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Systems1 > Hydraulics > Flashcards

Hydraulics Flashcards

1
Q

At the 2-hour point in flight you notice the right side HYD pressure is in excess of 3400 psi with indications of fluid loss. What is the possible cause of the problem?

A

An engine driven HYD pump malfunction

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2
Q

If the rudder power manual shutoff valve were inadvertently left closed, the ______, _______ and ________ would be deactivated.

A

APU System
A/R Boom
Powered Rudder

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3
Q

The right hydraulic system cannot be pressurized by the aux pump unless the __________ and _________ are off.

A

CIPS and Powered Rudder

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4
Q

Who’s brakes incorporate an anti-skid system?

A

The pilot’s brakes

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5
Q

During flight, you notice the #3 HYD pump inoperative light comes on and the right HYD quantity starts decreasing. What are you actions?

A

Immediately set the #3 HYD pump supply switch to close

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6
Q

When the left or right HYD pressure switch is set to off, the de-pressurization valve opens, connecting the pressure line to the return line. This reduces available pressure to ______ psi or less.

A

750

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7
Q

With _____ HYD system failure and _______, pull the anti-skid inboard breakers.

A

Left, only reserve brake pressure available for braking

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8
Q

Simultaneous operation of the ________ and __________ will result in slow operation of the gear and reduced climb out performance

A

Forward A/R pump and Landing gear

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9
Q

Left and Right HYD system pre-load pressure is approximately _______ psi @ 70F.

A

2000

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10
Q

Max speed for gear extension/retraction is ________ below 38,000ft. Max airspeed with gear extended is _______ below 30,500ft.

A

270; 320

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11
Q

The following conditions would prevent the landing gear from retracting normally.

A

Nose gear wheels not centered
Landing gear lever lock CB popped
Landing gear trucks not level and oleos fully extended

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12
Q

In the AUTO position, an auxiliary HYD pump will automatically go off when system pressure reaches ________, and comes on when the pressure drops to between 200 psi below this value and _________ psi.

A

2900 +/- 150, 2400

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13
Q

In the AUTO position, an auxiliary HYD pump will automatically turn on when system pressure reaches approximately ________ psi.

A

2400

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14
Q

With the left system auxiliary HYD pump switch held in Reserve Brake and with the battery power switch in NORM or EMER, electrical power is drawn directly from the _______.

A

Battery

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15
Q

In order to stop main wheel rotation during gear retraction _____.

A

HYD Pressure is automatically directed to the main gear brakes

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16
Q

Simultaneous operation of the landing gear and the ________ will cause slower gear retraction and reduced climb out performance

A

Forward A/R pumps

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17
Q

The normal main HYD system pressure range ______ psi.

A

2400-3050

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18
Q

Landing gear retraction on the ground is prevented because the main gear ______ are not extended

A

Oleos

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19
Q

In order for the nose gear steering to operate, the _____ HYD system must be pressurized

A

Right

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20
Q

Pulling the ____ bypasses the lock solenoid and allows the gear to be retracted regardless of the position of the safety switches

A

Override trigger

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21
Q

In order for the Left HYD system pressure to be built up using the AUX pump the ________.

A

Inboard spoiler must be cutoff

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22
Q

With only Reserve Brake pressure available to stop the aircraft and a fully charged Reserve Brake system, approximately _______ applications of the pilot’s brake will deplete the reservoir brake pressure.

A

3

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23
Q

Normal Reserve Brake pressure is _______ to _______.

A

1300 to 3050

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24
Q

Prior to pressurizing the Left HYD system while on the ground, the pilot must ensure ______.

A

No personnel are standing near the wheel well doors

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25
Q

When towing the airplane, de-pressurize the Right HYD system and ___.

A

Do not turn or hold the steering wheel

26
Q

Normally the AUX pumps are off during flight because ________.

A

They draw fluid from the main system return lines

27
Q

The rudder power manual shutoff valve must be open prior to flight since it is _____.

A

Not accessible during flight

28
Q

The HYD pump supply shutoff valve can be controlled in the cockpit by the _____ or ______.

A

Engine fire switches, HYD pump supply switches

29
Q

Placing the HYD pressure switch to the on position _______.

A

Closes the HYD depressurization valve

30
Q

The _____ pump is used as an alternate source of pressure for the pilot’s brakes

A

Left Auxiliary

31
Q

The HYD fluid reservoir should be considered empty when the gauge indicates approximately _______.

A

1 gallon

32
Q

A _____ will be indicated on the left HYD system indicator gage after the landing gear is retracted.

A

Drop of approximately 1 gallon

33
Q

The only component that can be crossed over from the left HYD system to the right HYD system is the ______.

A

Landing Gear

34
Q

If the Reserve brake pressure gage indicates 1300 psi, with the left HYD system depressurized, _____ brake application(s) will be available

A

1

35
Q

The HYD pump inoperative lights will flash _____.

A

Prior to engine start or anytime the system is depressurized

36
Q

When using the left AUX pump to recharge the Reserve brake system, the HYD fluid supply is drawn directly from the _____.

A

Main system return lines

37
Q

Which components normally powered by the Right HYD system can be operated by either HYD system by use of the cross over valve

A

Boom Controls
Main Flaps
APU Start System
Power Rudder

38
Q

The HYD quantity gauge for each system should indicate ______ after engine start

A

A minimum of 4.0 gallons

39
Q

Do not approach overheated brakes for ______ minutes

A

30

40
Q

Premature retraction of the landing gear after takeoff may cause the aircraft to _____ since open gear doors increase drag.

A

Settle

41
Q

When the nose gear steering fails, the aircraft should ______.

A

Only be taxied as necessary to clear the active runway

42
Q

With the Reserve Brake system fully charged, and the Left HYD system depressurized, enough pressure is available for approximately ______ applications of the pilot’s brakes

A

3

43
Q

After the final turn to line up with the parking spot, the aircraft should be taxied in a straight line for a short distance to _______.

A

Eliminate torsional loads on the main gear

44
Q

A Solenoid lock in the gear handle will not allow the landing gear to be raised unless both main gear trucks are level, both main gear oleos are extended, and ____.

A

The nose gear is centered

45
Q

HYD pump isolation in excess of ____ can result in self-destruction of the pump.

A

5 minutes

46
Q

The landing gear position indicators display the _____ position when electrical power is lost.

A

Intermediate

47
Q

The anti-skid system can cycle as fast as ____ cycles per second, causing loss of accumulator pressure in a very short time

A

3

48
Q

Reserve Brake accumulator pre-load pressure is approximately ____ psi @ 70F

A

1000

49
Q

It is safe to use the crossover valve after loss of fluid from either system provided ______.

A

Pressure can be built up and maintained in the affected system with the appropriate HYD pressure and AUX pump switches on

50
Q

The crews first directed action for a problem of Low HYD pressure with no other indications is to _______.

A

The crews first directed action for a problem of Low HYD pressure with no other indications is to _______.

51
Q

In the event of a complete failure of a HYD system or leak that cannot be controlled ______.

A

Land as soon as practicable

52
Q

What is the purpose of the hydraulic accumulators?

A

Protect hydraulic components against sudden pressure surges.

53
Q

Nosewheel steering is normally limited to _____________ degrees with the steering wheel and __________ degrees when using the rudder pedals

A

45, 8

54
Q

Both the red landing gear warning light knob and the warning horn come on ____________.

A

if one or more throttles is retarded to near idle and any gear is not down and locked

55
Q

Do not pressurize the reserve brake above ___________ when the parking brake is set; check valves will dump fluid overboard

A

3,100 psi

56
Q

What prevents an accidental collapse of the landing gear while the airplane is on the ground?

A

External ground safety locks

57
Q

Without using the position indicators in the cockpit, how do you know the gear’s position?

A

Alignment stripes, truck level indicators, oleo extension indicators

58
Q

An electrically driven pump in each system supplies hydraulic pressure for emergency use and for brake operation during ground operation and handling. (True or False)

A

True

59
Q

With inoperative rudder pedal nosewheel steering, the pilot in the left seat will keep his/her hand on the tiller until reaching ____________.

A

Vmcg + 20

60
Q

When setting parking brakes for engine start, pressurize the reserve brake accumulator until a pressure increase of at least __________ psi above preload pressure is observed.

A

300

61
Q

If both landing gear safety switches fail to the airborne position, the engines will remain in flight idle, the _________ will not operate normally, and the rudder pedal nosewheel steering will be inoperative

A

Pilot’s brakes

Systems1 (7 decks)

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