Hydraulics Flashcards
The primary purpose of the PTU (power transfer unit) is to supply the additional volume of hydraulic fluid needed to operate the autoslats and leading edge flaps and slats at the normal rate when ______ hydraulic pump volume is lost.
a. A system electric
b. A system engine driven
c. B system engine driven
d. Standby
B system engine driven
Reference: FRM 13.2.2.4
The purpose of the landing gear transfer unit is to supply the volume of hydraulic fluid needed to raise the landing gear at the normal rate when ______ pump volume is lost.
a. A system electric
b. A system engine-driven
c. B system engine-driven
d. Standby
A system engine-driven
Reference: FRM 13.2.2.5
If a leak develops in the system A hydraulic system in the engine-driven pump or its related lines, the reservoir quantity will indicate approximately _______ . If the leak develops in the electric motor-driven pump or its related lines, or components common to the engine and electric motor-driven pumps, thereservoir quantity will indicate _________.
a. 0, 0
b. 0, 20%
c. 20%, 0
d. 20%, 20%
20%, 0
Reference: FRM 13.2.2.2
If a leak develops in either pump, or line, or component of system B, the quantity decreases until it indicates approximately zero and system B pressure is lost. Will the PTU (power transfer unit) still
operate if the B system quantity indicates zero?
a. No, the PTU will not operate
b. Yes, standpipe fluid remaining is sufficient for PTU operation
c. No, B system quantity indicating zero indicates there is no standpipe fluid
d. None of the above
Yes, standpipe fluid remaining is sufficient for PTU operation
Reference: FRM 13.2.2.3
The Hydraulic system limitation states that Minimum fuel for ground operation of electric hydraulic pumps is 1,675 lbs in the respective tank. What are the respective tanks?
a. A system tank 2, B system tank 1
b. A system tank 1, B system tank 2
c. A and B system tank 1, standby system tank 2
d. A and standby system tank 1, B system tank 2
A system tank 1, B system tank 2
Reference: FRM 13.2.2.1
If a leak occurs in the standby system, the reservoir quantity decreases to ______ . The LOW QUANTITY light illuminates when the reservoir is approximately _____. System B continues to operate normally, however, the system B reservoir fluid level indication decreases and stabilizes at approximately ______ full.
a. 50%, half empty, 80%
b. 0, 0, 75%
c. 0, half empty, 72%
d. 20%, 0
0, half empty, 72%
Reference: FRM 13.2.3.3
If the hydraulic system is not properly pressurized, foaming can occur at higher altitudes and can be
recognized by _______ .
a. Pressure fluctuations
b. Blinking of the related low pressure lights
c. Master Caution and HYD annunciator lights may illuminate momentarily
d. All of the above
All of the above
Reference: FRM 13.2.4
During Pushback and Engine Start, the Captain informs the ground crew of hydraulic system status by stating _______ . This applies only if a bypass pin is NOT installed. True or False?
a. “B pumps ON, Brakes Set”, True
b. “B pumps ON, Brakes set”, False
c. “A pumps OFF, Brakes set”, True
d. “A pumps OFF, Brakes set”, False
“A pumps OFF, Brakes set”, False
Reference: AOM 7.1
The standby hydraulic system is provided as a backup if system A and/or B pressure is lost. The standby system can be activated manually or automatically and uses a single electric motor-driven pump to power _________ .
a. Thrust reversers, Rudder, LED’s (extend and retract), Standby Yaw Damper, Nose wheel
steering
b. Thrust reversers, Rudder, LED’s (extend only), Standby Yaw Damper, Nose wheel steering
c. Thrust reversers, Rudder, LED’s (extend and retract), Standby Yaw Damper
d. Thrust reversers, Rudder, LED’s (extend only), Standby Yaw Damper
Thrust reversers, Rudder, LED’s (extend only), Standby Yaw Damper
Reference: FRM 13.2.3
When is the Flight Control LOW PRESSURE light deactivated?
a. When the associated switch is placed to STBY RUD
b. When the standby rudder shutoff valve opens
c. Either a or b
d. Both a and b must occur
Both a and b must occur
Reference: FRM 13.1.3
