Term
|
Definition
| Right Front, Left Front, and Left Center. 964LBS |
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|
Term
|
Definition
| Right Center, Aft 1005LBS |
|
|
Term
|
Definition
43LBS of fuel
2 Boost Pumps
Left and right center cells |
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|
Term
|
Definition
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|
Term
| Max allowable PSI for pressure refueling |
|
Definition
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|
Term
|
Definition
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|
Term
|
Definition
Controls fuel flow in response to FADEC
Also provides backup mode for FADEC failure |
|
|
Term
|
Definition
270LBS per minute (40GPM)
Exhaust all fuel in 6.5 minutes |
|
|
Term
| Fuel actual bypass occurs at what PSI |
|
Definition
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|
Term
| Fuel pre-blockage switch will close and illuminate "FUEL FILT1" or "FUEL FILT 2" at what PSI |
|
Definition
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|
Term
| Low pressure switch mechanism will activate when oil pressure drops below what PSI |
|
Definition
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|
Term
| Oil filter is rated at how many microns |
|
Definition
|
|
Term
|
Definition
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|
Term
| AT what PSI will "ENG 1 OIL P" or "ENG 2 OIL P" Illuminate? |
|
Definition
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|
Term
| Oil pre-blockage indicator will activate at what PSI/ Actual bypass will occur at what PSI? |
|
Definition
Pre-blockage-36PSI
Actual Bypass-82PSI |
|
|
Term
|
Definition
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|
Term
| Thermostatic Bypass valve |
|
Definition
Below 74c- Closed
@ 74c- Beginning to Open
86c- Open |
|
|
Term
Normal NR Speed is @ ___ RPM
NR HI Speed is @ ___RPM |
|
Definition
Normal NR- 355RPM
NR HI- 365RPM |
|
|
Term
| IN Training mode NR droops to ___RPM |
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Definition
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|
Term
| Enging fire extinguisher agent |
|
Definition
| Bromotrifloromethane (CF3BR) |
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|
Term
| "L EXT" and "R EXT" will illuminate when PSI drops below ___PSI |
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Definition
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|
Term
| The rotor shaft transmits MGB output power to the tail rotor at approximately___RPM at a main rotor speed of ___RPM |
|
Definition
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|
Term
|
Definition
|
|
Term
| At what PSI will the "MGB PRESS" illuminate along with the 2 "MASTER" lights |
|
Definition
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|
Term
| (MGB Oil) At what temp. will the "MASTER" and the "OIL TEMP" illuminate |
|
Definition
|
|
Term
| Should PSI exceed ___PSI, OIL is bypassed to the MGB Sump |
|
Definition
|
|
Term
|
Definition
200 Volts, Three Phase,400Hz
(115Volt, Single phase) |
|
|
Term
|
Definition
Engine Driven
4.5kVA
28 Volts |
|
|
Term
| How long will a fully charged battery last? |
|
Definition
30 minutes continuous
60 minutes w/ "CPLT AVIONICS" Off |
|
|
Term
|
Definition
2 Transformers in baggage compartment
convert 115VAC into 26VAC |
|
|
Term
| 26VAC "FAIL" light will illuminate when output drops below___volts |
|
Definition
|
|
Term
|
Definition
|
|
Term
| Primary Hydraulic system ops |
|
Definition
870PSI
Upper /right flight control servos
1 gallon
10 micron filter |
|
|
Term
| Secondary Hydraulic System ops |
|
Definition
3000PSI
2.1GAL Reservoir
3micron and 10 micron filters
3000 PSI to hoist
2000PSI to landing gear, talon, and breaks
lower, left flight control servos(870PSI)
electric backup pump (1800PSI) |
|
|
Term
| How many brake cycles can you do with a fully charged accumulator? |
|
Definition
|
|
Term
|
Definition
|
|
Term
| When will the tail isolate activate? |
|
Definition
| When the secondary drops below 1/2 or 1 gallon |
|
|
Term
| What will the isolate valve isolate? |
|
Definition
Tail servos
landing gear
wheel brake
talon
hoist electrically |
|
|
Term
|
Definition
|
|
Term
|
Definition
|
|
Term
| Emergency blowdown bottle contains___ |
|
Definition
|
|
Term
| Emergency blowdown methods |
|
Definition
Center console handle
pin on left fwd of MLG |
|
|
Term
|
Definition
Disk brakes
parking brake
T-handle center console
top of pilot & co-pilot pedals
4 cylinders
accumulator |
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|
Term
|
Definition
|
|
Term
|
Definition
accumulator
acts as a primary tie-down |
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|
Term
|
Definition
|
|
Term
|
Definition
|
|
Term
|
Definition
|
|
Term
|
Definition
Normal- 0-200FPM
First and Last 10'- 0-50FPM
Pilot- Fixed 100FPM
Man Override- Fixed 50 FPM |
|
|
Term
| Hoist overload clutch will automatically pay out when load exceeds___LBS |
|
Definition
|
|
Term
| Max Transient Power (red diode) |
|
Definition
|
|
Term
| Max Take-off Power(red bar) |
|
Definition
|
|
Term
| Max Continuous Power (yellow bar) |
|
Definition
|
|
Term
|
Definition
FADEC Armed Stop
mechanical stop
engines will not putout any more power past this point |
|
|
Term
| When in manual override the speed of the hoist is? |
|
Definition
|
|
Term
| When refueling/defueling, keep all sources of sparks at least___ft from the operation |
|
Definition
|
|
Term
| Max allowable load in the baggage compartment |
|
Definition
|
|
Term
| After pushing the "AV CLG SW MAINT DISABLE", the "AVO/HEAT" light will still illuminate at what temp? |
|
Definition
|
|
Term
| Where is the ELT located? |
|
Definition
| FWD of baggage compartment door |
|
|
Term
| Remote ops switch for the ELT is |
|
Definition
| in the center console,IFF/COMM Panel |
|
|
Term
| Where is the UAB located? |
|
Definition
| On the Voice Flight Data Recorder |
|
|
Term
| What is the capacity of the windshield washer tank? |
|
Definition
|
|
Term
| With MRB folded, what is the max wind speed in any direction the blades can withstand? |
|
Definition
|
|
Term
| When gravity refueling to the aft filler neck, where will the fuel be allowed to flow? |
|
Definition
|
|
Term
| When the FM selects "ALT", where is the volume adjusted? |
|
Definition
|
|
Term
| When using manual override, what must you do once the device is in the cabin? |
|
Definition
| secure step 1 valve to prevent hoist creep |
|
|
Term
| C/B for emergency hoist power and emergency shear are located where? |
|
Definition
|
|
Term
| Rescue hoist is serviced with? |
|
Definition
|
|
Term
| In a sea state of 2, how long should the helo stay afloat upright w/ all 4 floats properly deployed? |
|
Definition
|
|
Term
| When preparing to tow the A/C, what should the brake accumulator pressure be? |
|
Definition
|
|
Term
| C/B for normal hoist power and normal shear are located where? |
|
Definition
|
|
Term
|
Definition
N2A- Pilot NR Guage (Triple Tach)
N2B- DECU
N2C- DECU |
|
|
Term
|
Definition
N1A- DECU
N1B- DECU
N1C- EBCAU/ VEMD |
|
|
Term
|
Definition
122.5% +/-1%
429RPM +/-4RPM |
|
|
Term
|
Definition
1 Transmission shaft/ accessory gearbox
2 Axial compressor
3 Gas generator
4 Power turbine
5 Reduction gearbox |
|
|
Term
|
Definition
|
|
Term
| Single Engine OPS SHP Rating |
|
Definition
|
|
Term
| Dual Engine OPS SHP Rating |
|
Definition
|
|
Term
| Max weight for prolonged hover |
|
Definition
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|
Term
|
Definition
|
|
Term
|
Definition
|
|
Term
|
Definition
| Vehicle, Fuel, EPC, System Status, FLI |
|
|
Term
|
Definition
|
|
Term
| White cicrle ina a square w/ a slash |
|
Definition
|
|
Term
|
Definition
|
|
Term
| When will the "ENG FUEL P" illuminate? |
|
Definition
|
|
Term
|
Definition
Nose compartment
Pilot FWD
Pilot AFT
Co-Pilot
Cockpit Avionics
Avionics Rack
Hoist Boom
Emergency Floats |
|
|
Term
|
Definition
Battery (24VDC)
Starter/Generator
External
T/R |
|
|
Term
|
Definition
|
|
Term
| Landing gear C/B locations |
|
Definition
|
|
Term
| Hydraulic secondary low pressure switch distribution manifold |
|
Definition
|
|
Term
| Hydraulic secondary low/ hight PSI switch hyd pump |
|
Definition
Below 2450PSI
Above 3480PSI |
|
|
Term
|
Definition
| Due to seriousness of the malfunction, the A/C shall be landed or ditched w/o delay. If extreme sea/terrain conditions seriously jeopardize aircrew survivability, the A/C may be air taxied to the NEAREST suitable site and landed or ditched immediatly. |
|
|
Term
|
Definition
| Aircraft shall be landed at the first site at which a safe landing can be made. |
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|
Term
| LAND AS SOON AS PRACTICABLE |
|
Definition
Extended flight is not recommended. The landing site and duration of flight is at the discretion of the pilot in
command. |
|
|
Term
|
Definition
The aircraft shall not proceed
on its assigned mission. Allows for continued flight to the DESIRED RECOVERY BASE |
|
|
Term
| CONTINUE FLIGHT AS APPROPRIATE |
|
Definition
| Allows continuation of the mission if the failed component is not required to accomplish the mission and airframe or component limitations have not been exceeded. |
|
|
Term
UNASSOCIATED MASTER WARNING LIGHT
Symptom |
|
Definition
Repeated illumination of pilot and copilot flashing
Master WARNING light without a WCA Panel warning
light illuminated. |
|
|
Term
UNASSOCIATED MASTER WARNING LIGHT
Corrective Action |
|
Definition
1. MONITOR FOR SECONDARY INDICATIONS
2. WCA TEST BUTTON − DEPRESS TO TEST
3. ABORT MISSION. URGENT MISSION MAY BE
COMPLETED |
|
|
Term
MAIN GEARBOX FAILURE IMMINENT
Symptoms |
|
Definition
1. Loss of XMSN lubrication OR illumination of a GB
CHIP warning light with an MGB CHIP annunciation
on the VEMD CAUTION/FUEL page in conjunction
with any one of the following:
Yaw kicks
Abnormal transmission noises
Unusually high power requirements
2. LOSS of XMSN lubrication AND illumination of a
GB CHIP warning light with an MGB CHIP annunciation on the VEMD CAUTION/FUEL page. |
|
|
Term
MAIN GEARBOX FAILURE IMMINENT
Corrective Action |
|
Definition
1. LANDING/HOVER CHECKLIST − COMPLETE
(200−foot checks at a minimum based on urgency)
2. LAND/DITCH IMMEDIATELY (POWER ON) |
|
|
Term
MAIN GEARBOX MALFUNCTION
Symptoms |
|
Definition
1. Loss of MGB Oil Pressure
2. Loss of XMSN lubrication
3. GB CHIP warning light illuminated with an MGB CHIP annunciation on the VEMD CAUTION/FUEL page
4. Abnormal transmission noises |
|
|
Term
MAIN GEARBOX MALFUNCTION
Corrective Action |
|
Definition
1. MONITOR FOR SECONDARY INDICATIONS
2. FLY AT MINIMUM SAFE ALTITUDE
3. AVOID HIGH POWER MANEUVERS
4. LAND AS SOON AS PRACTICABLE |
|
|
Term
MAIN GEARBOX PUMP MAIN ELEMENT FAILURE
Symptoms |
|
Definition
1. Illumination of MGB PMP MAIN caution light
2. Decrease in XMSN oil pressure
3. Increase in XMSN oil temperature |
|
|
Term
MAIN GEARBOX PUMP MAIN ELEMENT FAILURE
Corrective Action |
|
Definition
1. MONITOR XMSN OIL PRESSURE AND TEMPERATURE
2. LAND AS SOON AS PRACTICABLE |
|
|
Term
MAIN GEARBOX PUMP AUXILIARY ELEMENT
FAILURE
Symptoms |
|
Definition
1. Illumination of MGB PMP AUX caution light
Corrective Action:
1. MONITOR XMSN OIL PRESSURE AND TEMPERATURE
2. ABORT MISSION |
|
|
Term
MAIN GEARBOX INDICATING SYSTEM FAILURE
Symptoms |
|
Definition
1. MGB PRESS warning light illuminated
2. XMSN oil pressure in red or zero. (May be accompanied by MGB exceedance in CDU due to shared transducer)
3. OIL TEMP warning light illuminated
4. XMSN oil temperature in red or zero |
|
|
Term
MAIN GEARBOX INDICATING SYSTEM FAILURE
Corrective Action |
|
Definition
1. MONITOR FOR SECONDARY INDICATIONS
2. ABORT MISSION |
|
|
Term
MAIN GEARBOX OVERTEMP
Symptoms |
|
Definition
1. OIL TEMP warning light illuminated
2. Abnormal rise in MGB oil temperature |
|
|
Term
MAIN GEARBOX OVERTEMP
Corrective Action |
|
Definition
1. CRUISE AIRSPEED − 120 KIAS MINIMUM
2. LAND AS SOON AS PRACTICABLE |
|
|
Term
MAIN GEARBOX HIGH PRESSURE
Symptoms |
|
Definition
| 1. Transmission oil pressure greater than 80 psi. |
|
|
Term
MAIN GEARBOX HIGH PRESSURE
Corrective Action |
|
Definition
| 1. LAND AS SOON AS PRACTICABLE |
|
|
Term
MAIN GEARBOX FIRE
Symptoms |
|
Definition
1. MGB fire warning light illuminated
Additional possible symptoms:
2. Illumination of MGB related warning and caution lights
3. Loss of MGB oil pressure and/or rise in temperature
4. Drop in fuel or hydraulic pressure
5. Electrical system malfunctions |
|
|
Term
MAIN GEARBOX FIRE
Corrective Actions |
|
Definition
1. ATTEMPT TO CONFIRM PRESENCE OF FIRE
(alert crew)
2. LANDING/HOVER CHECKLIST − COMPLETE
(200−foot checks at a minimum based on urgency)
If fire confirmed:
3. LAND/DITCH IMMEDIATELY
If fire NOT confirmed:
3. LAND AS SOON AS POSSIBLE |
|
|
Term
ENGINE COMPARTMENT FIRE IN−FLIGHT
Symptoms |
|
Definition
1. FIRE warning light illuminated on the instrument panel
2. Red warning light illuminated on the corresponding
Emergency Fuel Shutoff Lever (EFSL)
3. Flames and/or smoke coming from engine compartment |
|
|
Term
ENGINE COMPARTMENT FIRE IN−FLIGHT
Corrective Action |
|
Definition
1. ATTEMPT TO CONFIRM PRESENCE OF FIRE(alert crew)
2. SINGLE ENGINE FLIGHT PROFILE − ESTABLISH
If fire confirmed:
3. FADEC CONTROL SWITCH (affected engine) − CONFIRM; IDLE; CONFIRM; OFF
4. EMERGENCY FUEL SHUTOFF LEVER − CONFIRM; OFF
5. BOOST PUMPS − (affected engine) − OFF
6. PRI FIRE EXTINGUISHER BUTTON (affected engine) − CONFIRM; PUSH
7. SEC FIRE EXTINGUISHER BUTTON (affected engine) − PUSH
8. LANDING/HOVER CHECKLIST − COMPLETE
(200−foot checks at a minimum based on urgency)
If fire still persists:
9. LAND/DITCH IMMEDIATELY
If fire no longer evident:
9. LAND AS SOON AS POSSIBLE
If fire NOT confirmed:
3. LAND AS SOON AS PRACTICABLE |
|
|
Term
ENGINE COMPARTMENT FIRE ON DECK
Symptoms |
|
Definition
1. FIRE warning light illuminated
2. Possible hand or voice signals from ground crew
3. Red warning light illuminated on the corresponding Emergency Fuel Shutoff Lever (EFSL) |
|
|
Term
ENGINE COMPARTMENT FIRE ON DECK
Corrective Action |
|
Definition
1. ATTEMPT TO CONFIRM PRESENCE OF FIRE
(alert crew)
2. FADEC CONTROL SWITCHES − BOTH OFF
3. EMERGENCY FUEL SHUTOFF LEVERS − BOTH
OFF
4. BOOST PUMPS − ALL OFF
If fire confirmed:
5. PRI FIRE EXTINGUISHER BUTTON (affected engine) − CONFIRM; PUSH
6. SEC FIRE EXTINGUISHER BUTTON (affected engine) − PUSH
7. EMERGENCY ELECTRICAL CUTOFF − OFF
8. ROTOR BRAKE − ON
9. EVACUATE AIRCRAFT |
|
|
Term
SMOKE AND FUME ELIMINATION
Corrective Action |
|
Definition
1. HEAT/COOL SWITCHES − OFF
2. RAM AIR − OPEN
3. CABIN SLIDING DOOR − OPEN
4. PILOT WINDOWS − OPEN
5. LAND AS SOON AS PRACTICABLE |
|
|
Term
INTERNAL FIRE (CABIN, ELECTRICAL, AND/OR AVIONICS)
Corrective Actions |
|
Definition
1. DESIGNATE CREWMEMBER TO FIGHT FIRE
2. AFFECTED EQUIPMENT − OFF
3. HEAT/COOL SWITCHES − OFF
4. RAM AIR − CLOSED
5. CABIN SLIDING DOOR − CLOSED
6. PILOT WINDOWS − CLOSED
7. RACK BLOWER CIRCUIT BREAKER − PULL (for avionics rack fire only − avionics rack panel R4
#4 in HH−65, R5 #4 in MH−65)
8. CIRCUIT BREAKERS − PULL (for affected circuits)
9. LANDING/HOVER CHECKLIST − COMPLETE
(200−foot checks at a minimum based on urgency)
If electrical or avionics fire persists:
10. EMERGENCY ELECTRICAL CUTOFF − OFF
If electrical or avionics fire persists:
11. LAND/DITCH IMMEDIATELY
If fire goes out:
11. LAND AS SOON AS POSSIBLE |
|
|
Term
ENGINE POST−SHUTDOWN FIRE
Symptom |
|
Definition
| TOT rises rapidly or does not decrease within 10 seconds after the FADEC control switch has been placed in the OFF position |
|
|
Term
ENGINE POST−SHUTDOWN FIRE
Corrective Action |
|
Definition
1. FADEC CONTROL SWITCH − CHECK OFF
2. BOOST PUMPS − CHECK OFF
3. EMERGENCY FUEL SHUTOFF LEVER − SHUT
OFF (ENSURE 10 SECONDS HAVE ELAPSED
PRIOR TO SHUTOFF)
4. CRANK BUTTON − DEPRESS UNTIL TOT DECREASES
If TOT continues to rise or does not decrease:
5. EMERGENCY ELECTRICAL CUTOFF − OFF
6. ROTOR BRAKE − ON
7. EVACUATE AIRCRAFT |
|
|
Term
FIRE DETECTOR FAILURE
Symptom |
|
Definition
| Fire detector FAIL light illuminated |
|
|
Term
FIRE DETECTOR FAILURE
Corrective Action |
|
Definition
| LAND AS SOON AS PRACTICABLE |
|
|
Term
FIRE SUPPRESSION FAILURE
Symptom |
|
Definition
| L or R EXT caution light illuminated |
|
|
Term
FIRE SUPPRESSION FAILURE
Corrective Action |
|
Definition
|
|
Term
ROTOR BLADE DAMAGE
Symptoms |
|
Definition
1. Rotor blade damage is known or suspected
AND
2. Secondary indications (such as vibrations) are more than moderate, flight characteristics are drastically
altered |
|
|
Term
ROTOR BLADE DAMAGE
Corrective Action |
|
Definition
1. LANDING/HOVER CHECKLIST − COMPLETE
(200−foot checks at a minimum based on
urgen- cy)
2. LAND/DITCH IMMEDIATELY |
|
|
Term
ROTOR BLADE DAMAGE
Symptoms |
|
Definition
1. Rotor blade damage is known or suspected, with or
without secondary indications of up to moderate |
|
|
Term
ROTOR BLADE DAMAGE
Corrective Action |
|
Definition
| 1. LAND AS SOON AS POSSIBLE |
|
|
Term
Abnormal Vibrations
Symptom |
|
Definition
| 1. Severe or intolerable vibrations of unknown origin |
|
|
Term
Abnormal Vibrations
Corrective Actions |
|
Definition
1. LANDING/HOVER CHECKLIST − COMPLETE
(200−foot checks at a minimum based on
urgen- cy)
2. LAND/DITCH IMMEDIATELY |
|
|
Term
Abnormal Vibrations
Symptom |
|
Definition
|
|
Term
Abnormal Vibrations
Corrective Actions |
|
Definition
1. CRUISE AIRSPEED − 75−120 KIAS
2. AVOID ABRUPTMANEUVERS
3. LAND AS SOON AS POSSIBLE |
|
|
Term
Abnormal Vibrations
Symptom |
|
Definition
|
|
Term
Abnormal Vibrations
Corrective Actions |
|
Definition
1. CRUISE AIRSPEED − 75−120 KIAS
2. AVOID ABRUPT MANEUVERS
3. LAND AS SOON AS PRACTICABLE |
|
|
Term
|
Definition
| 1. Either inner or outer pane on windshield cracked |
|
|
Term
WINDSCREEN CRACKS
Corrective Actions |
|
Definition
1. CRUISE AIRSPEED 70 KNOTS MAXIMUM
2. IF ARCING ON WINDSCREEN IS NOTICED, SECURE WINDSCREEN ANTI−ICE
3. ABORT MISSION. |
|
|
Term
|
Definition
| 1. Both inner and outer panes on windscreen cracked |
|
|
Term
WINDSCREEN CRACKS
Corrective Actions |
|
Definition
1. CRUISE AIRSPEED 70 KNOTS MAXIMUM
2. IF ARCING ON WINDSCREEN IS NOTICED, SECURE WINDSCREEN ANTI−ICE
3. LAND AS SOON AS PRACTICABLE |
|
|
Term
UNCOMMANDED LEFT YAW (ULY)
Symptom |
|
Definition
| 1. Any uncommanded left yaw not attributable to mechanical failure of the tail rotor drive system |
|
|
Term
UNCOMMANDED LEFT YAW (ULY)
Corrective Action |
|
Definition
1. IMMEDIATE FULL RIGHT PEDAL, MAXIMUM
DEFLECTION
2. ALTITUDE/OBSTACLES PERMITTING,
SMOOTHLY APPLY FORWARD CYCLIC TO INCREASE FORWARD AIRSPEED
3. ALTITUDE PERMITTING, REDUCE COLLECTIVE
4. NR SWITCH − HI |
|
|
Term
|
Definition
| 1. Illumination of the GB CHIP warning light and a TGB CHIP annunciation on the VEMD CAUTION/ FUEL page |
|
|
Term
TGB CHIP DETECTED
Corrective Action |
|
Definition
1. ESTABLISH SAFE ALTITUDE AND AIRSPEED
FOR POSSIBLE LOSS OF TAIL ROTOR
THRUST
2. LAND AS SOON AS POSSIBLE |
|
|
Term
LOSS OF TAIL ROTOR THRUST WHILE HOVERING
Symptoms |
|
Definition
1. A loss of tail rotor thrust will result in an IMMEDIATE,
rapid left yaw acceleration
2. Tail rotor pedals movable but with no apparent effect
3. Abnormal vibration or noise from the tail section
4. Illumination of the GB CHIP warning light and a TGB CHIP annunciation on the VEMD CAUTION/ FUEL page |
|
|
Term
LOSS OF TAIL ROTOR THRUST WHILE HOVERING
Corrective Action |
|
Definition
1. EMERGENCY FUEL SHUTOFF LEVERS − BOTH
OFF
2. MAINTAIN LANDING ATTITUDE
3. CUSHION LANDING WITH COLLECTIVE |
|
|
Term
LOSS OF TAIL ROTOR THRUST IN FORWARD
FLIGHT OR FIXED TAIL ROTOR PITCH
Symptom |
|
Definition
1. Uncommanded yaw to the left or right (loss of thrust)
2. Tail rotor pedals movable without effect (loss of thrust)
3. Abnormal vibration or noise from the tail section (loss of thrust or fixed pitch)
4. Possible illumination of the GB CHIP warning light (loss of thrust) with a TGB CHIP annunciation on the VEMD CAUTION/FUEL page
5. Cannot move pedals either left or right (fixed pitch) |
|
|
Term
LOSS OF TAIL ROTOR THRUST IN FORWARD
FLIGHT OR FIXED TAIL ROTOR PITCH
Corrective Action |
|
Definition
1. DIRECTIONAL CONTROL − MAINTAIN USING
CYCLIC AND COLLECTIVE
2. LAND AS SOON AS PRACTICABLE. UTILIZE
PROCEDURE FOR LANDING WITH TAIL ROTOR
MALFUNCTION |
|
|
Term
POWERED LANDING WITH TAIL ROTOR
MALFUNCTION
Corrective Action |
|
Definition
1. LANDING/HOVER CHECKLIST − COMPLETE
2. APPROACH ANGLE/SPEED − AS REQUIRED TO MAINTAIN RIGHT YAW (left sideslip)
3. TOUCHDOWN − ELIMINATE YAW AND DRIFT
4. ROLLOUT − COORDINATE CYCLIC AND COLLECTIVE TO MAINTAIN DIRECTIONAL CONTROL AND REDUCE GROUNDSPEED
5. BRAKES − APPLY AS REQUIRED |
|
|
Term
AUTOROTATIVE LANDING WITH TAIL ROTOR
MALFUNCTION
Corrective Action |
|
Definition
1. LANDING/HOVER CHECKLIST − COMPLETE
2. AIRSPEED − 75 KIAS
3. COLLECTIVE − DECREASE TO ESTABLISH AUTOROTATION
4. FADEC CONTROL SWITCHES − IDLE
5. AT 200 FEET RADALT − WHEELS AS REQUIRED
If satisfied that the approach will permit successful completion of the autorotation to the desired area:
6. FADEC CONTROL SWITCHES − OFF
7. AT 125 FEET RADALT − INITIATE FLARE. INFLATE FLOATS AS REQUIRED
8. ASSUME LANDING ATTITUDE, ELIMINATING
DRIFT PRIOR TO TOUCHDOWN
9. COLLECTIVE − CUSHION THE LANDING |
|
|
Term
ENGINE EMERGENCIES IN−FLIGHT − GENERAL
(BIG 4) |
|
Definition
1. Nr − MAINTAIN
2. AIRSPEED/ALTITUDE − CONTROL AND SET
LIMITS
3. WHEELS/FLOATS − AS REQUIRED
4. ANALYZE |
|
|
Term
DUAL ENGINE FAILURE IN−FLIGHT − GENERAL
Symptoms |
|
Definition
1. Low Nr horn − ON
2. Nr − DECAYING
3. Engine parameters − BOTH ENGINES DECREASING
4. Possible right yaw |
|
|
Term
DUAL ENGINE FAILURE IN−FLIGHT − GENERAL
Corrective Action |
|
Definition
1. Nr − MAINTAIN
2. PERFORM AUTOROTATION PROCEDURE |
|
|
Term
VISUAL AUTOROTATION PROCEDURES
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4" (airspeed 75−105
KIAS)
2. TURN TOWARD DESIRED LANDING AREA
AND/OR INTO THE WIND
3. AT 200 FT RADALT − WHEELS RECHECK
4. AT 125 FT RADALT − INITIATE FLARE; INFLATE FLOATS AS REQUIRED
5. ASSUME LANDING ATTITUDE, ELIMINATING
YAW AND DRIFT PRIOR TO TOUCHDOWN
6. COLLECTIVE − CUSHION THE LANDING
The following items should be completed if time and altitude
permit:
a. CABIN DOOR − OPEN
b. SHOULDER HARNESS − LOCKED
c. DISTRESS − TRANSMIT
d. IFF − EMERGENCY
e. FADEC CONTROL SWITCHES − BOTH OFF
f. ENGINE RESTART − CONSIDER ATTEMPT
g. LANDING LIGHTS − AS REQUIRED
h. BOOST PUMPS − OFF |
|
|
Term
INSTRUMENT AUTOROTATION PROCEDURES
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4" (airspeed 75 KIAS)
2. TURN TOWARD DESIRED LANDING AREA
AND/OR INTO THE WIND
3. AT 200 FEET RADALT − WHEELS RECHECK
4. AT 125 FEET RADALT − INITIATE FLARE. CONTROL
THE RATE TO ARRIVE AT 20 DEGREES
NOSE UP AT 75 FEET RADALT; INFLATE
FLOATS AS REQUIRED
5. MAINTAIN FLARE UNTIL DESIRED AIRSPEED
IS REACHED − 30 KT PLUS HALF THE WIND
SPEED
6. ASSUME 5 NOSE UP, WINGS−LEVEL LANDING ATTITUDE
7. AT 25 FEET RADALT − COLLECTIVE − CUSHION THE LANDING
The following items should be completed if time and altitude
permit:
a. CABIN DOOR − OPEN
b. SHOULDER HARNESS − LOCKED
c. DISTRESS − TRANSMIT
d. IFF − EMERGENCY
e. FADEC CONTROL SWITCHES − OFF
f. ENGINE RESTART − CONSIDER ATTEMPT
g. LANDING LIGHTS − AS REQUIRED
h. BOOST PUMPS − OFF |
|
|
Term
SINGLE−ENGINE FAILURES IN−FLIGHT TO
INCLUDE: LOW HOVER, HIGH HOVER, AND
TAKEOFF/LANDING TRANSITION
Symptoms |
|
Definition
1. Possible Nr droop
2. Abnormal engine parameters
3. DIF N1 warning light illuminated
4. Low Nr horn
5. Torque, TOT, N1, N2 decreasing
6. As engine spools down, additional symptoms will become evident such as Generator Failure, Eng Oil P light
7. FLI switches to OEI mode page
8. ECS disengages
9. Bleed air shuts off |
|
|
Term
SINGLE−ENGINE FAILURES IN−FLIGHT TO
INCLUDE: LOW HOVER, HIGH HOVER, AND
TAKEOFF/LANDING TRANSITION
Corrective Action |
|
Definition
1. Nr − MAINTAIN
2. AIRSPEED/ALTITUDE − CONTROL
3. WHEELS/FLOATS − AS REQUIRED
4. LAND BACK OR CONTINUE FLIGHT
LAND BACK PROCEDURE:
5. ASSUME LANDING ATTITUDE, ELIMINATE
YAW AND DRIFT PRIOR TO TOUCHDOWN
CONTINUED FLIGHT PROCEDURE:
6. COLLECTIVE − ADJUST TO MAXIMUM POWER, MAINTAINING MINIMUM Nr (at or above 345
RPM)
7. AIRSPEED − CLIMB AT 70−75 KIAS
8. Nr/OEI − SET AS NECESSARY
9. ANALYZE |
|
|
Term
|
Definition
1. Possible Nr droop
2. Abnormal engine parameters
3. DIF N1 warning light illuminated
4. Low Nr horn
5. Torque, TOT, N1, N2 decreasing
6. As engine spools down, additional symptoms will become evident such as Generator Failure, Eng Oil P light
7. FLI switches to OEI mode page
8. ECS disengages
9. Bleed air shuts off |
|
|
Term
FLAMEOUT
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
2. ENGINE SHUTDOWN PROCEDURE − COMPLETE |
|
|
Term
ENGINE CHIP DETECTED
Symptoms |
|
Definition
1. ENG No. CHIP warning light illuminated
2. Corresponding ENGINE CHIP annunciation on the VEMD CAUTION/FUEL page |
|
|
Term
ENGINE CHIP DETECTED
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
2. FADEC CONTROL SWITCH (AFFECTED ENGINE) − CONFIRM; IDLE
3. ENGINE − MONITOR
If ABNORMAL indications:
4. ENGINE SHUTDOWN PROCEDURE − COMPLETE
If NORMAL indications:
4. LAND AS SOON AS PRACTICABLE. (If additional power is required for landing, affected FCS may be switched to FLT position.) |
|
|
Term
ENGINE GEARBOX/OUTPUT SHAFT FAILURE
Symptoms |
|
Definition
1. N2 significantly above Nr
2. Zero torque on malfunctioning engine
3. Possible loud noises from the engine area |
|
|
Term
ENGINE GEARBOX/OUTPUT SHAFT FAILURE
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
2. ENGINE SHUTDOWN PROCEDURE − COMPLETE |
|
|
Term
N1 DIVERGENCE/PARTIAL POWER LOSS
Symptoms |
|
Definition
1. DIF N1 Warning Light illuminated
2. OEI GOV mode page
3. N1 difference between both engines is greater than 6% |
|
|
Term
N1 DIVERGENCE/PARTIAL POWER LOSS
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
2. ENGINE PARAMETERS − MONITOR
3. LAND AS SOON AS PRACTICABLE |
|
|
Term
MAJOR FADEC/GOVERNOR FAILURE
Symptoms |
|
Definition
1. FADEC No. 1 or 2 FAIL caution light illuminated
2. Red ENGINE STATUS light on the overhead quadrant illuminated
3. OEI GOV mode page displayed
4. Affected engine will not respond to collective movement due to Fuel Flow metering being frozen at the rate present when the FADEC failed |
|
|
Term
MAJOR FADEC/GOVERNOR FAILURE
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
2. TRNG SWITCH − FLT
3. FADEC BACKUP SWITCH (affected engine) − BACKUP
4. OEI − SET AS NECESSARY
5. LAND AS SOON AS PRACTICABLE |
|
|
Term
MINOR FADEC/GOVERNOR FAILURE
Symptom |
|
Definition
| 1. GOV caution light illuminated |
|
|
Term
MINOR FADEC/GOVERNOR FAILURE
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
2. ABORT MISSION. URGENT MISSION MAY BE
COMPLETED |
|
|
Term
|
Definition
1. LANE 1 FAILED > PRESS OFF 1
2. LANE 2 FAILED > PRESS OFF 2
3. CROSS TALK FAILED > PRESS OFF 1
4. CROSS TALK FAILED > PRESS OFF 2
5. Loss of one screen
6. FLI DEGR annunciation on the VEMD with BLANK TRQ parameters (No. 1 TRQ for top VEMD and No. 2 TRQ for bottom VEMD)
7. GOV caution light
8. NO BINGO annunciation |
|
|
Term
VEMD FAILURES
Corrective Action |
|
Definition
1. SHUT OFF SCREEN 1 OR 2 AS APPROPRIATE
2. CONTINUE FLIGHT AS APPROPRIATE |
|
|
Term
DUAL VEMD SCREEN FAILURE
Symptoms |
|
Definition
1. Both VEMD screens off or failed
2. GOV caution light illuminated |
|
|
Term
DUAL VEMD SCREEN FAILURE
Corrective Action |
|
Definition
1. SHUT OFF SCREEN 1 OR 2 AS APPROPRIATE
2. AVOID HIGH POWER SETTINGS, REFERENCE
PLACARD FOR COLLECTIVE PITCH SETTINGS
3. ABORT MISSION |
|
|
Term
LUBRICATION SYSTEM FAILURE
Possible Symptoms |
|
Definition
1. ENG No. OIL P warning light illuminated
2. Engine oil pressure fluctuates, increases or decreases abnormally
3. Red engine status light illuminated on the overhead control quadrant
4. Engine oil pressure less than 25 psi |
|
|
Term
LUBRICATION SYSTEM FAILURE
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
2. ENGINE SHUTDOWN PROCEDURE − COMPLETE |
|
|
Term
ENGINE SURGE OR COMPRESSOR STALL
IN−FLIGHT
Symptoms |
|
Definition
1. Popping or rumbling noises
2. TOT increases
3. Torque and N1 decreases
4. Airframe vibration |
|
|
Term
ENGINE SURGE OR COMPRESSOR STALL
IN−FLIGHT
Corrective Action |
|
Definition
1. COMPLETE THE BIG 4"
If NORMAL engine parameters or affected engine cannot be identified:
2. LAND AS SOON AS PRACTICABLE
If ABNORMAL engine parameters and affected engine can be identified:
2. FADEC CONTROL SWITCH (affected engine) − CONFIRM; IDLE
3. ENGINE − MONITOR
If ABNORMAL IDLE parameters:
4. ENGINE SHUTDOWN PROCEDURE − COMPLETE
If NORMAL IDLE parameters:
4. LAND AS SOON AS PRACTICABLE |
|
|
Term
ENGINE SURGE OR COMPRESSOR STALL
ON DECK
Possible Symptoms |
|
Definition
1. Popping or rumbling noises
2. TOT increases
3. Torque and N1 decreasing
4. Airframe vibration/shuddering |
|
|
Term
ENGINE SURGE OR COMPRESSOR STALL
ON DECK
Corrective Action |
|
Definition
1. FADEC CONTROL SWITCH (affected engine) − OFF
2. FUEL BOOST PUMPS (affected engine) − OFF
3. TOT − MONITOR FOR POST SHUTDOWN FIRE |
|
|
Term
ENGINE OIL COOLER FAN FAILURE
Symptoms |
|
Definition
1. OIL TEMP warning light illuminated
2. Abnormal rise in engine oil temperature
If BOTH engines are overheated:
1. CRUISE AIRSPEED − 120 KIAS MIN
2. LAND AS SOON AS PRACTICABLE
3. SHUT DOWN ENGINES AS SOON AS POSSIBLE |
|
|
Term
ENGINE OIL COOLER FAN FAILURE
Corrective Action |
|
Definition
If ONE engine is overheated:
1. CRUISE AIRSPEED − 75 KIAS MIN
2. FADEC CONTROL SWITCH (affected engine) − CONFIRM; IDLE
3. ENGINE OIL TEMPERATURE − MONITOR
4. LAND AS SOON AS PRACTICABLE (If additional power is required for landing, affected FCS may be switched to flight position.) |
|
|
Term
| ENGINE SHUTDOWN PROCEDURE IN−FLIGHT |
|
Definition
1. SINGLE−ENGINE FLIGHT PROFILE − ESTABLISH
2. FADEC CONTROL SWITCH (affected engine) − CONFIRM; IDLE; CONFIRM; OFF
3. BOOST PUMPS (affected engine) − OFF
4. TOT − MONITOR FOR POST SHUTDOWN FIRE
5. OEI − SET AS REQUIRED
6. FUEL − TRANSFER/JETTISON AS REQUIRED
(To transfer all useable fuel, the boost pumps on the failed engine side must be ON to drive the transfer injectors.)
7. LAND AS SOON AS PRACTICABLE (single−engine landing procedure) |
|
|
Term
RESTARTING ENGINE IN−FLIGHT
Corrective Action |
|
Definition
1. HEAT − OFF
2. EMERGENCY FUEL SHUTOFF LEVER − ENSURE FORWARD
3. BOOST PUMPS − ON
4. CHECK N1 LESS THAN 17%
5. PERFORM NORMAL START PROCEDURE
If engine start is successful:
6. LAND AS SOON AS PRACTICABLE
If engine fails to light off:
6. ENGINE SHUTDOWN PROCEDURE − COMPLETE |
|
|
Term
ENGINE START EMERGENCIES
Possible Symptoms |
|
Definition
1. Insufficient voltage (<17 VDC)
2. FADEC No.1 or 2 FAIL caution light illuminates
3. TOT digital value is underscored in red
4. No rise in N1 and/or TOT within 10 seconds
5. TOT rises rapidly and/or appears that it will exceed 750 degrees Celsius (hot start)
6. The main rotor does not turn prior to 25% N1
7. Engine does not reach 45% N1 by 30 seconds and is no longer accelerating
8. ENG No. OIL P warning light does not extinguish prior to 70% N1
9. The N2 needle passes the Nr needle |
|
|
Term
ENGINE START EMERGENCIES
Corrective Action |
|
Definition
1. FADEC CONTROL SWITCH − OFF
2. BOOST PUMPS − OFF
3. TOT − MONITOR FOR POST SHUTDOWN FIRE |
|
|
Term
TORQUE, TOT or N1 INDICATING SYSTEM
FAILURE
Possible Symptoms |
|
Definition
1. FLI DEGR annunciation on the VEMD
2. TRQ, TOT or N1 value missing with TRQ, TOT, or N1 label in boldface yellow type
3. GOV caution light
4. All other engine parameters normal |
|
|
Term
TORQUE, TOT or N1 INDICATING SYSTEM
FAILURE
Corrective Action |
|
Definition
1. COMPLETE THE 'BIG 4"
2. MONITOR OTHER ENGINE PARAMETERS
3. AVOID HIGH POWER SETTINGS
4. ABORT MISSION. |
|
|
Term
VEHICLE PAGE INDICATION FAILURES
Symptoms |
|
Definition
1. VEMD Vehicle page indicator blanked without numerical values.
2. VEHICLE PARAMETER OVER LIMIT annunciation on the VEMD. |
|
|
Term
VEHICLE PAGE INDICATION FAILURES
Corrective Action |
|
Definition
1. MONITOR FOR SECONDARY INDICATIONS
2. ABORT MISSION |
|
|
Term
PRIMARY HYDRAULIC SYSTEM FAILURE
Symptoms |
|
Definition
1. PRI SERVO P warning light illuminated
2. SERVO JAM warning light illuminated
3. LIMIT lights illuminated
4. HYD2 PRESS <720 psi
5. SERVO LIMIT annunciation on the VEMD CAUTION/ FUEL page
6. High−pitched noise from transmission area
7. Stiffness in flight controls |
|
|
Term
PRIMARY HYDRAULIC SYSTEM FAILURE
Corrective Action |
|
Definition
1. CRUISE AIRSPEED − 75 TO 100 KIAS
2. AVOID ABRUPT MANEUVERS
3. LAND AS SOON AS PRACTICABLE |
|
|
Term
SECONDARY HYDRAULIC SYSTEM FAILURE
Symptoms |
|
Definition
1. SEC SERVO P warning light illuminated
2. SEC HYD LO PRESS warning light illuminated
3. SERVO JAM warning light illuminated
4. HYD1 PRESS <720 psi
5. SEC HYD ISOLATE warning light illuminated. (Only if failure is due to a loss of hydraulic fluid)
6. High−pitched noise from transmission area
7. Stiffness in flight controls |
|
|
Term
SECONDARY HYDRAULIC SYSTEM FAILURE
Corrective Action |
|
Definition
1. CRUISE AIRSPEED − 75 TO 100 KIAS
2. AVOID ABRUPT MANEUVERS
3. TAIL HYD ISOLATE SWITCH − CUTOFF
4. EMERGENCY LANDING GEAR EXTENSION
HANDLE − PULL (not required if wheels are down)
5. LANDING GEAR HANDLE − DOWN
6. SAFETY PIN − INSTALL (if available)
If wheels fail to extend:
7. CONSIDER EXTERNAL ACTIVATION OF LANDING GEAR BLOW DOWN BOTTLE TO EXTEND
LANDING GEAR − ACTIVATE FROM THE
GROUND BY REMOVING FLAGGED SAFETY
PIN AND ACTUATOR PIN (located in chine panel forward of the left main mount)
If wheels still fail to extend:
8. CONSIDER USE OF EXTERNAL NITROGEN
CANISTER VIA THE LANDING GEAR NITROGEN
LINE T−FITTING TO EXTEND LANDING
GEAR (located in chine panel forward of the left main mount)
9. LAND AS SOON AS PRACTICABLE. (If loss of fluid situation exists or is suspected − PERFORM VERTICAL LANDING) |
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