F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
TABLE OF CONTENTS
DGT94085
02-49-00
PAGE 1 / 2
ISSUE 3
02-49 ATA 49 – AUXILIARY POWER UNIT
02-49-00 TABLE OF CONTENTS
02-49-05 GENERAL
Introduction
Sources
Equipment location
02-49-10 DESCRIPTION
Introduction
Description
Operating principle
APU systems
Distribution
02-49-15 CONTROL AND INDICATION
Control
Indication
02-49-20 SYSTEM PROTECTION
Circuit breakers
APU ECU protections
02-49-25 NORMAL OPERATION
Starting sequence
Shutdown
Limitations
02-49-30 ABNORMAL OPERATION
APU start with GPU
APU starting sequence failed
APU normal shutdown failed
APU overspeed
APU fire
CAS messages
DASSAULT AVIATION Proprietary Data
02-49-00
PAGE 2 / 2
ATA 49 – AUXILIARY POWER UNIT
TABLE OF CONTENTS
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
GENERAL
DGT94085
02-49-05
PAGE 1 / 4
ISSUE 3
INTRODUCTION
The Auxiliary Power Unit (APU) allows the Falcon 2000EX airplane to be self-supported
(providing electrical power and bleed air) during ground operations especially at remote
locations where ground servicing equipment may not be compatible or available.
It also provides backup electrical power and main engine starting bleed air in flight.
DASSAULT AVIATION Proprietary Data
02-49-05
PAGE 2 / 4
F2000EX EASY
ATA 49 – AUXILIARY POWER UNIT
CODDE 1
GENERAL
ISSUE 3
DGT94085
APU circuit breaker
APU fire
DC supply
overhead panel
APU control panel
CAS window
ENG synoptic
ENG-TRIM-BRK
window
FIGURE 02-49-05-00 FLIGHT DECK OVERVIEW
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
GENERAL
DGT94085
02-49-05
PAGE 3 / 4
ISSUE 3
SOURCES
The APU inputs are independent of all installed airplane systems except for the electrical
power source used during starting and fuel supply from the airplane fuel tanks.
ELECTRICAL POWER
APU starting requires
supplied either:
FUEL
electrical
-
by battery 1 through the battery bus,
-
by a Ground
ESSential bus.
Power
Unit
via
power
Fuel is supplied to the APU by the No. 2
engine fuel feed line.
the
¾ Refer to CODDE 1 / Chapter 02 / ATA 28
EQUIPMENT LOCATION
FIGURE 02-49-05-01 APU LOCATION
The APU is longitudinally mounted underneath the fin, inside the tail cone.
DASSAULT AVIATION Proprietary Data
02-49-05
PAGE 4 / 4
ATA 49 – AUXILIARY POWER UNIT
GENERAL
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
02-49-10
ATA 49 – AUXILIARY POWER UNIT
PAGE 1 / 4
DESCRIPTION
DGT94085
ISSUE 3
INTRODUCTION
The Falcon 2000EX incorporates an APU model GTCP36-150 (F2M) manufactured by
Honeywell. The unit is longitudinally mounted in the tail cone within a carbon fireproof
compartment. The APU is certified for both ground and in-flight operations.
DESCRIPTION
The APU consists of an air intake, located in the middle of the unit, a centrifugal compressor
and its discharge port for bleed air, a combustion chamber, a single stage turbine, an exhaust
duct and an accessory section. The accessories include the APU fuel control unit, the fuel
pump, the oil pump and the starter-generator.
APU
bleed air
valve
Upper left
compartment
inlet ventilation
Air intake door
Gearbox
Generator
inlet ventilation
Exhaust duct
Starter generator
Compressor
Generator outlet
ventilation
Lower right
compartment
inlet ventilation
Firewall
FIGURE 02-49-10-00 APU LAYOUT
DASSAULT AVIATION Proprietary Data
02-49-10
F2000EX EASY
ATA 49 – AUXILIARY POWER UNIT
PAGE 2 / 4
CODDE 1
DESCRIPTION
ISSUE 3
DGT94085
Air inlets are located on the right and left hand side of the tail cone.
Two air scoops on tail cone (upper LH and lower RH sides) provide APU compartment
ventilation.
The engine air intake door is located on the right hand upper side of the APU compartment.
The APU exhaust duct for engine gases and ventilation circulation is located at the rear of the
cone.
The APU generator has its own ventilation system. The air flows through a duct from the LH
inlet ahead of the tail cone. The RH outlet below the APU air intake allows for exhaust of APU
generator ventilation system.
A door opens on LH side for APU oil filling.
LH ventilation scoop
APU generator inlet
APU engine exhaust
Oil filler door
APU generator
exhaust outlet
APU air intake door
RH ventilation scoop
FIGURE 02-49-10-01 EXHAUST OUTLET AND AIR INLET
The hot bleed air necessary for main engine start and air conditioning is tapped from
compressor discharge.
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 49 – AUXILIARY POWER UNIT
CODDE 1
DESCRIPTION
DGT94085
02-49-10
PAGE 3 / 4
ISSUE 3
OPERATING PRINCIPLE
The starter-generator first drives the APU. Once APU speed has reached 5.6% N1, the fuel
induction begins and ignition is turned on. At 50% N1, energy extracted from exhaust gases is
sufficient to drive the compressor and the starter operation is terminated. When the engine
reaches 99% N1, ignition is terminated.
APU stabilizes to regulated N1 (below 106%). The stabilized exhaust gas temperature (EGT)
may vary depending on whether hot air is taken or not for air conditioning and on the ambient
air temperature. The engine then operates on a cycle of continuous induction, compression,
combustion and exhaust at a constant rpm.
In flight, airbrakes extension (position 2) may induce an increase of around 20°C EGT.
When APU BLEED AIR is selected, bleed air is available for engine start or air conditioning.
The APU generator self-connects to the ESS bus. When the APU generator is on line, LH,
ESS and battery buses are powered, BAT 1 is charging. Depending on bus tied rotary switch
position, the same applies to right side buses and BAT 2.
If the start relay fails to open, the amber STARTER APU
message appears in
the CAS message window.
If APU generator fails to connect, the amber APU GEN
message is then
displayed in the CAS message window.
APU SYSTEMS
OIL SYSTEM
The oil system provides cooling and lubrication of the main rotor bearings and accessory
gearbox.
A switch located downstream from the oil system indicates when oil pressure decreases
below the minimum operating value. If so, the APU is automatically shut down.
A thermostat, inside the oil sump, controls the temperature. If oil temperature exceeds the
maximum operating value, the APU is automatically shut down.
An electrical level measuring plug is fitted on the APU oil tank filler cap. The APU OIL status
can be checked on the TEST synoptic before APU start.
Filler cap
Measuring plug
FIGURE 02-49-10-02 APU OIL FILLER PORT
DASSAULT AVIATION Proprietary Data
02-49-10
PAGE 4 / 4
ATA 49 – AUXILIARY POWER UNIT
DESCRIPTION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
FUEL SYSTEM
Fuel is supplied to the APU by the No 2 engine fuel feed line through the fuel supply shut-off
valve. The APU fuel system features a bypass filter and a high pressure gear pump. A
solenoid shut-off valve permits the system to command APU shut-off in case of failure
detected by the APU Electronic Control Unit (APU ECU).
The fuel flow is controlled by the ECU to fit the different APU operation phases and loads.
IGNITION SYSTEM
The APU incorporates a high-energy ignition system consisting of a two-way exciter box,
and dual cable and dual igniter plug in the combustion chamber.
The ignition system is entirely controlled by the APU ECU. The ignition is started at 5.6% N1
and continues until N1 reaches 99%.
APU ELECTRONIC CONTROL UNIT (APU ECU)
The APU Electronic Control Unit (APU ECU) is located in the forward servicing
compartment.
It provides for automatic management of APU performance and safeties during starting,
operation and shutdown phases. APU ECU monitoring uses N1 signal generated by a
magnetic sensor mounted on the accessory gearbox and an EGT signal generated by the
single thermocouple probe installed in the APU exhaust duct.
The speed governing loop continuously monitors N1 and modulates fuel flow (timedacceleration during starting of the engine or control during self-sustaining operation).
The control speed is 105% N1 in flight above 6,000 ft for main engine starting, otherwise
102% N1.
The temperature loop is not active during APU starting or normal operation unless EGT
exceeds the maximum operating value.
DISTRIBUTION
APU GENERATOR
The starter-generator of the APU is rated at 9 kW (300A) to supply the airplane systems with
28.5 VDC and is regulated by an associated Generator Control Unit (GCU) mounted in the
forward servicing compartment. Its excitation circuits are fed when APU generator trip
magnetic switch is set to upward position.
It is capable of supplying the entire DC electrical system in addition to charging batteries.
BLEED AIR
The APU bleed air is driven through a BLEED AIR valve to the pneumatic system.
For main engine starting, the valve is fully open.
When used for air conditioning, the APU ECU controls the valve to obtain the desired cabin
temperature.
¾ for more information, refer to CODDE 1 / Chapter 02 / ATA 21.
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
CONTROL AND INDICATION
DGT94085
02-49-15
PAGE 1 / 8
ISSUE 3
CONTROL
Status
lights
Pushbuttons
FIGURE 02-49-15-00 APU CONTROL PANEL
Two-position APU generator trip magnetic switch
FIGURE 02-49-15-01 OVERHEAD PANEL DURING NORMAL IN-FLIGHT CONFIGURATION
DASSAULT AVIATION Proprietary Data
02-49-15
ATA 49 – AUXILIARY POWER UNIT
PAGE 2 / 8
CONTROL AND INDICATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
CONTROL
FUNCTION
-
-
TO ACTIVATE
TO DEACTIVATE
powers the APU if the
ON light is off (APU not
running and not
powered)
push to
power
before
start-up
deactivates the APU if
the ON light only is on
(APU only powered
and not running)
push to
deactivate
or stop
APU
SYNOPTIC
Empty windows
N1 and EGT values
(ENG synoptic and
ENG window of PDU)
-
abnormal APU stop
-
initiates APU starting
sequence when the
ON light only is on
-
initiates APU shutdown
when both ON and
RUN lights are on
(APU running)
ON
flashing
push to
start
push to
stop
DASSAULT AVIATION Proprietary Data
F2000EX EASY
02-49-15
ATA 49 – AUXILIARY POWER UNIT
CODDE 1
PAGE 3 / 8
CONTROL AND INDICATION
DGT94085
ISSUE 3
CONTROL
FUNCTION
TO ACTIVATE
TO DEACTIVATE
SYNOPTIC
contactor
closed
(Z< 35,000)
-
connects the APU
generator to the ESS
bus
-
allows excitation of
APU generator
-
trips automatically to
down position when
the GCU detects an
over-voltage
-
Connected
contactor
closed
(Z> 35,000)
contactor
open (APU
stopped or
GPU is on)
acts as a reset switch
when the fault is
cleared (only one reset
attempt is allowed)
Disconnected
DASSAULT AVIATION Proprietary Data
Abnormal
situation:
contactor
open with
APU running
and no GPU
02-49-15
PAGE 4 / 8
ATA 49 – AUXILIARY POWER UNIT
CONTROL AND INDICATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INDICATION
As the APU supplies electrical power to the airplane, APU electrical indications can be
displayed in the ELEC synoptic of the lower 2/3 MDU window. This page indicates APU
generator status and the corresponding ammeter measurement.
FIGURE 02-49-15-02 ELECTRICAL SYNOPTIC INDICATION, APU RUNNING
FIGURE 02-49-15-03 APU GENERATOR SYMBOL
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
CONTROL AND INDICATION
DGT94085
02-49-15
PAGE 5 / 8
ISSUE 3
The ammeter indicates normal operating values or abnormal values using the following rules.
Normal values
appear in green
Abnormal
values appear
in amber
Invalid data
FIGURE 02-49-15-04 APU GENERATOR AMMETER
For the APU generator, the analog ammeter and digital readout are only displayed when the
APU is running. The amber scale and associated indication range depend on the airplane
altitude.
APU engine parameters are only displayed when APU MASTER is ON, at the top RH corner
of the ENG synoptic and at the bottom of the ENG-TRM-BRK window. N1 (%) and EGT (°C)
are displayed as digital readouts. In case of failure, amber labels are displayed near APU
parameters: OVSP , OIL , BLEED and DOOR .
FIGURE 02-49-15-05 ENG SYNOPTIC
DASSAULT AVIATION Proprietary Data
02-49-15
PAGE 6 / 8
ATA 49 – AUXILIARY POWER UNIT
CONTROL AND INDICATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
FIGURE 02-49-15-06 ENG-TRM-BRK WINDOW
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
CONTROL AND INDICATION
DGT94085
02-49-15
PAGE 7 / 8
ISSUE 3
In the TEST synoptic of the MDU lower 2/3 window, APU OIL status can be obtained. The
system indicates:
-
if APU OIL level is ok ( LEVEL OK message, see figure below), or
-
if APU OIL level is too low ( ADD APU OIL ), or
-
if the oil data is invalid ( TEST FAIL ).
FIGURE 02-49-15-07 LOWER MDU TEST SYNOPTIC
An hourmeter, located in the aft servicing compartment, records APU operating time. It
automatically begins to record 4 sec after the APU engine N1 reaches 99%.
DASSAULT AVIATION Proprietary Data
02-49-15
PAGE 8 / 8
ATA 49 – AUXILIARY POWER UNIT
CONTROL AND INDICATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 49 – AUXILIARY POWER UNIT
CODDE 1
SYSTEM PROTECTION
DGT94085
02-49-20
PAGE 1 / 2
ISSUE 3
CIRCUIT BREAKERS
APU ECU circuit protection is provided by a conventional trip-free circuit breaker located
above the overhead panel.
FIGURE 02-49-20-00 OVERHEAD CIRCUIT BREAKER PANEL
APU ECU PROTECTIONS
The APU ECU incorporates comprehensive protection, which automatically shuts down the
unit and triggers the APU FAULT
CAS message when any of the following
conditions is met:
-
overspeed (110% ± 1%),
loss of N1 signal,
wrong position of APU air intake door,
APU ECU failure,
loss of DC power,
slow start (starting phase control),
speed drop.
The extra following conditions are also activated providing that in-flight dual engine failure
does not occur (in order to keep APU running in such an event):
-
EGT overheat (see next section, LIMITATIONS),
loss of EGT signal,
low oil pressure (below 31 psi though N1 above 99% for more than 10 sec),
high oil temperature (oil temperature in the sump above 163°C),
electrical fuel flow regulator failure,
APU fire,
air conditioning overheat.
DASSAULT AVIATION Proprietary Data
02-49-20
PAGE 2 / 2
ATA 49 – AUXILIARY POWER UNIT
SYSTEM PROTECTION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
NORMAL OPERATION
DGT94085
02-49-25
PAGE 1 / 4
ISSUE 3
STARTING SEQUENCE
The APU can be started using either airplane battery 1 or an external ground power unit.
On ground, the battery start is the usual operating mode. GPU start is detailed in the
ABNORMAL OPERATION sub-section.
Prior to starting the APU, the oil level must be checked as well as the security area.
Pushing the APU MASTER pushbutton turns the ON light on (steady green once air intake
door is open). APU ECU is powered.
Pushing the START / STOP pushbutton initiates the automatic start sequence and
automatically starts the stand-by No 2 booster pump. The RUN light then illuminates for
approximately 5 sec to indicate that the command is taken into account (steady green). It
extinguishes during APU starting (about 20 sec; BAT 2 symbol is displayed in gray on the
ELEC synoptic). When APU start is successful (generator on line), it illuminates again and
remains illuminated until the APU is stopped.
As long as the RUN remains illuminated, the starting sequence is successful. The engine
parameters can be monitored on the ENG-TRM-BRK window. N1 and EGT can be checked
while increasing up to approximately 101% for N1 and 400°C for EGT.
The electrical parameters can be checked on the ELEC synoptic before connecting
equipment.
The following examples show controls and indications displayed to the pilots during normal
ground operation of the APU.
FIGURE 02-49-25-00 APU CONTROL PANEL
DASSAULT AVIATION Proprietary Data
02-49-25
PAGE 2 / 4
ATA 49 – AUXILIARY POWER UNIT
NORMAL OPERATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
FIGURE 02-49-25-01 ELEC SYNOPTIC
FIGURE 02-49-25-02 LOWER ENG-TRM-BRK WINDOW
FIGURE 02-49-25-03 ENG SYNOPTIC
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
NORMAL OPERATION
DGT94085
02-49-25
PAGE 3 / 4
ISSUE 3
SHUTDOWN
The APU incorporates an automatic and manual shutdown system that is controlled by the
APU ECU and corresponds to the abnormal conditions detailed in the SYSTEM
PROTECTION section.
Pushing the START / STOP pushbutton closes the APU fuel shut-off valve, the APU STARTSTOP green RUN light flashes for 2 sec then extinguishes.
Pushing the APU MASTER pushbutton while ON light is steady green stops electrical power
to the APU ECU. The ON light extinguishes when the air intake door is closed.
NOTE 1
When the APU is shut down using the STOP pushbutton, or if automatic shutdown occurs, the
APU cannot be restarted unless the MASTER pushbutton is momentarily unlatched and
latched again (pushed twice).
NOTE 2
Due to APU ECU shutdown logic, a transient amber OVSP label is displayed.
DASSAULT AVIATION Proprietary Data
02-49-25
PAGE 4 / 4
ATA 49 – AUXILIARY POWER UNIT
NORMAL OPERATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
LIMITATIONS
The APU is certified for in-flight and ground use. Operation of the APU is not authorized
without supervision.
Maximum N1 speed : 110%.
Exhaust gas temperature limit (EGT):
-
-
Starting:
o
below 50% N1: between 870°C and 988°C, less than 10 sec,
o
above 50% N1: between 690°C and 870°C, less than 10 sec,
Stabilized: 690°C. EGT.
NOTE
The duration of operation on amber range (690°C to 746°C) must be as short as possible.
Maximum generator output:
-
transient: 350 A, less than 60 sec,
-
stabilized (amber range display automatically changes):
o
300 A below 10,000 ft,
o
250 A between 10,000 ft and 25,000 ft,
o
200 A above 25,000 ft.
DASSAULT AVIATION Proprietary Data
F2000EX EASY
CODDE 1
ATA 49 – AUXILIARY POWER UNIT
ABNORMAL OPERATION
DGT94085
02-49-30
PAGE 1 / 4
ISSUE 3
APU START WITH GPU
Prior to initiating the APU start cycle, the GPU must be plugged in and operating. When the
EXT POWER light pushbutton is illuminated, the following occurs:
-
batteries No.1 and 2 are isolated,
-
the battery bus, the ESS, right and left buses are powered by the GPU (buses are
automatically tied),
-
APU generator is inhibited.
Pushing APU MASTER pushbutton powers the APU ECU, opens the air intake door, opens
APU fuel supply valve and illuminates the ON light.
Pushing APU START / STOP pushbutton initiates the starting sequence. This sequence is the
same as the battery starting sequence except for BAT 1 contactor which close during the
sequence, its symbol turning from gray to green on ELEC synoptic.
Until EXT POWER is depressed, GPU generator continues to power the distribution system,
inhibiting all generators, including APU, BAT 1 and BAT 2 (gray symbols).
Since the engine speed is above 99% N1, APU bleed air is available for the air conditioning
system.
APU STARTING SEQUENCE FAILED
If the APU fails to start when the START / STOP pushbutton is used, the RUN light does not
illuminate and the ON light of the MASTER pushbutton flashes.
APU NORMAL SHUTDOWN FAILED
If the APU fails to shut down when the START / STOP pushbutton is pushed, an alternate
method is also available. Pushing the APU MASTER pushbutton turns off the ON light and
cuts off power to the APU ECU causing the APU fuel shut-off valve to close.
NOTE
This condition should be written up as a maintenance follow-up action. This problem may be
associated with the APU ECU automatic shutdown logic.
DASSAULT AVIATION Proprietary Data
02-49-30
PAGE 2 / 4
ATA 49 – AUXILIARY POWER UNIT
ABNORMAL OPERATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
APU OVERSPEED
In case of APU overspeed, the APU shuts down automatically.
FIGURE 02-49-30-00 ENG SYNOPTIC
FIGURE 02-49-30-01 ENG-TRM-BRK WINDOW
DASSAULT AVIATION Proprietary Data
F2000EX EASY
ATA 49 – AUXILIARY POWER UNIT
CODDE 1
ABNORMAL OPERATION
02-49-30
PAGE 3 / 4
DGT94085
ISSUE 3
APU FIRE
The fire warning activates the warning horn, causes the illumination of the corresponding
guarded
FI RE
AP U
pushbutton on the overhead control panel and displays the
CAS
message.
Pressing the
FI RE
AP U
pushbutton automatically shuts down the APU and shuts off the APU fuel
valve. Pressing the
DI SCH
pushbutton causes discharge of the single APU fire extinguisher
cylinder dedicated to this area.
¾ For more information, refer to CODDE 1 / Chapter 02 / ATA 26.
CAS MESSAGES
CAS MESSAGE
DEFINITION
FIRE APU
Fire detected on APU
APU CMPTR FAULT CODE
APU ECU fault (parking)
APU FAULT
APU fault detected by APU ECU
APU FIRE DETECT FAIL
APU fire detection system failure
APU GEN
APU generator not connected with APU running
STARTER APU
APU on and starter still active
APU CMPTR FAULT CODE
APU ECU fault (cruise)
APU GEN FAIL
On ground, APU contactor failed to open
DASSAULT AVIATION Proprietary Data
02-49-30
PAGE 4 / 4
ATA 49 – AUXILIARY POWER UNIT
ABNORMAL OPERATION
ISSUE 3
F2000EX EASY
CODDE 1
DGT94085
INTENTIONALLY LEFT BLANK
DASSAULT AVIATION Proprietary Data