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163 Cards in this Set
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- 3rd side (hint)
Describe HMU |
*Hydro-mechanical Unit *Engine mounted *Provides fuel modulation via stepper motor in Auto & hydro mechanical actuator in MANUAL |
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FADEC |
Full Authority Digital Engine Control |
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PMA |
*Permanent Magnetic Alternator *ECU power source |
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Describe ECU |
*Electronic Control Unit *Airframe mounted *Monitors inputs to modulate fuel flow & control engine speed, acceleration, rate, temp. |
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Anytime an operating limit is exceeded, what info should be included in the logbook entry? |
Which limit exceeded, duration, extreme value attained, any additional info |
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Max allowable cabin deck loading: Baggage compartment deck loading: |
75 lbs per square foot 86 lbs per square foot |
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Max allowable weight in baggage compartment |
*250 lbs *245 with cargo extender |
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Current FADEC software version: |
5.400 |
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Max & min internal GW for takeoff & landing: |
5250 lbs 2650 lbs |
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Basic Vne: |
140 KIAS up to 3,000' Hd, then follow placard |
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Vne at 93.5% to 100% TRQ (takeoff power): |
100 KIAS |
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Vne with any doors removed: |
100 KIAS |
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Vne for autorotation: |
100 KIAS |
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Max airspeed for sideward & rearward flight or crosswind hover: |
35 KTAS |
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Max operating altitude: |
20,000' Hd, or 20,000' Hp whichever is lower |
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Max rate of climb: |
2,000' per minute |
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Slope landing limits (side, nose up/down): Bonus: why nose down limit? |
10° side to side 10° nose up 5° nose down (mast tilt) |
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Max & min ambient air temp for operation |
51.7°C (125°F) -40°C (-40°F) |
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When should ENG ANTI ICE be ON? |
In visible moisture when OAT is below 5°C (40°F) |
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Generator Max continuous (below & above 10,000' Hp): Transient (2 min, 5 sec): |
*180 amps *170 amps *300 amps *400 amps |
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Starter: External Power Start attempts |
40 sec ON 30 sec OFF 40 sec ON 30 sec OFF 40 sec ON 30 Min OFF |
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Starter: Battery Start attempts |
60 sec ON 60 sec OFF 60 sec ON 60 sec OFF 60 sec ON 30 min OFF |
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Power Plant description & hp |
*Rolls-Royce 250-C47B *813 derated by HMU *674 takeoff *630 mcp |
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Ng (Gas Producer RPM) Continuous: Max continuous: 10 sec transient: |
63 to 105% 105% 105.1 to 106% |
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What will happen if power demand exceeds Ng placard limit? |
FADEC will limit Ng resulting in Nr decay |
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Np (Power Turbine RPM) Avoid continuous: Min & Max continuous: Max transient, 15 sec: |
68.4 to 87.1% 99 to 100% 102.1 to 107.3% |
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ENGINE OVSPD warning light will illuminate when Np vs. Torque is between: |
102.1% Np at 100% Torque 108.6% Np at 0% Torque |
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When operating in MANUAL mode, at what % should Np be maintained? |
Between 95 and 100% |
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MGT (Measured Gas Temperature) Max continuous: Takeoff, 5 min: Transient, 12 sec: Max starting: |
727°C 727 to 779°C 780 to 905°C No exceed 10 sec above 843°C or 1 sec at 927°C |
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ENGINE TORQUE Max continuous: Takeoff, 5 min: Transient, 5 sec: |
93.5% 93.5 to 100% 105% |
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FUEL PRESSURE Minimum: Continuous: Maximum: |
8 PSI 8 to 25 PSI 25 PSI |
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ENGINE OIL PRESSURE Min below 79% NG: Min from 79 to 94% NG: Min above 94% NG: Max: Max cold starts only: |
50 PSI 90 PSI 115 PSI 130 PSI 200 PSI |
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When 130 PSI oil press is exceeded during start, do what? |
Operate engine at idle until oil pressure drops below 130 PSI. |
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ENGINE OIL TEMPERATURE Continuous operation: |
0 to 107°C 107°C |
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If hovering with tailwind greater than 10 kts at OAT above 37.8°C(100°F), closely monitor engine oil temp. How may oil temp be reduced? |
Turning into wind, Reducing power, Transition to forward flight. |
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What is a positive oil temp indication? |
When the second segment of the trend arc is illuminated. |
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TRANSMISSION OIL PRESSURE Minimum: Continuous: Maximum: |
30 PSI 40 to 70 PSI 70 PSI |
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ROTOR RPM — POWER ON Continuous: Max continuous: |
99 to 100% 100% |
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ROTOR RPM — POWER OFF Minimum: Continuous: Max: |
85% 85 to 107% 107% |
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Rotor brake application is limited to after shut down and NR has decreased to what? |
40% or lower |
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Which 9 caution lights illuminate with BAT ON? |
ENG OUT XMSN OIL PRESS RPM HYDRAULIC SYSTEM GEN FAIL L/FUEL BOOST, R/FUEL BOOST L/FUEL XFR, R/FUEL XFR |
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Attempting to start engine when voltage is below 24 volts may result in what? |
Hot start |
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What will happen if the throttle is positioned in idle for more than 60 seconds? |
Starter latching is disabled and throttle must be repositioned to cutoff and then idle. |
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When starting, how long do you engage start switch and which lights should be observed? |
*Approximately 1 second *Observe START & AUTO RELIGHT |
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It is recommended that MGT be below what when below 10,000 feet HP or below what when above 10,000 feet HP prior to attempting an engine start. |
150°C 65°C |
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If main rotor is not rotating by what %, you should abort. |
25% NG |
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Describe which lights and when extinguish during start. |
START — at 50% NG ENG OUT -- at 55% NG AUTO RELIGHT — at 60% NG |
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What is a normal Voltmeter indication with GEN ON? |
28.5 ±0.5 volts |
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Components driven by NG turbine |
Starter Generator HMU Oil Pump assembly |
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Components driven by NP turbine |
Torquemeter Free wheeling unit PMA |
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What does "check instrument" light mean? |
Torque, NG, or MGT has, had, or about to exceed limitation |
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ECU monitored items |
1. CP - collective pitch 2. PLA - Power Lever Angle 3. MGT 4. NG 5. NP 6. NR 7. Torque 8. CIT - compressor inlet temp 9. Ambient pressure |
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Purpose of Engine Bleed Valve |
*Help prevent compressor stalls at low speed, *Closed at flight operation speeds, *Open during start and idle, *Modulates toward closed with engine accel. |
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While transitioning throttle from IDLE to FLY position, TORQUE should be maintained less than what or may result in what? |
40% Eng Overspeed, Overtorque, or surge. |
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When spooling up, at what % NR does the RPM warning light extinguish? |
95% NR |
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Failure to position & maintain throttle in FLY Detent prior to takeoff & during flight can result in what? |
Limit available engine power |
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At high power & high airspeed, cyclic only accelerations & maneuvering may result in what? |
Significant increase in MGT and TORQUE |
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When should the PEDAL STOP PTT ENGAGED annunciator illuminate? |
55 ±5 KIAS |
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Positioning THROTTLE out of CUTOFF during NG spool down may result in what? |
Post Engine Shutdown fire |
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Autorotation Max airspeed: Min rate of descent airspeed: Max glide distance airspeed: |
100 KIAS 55 KIAS 80 KIAS. |
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Engine UNDERSPEED indications: |
*No caution/warning/advisory lights illuminated, *Decrease in NG, *Subsequent decrease in NP, *Possible decrease in NR, *Decrease in TRQ. |
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Engine UNDERSPEED procedure: |
1. Collective — Adjust as required to maintain 85 to 107% NR. 2. Throttle — Confirm in FLY detent position. 3. Throttle — Position throttle to approximate bezel position that coincides with NG. 4. FADEC MODE switch — MAN. 5. NR — Maintain 95 to 100% with throttle & collective. 6. Land as soon as practical. |
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Engine OVERSPEED indications: |
*No caution/warning/advisory lights illuminated, *Increase in NR *Increase in NP *Increase in NG *Increase in TRQ
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Engine OVERSPEED procedure: |
1. Throttle — Retard. 2. NG or NP — Attempt to stabilize with throttle & collective. 3. FADEC MODE switch — MAN. 4. NR — Maintain 95 to 100% with throttle & collective. If unable to maintain NR, NP,NG, OR MGT, prepare for power off landing. |
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Engine COMPRESSOR STALL/SURGE indications: |
1. Engine pops. 2. High or erratic MGT. 3. Decreasing or erratic NG or NP. 4. TRQ oscillations. |
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Engine COMPRESSOR STALL/ Surge procedure: |
1. Collective — Reduce power, maintain slow cruise flight. 2. MGT and NG — Check for normal indications. 3. ENG ANTI ICE switch — ON. 4. PART SEP switch (if installed) — ON. 5. HEATER switch (if installed) — ON. 6. Collective — Increase slowly to achieve desired power level. 7. MGT and NG — Monitor for normal response. 8. Land as soon as practical. |
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Engine OIL PRESSURE Low, High, or Fluctuating indications: |
1. Eng oil press below min: a. Monitor eng oil press & temp. b. Land as soon as possible. 2. Eng oil press above max or fluctuating abnormally: a. Monitor eng oil press & temp. b. Land as soon as practical. |
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Engine OIL TEMP high procedure: |
Land as soon as practical |
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Driveshaft failure indications: |
1. Left yaw. 2. Rapid decrease in NR. 3. Rapid increase in NP. 4. LOW RPM audio horn. 5. Illumination of RPM light. 6. Increase in noise due to overspeeding engine and driveshaft breakage. |
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Driveshaft failure procedure: |
1. Maintain heading & attitude control. 2. Collective — Adjust as required to maintain 85 to 107% NR. 3. Cyclic — Adjust to obtain desired autorotative airspeed. NOTE: To maintain tail rotor effectiveness, do not shutdown engine. 4. Landing — Complete autorotation landing. 5. Complete helicopter shutdown |
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FADEC FAILURE indications: |
1. FADEC fail audio activated. (ding dong) 2. FADEC FAIL warning light illuminated. 3. FADEC MANUAL caution light illuminated. 4. FADEC MODE switch MAN light illuminated. |
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FADEC FAILURE procedure: |
1. Throttle — If time permits, match throttle bezel position to NG indication. 2. NR/NP — Maintain 95 to 100% with collective & throttle. 3. FADEC MODE switch — Depress one time, muting FADEC fail audio. AUTO RELIGHT advisory light illuminates. 4. Land as soon as practical. 5. Normal shutdown if possible. |
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ENGINE FIRE on ground procedure: |
1. Throttle — Closed. 2. FUEL VALVE switch — OFF. 3. GEN switch — OFF. 4. BATT switch — OFF. 5. Rotor brake (if installed) — Engage. 6. Exit helicopter (GTFO) |
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ENGINE FIRE during flight procedure: |
1. In-flight — Immediately enter autorotation. 2. Throttle — Closed. 3. FUEL VALVE switch — OFF. 4. If time permits, FUEL BOOST/XFR circuit breaker switches — OFF. 5. Execute autorotation 6. BATT switch — OFF |
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CABIN SMOKE OR FUMES procedure: |
1. In-flight — Start descent. 2. AIR COND BLO switch (if installed) —OFF. 3. HEATER switch (if installed) — OFF. 4. All vents — Open. 5. Side windows — Open if time & altitude permits: 6. Source — Attempt to identify & secure. 7. If smoke &/or fumes still persist — Land as soon as possible. 8. If smoke and/or fumes are cleared — Land as soon as practical. |
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ELECTRICAL FIRE procedure:
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1. Vents/side windows — Open, as required; ventilate cabin.
2. Begin descent. 3. Circuit breaker OFF or Gen switch OFF 4. Land as soon as practical. If smoke/fumes do not decrease: 5. Airspeed - 60 knots or less 6. BATT switch - OFF 7. FUEL BOOST/XFR LEFT (on) Land as soon as possible. |
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How long will the Left Fuel Boost/Xfr pump operate after battery depletion?
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1.7 hours on an 80% charged battery
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What happens to the Pedal Stop with loss of electrical power?
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It disengages
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What will the PMA do after battery depletion when throttle is repositioned to the idle stop?
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It will go offline & the engine may flame out.
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Complete Loss of Tail Rotor Thrust indications:
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1. Uncontrollable yawing to right 2. Nose down tucking 3. Possible roll of fuselage |
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Complete Loss of Tail Rotor Thrust procedure: |
1. Reduce throttle to idle 2. Enter autorotation 3. Maintain 55 KIAS minimum NOTE 4. Continue at low power & sufficient airspeed 5. Autorotation with mild flare, landing on aft portion of skids. (run-on) |
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Fixed TR Pitch Failures: |
*Hovering: Don't close throttle unless severe yaw. *Pull pedal stop emergency release *Fly to suitable landing area if possible *Adjust collective, throttle & airspeed to land |
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START EP |
*START circuit breaker; OUT *Land as soon as practical |
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RESTART FAULT EP |
*Cannot be restarted *Remain in Auto *Plan landing accordingly |
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Pedal Stop EP |
*Vne 60 KIAS *Pull pedal stop emergency release *Land as soon as practical |
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Fuel XFR EP |
One or both; Land as soon as practical |
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Loss of Hydraulic pressure indications: |
*HYDRAULIC SYSTEM caution light *Grinding or howling noise from pump *Increase in force required to move flight controls *Feedback forces in controls |
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Loss of Hydraulic pressure procedure: |
*Reduce airspeed to 70-100 KIAS *troubleshoot *HYD SYSTEM circuit breaker Out, if power not restored, push back in. *Switch off *Land as soon as practical *Run-on landing recommended |
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Actuator Hardover indications: |
*Uncommanded movements of one or two flight controls *Can occur any axis, opposes one axis |
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Actuator Hardover procedure: |
*Maintain attitude *HYD SYSTEM switch OFF *70-100 KIAS *Land as soon as possible |
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Generator Failure indications: |
*GEN FAIL caution light *AMPS indicates 0 *Voltmeter indicates 24 +- |
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Generator Failure procedure: |
*GEN FIELD & GEN RESET circuit breakers IN *GEN switch; RESET then GEN *If no power, GEN switch OFF, Land as soon as practical *approximately 21 mins battery |
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Excessive Electrical Load indications: |
*AMPS indicates excessive load *Smoke or fumes |
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Excessive Electrical Load procedure: |
*GEN switch OFF *BATT switch OFF *FUEL BOOST/XFR LEFT switch ON *Airspeed 60 KIAS *Land as soon as practical |
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How much fuel may be unusable after battery depletion? |
151 lbs |
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Dual Fuel Transfer Failure indications: |
*L/FUEL XFR & R/FUEL XFR caution lights *151 lbs of fuel may be unusable *Stops transferring from fwd to aft cell at 344 lbs total |
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Dual Fuel Transfer Failure procedure: |
*LEFT & RIGHT FUEL BOOST/XFR circuit breakers ON *Determine FUEL QTY in fwd cell *Subtract fwd trapped fuel from total *Plan landing accordingly |
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Cyclic Cam Jam indications: |
*High (15 lbs) fore & aft cyclic control forces *Other controls normal |
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Cyclic Cam Jam procedure: |
*Maintain normal pitch attitude *Do not turn off hydraulics *Land as soon as practical |
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BATTERY HOT EP |
*Turn BATT switch OFF *Land as soon as practical *If BATTERY RLY illuminates, turn GEN switch OFF *Land as soon as possible |
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ENGINE OVSPD EP |
*Adjust throttle & collective as needed *Determine if engine is controllable *If not, shut down *Maintenance required |
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FADEC FAIL EP (during start) |
*Close throttle immediately *Engage starter to reduce MGT *Maintenance required |
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FADEC FAIL EP (in-flight) |
*Match throttle bezel to NG *Maintain 95-100% NR/NP with throttle & collective *Depress FADEC MODE switch to mute *Land as soon as practical |
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FADEC FAIL EP (on approach) |
Go around, following FADEC FAIL procedure |
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RPM EP (with low RPM audio) |
*Reduce collective *Ensure throttle is in FLY (troubleshoot) *Will stop when NR is above 95% |
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RPM EP (without audio) |
*If RPM is above 107%, increase collective *Reduce severity of maneuver |
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XMSN OIL PRESS EP |
*Reduce power *Verify fault with gauge *Land as soon as possible |
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XMSN OIL TEMP EP |
*Reduce power *Verify fault with gauge *Land as soon as practical |
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CHECK INSTR EP |
*Reduce engine power *Press INSTR CHK button to display exceedance |
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ENGINE ANTI-ICE EP |
*Avoid ops requiring max power |
White |
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ENGINE, T/R, XMSN CHIP |
*Land as soon possible |
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FADEC DEGRADED EP |
*Remain in Auto mode *Fly smoothly & non-aggressively *Land as soon as practical |
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FADEC FAULT EP |
*Remain in Auto mode *Land as soon as practical |
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FADEC MANUAL EP |
*Fly smoothly & non-aggressively *Maintain NR with throttle & collective (gov off) *Land as soon as practical |
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FUEL FILTER EP |
*Land as soon as practical |
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How much fuel remains when FUEL LOW light illuminates? |
100+-10 lbs |
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R/FUEL OR L/FUEL BOOST EP |
*Descend below 8000 feet Hp *Land as soon as practical *If BOTH fail, Land as soon as possible |
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FUEL VALVE EP |
*Check FUEL VALVE circuit breaker *Land as soon as practical |
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L/FUEL OR R/FUEL XFR EP |
*Land as soon as practical *If BOTH fail, 151 lbs may be trapped *Land as soon as practical |
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HEATER OVERTEMP |
*Turn heater off |
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LITTER DOOR EP |
*Land as soon as practical |
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PEDAL STOP EP |
*Vne 60 KIAS *Pull PEDAL STOP emergency release *Land as soon as practical |
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RESTART FAULT EP |
*Remain in Auto mode *Plan landing accordingly |
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Describe MR system |
*Four-bladed, soft-in-plane with composite hub and individually interchangeable blades *35 feet |
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Why is the vertical fin canted outboard 9°? |
To reduce the required amount of TR thrust during fwd cruise flight |
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What is the purpose of the horizontal stabilizer? |
An inverted airfoil which provides downward resultant lift on the tailboom to maintain the cabin in a nearly level attitude |
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What is the purpose of the leading edge slats on the horizontal stabilizer? |
Improve pitch stability during climbs |
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Why are the aux fins (dynamic dihedrals) offset 5° outboard? |
To improve the roll stability in fwd flight |
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What does the "Ahlers" NR/NP gauge do differently than the rest? |
*No automatic BIT *gotta push LCD button |
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Which instruments have Exceedance Monitoring? |
TORQUE, MGT, Ng |
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What are the 9 ECU inputs? |
1. CP (collective pitch) 2. PLA (power lever angle) 3. P1 (ambient pressure) 4. MGT 5. Ng 6. Nr 7. Np 8. TRQ 9. CIT (compressor inlet temp) |
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Name the five categories of FADEC faults |
Cat 1 -- FADEC FAIL / FADEC MANUAL -- DRTM Cat 2 -- FADEC DEGRADED Cat 3 -- FADEC FAULT Cat 4 -- RESTART FAULT Cat 5 -- Maintenance advisory |
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Describe Category 1 FADEC FAIL fault |
*Requires pilot action *DRTM *FADEC FAIL horn, FADEC FAIL, FADEC MANUAL, RESTART FAULT |
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Describe Category 2 FADEC DEGRADED fault |
*Represents loss of some FADEC feature which causes degradation in performance *Possible Nr droop, Nr lag, reduced max power *Possible RESTART FAULT *Possible reversionary governor |
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Describe Category 3 FADEC FAULT fault |
*Indicates PMA, MGT, Np, Ng automatic limiting circuits may not be functional *FADEC FAULT & RESTART FAULT possible |
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Describe Category 4 RESTART FAULT fault |
*Indicates subsequent start may not be possible *Should not affect performance |
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Failure of the FADEC into Reversionary Governor mode is indicated by what? |
*FADEC FAULT *FADEC DEGRADED *RESTART FAULT |
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Describe Category 5 Maintenance Advisory fault |
*Minor in nature (not in flight problem) *FADEC DEGRADED serves as maintenance advisory light on shutdown *Check codes with Maintenance Terminal or Maintenance Mode |
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Describe magnetic chip detector locations |
1. Engine sump chip: Lower left side of engine gear box. 2. Engine scavenge chip: fwd right-hand side of engine gearbox. 3. Upper main XMSN 4. Lower main XMSN 5. Fwd freewheel housing 6. TR gearbox |
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Fail safe on systems |
*ENG ANTI ICE *Hydraulics *PRCU |
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What connects the aft fuel cell to the fwd tank? |
The gravity stand pipe |
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Describe fuel travel from fwd tank to engine. |
*Fwd to aft tank: two transfer pumps through stand pipe *From aft tank: two boost pumps *Through fuel shutoff valve *Through airframe fuel filter *To engine driven fuel pump on HMU |
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Will the boost pumps function with BATT off & why? |
Yes, left boost/xfr due to alternate circuit (yellow border) (with fuel valve on) |
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Describe "hotstart abort logic" |
FADEC automatically aborts start if: *MGT exceeds 843°C < 10,000' *MGT exceeds 912°C > 10,000' *note, I should abort at triangle *below 10.3 voltage |
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BATT switch on or off for a battery cart start? |
OFF; turn ON prior to disconnecting external power source |
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Describe CEFA |
*Combined Engine Filter Assembly *Provides fuel & scavenge lube filtration *Located lower left portion of the power & accessory gearbox *Has two LRBs to indicate impending bypass |
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Describe location of all LRBs |
*2 on hydraulic filters *1 XMSN filter *2 cefa *ptt airframe fuel filter |
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When is the PMA active? |
85% Np and above |
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Where does the ENG ANTI ICE get the hot air? |
*Compressor discharge *Heated by rapid compression |
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When will the AUTO RELIGHT advisory light be active? |
*During start until 60% Ng *During MANUAL mode above 55% Ng |
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When will the FUEL LOW caution light activate? |
100 lbs or less fuel remaining |
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What warning do you have prior to an exceedance? |
*Check INSTR light *Gauge LCD arc will flash |
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How does the Fuel Pressure / Ammeter gauge receive info? |
*Pressure transducer below the fuel valve *Measures boost pump output *DC current load on GEN |
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How does the Fuel Quantity gauge get info? |
Three probes in the fuel cells |
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How does the XMSN Oil Pressure / Temp gauge receive info? |
*Transducer on XMSN deck oil manifold *Thermo-bulb on XMSN Oil filter manifold |
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How does the Engine Oil Pressure / Temp gauge receive info? |
*Transducer on fwd right side of engine firewall *Thermo-bulb on engine oil tank |
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How does the Torque gauge receive info? |
*Oil pressure transducer |
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How does the MGT gauge receive info? |
*Four thermocouple probes between the gas producer turbine & power turbine |
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How does the Ng gauge receive info? |
*Monopole speed pickup on engine accessory gearbox |
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How does the Np/Nr dual tach gauge receive info? |
*Monopole speed pickup on engine *Monopole speed pickup on XMSN lower case |
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PRCU & when is it active? |
*Pedal Restrictor Control Unit *Activates at 55 KIAS *Deactivates at 50 KIAS |
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Purpose of the "pivot beam" on aft crosstube |
*Minimizes ground resonance *Allows limited lateral of airframe while on ground |
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Three systems energized by the "Weight on gear" switch |
*Cyclic centering *Hour meter *Flight time |
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