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Boeing-737 Study Items > Hydraulics/Landing Gear/Brakes > Flashcards

Hydraulics/Landing Gear/Brakes Flashcards

1
Q

The operation of the standby hydraulic system is _______ by a leak in hydraulic system B.
A. inhibited
B. not affected

A

B. not affected

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2
Q

What is the purpose of the PTU?
A. To supply the additional volume of hydraulic fluid needed to operate the autoslats or the leading edge flaps and slats at the normal rate when system A engine-driven pump volume is lost
B. To supply the additional volume of hydraulic fluid needed to operate the autoslats or the leading edge flaps and slats at the normal rate when system B engine-driven pump volume is lost
C. To supply the additional volume of hydraulic fluid needed to operate the autoslats or the leading edge flaps and slats at the normal rate when the standby system volume is lost

A

B. To supply the additional volume of hydraulic fluid needed to operate the autoslats or the leading edge flaps and slats at the normal rate when system B engine-driven pump volume is lost

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3
Q

What is the purpose of the landing gear transfer unit?
A. To raise the landing gear at the normal rate when system A engine-driven pump volume is lost
B. To raise the landing gear at the normal rate when system B engine-driven pump volume is lost
C. To raise the landing gear at the normal rate when the standby system volume is lost

A

A. To raise the landing gear at the normal rate when system A engine-driven pump volume is lost

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4
Q

The landing gear transfer unit operates when airborne, ______________, and the No. 1 engine RPM drops
below a limit value.
A. and a main landing gear is not up and locked
B. the landing gear is positioned up and both main landing gear is not up and locked
C. the landing gear is positioned up and either main landing gear is not up and locked

A

C. the landing gear is positioned up and either main landing gear is not up and locked

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5
Q

The standby system uses a single electric motor-driven pump and ____________________ .
A. can only be activated by placing the ALTERNATE FLAPS Master Switch to ARM
B. can only be activated by positioning either FLIGHT CONTROL switch to STBY RUD
C. can be activated manually or automatically

A

C. can be activated manually or automatically

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6
Q

The standby hydraulic system powers the thrust reversers, __________, and rudder.
A. leading edge flaps and slats (extend only) and the standby yaw damper
B. leading edge flaps and slats (extend and retract) and the standby yaw damper
C. leading edge flaps and slats (extend only), autobrakes and the standby yaw damper

A

A. leading edge flaps and slats (extend only) and the standby yaw damper

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7
Q

Automatic operation of the standby hydraulic pump is initiated when _______ and loss of hydraulic system A or B
A. flaps are extended; and airborne, or wheel speed greater than 60 knots
B. flaps are retracted and airborne
C. speed brake is used

A

A. flaps are extended; and airborne, or wheel speed greater than 60 knots

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8
Q

Positioning either FLT CONTROL switch to STBY RUD, __________, closes the related flight control shutoff valve; deactivates the related flight control LOW PRESSURE light; allows the standby system to power the rudder and thrust reversers.
A. activates the standby electric motor-driven pump
B. opens the standby rudder shutoff valve
C. all answers are correct

A

C. all answers are correct

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9
Q

Positioning the ALTERNATE FLAPS master switch to ARM: __________, operates the trailing edge flap bypass valve, allows the standby system to power the leading edge flaps and slats and thrust reversers, and arms the ALTERNATE FLAPS position switch.
A. engages the alternate asymmetrical flap protection computer
B. activates the standby electric motor-driven pump
C. positions the leading edge devices to FULL EXTEND

A

B. activates the standby electric motor-driven pump

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10
Q

On the B737-800, ___________ when there is a leak in the standby hydraulic system.
A. The LOW QUANTITY light illuminates, and the system A reservoir fluid decreases to zero
B. The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to zero
C. The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to approximately 72%

A

C. The LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to approximately 72%

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11
Q

What is indicated by an amber illuminated Electric Hydraulic Pump OVERHEAT light?
A. the hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated
B. the pump itself has overheated
C. all answers are correct

A

C. all answers are correct

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12
Q

The respective hydraulic pump LOW PRESSURE lights are ________ when pulling the Engine 1 fire warning switch.
A. activated
B. deactivated

A

B. deactivated

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13
Q

Positioning the ELECTRIC HYDRAULIC PUMP Switch to ON does what?
A. allows for transfer of hydraulic system fluid between system A and the standby system
B. controls the related electric motor-driven pump
C. allows for transfer of hydraulic system fluid between system B and A with the parking brake set

A

B. controls the related electric motor-driven pump

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14
Q

The HYDRAULIC System QUANTITY indicates digital ____________ of hydraulic quantity and is shown on the DU.
A. gallons
B. quarts
C. percentage

A

C. percentage

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15
Q

On the ground with both engines shutdown, what causes a REFILL indication, an illuminated white RF, next to the Hydraulic quantity?
A. hydraulic quantity below 86%
B. hydraulic quantity below 76%
C. the related hydraulic system is currently being refilled

A

B. hydraulic quantity below 76%

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16
Q

An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to which flight controls?
A. ailerons and elevator
B. rudder
C. all answers are correct

A

C. all answers are correct

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17
Q

An illuminated amber standby hydraulic LOW QUANTITY light is ___________ and indicates low quantity in the standby hydraulic reservoir.
A. armed only when the standby hydraulic pump operation has been selected or automatic standby pump operation is activated
B. deactivated when Engine 2 fire switch has been pulled
C. always armed

A

C

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18
Q

An illuminated amber standby hydraulic LOW PRESSURE light is __________ and indicates low output pressure.
A. always armed
B. armed only when the standby hydraulic pump operation has been selected or automatic standby pump operation is activated
C. deactivated when Engine 2 fire switch has been pulled

A

B. armed only when the standby hydraulic pump operation has been selected or automatic standby pump operation is activated

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19
Q

On the PFD/ND, how is hydraulic system quantity displayed
A. on the Upper Display Unit
B. at all times with the secondary engine indications
C. by pushing the MFD System (SYS) switch

A

C. by pushing the MFD System (SYS) switch

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20
Q

When Positioning the ENG 1 hydraulic pump switch to OFF, the pump_____ to rotate and fluid flow is isolated from the system component.
A. continues
B. ceases

A

A. continues

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21
Q

After an engine fire warning switch is pulled, the hydraulic fluid flow to the related engine-driven pump is shut off and ______________.
A. its LOW PRESSURE light is deactivated
B. the standby hydraulic system is engaged
C. the LOW PRESSURE light is activated

A

A. its LOW PRESSURE light is deactivated

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22
Q

_____ is the minimum fuel for ground operation of electric hydraulic pumps in the related main tank.
A. 1000 lbs.
B. 1676 lbs.
C. 2000 lbs.

A

B. 1676 lbs

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23
Q

What happens if a leak develops in the A system hydraulic engine-driven pump or its related lines?
A. the system quantity will steadily decrease to 15%
B. a standpipe in the reservoir prevents a total system fluid loss
C. the quantity in the reservoir steadily decreases to zero and all system pressure is lost

A

B. a standpipe in the reservoir prevents a total system fluid loss

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24
Q

What happens if a leak develops in the in the A system hydraulic electric motor-driven pump or its related lines?
A. the system quantity will steadily decrease to 15%
B. a standpipe in the reservoir prevents a total system fluid loss
C. the quantity in the reservoir steadily decreases to zero and all system pressure is lost

A

C

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25
Q

What happens if a leak develops in either pump, line or component of system B?
A. the system quantity will steadily decrease to 15%
B. the quantity in the reservoir steadily decreases approximately zero, system B pressure and the standby system pressure is lost
C. the quantity in the reservoir steadily decreases to approximately zero and system B pressure is lost, however the power transfer unit is still operational

A

C. the quantity in the reservoir steadily decreases to approximately zero and system B pressure is lost, however the power transfer unit is still operational

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26
Q

The operation of the standby hydraulic system _______ by a leak in hydraulic system B.
A. Is inhibited
B. Is not affected

A

B. Is not affected

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27
Q

How many hydraulic systems does the aircraft have?
A. three
B. two
C. one

A

A. three

28
Q

Which system can power all flight controls with no decrease in aircraft controllability?
A. The RAT
B. The standby hydraulic system
C. Either A or B hydraulic system

A

C. Either A or B hydraulic system

29
Q

What is the normal operating pressure for each hydraulic system?
A. 2000 psi
B. 3000 psi
C. 2800 psi

A

B. 3000 psi

30
Q

What is the maximum tire ground speed?
A. 175 knots
B. 185 knots
C. 195 knots

A

C. 195 knots

31
Q

The RTO feature is _________ to be armed for all takeoffs, if operable.
A. required
B. not required

A

A. required

32
Q

The brake wear indicators should extend beyond the brake flange with the parking brake in what position?
A. released
B. set
C. inop

A

B. set

33
Q

Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by which hydraulic system?
A. standby system
B. hydraulic system A
C. hydraulic system B

A

B. hydraulic system A

34
Q

The alternate brake system is powered by _________ and the normal brakes system is powered by _______.
A. hydraulic system A; hydraulic system B
B. hydraulic system B; hydraulic system A
C. hydraulic system B; hydraulic system B

A

A. hydraulic system A; hydraulic system B

35
Q

Antiskid protection is provided which brake system(s)?
A. with normal brakes only
B. with alternate brakes only
C. on both brake system (normal and alternate)

A

C. on both brake system (normal and alternate)

36
Q

The ____________ stop rotation of the main gear wheels during landing gear retraction.
A. snubbers
B. brakes automatically
C. parking brake should be momentarily set to

A

B. brakes automatically

37
Q

The nose wheels retract forward into the wheel well and nose wheel rotation is stopped by _________ during landing gear retraction.
A. brakes automatically
B. parking brake should be momentarily set to
C. snubbers

A

C. snubbers

38
Q

After retraction, the nose are held in place by ______and the main gear is held in place by ______________.
A. rubber seals; hydraulic pressure
B. hydraulic pressure; mechanical uplock
C. an over center lock; mechanical uplocks

A

C. an over center lock; mechanical uplocks

39
Q

What happens Moving the LANDING GEAR lever to the OFF position?
A. the brakes activate
B. hydraulic pressure from the landing gear system is removed
C. The over center locks are engaged

A

B. hydraulic pressure from the landing gear system is removed

40
Q

An illuminated red landing gear indicator light indicates the__________, or the related landing gear is in disagreement with LANDING GEAR lever position (in transits or unsafe).
A. landing gear is up
B. the landing gear manual extension must be used
C. landing gear is not down and locked (with either or both forward thrust levers retarded to idle and below 800 feet AGL)

A

C. landing gear is not down and locked (with either or both forward thrust levers retarded to idle and below 800 feet AGL)

41
Q

What does an extinguished green landing gear indicator light indicate?
A. landing gear is down and locked
B. landing gear is not down and locked
C. the landing gear manual extension must be used

A

B. landing gear is not down and locked

42
Q

What happens when the LANDING GEAR lever is moved to UP?
A. the landing gear retracts
B. the landing gear extends
C. hydraulic pressure is removed from the landing gear

A

A. the landing gear retracts

43
Q

When the LANDING GEAR lever is moved to DN, hydraulic system pressure is used to release the uplocks.
How is the landing gear extended?
A. hydraulic pressure, gravity, and air loads
B. gravity, and air loads
C. STBY, hydraulic pressure, gravity, and air loads

A

A. hydraulic pressure, gravity, and air loads

44
Q

If ____ green landing gear indicator light(s) (center panel and/or overhead panel) for each gear is/are illuminated, the landing gear is down and locked
A. both
B. At least one

A

B. At least one

45
Q

The landing gear transfer unit allows hydraulic system B to supply the volume of hydraulic fluid required to raise the landing gear at the normal rate when airborne, LANDING GEAR lever is positioned UP, ________, and either main landing gear is not up and locked.
A. No. 1 engine RPM drops below a limit value
B. No. 2 engine RPM drops below a limit value
C. the A electric hydraulic pump is inoperative

A

A. No. 1 engine RPM drops below a limit value

46
Q

What effect on landing gear retraction does opening the Manual Extension Access Door have?
A. disables it
B. does not effect

A

A. disables it

47
Q

With the landing gear lever ____________, manual landing gear extension is possible.
A. UP or DOWN
B. DOWN or OFF
C. in any position

A

C. in any position

48
Q

The 737 manual gear releases on the flight deck are used to_________ that allow the gear to_________ to the down and locked position.
A. engage uplocks; hydraulically extend
B. release uplocks; freefall
C. release uplocks; hydraulically extend

A

B. release uplocks; free-fall

49
Q

The tiller for the nose wheel steering wheel ___________ rudder pedal steering.
A. works in the opposite direction of the
B. is secondary to the
C. overrides

A

C. overrides

50
Q

Nose wheel steering will be available _____________________.
A. when the nose gear is in the down position and compressed by the weight of the airplane
B. when the nose gear is in the down position
C. at all times

A

A. when the nose gear is in the down position and compressed by the weight of the airplane

51
Q

Pushing the rudder pedal down allows for nose wheel turning up to ______in both directions.
A. 7 degrees
B. 25 degrees
C. 78 degrees

A

A. 7 degrees

52
Q

________ allows the aircraft to push back or be towed without depressurizing hydraulic system A.
A. A bypass switch on the forward panel
B. A lockout pin
C. Pulling nose wheel circuit breaker

A

B. A lockout pin

53
Q

Switching the Nose Wheel Steering Switch to ALT, allows ____________ to provide power for nose wheel steering.
A. hydraulic system A
B. hydraulic system B
C. the standby hydraulic system

A

B. hydraulic system B

54
Q

If the normal and alternate brake system pressure is lost, trapped hydraulic pressure in the brake accumulator can still provide ____________ or a parking brake application.
A. an unlimited number of normal braking applications
B. one brake application
C. several braking applications

A

C. several braking applications

55
Q

Skid, locked wheel, touchdown, and hydroplane protection will be available ____________.
A. only with the normal braking system
B. only with the alternate braking system
C. with the normal and alternate braking system

A

C. with the normal and alternate braking system

56
Q

If hydraulic system B is low or fails, _____________automatically supplies hydraulic pressure to the alternate brake system.
A. hydraulic system A
B. electric friction
C. standby system pressure

A

A. hydraulic system A

57
Q

The 737 parking brake can be set with _________.
A. hydraulic system A
B. hydraulic system B
C. A or B hydraulic system, or the accumulator if A and B are not pressurized

A

C. A or B hydraulic system, or the accumulator if A and B are not pressurized

58
Q

What is the normal hydraulic brake pressure as indicated on the brake accumulator _________.
A. 2500 psi
B. 3000 psi
C. 1676 psi

A

B. 3000 psi

59
Q

The 737 Anti-skid protection is provided in the _______________.
A. normal braking system only
B. normal and alternate brake systems
C. alternate braking system only

A

B. normal and alternate brake systems

60
Q

An illuminated amber AUTO BRAKE DISARM light indicates _______________.
A. the auto brakes are set to MAX
B. the AUTO BRAKE select switch is set to OFF
C. a malfunction exists in automatic braking system

A

C. a malfunction exists in automatic braking system

61
Q

Placing the AUTO BRAKE Select Switch to 1, 2, 3, or MAX, selects the desired ________for touchdown.
A. brake pressure
B. deceleration rate

A

B. deceleration rate

62
Q

With the AUTO BRAKE Select Switch in the RTO position, maximum brake pressure is automatically applied when the thrust levers are retarded to idle at or above ____ knots.
A. 60
B. 90
C. 120

A

B. 90

63
Q

An illuminated amber ANTISKID INOP light indicates _______________.
A. the anti-skid system need to be reset
B. the auto brakes need to be armed
C. a system fault is detected

A

C. a system fault is detected

64
Q

The 737 auto brake system uses ___________ to provide a maximum deceleration rate for a rejected takeoff.
A. hydraulic system A pressure
B. hydraulic system B pressure
C. hydraulic system A or B pressure

A

B. hydraulic system B pressure

65
Q

On a dry runway, the maximum autobrake deceleration rate in the landing mode is _______ that produced by full pedal braking.
A. more than
B. equal to
C. less than

A

C. less than

66
Q

After the autobraking has started decelerating, any of the following pilot actions disarm the system immediately and will illuminate the AUTO BRAKE DISARM light:
A. moving speed brake lever to full forward or applying manual brakes
B. advancing the forward thrust lever(s), except during the first 3 seconds after touchdown
C. all answers are correct

A

C. all answers are correct

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