Final Flashcards
takeoff weight
28,000
landing weight
23350
Ramp Weight
28120
Emergency Descent Items
Thrust Levers - close
Speed - Mmo/Vmo unless structural damage is suspected
Air Brakes - Open
Electrical Smoke/Fire
Crew Oxygen - don masks - 100% or emerg
Mic Selector - Oxy-Mic
Cabin Notices - ON
Engine Fire on Ground
Start PWR Switch(starting only) - Push For Abort
HP Cock (affected engine) - Close
LP Cock (affected engine) - close
ENG EXT (affected engine) - Shot 1
Double Eng Failure
Thrust Levers - Close
Crew Oxygen - Don Masks if above 15,000 FT
Mic Selector - Oxy-Mic if above 15,000 FT
Engine Indication - monitor
Vmo
ventral tank full
335
Vmo
ventral tank empty
280
Mmo
.8 mach
an over-voltage of ___ or higher will cause the GCU (generator control unit) to automatically open the GLC
32.5
What does the GCU do
provide output stabilization and load equalization
automatically switches from starter mode to generator mode
in generator mode, it will act as a voltage regulator
controls the generator by directly controlling the GLC (generator line contactor)
provides reverse current flow protection
Why are our batteries 24v but our system is 28v
The voltage all together needs to be greater so that the batteries can charge off of the extra voltage
How is the electricity in the electric system distributed
busses
How do we test the volts for our battery
the battery pushbutton connects ammeters to batteries to show the charge rate of the batteries.
it is hot-wired to the battery so there is no need to turn anything on. just turn a knob so that we are looking at it specifically.
What should our battery amps be at for takeoff
needs to be below 20 amps
GPU (ground power unit)
standard 3 pin, 28 volt DC ground power receptacle located on right rear fuselage
what is the only thing that can run everything with engines off
GPU
What information does the cabin triple indicator give us
cabin altitude
differential pressure
rate of change
Cabin pressure at FL 410
7500
8.55 PSI
How do we control cabin pressure
pressurization is achieved by supplying bleed air into pressure vessel and controlling the outflow
Max cabin pressure differential
8.55
Max Negative Cabin Pressure
-.5
Max Cabin Over Pressure
8.6-8.8
What is the limitation with engine bleed air ad APU bleed
can both be on for no more than 1 minute
What keeps the outflow valves open on the ground
venturi
when will the cabin high annunciator go off
9300 +/- 300
high datum - 14000 +/- 300
what color is the cabin high annunciator
red - it will set the master warning lights off
Will an annunciator extinguish after it has alluminated
yes, if the reason it went off goes away
what bus powers the MWS system
PE
3 ways and examples the aircraft talks to us
visually - annucniators
Audibly - bells and chimes
Tactically - stick pusher/stick shaker
how do we test all annunciators to max intensity
annunciator test button
Fuel pump types
Jet pumps - 4 - no moving parts - just moves fuel through the inner tank parts
Boost pumps- 2 - moves ventral fuel - helps move fuel from tanks to engine
engine driven - 2 - automizes fuel - if it dies we die
Boost pump locations
1 in each wing
max fuel imbalance
500 pounds in between the wings
What must be working for ventral tank transfer
boost pumps
stator vs compressor
stationary - stationary
compressor - rotating (rotary)
Why do we put the APR in armed position
activates when uncommanded split in N2 occurs of 15% or more
spool
twin stool engine (N1 and N2) compressor and turbine connected on a single shaft - we have 2
Axial Flow
low pressure compressor - 4 rows or compressors (spin/move) 4 rows of stators (stationary)
CZI vs MPI inspections
CZI - every 6000 hours - much more in depth and costly - complete disassembly of engine - compressor zone inspection - confused with overhaul
MPI - every 3000 hours - looks primarily at turbine section - a lot like a hot section - major periodic inspection
both are more complex than what they are associated with
For maximum T/O thrust what is the N1, N2, ITT and time limit
N1- 100
N2 - 101
ITT - 1022
5 minutes
what is on the accessory case
oil pump, fuel pump, starter generator, alternator, fuel control unit, hydraulic pump
when do we get notified the TKS fluid is low
30 minutes remaining
Vibrometer explianed
an electrical pulse is sent thorugh a probe making it vibrate. as you fly ice collects making the probe heavier and the vibrations slower. As it slows it talks to th aircraft saying ice is forming
Our icing system
rotary ice cutter on the forward left fuselage as ice forms it is being cut off causing the rotation to slow due to the friction. As this friction grows and the turn slows it talks to the airplane letting it know ice is forming
TKS anti-ice system
TKS fluid is pumped out of the front of the wings and the horizontal stabilizer
it is pushed over the wing and elevator by wind going over the surfaces preventing from ice build up
Hot wings
hot bleed air from engine is pushed to the front, top, and bottom of wings warming the surface of the aircraft and melting/ preventing ice on the surface
WIng boots
inflatable boots on the front of wings that after ice has formed you will inflate to knock already formed ice off of the wing
when will you get anti-ice low pressure system
low system pressure with pump on
what do the alternators do for anti-ice
2 engine driven alternators heat the windscreens-sidescreens - stall vanes electrically
Alternator 1 heats
left windscreen, right sidescreen, left stall vane
Alternator 2 heats
Right windscreen, left sidescreen, right stall vane
what does the fire annunciator tell us
something is very hot - just because it goes off does not mean there IS a fire
how do we choose which side our extinguishers go to
by choosing shot 1 or 2 on the engine ext button for the engine that is having the overheat/fire alarm
what does shot 2 run off of
PS2
at does shot 1 run off of
PE
where are the fire extinguisher shots located
aft equipment bay
when would we have the emergency brakes on
when we attempt to brake and have no braking authority
how do we turn the emergency brakes on
pull the wheel lever back 1 notch
Hawker Anti-Skid
only provided during normal braking
called maxaret
fully mechanical
wheels must be moving
lift dump limitations
must be on the ground
flaps must be “selected” 45
where does the APU get its fuel from
left tank at .5 gallon an hour
What does the APY do
provides power and bleed air on ground and in flight
who monitors the APU
it monitors itself
what happens for APU fire
APU overheat detector go off
fire bell and annunciator go off
single shot fire extinguisher can be set off by pilots or after 5 seconds after APU auto-shutdown due to overheating it will not automatically go off
Master supply valve
allows oxygen into entire oxygen system
pilots need it open/passengers neet it open
emergency passenger supply valve
deploys passenger masks manually
Cabin oxygen
supplies passengers with oxygen
knob located behind pilots head
Barometric Valve
supplies masks and oxygen to passengers at cabin altitude of 14500+/- 500 ft
The emergency escape hatch is on the ____ side, _____ window
Right; fourth
to recieve external power, the ground power unit must be plugged in to the ground power receptacle on the
right rear fuselage
This color annunciator indicates a condition that requires immediate crew action
red
electrical heating is provided for
forward static plates
pitot heads
windshields
when the cabin door is not in the fully locked position, microswitches connected to the master warning system illuminate the ___________ annunciator
yellow ENT DOOR UNLOCKED
the batteries will maintain essential service during a dual generator failure for
30 minutes minimum
the maximum battery amps for takeoff is
20 amps
when a generator si off-line and the GEN FAIL and ELECT look up annunciators are illuminated, the generator can be reinstated by
positioning the GEN switch to CLOSE for five seconds then releasing it
the battery-charging rate can be monitored by
Depressing the BATT ammeter pushboutton
for engine starting, the ground power unit must produce
28 volts, 1,500 amps with 1,100-amp current limiter
circuit breakers protecting unswitched PE circuits are marked to ease isolation in the event of smoke or fire with
a white background
when either the BATT 1 CNTCTR or BATT 2 CNTCTR annunciator illuminates it indicates that the respective
battery contactor or emergency contacctor is open
power for the EMERG-OFF-STORM switch (EMERG position) is controlled by the _____ bus bar
PE
the entry light switch is on the
left bulkhead sidewall
if the NO SMKG swithc is positioned in AUTO the NO SMOKING light illuminates when:
the nose gear locks down during extension
For normal operation, the EMERG lights switch on the roof panel should be positioned to
arm
the _______ switch provides circuit control for the instruments, pedestal lighting, and display panels
LTS MASTER
The MWS annunciator can be dimmed:
by pressing the face of either red MWS glareshield annunciator
With the exception fo the DUCT OVHT look up annunciator, the arrows on the center annunciator panel flashsers signify
that a roof panel annunciator is illuminated
the white annunciators indicate
completed operations and/or system status
the bus bar that powers the master warning system is
PE
the master warning flashing lights on the glare shield can be extinguished by
pressing the face of either red MWS annunciator
to illuminate all MWS annunciators at maximum intensity
press the ANNUN switch
to bypass the DIM circuit
position the DIM OVRD switch to OVRD
boost pumps are located in the
left and right wing tanks
when the ventral tank contains fuel, a low Vmo speed warning will sound whenever aircraft speed exceeds
280 kias
the maximum lateral imbalance permitted is
500 punds
with boost pumps inoperative
ventral tank fuel can not be transferred
if the ventral tank is to be used in flight, it must be full, and each wing must contain more than
3,450 pounds of fuel
the aircraft fuel sustem accepts a maximum refueling supply pressure of
50 psi
the function of the APU is to supply
bleed air and DC electrical power for ground operations and in flight operations
do not operate APU bleed air and marine engine bleed air simultaneously for longer than
1 minute
normal APU shut down is accomplished by
depressing the red STOP button on the APU control panel
the _____ supplies fuel for the APU
left main tank
the powerplant classification on Hawker 900 XP series aircraft is:
single-spool turbojet
When the aircraft is static on a standard day at sea level, each engine develops
4660 pounds of thrust
the primary overspeed rpm-limiting device on the 731 series engine is the:
mechanical governor in FCU
the maximum HP rotor (N2) overspeed is:
102% for 10 seconds
the maximum oil pressure for power at or above idle rpm without a time limit is
80psi
the maximum interturbine temperature for engine starting or relight is
994C
the maximum transient oil pressure permissible is
100psi
if the MWS reverser annunciator illuminates during the deploy cycle, it indicates
rudder bias not inhibited
to facilitate an accurate setting of climb power:
CLIMB in green displayed on the MFD engine display
the APR system is available
to any engine with an operative computer
engine fire bottles are in the
rear equipment bay
the exterior preflight check fo the fire extenguisher includes
Checking the condition of two engine discharge indicators
the engien fire bell can be silenced
by pressing the BELL CANCEL switch
which statement is true regarding discharge fo the fire bottles
When a visual fire warning appears, discharge SHOT 1 first. If necessary, then discharge SHOT 2.
the following bus bar(s) provide(s) DC power for engine fire extenguisher operation:
PE and PS2
a portable handheld fire extinguisher is stowed in the
cockpit
baggage compartment
for a fire in the APU:
a switch on the APU control panel controls the firing of a separate fire exinguisher
the APU fire extinguisher automatically discharges _____ seconds after the detection of the APU fire alarm
5
The HP bleed air supplements the LF bleed air at the mixing valve when both main air valves switches are selected to OPEN and:
LP bleed-air pressure drops to 27 psi
Prior to takeoff and landing, ensure that the flight deck valve and the main air valves are set to the _________ position
close
This occurs when a main air valve switch si moved from the CLOSE position to the LP ON position
the main air valve opens, but HP air augmentation is not allowed
the position fo the MAIN AIR VLV 1 or 2 switch in which electrical power is applied to a pressure switch is
OPEN
when placed in the “open” circuit, the No. 1 MAV has a time delay of approximately _____ before it reaches the fully open position:
20 seconds
the following component(s) is/are anti-iced by the use of hot bleed air
Engine inlet cowling
for takeoff or landing approach in icing conditions, the following switches must be turned on:
ENG IGNITION, ENG ANTICE, WING/TAIL ANTICE
the following switches provide DC power to the rudder bias heater muffs:
PITOT/VANE HEAT
the following statement is/are true
the engien inlet cowling is heated by bleed air
with the ENG ANTICE switch energized and the computer switch in AUTO, electrical power is supplied to heating elements don’t eh P2T2 sensor
when not in icing conditions, engine anti-icing must not be used or more than 10 seconds in ambient air temperatures above 10C
the ICE PROT look up annunciator on the MWS panel does not illuminate when
PITOT/VANE HEAT is on and operating normally
the following component may fail to operate satisfactorily when the left pitot heat is inoperative
ADC No. 1
the ENG 1 (or2) A/ICE annunciator (when illuminated) indicates:
that anit-icing air pressure is not available at sufficient pressure
The PITOT AMPS ammeter checks amperage of:
the left or right pitot heating elements (as selected)
the forward static plates are heated:
only when airborne
engine anti-icing si required, the ENG ANTICE switches should be turned on:
before takeoff power is set
the TKS fluid supply lasts for approximately
108 minutes
the airframe anti-icing system:
should be primed before flight
The following ICE PROTECTION switches shall always be switched on before takeoff and remain on throughout the flight:
PITOT/VANE HEAT and SCREEN HEAT
which component in the air conditioning system determines the temperature of the air after entering the water separator
low-limit temperature control
the duct temperature limiter senses a duct temperature of 116C:
the limiter illuminates the DUCT oVHT look up annunciator and automatically gives reduction in duct temperature
in delivery air temperature is controlled by operation of the:
Cabin temperature control valve
a pressure switch downstream of the PRSOV protects the ACM from overspeed if pressure rises above
40 psi
when too much air pressure is present, the 40-psi pressure switch protects the ACM from overspeed by closing:
the No. 2 main air vlave
the switch that controls the auxiliary heating valve to provide additional heating to the cockpit is the:
F/DK VLV switch
the ______ bus powers the CABIN TEMP-MANUAL mode
PE
the pressurization system is capable fo maintaining a cabin altitude of 7,500 feet when the airplane altitude is
41,000 feet
the pressurization system can maintain a maximum cabin differential pressure of
8.55 psi
the maximum allowable negatice cabin differential pressure is
-.5 psi
the fan-operated ventrui will provide suction to open:
both outflow valves
with the CABIN HIGH DATUM not selected the CABIN ALTITUDE warning annunciator illuminates and the warning horn sounds at __________________
9,300 +/- 300
if one hydraulic engine-driven pump fails:
the hydraulic pressure indicator will display 3,000psi, and the applicable low-pressure annunciator will illuminate
if both hydraulic engine-driven pumps fail:
indicated pressure is 2,300psi, and both low-pressure annunciators are illuminated
the main hydraulic reservoir is pressurized to prevent:
pump cavitation
the first step in operating the auxiliary hydraulic system is to:
pull the AUX HYD SYSTEM lever
the purpose of the pressure-maintaining valve in the main hydraulic system is:
to maintain 2,399 psi in the main accumulator for normal brake operation
if one hydraulic engine-driven pump fails:
the remaining pump is capable fo actuating all subsystems
inadvertent landing gear retraction on the ground is prevented by:
A solenoid-operated device engaging the selector lever.
when all landing gear are up and locked, position indications are:
no green or red annunciators illuminated
the main landing gear inboard doors are closed
when the gear is in either the extended with the auxiliary system
the landing gear warning horn will sound when:
the gear is not locked down with flaps selected to 25
the gear is not locked down with either power lever between 60% and 70% N1, and airspeed is below 150 knots
the gear is down and locked, the LANDING GEAR lever is not selected down, and start power is selected
an indication of landing gear down and locked (3 green annunciators) accompanied by 3 red annunciators indicates:
the LANDING GEAR lever is not in the down position and the landing gear is down and locked
if the nose gear does not lock down during extension, the indication is that:
the red N GEAR annunciator on the panel is illuminated, and the mechanical indicator on the pedestal is not extended
nosewheel steering with the gear retracted is prevented by:
a mechanically actuated hydraulic shut-off valve
The EMERG (or EMERG) BRK LO PRESS annunciator illuminates
When emergency brake accumulator pressure drops to 2,250 psi and below
Antiskid protection is available:
when braking is from the normal system
In order to select emergency brakes, the WHEEL BRAKE lever must be positioned:
to the first aft notch marked in red
the elevator trim tabs can be actuated:
mechanically and electrically
the purpose of the rudder bias system is:
to automatically counteract asymmetrical thrust due to engine failure
if takeoff is attempted with the aileron/elevator gust lock engaged:
only one throttle can be advanced to full power
the guard is removed from a pitch trim switch
during testing, to ascertain the trimming cannot be accomplished with one element of the switch
the flight control surfaces that are hydraulically actuated are:
flaps and airbrakes
asymmetrical flap operation is prevented by:
A synchronizing cable arrangement that isolates the hydraulic supply to the flap motor, stopping the flaps
the purpose of lift dump is:
to increase drag and decrease lift on the ground
stall warning is provided by:
the stick shaker
stall identification is provided by:
the stick pusher
in the stall warning and identification system:
Flap position is integrated with angle-of-attack signals to determine critical angle of attack of the wing
inadvertent stick pusher operation can be prevented by inhibiting
both channel 1 and channel 2 at the same time
the RUDDER BIAS annunciator extinguishes when:
Both RUDDER BIAS switches are on
engine indications are normally displayed on the:
pilot MFD
aircraft attitude and dynamic flight data are normally displayed on the:
pilot mfd
if one of the AFDs becomes unusable due to a failure, the same display can be moved to a different display unit by using the controls on the:
reversionary control panel
which of the following is not a lateral ode of flight guidance system
flight level change
RA MIN, BARO MIN, and V-speeds can be set manually in the ______ menu pages on the PFD
REFS
the display control panels are located
Above the PFD and MFD
If a PFD failure were to occur:
Power down the failed PFD by pushing the MFD REV switch. A composite PFD/MFD format will display on the MFD
