Daher TBM 700 Manual

October 31, 2014 --- Rev. 8 Printed in FRANCEP/N : T00.DMCPIPYE
TBM 700
Version C
PILOT’S
INFORMATION MANUAL
CAUTION
THIS INFORMATION MANUAL IS A NON---OFFICIAL COPY OF THE PILOT’S
OPERATING HANDBOOK AND MAY BE USED FOR GENERAL INFORMATION
PURPOSES ONLY.
IT IS NOT KEPT CURRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE
FOR AIRWORTHINESS AUTHORITIES APPROVED MANUAL WHICH IS THE ONLY ONE
INTENDED FOR OPERATION OF THE AIRPLANE.
The content of this document is the property of SOCATA 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 this document is subject to change without notice.
2002 thru 2012, 2014 --- SOCATA SAS --- All rights reserved
For any information concerning this document, please contact :
SOCATA SAS
CUSTOMER SUPPORT TELEPHONE : [phone]
65921 TARBES CEDEX 9 TELEFAX : 33 (0)5 62.41.76.54
FRANCE

TBM
PILOT’S OPERATING HANDBOOK 700
SECTION 0
Page 0.5A Rev. 7
SOCATA MODIFICATIONS -- INDEX
NOTE :
The standardized name for SOCATA modifications is :
MOD70--XXX--XX
MOD70 No. SUBJECT CLASSIF.
021--32 New A14 landing gear control panel Major
124--71 Engine drains minor
138--53 ELT housing minor
139--00 TBM 700 takeoff max. weight increase Major
140--00 Evolutions from TBM 700B to TBM 700C1 :
MTOW 6579 lbs (2984 kg)
Major
142--21 Air 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 --
TBM700C equipped with MOD70--143--21
minor
0156--32 AIR SYSTEMS control panel and landing
gear indicating P/N A14 LGCP 94--11
Amdt D
minor
0157--21 Evaporator air inlet protection --
TBM700C not equipped with
MOD70--155--21
minor

SECTION 0
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700 PILOT’S OPERATING HANDBOOK
Page 0.5B
Rev. 7
CLASSIF.SUBJECTMOD70 No.
0161--27 Aileron control emergency stop minor
0162--21 Air cycle system (ACS) -- TBM700C
equipped with MOD70--142--21
minor
0163--77 Torque transducer static port tube minor
0166--53 Change of glass fiber fabric type on TBM
700 composite floors
minor
0168--57 Modification of TBM 700 internal flap
carriage pin definition (external flap
carriages are processed by amendment)
minor
0170--23 Separation of audio circuit low points (GMA
340) -- TBM 700 equipped 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 700C S/N 205, 240, 245 to 268, 270 to
286, 288
minor
0186--57 Inserts hot--fitted on flap ribs minor
0190--32 Reinforcement of main landing gear legs Major
0191--71 Engine drainage breather pipe modification
-- TBM 700A, B, C equipped with
MOD70--124--71 (engine drainage) and TBM
700N (850)
minor
0194--25 Linings Generation 2005--3 minor

TBM
PILOT’S OPERATING HANDBOOK 700
SECTION 0
Page 0.5C Rev. 8
CLASSIF.SUBJECTMOD70 No.
0195--56 Rear cabin window (same as front cabine
window)
minor
0201--32 Landing 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

SECTION 0
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700 PILOT’S OPERATING HANDBOOK
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TBM
PILOT’S OPERATING HANDBOOK 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

SECTION 1
GENERAL
TBM
700 PILOT’S OPERATING HANDBOOK
Page 1.0.1
Rev. 0
SECTION 1
GENERAL
TABLE OF CONTENTS
Page
1.1 GENERAL 1.1.1
..................................................
1.2 THREE VIEW DRAWING 1.2.1...................................
1.3 DESCRIPTIVE DATA 1.3.1.......................................
ENGINE 1.3.1.......................................................
PROPELLER 1.3.1..................................................
FUEL 1.3.2.........................................................
ENGINE OIL 1.3.3...................................................
MAXIMUM CERTIFICATED WEIGHTS 1.3.3............................
STANDARD AIRPLANE WEIGHTS 1.3.3...............................
CABIN 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 FACTORS 1.5.1.................................
1.6 PRESSURE AND STANDARD ATMOSPHERE 1.6.1...........
STANDARD ATMOSPHERE 1.6.1.....................................
PRESSURE CONVERSION TABLE 1.6.2...............................

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GENERAL
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SECTION 1
GENERAL
TBM
700 PILOT’S OPERATING HANDBOOK
Page 1.1.1
Rev. 0
1.1 -- GENERAL
This Handbook contains 9 Sections, and includes the material required by
FAR Part 23 to be furnished to the pilot for operation of the TBM 700 airplane.
It also contains supplemental data supplied by the manufacturer.
Section 1 provides basic data and information of general interest. It also
contains definitions or explanations of abbreviations and terminology
commonly used.
The general for complex optional systems are given in Section 9,
”Supplements” of the Pilot’s Operating Handbook.

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PILOT’S OPERATING HANDBOOK 700
SECTION 1
GENERAL
Page 1.1.2 Rev. 0
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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

TBM
PILOT’S OPERATING HANDBOOK 700
SECTION 1
GENERAL
Page 1.2.2 Rev. 7
Figure 1.2.1 (2/2) -- THREE VIEW DRAWING

SECTION 1
GENERAL
TBM
700 PILOT’S OPERATING HANDBOOK
Page 1.3.1
Rev. 5
1.3 -- DESCRIPTIVE DATA
ENGINE
Number of engines : 1
Engine manufacturer : PRATT & WHITNEY CANADA
Engine model number : PT6A -- 64
Engine type : Free turbine, reverse flow and 2 turbine sections
Compressor type : 4 axial stages
1 centrifugal stage
Combustion chamber type : Annular
Turbine type : 1 gas generator turbine stage
2 power turbines stages
Horsepower rating and propeller speed : 700 SHP at 2000 RPM
PROPELLER
Number of propellers : 1
Propeller manufacturer : HARTZELL
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 reverse
Propeller blade setting at 30 inches station
Low pitch : 21°
Feathering : 86°
Maximum reverse : - 11°
Propeller governor : 8210.007 WOODWARD

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PILOT’S OPERATING HANDBOOK 700
SECTION 1
GENERAL
Page 1.3.2 Rev. 5
FUEL
Total capacity : 290.6 us gal (1100 Litres)
Total capacity each tank : 145.3 us gal (550 Litres)
Total usable : 281.6 us gal (1066 Litres)
CAUTION
THE USED FUEL MUST CONTAIN AN ANTI--ICE ADDITIVE, IN
ACCORDANCE WITH SPECIFICATION MIL--I--27686 or MIL--I--85470.
ADDITIVE CONCENTRATIONS (EGME or DIEGME) SHALL BE
COMPRISED BETWEEN A MINIMUM OF 0.06 % AND A MAXIMUM OF
0.15 % BY VOLUME. REFER TO SECTION 8 ”HANDLING, SERVICING
AND MAINTENANCE” FOR ADDITIONAL INFORMATION.
CAUTION
THE USE OF AVIATION GASOLINE (AVGAS) MUST BE RESTRICTED
TO EMERGENCY PURPOSES ONLY. AVGAS SHALL NOT BE USED
FOR MORE THAN 150 CUMULATIVE HOURS DURING ANY PERIOD
BETWEEN ENGINE OVERHAUL PERIODS
NOTE :
Use of AVGAS to be recorded in engine module logbook
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 DERD 2454 Issue 4 Amdt 1
F40 with
additive
MIL--DTL--5624
Grade JP--5 AIR 3404C Grade F44 DERD 2452 Issue 2 Amdt 1
F44 with
additive when
utilization
MIL--DTL--83133
Grade JP--8 AIR 3405C Grade F34 DERD 2453 Issue 4 Amdt 1
F34 with
additive S748
AIR 3404C Grade F43 DERD 2498 Issue 7 F43 without
additive
Figure 1.3.1 -- RECOMMENDED FUEL TYPES
(Reference : Service Bulletin P & W C. No. 14004)

SECTION 1
GENERAL
TBM
700 PILOT’S OPERATING HANDBOOK
Page 1.3.3
Rev. 7
ENGINE OIL
System total capacity :
12.7 Quarts (12 Litres) (oil cooler included)
Usable capacity :
6 Quarts (5.7 Litres)
Maximum consumption : 0.14 qt / hr (0.13 l / hr)
[0.3 lb/hr (0.136 kg/h)]
CAUTION
DO NOT MIX DIFFERENT BRANDS OR TYPES
Nominal
Viscosity
US Specification
(US)
French
Specification
(FR)
English
Specification
(UK)
NATO
Code
Type 5cSt MIL--L--23699C
Amdt1
MIL--L--23699C
Amdt1
DERD 2499
Issue 1 O.156
Figure 1.3.2 -- RECOMMENDED ENGINE OIL TYPES
(Reference : Service Bulletin P & W C. No. 14001)
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 kg)
In aft compartment : 77 lbs (35 kg)
STANDARD AIRPLANE WEIGHTS
Standard empty weight : 4167 lbs (1890 kg)
With ”pilot” door : 4211 lbs (1910 kg)
Maximum useful load : 2447 lbs (1110 kg)
With ”pilot” door : 2403 lbs (1090 kg)

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PILOT’S OPERATING HANDBOOK 700
SECTION 1
GENERAL
Page 1.3.4 Rev. 5
CABIN AND ENTRY DIMENSIONS
Maximum cabin width : 3’ 11.64” (1.21 m)
Maximum cabin length : 13’ 3.45” (4.05 m)
Maximum cabin height : 4’ (1.22 m)
Number of cabin entries : 1 (standard) + 1 ”pilot” door (if installed)
Entry width (standard) : 3’ 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)

SECTION 1
GENERAL
TBM
700 PILOT’S OPERATING HANDBOOK
Page 1.4.1
Rev. 0
1.4 -- ABBREVIATIONS AND TERMINOLOGY
METEOROLOGICAL TERMINOLOGY
ISA : International standard atmosphere
OAT : Outside air temperature is the free air static temperature. It
is expressed in either degrees Celsius or degrees
Fahrenheit.
SAT : Static air temperature
IOAT : Indicated outside air temperature
QFE : Atmospheric pressure at the airport reference point.
QNH : QFE value corrected according to the airport altitude.
NOTE :
On the ground, the altimeter will indicate ”zero” if it is set to QFE ; it will
indicate airport 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
expressed in knots corrected for position and instrument
error. Knots calibrated airspeed is equal to KTAS in standard
atmosphere at sea level.
KIAS : Knots Indicated Airspeed is the speed shown on the
airspeed indicator and expressed in knots.
KTAS : Knots True Airspeed is the airspeed expressed in knots
relative to undisturbed air which is KCAS corrected for
altitude and temperature.

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PILOT’S OPERATING HANDBOOK 700
SECTION 1
GENERAL
Page 1.4.2 Rev. 0
VA:Maneuvering Speed is the maximum speed at which full or
abrupt control movements may be used.
VFE :Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended position.
VLE :Maximum Landing Gear Extended Speed is the maximum
speed at which an airplane can be safely flown with the
landing gear extended.
VLO :Maximum Landing Gear Operating Speed is the maximum
speed at which the landing gear can be safely extended or
retracted.
VMO :Maximum Operating Speed is the speed limit that may not
be deliberately exceeded in normal flight operations.
VR:Rotation Speed is the speed at which rotation is 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 the minimum steady flight speed
obtained in a specific configuration.
Vx:Best Angle of Climb Speed is the airspeed which delivers
the greatest gain of altitude in the shortest possible horizontal
distance.
VY:Best Rate of Climb Speed is the airspeed which delivers the
greatest gain in altitude in the shortest possible time.

SECTION 1
GENERAL
TBM
700 PILOT’S OPERATING HANDBOOK
Page 1.4.3
Rev. 7
POWER TERMINOLOGY
Recovery altitude :
Maximum altitude at which it is possible, in standard
temperature, to maintain a specified power.
Overheated start :
Engine start or attempt to start which causes the interturbine
temperature to be higher than the maximum value
permissible during start .
Flame out : Involuntary 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 : Drag produced when the propeller blade setting is negative.
RPM : Revolutions per minute is engine speed.
SHP : Standard Horsepower is the power developed by the engine.
TRQ : Torque.

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PILOT’S OPERATING HANDBOOK 700
SECTION 1
GENERAL
Page 1.4.4 Rev. 0
AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY
Climb gradient :
Is the ratio of the change in height during a portion of climb, to
the horizontal distance traversed in the same time interval.
Demonstrated crosswind velocity :
Is the velocity of the crosswind component for which
adequate control of the airplane during takeoff and landing
was actually demonstrated during certification tests. The
value shown is not considered to be limiting.
g:Is acceleration due to gravity.
Usable fuel : Total fuel which can be effectively consumed by the engine.
WEIGHT AND 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
gravity (C.G.) of an item.
Moment : Is the product of the weight of an item multiplied by its arm.
Center of gravity (C.G.) :
Airplane balance point. Its distance from the reference datum
is found by dividing the total moment by the total weight of the
airplane.