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ERASED TEST, YOU MAY BE INTERESTED ON 737 AQP Landing Gear/ brakes
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Title of test:
737 AQP Landing Gear/ brakes

Description:
737 Landing Gear/ brakes

Author:
Skalar
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Creation Date:
02/11/2020

Category: Others

Number of questions: 37
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Content:
The maximum tire ground speed is _____. 195 knots 185 knots 175 knots.
Arming the RTO feature is _________ for all takeoffs, if operable. required no required.
The brake wear indicators should extend beyond the brake flange with the parking brake _____________. set released.
Hydraulic power for retraction, extension, and nose wheel steering is normally supplied by _______________. standby system hydraulic system A hydraulic system B.
The normal brake system is powered by _________ and the alternate brakes system is powered by _______. hydraulic system A; hydraulic system B hydraulic system B; hydraulic system B hydraulic system B; hydraulic system A.
Antiskid protection is provided _________________. with normal brakes only with alternate brakes only on both brake system (normal and alternate).
During retraction, the ____________ stop rotation of the main gear wheels. snubbers brakes automatically parking brake should be momentarily set to.
During retraction, the nose wheels retract forward into the wheel well and nose wheel rotation is stopped by _________. snubbers brakes automatically parking brake should be momentarily set to.
After retraction, the main gear are held in place by ______and the nose gear is held in place by ______________. hydraulic pressure; mechanical uplock mechanical uplocks; an overcenter lock rubber seals; hydraulic pressure.
Moving the LANDING GEAR lever to the OFF position ____________________. engages the over center locks removes hydraulic pressure from the landing gear system is not recommended below 235 knots.
An illuminated red landing gear indicator light indicates the related landing gear is in disagreement with LANDING GEAR lever position (in transits or unsafe), or ____________________. landing gear is up the landing gear manual extension must be used landing gear is not down and locked (with either or both forward thrust levers retarded to idle and below 800 feet AGL).
An extinguished green landing gear indicator light indicates _______________. landing gear is down and locked the landing gear manual extension must be used landing gear is not down and locked.
When the LANDING GEAR lever is moved to UP, _______________. the landing gear retracts the landing gear extends hydraulic pressure is removed from the landing gear.
When the LANDING GEAR lever is moved to DN, hydraulic system ___ pressure is used to release the uplocks. The landing gear extends by _______________. A; hydraulic pressure, gravity, and air loads B; gravity, and air loads STBY, hydraulic pressure, gravity, and air loads.
The landing gear is down and locked _________ green landing gear indicator light(s) (center panel and/or overhead panel) for each gear is/are illuminated. as long as one with both.
The landing gear transfer unit allows hydraulic system B to supply the volume of hydraulic fluid required to raise the landing gear at the normal rate when airborne, LANDING GEAR lever is positioned UP, either main landing gear is not up and locked and ________________. the A electric hydraulic pump is inoperative No. 1 engine RPM drops below a limit value No. 2 engine RPM drops below a limit value.
Manual landing gear extension is possible with the landing gear lever ____________. in any position UP or DOWN DOWN or OFF.
Manual gear releases on the flight deck are used to_________ that allow the gear to_________ to the down and locked position. engage uplocks; hydraulically extend release uplocks; hydraulically extend release uplocks; free-fall.
The nose wheel steering wheel _________________ rudder pedal steering. works in the opposite direction of the is secondary to the overrides.
Nose wheel steering is available _____________________. when the nose gear is in the down position and compressed by the weight of the airplane when the nose gear is in the down position at all times.
Pushing the rudder pedal allows for nose wheel turning up to ______in either direction. 7 degrees 25 degrees 78 degrees.
________ allows the aircraft to push back or be towed without depressurizing system A. A bypass switch on the forward panel Pulling nose wheel circuit breaker A lockout pin.
Placing the Nose Wheel Steering Switch to ALT, allows ____________ to provide power for nose wheel steering. hydraulic system A hydraulic system B the standby hydraulic system.
Skid, locked wheel, touchdown, and hydroplane protection is available ____________. with the normal and alternate braking system only with the normal braking system only with the alternate braking system.
If hydraulic system B is low or fails, _____________automatically supplies pressure to the alternate brake system. standby system pressure electric friction hydraulic system A.
The parking brake can be set with _________. hydraulic system A hydraulic system B A or B hydraulic system, or the accumulator if A and B are not pressurized.
If normal and alternate brake system pressure is lost, trapped hydraulic pressure in the brake accumulator can still provide ____________ or parking brake application. an unlimited number of normal braking applications several braking applications one brake application.
Normal hydraulic brake pressure as indicated on the brake accumulator _________. 3000 psi 2500 psi 1676 psi.
Anti-skid protection is provided in the _______________. normal braking system only alternate braking system only normal and alternate brake systems.
An amber illuminated AUTO BRAKE DISARM light indicates _______________. the auto brakes are set to MAX a malfunction exists in automatic braking system the AUTO BRAKE select switch is set to OF.
With the AUTO BRAKE Select Switch in RTO, maximum brake pressure is automatically applied when the thrust levers are retarded to idle at or above ____ knots. 120 90 60.
Placing the AUTO BRAKE Select Switch to 1, 2, 3, or MAX, selects desired landing. deceleration rate brake pressure.
An amber illuminated ANTISKID INOP light indicates _______________. a system fault is detected the anti-skid system need to be reset the auto brakes need to be armed.
The auto brake system uses ______________ to provide maximum deceleration for rejected takeoff. hydraulic system A pressure hydraulic system B pressure hydraulic system A or B pressure.
On dry runways, the maximum autobrake deceleration rate in the landing mode is _______ that produced by full pedal braking. more than less than equal to.
After the autobraking has started, any of the following pilot actions disarm the system immediately and illuminate the AUTO BRAKE DISARM light: moving speed brake lever to full forward or applying manual brakes advancing the forward thrust lever(s), except during the first 3 seconds after touchdown for landing or applying manual brakes all answers are correct.
What effect on landing gear retraction does opening the Manual Extension Access Door have? disables it does not effect.
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