falcon 2000 ptm v2r2 mcd description des systemes

8/18/2019 Falcon 2000 PTM V2r2 MCD Description Des Systemes

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FALCON 2000 PILOT TRAINING MANUAL

Record of Revision No. 2

This is a complete reprint of the Falcon 2000 Pilot Training Manual , Volume 2.

The portion of the text or figure affected by the current revision is indicated by a solid

vertical line in the margin. A vertical line adjacent to blank space means that materialhas been deleted. In addition, each revised page is marked “Revision 2” in the lower

left or right corner.

The changes made in this revision will be further explained at the appropriate time in

the training course.

FlightSafetyinternational

INSTRUCTIONAL SYSTEMS DIVISION 8900 Trinity Blvd. Hurst, Texas 76053 (817) 276-7500 FAX 817) 276-7501

The best safety device in any aircraft is a well-trained pilot…


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FlightSafety International, Inc.Marine Air Terminal, LaGuardia Airport

Flushing, New York 11371(718) 565-4100

www.flightsafety.com

FALCON 2000

PILOT TRAINING MANUAL

VOLUME 2 AIRCRAFT SYSTEMS


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Copyright © 2001 by FlightSafety International, Inc.All rights reserved.

Printed in the United States of America.

Courses for the Falcon 2000 and other Falcon aircraft are taught at the followingFlightSafety learning centers:

FlightSafety InternationalTeterboro Learning Center

Teterboro Airport 100 Moonachie AvenueMoonachie, New Jersey 07074Phone: (201) 528-0100Toll-Free: (800) 827-8058Fax: (201) 528-0101

FlightSafety InternationalDFW Learning Center3201 E. Airfield DriveP.O. Box 613169DFW Airport, TX 75261-3169Phone: (972) 534-3200

Toll-Free: (866) 486-8733Fax: (972) 534-3199

FlightSafety InternationalParis Learning CenterFlightSafety International SARLBP 25, Zone d’Aviation d’AffairesBldg. 404, Aeroport du Bourget 93352 Le Bourget, CEDEX FRANCEPhone: +33 (1) 49-92-19-19Fax: +33 (1) 49-92-18-92

FlightSafety InternationalColumbus Learning CenterPort Columbus International Airport 625 North Hamilton RoadColumbus, OHIO 43219Phone: (614) 559-3700Toll-Free: (800) 896-9653Fax: (614) 559-3715


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NOTICE

The material contained in this training manual is based on information obtained from theaircraft manufacturer’s Pilot Manuals and Maintenance Manuals. It is to be used forfamiliarization and training purposes only.

At the time of printing it contained then-current information. In the event of conflictbetween data provided herein and that in publications issued by the manufacturer or theFAA, that of the manufacturer or the FAA shall take precedence.

We at FlightSafety want you to have the best training possible. We welcome anysuggestions you might have for improving this manual or any other aspect of ourtraining program.

FOR TRAINING PURPOSES ONLY



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CONTENTS

Chapter 1 AIRCRAFT GENERAL

Chapter 2 ELECTRICAL POWER SYSTEMS

Chapter 3 LIGHTING

Chapter 4 MASTER WARNING SYSTEM

Chapter 5 FUEL SYSTEM

Chapter 6 AUXILIARY POWER UNIT

Chapter 7 POWERPLANT

Chapter 8 FIRE PROTECTION

Chapter 9 PNEUMATICS

Chapter 10 ICE AND RAIN PROTECTION

Chapter 11 AIR CONDITIONING

Chapter 12 PRESSURIZATION

Chapter 13 HYDRAULIC POWER SYSTEMS

Chapter 14 LANDING GEAR AND BRAKES

Chapter 15 FLIGHT CONTROLS

Chapter 16 AVIONICS

Chapter 17 MISCELLANEOUS SYSTEMS

APPENDIX

ANNUNCIATOR PANEL

INSTRUMENT PANEL POSTER


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CHAPTER 1

AIRCRAFT GENERAL

CONTENTS

Page

INTRODUCTION ................................................................................................................... 1-1

GENERAL............................................................................................................................... 1-1

STRUCTURES........................................................................................................................ 1-3

General ............................................................................................................................. 1-3

Fuselage ........................................................................................................................... 1-3

Engine Nacelles ............................................................................................................. 1-19

Wings ............................................................................................................................. 1-20

Empennage..................................................................................................................... 1-20

AIRPLANE SYSTEMS ........................................................................................................ 1-21

General........................................................................................................................... 1-21

Electrical Power System ................................................................................................ 1-21Master Warning System................................................................................................. 1-22

Lighting System............................................................................................................. 1-22

Fuel System.................................................................................................................... 1-25

Auxiliary Power Unit..................................................................................................... 1-26

Powerplant ..................................................................................................................... 1-26

Fire Protection System................................................................................................... 1-27

Pneumatic System.......................................................................................................... 1-27

Ice and Rain Protection Systems ................................................................................... 1-28

Air-Conditioning System............................................................................................... 1-29

Pressurization................................................................................................................. 1-29


Revision 1 1-iFOR TRAINING PURPOSES ONLY


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Hydraulic Power Systems.............................................................................................. 1-30

Landing Gear and Brakes .............................................................................................. 1-31

Flight Controls ............................................................................................................... 1-32

Avionics ......................................................................................................................... 1-35

Oxygen System.............................................................................................................. 1-37

Water System ................................................................................................................. 1-38

PARKING AND MOORING................................................................................................ 1-38


Revision 11-ii FOR TRAINING PURPOSES ONLY


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ILLUSTRATIONS

Figure Title Page

1-1 Exterior Dimensions.................................................................................................... 1-2

1-2 Minimum Turning Radii ............................................................................................. 1-3

1-3 Release of Steering Control (Towing)......................................................................... 1-4

1-4 Cockpit ........................................................................................................................ 1-5

1-5 Pilot’s and Copilot’s Seats........................................................................................... 1-6

1-6 Passenger Cabin (Typical)........................................................................................... 1-7

1-7 Tail Cone ..................................................................................................................... 1-8

1-8 Overall Layout and Structure ...................................................................................... 1-9

1-9 Passenger/Crew Door Assembly............................................................................... 1-10

1-10 Passenger Door Latching and Unlatching Mechanism ............................................. 1-11

1-11 Electrical Lifting Mod for Passenger Door............................................................... 1-12

1-12 Baggage Compartment Door .................................................................................... 1-14

1-13 Baggage Compartment Door Handle Control Mechanism....................................... 1-15

1-14 Forward Servicing Compartment Door..................................................................... 1-16

1-15 Aft Servicing Compartment Door............................................................................. 1-17

1-16 Emergency Exit Door Location, Controls, and Indicators........................................ 1-18

1-17 Main Landing Gear Doors ........................................................................................ 1-19

1-18 Wings and Empennage.............................................................................................. 1-20

1-19 DC Power Generation System .................................................................................. 1-21

1-20 Warning Panel ........................................................................................................... 1-221-21 Engine Indication Electronic Displays...................................................................... 1-22

1-22 Exterior Lighting System.......................................................................................... 1-23

1-23 Emergency Lighting System..................................................................................... 1-24

1-24 Wing Fuel Tanks ....................................................................................................... 1-25


Revision 1 1-iiiFOR TRAINING PURPOSES ONLY


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1-25 Engine ....................................................................................................................... 1-26

1-26 Fire and Smoke Detection System............................................................................ 1-27

1-27 Ice and Rain Protection Systems............................................................................... 1-28

1-28 Air-Conditioning System .......................................................................................... 1-29

1-29 Hydraulic Power System........................................................................................... 1-30

1-30 Landing Gear and Wheel Well Door......................................................................... 1-31

1-31 Landing Gear System................................................................................................ 1-32

1-32 Aileron Control System ............................................................................................ 1-33

1-33 Rudder Controls ........................................................................................................ 1-34

1-34 Avionics Master Switchlights ................................................................................... 1-35

1-35 Antenna Locations .................................................................................................... 1-36

1-36 Cockpit Oxygen System............................................................................................ 1-37

1-37 Right Front Galley and Electrical Panel.................................................................... 1-38

1-38 Parking and Mooring ............................................................................................... 1-39


Revision 11-iv FOR TRAINING PURPOSES ONLY


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1-1FOR TRAINING PURPOSES ONLY

INTRODUCTION

This training manual provides a description of the major airframe and engine systemsinstalled in the Falcon 2000. The information contained herein is intended only as aninstructional aid. This material does not supersede, nor is it meant to substitut e for,any of the manufacturer’s system or operating manuals. The material presented hasbeen prepared from the basic design data. All subsequent changes in airplane ap-pearance or system operation will be covered during academic training and subsequentrevisions to this manual.

GENERAL

The Falcon 2000 is manufactured by DassaultAviation. It is a light-alloy, low-wing, twin-jetmonoplane with one CFE-738-1-1B engine oneach side of the fuselage and a Garrett GTCP36-150 (F2M) auxiliary power unit. Its overall

length is 66 feet 3 inches, and it has a wingtip-to-wingtip width of 63 feet 4 inches. These andother dimensions of the aircraft are shown inFigure 1-1.

CHAPTER 1AIRCRAFT GENERAL


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1-2 FOR TRAINING PURPOSES ONLY

F i g u r e

1 - 1 .

E x t e r i o r D i m e n s i o n s

( 2 4 F T 3

I N . )

7 . 3 9 4 M (

6 6 F T 3 I N . )

2 0 . 2 2 8 M

( 2 2 F T 9 I N . )

6 . 9 8 0 M

( 1 4 F T 7 I N . )

4 . 4 5 0 M

( 9 8 . 4

I N . )

2 . 5 0

0 M

( 6 3 F T 4 I N . )

1 9 . 3 2 8 M

N O T E ;

A M I N I M U M T A I L C L E A R A N C E O F

7 . 2 m ( 2 3 F E E T 8 I N C H E S ) I S R E Q U I R E D

F O R T H E H A N G A R ( F L O O R T O C E I L I N G )

.


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The nosewheel maximum steering angle dur-ing taxiing is 60°, and the turning radius ap-plicable to this angle is shown in Figure 1-2.Towing of the aircraft requires the release of

the steering control Figure 1-3.

This aircraft is designed to be flown with aminimum flight crew of two. Passenger seat-ing varies according to the client’s selected op-tions. Most cabin configurations allow foreight to ten passengers.

STRUCTURES

GENERAL

The airplane is primarily constructed of high-resistance aluminum alloy, although certainstructures are made of other materials. The pri-mary structures of the aircraft include the fuse-lage, engine nacelles, wings, and empennage.

FUSELAGE

The fuselage is of monocoque construction andis made of a light alloy. The framework is of fail-

safe design and satisfies damage tolerance cal-culation conditions. The outer skins of thefuselage are chemically milled and stiffened bystringers made of extrusions of variable thick-nesses and sections. The stringers are rivetedto the structure.

Skids are positioned underneath the fuselageto protect the fuel tanks in the event of a bellylanding.

The main sections of the fuselage include thenose cone, cockpit, cabin, and baggage com-

partment. These sections are pressurized.

In addition, there is an unpressurized aft fuse-lage and tail cone section.

60

90

14 FT (4.2 M)

~

3 3 F T ( r

- 1 0 . 0 8

M )

N W S

U N C O

U P L E

D ~

4 7 F T ( r

- 1 4 . 3 M )

N W S

C O U P

L E D

Figure 1-2. Minimum Turning Radii


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F I T T I N G S T O P I N T O R Q U E

L I N K U P P E R A R M I N U P

P O S I T I O N W I T H T H

R E A D E D

P I N A N D N U T

P O S I T I O N

W H E N

C O U P

L E D

P O S I T I O N

W H E N

U N C O U P L E D

S H O C K

A B S O R B E R

S L I D I N G

T U B E

S W I V E L

C R

O S S - S E C T I O N A

T O R Q U E L I N

K H I N G E D E T A I L

T O R Q U E L I N K

A R M

P I N

N U T

L O C K I N G T A B

C O U P L I N G

/ U N C O U P L I N G

P O S I T I O N

( U N S T A B L E )

P O S I T I O N W H E N

B A R I S H O O K E D

T O W B

A R

F R O N T

T O R Q

U E L I N K

Q U I C K R

E M O V A L P I N

U N C O U P L E D T

O R Q U E

L I N K L O W E R

A R M

T O W

F I T T I N G S

F

D E T A I L F

A

F i g u r e 1 - 3 .

R e l e a s e o f S t e e r i n g C o n t r o l ( T o

w i n g )


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Nose ConeThe nose cone consists of a radome made of composite materials. It is hinged on a chassiswhich moves parallel to the aircraft center-line. A counterbalancing actuator holds thecone in the up position. This position allowsan umbrella-like shield to be extended in badweather to protect the equipment mounted onthe fixed chassis.

Cockpit

The cockpit is composed of a variety of phys-ical and structural features designed for thecontrol and flight of the aircraft (Figure 1-4).For the comfort and protection of the crew, the

cockpit is insulated against sound and heat. Acentral pedestal is located between the pilot’sand copilot’s seats. The central pedestal con-tains the engine and flight controls includingthe flaps, slats, airbrakes, ailerons, rudder,and horizontal stabilizer trim. Also locatedon the central pedestal are the radio and nav-igation controls. Other components located

in the cockpit are the instrument panel ,glareshield, overhead panel, side consoles,circuit-breaker panels, lighting, three seats, afalse floor in part of the compartment, an op-

tional separating curtain, two closets, threewindshields and four windows, an optionalsliding door to separate the cockpit from thepassenger cabin, and an optional lavatory.

The instrument panel glareshield is coveredwith black leather and has a slide-mountedsun visor on each side. This sun visor consistsof a sheet of tinted plexiglass. Each sun visorcan be pulled rearward and raised to cover thefront windshield and part of the pilot’s andcopilot’s windshields. For additional sun pro-tection, two roller-type sunshades are mounted

on each side of the cockpit. These can be usedto completely or partially cover the rear sidewindows and the front side windows.

PILOT SEAT

PILOT CLOSET

CENTRALPEDESTAL

GLARESHIELD

COPILOT SEAT

THIRD CREWMEMBERSEAT

Figure 1-4. Cockpit


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The cockpit is designed for a crew of three. Thecontrols and seating are identical for the pilotand copilot for maximum comfort and safety.The control pedals are adjustable to allow for a

pilot height of 60 to 75 inches.

Pilot’s and Copilot’s Seats

The pilot’s and copilot’s seats manually adjustforward and backward. They have a manualbackrest and armrest tilt angle adjus ter. Theseat height adjustment system is electrical.

Each seat has a five-point harness and beltassembly secured to the seat structure. To allowfull freedom of movement for the pilot, theharness assembly consists of a horizontal lap belt,

a harness consisting of two inertia-reel-mountedshoulder straps, and a strap fixed to the front of theseat passing between the knees leading to thebuckle. The seat adjustment controls and locationsare illustrated in Figure 1-5.

Jump Seat

The third crewmember uses the jump seatsituated adjacent to the passenger compart-ment door.

For safety, this seat is equipped with a three-point harness consisting of an upper shoulderstrap equipped with an inertia reel, and twolower side straps of adjustable length joinedto the seat pan.

A life jacket is located under each cockpit seat.

Passenger CabinThe passenger cabin is designed so that thebasic installation can be adapted to suit the par-ticular requirements of the customer (Figure1-6). The sofa, seats, galley, video cabinet, re-frigerator, bar, tables, ambient lighting, and ar-rangement of the lavatory can be varied as

BACKREST ANGLEPUSHBUTTON

HEIGHT ADJUSTMENTSWITCH

HEIGHT ADJUSTMENTELECTRIC MOTORTRANSLATION DISPLACEMENT CONTROL

ARMREST VERTICALADJUSTMENT LEVER

Figure 1-5. Pilot’s and Copilot’s Seats


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E X I T E

X I T

P U L L H E R E

T O O

P E N

E X I T

E X I T

E X I T

E X I T

E X I T

E X I T

F i g u r e 1 - 6 .

P a s s e n g e r C a b i n ( T y p i c a l )


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required to meet client needs. An emergencyexit is located on the right side at the 7th win-dow. An EXIT sign is located above the emer-gency exit.

The cabin is insulated against heat and sound.The walls have a lining shell consisting of strip panels, window panels, and ceiling.These are assembled together to form a rigid,independent shell, connected to the structureby flexible supports. The lining shell meetssafety standards and complies with f ire-proofing regulations.

The cabin has 18 windows with an option fortwo additional windows.

Ordinance signs which notify the passengerswhen to fasten seat belts and when not to smokeare located throughout the passenger cabin. ARETURN TO SEAT indicator light located inthe lavatory illuminates simultaneously with thecabin FASTEN BELT signs. Other ordinancesigns include an attendant call switchlight andthe accompanying indicator lights on the galleyfront face to notify the attendant of the callorigin. An optional gong, heard through thepilots’ and passengers’ loudspeakers when theFASTEN BELT sign illuminates, is available.

Baggage Compartment

The baggage compartment is located aft of the passenger cabin and is divided to formtwo sections. It has a fireproof trim panel as-sembly made of aluminum honeycomb.

The forward section contains a wardrobe whilethe aft section is equipped with two foldingshelves for hand baggage. The shelves can beplaced in either stowage or normal use posi-tion, depending on the volume of baggage ona given flight. Nets are provided to hold the bag-gage in place. The compartment is limited toa maximum weight capacity of 1,600 pounds.

The baggage compartment contains a smokedetector, and can be accessed through the lava-tory to allow fire fighting.

Aft Fuselage and Tail ConeSection

The aft fuselage is located behind the bag-

gage compartment. It is an unpressurized com-partment and contains the forward servicecompartment (FSC) and aft service compart-ment (ASC). The tail cone, aft of the ASC,houses the APU (Figure 1-7).

Doors

General

The Falcon 2000 has five exterior doors (Figure1-8). On the left side of the fuselage are thepassenger/crew door, the baggage compartment

door, and the forward servicing compartmentdoor. The emergency exit is located on the rightside of the fuselage. The aft servicingcompartment door is located underneath thefuselage, aft of the FSC.

Revision 11-8 FOR TRAINING PURPOSES ONLY

APU

Figure 1-7. Tail Cone


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0

5

7

1 9

2 1

2 6

3 3

3 9

P A S S E N G E R C

A B I N

E M E R G E N C Y E X I T

( R H S I D E )

F O R W A R D

S E R V

I C I N G

C O M P A

R T M E N T

E N T R A N C E

D O O R

F U E L

T A N K S B

A G G A G E

C O M P A R T M E N T

D O O R

F O R W A R D

S E R V I C I N G

C O M P A R T M E N T D O O R

A F T

S E R V I C I N G


A F T S E R

V I C I N G

C O M P A R

T M E N T

D O O R

A P U C O M P A R

T M E N T

N O S E C O N E

C O C

K P I T

E N T R A N C E

T O I L E T

B A G G A G E


F i g u r e 1 - 8 .

O v e r a l l L a y o u t a n d S t r u c t u r e


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Passenger/Crew Door

The passenger/crew door provides normal ac-cess to the aircraft. Located on the forward leftside of the aircraft, it is hinged at its lower sec-

tion and equipped with an integral airstair(Figure 1-9). Two lateral telescopic rods limitthe amount of opening of the door. The doorhas an opening/closing control with a coun-terbalancing device, two latching/unlatchingcontrols (one inboard and one outboard), anda mechanical locking device which is con-trolled by the pressurizing flap. The functionof the pressurizing flap is to block the doorcontrol mechanism during pressurized flight.

When not in flight, the door is opened by firstunlocking the outboard handle with a key.After the door is unlocked, it must be un-latched. The unlatching device is controlledby a dual mechanism. It can be ac tuated frominside with a handle on the airstair box orfrom the outside by a handle located on thelower center section of the door. The door isopened by tilting it on its hinge. When thedoor is opened from the outside, door move-ment must be manually supported while inmotion. Opening the door from the inside can

be accomplished by turning the control han-dle 230°. A DOORS warning light on the warn-ing panel illuminates when the aircraft systemsare energized and when either of the two han-

dles are moved from the latched position.

The door can be closed from either inside oroutside the aircraft. To close the door fromthe inside, one must lift the door by means of the control handle. To close the door from theoutside, it must be pushed up manually. Whenthe door engages the frame, it is guided by aroller which engages the guide track of theframe and the handrail guide. The end of travelis controlled with the outboard handle.


FIXED HANDRAIL

GUIDE AT FR 7

GUIDE AT FR 5

TELESCOPICHANDRAIL

TELESCOPIC ROD

SPOTLIGHT

WINDOW

FOLDING STEP

CRANKPIN

INBOARDCONTROL HANDLE

LATCHING/UNLATCHING

STEP LIGHTING

SWITCH

STOP

TELESCOPIC ROD

RETRACTABLESTEP

Figure 1-9. Passenger/Crew Door Assembly


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Revision 1 1-11FOR TRAINING PURPOSES ONLY

;

;

;

; WINDOW

LATCHING/UNLATCHINGCONTROL HANDLE

OUTER OPENINGMECHANISM BOX

LINK RODS

Figure 1-10. Passenger Door Latching and Unlatching Mechanism


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EXTERNAL LIFT PUSHBUTTON

DOOR LIFT AND EXT LIFT INHIBTPUSHLIGHTS ARE ADDED

DOORLIFT

EXTLIFT

INHIBITMECHANICAL DOOR LIFTING

HANDLE IS REMOVED

Figure 1-11. Electrical Lifting Mod for Passenger Door


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PASSENGER DOOR (ElectricalLifting Mod)

Aircraft serial number 138 and subsequent in-

corporate Modification M1378 which removesthe mechanical door lifting handle of the pas-senger door and installs controls for electri-cal lifting of the door. This function is onlyoperational on the ground.

Electrical lifting may be controlled from in-side or from outside the aircraft via the DOORLIFT pushbutton. Lifting is controlled byholding down the pushbutton. When the dooris fully up, releasing the pushbutton initiatesa 2-second timeout holding the door againstits stops and giving the operator time to grasp

the door to close it.

The internal control is located on the top stripof the cabinet located behind the Pilots seat.The control button is a square, lighted push-button marked DOOR LIFT, fitted with a trans-parent guard to prevent unwanted operation(Figure 1-11).

The external control is located on the fuselagenext to the oxygen vent. The pushbutton, lo-cated behind a silicone membrane, is markedDOOR LIFT and can be controlled directlyfrom the outside.

The external control can be inhibited from theinside by pressing the EXT LIFT INHIBITpushbutton. This pushbutton is lit white whenpushed down.

During lifting, the geared motor automati-cally disconnects its power supply:

• If an overload is detected during oper-ation (obstacle, etc.)

• If lifting is not completed within 30 sec-onds. In particular, if the pushbutton isblocked pressed in, the geared motor isonly supplied for 30 seconds.

The geared motor supply is from a direct bat-tery line via the ceiling light PCB (crash PCB).



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Baggage Compartment Door

The baggage compartment may be accessedfrom the aircraft interior, through the lava-tory or through an exterior door. The interior

door provides in-flight access to the com-partment in case of fire or other needs. The ex-terior door provides loading access for baggageand is located on the left side of the fuselage.

The exterior baggage compartment door(Figure 1-12) is hinged on its lower side andopens outward by tilting the door forward.

The spring counterbalancing device supportsthe door weight during the opening motion.Opening travel is limited by two cables woundon reels and installed on either side of the

door. This door is equipped with three fixedsteps and one folding step, a control device,and a counterbalancing device. Additionaldoor components include a pressurizing flaplocated inside the door, a latching assembly,and a door-locking safety assembly.


MICROSWITCH

UPPERGUIDE

LOWERGUIDE

COUNTER-BALANCING

CABLE

HOLDINGCABLE

LATCHINGPAWL

FOLDINGSTEP

DOOR

DOORFRAME

LATCHFITTING

PROXIMITYSENSOR

DOORTHRESHOLDFAIRING

AUXILIARYDOOR

DOOR MECHANISMACCESS DOOR

FOLDING STEPSTOW CAP

REEL

Figure 1-12. Baggage Compartment Door


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Three separate mechanisms control the open-ing and closing of the door: the safety lock, theunlocking flap, and the control handle. Thesafety lock controls locking and unlocking of

the latching mechanism. When the unlockingflap is depressed, it frees the latch pawl. Thecontrol handle allows the door to be movedclear of the frame or to engage it by lifting orlowering the handle. The baggage door handlecontrol mechanism is illustrated in Figure 1-13.

To close the door, the bottom step must firstbe folded and locked in its retaining clip. Thedoor may then be lifted using the control han-dle, and engaged in its frame. When the con-trol handle is lowered, the unlocking flap isautomatically returned to a flush position. The

latch pawl holds the door against the frame.

A microswitch located under each upper guidecontrols illumination of the compartment whenthe airplane is on the ground or in flight and thedoor is unlatched. These microswitches also

indicate a door-unlatched condition throughillumination of the warning panel DOORS light.Two proximity sensors also actuate illuminationof the compartment and the DOORS warninglight when they detect the latch pawl or thesafety finger leave the engaged position. Thedoor-closed-and-latched condition is checkedwhile the aircraft systems are energized and theaircraft is sitting on its wheels, it is alsomonitored in flight.


PUSH

EXTERNAL CONTROL

UNLOCKED POSITION

LOCK

CONTROLHANDLE

SAFETY FLAP

BAGGAGECOMPARTMENT

DOOR

Figure 1-13. Baggage Compartment Door Handle Control Mechanism


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Forward ServicingCompartment Door

The forward servicing compartment door pro-vides access to the forward servicing com-

partment and is equipped with a folding ladderfor entry (Figure 1-14). The door is hinged onits lower side and is latched with a three-latchmechanism controlled from the outside by aretractable handle. This handle is locked in po-sition with a key.

The forward servicing compartment door opensfrom the outside only. The door is opened byfirst releasing the control handle from its hous-ing by depressing the button labeled “PUSH.”

The handle is rotated downward, allowing thedoor to tilt outward. The door must be manu-ally supported during its travel. Cables supportthe door once reaching its maximum opening

position. The ladder tilts outward from thedoor opening and may be unfolded afterremoving the locking pin. The ladder isequipped with a cable to limit its travel, andafter being unfolded it is held in place by a stripand pin located on its lower element. Closingthe door can be accomplished by reversing thisprocess. A microswitch monitors the door andilluminates the DOORS light on the warningpanel if the forward servicing compartmentdoor is not closed and latched. The forwardservice compartment door is monitored onthe ground only.


LADDER HOLDINGCABLE

LADDER SLIDINGLATCH

DOOR/LADDERRETAINING STRIP

DOOR/LADDERRETAINING PIN

PANEL

REAR PAWL

LADDER HOLDING

CABLE

DOOR HINGE

Figure 1-14. Forward Servicing Compartment Door


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Aft Servicing Compartment Door

The aft servicing compartment door is locatedunder the aircraft, on the centerline, and isequipped with two fixed steps and a folding

ladder (Figure 1-15). This door provides ac-cess to the aft service compartment, whichhouses the engine and APU fire bottles, aswell as various hydraulic components.

This door is opened by first unlocking it witha key and then rotating the latch which blocksthe unlatching mechanism pushbutton. The

unlatching pushbutton may then be depressedto actuate the latch control handle. The doormust be manually supported during its open-ing travel.

The door-closing procedure is the reverse of the door-opening procedure. A microswitch inthe door actuates illumination of both the com-partment interior and the DOOR warning lightin the cockpit. The aft service compartmentdoor is monitored on the ground only.


34

36 BEARING

RUBBER STOP

FOLDED EDGE

STEP

STEP

PAWL

FOLDING LADDER

LOCK

CABLE

Figure 1-15. Aft Servicing Compartment Door


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Emergency Exit

The emergency exit is a panel located on theright side of the aircraft (Figure 1-16). Thispanel is at the midsection of the airplane and

opens over the right wing. It is fitted with a cen-ter window and equipped with a quick-releasemechanism which can be actuated from in-side or outside the aircraft. The emergencyexit can be identified inside the aircraft bythe indicating plate next to the handle and theilluminated sign above the window frame.

To open the emergency exit from the passengercabin, one must simply pull the handle. To openfrom the outside, a red plexiglass cover must firstbe broken. Press the pushbutton within the cover

to open the emergency exit. Figure 1-16illustrates the location of the emergency exit andits interior and exterior opening control locations.As an option the aircraft may be fitted with anemergency exit panel located on the left side of the aircraft.


EXIT

PULL HERETO OPEN

EXIT

PUSH TO OPEN

POUSSER POUR OUVRIR

PULL RED HANDLELIFT UP EXITTHROW EXIT OUTSIDETIRER LA POIGNEE ROUGESOULEVER L'ISSUEJETER L'ISSUE A L'EXTERIEUR

PLACARD

CABINLIGHTS

(INSTRUCTIONS ON HINGEDHANDLE COVER)

EMERGENCY EXIT

INBOARD VIEW

EMERGENCY EXITOUTBOARD VIEW

RED FRANGIBLECOVER

PLACARD

Figure 1-16. Emergency Exit Door Location, Controls, and Indicators


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Landing Gear Doors

The landing gear doors enclose the wheelwells when the landing gear is retracted. Eachmain landing gear has a main door and a strut

door (Figure 1-17). The nose landing gear hastwo symmetrical main doors, a main shielddoor, and an auxiliary shield door.

The main landing gear main doors are hingedto the fuse lage lower sec t ion and a rehydraulically actuated. Each strut door ishinged on the lower surface of the wing.

The nose landing gear main doors open later-ally on two hinges with the actuating rod con-nected to the rear hinge fitting. The mainshield door is hinged on the aircraft structureand linked to the landing gear strut by twoadjustable rods. The auxiliary shield door isattached to the torque link.

Windows

Cockpit

The cockpit has a front windshield, pilot’sand copilot’s windshields, left and right frontwindows, and left and right rear windows. Allwindows are equipped with an electrical anti-icing system. The left front window, next tothe pilot, slides rearward to open.

Passenger Cabin

The passenger cabin has 18 windows with anoption of two additional windows. One of these windows is located in the center of theemergency exit panel.

ENGINE NACELLES

The nacelles house the engines and consist of the air intake, cowlings, rear body, and fan rearinner cowling. They are mounted by pylons toeach side of the aft fuselage.


WHEELS

SLIDING ROD

MAIN L/G STRUT

STRUTDOOR

LINK ROD

MAIN L/G BRACESTRUT ACTUATOR

MAIN L/G DOORLATCH

MAIN L/G DOORACTUATOR

MAIN L/G UPLOCK

MAIN DOOR

Figure 1-17. Main Landing Gear Doors


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WINGS

The aircraft wings are dual swept. Each wingconsists of a fixed stressed structure and sev-

eral mobile components (Figure 1-18).

The fixed structure includes a fuel tank; theoutboard leading edges; and compartmentsfor the airbrakes, ailerons and flaps, and mainlanding gear. The mobile components includea leading-edge slat, dual slotted flaps, oneaileron, and three airbrake panels.

EMPENNAGE

The aircraft empennage includes a horizontalstabilizer and a swept-back vertical stabilizer

(Figure 1-18).

The horizontal stabilizer supports the pitchcontrol surface through two elevators and twofairings. It has an adjustable angle of attack to provide for the pitch trim function.

The vertical stabilizer consists of a vertical finand a rudder which is hinged on the fin. Thefairings remain in contact with the verticalstabilizer, regardless of the horizontal stabi-lizer angle of attack.


AIRBRAKES

SLAT

AILERON

FLAPS

AIRBRAKES

SLAT

AILERON

FLAPSELEVATOR

RUDDER

NACELLES

Figure 1-18. Wings and Empennage


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Interior Lighting

The interior of the aircraft has lighting in thecockpit, passenger and crew areas, baggage

compartment, and service compartments. Thecockpit has glareshield lights, indicator andwarning lights, and overhead lights. The pas-senger area has illuminated switches and signs,aisle lighting, entranceway lighting, and read-ing lights. Baggage and service compartmentsare also illuminated.

Emergency Lighting

The Falcon 2000 has an emergency lightingsystem (Figure 1-23) in case of total power fail-

ure. This system illuminates the pilot’s andcopilot’s dome lights, passenger door and aislespotlights, the exit and emergency exit lights,and necessary signal signs.


RED ANTICOLLISIONLIGHT

LANDING ANDTAXI LIGHT

REAR NAVIGATIONAND ANTICOLLISION

WHITE LIGHT

BELLYANTICOLLISION

LIGHT (OPTIONAL)

RH NAVIGATIONGREEN LIGHT AND

ANTICOLLISIONWHITE LIGHT

LH NAVIGATIONRED LIGHT ANDANTICOLLISION

WHITE LIGHTFIN LOGO

LIGHTS(OPTIONAL)

EXTERIOREVACUATION

LIGHT

EXTERIOREMERGENCY

EXIT LIGHT

WING ICEDETECTION

LIGHTS

Figure 1-22. Exterior Lighting System


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E X I T

E X I T

E X I T

E X I T

E X I T

P U L L H E R E

T O

O P E N

E X I T

A I S L E L I G H T

A I S L E L I G H T S

E M E R G E N C Y

L I G H T I N G

B A T T E R Y P A C K

E

M E R G E N C Y

L I G H T I N G


P I L O T

D O M E L I G H T

C O P I L O T

D O M E L I G H T

P A S S E N G E R

D O O R

S P O T L I G H T S

A I S L E L I G H T

A I S L E L I G H T

E M E R G E N C Y E X I T

H A N D L E L I G H T

E M E R G E N C Y L I G H T I N G


E X I T

E X I T

F i g u r e 1 - 2 3

.

E m e r g e n c y L i g h t i n g S y s t e

m


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FUEL SYSTEM

Engine fuel is stored in wing tanks (Figure1-24). The tanks are sealed structurally and are

coated with protective paint. They containdrainage systems for defueling and evacuationof water. Total fuel capaci ty is 12,155 pounds.

Fuel is supplied to the engines a nd APU bybooster pumps and jet pumps. Crossfeedunits exist to balance fuel levels betweentanks, and supply fuel to an engin e from theopposite system in case of a pump failure.

The aircraft uses a pressure-refueling system,or it can be gravity-refueled. The cockpit hasswitches, lights, and electronic displays tocontrol and indicate conditions of the fuel

system. Switches are used to shut off fuel tothe engines if necessary. Lights indicate valvesthat are open, discrepancies between valveand switch positions, and low fuel levels.Electronic displays indicate fuel quantity,flow, and temperature data.


Figure 1-24. Wing Fuel Tanks


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AUXILIARY POWER UNIT

The aircraft is equipped with a Garrett GTCP36-150 (F2M) auxiliary power unit (APU) in-

stalled inside the tail cone. The functions of the APU include:

• Environmental control system airflow

• Main engine starting

• Electrical power supply

The cockpit, overhead panel, warning panel,maintenance panel, and EIED have specificsections for APU controls and indications.

POWERPLANT

The Falcon 2000 is equipped with two jet en-gines with dual flow, a front single-stage fan,

two spool turbines, and a mixer nozzle (Figure1-25). Thrust load is approximately 5,888pounds at 86˚F at sea level. The engines pro-vide a five-stage HP axial flow compressorfor quick acceleration and deceleration with-out compressor stall risks and to enhancefuel consumption control at all engine speeds.The engines are mounted on the airplane withfail-safe-type mounts on the front and rear.


IGNITION EXCITER

IGNITER PLUG

FAN SHROUD

FANSPINNER

ACCESSORY GEARBOX WITH (GENERATOR, HYD PUMP(s), OIL PUMPS, PMA)

AIR TURBINESTARTER

HYDRO MECHANICAL UNIT WITH FUEL PUMP AND FILTER

MIXERNOZZLE

IN-LINE COMBUSTION

FADEC

Figure 1-25. Engine


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FIRE PROTECTION SYSTEM

The f ire protection system consists of afire/heat/smoke detection system, warning

system and fire extinguishers.

Detection System

The detection system (Figure 1-26) consistsof fire detectors, overheat sensors and a smokedetector. The engines and APU have f iredetectors. Overheat sensors are located in theforward service compartment, landing gearwheel wells, and the nose cone avionics bay.A smoke detector is located in the baggagecompartment.

Warning SystemIf a fire is detected in the aircraft, an audiowarning is activated, and visual warnings ap-

pear on the fire control panel and/or warningpanel. The visual warnings indicate whichpart of the aircraft is affected so appropriatemeasures may be taken.

Extinguishing System

Aircraft fires can be extinguished by fire ex-tinguishers in each engine and APU com-partment and hand-held fire extinguisherslocated in the cabin and cockpit. Landing gearwheel well overheating may be eliminated byextending the landing gear.

PNEUMATIC SYSTEM

The pneumatic system supplies pressurized

air required by some aircraft systems andequipment. This is accomplished by bleed airfrom both engines or APU.


RH MAIN L/G COMPARTMENTOVERHEAT SENSOR

LH MAIN L/G COMPARTMENTOVERHEAT SENSOR

FSC OVERHEATPROBE

ENGINE FIRE 1DETECTOR

SMOKEDETECTOR

ENGINE FIRE 1DETECTOR

APU FIREDETECTOR

Figure 1-26. Fire and Smoke Detection System


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AIR-CONDITIONING SYSTEM

The air-conditioning system (Figure 1-28)maintains the cockpit, passenger cabin, bag-

gage compartment, and nose cone at a suitablepressure and temperature regardless of flyingconditions. The system consists of:

• Distribution system supplying the cock-pit and passenger cabin

• Cabin, nose cone, and baggage compart-ment pressurization system

• Environmental control unit supplyingconditioned air for temperature controlto the gaspers, EFIS, and various systems

according to the options available

Air-conditioning distribution contains foursystems, which route air to various usingpoints to obtain optimum air temperaturedistribution:

• Cockpit air-conditioning system

• Passenger cabin air-conditioning andfloor-heating system

• Cockpit and cabin recirculation system

• Cold-air system (air conditioning, cabinand cockpit gaspers, and EFIS cooling)

PRESSURIZATION

The pressurization system maintains a pres-sure inside the fuselage which is comfortablefor the passengers and crew regardless of theflying conditions. Two areas of the aircraftare pressurized.

The main pressurized area consists of thecockpit, passenger cabin, lavatory, and bag-gage compartment. This area is supplied by theair- conditioning system. The other pressur-ized area is the nose cone. It is slightly pres-surized in flight by an automatic control

system.

Pressurization can be maintained automati-cally or manually. In automatic mode, a pro-grammed pressurization law is followed toensure the nominal differential pressure is9 psi.

A warning system alerts the crew if the cabinaltitude pressure exceeds 10,000 feet or if there is a fai lure in the air recirculat ionautomatic closure system.


PASSENGERDOOR

HEATING PAX GASPERS

COCKPIT DUCTTEMP SENSOR

AIR-CONDITIONINGCOMPUTER

LAVATORYHEATING

PAX GASPERSCOCKPITTEMPERATURESENSOR

PILOT A/C

PILOTGASPER

COPILOT A/C

COPILOT GASPER

Figure 1-28. Air-Conditioning System


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HYDRAULIC POWER SYSTEMS

The hydraulic power system (Figure 1-29) iscomprised of a main hydraulic power supply

system and an auxiliary system.

Hydraulic power is used throughout the aircraftto control various systems. The main hydraulicpower supply consists of two independent, si-multaneously operating systems, designatedas the No. 1 and No. 2 hydraulic systems. Eachsystem draws hydraulic fluid from its respec-tive reservoir, pressurizes the fluid, and routesit to components of the user systems.

The No. 1 hydraulic system supplies pressur-ized fluid to components of the following:

• Flight control servo actuators

• Pitch Arthur variable bellcrank

• No.1 engine thrust reverser

• Slats (normal)

• No. 1 braking system with anti-skid

PUMPHYDR # 2

HYDR # TKPRESS

PUMP 1HYDR # 1

PUMP 2HYDR # 1

PRESS SWS

PRESS SW

PRESS SW

4. #1 STBY PUMP PRESS SW

5. #2 STBY PUMP PRESS SW

6. #1 HYDR SYS PRESS TRANSMITTER

7. PUMP 2 HYDR # 1 OVERPRESS RELIEF

8. PUMP 1 HYDR # 1 OVERPRESS RELIEF

1.

2.

3.

9.

10. #2 HYDR SYS PRESS TRANSMITTER

11. SYS 2 PUMP OVERPRESS RELIEF

PRESS SW

“IN FLIGHT”

ISOLATIONVALVE

“GRND TEST”

4

6

8

7

2

1

130 PSI

ENGINE 2

21 PSIA

5

10

11

9

3

#1 SYSTEMRESERVOIR

FUEL

SHUT OFF

TRANS

FUEL

SHUT OFF

TRANS

ENGINE 1

SELECTOR

LH ENGINE

#2 SYSTEMRESERVOIR

RH ENGINE

PMP1SYS1

PMP2SYS1

PMPSYS2

ENGINE #1 T/R (OPT)

PITCH ARTHUR< S/N 63

SLATS

BRAKING

L G & DOORS

NWS

EMERGENCY/ PARKING BRAKE

ENGINE #2 T/R (OPT)

AIRBRAKES

EMER SLATS

BRAKING

FLAPS

ROLLSERVO-ACTUATOR

PITCHSERVO-ACTUATOR

RUDDERSERVO-ACTUATOR

STANDBYPUMP

SUPPLY

SYSTEM #1PRESSURE

SYSTEM #2PRESSURE

STANDBY PUMPPRESSURE

LEGEND

AIRBRAKEHOLD DOWNACCUMULATOR

Figure 1-29. Hydraulic Power System


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• Landing gear

• Nosewheel steering

The No. 2 hydraulic system supplies pressur-ized fluid to components of the following:

• Flight-control servoactuators

• No. 2 engine thrust reverser

• Slats (emergency)

• No. 2 braking system with anti-skid

• Parking/emergency brake

• Flaps

• Airbrakes

The auxiliary hydraulic system operates as anautomatic emergency backup in case of fail-ure of the No. 2 hydraulic systems. It alsoprovides hydraulic supply for the pitch andrudder servoactuators.

Cockpit indicators exist to warn of hydraulicsystem problems.

LANDING GEAR AND BRAKES

Landing Gear

The landing gear consists of two main land-ing gears and a nose land ing gear. Each land-ing gear is a retractable tricycle-type fittedwith a dual-wheel arrangement (Figure 1-30).The nose landing gear retracts forward, andeach main landing gear retracts inboard. Doorsare provided for closure of the landing gear

wheel wells. The landing gears are electricallycontrolled, hydraulically actuated, and me-chanically locked. The landing gear system isillustrated in Figure 1-31.

The nose landing gear has nosewheel steeringcapabilities for taxiing with a turning radiusof 60˚ left or right of center.

Brakes

The braking system consists of a control unitassembly, a carbon (hot) section, and an antiskidsystem. The braking system is electricallycontrolled through the braking and steeringcontrol unit (BSCU), which determines thehydraulic pressure applied to the brakes. Aparking brake control al lows emergencynondifferential progressive braking.

The carbon wheel brakes consist of a doublehydraulic crown equipped with two separategroups of brake pistons. These are located inthe main landing gear wheels . They aresupplied with hydraulic power by two separatecircuits which may be used separately or

simultaneously.


Figure 1-30. Landing Gear and WheelWell Door


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FLIGHT CONTROLS

The aircraft flight controls are hydraulicallyboosted, nonreversible, and fully reversionary.The controls are hydraulically operated but,in case of total hydraulic failure, the aircraftcan be fully controlled.

In flight, the aircraft is controlled by thefollowing:

• Ailerons for roll control

• E l ev at o r s an d a m ob i l e h o r iz o n ta lstabilizer for pitch control

• Rudder for yaw control

• Leading edge slats and flaps for high lift

• Airbrake panels

• Flight environment data group

• Attitude and direction data group

• Inertial reference system

Ailerons

The two ailerons are controlled from thepilot’s and copilot’s control columns and areactuated through linkage rods (Figure 1-32).They can also be controlled by the autopilotservomotor.

Elevators

The two elevators control pitch from the pilot’sand copilot’s control columns through controllinkage rods actuating the servoactuator. Thepitch control uses an independent trim systemto set the horizontal stabilizer deflection angle.

Figure 1-31. Landing Gear System


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Rudder

The rudder is controlled from the pilot’s andcopilot’s control pedals through control link-

age rods actuating the rudder (Figure 1-33).The pedal assemblies may be adjusted to fit theheight of the pilot.

Slats

The two leading-edge slats are on the outersection of each wing. These provide properaerodynamic lift and flow.

Flaps

Each wing has two flaps for high lift which arecontrolled by the pilot. These are designed to

increase the aerodynamic lift during takeoff and landing phases.

Airbrakes

Airbrakes provide the aircraft with aerody-namic braking. There are six airbrake panelswhich are actuated by individual differentialactuators. There is no mechanical synchro-nization between the airbrakes.

RUDDERLINKAGE

RUDDERSERVO

RUDDERPEDALS

Figure 1-33. Rudder Controls


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CommunicationsThe communicat ions system al lows thecrewmembers to speak with each other, thepassengers, other aircraft, and ground radiostations. Radio frequencies can be changedmanually or preloaded and controlled by inputsfrom the flight management system.

The basic communication system includes avery high frequency (VHF) system, a publicaddress (PA) system, an interphone system,and an audio interface unit. Controls for eachsystem are located on the pilot’s and copilot’scontrol panels. Antennas for these systemsare located at various points on the aircraft, asillustrated in Figure 1-35.

T h e V H F sy s t e m p r o v i d e s sh o r t - r a n g ecommunication with ground and air radiostations. The PA system allows the crew tomake announcements to the passengers and

flight attendants. The interphone systempermits communication with the groundservicing personnel and cabin crews. Theaudio interface unit selects and controls thevarious aircraft audio signals.


VHF 2

VHF 1VHF 1

VHF 3

Figure 1-35. Antenna Locations


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OXYGEN SYSTEM

The aircraft has an oxygen system (Figure 1-36)to supply oxygen to the crew and passengers in

case of depressurization or in case smoke inthe cabin. The system is supplied by a high-pres-sure gas cylinder.

The crew oxygen system includes masks withintegrated regulators. The passenger systemi n c l u d e s m a sk s su p p l i e d w i t h o x y g e ncontrollers for high altitudes.


COPILOT MASK BOXWITH MASK INSTALLED

"EMERGENCY" TESTAND CONTROL KNOB

OXYGEN FLOWMETER INDICATOR

MIKE

HARNESS

PILOT OXYGEN MASK

PILOT OXYGEN

MASK BOX

COPILOT CONSOLE

COPILOT OXYGENMASK BOX

COPILOT OXYGEN MASK TO THERAPEUTIC SOCKETS

OXYGEN SUPPLY

OXYGEN CYLINDER

TO PASSENGEROXYGEN CONTROLLER

Figure 1-36. Cockpit Oxygen System


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INSTALLATION OF

MOORING LUGSUNDERNEATH WINGS

INSTALLATION OFMOORING LUG

AT FRONT JACKING POINT

TIEDOWN RING(AH21)

Figure 1-38. Parking and Mooring (Sheet 1 of 3)


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2-i

CHAPTER 2

ELECTRICAL POWER SYSTEMS

CONTENTS

Page

INTRODUCTION ................................................................................................................... 2-1

GENERAL............................................................................................................................... 2-1

DC POWER SYSTEM ............................................................................................................ 2-2

General ............................................................................................................................. 2-2

Distribution Buses............................................................................................................ 2-2

Protection ......................................................................................................................... 2-4

Control ............................................................................................................................. 2-4

Indication and Warning.................................................................................................... 2-6

BATTERY................................................................................................................................ 2-7

General ............................................................................................................................. 2-7

Ventilation ........................................................................................................................ 2-7Indication and Monitoring ............................................................................................... 2-7

Digital Battery Temperature Indicator ............................................................................. 2-8

Control ............................................................................................................................. 2-8

Operation.......................................................................................................................... 2-9

Battery Bus Circuits ......................................................................................................... 2-9

APU GENERATOR................................................................................................................. 2-9

General ............................................................................................................................. 2-9

Indication ....................................................................................................................... 2-12

Control ........................................................................................................................... 2-12

Operation ....................................................................................................................... 2-12




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GENERATORS..................................................................................................................... 2-12

General........................................................................................................................... 2-12

Indication ....................................................................................................................... 2-14

Control ........................................................................................................................... 2-14

Operation ....................................................................................................................... 2-15

EXTERNAL DC POWER..................................................................................................... 2-15

General........................................................................................................................... 2-15

Control ........................................................................................................................... 2-15

Protection....................................................................................................................... 2-15

Indication ....................................................................................................................... 2-15

Operation ....................................................................................................................... 2-18

DC POWER DISTRIBUTION.............................................................................................. 2-20

System Description........................................................................................................ 2-20

Bus-Tie Relays............................................................................................................... 2-20

Circuit-Breaker Panels ................................................................................................... 2-20

Battery Bus .................................................................................................................... 2-20

Avionics Masters............................................................................................................ 2-20

Automatic Load Shedding and Switching ..................................................................... 2-21

Normal Operation .......................................................................................................... 2-24

Abnormal Operation ...................................................................................................... 2-24

Non-Essential System Load Shed.................................................................................. 2-24

Revision 22-ii FOR TRAINING PURPOSES ONLY



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INTRODUCTION

This chapter describes the electrical power systems of the Falcon 2000 aircraft. All val-ues used for voltage, amperage, and tolerances are for illustrat ive purposes only. Actualvalues must be obtained from the manuals and publications issued by or on behalf of theairplane manufacturer, the certification agency of the country of origin, and the FederalAviation Administration.

GENERAL

The Falcon 2000 uses DC power for control,operation, and indication of the various sys-tems installed in the aircraft.

DC power is provided by two engine-drivenalternator-rectifiers and by a conventional 24-VDC nicad battery. The alternator-rectifierswill be referred to as “generators” for theremainder of this training manual. Electricalpower is also provided by an auxiliary powerunit (APU) and, on the ground, by a groundpower unit (GPU).

For power distribution, the electrical systemincorporates a multiple-bus system intercon-nected by relays, circuit breakers, and con-

tactors , which may be used to i sola te amalfunctioning bus or power source.

The Falcon 2000 is unique in that it does notuse conventional inverters to provide the 115-and 26-volt AC requirements of the aircraft.Equipment requiring alternating current con-tain integral inverters to provide the requiredcurrent. Solid-state inverters may be installedto satisfy various customer options.

# 1 S E R

V O

S Y S T E M

B A T T

H O T

B A T O F F

A C

G E N

# 1 D C

G E N

# 1 E N G

O I L P L

CHAPTER 2ELECTRICAL POWER SYSTEMS




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OVERHEADPANELS

CIRCUIT-BREAKERPANELS

ELECTRICAL CABINETS• CONNECTIONS• PCB• RELAYS

BATTERY

RECTIFIERALTERNATOR

(GENERATOR)

EXTERNALPOWERRECEPTACLE

APU STARTER-GENERATOR

MAINELECTRICALBOXESRECTIFIER ALTERNATOR

(GENERATOR)

GCU

Figure 2-1. DC Power Generation System

DC POWER SYSTEM

GENERAL

The DC power system of the Falcon 2000 is aconventional 24 to 28.5-volt system that hasfour power sources: one battery, two engine-driven generators, and an APU-driven startergenerator that may be operated in flight up to35,000 feet. The electrical system may also bepowered on the ground by a GPU.

The battery provides power primarily to startthe APU and acts as a surge damper for the gen-erators. It may also be a source of emergencyin-flight power for a limited period of time if

all generated power is lost.

Either of the engine-driven generators or theAPU generator is capable of powering theentire DC system and of providing battery

charging. As the CFE738 engines are air-started, electrical power is not needed forengine starting except to control the startsequence.

An approved GPU may be used for prolongedperiods to power the DC system to facilitatemaintenance and servicing. The GPU mayalso be used to start the APU but it cannot beused to charge the battery.

Figure 2-1 depicts the major electrical com-ponents of the DC power system and theirlocations.

DISTRIBUTION BUSES

DC power dis t r ibut ion is achieved by amultiple-bus system consisting of four majorbuses: battery bus, left main bus, essentialbus, and right main bus (Figure 2-2).


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G E N

1

B A T

G E N

2

F U E L 1

H O T B A T

L H

B U S

I S O L

R H

B U S

T I E D

F U E L 2

T H R U S T

R E V E R S E R

1

T H R U S

T

R E V E R S E R

2

A P U

F A U L T

A P

U

G E N

A P R

B A T T E R Y

A 1 B U S

A 2 B U S

A 3 W I N

D S H I E L D

A 4 C A B

I N

A C C O M

M O D A T I O N

T O V O L T M E T E R

L H / E S S

B U S - T I E R E L

A Y

E S S / R H

B U S - T I E R E L A Y

E S S E N

T I A L B U S


B 1 B U S

B 2 B U S

B 3 W I N

D S H I E L D

B 4 G A L

L E Y


S T -

B Y P U M P

LH MAIN BUS ESSENTIAL BUS RH MAIN BUS

T O A M M E T E R

T O A M M

E T E R

G E N E R A T O R 2

G

P U R E C E P T A C L E

A P U G E N

G E N E R A T O R 1

A P U S T A R T

C O N T A C T O R

G E N 1

C O N T A C T O R

A P U

C O N T A C T O R

B A T T E R Y

C O N T A C T O R

G P U

C O N T A C T O R

G E N 2

C O N T A C T O R

T O A M M

E T E R

T O A M M

E T E R

LH/ESS BUSTIE LOGIC

CIRCUIT

ESS/RH BUSTIE LOGIC

CIRCUIT

H R Z N

G E N 1 A P U B A T

A H S 1

G E N 1

A H S 2

0 2 0

2 5 3

0 3 0 0

2 0 0

4 0 0

4 5 0

1 0 0

1 0 0

0

V -

B A T

G E N

A -

3 0 0

2 0 0

4 0 0

4 5 0

1 0 0

1 0 0

0

A -

0 2 0

2 5

3 0

V -

B A T

G E N

A P U

B A T

G E N 2

E S S B U S

E X T P W R

F L I G H T

N O R M

D C S U P P L Y

R H B U S

L H B U S

BATTERY BUS

L I G H T S 2

L I G H T S 1 ( A N D M A I N C A B I N

D O O R C

L O S I N G

> S N 1 3 8 )

P

R E S S U R E R E F U E L

S L A T S

F I R E S O V

F I R

E E X T I N G U I S H E R S

4 P C O N T R O L

( A P U )

F i g u r e 2 - 2

. E l e c t r i c a l P o w e r S c h e m a t i c


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The DC distribution system is normally op-erated as independent left and right systems.The left system consists of the left main busand the essential bus, which are connected by

the normally closed LH/ESS bus-tie relay.

The battery bus is connected to the essentialbus by the battery contactor. The right systemconsists of the right main bus. The two systemsmay be connected, if required, by the normallyopen ESS/RH bus-tie relay.

The two bus-tie relays may be automaticallypositioned by system logic during certainoperations that will be discussed in detail laterin this chapter. Further, there are various au-tomatic and selective load-shedding features.

The buses and bus ties are contained in the LHand RH main electrical boxes located in theforward service compartment (Figure 2-3).

PROTECTION

Circuit protection is provided by conventionaltrip-free circuit breakers located above the

overhead panel (see Panel Poster). Feeder ca-bles to the sub-buses are protected by currentlimiters. Hall-effect current sensors detectexcessive reverse current flow to the powersources.

CONTROL

The electrical system is controlled by switcheslocated on the DC SUPPLY section of theoverhead panel (Figure 2-4). The engine gen-erators, APU generator, battery, and externalpower are controlled by switches that will be

covered in separate sections to follow. Thebus- t i e r e l ays a re con t ro l l ed by ro ta ryswitches.



GCU 2

LH MAIN

ELECTRICA

L

BOX

RH MAIN

ELECTRICA

L

BOX

GCU 1

APU GCU

BATTERY

FWD

Figure 2-3. Main Electrical Boxes


58/386



HRZN

GEN1 APU BAT

AHS1

GEN 1

AHS2

0

20

25

30

V-

BAT

GEN

0

20

25

30

V-

BAT

GEN

300

400

450100

100

0

A-

300

400

450100

100

0

A-

APU BAT GEN 2

ESS BUS

EXT PWRFLIGHT

NORM

DC SUPPLY

RH BUSLH BUS

0

20

25

30V-

BAT

GEN

300

400

450100

100

0

A-

0

20

25

30

V-

BAT

GEN

300

400

450100

100

0

A-

VOLTMETER

AHS 2PUSHBUTTON

EXTERNAL POWERSWITCHLIGHT

RIGHT BUS-TIEROTARY SWITCH

LEFT ESSENTIALBUS-TIEROTARY SWITCH

AHS 1PUSHBUTTON

HORIZONPUSHBUTTON

AMMETER ANDVOLTMETER

SELECTOR SWITCH

GEN 1SWITCH

APUSWITCH

BATSWITCH

GEN 2SWITCH

AMMETER

Figure 2-4. DC Supply Control Panel


59/386


60/386

BATTERY

GENERAL

A single 24-volt, 36-ampere-hour nickel-cadmium battery is mounted on the DC powerrack in the forward service compartment (seeFigure 2-3). The battery is connected directlyto the battery bus, which is connected to theessential bus through the battery contactor.The battery connection is a standard quick-disconnect adapter.

VENTILATION

The battery is always venti lated. On the

ground, ventilation is provided by a battery fan.The fan operates if the battery switch is on,ground proximity sensors detect an on-groundsituation, and the EXT PWR switch is off. Inflight, continuous ventilation is provided bya venturi airflow system that operates throughthe battery drain tube.

INDICATION AND MONITORING

The position of the battery contactor is indi-cated on the master warning panel by the BAT

annunciator. When the contactor is closed,the annunciator is extinguished and when it isopen, the annunciator is illuminated. Batteryvoltage and amperage readings are controlledby the GEN 1–APU–BAT selector switch.

When it is selected to the BAT position, the leftvoltmeter reads essential bus voltage and theleft ammeter reads the rate of battery chargeor discharge. A standard battery temperature

indicator is located on the copilot instrumentpanel (Figure 2-6). The indicator scale is color-coded as follows:

Red 160 to 190°F Hot

falcon 2000 ptm v2r2 mcd description des systemes

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