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SV STUDY GUIDE 737 > 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
  1. 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 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
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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
  • the landing gear is positioned up and either main landing gear is not up and locked
    5.
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5
Q

The standby system uses a single electric motor-driven pump and ____________________ .

A
  • 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
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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
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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
  • 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
  • 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 B reservoir fluid decreases to approximately
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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
  • the pump itself has overheated
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12
Q

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

A
  • deactivated
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13
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
  • rudder
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14
Q

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

A
  • always armed
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15
Q

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

A
  • armed only when the standby hydraulic pump operation has been selected or automatic standby pump
    operation is activated
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16
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
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17
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
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18
Q

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

A
  • 1675 lbs.
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19
Q

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

A

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

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20
Q

What happens if a leak develops in either pump, line or component of system B?

A
  • 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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21
Q

The operation of the standby hydraulic system _______ by a leak in hydraulic system B.

A
  • Is not affected
22
Q

Which system can power all flight controls with no decrease in aircraft controllability?

A
  • Either A or B hydraulic system
23
Q

What is the maximum tire ground speed?

A
  • 195 knots
24
Q

The brake wear indicators should extend beyond the brake flange with the parking brake in what position?

A
  • set
25
Q

Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by which hydraulic
system?

A
  • hydraulic system A
26
Q

The alternate brake system is powered by _________ and the normal brakes system is powered by _______.

A
  • hydraulic system A; hydraulic system B
27
Q

Antiskid protection is provided which brake system(s)?

A

on both brake system (normal and alternate)

28
Q

The ____________ stop rotation of the main gear wheels during landing gear retraction.

A
  • brakes automatically
29
Q

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

A
  • snubbers
30
Q

What happens Moving the LANDING GEAR lever to the OFF position?

A
  • hydraulic pressure from the landing gear system is removed
31
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 not down and locked (with either or both forward thrust levers retarded to idle and below
    800 feet AGL)
32
Q

What does an extinguished green landing gear indicator light indicate?

A
  • landing gear is not down and locked
33
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
34
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
  • At least one
35
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
36
Q

What effect on landing gear retraction does opening the Manual Extension Access Door have?

A
  • disables it
37
Q

With the landing gear lever ____________, manual landing gear extension is possible.

A
  • in any position
38
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
  • release uplocks; free-fall
39
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
40
Q

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

A
  • 7 degrees
41
Q

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

A

A lockout pin

42
Q

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

A
  • hydraulic system B
43
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
  • several braking applications
44
Q

Skid, locked wheel, touchdown, and hydroplane protection will be available ____________.

A
  • with the normal and alternate braking system
45
Q

The 737 parking brake can be set with _________.

A
  • A or B hydraulic system, or the accumulator if A and B are not pressurized
46
Q

What is the normal hydraulic brake pressure as indicated on the brake accumulator _________?

A
  • 3000 psi
47
Q

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

A
  • deceleration rate
48
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
  • 90 knots
49
Q

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

A
  • less than
50
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
  • advancing the forward thrust lever(s), except during the first 3 seconds after touchdown

SV STUDY GUIDE 737 (15 decks)

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