Aircraft DGAC-DMF8008B

August 2009

Specification
Falcon 2000LX
 DASSAULT
FALCON

Falcon 2000LX

Aircraft
Specification
© Copyright Dassault Aviation, August 2009

DGAC-DMF8008B August 2009
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Note:
Dassault Aviation reserves the right to substitute equipment in lieu of that
specified herein, whenever such substitution is deemed necessary to pre-
vent delay in delivery, improve the product, or meet the requirements of the
appropriate airworthiness authorities.
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Contents

Topic Page

Aircraft Description
General.................................................................................................................................................... 5
Certification............................................................................................................................................. 5
Layout..................................................................................................................................................... 5
Structure................................................................................................................................................. 5
Three-view Drawing................................................................................................................................ 6
Dimensions............................................................................................................................................. 7
• Airframe..................................................................................................................................... 7
• Cabin......................................................................................................................................... 7
• Landing Gear............................................................................................................................. 7
Limitations............................................................................................................................................... 8
• Weights...................................................................................................................................... 8
• CG Location.............................................................................................................................. 8
• Fuel Quantity............................................................................................................................. 8
• Speeds...................................................................................................................................... 8
• Altitudes and Temperatures...................................................................................................... 8
Guaranteed Performance....................................................................................................................... 9
• Takeoff Distance........................................................................................................................ 9
• Range........................................................................................................................................ 9
• Cruise Speed............................................................................................................................. 9
• Approach Speed....................................................................................................................... 9
• Landing Distance...................................................................................................................... 9
• Assumptions.............................................................................................................................. 9

Passenger Cabin
Interior layout.......................................................................................................................................... 10
General Description................................................................................................................................ 11
• Flight deck - Entryway - Galley................................................................................................ 11
• Forward Cabin........................................................................................................................... 11
• Aft Cabin.................................................................................................................................... 11
• Aft Lavatory............................................................................................................................... 11
• Baggage Compartment............................................................................................................ 11
• Interior Finishing........................................................................................................................ 11

Systems
Engines................................................................................................................................................... 12
Thrust Reverser....................................................................................................................................... 12
Fuel System............................................................................................................................................ 12
Hydraulic System.................................................................................................................................... 12
Flight Controls......................................................................................................................................... 12
Landing Gear.......................................................................................................................................... 13
Electrical System.................................................................................................................................... 13
Pneumatic System.................................................................................................................................. 13
Auxiliary Power Unit................................................................................................................................ 13
Ice and Rain Protection.......................................................................................................................... 14
Fire Protection System........................................................................................................................... 14
Oxygen System...................................................................................................................................... 14
Avionics................................................................................................................................................... 15
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Aircraft description

GENERAL LAYOUT
The Falcon 2000LX is a high-performance, widebody The Falcon 2000LX is built from metal alloys and com-
business jet designed and produced by Dassault posite materials. It relies on a double-swept, Mach-
Aviation of France. The aircraft is powered by two Pratt optimized profile wing similar to that of the Falcon 900
& Whitney PW308C turbofan engines. The standard series. Its tail assembly features a movable tailplane at
configuration is designed for 8 passengers. Its Type III the lower third of the fin. The aircraft’s avionics cabinets
emergency exit qualifies it to hold up to 19 passen- are located in the nose cone and under the floor in the
gers. front cabin. The radio cabinets are located in the nose
cone and in the left-hand side flight deck closet. The
main entry door is electrically controlled and operated,
CERTIFICATION is located on the left-hand side of the aircraft behind
the flight deck. An emergency exit is located farther aft
The Falcon 2000LX is certified to Transport Category in the cabin on the right-hand side. A stand-up lavatory
Aircraft Standards by both the European Aviation and a large baggage compartment with in-flight acces-
Safety Agency (EASA) and by the United States sibility are located in the aft cabin.
Federal Aviation Administration (FAA).
The aircraft’s engines are mounted at the rear of the
The Falcon 2000LX meets EASA CS-25 and FAR 25 fuselage with standard target-type thrust reversers.
Amendment 94 Transport Category Aircraft require- Fuel is contained in structural tanks in both wings, in
ments. day/night IFR (Cat I and II), and flight into the center wing section, and in forward and aft fuse-
known icing conditions. lage tanks.
The Falcon 2000LX meets FAR 36 Stage IV and ICAO
Annex 16 (chapter 4, with following noise levels, EPN dB): Standard exterior items
Takeoff...................................................... 80.7 • White paint with two color stripes
Sideline.................................................... 91.7 • Single-point pressure refueling/defueling
Approach................................................. 91.0
• Dayton-Granger static discharge system
The Falcon 2000LX and all systems is capable of the
following types of operations: Minimum Navigation • Pulsed wing-root landing lights
Performance Specifications (MNPS) and Reduced • Red tail and belly anti-collision lights
Vertical Separation Minimums (RVSM) standards oper-
• Wing ice detection lights
ations in the North Atlantic (NAT), Domestic US and
Europe Airspace Regions, RNAV-5 (B-RNAV), RNAV-1 • Wing tip and tail navigation position lights
(P-RNAV), RNP-0.3, RNP-10 and GPS Non-Precision • RH and LH pylon lights and internal servicing lights
approach requirements.
• Three white light strobe system (wing and tail)
• Taxi light on the nose gear

STRUCTURE
The Falcon 2000LX structure employs mainly high-
strength aluminum alloys and complies fully with
“damage tolerance” requirements. The aircraft relies
on multiple load paths and low stress levels to transfer
stress to alternate paths if the primary load path fails.
Wing planks are manufactured from solid blocks of
aluminum. Kevlar or glass composites are selected for
nose cone, horizontal stabilizer (carbon and titanium),
rear cone, fillets and similar secondary structure com-
ponents.
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AIRCRAFT DESCRIPTION

Three-view drawing
70 ft 2 in
21.38 m

98.4 in
2.50 m

23 ft 2 in
7.06 m

24 ft 3.1 in 7.39 m
66 ft 4 in 20.23 m

14 ft 7.2 in
4.45 m
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Aircraft description

Dimensions

Airframe
Overall length 66 ft 4 in 20.23 m
Overall height 23 ft 2 in 7.06 m
Wing span 70 ft 2 in 21.38 m
Wing sweep at quaterchord 29°/24°50’
Wing area, gross 527.4 ft2 49.00 m2
Aspect ratio 7.66
Mean aerodynamic chord 113.7 in 2.89 m
Cross Section (external) 98.4 in 2.50 m

Cabin
Cabin height 74 in 1.88 m
Cabin width (maximum) 92 in 2.34 m
Cabin width (floor) 75.2 in 1.91 m
Cabin length
(flight deck separator to baggage door) 26 ft 2 in 7.98 m
Cabin volume
(flight deck separator to baggage door) 1,024 ft3 29.00 m3
Flight deck volume 132.4 ft3 3.75 m3
Baggage volume
(internal/external access) 130.6 ft3 3.70 m3
Mechanic’s servicing compartment (non-pressurized) 50.0 ft3 1.42 m3
Main entry door size 31.5 in x 67.7 in 0.80 m x 1.72 m
Emergency exit size (Type III) 21.0 in x 36 in 0.53 m x 0.92 m
Cabin window size 15.1 in x 11.8 in 0.38 m x 0.30 m
Baggage door size 30.5 in x 29.5 in 0.775 m x 0.75 m

Landing Gear
Wheelbase 24 ft 3.1 in 7.39 m
Track 14 ft 7.2 in 4.45 m
Minimum turning radius
(with nose wheel steering at 60°) 49 ft 3.8 in 15.03 m
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Aircraft description

Limitations

Weights Speeds
Maximum ramp weight............. 42,400 lb 19,233 kg Maximum Operating Speed (VMO)...... 370/350 kias
Maximum takeoff weight.......... 42,200 lb 19,142 kg Maximum Operating Mach (MMO)...... .862/.85
Maximum landing weight......... 39,300 lb 17,826 kg VFE: SF1 (Slats + Flaps 10°).............. 200 kias
Maximum zero fuel weight....... 29,700 lb 13,472 kg VFE: SF2 (Slats + Flaps 20°).............. 190 kias
Equipped empty weight*.......... 22,635 lb 10,267 kg VFE: SF3 (Slats + Flaps 40°).............. 180 kias
* Based on standard configuration including un­us­able VLO: Landing gear operating............. 190 kias
fuel, engine oil, basic interior, standard avionics and
paint. VLE: Landing gear extended.............. 245 kias
Airbrakes operating or extended........ no limitation
CG location
Altitude and Temperatures
CG limits: From 32.5% of Mean Aerodynamic Chord
(MAC) aft to 14% of MAC Forward. Maximum operating altitude................ 47,000 ft
Airport altitude (maximum).................. 14,000 ft
Fuel Quantity
Operating temperatures at
The approximate total usable fuel capacity is 16,660 lb sea level......................................... -54 °C to +50 °C
(7,557 kg) or, at a 6.7 lb/US gallon (0.803 kg/l) fuel den- -65 °F to +122 °F
sity, 2,487 US gallons (9,411 l).
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Aircraft description

Guaranteed Performance

Takeoff Distance Assumptions

Balanced Field Length The performance data are based on the following
42,200 lb (19,142 kg)....................... 5,585 ft (1,702 m)** conditions:
(Maximum takeoff weight).............................................. • Equipped empty weight: 22,635 lb (10,267 kg) with
(sea level, ISA) standard equipment including paint.
• In accordance with EASA CS-25 and FAR 25
Range Amendment 94 regulations, takeoff and landing per-
(Full fuel, 6 passengers, 2 crew, formance data are calculated on the basis of a
23,465 lb (10,643 kg) basic operating weight, smooth, hard, dry-surfaced runway with zero wind,
M.80*, ISA, zero wind no slope, and an anti-skid system in operation.
NBAA IFR reserves)....................... 4,000 nm** • Range is determined by using the NBAA IFR fuel
reserves performed in still air at standard atmo-
Cruise Speed sphere. Includes climb, cruise at three flight levels
(maximum), and descent.
The maximum cruise speed at the weight of 32,000 lb • The fuel quantity allows (in addition to the planned
(14,515 kg) as limited by the maximum cruise thrust distance flown): 10 minutes of taxiing, one minute
setting or MMO is 508 KTAS* at 25,000 ft (7,620 m) of takeoff, and NBAA IFR reserves (one approach,
and stan­dard temperature. one go-around, holding for five minutes at 5,000 ft
(1,524 m), a flight of 200 nm (370 km) to an alternate
Approach Speed (Vref)........... 113 kias* airport, and holding for up to 30 minutes at 5,000 ft)
26,490 lb (12,015 kg) (1,524 m).
(Typical landing weight, • The fuel is assumed to have a heating value
6 passengers, NBAA IFR reserves) of 18,400 BTU/lb (42,800 kN/kg) and a density of
6.7 lb/US gallon (0.803 kg/l).
Landing Distance
26,490 lb (12,015 kg)........................ 2,630 ft (801 m)**
(Typical landing weight, (sea level, ISA,
6 passengers, NBAA IFR reserves) FAR 91)

* Guaranteed Performance (±3%)

** Guaranteed Performance (±5%)
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Passenger cabin

Interior layout

Flight deck RH Flight deck

Fire Extinguisher Closet

LH Flightdeck 36-in Galley-Bar

Closet Cabinet

Entryway Acoustical Life-raft

Curtain

Side Ledge Storage

Fire Extinguisher Compartments

Tracking Table Storage

Magazine Rack Compartment

Remote Cabin
Individual Seat Temperature Control
(20-in wide)

Telescoping
Folding Stowable Console Table
Console Tables (26 in x 24 in)
(28 in x 24 in)

Ashtray/Cupholder
Module

Individual Seat Tracking

(20-in wide) Magazine Rack

Life-raft Fire Extinguisher

Vanity Cabinet with Electric Flushing

Hot/Cold Water Toilet with
& Storage External Servicing

Baggage Compartment
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Passenger cabin

GENERAL DESCRIPTION
The passenger cabin is soundproofed and insulated, Rear cabin
and measures 26 ft 2 in (7.98 m) in length including an
aft lavatory. It is configured with eight individual pas- The rear cabin also features four (20-in wide) individual
senger seats. Each passenger seat is provided with an seats arranged as in the forward lounge and function-
ashtray and cupholder module, a cold air outlet and ally identical. The right-hand side pair of seats is pro-
a reading light. A stowable, folding console table is vided with a telescoping, 26 in x 24 in console table.
installed for each pair of facing seats.
Lavatory
Two indirect lighting systems provide general lighting
throughout the cabin. They are divided into two zones. The lavatory is equipped with an electric flush toilet on
Individual reading and table lights are also provided. the right and a vanity cabinet on the left-hand side of
Emergency equipment, including a first-aid kit, smoke the compartment. The vanity cabinet includes a sink
hood, life jackets vests and life rafts are provided on with hot and cold water.
the aircraft. Oxygen masks are installed for all passen- The external toilet-servicing connector is located on
gers in the cabin and in the lavatory. the right-hand side of the aircraft. The galley and the
A maintenance ladder is installed in the mechanic’s lavatory are supplied through a central water system,
servicing compartment. which can be drained externally. It also has an internal
filler cap and gauge.
Flight deck - Entryway - Galley To ensure privacy, the lavatory compartment is sepa-
rated from the cabin by a door.
The aircraft main entry door (electrically controlled and
operated) is located on the forward, left-hand side
Baggage Compartment
of the fuselage. LH and RH flight deck closets are
installed forward of the door. The compartment’s volume is 130.6 ft3 (3.7 m3).
A 36-in galley-bar unit is located on the right-hand Access to the baggage compartment is available from
side of the cabin and opposite the entry door. It offers inside or outside the aircraft. The compartment is lined
adequate work surfaces and includes: and features garment hanger racks in the forward area
• a sink supplied with hot and cold water and fold-down baggage shelves to maximize baggage
• a high temperature oven storage.
• an automatic cappuccino/expresso coffee machine
with hot/cold water spigot Interior Finishing
• two ice chests
The cabin provides generous proportions for comfort
• storage drawers
and ease of movement during lengthy flights. Each
• a trash container interior is finished with:
• glass storage racks.
Headliner, Flight deck: ................... Ultra Leather/suede
Forward cabin Headliner, Main Cabin: .................. Ultra Leather/suede
Window Panels, Shades: .................................... Fabric
The forward cabin features four (20-in wide) individual Service Ledges, Main Cabin: ............................ Leather
seats (certified to the 16g requirements) and arranged Lower Sidewalls, Main Cabin: . ......................... Leather
in facing pairs on the left-and right-hand sides of the Carpet:................................... High-Quality, 100% Wool
cabin.
Bulkheads & Doors: . ............................... Wood Veneer
Each seat includes floor tracking, base tracking, side Cabinetry: ........................... Wood Veneer & Laminates
tracking, swivel, full flat recline (berthing), integral Metal Finish: ................................... Brushed Aluminum
headrests and retractable armrests, electrically con- Tables: ............................Composite with Wood Veneer
trolled lumbar.
Seats: ............................................... Fabrics or Leather
Each pair of forward seats is provided with a folding Closet/Baggage Compartment Lining: ......... Grospoint
stowable console table (28 in x 24 in).
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SYSTEMS

ENGINES HYDRAULIC SYSTEM

The Falcon 2000LX operates with two Pratt & Whitney The hydraulic system provides power to operate flight
PW308C engines with a rated takeoff thrust of 7,000 lb controls, landing gear and brakes. The Falcon 2000LX
(at sea level, up to 30°C) each. The engine is a two- operates with two main, independent and simultane-
spool turbofan with a front-mounted single stage fan. ous hydraulic systems for added safety. The hydrau-
lic system operates with MIL-PRF-5606 hydraulic
The Falcon 2000LX’s two engines are controlled by
fluid under a working pressure between 2,850 psi
dual FADEC systems (Full-Authority Digital Electronic
(19.6 MPa) and 3,050 psi (21.0 MPa).
Controls). The engines meet EPA Part 87 requirements
for emissions. Engine parameters are displayed into • The left system is powered by two hydraulic pumps
Engine/CAS windows on each Primary Display Unit. (one on each engine)
The nacelles and engines are separated from the • The right system is powered by the hydraulic pump
airplane’s fuselage and pylons by firewalls. of right engine and by a stand-by pump.
When powered by the stand-by pump, the right system
operates between 1,550 psi to 2,400 psi (10.7 MPa to
THRUST REVERSERS 16.5 MPa). The stand-by pump can be operated man-
ually to power either of the dual hydraulic systems and
Each engine is fitted with a hydraulically operated
to supply hydraulic fluid to operate the flight controls,
thrust reverser for ground use.
landing gear and the brakes, for maintenance opera-
tions on the ground.
FUEL SYSTEM The reservoirs are pressurized by bleed-air.

The fuel system consists of two distinct subsystems

that control fuel tanks in each of the wings, in the cen- FLIGHT CONTROLS
ter section and in forward and aft tanks. Each engine
draws fuel from its respective wing tank, one-half of The Falcon 2000LX is controlled in flight using con­
the center section tank and one forward or aft tank. ventional flight control surfaces:
Fuel flows from pressurized tanks to the engines by These are:
four brushless booster pumps installed in a sump,
supplied by jet pumps. Pressurizing the fuel tanks • Two ailerons for roll and an emergency aileron actua-
permits the engines to continue drawing fuel if the tor.
booster pumps fail during maximum demand on take- • Two elevators and a movable horizontal stabilizer for
off. Interconnecting the LH and RH tanks enables fuel pitch.
levels to balance. Falcon 2000LX is designed so any • A rudder for yaw. A yaw damper unit is installed on
fuel tank can feed any engine and feature single-point the rudder control linkage.
refueling capability. • Two mobile outboard leading edge slats and four
double-slotted Fowler flaps for takeoff, approach
The total usable fuel capacity is approximately 16,660 lb
and landing,
(7,557 kg) or, at a 6.7 lb/US gallon (0.803 kg/l) fuel den-
sity, 2,487 US gallons (9,411 l). • Six airbrakes for aerodynamic braking with automatic
activation after landing and RTO (Rejected TakeOff).
The airplane’s primary flight controls incorporate:
• An AFU (Artificial Feel Unit) that consists of springs
on each axis.
• On the aileron and rudder controls, the main AFU’s
are mounted in series with electrical actuators.
• In the aileron control system, a fully electrical “Arthur
Q” unit causes the feel force to vary with the air-
speed.
• In the elevator control system, an electrical “Arthur
Q” unit slaved to the horizontal stabilizer position is
used to maintain the stick force per “g” to a nearly
constant level throughout the flight envelope.
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Systems

ELECTRICAL SYSTEM
In the event of failure, the aileron and elevator feel sys- The Falcon 2000LX’s electrical system is a 28-Volt DC
tems are returned to their lowest values to ensure safe system. It operates under any of four available sources
surfaces displacement at any aircraft speed. of power: two 12 kW rectifier-alternators, each one
The elevator, rudder and ailerons are controlled by driven by an engine; a 9 kW starter generator driven by
push-pull rods that drive dual barrel hydraulic servo- the APU (Auxiliary Power Unit), by external power and
actuators. The rudder and aileron can be trimmed by two batteries. A 28-Volt DC ground power recep-
using electrical actuators that adjust the neutral posi- tacle with over-voltage protection enables electricity to
tion of the AFU on the respective linkages. be supplied from an external power source for routine
maintenance purposes and as an alternate method
To accomplish pitch trim, two electric motors drive a for starting the APU. The two 36 A/h nickel-cadmium
jackscrew that displaces the stabilizer around a hinge batteries provide for on-ground APU or in-flight engine
point. starts.
The airbrakes and slats are hydraulically actuated. The The two rectifier-alternators supply power to three
flaps may be operated in increments by a jackscrew independent bus bars (LH, RH and essential), which
powered by a hydraulic motor. serve as a conduit to distribute power to the airplane’s
Two angle of attack sensors allow the automatic exten- various systems. The buses can be tied or untied by
sion of slats at high angles of attack. switches on the overhead panel.

LANDING GEAR PNEUMATIC SYSTEM

The landing gear is a retractable tricycle-type with dual The pneumatic system relies on Low-Pressure (LP)
wheels on all landing gear. It is electrically controlled and High-Pressure (HP) bleed air drawn from the two
and hydraulically actuated. engines or from the APU, which is supplied to the
cabin and the anti-icing system. HP bleed is regulated
The main trailing arm gear retracts by swinging laterally by an electrical valve controlled by a Bleed Air Supply
inward. It is fitted with 26 in x 6.6 in - 14 in - 225 mph Computer.
radial tires (tire pressure: 219 psi/1.51 MPa).
The air conditioning system supplies the cabin with
The nose gear retracts by swinging forward. Before a mixture of cool and warm air on demand. Cool air
retraction, the nose wheels are mechanically centered. is provided by a single two-wheel bootstrap air cycle
The nose gear is fitted with 14.5 in x 5.5 in - 6 in - cooling unit connected to primary and secondary heat
225 mph radial tires (tire pressure: 183 psi/1.26 MPa). exchangers and a condenser. A jet pump provides cir-
The hydraulic system powers the nose wheel steering, culation through the exchangers when the airplane is
which is electrically controlled from the left-hand pilot’s on the ground or flying at low speed.
station. In the event of failure, a shimmy damper main- Temperatures in the passenger and crew compart-
tains nose wheel directional stability. ments can be controlled by two automatic, indepen-
The standby landing gear extension, with an emer- dent temperature control systems and by a backup
gency hydraulic extension handle on the front panel, manual control system.
operates hydraulically and does not include electrical The pressurization system can maintain cabin and
sequencing. Three manual override handles in the flight baggage compartment pressures up to the rated pres-
deck allow the landing gear to free fall into a down and sure differential of 9.00 psi (620 hPa) for all flight alti-
locked position in an emergency. tudes below 47,000 ft (14,325 m), ensuring a maximum
A temperature sensor is fitted on each brake. Brake cabin altitude of 8,000 ft (2,438 m). Cabin pressure is
temperature is displayed in the hydraulic synoptic on controlled by two outflow valves. The nose cone is also
the flight panel displays. pressurized from the cabin air.
The landing gear carbon disk brakes are powered The pneumatic system also controls pressurization of
independently by two hydraulic systems. The N° 2 the fuel tanks.
hydraulic system provides back-up braking with an A catalytic ozone-removal system is installed.
accumulator for parking and emergency braking. The
braking system provides a signal for automatic air-
brake activation upon touch down or landing.
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Systems

AUXILIARY POWER UNIT FIRE PROTECTION SYSTEM

A self-contained APU (Auxiliary Power Unit) is installed The Falcon 2000LX is equipped with a fire-detec­tion
in the aft fuselage. It is designed for ground and system that includes audio and visual warnings. Fire
in flight operation: Maximum operating altitude is detectors are located in zones 1 and 2 of each engine
35,000 ft (10,668 m), used to start the engines, and to area, in the APU shroud and in the landing gear wheel
deliver bleed air to the air conditioning system when wells. One fire extinguisher con­tainer, with a two-shot
the airplane is on the ground. A 9 kW starter generator capacity, is positioned at each of the air­craft’s two
starts the APU itself, supplies power to aircraft sys- engines, and a third is located at the APU.
tems and is fitted with an APU Electronic Control Unit.
In addition, three portable fire extinguishers are located
in the air­craft, one in the flight deck and the others in
the passenger cabin. A smoke detector is installed in
ICE AND RAIN PROTECTION the baggage compartment.
The ice-protection system is intended to permit safe
flight into and through intermittent or continuous maxi­
mum icing conditions. Heated bleed air pro­duced by
OXYGEN SYSTEM
the engines and directed to the air con­di­tioning sys­tem
In case of depressurization, drop-down masks are
serves as an anti-icing agent on the leading edges of
automatically released (or can be manually released)
the wings, the engine air-inlets and the nacelles. The
so passengers can breathe low-pressure oxygen from
windshield, pitot probes, temperature probes, static
a 77.6 ft3 (2,150 l) container.
ports and angle-of-attack sensors are electrically heat-
ed for ice protection. Oxygen flow is regulated by cabin altitude.
The inner surface of the windshield panels is de­fogged Oxygen is continuously provided to the crew on
using air from the air conditioning system. The side demand. The flight deck is equipped with quick-don-
windshield panels and the pilot’s sliding window are ning masks with built-in regulators and comfort har-
defogged electrically. The cabin windows can be kept nesses.
free of fog by preventing moisture from accu­mu­lating The oxygen system is fitted with an electronic com-
in the airspace between the window panes. puter for airport altitudes up to 14,000 ft (4,267 m).
Independent, electrically-operated wipers help keep
the front windshields free of rain.
 15
Systems

Avionics
The Falcon 2000LX’s avionics system encompasses:

Description Quantity Vendor

Honeywell Primus Epic System
Flight Display System (w/4 each 14” LCD’s, 2 each 1 Honeywell
Cursor controls & 2 each keyboards)
Flight Control Systems 2 Honeywell
Autothrottle System 1 Honeywell
Crew Alerting & Aural Warning Systems 3 Honeywell
Central Maintenance Computer 1 Honeywell
Interactive Checklist 1* Honeywell
Flight Management Systems 2 Honeywell
Global Positioning Systems 2 Honeywell
Air Data Systems 2 Honeywell
Enhanced Ground Proximity & Windshear Warning System 1 Honeywell
VHF Communication Systems 2 Honeywell
VOR/ILS/Marker Navigation Systems 2 Honeywell
DME Systems 2 Honeywell
ADF Systems 2 Honeywell
Mode S Transponder Systems 2 Honeywell

Complementary Systems
TCAS II System 1 ACSS
Data Loader 1 Honeywell
Inertial Reference Systems 2 Honeywell
Color Weather Radar System 1 Honeywell
Radio Altimeter System 1 Honeywell
Cockpit Voice Recorder 1 Honeywell
Flight deck Audio Systems w/radio & intercom functions 2 Honeywell
& SELCAL (HF1 & 2, VHF1 & 2)
Flight deck Headsets 2 Telex
Falcon Cabin Management System (FCMS) 1 Rockwell Collins
(PA/chime, lights, temperature only, without entertainment)
HF Communication Systems 2 Rockwell Collins
ELT (Tri-frequency) System 1 ELTA

Emergency Equipment
Standby Magnetic Compass 1 Smiths
Integrated Electronic Standby Indicator 1 Meggitt
(Attitude, Altitude, Mach/Airspeed)
Rechargeable Flashlights 2 DME

* 2nd Interactive Checklist will be available in EASy Phase 2

 Réalisé par armon@ - Paris

Imprimé en France – Août 2009

 armon@ - +33 (0) 663 426 552 - Août 2009

Dassault Falcon Jet

Teterboro Airport, Box 2000, South Hackensack, NJ 07606
Phone: (1) 201-440-6700
Fax: (1) 201-541-4469
DGAC-DMF8008B

Dassault Aviation
Cedex 300 - 92552 Saint Cloud Cedex - France
Phone: 33 (0) 1 47 11 82 82
Fax: 33 (0) 1 47 11 89 17