Hydraulic Scenario 02

Question 1

Enroute from MDW to DEN at FL340, you notice the following lights illuminate:
MASTER CAUTION
FLT CONTROL B LOW PRESSURE
HYD PUMPS ENG 2 LOW PRESSURE
HYD PUMPS ELEC 1 LOW PRESSURE

Q.4.8 What is your assessment of the problem?

Answer 1

Loss of system B hydraulics

Reference: FRM 13.1.3, 15.2.3.1

Question 2

Enroute from MDW to DEN at FL340, you notice the following lights illuminate:
MASTER CAUTION
FLT CONTROL B LOW PRESSURE
HYD PUMPS ENG 2 LOW PRESSURE
HYD PUMPS ELEC 1 LOW PRESSURE

Q.4.9 What major systems are affected?

Answer 2

B autopilot, yaw damper, trailing edge flaps and leading edge devices normal hydraulic pressure,
autobrake, normal brakes, engine 2 thrust reverser
normal hydraulic pressure, 2 spoilers each wing.

Reference: FRM 13.2.2, QRH 13.6

Question 3

Enroute from MDW to DEN at FL340, you notice the following lights illuminate:
MASTER CAUTION
FLT CONTROL B LOW PRESSURE
HYD PUMPS ENG 2 LOW PRESSURE
HYD PUMPS ELEC 1 LOW PRESSURE

Q.4.10 Why do you plan a flaps 15 landing?

Answer 3

To improve go-around capabilities.

Reference: AOM 5.11.1

Question 4

Enroute from MDW to DEN at FL340, you notice the following lights illuminate:
MASTER CAUTION
FLT CONTROL B LOW PRESSURE
HYD PUMPS ENG 2 LOW PRESSURE
HYD PUMPS ELEC 1 LOW PRESSURE

Q.4.11 What would you do if you also had STANDBY
HYD LOW QUANTITY?

Answer 4

Plan to land at the nearest suitable airport.

Reference: AOM 5.1.1

Question 5

Enroute from MDW to DEN at FL340, you notice the following lights illuminate:
MASTER CAUTION
FLT CONTROL B LOW PRESSURE
HYD PUMPS ENG 2 LOW PRESSURE
HYD PUMPS ELEC 1 LOW PRESSURE

Q.4.12 What should you consider prior to extending
the flaps?

Answer 5

Leading edge devices cannot be retracted after
extension with alternate flap extension system. The
drag penalty with leading edge devices extended
may make it impossible to reach an alternate field.

Reference: QRH 13.6

Question 6

Q.4.13 Before pushback, which hydraulic system
must be depressurized (both pumps OFF and LOW
PRESSURE lights illuminated)?

Answer 6

System A

RRrreRReference: AOM 3.13

Question 7

Q.4.14 The aircraft must not be towed forward unless
both engines are shut down and which hydraulic system is depressurized?

Answer 7

System A

Reference: AOM 3.13

Question 8

Q.4.15 How can the standby hydraulic pump be
activated?

Answer 8

Manually: By moving either FLT CONTROL switch to
STBY RUD or ALTERNATE FLAPS master switch to
ARM.

Automatically: Inflight or on the ground with a loss of
system A or B, under specific conditions,

or Force
Fight Monitor (FFM) activation.

Reference: FRM 13.2.3.1, 13.2.3.2

Question 9

Q.4.16 What is the significant difference in capability
between an engine-driven pump and an AC electric
motor-driven pump?

Answer 9

An engine-driven pump supplies six times the fluid
volume than the related electric motor-driven
hydraulic pump.

Reference: FRM 13.2.2

Question 10

Q.4.17 What does an illuminated OVERHEAT light on
the Electric Hydraulic Pump indicate?

Answer 10

The associated electric motor driven pump is
overheated, or the hydraulic fluid used to cool and
lubricate the corresponding electric motor driven
pump is overheated.

Reference: FRM 13.1.1, QRH 13.2

Question 11

Q.4.18 For which components does the standby
hydraulic system provide back up for Systems A and
or B?

Answer 11

• Thrust reversers
• Rudder
• Leading edge flaps and slats (extend only)
• Standby yaw damper

Reference: FRM 13.2.3