Daher TBM 960 Quick setup guide

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DAHER AEROSPACE
Customer Care
65921 TARBES CEDEX 9
FRANCE Printed in FRANCE
TBM 960
Pilot's Information Manual
P/N DMMPIPYEE0EN - Edition 0 - Revision 2
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 list of effective pages in this manual corresponds to that of the basic
Pilot's Operating Handbook.
PIM - DO NOT USE FOR FLIGHT OPERATIONS

List of Effective Pages and Validities
Original issue: January 27, 2022
Airplanes equipped with MOD70-0621-76
P/N DMMFM00EE0ENR02
Page No. Rev. No. Rev. Date
1.0.1 to 1.0.1 02 APR 2022
1.1.1 to 1.1.1 00 JAN 2022
1.2.1 to 1.2.2 00 JAN 2022
1.3.1 to 1.3.4 00 JAN 2022
1.4.1 to 1.4.9 00 JAN 2022
1.5.1 to 1.5.4 00 JAN 2022
1.6.1 to 1.6.2 00 JAN 2022
2.0.1 to 2.0.2 02 APR 2022
2.1.1 to 2.1.1 00 JAN 2022
2.2.1 to 2.2.1 00 JAN 2022
2.3.1 to 2.3.4 00 JAN 2022
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2.5.1 to 2.5.4 00 JAN 2022
2.6.1 to 2.6.16 00 JAN 2022
2.7.1 to 2.7.2 01 MAR 2022
2.8.1 to 2.8.5 00 JAN 2022
2.9.1 to 2.9.11 01 MAR 2022
3.A.1 to 3.A.3 02 APR 2022
3.0.1 to 3.0.3 02 APR 2022
3.1.1 to 3.1.4 00 JAN 2022
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0.1 to 0.102
0.3 to 0.600 JAN 2022
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0.8 to 0.8 01 MAR 2022
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3A.0.1 to 3A.0.3 02 APR 2022
3A.1.1 to 3A.1.1 00 JAN 2022
3A.2.1 to 3A.2.1 00 JAN 2022
3A.3.1 to 3A.3.9 00 JAN 2022
3A.4.1 to 3A.2.1 00 JAN 2022
3A.5.1 to 3A.2.1 00 JAN 2022
3A.6.1 to 3A.2.1 00 JAN 2022
3A.7.1 to 3A.7.15 01 MAR 2022
3A.8.1 to 3A.8.5 00 JAN 2022
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3A.10.1 to 3A.10.5 00 JAN 2022
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3A.12.1 to 3A.12.22 00 JAN 2022
3A.13.1 to 3A.13.4 00 JAN 2022
4.0.1 to 4.0.3 02 APR 2022
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4.2.1 to 4.2.1 00 JAN 2022
4.3.1 to 4.3.23 01 MAR 2022
4.4.1 to 4.4.65 01 MAR 2022
4.5.1 to 4.5.29 01 MAR 2022
5.0.1 to 5.0.2 02 APR 2022
5.1.1 to 5.1.1 01 MAR 2022
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5.4.1 to 5.4.1 01 MAR 2022
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5.6.1 to 5.6.1 00 JAN 2022
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Rev. 02
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Page No. Rev. No. Rev. Date
5.7.1 to 5.7.1 00 JAN 2022
5.8.1 to 5.8.52 01 MAR 2022
5.9.1 to 5.9.10 01 MAR 2022
5.10.1 to 5.10.12 01 MAR 2022
5.11.1 to 5.11.62 01 MAR 2022
5.12.1 to 5.12.1 00 JAN 2022
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5.14.1 to 5.14.4 01 MAR 2022
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Page No. Rev. No. Rev. Date
8.9.1 to 8.9.15 01 MAR 2022
8.10.1 to 8.10.2 00 JAN 2022
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Rev. 02
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Table of Contents
Section
General 1
Limitations 2
Emergency Procedures 3
Abnormal Procedures 3A
Normal Procedures 4
Performance 5
Weight and Balance 6
Description 7
Handling, Servicing and Maintenance 8
Section 0
Pilot's Information Manual
PIM TBM 960 - Edition 0
Rev. 02
PIM - DO NOT USE FOR FLIGHT OPERATIONS

Section 1
General
Table of Contents
1.1 -General ...................................................................................... 1.1.1
Part 135 Operations ............................................................. 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 ....................................................................................... 1.3.1
Engine Oil ............................................................................. 1.3.2
Maximum Certificated Weights ............................................. 1.3.3
Standard Airplane Weights ................................................... 1.3.3
Cabin and Entry Dimensions ................................................ 1.3.3
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 ............................................................... 1.4.2
Airplane Performance and Flight Planning Terminology ....... 1.4.2
Weight and Balance Terminology ......................................... 1.4.3
General Abbreviations .......................................................... 1.4.3
Radio Navigation Abbreviations ........................................... 1.4.8
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
Section 1
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Rev. 02
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1.1 - General
This POH contains nine sections and includes the material required by FAR Part
23 to be furnished to the pilot for operation of the TBM airplane. It also contains
supplemental data supplied by the manufacturer, in accordance with GAMA
(General Aviation Manufacturers Association) standards.
Section 1 provides basic data and information of general interest. It also contains
definitions or explanations of commonly used abbreviations and terminology.
Whenever this POH refers to the Garmin Integrated Flight Deck Pilot's Guide, it
denotes the guide described in Subsection 2.1. General.
Whenever this POH refers to the MD302 Pilot's Guide, it denotes the guide
described in Subsection 2.1. General.
The general information for complex optional systems are given in Section 9:
Supplements.
The installed ADS-B OUT system has been shown to meet the equipment
requirements of 14 CFR 91.227.
The installed transponder system is able to respond to interrogations in Modes A,
C and S and is fully compliant with the requirements of CS ACNS.D.ELS/EHS
(Mode S Elementary/Enhanced Surveillance).
The installed ADS-B OUT system is fully compliant with the requirements of CS
ACNS.D.ADSB (1090 MHz Extended Squitter ADS-B OUT).
Part 135 Operations
For 14 CFR 135 operations, the TBM airplane's alternative source of electric
power is capable of supplying 150 percent of the electrical loads of all required
instruments and equipment for safe emergency operation of the airplane for at
least one hour.
The electrical load shedding procedure provided in Section 3 of this POH must be
followed to meet requirements of paragraph 14 CFR 135.163(f)(2).
Section 1
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1.2 - Three View Drawing
Figure 1.2.1 - Three View Drawing (1/2)
8.15 in
9.56 ft
(*)
(*)
12.71 ft
mini 0.207 m
2.914 m
3.874 m
4.355 m
14.29 ft
I4061000AAAHMA8000
10.736 m
35.22 ft
(*) Airplane on a level surface with fully extended FWD shock absorber
Section 1
General
Pilot's Information Manual
PIM TBM 960 - Edition 0
Rev. 00
Page 1.2.1
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Figure 1.2.2 - Three View Drawing (2/2)
I4061000AAAIMA8000
16.36 ft
4.988 m
12.833 m
42.1 ft
Section 1
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Rev. 00
Page 1.2.2
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1.3 - Descriptive Data
Engine
Number of engines: 1
Engine manufacturer: Pratt & Whitney Canada
Engine model number: PT6E-66XT
Engine type: Free turbine, reverse flow and two turbine sections
-Compressor type: four axial stages, one centrifugal stage
-Combustion chamber type: annular
-Turbine type: one gas generator turbine stage, two power turbine stages
Horsepower rating and propeller speed: 895 SHP (667 kW) at 1,925 RPM
The engine is electronically controlled by a Full Authority Digital Engine Control
(FADEC) system.
Propeller
Number of propellers: 1
Propeller manufacturer: Hartzell
Propeller model number: 5D31-NK366B1 / 86DB01B
Number of blades: 5
Propeller diameter: 91 in (2.311 m)
Propeller type: Adjustable constant speed, with feathering and hydraulic control
reverse
Propeller blade setting at 30-inch station:
- Low pitch: 19.5°
- Feathering: 86.1°
- Maximum reverse: - 9.3°
The electro-hydro-mechanical Propeller Control Unit (PCU) modulates the blade
angle.
Fuel
Total capacity: 301 USG (1,140 liters)
Total capacity, each tank: 150.5 USG (570 liters)
Section 1
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Rev. 00
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Total usable: 292 USG (1,106 liters)
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 between a minimum of 0.06% and a maximum of 0.15% by
volume. Refer to Paragraph Fuel in Subsection 8.7. for additional information.
Table 1.3.1 - Recommended Fuel Types [Reference: P&WC Engine Maintenance
Manual, latest revision]
US Specification
(US)
French Specification
(FR)
English Specification
(UK) NATO Code
ASTM-D1655 JET A
ASTM-D1655 JET A1 AIR 3405C Grade F35 DERD 2494 Issue 9 F35**
MIL-DTL-5624 Grade
JP-5 AIR 3404C Grade F44 DERD 2452 Issue 2 Amendment 1 F44*
MIL-DTL-83133 Grade
JP-8 AIR 3405C Grade F34 DERD 2453 Issue 4 Amendment 1 F34*
AIR 3404C Grade F43 DERD 2498 Issue 7 F43**
* Already contains an anti-ice additive.
** Requires an anti-ice additive.
Engine Oil
System total capacity: 12.7 qt (12 liters) (oil cooler included)
Usable capacity: 6 qt (5.7 liters)
Maximum oil consumption in a 10-hour period: 0.14 qt/h (0.13 l/h) [0.3 lb/h (136
cc/h)]
Specification
Section 1
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Rev. 00
Page 1.3.2
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Table 1.3.2 - Recommended Engine Oil Types [Reference: P&WC Engine
Maintenance Manual, latest revision]
Nominal viscosity Specification NATO code
5cSt MIL-PRF-23699 O-156 (STD)
O-154 (HTS)
Maximum Certificated Weights
Maximum airplane weight:
Maximum Ramp Weight (MRW) 7,430 lbs to 7,650 lbs *
(3,370 kg to 3,470 kg) *
Maximum Takeoff Weight (MTOW) 7,394 lbs to 7,615 lbs *
(3,354 kg to 3,454 kg) *
Maximum Landing Weight (MLW) 7,110 lbs
(3,225 kg)
* Depending on the C.G. position – see Figure 2.5.2
Baggage weight:
- For weight and C.G. limits, refer to Paragraph Weight Limits in Subsection
2.5.
- For cargo loading instructions, refer to Subsection 6.3. Baggage Loading
Standard Airplane Weights
Standard empty weight: 4,784 lbs (2,170 kg)
Maximum useful load: 2,831 lbs (1,284 kg)
Cabin and Entry Dimensions
Maximum cabin width: 3.97 ft (1.21 m)
Maximum cabin length: 13.29 ft (4.05 m)
Maximum cabin height: 4 ft (1.22 m)
Number of cabin entries: 1 (standard) + 1 pilot door (if installed)
Entry width (standard): 3.54 ft (1.08 m)
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Entry height (standard): 3.9 ft (1.19 m)
Pilot entry mean width: 2.3 ft (0.70 m)
Pilot entry mean height: 3.18 ft (0.97 m)
Specific Loadings
Wing loading: 39.3 lbs/ft2 (191.9 kg/m2)
Power loading: 8.5 lbs/SHP (3.86 kg/SHP)
Section 1
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Rev. 00
Page 1.3.4
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1.4 - Abbreviations and Terminology
Meteorological Terminology
ISA International Standard Atmosphere
IMC Instrument Meteorological Conditions
VMC Visual Meteorological Conditions
OATOutside Air Temperature
SAT Static Air Temperature
QFE Atmospheric pressure at the airport reference point.
QNH Atmospheric pressure at sea level, at airplane position.
Standard
temperature
15 °C (59 °F) at sea level pressure altitude, decreasing by 2 °C
(3.6 °F) for each 1,000 ft of altitude.
Pressure
altitude
The altitude read from an altimeter when the altimeter's
barometric scale has been set to 29.92 inches of mercury
(1,013.2 hPa).
General Airspeed Terminology and Symbols
KCAS Knots Calibrated Airspeed: 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: the speed shown on the airspeed
indicator and expressed in knots.
KTAS Knots True Airspeed: the airspeed expressed in knots relative
to undisturbed air which is KCAS corrected for altitude and
temperature.
VAManeuvering Speed: the maximum speed at which full or
abrupt control movements may be used.
VFE Maximum Flap Extended Speed: the highest speed
permissible with wing flaps in a prescribed extended position.
VLE Maximum Landing Gear Extended Speed: the maximum
speed at which an airplane can be safely flown with the landing
gear extended.
VLO Maximum Landing Gear Operating Speed: the maximum
speed at which the landing gear can be safely extended or
retracted.
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VMO Maximum Operating Speed: the speed limit that may not be
deliberately exceeded in normal flight operations.
VRRotation Speed: the speed at which rotation is initiated during
takeoff to achieve takeoff safety speed at screen height.
VS0 Stalling Speed: the minimum steady flight speed at which the
airplane is controllable in the landing configuration.
VS1 Stalling Speed: the minimum steady flight speed obtained in a
specific configuration.
VXBest Angle of Climb Speed: the airspeed which delivers the
greatest gain of altitude in the shortest possible horizontal
distance.
VYBest Rate of Climb Speed: the airspeed which delivers the
greatest gain in altitude in the shortest possible time.
Power Terminology
Recovery
altitude
Maximum altitude at which it is possible, in standard
temperature conditions, to maintain a specified power.
Hot start Engine start or attempt to start that causes the interturbine
temperature to be higher than the maximum value permissible
during start.
Flameout Involuntary loss of the combustion chamber flame during
operation.
GPU Ground Power Unit
Feathering Action which reduces the drag of a propeller by positioning
blades at the pitch angle creating minimal drag.
Maximum
Cruise Power
Power developed in relation to outside flight level and
temperature conditions.
Ng Gas generator RPM
Np Propeller rotation speed
Reverse Drag produced when the propeller blade setting is negative.
RPM Revolutions Per Minute
SHP Shaft Horsepower
TRQ Torque
Airplane Performance and Flight Planning Terminology
Climb gradient The ratio of the change in height during a portion of climb to the
horizontal distance traversed during the same time interval.
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Rev. 00
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Demonstrated
crosswind
velocity
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.
gThe force of gravity or acceleration.
Usable fuel Total fuel that can be effectively consumed by the engine.
D50 Takeoff or landing distance over a 50-foot (15-meter) obstacle
Weight and Balance Terminology
Reference
datum
Datum perpendicular to the longitudinal airplane centerline from
which all distances are measured for weight and balance
purposes.
Arm The distance from the reference datum to the center of gravity
(C.G.) of an item.
Moment The product of the weight of an item multiplied by its arm.
Center of
gravity
Airplane balance point. Its distance from the reference datum is
found by dividing the total moment by the total weight of the
airplane.
C.G. limits The extreme center of gravity locations within which the airplane
must be operated at a given weight.
Standard
empty weight
Weight of a standard airplane, including unusable fuel and full
operating fluids (oil and hydraulic fluids).
Basic empty
weight
Standard empty weight plus optional equipment.
Useful load The difference between maximum ramp weight and the basic
empty weight.
Maximum
Ramp Weight
The maximum weight approved for ground maneuver. It includes
the weight of start, taxi and run up fuel.
Maximum
Takeoff Weight
The maximum weight approved at the beginning of the takeoff
run.
Maximum
Landing
Weight
The maximum weight approved for landing touchdown.
General Abbreviations
AAmpere
A/C Air Conditioning
ADC Air Data Computer
Section 1
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AGL Above Ground Level
AIL TRIM Aileron TRIM
ALTI Altimeter
ALT SEL Altitude Selection
AMP Ampere
AMPS Amperes
AoA Angle of Attack
AT Autothrottle
ATIS Automatic Terminal Information Service
AUTO SEL Auto Selector
AUX BP Auxiliary Boost Pump
BAT Battery
BRT Brightness
°C Degrees Celsius
CAS Crew Alerting System
CAS Calibrated Airspeed
cc/h Cubic Centimeter per Hour
C.G. Center of Gravity
CONT Control
cu.ft Cubic Feet
DCTU Data Collection and Transmission Unit
DIEGME Diethylene Glycol Monomethyl Ether
DISC Disconnect
DN Down
ECS Environmental Control System
EDM Emergency Descent Mode
EGME Ethylene Glycol Monomethyl Ether
EIS Engine Indication System
EMER Emergency
ESP Electronic Stability Protection
ESS BUS TIE Essential Bus Tie
EXT LIGHTS External Lights
°F Degrees Fahrenheit
FADEC Full Authority Digital Engine Control
Section 1
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