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MH-60R RDAF > Progress EP's > Flashcards

Progress EP's Flashcards

1
Q

Loss of Tail Rotor Control

A

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.

  1. 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.
  2. External cargo/stores/fuel — Jettison/dump, as required.
  3. Land as soon as practicable.
  4. APU Emergency Start procedure — Perform prior to landing.
  5. PCLs — As required.
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2
Q

Land As Soon As Possible

A

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

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3
Q

Unusual vibration on deck

A

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

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4
Q

APU FIRE

A

*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

  1. Fuel pump switch - OFF
  2. APU CTRL switch - OFF
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5
Q

Single-Engine Failure in Flight

A

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

  1. Land as soon as practicable.

Consideration should be given to performing the following:

  1. Engine Shutdown in Flight emergency procedure.
  2. Engine Air Restart emergency procedure.
  3. Single-Engine Landing emergency procedure.
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6
Q

Tail/Intermediate Transmission Malfunction

A

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.

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7
Q

Land as soon as practicable

A

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

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8
Q

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

A

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

  1. Land as soon as practicable.
    If affected engine indications are abnormal:
  2. Engine Malfunction in Flight procedure perform.
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9
Q

Main Transmission Malfunction

A

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.

  1. APU Emergency Start procedure — Perform.
  2. No. 1 and No. 2 GENERATOR switches — OFF, as required.

If no secondary indications are present:

  1. 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.
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10
Q

Underwater Egress

A

*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.

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11
Q

Boost Servo Hardover

A

*1. PAC call — “BOOST, BOOST, BOOST”.

*2. SAS/BOOST pushbutton — Off.

  1. Minimize flight control movements.
  2. Land as soon as practicable.
  3. 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.
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12
Q

Abort Start

A

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
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13
Q

APU Emergency Start

A

*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.

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14
Q

1 Primary Servo or #1 Transfer Module Leak

A

*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.

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15
Q

Smoke and Fumes elimination

A

*1. Airspeed - adjust as required

*2. Doors/windows/vents - Open

*3. Aircraft - Yaw, as required.

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16
Q

Engine Torque or TGT Spiking/Fluctuations

A

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:

  1. 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:

  1. PCL (engine in LOCKOUT) — Retard to IDLE, then return to FLY.
  2. Repeat Steps 3. and 4. for other engine, as required.

If an engine instrument is spiking/fluctuating with

no secondary indications:

  1. Land as soon as practicable.
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17
Q

Compressor Stall

A

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

*2. PCL (malfunctioning engine) — IDLE.

If TGT decreases and stall clears:

  1. PCL — Slowly advance to FLY.

If stall remains cleared:

  1. 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:

  1. Engine Shutdown in Flight emergency procedure — Perform.
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18
Q

Engine Low-Side Failure

A

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

  1. 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.
  2. Land as soon as practicable.
19
Q

Electrical Power Failure/Dual Generator Failure

A

*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:

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

If dc electrical failure:

  1. 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:

  1. Land as soon as possible.
  2. Nonessential electrical equipment — Off.
20
Q

Immediate Landing/Ditching (Pilot)

A

*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
Q

Internal Engine Fire

A

*1. Starter - Engage. Motor Engine.

  1. Portable fire extinguisher - As required.
  2. Starter - Secure (once TGT decreases below 540 celcius)
22
Q 
#1 FUEL FLTR BYPASS and #2 FLTR BYPASS
or
#1 FUEL PRESS and #2 FUEL PRESS
A

*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
Q

Engine Malfunction During Hover/Takeoff

A

*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
Q

Land immediately

A

Execute a landing without delay

25
Q

Engine Air Restart

A

*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
Q

AFCS Degraded Caution

A

*1. Safe altitude and airspeed — Establish

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

  1. AFCS CONTROL panel — Check status (RAD ALT/BAR ALT hold).
  2. AKNL ADVSY pushbutton — Press.
  3. FAIL ADVISORY MODE RESET pushbutton — Press.

If #1/#2 EGI FAIL advisory appears:

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

If malfunction is not eliminated:

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

If malfunction is still not eliminated:

  1. Malfunctioning system — Off (if possible).
27
Q

External Engine Fire

A

*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

  1. Single-Engine landing emergency procedure - Perform.
  2. Fire extinguisher - Discharge into engine compartment.
28
Q

Engine High-Speed Shaft Failure

A

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.

  1. Land as soon as practicable.

Consideration should be given to performing

the following:

  1. Engine Shutdown in Flight emergency

procedure.

  1. Single-Engine Landing emergency

procedure.

29
Q

Low Rotor RPM Warning

A

*1. Control Nr.

  1. Determine cause of low Nr condition.
30
Q

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

A

*1. PAC call — “HOVER, HOVER, HOVER.”

*2. Collective — Lower.

*3. PNAC — Hands on PCLs.

*4. PCLs — OFF when directed (approximately 20 to 30 ft).

31
Q

Dual Engine Failure

A

*1. Autorotation - Establish

*2. Immediate Landing/Ditching emergency procedure - Perform

If time and altitude permit:
*3. Engine Air Restart emergency procedure - Perform.

32
Q

Hung Droop Stops.

A

1*. Reengage Rotor to greater than 75% Nr.

  1. Sligthy displace cyclic in an attempt to dislodge jammed droop stops.
    If, after several attempts, the droop stops do not engage:
  2. Cyclic - Neutral
  3. Show down engines
    If condition permits:
  4. Do not apply rotor brake.
33
Q

2 Primary Servo or #2 Transfer Module Leak

A

*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.

34
Q

Cockpit Fire/Cabin Fire

A

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%.

  1. Stabilator - Manually slew to zero
  2. No 1. and NO. 2. GENERATOR switches - OFF, as required.
  3. BATT switch - OFF, as required.
    If fire is extinguished:
  4. Smoke and Fumes elimination emergency procedure - Perform.
  5. Land as soon as practicable.
35
Q

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

A

*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).

36
Q

Stabilator Auto Mode Failure

A

*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:

  1. 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).
  2. STABILATOR AUTO CONTROL pushbutton switch — Press on once, as required.

If automatic control is not regained and manual mode is operable:

  1. 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:

  1. Fly at or below speed shown:

STAB ANGLE (TRAILING-EDGE DOWN) - KIAS LIMIT

0° - 150

10° - 100

20° - 80

30° - 60

40° - 45

  1. Land as soon as practicable.
37
Q

Engine High-Side Failure on Deck

A

*1. PCLs — IDLE.

38
Q

Unusual Attitude Recovery

A

*1. Level wings.

*2. Nose on horizon.

*3. Center ball.

*4. Stop rate of climb/descent.

*5. Control airspeed.

39
Q

Engine Malfunction In Flight

A

*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.

40
Q

Dual-EGI failure

A

*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.

41
Q

Tail Rotor Quadrant Caution

A

*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:

  1. Land as soon as practicable.
42
Q

1 and #2 HYD Pump Failure

A

*1. Restrict flight control movement.

*2. Land as soon as possible.

43
Q

Engine High-Side Failure in Flight

A

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

Note

  • Ng does not pass through the EDECU and is a highly reliable signal.
  • Torque signal may be erratic or drop off for high side conditions driven by EDECU failure.

*2. PCL (malfunctioning engine) — Retard to set:

a. Torque 10% below good engine, or

b. Matched Ng, or

c. Matched TGT.

  1. Land as soon as practicable.
44
Q

(#1/#2) INPUT CHIP Caution

A

*1. Main Transmission Malfunction emergency procedure — Perform.

If engine secondary indications are present:

  1. Engine Malfunction in Flight emergency procedure — Perform.
  2. PCL (engine with affected input module) — IDLE.

MH-60R RDAF (5 decks)

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