MH-65C EPs and Limits

• Corrective Action:
• 1. LANDING/HOVER CHECKLIST − COMPLETE (200 foot checks at a minimum based on urgency).
• 2. LAND/DITCH IMMEDIATELY (POWER ON).

WARNING: The potential loss of the airframe after aircrew egress is not sufficient cause to continue flight.

• Symptoms:
• 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.

• Corrective Action:
• 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.

WARNING: Due to the potential for fire damage to the flight control servos and/or the associated hydraulic lines, a fire in this compartment may result in complete loss of aircraft control.

• Symptoms:
• 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.

• Corrective Action:
• 1. ATTEMPT TO CONFIRM PRESENCE OF FIRE (alert crew).
• 2. SINGLE ENGINE FLIGHT PROFILE − ESTABLISH.
• If fire NOT confirmed:
• 3. LAND AS SOON AS PRACTICABLE.
• 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 no longer evident:
• 9. ENGINE SHUTDOWN PROCEDURE − COMPLETE.
• If fire still persists:
• 9. LAND/DITCH IMMEDIATELY.

• Symptoms:
• 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.

• Corrective Action:
• 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.

• Symptoms:
• 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).

• Corrective action:
• 1. DESIGNATE CREWMAN TO FIGHT FIRE.
• 2. AFFECTED EQUIPMENT − OFF.
• 3. HEAT/COOL SWITCHES − OFF.
• 4. RAM AIR − CLOSED.
• 5. CABIN SLIDING DOOR − CLOSED.
• 6. PILOT’S WINDOWS − CLOSED.
• 7. RACK BLOWER CIRCUIT BREAKER − PULL (for avionics rack fire only − avionics rack panel R4 #4).
• 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.

CAUTION: A popped circuit breaker should only be reset once. Repeated resetting or holding in may result in an electrical fire.

• NOTE: An avionics fire will be fought by disconnecting enough camlocks on the avionics rack panel to allow access for the fire extinguisher nozzle. Short blasts are advised to preserve extinguishing agent
• in case of a reflash. Close rack panel and monitor for reflash.

• NOTE: All communication, both internal and external, and all aircraft system lighting will be lost after
• activating Emergency Cut−Off switch.

WARNING: The severity of the fire and actual flight conditions (night/instrument) will dictate the immediate procedures to be followed. It may not be advisable to secure all electrical power, thus losing AFCS and flight instruments, prior to achieving VMC.

WARNING: With the emergency electrical cutoff in the OFF position, the flotation system will not be available. Consideration should be given to activating floats prior to securing if ditching is anticipated.

• Corrective Action:
• 1. HEAT/COOL SWITCHES − OFF.
• 2. RAM AIR − OPEN.
• 3. CABIN SLIDING DOOR − OPEN.
• 4. PILOTS’ WINDOWS − OPEN.
• 5. LAND AS SOON AS PRACTICABLE.

WARNING: If fuel fumes are present, limit radio transmissions to a minimum. Due to antenna location, COMM 1 is the best choice.

CAUTION: To avoid the possibility of rotor blade or structural damage, do not jettison any window or door unless deemed absolutely essential for smoke or fume removal.

• Corrective Action:
• 1. FADEC CONTROL SWITCHES − 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:
• 5. EMERGENCY ELECTRICAL CUTOFF − OFF.
• 6. ROTOR BRAKE − ON.
• 7. EVACUATE AIRCRAFT.

• Symptom:
• 1. TOT rises or does not decrease within 10 seconds after the FADEC control switch has been placed in the OFF position.

CAUTION: If the engine does not stop immediately (solenoid valve failure), the FADEC will shut down the engine 5 to 6 seconds later. Do not move the Emergency Fuel Shutoff Lever to the shutoff position before 10 seconds have elapsed.

CAUTION: Operation of the crank button with the EFSL pulled will cause severe damage to the engine fuel pump.

• 1. LAND AS SOON AS POSSIBLE.
• or
• 1. LANDING/HOVER CHECKLIST − COMPLETE (200 foot checks at a minimum based on urgency).
• 2. LAND/DITCH IMMEDIATELY.

• Symptom:
• 1. Rotor blade damage is known or suspected, with or without secondary indications of up to mild.
• or
• Symptoms:
• 1. Rotor blade damage is known or suspected.
• AND
• 2. Secondary indications (such as vibrations) are more than mild, flight characteristics are drastically
• altered.

WARNING: The potential loss of the airframe after aircrew egress is not sufficient cause to continue flight.

NOTE: A reduction in airspeed may reduce vibrations and improve flight characteristics (weather, flight conditions, and distance from landing area permitting).

• Corrective Action:
• 1. COMPLETE THE “BIG 4.”
• 2. MONITOR OTHER NR INDICATOR (IF OPERABLE) OR N2.
• 3. AVOID ABRUPT MANEUVERS.
• 4. ABORT MISSION.

• Symptom:
• 1. One or both Nr gauges fluctuates abnormally or indicates zero.

NOTE: The Low Nr audio will still function even when the Nr indicator fails.

• Corrective Action:
• 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.

• Symptom:
• 1. Any uncommanded left yaw not attributable to mechanical failure of the tail rotor drive system.

CAUTION: Gradual pedal input will not arrest increasing rates of yaw. Recovery will lag pedal input. During flight testing, up to 300 degrees of lag has been experienced between pedal application and yaw stabilization. This should not be mistaken for a loss of thrust situation.

WARNING: Rapidly lowering the collective can initiate or increase an undesirable descent rate. If a large descent rate develops close to the ground/water, the subsequent large collective increase required to arrest the descent prior to ground/water contact may aggravate or re−initiate ULY.

• Corrective Action:
• 1. ESTABLISH SAFE ALTITUDE AND AIRSPEED FOR POSSIBLE LOSS OF TAIL ROTOR THRUST.
• 2. LAND AS SOON AS POSSIBLE.

• Symptom:
• 1. Illumination of the GB CHIP warning light and a TGB CHIP annunciation on the VEMD CAUTION/FUEL page.

• Corrective Action:
• 1. EMERGENCY FUEL SHUTOFF LEVERS − BOTH OFF.
• 2. MAINTAIN LANDING ATTITUDE.
• 3. CUSHION LANDING WITH COLLECTIVE.

• Symptoms:
• 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.

• Corrective Action:
• 1. DIRECTIONAL CONTROL − MAINTAIN USING CYCLIC AND COLLECTIVE.
• 2. LAND AS SOON AS PRACTICABLE. UTILIZE PROCEDURE FOR LANDING WITH TAIL
• ROTOR MALFUNCTION.

• Possible Symptoms:
• 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).

WARNING: If a suitable surface is not available, a power−off autorotative landing to the best available area is required.

• 1. Nr − MAINTAIN.
• 2. AIRSPEED/ALTITUDE − CONTROL AND SET LIMITS.
• 3. WHEELS/FLOATS − AS REQUIRED.
• 4. ANALYZE.

CAUTION: Any operation of the engines in the 30 Second power range will require major engine maintenance. The helicopter shall be landed as soon as practicable. Further flight shall not be attempted until a thorough inspection has been accomplished by qualified maintenance personnel and a maintenance release obtained.

• MAXIMUM GLIDE - 105 - 360
• A speed of 105 KIAS and 360 RPM will result in maximum glide distance.

• MINIMUM RATE OF DESCENT - 75 - 360
• A speed of 75 KIAS and 360 RPM will result in the minimum rate of descent. Any increase in rotor RPM will result in a greater rate of descent.

• Corrective Action:
• 1. Nr − MAINTAIN.
• 2. PERFORM AUTOROTATION PROCEDURE.

• Symptoms:
• 1. Low Nr horn − ON.
• 2. Nr − DECAYING.
• 3. Engine parameters − BOTH ENGINES DECREASING.
• 4. Possible right yaw.

• Corrective Action:
• 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.

• Corrective Action:
• 1. COMPLETE THE “BIG 4” (airspeed 75 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. CONTROL THE RATE TO ARRIVE AT 20 DEGREES NOSE − UP AT 75 FT RADALT; INFLATE FLOATS AS REQUIRED.
• 5. MAINTAIN FLARE UNTIL DESIRED AIRSPEED IS REACHED − 30 KTS PLUS HALF THE WIND SPEED.
• 6. ASSUME 5 NOSE UP, WINGS−LEVEL LANDING ATTITUDE.
• 7. AT 25 FT 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.

• Corrective Action:
• 1. Nr − MAINTAIN.
• 2. AIRSPEED/ALTITUDE − CONTROL
• 3. WHEELS/FLOATS − AS REQUIRED.
• 4. LAND BACK OR CONTINUE FLIGHT.
• LANDBACK 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

• Symptoms:
• 1. Possible Nr droop.
• 2. Abnormal engine parameters.
• 3. DIF N1 warning light illuminated.
• 4. Low Nr horn.
• 5. Torque, TOT, N1, N2, fuel pressure decreasing.
• 6. As engine spools down, additional symptoms will become evident such as Generator Failure, Eng Oil P light.
• 7. FLI switches to single engine display.
• 8. ECS disengages.
• 9. Bleed air shuts off.

NOTE: Where continued flight is hindered by gross weight, consideration should be given to jettisoning fuel.


WARNING: Do not allow rotor RPM to decrease below 300 RPM Nr.

• Corrective Action:
• 1. COMPLETE THE “BIG 4.”
• 2. ENGINE SHUTDOWN PROCEDURE −
• COMPLETE.

• Symptoms:
• 1. Possible Nr droop.
• 2. Abnormal engine parameters.
• 3. DIF N1 warning light illuminated.
• 4. Low Nr horn.
• 5. Torque, TOT, N1, N2, fuel pressure decreasing.
• 6. As engine spools down, additional symptoms will become evident such as Generator Failure, Eng Oil P light.
• 7. FLI switches to single engine display.
• 8. ECS disengages.
• 9. Bleed air shuts off.

• If the situation warrants and time permits, an ENGINE RESTART may be attempted.
• NOTE: If the engine can not be restarted, ECS may still be recovered by resetting the COOL switch.

• Corrective Action:
• 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.)

• Symptoms:
• 1. ENG # CHIP warning light illuminated.
• 2. Corresponding ENGINE CHIP annunciation on the VEMD CAUTION/ FUEL page.

• Corrective Action:
• 1. COMPLETE THE “BIG 4.”
• 2. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

• Symptoms:
• 1. N2 significantly above Nr.
• 2. Zero torque on malfunctioning engine.
• 3. Possible loud noises from the engine area.

CAUTION: When N2 reaches 122.4% (±1%), the FADEC will operate the stop electro−valve via the BIM and shut the engine down.

• Corrective Action:
• 1. COMPLETE THE “BIG 4.”
• 2. ENGINE PARAMETERS − MONITOR.
• 3. LAND AS SOON AS PRACTICABLE.

• Symptoms:
• 1. DIF N1 Warning Light illuminated.
• 2. Single engine FLI display.
• 3. N1 difference between both engines is greater than 6%.

• Corrective Action:
• 1. COMPLETE THE “BIG 4.”
• 2. TRNG SWITCH − FLT.
• 3. FADEC BACK−UP SWITCH (affected engine) − BACK−UP.
• 4. OEI − SET AS NECESSARY.
• 5. LAND AS SOON AS PRACTICABLE.

• Symptoms:
• 1. FADEC # FAIL caution light illuminated.
• 2. Red ENGINE STATUS light on the overhead quadrant illuminated.
• 3. DUAL ENGINE FLI DISPLAY with OEI.
• 4. Affected engine will not respond to collective movement due to Fuel Flow metering being frozen at the rate present when the FADEC failed.

NOTE: In back−up mode, FADEC will match the N1 of the affected engine to the N1 of the good engine. While N1 matching is assured, there will be some acceleration delay on the engine in back−up mode.

WARNING: With the FADEC Back−up Switch in back−up, N1 matching will occur without regard to the opposite engine’s current N1 setting.

WARNING: The FADEC Back−up Switch shall not be in the back−up position when an engine is at training idle.

• Corrective Action:
• 1. COMPLETE THE “BIG 4.”
• 2. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

• Possible Symptoms:
• 1. ENG # OIL P warning light illuminated.
• 2. Engine oil pressure fluctuates, increases or decreases abnormally.
• 3. Engine warning light illuminated on the overhead control quadrant.
• 4. Engine oil pressure less than 25 psi.

CAUTION: A combination of the engine oil pressure gauge decreasing or reading zero AND illumination of the OIL P warning light shall not be treated as an indicating malfunction, but rather as a lubrication system failure. Pilots shall not wait for additional symptoms before completing the engine shutdown procedure.

NOTE: Oil pump failure resulting in the above symptoms may be preceded by an initial increase in oil pressure above 100 psi, accompanied by a CHECK CDU annunciation.

• Corrective Action:
• 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 NORMAL IDLE parameters:
• 4. LAND AS SOON AS PRACTICABLE.
• If ABNORMAL IDLE parameters:
• 4. ENGINE SHUTDOWN PROCEDURE − COMPLETE

• Possible Symptoms:
• 1. Popping or rumbling noises.
• 2. TOT increases.
• 3. Torque and N1 decreases.
• 4. Airframe vibration.

NOTE: If additional power is required for landing, the engine may be switched to FLT mode. A surge may reoccur at any time.

• Corrective Action:
• 1. FADEC CONTROL SWITCH (affected engine) − OFF.
• 2. FUEL BOOST PUMPS (affected engine) − OFF.
• 3. TOT − MONITOR FOR POST SHUTDOWN FIRE.

• Possible Symptoms:
• 1. Popping or rumbling noises.
• 2. TOT increases.
• 3. Torque and N1 decreasing.
• 4. Airframe vibration/shuddering.

• If ONE engine 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.)
• If BOTH engines overheated:
• 1. CRUISE AIRSPEED − 120 KIAS MIN.
• 2. LAND AS SOON AS POSSIBLE.
• 3. SHUT DOWN ENGINES AS SOON AS POSSIBLE.
• High power settings may increase temperatures. This failure may not be evident at airspeeds above 120 KIAS.
• Symptoms:
• 1. OIL TEMP warning light illuminated.
• 2. Abnormal rise in ENG OIL TEMP.

• 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).

• Corrective Action:
• 1. HEAT − OFF.
• 2. BOOST PUMPS − ON.
• 3. EMERGENCY FUEL SHUTOFF LEVER − ENSURE FORWARD.
• 4. CHECK N1 LESS THAN 17%.
• 5. PERFORM NORMAL START PROCEDURE.
• If engine start successful:
• 6. LAND AS SOON AS PRACTICABLE.
• If engine fails to light off:
• 6. ENGINE SHUTDOWN PROCEDURE − COMPLETE.

• Corrective Action:
• 1. FADEC CONTROL SWITCH − OFF.
• 2. TOT − MONITOR FOR POST SHUTDOWN FIRE.

• Possible Symptoms:
• 1. Insufficient voltage to start.
• 2. Voltage drops below 17 VDC.
• 3. TOT rises rapidly and/or appears that it will exceed 750 ^oC (Hot start).
• 4. The rotor system does not turn by 25% N1.
• 5. No rise in TOT or N1 within 10 seconds after FADEC CONTROL SWITCH is moved.
• 6. Engine does not reach 45% N1 by 30 seconds and is no longer accelerating.

NOTE: The FADEC will automatically shut the engine down during start if the TOT exceeds 840 ^oC. The pilot shall initiate a shut down if it appears that the TOT will exceed 750 ^oC.

CAUTION: If engine start fails and OAT is at or below 0 ^oC with TOT greater than 120 ^oC, crank engine for 20 seconds prior to subsequent start.

• Corrective Action:
• 1. COMPLETE THE “BIG 4.”
• 2. MONITOR OTHER ENGINE PARAMETERS.
• 3. AVOID HIGH POWER SETTINGS.
• 4. ABORT MISSION. URGENT MISSION MAY BE COMPLETED.

• Possible Symptoms:
• 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 (TOT failure).
• 4. All other engine parameters normal.