Hydraulics System Flashcards
The aircraft has ______ hydraulic systems.
3
_____________ can power all flight controls with no decrease in aircraft controllability.
Either A or B hydraulic system
Normal operating pressure for each hydraulic system is ______________ psi.
3000
Positioning the ENG 1 hydraulic pump switch to OFF isolates fluid flow from the system components and the pump ________ to rotate.
continues
Pulling an engine fire warning switch shuts off the hydraulic fluid flow to the related engine-driven pump and ______________.
deactivates it LOW PRESSURE light
The minimum fuel for ground operation of electric hydraulic pumps is _____ in the related main tank
1676 lbs
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
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
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
A leak in hydraulic system B __________ the operation of the standby hydraulic system.
does not affect
The purpose of the PTU is 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
The purpose of the landing gear transfer unit is 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 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 ____________________ and uses a single electric motor-driven pump
can be activated manually or automatically
The standby hydraulic system powers the thrust reversers, rudder, ____________.
leading edge flaps and slats (extend only) and the standby yaw damper
Automatic operation of the standby hydraulic pump is initiated when loss of hydraulic system A or B; and __________
flaps extended; and airborne, or wheel speed greater than 60kt
Positioning either FLT CONTROL switch to STBY RUD, closes the related flight control shutoff valve; deactivates the related flight control LOW RPESSURE light; allows the standby system to power the rudder and thrust reversers; and ___________________________________________
all answers are correct
- activates the standby electric motor-driven pump
- opens the standby rudder shutoff valve
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, arms the ALTERNATE FLAPS position switch and _________________
- activates the standby electric motor-driven pump
- engages the alternate assymetrical flap protection computer
- positions the leading edge devices to FULL EXTEND
On the B737-800, what occurs when there is a leak in the standby hydraulic system ___________________________________________
the LOW QUANTITY light illuminates, and the system B reservoir fluid decreases to aprox 72%
An amber illuminated Electric Hydraulic Pump OVERHEAT light indicates ___________________________________________
all answers are correct
- the hydraulic fluis used to cool and lubricate the corresponding electric motor-driven pump has overheated
- the pump itself has overheated
Pulling the Engine 1 fire warning switch ____________ the respective hydraulic pump LOW PRESSURE lights
deactivates
Positioning the ELECTRIC HYDRAULIC PUMP Switch to ON ________________.
controls the related electric motor-driven pump
The HYDRAULIC System QUANTITY is shown on the DU, and indicates digital ____________ of hydraulic quantity
percentage
On the ground with both engines shutdown, a REFILL indication, illuminated white RF next to the Hydraulic quantity indicates ___________.
hydraulic quantity below 76%
An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to ___________.
all answers are correct
- ailerons and elevator
- rudder
An illuminated amber standby hydraulic LOW QUANTITY light indicates low quantity in standby hydraulic reservoir, and is ___________.
always armed
An illuminated amber standby hydraulic LOW PRESSURE light indicates low output pressure, and is ___________.
armed only when the standby hydaulic pump operation has been selected or automatic standby pump operation is activated
On the PFD/ND, hydraulic system quantity is displayed __________.
by pushing the MFD system (SYS) switch
