MH60R EPs

#1 Primary Servo or #1 Transfer Module Leak indications

#1 RSVR LOW and #1 HYD PUMP and BACK UP PUMP ON

Tail rotor servo malfunction cautions

#1 TAIL RTR SERVO and BACKUP PUMP ON and #2 TAIL RTR SERVO ON

Pilot Assist Servo Leak cautions

#2 RSVR LOW and BOOST SERVO OFF and SAS and AFCS DEGRADED

#1 and #2 FUEL FLTR BYPASS or #1 and #2 FUEL PRESS Caution

*1 Land as soon as possible *2 APU Emergency Start procedure - Perform W: Be prepared for dual-engine failure. Recommend 80 KIAS to minimize Nr droop should dual-engine failure occur N: Consideration should be given to performing applicable steps of the Immediate Landing/Ditching emergency procedure W: Intermittent appearance of a FUEL PRESS caution may be an indication of air leaking into the fuel supply lines, which could cause momentary fluctuation in engine power or flameout

Utility HYD Pump

*1 Stop dome C: Utility hydraulic pump with low or no hydraulic fluid shall be secured to prevent damage to the pump

APU Fire

*1. APU T-handle - Pull *2. Confirm fire *3. FIRE EXTGH switch - RESERVE (MAIN if required and available) If airborne and fire continues: *4. Land immediately If fire appears extinguished: *5. Land as soon as possible If on ground: *6. Fire extinguisher- as required N: HF transmissions, sunlight filtered through smoke/haze/water/sunrise or sunset may trigger fire light false indication

Smoke and fumes elimination

*1. Airspeed - Adjust, as required *2. Doors/windows/vents - Open *3. Aircraft - Yaw, as required

Dual Engine Failure

*1. Autorotation - Establish *2. Immediate Landing/ Ditching EP - Perform. If time and altitude permit: *3. Engine Air Restart EP - Perform. W: Nr decay rapidly, delay in lowering collective result in loss of rotor rpm and catastrophic failure of rotor system due to dynamic instability W: altitude hold engaged unless deselected. AFCS commanded collective movement could result in catastrophic loss of Nr W: >110% Q with OEI -> unrecoverable decay in Nr. Generators offline 80% Nr

Dual EGI Failure

*1. Backup instruments - scan, as required *2. #1 and #2 EGI PWR switches - OFF, then ON

Immediate Landing/Ditching

*1. Crew and passengers - alert *2. Shoulder harness - locked *3. external cargo/ stores/ fuel - jettison/dump, as required *4. Searchlight - as required *5. MAYDAY/ IFF- TRANSMIT/ EMER time permitting consideration should be given to executing APU emergency start to maintain hyd and electrical power upon rotor disengagement In the flare: *6. Windows - Jettison, as required W: after actuation handle may snag during egress. Stow before egress if time permits After landing: *7. PCLs- OFF *8. Rotor Brake -ON *9. Copilot collective - Stow *10. Pilot HCU- stow After all violent motion stops: *11. Egress W: failure to wait may -> injury or incapacitation

APU Emergency Start

*1. ECS- OFF *2. AIR SOURCE ECS/START switch - APU *3. FUEL PUMP switch - APU BOOST *4. APU CTRL switch -ON *5. APU GENERATOR switch - ON

Underwater Egress

*1. Emergency Breathing Device- as required *2. Cord(s) - disconnect *3. Door/ window - open/ jettison *4. Place hand on known reference point *5. Harness- release *6. Exit helicopter After egress: *7. Swim clear of helicopter and inflate LPU W: if egress delayed use emergency breathing device W: failure to disconnect ICS cord can impede egress W: water px may prevent opening windows until cabin full of water. Windows should be jettisoned prior to water entry W: downstroke of seat may change frame of reference W: Don't inflate LPU until outside helo

HYD Warning

*1. Land immediately.

Boost Servo Hardover

*1. PAC call - "BOOST, BOOST, BOOST" *2. SAS/BOOST pushbutton - OFF C: up to 75lb left pedal force req with stbd crosswind C: Landing boost off on single spot air capable ship should only be attempted if no larger ship or shore landing available

Loss of tail rotor drive (altitude and airspeed not sufficient to establish autorotation)

*1. PAC call - "HOVER, HOVER, HOVER." *2. Collective - Lower. *3. PNAC - Hands on PCLs. *4. PCLs - OFF when directed (approximately 20 to 30 ft). C: altitude may have to be adjusted based on rate of yaw and/or turn

Hung Droop Stop(s)

*1. Reengage rotor to greater than 75% Nr N: in cold wx consider turning blade de-ice power on to activate droop stop heaters which can aid in droop stop seating

Internal Engine Fire

*1. Starter - Engage Motor Engine.

Tail rotor control cable failure info

-TAIL ROTOR QUADRANT caution -No change in handling req, land practicable -lose both cables -> loss TR control...preset spring loaded position FOR 19,500lb level flight AT 25KIAS or 145KIAS (adj based on environment). Yaw R outside range, L inside range

Tail rotor servo failure info

-if lose #1 hyd pump and backup pump - yaw boost servo is still px so normal yaw 40-120KIAS. Pedals less effective near outside of the range. -roll on ldg above 40KIAS recommended

#2 Primary Servo or #2 Transfer Module Leak

1) SERVO switch — 2ND OFF. 2) Land as soon as practicable. IF THE BACKUP RSVR LOW CAUTION ALSO APPEARS OR BACKUP PUMP FAILS: 3) Land as soon as possible. IF THE #1 PRI SERVO CAUTION AND/OR HYD WARNING APPEARS: 4) Land immediately. N: failure to ensure backup pump auto or on prior to landing with #2 HYD PUMP caution -> loss PAS when WOW N: if lose back up too be orepearws for loss of PAS

Uncommanded lasing

1. ACI MASTER ARM- safe 2. LASER SEECT switch - safe If lasing continues 3. FLIR beze key > +FLIR OFF -select

Engine air reatart

1. APU emergency start procedure - as req 2. Engine ignition switch- norm 3. Fuel sector lever(s)- DIR or XFD 4. PCL(s)- OFF 5. Starter(s)- engage, motor engine 6. PCL(s)- idle (TGT 80C or less of time permits) 7. PCL(s)- advance to FLY after starter dropout W: if APU unavailable and xbld start req, Q for level flight may not be available. Ensure AIR SOURCE ECS/START switch to ENG C: for xbld start donor max available, receiving eng 24% Ng min or else possible hot start W: if explosion or unusual noise don't restart or else possible fire N: if alternator fails, Ng signal unavailable. Engine start won't be possible without AC power to ignition exciter N: can do either single or dual engine restart

Sonar EP steps

1. Alert crew 2. Execute teeing machine malfunction emergency procedure 3. Complete the sonar troubleshooting checklist

All stores jettison

1. All stores jettison PB press

TAIL ROTOR QUADRANT CAUTION

1. Check for tail rotor control If tail rotor control is not available: 2. Loss of TR control EP- perform C: if helo is shutdown or hyd power is removed with one TR cable failed, the other cable will disconnect

Loss of Tail Rotor Control

1. Collective/airspeed-adjust as required to control yaw W: #1 TR servo caution without #2 TR servo and backup pump -> loss of TR control below 40KIAS W: after touchdown rapid collective lowering-> excessive yaw rates W: uncontrolled R yaw at low AS -> loss wave off ability. May need to perform loss of TR drive alt not sufficient W: TR control cables damaged, hyd transients associated with switching to backup may damage TR controls W: servo hardover in yaw channel may result in loss of TR control N: momentary uncommaded R yaw when TR servo switches to backup in hover

External Engine Fire

1. Confirm Fire. 2. EMIF EP - Perform. 3. PCL (affected engine) - OFF. 4. Engine T-handle (affected engine) - Pull. 5. FIRE EXTGH switch - MAIN (RESERVE if required or ac power is off). If airborne and fire continues: 6. LAND IMMEDIATELY. If fire appears extinguished: 7. LAND AS SOON AS POSSIBLE. N: HF transmissions, sunlight filtered through smoke/haze/water/sunrise or sunset may trigger fire light false indication

LOW ROTOR RPM

1. Control Nr. *<96 on VID

Engine malfunction during hover/takeoff

1. Control Nr. 2. CONTGCY PWR switch - ON. If a suitable landing site exists or unable to transition to forward flight: 3. Set level attitude, eliminate drift, cushion landing. If able to transition to forward flight: 4. EMIF EP - Perform.

Engine malfunction in flight

1. Control Nr. W: flying with >110% Q with OEI may result in unrecoverable decay in Nr in event of dual eng failure 2. CONTGCY PWR switch - ON. 3. Single-engine conditions - Establish. 4. ENG ANTI-ICE switches - As required. W: with AI on up to 18% Q available lost. Up to 49% lost with improperly op inlet AI valve 5. External cargo/stores/fuel - Jettison/dump, as required. 6. Identify malfunction.

Single-Engine Failure in Flight

1. EMIF EP - Perform.

Engine High-Side Failure in Flight

1. EMIF EP- perform 2. PCL (malf eng)- retard to set A) Q 10% below good engine or B) matched Ng C) matched TGT N: Ng doesn't pass through edecu so is highly reliable. W signal may be erratic or drop off if edecu high side C: if Np overspeed exists (120%), system will flameout and auto-ignition system will relight. Will continue cycling until Np/Nr controlled. Yaw kick with each relight N: at high collective setting confirmation may be difficult, reducing collective will help ID All the following conditions exist: 1 Q 10% or greater than other eng 2 Ng 5% or greater than other eng 3 Np is matched within 5 4 Nr at or above 103%

Engine Low-Side Failure

1. EMIF EP- perform C: in LOCKOUT eng response is faster and TGT limiting inop. Np overspeed system will still be operative. Take care. It to exceed TGT, Np, Nr. All of the following exist: 1 Q 10% below good eng 2 Ng 5% or less than good eng 3 Np at or below 98 4 Nr at or below 97

Compressor Stall

1. EMIF-Perform 2. PCL (malfunctioning engine)-IDLE C: if Ng decay relight feature attempts to relight the engine, subsequent compressor stalls may occur and damage the engine. Yaw kick with each relight. The eng must be manually shutdown.

Engine anti ice/start bleed valve malfunction indications

1. ENG AI ON above 90% Ng (94% Ng OAT>=15) 2. No ENG AI ON below 88% Ng 3. No ENG AI ON when engine anti ice switch ON 4. No rise TGT when engine anti ice switch ON

#1/#2 FUEL FLTR BYPASS or #1/#2 FUEL PRESS Caution

1. Fuel selector lever (affected engine)- XFD (DIR if currently in XFD)

Unusual Attitude Recovery

1. Level wings. 2. Nose on horizon. 3. Center ball. 4. Stop rate of climb/descent. 5. Control airspeed. 30 pitch, 60 bank

#1/#2 input chip

1. Main transmission malfunction EP-perform N: consider returning PCL to FLY for landing

The following should be performed for all emergencies:

1. Maintain control of the aircraft 2. Alert crew 3. Determine the precise nature of the problem 4. Complete the applicable emergency procedure or take action appropriate for the problem 5. Determine landing criteria and land as required

Reasons to abort start

1. Ng not 14% in 6 seconds of started engagement 2. No oil px in 30 sec of starter engagement 3. No light off in 30 sec of PCL to idle 4. TGT likely to exceed 851C before idle speed attained 5. Starter dropout before 52% Ng

Stab Auto Mode Failure

1. PAC Call- "STAB STAB STAB" 2. Cyclic- Arrest pitch rate 3. Collective-Do not reduce 4. Man slew switch-Adjust to 0 ADD WARNINGS

Loss of tail rotor drive (altitude and airspeed sufficient to establish auto)

1. PAC call "AUTO AUTO AUTO" 2. Autorotation- establish. Center tail rotor pedals 3. Drive failure- attempt to verify 4. Immediate landing/ditching EP- perform 5. PCLs- OFF when directed (prior to the flare) W: altitude hold will remain engaged. AFCS commanded collective movement can result in accelerated yaw rate

Sonar cable angle malfunction

1. PAC call "CABLE CABLE CABLE" 2. Cable angle pb- off 3. Cable angle display- center 4. SO- fold array

Engine High-Side Failure on Deck

1. PCLs - IDLE.

Rocket hang fire OR misfire

1. Point weapon in a safe direction 2. Safe weapon A. +1760 off - select B. ACI MASTER ARM safe

#1 and #2 HYD PUMP Failure

1. Restrict flight control movement 2. Land as soon as possible

2 types LDS malfunction

1. Roll pin failure- max LDS input to HMU regardless of collective position...DECU ability to match engine torque may mask it 2. LDS cable malfunction- minimum input to HMU regardless of collective position...restricted max power available, LOCKOUT won't help

Electrical power failure/dual gen failure

1. Safe altitude and airspeed- establish 2. Stabilator- check position and slew as req 3. APU emergency start procedure- perform 4. CMPTR PWR/RESET, SAS1, SAS2, TRIM, AUTOPLT, STAB AUTO CONTROL- ON W: exceed AS/stab angles -> unrecoverable pitch angles W: stab position indicator inop without AC pwr. Check visually W: loss of power-> AI activation (18%/49% torque loss) N: can still slew stab with DV essential bus. 35 degrees if failed full down, 30 degrees if failed full up

AFCS DEGRADED

1. Safe altitude and airspeed-Establish (Waveoff/ITO as required) N: if appears during night/IMC auto approach or coupled hover, consider continuing if not disoriented or unstable

#1 Primary Servo or #1 Transfer Module Leak

1. Servo Switch-1st off 2. Land as soon as practicable If backup rsvr low caution also appears or the backup pump fails: 3. Land as soon as possible If the #2 PRI SERVO caution and/or HYD warning appears: 4. Land Immediately N: if backup also fails be prepared for loss of TR control W: failure to ensure back up pump on or auto prior to landing with #1 RES LOW and #1 HYD PUMP will result in loss of TR control when WOW switch activated

PAS malfunction cautions

BOOST SERVO OFF and AFCS DEGRADED and SAS

Loss of tail rotor control malfunction types

Cable failure Servo failure Restricted flight controls

Ground Resonance

Cg of rotor blades off center...abnormal lead lag Caused by -blade out of track -weird landing conditions -malfunctioning damper

Stab airspeeds

Degrees down/KIAS 0/150 10/100 20/80 30/60 40/45

Single engine conditions

Flight regime that permits sustained flight with OEI. establishing may include increasing power available (CPWR on, Anti-ice off) or decreasing power required (dump fuel/cargo)

Engine Torque or TGT Spiking/Fluctuations

If an engine instrument is spiking/fluctuating and inducing secondary indications in Ng, Np, and/or Nr: 1. EMIF EP - Perform. If fuel contamination is suspected: 2. LAND AS SOON AS POSSIBLE. W: PCL movement during engine fluctuations may precipitate an eng fail. Consider APU emergency start. A low power setting when moving PCL will minimize the Nr decay if eng fails

Main Transmission Malfunction

If failure is imminent: *1. LAND IMMEDIATELY W: yaw attitude excursions with no control input, increase in Preq for fixed collective setting, failure of main gen or hyd pump, increased noise, increased vibration, abnormal fumes If secondary indications are present: *2. LAND AS SOON AS POSSIBLE W: operation with no oil px may lead to loss of TR drive N: consider performing applicable steps of immediate ldg/ditching and fly 80/80 to permit quick flare and ldg N: loss of all main xmsn lubricating oil -> unreliable Xmsn temp N: continued op in precautionary range acceptable according to limit section

Ground resonance/Unusual Vibrations on Deck

If ground resonance is encountered and a safe takeoff is possible: 1. Takeoff immediately 2. Unusual vibrations in flight EP-perform If ground resonance is not encountered, or a safe takeoff is not possible: 3. Collective - Lower. 4. PCLs - OFF. 5. Rotor brake - Apply as required. W: ground resonance can occur rapidly (within 3 seconds) and produce violent lateral, vertical, and circular vibrations resulting in difficulty reaching PCLs, pilot induced oscillations, and possible dynamic rollover W: failure to ensure that ground personnel are clear of the rotor arc and aircraft is free from the deck and chains may result in loss of aircraft or ground personnel C: application of RB may aggravate lead/lag tendencies and cause mechanical failure

Hellfire hangfire

If rocket motor ignited and aircraft yaws 1. Adjust controls as required to maintain straight and level flight

Cockpit Fire/Cabin Fire

If source is known: *1. Affected power switches and cbs - OFF/pull *2. Portable Fire Extinguisher- as required If fire continues or source is unknown: *3. Cabin/doors/ vents/ ECS - CLOSE/OFF, as required *4. Unnecessary electrical equipment and cbs -OFF/pull If fire continues: *5. Land as soon as possible W: loss of power -> anti-ice activation (18/49) W: severity determines immediate landing/ditching W: Ventilate as soon as practicable after portable fire extinguisher W: secure all electrical power-> lose AFCS, ICS, and flight instruments. Try to get VMC first C: if source unknown consider securing mission power to prevent system damage N: diag page can help determine source

Tail/Intermediate Transmission Malfunction

Indications of imminent: strong med freq vibrations, hot metal fumes Indications: tail/intm Xmsn chip or oil hot If failure is imminent: 1. Land immediately If failure is not imminent: 2. Land as soon as possible W: high power settings require max performance of TR and may precipitate ultimate drive failure W: consider transiting at an altitude sufficient for auto and performing applicable steps of immediate landing/ditching EP

Engine High-Speed Shaft Failure

Indications: howl. Med-high freq vibrations. High speed shaft seal at input module damaged-Xmsn oil temp and px secondary indications 1. EMIF-Perform 2. PCL (Malfunctioning engine)-OFF C: following high speed shaft fail the eng will overspeed. Np overspeed system will flameout and auto ignition system will relight. Np gov will bring system to 100% Np but eng must be shutdown to prevent further damage. N: Np sensor unreliable <20%. Ignore #1/#2 DRVSHAFT FAIL if below 20%, no maintenance action required

Compressor Stall Indications

Rapid increase in TGT Hang up or rapid decrease in Ng Loss of power Change in engine noise level

Abort Start

To abort start: 1. PCL- OFF 2. Engine ignition switch- OFF If eng oil px is indicated: 3. Starter- engage C: failure to immediately stop FF may result in overtemp