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The AUTO FAIL light on the cabin pressurisation panel is illuminated alone.

This indicates a dual controller failure.

The Auto position of the Cockpit Voice Recorder (CVR) On/Auto switch:

Powers the CVR from first engine start until 5 minutes after last engine shutdown.

The AUTO SLAT FAIL light illuminates during MASTER CAUTION recall. The light extinguishes when master caustion system is reset. This indicates:

failure of a single Stall Management/Yaw Damper (SMYD) computer.

The autoslat system:

drives the slats to FULL EXTEND when TE Flaps 1 through 5 are selected and the aircraft approaches a stall.

The bleed air pressure indicator has L and R pointers. These pointers:

may indicate a L/R duct pressure difference which is considered normal as long as there is sufficient air for cabin pressurisation

The BLEED TRIP OFF light indicates an

Overpressure or Overheat in the bleed air duct system

The BLEED TRIP OFF light:

Indicates excessive engine bleed air pressure or temperature.

The blue 'APU GEN OFF BUS' light will illuminate:

when the APU is at operational speed and is not supplying an AC transfer bus

The brake accumulator provides pressure to the brake system and:

parking brake system

The Cabin Altitude and Takeoff Configuration Warnings:

both use the same intermittent warning horn when activated

The cabin begins to pressurize

on the ground at high power settings

The call system from flight deck to an attendant station in the passenger cabin operates:

pink master call lights and a two-tone chime

The call system from flight deck to cabin operates:

pink call lights and a two-tone chime

The cargo compartment fire detection system has dual detection loops and in normal operation:

both loops must detect the presence of smoke to cause an alert.

The cargo compartment fire protection system includes:

A single fire extinguisher bottle

The cargo compartments have

Smoke detection powered by DC Bus 1 and DC bus 2

The center tank fuel scavenge jet pump operates when:

the No. 1 main fuel tank is about 1/2 full

The center tank scavenge jet pump operates when:

the No. 1 main fuel tank is about 1/2 full

The cockpit voice decorrer records audio for:

120 minutes

The Cockpit Voice Recorder (CVR) can be erased by:

Pushing the ERASE switch for 2 seconds when the aircraft is on ground and parking brake is set

The Cockpit Voice Recorder (CVR) can be erased:

Pushing erase button for 2 seconds and aircraft on ground with parking brake ON

The cockpit voice recorder records audio for:

120 minutes

The columns and wheels are connected through transfer mechanisms which allow the pilots to bypass a jammed control or surface. If the ailerons control system is jammed, force applied to:

force applied to the First Officer’s control wheel provides roll control from the spoilers. The ailerons and the Captain’s control wheel are inoperative.

The controller programs the cabin to land slightly pressurized. After landing to depressurize the aircraft:

while taxiing in, the controller slowly drives the outflow valve fully open.

The COWL ANTI-ICE light illuminates amber:

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

The COWL ANTI-ICE light illuminates amber:

to indicate excessive pressure in the duct leading from the cowl anti-ice valve to the cowl lip

The Cross Bus Tie relay:

opens if the BUS TRANSFER switch is moved to OFF.

The curved trend vector extending from the aircraft symbol on ND MAP and MAP CTR is divided into three segments. With the range set greater than 20 nm, each segment represents:

predicts position at the end of 30,60 and 90 second intervals

The decision height (DH) display on the CDS is set:

independently by each pilot using his/her EFIS control panel

The display selector on the IRS Display Unit (ISDU) is moved to position HDG/STS during alignment. What is shown in the right window:

right window displays minutes remaining until alignment is complete

The DUAL BLEED light is illuminated amber. This indicates:

Eng No 1 BLEED air switch ON and APU bleed air valve open

The EEC has automatically changed to Soft Alternate Mode, with the ALTN switch illuminated and the ON indication remaining visible. What would cause the EEC to change to Hard Alternate mode?

Either retarding the thrust lever to idle or manually selecting ALTN with the EEC switch on the aft overhead panel.

The EEC has automatically changed to Soft Alternate Mode, with the ALTN switch illuminated and the ON indication remaining visible. What would cause the EEC to change to Hard Alternate mode?

Either retarding the thrust lever to idle or manually selecting ALTN with the EEC switch on the aft overhead panel

The Electrical (ELEC) Light will illuminate in flight if:

the ELEC light only operates on the ground

The Emergency Exit Lights switch, when placed in the ARMED position:

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

The ENG ANTI-ICE switch are positioned to ON in flight. The stall warning logic:

Adjusts stick shaker and minimum maneuver speed bars on the airspeed indicator.

The engine and APU fire detection systems are run from the

Battery Bus

The engine bleed air valve acts as:

a pressure regulator and shutoff valve

The equipment cooling system comprises:

4 fans

The equipment cooling system comprises:

4 fans - 2 supply duct and 2 exhaust duct

The First Officer observes the word PITCH displayed in amber in the lower portion of the PFD during an ILS approach. This means?

the Captain's and First Officer's pitch angle displays differ by more than 5 degrees

The First Officer observes the word PITCH displayed in amber in the lower portion of the PFD during an ILS approach. This means?

the Captain's and First Officer's pitch displays differ by 5 degrees or more

The flap load relief system is operational at (assume for aircraft YC496 through YW097):

flaps 30 and 40

The Flap Load Relief system:

will retract the TE Flaps from 40 to 30 if airspeed exceeds 163 knots.

The flap/slat electronics unit (FSEU) provides:

protection for LE devices if two or more slats on one wing move from the commanded position

The flight crew oxygen mask EMERGENCY/TEST Selector rotated to the EMERGENCY position:

supplies 100% oxygen under positive pressure at all cabin altitude

The flight crew oxygen system pressure may be as high as:

1850psi

The flight crew oxygen system uses auto pressure breathing masks/regulators with pressure breathing starting at:

27,000 feet

The flight crew oxygen system usesauto pressure breathing masks/regulators with pressure breathing starting at:

27,000 feet

The flight directors must be ON to engage the AFDS in Go around mode?

FALSE

The FMC advisory message "BUFFET ALERT" indicates:

Current conditions result in a manoeuvre margin less than required.

The FMC alerting message 'RESET MCP ALT' means:

aircraft within 5 NM of the FMC calculated Top of Descent (TOD) point without selecting lower altitude on the MCP

The FMC Alerting Message 'VERIFY POSITION' indicates:

position information is contradictory on the ground only

The FMC Alerting Message RESET MCP ALT means:

The aircraft is within 5 NM of the FMC calculated Top of Descent (TOD) point without selecting a lower altitude on the MCP

The FMC alerting message VERIFY GW AND FUEL is shown in the CDU scratchpad:

When fuel quantity data is invalid and estimated fuel weight has to be entered manually

The forward cabin temperature control fails.

FWD CAB Temperature selector works normally, but the cabin temperature is maintained at the average of the FWD and AFT CAB temperature selector settings.

The FSEU (flap/slat electronic unit) provides:

protection and indication for TE Flap asymmetry, skew and uncommanded motion.

The fuel quantity displayed on the FMC PROGRESS Page 1 is:

present total fuel remaining, as obtained from the fuel quantity indication system

The fuel quantity displayed on the FMC PROGRESS page is:

total fuel onboard, as obtained from the fuel quantity indication system

The FWD and AFT cargo compartments each have smoke detectors

In a dual loop configuration. Normally, both detection loops must sense smoke to cause an alert

The FWD CAB ZONE TEMP light illuminates amber. This indicates duct temperature overheat.

The system may be reset by pushing the TRIP RESET switch

The Galley busses are powered from:

the AC Transfer busses.

The green LE FLAPS EXT light:

illuminates for all LE devices fully extended (TE flap positions 10 - 40).

The HF Sensitivity Control is used for which purpose?

To set HF sensitivity on the on-side HF receiver.

The indications for the Cargo Fire test

Fire warning bell sounds, both master FIRE WARN lights illuminate, the extinguisher test lights illuminate, FWD and AFT cargo fire warning lights illuminate, and the cargo fire bottle DISCH light illuminates

The indications of an engine overheat are:

Both MASTER CAUTION lights, the related ENG OVERHEAT light and the OVHT/DET system annunciator light illuminate.

The isolation valve is _____ operated?

AC

The ISOLATION VALVE switch is in the AUTO position, both engine bleed switches are ON, the L PACK switch is in the AUTO position and the R PACK switch is in the HIGH position. What is the position of the isolation valve?

Closed

The landing gear configuration warning horn will activate anytime a gear is not down and locked:

with the flaps set to 15, one thrust lever at idle and the other at low power setting (below 34 degrees)

The Landing Gear Transfer Unit:

Ensures System B can assist raising the gear on loss of System A

The landing gear warning horn sounds and cannot be silenced with the landing gear warning HORN CUTOUT switch. What is the aircraft's condition (both engines are operating)?

On approach passing 1500ft RA and selecting Flaps 30 with any gear not down and locked

The landing gear warning horn sounds and cannot be silenced. What is the aircraft's condition?

On approach passing 1500ft RA and selecting Flap 30 with any gear not down and locked

The loss of one DEU results in activation of the EEC's alternate mode. In this situation, which of the following statements is correct?

The soft alternate mode is entered first, using last valid flight condition to define engine parameters

The mach/airspeed warning system can only be checked on the ground:

yes

The Mach/airspeed warning system provides a distinct aural warning:

a clacker

The main wheel well has

Fire detection only

The maximum differential pressure is:

9.10 psi

The minimum equipment requirement for RAs to be generated is if the other airplane has a working:

Mode C transponder.

The Navigation Display (ND) wind direction/speed and wind arrow is:

Displayed if wind speed is greater than 6 knots

The number of flight spoilers located on each wing are:

4

The number of ground spoilers on each wing are:

2

The number of slats located on each wing are:

Four outboard of each engine

The outflow valve position indicator indicates the position of the outflow valve:

in all modes

The PASS OXY ON Light illuminates, what does this indicate?

Passenger oxygen system is activated

The position trend vector extending from the aircraft symbol on the ND in modes MAP and MAP CTR is divided into three segments. With the range set greater than 20 nm, each segment represents:

predicts position at the end of 30, 60 and 90 second intervals

The power source for Fire Extinguishing is:

the Hot Battery Bus

The Power Transfer Unit (PTU) provides a backup source of hydraulic pressure to operate the:

Autoslats and leading edge flaps and slats.

The Power Transfer Unit (PTU) provides an alternative source of power for the Autoslat system if:

A loss of pressure from Hydraulic System B engine driven pump is sensed

The Power Transfer Unit provides a backup source of hydraulic pressure to operate which of the following items?

autoslats

The Power Transfer Unit provides an alternate source of hydraulic power for the Autoslat System if:

a loss of pressure from the Hydraulic System B engine-driven pump is sensed.

The Proximity Switch Electronic Unit (PSEU) light is inhibited:

at all times in flight, when the thrust levers are advanced toward takeoff power at any time and for 30 seconds after landing.

The Proximity Switch Electronic Unit (PSEU) monitors:

takeoff and landing configuration warnings, landing gear, air/ground sensors

The purpose of the Landing Gear Transfer Unit is to:

automatically use hydraulic system B for gear retraction if No. 1 engine is lost and the landing gear lever is positioned up

The R ELEV PITOT Light is illuminated and both PROBE HEAT switches are in the ON position. What does this indicate?

The right elevator pitot is not heated

The RA aural alert 'CLIMB' CLIMB NOW' means:

Reversal manoeuvre from initial descent RA.

The Recirculation Fan:

reduces air conditioning pack load and the engine bleed air demand

The red landing gear indication lights are illuminated under which of the following conditions?

Landing gear is in disagreement with LANDING GEAR lever position OR the landing gear is not down and locked (with either or both thrust levers retarded to idle, and below 800 feet AGL).

The right IRS is electrically powered from:

normally AC Transfer Bus 2 - in emergency from switched hot battery bus for a maximum of 5 minutes

The right primary pack control fails. The right pack:

is controlled by the left pack standby control

The scratch pad message VERIFY GW AND FUEL appears:

When fuel data is invalid and fuel has to be entered manually.