SV: Hydraulics / Landing Gear / Brakes Flashcards
The operation of the standby hydraulic system is _______ by a leak in hydraulic system B.
not affected
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
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
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
The standby system uses a single electric motor-driven pump and ____________________ .
can be activated manually or automatically
The standby hydraulic system powers the thrust reversers, __________, and rudder.
leading edge flaps and slats (extend only) and the standby yaw damper
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
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
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
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%
What is indicated by an amber illuminated Electric Hydraulic Pump OVERHEAT light?
- the hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated
- the pump itself has overheated
The respective engine-driven hydraulic pump LOW PRESSURE light is ________ when pulling the Engine 1 fire warning switch.
deactivated
An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to which flight controls?
- ailerons and elevator
* rudder
An illuminated amber standby hydraulic LOW QUANTITY light is ___________ and indicates low quantity in the standby hydraulic reservoir.
always armed
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
When Positioning the ENG 1 hydraulic pump switch to OFF, the pump_____ to rotate and fluid flow is isolated from the system component.
continues
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
_____ is the minimum fuel for ground operation of electric hydraulic pumps in the related main tank.
1675 lbs
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
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
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
The operation of the standby hydraulic system _______ by a leak in hydraulic system B.
Is not affected
Which system can power all flight controls with no decrease in aircraft controllability?
Either A or B hydraulic system
What is the maximum tire ground speed?
195 knots
The brake wear indicators should extend beyond the brake flange with the parking brake in what position?
set
Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by which hydraulic system?
hydraulic system A
The alternate brake system is powered by _________ and the normal brakes system is powered by _______.
hydraulic system A; hydraulic system B
Antiskid protection is provided which brake system(s)?
on both brake system (normal and alternate)
The ____________ stop rotation of the main gear wheels during landing gear retraction.
brakes automatically
The nose wheels retract forward into the wheel well and nose wheel rotation is stopped by _________ during landing gear retraction.
snubbers
What happens Moving the LANDING GEAR lever to the OFF position?
hydraulic pressure from the landing gear system is removed
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)
What does an extinguished green landing gear indicator light indicate?
landing gear is not down and locked
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
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
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
What effect on landing gear retraction does opening the Manual Extension Access Door have?
disables it
With the landing gear lever ____________, manual landing gear extension is possible.
in any position
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
Nose wheel steering will be available _____________________.
when the nose gear is in the down position and compressed by the weight of the airplane
Pushing the rudder pedal down allows for nose wheel turning up to ______in both directions.
7 degrees
________ allows the aircraft to push back or be towed without depressurizing hydraulic system A.
A lockout pin
Switching the Nose Wheel Steering Switch to ALT, allows ____________ to provide power for nose wheel steering.
hydraulic system B
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
Skid, locked wheel, touchdown, and hydroplane protection will be available ____________.
with the normal and alternate braking system
The 737 parking brake can be set with _________.
A or B hydraulic system, or the accumulator if A and B are not pressurized
What is the normal hydraulic brake pressure as indicated on the brake accumulator _________?
3,000 psi
Placing the AUTO BRAKE Select Switch to 1, 2, 3, or MAX, selects the desired ________for touchdown.
deceleration rate
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 kts
On a dry runway, the maximum autobrake deceleration rate in the landing mode is _______ that produced by full pedal braking.
less than
After the autobraking has started decelerating, any of the following pilot actions disarm the system immediately and will illuminate the AUTO BRAKE DISARM light:
- 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
