Systems oral

Question 1

When does the Cross Bus Tie open automatically?

Answer 1

-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.

Question 2

Proximity switch electronic unit (PSEU) illuminated.

Answer 2

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.

Question 3

TAKEOFF CONFIG light illuminates:

Answer 3

-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

Question 4

CABIN ALTITUDE light illuminated:

Answer 4

-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.

Question 5

MACH AIRSPEED WARNING TEST switches

Answer 5

Push tests respective Mach/airspeed warning system.
-clacker sounds.
-inhibited while airborn.

Question 6

STALL WARNING TEST Switch

Answer 6

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.

Question 7

Landing Gear Warning Cutout switch:

Answer 7

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.

Question 8

SPEED TRIM FAIL

Answer 8

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.

Question 9

AUTO SLAT FAIL light:

Answer 9

Indicates failure of the auto slat system.

Talk about the PTU.

Question 10

IRS panel:

Answer 10

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:

Question 11

Engine panel and EEC

Answer 11

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.

Question 12

Window heat panel:

Answer 12

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.

Question 13

PROBE HEAT switch:

Answer 13

Off= off
On= On
Auto= On when either engine is running.

Question 14

Probe heat lights:

Answer 14

Illuminated: related probe not heated.

If operating on standby power, do not indicate system status, captains is heated.

Question 15

COWL ANTI-ICE light

Answer 15

Overpressure in duct downstream of engine anti-ice valve.

Question 16

ENGINE ANTI-ICE switches

Answer 16

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.

Question 17

Wing anti-ice VALVE OPEN lights:

Answer 17

Bright: in transit or disagrees.

Dim: Wing anti-ice valve is open (switch on)

OFF.

Question 18

WING ANTI-ICE Switch

Answer 18

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.

Question 19

Power transfer Unit PTU

Answer 19

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

Question 20

Landing gear transfer unit

Answer 20

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.

Question 21

Anti skid protection

Answer 21

STHL:
Skid
Touch down
Hydro
Lock wheel

Question 22

EQUIP COOLING panel:

Answer 22

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.

Question 23

Engine Start switch:

Answer 23

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.

Question 24

Bleed air control panel:

Answer 24

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.

Question 25

Cargo fire panel:

Answer 25

One fire bottle to be fired in either forward or aft.

Test button turns on green squib lights if they are good.

DETECTOR FAULT light: Both loops in one or both cargo compartment has failed.

ARMED light: You’ve armed respective extinguisher.

FWD/AFT: At least one detector in each loop detects smoke.
- FIRE WARN lights illuminate and fire bell sounds.

Limitations: Must land within 60 mins or 180 ETOPS.

Question 26

Flight control and Standby rudder panel.

Answer 26

Three hydraulic systems: A, B and Standby.

FLT CONTROL switches: Down, guarded and ON is normal.

OFF: Closes flight control shutoff valve, isolating ailerons, elevators, and rudder from respective side.
STBY RUD: activates standby hydraulic pump and opens standby rudder shutoff valve. Inhibits the low pressure light below the switch. Turns STBY RUD light on. Arms LOW PRESSURE light on the right.

STANDBY HYD lights:
LOW QUANTITY: Always armed, indicates less than 50%.
LOW PRESSURE: Armed only when standby pump selected or standby function activated.
STBY RUD ON: lost the hydraulic system or force flight monitor triggered standby Hydraulics.

ALTERNATE FLAPS: guarded and OFF is normal.
ARM: closes trailing edge flap bypass valve, activates standby pump, arms flap position switch.

Limitations:
- One cycle is 0-15 and back up, then 5 mins before moving. Must wait 15 seconds before switching directions.

FEEL DIFF PRESS light:
-Excessive differential pressure in elevator feel computer.

SPEED TRIM FAIL light: it’s failed.
Speed trim operates 10 seconds after takeoff when high power setting, low gross weight, aft CG and 5 pauses for 5 seconds if manual trim is activated.

YAW DAMPER light: illuminated when the damper isn’t on.
-Will initially indicates as on when you lose system B until you’ve made system config changes.

AUTOSLAT fail: When you approach a stall in the extended position (not clean) they will fully extend.
-Flaps 1-5 (700)
-flaps 1-25 (800)

Standby yaw damper won’t engage until both systems have been switched to STBY RUD.

PTU

LGTU

Question 27

Speed break limitations

Answer 27

-In flight, do not extend the speedbrake lever beyond the FLIGHT DETENT.
-Do not use speedbrakes in flight below 1,000 ft AGL.
-In flight, do not use speedbrakes with greater than flaps 10.
–700W - Do not operate the aircraft at speeds in excess of 320 kt at weights over 143,000 lb if the speedbrake wing load alleviation system is inoperative.

Question 28

Electric and Standby panel:

Answer 28

BAT DISCHARGE light:
-Illuminates if excessive battery discharge occurs.
-22-30V is normal.

TR UNIT light:
On ground: Any TR has failed.
Air: TR1 or TR2 and TR3 have failed.

ELEC light: Illuminates on the ground only and indicates a fault in the DC power system or Standby power system.

BAT Switch:
OFF: removes power from
-battery bus
-switched hot battery bus
-DC standby
-AC standby

STANDBY POWER switch:
-AUTO: AC and DC standby bus and battery powered.
-OFF: AC standby bus, DC standby bus is not powered. (STANDBY PWR OFF light illuminates.)
-BAT: Battery powers AC/DC standby bus.

DRIVE light:Integrated Drive Generator (IDG) either under frequency condition, or low oil pressure caused by one of the following.
-IDG failure
-Engine shutdown
-IDG auto disconnect high oil temp
-IDG disconnected through gen drive DISCONNECT switch.

Question 29

Generator/Ground power panel:

Answer 29

BUS TRANSFER switch:
AUTO: allows auto transfer using the bus tie breakers and DC cross tie.

GEN OFF BUS light: Engine gen is not powering the related AC transfer bus.

Question 30

Fuel panel:

Answer 30

Fuel temp is measured from left main tank.

Fuel pump, fuel pump control, or fuel quantity circuit breakers cannot be reset.

Limitations:
-Mains must be filled first.
-Up to 1000 lbs in center w/out full mains.
-Above 1000 lbs in center tank pumps must be on.
-Less than 1000 lbs center pumps are off (on ground)
-If center pump is on someone must be in cockpit.
-1000 point max imbalance.
-Cannot use radar on the ground with fueling or fuel spill.
-If you transfer or defuel and the respective tank goes below 2000 lbs only essential crew.

Question 31

Ground power/APU/GEN panel

Answer 31

BUS TRANSFER switch:
AUTO (guarded): BTB’s and DC cross tie relay automatically maintain power to AC transfer busses.
OFF: Isolates AC transfer bus one from bus two. DC cross tie opens to isolate DC 1 from 2.

SOURCE OFF: No source has been selected or the manually selected source has disconnected.

GEN OFF: IDG is not supplying power to the related transfer bus.

APU GEN OFF: APU is running and not powering the bus.

Limits:
-APU start 41,000
-APU electric only 41,000
-Bleed only 17,000
-Bleed and electric 10,000

Question 32

Passenger Oxygen

Answer 32

NORMAL: mask auto drop at 14000.

ON: drops masks.

PASS OXY ON light: pass oxygen system is operation and masks have dropped.

Question 33

Hydraulic Pumps:

Answer 33

OVERHEAT light: Fluid has overheated or pump itself has.

ON/OFF engine driven pump switch doesn’t actually shut off the engine driven pump, just energizes blocking valve.

Pumps are labeled and cross wired to allow the electric pump to power opposite side

Question 34

Stab trim override.