Aircraft Systems and Power Up Procedures

Flashcards covering electrical power up procedures, flight deck switches, annunciator lights, and aircraft system operations based on lecture notes.

AC BATTERY Switch (ON - Guarded Position)

Provides power to the switched hot battery bus and energizes relays to provide automatic switching of the standby electrical system to battery power with the loss of normal power.

STANDBY POWER Switch (AUTO - Guarded Position)

In flight or on the ground with AC transfer busses powered, AC standby bus is powered by AC transfer bus 1 and DC standby bus is powered by TR1, TR2, and TR3; upon loss of all AC power, battery powers the AC standby bus (through the static inverter), DC standby bus, and battery bus.

STANDBY PWR OFF Light

Illuminates when one or more of the following busses are unpowered: AC standby bus, DC standby bus, or Battery bus.

GRD POWER AVAILABLE Light

Illuminates when ground power is connected and meets airplane power quality standards.

SOURCE OFF Light

Illuminates when no source has been manually selected to power the related transfer bus, or the manually selected source has been disconnected. If a source has been selected to power the opposite transfer bus, both transfer busses are powered.

TRANSFER BUS OFF Light

Illuminates when the related transfer bus is not powered.

EXTINGUISHER TEST

Tests bottle discharge circuits for all three extinguisher bottles, verifying circuit continuity from the squib to the engine fire warning switch.

APU GEN OFF BUS Light

Illuminates when the APU is running and not powering a bus.

APU LOW OIL PRESSURE Light

Amber light that illuminates during start until APU oil pressure is normal, or when low oil pressure causes an automatic shutdown (after start cycle is complete). If illuminated when the APU switch is moved to OFF, it extinguishes after $5\text{ minutes}$.

APU OVERSPEED Light

Amber light indicating that the APU RPM limit has been exceeded resulting in an automatic shutdown, or that the overspeed shutdown protection feature has failed a self-test during a normal APU shutdown.

IRS ON DC Light

Amber light indicating the related IRS is operating on DC power from the switched hot battery bus (AC power not normal). On the ground, sounds the ground-call horn in the nose wheel well to alert that a battery drain condition exists.

IRS ALIGN Light (Flashing)

Illuminates white and flashes when alignment cannot be completed due to IRS detection of a significant difference between previous and entered positions ($4\text{ NM}$), an unreasonable present position entry, or no present position entry.

VOICE RECORDER (AUTO Position)

Powers the cockpit voice recorder to record flight deck audio for $120\text{ minutes}$ from first engine start until $5\text{ minutes}$ after last engine shutdown.

Hydraulic Quantity RF Light

White light that illuminates when hydraulic quantity is below $76\%$ ($60\%$).

ENGINE CONTROL Light

Amber light indicating the engine control system is not dispatchable due to system faults. Operates when engine is operating on the ground below $80\text{ kt}$ prior to takeoff or approximately $30\text{ seconds}$ after touchdown.

PASSENGER OXYGEN Switch (NORMAL Position)

Guarded switch position where passenger masks drop and the passenger oxygen system is automatically activated if the cabin altitude climbs to $14{,}000\text{ feet}$ (or $14{,}650\text{ feet}$ with High Altitude Landing Switch option).

PSEU Light

On the ground, illuminates when a fault is detected in the PSEU or an overwing exit flight lock fails to disengage when commanded. In flight, it is inhibited from thrust lever advance for takeoff until $30\text{ seconds}$ after landing.

FLIGHT CONTROL Switch (STBY RUD Position)

Activates the standby electric motor-driven pump, closes the flight control shutoff valve to isolate ailerons, elevators, and rudder from related system pressure, opens the standby rudder shutoff valve, and deactivates the related flight control LOW PRESSURE light.

FEEL DIFF PRESS Light

Armed when trailing edge flaps are up or down; illuminates when excessive differential hydraulic pressure is sensed in the elevator feel computer, occurring when either hydraulic system or the elevator feel pitot system fails.

MACH TRIM FAIL Light

Illuminates to indicate failure of the Mach trim system (which operates above Mach $0.615$), or failure of a single FCC channel when MASTER CAUTION recall is activated.

CROSSFEED Selector

Interconnects engine fuel manifolds using a DC motor-operated valve powered from the battery bus, allowing fuel pressure from a main tank with operating fuel pumps to be provided to both engines.

TR UNIT Light

Illuminates on the ground if any TR has failed; illuminates in flight if TR1 has failed, or if both TR2 and TR3 have failed.

ELEC Light

Illuminates on the ground only to indicate that a fault exists in the DC power system or standby power system.

BUS TRANSFER Switch (AUTO Position)

Guarded position allowing Bus Tie Breakers (BTBs) to operate automatically to maintain power to AC transfer busses from any operating generator or external power.

EMERGENCY EXIT LIGHTS Switch (ARMED Position)

Guarded position ensuring all emergency lights illuminate automatically if airplane electrical power to DC bus No. 1 fails or AC power is turned off.

WING ANTI-ICE Switch (ON - On Ground)

Opens wing anti-ice control valves if thrust on both engines is below takeoff warning setting and temperature inside both distribution ducts is below thermal switch activation temperature; trips OFF at lift-off.

COWL ANTI-ICE Light

Illuminates to indicate an overpressure condition in the duct downstream of the engine cowl anti-ice valve.

DUAL BLEED Light

Illuminates when the APU bleed air valve is open and the engine No. 1 BLEED air switch is ON, or the engine No. 2 BLEED air switch is ON and both the APU bleed air valve and isolation valve are open.

BLEED TRIP OFF Light

Illuminates to indicate excessive engine bleed air temperature or pressure, causing the related engine bleed air valve to close automatically and requiring a system reset.

AUTO FAIL Light

Illuminates on loss of DC power, controller fault, outflow valve control fault, excessive differential pressure ($> 8.75\text{ psi}$), excessive rate of cabin pressure change ($\pm 2000\text{ sea level feet/minute}$), or high cabin altitude (above $15{,}800\text{ feet}$).

AUTO BRAKE Select Switch (RTO Position)

Automatically applies maximum brake pressure when thrust levers are retarded to idle at or above $90\text{ knots}$.

SPEEDBRAKES EXTENDED Light (In-Flight)

Illuminates to warn the crew that speed brakes are extended when the SPEED BRAKE lever is beyond the ARMED position and either TE flaps are extended more than flaps $10$ or radio altitude is less than $800\text{ feet}$.

Engine Start Switch (FLT Position)

Provides ignition to both igniters when the engine start lever is in IDLE.

CDS Fault Annunciation

Indicates a non-dispatchable CDS fault has occurred; displayed on the ground only, prior to the start of the second engine.