Hydraulics / Landing Gear / Brakes

Question 1

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

Answer 1

15. not affected

Question 2

What is the purpose of the PTU?

Answer 2

• 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

Question 3

What is the purpose of the landing gear transfer unit?

Answer 3

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

Question 4

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

Answer 4

• the landing gear is positioned up and either main landing gear is not up and locked
  5.

Question 5

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

Answer 5

• can be activated manually or automatically

Question 6

The standby hydraulic system powers the thrust reversers, __________, and rudder.

Answer 6

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

Question 7

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

Answer 7

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

Question 8

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.

Answer 8

• all answers are correct

Question 9

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.

Answer 9

• activates the standby electric motor-driven pump

Question 10

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

Answer 10

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

Question 11

What is indicated by an amber illuminated Electric Hydraulic Pump OVERHEAT light?

Answer 11

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

Question 12

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

Answer 12

• deactivated

Question 13

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

Answer 13

• ailerons and elevator
• rudder

Question 14

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

Answer 14

• always armed

Question 15

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

Answer 15

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

Question 16

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

Answer 16

• continues

Question 17

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

Answer 17

• its LOW PRESSURE light is deactivated

Question 18

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

Answer 18

• 1675 lbs.

Question 19

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

Answer 19

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

Question 20

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

Answer 20

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

Question 21

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

Answer 21

• Is not affected

Question 22

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

Answer 22

• Either A or B hydraulic system

Question 23

What is the maximum tire ground speed?

Answer 23

• 195 knots

Question 24

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

Answer 24

• set

Question 25

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

Answer 25

* hydraulic system A

Question 26

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

Answer 26

* hydraulic system A; hydraulic system B

Question 27

Antiskid protection is provided which brake system(s)?

Answer 27

on both brake system (normal and alternate)

Question 28

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

Answer 28

* brakes automatically

Question 29

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

Answer 29

* snubbers

Question 30

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

Answer 30

* hydraulic pressure from the landing gear system is removed

Question 31

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).

Answer 31

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

Question 32

What does an extinguished green landing gear indicator light indicate?

Answer 32

* landing gear is not down and locked

Question 33

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

Answer 33

* hydraulic pressure, gravity, and air loads

Question 34

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

Answer 34

* At least one

Question 35

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.

Answer 35

* No. 1 engine RPM drops below a limit value

Question 36

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

Answer 36

* disables it

Question 37

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

Answer 37

* in any position

Question 38

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

Answer 38

* release uplocks; free-fall

Question 39

Nose wheel steering will be available _____________________.

Answer 39

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

Question 40

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

Answer 40

* 7 degrees

Question 41

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

Answer 41

A lockout pin

Question 42

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

Answer 42

* hydraulic system B

Question 43

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.

Answer 43

* several braking applications

Question 44

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

Answer 44

* with the normal and alternate braking system

Question 45

The 737 parking brake can be set with _________.

Answer 45

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

Question 46

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

Answer 46

* 3000 psi

Question 47

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

Answer 47

* deceleration rate

Question 48

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.

Answer 48

* 90 knots

Question 49

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

Answer 49

* less than

Question 50

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

Answer 50

* 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