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1

Loss of Tail Rotor Control

WARNING



• Following the appearance of the #1 TAIL RTR SERVO caution without the associated BACK UP PUMP ON and #2 TAIL RTR SERVO ON advisories, the aircraft will demonstrate normal yaw responses in flight regimes that do not require excessive tail rotor performance; however, at slower airspeeds, below approximately 40 KIAS, more pronounced effects of loss of tail rotor control may become more apparent.



• After touchdown, rapid reduction of collective or PCLs may cause excessive and uncontrollable yaw rates.



• If an uncontrolled right yaw develops at too low of an airspeed, loss of waveoff capability may result. Increasing collective may increase the yaw to unrecoverable rates. Performing Loss Of Tail Rotor Drive (Altitude And Airspeed Not Sufficient To Establish Autorotation) procedure may be required.



*1. Collective/airspeed — Adjust as required to control yaw.



WARNING



If the tail rotor control cables are damaged, the hydraulic transients associated with switching the TAIL SERVO switch from NORM to BKUP may cause catastrophic damage to the tail rotor controls.



2. If hydraulic malfunction is evident:



a. TAIL SERVO switch — BKUP.



b. BACKUP HYD PMP switch — Check ON.



c. Backup Hydraulic Pump Fails to Operate emergency procedure — Perform, as required.



3. External cargo/stores/fuel — Jettison/dump, as required.



4. Land as soon as practicable.



5. APU Emergency Start procedure — Perform prior to landing.



6. PCLs — As required.

2

Land As Soon As Possible

Execute a landing at the first site at which a safe landing can be made

3

Unusual vibration on deck

*1. Collective - Lower.

*2. PCL - OFF. 

*3. Rotor brake - Apply as required. 

4

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



7. Fuel pump switch - OFF



8. APU CTRL switch - OFF 

5

Single-Engine Failure in Flight

*1. Engine Malfunction in Flight emergency procedure — Perform.



2. Land as soon as practicable.



Consideration should be given to performing the following:



3. Engine Shutdown in Flight emergency procedure.



4. Engine Air Restart emergency procedure.



5. Single-Engine Landing emergency procedure.

6

Tail/Intermediate Transmission Malfunction

If failure is imminent:



*1. Land immediately.



If failure is not imminent:



*2. Land as soon as possible.



WARNING



• High power settings require maximum performance of the tail rotor drive system and may precipitate ultimate drive failure.



• Consideration should be given to transiting at an altitude sufficient to enter an autorotation and performing the applicable steps of the Immediate Landing/Ditching emergency procedure.



Note



An INT XMSN OIL HOT or TAIL XMSN OIL HOT caution occurring simultaneously with a WCA MISCOMPARE alert may be an indication of a mission computer/backup computer card failure.

7

Land as soon as practicable

Extended flight is not recommended. The landing site and duration of flight is at the discretion of the PIC.

8

(#1/#2) Fuel Filter Bypass or (#1/#2) Fuel Press

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



2. Land as soon as practicable. 

If affected engine indications are abnormal: 

3. Engine Malfunction in Flight procedure perform. 

9

Main Transmission Malfunction

WARNING



Possible indications of main transmission imminent failure may include: yaw attitude excursions with no control input, an increase in power required for a fixed collective setting, failure of a main generator or hydraulic pump, increased noise, increased vibration levels, or abnormal fumes in the cabin.



If failure is imminent:



*1. Land immediately.



If secondary indications are present:



*2. Land as soon as possible.



3. APU Emergency Start procedure — Perform.



4. No. 1 and No. 2 GENERATOR switches — OFF, as required.



If no secondary indications are present:



5. Land as soon as practicable.



WARNING



Operation of the main gearbox with no oil pressure may result in failure of the tail rotor drive takeoff pinion gear and subsequent loss of tail rotor drive.



Note



• Consideration should be given to performing the applicable steps of the Immediate Landing/Ditching emergency procedure and transiting at a minimum power airspeed and low altitude flight profile (approximately 80 feet and 80 KIAS) to permit a quick flare followed by an immediate landing/ditching.



• A loss of all main transmission lubricating oil may result in unreliable temperature indications from the main transmission temperature gauge and temperature sensor (caution).



• Continued operations in the precautionary range for temperature and pressure are acceptable provided that the ambient conditions and flight regime of the aircraft correspond with the guidance set forth in the transmission limitations section of Chapter 4.

10

Underwater Egress

*1. Emergency breating decive - As required

*2. Cords - 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.

11

Boost Servo Hardover

*1. PAC call — “BOOST, BOOST, BOOST”.



*2. SAS/BOOST pushbutton — Off.



3. Minimize flight control movements.



4. Land as soon as practicable.



5. Make a shallow approach to a hover, maximum 15 knots crosswind. Taxi no more than necessary.



Caution



• Up to 75 pounds of left pedal force will be required when hovering with boost servos off with starboard crosswinds. This value is significantly reduced with port crosswinds.



• Landings with boost servos off on all single spot air-capable ships should only be attempted if there is no large landing platform (LPD or larger) or shore base available.

12

Abort Start

To abort start: 



*1. PCL - OFF



*2. ENGINE IGNITION switch - OFF

If engine oil pressure is indicated: 



*3. Starter - Engage

4. Starter - Disengage after 30 seconds and TGT below 540 Celcius 

13

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 - ON. 



 

14

#1 Primary Servo or #1 Transfer Module Leak

*1. SERVO switch — 1ST OFF.



*2. Land as soon as practicable.



If the BACK UP RSVR LOW caution also appears or the backup pump fails:



*3. Land as soon as possible.



Note



Be prepared for loss of tail rotor control.



If the #2 PRI SERVO PRESS caution and/or HYD warning appears:



*4. Land immediately.



WARNING



Failure to ensure BACKUP HYD PMP switch is in AUTO or ON position prior to landing with a #1 RSVR LOW or #1 HYD PUMP caution present will result in loss of tail rotor directional control when the weight on wheels switch is activated.

15

Smoke and Fumes elimination

*1. Airspeed - adjust as required



*2. Doors/windows/vents - Open



*3. Aircraft - Yaw, as required. 

16

Engine Torque or TGT Spiking/Fluctuations

If an engine instrument is spiking/fluctuating and inducing secondary indications in Ng, Np, and/or Nr:



*1. Engine Malfunction in Flight emergency procedure — Perform.



If fuel contamination is suspected:



*2. Land as soon as possible.



WARNING:



PCL movement during engine fluctuations may precipitate an engine failure. Consider performing APU Emergency Start procedure prior to manipulating the PCL. Maintaining a low power setting when moving the PCL will minimize the Nr decay rate if the malfunctioning engine fails.



If engine electronic circuitry is suspected:



3. PCL (malfunctioning engine) — Momentarily advance to LOCKOUT, then retard to set:



a. Torque 10% below good engine, or



b. Matched Ng, or



c. Matched TGT.



If fluctuations persist:



4. PCL (engine in LOCKOUT) — Retard to IDLE, then return to FLY.



5. Repeat Steps 3. and 4. for other engine, as required.



If an engine instrument is spiking/fluctuating with



no secondary indications:



6. Land as soon as practicable.

17

Compressor Stall

*1. Engine Malfunction in Flight emergency procedure — Perform.



*2. PCL (malfunctioning engine) — IDLE.



If TGT decreases and stall clears:



3. PCL — Slowly advance to FLY.



If stall remains cleared:



4. Land as soon as practicable. Avoid rapid collective movement.



If TGT continues to rise, Ng decreases below normal idle speed, or any other malfunction is indicated:



5. Engine Shutdown in Flight emergency procedure — Perform.

18

Engine Low-Side Failure

*1. Engine Malfunction in Flight emergency procedure — Perform.



2. PCL (malfunctioning engine) — Momentarily advance to LOCKOUT, then retard to set:



a. Torque 10% below good engine, or



b. Matched Ng, or



c. Matched TGT.



3. Land as soon as practicable.

19

Electrical Power Failure/Dual Generator Failure

*1. Safe altitude and airspeed — Establish.



*2. Stabilator — Check position, slew as required.



WARNING



Exceeding airspeed versus stabilator angle limits may result in unrecoverable pitch angles.



Note



The stabilator position indicator will be inoperative with no power to the ac essential bus. Attempt to check visually.



*3. APU Emergency Start procedure — Perform.



*4. CMPTR PWR/RESET, SAS 1, SAS 2, TRIM, AUTO PLT, STABILATOR AUTO CONTROL pushbuttons — On.



If ac electrical failure:



5. NO. 1 and NO. 2 GENERATOR switches — RESET, then ON.



If dc electrical failure:



6. Converter circuit breakers — Cycle.



a. NO. 1 CONVERTER POWER (CENTER, NO. 1 AC PRIMARY BUS, RW 1, cb 14).



b. NO. 2 CONVERTER POWER (CORNER, NO. 2 AC PRIMARY BUS, RW 2, cb 4).



If ac and/or dc electrical power is not restored:



7. Land as soon as possible.



8. Nonessential electrical equipment — Off.

20

Immediate Landing/Ditching (Pilot)

*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 procedure to maintain electrical and hydraulic power upon rotor disengagement.



In the flare:



*6. Windows — Jettison, as required.



WARNING



After actuation, the position of the window emergency jettison lever may cause snagging of personal survival gear, impeding egress. Time permitting, reset jettison handle to the aft position prior to egress.



After landing:



*7. PCLs — OFF.



*8. Rotor brake — On.



*9. Copilot collective — Stow.



*10. Pilot HCU — Stow.



After all violent motion stops:



*11. Egress.



WARNING



Failure to remain strapped in aircraft until all violent motion or in-rushing water stops may result in injury or incapacitation.

21

Internal Engine Fire

*1. Starter - Engage. Motor Engine. 



2. Portable fire extinguisher - As required. 



3. Starter - Secure (once TGT decreases below 540 celcius) 

22

#1 FUEL FLTR BYPASS and #2 FLTR BYPASS

or

#1 FUEL PRESS and #2 FUEL PRESS

*1. Land as soon as possible



*2. APU Emergency Start Procedure - Perform



WARNING

Be prepared for dual-engine failure. Recommended airspeed is 80 KIAS to minimize Nr droop should dual-engine failure occur. 

NOTE

Consideration should be given to performing applicable steps of the immediate Landing/Ditching emergency procedure. 

23

Engine Malfunction During Hover/Takeoff

*1. Control Nr

*2. CONTGCYPWR switch - ON


If a suitable landing site exist or unable to transition to forward flight: 



*3. Set level attitude, eliminate drift, cushion landing



If able to transition to forward flight: 

*4. Engine malfunction in Flight emergency procedure - Perform. 

24

Land immediately

Execute a landing without delay

25

Engine Air Restart

*1. APU Emergency Start procedure — As required.



*2. ENGINE IGNITION switch — NORM.



*3. Fuel selector lever — DIR or XFD.



*4. PCL — OFF.



*5. Starter — Engage, motor engine.



*6. PCL — IDLE (TGT 80 °C or less, if time permits).



*7. PCL — Advance to FLY after starter dropout.



WARNING:



If APU is unavailable, and a crossbleed start is necessary, maximum torque available will be reduced during the start sequence. Depending on operating conditions, level flight may not be possible. Ensure AIR SOURCE ECS/START switch is placed to ENG for crossbleed starts.

26

AFCS Degraded Caution

*1. Safe altitude and airspeed — Establish



(waveoff/Instrument Takeoff [ITO], as required).



2. AFCS CONTROL panel — Check status (RAD ALT/BAR ALT hold).



3. AKNL ADVSY pushbutton — Press.



4. FAIL ADVISORY MODE RESET pushbutton — Press.



If #1/#2 EGI FAIL advisory appears:



5. Single/Dual EGI Failure emergency procedure — Perform, as required.



If malfunction is not eliminated:



6. CMPTR PWR/RESET pushbutton — Cycle, as required.



If malfunction is still not eliminated:



7. Malfunctioning system — Off (if possible).

27

External Engine Fire

*1. Confirm fire. 



*2. Engine Malfunction in Flight emergency procedure - 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



8. Single-Engine landing emergency procedure - Perform. 



9. Fire extinguisher - Discharge into engine compartment. 



 

28

Engine High-Speed Shaft Failure

CAUTION:



Following a high-speed shaft failure, the engine will overspeed, the Np overspeed system will flame out the engine, and the auto-ignition system will activate the relight feature. The engine Np governor will eventually bring Np down toward 100%. The engine must be manually shut down to prevent further damage.



*1. Engine Malfunction in Flight emergency procedure — Perform.



*2. PCL (malfunctioning engine) — OFF.



3. Land as soon as practicable.



Consideration should be given to performing



the following:



4. Engine Shutdown in Flight emergency



procedure.



5. Single-Engine Landing emergency



procedure.

29

Low Rotor RPM Warning

*1. Control Nr.



2. Determine cause of low Nr condition.

30

Loss of Tail Rotor Drive (Altitude/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).