Systems Module 104X - Electronic Systems Validation (ESV)

Ground power is connected and meets airplane power quality standards when the GRD POWER AVAILABLE light illuminates…

A. Blue

B. Green

C. Amber

A. Blue

APU GEN OFF BUS illuminates BLUE when the APU is...

A. Running and powering a BUS

B. Not running but could be made available

C. Running and not powering a BUS

C. Running and not powering a BUS

The GEN OFF BUS light illuminates when...

A. An IDG is not supplying power to the related BUS

B. An IDG is supplying power to the related BUS

C. An IDG is off

A. An IDG is not supplying power to the related BUS

Where are the ELEC System Volts and FREQS Displayed?

A. Primary Flight Display when NAV Data Display

B. Forward Overhead Panel

C. On the ENGINE Display Page

D. It is Automatic

B. Forward Overhead Panel

How many minutes of Standby Power is available with two fully charged batteries?

A. 30

B. 60

C. 120

B. 60

The Ground Power (GRD PWR) switch in the ON position will…

A. Remove previously connected power from AC transfer busses

B. Connect ground power to AC transfer bus when power quality is correct

C. Both A&B

C. Both A&B

The Ground Power (GRD PWR) switch in the OFF position will…

A. Disconnect ground power from AC BUS

B. Disconnect power from DC BUS

C. Disconnects power from the APU

A. Disconnect ground power from AC BUS

Can the AC System be powered by both APU power and ground (GRD) power at the

same time?

A. Yes, AC can be powered by two sources at the same time

B. No, The AC system must not have parallelling sources of power

B. No, The AC system must not have parallelling sources of power

Moving the APU GEN switch to ON with NEITHER AC transfer bus powered by an IDG will:

A. Power both AC transfer busses

B. Disconnect external power and power both AC transfer busses

C. Power one AC transfer bus

B. Disconnect external power and power both AC transfer busses

Moving the APU GEN switch to ON with BOTH AC transfer

busses powered by an IDG will

A. Power the related ac bus from the APU generator and the other AC transfer bus will continue to receive power from the IDG

B. Power both busses from the APU and disconnect ground power

C. All of the above

A. Power the related ac bus from the APU generator and the other AC transfer bus will continue to receive power from the IDG

Generator (GEN) switches in the OFF position disconnects IDG from related AC transfer BUS by...

A. Connecting APU generator

B. Opening generator circuit breaker

C. Closing generator circuit breaker

B. Opening generator circuit breaker

Generator (GEN) switch in the ON position connects IDG to

related AC transfer bus by...

A. Disconnecting previous power source and closing generator

circuit breaker

B. Opening generator circuit breaker

C. Connecting APU generator

A. Disconnecting previous power source and closing generator

circuit breaker

The Generator Drive Disconnect switch disconnects IDG if electrical power is

available and engine is at _____ power. The IDG _______ be reconnected in the air.

A. Idle, can

B. Idle, Cannot

C. Cruise, cannot

B. Idle, Cannot

The BAT (Battery) switch in the ON position provides Automatic

Switching of Standby Electrical power in the event it is required.

A. True

B. False

A. True

What does a hydraulic LOW PRESSURE indication indicate? (VOL 2 / 13.1.1)

A. Indicates output pressure of the associated pump is low

B. Indicates leak in a hydraulic line

C. Indicates problem in pressure sensors

A. Indicates output pressure of the associated pump is low

Which of the following are functions of the ENGINE HYDRAULIC PUMP switches? (VOL 2 / 13.1.1)

A. ON - de-energizes blocking valve in pump to allow pressure to enter the system

B. OFF - energizes blocking valve to block pump output

C. AUTO - de-energizes blocking valve as needed to maintain desired pressure

A. ON - de-energizes blocking valve in pump to allow pressure to enter the system

B. OFF - energizes blocking valve to block pump output

What are the 3 independent hydraulic systems on the 737-800? (VOL 2 / 13.2.1)

A. System A, System B, System C

B. System A, System B, Standby System

C. Primary System, Backup System, Standby System

B. System A, System B, Standby System

Which of the following are functions of the ELECTRIC HYDRAULIC PUMP switches? (VOL 2 / 13.1.1)

A. ON - provides power to associated electric motor-driven pump

B. AUTO - cycles power to associated electric motor- driven pump to achieve desired pressure

C. OFF - electrical power removed from the pump

A. ON - provides power to associated electric motor-driven pump

C. OFF - electrical power removed from the pump

What radio altitude can Speed brakes be extended in flight?

A. Less than 800 feet

B. Less than 1000 feet

C. Less than 200 feet

A. Less than 800 feet

To extend the Speedbrakes on the ground, the Speedbrake lever is in the ___

detent, and the ground spoilers are not ____

A. Up, Stowed

B. Down, Stowed

C. Up, Extended

B. Down, Stowed

When does the LE FLAPS TRANSIT light illuminate AMBER

A. When any LE device is in transit AND any LE device is not in the selected position

B. Auto Slat operation in flight

C. Any LE device is fully extended

A. When any LE device is in transit AND any LE device is not in the selected position

When does the YAW DAMPER light illuminate

C. Yaw damper not engaged

D. Yaw damper engaged

E. Yaw damper failed

C. Yaw damper not engaged

When flaps are set to 40, the TE flaps retract to __ when the airspeed for flaps 40 is exceeded (Flap Load Relief System)

A. 35

B. 30

C. 25

B. 30

When flaps are set to 30, the TE flaps retract to __ when the airspeed for flaps 30 is exceeded (Flap Load Relief System)

A. 25

B. 20

C. 15

A. 25

The Flap Load Relief System re-extends the flaps the desired setting after retracting them to protect from a flap overspeed

A. True, the flaps are re-extended to the selected flap setting

B. False, the flaps must be manually re-extended after a flap overspeed

A. True, the flaps are re-extended to the selected flap setting

Hydraulic power to manipulate flight controls comes from what source?

A. System A

B. System B

C. Either one selected

C. Either one selected

Can the rudder be operated by a system other than A&B

A. Yes, Manually

B. No, one is required

C. Yes, Standby Hydraulic System

C. Yes, Standby Hydraulic System

Can the ailerons and elevators be operated manually?

A. Yes, they may be operated manually if required

B. No, standby hydraulic power must be used

A. Yes, they may be operated manually if required

Approximately how many degrees must the control wheel be displaced to initiate spoiler deflection

A. 6

B. 8

C. 10

C. 10

Prior to spoiler deflection, the spoiler is operated on the wing ___ and stays in

place on the wing ___

A. Descending, Rising

B. Rising, Descending

A. Descending, Rising

What is meant when the Speed Brake Lever is in the DOWN (faired) position?

A. The speed brakes are deployed

B. The speed brakes are stowed

B. The speed brakes are stowed

Upon touchdown, the speed brake lever should be in the ____ position, and

automatically moves to the ___ position to be extended

A. Armed, Up

B. Flight Detent, Down

C. Armed, Down

A. Armed, Up

At what radio altitude will the AUTO speed brake system operate when in the

ARMED position?

A. 800

B. 100

C. 10

C. 10

What is the minimum wheel speed for the AUTO Speed Brake System to operate regardless of ARMED or DOWN position

A. 73

B. 60

C. 100

B. 60

What position must the thrust levers be to allow the AUTO Speed Brakes to operate

A. Below 25%

B. Below 10%

C. Idle

C. Idle

What does a landing gear indicator light (GREEN) indicate? (VOL 2 / 14.1.1 ;

14.1.2)

A. Gear is in up and locked position

B. Gear is in down and locked position

C. Gear is currently in motion

B. Gear is in down and locked position

Landing gear is down and locked as long as one landing gear indicator light (GREEN) on the center or overhead panel for each gear is illuminated. (VOL 2 / 14.1.1 ; 14.1.2)

A. True

B. False

A. True

Which of the following are indications of the AUTO BRAKE DISARM (AMBER)

light? (VOL 2 / 14.1.4)

A. SPEED BRAKE lever moved to down detent during RTO or landing

B. Manual brakes applied during RTO or landing

C. Thrust lever(s) advanced during RTO or landing (except during first 3 seconds after touchdown)

D. Landing made with RTO selected

E. RTO selected on ground (illuminates for 2 seconds, then extinguishes)

F. A malfunction exists in auto brake system

A. SPEED BRAKE lever moved to down detent during RTO or landing

B. Manual brakes applied during RTO or landing

C. Thrust lever(s) advanced during RTO or landing (except during first 3 seconds after touchdown)

D. Landing made with RTO selected

E. RTO selected on ground (illuminates for 2 seconds, then extinguishes)

F. A malfunction exists in auto brake system

Which of the following are braking systems on the 737-800?

(VOL 2 / 14.2.4 ; PLEASE READ TO GO OVER BRAKING SYSTEMS IN DETAIL)

A. Normal brake system

B. Alternate brake system

C. Brake accumulator

D. Autobrake system

E. Parking brake

A. Normal brake system

B. Alternate brake system

C. Brake accumulator

D. Autobrake system

E. Parking brake

How can the auto brakes be disarmed? (VOL 2 / 14.2.4.5.3)

A. Moving the SPEED BRAKE lever to the down detent

B. Advancing the forward thrust lever(s), except during the first 3 seconds after touchdown

C. Applying manual brakes

D. Moving the selector switch to the off position

E. All of the above

E. All of the above