737 Hydraulics

HYD118 - (6.130.10.5) 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

HYD110 - (6.130.10.4) A leak in hydraulic system B __________ the operation of the standby hydraulic system.

does not affect

HYD116 - (6.130.10.6) 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 60 knots

HYD124 - (6.130.20.2) On the ground with both engines shutdown, a REFILL indication, illuminated white RF next to the Hydraulic quantity indicates ___________.

hydraulic quantity below 76%

HYD106 - (1.30.19) The minimum fuel for ground operation of electric hydraulic pumps is _____ in the related main tank.

1676 lbs.

HYD103 - (6.130.20.2) Normal operating pressure for each hydraulic system is ______________ psi.

3,000

HYD117 - (6.130.10.5) 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 ___________________________________________

Activates the standby electric motor-driven pump, Opens the standby rudder shutoff valve.

HYD102 - (6.130.10.1) _____________ can power all flight controls with no decrease in aircraft controllability.

Either A or B hydraulic system

HYD120 - (6.130.20.1) An amber illuminated Electric Hydraulic Pump OVERHEAT light indicates ___________________________________________

Hydraulic fluid used to cool and lubricate the corresponding electric motor driven pump has overheated or the pump itself has overheated.

HYD119 - (6.130.10.7) 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 approximately 72%

HYD107 - (6.130.10.4) 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

HYD125 - (6.130.20.3) An illuminated amber Flight Control LOW PRESSURE light indicates low hydraulic system A or B pressure to ___________.

ailerons, elevator, and rudder

HYD126 - (6.130.20.4) An illuminated amber standby hydraulic LOW QUANTITY light indicates low quantity in standby hydraulic reservoir, and is ___________.

always armed

HYD127 - (6.130.20.4) An illuminated amber standby hydraulic LOW PRESSURE light indicates low output pressure, and is ___________.

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

HYD128 - (6.130.20.2) On the PFD/ND, hydraulic system quantity is displayed __________.

by pushing the MFD System (SYS) switch

HYD114 - (6.130.10.5) The standby system can ____________________ and uses a single electric motor-driven pump.

can be activated manually or automatically

HYD104 - (6.130.10.3) Positioning the ENG 1 hydraulic pump switch to OFF isolates fluid flow from the system components and the pump ________ to rotate.

continues

HYD122 - (6.130.10.3) Positioning the ELECTRIC HYDRAULIC PUMP Switch to ON ________________.

controls the related electric motor-driven pump

HYD121 - (6.130.10.3) Pulling the Engine 1 fire warning switch ____________ the respective hydraulic pump LOW PRESSURE lights.

deactivates

HYD105 - (6.130.10.3) Pulling an engine fire warning switch shuts off the hydraulic fluid flow to the related engine-driven pump and ______________.

deactivates it LOW PRESSURE light

HYD115 - (6.130.10.5) The standby hydraulic system powers the thrust reversers, rudder, ____________.

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

HYD123 - (6.130.20.2) The HYDRAULIC System QUANTITY is shown on the DU, and indicates digital ____________ of hydraulic quantity.

percentage

HYD112 - (6.130.10.4) 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

HYD111 - (6.130.10.4) 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

HYD113 - (6.130.10.4) 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

HYD109 - (6.130.10.4) 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

HYD108 - (6.130.10.4) 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

HYD101 - (6.130.10.1) The aircraft has ______ hydraulic systems.

three