Hydraulics/Landing Gear/Brakes Flashcards
Will a leak in Hydraulic system B have an impact on the operations of the standby hydraulic system?
No
What is the purpose of the PTU?
To supply the additional volume of hydraulic fluid needed to operate the auto slats for 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, the gear is up and either main is not up and locked, and
the number 1 engine drops below a limit value
The standby system uses a single electric motor-driven pump and
can be activated automatically or manually
The standby hydraulic system powers
- the thrust reversers
- leading edge flaps and slats
- standby yaw damper
- Rudder
with the loss of system A or B what criteria is met for the Standby Hydraulic system to power the thrust reversers?
Flaps are extended, airborne or wheel speed is greater then 60 knots
Positioning either FLT CONTROL switch to STBY RUD does….
- 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.
Position the ALTERNATE FLAPS master switch to ARM
- activates the standby electric driven pump
- operates the trailing edge flaps bypass valve
- allows the standby system to power the leading edge flaps, slats, and thrust reversers
- arms the ALTERNATE FLAPS position switches
If there is a leak in the standby hydraulic system what should we expect
LOW QUANTITY light illuminates, the system B reservoir fluid decreases to approximately 72%
What is indicated by an amber illuminated electric hydraulic pump OVERHEAT light
Hydraulic fluid to cool and lubricate has overheated
the pump itself has overheated
When Engine 1 fire warning switch is pulled the what happens to the Hydraulic pump LOW PRESSURE light?
It is deactivated
A flight control LOW PRESSURE light indicates
System A or B pressure is low to the ailerons, elevator and rudder
the amber standby hydraulic LOW QUANTITY light is always armed and indicates
Low quantity in the standby hydraulic reservoir
An amber standby LOW PRESSURE light is armed only with the standby hydraulic pump operation has ben selected ______ or _____ and _____.
manually,
automatically
indicates low output.
Does shutting off ENG1 stop the pump?
No it continues to turn, its just isolated from the system
Is the LOW PRESSURE light deactivated after pulling the engine fire switch?
Yes, the related fluid flow to the engine is shut off.
what is the minimum fuel for ground operation of electric hydraulic pumps
1675 lbs
What happens if a leak develops in the A system hydraulic engine driven pump or related lines
a standpipe in the reservoir prevents a total system fluid loss
What happens if a leak develops in the A system hydraulic electric driven pump or 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
If System B has a leak is the standby hydraulic system affected?
No
Which system can power all flight controls with no decreases in aircraft controllability?
Either A or B
Max tire speed
195 knots
brake wear indicator should extend beyond the brake flange with the parking break
set
What hydraulic system powers the nose gear retraction?
system A
the alternate brake system is powered by…
the normal brake system is powered by
system A
system B
What brake system is anti skid provided
Both
What stops the rotation of the landing gear during retraction
the brakes automatically
What stops the rotation of the nose wheel on retraction?
snubbers
What happens Moving the landing gear lever to the off position
Hydraulic pressure is removed from the system
What does an extinguished green landing gear light indicate?
landing gear is not down and locked
Red landing gear light indicates
gear not down and locked
disagreement or in transit
(below 800 feet and thrust lever idle)
With the landing gear lever to down how does the system work?
Hydraulic pressure releases the uplocks
Combo of Hydraulic pressure, gravity and air loads
What effect does opening the Manual Extension Access door have?
It disables landing gear retraction.
What position must the landing gear lever be in in order to do manual extension of the gear
position does not affect the manual extension.
How does the manual release work?
It unlocks the up hooks, gravity and air loads secure it down and locked
Nose wheel steering is available when
down and locked with weight on wheels
Nose wheel steering with the rudder pedals is
7° side to side
What must be in place to push or tow the plane without depressurizing the hydraulic system
a lockout pin
Switching the nose wheel steering to
uses System B
If both systems fail can one sill use the brakes?
Yes, there should be residual pressure in the accumulators for several brake applications and parking brake
Normal and Alt braking systems both provide
Locked wheel, skid, touch down, and hydroplane protection
Parking brake can be set with
A, B, or accumulator pressure
What is the normal hydraulic brake pressure as indicated on th brake accumulator
3000 psi
Settings for the auto brakes selects
desired deceleration rate for touchdown
At what speed does RTO automatically give max brake pressure
at or above 90 knots
on a dry runway can manual breaking be more effective then Max Autobrake
yes
How can auto brake be disengaged?
Move speed brake lever full forward
Apply manual brakes
Advancing the thrust levers 3 sec after touchdown
What are the conditions for the PTU to operate 
- the aircraft must be airborne
- system be engine driven pump pressure is low
- Flaps are less than 15 but not up.
Landing gear transfer unit operation requirements
- Aircraft must be airborne 2. number one engine RPM is low
- landing gear lever is up
- either maingear is not up and lock
