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33 Cards in this Set

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IMMEDIATE ACTION EMERGENCY STEPS-NOTE
THE URGENCY OF CERTAIN EMERGENCIES REQUIRES IMMEDIATE AND INSTINCTIVE ACTION BY THE PILOT. THE MOST IMPORTANT SINGLE CONSIDERATION IS HELICOPTER CONTROL. ALL OTHER PROCEDURES ARE SUBORDINATE TO THIS REQUIREMENT.
EMER SHUTDOWN-WARNING
COMPLETE LOSS OF DC POWER WILL RESULT IN A LOSS OF ROTOR RPM INDICATIONS.
EMER SHUTDOWN-NOTE
BEFORE TURNING THE BATTERY SWITCH OFF DURING IN-FLIGHT EMERGENCIES REQUIRING EMER SHUTDOWN, THE PILOT SHOULD CONSIDER MAYDAY CALL, TRANSPONDER EMERGENCY, AND THE POSSIBLE ADVERSE EFFECTS OF TOTAL ELECTRICAL FAILURE. THE LOSS OF ALL CDS INDICATIONS WILL OCCUR.
FADEC MANUAL OPERATION-WARNING
IF THE THROTTLE IS NOT CLOSED, EXCESSIVE LEFT AND RIGHT YAWS MAY CAUSE LOSS OF AIRCRAFT CONTROL JUST PRIOR TO TOUCHDOWN.
ENGINE MALFUNCTION- PARTIAL OR COMPLETE POWER LOSS- WARNING
DO NOT RESPOND TO THE RPM AUDIO AND/OR DISPLAY ON MFD AND/OR MPD WITHOUT FIRST CONFIRMING ENGINE FAILURE BY OBSERVING ONE OR MORE OF THE OTHER INDICATIONS. NORMAL INDICATIONS SIGNIFY THAT THE ENGINE IS FUNCTIONING PROPERLY AND THAT THERE IS A MALFUNCTION IN THE ENGINE OR ROTOR INDICATION SYSTEM(S).
AUTOROTATIONAL GLIDE CHARACTERISTICS CHART-NOTE
AUTOROTATIONAL DESCENT PERFORMANCE IS A FUNCTION OF AIRSPEED AND IS ESSENTIALY UNAFFECTED BY DENSITY ALTITUDE AND GROSS WEIGHT.
FADEC FAILURE-CAUTION
-ENGINE INSTABILITY OR SURGE, IN MANUAL MODE, IS POSSIBLE ABOVE ALTITUDES OF 13000 FT. THE PILOT SHOULD BE PREPARED FOR ENGINE SURGE/INSTABILITY IF RAPID ACCELERATIONS OR DECELERATIONS ARE REQUIRED IN MANUAL MODE.
FADEC FAILURE-NOTE
TURNING THE FADEC CIRCUIT BREAKER SWITCH TO THE OFF POSITION AT ENGINE SPEEDS BELOW 85% NP MAY RESULT IN INTERMITTENT ACTIVATION OF THE FADEC FAIL AND FADEC MANUAL WARNING MESSAGES AND AUDIO TONES.IF THERE IS A COMPLETE LOSS OF AIRFRAME POWER AND THE PMA IS NOT PRODUCING POWER TO THE ECU, NO FADEC WARNING MESSAGES OR AUDIO TONES WILL BE ACTIVATED. WITH THE FADEC CIRCUIT BREAKER TO THE OFF POSITION OR COMPLETE LOSS OF ELECTRICAL POWER AT NG SPEEDS BELOW APPROXIMATELY 70%, ENGINE MAY FLAME OUT.
FADEC FAILURE-FIXED FUEL FLOW WARNING
-REGARDLESS OF ANNUNCIATOR INDICATION, THE FADEC AUTO/MAN SWITCH SHALL BE PLACED IN THE MAUAL MODE.
-FAILURE TO SWITCH TO MANUAL MODE WILL CAUSE MAIN ROTOR RPM TO DROOP/OVERSPEED AS COLLECTIVE IS INCREASED/DECREASED.
FADEC FAILURE-FAIL TO MANUAL MODE-CAUTION
THE FADEC MANUAL MODE IS DESIGNED FOR POWER MODULATION UPON SELECTION/ECU FAILURE. WHEN PERFORMING FADEC MANUAL OPERATIONS, THE PILOT MUST COORDINATE THROTTLE AND COLLECTIVE INPUTS. FAILURE TO DO SO MAY RESULT IN ENGINE OVERSPEED, OVERTEMP, OVERTORQUE, OR INADVERTENT ACTIVATION OF THE NP OVERSPEED PROTECTION SYSTEM. THE PILOT MUST ALSO RATE/ LIMIT THROTTLE MOVEMENT TO PREVENT ENGINE SURGES AS THE ENGINE IS NOT SELF-RECOVERABLE FROM STALL IN THE FADEC MANUAL MODE.
FADEC FAILURE-FAIL TO MANUAL MODE-CAUTION 2
PILOT PROCEDURES FOR BOTH FAILURES, FIXED FUEL FLOW AND FAIL TO MANUAL MODE ARE THE SAME.
FADEC DEGRADE NOTE
CREW MAY WANT TO CONSIDER REDUCING THROTTLE TO THE INDEX MARK.
EBF SWITCH-- FILTER SEGMENT LIGHT ILLUMINATION (INTERMITTENT OR STEADY)- CAUTION
OPERATING AIRCRAFT WITH THE FILTER BYPASS DOOR OPEN CHANNELS UNFILTERED AIR DIRECTLY INTO THE ENGINE INTAKE. ENGINE DAMAGE AND POWER LOSS WILL RESULT IF SOLID AIRBORNE PARTICLES ARE PRESENT. LONGER OPERATION AND/OR HEAVIER AIRBORNE PARTICULATE WILL RESULT IN INCREASED ENGINE DAMAGE AND INCREASED POWER LOSS.
COMPLETE LOSS OF TAIL ROTOR THRUST-WARNING
HELICOPTER SIDESLIP MAY BECOME UNCONTROLLABLE AND WILL BEGIN TO SPIN ON ITS VERTICAL AXIS AND AIRSPEEDS BELOW 40 KNOTS. DEGREE OF ROLL AND SIDESLIP MAY BE VARIED BY VARYING THROTTLE AND/OR COLLECTIVE. AUTOROTATION MAY BE THE ONLY OPTION.
FIXED PEDAL AT A HOVER NOTE
-THE MINIMUM SPEED REQUIRED FOR DIRECTIONAL CONTROL CAN CHANGE AND IS DEPENDENT UPON THE AMOUNT OF TORQUE APPLIED IN THE ROTOR SYSTEM, THE AMOUNT OF PEDAL APPLIED, AIRCRAFT WEIGHT, AND WIND CONDITIONS.
-WHEN A FIXED PEDAL MALFUNCTION OCCURS NEAR A "NEUTRAL" PEDAL SETTING; DURING THE TOUCHDOWN PHASE IT CAN CHANGE INTO EITHER A FIXED LEFT OR RIGHT PEDAL SETTING, DEPENDING UPON THE CONDITIONS AT THE TIME OF TOUCHDOWN. THE PILOT MUST BE AWARE OF THIS AND ADJUST FLIGHT CONTROLS ACCORDINGLY.
MAIN DRIVE SHAFT FAILURE-NOTE
THE ENGINE MUST CONTINUE TO OPERATE IN ORDER TO PROVIDE TAIL ROTOR CONTROL. PILOTS NEED TO BE AWARE THAT THE FADEC SYSTEM MAY FAIL FOLLOWING A MAIN DRIVESHAFT FAILURE, IF THE FADEC DOES FAIL, WITH THROTTLE FULL OPEN, THE ENGINE WILL MOST LIKELY OVERSPEED/SURGE. AN ENGINE OVERSPEED WILL CAUSE THE TAIL ROTOR TO HAVE A CORRESPONDING RPM INCREASE, WHICH MAY CAUSE INCREASED TAIL ROTOR PEDAL SENSITIVITY. ENGINE SURGES WILL CAUSE YAW RATE CHANGES THAT MAY BECOME UNCONTROLLABLE AT LOW AIRSPEEDS. PILOTS MUST BE PREPARED TO PLACE THE FADEC AUTO/MAN SWITCH IN THE MAN POSITION UPON INDICATION OF A FADEC FAILURE.
MAIN DRIVE SHAFT FAILURE NOTES
-ENGINE RPM (NP) EXCEEDING ROTOR RPM (NR), EVEN IF MOMENTARY, IS A CLEAR INDICATION OF A MAIN DRIVE SHAFT FAILURE.
-A FAILURE OF THE MAIN DRIVE SHAFT CAN BE SUDDEN, OR MAY FIRST EXHIBIT A WARNING IN THE FORM OF NOISE AND/OR VIBRATIONS.
FIRE-WARNING
TOXIC FUMES OF THE EXTINGUISHING AGENT MAY CAUSE INJURY. LIQUID AGENT. LIQUID AGENT MAY CAUSE FROSTBITE OR LOW-TEMPERATURE BURNS.
ABORT START/HOT START/ RESIDUAL FIRE-CAUTION
TO PREVENT ENGINE DAMAGE DO NOT DEPEND ON THE FADEC SYSTEM TO MOTOR THE STARTER AUTOMATICALLY DURING AN ABORTED START. IN A LOW BATTERY VOLTAGE CONDITION, THE ECU MAY NOT OPERATE PROPERLY.
ABORT START/HOT START/ RESIDUAL FIRE-NOTE
• DURING ENGINE STARTING THE FADEC SYSTEMS MONITORS ENGINE PARAMETERS AND WILL AUTOMATICALLY ABORT THE START IF IT BECOMES APPARENT THAT TGT LIMITS MAY BE EXCEEDED. IT WILL CONTINUE TO MOTOR THE STARTER FOR 60 SECONDS OR UNTIL TGT IS BELOW 149° C.
• ABORT SEQUENCE BEGINS AT 843° C FOR MOST OPERATIONS. HOWEVER IT WILL BEGIN AT 913°C IF PRESSURE ALTITUDE IS GREATER THAN 10000 FEET OR IF RESIDUAL TGT IS GREATER THAN 82.2°C AT INITIATION OF ENGINE START.
SMOKE AND FUME ELIMINATION-CAUTION
TO PREVENT DAMAGE TO HELICOPTER, DO NOT JETTISON DOORS IN FLIGHT ABOVE EFFECTIVE TRANSLATIONAL LIFT.
COMPLETE LOSS OF ELECTRICAL POWER NOTE
DURING A COMPLETE ELECTRICAL FAILURE THE FADEC SYSTEM WILL CONTINUE TO OPERATE AND CONTROL ENGINE RPM IF THE PMA IS FUNCTIONING PROPERLY.
DC GENERATOR FAILURE NOTE
FOLLOWING LOSS OF THE DC GENERATOR, BATTERY CHARGING DOES NOT OCCUR. WHENEVER THE THROTTLE IS REDUCED BELOW 91% NP THE TRU IS OFF LINE AND ALL DC SYSTEMS ARE POWERED BY THE BATTERY. LOW BATTERY POWER MAY RESULT IN LOSS OF ALL CDS INDICATIONS. ADDITIONALLY, WITHOUT DC POWER TO THE ECU, THE ENGINE MAY FLAMEOUT.
AC GENERATOR FAILURE CAUTION
AN AC GEN FAIL CAUTION MESSAGE ACCOMPANIED BY A CHIPS ENG LOWER CAUTION MESSAGE MAY BE AN INDICATION OF A GENERATOR DRIVE GEAR FAILURE , IN WHICH CASE, ADJUST YOUR ALTITUDE AND FLIGHT PATH AS APPROPRIATE DEPENDING UPON MISSION, TO ENSURE AVAILABLE FORCED LANDING AREAS.
INVERTER FAIL NOTE
WITH INVERTER POWER OFF, ALL AC POWERED EQUIPMENT TO INCLUDE INSTRUMENT LIGHTING AND SCAS WILL BE LOST AT NP SPEEDS BELOW 91%.
LEFT MCPU/RIGHT MCPU FAILURE NOTE
IN THE EVENT OF AN IMCPU FAILURE, THE EGI MAY RESET. AFTER IMCPU FUNCTION IS RESTORED, THE EGI WILL PERFORM AN IN-FLIGHT ALIGNMENT UNLESS THE AIRCRAFT IS LANDED AND A MANUAL ALIGNMENT IS PERFORMED.
HYDRAULIC POWER FAILURE-WARNING
BANK ANGLES EXCEEDING 45° WITHOUT HYDRAULIC BOOST MAY CAUSE ROLL RATES TO EXCEED CONTROLLABLE LIMITS.
HYDRAULIC POWER FAILURE-NOTE
ABRUPT COLLECTIVE CHANGES, UP OR DOWN, WILL CAUSE INCREASED PILOT WORKLOAD, ESPECIALLY WITH ROLL ATTITUDE. LOSSOF GYDRAULIC POWER WILL RESULT IN LOSS OF SCAS, THEREBY RESULTING IN A DETERIORATION IN FLYING QUALITIES.
HYDRAULIC POWER FAILURE-WARNING 2
DO NOT RETURN THE HYD SYS SWITCH TO THE HYD SYS POSITION FOR THE REMAINDER OF THE FLIGHT. THIS PREVENTS ANY POSSIBILITY OF A SURGE IN THE HYDRAULIC SYSTEM CREATING SUDDEN, UNEXPECTED CONTROL MOVEMENTS.
INADVERTENT AIR BAG DEPLOYMENT-NOTE
WHEN ACTIVATED, GAS GENERATORS PRODUCE A LOUD NOISE AND RAPIDLY EXPANDING AIR BAGS, WHICH MAY STARTLE THE CREW.
EMERGENCY INGRESS/EGRESSS-NOTE
EMERGENCY INGRESS WILL NOT BE NECESSARY WITH DEPLOYED AIR BAGS; EXTRACTION PROCEDURES CAN BE PERFORMED WITHOUT ENTERING THE COCKPIT.
ROCKET/MISSLE--HANGFIRE-WARNING
ACTIVATION OF JETTISON SWITCH DURING MISSILE HANGFIRE MAY CAUSE MISSILE LAUNCHER PACKAGE TO VEER OFF COURSE, POSSIBLY INTO THE AIRCRAFT OR ROTOR DISK.
ROCKET/MISSLE--HANGFIRE-CAUTION
IF A HELLFIRE LAUNCHER IS JETTISONED A SINGLE MISSILE ON THE INBOARD LAUNCHER RAIL, THE LAUNCHER MAY CONTACT THE LANDING GEAR SKID TUBE.