Systems oral Flashcards
(34 cards)
When does the Cross Bus Tie open automatically?
-Glide slope capture with flight director or autopilot selected to ILS approach. This isolates the DC busses and prevents failures of one DC bus from affecting both Nav receivers and flight control computers.
-BUS TRANSFER switch selected to OFF.
Proximity switch electronic unit (PSEU) illuminated.
On ground:
-Fault is detected in PSEU, or
-An overwind exit flight lock fails to disengage when commanded.
In flight:
-inhibited from thrust lever advance for takeoff until 30 seconds after landing.
TAKEOFF CONFIG light illuminates:
-as throttles are advanced if the aircraft is not correctly configured for takeoff.
-simultaneous with aural warning intermittent hot for TAKEOFF CONFIGURATION alert.
-trim
-flaps
-parking brake
-speed brake handle down
-speed brakes on the wing are down
CABIN ALTITUDE light illuminated:
-illuminates when cabin altitude exceeds 10,000 ft.
-activation is simultaneous with aural warning intermittent horn for CABIN ALTITUDE alert.
-Extinguishes when cabin altitude drops below 10,000.
MACH AIRSPEED WARNING TEST switches
Push tests respective Mach/airspeed warning system.
-clacker sounds.
-inhibited while airborn.
STALL WARNING TEST Switch
On ground with AC power available:
-Tests Stall Management Yaw Damper (SMYD) computer No. 1 & 2.
- # 1 SMYD shakes captains control column.
- # 2 SMYD shakes FO’s control column.
- Vibrations can be felt on both columns. Inhibited airborne.
Landing Gear Warning Cutout switch:
Silences landing gear configuration warning aural indication at flaps up through 10 and above 200ft RA.
-aural wanting cannot be silenced at flaps greater than 10.
SPEED TRIM FAIL
Indicates failure of speed trim system.
Auto trims: 10 seconds after takeoff, high power, low gross weight, aft CG (things that would make the plane pitch up)
Inhibited for 5 seconds whenever trim is manually activated.
AUTO SLAT FAIL light:
Indicates failure of the auto slat system.
Talk about the PTU.
IRS panel:
ALIGN light:
-Illuminated: the related IRS is aligning or shutdown cycle.
-Flashing: Couldn’t align because you didn’t put in a position, you put in the wrong position or the plane had excessive movement during the align.
ON DC: Means you are on DC power (bad). If on the ground horn in nose wheel will sound. After 5 mins the right side will shut off to reduce use of battery.
-momentarily illuminates during alignment self-test.
FAULT: Fault in system.
DC FAIL:
Engine panel and EEC
REVERSER light:
ATIS:
-Auto restow circuit has been activated.
-Thrust reverser sleeve not in commanded position
.-Isolation valve is not in commanded position.
-shaft lock failure.
Electronic Engine Control (EEC) switches.
-ON light: normal control mode is selected.
-ALTN : Has been switched to alternate manually.
-Both ON and ALTN: Autoswitched to soft alternate mode.
ENGINE CONTROL light:
-Internal faults, none dispatch able.
-Light operates with engine operating, airplane on ground, below 80 knots or approx 30 seconds after touchdown.
Window heat panel:
ON light:
Green: heat is being applied to window.
Extinguished:
-Switch is OFF, or
-Overheat detected.
-System failure occurred.
-System at correct temp.
OVERHEAT: Overheat condition exists.
WINDOW HEAT test switch:
PWR TEST switch: confidence test. (applies power)
OVHT: Simulates overheat.
PROBE HEAT switch:
Off= off
On= On
Auto= On when either engine is running.
Probe heat lights:
Illuminated: related probe not heated.
If operating on standby power, do not indicate system status, captains is heated.
COWL ANTI-ICE light
Overpressure in duct downstream of engine anti-ice valve.
ENGINE ANTI-ICE switches
On: Related engine Anti- ice valve is opened.
-Stick shaker logic is set for icing conditions.
OFF: Valve is commanded closed.
-Stick shaker logics returns to normal if wing anti-ice has not been used in flight.
Wing anti-ice VALVE OPEN lights:
Bright: in transit or disagrees.
Dim: Wing anti-ice valve is open (switch on)
OFF.
WING ANTI-ICE Switch
ON (in air):
-wing anti-ice valves are open.
-Stick shaker logic is set for icing conditions. (remains for remainder of flight)
If you forget to turn this off on the ground before takeoff it will shutoff at liftoff. Valves will auto close when takeoff thrust is applied.
Power transfer Unit PTU
Allows normal operation of leading edge flaps in the event of a failure on the B hydraulic system.
Airborne
Flaps not up
Failure of B system
Landing gear transfer unit
Allows normal operation of the landing gear in the event of engine #1 roll back.
-in the air
-gear selected up
-#1 rollback
A uses B pressure.
Anti skid protection
STHL:
Skid
Touch down
Hydro
Lock wheel
EQUIP COOLING panel:
There are two supply and exhaust fans. The NORM position is the normal position and if one of the OFF lights illuminates it means there is no flow. You would then switch the corresponding switch to ALTN to use the alternate corresponding fan.
Engine Start switch:
Ground: Opens starter valve, closes the bleed air, and arms the igniter.
OFF: both igniters activated when start lever in idle and uncommanded rapid decrease in N2 or between 57% and 50% or N2 between idle and 5%.
Continuous: Continuously fires igniters.
FLT: looks at switch and fires that igniter.
Bleed air control panel:
DUAL BLEED light: Possible back pressure. Know how.
PACK switch:
OFF: pack off
AUTO: w/both packs low flow.
- w/ one pack regulated high flow in flight with flaps up.
- w/one pack from APU regulates high flow.
-HIGH: high flow
Isolation valve AUTO: opens automatically if either BLEED or PACK switch is positioned OFF
PACK TRIP OFF light: pack tripped off or failure of both primary and standby pack controller.
-extinguishes with master caution reset.
WING BODY OVERHEAT light: Overheat in bleed duct: strut, leading edge, air con bay (right), plus keel beam and APU bleed air duct (left)
-Use duct diagram for reference.
BLEED TRIP OFF light: Excessive bleed temp or pressure.
-reset required.
