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MH-60R - EPs Flashcards

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0
Q

During emergencies, the PNAC shall…

A
  1. Assist in ensuring the continued safe flight of the aircraft.
  2. Perform the critical memory items that do not involve the flight controls.
  3. Use the pocket checklist to complete non-critical memory items.
  4. Troubleshoot as required.
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1
Q

During emergencies, the PAC shall…

A

Complete the critical memory items that do not require releasing the flight controls

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2
Q

During emergencies, the aircrewman shall…

A
  1. Provide the pilots with verbal calls as necessary to ensure the continued safe flight of the aircraft.
  2. Complete the applicable critical memory items.
  3. Utilize the pocket checklist to complete the remaining non-critical memory items.
  4. Back up the pilots with the pocket checklist to the maximum extent possible.
  5. Assist the PNAC with troubleshooting.
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3
Q

What should be performed for all emergencies?

A
  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.
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4
Q

Land Immediately

A

Execute a landing without delay. The primary consideration is to ensure the survival of the occupants.

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5
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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6
Q

Land as soon as practicable

A

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

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7
Q

Engine Malfunction in Flight

A
  1. Control Nr.

WARNING:
Flying with a torque greater than 110% with one engine inoperative may result in unrecoverable decay of Nr in the event of a dual-engine failure.

  1. CONTGCY PWR switch - On
  2. Single-engine conditions - Establish
  3. ENG ANTI-ICE switches - As required

WARNING:
With 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.

  1. External cargo/stores/fuel - Jettison/dump, as required
  2. Identify malfunction
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8
Q

Engine High-Side Failure in flight

A
  1. Engine Malfunction in Flight emergency procedure - Perform
  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
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9
Q

Engine High-Side Failure on Deck

A
  1. PCLs - IDLE
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10
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.

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11
Q

Compressor Stall

A

CAUTION:
If the Ng decay relight feature attempts to relight the engine, subsequent compressor stalls may occur and damage the engine. A yaw kick may be experienced each time the engine relights. The engine must be manually shut down.

  1. Engine malfunction in flight emergency procedure - Perform
  2. PCL (malfunctioning engine) - IDLE
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12
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
  3. Land as soon as practicable
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13
Q

Abort Start indications

A

Abort engine start if any of the following limits are exceeded:

  1. Ng does not reach 14% within 6 seconds after starter initiation.
  2. No oil pressure within 30 seconds after starter initiation (do not motor engine)
  3. No light-off within 30 seconds after moving PCL to IDLE.
  4. ENG STARTER advisory disappears before reaching 52% Ng.
  5. TGT reaches 851C before idle is attained.

CAUTION:
For aborted starts, fuel flow must be stopped immediately (PCL - OFF) to prevent engine overtemperature.

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14
Q

Abort Start

A

To abort start:

  1. PCL - OFF
  2. ENGINE IGNITION switch - OFF

If engine oil pressure is indicated:

  1. Starter - ENGAGE
  2. Starter - DISENGAGE after 30 seconds and TGT below 540C
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15
Q

Engine Malfunction during Hover/Takeoff

A
  1. Control - Nr
  2. CONTGCY PWR switch - ON

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

  1. Set level attitude, eliminate drift, cushion landing.

If able to transition to forward flight:

  1. Engine malfunction in flight emergency procedure - perform
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16
Q

Dual Engine Failure

A
  1. Autorotation - Establish
  2. Immediate Landing/Ditching emergency procedure - Perform.

If time and altitude permit:

  1. Engine Air Restart emergency procedure - Perform
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17
Q

Single-Engine Failure in Flight

A
  1. Engine Malfunction in Flight emergency procedure - Perform.
  2. Land as soon as practicable.
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18
Q

Engine Air Restart

A

CAUTION: For a crossbreed start, use the maximum Ng safely obtainable on the donor engine. Ng less than 94% may result in hot starts.

NOTE:
Either single- or dual-engine restart may be attempted following dual-engine failure. Decision should be based on applicability of respective start envelopes and considerations of longer time to idle when executing a dual-engine start.

  1. APU Emergency Start procedure - As required
  2. ENGINE IGNITION switch - NORM
  3. Fuel selector lever(s) - DIR or XFD.
  4. PCL(s) - OFF
  5. Starter(s) - Engage, motor engine
  6. PCL(s) - IDLE (TGT 80C or less, if time permits)
  7. PCL(s) - Advance to FLY after starter dropout.

WARNING:
If APU is unavailable, and a crossbreed 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 crossbreed starts.

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19
Q

APU Emergency Start

A
  1. ECS - OFF
  2. AIR SOURCE ECS/START switch - APU
  3. FUEL PUMP switch - APU BOOST
  4. APU CONTR switch - ON
  5. APU GENERATOR switch - ON
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20
Q

Unusual Vibrations on Deck

A

CAUTION:

Application of the rotor break may aggravate lead/lag tendencies and cause a mechanical failure.

  1. Collective - Lower
  2. PCLs - OFF
  3. Rotor break - Apply as required
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21
Q

Hung Droop Stop(s)

A

NOTE:
While operating in cold weather, consideration should be given to turning the BLADE DE-ICE control panel POWER switch to the POWER ON position. This will activate the droop-stop heaters and aid the droop-stops in seating.

  1. Reengage rotor to greater than 75% Nr
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22
Q

Low Rotor Rpm

A

Warning light is activated by the vertical instrument when Nr is less than 96%.

  1. Control Nr.
  2. Determine cause of low Nr condition.
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23
Q

Main transmission malfunction

A

If failure is imminent:

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.

  1. Land immediately

If secondary indications are present:

  1. Land as soon as possible
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24
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.
25
INPUT CHIP (#1/#2) Caution Lights On
1. Main Transmission Malfunction emergency procedure - Perform
26
Loss of Tail Rotor Drive Altitude and Airspeed Sufficient to Establish Autorotation
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)
27
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)
28
Loss of Tail Rotor Control procedure
1. Collective/airspeed - Adjust as required to control yaw
29
Hydraulic System warning indications
HYD warning light - the HYD warning will occur as a result of several compounded hydraulic malfunctions. The order in which the hydraulic emergency will present itself should allow the pilot early indications of the impending failure.
30
Hydraulic system warning procedure
1. Land immediately
31
#1 and #2 HYD PUMP failure indications
#1 HYD PUMP and #2 HYD PUMP and #1 + #2 HYD PUMP FAIL cautions and BACK UP PUMP ON advisory. Low pressure at the outlet of hydraulic pumps.
32
#1 and #2 HYD PUMP failure procedure
1. Restrict flight control movement | 2. Land as soon as possible
33
#1 Primary servo or #1 Transfer module leak indications
#1 RSVR LOW and #1 HYD PUMP cautions and BACK UP PUMP ON advisory After the #1 RSVR LOW caution light and the #1 HYD PUMP caution light illuminate, the pilot positions the SERVO switch to 1ST OFF. The SERVO switch is positioned to 1ST OFF to prevent any further fluid leakage in the event the leak is in the No. 1 primary servos. The LDI system should continue to operate normally, powering the No. 1 Hydraulic system with the backup pump.
34
#1 Primary servo or #1 Transfer module leak procedure
1. SERVO switch - 1ST OFF. 2. Land as soon as practicable. If the 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.
35
#1 Primary servo or #1 Transfer module leak indications
#2 RSVR LOW and #2 HYD PUMP cautions and BACK UP PUMP ON advisory After the #2 RSVR LOW caution light and the #2 HYD PUMP caution light illuminate, the pilot positions the SERVO switch to 2ND OFF. The SERVO switch is positioned to 2ND OFF to prevent any further fluid leakage in the event the leak is in the No. 2 primary servos. The LDI system should continue to operate normally, powering the No. 2 Hydraulic system with the backup pump.
36
#2 Primary servo or #2 Transfer module leak procedure
1. SERVO switch - 2ND OFF. 2. Land as soon as practicable. If the BACKUP RSVR LOW caution also appears or the backup pump fails: 3. Land as soon as possible. IF THE #1 PRI SERVO caution and/or HYD warning appears: 4. Land immediately.
37
Boost Servo Hardover indications
A failure of the collective or yaw boost servo may result in high cockpit control forces. The control loads resulting from a hardover condition can be immediately eliminated by shutting off the boost servos. Resulting cockpit control loads will then be the same as for in-flight boost servos off. The control free play noted will be about 1/2 inch.
38
Boost servo hardover procedure
1. SAS/BOOST pushbutton - OFF
39
Utility Pump caution lights indications
UTILITY HYD PUMP caution - Utility hydraulic system pressure is low UTILITY HYD PUMP HOT caution - Utility hydraulic system temperature is high UTILITY HYD RSVR LOW caution - Utility hydraulic system reservoir is low
40
Utility Pump caution lights procedure
1. Stop dome.
41
AFCS DEGRADED caution light on indications
Failure of one or more modes of the AFCC. Pilot action is dependent on associated fail advisory lights and system performance. The AFCS Coupler-related failures table describes coupler malfunctions.
42
AFCS DEGRADED caution light on procedure
1. Safe altitude and airspeed - Establish (wave off/ instrument takeoff, as required)
43
Stabilator Auto Mode Failure indications
STABILATOR caution light - Stabilator reverted to manual mode
44
Stabilator Auto Mode failure procedure
1. PAC call - "STAB, STAB, STAB" 2. Cyclic - Arrest pitch rate 3. Collective - Do not reduce. 4. MAN SLEW switch - Adjust to 0 degrees
45
Unusual Attitude Recovery procedure
1. Level wings. 2. Nose on horizon. 3. Center ball. 4. Stop rate of climb/descent. 5. Control airspeed.
46
Unusual Attitude Recovery indications.
Unusual attitudes are considered to be attitudes of over 30 degrees pitch and/or 60 degrees bank. There are three general unusual attitudes: Nose-low, nose-high, and high-bank angles. During all unusual attitude recoveries, the nose-low attitude is the desired condition from which to complete all recoveries.
47
Total AC Power failure/Dual Generator failure procedure
1. Safe altitude and airspeed - Establish 2. Stabilator - Check position, slew as required. 3. APU Emergency Start Procedure - Perform. 4. CMPTR PWR, SAS 1, SAS 2, TRIM, AUTO PILOT, and STABILATOR AUTO CONTROL - ON
48
#1 or #2 FUEL FLTR BYPASS or #1 or #2 FUEL PRESS caution lights indications
#1 or #2 FUEL FLTR BYPASS caution lights - Fuel Filter is bypassing #1 or #2 FUEL PRESS caution lights - Low fuel pressure from the respective engine-driven boost pump
49
#1 or #2 FUEL FLTR BYPASS or #1 or #2 FUEL PRESS caution lights procedure
1. Fuel selector lever (affected engine) - XFD (DIR if currently in XFD)
50
#1 and #2 FUEL FLTR BYPASS or #1 and #2 FUEL PRESS caution lights indications
1. Land as soon as possible | 2. APU Emergency Start Procedure - Perform
51
Refueling Hose Jettison (HIFR) procedure
1. T-Handle pull (if applicable) 2. Hose status - Report If hose fails to break away: 3. Quickly disengage the nozzle and grounding wire, then cut the hoist cable.
52
External Engine fire indication
FIRE (#1/#2 ENG) warning light - Indicates that a fire detector has actuated a fire warning circuit. The safety of the helicopter's occupants is the primary consideration when a fire occurs. If airborne, the most important single action that can be taken by the pilot is to land the helicopter safely.
53
External Engine fire procedure
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 of required or AC power is off) If airborne and fire continues: 6. Land immediately. If fire appears extinguished: 7. Land as soon as possible.
54
Internal Engine fire indications
An internal engine fire is indicated by a rise in TGT above 540 degrees after engine shutdown.
55
Internal Engine fire procedure
1. Starter - Engage. Motor engine.
56
APU fire indications
FIRE (APU) warning light - Indicates that a fire detector has actuated a fire warning circuit. The safety of the helicopter's occupants is the primary consideration when a fire occurs. If airborne, the most important single action that can be taken by the pilot is to land the helicopter safely as soon as possible.
57
APU Fire procedure
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.
58
Cockpit fire/Cabin fire procedure
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.
59
Smoke and Fumes Elimination
1. Airspeed - Adjust, as required. 2. Doors/windows/vents - Open. 3. Aircraft - Yaw, as required.
60
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. In the flare: 6. Windows - Jettison, as required. After landing: 7. PCLs - OFF. 8. Rotor Brake - ON. 9. Copilot collective - Stow. 10. Pilot HCU - Stow. After all violent motion stops: 11. Egress.
61
Underwater Egress procedure
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.
62
Definition of "single engine condition"
A flight regime that permits sustained flight with One Engine Inoperative (OEI).
63
What are the dual concurrence items?
1. PCLs. 2. Engine T-handles. 3. Fuel selectors. 4. Generators. 5. CMPTR PWR switches. 6. EGI PWR switches.

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