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331

If the light is illuminated due to a leak in the #1 (System A) engine-driven pump, then System A quantity will 

a. Drop to approximately 0%.

b. Drop to approximately 20%.

c. Show approximately 72%.

d. show approximately 76%

Drop to approximately20%

332

Both engines are still operating. Turning OFF the #1 Engine Hydraulic PumpSwitch

a. will shut off fluid to thepump

b. will deactivate the pump Low Pressure light

c. does not affect the rotation of the pump

d. will stop the pump from rotating

c. does not affect the rotation of the pump

333

Which of the following statements is true if the LOW PRESSURE light (right) illuminates inflight?

a. There is a leak in Hydraulic SystemB.

b. It the light is intermittent, then there is a heavy demandon SystemB.

c. Output pressure of System B electric motor-driven pumpis low.

d. Output pressure of System B engine driven pump is low.

d. Output pressure of System B engine driven pump is low.

334

This light illuminates during takeoff, climbing through 1,000 feet AGL, and during flapretraction. Which statement below is mostcorrect?

a. The leading edge devices will retract slowly because of the low volume output of theelectric motor-drivenpump.

b. The leading edge devices will retract at a normal rate through the PTU.

c. The leading edge devices will notretract.

d. The leading edge devices must be retracted using the Alternate FlapSwitches.

b. The leading edge devices will retract at a normal rate through the PTU.

335

How would this condition effect the flap operation prior to landing?

a. The PTU should automatically aid in extending the leading edge devices with the trailingedge flaps less than 15 degrees, but not up.

b. The PTU should aid in extending the leading edge flaps and slats, but the autoslats willbe inoperative.

c. The PTU should not aid in extending the leading edgedevices.

d. The PTU should automatically aid in extending the trailing edgedevices.

a. The PTU should automatically aid in extending the leading edge devices with the trailingedge flaps less than 15 degrees, but not up.

336

With Hydraulic System B quantity near 0, what do theselights indicate?

a. System B is lost with no fluid left in thereservoir.

b. System B is lost with some fluid trapped in the reservoir.

c. System B pressure is normal but the Standby Hydraulic System islost.

d. System B and the Standby Hydraulic System are lost.

b. System B is lost with some fluid trapped in the reservoir.

337

When lowering the flaps withthiscondition,_____

a. the flaps will have to be lowered electrically with the aid of the PTU

b. the trailing edge flaps will be lowered electrically and the leading edge flaps and slats will be extended by thePTU

c. the trailing edge flaps and the leading edge devices willbe extended using the Alternate Flap Extension method

d. Landing must be made with the flapsup

c. the trailing edge flaps and the leading edge devices willbe extended using the Alternate Flap Extension method

338

In addition to both lights (above) being illuminated, the airplane is airborne, flaps are extended, and the FLT CONTROL B Hydraulic System Switch is ON. Which of the following conditions is alsotrue?

a. The Landing Gear Transfer Unit will operate.

b. Autopilot A will beinoperative.

c. Automatic operation of the Standby Hydraulic System will occur.

d. The Normal Brake System isavailable.

c. Automatic operation of the Standby Hydraulic System will occur.

339

With these lights illuminated' and switches positioned as shown on the Hydraulic Panel, the pressure in Hydraulic System A should read_____psi.

a.   1500

b.   3000

c.   0

d. 1000

c.   0

340

 

_____is/are not available with no pressure in Hydraulic SystemA.

a. All spoilers

b. The rudder

c. The elevator

d. Half of the flight spoilers and all of the ground spoilers

d. Half of the flight spoilers and all of the ground spoilers

341

If on descent, how would the landing gear be lowered with this condition?

a. The gear can be lowered using Hydraulic System B through the landing gear transferunit.

b. The gear can be lowered by the Standby HydraulicSystem.

c. The gear will have to be lowered manually.

d. The gear cannot belowered

c. The gear will have to be lowered manually.

342

In flight, what conditions could cause these two lights toilluminate?

a. The fluid used to cool and lubricate the Hydraulic System B electric-motor driven pumphas overheated, or the pump itself has over heated.

b. The Hydraulic System B electric motor driven pump has overheated, but the fluid used to cool that pump is stillbelow limits.

c. The fluid used to cool and lubricate the Hydraulic System B engine-driven pump has overheated, but the pump is still operating.

d. An overheat condition has been detected in Hydraulic SystemA.

a. The fluid used to cool and lubricate the Hydraulic System B electric-motor driven pumphas overheated, or the pump itself has over heated.

343

When the overheat was detected in Hydraulic System B, what happens to the corresponding electric motor driven pump?

a. The pump continues to operate with normalpressure.

b. The pump continues to operate at a reduced pressure.

c. The pump shuts off automatically.

d. The pump will eventually destruct if not shut down by thecrew manually.

c. The pump shuts off automatically.

344

The QRH directs the crew to switch the Hydraulic System Belectric this affect the operation of the Power Transfer Unit(PTU)?

a. While in flight, the PTU assists in the operation of the autoslats and leading edge flaps andslats at a reducedrate.

b. The PTU would automatically operate with flaps less than 15 but notup.

c. The PTU would automatically operate if you areairborne.

d. System B electric motor driven pump pressure does not determine operation of thePTU.

d. System B electric motor driven pump pressure does not determine operation of thePTU.

345

These four lights are illuminated at the same lime. Choose the answer below that most accurately describes which hydraulic system(s) is/arelost?

a. Hydraulic System Aonly

b. Hydraulic System Bonly

c. Standby Hydraulic Systemonly

d. Both Hydraulic System A and Hydraulic System B

d. Both Hydraulic System A and Hydraulic System B

346

Hydraulic Systems A and B are unavailable. How does this affect the BrakeSystem?

a. Braking is notavailable

b. Braking is available via trapped hydraulic pressure in the brake accumulator.

c. Braking is available via the Normal Brake Systempressure.

d. Braking is available via the Alternate Brake Systempressure.

b. Braking is available via trapped hydraulic pressure in the brake accumulator.

347

With the same conditions, which primary flight control(s) will still be pressurized?

a. The rudder using the Standby Hydraulic System.

b. The elevators using the Standby Hydraulic System.

c. The ailerons using the Standby Hydraulic System.

d. The rudder, elevators and ailerons using the Standby Hydraulic System.

a. The rudder using the Standby Hydraulic System.

348

The crew suspects a leak in Hydraulic Systems B as indicated above. Howwould the trailing edge (TE) flaps be extended in flight under theseconditions?

a. The TE flaps can be extended normally via the Standby HydraulicSystem.

b. The TE flaps can be extended hydraulically from System A viathe ALTERNATE FLAPS PositionSwitch

c. The TE flaps can be extended electrically via the ALTERNATE FLAP Position Switch.

d. The TE flaps cannot be extended when Hydraulic System B islost.

c. The TE flaps can be extended electrically via the ALTERNATE FLAP Position Switch.

349

After a few minutes, the crew notices that both Hydraulic Systems A and B are now unavailableas shown. How can the landing gear be extended prior tolanding?

a. Only by using manual landing gear extension.

b. Normally via the Standby HydraulicSystem.

c. Automatically via the Landing Gear TransferUnit

d. The landing gear cannot be extended, and the QRH directs the crew to apply the Gear up LandingProcedure.

a. Only by using manual landing gear extension.

350

Both Hydraulic Systems A and B are still unavailable after landing. Select the answer which best describes the operation of the nose wheel steering in this condition.

a. It does not work without pressure from Hydraulic Systems A or B.

b. It will work using the Alternate Nose Wheel Steeringselection.

c. It will work via the Nose Wheel Steeringaccumulator.

d. It will work via the Landing Gear Transfer Unit but with limited displacement in eitherdirection.

a. It does not work without pressure from Hydraulic Systems A or B.

351

If the standby hydraulic low quantity light is illuminated,           .

a. at least half of the standby fluid has been depleted

b. the B system has decreased to the 50%level

c. the PTU has lost hydraulic fluid

d. this light only arms with the standby pump operating and indicates normaloperation

a. at least half of the standby fluid has been depleted

352

This light is armed_____.

a. only when the standby pump is running

b. only when system B is pressurized

c. any time there is power on the aircraft

d. only when the engines are running

c. any time there is power on the aircraft

353

With this light illuminated, Hydraulic System B quantityshouldread    %.

a.20

b.76

c.0

d. 72

d. 72

354

System A low pressure light is illuminated on the overhead panel. With this light on, how can thegear be extended?

a. Use the manual gear extensionprocedures.

b. Gear cannot be extended.

c. Normal gear extension

d. The landing gear transfer unit will deploy the gear when normallyextended.

c. Normal gear extension

355

With the A hydraulic system engine driven pump low pressure light on and indicating volume in the A reservoir.

a. you must lower the landing gearmanually

b. you cannot retract the gear

c. gear will retract at a slower rate

d. only two spoilers on each wing work normally

c. gear will retract at a slower rate

356

With this light on during gear retraction, the landing gear transfer unit will activate with         .

a. Low RPM on the #2engine.

b. loss of Hydraulic System B

c. the loss of System A electric pump

d. low RPM on the #1  Engine

d. low RPM on the #1  Engine

357

The brake pressure indicator reads as shown (3000 psi) after the loss of Hydraulic Systems A and B. What type of problem does thisindicate?

a. There is too much pressure to the brakes, and they should be bled to 1000psi.

b. The brake accumulator was not pre-chargedcorrectly.

c. This indication is normal.

d. The indicator should only indicate a pre-charged pressure of 1000 psi, andis thereforeinop.

c. This indication is normal.

358

With the Gear Handle up after takeoff, these lights are illuminated. Whatis themost likelyproblem?

a. The left gear pin was leftinstalled.

b. The nose gear pin was leftinstalled.

c. Tread separation, on a right tire, impacted a fitting on the wheel well ring.

d. Number one engine driven pump waslost.

c. Tread separation, on a right tire, impacted a fitting on the wheel well ring.

359

With the damaged tire sensor broken, the rightmaingear         .

a. will have to be raised with the aid of thePTU

b. can be raised through the gear transferunit

c. will not retract

d. can be retractedmanually

c. will not retract

360

If the crew decides to return to the departurefield,               

a. they will have to land with anti-skidinoperative

b. landing is made with a normal gear configuration

c. the right main will be retracted forlanding

d. they will make a gear uplanding

b. landing is made with a normal gear configuration