B737 Landing Gear

When the manual extension access door is open: Manual landing gear extension is possible with landing gear lever in any position. Normal landing gear extension is still possible if hydraulic system B pressure is available. Landing gear retraction is enabled. Normal landing gear extension is possible with the loss of system A.

Damaged Tread Impact Fittings located in the wheel well ring opening. are intended to provide automatic braking to main gear wheels during retraction. provide positive uplock during main gear retraction. are intended to provide protection to wheel well components during gear retraction by preventing a gear with a spinning tire and loose tread from entering the wheel well. allow the landing gear transfer unit to use hydraulic system B pressure to raise the gear if hydraulic system A fails.

Which pressure is indicated by the hydraulic brake pressure indicator?. Normal pressure of 3500 psi. A maximum pressure of3500 psi. A normal precharge of2800 psi. A normal precharge of the brake accumulator of 1200 psi.

During alternate brake system operation, the following protection is provided: skid, locked wheel, touchdown and hydroplane. skid and hydroplane only. skid, locked wheel and hydroplane only. None of the above are correct.

If a landing is made with RTO selected: automatic braking action occurs at the RTO level. automatic braking occurs at the MAX level. the AUTO BRAKE DISARM light illuminates three seconds after touchdown. the AUTO BRAKE DISARM light illuminates two seconds after touchdown and no automatic braking action occurs.

Landing autobrake settings may be selected after touchdown: however, the AUTO BRAKE DISARM light will illuminate and autobrake application will not occur. however, autobrake action will occur only when both thrust levers are retracted to reverse thrust range. prior to decelerating through 60 knots groundspeed. after decelerating through 60 knots groundspeed.

After braking has started, which of the following pilot actions will disarm the system immediately and illuminate the AUTO BRAKE DISARM light: moving the SPEED BRAKE lever to the flight detent position. advancing the forward thrust lever(s), except during the first three seconds after touchdown for landing. applying manual brakes. Both band c are correct.

The air/ground system receives air/ground logic signals from: the altimeter. the cabin pressure controller. six sensors, two on each landing gear. the FMC positin updating from the GPS.

What system normally provides hydraulic pressure for nose wheel steering?. System A. System B. The Standby System. The nose wheel steering accumulator.

If the nose gear steering lockout pin is not installed for pushback or towing: the system B hydraulic pumps must be placed OFF. movement of the nose wheel is possible greater than 78 degrees left or right of center. the system A hydraulic pumps must be placed OFF. system A and B must be pressurized.

Which of the following is not part of the braking systems?. Antiskid protection. The parking brake. The brake accumulator. The nose wheel brakes.

Which of the following conditions must exist to arm the RTO mode prior to takeoff?. The AUTO BRAKE select switch positioned to ON. Wheel speed greater than 60 knots. Forward thrust levers positioned to IDLE. The ANTISKID switch positioned to RTO.

What could cause the amber ANTISKID INOP light to illuminate?. The AUTO BRAKE select switch positioned to OFF. A system fault bas been detected by the antiskid monitoring system. Forward thrust levers positioned to IDLE. The ANTISKID switch positioned to RTO.

What airspeed must be considered with a wheel well fire situation?. The extend limit speed of 280K/.72M. The retract landing gear speed of 245 knots maximum. 235 knots maximum for 20 minutes. The extend limit speed of270 knots/.82M.

What happens if you reject a takeoff after reaching 90 knots with the autobrakes in RTO?. Maximum braking when thrust levers are retarded to idle. Automatic braking when reverse thrust selected. Automatic speed brake deployment when thrust levers are retarded to idle. The AUTO BRAKE DISARM light will illuminate.

The brake pressure accumulator also provides pressure to maintain the parking brake when hydraulic systems A and B are depressurized. True. False.

Hydraulic pressure from System B will be used to raise the landing gear: when System A pressure is low and the landing lever is positioned up. when the ALTERNATE NOSE WHEEL switch is positioned ON. when the No. 1 engine RPM drops below a limit value (i.e. engine number 1 fails), with either main landing gear not up and locked, and the landing gear lever is positioned UP. after a failure of the No. 1 engine hydraulic pump with the landing gear still down and the landing gear lever is positioned up.