lever FEATHER 13 GPU HAVE IT DISCONNECTED WARNING LIGHT GPU OFF 14 Condition lever HI IDLE 15 Propeller governor lever MAX RPM 16 Engine instruments CHECK Ng 68 1 Oil pressure Oil temperature ITT green sector 17 FUEL panel AUX BP switch AUTO WARNING LIGHT AUX BP ON OFF 18 Generator WARNING LIGHT MAIN GEN OFF RESET if necessary Battery ammeter CHARGE CHECKED Battery voltage CHEC...

Page 185: ...RE INDICATION APPEARS MAX ITT 870 C FOR MORE THAN 20 SECONDS 1000 C FOR MORE THAN 5 SECONDS INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or AUTO Wait ITT 800 C then STARTER switch OFF BEFORE ANY RESTARTING ATTEMPT CARRY OUT A MOTORING Refer to paragraph MOTORING CAUTION IF ENGINE STAGNATES INTERRUPT STARTING PROCEDURE Condition lever CUT OFF IGNITION switch OFF or AUTO ...

Page 186: ... IGNITION ON Ng 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING LIGHT OIL PRESS OFF Ng 50 STARTER switch OFF STARTER IGNITION Engine instruments CHECK Ng increasing to 68 1 Oil pressure ITT green sector NOTE This behaviour should only be observed with outside low temperature IOAT 0 C cold engine This procedure may...

Page 187: ...OTAL 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 THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON WARNING LIGHTS AUX BP ON ON FUEL PRESS OFF ...

Page 188: ...ION OFF To clear fuel and vapor internally trapped 4 STARTER switch ON during 15 sec maxi WARNING LIGHT STARTER FLASHING To cool engine following shut down in high temperature environment 4 STARTER switch ON during 30 sec WARNING LIGHT STARTER FLASHING 5 STARTER switch OFF WARNING LIGHT STARTER OFF 6 FUEL panel AUX BP switch OFF WARNING LIGHTS AUX BP ON OFF FUEL PRESS ON ...

Page 189: ...procedure 1 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 2 Fuel Tank selector L or R AUX BP switch ON WARNING LIGHTS AUX BP ON ON FUEL PRESS OFF 3 IGNITION switch OFF 4 STARTER switch ON during 15 sec 5 Afte...

Page 190: ...ds max Ng Oil pressure WARNING LIGHT OIL PRESS OFF Ng 50 stable STARTER switch OFF STARTER IGNITION 7 Engine instruments CHECK Ng 52 Oil pressure ITT green sector 8 Condition lever HI IDLE 9 Engine instruments CHECK Ng 68 1 Oil pressure Oil temperature ITT green sector 10 FUEL panel AUX BP switch AUTO WARNING LIGHT AUX BP ON OFF 11 Generator WARNING LIGHT MAIN GEN OFF RESET if necessary Battery am...

Page 191: ...ON Check illumination of the green light located above the switch PROP DE ICE switch OFF L WINDSHIELD switch ON R WINDSHIELD switch ON Check illumination of the green light located above the switch except if hot conditions L WINDSHIELD switch OFF R WINDSHIELD switch OFF Increase power so as to get Ng 80 to check AIRFRAME DE ICE AIRFRAME DE ICE switch ON Visually check functioning of deicer boots d...

Page 192: ...tch As required AIR COND switch ON CABIN TEMP C selector ADJUST AIR FLOW distributor AS REQUIRED Cabin altitude selector Airfield altitude 500 feet Cabin rate selector ARROW UPWARDS at the halfway post 8 RADIO MASTER switch ON VHF VOR GPS TAS EGPWS WX means if installed ADJUSTED TESTED 9 EFIS MASTER switch ON TEST CMPST button PRESS TST REF button PRESS at least 3 seconds 10 AP TRIMS MASTER switch...

Page 193: ...erature IOAT Read 1 Determine the usable oxygen percent using the chart Figure 4 3 2 Figure 4 3 2 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 4 3 3 by the percent obtained with the chart Figure 4 3 2 Number of passen gers Duration Passengers plus 1 pilot Duration Passengers plus 2 pilots 0 226 113 1 162 94 2 127 81 3 104 71 4 88 65 Figure 4 3 3 ...

Page 194: ...t ON 2 INERT SEP switch CHECKED ON CHECK WARNING LIGHT INERT SEP ON 3 Passenger briefing AS REQUIRED 4 Parking brake RELEASED WARNING LIGHT PARK BRAKE OFF 5 L H and R H seats brakes CHECKED 6 Nose wheel steering CHECKED 7 Power lever AS REQUIRED CAUTION AVOID USING REVERSE DURING TAXIING 8 Flight instruments CHECK 9 Advisory panel CHECK ...

Page 195: ...AX RPM 4 Fuel Gages CHECK Quantity Symmetry FUEL SEL CHECK AUTO AUX BP CHECK AUTO 5 Flaps TO 6 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 LIGHT INERT SEP OFF If there is standing water or other contamination on the runway INERT SEP switch Leave ON WARNING LIGHT INERT SEP ...

Page 196: ... All warning lights OFF except PARK BRAKE ON and if used INERT SEP ON 8 Electronic equipment Flight instruments Radar CHECK ADJUST 9 Engine instruments CHECK 10 Pilot s Passengers belts CHECK 11 Flight controls DEFLECTIONS CHECKED 12 Trims Pitch ADJUSTED Yaw ADJUSTED Roll ADJUSTED 13 Parking brake RELEASED WARNING LIGHT PARK BRAKE OFF 14 STROBE switch ON CAUTION DO NOT TAKE OFF IF BATTERY CHARGE 5...

Page 197: ...TION TURN IGNITION AND INERT SEP ON IF ICING CONDITIONS ARE FORESEEN REFER TO CHAPTER 4 5 PARAGRAPH FLIGHT INTO KNOWN ICING CONDITIONS 1 Heading HSI Stand by compass CHECK Altimeter setting CHECK 2 Horizon Attitude 2 CHECK 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ITT green sector 5 Advisory panel CHECK All warning lights OFF except INERT SEP if used except IGNITION if used 6 Radar s...

Page 198: ...ller RPM increases by a minimum of 50 RPM when compared to minimum value during PROP O SPEED test 8 Brakes RELEASED 9 Power lever TRQ 100 10 Takeoff ROTATION See Takeoff distances Chapter 5 8 Normal takeoff ATTITUDE 7 5 Short takeoff ATTITUDE 15 11 Vertical speed indicator POSITIVE 12 Brakes APPLY Briefly 13 Landing gear control IAS 128 KIAS UP At sequence end check All warning lights OFF 14 Light...

Page 199: ...ITT T AND OIL PRESSURE LIMITATIONS AND OR REFER TO TABLES IN CHAPTER 5 7 2 Climb speed AS REQUIRED 3 ECS panel Cabin altitude selector Cruise altitude 1000 feet Cabin rate selector ADJUST Pressurization CHECK CABIN TEMP C selector ADJUST 4 Fuel tank gages CHECK CORRECT Quantity Symmetry 5 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNIT...

Page 200: ...REFER TO TABLES IN CHAPTER 5 7 2 Pressurization CHECK 3 Fuel Gages CHECK REGULARLY CHECK consumption Pre MOD70 0402 28 tank automatic change every 10 minutes Post MOD70 0402 28 tank automatic change every 5 minutes All symmetry max dissymmetry 25 us gal 95 Litres 4 ETM When the cruise parameters are fully established RECORD Push 5 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURE...

Page 201: ...tude selector Airfield altitude 500 feet Cabin rate selector Adjusted 3 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNITION AND INERT SEP ON 4 Windshield misting protection system As required 5 Fuel Gages CHECK Quantity Symmetry Fullest tank SELECT 6 Passengers briefing As required 7 Seats belts and harnesses LOCKED ...

Page 202: ... Altimeters 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 Green indicator lights ON 6 Flaps IAS 178 KIAS TO 7 Lights L LDG TAXI R LDG ON 8 Autopilot OFF 9 Radar switch SBY Short final 10 Flaps IAS 122 KIAS LDG 11 Approach speed Flaps LDG 80 KIAS 12 YAW DAMPER push button OFF ...

Page 203: ... Reverse may be applied as soon as the wheels touch the ground To avoid ingestion of foreign objects come out the reverse as speed reduces and use the brakes if necessary for further deceleration CAUTION USE OF CONTROL REVERSE BETA β RANGE BEHIND THE FLIGHT IDLE POSITION IS PROHIBITED DURING FLIGHT CAUTION ON SNOWY OR DIRTY RUNWAY IT IS BETTER NOT TO USE REVERSE 3 Brakes As required ...

Page 204: ...OCEDURES GO AROUND Refer to Supplement 41 for TBM 700C2 airplane 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 KIAS 3 Landing gear control UP All warning lights OFF If IAS is at or above 110 KIAS 4 Flaps UP 5 Climb speed AS REQUIRED ...

Page 205: ...off distances Chapter 5 8 Normal takeoff ATTITUDE 7 5 Short takeoff ATTITUDE 15 AFTER LANDING RUNWAY CLEAR AIRPLANE STOPPED 1 DE ICE SYSTEM panel AIRFRAME DE ICE switch OFF PROP DE ICE switch OFF INERT SEP switch CHECKED ON L WINDSHIELD switch As required R WINDSHIELD switch As required PITOT 1 HTR switch OFF PITOT 2 STALL HTR switch OFF BLEED switch As required 2 Radar switch CHECKED SBY 3 Transp...

Page 206: ...heck for cabin depressurization 4 FAN FLOW switch As required 5 AIR COND switch OFF 6 Condition lever HI IDLE 7 Power lever IDLE for 2 minutes 8 GYRO INST panel All switches OFF 9 EFIS MASTER switch OFF 10 AP TRIMS MASTER switch OFF 11 RADIO MASTER switch OFF 12 Propeller governor lever FEATHER for 15 seconds 13 Condition lever CUT OFF CAUTION IN CASE OF SHUT DOWN ON A CONTAMINATED AREA Condition ...

Page 207: ...bin depressurization 4 FAN FLOW switch As required 5 AIR COND switch OFF 6 Condition lever HI IDLE 7 Power lever IDLE for 2 minutes minimum 8 GYRO INST panel All switches OFF 9 EFIS MASTER switch OFF 10 AP TRIMS MASTER switch OFF 11 RADIO MASTER switch OFF 12 Propeller governor lever FEATHER for 15 seconds 13 Condition lever CUT OFF CAUTION IN CASE OF SHUT DOWN ON A CONTAMINATED AREA Condition lev...

Page 208: ...itch MAN Tank selector OFF 15 INERT SEP switch OFF 16 INT LIGHTS panel All switches OFF 17 EXT LIGHTS panel All switches OFF 18 GENERATOR selector OFF 19 SOURCE selector OFF CAUTION IN CASE OF HIGH OAT ABOVE 35 C 95 F IT IS REQUIRED TO PERFORM 30 SECONDS DRY MOTORING RUN AFTER SHUT DOWN TO IMPROVE COOLING OF THE BEARING CAVITIES AND MINIMIZE OIL COKING REFER TO PARAGRAPH MOTORING ...

Page 209: ...N Tank selector OFF 15 INERT SEP switch OFF 16 INT LIGHTS panel All switches OFF 17 EXT LIGHTS panel All switches OFF 18 GENERATOR selector OFF 19 SOURCE selector OFF CAUTION IN CASE OF HIGH OAT ABOVE 35 C 95 F IT IS RECOMMENDED TO PERFORM 30 SECONDS DRY MOTORING RUN AFTER SHUT DOWN TO IMPROVE COOLING OF THE BEARING CAVITIES AND PREVENT OIL COKING REFER TO PARAGRAPH MOTORING ...

Page 210: ...N 2 ENGINE START panel IGNITION switch AUTO or OFF The IGNITION switch is normally selected to AUTO This ensures ignition whenever the STARTER switch is set to ON STARTER switch OFF If not starter is going to operate as soon as SOURCE selector is moved to BAT or GPU if connected 3 EXT LIGHTS panel All switches OFF 4 GYRO INST panel All switches OFF 5 Breakers panel All breakers ENGAGED 6 DE ICE SY...

Page 211: ...op so as to have the door in place 9 AP TRIMS MASTER switch OFF 10 RADIO MASTER switch OFF 11 ECS panel BLEED switch OFF AIR COND switch OFF DUMP switch GUARDED 12 RAM AIR control PUSHED 13 Fuel FUEL SEL selector MAN AUX BP switch OFF Tank selector L or R 14 ELT ARM 15 Flight control lock REMOVED STOWED The flight control lock is normally stowed in the front cargo compartment with the towing bar a...

Page 212: ...s movement into reverse range Trying to force the mechanism will cause damage Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 19 Flaps control UP 20 BAT BUS power supply Stop watch CHECKED Access lighting CHECKED Emergency lighting CHECKED This check allows to ensure that the fuse of the BAT BUS operates correctly CAUTION BEFORE SELECTING SOURCE CHECK 21 ...

Page 213: ...PU ensure that it provides a 28 volt regulated voltage with negative on earth as well as it supplies 800 amperes minimum and 1400 amperes maximum See placard located near ground power receptacle door 26 EXT LIGHTS panel LTS TEST push button PRESS 3 green lamps L LDG TAXI R LDG ON L LDG TAXI R LDG switches ON 3 green lamps ON An outside inspection is not necessary the illuminated three green lamps ...

Page 214: ...low altitude in order to be used in case of smoke in the cabin 30 INT LIGHTS panel CHECK 31 ECS panel LT TEST push button PRESS amber indicator light ON 32 Flaps LDG 33 Landing gear panel Warning lights 3 GREEN ON Test 1 then 2 RED ON 3 GREEN ON Test 1 and 2 correspond to BUS bars 1 or 2 which feed them respectively 34 PITOT 1 HTR switch ON WARNING LIGHT PITOT 1 OFF Correct operation of pitot PITO...

Page 215: ...OT 2 STALL HTR switch OFF 36 DE ICE SYSTEM panel LTS TEST push button PRESS All green lights ON WARNING DO NOT TOUCH PITOTS NOR STALL WARNING VANE THEY COULD BE HOT ENOUGH TO BURN SKIN 37 EXT LIGHTS panel STROBE ON NAV ON ICE LIGHT ON From outside the airplane check operation of all lights and the stall warning horn 38 Reentering the airplane EXT LIGHTS panel ALL SWITCHES OFF DE ICE SYSTEM panel A...

Page 216: ...Cabin fire extinguisher CHECK Pressure Attachment The fire extinguisher is provided with a pressure gage 2 Seats belts 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 IN PLACE 7 Doors operation CHECK 8 Stairs condition CHECK Condition Play ...

Page 217: ... the use of the flight control lock and blanking covers is recommended Propeller should be tied down to prevent rotation without oil pressure When the airplane is stored for extended periods of time a thorough preflight inspection is recommended Particular attention should be paid to possible blockages in airspeed sensing lines foreign objects in engine intake and exhaust stubs and water contamina...

Page 218: ...o lock and unlock them to avoid water infiltration in case of rain on ground and to avoid fuel loss in flight 7 Fuel tank air vent UNOBSTRUCTED CHECK Air vent is not likely to be obstructed by ice or water as it is located in a wing lower surface recess 8 External pitot IAS Condition CHECK 9 Internal pitot VMO Condition CHECK 10 Wing lower surface CHECK Check fuel tank access doors for leaks Check...

Page 219: ...tion 8 for servicing operations relative to fuel additives 13 L H main landing gear Shock absorber doors tire wheel well CHECK If airplane has been used from muddy airfields or in snow check wheel wells to make sure they are clean and not obstructed Check frequently all landing gear retraction mechanism components shock absorbers tires and brakes This is particularly important for airplanes used f...

Page 220: ...nation Filter contamination indicator CHECK Open the inspection door located on L H side under front baggage compartment 4 L H exhaust stub CHECK Condition No crack Inspect if possible pressure port located inside exhaust stub A missing port or a cracked port may hinder correct operation of continuous heating of air inlet lip 5 Upper engine cowls OPEN For the first flight of the day Oil cap CLOSED...

Page 221: ...r and spinner CHECK No nicks cracks or oil leaks Attachment In case of operation from contaminated runways it is necessary to carefully examine propeller blades where traces of abrasion may be found Propeller damage may reduce blade life time and degrade performance Any propeller damage should be referred to maintenance personnel 9 Nose gear Landing light shock absorber doors tire wheel well CHECK...

Page 222: ... absorber doors tire wheel well CHECK 3 Wing deicer boots CHECK Condition Attachment 4 Stall warning CHECK Condition Deflection 5 Wing lower surface CHECK No leaks 6 Fuel tank CAP CLOSED LOCKED 7 Fuel tank air vent Unobstructed CHECK 8 Wing tip nav light strobe landing light Condition CHECK 9 Trailing edge static discharger CHECK Condition Number Attachment 10 Aileron spoiler CHECK Condition Free ...

Page 223: ... Ventral fins are made of two parts one fixed part and one removable part with rear lower inspection door Check that these two parts are connected by the locking roller 4 Inspection door under fuselage CLOSED CHECK Attachments 5 Horizontal stabilizer deicer boots R H side CHECK Condition Attachments 6 Elevator and trim CHECK Condition Deflection free movement Trim position To check the deflection ...

Page 224: ... S OPERATING HANDBOOK Page 4 4 15 Rev 7 AMPLIFIED PROCEDURES PREFLIGHT INSPECTION Cont d 10 Static dischargers CHECK Condition 11 Tail cone Condition CHECK 12 Static pressure ports Clean CHECK 13 Rear baggage compartment Inside CONTROLLED Door CLOSED LOCKED ...

Page 225: ...EMPERATURE OR ABNORMAL ACCELERATION AT START CAUTION MAKE SURE THAT MAN OVRD CONTROL IS OFF TO AVOID OVERTEMPERATURE RISKS AT START 1 Preflight inspection COMPLETED 2 Cabin access door CLOSED LOCKED 3 Pilot door if installed CLOSED LOCKED 4 Baggage STOWED 5 Parking brake SET PARK BRAKE warning light located on advisory panel does not indicate that parking brake is set For that press on brake pedal...

Page 226: ... AND INTERMEDIATE POSITIONS Adjust pilot s and R H front station seats and harnesses so as to permit access to all flight controls The pilot at L H station must be able to easily reach ECS panel 8 R H and L H pedals ADJUSTED 9 Belts and harnesses Pilot and passengers FASTENED Check belt buckles for correct locking as well as automatic locking of shoulder harness by exerting a rapid pull on the lat...

Page 227: ...ED An electric relay automatically cuts off radio equipment during starter operation The function GND CLR ground clearance enables when RADIO MASTER switch is ON to obtain VHF1 supply without having selected battery contact 21 Authorization for engine starting ASKED 22 ETM Fuel remaining Check Added fuel Insert Fuel flow page Select The SHADIN ETM operation normal procedures are described in the O...

Page 228: ...elector L or R CHECKED FUEL SEL switch AUTO WARNING LIGHT AUTO SEL OFF SHIFT push button PRESS The selector changes tank On ground observe a tank change every minute and 15 seconds 28 ETM fuel flowmeter totalizer CHECKED ADJUSTED Total fuel quantity on board may be set on flowmeter totalizer see instructions in Section 7 or refer to manufacturer technical data 29 Engine instruments CHECK 30 ITT TE...

Page 229: ...hen GND CLR ground clearance is available on airplane VHF1 can be operated by setting SOURCE selector to OFF and RADIO MASTER switch to ON A correct operation is provided by the GND CLR green light illuminating above the RADIO MASTER switch If battery voltage is low near 25 volts turn off all unessential electrical equipment before selecting the starter ON By night emergency lighting provided by t...

Page 230: ...OFF 4 Landing gear control DN 5 ELECTRIC POWER panel SOURCE selector BAT Mains voltage CHECKED 25 Volts 6 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT OFF 7 FUEL panel AUX BP switch ON WARNING LIGHT AUX BP ON ON...

Page 231: ...fore having obtained 13 of Ng there is a risk of overtemperature further to an excessive accumulation of fuel inside the combustion chamber before ignition Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max The absolute limit read on the indicator is 1090 C during the starting sequence red triangle However the ITT limits during the starting sequence are 870 C for 20 ...

Page 232: ...onds 1000 C for more than 5 seconds maintaining during few seconds STARTER switch ON within starter operating limits may reduce max ITT obtained by ventilating combustion chamber NOTE No action is required for the following conditions ITT from 800 C to 870 C limited to 20 seconds from 870 C to 1000 C limited to 5 seconds CAUTION IF 10 SECONDS AFTER HAVING POSITIONED CONDITION LEVER TO LO IDLE THER...

Page 233: ...ot exceeded Lengthy operation of the starter results in excessive temperature of the engine If Ng does not reach 30 within 30 seconds after the starter is selected ON abort the start 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 LIGHT OIL PRESS OFF CAUTION IF ENGINE STAGNATES ...

Page 234: ...ARTING ENGINE USING AIRPLANE POWER 5 6 ENGINE START panel IGNITION switch AUTO STARTER switch ON STARTER FLASHING IGNITION ON Ng 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING LIGHT OIL PRESS OFF Ng 50 STARTER switch OFF STARTER IGNITION WARNING LIGHTS ...

Page 235: ...g of the day CONTINUE WITH NORMAL PROCEDURE HEREAFTER 10 STARTER switch OFF Check Ng 52 11 Condition lever HI IDLE 12 Engine instruments CHECK Ng 68 1 Oil pressure Oil temperature ITT green sector 13 FUEL panel AUX BP switch AUTO At this time observing a drop in the fuel pressure is normal WARNING LIGHT AUX BP ON OFF 14 Generator WARNING LIGHT MAIN GEN OFF RESET if necessary MAIN GEN warning light...

Page 236: ... OFF 4 INERT SEP switch OFF 5 Landing gear control DN 6 SOURCE selector GPU WARNING LIGHT GPU ON WARNING LIGHT BAT OFF ON Voltmeter VOLTAGE CHECKED V 28 Volts If voltage is 30 volts immediately turn SOURCE selector to OFF Radio navigation equipment may be damaged before main fuse failure 7 Engine controls MAN OVRD control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE ...

Page 237: ...panel IGNITION switch AUTO STARTER switch ON WARNING LIGHTS STARTER FLASHING IGNITION ON NOTE The use of the starter is limited Refer to Chapter 2 4 STARTER OPERATION LIMITS Ng 13 Condition lever LO IDLE When condition lever is positioned on LO IDLE before having obtained 13 of Ng there is a risk of overtemperature further to an excessive accumulation of fuel inside the combustion chamber before i...

Page 238: ... allow to stay within above mentioned ITT limits In case of higher temperature and longer time stop immediately the starting procedure as indicated in the following caution and inform the maintenance department This starting engine procedure must be also applied in case of drop in voltage supplied by GPU This drop will be shown by a low or zero Ng acceleration If starting engine procedure is abort...

Page 239: ...er CUT OFF IGNITION switch OFF or AUTO Wait ITT 800 C then STARTER switch OFF BEFORE ANY RESTARTING ATTEMPT CARRY OUT A MOTORING Refer to paragraph MOTORING CONTINUE WITH NORMAL PROCEDURE HEREAFTER Ng The start sequence must be timed to ensure starter limits are not exceeded Lengthy operation of the starter results in excessive temperature of the engine If Ng does not reach 30 within 30 seconds af...

Page 240: ...URE Condition lever CUT OFF IGNITION switch OFF or AUTO STARTER switch OFF WAIT FOR 1 MINUTE Refer to Chapter 2 4 STARTER OPERATION LIMITS THEN TRY TO RESTART ENGINE START panel IGNITION switch AUTO STARTER switch ON WARNING LIGHTS STARTER FLASHING IGNITION ON Ng 13 Condition lever HI IDLE Monitor increase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng Oil pressure WARNING LIG...

Page 241: ...viour should only be observed with outside low temperature IOAT 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 LIGHT BAT OFF OFF 12 Propeller governor lever FEATHER This reduces propeller blast on the person disconnecting the GPU 13 GPU HAVE IT DISCONNECTED WARNING LIGHT GPU OFF This means that gr...

Page 242: ...il temperature ITT green sector 17 FUEL panel AUX BP switch AUTO At this time observing a drop in the fuel pressure is normal WARNING LIGHT AUX BP ON OFF 18 Generator WARNING LIGHT MAIN GEN OFF RESET if necessary MAIN GEN warning light normally goes out as soon as STARTER warning light goes out If not increase Ng over 70 to start main generator Battery ammeter CHARGE CHECKED Battery voltage CHECKE...

Page 243: ...the bearing cavities and prevent oil coking after shut down in high OAT above 35 C 95 F environment it is recommended to perform a 30 second dry motoring run It is possible that no trace of drainage be observed under engine due to the drainage collector intended to prevent parking area from contamination CAUTION AFTER ANY STARTING INTERRUPT PROCEDURE WAIT FOR ENGINE TOTAL SHUT DOWN WAIT AT LEAST 3...

Page 244: ...ump 3 IGNITION switch OFF WARNING LIGHT IGNITION OFF To clear fuel and vapor internally trapped 4 STARTER switch ON for 15 sec maxi WARNING LIGHT STARTER FLASHING To cool engine following shut down in high temperature environment 4 STARTER switch ON during 30 sec WARNING LIGHT STARTER FLASHING If ignition symptoms occur ITT increasing check that IGNITION switch is OFF that condition lever is on CU...

Page 245: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 4 NORMAL PROCEDURES EASA Approved Page 4 4 36 Rev 7 AMPLIFIED PROCEDURES MOTORING 3 3 6 FUEL panel AUX BP switch OFF WARNING LIGHTS AUX BP ON OFF FUEL PRESS ON ...

Page 246: ...ute 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 control OFF Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Flight idle stop Propeller governor lever MAX RPM Condition lever CUT ...

Page 247: ...ase of ITT max ITT 870 C for 20 seconds max 1000 C for 5 seconds max Ng oil pressure WARNING LIGHT OIL PRESS OFF 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 Ng 50 stable STARTER switch OFF STARTER IGNITION 7 Engine instruments CHECK Ng 52 Oil pressure ITT green sector 8 Condition lever HI IDLE 9...

Page 248: ...NDBOOK Page 4 4 39 Rev 7 AMPLIFIED PROCEDURES MOTORING FOLLOWED BY AN ENGINE START 3 3 10 FUEL panel AUX BP switch AUTO WARNING LIGHT AUX BP ON OFF 11 Generator WARNING LIGHT MAIN GEN OFF RESET if necessary Battery ammeter CHARGE CHECKED Battery voltage CHECKED V 28 Volts ...

Page 249: ...horized only when all ice protection equipment are operating correctly This equipment may be activated before takeoff even during taxiing in case of icing conditions on ground Refer to Chapter 4 5 PARTICULAR PROCEDURES of this Section PROP DE ICE switch ON Check illumination of the green light located above the switch Illumination of the green light shows that power supplied to blade root electric...

Page 250: ...ion 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 the two green lights and avoiding VACUUM LO untimely alarms AIRFRAME DE ICE switch ON Visually check functioning of deicer boot during 1 total cycle and illumination of the two green lights located above the...

Page 251: ...aps UP 7 ECS panel BLEED switch ON FAN FLOW switch As required AIR COND switch ON A cabin temperature good regulation will only be obtained if AIR COND switch is set to ON There is no inconvenience to set AIR COND switch to FAN ONLY before starting engine for passenger and crew comfort provided that voltage is 25 volts CABIN TEMP C selector ADJUST AIR FLOW distributor AS REQUIRED Usually selected ...

Page 252: ...tem are described in Section 9 Supplements 10 AP TRIMS MASTER switch ON Preflight test button PRESS AP TRIMS MASTER operation CHECK Detailed control procedures of autopilot and electrical pitch trim are described in Section 9 Supplements Pitch trim UP DN then ADJUSTED Adjust the indicator in green range graduated from 12 to 37 of center of gravity facing corresponding center of gravity Yaw trim L ...

Page 253: ...rature IOAT Read 1 Determine the usable oxygen percent using the chart Figure 4 4 1 Figure 4 4 1 2 Determine the oxygen duration in minutes by multiplying the values read on table Figure 4 4 2 by the percent obtained with the chart Figure 4 4 1 Number of passen gers Duration Passengers plus 1 pilot Duration Passengers plus 2 pilots 0 226 113 1 162 94 2 127 81 3 104 71 4 88 65 Figure 4 4 2 ...

Page 254: ...ED Make sure that chocks are removed if used WARNING LIGHT PARK BRAKE OFF 5 L H and R H seat brakes CHECKED 6 Nose wheel steering CHECKED The control wheel will move roll in the same direction as the rudder pedals due to the rudder aileron interconnect 7 Power lever AS REQUIRED After initial acceleration power lever may be in the TAXI RANGE sector avoiding excessive movements in order to keep a co...

Page 255: ...ge 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 OFF and cause damage to the propeller 8 Flight instruments CHECK Check navigation and communication systems before or during taxiing check gyroscopic instruments during ground turns 9 Advisory panel CHECK...

Page 256: ...er lever must be at flight idle Keep the time spent with the propeller RPM in the caution yellow range at a minimum 4 Fuel Gages CHECK Quantity Symmetry FUEL SEL switch CHECKED AUTO AUX BP switch CHECKED AUTO 5 Flaps TO 6 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 LIGHT I...

Page 257: ...1 HTR switch ON PITOT 2 STALL HTR switch ON 7 Advisory panel CHECK All warning lights OFF except PARK BRAKE ON and if used INERT SEP ON 8 Electronic equipment Flight instruments Radar CHECK ADJUST On ground maintain radar on SBY in order not to generate radiations prejudicial to outside persons 9 Engine instruments CHECK All engine parameters must be in green range except propeller RPM which will ...

Page 258: ...ED Roll ADJUSTED 13 Parking brake RELEASED WARNING LIGHT PARK BRAKE OFF 14 STROBE switch ON CAUTION DO NOT TAKE OFF IF BATTERY CHARGE 50 Amperes After starting engine with airplane power a battery charge above 50 amperes is normal If this indication remains steady at a high value it may be then a battery or generation system failure Do not take off in these conditions ...

Page 259: ...APH FLIGHT INTO KNOWN ICING CONDITIONS 1 Heading HSI Stand by compass CHECK The indication of the stand by compass is disturbed when windshield s deice system s is are activated Altimeter setting CHECK 2 Horizon Attitude 2 CHECK Horizon has been set so as to indicate a 2 nose up attitude when airplane center of gravity is at a middle average 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ...

Page 260: ...RPM when compared to minimum value during PROP O SPEED test 8 Brakes RELEASED It is not necessary to reduce power at the end of OVERSPEED test torque will be about 40 before brake release For a normal takeoff maximum torque 100 will be applied after brake release On short runway maximum torque will be applied before brake release 9 Power lever TRQ 100 10 Takeoff ROTATION See Takeoff distances Chap...

Page 261: ...d 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 off at the end of the sequence At sequence end check All warning lights OFF In practice if preconized attitude is kept there is no difficulty to maintain a speed 128 KIAS until landing gear retraction is completed 14 Light...

Page 262: ...b power torque setting MXCL For each engine when torque is reduced below 100 at high altitude according to the tables the ITT will be approximately constant during final climb giving a particular value of ITT For a simplified engine operation during climb power may be set first of all by torque using 100 then when the ITT typical value for climb is reached by indicated ITT using this particular va...

Page 263: ...ation CHECK CABIN TEMP C selector ADJUST 4 Fuel tank gages CHECK CORRECT Quantity Symmetry Pre MOD70 0402 28 In spite of fuel selector automatic operation a non negligible dissymmetry may be observed at the end of climb for example when 10 minutes of climb have been performed on the same fuel tank Consequently it is recommended to select the fullest tank by pushing the SHIFT push button at the beg...

Page 264: ...110 red line on indicator at sea level and drops to about 100 at 31000 ft Therefore any propeller RPM reducing performed in altitude from a torque close to 100 if ITT limit permits it will be followed by a non negligible power and performance decrease owing to torque limiter CAUTION OBSERVE TRQ Ng Np ITT T AND OIL PRESSURE LIMITATIONS USE OPTIMUM TORQUE AND OR REFER TO TABLES IN CHAPTER 5 7 Engine...

Page 265: ... 10 minutes Post MOD70 0402 28 tank automatic change every 5 minutes All symmetry max dissymmetry 25 us gal 95 Litres 4 ETM When the cruise parameters are fully established RECORD Push The SHADIN ETM operation normal procedures are described in the Operation Manual at the latest revision 5 DE ICE SYSTEM As required Refer to Chapter 4 5 PARTICULAR PROCEDURES CAUTION IF HEAVY PRECIPITATION TURN IGNI...

Page 266: ...EM 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 inertial separator is 200 KIAS Prior to descending into or through known or suspected icing conditions select INERT SEP switch ON prior to accelerating beyond 200 KIAS There are no special speed limitations with the inertial sepa...

Page 267: ...istributor in DEFOG section and set WINDSHIELD switches to ON to avoid canopy misting If misting continues set AIR FLOW distributor to HOT or refer to Chapter 3 12 Paragraph WINDSHIELD MISTING OR INTERNAL ICING 5 Fuel Gages CHECK Quantity Symmetry Fullest tank SELECT Even if dissymmetry is 25 us gal 95 Litres it is better at this time to choose the fullest tank 6 Passengers briefing As required 7 ...

Page 268: ...er MAX RPM 5 Landing gear control IAS 178 KIAS DN During the sequence The red warning light flashes it indicates that the landing gear motor is electrically supplied It goes off when the 3 landing gears 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 co...

Page 269: ...22 KIAS LDG However when autopilot is engaged in APR mode with coupled GS flaps must be extended in landing position before crossing the OUTER MARKER 11 Approach speed Flaps LDG 80 KIAS To ensure positive and rapid engine response to throttle movement it is recommended that a minimum of 10 torque be maintained on final approach until landing is assured 12 YAW DAMPER push button OFF The pilot effor...

Page 270: ...d To avoid ingestion of foreign objects come out the reverse as speed reduces and use the brakes if necessary for further deceleration High power reverse at low speed can throw loose material into the air and can cause control problems and decrease the comfort of crew and passengers If permitted by the runway length it is better to adopt a moderate reverse CAUTION ON SNOWY OR DIRTY RUNWAY IT IS BE...

Page 271: ... left when 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 TRQ 100 select TO flaps as soon as the 8 attitude has been attained If the vertical speed is positive and if IAS is at or above 85 KIAS 3 Landing gear control UP All warning lights OFF If IAS ...

Page 272: ...maturely at low speed 2 Elevator trim Green sector To use elevator trim manual control is faster than to use electric control Ensure that runway length is sufficient to complete this sequence 3 Power lever Display TRQ 100 4 Takeoff ROTATION See Takeoff distances Chapter 5 8 Normal takeoff ATTITUDE 7 5 Short takeoff ATTITUDE 15 Rotation speed at takeoff according to airplane weight is also given in...

Page 273: ...D switch As required R WINDSHIELD switch As required PITOT 1 HTR switch OFF PITOT 2 STALL HTR switch OFF BLEED switch As required Taxiing with BLEED OFF may slightly help reduce the ITT thus reducing the required stabilization time before shut down This should be applied only for short taxi duration and is left to the pilot judgement 2 Radar switch CHECKED SBY Maintain radar on SBY in order not to...

Page 274: ...As required 5 AIR COND switch OFF 6 Condition lever HI IDLE 7 Power lever IDLE for 2 minutes This allows the engine to stabilize at minimum obtainable ITT in order to minimize the likelihood of oil coking in the 3 bearing area 8 GYRO INST panel All switches OFF 9 EFIS MASTER switch OFF 10 AP TRIMS MASTER switch OFF 11 RADIO MASTER switch OFF 12 Propeller governor lever FEATHER for 15 seconds Keep ...

Page 275: ...at minimum obtainable ITT in order to prevent the likelihood of oil coking in the 3 bearing area ITT is considered stabilized when variations are less than 5 C If BLEED was selected to OFF after landing and taxi was performed at IDLE power the taxi time is considered as cooling time Therefore the above stabilization time can be reduced accordingly 8 GYRO INST panel All switches OFF 9 EFIS MASTER s...

Page 276: ...el When fuel pressure is below 10 psi 2 psi check AUX BP pump is operating AUX BP switch OFF FUEL SEL switch MAN Tank selector OFF 15 INERT SEP switch OFF 16 INT LIGHTS panel All switches OFF 17 EXT LIGHTS panel All switches OFF 18 GENERATOR selector OFF 19 SOURCE selector OFF CAUTION IN CASE OF HIGH OAT ABOVE 35 C 95 F IT IS REQUIRED TO PERFORM 30 SECONDS DRY MOTORING RUN AFTER SHUT DOWN TO IMPRO...

Page 277: ...fuel pressure is below 10 psi 2 psi check AUX BP pump is operating AUX BP switch OFF FUEL SEL switch MAN Tank selector OFF 15 INERT SEP switch OFF 16 INT LIGHTS panel All switches OFF 17 EXT LIGHTS panel All switches OFF 18 GENERATOR selector OFF 19 SOURCE selector OFF CAUTION IN CASE OF HIGH OAT ABOVE 35 C 95 F IT IS RECOMMENDED TO PERFORM 30 SECONDS DRY MOTORING RUN AFTER SHUT DOWN TO IMPROVE CO...

Page 278: ...nd when operating on ramps taxiways or runways where surface snow ice standing water or slush may be ingested by the engine or freeze on engine or cowlings NOTE Refer to Figure 5 4 1 to convert IOAT to SAT in flight SAT IOAT 2 C on the ground 3 Flight into known icing conditions is authorized when all airplane equipment provided for ice protection is operating correctly This includes Pneumatic dei...

Page 279: ... soon as possible icing conditions Apply LEADING EDGES DEICING FAILURE emergency procedure Ice protection procedures 1 Prior to entering IMC as a preventive If IOAT 13 C INERT SEP switch ON IGNITION switch ON PROP DE ICE switch ON AIRFRAME DE ICE switch ON WINDSHIELD DE ICE switch ON 2 When operating under IMC INERT SEP switch ON IGNITION switch ON PROP DE ICE switch ON AIRFRAME DE ICE switch ON W...

Page 280: ...o ON before accelerating This will avoid reducing speed below 200 KIAS during descent to set the inertial separator IF AIRPLANE LEAVES ICING CONDITIONS MAINTAIN INERT SEP ON AS LONG AS ICE THICKNESS ON NON DEICED VISIBLE PARTS EXCEEDS 15 mm OR INCH This will avoid ice fragments coming from propeller spinner and being ingested by engine INERTIAL SEPARATOR POSITION AFFECTS ENGINE PARAMETERS PARTICUL...

Page 281: ...cumulated on the unprotected surfaces of the airplane aerodynamic characteristics may be changed Particularly stall speeds may increase by up to Flaps UP 20 KIAS Flaps TO 15 KIAS Flaps LDG 10 KIAS Correct operation of the aural stall warning may be altered by severe or prolonged icing Indeed in case of severe or prolonged icing an ice concretion due to refreezing around the heated stall warning ma...

Page 282: ... be decreased by 10 if cruise power is not changed or more if cruise power setting should be decreased due to the additional inertial separator limitations ITT limitation Because of the higher landing speed landing distances will be increased In the landing configuration using 90 KIAS approach speed increases landing distance by 20 refer to Chapter 5 13 LANDING DISTANCES ...

Page 283: ...d as 18 C increased vigilance is warranted at temperatures around freezing with visible moisture present If the visual cues specified in Section 2 Limitations for identifying severe icing conditions are observed accomplish the following 1 Immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the severe icing conditions in order to avoid ...

Page 284: ...s when holding in icing conditions Operation with flaps extended can result in a reduced wing angle of attack with the possibility of ice forming on the upper surface further aft on the wing than normal possibly aft of the protected area 7 If the flaps are extended do not retract them until the airframe is clear of ice 8 Report these weather conditions to Air Traffic Control ...

Page 285: ...TION switch ON This action is intended in highly improbable case of an engine flame out further to an important ingestion to ensure immediate restarting without action of the pilot 2 INERT SEP switch ON UTILIZATION ON RUNWAYS COVERED WITH WATER If takeoff or landing must be performed on a runway covered with water 1 IGNITION switch ON 2 INERT SEP switch ON ...

Page 286: ...rfaces upper and lower surfaces and in the landing gear wells shortly before takeoff Taxiing 1 INERT SEP switch ON 2 Taxi at very slow speed max 5 KIAS flaps up brake occasionally to maintain the brake pads warm this will prevent any subsequent locking due to freezing after takeoff Before takeoff 1 If the runway is long enough takeoff should be performed with the flaps in the up position In that c...

Page 287: ... takeoff run in order to reduce the forward resistance due to snow accumulation against the wheel 2 After takeoff normally retract the landing gear then perform a complete cycle extension retraction at IAS 128 KIAS Before landing 1 IGNITION switch ON 2 INERT SEP switch ON Touch and Go Prohibited On the ramp after landing or taxiing 1 Do not use the parking brake to prevent brake lock 2 Use chocks ...

Page 288: ...he wings stabilizers and movable surfaces upper and lower surfaces shortly before takeoff Taxiing 1 INERT SEP switch ON 2 Taxi at very slow speed max 5 KIAS Use β area of power lever to adjust speed Apply very smooth variations using power lever 3 Steer the airplane using the rudder Make turns at a very low speed engine torque tends to make the airplane turn to the left 4 Use brakes only at very l...

Page 289: ...e engine torque tends to make the airplane turn to the left 2 Taxi at very slow speed max 5 KIAS Use β area of power lever to adjust speed Apply very smooth variations using power lever 3 Steer the airplane using the rudder Make turns at a very low speed engine torque tends to make the airplane turn to the left 4 Use brakes only at very low speed and progressively On the ramp after landing or taxi...

Page 290: ...rocedures for the airplane use when operating under temperatures between 0 C and 40 C on ground Figure 4 5 1 OPERATING ENVELOPES BY COLD WEATHER 0 C to 25 C AND VERY COLD WEATHER 25 C to 40 C 40 30 20 10 0 10 OPERATING ENVELOPES Transit time hours O A T C 10 9 8 7 6 5 4 3 2 1 0 ENVELOPE 2 Hot air preheating GPU starting Feather Hi Idle Normal procedures ENVELOPE 1 Normal procedures BAT starting MA...

Page 291: ...OVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS 2 Carry out a complete rotation of the propeller to check its free rotation 3 Do not perform a fuel draining If the airplane is operating permanently under negative temperatures drainings will have to be performed once a week after having parked the airplane in a heated hangar 4 Remove c...

Page 292: ...es UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Landing After landing 1 Apply normal procedures defined in Chapter s 4 3 and or 4 4 2 Apply according to the condition of runways and taxiways the procedures UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVERED WITH TAMPED SNOW RUNWAYS Shut down 1 Parking brake RELEASED WARNING LIGHT...

Page 293: ...he cabin by half opening the door in the R H front compartment for the EFIS versions during 10 minutes at the end of the engine preheating 2 Remove any snow or ice from the wings stabilizers and movable surfaces Apply according to the condition of runways and taxiways the procedures UTILIZATION ON RUNWAYS COVERED WITH MELTING OR NOT TAMPED SNOW or the procedures UTILIZATION ON ICY OR COVERED WITH ...

Page 294: ...f the power lever and of the propeller governor lever 9 IGNITION switch ON during 30 seconds WARNING LIGHT IGNITION ON then IGNITION switch AUTO WARNING LIGHT IGNITION OFF This enables to preheat spark igniters before starting the engine Before starting the engine Apply normal procedures defined in Chapter s 4 3 and or 4 4 Starting the engine The starting must be mandatorily performed using an ext...

Page 295: ...Notched CAUTION WHEN THE ENGINE IS SHUTDOWN THE POWER LEVER MUST NOT BE MOVED BEHIND THE FLIGHT IDLE POSITION Power lever IDLE Propeller governor lever Feather Condition lever CUT OFF 4 Fuel panel AUX BP switch ON WARNING LIGHT AUX BP ON ON WARNING LIGHT FUEL PRESS OFF Fuel pressure indicator Check 5 Propeller AREA CLEAR 6 ENGINE START panel IGNITION switch ON WARNING LIGHT IGNITION ON STARTER swi...

Page 296: ...he more the temperature is low the more the selector is hard to move Starter limits and checks of starting sequence are unchanged 7 Engine instruments Check NG 68 1 Oil pressure ITT green sector 8 SOURCE selector BAT WARNING LIGHT BAT OFF OFF 9 IGNITION switch AUTO WARNING LIGHT IGNITION OFF 10 Ground power unit HAVE IT DISCONNECTED WARNING LIGHT GPU OFF 11 FUEL panel AUX BP switch AUTO WARNING LI...

Page 297: ...s soon as the current flow is lower than 100 A BLEED switch ON CABIN TEMP C selector FULL HOT 2 Propeller governor lever As soon as the oil temperature is greater than 0 C Propeller governor lever MAX RPM Perform 2 propeller regulations 3 Apply normal procedures defined in Chapter s 4 3 and or 4 4 Taxiing Before takeoff Takeoff Apply procedures defined for Envelope 1 Landing After landing Shut dow...

Page 298: ...ied as follows Preflight inspection Before starting the engine Starting the engine Apply the procedures defined for the Envelope 2 After starting the engine 1 ECS panel As soon as the current flow is lower than 100 A BLEED switch ON CABIN TEMP C selector FULL HOT Preheat the cabin respecting time defined in Figure 4 5 2 before switching on the navigation and monitoring systems This allows to respe...

Page 299: ...40 C 10 10 Taxiing Before takeoff Takeoff Apply procedures defined for Envelope 1 Landing After landing Shut down Apply procedures defined for Envelope 1 Complement If landing is foreseen by cold or very cold weather or in case of prolonged operation of the airplane in such conditions it is recommended to prepare the airplane as specified in Chapter 8 9 Figure 4 5 2 PREHEATING DURATION ...

Page 300: ... 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 final on a short runway it is necessary to use normal approach speed 80 KIAS with flaps LDG in order to avoid an excessive speed Indeed in this case landing distance indicated in Chapter 5 13 would not be respected ...

Page 301: ...ion may provide pitch oscillations while increasing the yaw movement to the wind Do not deflect ailerons into wind while taxiing This will raise spoilers and have a detrimental effect A good solution is to maintain ailerons to neutral position during second taxi phase after landing and during first taxi phase before takeoff Maximum demonstrated crosswind for landing is 20 kt The most restrictive s...

Page 302: ...F 1 INERT SEP switch ON 2 Reverse Do not use In fact on a flat runway with grass it is necessary to adopt a power greater than the one obtained when the power lever is set to IDLE so the pilot will not be tempted to use the reverse LANDING 1 INERT SEP switch ON After wheel touch down 2 Reverse Only if necessary Do not maintain reverse at speeds below 40 KIAS to avoid ingestion of foreign matter In...

Page 303: ... PARTICULAR PROCEDURES OPERATION IN RVSM CONDITIONS After altitude capture in altitude hold mode of the autopilot discrepancy between desired altitude and held altitude must be adjusted using the vertical trim control in order not to exceed 20 ft In RVSM area the transponder 1 must be used first ...

Page 304: ... Maximum climb power FL 200 5 7 2 Maximum climb power FL 200 5 7 3 Maximum cruise power FL 200 5 7 4 Maximum cruise power FL 200 5 7 5 Normal recommended cruise power FL 200 5 7 6 Normal recommended cruise power FL 200 5 7 7 5 8 TAKEOFF DISTANCES 5 8 1 5 9 CLIMB PERFORMANCE 5 9 1 CLIMB SPEEDS IAS 130 KIAS 5 9 1 CLIMB SPEEDS IAS 160 KIAS 5 9 2 TIME CONSUMPTION AND CLIMB DISTANCE IAS 130 KIAS 5 9 3 ...

Page 305: ...10 16 Long Range cruise 5512 lbs 2500 kg Altitude 24000 ft 5 10 23 Long Range cruise 5512 lbs 2500 kg Altitude 24000 ft 5 10 24 Long Range cruise 6173 lbs 2800 kg Altitude 24000 ft 5 10 25 Long Range cruise 6173 lbs 2800 kg Altitude 24000 ft 5 10 26 5 11 TIME CONSUMPTION AND DESCENT DISTANCE 5 11 1 5 12 HOLDING TIME 5 12 1 5 13 LANDING DISTANCES 5 13 1 Weight 6250 lbs 2835 kg 5 13 1 Weight 5071 lb...

Page 306: ...00C2 airplane Maximum noise level permissible Demonstrated noise level FAR PART 36 Appendix G Amdt 17 85 dB A 77 4 dB A ICAO Annex 16 Chapter 10 Appendix 6 88 dB A 80 4 dB A TBM 700 airplane has received the noise limitation type certificate Nr N181 dated 31st January 1990 replaced by the Type Certificate Data Sheet EASA A 010 on 14th July 2004 ...

Page 307: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE EASA Approved Page 5 1 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 308: ...O LDG GR DN FLAPS LDG LDG GR DN KIAS KCAS KIAS KCAS KIAS KCAS 125 150 175 200 225 250 266 127 152 177 205 228 253 271 70 80 90 100 120 140 160 69 80 90 101 121 141 162 60 70 80 90 100 110 120 58 68 78 88 98 108 118 MPH IAS MPH CAS MPH IAS MPH CAS MPH IAS MPH CAS 144 173 201 230 259 288 307 146 175 204 233 262 292 311 81 92 104 115 138 161 184 79 92 104 116 139 162 187 69 81 92 104 115 127 138 67 7...

Page 309: ...0 225 250 271 124 149 174 199 224 249 270 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 144 173 201 230 259 288 312 142 171 200 229 258 287 311 81 92 104 115 138 161 184 81 92 104 115 138 160 183 69 81 92 104 115 127 138 68 79 91 104 115 127 138 Figure 5 2 2 ALTERNATE STATIC SOURCE BLEED ON ...

Page 310: ...3 1 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 PRESSURIZATION USEFUL ENVELOPE 9350 ft cabin P 6 2 PSI max 9000 310 Flight level FL ...

Page 311: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE Page 5 3 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 312: ...01 08 11 18 21 28 31 38 4000 13 06 03 04 07 14 17 25 27 35 6000 17 10 07 00 03 11 13 21 23 31 8000 21 13 11 03 01 07 09 17 19 27 10000 25 17 15 07 05 03 05 13 15 23 12000 29 21 19 11 09 01 01 10 11 20 14000 33 25 23 14 13 04 03 06 07 16 16000 37 28 27 18 17 08 07 02 03 12 18000 41 32 31 22 21 12 11 01 01 08 20000 45 36 35 26 25 15 15 05 05 04 22000 48 39 38 29 28 19 18 09 08 00 24000 52 43 42 33 3...

Page 313: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE Page 5 4 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 314: ...S MPH IAS 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 57 81 76 66 75 71 61 76 72 61 86 82 70 82 78 68 84 80 68 94 90 78 98 93 81 100 95 81 113 107 93 6579 lbs 2984 kg UP DN DN UP TO LDG 75 71 61 76 72 61 86 82 70 80 75 66 82 77 66 92 86 76 88 84 7...

Page 315: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE EASA Approved Page 5 5 2 Rev 7 INTENTIONALLY LEFT BLANK ...

Page 316: ...FORMANCE TBM 700 PILOT S OPERATING HANDBOOK Page 5 6 1 Rev 0 5 6 WIND COMPONENTS Figure 5 6 1 WIND COMPONENTS EXAMPLE Angle between wind direction and flight path 50 Headwind 8 kts Crosswind 10 kts Wind speed 13 kts ...

Page 317: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE Page 5 6 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 318: ...ve 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 power TRQ 98 cf tables Figures 5 7 2A and 5 7 2B Recommended cruise power TRQ 92 cf tables Figures 5 7 3A and 5 7 3B CAUTION THE TRQ SETTING MUST NEVER EXCEED 100 FOR NP 2000 RPM REMARK The engine ITT limit at 800 ...

Page 319: ...09 97 13 07 100 95 11 05 98 93 09 03 100 96 91 07 01 99 94 89 05 01 100 97 92 87 03 03 99 95 90 85 01 05 97 93 87 82 01 07 100 95 90 85 80 03 09 98 93 88 82 78 05 11 100 95 91 86 80 75 07 13 98 93 88 83 78 72 09 15 100 95 90 86 81 74 69 11 17 100 97 93 88 83 78 71 66 13 19 99 95 90 85 80 74 69 15 21 100 97 92 88 82 77 71 17 23 99 94 90 84 79 67 19 25 100 96 92 86 81 67 21 27 98 94 88 83 68 23 29 1...

Page 320: ... 72 67 37 30 98 94 89 84 79 74 70 65 35 28 97 92 87 82 77 73 68 64 33 26 100 95 91 86 81 76 71 66 62 31 25 99 94 89 84 79 74 69 65 61 29 23 97 92 87 82 77 72 68 63 59 27 21 100 95 90 85 80 75 70 66 61 57 25 19 98 93 88 83 78 73 69 64 59 55 23 17 100 95 91 86 81 76 71 67 62 58 54 21 15 98 94 89 84 79 74 70 65 60 57 53 19 13 100 96 92 87 82 77 73 68 63 59 55 17 11 99 94 90 85 80 75 71 66 61 57 53 15...

Page 321: ... 200 25 15 23 13 21 11 19 09 TRQ 100 17 07 TRQ 100 15 05 13 03 11 02 09 00 100 07 02 99 05 04 97 03 06 100 95 01 08 98 93 01 10 100 95 91 03 12 98 93 88 05 14 100 96 91 85 07 16 98 93 88 82 09 18 100 96 91 84 78 11 20 98 93 87 81 75 13 22 97 91 85 79 15 24 100 93 87 82 17 26 100 96 90 84 19 28 98 92 86 21 29 100 95 89 23 31 100 97 84 25 33 100 92 84 27 35 100 92 83 29 37 91 83 31 39 82 CAUTION THE...

Page 322: ...5 24 97 91 86 81 75 70 33 22 100 95 89 84 79 73 68 31 20 98 93 88 82 77 71 66 29 19 96 91 86 80 75 69 64 27 17 100 94 89 84 78 73 67 62 25 15 98 92 87 82 76 71 66 60 23 13 100 96 90 85 80 74 69 64 59 21 11 98 94 88 83 78 72 67 62 57 19 09 97 92 86 81 76 70 65 61 17 07 100 95 90 84 79 74 68 63 59 15 05 98 93 88 82 77 72 66 61 57 13 03 100 96 91 86 80 74 69 64 59 55 11 02 98 94 88 84 78 72 67 62 57 ...

Page 323: ...11 02 96 09 00 100 94 07 02 98 92 05 04 100 96 90 03 06 99 93 87 01 08 100 96 91 85 01 10 98 93 88 82 03 12 100 95 90 85 79 05 14 98 93 88 83 76 07 16 100 95 90 85 81 74 09 18 98 93 88 83 78 71 11 20 100 95 90 86 80 74 67 13 22 98 93 88 82 76 62 15 24 100 95 91 85 72 63 17 26 100 97 93 84 72 63 19 28 100 99 95 81 72 64 21 29 100 94 88 80 72 64 23 31 93 88 80 72 65 25 33 87 79 71 66 27 35 79 73 67 ...

Page 324: ...9 65 33 23 100 95 90 83 78 73 67 63 31 21 98 93 88 81 76 71 66 61 29 19 100 96 91 86 79 74 69 64 59 27 17 98 94 89 83 77 72 67 62 57 25 15 96 92 87 81 75 70 65 60 56 23 13 100 94 90 85 79 73 68 63 58 54 21 12 98 92 87 83 76 71 66 61 57 52 19 10 100 96 90 85 80 74 69 64 59 55 17 08 98 93 88 83 78 72 67 62 58 53 15 06 100 96 91 86 81 76 70 65 60 56 51 13 04 98 94 89 83 78 73 67 63 58 54 50 11 02 96 ...

Page 325: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE Page 5 7 8 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 326: ...1903 2149 951 1066 1181 1329 1526 1493 1657 1837 2051 2329 1017 1132 1280 1444 1657 1591 1772 1968 2215 2510 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1083 1214 1363 1575 1804 1690 1870 2100 2379 2707 1148 1296 1476 1690 1968 1788 1985 2247 2559 2920 1214 1378 1575 1837 2100 1903 2133 2411 2756 3133 1247 1444 1640 1919 2198 1969 2231...

Page 327: ...0 1837 2067 2001 2198 2461 2723 3051 1378 1542 1739 1968 2231 2133 2362 2625 2920 3281 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1476 1673 1870 2100 2428 2264 2493 2789 3117 3543 1575 1772 2001 2297 2657 2395 2657 2953 3346 3839 1690 1903 2149 2461 2854 2559 2854 3182 3609 4134 1755 1969 2231 2543 2969 2657 2953 3314 3740 4298 Figure...

Page 328: ...L 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 6000 8000 2600 2570 2540 2510 2480 2485 2455 2425 2395 2350 2380 2350 2320 2290 2250 2285 2250 2220 2185 2150 2190 2160 2130 2090 2035 2105 2080 2045 2010 1975 6579 lbs 2984 kg SL 2000 4000 6000 800...

Page 329: ...0 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 6000 8000 2290 2250 2200 2150 2110 2180 2135 2090 2050 2000 2000 2030 1990 1945 1895 1980 1940 1895 1845 1795 1890 1850 1805 1760 1730 1805 1765 1725 1680 1625 6579 lbs 2984 kg SL 2000 4000 6000 8000 1820 1780 1740 1700 166...

Page 330: ... 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 00 18 14 4 8 9 04 45 21 17 5 5 11 06 00 27 22 7 1 14 14000 04 45 21 17 5 5 11 05 30 25 19 6 6 13 07 15 32 25 8 5 16 16000 05 30 24 19 6 3 13 06 30 28 22 7 4 15 08 15 36 28 9 5 19 18000 06 00 27 21 7 1 15 07 15 31 25 8 2 17 09 30 40 32 10 6 22 20...

Page 331: ... 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 04 30 20 16 5 3 10 05 15 24 19 6 3 12 06 45 31 24 8 2 16 14000 05 00 24 19 6 3 12 06 15 28 22 7 4 15 08 00 36 28 9 5 19 16000 06 00 27 21 7 1 14 07 00 32 25 8 5 17 09 00 41 32 10 8 22 18000 06 45 30 23 7 9 17 08 00 35 28 9 2 20 10 30 46 36 12 2 26...

Page 332: ... 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 00 23 18 6 1 12 05 45 27 21 7 1 14 07 30 35 27 9 2 18 14000 05 45 26 21 6 9 14 06 45 31 24 8 2 17 08 45 40 32 10 6 22 16000 06 30 30 23 7 9 16 07 45 35 28 9 2 19 10 00 46 36 12 2 25 18000 07 30 34 26 9 0 19 08 45 40 31 10 6 23 11 30 52 40 13 7 30...

Page 333: ... 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 21 7 1 16 12000 04 45 21 17 5 5 13 05 30 25 20 6 6 15 07 00 32 25 8 5 20 14000 05 30 25 19 6 6 16 06 30 29 23 7 7 19 08 15 37 29 9 8 24 16000 06 30 28 22 7 4 18 07 30 33 26 8 7 22 09 30 42 33 11 1 28 18000 07 15 31 25 8 2 21 08 30 37 29 9 8 25 1...

Page 334: ... 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 24 7 9 18 12000 05 15 24 19 6 3 15 06 00 28 22 7 4 18 08 00 36 28 9 5 23 14000 06 15 28 22 7 4 18 07 15 33 26 8 7 21 09 15 42 33 11 1 28 16000 07 15 32 25 8 5 21 08 30 37 29 9 8 25 10 45 48 38 12 7 33 18000 08 15 36 28 9 5 25 09 45 42 33 11 1 29...

Page 335: ... 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 0 21 12000 05 45 27 21 7 1 17 06 45 32 25 8 5 21 08 45 41 32 10 8 26 14000 06 45 32 25 8 5 21 08 00 37 29 9 8 25 10 15 48 38 12 7 32 16000 08 00 36 28 9 5 25 09 30 43 33 11 4 29 12 00 55 43 14 5 38 18000 09 00 41 32 10 8 29 11 00 48 38 12 7 35 14 0...

Page 336: ...70 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 1860 1820 1790 1750 1750 1720 1680 1630 1590 1660 1630 1590 1550 1500 1580 1550 1500 1460 1410 1500 1470 1430 1380 1330 1435 1395 1350 1305 1255 1355 1330 1285 1235 1185 6579 lbs 2984 kg SL 2000 4000 6000 8000 14...

Page 337: ...20 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 2680 2650 2620 2540 2520 2490 2460 2440 2430 2400 2380 2350 2320 2330 2300 2270 2250 2220 2230 2200 2180 2150 2120 2145 2120 2090 2060 2030 2050 2035 2005 1975 1940 6579 lbs 2984 kg SL 2000 4000 6000 8000 2140 21...

Page 338: ...ATING HANDBOOK Page 5 10 1 Rev 5 5 10 CRUISE PERFORMANCE Refer to Supplement 41 for TBM 700C2 airplane Conditions ISA Weight 5512 lbs 2500 kg Figure 5 10 1 CRUISE PERFORMANCE TAS KTAS Flight level FL 100 200 300 200 300 250 LRCR IRCR NOCR MXCR ...

Page 339: ...209 275 208 273 21000 37 100 216 170 57 1 210 280 208 278 207 276 22000 39 100 214 168 56 5 209 283 207 281 206 279 23000 41 100 212 166 56 0 208 286 206 284 205 282 24000 43 100 210 165 55 6 207 290 205 287 203 285 25000 45 100 209 164 55 3 206 293 204 291 202 288 26000 46 100 208 163 54 9 205 296 203 294 201 291 27000 48 100 207 162 54 7 204 300 202 297 200 294 28000 50 100 206 162 54 4 203 303 ...

Page 340: ... 207 278 206 276 21000 27 100 218 171 57 6 208 284 206 281 205 279 22000 29 100 216 170 57 1 207 287 205 285 204 282 23000 31 100 215 168 56 7 206 290 204 288 202 285 24000 33 100 213 167 56 3 205 293 203 291 201 288 25000 34 100 212 166 55 9 204 297 202 294 200 291 26000 36 100 210 165 55 6 203 300 201 298 199 295 27000 38 100 209 164 55 3 202 304 200 301 198 298 28000 40 100 209 164 55 2 201 307...

Page 341: ...2 206 280 205 278 21000 22 100 220 173 58 1 207 285 205 283 204 281 22000 24 100 218 171 57 5 206 289 204 286 203 284 23000 26 100 216 170 57 1 205 292 203 289 202 287 24000 28 100 215 168 56 7 204 295 202 293 200 290 25000 29 100 213 167 56 3 203 298 201 296 199 293 26000 31 100 212 166 56 0 202 302 200 299 198 296 27000 33 99 210 165 55 5 200 304 198 301 196 299 28000 35 96 202 159 53 5 197 304 ...

Page 342: ...84 205 281 204 279 21000 17 100 221 174 58 5 206 287 204 285 203 282 22000 19 100 220 172 58 0 205 290 203 288 202 285 23000 21 100 218 171 57 5 204 293 202 291 201 289 24000 22 100 216 170 57 1 203 297 201 294 199 292 25000 24 100 215 169 56 8 202 300 200 298 198 295 26000 26 99 209 164 55 2 200 303 198 300 197 298 27000 28 95 202 159 53 5 196 302 194 298 193 297 28000 30 91 195 153 51 6 192 301 ...

Page 343: ...85 204 283 203 281 21000 12 100 223 175 58 9 205 288 203 286 202 284 22000 14 100 221 174 58 5 204 291 202 289 201 287 23000 16 100 220 172 58 0 203 295 201 292 200 290 24000 17 100 218 172 57 7 202 298 200 296 198 293 25000 19 97 211 166 55 9 199 299 197 296 195 294 26000 21 94 204 161 54 0 196 299 193 296 192 293 27000 23 90 197 155 52 0 192 298 189 294 188 292 28000 25 87 190 149 50 1 188 297 1...

Page 344: ... 287 203 284 202 283 21000 7 100 224 176 59 2 205 291 202 287 201 286 22000 9 100 223 175 58 9 203 294 201 291 200 289 23000 11 98 218 171 57 6 201 295 200 294 197 290 24000 13 96 211 166 55 7 198 296 196 293 194 290 25000 15 92 204 160 53 9 195 296 192 292 191 290 26000 17 89 197 155 52 0 191 296 188 291 186 288 27000 19 86 190 150 50 3 187 295 185 290 182 287 28000 20 82 184 144 48 5 184 294 181...

Page 345: ...202 288 201 287 199 284 21000 2 94 218 171 57 5 198 288 198 286 196 283 22000 0 92 211 166 55 7 196 288 193 285 191 282 23000 2 88 204 160 53 9 195 292 190 284 188 281 24000 3 86 197 155 52 0 188 287 185 283 184 280 25000 5 82 190 149 50 2 185 286 182 282 179 278 26000 7 79 183 144 48 3 181 285 178 281 175 276 27000 9 76 176 139 46 6 176 283 174 279 170 274 28000 11 72 170 133 44 8 172 281 169 276...

Page 346: ...11 277 209 275 208 273 21000 37 100 216 170 57 1 210 280 208 278 207 276 22000 39 100 214 168 56 5 209 283 207 281 206 279 23000 41 100 212 166 56 0 208 286 206 284 205 282 24000 43 100 210 165 55 6 207 290 205 287 203 285 25000 45 100 209 164 55 3 206 293 204 291 202 288 26000 46 100 208 163 54 9 205 296 203 294 201 291 27000 48 100 207 162 54 7 204 300 202 297 200 294 28000 50 100 206 162 54 4 2...

Page 347: ... 209 281 207 278 206 276 21000 27 100 218 171 57 6 208 284 206 281 205 279 22000 29 100 216 170 57 1 207 287 205 285 204 282 23000 31 100 215 168 56 7 206 290 204 288 202 285 24000 33 100 213 167 56 3 205 293 203 291 201 288 25000 34 100 212 166 55 9 204 297 202 294 200 291 26000 36 100 210 165 55 6 203 300 201 298 199 295 27000 38 99 207 162 54 7 201 302 199 299 196 296 28000 40 96 199 157 52 7 1...

Page 348: ...6 208 282 206 280 205 278 21000 22 100 220 173 58 1 207 285 205 283 204 281 22000 24 100 218 171 57 5 206 289 204 286 203 284 23000 26 100 216 170 57 1 205 292 203 289 202 287 24000 28 100 215 168 56 7 204 295 202 293 200 290 25000 29 100 213 167 56 3 203 298 201 296 199 293 26000 31 98 208 163 54 9 200 299 198 295 196 293 27000 33 95 201 158 53 1 196 298 194 296 192 292 28000 35 91 195 153 51 4 1...

Page 349: ...9 207 284 205 281 204 279 21000 17 100 221 174 58 5 206 287 204 285 203 282 22000 19 100 220 172 58 0 205 290 203 288 202 285 23000 21 100 218 171 57 5 204 293 202 291 201 289 24000 22 100 216 170 57 1 203 297 201 294 199 292 25000 24 97 209 164 55 3 199 296 197 294 195 291 26000 26 94 203 159 53 6 195 295 194 293 191 290 27000 28 90 196 154 51 9 192 295 190 292 187 287 28000 31 86 190 149 50 1 18...

Page 350: ... 3 206 286 204 283 203 281 21000 12 100 223 175 58 9 205 288 203 286 202 284 22000 14 100 221 174 58 5 204 291 202 289 201 287 23000 16 97 216 170 57 1 201 292 199 290 198 287 24000 18 95 209 164 55 1 198 292 196 290 194 287 25000 20 92 202 159 53 4 194 292 192 289 190 286 26000 22 89 195 153 51 5 190 291 189 289 186 285 27000 24 84 188 148 49 8 187 290 185 287 181 283 28000 26 81 182 143 48 0 183...

Page 351: ...9 7 206 287 203 284 202 283 21000 8 98 220 173 58 1 203 288 202 286 199 283 22000 10 96 214 168 56 5 200 289 198 286 196 284 23000 12 92 207 162 54 7 197 289 195 286 192 283 24000 13 90 200 157 52 8 193 289 191 286 188 282 25000 15 87 193 152 51 1 190 288 187 285 185 281 26000 17 83 187 147 49 4 185 287 184 284 181 279 27000 19 79 181 142 47 7 182 286 179 282 176 277 28000 21 76 174 137 46 0 178 2...

Page 352: ... 167 56 3 196 280 194 277 193 275 21000 2 87 206 162 54 4 193 279 191 277 189 274 22000 0 84 200 157 52 8 189 279 187 276 185 274 23000 2 81 193 152 51 0 185 278 184 275 182 272 24000 4 78 187 146 49 3 181 276 180 274 178 271 25000 6 76 180 141 47 6 177 275 176 273 173 269 26000 8 72 173 136 45 8 173 273 172 271 169 267 27000 10 69 167 131 44 1 169 272 168 270 164 264 28000 12 66 160 126 42 3 164 ...

Page 353: ... 38 88 198 155 52 2 200 267 198 265 196 262 22000 40 88 195 153 51 6 199 270 197 268 195 265 23000 42 88 193 152 51 1 198 273 196 271 194 268 24000 44 88 192 151 50 7 197 276 195 274 193 271 25000 45 88 190 149 50 2 196 279 194 277 192 274 26000 47 88 188 148 49 7 195 283 193 280 191 277 27000 49 88 187 147 49 4 194 286 192 283 190 280 28000 51 88 186 146 49 1 193 289 191 286 189 283 29000 53 88 1...

Page 354: ...0 28 88 199 157 52 7 198 271 196 268 195 266 22000 30 88 198 155 52 2 197 274 196 271 193 268 23000 31 88 195 153 51 6 196 277 195 274 192 271 24000 33 88 194 152 51 2 195 280 193 277 191 274 25000 35 88 192 151 50 7 194 283 192 280 190 277 26000 37 88 190 150 50 3 192 285 191 283 188 279 27000 39 85 185 146 49 0 189 285 188 283 185 279 28000 41 82 179 141 47 3 186 285 184 281 182 278 29000 43 79 ...

Page 355: ... 88 201 158 53 1 197 272 196 270 194 267 22000 25 88 199 156 52 5 196 275 195 273 193 270 23000 26 88 197 155 52 0 195 278 194 276 191 273 24000 28 88 195 153 51 5 194 281 193 279 190 276 25000 30 87 5 193 151 50 9 192 283 191 281 188 278 26000 32 84 7 187 146 49 3 189 283 187 281 185 277 27000 34 82 181 142 47 7 185 283 184 280 181 276 28000 36 79 174 137 46 0 182 282 180 279 177 274 29000 38 76 ...

Page 356: ...8 88 202 159 53 5 196 273 195 272 193 269 22000 20 88 200 157 52 8 195 277 194 275 192 272 23000 21 88 198 156 52 4 194 280 193 278 191 275 24000 23 87 3 195 153 51 5 193 283 191 280 188 276 25000 25 84 3 188 148 49 8 189 282 188 279 185 275 26000 27 81 2 182 143 48 1 185 281 184 278 181 274 27000 29 78 176 138 46 4 182 280 180 277 177 272 28000 31 75 169 133 44 6 178 279 176 276 172 270 29000 33 ...

Page 357: ...204 160 53 9 195 275 194 273 192 270 22000 14 88 201 158 53 1 194 278 193 276 190 272 23000 16 85 6 195 153 51 5 191 279 189 276 187 272 24000 18 82 7 189 148 49 9 188 279 186 276 183 272 25000 20 79 8 182 143 48 2 185 278 182 275 180 271 26000 22 76 9 176 139 46 6 181 277 179 274 175 269 27000 24 74 170 134 45 0 177 275 174 272 172 269 28000 27 71 164 129 43 3 173 274 170 270 166 264 29000 29 68 ...

Page 358: ...000 8 86 5 201 158 53 1 194 275 191 272 189 269 22000 10 84 195 153 51 5 190 275 188 272 186 269 23000 12 81 190 149 50 1 187 275 185 271 182 268 24000 14 78 183 144 48 3 184 275 181 271 178 267 25000 16 75 5 177 139 46 8 180 273 177 270 174 266 26000 18 73 171 134 45 2 176 272 174 269 170 263 27000 20 70 165 130 43 6 172 271 169 267 168 265 28000 22 67 159 124 41 9 168 269 165 265 161 258 29000 2...

Page 359: ...0 21000 2 76 4 190 150 50 3 183 266 181 263 179 259 22000 0 74 184 144 48 6 180 265 178 262 175 258 23000 2 71 2 178 140 47 0 176 264 174 262 171 257 24000 4 69 172 135 45 4 173 264 171 261 167 255 25000 6 66 165 130 43 7 169 262 166 259 162 253 26000 8 63 4 159 125 42 1 165 261 162 256 158 250 27000 10 60 7 154 120 40 6 160 258 157 254 153 247 28000 12 58 148 116 39 0 157 257 153 251 148 243 2900...

Page 360: ...8 43 1 282 163 228 2 43 7 287 161 231 21000 57 5 40 40 4 265 166 223 30 40 8 267 164 225 20 41 5 271 163 228 10 42 1 276 161 230 0 42 7 280 160 232 22000 57 0 42 39 5 258 165 224 32 39 9 262 163 227 22 40 6 265 161 229 12 41 2 269 159 232 1 41 7 273 158 234 23000 56 5 44 38 7 254 163 226 34 39 1 256 161 228 24 39 7 260 159 231 13 40 3 265 158 233 3 40 9 267 156 235 24000 56 0 46 37 9 249 161 227 3...

Page 361: ... 21 37 1 243 151 238 11 37 6 247 149 240 28000 54 0 53 35 1 229 154 231 43 35 5 234 152 235 33 36 1 236 151 237 23 36 5 238 149 239 13 37 0 243 147 241 29000 53 5 55 34 6 227 152 232 45 35 0 229 150 236 35 35 5 231 149 239 25 35 9 236 147 241 15 36 3 238 145 242 30000 54 0 57 34 4 225 152 237 47 34 8 228 150 239 37 35 2 231 148 242 27 35 7 234 146 244 17 36 1 236 144 246 31000 54 5 59 34 2 224 151...

Page 362: ...8 45 0 295 166 233 3 45 6 298 164 234 21000 62 5 40 42 3 278 169 226 30 42 9 280 167 229 20 43 5 284 166 232 9 44 1 289 164 234 1 44 6 293 162 236 22000 62 0 42 41 5 271 167 227 32 42 0 276 165 230 21 42 5 278 164 233 11 43 2 282 162 236 1 43 7 287 161 238 23000 61 5 44 40 6 267 165 229 34 41 1 269 164 232 23 41 7 273 162 235 13 42 3 278 161 237 3 42 9 280 159 239 24000 61 0 46 39 8 260 164 230 35...

Page 363: ... 21 39 2 258 153 242 11 39 8 260 151 244 28000 59 0 53 37 0 243 157 236 43 37 5 245 155 238 33 38 0 249 153 241 23 38 6 254 151 243 13 39 1 256 149 245 29000 58 5 55 36 5 238 155 238 45 37 0 243 153 239 35 37 5 245 151 242 25 38 0 249 149 244 15 38 5 251 147 246 30000 59 0 57 36 4 238 154 240 47 36 9 242 152 243 37 37 3 244 150 245 27 37 8 248 148 247 17 38 2 250 146 248 31000 59 5 59 36 3 238 154...

Page 364: ... 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 24 19 6 3 35 18000 12 00 45 35 11 9 50 09 00 31 24 8 2 40 07 10 23 18 6 1 31 16000 10 40 40 31 10 6 45 08 00 28 22 7 4 35 06 25 20 16 5 3 27 14000 09 20 35 28 9 2 40 07 00 24 19 6 3 30 05 35 18 14 4 8 23 12000 08 0...

Page 365: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE Page 5 11 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 366: ...ght 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 72 24 6 5000 25 20 6 6 75 60 19 8 27 21 7 1 81 63 21 4 10000 23 18 6 1 69 54 18 2 24 19 6 3 72 57 19 0 15000 20 16 5 3 60 48 15 8 22 17 5 8 66 51 17 4 20000 19 15 5 0 57 45 15 0 20 16 5 3 60 48 15 8 Figure 5 12 1 H...

Page 367: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 5 PERFORMANCE Page 5 12 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 368: ...0 1380 1475 2000 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 ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1280 1345 1445 1575 1705 2200 2330 2460 2645 2790 1310 1410 1510 1640 1770 2300 2430 2560 2720 2885 1380 1475 1575 1705 1835 2360 2495 2655 2820 2985 1445 1...

Page 369: ...2360 2490 1000 1065 1150 1230 1310 2070 2200 2330 2460 2590 1030 1115 1200 1280 1360 2135 2265 2395 2525 2690 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1080 1150 1230 1345 1445 2200 2330 2460 2645 2790 1115 1200 1280 1395 1510 2300 2430 2560 2720 2885 1180 1245 1345 1445 1560 2360 2495 2655 2820 2985 1230 1310 1395 1510 1610 2430 256...

Page 370: ...T 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 OF WEIGHT AND BALANCE GRAPH 6 4 1 DETERMINING EMPTY AIRPLANE CHARACTERISTICS 6 4 7 6 5 LIST OF EQUIPMENT 6 5 1 ...

Page 371: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 0 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 372: ...ight 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 of specific optional equipment installed on your airplane as delivered from the factory can be found in the records carried in the airplane IT IS THE PILOT S RESPONSIBILITY TO ENSURE THAT THE AIRPLANE IS LOADED ...

Page 373: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 1 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 374: ...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 The list of this equipment and the total weight is noted in the Individual Inspection Record ...

Page 375: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 2 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 376: ...ermined using the baggage loading graph Figure 6 3 1 Stowing straps are provided for securing parcels and baggage on pressurized baggage compartment floor A partition net separating the cabin from the baggage compartment is attached to frame C14 The rear non pressurized baggage compartment is provided with a holding elastic net WARNING IT IS THE PILOT S RESPONSIBILITY TO CHECK THAT ALL THE PARCELS...

Page 377: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 3 2 Rev 7 Figure 6 3 1 BAGGAGE LOADING GRAPH ...

Page 378: ... and the corresponding balance allow to calculate the airplane 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 balance for instance optional equipment installation UTILIZATION OF WEIGHT AND BALANCE GRAPH Figures 6 4 1 6 4 1A and 6 4 2 6 4 2A Refer to Supplement...

Page 379: ... 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 in the arrow gives pitch value between two oblique lines c Then continue the line vertically downwards up to interception of oblique lines of second heading and work in the same way as before procedure described in b d Proceed in ...

Page 380: ...SECTION 6 WEIGHT AND BALANCE TBM 700 PILOT S OPERATING HANDBOOK Page 6 4 3 Rev 7 Figure 6 4 1 LOADING SAMPLE in Kg and Litres ...

Page 381: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 4 4 Rev 7 Figure 6 4 1A LOADING SAMPLE in lbs and us gal ...

Page 382: ...SECTION 6 WEIGHT AND BALANCE TBM 700 PILOT S OPERATING HANDBOOK Page 6 4 5 Rev 7 Figure 6 4 2 WEIGHT AND BALANCE GRAPH in Kg and Litres ...

Page 383: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 4 6 Rev 5 Figure 6 4 2A WEIGHT AND BALANCE GRAPH in lbs and us gal ...

Page 384: ...elow to compute new empty weight and corresponding balance if necessary EQUIPMENT OR WEIGHT MODIFICATION BASIC EMPTY WEIGHT DATE OR MODIFICATION DESCRIPTION Weight lb Arm in Moment lb in 1000 Weight W Arm do Moment According to delivery Figure 6 4 3 SAMPLE WEIGHT AND BALANCE RECORD CG m a c do 172 93 59 45 100 Use the above formula to express arm do in of mean aerodynamic chord NOTE Arm expressed ...

Page 385: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 6 WEIGHT AND BALANCE Page 6 4 8 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 386: ... the factory in your specific airplane is provided in your airplane file Columns showing weight in pounds and arm in inches provide the weight and center of gravity location for the equipment In the list of Required Standard or Optional equipment not restrictive a letter R S O or A allows classifying the equipment R equipment items required for certification S standard equipment items A optional e...

Page 387: ...D70 REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 01 SPECIFIC OPTIONAL EQUIPMENT S 01019 DME KN63 shield case SOCATA 0 33 0 150 231 50 5 880 S 01026A Flight ceiling at 31000 ft SOCATA A 01029 Provision for TBM 700C2 SOCATA 112 17 50 88 230 83 5 863 ...

Page 388: ...1 CONDEC EATON 0 08 0 035 153 94 3 910 S Cabin pressurization dump solenoïd valve 5112 1 AEROSPACE 0 44 0 200 181 10 4 600 S Cabin aP warn switch 17 600 01 UMA 0 14 0 065 139 76 3 550 S Check valve 985C 63 3 LE BOZEC 0 20 0 090 118 11 3 000 S Outflow valve controller 130618 1 GARRETT 1 65 0 750 157 48 4 000 S Outflow valve 103760 1 GARRETT 1 54 0 700 317 32 8 060 S Safety valve 103760 2 GARRETT 1 ...

Page 389: ... 25 2 902 S Water separator 6055C000 002 NORMALAIR GARRETT 2 05 0 930 97 80 2 484 21 55 Vapor cycle cooling system S Compressor condenser pack 11 92364 SECAN 55 12 25 000 125 39 3 185 S Evaporator 11 91364 SECAN 11 02 5 000 309 45 7 860 21 60 Temperature regulation S Temperature control valve 6094C000 001 NORMALAIR GARRETT 2 50 1 134 113 15 2 874 S Controller 6054C000 001 NORMALAIR GARRETT 2 43 1 ...

Page 390: ...065 00086 0008 HONEYWELL 0 882 0 400 155 51 3 950 S Amplifier separator KA 21 SOCATA 1 279 0 580 194 88 4 950 S Audio alerter KAA 15 P N 071 01466 0000 HONEYWELL 0 750 0 340 171 26 4 350 S Pitch servo KS 270A P N 065 00061 0050 HONEYWELL 2 601 1 180 247 44 6 285 S Pitch trim servo KS 272A P N 065 00059 0023 HONEYWELL 2 403 1 090 157 48 4 000 S Roll servo KS 271A P N 065 00060 0001 HONEYWELL 2 403 ...

Page 391: ...0 A 23009A Additional equipment for electrostatic dischargers CHELTON Neglig S 23011F Radio stereo headset Serie X BOSE O 23011G Radio stereo headset HMEC 25 6A SENNHEISER A 23012B Audio Marker PMA 7000 MS with EFIS equipment PS ENGINEERING 1 43 0 650 151 57 3 850 O 23017C COM1 NAV 1 KX 165A with EFIS with KN40 converter HONEYWELL 3 99 1 810 153 54 3 900 O 23022C COM1 NAV 2 with EFIS KX 165A HONEY...

Page 392: ... fuselage 16 21B P3 CHELTON 0 86 0 390 271 65 6 900 GPS antenna GA 56 GARMIN 0 46 0 210 204 84 5 203 Version C antenna rearward of frame 7 From S N 312 Transceiver GNS530 GARMIN 8 49 3 850 151 57 3 850 VHF antenna under fuselage 16 21B P3 CHELTON 0 86 0 390 271 65 6 900 GPS antenna GA 56A GARMIN 0 46 0 210 204 84 5 203 A 23025 COM NAV GPS 2 B RNAV system with EFIS interfaced with GI 106A CDI and E...

Page 393: ...S antenna GA 56 GARMIN 0 46 0 210 204 84 5 203 CDI GI 106A MID CONTINENT 1 46 0 660 155 51 3 950 Version C antenna on R H side of aircraft centerline From S N 312 Transceiver GNS530 GARMIN 8 49 3 850 151 57 3 850 VHF antenna upper fuselage 16 21B P3 CHELTON 0 86 0 390 271 65 6 900 GPS antenna GA 57 GARMIN 0 46 0 210 204 84 5 203 CDI GI 106A MID CONTINENT 1 46 0 660 155 51 3 950 Version E antenna o...

Page 394: ...TANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O A 23026 VHF Data Link KDR510 HONEYWELL Version A antenna under wing 2 45 1 113 191 69 4 869 A 0214 23 Receiver GDL 69A Coupled with MFD GMX 200 and Audio Marker GMA 340 From S N 312 equipped with OPT70 23025 GNS 530 2 Version C Valid for US and CANADA GARMIN 2 80 1 27 204 72 5 200 ...

Page 395: ...05 ECE 11 02 5 000 127 95 3 250 R Stand by generator T700A243008000601 SOCATA 12 13 5 500 102 36 2 600 R Starter generator 8012F AUXILEC 24 47 11 100 110 24 2 800 R Voltmeter VT99 04 FALGAYRAS 0 22 0 100 175 20 4 450 O 24001A Battery 4076 1 SAFT 83 33 37 800 112 00 2 845 S 24002A Lead Acid battery RG 380E 44 CONCORDE 85 98 39 000 112 20 2 850 A 0303 24 Charger Maintainer for lead acid battery Airp...

Page 396: ... A 25006H Refreshment cabinet Composite wood and leather SOCATA 20 28 9 200 202 76 5 150 A 25009G BECKER audio cabinet SOCATA 26 23 11 900 225 43 5 726 A 0171 25 Generation 2005 cabinets From S N 328 Vers A L H low cabinet Vers B R H low cabinet Vers C Removable low insu lated picnic bag Vers D L H top storage cabinet Vers E R H top storage cabinet Vers F R H top storage cabinet audio Vers G L H t...

Page 397: ...é SOCATA 1 98 0 900 314 64 7 992 S 25026A Partition net between the cabin and the baggage compartment SOCATA 2 76 1 250 289 53 7 354 A 25027A Cargo transportation capability pilot alone on board SOCATA 25 35 11 500 246 69 6 266 A 25027B Cargo transportation capability 1 pilot 1 front passenger SOCATA 30 86 14 000 246 10 6 251 A 25032 Front seats ease covers SOCATA 2 76 1 250 183 78 4 668 A 0151 25...

Page 398: ...ack to flight direction T700A2522004 PPI 25 507 11 570 218 31 5 545 O Rear divan T700B2520018 PPI 57 319 26 000 271 30 6 891 Leather seats Belts S Pilot s seat T700A2512082 SOCATA 27 56 12 500 182 68 4 640 S Front R H Seat T700A2512082 SOCATA 27 56 12 500 182 68 4 640 S L H Intermediate seat back to flight direction T700A2522004 SOCATA 24 25 11 000 218 30 5 545 S R H Intermediate seat back to flig...

Page 399: ...LT NAV interface box 453 6500 ARTEX 2 69 1 220 353 15 8 970 Antenna 21 41 CHELTON 0 31 0 140 318 70 8 095 O 25030B Three frequency emergency locator transmitter C406 1 with base and reinforcement Nav interface and GPS coupled of which ARTEX 7 63 3 459 350 39 8 900 ELT C406 1 ARTEX 3 36 1 525 354 72 9 010 ELT NAV interface box 453 6500 ARTEX 2 69 1 220 353 15 8 970 Antenna 21 41 CHELTON 0 31 0 140 ...

Page 400: ...MENT SUPPLIER REQUIRED R OR STANDARD S OR OPTIONAL A or O EQUIPMENT ITEM OPT70 or MOD70 S R A O O 0153 25C Emergency beacon KANNAD 406AF installed in tail area with support SERPE IESM 2 45 1 110 347 09 8 816 ELT NAV interface box CS144A SERPE IESM 1 81 0 823 347 09 8 816 Antenna 1327 82 CHELTON 0 33 0 150 339 37 8 620 ...

Page 401: ...b kg ARM in m 26 FIRE PROTECTION S 26001B Portable fire extinguisher unit 863520 00 L HOTELLIER 3 64 1 650 192 16 4 881 A 26002B Engine fire detection system L HOTELLIER 1 45 0 660 96 06 2 440 A 0391 26 Portable fire extinguisher unit 74 00 AIR TOTAL Version A AIR TOTAL 4 89 2 220 170 11 4 321 Version B AIR TOTAL 4 89 2 220 192 16 or 194 16 4 881 or 4 932 Version C AIR TOTAL 4 96 2 250 193 80 4 92...

Page 402: ...trol R Rudder trim actuator 145700 02 LPMI 1 54 0 700 395 27 10 040 R Trim and flap indicator 4724 PEKLY S A 1 10 0 500 159 45 4 050 S AFC and electric trim control on R H control wheel SOCATA 0 88 0 400 157 48 4 000 27 30 Pitch control S Pitch trim actuator 145400 02 LPMI 1 21 0 550 425 20 10 800 27 50 Wing flaps control R Flap control including AVIAC 15 52 7 040 218 50 5 550 Flap motor 6157 1 AV...

Page 403: ...IQUE 4 59 2 080 133 07 3 380 R A35 fuel sequencer unit TFE 1 10 0 500 125 98 3 200 28 40 Fuel indication R Amplifier indicator in us gal 748 859 2 INTER TECHNIQUE 1 48 0 670 157 48 4 000 R Fuel pressure indicator PC99 06 FALGAYRAS 0 31 0 140 157 48 4 000 R Inboard L H gage 768 403 or 762438 1 0 INTER TECHNIQUE 0 33 0 150 183 07 4 650 R Inboard R H gage 768 404 or 762439 1 0 INTER TECHNIQUE 0 33 0 ...

Page 404: ... wing T700A3010001002 SOCATA 5 73 2 600 173 23 4 400 S Deicer inboard R H wing T700A3010001003 SOCATA 5 73 2 600 173 23 4 400 S Deicer middle L H wing T700A3010001004 SOCATA 3 75 1 700 173 23 4 400 S Deicer middle R H wing T700A3010001005 SOCATA 3 75 1 700 173 23 4 400 S Deicer outboard L H wing T700A3010012000 SOCATA 2 65 1 200 173 23 4 400 S Deicer outboard R H wing T700A3010001007 SOCATA 3 31 1...

Page 405: ...ev 8 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 30 60 Propeller deicing S Modular brush assy 3E2044 2 BF GOODRICH 0 44 0 200 47 05 1 195 S Timer 3E2311 4 BF GOODRICH 0 44 0 200 200 79 5 100 ...

Page 406: ...ent instruments S Chronometer 420000 ASTROTECH 0 15 0 070 157 48 4 000 O 31001A Stop watch Q18 945 22 28 1 LE THOMMEN 0 42 0 190 157 48 4 000 O 31002A Hourmeter 56457 3 engine running time DATCON 0 55 0 250 156 30 3 970 O 31002B Hourmeter 56457 3 flying time DATCON 0 55 0 250 156 30 3 970 31 50 Aural warning R Aural warning system T700A3155011000 SOCATA 0 66 0 300 183 07 4 650 31 60 Visual warning...

Page 407: ...r D23767000 MESSIER DOWTY 51 59 23 400 200 39 5 090 O 0141 32 R H main landing gear D23768000 MESSIER DOWTY 51 59 23 400 200 39 5 090 32 20 Nose landing gear R Nose gear 21130 001 00 ERAM 52 910 24 000 93 70 2 380 O 0141 32 Nose gear D23766000 MESSIER DOWTY 53 57 24 300 93 70 2 380 32 30 Extension and retraction R Door actuator EC 6230 HRL 1 35 0 610 192 91 4 900 R Main locking actuator 08 1480 HR...

Page 408: ... Brake assembly 030 19100 PARKER 14 99 6 800 204 33 5 190 R Main tire 18x5 5 8 190T MICHELIN 12 20 5 534 204 33 5 190 R Main tire 18x5 5 8PR FLE GOODYEAR 13 45 6 101 204 33 5 190 R Master cylinder 010 07801 PARKER 0 88 0 400 145 67 3 700 R Master cylinder 010 07802 PARKER 0 88 0 400 145 67 3 700 R Nose tire 5 00x5 6PR DUNLOP 6 400 2 903 89 57 2 275 R Nose tire 5 00 5 10PR TL MICHELIN 6 000 or 5 60...

Page 409: ...4 Rev 8 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 Main wheel 040 27000 PARKER 11 02 5 000 204 33 5 190 R Parking brake valve T700A3240010 or T700B3240001 SOCATA 0 33 0 150 157 48 4 000 ...

Page 410: ...240 3 WEMAC 0 11 0 050 181 10 4 600 A 33001A PULSELITE unit 1NC P N 1220 2410 2 for landing lights PRECISE FLIGHT 1 27 0 574 202 60 5 146 33 40 External lighting S L H wing inspection light icing detection T700A3340012 SOCATA 0 20 0 090 151 57 3 850 S Landing lights 4596 GE 0 79 0 360 179 13 4 550 S Taxi light assy T700A3340006 SOCATA 1 10 0 500 93 70 2 380 S NAV Anticollision system With bulb str...

Page 411: ...eference plug T700A3415017 SOCATA Neglig S Static reference selector TB30 77010000 SOCATA 0 22 0 100 157 48 4 000 S Vertical speed indicator 3 L H Instrument panel 7060 C 118 UNITED INSTRUMENTS 0 82 0 370 157 48 4 000 R VMO aP switch 32202 1 HYDRA ELECTRIC 0 22 0 100 141 73 3 600 S 34011A Airspeed indicator 1 8140 Code B 666 UNITED INSTRUMENTS 0 75 0 340 157 48 4 000 O 34012A Servoed encoding alti...

Page 412: ... 900 Version B Standard altimeter 2 kept 4 10 1 86 153 54 3 900 34 13 Outside temperature S Outside air temperature indicator 301C DAVTRON 0 27 0 120 157 48 4 000 34 21 Heading reference system S Directional gyro KG 102A P N 060 00015 0000 KING 4 30 1 950 192 91 4 900 A Flux valve KMT 112 P N 071 01052 0000 KING 0 31 0 140 181 10 4 600 S HSI Slave KA 51B P N 071 01242 0006 KING 0 20 0 090 153 54 3...

Page 413: ... 3 00 1 360 172 83 4 390 Converter KN 40 HONEYWELL 4 23 1 920 257 87 6 550 O 34020F RMI 1 KNI 582 L H instrument panel EFIS coupled HONEYWELL 3 51 1 590 161 50 4 102 Converter KN 40 HONEYWELL 4 23 1 920 257 87 6 550 34 28 Electronic flight instrumentation system S 34001C EFIS EFS 40 AP KFC 325 KING with DME KDI 574 without KN 40 converter KING 67 813 30 760 125 63 3 191 34 31 Marker S MARKER anten...

Page 414: ...es EFIS coupled of which 8 18 3 710 195 82 4 974 Transceiver KRA 405B HONEYWELL 2 80 1 270 231 18 5 872 Indicator KNI 415 HONEYWELL 1 70 0 770 155 24 3 943 Antennas Qty 2 DM 19 2 1 DORNE MARGOLIN 0 40 0 180 182 09 4 625 and 205 83 5 228 A 34037H Radioaltimeter KRA 405B EFIS coupled with aural warning and without KNI indicator of which 5 73 2 600 209 37 5 318 Transceiver KRA 405B HONEYWELL 2 80 1 2...

Page 415: ...BF GOODRICH 2 29 1 040 218 50 5 550 Processor TRC899 BF GOODRICH 8 88 4 030 133 86 3 400 A 34059B SKYWATCH HP Traffic advisory system SKY 899 TAS EFIS coupled with indicator on MFD KMD 850 or GNS 530 of which BF GOODRICH 12 72 5 770 151 18 3 840 Antenna NY164 BF GOODRICH 2 29 1 040 218 50 5 550 Processor TRC899 BF GOODRICH 8 88 4 030 133 86 3 400 A 34061A TAS TAWS system KMH 880 not autonomous wit...

Page 416: ... 0 95 0 430 0 95 0 430 218 11 5 540 256 69 6 520 Antenna KA 92 HONEYWELL 0 26 0 120 196 85 5 000 A 34061C TAS TAWS system KMH 880 with indicator on MFD KMD 850 or GMX 200 of which HONEYWELL 15 65 7 10 158 42 4 024 Processor KMH 880 HONEYWELL 9 68 4 390 133 07 3 380 Control box MD41 1208 MID CONTINENT 5 00 2 270 157 08 3 990 Antenna KA 815 upper fuselage under fuselage HONEYWELL 0 95 0 430 0 95 0 4...

Page 417: ...r A 34021G Transponder 2 interfaced with encoding altimeter 2 KT 76C HONEYWELL 3 17 1 440 150 59 3 825 Antenna KA 60 0 20 0 090 157 48 4 000 O 34026C Transponder 1 KT 76C of which HONEYWELL 3 17 1 440 150 59 3 825 Antenna KA 60 0 20 0 090 157 48 4 000 O 34057A Transponder 1 GTX327 of which GARMIN 5 60 2 540 148 66 3 776 Antenna KA 60 0 20 0 090 157 48 4 000 A 34058A Transponder 2 GTX327 of which G...

Page 418: ...der fuselage above fuselage between frames 6 and 7 0 20 0 090 0 20 0 090 150 08 3 812 193 22 4 908 34 54 Automatic Direction Finder ADF S 34055B ADF SC EFIS coupled Receiver KR 87 Indicator KI 227 P N 066 01072 0014 HONEYWELL 3 90 1 770 157 48 4 000 Antenna KA 44B HONEYWELL 2 80 1 270 195 28 4 960 RMI 1 KI 229 P N 066 03038 0000 L H instrument panel European countries only KING 2 87 1 300 153 86 3...

Page 419: ... 3 850 Receiver KN 63 HONEYWELL 2 80 1 270 232 28 5 900 Antenna KA 60 0 20 0 090 230 31 5 850 34 57 Global Positioning System GPS A 34033D GPS KLN 90B B RNAV EFIS coupled of which HONEYWELL 8 77 3 980 155 20 3 942 Receiver KLN 90B HONEYWELL 6 19 2 810 155 20 3 942 Antenna KA 92 HONEYWELL 0 26 0 120 240 16 6 100 34 62 Multifunction Display S 34054A Multifunction display KMD 850 HONEYWELL 6 42 2 910...

Page 420: ...TING HANDBOOK Page 6 5 35 Rev 8 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 35 OXYGEN S 35001B Gaseous oxygen system EROS INTER TECHNIQUE 24 69 11 200 178 19 4 526 ...

Page 421: ...T per unit lb kg ARM in m 37 VACUUM S Air ejector valve 19E17 5A LUCAS 0 66 0 300 116 14 2 950 S Gyro suction gage 3 310 5 UMA 0 14 0 065 157 48 4 000 S Gyro vacuum air filter 1J7 2 AIRBORNE 0 38 0 170 139 76 3 550 S Regulator and relief valve 38E 96 2D LUCAS 1 32 0 600 116 14 2 950 S Vacuum relief valve 691 21A LUCAS 0 33 0 150 139 76 3 550 S Valve 557 18 E LUCAS 0 35 0 160 118 11 3 000 ...

Page 422: ...37 Rev 8 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 52 DOORS A 52002A Pilot door SOCATA 44 092 20 000 171 26 4 350 A 0342 52 Additional landing gear doors SOCATA 6 613 3 000 204 33 5 190 ...

Page 423: ...ALANCE Page 6 5 38 Rev 8 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 57 WINGS S 57001A Utilization on runways covered with melting snow SOCATA a 7 716 a 3 500 200 00 5 080 ...

Page 424: ...D 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 4 blade HC E4N 3 E 9083 S K HARTZELL 153 22 69 500 43 11 1 095 61 20 Controls R Overspeed governor A210632 WOODWARD 2 73 1 240 59 06 1 500 S Propeller governor 8210 007 WOODWARD 2 65 1 200 59 06 1 500 ...

Page 425: ... OR STANDARD S OR OPTIONAL A or O EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 71 POWER PLANT R Turboprop engine PT6 A 64 P W CANADA 496 30 225 000 79 72 2 025 S Silentblocks Qty 4 95007 16 BARRY 2 92 1 325 79 72 2 025 71 60 Air inlet R Inertia ice separator actuator 148600 09A LPMI 1 72 0 780 62 99 1 600 ...

Page 426: ...ator Ng 5428 703 91 03 SEXTANT 1 290 0 585 151 57 3 850 R Propeller speed indicator 5428 704 91 03 SEXTANT 1 290 0 585 151 57 3 850 R Propeller tacho generator Np P N 32005 007 MIL G 26611 GEU 7 A QPL AIRCRAFT APPLIANCES AND EQUI LTD 0 981 0 445 55 12 1 400 R Torquemeter 5428 750 91 03 SEXTANT 1 257 0 570 151 57 3 850 R Torque transducer 8107 200 00 10 MORS SEXTANT 0 463 0 210 53 54 1 360 77 20 En...

Page 427: ...nit 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 Indicating O Oil dual indicator 5427 350 91 03 SEXTANT 1 179 0 535 151 57 3 850 R 79001A Oil pressure transmitter 8107 400 00 10 THALES 0 441 0 200 106 30 2 700 A 0169 79A Chip detection system 2 detectors P W CANADA Neglig A 0169 79B Chip detection system 1 detector P W CANADA Neglig ...

Page 428: ... 7 3 ACCOMMODATIONS 7 3 1 INSTRUMENT PANEL 7 3 1 DOORS WINDOWS AND EMERGENCY EXIT 7 3 22 SEATS BELTS AND HARNESSES 7 3 30 BAGGAGE COMPARTMENTS 7 3 31 7 4 FLIGHT CONTROLS 7 4 1 ROLL 7 4 1 ROLL TRIM 7 4 1 ELEVATOR 7 4 7 PITCH TRIM 7 4 7 RUDDER 7 4 13 RUDDER TRIM 7 4 13 7 5 LANDING GEAR 7 5 1 HYDRAULIC PRESSURE 7 5 2 LANDING GEAR CONTROL 7 5 2 LANDING GEAR INDICATOR 7 5 2 SAFETY 7 5 4 GROUND MANEUVER...

Page 429: ...1 FUEL TANKS 7 7 1 FUEL UNIT 7 7 1 TANK MANUAL SELECTOR 7 7 1 AUTOMATIC TANK SELECTOR 7 7 4 ELECTRIC BOOST PUMP 7 7 5 MAIN MECHANICAL BOOST PUMP 7 7 8 ENGINE FUEL SYSTEM 7 7 8 FUEL GAGING INSTALLATION 7 7 8 ETM INDICATOR COMPUTER 7 7 8 FUEL MONITORING INSTALLATION 7 7 9 FUEL SYSTEM DRAINING AND CLOGGING INDICATOR 7 7 10 7 8 ELECTRICAL SYSTEM 7 8 1 STARTER GENERATOR 7 8 1 STAND BY GENERATOR 7 8 2 B...

Page 430: ...STRUMENTS 7 11 1 STATIC PRESSURE SYSTEMS 7 11 1 DYNAMIC PRESSURE SYSTEM 7 11 4 7 12 VACUUM SYSTEM AND INSTRUMENTS 7 12 1 ATTITUDE INDICATOR 7 12 1 GYROSCOPIC INSTRUMENTS CONTROL 7 12 5 SUCTION GAGE 7 12 5 7 13 ICE PROTECTION EQUIPMENT 7 13 1 WING AND EMPENNAGE DEICING 7 13 1 PROPELLER DEICING 7 13 2 WINDSHIELD DEICING 7 13 2 HEATING OF PITOTS AND STALL WARNING SENSOR 7 13 3 TURBINE AIR INLET PROTE...

Page 431: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 0 4 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 432: ...e and its systems Some of the equipment described herein is optional and may not be installed in the airplane Details of other optional systems and equipment are presented in Section 9 Supplements of the pilot s operating handbook NOTE Description and operation of communication and radio navigation equipment are detailed in manufacturer technical handbooks ...

Page 433: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 0 DESCRIPTION Page 7 1 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 434: ...prising a hand rail allowing pilot and passengers boarding The occupants have access to cockpit and to rear seats through a central aisle A pilot door if installed located forward of the cabin on the left side allows to gain access to the cockpit by means of folding stairs The cabin rear part is a baggage compartment In fuselage non pressurized rear section a compartment located between the rear p...

Page 435: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 2 2 Rev 0 Figure 7 2 1 CABIN ARRANGEMENT ...

Page 436: ...poilers located in front of flaps on top skin side are mechanically linked to the ailerons Trim tab knob attached on the trailing edge of L H aileron is electrically activated by a trim knob through an actuator WING FLAPS Figure 7 2 2 The wing flaps are large span slotted flaps with a single rotation point They are activated by actuating rod controlled screw jacks linked to an electric motor locat...

Page 437: ...gging angle to fuselage horizontal datum 2 Sweep angle at 25 chord 0 Dihedral at datum plane 6 5 Aspect ratio platform reference 8 216 Taper ratio 0 608 Airfoil section at wing root RA 16 43 Airfoil section at wing tip RA 13 3 43 Twist 0 Aileron spoilers characteristics Global aileron area including trim tab 9 65 sq ft 0 897 m2 Aileron trim tab area 0 78 sq ft 0 072 m2 Spoiler area 1 80 sq ft 0 16...

Page 438: ...ON TBM 700 PILOT S OPERATING HANDBOOK Page 7 2 5 Rev 0 Figure 7 2 2 1 2 WING FLAPS 1 Geared motor 2 Internal actuator 3 Intermediate bearings 4 Wing flap 5 External actuator 6 Rods 7 Position indicator 8 Control selector ...

Page 439: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 2 6 Rev 0 Figure 7 2 2 2 2 WING FLAPS ...

Page 440: ...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 ratio 5 034 Elevator global area including trim tabs 21 76 sq ft 2 022 m2 Elevator trim tab area right datum plane 3 47 sq ft 0 322 m2 Vertical stabilizer characteristics Global area 33 28 sq ft 3 092 m2 Constructio...

Page 441: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 2 8 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 442: ...trument panel consists of three parts left central and right Left instrument panel Figure 7 3 3 includes general alarms flight indicators and instruments engine controls deicing controls and indicators landing gear control panel parking brake control and left station control wheel Central instrument panel Figure 7 3 4 surmounted by the stand by compass includes control and AP computer boxes adviso...

Page 443: ... red flashing indicator and a MASTER CAUTION amber flashing indicator located on instrument panel in front of the pilot illuminate as soon as one or several indicators of same color illuminate on the advisory panel To cancel and reset a general alarm press on the red or amber indicator A TEST push button and a BRIGHT DIM switch located on the right side of the advisory panel allows testing warning...

Page 444: ...d speaker According to the airplane configuration different signals are produced by the logic circuits gear up and idle high pitched sound gear up and extended flaps high pitched sound stall low pitched sound gear up idle and stall alternate high pitched d l it h d d g p g p and low pitched sounds gear up extended flaps and stall alternate high pitched g p p g p and low pitched sounds The aural wa...

Page 445: ...cted by AP ALT SEL circuit breaker the autopilot disconnection indicating buzzer is electrically supplied by BUS 3 bar and protected by AP ALERT circuit breaker and the emergency lighting rheostat is electrically supplied by BUS BAT bar and protected by PANEL EMER circuit breaker Amplifier The amplifier allows to fit alarm signals heard in head set to radio loud speaker It is fixed under cabin flo...

Page 446: ...he VMO buzzer emits three bips the alarm loud speaker emits alternate low pitched and high pitched sounds Release the knob to stop the alarms NOTE The test is effective for head equipment when AP TRIMS MASTER switch is set to ON Operation of the radar altimeter aural warning The radar altimeter aural warning momentary is coupled with the DH warning light permanent illumination on the radar altimet...

Page 447: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 6 Rev 0 Figure 7 3 1 INSTRUMENT PANEL ASSEMBLY Typical arrangement ...

Page 448: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 7 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 449: ...l warning horn 4 R H instrument panel emergency lighting 5 Cockpit floodlight switches rheostats 6 R H side upper panel postlight 7 R H cockpit floodlight 8 Ammeter 9 Voltmeter 10 ENGINE START switches Figure 7 6 5 11 ELECTRIC POWER switches Figure 7 8 5 12 GYRO INST gyroscopic instrument switches Figure 7 12 2 13 EXT LIGHTS external lighting switches Figure 7 8 6 14 L H cockpit floodlight 15 L H ...

Page 450: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 9 Rev 0 Figure 7 3 2 2 2 UPPER PANEL AND COCKPIT OVERHEAD PANEL ...

Page 451: ...t station control wheel tube 17 Parking brake control 18 EHSI indicator 19 RMI indicator 20 Deicing control and check panel Figure 7 13 1 21 Circuit breakers panel postlight without pilot door 22 AP DISC TRM INT red push button 23 Electric pitch trim control 24 Maps reading tablet 25 Electric rudder trim control 26 Left station reception micro jacks 27 L H station rudder pedals adjusting handle 28...

Page 452: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 11 Rev 7 Figure 7 3 3 2 2 LEFT INSTRUMENT PANEL Typical arrangement ...

Page 453: ...de controller see Section 9 3 Advisory panel Figure 7 3 8 4 Audio control box 5 COM NAV GPS 1 6 COM NAV GPS 2 7 Cabin interior lighting rheostats and switches Figure 7 8 7 8 RADIO MASTER switch Figure 7 14 1 9 EFIS MASTER switch see Section 9 10 AP TRIMS MASTER switch see Section 9 11 GND CLR ground communication indicating light Figure 7 14 1 ...

Page 454: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 13 Rev 0 Figure 7 3 4 2 2 CENTRAL INSTRUMENT PANEL Typical arrangement ...

Page 455: ...or 2 9 Transponder 2 10 DME 11 Hour meter 12 Adjustable air outlet 13 R H station rudder pedals adjusting handle 14 Right station reception micro jacks 15 Circuit breakers panel postlight with pilot door 16 Electric pitch trim control 17 Electric rudder trim control 18 AP DISC TRM INT red push button 19 Maps reading tablet 20 Radar altimeter buzzer 21 Cabin emergency air control RAM AIR control kn...

Page 456: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 15 Rev 0 Figure 7 3 5 2 2 RIGHT INSTRUMENT PANEL Typical arrangement ...

Page 457: ...dicators 2 Flaps position indicator 3 Propeller governor lever 4 Power lever 5 Flaps control 6 Condition lever 7 Levers friction adjustment 8 Emergency fuel control 9 Manual fuel tank selector Figure 7 7 2 10 Roll trim tab control 11 Pitch trim tab control 12 Lock for access door to landing gear emergency pump Figure 7 5 2 ...

Page 458: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 17 Rev 0 Figure 7 3 6 2 2 PEDESTAL CONSOLE Typical arrangement ...

Page 459: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 18 Rev 0 Figure 7 3 7 CIRCUIT BREAKERS PANEL Without pilot door ...

Page 460: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 19 Rev 0 Figure 7 3 7A CIRCUIT BREAKERS PANEL With pilot door ...

Page 461: ... tube Nr 1 not heated PITOT 2 Pitot tube Nr 2 not heated STALL HTR Stall warning not heated INERT SEP Inertial separator INERT SEP control switch set to ON VACUUM LO Vacuum generator vacuum 3 75 in Hg BAT OVHT Battery abnormal temperature if Cadmium Nickel battery installed BAT OFF Battery unconnected and main distribution bar supplied by another generator MAIN GEN Starter generator unconnected LO...

Page 462: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 21 Rev 0 Figure 7 3 8 2 2 ADVISORY PANEL AND GENERAL ALARMS WARNING LIGHTS ...

Page 463: ...wards Stairs down movement is damped by means of two gas struts and leads the hand rail to extend CAUTION RETRACT STAIRS BEFORE CLOSING ACCESS DOOR AND MAKE SURE DOOR DEFLECTION AREA IS CLEAR To retract stairs press on locking pin located on stairs front string board see detail 1 raise retractable handle see detail 2 and pull stairs inside cabin While stairs are retracted the hand rail folds up To...

Page 464: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 23 Rev 0 Figure 7 3 9 CABIN ACCESS DOOR ...

Page 465: ...ract 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 from outside the airplane press on knob on outside fuselage at the right side of the door The door driven by a geared motor tilts downwards up to a position near the complete closing Push the door until it alig...

Page 466: ... FOOTSTEP BEFORE CLOSING ACCESS DOOR Fold and tilt footstep upwards To close the door from inside the airplane pull the door until it aligns with fuselage and lock it by moving inside handle downwards Check that each latch is correctly engaged in its recess visible green marks The DOOR warning light located on advisory panel remains illuminated as long as cabin access door and or pilot access door...

Page 467: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 26 Rev 0 Figure 7 3 9A COCKPIT ACCESS DOOR PILOT DOOR ...

Page 468: ...aintained in the up position by a compensation rod Two interlocking type latches ensure its closing and it is equipped with a lock same key as for the access door pilot door if installed and FWD compartment door When the door is closed latches are flush with the fuselage profile Windows Windows do not open The windshield consists of two parts electrically deiced Emergency exit Figure 7 3 10 The em...

Page 469: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 28 Rev 0 Figure 7 3 10 EMERGENCY EXIT ...

Page 470: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 29 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 471: ... direction mounted 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 forwards to ease baggage loading in baggage compartment Belts and harnesses Figure 7 3 12 WARNING INCORRECT CLOSURE OF THE SAFETY BELT MAY INTRODUCE A RISK MAKE SURE IT IS TIGHTENED W...

Page 472: ...esignedforthecarryingoflowdensityloads loadingand unloading must be carried out with caution to avoid any damage to airplane The cabin is separated from the baggage compartment by a partition net intended to protect the passengers from injuries that could be caused by improper tie down of a content The partition net is mounted at frame C14 Figure 7 2 1 it is secured at the bottom to 4 points of th...

Page 473: ... longitudinal shift control 8 Front seat s height control 9 Front seat s back rest tilt control 10 Drawer for pilot s piddle pak front side new bags rear side used bags 11 Intermediate seat s back rest tilt control 12 Rear bench seat s back rest tilt control 13 Rear bench L H seat tilt control NOTE To have access to the baggage compartment pull forwards the back rest of rear bench L H seat then pu...

Page 474: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 3 33 Rev 0 Figure 7 3 11 2 2 SEATS ...

Page 475: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 3 34 Rev 0 Figure 7 3 12 FRONT OR REAR SEAT BELT with movable straps AND HARNESSES ...

Page 476: ...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 the floor The movement is then transmitted through cables to the spoiler mechanism and from the spoiler mechanism to wing roll lever which activates the aileron through a rod A rudder roll combination spring type sy...

Page 477: ...T S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 2 Rev 0 Figure 7 4 1 1 2 ROLL 1 Pedestal assembly 2 Control wheels 3 Fuselage roll lever 4 Spoiler 5 Aileron 6 Aileron control in wing 7 Spoiler control ...

Page 478: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 3 Rev 0 Figure 7 4 1 2 2 ROLL ...

Page 479: ...OOK 700 SECTION 7 DESCRIPTION Page 7 4 4 Rev 0 Figure 7 4 2 1 2 LATERAL TRIM 1 Roll trim tab 2 Aileron 3 Adjustable rods 4 Actuator 5 Trim tab control wiring 6 Aileron trim tab position indicator 7 Trim switch on pedestal console ...

Page 480: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 5 Rev 0 Figure 7 4 2 2 2 LATERAL TRIM ...

Page 481: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 6 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 482: ...ovided with an automatic anti tab automaticity about 0 3 which is also used as trim tab PITCH TRIM Figure 7 4 4 The pitch trim is accomplished through the two anti tabs located on left and right elevators The trim tab can be controlled electrically or manually It is activated through cables and a chain on two screw actuators attached to the horizontal empennage The electrical control consists of a...

Page 483: ...N 7 DESCRIPTION Page 7 4 8 Rev 0 Figure 7 4 3 1 2 ELEVATOR 1 Control wheel assembly 2 Elevators 3 Lever assembly fuselage rear part 4 Elevator bellcrank 5 Rod with presseal connection 6 Lever assembly under floor 7 Pedestal assembly 8 Actuator ...

Page 484: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 9 Rev 0 Figure 7 4 3 2 2 ELEVATOR ...

Page 485: ... SECTION 7 DESCRIPTION Page 7 4 10 Rev 7 Figure 7 4 4 1 2 PITCH TRIM 1 Cables 2 Pulleys 3 Pitch trim tabs 4 Actuating rods 5 Actuator 6 Pitch trim tab position indicator 7 Pitch trim manual control wheel 8 Pitch trim electrical control ...

Page 486: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 11 Rev 0 Figure 7 4 4 2 2 PITCH TRIM ...

Page 487: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 12 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 488: ...neath the instrument panel and a locking device on the rudder pedals This ball locking device allows selecting six different positions When landing gear is down rudder pedals are linked to nose gear steering system Spring system of rudder roll combination induces aileron deflection at the time of pedal displacement and vice versa RUDDER TRIM Figure 7 4 6 A trim tab hinged at two points located at ...

Page 489: ...700 SECTION 7 DESCRIPTION Page 7 4 14 Rev 0 Figure 7 4 5 1 2 RUDDER 1 Roll rudder combination bellcrank installation 2 Rudder pedals assembly 3 Control cables 4 Pulleys 5 Rudder lever assembly 6 Rod 7 Rudder 8 Nose gear steering rod ...

Page 490: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 15 Rev 0 Figure 7 4 5 2 2 RUDDER ...

Page 491: ...TING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 16 Rev 0 Figure 7 4 6 1 2 RUDDER TRIM 1 Trim switch on control wheel 2 Actuator 3 Rudder trim tab 4 Rods 5 Rudder trim control wiring 6 Rudder trim tab position indicator ...

Page 492: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 4 17 Rev 0 Figure 7 4 6 2 2 RUDDER TRIM ...

Page 493: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 4 18 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 494: ...so 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 provides up and down locking The nose wheel is steerable It is connected to pedals through a spring rod and is provided with a shimmy damper In UP position nose wheel is automatically disconnected Actuating cylinder...

Page 495: ... generator LANDING GEAR INDICATOR Figure 7 5 1 Landing gear position indication is accomplished by 4 warning lights 3 green indicator lights one per landing gear indicate that each landing gear is down locked 1 red warning light indicates that landing gears are operating or not locked down or up NOTE The red warning light flashes as soon as landing gears are operating and remains continuously on i...

Page 496: ...TBM 700 PILOT S OPERATING HANDBOOK Page 7 5 3 Rev 0 Figure 7 5 1 CONTROL PANEL AND LANDING GEAR INDICATING 1 Red warning light LDG GR 2 Green indicator light LDG GR 3 Landing gear control selector 4 Test switch 5 Test knobs ...

Page 497: ... 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 warning signal becomes alternated high pitched sound low pitched sound Emergency landing gear extension control Figure 7 5 2 Emergency landing gear extension control consists of a hand pump and a by pass selector This c...

Page 498: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 5 5 Rev 7 Figure 7 5 2 EMERGENCY LANDING GEAR EXTENSION CONTROL ...

Page 499: ...wivels about 20 Steering may be increased up to 28 by applying differential braking to each side Airplane may be towed by attaching a steering or towing bar on nose gear Refer to Chapter 8 6 for operation In that case nose wheel steering angle is limited to 28 Minimum turn diameter Minimum turn diameter Figure 7 5 4 is obtained by using nose gear steering and differential braking Since tight turns...

Page 500: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 5 7 Rev 8 Figure 7 5 3 MINIMUM TURN DIAMETER Full rudder pedals travel without using differential braking ...

Page 501: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 5 8 Rev 0 Figure 7 5 4 MINIMUM TURN DIAMETER Full rudder pedals travel by using differential braking ...

Page 502: ...s 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 and a PARK BRAKE warning light located on advisory panel To apply parking brake press on toe brake of rudder pedals and position control knob on ON PARK BRAKE warning light illuminates when control knob is positioned on ON NOTE Operating the parki...

Page 503: ... DESCRIPTION Page 7 5 10 Rev 0 Figure 7 5 5 1 2 BRAKE SYSTEM 1 Reservoir 2 Vent 3 R H station master cylinders 4 Parking brake control knob 5 Parking brake valve 6 Drain 7 Pilot s station master cylinders 8 L H brake assembly 9 R H brake assembly ...

Page 504: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 5 11 Rev 0 Figure 7 5 5 2 2 BRAKE SYSTEM ...

Page 505: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 5 12 Rev 0 Figure 7 5 6 PARKING BRAKE ...

Page 506: ...ntinues 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 two other ones power turbines independant from the first one drive propeller shaft through a reduction gear box Hot gases are evacuated through two exhaust stubs located laterally on both sides forward of...

Page 507: ...NT 1 Propeller governor 2 Exhaust stub 3 Axial compressors 4 Accessory gearbox 5 FCU Fuel control unit 6 Oil to fuel heater 7 Compressor stubshaft 8 Air intake 9 Centrifugal impeller 10 Combustion chamber 11 Compressor turbine 12 Power turbine 1st stage 13 Power turbine 2nd stage 14 Power turbineshaft ...

Page 508: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 6 3 Rev 0 Figure 7 6 1 2 2 POWER PLANT ...

Page 509: ...gine operation requires use of four levers located on pedestal console in cabin power lever Item 2 and its detent for reverse Item 6 propeller governor lever Item 1 condition lever Item 3 MAN OVRD emergency fuel regulation lever Item 5 NOTE Thumbwheel for lever friction Item 4 Figure 7 6 2 ENGINE CONTROLS LEVERS ...

Page 510: ...cks 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 cable Propeller governor lever The propeller governor lever activates the propeller governor located forward of the engine to select and maintain any propeller speed between 1600 and 2000 RPM This lever allows pr...

Page 511: ...t rearwards MAN OVRD emergency fuel regulation lever Emergency fuel regulation lever is normally in locked position In case of FCU or power lever failure it allows setting engine power manually Unlocking and locking are performed by pulling lever knob up NOTE The power available if the power lever fails will be limited by the position of the lever Lever friction Figure 7 6 2 A thumbwheel Item 4 lo...

Page 512: ...t illuminates on advisory panel when interturbine temperature exceeds 800 C Gas generator speed indicator Ng indicates generator rotation speed expressed in percent Oil pressure and temperature indicator ENG OIL is a dual indicator graduated in C and in PSI NOTE Each instrument is provided with marks indicating utilization limits Lubrication system monitoring is ensured by OIL PRESS warning light ...

Page 513: ...automatically recorded The ETM can be connected to a navigation system GPS The system consists of three major components the panel mounted indicator computer the various engine and environment transducers the external data recorder with the datakey located under the L H back seat PROP O SPEED TEST button allows checking the overspeed valve for correct operation ITT TEST button allows checking the ...

Page 514: ...RATING HANDBOOK Page 7 6 9 Rev 0 Figure 7 6 3 ENGINE INSTRUMENTS 1 Torque indicator 2 PROP O SPEED TEST knob 3 Propeller indicator 4 ITT indicator 5 ITT test knob 6 Ng indicator 7 Oil pressure and temperature indicator 8 ETM indicator computer ...

Page 515: ...en the stopwatch is activated this switch starts and stops it 4 STOPWATCH RESET BUTTON Press this button to activate the stopwatch Resets the stopwatch once it has been stopped 5 PAGE UP DOWN SWITCH Used for scrolling through the pages of each file 6 INCREMENT DECREMENT SWITCH This switch is used to scroll through subpages and increment or decrement an input value such as gross weight or fuel adde...

Page 516: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 6 11 Rev 0 Figure 7 6 4 2 2 ETM INDICATOR COMPUTER ...

Page 517: ...ng up refer to Section 8 ENGINE STARTING Figure 7 6 5 Ignition function Ignition system consists of an ignition unit and two spark igniter plugs in power plant a three position IGNITION switch OFF AUTO ON located on ENGINE START panel at upper panel and IGNITION warning light located on advisory panel Ignition unit supplies from 28 Volt source high voltage current necessary to spark igniter plugs ...

Page 518: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 6 13 Rev 0 Figure 7 6 5 ENGINE STARTING ...

Page 519: ...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 water ice fine gravels sand Separator consists of two movable vanes During normal operation air is channelled directly towards engine air inlet To separate particles suspended in the air vanes are pos...

Page 520: ...upplies fuel nozzles flow being controlled by fuel regulator FCU Fuel provided by engine driven main pump mechanical enters high pressure pump through a filter then it is discharged under pressure into fuel regulator 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...

Page 521: ...Propeller overspeed limiter is installed on left side of the reduction gear box It prevents a propeller overspeed in case of main propeller governor failure Propeller overspeed limiter is equipped with a test solenoïd which allows performing ground tests by arming limiter under normal overspeed power PROP O SPEED TEST propeller test push button Figure 7 6 3 of overspeed limiter is located on instr...

Page 522: ...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 pitch allows reduced taxiing speed or landing roll Change from idle to reverse position is performed with power lever Refer to Paragraph ENGINE CONTROLS Propeller overspeed regulator tests Figure 7 6 3 PROP O SPEED ...

Page 523: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 6 18 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 524: ... a suction strainer and three level gages FUEL UNIT The fuel unit combines shut off valve tank selector and filter functions It is connected to the manual selector through a mechanical control The fuel filter is located in a bowl at the lower part of the unit It is fitted with a by pass valve a clogging indicator and a drain valve TANK MANUAL SELECTOR Figure 7 7 2 The tank manual selector is locat...

Page 525: ...mitter 9 Fuel jet 10 Main mechanical boost pump 11 Electric boost pump 12 Fuel filter 13 Filter clogging by pass valve 14 Filter clogging indicator 15 Fuel unit 16 Filter drain 17 Fuel return pipe 18 Filling port 19 NACA scoop 20 Tank vent valve 21 Fuel level gages 22 Tank drain valve 23 Check valve 24 Low level detector 25 Suction strainer 26 Fuel pressure indicator 27 Fuel gage indicator 28 Sequ...

Page 526: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 7 3 Rev 0 Figure 7 7 1 2 2 FUEL SYSTEM ...

Page 527: ...the selected tank The sequencer controls the time during which the selected tank will operate This time varies depending on airplane conditions Airplane on ground tank is changed every minute and 15 seconds Pre MOD70 402 28 Airplane in flight tank is changed every ten minutes as long as FUEL L LO or FUEL R LO low level warning light is not illuminated When the first low level warning light illumin...

Page 528: ...eferably choose the tank from which he wants to take fuel In all cases proper system operation is indicated by rotation of the manual selector Setting FUEL SEL switch to MAN position or setting manual selector to OFF position leads to system de activating and illumination of AUTO SEL warning light on advisory panel AUTO SEL warning light also illuminates when order given by the sequencer has not b...

Page 529: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 7 6 Rev 0 Figure 7 7 2 MANUAL SELECTOR OF FUEL TANKS ...

Page 530: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 7 7 Rev 0 Figure 7 7 3 FUEL CONTROL PANEL ...

Page 531: ...is a capacitive type and consists of a dual indicator graduated in us gallons Figure 7 7 3 and fuel level gages Three fuel level gages are installed in each tank The wing root side fuel level gage is equipped with a low level detector which leads to FUEL L LO or FUEL R LO warning light illumination when usable fuel quantity remaining in the concerned fuel tank is under about 9 1 us gal 34 6 Litres...

Page 532: ...sure at main booster pump outlet Indications provided by illumination of warning lights on advisory panel FUEL OFF Fuel tank selector set to OFF FUEL PRESS Fuel pressure at mechanic pump outlet under 10 psi 2 psi AUX BP ON Electric boost pump operating FUEL L LO Fuel quantity in L H fuel tank under about 9 1 us gal 34 6 Litres of usable fuel FUEL R LO Fuel quantity in R H fuel tank under about 9 1...

Page 533: ...pick off fuel at the two drain valves of each tank and at the filter vent valve A red filter bypass flag on the fuel unit and visible from outside when an inspection door located on L H side under front baggage compartment is open indicates filter clogging A push button adjacent to the inspection door controls the illumination of a light provided to improve visibility of the clogging indicator Thi...

Page 534: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 7 11 Rev 0 Figure 7 7 4 2 2 FUEL SYSTEM DRAINING POINTS AND CLOGGING INDICATOR ...

Page 535: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 7 12 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 536: ...de It 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 front baggage compartment upper section Indicating and checking warning lights are grouped on advisory panel STARTER GENERATOR The starter generator is the main electrical power source It only perform...

Page 537: ...d 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 bus bar is controlled through SOURCE selector set to BAT position BAT OFF warning light is illuminated when battery is isolated from the main bus and when main bus is supplied through another source GROUND POWER RE...

Page 538: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 3 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 539: ...n bus bar through ESS BUS TIE selector set to NORM position ESS BUS TIE selector is attached 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 breaker BUS BAT bar is directly connected to the battery it is protected by a fuse located in electrical power c...

Page 540: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 5 Rev 0 Figure 7 8 1 ELECTRICAL DIAGRAM ...

Page 541: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 8 6 Rev 0 Figure 7 8 2 1 2 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 542: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 7 Rev 0 Figure 7 8 2 2 2 ELECTRICAL DISTRIBUTION OF BUS BARS ...

Page 543: ...tion AUDIO WARN Audio warnings protection AUDIO CD reader protection CD if installed ESS BUS Essential bus 1 1 circuit protection ESS BUS Essential bus 2 2 circuit protection MEMORY Stop watch and CLOCK flowmeter protec ACCESS Cabin lightings access door closing geared motor protec CABIN BLEEDCabin air bleed valve protec AIR Cabin ventilation and vapor COND cycle cooling system protec EHSI EHSI pr...

Page 544: ...0 PILOT S OPERATING HANDBOOK Page 7 8 9 Rev 0 Figure 7 8 3 2 3 CIRCUIT BREAKER PANEL HONEYWELL typical arrangement NOTE If an additional equipment is installed its circuit breaker is installed on a free location Without pilot door ...

Page 545: ...OOK 700 SECTION 7 DESCRIPTION Page 7 8 10 Rev 0 Figure 7 8 3 3 3 CIRCUIT BREAKER PANEL GARMIN typical arrangement NOTE If an additional equipment is installed its circuit breaker is installed on a free location Without pilot door ...

Page 546: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 11 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 547: ...e protec AIR Cabin ventilat and vapor COND cycle cooling system protec ELT Emergency beacon protection EHSI EHSI protection EADI EADI protection GYRO EFIS static converter protection RMI RMI 1 protection ADI 2 ADI No 2 protection RMI 2 RMI 2 protection HSI 2 HSI 2 protection RADIO ALTI RADIO ALTI protection 28VDC PLUGS28 volts plugs protection PHONE MKR Reception line and loudspeaker MKR protectio...

Page 548: ...0 PILOT S OPERATING HANDBOOK Page 7 8 13 Rev 0 Figure 7 8 3A 2 3 CIRCUIT BREAKER PANEL HONEYWELL typical arrangement NOTE If an additional equipment is installed its circuit breaker is installed on a free location With pilot door ...

Page 549: ...BOOK 700 SECTION 7 DESCRIPTION Page 7 8 14 Rev 0 Figure 7 8 3A 3 3 CIRCUIT BREAKER PANEL GARMIN typical arrangement NOTE If an additional equipment is installed its circuit breaker is installed on a free location With pilot door ...

Page 550: ...us bar Indications provided by warning light illumination are as follows BAT OVHT Overheat inside the battery if Cadmium Nickel battery installed BAT OFF Battery is not connected to main bus bar and the latter is supplied by another power source MAIN GEN Starter generator is not connected to main bus bar LO VOLT Battery voltage is below the minimum value and main bus bar is supplied GPU Ground pow...

Page 551: ...receptacle short circuit in starter generator feeder starter generator undervoltage In case of disconnection of starter generator or stand by generator following a failure it is possible to re activate the system by pressing on MAIN or ST BY knob of GENERATOR RESET A crash lever located on upper panel center part allows isolating simultaneously BUS BAT bar and setting to OFF SOURCE and GENERATOR s...

Page 552: ... Page 7 8 17 Rev 0 Figure 7 8 4 1 2 INDICATING 1 Ammeter 2 Voltmeter 3 General flashing red and amber warning lights 4 Electric system warning lights on the ADVISORY PANEL 5 Battery temperature indicator if installed 6 BAT TEMP TEST push button if installed ...

Page 553: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 8 18 Rev 0 Figure 7 8 4 2 2 INDICATING ...

Page 554: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 19 Rev 0 Figure 7 8 5 ELECTRICAL CONTROL 1 MAIN reset knob 2 ST BY reset knob 3 Crash lever 4 SOURCE selector 5 GENERATOR selector ...

Page 555: ...ted on upper panel A warning light is incorporated in each switch to indicate proper operation of used landing light The Pulse lite system if installed enables the pilot to control landing light flashing to be seen by the control tower or in heavy traffic areas Taxi light The taxi light is attached to the nose gear it is controlled by TAXI switch located on upper panel A warning light is incorpora...

Page 556: ...ICE SYSTEM panel Figure 7 13 1 FWD compartment light The dome light of the FWD compartment has two positions the first allows automatic illumination via the switch located in the upper section of the door frame the second maintains the dome light permanently off regardless of the door position Fuel unit compartment light The lighting of the fuel unit compartment allows improving the visibility of ...

Page 557: ... 8 22 Rev 0 Figure 7 8 6 1 2 EXTERNAL LIGHTING CONTROLS 1 L H landing light switch 2 Test knob test light integrated to switches 3 Taxi light switch 4 R H landing light switch 5 Navigation lights switch 6 Strobe lights switch 7 Pulse lite system switch if installed ...

Page 558: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 23 Rev 0 Figure 7 8 6 2 2 EXTERNAL LIGHTING CONTROLS ...

Page 559: ...ront seats six individual floodlights for rear passenger seats and the baggage compartment R H dome light Each floodlight is controlled by a switch located on side upholstering 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 baggage compartment dome light with the CABIN switch Instrument panel...

Page 560: ... visor lighting and or instrument integrated lighting failure The rheostat located near R H floodlight controls emergency lighting operation and intensity Forward rotation of control knob allows changing from OFF position to minimum lighting then increasing lighting to maximum brightness Map reading light illumination The illumination of the map reading lights located on control wheels is controll...

Page 561: ... 8 7 1 2 INTERNAL LIGHTING CONTROLS 1 Instrument lighting switch rheostat 2 Instrument panel lighting switch rheostat 3 Cabin lighting switch rear seats reading light 4 Access door baggage compartment and FWD dome light delayed breaker push button 5 Emergency lighting switch rheostat ...

Page 562: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 8 27 Rev 0 Figure 7 8 7 2 2 INTERNAL LIGHTING CONTROLS ...

Page 563: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 8 28 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 564: ...ir is cooled by going through a temperature exchanger and a cooling turbine then it reduces the humidity through the water separator before entering the cabin through a check valve Temperature exchanger is located in a duct which directs cooling air This air is picked up outside by the NACA scoop located on R H FWD engine cowling When the airplane is on ground air flow is created by the cooling tu...

Page 565: ...h pressure switch HP rated at 406 psi 28 bars ensure system safety by cutting out electrical power supply of the high pressure pack when either pressure is reached This pack is also equipped with an overpressure relief valve rated to open at 464 psi 32 bars The pack is installed in the FWD compartment between frames C1 and C2 inside a metallic housing This housing is connected by means of a flexib...

Page 566: ...e and controlled by the high pressure pack It is intended to avoid refrigerant migrations when the system is off Two service valves The low pressure LP service valve and the high pressure HP service valve are installed into supply hoses in the R H equipment compartment between frames C1 and C2 Both valves fool proofing is ensured by their different diameters LP service valve diameter is more impor...

Page 567: ...ribution orifices 10 Outflow valve 11 Safety valve 12 Cabin fan 13 Depressurization solenoïd valve 14 Evaporator 15 Refrigerant solenoïd valve 16 Cabin temperature sensor 17 Ground safety switch 18 Control panel 19 Cabin altitude switch 20 Advisory panel 21 Cabin differential pressure switch 22 Auxiliary volume tank 23 Emergency air supply 24 Controller 25 Compressor condenser pack 26 Pressure reg...

Page 568: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 9 5 Rev 2 Figure 7 9 1 2 2 AIR CONDITIONING ...

Page 569: ... exchanger The expansion of the high pressure liquid refrigerant to a low pressure liquid extracts heat from the cabin air flowing through the evaporator and the low pressure refrigerant gas flows back to the compressor through the LP pressure switch The evaporator fan sucts hot and moistened cabin air through the evaporator heat exchanger and expells it cold and dry in a duct where it is blown in...

Page 570: ...urs when BLEED switch is set to ON what leads to opening of pressure regulator and shut off valve and switches off BLEED OFF warning light and at the same time AIR COND switch is set to ON what ensures automatic regulation of cabin temperature Two overtemperature switches cause the illumination of BLEED OFF and BLEED TEMP warning lights located on advisory panel and simultaneously the closing of t...

Page 571: ...t requested temperature in the cabin An ECS FAULT amber light illuminates when the controller detects a faulty operation of ECS system NOTE If ECS FAULT light illuminates inform maintenance service AIR FLOW distributor directs air flow to demisting outlets DEFOG or to the cabin CABIN Whatever the selected cabin temperature is HOT position enables hot air to be directed only to demisting outlets an...

Page 572: ...fety valve limits differential pressure between cabin and atmosphere at 6 2 psi 427 mb These valves are attached to rear pressure bulkhead 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 airplane is on ground through landing gear switch airplane on ground or...

Page 573: ...ev 0 Figure 7 9 2 1 2 PRESSURIZATION 1 Check valve 2 Cabin differential pressure switch 3 Advisory panel 4 Outflow valve 5 Safety valve 6 Depressurization valve 7 Landing gear switch airplane on ground 8 Pressure controller 9 Cabin altitude switch 10 Auxiliary volume tank ...

Page 574: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 9 11 Rev 0 Figure 7 9 2 2 2 PRESSURIZATION ...

Page 575: ...light 2 Warning light test push button 3 BLEED switch ON OFF RST 4 AIR COND switch ON FAN ONLY OFF 5 FAN FLOW switch AUTO LO 6 DUMP switch 7 AIR FLOW distributor HOT DEFOG CABIN 8 CABIN TEMP C selector 9 Cabin rate selector 10 Cabin altitude selector 11 Three position indicator cabin altitude cabin climb speed and differential pressure ...

Page 576: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 9 13 Rev 5 Figure 7 9 3 2 2 ECS CONTROL AND CHECK PANEL ...

Page 577: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 9 14 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 578: ...tside temperature is given in Section 8 Figure 8 7 4 as well as on a placard on the inside of the cylinder service door minimum pressure 217 PSIG 15 bars The oxygen cylinder head is equipped with a hand controlled isolation valve to permit cylinder installation and removal a microswitch supplying the OXYGEN warning light located on the advisory panel This warning light illuminates when the isolati...

Page 579: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 10 2 Rev 0 Figure 7 10 1 EMERGENCY OXYGEN SYSTEM 1 Microphone switch ...

Page 580: ...led in cups on the cabin walls aft of the front seats Permanently connected to the oxygen system they are equipped with a micro controlled by the switch NORMAL MASK micro inverter under cover located on the instrument panel near the pilot s control wheel with a three position selector NORMAL 100 and EMERGENCY and with a push button PRESS TO TEST The proper flow is signaled by a flow indicator blin...

Page 581: ...0 563 546 529 1 1 759 736 713 691 668 646 623 1 2 885 856 828 799 771 743 715 1 3 1010 976 941 907 873 839 806 1 4 1137 1096 1056 1015 975 935 897 2 0 1037 1001 965 930 894 859 825 2 1 1164 1122 1080 1038 997 956 916 2 2 1289 1241 1192 1144 1097 1050 1004 2 3 1416 1361 1306 1252 1198 1145 1093 2 4 1541 1480 1418 1357 1297 1238 1180 Values in PSIG Conditions 1 4 minutes from 31000 to 15000 ft All e...

Page 582: ... 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 1382 1326 1270 1215 1161 1108 2 3 1662 1593 1525 1457 1391 1326 1262 2 4 1888 1807 1725 1645 1567 1490 1415 Values in PSIG Conditions 1 Flight above 15000 ft All equipment used 2 1 hour usage by each pilot and passenger 3 P...

Page 583: ... 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 1083 1035 2 3 1333 1282 1231 1181 1131 1083 1035 2 4 1333 1282 1231 1181 1131 1083 1035 Values in PSIG Conditions 1 Flight under 15000 ft 2 90 minutes usage by each pilot and one passenger 3 Plus 30 minutes usage by each pi...

Page 584: ...ds static pressure is picked from a port located in airplane rear fuselage two separate dynamic pressure systems supplying the airspeed indicators systems VMO audio warning detector and the Autopilot system Air Data Computer ADC STATIC PRESSURE SYSTEMS Primary systems Two dual static ports one on either side of the fuselage tail part supply a dual system routed towards the cockpit System 1 is conn...

Page 585: ... 8 Static drain 9 FWD pressure bulkhead 10 Airspeed indicator 1 11 Encoding altimeter 1 12 Vertical speed indicator 1 13 P cabin 14 Altimeter 2 15 Airspeed indicator 2 16 Vertical speed indicator 2 17 ADC dynamic drain 18 Autopilot system Air Data Computer ADC 19 Static source Normal Alternate 20 Instrument panel 21 ADC static drain 22 Rear pressure bulkhead 23 R H static ports 24 Emergency bleed ...

Page 586: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 11 3 Rev 0 Figure 7 11 1 2 2 AIR DATA SYSTEM ...

Page 587: ...opilot system Air Data Computer ADC The second one supplies the VMO audio warning and optional equipment Both lines incorporate a drain plug located in the L H wing root On dynamic system 1 an additional drain is installed on ADC system It is located under the floor and is accessible from emergency landing gear door Pitot heating Pitot heating is controlled by PITOT 1 HTR and PITOT 2 STALL HTR swi...

Page 588: ...y vacuum by 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 failure by illuminating VACUUM LO warning light on the advisory panel ATTITUDE INDICATOR The attitude indicator provides a visual reference of actual airplane flight attitude An index at the ...

Page 589: ...ERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 12 2 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 6 Failure warning light Figure 7 3 8 ...

Page 590: ...SECTION 7 DESCRIPTION TBM 700 PILOT S OPERATING HANDBOOK Page 7 12 3 Rev 0 Figure 7 12 1 2 2 VACUUM SYSTEM ...

Page 591: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 12 4 Rev 0 Figure 7 12 2 GYROSCOPIC INSTRUMENTS CONTROL ...

Page 592: ...panel upper strip SUCTION GAGE The suction gage is calibrated in inches of mercury and indicates the suction available for operation of the attitude indicator The desired vacuum range is 4 4 to 5 2 in Hg A vacuum reading out of this range may indicate a system malfunction or improper adjustment In this case all pneumatic instruments should be considered unreliable The suction gage is located on L ...

Page 593: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 12 6 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 594: ...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 The system automatically cycles when AIRFRAME DE ICE switch is set to ON The 67 second cycle breaks down in two inflation cycles a first cycle induces inflation of leading edges deicer boots in horizontal stabilizer...

Page 595: ...y L WINDSHIELD and R WINDSHIELD switches When the switch is positioned to ON the controller supplies the heating resistors the windshield temperature is monitored by probe 1 When the temperature reaches 45 C 113 F the controller cuts the electrical supply to the heating resistors and resumes supply when the temperature falls below 30 C 86 F The cycle continues as long as the switch remains set to ...

Page 596: ...cally heated This deice equipment must be used even during flight into non icing conditions in that case PITOT 1 HTR PITOT 2 STALL HTR switches set to ON when PITOT 1 PITOT 2 or STALL HTR are lit corresponding probe heating has failed NOTE Correct operation of the audible stall warning may be altered by severe or prolonged icing TURBINE AIR INLET PROTECTION Operation and description are set forth ...

Page 597: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 13 4 Rev 0 Figure 7 13 1 DEICING CONTROL AND CHECK PANEL ...

Page 598: ...he COM 1 installation from the BUS BAT when the SOURCE selector is OFF The ground clearance function is operating as soon as the RADIO MASTER switch is set to ON and the SOURCE selector is OFF The GND CLR green indicator light located near the RADIO MASTER switch is ON when the function is activated The SOURCE selector setting to the BAT or GPU positions de activates the ground clearance function ...

Page 599: ...ILOT S OPERATING HANDBOOK 700 SECTION 7 DESCRIPTION Page 7 14 2 Rev 0 Figure 7 14 1 RADIO MASTER AND GROUND COMMUNICATION 1 RADIO MASTER switch 2 GND CLR ground clearance ground communication indicator light ...

Page 600: ...prolonged icing STATIC DISCHARGERS As an aid in flight static dischargers are installed to improve radio communications during flight by reducing interference from dust or various forms of precipitations rain snow or ice crystals Under these conditions the build up and discharge of static electricity from the trailing edges of the wings flaps and ailerons rudder stabilator propeller tips and radio...

Page 601: ... transmitter which enables to locate it in case of distress It is located in fuselage rear section with a service door on fuselage R H side The emergency locator transmitter assembly is constituted of a transmitter supplied by a battery of an antenna attached on upper fuselage and of a remote control located on R H instrument panel NOTE For test sequences refer to manufacturer manual ELT ARTEX C40...

Page 602: ...rol switch or ELT switch to ON a The ELT keeps on transmitting emergency signal b On remote control box red indicator light flashes c On ELT red indicator light flashes d Near ELT the buzzer sounds 2 Wait approximately for 1 second 3 Set remote control switch to ARM or ELT switch to OFF a The ELT does not transmit emergency signal any longer b On remote control box red indicator light illuminates ...

Page 603: ...plied by a battery of an antenna attached on upper fuselage and of a remote control located on R H instrument panel NOTE For test sequences refer to manufacturer manual ELT ARTEX C406 1 Operation of the emergency locator transmitter is obtained as follows from the instrument panel by setting ON ARM remote control switch to ON locator transmitter ON OFF switch set to OFF from the locator transmitte...

Page 604: ... control box red indicator light flashes c On ELT red indicator light flashes d Near ELT the buzzer sounds 2 Wait approximately for 1 second 3 Set remote control switch to ARM or ELT switch to OFF a The ELT does not transmit emergency signal any longer b On remote control box red indicator light illuminates for about 1 second then goes off or c On ELT red indicator light goes off d Near ELT the bu...

Page 605: ...ally in case of shock when remote control switch is set to ARMED and locator transmitter switch is set to ARM A red indicator light located on ELT remote control switch in the cockpit indicates to the pilot the emergency locator transmitter is transmitting A red indicator light located above locator transmitter switch and a buzzer located in the fuselage rear section indicate the emergency locator...

Page 606: ...TIFICATION PLATE 8 2 1 8 3 PUBLICATIONS 8 3 1 8 4 INSPECTION PERIODS 8 4 1 8 5 ALTERATIONS OR REPAIRS 8 5 1 8 6 GROUND HANDLING 8 6 1 TOWING 8 6 1 PARKING 8 6 1 TIE DOWN 8 6 3 JACKING 8 6 3 LEVELING 8 6 3 FLYABLE STORAGE 8 6 5 LONG TERM STORAGE WITHOUT FLYING 8 6 5 8 7 SERVICING 8 7 1 MAINTENANCE 8 7 1 ENGINE OIL 8 7 1 FUEL 8 7 2 LANDING GEAR 8 7 7 OXYGEN 8 7 8 ETM DATAKEY OPERATION 8 7 14 ...

Page 607: ...Page 8 0 2 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 CARE 8 8 2 8 9 UTILIZATION BY COLD WEATHER 0 C to 25 C OR VERY COLD WEATHER 25 C to 40 C 8 9 1 ...

Page 608: ...ing 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 It is recommended that a planned schedule of lubrication and preventive maintenance be followed and that this schedule be tailored to the climatic or flying conditions to which the airplane is subjected For this...

Page 609: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 1 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 610: ...IFICATION PLATE Any correspondence regarding your airplane should include its serial number This number together with the model number type certificate number and production certificate number are stamped on the identification plate attached to the left side of the fuselage beneath the horizontal stabilizer ...

Page 611: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 2 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 612: ...pplemental data covering optional equipment installed in the airplane refer to Section 9 Supplements and pilot s guides In addition the owner may purchase the following Maintenance Manual Wiring Manual Illustrated Parts Catalog Bilingual Illustrated Tool and Equipment Manual Catalog of Service Bulletins Service Letters and Service Information Letters CAUTION PILOT S OPERATING HANDBOOK MUST ALWAYS ...

Page 613: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 3 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 614: ...DS Refer to regulations in force in the certification country for information concerning preventive maintenance to be carried out A maintenance Manual must be obtained prior to performing any preventive maintenance to make sure that proper procedures are followed Maintenance must be accomplished by licensed personnel ...

Page 615: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 4 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 616: ... 8 5 1 Rev 0 8 5 ALTERATIONS OR REPAIRS It is essential that the Airworthiness authorities be contacted prior to any alterations or repairs on the airplane to make sure that airworthiness of the airplane is not violated Alterations or repairs must be accomplished by licensed personnel ...

Page 617: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 5 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 618: ...quipped with an integrated towing fitting CAUTION DO NOT TOW THE AIRPLANE WHEN CONTROLS ARE SECURED WHEN TOWING WITH A VEHICLE DO NOT EXCEED THE NOSE GEAR TURNING ANGLE AS THIS MAY RESULT IN DAMAGE TO THE GEAR AND STEERING MECHANISM see Figure 8 6 1 PARKING When parking the airplane head it into the wind Do not set the parking brake when brakes are overheated or during cold weather when accumulate...

Page 619: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 6 2 Rev 0 Figure 8 6 1 TURNING ANGLE LIMITS ...

Page 620: ...ckpit cover tie downs wheel chocks and control lock are recommended In severe weather and high wind conditions tie the airplane down as outlined in the following paragraph TIE DOWN Proper tie down procedure is the best protection against damage to the airplane by gusty or strong winds To tiedown the airplane securely proceed as follows Install control lock see Figure 8 6 2 Chock all wheels Tie suf...

Page 621: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 6 4 Rev 0 Figure 8 6 2 CONTROL LOCK DEVICE ...

Page 622: ...rged to prevent the electrolyte from freezing in cold weather Close oxygen cylinder isolation valve Storage from 8 to 28 days Engine according to Maintenance Manual P W C Airplane fueling Keep fuel tanks full to minimize condensation in the tanks Keep the battery fully charged to prevent the electrolyte from freezing in cold weather Close oxygen cylinder isolation valve Battery remaining in the ai...

Page 623: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 6 6 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 624: ...f oil CAUTION DO NOT MIX DIFFERENT BRANDS OR TYPES Nominal viscosity US specification US French specification FR English specification UK NATO code Type 5cSt MIL L 23699C Amdt 1 MIL L 23699C Amdt 1 DERD 2499 Issue 1 O 156 Figure 8 7 1 RECOMMENDED ENGINE OIL TYPES Reference Service Bulletin P W C No 14001 Oil capacity System total capacity 12 7 Quarts 12 Litres oil cooler included Usable capacity 6...

Page 625: ...verify 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 oil level before adding oil FUEL Total capacity each tank 145 3 us gal 550 l NOTE To minimize condensation it is recommended that airplane be refueled after each flight respecting weight and balance limits CAUTION N...

Page 626: ...MENT 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 Specification US French Specification FR English Specification UK NATO Code ASTM D1655 JET A ASTM D1655 JET A1 ASTM D1655 JET B AIR 3405C Grade F35 DERD 2494 Issue 9 F35 without additive MIL DTL 5624 Grade JP 4 AIR 3407B...

Page 627: ...itions small amounts of water emulsified can precipitate from the fuel stream and freeze in sufficient quantities to induce partial icing of the engine fuel system While these conditions are quite rare and will not normally be a problem to owners and operators they do exist in certain areas of the world and consequently must be dealt with when encountered Therefore to alleviate the possibility of ...

Page 628: ...dup in the fuel which leeches out the additive An indication of this is when an excessive amount of water accumulates in the fuel tank sumps The concentration can be checked using a differential refractometer It is imperative that the technical manual for the differential refractometer be followed explicitly when checking the additive concentration Fuel and fuel additives in Ukraine and CIS countr...

Page 629: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 7 6 Rev 0 Figure 8 7 3 ADDITIVE MIXING RATIO EGME or DIEGME ...

Page 630: ...gen to 87 psi 6 bars Main gear shock absorbers Fill with hydraulic fluid AIR 3520 B MIL H5606E inflate with nitrogen to 160 psi 11 bars Hydraulic system Check every 100 hours and service with AIR 3520 B MIL H5606E hydraulic fluid Brakes Service as required with AIR 3520 B MIL H5606E hydraulic fluid NOTE A higher inflation pressure has to be applied to tires and shock absorbers when in very cold co...

Page 631: ...oxygen cylinder is installed directly on the cylinder head It consists of a charging valve and of a pressure gage graduated from 0 to 2000 PSIG A chart see Figure 8 7 4 located on the inside of the cylinder service door gives the cylinder charge maximum pressure according to the environment temperature Figure 8 7 4 Charge pressure chart ...

Page 632: ...OUS 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 200 PSIG 13 7 BARS PER MINUTE CAUTION REPLENISHMENT OF THE OXYGEN SYSTEM SHOULD ONLY BE CARRIED OUT BY QUALIFIED PERSONNEL NOTE The cylinder full charge is assured for a pressure of 1850 PSIG 127 bars at a te...

Page 633: ...he 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 all the tools and materials are removed and the work area is clean and free from debris Close the oxygen service door Passengers masks repacking instructions WARNING DO NOT USE OIL OR OTHER PETROLEUM BASED LUBRIC...

Page 634: ...on 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 with Neo Novacite powder Scott Aviation P N 00 736 Contamination can be removed with mild soap and water solution Fold headstrap into facepiece Pull lanyard cord out to side of facepiece so that it does not inter...

Page 635: ...ING AND MAINTENANCE Page 8 7 12 Rev 0 Gently fold reservoir bag lengthwise into thirds outside edges folded inward over center of bag Do not crease bag Fold reservoir bag away from breathing valves and into facepiece Make sure bag does not cover breathing valves ...

Page 636: ... IS INSERTED INTO CORRECT CHECK VALVE FOR MASK BEING INSTALLED CROSS CONNECTED PINS WILL RESULT IN PASSENGERS PULLING LANYARD CORDS ONLY TO INITIATE OXYGEN FLOW TO ANOTHER MASK Insert lanyard pin into corresponding check valve Place mask facepiece first in deployment container Make sure that oxygen tubing and lanyard cord are free to deploy and are not caught between the container and lid Close an...

Page 637: ... a memory chip in the key When the key is removed from the airplane it can then be carried to a personal computer with a receptacle attached for the key and downloaded Operating using the Datakey a Insert initialized key into airplane receptacle prior to power up turn 90 b Conduct flight c Remove key after power down NOTE The key will hold several flights of data depending of the number of events ...

Page 638: ... 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 OBJECTS FROM TOUCHING THE WINDSHIELD AND THE WINDOWS ADHESIVE TAPES OTHER THAN MINNESOTA 3M TYPE 670 SHALL NOT BE USED ON ACRYLIC SURFACES NEVER USE BUFFING MACHINES AS EXCESSIVE FORCES OR SPEEDS MIGHT PRODUCE REDHIBITORY...

Page 639: ...ill 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 concentrations and if not removed may result in cracks Never use an alkaline cleaner on the blades remove grease and dirt ENGINE CARE Refer to Maintenance Manual for the procedures to follow INTERIOR CARE To remove du...

Page 640: ...om temperature of 15 C 4 Position a 0 59 in 15 mm shim at the bottom of the piston tube and against forward landing gear half fork to reduce shock absorber travel Refill with hydraulic liquid Remove the shim and inflate shock absorber to 138 psi 9 5 bars at a room temperature of 15 C 5 Inflate main landing gear tires to 131 psi 9 bars and nose tire to 102 psi 7 bars at a room temperature of 15 C C...

Page 641: ...TBM PILOT S OPERATING HANDBOOK 700 SECTION 8 HANDLING SERVICING AND MAINTENANCE Page 8 9 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 642: ...al speed and altitude selector type KAS 297C All From S N 1 to S N 433 except S N 269 31 03 90 3 BENDIX KING RDS 81 weather radar TBM 700A and TBM 700B From S N 1 30 11 90 4 BENDIX KING RDS 82 weather radar TBM 700A and TBM 700B From S N 1 30 11 90 5 BENDIX KING RDS 82 VP vertical profile weather radar TBM 700A and TBM 700B From S N 1 30 11 90 6 BFG WX 500 or WX 950 or WX 1000 or 1000 or 1000E sto...

Page 643: ...pilot type KFC 325 All From S N 1 to S N 433 except S N 269 31 05 91 11 CASEY COPTER freon air conditioning TBM 700A From S N 24 31 05 92 12 Window and capability of Camera Observation TBM 700A From S N 1 31 01 94 13 BENDIX KING KLN90A GPS navigation system interfaced with HSI KI 525A TBM 700A and TBM 700B From S N 1 30 04 94 14 BENDIX KING KLN90A GPS navigation system interfaced with EHSI OF EFS ...

Page 644: ...0 04 96 18 L HOTELLIER Engine fire detection system All From S N 1 31 01 96 19 SHADIN ETM Engine Trend Monitor TBM 700A TBM 700B and TBM 850 From S N 1 31 01 96 20 BENDIX KING GC 360A radar graphics interface TBM 700A and TBM 700B From S N 1 29 02 96 21 BENDIX KING KLN90B GPS navigation system interfaced with the HSI KI525A TBM 700A and TBM 700B From S N 1 30 04 96 22 BENDIX KING RDR 2000 vertical...

Page 645: ...th EFS 40 EHSI TBM 700A TBM 700B and TBM 700C From S N 1 30 11 98 27 BENDIX KING KLN90B GPS B RNAV navigation system interfaced with electromechanical HSI TBM 700A and TBM 700B From S N 1 15 06 99 28 BFG SKYWATCH SKY 497 or SKY 899 traffic advisory system All From S N 1 to S N 433 except S N 269 31 08 99 29 EROS INTERTECHNIQUE gaseous oxygen system 30000 ft TBM 700A and TBM 700B From S N 40 plus S...

Page 646: ...KMD 850 Multi function display TBM 700B TBM 700C and TBM 850 From S N 192 to S N 433 except S N 269 31 01 01 36 GARMIN GNS 530 GPS B RNAV navigation system interfaced with EHSI OF EFS 40 All From S N 1 to S N 433 except S N 269 31 10 01 37 EROS INTERTECHNIQUE gaseous oxygen system 31000 ft TBM 700A and TBM 700B From S N 40 plus S N 24 and 36 30 08 01 38 Operation at 31000 ft TBM 700A and TBM 700B ...

Page 647: ...o S N 433 except S N 269 30 09 02 43 Provision for TBM 700C2 TBM 700C1 From S N 244 plus S N 205 and S N 240 10 12 02 44 Chip detection system All From S N 1 10 02 05 45 Intentionally left free 46 GARMIN GMX 200 Multi function display All TBM airplanes equipped with option OPT70 34040F From S N 1 to S N 433 except S N 269 31 10 06 The Supplement Revision 24 is approved under authority of DOA EASA ...

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Page 660: ...v 6 SUPPLEMENT BFG WX 500 OR WX 950 OR WX 1000 OR 1000 OR 1000E STORMSCOPE TABLE OF CONTENTS Page 1 GENERAL 9 6 2 2 LIMITATIONS 9 6 2 3 EMERGENCY PROCEDURES 9 6 3 4 NORMAL PROCEDURES 9 6 4 5 PERFORMANCE 9 6 4 6 WEIGHT AND BALANCE 9 6 5 7 DESCRIPTION 9 6 7 ...

Page 661: ...airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook The BFG stormscope systems signal displays are not intended for the purpose of penetrating thunderstorm areas or areas of severe turbulence such intentional use is prohibited NOTE Range selection determines receiver sensitivity and therefore relative range Displayed range is based on signal strength and is not to b...

Page 662: ...00 or The WX 500 Pilot s guide Series II No 009 11501 001 and the GARMIN GMX 200 Pilot s Guide No 190 00607 02 or Post MOD70 0176 00 The WX 500 Pilot s guide Series II No 009 11501 001 and the GARMIN G1000 Integrated Flight Deck Cockpit Reference Guide for the Socata TBM 850 No 190 00708 00 at their last revision shall be readily available to the pilot each time the BFG stormscope operation is for...

Page 663: ...l WX 1000 or 1000 or 1000E or the WX 950 Pilot s Guide Series II No 009 10951 001 at its last revision for BFG stormscope model WX 950 or the WX 500 Pilot s Guide Series II No 009 11501 001 at its last revision for BFG stormscope model WX 500 SECTION 5 PERFORMANCE Installation and operation of BFG stormscope do not change the basic emergency procedures of the airplane described in Section 5 Perfor...

Page 664: ...8 35 5 800 A Stormscope WX 1000 OPT 70 34009B BFG 15 432 7 000 230 71 5 860 A Stormscope WX 1000 EFIS coupled OPT 70 34009C BFG 15 432 7 000 230 71 5 860 A Stormscope WX 1000E EFIS coupled Remote installed control OPT 70 34009D BFG 9 502 4 310 269 09 6 835 A Stormscope WX 1000E EFIS coupled OPT 70 34009E BFG 15 939 7 230 230 94 5 866 A Stormscope WX 1000E shared with the SKYWATCH OPT 70 34009F BFG...

Page 665: ...HT per unit lb kg EQUIPMENT SUPPLIER OPTIONAL EQUIPMENT A Stormscope WX 500 shared with the GNS 530 GPS or with the KMD 850 or GMX 200 MFD OPT 70 34056A BFG 4 94 2 240 232 28 5 900 A Stormscope WX 500 shared with the GARMIN G1000 system OPT 70 34056B BFG 4 94 2 240 232 28 5 900 ...

Page 666: ... to detect severe thunderstorm activity A series of green dots or of strike points will be displayed on the screen to indicate the electrical discharge areas Dots or strike points may be displayed on two selectable wiews 360 view of surrounding airspace and 120 view of forward airspace only The display scope provides full scale selectable ranges of 200 100 50 and 25 NM Post MOD70 125 23 and Pre MO...

Page 667: ...TBM 700 850 SUPPLEMENT 6 BFG STORMSCOPE Page 9 6 8 Rev 6 INTENTIONALLY LEFT BLANK ...

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Page 738: ...0 850 Page 9 16 1 Rev 3 SUPPLEMENT BENDIX KING KRA 405 RADAR ALTIMETER TABLE OF CONTENTS Page 1 GENERAL 9 16 2 2 LIMITATIONS 9 16 2 3 EMERGENCY PROCEDURES 9 16 2 4 NORMAL PROCEDURES 9 16 3 5 PERFORMANCE 9 16 4 6 WEIGHT AND BALANCE 9 16 4 7 DESCRIPTION 9 16 6 ...

Page 739: ...he basic Pilot s Operating Handbook The radio altimeter is not approved as an additional accurate approach aid SECTION 3 EMERGENCY PROCEDURES The emergency procedures given hereafter complete those of the standard airplane described in Section 3 Emergency procedures of the basic Pilot s Operating Handbook During the test if the radio altimeter does not indicate 50 ft 5 ft the information provided ...

Page 740: ...ed altitude is reached 3 With the TEST button depressed slowly increase the adjusted DH When the DH annunciator or the DH lamp comes on the adjusted altitude should be 50 ft 5 ft The DH annunciator or the DH lamp should also be illuminated at all altitudes above 50 feet 4 Release the TEST button The indicated altitude should be 0 ft 5 ft Prior to landing 1 Select the decision height 2 Depress the ...

Page 741: ...ter does not change the basic performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Weight and balance corresponding to the BENDIX KING KRA 405 radar altimeter are given in the optional equipment list attached to Section 6 Weight and balance of the basic Pilot s Operating Handbook ...

Page 742: ...SUPPLEMENT 16 BENDIX KING KRA 405 RADAR ALTIMETER TBM 700 850 Page 9 16 5 Rev 3 INTENTIONALLY LEFT BLANK ...

Page 743: ...ECTION 7 DESCRIPTION STANDARD VERSION KNI 415 INDICATOR Figure 9 16 1 The DH lamp can be disabled by depressing it and rearmed by depressing it once again Figure 9 16 1 1 2 KNI 415 INDICATOR 1 DH lamp 2 Flag 3 Indicator pointer 4 Altitude scale 5 DH bug 6 DH knob 7 Self test button ...

Page 744: ...SUPPLEMENT 16 BENDIX KING KRA 405 RADAR ALTIMETER TBM 700 850 Page 9 16 7 Rev 3 Figure 9 16 1 2 2 KNI 415 INDICATOR ...

Page 745: ...DAR ALTIMETER Page 9 16 8 Rev 3 Figure 9 16 2 1 2 RADAR ALTIMETER EFIS VERSION WITHOUT KNI 415 INDICATOR 1 Radar altimeter altitude display 2 DH annunciator 3 Selected decision height 4 DH selection pull knob 5 TEST button EFIS VERSION Figure 9 16 2 ...

Page 746: ...SUPPLEMENT 16 BENDIX KING KRA 405 RADAR ALTIMETER TBM 700 850 Page 9 16 9 Rev 3 Figure 9 16 2 2 2 RADAR ALTIMETER EFIS VERSION WITHOUT KNI 415 INDICATOR ...

Page 747: ...PLEMENT 16 BENDIX KING KRA 405 RADAR ALTIMETER Page 9 16 10 Rev 3 COMBINED VERSION The radar altimeter information given in the EADI system are a recopy of the indications and selections made on the KNI 415 indicator ...

Page 748: ...e 9 22 1 Rev 2 SUPPLEMENT BENDIX KING RDR 2000 VERTICAL PROFILE WEATHER RADAR TABLE OF CONTENTS Page 1 GENERAL 9 22 2 2 LIMITATIONS 9 22 2 3 EMERGENCY PROCEDURES 9 22 3 4 NORMAL PROCEDURES 9 22 3 5 PERFORMANCE 9 22 5 6 WEIGHT AND BALANCE 9 22 5 7 DESCRIPTION 9 22 6 ...

Page 749: ...g refueling operations or in the vicinity of trucks or containers containing flammables or explosives Do not allow personel within 15 feet of area being scanned by antenna when system is transmitting 2 1 RDR 2000 weather radar not interfaced with multi function display KMD 850 or GMX 200 The BENDIX KING RDR 2000 Pilot s Guide P N 006 08755 0000 at its latest revision shall be readily available to ...

Page 750: ...mergency procedures of the airplane described in Section 3 Emergency procedures of the basic Pilot s Operating Handbook CAUTION IN CASE OF AP COMPUTER FAILURE THE ANTENNA STABILIZATION WILL NOT BE OPERATIVE SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard airplane described in Section 4 Normal procedures of the basic Pilot s Operating Handbook Normal ope...

Page 751: ...ed or in the RH lower corner of the radar screen if multi function display not installed The radar radiation is inhibited The radar automatically radiates as soon as the aircraft takes off TAKE OFF BEFORE LANDING Radar function selection switch SBY RDR 2000 weather radar interfaced with multi function display KMD 850 or GMX 200 RADIO MASTER switch OFF RDR 2000 weather radar not interfaced with mul...

Page 752: ...on 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 34 NAVIGATION A Weather radar RDR 2000 OPT70 34040A KING 21 054 9 550 163 70 4 158 A Weather radar RDR 2000 GC 360A coupled OPT70 34040B KING 25 154 11 410 161 22 4 095 A Weather radar RDR 2000 EFIS coupled OPT70 34040E KING 21 054 9 550 163 70 4 158 A Weather...

Page 753: ...file mode selector button 5 Weather and Weather Alert toggle selector button 6 Screen brightness control knob 7 Left or right Track mode annunciation 8 Degrees of Track left or right of airplane nose 9 Vertical Profile mode annunciation 10 Relative altitude reference line 11 Plus minus thousands of feet from relative altitude 12 Radar function selection switch 13 Range selector buttons 14 Left or ...

Page 754: ...SUPPLEMENT 22 BENDIX KING RDR 2000 WEATHER RADAR TBM 700 850 Page 9 22 7 Rev 2 Figure 9 22 1 2 2 Indicator ...

Page 755: ...tes gain control The magenta is not activated in the GND MAP mode Places indicator in navigation mode so that preprogrammed waypoints may be displayed If other modes are also selected the NAV display will be superimposed on them This button is effective only if an optional radar graphics unit and Flight Management System is installed If actuated without these units it will cause NO NAV to appear a...

Page 756: ...ight from the nose of the airplane For VP operations the TRK button performs two functions 1 Prior to engaging VP the appropriate button left or right is used to place the track line at the desired azimuth angle to be vertically scanned sliced When VP is engaged the slice will be taken at the last position of the track line whether it is visible or not If the track line has not been selected after...

Page 757: ... display WX KMD 850 radar function selection When the KMD 850 is set to radar function equivalences between KMD 850 and radar standard operational controls described in chapter 7 1 are as follows KMD 850 CONTROL RDR 2000 STANDARD OPERATIONAL CONTROL MODE WX GND MAP RNG RNG RNG VIEW VP Joystick horizontal movement TRK Joystick vertical movement TILT 1 Outer knob SBY TST ON 2 Inner knob GAIN ...

Page 758: ...function display 1 WX GMX 200 radar function selection When the GMX 200 is set to radar function equivalences between GMX 200 and radar standard operational controls described in chapter 7 1 are as follows GMX 200 CONTROL RDR 2000 STANDARD OPERATIONAL CONTROL 1 label depends on precedent action SBY ON OFF 2 Rng Rng RNG 3 Tilt Tilt TILT 3 Brg Brg TRK 3 Gain Gain GAIN 4 HORIZ VERT VP ...

Page 759: ...TBM 700 850 SUPPLEMENT 22 BENDIX KING RDR 2000 WEATHER RADAR Page 9 22 12 Rev 2 Post MOD70 125 23 Radar setting to ON or OFF is performed by using the RADIO MASTER switch ...

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Page 776: ... 28 1 Rev 1 SUPPLEMENT BFG SKYWATCH SKY 497 OR SKY 899 TRAFFIC ADVISORY SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 28 3 2 LIMITATIONS 9 28 3 3 EMERGENCY PROCEDURES 9 28 3 4 NORMAL PROCEDURES 9 28 4 5 PERFORMANCE 9 28 4 6 WEIGHT AND BALANCE 9 28 5 7 DESCRIPTION 9 28 6 ...

Page 777: ...TBM 700 SUPPLEMENT 28 BFG SKYWATCH TRAFFIC ADVISORY SYSTEM Page 9 28 2 Rev 1 INTENTIONALLY LEFT BLANK ...

Page 778: ...ircraft transponders It does neither detect nor track aircraft which are not equipped with an operating ATCRBS transponder SECTION 2 LIMITATIONS The installation of the BFG SKYWATCH traffic advisory system does not change the basic limitations of the airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook REMARK The SKYWATCH is a TAS advisory means not a TCAS SECTION 3 ...

Page 779: ... data are displayed on a KMD 850 MFD the GARMIN GNS 530 Pilot s Guide P N 190 00181 00 Revision A dated 04 00 or any applicable following edition if data are displayed on a GNS 530 GPS WARNING DO NOT ATTEMPT EVASIVE MANEUVERS BASED SOLELY ON TRAFFIC INFORMATION SHOWN ON THE SKYWATCH DISPLAY INFORMATION ON THE DISPLAY IS PROVIDED TO THE FLIGHT CREW AS AN AID IN VISUALLY ACQUIRING TRAFFIC IT IS NOT ...

Page 780: ...lance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 34 NAVIGATION A Traffic advisory system SKYWATCH SKY 497 OPT70 34047A BFG 15 780 7 16 145 91 3 706 A Traffic advisory system EFIS version SKYWATCH SKY 497 OPT70 34047B BFG 13 140 5 96 150 12 3 813 A Traffic advisory system SKYWATCH9 HP SKY 899 OPT70 34059 BFG 12 720 5 77 151 18...

Page 781: ...ay whether a stormscope system is installed or not The display range is 2 NM or 6 NM SKYWATCH SKY 899 The traffic can be shown on a dedicated screen KMD 850 MFD or GNS 530 GPS and or on the EFS 40 The controls TEST or TEST MODE ON OFF and ST BY OPR are remote from the screen see Figures 9 28 1 and 9 28 2 The display range is between 2 NM and 20 NM All The traffic detected is displayed when the ver...

Page 782: ...TER switch AIRCRAFT EQUIPPED WITH THE KRA 405B RADIO ALTIMETER When the aircraft is at a ground height lower than 2000 ft the Traffic Advisory TA criteria which initiate a visual and or an aural alert are sensitivity level A detection of an intruder aircraft within a 0 2 NM horizontal radius and a 600 ft relative altitude approach of an intruder aircraft on a course that will intercept your course...

Page 783: ...ntrol with display on EFS 40 ST BY OPR Skywatch stand by TEST MODE 1st case When the SKY 899 is in stand by tests the Skywatch 2nd case When the SKY 899 is in OPR changes display type NORM BLW ABV in the EFS 40 NOTE EFS 40 TEST REF knob enables selection of SKY 899 Skywatch data display in the EFS 40 TEST Held position for test ST BY OPR 1st press Skywatch stand by 2nd press OPR selection ...

Page 784: ...UPPLEMENT CARGO TRANSPORTATION CAPABILITY TABLE OF CONTENTS Page 1 GENERAL 9 30 3 2 LIMITATIONS 9 30 3 3 EMERGENCY PROCEDURES 9 30 6 4 NORMAL PROCEDURES 9 30 6 5 PERFORMANCE 9 30 6 6 WEIGHT AND BALANCE 9 30 7 7 DESCRIPTION 9 30 16 8 HANDLING SERVICING AND MAINTENANCE 9 30 21 ...

Page 785: ...TBM 700 SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Page 9 30 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 786: ...rd airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the airplane is equipped with the option CARGO TRANSPORTATION CAPABILITY OCCUPANTS Front L H seat 1 pilot Front R H seat 0 with partition net P N T700B259001100000 emergency exit not accessible 1 with partition net P N T700B259001800000 emergency exit accessible Front R H seat occupied The specific partitio...

Page 787: ...ion net 220 lbs 100 kg Container pallet or heavy box freight front container pallet or heavy box 396 8 lbs 180 kg rear container pallet or heavy box 330 7 lbs 150 kg Max floor load 38 5 lb sq ft 188 kg m2 Max dimensions of containers pallets or heavy boxes Length 47 24 in 1 20 m Width 31 50 in 0 80 m Height front container pallet or heavy box 39 37 in 1 00 m Height rear container pallet or heavy b...

Page 788: ...SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY TBM 700 Page 9 30 5 Rev 2 PLACARDS 1 On the raiser at frame 13bis inside the cabin 2 Under L H front side window ...

Page 789: ...ures hereafter supplement those of the standard airplane described in Section 4 Normal procedures of the basic Pilot s Operating Handbook when the airplane is equipped with the option CARGO TRANSPORTATION CAPABILITY PREFLIGHT INSPECTION Bulk freight Partition nets in place CHECK Container pallet or heavy box freight Stowing nets in place CHECK SECTION 5 PERFORMANCE The installation of the option C...

Page 790: ... capability Partition net at frame 7 Partition net at frame 14 Stowing net Front stop Rear shim OPT70 25027A SOCATA SOCATA SOCATA SOCATA SOCATA 2 205 1 00 2 205 1 00 6 614 3 00 1 014 0 46 6 173 2 80 200 31 5 088 289 53 7 354 224 41 5 700 or 275 59 7 000 202 76 5 150 255 12 6 480 A Cargo transportation capability Partition net at frames 7 10 Partition net at frame 14 OPT70 25027B SOCATA SOCATA 5 07...

Page 791: ...500 252 36 6 410 S Cabin and baggage compartment carpets SOCATA 23 369 10 600 234 02 5 944 A JEPPESEN cabinet Composite OPT70 25005C SOCATA 14 991 6 800 202 76 5 150 A Storage cabinet Composite OPT70 25006E SOCATA 16 314 7 400 202 76 5 150 A Refreshment cabinet Composite OPT70 25006F SOCATA 18 960 8 600 202 76 5 150 A Audio cabinet Composite OPT70 25009C SOCATA 24 052 10 910 206 14 5 236 ...

Page 792: ...rgo according to the position of the C G arm from Figure 9 30 1 Enter the moment of each item in the appropriate blocks on the Loading Form Figure 9 30 2 1 3 Add the weight and moment of all the items to the basic empty weight and moment of the airplane to determine the zero fuel weight and moment Divide the moment by the weight to determine the C G arm do Determine the moment of the fuel load Ent...

Page 793: ...ted index 3 in the upper index scale and proceed according to the method described in Figure 9 30 3 Draw a vertical line corresponding to the final index loaded airplane until you reach the airplane weight horizontal line Read the corresponding balance while checking that the obtained point falls within the weight and balance envelope Also check that the total zero fuel weight does not exceed the ...

Page 794: ...CAPABILITY TBM 700 Page 9 30 11 Rev 2 Figure 9 30 1 CG arm calculation Measure the cargo CG position x dimension from the anchor plates at frame 7 Express the cargo CG arm according to the following formula do 208 31 x in or do 5 291 x m ...

Page 795: ... C G ARM in m MOMENT lb in m kg 1 Basic empty weight 2 Cargo conversion 3 Pilot 180 5 4 585 4 R H seat passenger 180 5 4 585 5 Front baggage 128 0 3 250 6 Cargo 7 Cargo 8 Cargo 9 Cargo 10 Rear baggage 303 0 7 695 11 Zero fuel weight 12 Fuel 188 19 4 780 13 Weight with fuel Figure 9 30 2 1 3 Loading Form ...

Page 796: ... do 172 93 x 100 m a c 59 45 ITEM WEIGHT lb do in CG m a c 14 Zero fuel weight 15 Weight with fuel Figure 9 30 2 2 3 Loading Form lbs and in CG do 4 3925 x 100 cam 1 51 ITEM WEIGHT kg do m CG m a c 14 Zero fuel weight 15 Weight with fuel Figure 9 30 2 3 3 Loading Form kg and m ...

Page 797: ...TBM 700 SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Page 9 30 14 Rev 2 Figure 9 30 3 Weight and balance graph in lbs ...

Page 798: ...SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY TBM 700 Page 9 30 15 Rev 2 Figure 9 30 3A Weight and balance graph in kg ...

Page 799: ...ipped with anchor fittings allowing their attachment to the seat rails or into anchor points provided in the baggage compartment LOADING INSTRUCTIONS CAUTION CARGO MUST BE STRAPPED ON THE PALLET FROM THE FRONT TO THE REAR PART OF THE CARGO When positioned at the front the container pallet or heavy case must be installed against retaining angles attached to the seat rails and it must be stowed with...

Page 800: ...SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY TBM 700 Page 9 30 17 Rev 2 Figure 9 30 4 Partition nets version with a pilot ...

Page 801: ...TBM 700 SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Page 9 30 18 Rev 2 Figure 9 30 4A Partition nets version with a pilot and a R H passenger ...

Page 802: ...SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY TBM 700 Page 9 30 19 Rev 2 Figure 9 30 5 1 2 Stowing of front container pallet or heavy box pilot alone on board ...

Page 803: ...TBM 700 SUPPLEMENT 30 CARGO TRANSPORTATION CAPABILITY Page 9 30 20 Rev 2 Figure 9 30 5 2 2 Stowing of rear container pallet or heavy box pilot alone on board ...

Page 804: ...et P N T700B259001100000 7 Attach the rear partition net P N T700B259000100000 Bulk freight with a pilot and a passenger 6 Attach the front partition net P N T700B259001800000 7 Attach the rear partition net P N T700B259000100000 Container pallet or heavy box freight 6 Position and secure the retaining angles P N T700B259003100000 CAUTION CARGO MUST BE STRAPPED ON THE PALLET FROM THE FRONT TO THE ...

Page 805: ...les P N T700B259003100000 the front partition net P N T700B259001100000 or T700B259001800000 if necessary the rear partition net P N T700B259000100000 the block P N T700B259001500000 3 If removed install both attachment lugs and the rings at the level of frame 14 4 Install the cabin and baggage compartment carpets 5 If removed install the cabinets 6 Install the intermediate passengers seats and th...

Page 806: ...700 Page 9 35 1 Rev 0 SUPPLEMENT HONEYWELL KMD 850 MULTI FUNCTION DISPLAY TABLE OF CONTENTS Page 1 GENERAL 9 35 2 2 LIMITATIONS 9 35 3 3 EMERGENCY PROCEDURES 9 35 4 4 NORMAL PROCEDURES 9 35 4 5 PERFORMANCE 9 35 5 6 WEIGHT AND BALANCE 9 35 5 7 DESCRIPTION 9 35 6 ...

Page 807: ...dard airplane described in Section 1 General of the basic Pilot s Operating Handbook when the TBM 700 airplane is equipped with the option HONEYWELL KMD 850 MULTI FUNCTION DISPLAY The KMD 850 is a multifunction display screen which allows to display topographical type information rivers roads aeronautical type information VOR Airport NDB as well as information issued from a weather radar a stormsc...

Page 808: ...TI FUNCTION DISPLAY KMD 550 850 Multi function Display Pilot s Guide P N 006 18222 0000 Revision 0 dated Oct 2000 or any applicable following edition shall be readily available to the pilot The KMD 850 may be used only as an aid to navigation if navigation is based on other approved instruments the KMD 850 data base is current and compatible with the flight KMD 850 and associated GPS data bases co...

Page 809: ...ing Handbook SECTION 4 NORMAL PROCEDURES The normal procedures hereafter supplement those of the standard aircraft described in Section 4 Normal procedures of the basic Pilot s Operating Handbook when the TB aircraft is equipped with the option HONEYWELL KMD 850 MULTI FUNCTION DISPLAY KMD normal operating procedures recommended by the manufacturer are outlined in the KMD 550 850 Multi function Dis...

Page 810: ...e 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 in Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 34 NAVIGATION A Multi function display KMD 850 OPT70 34054 HONEY...

Page 811: ...Figure 9 35 1 KMD 850 Multi function display front view 1 Brightness control 2 Data card 3 LCD display 4 Available function 5 ON OFF control 6 Selected function indicators 7 Function select keys 8 Control knobs inner and outer 9 Power key labels 10 Soft labels 11 Joystick 12 Power keys 13 Fault indicator ...

Page 812: ...0 Page 9 36 1 Rev 0 SUPPLEMENT GARMIN GNS 530 GPS NAVIGATION SYSTEM B RNAV INTERFACED WITH EHSI OF EFS 40 TABLE OF CONTENTS Page 1 GENERAL 9 36 2 2 LIMITATIONS 9 36 3 3 EMERGENCY PROCEDURES 9 36 6 4 NORMAL PROCEDURES 9 36 8 5 PERFORMANCE 9 36 12 6 WEIGHT AND BALANCE 9 36 12 7 DESCRIPTION 9 36 13 ...

Page 813: ...bed in Section 1 General of the basic Pilot s Operating Handbook when the TBM 700 airplane is equipped with the option GARMIN GNS 530 GPS NAVIGATION SYSTEM B RNAV INTERFACED WITH EHSI OF EFS 40 This supplement does not constitute an operational utilization authorization The GPS is an automatic tridimensional latitude longitude altitude location and navigation means using information provided by sa...

Page 814: ... dated 04 00 or any applicable following edition shall be readily available to the pilot each time the GPS navigation system is used The system must utilize the following software versions or more recent ones Subsystem Software MAIN 2 06 GPS 2 10 Data base updating must be verified before each flight The navigation sources required for the anticipated flight shall be serviceable and allow an immed...

Page 815: ...5 minutes the flight cannot be done In that case the flight will either be postponed or another route will be chosen The prediction software must then be used again Preflight procedures During preflight checks it is necessary to verify data base validity updating of the last AIRAC cycle The onboard equipment must be initialized in compliance with manufacturer procedures refer to GARMIN GNS 530 Pil...

Page 816: ...approach Non precision approach Use of the GPS to perform an instrument approach is possible as long as this use is approved by the air navigation local authority for the approach in question Instrument approaches performed with the GPS must be achieved according to approved approach procedures given in the GPS data base The data base must be kept up to date and base data accuracy checked with reg...

Page 817: ...I OF EFS 40 In navigation GPS 1 OPT70 23024 Return to VOR ADF or if installed GPS 2 navigation sources and to remaining operational navigation equipment Selection of GPS 2 if installed and BRNAV authorized PRESS ONCE on 1 2 push button of the EHSI or Selection of VOR or ADF PRESS ONCE or TWICE on NAV push button of the EHSI In navigation GPS 2 OPT70 23025 Return to VOR ADF or GPS 1 navigation sour...

Page 818: ... area the aircraft must not enter B RNAV area If RAIM loss occurs in B RNAV area GPS navigation can be continued as long as cross checkings done with conventional 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 to conventional navigation If GPS navigation i...

Page 819: ...se is current Verify data on the self test page Verify that altitude data is valid for the GPS prior to flight In case of B RNAV use During the preflight planning phase the availability of GPS integrity RAIM shall be confirmed for the intended flight route and time B RNAV flight dispatch shall not be made in the event of a continuous loss of RAIM for more than 5 minutes predicted in any part of th...

Page 820: ...push button This push button may be used to select data for presentation on the pilot s EHSI either NAV data from NAV 1 or NAV 2 navigation receiver or GPS 1 or if installed GPS 2 data or ADF data NAV symbol is green GPS1 symbol is blue GPS2 symbol is yellow and ADF symbol is green Colors relative to EHSI symbols are as follows CONFIGURATION TEXTS LEG OR NEEDLE GPS1 Blue Active leg Blue Not active...

Page 821: ...nunciator of GPS 2 system OPT70 23025 are displayed on L H instrument panel amber indication see Figure 9 36 1 Detail A WPT Waypoint annunciator This annunciator illuminates 10 seconds before warning TURN TO XXX WPT Waypoint annunciator is also displayed on the L H side of the EHSI APR annunciator is also displayed on the L H side of the EHSI Flight director autopilot coupled operation The EHSI ma...

Page 822: ...temporarily disengage the autopilot NAV mode before changing source GPS flight plan In the active flight plan addition of a STAR or an approach is always made at the end of the flight plan In the scope of these additions the pilot must pay attention not to duplicate points Non precision approach with coupled autopilot The EHSI must be set in HSI Compass Rose mode Coupling with autopilot must be ma...

Page 823: ...ion 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEIGHT per unit lb kg ARM in m 23 COMMUNICATIONS A COM NAV GPS 1 GNS 530 B RNAV interfaced with EHSI OPT70 23024 GARMIN 1 8...

Page 824: ...T70 23024 The option includes the GPS 1 system consisting of one GNS 530 GPS see Figure 9 36 1 This GPS may be a navigation source for the autopilot Course deviation information is then displayed on the EHSI one MSG1 repeater on pilot s instrument panel 7 2 GNS 530 System 2 OPTION OPT70 23025 The option includes the GPS 2 system consisting of one GNS 530 GPS see Figure 9 36 1 This GPS may be a nav...

Page 825: ...TBM 700 SUPPLEMENT 36 GARMIN GNS 530 GPS NAVIGATION SYSTEM B RNAV INTERFACED WITH EHSI OF EFS 40 Page 9 36 14 Rev 1 Figure 9 36 1 GARMIN GNS 530 GPS SYSTEMS ...

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Page 838: ...URES 9 41 11 Airspeeds for normal operation 9 41 11 Check list procedures 9 41 11A Amplified procedures 9 41 15A Particular procedures 9 41 25 5 PERFORMANCE 9 41 30 Acoustic limitation 9 41 32 Stall speeds 9 41 33 Demonstrated crosswind 9 41 33 Takeoff distances 9 41 34 Climb performance 9 41 35 Cruise performance 9 41 40 Landing distances 9 41 65 6 WEIGHT AND BALANCE 9 41 66 General 9 41 66 Deter...

Page 839: ...PPLEMENT 41 TBM 700C2 Page 9 41 2 Rev 5 TABLE OF CONTENTS Continued 8 HANDLING SERVICING AND MAINTENANCE 9 41 78 Servicing 9 41 78 Utilization by cold weather 0 C to 25 C or very cold weather 25 C to 40 C 9 41 78 ...

Page 840: ... Power loading 10 55 lbs SHP 4 79 kg SHP SECTION 2 LIMITATIONS The limitations hereafter supplement or replace those of the TBM 700C1 airplane described in Section 2 Limitations of the TBM 700C1 Pilot s Operating Handbook when using the TBM 700C2 airplane between 6579 lbs 2984 kg and 7394 lbs 3354 kg for takeoff weight and or between 6250 lbs 2835 kg and 7024 lbs 3186 kg for landing weight 2 1 WEI...

Page 841: ...at 6579 lbs 2984 kg 20 85 of m a c 187 inches 4 752 m aft of datum at all weights above 7024 lbs 3186 kg 23 8 of m a c Aft limits 194 9 inches 4 951 m aft of datum at all weights below 6250 lbs 2835 kg 37 of m a c 194 3 inches 4 936 m aft of datum at 6579 lbs 2984 kg 36 of m a c 193 65 inches 4 921 m aft of datum at 7394 lbs 3354 kg 35 of m a c 2 2 OPERATION LIMITS FLIGHT LOAD FACTOR LIMITS Flaps ...

Page 842: ...G KIAS Value or range SIGNIFICANCE White arc Wide Narrow 65 122 65 81 81 122 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Transition point between wide and narrow arcs is stall speed with flaps UP Upper limit is maximum speed permissible with flaps LDG Red line 266 Maximum speed for all operations Figure 9 41 1 AIRSPEED INDICATOR MARKINGS ...

Page 843: ...TBM 700 SUPPLEMENT 41 TBM 700C2 Page 9 41 2D Rev 5 INTENTIONALLY LEFT BLANK ...

Page 844: ...v 4 2 4 PLACARDS Under L H front side window On main gear leg MAIN LANDING GEAR TIRE PRESSURE 8 96 bar 130 psi On pressurized baggage compartment partition wall With partition net version A refer to Section 6 of TBM 700C1 Pilot s Operating Handbook ...

Page 845: ...TBM 700 SUPPLEMENT 41 TBM 700C2 Page 9 41 4 Rev 1 With partition net version B refer to Section 6 of TBM 700C1 Pilot s Operating Handbook ...

Page 846: ...g weight 3 1 ENGINE FAILURES ENGINE FAILURE AFTER ROTATION If altitude does not allow to choose a favourable runway or field Land straight ahead keeping flaps at TO and without changing landing gear position Before touch down 1 Maintain IAS 85 KIAS 2 Power lever IDLE 3 Condition lever CUT OFF 4 Tank selector OFF 5 CRASH lever PULL DOWN If altitude allows to reach a favourable runway or ground 1 LD...

Page 847: ...COND switch OFF 8 DUMP switch ACTUATED 9 Glide speed 120 KIAS maintained until favourable ground approach If ground allows it 10 ESS BUS TIE reverse switch NORMAL in order to have GEAR and FLAPS available 11 Landing gear DN If night conditions 12 L LDG R LDG ON If ground does not allow it 13 Keep landing gear UP 14 When chosen ground is assured FLAPS LDG 15 CRASH lever PULL DOWN 16 Final approach ...

Page 848: ...N 1 Transfer passengers to the rear if necessary 2 Approach Flaps TO IAS 95 KIAS 3 Land with nose up attitude keep nose high 4 Condition lever CUT OFF 5 Propeller governor lever FEATHER 6 Touch down slowly with nose wheel and keep elevator at nose up stop 7 Moderate braking 8 CRASH lever PULL DOWN 9 EVACUATE after airplane comes to a stop ...

Page 849: ...l approach Standard Flaps LDG IAS 85 KIAS 2 BLEED switch OFF 3 DUMP switch ACTUATED When runway is assured 4 Power lever IDLE 5 Propeller governor lever FEATHER 6 Condition lever CUT OFF 7 Tank selector OFF 8 Flare out 9 After touch down CRASH lever PULL DOWN 10 EVACUATE after airplane comes to a stop ...

Page 850: ...ning approach airspeed Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 100 KIAS IAS 105 KIAS Provide for a landing distance increased up to about 60 For flaps deflections greater than TO position Proceed as for a normal landing maintaining approach airspeed Weight 6250 lbs 2835 kg Weight 6250 lbs 2835 kg IAS 95 KIAS IAS 100 KIAS Provide for a landing distance increased up to about 50 ...

Page 851: ...TBM 700 SUPPLEMENT 41 TBM 700C2 Page 9 41 8B Rev 5 INTENTIONALLY LEFT BLANK ...

Page 852: ... land parallel to the swell rollers In heavy wind land facing wind 2 Flaps LDG 3 Maintain a descent rate as low as possible when approaching the water 4 Airspeed IAS 85 KIAS 5 BLEED switch OFF 6 DUMP switch ACTUATED 7 CRASH lever PULL DOWN 8 Maintain attitude without rounding off until touch down 9 EVACUATE through EMERGENCY EXIT ...

Page 853: ... L WINDSHIELD switch ON 4 R WINDSHIELD switch ON If not successful to gain sufficient visibility 5 Manually clean a sufficient visibility area 6 If necessary clean L H side window and conduct a sideslip approach rudder pedals to the right in order to get sufficient landing visual references 7 Maintain IAS 95 KIAS CAUTION IN CASE OF SIDESLIP APPROACH WITH PEDAL ON THE RIGHT DURING A LONG PERIOD SEL...

Page 854: ...CONDITIONS Takeoff weight 7394 lbs 3354 kg Landing weight 7024 lbs 3186 kg 1 Rotation airspeed VR Flaps TO Depending on weight See Takeoff distances Chapter 5 4 of this Supplement 2 Best rate of climb speed VY Landing gear UP flaps UP 124 KIAS 3 Best angle of climb speed Vx 100 KIAS 4 Maximum speed Flaps TO 178 KIAS Flaps LDG 122 KIAS 5 Maximum speed with landing gear down 178 KIAS 6 Maximum landi...

Page 855: ...r if installed CLOSED LOCKED 4 Baggage STOWED 5 Parking brake SET 6 Weight and balance COMPUTED CHECKED 7 Pilot seat and R H front seat if occupied Height adjustment Maximum UP Fore and aft adjustment ADJUST and CHECK LOCKING Height adjustment ADJUST 8 R H and L H pedals ADJUSTED 9 Belts and harnesses Pilot and passengers FASTENED 10 Oxygen supply Available for the planned flight see tables in Cha...

Page 856: ...4 NORMAL MASK micro inverter NORMAL 15 IGNITION switch AUTO or OFF 16 STARTER switch OFF 17 Landing gear control DN 18 RADIO MASTER switch ON 19 RADIO VHF1 ON ADJUSTED 20 Authorization for engine starting ASKED 21 ETM Fuel remaining Check Added fuel Insert Fuel flow page Select 22 SOURCE selector BAT or GPU 23 BAT TEMP TEST push button Cadmium Nickel battery if installed PRESS 24 Passengers briefi...

Page 857: ...LIGHT AUTO SEL OFF SHIFT push button PRESS The selector changes tank On ground observe a tank change every minute and 15 seconds 27 ETM fuel flowmeter totalizer CHECKED ADJUSTED 28 Engine instruments CHECK 29 ITT TEST CARRY OUT 30 EXT LIGHTS panel STROBE AS REQUIRED 31 In case of night flight INT LIGHTS panel INSTR PANEL ADJUSTED Navigation lights ON Flashlight if necessary IN PLACE ...

Page 858: ...SUPPLEMENT 41 TBM 700C2 TBM 700 Page 9 41 11D Rev 5 INTENTIONALLY LEFT BLANK ...

Page 859: ...CK 2 Horizon Attitude 2 CHECK 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ITT green sector 5 Advisory panel CHECK All warning lights OFF except INERT SEP if used except IGNITION if used 6 Radar switch As required 7 PROP O SPEED GOVERNOR TEST Increase power until propeller RPM reaches 1900 RPM PROP O SPEED TEST Maintain engaged Observe that propeller RPM decreases by 50 to 250 RPM PROP ...

Page 860: ...f this Supplement Attitude for normal takeoff 7 5 Attitude for performance takeoff 12 5 11 Vertical speed indicator POSITIVE 12 Brakes APPLY Briefly 13 Landing gear control IAS 128 KIAS UP At sequence end check All warning lights OFF 14 Lights TAXI OFF L LDG R LDG AS REQUIRED 15 Initial climb speed 115 KIAS 16 Flaps UP 17 Climb speed recommended 130 KIAS 18 YAW DAMPER push button ON ...

Page 861: ...tity 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 Green indicator lights ON 6 Flaps IAS 178 KIAS TO 7 Lights L LDG TAXI R LDG ON 8 Autopilot OFF 9 Radar switch SBY Short final 10 Flaps IAS 122 KIAS LDG 11 Approach speed Flaps LDG 85 KIAS 12 YAW DAMPER push button OFF ...

Page 862: ...tical speed is positive and if IAS is at or above 90 kt 3 Landing gear control UP All warning lights OFF If IAS is at or above 115 kt 4 Flaps UP 5 Climb speed AS REQUIRED TOUCH AND GO After wheel touch 1 Flaps TO 2 Elevator trim Green sector 3 Power lever Display TRQ 100 4 Takeoff ROTATION See Takeoff distances Chapter 5 4 of this Supplement ATTITUDE 7 5 ...

Page 863: ...ITCH ON MAY CAUSE OVERTEMPERATURE OR ABNORMAL ACCELERATION AT START CAUTION MAKE SURE THAT MAN OVRD CONTROL IS OFF TO AVOID OVERTEMPERATURE RISKS AT START 1 Preflight inspection COMPLETED 2 Cabin access door CLOSED LOCKED 3 Pilot door if installed CLOSED LOCKED 4 Baggage STOWED 5 Parking brake SET PARK BRAKE warning light located on advisory panel does not indicate that parking brake is set For th...

Page 864: ...esses so as to permit access to all flight controls The pilot at L H station must be able to easily reach ECS panel 8 R H and L H pedals ADJUSTED 9 Belts and harnesses Pilot and passengers FASTENED Check belt buckles for correct locking as well as automatic locking of shoulder harness by exerting a rapid pull on the latter 10 Oxygen supply Available for the planned flight see tables in Chapter 4 3...

Page 865: ... automatically cuts off radio equipment during starter operation The function GND CLR ground clearance enables when RADIO MASTER switch is ON to obtain VHF1 supply without having selected battery contact 20 Authorization for engine starting ASKED 21 ETM Fuel remaining Check Added fuel Insert Fuel flow page Select The SHADIN ETM operation normal procedures are described in the Operation Manual at t...

Page 866: ...O WARNING LIGHT AUTO SEL OFF SHIFT push button PRESS The selector changes tank On ground observe a tank change every minute and 15 seconds 27 ETM fuel flowmeter totalizer CHECKED ADJUSTED Total fuel quantity on board may be set on flowmeter totalizer see instruction in Section 7 of the TBM 700C1 Pilot s Operating Handbook or refer to manufacturer technical data 28 Engine instruments CHECK 29 ITT T...

Page 867: ...learance is available on airplane VHF1 can be operated by setting SOURCE selector to OFF and RADIO MASTER switch to ON A correct operation is provided by the GND CLR green light illuminating above the RADIO MASTER switch If battery voltage is low near 25 volts turn off all unessential electrical equipment before selecting the starter ON By night emergency lighting provided by two luminous spot lig...

Page 868: ...SUPPLEMENT 41 TBM 700C2 TBM 700 Page 9 41 15F Rev 5 INTENTIONALLY LEFT BLANK ...

Page 869: ...S 1 Heading HSI Stand by compass CHECK The indication of the stand by compass is disturbed when windshield s deice system s is are activated Altimeter setting CHECK 2 Horizon Attitude 2 CHECK Horizon has been set so as to indicate a 2 nose up attitude when airplane center of gravity is at a middle average 3 Lights L LDG TAXI R LDG ON 4 Engine instruments CHECK ITT green sector 5 Advisory panel CHE...

Page 870: ...O SPEED test 8 Brakes RELEASED It is not necessary to reduce power at the end of OVERSPEED test torque will be about 40 before brake release For a normal takeoff maximum torque 100 will be applied after brake release On short runway maximum torque will be applied before brake release 9 Power lever TRQ 100 10 Takeoff ROTATION See Takeoff distances Chapter 5 4 of this Supplement Attitude for normal ...

Page 871: ...xed 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 off at the end of the sequence At sequence end check All warning lights OFF In practice if preconized attitude is kept there is no difficulty to maintain a speed 128 KIAS until landing gear retraction is completed 14 Lights TAXI OFF L LDG R LD...

Page 872: ...ower torque setting MXCL For each engine when torque is reduced below 100 at high altitude according to the tables the ITT will be approximately constant during final climb giving a particular value of ITT For a simplified engine operation during climb power may be set first of all by torque using 100 then when the ITT typical value for climb is reached by indicated ITT using this particular value...

Page 873: ...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 Pre MOD70 0402 28 In spite of fuel selector automatic operation a non negligible dissymmetry may be observed at the end of climb for example when 10 minutes of climb have been performed on the same fuel tank Tolerated maximum dissymmetry is 25...

Page 874: ...ence The red warning light flashes it indicates that the landing gear motor is electrically supplied It goes off when the 3 landing gears are locked If the red warning light is fixed ON there is a discrepancy refer to EMERGENCY PROCEDURES of the TBM 700C1 Pilot s Operating Handbook It is possible that the 3 landing gear position green indicator lights flash uncertainly then come on at the end of t...

Page 875: ...hen autopilot is engaged in APR mode with coupled GS flaps must be extended in landing position before crossing the OUTER MARKER 11 Approach speed Flaps LDG 85 KIAS To ensure positive and rapid engine response to throttle movement it is recommended that a minimum of 10 torque be maintained on final approach until landing is assured 12 YAW DAMPER push button OFF The pilot effort required to use the...

Page 876: ...sure will be required to maintain coordinated straight flight until the rudder trim can be adjusted to TO sector 2 Flaps TO If speed has been maintained at 85 KIAS or more and TRQ 100 select TO flaps as soon as the 7 5 attitude has been attained If the vertical speed is positive and if IAS is at or above 90 KIAS 3 Landing gear control UP All warning lights OFF If IAS is at or above 115 KIAS 4 Flap...

Page 877: ... 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 length is sufficient to complete this sequence 3 Power lever Display TRQ 100 4 Takeoff ROTATION See Takeoff distances Chapter 5 4 of this Supplement ATTITUDE 7 5 However the pilot s operating handbook does not supply distances concerning touch and...

Page 878: ... engine or cowlings NOTE Refer to Figure 5 4 1 of the TBM 700C1 Pilot s Operating Handbook to convert IOAT to SAT in flight SAT IOAT 2 C on the ground 3 Flight into known icing conditions is authorized when all airplane equipment provided for ice protection is operating correctly This includes Pneumatic deice system for inboard and outboard wing for stabilizers and for elevator horns Propeller ele...

Page 879: ...EADING EDGES DEICING FAILURE emergency procedure of the TBM 700C1 Pilot s Operating Hankbook Ice protection procedures 1 Prior to entering IMC as a preventive If IOAT 13 C INERT SEP switch ON IGNITION switch ON PROP DE ICE switch ON AIRFRAME DE ICE switch ON WINDSHIELD DE ICE switch ON 2 When operating under IMC INERT SEP switch ON IGNITION switch ON PROP DE ICE switch ON AIRFRAME DE ICE switch ON...

Page 880: ...peed 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 during descent to set the inertial separator IF AIRPLANE LEAVES ICING CONDITIONS MAINTAIN INERT SEP ON AS LONG AS ICE THICKNESS ON NON DEICED VISIBLE PARTS EXCEEDS 15 mm OR INCH This will avoid ice fragments coming from propeller spinner...

Page 881: ...altered when windshield deicing system s operate s 3 Procedures for holding approach and landing in icing conditions Minimum recommended speeds are Flaps UP 135 KIAS Flaps TO 115 KIAS Flaps LDG 95 KIAS If there is ice on the unprotected surfaces of the airplane during flight end phase conduct holding with the flaps up Use flaps as required for final approach and landing at minimum speeds noted abo...

Page 882: ... 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 increase of the iced up airplane taking as a basis the airplane maximum weight when not iced up Rate of climb values with ice accumulation on the unprotected surfaces are to be decreased by 10 Cruise speeds may be decreased by 10 if cruise powe...

Page 883: ...SA 20 C 9 41 38 Fig 9 41 8 CLIMB PERFORMANCE AFTER GO AROUND 9 41 39 Fig 9 41 9 CLIMB PERFORMANCE FLAPS TO 9 41 39 5 6 CRUISE PERFORMANCE 9 41 40 Maximum cruise 9 41 40 Fig 9 41 10 Conditions ISA 20 C 9 41 40 Fig 9 41 11 Conditions ISA 10 C 9 41 41 Fig 9 41 12 Conditions ISA 5 C 9 41 42 Fig 9 41 13 Conditions ISA 9 41 43 Fig 9 41 14 Conditions ISA 5 C 9 41 44 Fig 9 41 15 Conditions ISA 10 C 9 41 4...

Page 884: ... 9 41 57 Fig 9 41 28 Conditions ISA 5 C 9 41 58 Fig 9 41 29 Conditions ISA 10 C 9 41 59 Fig 9 41 30 Conditions ISA 20 C 9 41 60 Long Range Cruise 6614 lbs 3000 kg 9 41 61 Fig 9 41 31 1 2 Altitude 24000 ft 9 41 61 Fig 9 41 31 2 2 Altitude 24000 ft 9 41 62 Long Range Cruise 7275 lbs 3300 kg 9 41 63 Fig 9 41 32 1 2 Altitude 24000 ft 9 41 63 Fig 9 41 32 2 2 Altitude 24000 ft 9 41 64 5 7 LANDING DISTAN...

Page 885: ...2984 kg and 7394 lbs 3354 kg for takeoff weight and or between 6250 lbs 2835 kg and 7024 lbs 3186 kg for landing weight 5 1 ACOUSTIC LIMITATION Maximum noise level permissible Demonstrated noise level FAR PART 36 Appendix G Amendment 22 OACI Annex 16 Chapter 10 Appendix 6 88 dB A 79 6 dB A TBM 700 airplane has received the noise limitation type certificate Nr N181 dated 31st January 1990 as well a...

Page 886: ...0 45 60 WEIGHT LDG GR Flaps KIAS KCAS MPH IAS KIAS KCAS MPH IAS KIAS KCAS MPH IAS KIAS KCAS MPH IAS 7394 lbs 3354 kg UP DN DN UP TO LDG 81 77 65 83 77 65 93 89 75 88 81 69 89 83 70 101 93 79 97 91 76 99 92 77 112 105 88 119 108 92 117 109 92 137 124 106 Figure 9 41 2 STALL SPEEDS 5 3 DEMONSTRATED CROSSWIND 20 kts ...

Page 887: ...80 2790 2495 2755 3055 3415 3825 1905 2120 2380 2675 3055 2675 2955 3285 3675 4135 2035 2280 2545 2890 3315 2840 3150 3510 3955 4445 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 2165 2445 2740 3135 3560 3020 3365 3760 4235 4760 2315 2595 2955 3380 3855 3200 3580 4035 4530 5105 2480 2780 3185 3625 4170 3415 3805 4300 4825 5450 2560 2920 ...

Page 888: ...eet ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 130 SL 2000 4000 6000 8000 1725 1700 1670 1640 1610 1645 1615 1590 1555 1525 1570 1540 1510 1480 1445 1500 1470 1440 1410 1375 1435 1405 1375 1340 1310 1380 1345 1315 1280 1250 160 SL 2000 4000 6000 8000 1540 1510 1470 1430 1395 1460 1430 1390 1350 1315 1390 1355 1315 1275 1240 1320 1285 1245 1205 1170 1255 1225 1185 1140 1105 1200 1165 1125 108...

Page 889: ...0 7 5 2 3 4000 02 25 11 9 3 5 02 40 13 10 3 7 6000 03 35 17 13 4 8 04 00 19 15 5 11 8000 04 50 22 18 6 11 05 25 25 20 7 15 10000 06 00 28 22 7 13 06 55 32 25 8 19 12000 07 20 33 26 9 17 08 25 38 30 10 23 14000 08 35 38 30 10 20 09 55 44 34 12 28 16000 09 55 43 34 11 23 11 30 50 39 13 33 18000 11 20 48 38 13 27 13 05 56 44 15 38 20000 12 40 54 42 14 31 14 55 63 49 17 45 22000 14 05 59 46 16 35 16 3...

Page 890: ... 2 4 4000 02 35 13 10 3 6 03 00 15 12 4 8 6000 03 50 19 15 5 9 04 30 22 17 6 12 8000 05 20 25 20 7 12 06 05 29 23 8 17 10000 06 40 31 25 8 15 07 40 36 28 10 22 12000 08 05 37 29 10 19 09 25 43 34 11 27 14000 09 30 43 34 11 23 11 05 50 40 13 33 16000 11 00 49 39 13 27 13 00 58 45 15 39 18000 12 30 55 43 15 31 14 55 65 51 17 46 20000 14 05 61 48 16 36 16 55 73 57 19 53 22000 15 50 67 53 18 41 18 55 ...

Page 891: ...8 7 2 5 4000 02 50 15 11 4 7 03 20 17 13 4 9 6000 04 20 22 17 6 10 05 00 25 20 7 14 8000 05 50 28 22 8 14 06 40 33 26 9 20 10000 07 20 35 28 9 18 08 35 41 32 11 25 12000 08 55 42 33 11 22 10 30 49 39 13 32 14000 10 30 49 38 13 26 12 30 58 45 15 38 16000 12 10 56 44 15 31 14 35 66 52 17 46 18000 14 00 63 49 17 36 17 00 75 59 20 54 20000 16 10 70 55 19 43 19 55 86 68 23 65 22000 18 40 79 62 21 51 23...

Page 892: ...905 865 825 780 740 850 810 770 730 685 805 765 720 680 630 760 715 675 630 580 Figure 9 41 8 CLIMB PERFORMANCE AFTER GO AROUND CLIMB PERFORMANCE FLAPS TO Conditions Climb maximum power Landing gear UP and flaps TO IAS 115 KIAS Airplane Pressure RATE OF CLIMB ft min Airplane weight Pressure altitude feet ISA 35 C ISA 20 C ISA 10 C ISA ISA 10 C ISA 20 C ISA 30 C 7394 lbs 3354 kg SL 2000 4000 6000 8...

Page 893: ... 271 204 269 21000 37 100 216 170 57 1 205 274 203 271 22000 39 100 214 168 56 5 204 277 202 274 23000 41 100 212 166 56 0 203 280 200 278 24000 43 100 210 165 55 6 202 283 200 280 25000 45 100 209 164 55 3 201 286 198 283 26000 46 100 208 163 54 9 200 289 197 286 27000 48 100 207 162 54 7 198 292 196 289 28000 50 100 206 162 54 4 197 295 195 292 29000 52 100 206 161 54 3 196 299 194 295 30000 54 ...

Page 894: ...274 202 272 21000 27 100 218 171 57 6 203 277 201 275 22000 29 100 216 170 57 1 202 280 200 277 23000 31 100 215 168 56 7 201 283 198 281 24000 33 100 213 167 56 3 199 286 197 283 25000 34 100 212 166 55 9 198 289 196 286 26000 36 100 210 165 55 6 197 292 195 289 27000 38 100 209 164 55 3 196 296 194 292 28000 40 100 209 164 55 2 195 299 192 295 29000 42 97 201 158 53 2 191 297 188 292 30000 44 93...

Page 895: ... 276 201 273 21000 22 100 220 173 58 1 202 279 200 276 22000 24 100 218 171 57 5 201 282 199 279 23000 26 100 216 170 57 1 200 285 197 283 24000 28 100 215 168 56 7 199 288 196 285 25000 29 100 213 167 56 3 198 291 195 288 26000 31 100 212 166 56 0 196 294 194 291 27000 33 99 210 165 55 5 194 296 192 292 28000 35 96 202 159 53 5 190 294 187 290 29000 37 92 195 153 51 5 185 292 182 287 30000 39 88 ...

Page 896: ...2 278 200 275 21000 17 100 221 174 58 5 201 281 199 278 22000 19 100 220 172 58 0 200 283 198 280 23000 21 100 218 171 57 5 199 286 196 284 24000 22 100 216 170 57 1 198 290 195 286 25000 24 100 215 169 56 8 197 293 194 289 26000 26 99 209 164 55 2 194 294 191 290 27000 28 95 202 159 53 5 190 292 187 287 28000 30 91 195 153 51 6 185 290 182 285 29000 32 88 188 148 49 8 181 288 177 282 30000 34 84 ...

Page 897: ...1 279 199 276 21000 12 100 223 175 58 9 200 282 198 279 22000 14 100 221 174 58 5 199 285 197 282 23000 16 100 220 172 58 0 198 288 195 286 24000 17 100 218 172 57 7 197 291 194 288 25000 19 97 211 166 55 9 194 292 192 288 26000 21 94 204 161 54 0 190 291 187 286 27000 23 90 197 155 52 0 185 289 182 283 28000 25 87 190 149 50 1 181 287 177 281 29000 27 83 182 143 48 2 176 284 172 277 30000 29 80 1...

Page 898: ...200 281 198 278 21000 7 100 224 176 59 2 199 284 197 280 22000 9 100 223 175 58 9 198 286 196 283 23000 11 98 218 171 57 6 197 289 193 285 24000 13 96 211 166 55 7 193 288 190 284 25000 15 92 204 160 53 9 189 287 186 282 26000 17 89 197 155 52 0 184 285 181 280 27000 19 86 190 150 50 3 180 283 176 278 28000 20 82 184 144 48 5 175 281 171 274 29000 22 79 176 139 46 6 171 278 166 271 30000 24 75 170...

Page 899: ... 4 197 282 195 278 21000 2 94 218 171 57 5 193 280 190 276 22000 0 92 211 166 55 7 190 280 187 276 23000 2 88 204 160 53 9 186 278 181 273 24000 3 86 197 155 52 0 182 277 178 272 25000 5 82 190 149 50 2 178 275 174 270 26000 7 79 183 144 48 3 173 273 169 266 27000 9 76 176 139 46 6 168 270 163 263 28000 11 72 170 133 44 8 163 266 157 258 29000 13 69 163 128 43 1 157 263 151 253 30000 15 66 156 122...

Page 900: ...6 206 271 204 269 21000 37 100 216 170 57 1 205 274 203 271 22000 39 100 214 168 56 5 204 277 202 274 23000 41 100 212 166 56 0 203 280 201 277 24000 43 100 210 165 55 6 202 283 200 280 25000 45 100 209 164 55 3 201 286 198 283 26000 46 100 208 163 54 9 200 289 197 286 27000 48 100 207 162 54 7 198 292 196 289 28000 50 100 206 162 54 4 197 295 195 292 29000 52 100 206 161 54 3 196 299 194 295 3000...

Page 901: ...8 2 204 274 202 272 21000 27 100 218 171 57 6 203 277 201 275 22000 29 100 216 170 57 1 202 280 200 277 23000 31 100 215 168 56 7 201 283 199 280 24000 33 100 213 167 56 3 200 286 197 283 25000 34 100 212 166 55 9 198 289 196 286 26000 36 100 210 165 55 6 197 292 195 289 27000 38 99 207 162 54 7 195 293 192 289 28000 40 96 199 157 52 7 190 292 187 287 29000 42 92 193 151 50 9 186 290 183 285 30000...

Page 902: ...58 6 203 276 201 273 21000 22 100 220 173 58 1 202 279 200 276 22000 24 100 218 171 57 5 201 282 199 279 23000 26 100 216 170 57 1 200 285 198 282 24000 28 100 215 168 56 7 199 288 196 285 25000 29 100 213 167 56 3 198 291 195 287 26000 31 98 208 163 54 9 194 291 192 287 27000 33 95 201 158 53 1 190 289 187 285 28000 35 91 195 153 51 4 185 287 182 282 29000 37 87 188 147 49 6 181 285 177 279 30000...

Page 903: ...58 9 202 278 200 275 21000 17 100 221 174 58 5 201 281 199 278 22000 19 100 220 172 58 0 200 283 198 280 23000 21 100 218 171 57 5 199 286 196 283 24000 22 100 216 170 57 1 198 290 195 286 25000 24 97 209 164 55 3 194 289 191 285 26000 26 94 203 159 53 6 190 288 187 283 27000 28 90 196 154 51 9 185 286 182 281 28000 31 86 190 149 50 1 181 284 177 278 29000 33 83 183 144 48 3 176 281 172 274 30000 ...

Page 904: ... 59 3 201 279 199 276 21000 12 100 223 175 58 9 200 282 198 279 22000 14 100 221 174 58 5 199 285 197 282 23000 16 97 216 170 57 1 196 286 194 282 24000 18 95 209 164 55 1 192 285 190 281 25000 20 92 202 159 53 4 188 284 186 279 26000 22 89 195 153 51 5 184 282 181 277 27000 24 84 188 148 49 8 180 280 176 275 28000 26 81 182 143 48 0 175 278 171 272 29000 28 78 175 137 46 2 171 275 166 268 30000 3...

Page 905: ...196 279 22000 10 96 214 168 56 5 195 282 192 278 23000 12 92 207 162 54 7 191 281 188 277 24000 13 90 200 157 52 8 187 279 184 275 25000 15 87 193 152 51 1 183 278 180 273 26000 17 83 187 147 49 4 178 276 175 271 27000 19 79 181 142 47 7 174 274 170 267 28000 21 76 174 137 46 0 169 271 164 264 29000 23 73 167 131 44 1 164 268 159 259 30000 25 69 166 130 43 9 159 264 153 254 31000 27 67 154 121 40 ...

Page 906: ...91 272 188 268 21000 2 87 206 162 54 4 187 272 184 267 22000 0 84 200 157 52 8 183 270 180 266 23000 2 81 193 152 51 0 179 269 176 264 24000 4 78 187 146 49 3 175 267 171 262 25000 6 76 180 141 47 6 171 265 167 259 26000 8 72 173 136 45 8 166 262 161 255 27000 10 69 167 131 44 1 161 259 155 250 28000 12 66 160 126 42 3 155 255 29000 14 63 157 120 40 6 150 251 Figure 9 41 23 CRUISE PERFORMANCE Norm...

Page 907: ...8 198 155 52 2 195 260 192 257 22000 40 88 195 153 51 6 193 263 191 260 23000 42 88 193 152 51 1 192 266 190 262 24000 44 88 192 151 50 7 191 268 189 265 25000 45 88 190 149 50 2 190 271 188 267 26000 47 88 188 148 49 7 189 274 186 270 27000 49 88 187 147 49 4 188 277 185 273 28000 51 88 186 146 49 1 187 280 184 275 29000 53 88 185 145 48 9 186 283 183 279 30000 54 87 183 144 48 3 184 285 181 280 ...

Page 908: ...88 199 157 52 7 193 263 190 260 22000 30 88 198 155 52 2 192 266 189 263 23000 31 88 195 153 51 6 190 269 188 265 24000 33 88 194 152 51 2 189 272 187 268 25000 35 88 192 151 50 7 188 274 185 270 26000 37 88 190 150 50 3 187 277 184 273 27000 39 85 185 146 49 0 183 276 180 272 28000 41 82 179 141 47 3 179 275 176 269 29000 43 79 173 135 45 6 175 273 171 267 30000 45 76 166 130 43 9 170 271 166 264...

Page 909: ...01 158 53 1 192 265 189 261 22000 25 88 199 156 52 5 191 267 188 264 23000 26 88 197 155 52 0 189 270 187 267 24000 28 88 195 153 51 5 188 273 186 269 25000 30 87 5 193 151 50 9 187 276 184 271 26000 32 84 7 187 146 49 3 183 274 180 270 27000 34 82 181 142 47 7 179 273 176 268 28000 36 79 174 137 46 0 175 272 171 266 29000 38 76 167 131 44 2 171 269 167 263 30000 40 73 3 161 126 42 5 166 267 162 2...

Page 910: ...90 269 187 265 23000 21 88 198 156 52 4 189 272 186 268 24000 23 87 3 195 153 51 5 187 274 184 270 25000 25 84 3 188 148 49 8 183 273 180 268 26000 27 81 2 182 143 48 1 179 271 175 266 27000 29 78 176 138 46 4 174 269 170 263 28000 31 75 169 133 44 6 170 266 166 260 29000 33 72 162 128 42 9 165 264 160 256 30000 35 69 156 122 41 2 160 260 155 252 31000 37 66 151 118 39 8 155 256 Figure 9 41 27 CRU...

Page 911: ...1 189 270 186 267 23000 16 85 6 195 153 51 5 185 270 183 266 24000 18 82 7 189 148 49 9 182 269 179 264 25000 20 79 8 182 143 48 2 178 267 174 262 26000 22 76 9 176 139 46 6 173 265 169 260 27000 24 74 170 134 45 0 169 263 165 257 28000 27 71 164 129 43 3 164 261 159 253 29000 29 68 1 157 124 41 6 159 258 30000 31 65 2 151 119 39 9 154 253 31000 33 62 5 146 114 38 5 149 250 Figure 9 41 28 CRUISE P...

Page 912: ...53 1 188 267 185 263 22000 10 84 195 153 51 5 184 267 181 262 23000 12 81 190 149 50 1 180 265 177 261 24000 14 78 183 144 48 3 176 263 173 258 25000 16 75 5 177 139 46 8 172 262 168 256 26000 18 73 171 134 45 2 168 260 164 254 27000 20 70 165 130 43 6 163 258 158 250 28000 22 67 159 124 41 9 158 254 29000 24 64 153 120 40 3 152 250 Figure 9 41 29 CRUISE PERFORMANCE Intermediate cruise ISA 10 C NO...

Page 913: ...154 51 9 180 257 177 253 21000 2 76 4 190 150 50 3 176 256 173 251 22000 0 74 184 144 48 6 173 255 169 249 23000 2 71 2 178 140 47 0 168 252 164 246 24000 4 69 172 135 45 4 164 251 160 244 25000 6 66 165 130 43 7 159 248 26000 8 63 4 159 125 42 1 154 244 27000 10 60 7 154 120 40 6 149 240 Figure 9 41 30 CRUISE PERFORMANCE Intermediate cruise ISA 20 C NOTE No airspeed data means that the cruise spe...

Page 914: ...6 279 218 43 2 283 220 40 160 30 158 20 156 10 155 0 153 21000 57 5 40 40 4 160 30 40 9 158 20 41 5 156 10 42 1 155 0 42 6 153 21000 57 5 40 4 265 214 40 9 268 217 41 5 272 219 42 1 276 221 42 6 279 223 42 159 32 158 22 156 12 154 2 152 22000 58 0 42 39 9 159 32 40 4 158 22 40 9 156 12 41 5 154 2 42 0 152 22000 58 0 39 9 261 217 40 4 265 220 40 9 268 222 41 5 272 224 42 0 275 225 44 159 34 157 24 ...

Page 915: ...36 39 6 259 238 40 2 263 240 53 156 43 154 33 152 23 150 13 148 28000 61 0 53 38 0 156 43 38 4 154 33 38 9 152 23 39 4 150 13 39 9 148 28000 61 0 38 0 249 235 38 4 252 237 38 9 255 239 39 4 258 241 39 9 261 243 55 156 45 153 35 151 25 149 15 147 29000 61 5 55 37 8 156 45 38 3 153 35 38 8 151 25 39 2 149 15 39 7 147 29000 61 5 37 8 248 239 38 3 251 240 38 8 254 243 39 2 257 244 39 7 260 246 57 155 ...

Page 916: ...2 296 225 45 8 300 227 40 166 30 164 20 162 10 160 0 158 21000 64 5 40 43 1 166 30 43 7 164 20 44 2 162 10 44 7 160 0 45 3 158 21000 64 5 43 1 282 222 43 7 286 224 44 2 290 226 44 7 293 228 45 3 297 230 42 165 32 163 22 161 12 159 2 157 22000 65 0 42 42 7 165 32 43 2 163 22 43 7 161 12 44 2 159 2 44 8 157 22000 65 0 42 7 280 225 43 2 283 227 43 7 286 229 44 2 290 231 44 8 293 233 44 165 34 163 24 ...

Page 917: ...3 159 33 41 8 156 23 42 3 154 13 42 8 152 28000 68 0 40 9 268 242 41 3 271 244 41 8 274 246 42 3 277 248 42 8 280 249 55 160 45 158 35 156 25 153 15 151 29000 68 5 55 40 7 160 45 41 2 158 35 41 7 156 25 42 2 153 15 42 7 151 29000 68 5 40 7 267 245 41 2 270 247 41 7 273 249 42 2 276 251 42 7 280 252 69 0 57 160 47 157 37 155 27 152 17 144 30000 69 0 1 57 40 6 160 47 41 0 157 37 41 5 155 27 42 0 152...

Page 918: ...870 2035 2200 2360 2330 2495 2660 2855 3020 1840 1970 2135 2300 2495 2430 2590 2790 2955 3180 PRESSURE ALTITUDE ft ISA 10 C ISA 20 C ISA 30 C ISA 37 C GR D50 GR D50 GR D50 GR D50 0 2000 4000 6000 8000 1905 2070 2230 2395 2590 2530 2690 2890 3050 3280 2000 2135 2330 2530 2725 2625 2790 2985 3215 3410 2070 2230 2430 2625 2855 2690 2890 3085 3315 3570 2135 2300 2495 2690 2920 2790 2955 3185 3380 3640...

Page 919: ...ILITY TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY AND THE WEIGHT AND BALANCE LIMITS ARE ADHERED TO 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 balance for instance optional equipment installation DETERMINING WEIGHT AND BALANCE Refer to weight and balance graphs Figu...

Page 920: ...SUPPLEMENT 41 TBM 700C2 TBM 700 Page 9 41 67 Rev 5 Figure 9 41 34 WEIGHT AND BALANCE GRAPH in Kg and Litres ...

Page 921: ...TBM 700 SUPPLEMENT 41 TBM 700C2 Page 9 41 68 Rev 5 Figure 9 41 34A WEIGHT AND BALANCE GRAPH in lbs and us gal ...

Page 922: ...ASIC EMPTY WEIGHT DATE OR MODIFICATION DESCRIPTION Weight lb Arm in Moment lb in 1000 Weight W Arm do Moment According to delivery Figure 9 41 35 SAMPLE WEIGHT AND BALANCE RECORD CG m a c do 172 93 59 45 100 Use the above formula to express arm do in of mean aerodynamic chord NOTE Arm expressed in inches with regard to reference Post MOD70 148 25 Front seats 178 5 in 4 534 m 178 5 in 4 534 m Inter...

Page 923: ...00 203 74 5 175 205 79 5 227 S Partition net at frame 14 between the cabin and the baggage compartment T700B2590001 SOCATA 1 698 0 770 289 53 7 354 Seats Belts Standard equipment S Seats Pilot s seat T700C2500002 SOCATA 55 12 25 00 183 90 4 671 Front R H seat T700C2500002 SOCATA 55 12 25 00 183 90 4 671 S O L H intermediate seat back to flight direction T700C2500003 or Post MOD70 148 25 SOCATA 35 ...

Page 924: ...gear O L H Main landing gear D23767001 OPT70 0190 32 MESSIER DOWTY 53 79 24 400 200 39 5 090 O R H Main landing gear D23768001 OPT70 0190 32 MESSIER DOWTY 53 79 24 400 200 39 5 090 32 20 Nose landing gear R Nose gear D23766000 OPT70 0134 32 MESSIER DOWTY 53 57 24 300 93 70 2 380 32 40 Wheels and brakes R Main tire 18x5 5 10PR MICHELIN 13 50 6 123 204 33 5 190 R Main tire 18x5 5 10PR OPT70 0409 32 ...

Page 925: ...eed indicator 1 8140 Code B 851 OPT70 34011B UNITED INSTRUMENTS 0 75 0 340 157 48 4 000 O Airspeed indicator 2 8040 Code B 850 R H Instrument panel OPT70 34019C UNITED INSTRUMENTS 0 75 0 340 157 48 4 000 S TAS airspeed indicator 2 8140 Code B 851 R H Instrument panel OPT70 34019D UNITED INSTRUMENTS 0 75 0 340 157 48 4 000 S Authorization to operate in RVSM area OPT70 0160 34A 77 ENGINE INDICATING ...

Page 926: ...SUPPLEMENT 41 TBM 700C2 TBM 700 Page 9 41 73 Rev 5 INTENTIONALLY LEFT BLANK ...

Page 927: ...ngle is adjusted by pulling up side handle two rear seats arranged as a bench mounted on the same rails as the front seats The seat back rests tilt forward by pulling up a rear handle and each seat may tilt forwards by pulling up a side rear handle to ease baggage loading in baggage compartment For longitudinal setting pull up the handle located forward Belts and harnesses WARNING INCORRECT CLOSUR...

Page 928: ...SUPPLEMENT 41 TBM 700C2 TBM 700 Page 9 41 75 Rev 5 Figure 9 41 36 FRONT AND REAR SEAT BELTS with movable straps AND HARNESSES FRONT SEATS REAR SEATS ...

Page 929: ...l shift control 8 Front seat s height control 9 Front seat s back rest tilt control 10 Drawer for pilot s piddle pak front side new bags rear side used bags 11 Intermediate seat s back rest tilt control 12 Rear bench seat s back rest tilt control 13 Rear bench L H seat tilt control NOTE To have access to the baggage compartment pull forwards the back rest of rear bench L H seat then pull forwards ...

Page 930: ...SUPPLEMENT 41 TBM 700C2 TBM 700 Page 9 41 77 Rev 5 Figure 9 41 37 2 2 SEATS ...

Page 931: ...re given for an airplane on ground at 21 C An ambient temperature change of 3 C produces approximately 1 pressure change 8 2 UTILIZATION BY COLD WEATHER 0 C TO 25 C OR VERY COLD WEATHER 25 C TO 40 C NOTE Check pressure values in a hangar heated at about 15 C with control equipment at room temperature OAT C 40 30 20 10 15 PRESSURES psi bars Main landing gear tire 144 9 96 144 9 96 130 8 96 130 8 96...

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Page 950: ...SUPPLEMENT PROVISION FOR TBM 700C2 TABLE OF CONTENTS Page 1 GENERAL 9 43 3 2 LIMITATIONS 9 43 3 3 EMERGENCY PROCEDURES 9 43 4 4 NORMAL PROCEDURES 9 43 4 5 PERFORMANCE 9 43 4 6 WEIGHT AND BALANCE 9 43 5 7 DESCRIPTION 9 43 6 8 HANDLING SERVICING AND MAINTENANCE 9 43 7 ...

Page 951: ...TBM 700 SUPPLEMENT 43 PROVISION FOR TBM 700C2 Page 9 43 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 952: ...M 700C2 The option consists of new seats with integral belt and shoulder harnesses reinforced main wheels and tires SECTION 2 LIMITATIONS The limitations hereafter supplement those of the standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the TBM 700C1 airplane is equipped with the option PROVISION FOR TBM 700C2 2 1 PLACARDS On main gear leg MAIN LAND...

Page 953: ...700C1 Pilot s Operating Handbook SECTION 4 NORMAL PROCEDURES The installation of the option PROVISION FOR TBM 700C2 does not change the basic normal procedures of the airplane described in Section 4 Normal procedures of the TBM 700C1 Pilot s Operating Handbook SECTION 5 PERFORMANCE The installation of the option PROVISION FOR TBM 700C2 does not change the basic performance of the airplane describe...

Page 954: ...IGHT per unit lb kg ARM in m O PROVISION FOR TBM 700C2 OPT70 01029 25 EQUIPMENT FURNISHINGS Seats Belts Seats Pilot s seat IAI 55 12 25 00 183 90 4 671 Front R H seat IAI 55 12 25 00 183 90 4 671 Intermediate seat back to flight direction IAI 35 27 16 00 219 96 5 587 Double chair R H seat L H seat IAI 52 91 24 00 52 91 24 00 278 19 7 066 278 19 7 066 32 LANDING GEARS 32 40 Wheels and brakes Main t...

Page 955: ...o individual seats installed back to the flight direction mounted on the same rails as the front seats The seat back angle is adjusted by pulling up side handle two rear seats arranged as a bench mounted on the same rails as the front seats The seat back rests tilt forward by pulling up a rear handle and each seat may tilt forwards by pulling up a rear handle to ease baggage loading in baggage com...

Page 956: ...essures are given for an airplane on ground at 21 C An ambient temperature change of 3 C produces approximately 1 pressure change 8 2 UTILIZATION BY COLD WEATHER 0 C TO 25 C OR VERY COLD WEATHER 25 C TO 40 C NOTE Check pressure values in a hangar heated at about 15 C with control equipment at room temperature OAT C 40 30 20 10 15 PRESSURES psi bars Main landing gear tire 144 9 96 144 9 96 130 8 96...

Page 957: ...TBM 700 SUPPLEMENT 43 PROVISION FOR TBM 700C2 Page 9 43 8 Rev 0 INTENTIONALLY LEFT BLANK ...

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Page 960: ...ook when the TBM airplane is equipped with the option CHIP DETECTION SYSTEM Indication CHIP amber warning on On ground Before engine start 1 Do not start engine After engine start or after landing 1 Return to parking area 2 Shut down engine 3 Inspect chip detector s and engine if required In flight 1 Check and monitor engine parameters 2 Land as soon as practical 3 Shut down engine 4 Inspect chip ...

Page 961: ...ation and the operation of the CHIP DETECTION SYSTEM do not change the basic performance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section 6 Weight and balance of the basic Pilot s Operating Handbook A or O OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER WEI...

Page 962: ...s the monitoring of engine oil system The system includes one chip detector installed on propeller reduction gear box and if installed a second chip detector installed on engine accessory gear box In case of chip detection amber warning light CHIP on advisory panel or amber CAS message CHIP on G1000 system screen goes on ...

Page 963: ...TBM 700 850 SUPPLEMENT 44 CHIP DETECTION SYSTEM Page 9 44 6 Rev 1 INTENTIONALLY LEFT BLANK ...

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Page 972: ... 850 Page 9 53 1 Rev 0 SUPPLEMENT MULTI MISSION AIRCRAFT TABLE OF CONTENTS Page 1 GENERAL 9 53 3 2 LIMITATIONS 9 53 4 3 EMERGENCY PROCEDURES 9 53 6 4 NORMAL PROCEDURES 9 53 7 5 PERFORMANCE 9 53 9 6 WEIGHT AND BALANCE 9 53 11 7 DESCRIPTION 9 53 12 ...

Page 973: ...SUPPLEMENT 53 MULTI MISSION AIRCRAFT TBM 700 850 Page 9 53 2 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 974: ...The MMA consists in different versions provided in the table hereafter VERSION EQUIPMENT A THALES AGILE II sphere Console The TBM700 MMA may fly VERSION CONFIGURATION A A1 Sphere extended Cabin mission layout A2 Sphere retracted Cabin standard or mission lay out A3 Sphere removed Cabin standard or mission lay out When the airplane is flying in A2 or A3 configuration the airplane geometry maximum t...

Page 975: ...IONS VERSION SPEED KIAS KCAS A Maximum operating speed when the sphere is totally or partially extended 160 163 for TBM700 A B C N 164 for TBM850 S N 269 and from S N 434 2 3 OPERATING LIMITS CAUTION IT IS PROHIBITED TO OCCUPY THE OPERATOR CONSOLE SEAT DURING TAKEOFF AND LANDING FLIGHT INTO KNOWN ICING CONDITIONS WITH TOTALLY OR PARTIALLY EXTENDED SPHERE IS PROHIBITED TAKEOFF WITH TOTALLY OR PARTI...

Page 976: ...ON CONFIGURATION Maximum altitude A Sphere is totally or partially extended 20000 ft 6096 m 2 5 MISCELLANEOUS LIMITS Only cabin standard or mission lay out is allowed to fly 2 6 LABELS EXTENDED SPHERE IAS 160 KIAS Pressure Altitude 20 000 Ft Crosswind 15 kt Landing prohibited except in case of failure ...

Page 977: ...ting Handbook when the TBM700 airplane is equipped with the MULTI MISSION AIRCRAFT option Symptom Red warning light FIXED 1 Maintain airspeed below 160 KIAS 2 Shorten the flight 3 Maximum demonstrated crosswind for landing 15 Kts SPHERE EXTENSION RETRACTION FAILURE OR USE OF EMERGENCY STOP ELECTRICAL FAILURE BOTH GENERATOR FAILURE CONFIRMED MAIN GEN AND ST BY If sphere is not retracted RETRACT IT ...

Page 978: ...n the TBM700 airplane is equipped with the MULTI MISSION AIRCRAFT option 1 Extension retraction switch CHECK UNDER GUARD 2 Control panel lights TEST Red and blue lights ON BEFORE TAXIING 1 Airspeed below 160 KIAS 2 Extension retraction switch ACTUATED and DN 3 Red warning light FLASHING The red warning light flashes during the whole maneuver It goes off at the end of the maneuver Duration around 1...

Page 979: ...witch UP 3 Blue indicator light OFF 4 Red warning light FLASHING The red warning light flashes during the whole maneuver It goes off at the end of the maneuver Duration around 1 min 30 sec 5 Extension retraction switch CHECK UNDER GUARD RETRACT THE SPHERE 1 Extension retraction switch CHECK UNDER GUARD BEFORE LANDING ...

Page 980: ... of the standard airplane described in Section 5 Performance of the basic Pilot s Operating Handbook when the TBM700 airplane is equipped with the MULTI MISSION AIRCRAFT option 5 1 LONG RANGE CRUISE When the sphere is extended at iso torque the airspeed is decreased by 4 KIAS at iso airspeed the fuel flow is increased by 2 US Gal h ...

Page 981: ...53 MULTI MISSION AIRCRAFT TBM 700 850 Page 9 53 10 Rev 0 5 2 WIND COMPONENTS EXAMPLE Angle between wind direction and flight path 50 Headwind 8 kts Crosswind 10 kts Wind speed 13 kts Figure 9 53 1 WIND COMPONENTS ...

Page 982: ... in Section 6 Weight and Balance of the basic Pilot s Operating Handbook when the TBM700 airplane is equipped with the MULTI MISSION AIRCRAFT option GENERAL IT IS THE PILOT S RESPONSIBILITY TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY AND THE WEIGHT AND BALANCE LIMITS ARE ADHERED TO VERSION EQUIPMENT WEIGHT lb kg ARM lb kg A Console 48 5 22 236 2 6 15 A Sphere 46 3 21 354 3 9 4 ...

Page 983: ... airplane is equipped with the MULTI MISSION AIRCRAFT option The main components of the Multi mission aircraft are 1 One extension retraction control panel pilot control only 2 One console in order to operate the sphere when extended 3 One external sphere located between the two lateral keels NOTE The airplane can be flown with the sphere removed Figure 9 53 2 MMA COMPONENTS VERSION DESCRIPTION A ...

Page 984: ...ygen Either L H intermediate seat Item 1 or L H rear seat Item 2 can be removed if necessary Aircraft equipped with chemical oxygen Either L H intermediate seat Item 1 or L H rear seat Item 2 can be removed if necessary provided that access to oxygen masks is possible for every passenger aboard during all flight phases ...

Page 985: ...SUPPLEMENT 53 MULTI MISSION AIRCRAFT TBM 700 850 Page 9 53 14 Rev 0 Figure 9 53 3 CABIN LAYOUTS ...

Page 986: ...trol 3 Blue indicator light light is ON if the sphere is extended 4 Red warning light flashes during sphere maneuver is ON if a failure is detected 5 Test when pushed lights on blue red lights Figure 9 53 4 CONTROL PANEL 7 3 BREAKERS MMA EXT RET breaker protects the EO IR extension retraction system MMA CONSOLE breaker protects the console functioning These two breakers are located on the PL 1 bre...

Page 987: ...SUPPLEMENT 53 MULTI MISSION AIRCRAFT TBM 700 850 Page 9 53 16 Rev 0 INTENTIONALLY LEFT BLANK ...

Page 988: ... 0 Page 9 60 1 SUPPLEMENT ADS B OUT FUNCTION TABLE OF CONTENTS Page 1 GENERAL 9 60 2 2 LIMITATIONS 9 60 2 3 EMERGENCY PROCEDURES 9 60 2 4 NORMAL PROCEDURES 9 60 3 5 PERFORMANCE 9 60 3 6 WEIGHT AND BALANCE 9 60 3 7 DESCRIPTION 9 60 4 8 HANDLING SERVICING AND MAINTENANCE 9 60 4 ...

Page 989: ...he extended squitter functionality The installed ADS B OUT system has been shown to meet the equipment requirements of 14 CFR 91 227 1 4 ABBREVIATIONS AND TERMINOLOGY RADIO NAVIGATION ABBREVIATIONS ADS B Automatic Dependent Surveillance Broadcast SECTION 2 LIMITATIONS Operation of ADS B OUT function does not change the limitations of the airplane described in Section 2 Limitations of the basic Pil...

Page 990: ... airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement or replace those of the standard airplane described in Section 6 Weight and Balance of the basic Pilot s Operating Handbook when the airplane is equipped with the ADS B OUT function S R A O ITEM OPT70 or MOD70 REQUIRED R OR STANDARD S OR OPTIONAL A or O...

Page 991: ...d input to the transponder 1 may cause the transponder to stop transmitting ADS B OUT data Depending on the nature of the fault or failure the transponder may no longer be transmitting all of the required data in the ADS B OUT messages If the transponder 1 detects any internal fault or failure with the ADS B OUT functionality the following advisory message NO ADSB will be displayed on the transpon...

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Daher TBM 700, Pilot'S Manual

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