Closed Book Flashcards
PUSHING IN THE FEATHER BUTTON TO THE FEATHER POSITION
ALL OF THE ABOVE
DURING A RESTART, THE FEATHER BUTTON LIGHT REMAINS ON FOLLOWING PCO. YOU SHOULD
PULL THE E-HANDLE. IF THE LIGHT GOES OUT, PUSH THE E-HANDLE IN AND CONTINUE THE RESTART PROCEDURE.
THE NEGATIVE TORQUE SENSING SYSTEM
LIMITS NEGATIVE TORQUE TO APPROX -150 TO -500 SHP FOR THE OUTBOARD PROPELLERS
FAILURE OF AN ENGINE NTS LIGHT TO ILLUMINATE FOLLOWING ENGINE SHUTDOWN FROM LOW RPM WITH THE FUEL AND IGNITION SWITCH REQUIRES MAINTENANCE ACTION.
TRUE
DURING AN INFLIGHT RESTART, BLADE/ANGLE ROTATIONIS OBSERVED AFTER PUSHING PCO YOU SHOULD
EXECUTE THE EMERGENCY SHUTDOWN PROCEDURE
DURING A LOITER SHUTDOWN, RPM STABILIZES AT 8% AFTER THE E-HANDLE IS PULLED. YOU SHOULD
PERFORM THE PROP FAIL TO FEATHER PROCEDURES
UNDER EXTREMELY COLD CONDITIONS YOU MAY OPERATE AN ENGINE WITH OIL TEMPERATURE BETWEEN 50-60 DEGREES C PROVIDED
ALL OIL PX LIMITATIONS ARE MAINTAINED
WITH AN ENGINE OIL TEMPERATURE BETWEEN 0 AND 40 DEGREES C, THE MAXIMUM ALLOWABLE SHP IS
1000
THE MINIMUM RECOMMENDED AIRSPEED FOR A NORMAL INFLIGHT RESTART IS
170 KIAS
PITCHLOCK IS MECHANICALLY CAMMED OUT
BELOW 17 DEGREES BLADE ANGLE AND ABOVE 57 DEGREES BLADE ANGLE
IF FORCED TO OPERATE A PITCHLOCKED PROPELLER WITH AN INOPERATIVE ELECTRONIC SYNC SYSTEM, ATTEMPT TO
MAINTAIN RPM IN THE UNDERSPREED RANGE OF 96-98 PERCENT TO REINFORCE PITCHLOCK
PITCHLOCK PROVIDES PROTECTIONS AGAINST AN UNCOTROLLABLE OVERSPEED BY PREVENTING AN INCREASE OR DECREASE IN BLADE ANGLE
FALSE
PRIOR TO TURNING OFF THE FUEL/IGNITION SWITCH DURING PITCHLOCK PROP PROCEDURES, WHAT CAN BE DONE TO INCREASE SHP
DECREASE TAS
AFTER FUEL CHOPPING A PITVHLOCKED PROP, THE INSTRUMENTS INDICATIONS ARE: RPM 35%, SHP -300 TO -400, AND A FLASHING FEATHER VALVE LIGHT. YOU MAY ASSUME YOU HAVE STABILIZED NTS AND THE EMERGENCY SHUT DOWN HANDLE SHOULD BE PULLED
TRUE
THE PROPER PROCEDURE FOR HANDLING A PITCHLOCKED PROP WITHOUT OVERSPEED IS TO FUEL CHOPPED THE ENGINE IN THE TERMINAL AREA. WITH STABILIZED NTS, PULL THE EHANDLE.
FALSE
TEMPERATURE BELOW 0 DEGREES CELSIUS CAN RESULT IN ERRONEOUS ALTIMETER READINGS. TO ENSURE OBSTACLE CLEARANCE DURING APPROACH PHASE OF FLIGHT WHEN TEMPERATURES ARE BELOW 0, REFER TO FIH SECTION D FOR CORRECTIONS TO_ , _ AND _ IN THE FINAL APPROACH FIX
DECISION HEIGHT, MDA AND STEP DOWN FIXES
THE INDICATIONS OF A SPIN ARE
STALLED AOA, PEGGED TURN NEEDLE, AND STABILIZED AIRSPEED
OVERSPEEDING OF THE GEAR OR FLAPS, IF EXTENDED, IS LIKELY TO OCCUR DURING OUT OF CONTROL FLIGHT RECOVERY PROCEDURES. IF OVERSPEED OCCURS, FURTHER MOVEMENT OF THE FLAPS OR LANDING GEAR MAY RESULT IN ADDITIONAL
DAMAGE
THE MAX SYMMETRICAL G LIMIT FOR GROSS WEIGHTS ABOVE 125000 IS
2.0
AFTER POWER TO THE DAS, WAIT APPROX _ SECONDS BEFORE ENGAGING THE AUTOPILOT TO ENSURE THE STARTUP BIT IS COMPLETE
20
THE DAS REQUIRES REMOVAL OF STATIC PLUGS, PITOT COVERS, AND INERTIAL ALIGNMENT TO PASS A SUCCESSFUL IBIT
TRUE
THE COPILOT SHALL CALL “APPROACH ACTIVE” DURING FMS APPROACHES WHEN RNP VALUES SEQUENCES TO _ AND APPROACH IS DISPLAYED ON THE CDU-7000
RNP 0.3
THE RINU-G _ ARE/IS CERTIFIED FOR UTILIZING THE GPS AS THE PRIMARY MEANS OF NAVIGATION FOR OCEANIC, ENROUTE, TERMINAL, APPROACH OPERATIONS AND AS AN EXTERNAL FIXING SOURCE b
BOTH A AND B
HE ADDU IS POWERED BY
MON DC AND FLIGHT DC
THE ADDU ALERT LIGHT WILL ILLUMINATE WHEN THE AIRCRAFT ALTITUDE IS WITHIN A CAPTURE WINDOW OF _ FT OF THE SELECTED ALTITUDE, THE ALERT LIGHT GOES OUT WITH _ OF SELECTED ALTITUDE. AFTER ALTITUDE IS CAPTURED, IF THE AIRCRAFT DEVIATES MORE THAN _ FT THE ALERT LIGHT WILL ILLUMINATE.
1000/200/200
THE MLR 2020A-1 MULTIMODE RECEIVERS ARE LOCATED IN RACK J-2. THESE MULTIMODE RECIVERS
PROVIDE FM-IMMUNE VHF RECEPTION IN THE 108.0 TO 117.95 MHZ FREQUENCY RANGE
