Bombardier-Challenger_01-Auxiliary_Power_Unit
1.
2.
3.
4.
5.
6.
GENERAL
APU CONTROL
START SYSTEM
SHUTDOWN
BLEED AIR SYSTEM
OIL SYSTEM
OPERATING MANUAL.
PSP 601A-6
SECTION 5
AUXILIARY POWER UNIT (APU)
TABLE OF CONTENTS
Page
1
2
2
2
3
3
Figure
Number
LIST OF ILLUSTRATIONS
Title
1 APU Controls and Indicators
2 Auxiliary Battery Panel
3 APU Fault Indications
Page
4
5
6
5 - CONTENTS
Page 1
Apr 10/95
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OPERATING MANUAL
PSP 601A-6
SECTION 5
AUXILIARY POWER UNIT (APU)
1. GENERAL
Airborne auxiliary power is supplied by a Garrett GTCP-36-100 (E) Auxiliary
power unit (APU) which supplies pneumatic and shaft power for essential
aircraft services independent of ground facilities. The unit is cleared for
in-flight start up to 20,000 feet, and is fully operational from sea level to
30,000 feet.
Clean compressed air produced by the APU is used for cabin and flight
compartment air conditioning on the ground, and ground and in-flight start of
engines. The shaft power is used to drive an electrical generator for supply
of ground electrical power and in-flight standby conditions.
The APU is mounted on a support skid assembly within a banadized aluminum
enclosure in the rear fuselage behind the rear pressure bulkhead. Access is
through the rear fuselage equipment bay door. The APU is self-contained and
requires only a source of fuel and dc electrical power.
Under normal operating conditions, fuel is provided under pressure from a
canister type pump mounted in the right main tank. Shrouded fuel lines pass
the fuel, through an APU fuel selector valve mounted between the wing and the
fuselage, to the APU fuel control unit. The APU fuel selector valve is
normally controlled by a START/STOP switch/light on the APU control panel, if
the PWR-FUEL ON/OFF switch/light is on. The valve will close automatically
to shut off fuel to the APU whenever the APU fire extinguishing system is
activated.
Under negative G conditions, to prevent an abnormal APU shutdown, fuel is
automatically supplied to the APU from the left main engine fuel supply. A
tap off in the left main engine fuel supply tube in the left pylon supplies
fuel, through a shutoff valve and check valve assembly, to a bulkhead
connector on the APU enclosure left wall. From the bulkhead connector, a
fuel tube connects with the main fuel inlet tube to the APU fuel control
unit.
Electrical power for starting the APU is provided by the aircraft internal
battery or by an external dc power supply.
An inlet duct located on the top rear fuselage provides entry for APU inlet
air. Ducting channels the inlet air through the enclosure roof to the APU
air inlet. APU exhaust gases are vented from the APU exhaust nozzle through
the enclosure side wall and, via ducting, to the APU exhaust outlet duct on
the right side rear fuselage.
On aircraft 5041 and 5146,
Ventilation air for the APU enclosure is drawn from outside ambient air
through an APU enclosure vent duct, mounted on the left side of the aircraft.
An APU CONTROL panel, located on the flight compartment overhead panel,
contains essential indicators and control switch/1iqhts. An APU FAULT panel.
located behind an access door on the left side rear fuselage, contains fault
flag indicators, a fault flag indicator IND RESET button and a remote APU
STOP button.
SECTION 5
Page 1
Aug 14/02
cacnhaadnaeinr cjer
OPERATING MANUAL
PSP 601A-6
APU CONTROL (Figure 1)
An electronic control unit (ECU) is mounted on the APU support beam on the
left of the APU enclosure. The ECU monitors engine speed, exhaust gas
temperature, oil pressure and temperature and overcurrent conditions during
APU operation. Signals from sensors on the APU are relayed through the ECU
to the appropriate indicators on the APU CONTROL and APU FAULT panels. The
ECU also shuts down the APU under certain fault conditions (refer to
paragraph 4.).
Fire protection is from a single Firex bottle mounted on the fuselage
structure outside the APU enclosure. Indication and control is from the
flight compartment (refer to SECTION 9, FIRE PROTECTION).
START SYSTEM (Figures 1 and 2)
28-volt dc power from the battery bus is required to start the APU and is
available from the battery alone, an external dc power source or whenever one
of the engine driven generators is on line. During start, 28-volt dc power
is also supplied by the APU auxiliary battery to the ECU. The auxiliary
power prevents automatic start shutdown that would otherwise occur during
cold weather starts if the ECU detected a large voltage drop on the battery
bus.
On aircraft 5001 to 5134,
cold weather starting of the APU is improved by the addition of an auxiliary
battery and by allowing the APU firewall shut-off valve to open when the APU
fuel pump is selected on. A panel is added to control the auxiliary battery
charger.
On aircraft 5135 and subsequent and aircraft incorporating Canadair Service
Bulletin 601-0418,
the electronic control unit for the APU receives a source of voltage from the
IRS battery No. 2 for improved cold weather starting.
The start cycle is initiated by pressing in the PWR-FUEL ON/OFF switch/light,
followed by the START/STOP switch/light on the APU control panel. The
PWR-FUEL ON/OFF switch/light energizes the APU fuel pump, completes an
electrical power supply circuit to the START/STOP switch/light, and opens the
engine-mounted fuel shut-off valve. When the START/STOP switch/light is
pressed in, the APU starter motor is energized and the STARTER legend on the
switch/light comes on. At 10% rpm, the ignition system is energized. At
60% rpm, the STARTER light goes out, indicating that the starter has
disengaged. At 95% rpm, ignition is de-energized and a green APU RDY light
on the START/STOP switch/light comes on. The engine accelerates to 100% rpm.
Normally, the engine accelerates to running rpm in not more than 60 seconds.
SHUTDOWN (Figures 1 and 3)
Normal shutdown of the APU is accomplished by removing all loads from the
unit, thpn prpssing nut thp START/STOP switrh/1ight on thp APU CONTROL panel .
When the APU has completely stopped, pressing out the PWR-FUEL ON/OFF
switch/light de-energizes the APU fuel pump and disconnects the electrical
power supply circuit to the START/STOP switch/light.
SECTION 5
Page 2
Apr 10/95
OPERATING MANUAL
PSP 601A-6
Remote APU shutdown is accomplished by pressing the APU STOP pushbutton on
the external APU FAULT panel- After a remote shutdown, the PWR-FUEL ON/OFF
switch/light and the START/STOP switch/light must be pressed out to reset the
APU starting system.
The APU electronic control unit shuts down the APU automatically for any of
the following reasons:
APU overspeed
Overcurrent
High exhaust gas temperature
Low oil pressure
High oil temperature
Generator adapter low oil pressure
Generator adapter high oil temperature
White triangle flag indicators on the APU FAULT panel show the fault
responsible for the automatic shutdown.
5. BLEED AIR SYSTEM
The APU supplies compressed air to the 10th stage bleed air manifold and
shaft horse power to drive the APU generator, which supplies the aircraft
electrical systems*
The BLEED AIR switch/light controls two valves: a surge valve, which
prevents compressor surge by bleeding off air i f there is excessive pressure,
and a load control valve, which opens to deliver the bleed air to the 10th
stage bleed air manifold.
After the EGT and rpm have stabilized and the green APU RDY light comes on,
bleed air may be selected by pressing in the BLEED AIR switch/light. The
surge valve then closes and the load control valve opens.
When bleed air is no longer required, the system is shutdown by pressing out
the BLEED AIR switch/light.
6. OIL SYSTEM
The APU engine oil system provides pressure oil and splash lubrication for
all drive gears and shaft bearings in the APU engine• If low oil pressure
occurs during APU operation, a low oil pressure switch, located in the engine
gearcase, transmits a signal and illuminates the LO PRESS light on the APU
CONTROL panel- Similarly, a high temperature switch, located near the oil
pressure switch, transmits a signal to illuminate the HI TEMP light. The APU
generator adapter has a self-contained oil system for lubrication and
cooling. Adapter oil LO PRESS and HI TEMP warning lights are also provided.
SECTION 5
Page 3
Apr 10/95
OPERATING MANUAL
PSP 601A-6
BLEED AIR SWITCH/LIGHT
i m. green OPEN light
comes on, load control valve opens
and APU air is available for aircraft
systems.
Whan pressed out, load control
van* cioaes arid OPEN fight goes
out.
Amber FAILED ight comes on if
load control vane fate to respond to
switch/fight commands or if engine
valve teas to dose.
NOTE
ON A/C 5135 and SUBS and
A/C POST SB 601-0394
the light data recorder system
records the opening and dosing
of the load control valve (LCV)
ADAPTBt OIL FAULT LIGHTS
Amber HI TEMP ight comas on to
trioleate generator adipter high oH
temperature. APU shuts down
eutomaoceJry.
Amber LO PRESS ight comes on to
indicate generator adapter low oil
pressure. APU shuts down
automaucatty.
PWR FUEL ON/OFF
SWITCH/LIGHT
When pressed in, fuel booster pump
is energized and power is connected
to START/STOP switch/light.
Amber PUMP INOP light comes on
when switch/tight is pressed and
fuel booster pump fads.
When preiiori out, fuel booster
pump is deenergnced and power is
removed from START/STOP
switch/ight.
K the APU FIRE PUSH switch/light
is pressed after a fire warning, the
fuel shutoff valve closes and diverts
fuel back to the tank. The white
SOV CLOSED light comes on.
START/STOP SWITCH/LIGHT
When pressed in. both APU fuel
feed system shutoff valves open,
starter motor s energized and amber
STARTER ight comes on. At 60%
rpm. amber STARTER light goes
out. At 96% rpm and 4 ± 1 :
later, green APU READY light
comes on.
When pressed out, APU READY
ight goes out. fuel solenoid valve
closes and APU shuts down.
APU OIL FAULT LIGHTS
Amber HI TQAP ight comes on to
indicate APU high oil temperature.
APU shuts down automatically.
onto
APU
Amber LO PRESS light
indicate APU low o2 pressure.
shuts down automatically.
EXHAUST GAS
TEMPERATURE
INDICATOR
ENGINE SPEED
INDICATOR
OVERHEAD PANEL
APU Controls and Indicators
Figure 1
SECTION 5
Page 4
Apr 10/95
OPERATING MANUAL
PSP 601A-6
FAIL LIGHT
Amber light comes on if auxiliary
battery is not providing 28 volt dc
output or if internal monitoring
detects a failure.
EJ
~ [ AUXILIARY BATTERY
FAIL I
ON I
I IRS I
1
I IRS I
2
IRS
3
| APUBATT/CHARGER FAIL
TA C
EFFECTIVITY: A/C 5001 TO 5134
ON LIGHT
White ON light comes on when
PWR FUEL ON/OFF switch/light is
pressed in to indicate that
auxiliary battery is providing
full 28 volt dc output to APU
start system.
AUXILIARY BATTERY CHARGER
FAILANNUNCIATOR
Comes on (amber) to indicate
that the lock-up battery is
not charging.
NOTE
IRS 2 auxilisry battery
powers the APU ECU
y<. ^\
b V
AUXILIARY BATTERY
I IRS I
1
APU BA"
II IRS I
2
nVCHARC
IRS
3
3ER FAI
",A q L II
EFFECTIVITY: A/C 5135 AND SUBS AND
POST SB 601-0418
COPILOT'S CONSOLE
Auxiliary Battery Panel
Figure 2
SECTION 5
Page 5
Apr 20/98
canactair
cftauentjer
OPERATING MANUAL
PSP 601A-6
APU OVERCURRENT FAULT FLAG
White triangles indicate overcurrent fault.
APU shuts down automatically.
APU OVERSPEED FAULT FLAG
White triangles indicate APU overspeed. APU
shuts down automatically.
APU EGT HIGH FAULT FLAG
White triangles indicate APU high exhaust
gas temperature. APU shuts down
automatically.
APU OIL PRESS LOW FAULT FLAG APU OIL TEMP HIGH FAULT FLAG
White triangles indicate APU low oil pressure
APU shuts down automatically.
White triangles indicate APU high oil
temperature. APU shuts down automatically.
GEN ADAPTER OIL PRESS LOW
FAULT FLAG
White triangles indicate generator adapter
low oil pressure. APU shuts down
automatically.
GEN ADAPTER OIL TEMP HIGH
FAULT FLAG
White triangles indicate generator adapter
high oil temperature. APU shuts down
automatically.
IND RESET PUSHBUTTON
Wher> pressed, fault flags are reset by
rotating them out of view. If condition has not
been corrected, flags stay in view.
APU STOP PUSHBUTTON
When pressed, stops APU at any time.
APU Fault Indications SECTION5
Figure 3 Page 6
ADr 02/87
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