Progress EP's

Question 1

Loss of Tail Rotor Control

Answer 1

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.

Question 2

Land As Soon As Possible

Answer 2

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

Question 3

Unusual vibration on deck

Answer 3

*1. Collective - Lower.
*2. PCL - OFF.
*3. Rotor brake - Apply as required.

Question 4

APU FIRE

Answer 4

*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

Question 5

Single-Engine Failure in Flight

Answer 5

*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.

Question 6

Tail/Intermediate Transmission Malfunction

Answer 6

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.

Question 7

Land as soon as practicable

Answer 7

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

Question 8

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

Answer 8

*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.

Question 9

Main Transmission Malfunction

Answer 9

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.

Question 10

Underwater Egress

Answer 10

*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.

Question 11

Boost Servo Hardover

Answer 11

*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.

Question 12

Abort Start

Answer 12

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

Question 13

APU Emergency Start

Answer 13

*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.

Question 14

1 Primary Servo or #1 Transfer Module Leak

Answer 14

*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.

Question 15

Smoke and Fumes elimination

Answer 15

*1. Airspeed - adjust as required

*2. Doors/windows/vents - Open

*3. Aircraft - Yaw, as required.

Question 16

Engine Torque or TGT Spiking/Fluctuations

Answer 16

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.

Question 17

Compressor Stall

Answer 17

*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.

Question 18

Engine Low-Side Failure

Answer 18

*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.

Question 19

Electrical Power Failure/Dual Generator Failure

Answer 19

*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.

Question 20

Immediate Landing/Ditching (Pilot)

Answer 20

*1. Crew and passengers — Alert.

*2. Harness — Locked.

*3. APU Emergency Start Procedure — Perform, as required.

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

*5. Searchlight — As required.

*6. Mayday/IFF — TRANSMIT/EMER.

In the flare:

*7. Windows — Jettison, handle reset, as required.

WARNING

After actuation, the position of the window emergency jettison handle may cause snagging of personal survival gear, impeding 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

Unstrapping and attempting to egress before all violent motion or in-rushing water stops may result in injury or incapacitation.

Question 21

Internal Engine Fire

Answer 21

*1. Starter - Engage. Motor Engine.

2. Portable fire extinguisher - As required.
3. Starter - Secure (once TGT decreases below 540 celcius)

Question 22

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

Answer 22

*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.

Question 23

Engine Malfunction During Hover/Takeoff

Answer 23

*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.

Question 24

Land immediately

Answer 24

Execute a landing without delay

Question 25

Engine Air Restart

Answer 25

**\*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.

Question 26

AFCS Degraded Caution

Answer 26

**\*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).

Question 27

External Engine Fire

Answer 27

**\*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.

Question 28

Engine High-Speed Shaft Failure

Answer 28

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.

Question 29

Low Rotor RPM Warning

Answer 29

**\*1. Control Nr.** 2. Determine cause of low Nr condition.

Question 30

Loss of Tail Rotor Drive (Altitude/Airspeed Not Sufficient to Establish Autorotation)

Answer 30

## Footnote **\*1. PAC call — “HOVER, HOVER, HOVER.”** **\*2. Collective — Lower.** **\*3. PNAC — Hands on PCLs.** **\*4. PCLs — OFF when directed (approximately 20 to 30 ft).**

Question 31

Dual Engine Failure

Answer 31

**\*1. Autorotation - Establish** **\*2. Immediate Landing/Ditching emergency procedure - Perform** If time and altitude permit: **\*3. Engine Air Restart emergency procedure - Perform.**

Question 32

Hung Droop Stops.

Answer 32

**1\*. Reengage Rotor to greater than 75% Nr.** 2. Sligthy displace cyclic in an attempt to dislodge jammed droop stops. If, after several attempts, the droop stops do not engage: 3. Cyclic - Neutral 4. Show down engines If condition permits: 5. Do not apply rotor brake.

Question 33

#2 Primary Servo or #2 Transfer Module Leak

Answer 33

**\*1. SERVO switch — 2ND OFF.** **\*2. Land as soon as practicable.** Note Failure to ensure BACKUP PUMP switchis in AUTO or ON position prior to landing with a #2 HYD PUMP caution present will result in loss of pilot assist servos when the weight on wheels switch is activated. If the BACK UP RSVR LOW caution also appears or backup pump fails: **\*3. Land as soon as possible.** Note Be prepared for loss of the pilot-assist servos. If the #1 PRI SERVO PRESS caution and/or HYD warning appears: **\*4. Land immediately.**

Question 34

Cockpit Fire/Cabin Fire

Answer 34

If source is known: **\*1. Affected power switches and circuit breakers - 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 circuit breakers - OFF/Pull** If fire continues: **\*5. Land as soon as possible** WARNING: Loss of electrical power to the engine will result in engine anti-ice activation regardless of ENG ANTI-ICE or DE-ICE MASTER switch position, reducing maximum torque available by up to 18%. With a malfunctioning inlet anti-ice valve, torque available can be reduced by as much as 49%. 6. Stabilator - Manually slew to zero 7. No 1. and NO. 2. GENERATOR switches - OFF, as required. 8. BATT switch - OFF, as required. If fire is extinguished: 9. Smoke and Fumes elimination emergency procedure - Perform. 10. Land as soon as practicable.

Question 35

Loss of Tail Rotor Drive (Altitude/Airspeed Sufficient to Establish Autorotation)

Answer 35

## Footnote **\*1. PAC call — “AUTO, AUTO, AUTO.”** **\*2. Autorotation — Establish. Center tail rotor pedals.** **\*3. Drive failure — Attempt to verify.** **\*4. Immediate Landing/Ditching emergency procedure — Perform.** **\*5. PCLs — OFF when directed (prior to the flare).**

Question 36

Stabilator Auto Mode Failure

Answer 36

**\*1. PAC call — “STAB, STAB, STAB”.** **\*2. Cyclic — Arrest pitch rate.** **\*3. Collective — Do not reduce.** **\*4. STABILATOR MAN SLEW switch — Adjust to 0°.** When at a safe altitude and airspeed: 5. Stabilator circuit breakers — Reset. a. STAB PWR (COPILOT, NO. 1 DC PRIMARY BUS, RW 3, cb 7). b. STAB SYS PWR (COPILOT OVHD, DC ESNTL BUS, RW 2, cb 4). c. STAB CTRL (CENTER, NO. 1 AC PRIMARY BUS, RW 1, cb 10). d. STAB IND (CENTER, AC ESSENTIAL BUS, RW 1, cb 6). e. STAB CTRL (CENTER, AC ESSENTIAL BUS, RW 3, cb 7). 6. STABILATOR AUTO CONTROL pushbutton switch — Press on once, as required. If automatic control is not regained and manual mode is operable: 7. STABILATOR MAN SLEW switch — Adjust as required. Do not exceed stabilator versus airspeed limits shown below. Note In Manual mode, the following are not recommended: — Swimmer deployments lower than 15 feet AGL. — Night takeoffs, approaches, and landings (except one-time landing following failure). — Automatic approaches to a hover. — Simulated emergency procedures, including practice autorotations. — Flight in known IMC. If automatic control is not regained and manual mode is not operable: 8. Fly at or below speed shown: STAB ANGLE (TRAILING-EDGE DOWN) - KIAS LIMIT 0° - 150 10° - 100 20° - 80 30° - 60 40° - 45 9. Land as soon as practicable.

Question 37

Engine High-Side Failure on Deck

Answer 37

## Footnote **\*1. PCLs — IDLE.**

Question 38

Unusual Attitude Recovery

Answer 38

## Footnote **\*1. Level wings.** **\*2. Nose on horizon.** **\*3. Center ball.** **\*4. Stop rate of climb/descent.** **\*5. Control airspeed.**

Question 39

Engine Malfunction In Flight

Answer 39

**\*1. Control Nr** WARNING: Flying with greater than 110% torque with one engine inoperative may result in unrecoveable decay of Nr in the event of dual engine failure. **\*2. CONTGCY PWR switch - ON** **\*3. Single-engine conditions - Establish.** **4\*. ENG ANTI-ICE switches - As required.** WARNING With engine anti-ice on, up to 18% torque available is lost. Torque may be reduced as much as 49% with improperly operating engine inlet anti-ice valves. **\*5. External cargo/stores/fuel - Jettison/dump, as required.** **\*6. Indentify malfunction**.

Question 40

Dual-EGI failure

Answer 40

**\*1. Backup instruments - Scan, as required.** **\*2. #1 and #2 EGI PWR switches - OFF, then ON.** 3. If IMC, transition to VMC. 4. Mission display - Ensure dual in-flight alignment has commenced. If IMC and neither EGI will align 5. Land as soon as possible If VMC and neither EGI will allign 6. Land as soon as practicable.

Question 41

Tail Rotor Quadrant Caution

Answer 41

**\*1. Check for tail rotor control.** If tail rotor control is not available: **\*2. Loss of Tail Rotor Control Emergency procedure — Perform.** If tail rotor control is available: 3. Land as soon as practicable.

Question 42

#1 and #2 HYD Pump Failure

Answer 42

## Footnote **\*1. Restrict flight control movement.** **\*2. Land as soon as possible.**

Question 43

Engine High-Side Failure in Flight

Answer 43

**\*1. Engine Malfunction in Flight emergency procedure — Perform.** Note * Ng does not pass through the CEDECU and is a highly reliable signal. * Torque signal may be erratic or drop off for high side conditions driven by CEDECU failure. **\*2. PCL (malfunctioning engine) — Retard to set:** **a. Torque 10% below good engine, or** **b. Matched Ng, or** **c. Matched TGT.** 3. Land as soon as practicable.

Question 44

(#1/#2) INPUT CHIP Caution

Answer 44

**\*1. Main Transmission Malfunction emergency procedure — Perform.** If engine secondary indications are present: 2. Engine Malfunction in Flight emergency procedure — Perform. 3. PCL (engine with affected input module) — IDLE.