Systems 1 Flashcards
L and R FLTR BYPASS indicates
unfiltered fuel is being supplied to the engine
L F FLTR BYPASS indicates
a clogged left fuel filter
When the L F XFR PRESS LO annunciator illuminates before the fuselage tanks are empty a possible malfunction is
that the the left transfer pump has failed
If a wing fuel tank overpressure occurs during a climb
you should discontinue the climb
During flight with the R F FLTR BYPASS annunciator illuminated consider shutting down the right engine if
you observe erratic right engine operations
*With the amber L FUEL FEED annunciator illuminates,
*approximately 70 pounds (11 gallons) of usable fuel in the left fuel feed chamber
The L WG TK OV PRESS annunciator illuminates
if the left wing level-control pilot valve malfunctions during fuel transfer
Pressing the guarded LH ENG FIRE PUSH switch
closes the left fuel and hydraulic system valves
During engine failure or fire on takeoff you should not secure the engine until
reaching 400 feet AGL
clear of obstructions
Failure of the left engine with synchronization ON could result in
a roll back of up to 1.5% N1 in the right engine
After retarding the throttle to idle due to an engine fire indication during flight the ENG FIRE PUSH switch light goes out. You test the fire detect system and the system fails. You should assume
there is an engine fire and continue the boldface procedure/checklist
If the engine failure is accompanied by a loud bang and zero N2, what should you not attempt
do not attempt restart
The crew chief reports a flame in the left engine tailpipe on start. At the same time you see the LH ENG FIRE PUSH switch light. What should you accomplish?
the procedures for Engine Fire During Ground Operations.
Oil bypasses the filter to continue…
lubricating the engine if the oil filter becomes clogged with contaminants
TRT on takeoff:
700 for 5 minutes
MCT (Max continuos):
680
Max en route and landing wing fuel imbalance:
300lbs
Max takeoff and touch-and-go wing fuel imbalance:
100lbs
Max oil pressure for start in cold weather:
95psi for 90seconds
Max normal pressure
83psi
Min oil pressure above 60% N2
60psi
Min idle oil pressure
40psi
Engine start:
550-600 4sec, 600-700 2sec, 700-720 1sec
Transient ITT:
720 for 2 seconds max
N1 limit:
104% during normal operations
Idle N2%
52%
Max N2:
96%
Fan is connected to the fan turbine by
a shaft running through the center of the hollow impeller shaft
The speed of the engine fan is displayed as
is displayed by the N1 gauge
*Bypass airflow provides most of the
*engine thrust (at low altitude)
The turbofan engine core airflow provides
power to turn the low pressure turbine
The hydromechanical metering unit (HMU) ___ for engines
must be functioning for an engine to operate
The engine vibration indicator assists in
reporting excessive engine vibration trends
The engine vibration indicator displays
the relative level of vibration in both engines
With electronic fuel control (EFC) OFF do not attempt to turn the EFC ON with the throttle
above the NORM TO position
With electronic fuel control (EFC) failure, how should you move the throttle
move the throttle of the affected engine slowly in order to avoid engine compressor stalls
If the electronic fuel control (EFC) fails expect
loss of thrust
slow engine acceleration
Flight with the electronic fuel control (EFC) off can result in
carbon build up (coking) on the fuel nozzles
The electronic fuel control (EFC) provides
a refinement of the fuel control signals to the HMU
The engine ignition system provides a source of ignition from
engine flameout
icing condition problems
stall attitude problems
After takeoff, when ignition is not required, the ignition switches
should be set to the STBY position
Ignition switches should be placed in. the ON position for
takeoff, approaches and landings
With the ignition switches in STBY position, the igniters fire automatically when
the angle of attack system detects an approach to stall condition (and E?NGINE anti-ice on)
The engine synchronization system uses
the left engine as the master
The engines can be synchronized to
either fan or turbine speed
Engine synchronization should
not be used during takeoff and landing
Used oil is collected and returned to the oil pump by
two scavenger pumps on each engine
Oil is cooled by
exchanging heat with aircraft fuel
A popped fuel system circuit breaker should
not be reset
The fuselage quantity gauge receives its input from
probes in the:
mid fuselage
aft fuselage
aft cabin tanks
The fuel fuselage fuel indicator displays
the amount of fuel remains in all fuselage tanks
Low fuel quantity is indicated by the L or R FUEL LEVEL LO annunciator illuminating when
approximately 200 pounds (32 gallons) of usable fuel remain in the respective wing tank
During the fuel transfer process, gravity flow is used to move fuel from
the aft cabin in to the aft fuselage tank and then to the mid tanks
There are 4 fuel tanks located in
the fuselage of the T1-A
With the FUEL TRANS switch set to the AUTO position, the transfer pump operates continuously until
fuel in the mid tank is exhausted
the line pressure drops below 5 +- 0.5 psi
Fuel to the engines come directly from
the fuel feed chamber
Each wing tank contains
3 bays
During normal inflight operations, the BOOST PUMP switches remain in the
AUTO position
If the BOOST PUMP switches are in the AUTO position, the appropriate boost pump automatically activates when
the volume in the fuel feed chamber falls blow approximately 11 gallons
