The illumination of the green landing gear light indicates that the landing gear is ? Knowledge > lift > off
The damping element in a landing gear shock absorber used on large aircrafts is ?
The damping element in a landing gear shock absorber used on large aircrafts
'Nose wheel shimmy' may be described as ?
'nose wheel shimmy' may be described as A possibly damaging vibration of nose wheel when moving on ground. The abs auto brake system being disconnected after landing A possibly damaging vibration of nose wheel when moving on ground.
1 auto brake disarm light
illuminated (amber)
speed brake lever moved to down detent during rto or landing
manual brakes applied during rto or landing
thrust lever(s) advanced during rto or landing
except during first 3 seconds after touchdown landing
landing made with rto selected
rto mode selected on ground
illuminates one to two seconds then extinguishes
a malfunction exists in automatic braking system
extinguished
auto brake select switch set to off
autobrake armed
2 auto brake select switch
off autobrake system deactivated
1 2 3 or max
selects desired deceleration rate landing
switch must be pulled out to select max deceleration
rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots
3 antiskid inoperative (antiskid inop) light
illuminated (amber) a system fault detected antiskid monitoring system
extinguished antiskid system operating normally. The purposes of oil and nitrogen in an oleo pneumatic strut are The oil supplies damping function the nitrogen supplies spring function.
1 auto brake disarm light
illuminated (amber)
speed brake lever moved to down detent during rto or landing
manual brakes applied during rto or landing
thrust lever(s) advanced during rto or landing
except during first 3 seconds after touchdown landing
landing made with rto selected
rto mode selected on ground
illuminates one to two seconds then extinguishes
a malfunction exists in automatic braking system
extinguished
auto brake select switch set to off
autobrake armed
2 auto brake select switch
off autobrake system deactivated
1 2 3 or max
selects desired deceleration rate landing
switch must be pulled out to select max deceleration
rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots
3 antiskid inoperative (antiskid inop) light
illuminated (amber) a system fault detected antiskid monitoring system
extinguished antiskid system operating normally. The highest load on torsion link in a bogie gear Whilst turning on ground with a small radius.
1 auto brake disarm light
illuminated (amber)
speed brake lever moved to down detent during rto or landing
manual brakes applied during rto or landing
thrust lever(s) advanced during rto or landing
except during first 3 seconds after touchdown landing
landing made with rto selected
rto mode selected on ground
illuminates one to two seconds then extinguishes
a malfunction exists in automatic braking system
extinguished
auto brake select switch set to off
autobrake armed
2 auto brake select switch
off autobrake system deactivated
1 2 3 or max
selects desired deceleration rate landing
switch must be pulled out to select max deceleration
rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots
3 antiskid inoperative (antiskid inop) light
illuminated (amber) a system fault detected antiskid monitoring system
extinguished antiskid system operating normally. The function of a fusible plug to Protect tyre against explosion due to excessive temperature.
1 auto brake disarm light
illuminated (amber)
speed brake lever moved to down detent during rto or landing
manual brakes applied during rto or landing
thrust lever(s) advanced during rto or landing
except during first 3 seconds after touchdown landing
landing made with rto selected
rto mode selected on ground
illuminates one to two seconds then extinguishes
a malfunction exists in automatic braking system
extinguished
auto brake select switch set to off
autobrake armed
2 auto brake select switch
off autobrake system deactivated
1 2 3 or max
selects desired deceleration rate landing
switch must be pulled out to select max deceleration
rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots
3 antiskid inoperative (antiskid inop) light
illuminated (amber) a system fault detected antiskid monitoring system
extinguished antiskid system operating normally. 8 Compared to a tyre fitted with an inner tube a tubeless tyre presents following characteristics 1 high heating2 valve fragility3 lower risk of bursting4 better adjustment to wheelsthe combination containing all correct statements Protect tyre against explosion due to excessive temperature.
1 auto brake disarm light
illuminated (amber)
speed brake lever moved to down detent during rto or landing
manual brakes applied during rto or landing
thrust lever(s) advanced during rto or landing
except during first 3 seconds after touchdown landing
landing made with rto selected
rto mode selected on ground
illuminates one to two seconds then extinguishes
a malfunction exists in automatic braking system
extinguished
auto brake select switch set to off
autobrake armed
2 auto brake select switch
off autobrake system deactivated
1 2 3 or max
selects desired deceleration rate landing
switch must be pulled out to select max deceleration
rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots
3 antiskid inoperative (antiskid inop) light
illuminated (amber) a system fault detected antiskid monitoring system
extinguished antiskid system operating normally. 9 An under inflated tyre will Experience increased wear at shoulders.
1 auto brake disarm light
illuminated (amber)
speed brake lever moved to down detent during rto or landing
manual brakes applied during rto or landing
thrust lever(s) advanced during rto or landing
except during first 3 seconds after touchdown landing
landing made with rto selected
rto mode selected on ground
illuminates one to two seconds then extinguishes
a malfunction exists in automatic braking system
extinguished
auto brake select switch set to off
autobrake armed
2 auto brake select switch
off autobrake system deactivated
1 2 3 or max
selects desired deceleration rate landing
switch must be pulled out to select max deceleration
rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots
3 antiskid inoperative (antiskid inop) light
illuminated (amber) a system fault detected antiskid monitoring system
extinguished antiskid system operating normally. 10 A scissor torsion link a component found on landing gears its function to Prevent any rotation of oleo strut in landing gear shock absorber. The torque links prevent rotation about vertical axis to maintain wheel alignment in fore and aft direction throughout vertical range of oleo travel in maintaining proper wheel alignment torque links stabilize any torsional oscillations (shimmy)
by their design torque links have their maximum mechanical advantage control when oleo compressed minimum advantage when oleo fully extended
sometime it doesn't work
. 11 Associate correct legend to each of numbered diagrams 841 cantilever 2 fork 3 half fork 4 dual wheels. The torque links prevent rotation about vertical axis to maintain wheel alignment in fore and aft direction throughout vertical range of oleo travel in maintaining proper wheel alignment torque links stabilize any torsional oscillations (shimmy)
by their design torque links have their maximum mechanical advantage control when oleo compressed minimum advantage when oleo fully extended
sometime it doesn't work
. 12 The function of an accumulator in a hydraulic brake system To supply a limited amount of brake energy in event of failure of hydraulic system normally supplying brakes. The torque links prevent rotation about vertical axis to maintain wheel alignment in fore and aft direction throughout vertical range of oleo travel in maintaining proper wheel alignment torque links stabilize any torsional oscillations (shimmy)
by their design torque links have their maximum mechanical advantage control when oleo compressed minimum advantage when oleo fully extended
sometime it doesn't work
. 13 A red or an amber light on an undercarriage position indicator signifies At least one wheel in travelling or unlocked condition. The torque links prevent rotation about vertical axis to maintain wheel alignment in fore and aft direction throughout vertical range of oleo travel in maintaining proper wheel alignment torque links stabilize any torsional oscillations (shimmy)
by their design torque links have their maximum mechanical advantage control when oleo compressed minimum advantage when oleo fully extended
sometime it doesn't work
. 14 In some aircraft there a protection device to avoid landing gear being inadvertently retracted on ground it consists of A latch located in landing gear lever. The torque links prevent rotation about vertical axis to maintain wheel alignment in fore and aft direction throughout vertical range of oleo travel in maintaining proper wheel alignment torque links stabilize any torsional oscillations (shimmy)
by their design torque links have their maximum mechanical advantage control when oleo compressed minimum advantage when oleo fully extended
sometime it doesn't work
. 15 Overcentre mechanisms in landing gear systems are used to Lock landing gear in up and/or down positions. That naturally depends on type of aircraft main undercarriage units are locked down mechanical overcentre geometric locks hook locks are generally used the up position. 16 The systems used emergency extension of landing systems may comprise 1 compressed c0²2 compressed nitrogen3 compressed oxygen4 mechanical/manual system5 freefallthe combination containing all of correct statements Lock landing gear in up and/or down positions. That naturally depends on type of aircraft main undercarriage units are locked down mechanical overcentre geometric locks hook locks are generally used the up position. 17 The working principle of anti skid system Reduction of brake pressure at slower turning wheels. Anti skid protection provided to allow maximum braking efficiency which in turn minimizes landing distances if pilot applies enough brake pedal force to cause slippage between tires the runway wheel speed transducer data received a control box will indicate a sudden deceleration the slipping wheel the control box will determine severity of impending skid send appropriate current signal to anti skid servo valve to reduce brake pressure accordingly dual servo valves reduce pressure either brake independently
therefore a single wheel skid will result in reduction of brake pressure at skidding wheel only. 18 Vle the maximum Flight speed with landing gear down. Anti skid protection provided to allow maximum braking efficiency which in turn minimizes landing distances if pilot applies enough brake pedal force to cause slippage between tires the runway wheel speed transducer data received a control box will indicate a sudden deceleration the slipping wheel the control box will determine severity of impending skid send appropriate current signal to anti skid servo valve to reduce brake pressure accordingly dual servo valves reduce pressure either brake independently
therefore a single wheel skid will result in reduction of brake pressure at skidding wheel only. 19 Vlo the maximum Speed at which landing gear can be operated with full safety. Anti skid protection provided to allow maximum braking efficiency which in turn minimizes landing distances if pilot applies enough brake pedal force to cause slippage between tires the runway wheel speed transducer data received a control box will indicate a sudden deceleration the slipping wheel the control box will determine severity of impending skid send appropriate current signal to anti skid servo valve to reduce brake pressure accordingly dual servo valves reduce pressure either brake independently
therefore a single wheel skid will result in reduction of brake pressure at skidding wheel only. 20 What the correct statement about rudder deflection and steering nose When performing a rudder check during taxiing an additional pilot action required to avoid deflection of nose wheel. Revised ecqb03 september 2016
during taxiing if pilots want to use rudder pedals to check rudder deflection without interfering with steering they have a pushbutton on either steering hand wheel (on a320) or tiller must be physically held so as to prevent aircraft from turning (for b737)
the hand wheel controller (tiller) only suitable at beginning of take off roll on a320 effectiveness of hand wheel diminished above 20 kt is canceled above 80 kt on b737 hand wheel controller was to be used under 60 kt. Exclusive rights: Content under private and protected license, reproduction prohibited and prosecuted.
