Reading...
Play button
Play button
Use LEFT and RIGHT arrow keys to navigate between flashcards;
Use UP and DOWN arrow keys to flip the card;
H to show hint;
A reads text to speech;
28 Cards in this Set
- Front
- Back
|
WHEN THE CONTROL WHEEL IS DISPLACED MORE THAN APPROXIMATELY 10 DEGREES
|
SPOILER DEFLECTION IS INITIATED
|
|
|
DURING LANDING, THE AUTO SPEED BARAKE SYSTEM OPERATES WHEN THESE CONDITION OCCUR
|
SPEED BRAKE LEVER IS IN ARMED POSITION
SPEED BRAKE ARMED LIGHT IS ILLUMINATED RADIO ALTITUDE IS LESS THAN 10 FEET LANDING GEAR STRUT COMPRESSES ON TOUCHDOWN BOTH THRUST LEVERS ARE RETARDED TO IDLE MAIN LANDING GEAR WHEEL SPIN UP MORE THAN 60K |
|
|
ANY LANDING GEAR
MAIN LANDING GEAR |
FLIGHT SPOILERS
GROUND SPOILERS |
|
|
IF THE SPEED BRAKE LEVER IS IN THE DOWN POSITION DURING LANDING OR REJECTED TO AUTO SPEED BRAKE
SYSTEM OPERATES |
MAIN LANDING GEAR WHEELS SPIN UP
BOTH THRUST LEVERS ARE RETARDED TO IDLE REVERSE THRUST LEVERS ARE POSITION FOR REVERSE THRUST |
|
|
IF THE AILERONS JAM
|
FORCE APPLIED TO THE FIRST OFFICERS CONTROL WHEEL OPERATES THE SPOILERS TO ROLL THE AIRPLANE
|
|
|
THE ELEVATOR IS MOVED BY
|
CONTROL COLUMNS
AUTOPILOT MACH TRIM SYSTEM |
|
|
MACH TRIM SYSTEM IS AUTOMATIC AT SPEEDS ABOVE
|
M 0.615 THE AIR DATA PART OF THE ADIRU SEES AIRSPEED AND SEND SIGNAL TO THE FCCS
|
|
|
STABILIZER MOVED BY
|
STABILIZER TRIM
MAIN ELECTRIC TRIM AUTOPILOT TRIM |
|
|
AUTOMATIC SPEED TRIM SYSTEM
|
ADJUST TRIM TO IMPROVE MANUAL FLIGHT CHARACTERISTICS. THE SYSTEM OPERATES WHEN THE AUTOPILOT IS DISENGAGED AND THERE ARE AIRPLANE CONDITIONS OF LOW GROSS WEIGHT, AFT CENTER OF GRAVITY AND HIGH THRUST
|
|
|
SPEED TRIM SENDS A SIGNAL THROUGH THE AUTOPILOT TRIM SYSTEM
|
TO MOVE THE STABILIZER
|
|
|
FEEL DIFF PRESS LIGHT ILLUMINATES
|
WHEN THE ELEVATOR FEEL COMPUTER SENSES A SIGNIFICANT HYDRAULIC PRESSURE DIFFERENCE BETWEEN HYDRAULIC SYSTEM A AND B AND THE FLAPS ARE UP
|
|
|
AIR PRESSURE DIFFERENTIAL CAUSED BY A |
BLOCKED PITOT TUBE WILL ALSO CAUSE THE FEEL DIFF PRESS, MASTER CAUTION AND FLIGHT CONT LIGHTS TO COME ON |
|
|
SPEED TRIM FAIL ILLUMINATED AMBER
|
INDICATES FAILURE OF THE SPEED TRIM SYSTEM
INDICATES FAILURE OF A SINGLE FCC CHANNEL WHEM MX LIGHT RECALL IS ACTIVATED AND LIGHT EXTINGUISHES WHEN MX SYSTEM IS RESET |
|
|
SPEED TRIM SYSTEM OPERATES MOST FREQUENTLY DURING T/O, CLIMBS AND GO-AROUNDS
|
AIRSPEED BETWEEN 100 KIAS AND MACH 0.5
10 SECONDS AFTER TAKEOFF 5 SECONDS FOLLOWING RELEASE OF TRIM SWITCHES AUTOPILOT NOT ENGAGED SENSING OF TRIM REQUIREMENT |
|
|
THE YAW DAMPER OPERATIONS ARE CONTROLLED THROUH
|
2 STALL MANAGEMENT YAW DAMPER SMYD COMPUTERS
|
|
|
THE LEFT SMYD COMPUTER SUPPLIES
|
YAW DAMPER INPUTS TO THE MAIN RUDDER PCU TO TELL HOW MUCH TO MOVE THE RUDDER
|
|
|
THE RIGHT SMYD COMPUTER SUPPLIES
|
TURN COORDINATION, GUST DAMPING AND DUTCH ROLL PREVENTION THROUGH THE STANDBY YAW DAMPER
|
|
|
THE ADIRUS SEND SPEED AND YAW RATE DATA
|
TO THE STALL MANAGEMENT YAW DAMPER COMPUTERS
|
|
|
YAW DAMPER PROTECTION IS AVAILABLE
|
THROUGH THE STANDBY YAW DAMPER
|
|
|
SPEEDBRAKES EXTENDED LIGHT ILLUMINATED IN FLIGHT
|
SPEED BRAKE LEVER IS BEYOND THE ARMED POSITION
TE FLAPS EXTENDED MORE THAN 10 OR RADIO ALTITUDE LESS THAN 800 FEET |
|
|
SPEEDBRAKES EXTENDED LIGHT ILLUMINATED ON THE GROUND
|
SPEED BRAKE LEVER IS IN THE DOWN DETEND
GROUND SPOILERS ARE NOT STOWED |
|
|
LE FLAPS
LE SLATS |
UP AND FULL EXTENDED
UP, EXTENDED, FULL EXTENDED |
|
|
THE FLAP SLAT ELECTRONICS UNIT OR FSEU SUPPLIES
|
TRAILING EDGE FLAP LOAD RELIEF FROM HIGHER THAN NORMAL AIR SPEEDS FOR FLAPS 40 AND 30
|
|
|
40 - 30
30 - 25 |
163 158
176 171 |
|
|
AUTOSLATS
|
ALTERNATE SOURCE OF POER IS PROVIDED BY SYSTEM A THROUGH A POWER TRANSFER UNIT IF A LOSS OF PRESSURE IS SENSED FROM THE HIGHER VOLUME SYSTEM B ENGINE DRIVEN PUMP
|
|
|
TE 5
TE 40 |
SLATS EXTENDED 1
SLATS FULL EXTENDED 5 |
|
|
THE FSEU MONITORS
|
THE TRAILING EDGE FLAPS FOR ASYMMETRY AND SKEW CONDITIONS. THE LEADING EDGE DEVICES FOR AN INCORRECT POSITION AND THE LEADING EDGE SLATS 2 THROUGH 7 FOR A SKEW CONDITION
|
|
|
THERE IS NO SKEW DETECTION FOR
|
THE LEADING EDGE FLAPS OR SLATS 1 AND 8 AND A SLAT SKEW IS NOT MONITORING DURING AUTO SLAT OPERATION
|
