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United 737 Systems Validation Study Guide (26 July 2021) > Hydraulics / Landing Gear/Brakes > Flashcards

Hydraulics / Landing Gear/Brakes Flashcards

1
Q
  1. The operation of the standby hydraulic system is _______ by a leak in hydraulic system B.
A
  1. The operation of the standby hydraulic system is _______ by a leak in hydraulic system B.

not affected

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2
Q
  1. What is the purpose of the PTU?
A
  1. What is the purpose of the PTU?

• 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
  1. What is the purpose of the landing gear transfer unit?
A
  1. What is the purpose of the landing gear transfer unit?

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

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4
Q
  1. The landing gear transfer unit operates when airborne, ______________, and the No. 1 engine RPM drops below a limit value.
A
  1. The landing gear transfer unit operates when airborne, ______________, and the No. 1 engine RPM drops below a limit value.

• the landing gear is positioned up and either main landing gear is not up and locked

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5
Q
  1. The standby system uses a single electric motor-driven pump and ____________________ .
A
  1. The standby system uses a single electric motor-driven pump and ____________________ .

• can be activated manually or automatically

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6
Q
  1. The standby hydraulic system powers the thrust reversers, __________, and rudder.
A
  1. The standby hydraulic system powers the thrust reversers, __________, and rudder.

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

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7
Q
  1. Automatic operation of the standby hydraulic pump is initiated when _______ and loss of hydraulic system A or B
A
  1. Automatic operation of the standby hydraulic pump is initiated when _______ and loss of hydraulic system A or B

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

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8
Q
  1. 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
  1. 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.

• all answers are correct

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9
Q
  1. 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
  1. 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.

• activates the standby electric motor-driven pump

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10
Q
  1. On the B737-800, ___________ when there is a leak in the standby hydraulic system.
A
  1. On the B737-800, ___________ when there is a leak in the standby hydraulic system.

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

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11
Q
  1. What is indicated by an amber illuminated Electric Hydraulic Pump OVERHEAT light?
A
  1. On the B737-800, ___________ when there is a leak in the standby hydraulic system.

• the hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated
• the pump itself has overheated

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12
Q
  1. The respective engine-driven hydraulic pump LOW PRESSURE light is ________ when pulling the Engine 1 fire warning switch.
A
  1. The respective engine-driven hydraulic pump LOW PRESSURE light is ________ when pulling the Engine 1 fire warning switch.

• deactivated

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13
Q
  1. An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to which flight controls?
A
  1. An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to which flight controls?

• ailerons and elevator
• rudder

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14
Q
  1. An illuminated amber standby hydraulic LOW QUANTITY light is ___________ and indicates low quantity in the standby hydraulic reservoir.
A
  1. An illuminated amber standby hydraulic LOW QUANTITY light is ___________ and indicates low quantity in the standby hydraulic reservoir.

• always armed

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15
Q
  1. An illuminated amber standby hydraulic LOW PRESSURE light is __________ and indicates low output pressure.
A
  1. An illuminated amber standby hydraulic LOW PRESSURE light is __________ and indicates low output pressure.

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

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16
Q
  1. When Positioning the ENG 1 hydraulic pump switch to OFF, the pump_____ to rotate and fluid flow is isolated from the system component.
A
  1. When Positioning the ENG 1 hydraulic pump switch to OFF, the pump_____ to rotate and fluid flow is isolated from the system component.

• continues

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17
Q
  1. After an engine fire warning switch is pulled, the hydraulic fluid flow to the related engine-driven pump is shut off and ______________.
A
  1. After an engine fire warning switch is pulled, the hydraulic fluid flow to the related engine-driven pump is shut off and ______________.

• its LOW PRESSURE light is deactivated

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18
Q
  1. _____ is the minimum fuel for ground operation of electric hydraulic pumps in the related main tank.
A
  1. _____ is the minimum fuel for ground operation of electric hydraulic pumps in the related main tank.

• 1675 lbs.

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19
Q
  1. What happens if a leak develops in the A system hydraulic engine-driven pump or its related lines?
A
  1. What happens if a leak develops in the A system hydraulic engine-driven pump or its related lines?

• a standpipe in the reservoir prevents a total system fluid loss

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20
Q
  1. What happens if a leak develops in the in the A system hydraulic electric motor-driven pump or its related lines?
A
  1. What happens if a leak develops in the in the A system hydraulic electric motor-driven pump or its related lines?

• the quantity in the reservoir steadily decreases to zero and all system pressure is lost

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21
Q
  1. What happens if a leak develops in either pump, line or component of system B?
A
  1. What happens if a leak develops in either pump, line or component of system B?

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

22
Q
  1. The operation of the standby hydraulic system _______ by a leak in hydraulic system B.
A
  1. The operation of the standby hydraulic system _______ by a leak in hydraulic system B.

• Is not affected

23
Q
  1. Which system can power all flight controls with no decrease in aircraft controllability?
A
  1. Which system can power all flight controls with no decrease in aircraft controllability?

• Either A or B hydraulic system

24
Q
  1. What is the maximum tire ground speed?
A
  1. What is the maximum tire ground speed?

• 195 knots

25
Q
  1. The brake wear indicators should extend beyond the brake flange with the parking brake in what position?
A
  1. The brake wear indicators should extend beyond the brake flange with the parking brake in what position?

• set

26
Q
  1. Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by which hydraulic system?
A
  1. Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by which hydraulic system?

• hydraulic system A

27
Q
  1. The alternate brake system is powered by _________ and the normal brakes system is powered by _______.
A
  1. The alternate brake system is powered by _________ and the normal brakes system is powered by _______.

• hydraulic system A; hydraulic system B

28
Q
  1. Antiskid protection is provided which brake system(s)?
A
  1. Antiskid protection is provided which brake system(s)?

• on both brake system (normal and alternate)

29
Q
  1. The ____________ stop rotation of the main gear wheels during landing gear retraction.
A
  1. The ____________ stop rotation of the main gear wheels during landing gear retraction.

• brakes automatically

30
Q
  1. The nose wheels retract forward into the wheel well and nose wheel rotation is stopped by _________ during landing gear retraction.
A
  1. The nose wheels retract forward into the wheel well and nose wheel rotation is stopped by _________ during landing gear retraction.

• snubbers

31
Q
  1. What happens Moving the LANDING GEAR lever to the OFF position?
A
  1. What happens Moving the LANDING GEAR lever to the OFF position?

• hydraulic pressure from the landing gear system is removed

32
Q
  1. 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
  1. 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).

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

33
Q
  1. What does an extinguished green landing gear indicator light indicate?
A
  1. What does an extinguished green landing gear indicator light indicate?

• landing gear is not down and locked

34
Q
  1. 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
  1. When the LANDING GEAR lever is moved to DN, hydraulic system pressure is used to release the uplocks. How is the landing gear extended?

• hydraulic pressure, gravity, and air loads

35
Q
  1. 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
  1. 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

At least one

36
Q
  1. 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
  1. 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.

• No. 1 engine RPM drops below a limit value

37
Q
  1. What effect on landing gear retraction does opening the Manual Extension Access Door have?
A
  1. What effect on landing gear retraction does opening the Manual Extension Access Door have?

• disables it

38
Q
  1. With the landing gear lever ____________, manual landing gear extension is possible.
A
  1. With the landing gear lever ____________, manual landing gear extension is possible.

• in any position

39
Q
  1. The 737 manual gear releases on the flight deck are used to_________ that allow the gear to_________ to the down and locked position.
A
  1. The 737 manual gear releases on the flight deck are used to_________ that allow the gear to_________ to the down and locked position.

• release uplocks; free-fall

40
Q
  1. Nose wheel steering will be available _____________________.
A
  1. Nose wheel steering will be available _____________________.

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

41
Q
  1. Pushing the rudder pedal down allows for nose wheel turning up to ______in both directions.
A
  1. Pushing the rudder pedal down allows for nose wheel turning up to ______in both directions.

• 7 degrees

42
Q
  1. ________ allows the aircraft to push back or be towed without depressurizing hydraulic system A.
A
  1. ________ allows the aircraft to push back or be towed without depressurizing hydraulic system A.

• A lockout pin

43
Q
  1. Switching the Nose Wheel Steering Switch to ALT, allows ____________ to provide power for nose wheel steering.
A
  1. Switching the Nose Wheel Steering Switch to ALT, allows ____________ to provide power for nose wheel steering.

• hydraulic system B

44
Q
  1. 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
  1. 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.

• several braking applications

45
Q
  1. Skid, locked wheel, touchdown, and hydroplane protection will be available ____________.
A
  1. 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.

• with the normal and alternate braking system

46
Q
  1. The 737 parking brake can be set with _________.
A
  1. The 737 parking brake can be set with _________.

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

47
Q
  1. What is the normal hydraulic brake pressure as indicated on the brake accumulator _________?
A
  1. What is the normal hydraulic brake pressure as indicated on the brake accumulator _________?

• 3000 psi

48
Q
  1. Placing the AUTO BRAKE Select Switch to 1, 2, 3, or MAX, selects the desired ________for touchdown.
A
  1. Placing the AUTO BRAKE Select Switch to 1, 2, 3, or MAX, selects the desired ________for touchdown.

• deceleration rate

49
Q
  1. 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
  1. 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.

• 90 knots

50
Q
  1. On a dry runway, the maximum autobrake deceleration rate in the landing mode is _______ that produced by full pedal braking.
A
  1. On a dry runway, the maximum autobrake deceleration rate in the landing mode is _______ that produced by full pedal braking.

• less than

51
Q
  1. 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
  1. After the autobraking has started decelerating, any of the following pilot actions disarm the system immediately and will illuminate the AUTO BRAKE DISARM light:

all answers are correct

  • *• moving speed brake lever to full forward or applying manual brakes**
  • *• advancing the forward thrust lever(s), except during the first 3 seconds after touchdown**
52
Q

(NOTE: This question is not in SV Study Guide but does appear in the B737 Landing Gear/Brakes Quiz V4)

xx. After retraction, the main gear are held in place by ______and the nose gear is held in place by ______________.

A

(NOTE: This question is not in SV Study Guide but does appear in the B737 Landing Gear/Brakes Quiz V4)

xx. After retraction, the main gear are held in place by ______and the nose gear is held in place by ______________.

mechanical uplocks; an overcenter lock

United 737 Systems Validation Study Guide (26 July 2021) (14 decks)

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