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60 Cards in this Set
- Front
- Back
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Landing gear operation is _________ controlled and _________ operated. |
Electrically Controlled
Hydraulically Operated |
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Which hydraulic system powers the "Main Landing Gear" system?
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#2 Main Hydraulic System
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Which hydraulic system powers the Main Landing Gear "Brakes"?
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#1 Main Hydraulic System
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The Emergency/Parking brake system is powered through which hydraulic system?
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#2 Main Hydraulic System
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Which hydraulic system powers the "Nose Wheel Steering"?
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#2 Main Hydraulic System
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In the event that the Main Landing Gear extension system fails, what provides the backup means for extending the gear?
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The "Alternate Landing Gear Extension System".
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The Alternate Landing Gear Extension System is powered how?
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By hydraulic system #4 (Auxiliary System).
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What provides an alternate means of verifying that the Main Landing Gear is down and locked?
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The "Alternate Downlock Verification System".
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The Main Landing Gear extends _____ and retracts ______.
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Extends Forward
Retracts Aft |
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How many doors are there on the "Main Gear"?
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Two (2) sets of doors.
Forward Doors Aft Doors |
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Do the gear doors remain open or closed with the main gear extended?
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The "Forward Doors" remain OPEN with the gear extended.
The "Aft Doors" will close. |
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How are the gear doors controlled for the Main Gear?
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The forward doors are mechanically linked to the gear strut.
The aft doors are hydraulically sequenced doors. |
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The Nose Gear extends ______ and retracts ______.
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Extends Aft
Retracts Forward |
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How many "pairs" of doors are there for the nose gear?
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Two (2)
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The forward doors for the nose gear are sequenced how?
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Hydraulically
They open and close automatically with the gears extension and retraction. |
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How are the aft nose gear doors sequenced?
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Mechanically
They are mechanically linked to the nose strut. |
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Landing gear operation is controlled and monitored from what panel?
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Landing Gear Control Panel
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What must be accomplished to allow the gear selector handle to move?
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The "Lock Release Lever" must be held in the down position to allow the gear selector to move in either direction.
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What indicates that the gear is in transition?
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The gear selector handle will illuminate.
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Where are the three (3) "Alternate Downlock Verification" lights located?
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Under the "Landing Gear Alternate Extension" panel on the flight deck floor.
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When will the landing gear warning horn sound?
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Gear is "UP"
1. The flaps are greater than 8.5 degrees 2. "Both" power levers are aft of the "RATING" detent. 3. "Either" engine torque below 50% "or" Gear is "UP" The airspeed is below 156 kts with "both" power levers "near" the Flight Idle Detent (within approx. 12 degrees of flight idle). |
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At what time is it possible to "MUTE" the landing gear horn?
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The horn may be muted when only one power lever is pulled aft towards flight idle.
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How may the Gear Horn Mute be tested?
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By pressing the "HORN MUTE/TEST" switch to the "TEST" position.
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What is indicated if the "LDG GEAR INOP" caution message is displayed?
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Failure of a gear door sequencing valve.
"or" Failure of a proximity sensor on any of the gear doors. |
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What must be accomplished if the "LDG GEAR INOP" caution light illuminates?
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The landing gear must be extended using the "Alternate Landing Gear Extension" method.
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At what times would it be required to extend the gear using the "Alternate Landing Gear Extension" method?
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1. "LDG GEAR INOP" caution message is displayed.
2. Loss of the #2 Main Hydraulic System fluid. 3. The landing gear indication fails. |
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What steps are required to extend the main landing gear using the "Alternate Landing Gear Extension" method?
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1. Select the inhibit switch to "INHIBIT" on the panel above the first officer's seat.
2. Place the landing gear handle in the "down" position. 3. Open the "Landing Gear Alternate Release" door above the first officer's seat. 4. Pull the "Main Landing Gear Release" handle to release the uplocks and allow the main gear to free fall down. |
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What is accomplished when the inhibit switch is selected to the "INHIBIT" position?
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The electrical command from the "normal" gear extension system is inhibited to the solenoid valve.
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Opening the "Landing Gear Alternate Release" door in the ceiling actually accomplishes what?
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1. It mechanically opens a bypass valve in the normal extension system.
2. It allows access to the "Main L/G Release" handle. |
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The "Alternate Gear Extension System" utilizes hydraulic pressure from what system?
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Hydraulic System #4 - Auxiliary Hydraulic System
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What is the fluid capacity for the auxiliary Hydraulic System?
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1.2 quarts
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Where is the reservoir physically located for the Auxiliary hydraulic system?
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The Right/Forward/Lower compartment of the flight deck.
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Is there any fluid quantity indication on the flight deck for the Auxiliary hydraulic system?
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No
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Opening the "Landing Gear Alternate Extension" door on the flight deck floor allows access to what?
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1. The alternate extension hand pump.
2. The nose landing gear release handle. 3. The alternate downlock verification system. |
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What will automatically happen when the "Landing Gear Alternate Extension" door on the cockpit floor is opened?
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It will mechanically "CLOSE" the main landing gear alternate selector valve.
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What occurs when the "Nose L/G Release" handle is pulled?
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The uplocks are released on both nose gear doors and the nose gear is allowed to free fall down.
Airflow will assist in the gears extension. |
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Where is the pump handle stowed to operate the main landing gear pump?
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Behind the first officer's seat.
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Which hydraulic system powers the "Main Brakes"?
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#1 Main Hydraulic System
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How many "Anti-Skid Control Units" are there for the main brakes?
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Four (4)
One for each wheel. |
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The "Anti-Skid Control Units" has the following functions:
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- Monitors the "Main Gear" wheel speeds.
- Modulates the brake pressure to each individual wheel to prevent lock up. - Gives maximum braking at all levels of runway friction. |
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Where is the "Anti-Skid" control switch located?
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On the first officers glareshield.
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When selected to "ON", at what time will the Anti-Skid become operational?
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TAXI
Above 10 kts LANDING Weight on wheels with the gear speed above 35 kts. "or" 5 seconds after weight on wheels. |
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At what time is the Anti-Skid system deactivated?
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Wheel speeds below 10 kts.
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At what times will the "Anti-Skid" system "Self Test" itself?
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1. When the anti-skid is selected to "ON".
2. When the anti-skid is selected to the "TEST" position. |
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What will be indicated when the Anti-Skid system is tested while:
On Ground? / Inflight? |
ON GROUND:
Both the "INBD ANTISKID" and "OUTBD ANTISKID" caution lights will illuminate for 6 seconds. INFLIGHT: Both the "INBD ANTISKID" and "OUTBD ANTISKID" caution lights will illuminate for 3 seconds only. |
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Which hydraulic system powers the "Parking/Emergency Brake" system?
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#2 Main Hydraulic System
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The parking brake "accumulator" will provide up to how many brake applications with the hydraulics depressurized?
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Six (6)
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Where is the "Emergency/Park Brake" hydraulic pressure indicated?
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1. On the "PK BRAKE" indicator on the bottom of MFD2.
2. On the remote pressure gauge in the right wing fairing. |
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What is the "minimum" parking brake pressure required prior to starting the engines?
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Starting the Left engine first: 1,000 PSI
Starting the Right engine first: 500 PSI |
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Is there any anti-skid protection when using the "Emergency Brake" to stop the aircraft?
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No
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If the Parking Brake hydraulic pressure has fallen below the minimum engine starting pressure, how can it be restored?
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By using the manually operated hand pump in the right landing gear wheel well.
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Is it permissible to use the accumulator pressure gauge located in the right wing fairing to determine the minimum parking brake pressure for starting the engines?
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No
Use the indication on MFD2 only! |
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Which hydraulic system powers the nose wheel steering system?
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#2 Main Hydraulic System
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What is the nose wheel steering limits for:
Rudders? / Tiller? / Free Caster? |
Rudders: +/- 8 degrees
Tiller: +/- 70 degrees Free Caster: +/- 120 degrees |
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Will the nose wheel automatically "center" itself during nose wheel retraction?
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Yes
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What conditions must be met for the nose wheel "Tiller" to be operational?
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1. The steering switch must be selected to "ON".
2. The nose wheel must be within +/- 70 degrees of center. 3. Hydraulic System #2 pressure must be available. |
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What indication is there in the cockpit to determine the nose wheel position?
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The tiller has index marks on it to indicate the relative position of the nose wheel.
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At what times will the nose wheel steering system revert to the "Free Caster" mode?
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1. The nose wheel angle exceeds +/- 70 degrees.
2. The "Steering Control Unit" fails. 3. The steering switch is selected to "OFF". |
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When operating in the "Free Caster" mode what may be required to control the steering of the aircraft?
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Differential power and braking may be required.
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When operating in the "Free Caster" mode why is it recommended to turn the steering switch to the "OFF" position?
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To prevent the nose wheel from suddenly "centering" when within 70 degrees of center.
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