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Emergency Procedures Flashcards

1
Q

Define “Single-Engine Airspeed”

A

Maneuvering the aircraft to an appropriate airspeed that will allow for continued flight under partial power conditions to a suitable recover area.

(Adjust cyclic, collective, and airspeed as required)

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2
Q

Define “Emergency Engine Shutdown” and explain the procedure.

A

Engine shutdown without delay.

Procedures:
Engine control levers, fuel system selectors, and fuel boost pumps - OFF
Motor engine 30 seconds if TGT rises above 538°C on shutdown

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3
Q

Define “Lockout.”

A

Manual control of the engine RPM while bypassing 701D/CC DEC/EDECU functions.

Note* Under certain conditions the most reliable indication of engine power will be TGT.

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4
Q

Single Engine Failure

A
  1. Establish single engine airspeed
    (2). External cargo - Jettison (if required)

If continued flight not possible:
3. Land as soon as possible

If continued flight possible:
3. Land as soon as practicable

  • Do not respond to ENG OUT warning and audio until checking TGT, NG, and % RPM 1 and 2
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5
Q

Dual Engine Failure

A
  1. Auto rotate
  • Do not respond to ENG OUT warning and audio until checking TGT, NG, and % rpm 1 and 2.
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6
Q

ECU / DEC / EDECU Low Side Failure

A
  1. Establish single engine airspeed
  2. ENG CONT Lever - lockout, Maintain % TRQ approximately 10% below other engine
  3. Land as soon as practicable

*Lockout does not remove max fuel flow or NG limits. % RPM R will decrease below normal range if max fuel flow or NG limits are exceeded.

  • Care must be taken not to exceed TGT limits and keep RPM within range.
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7
Q

ECU / DEC / EDECU High Side Failure

A
  1. Establish single engine airspeed
    (2). Engine power control lever - Retard. Maintain % TRQ approximately 10% below other engine
  2. Land as soon as practicable

*If affected engine does not respond to ENG CONT Lever movement in the range between Fly and Idle, the HMU may be malfunctioning internally. If so:
(4). Emergency ENG Shutdown
(5). Refer to single-engine failure

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8
Q

% TRQ Split Between ENG 1 and 2

A
  1. Establish Single Engine Airspeed
  2. Refer to checklist for procedure
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9
Q

1 or #2 Oil FLTR Bypass Caution

A
  1. Establish Single Engine Airspeed
    (2). ENG CONT Lever - Retard
  2. Land as soon as practicable
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10
Q

Chip #1 or #2 Engine, #1 or #2 ENG Oil Press, #1 or #2 ENG Oil Temp Caution

A
  1. Establish single engine airspeed
    (2). Eng Control Lever - Retard

*If oil pressure is below minimum limits or if oil temp remains above limits:
(3). Emergency Engine Shutdown
(4). Refer to single - engine failure emergency procedures

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11
Q

Engine High Speed Shaft Failure

A
  1. Establish single engine airspeed
    (2). Emergency engine shutdown
    (3). Refer to single - engine failure emergency procedures
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12
Q

Loss of Tail Rotor Thrust or Tail Rotor Quadrant Caution Appears with Loss of Control at Low Airspeed / Hover (right rotation)

A
  1. Collective - Reduce
  2. Engine Power Control Levers - OFF (5-10’ AGL)
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13
Q

1 Tail Rotor Servo Caution Appears and Back-up Pump on Advisory Does Not Appear or #2 Tail RTR Servo ON Advisory Does Not Appear

A

(1). Tail Servo Switch - Back-up
(2). Back-up HYD Pump Switch - ON
3. Land as soon as practicable

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14
Q

Main XMSN Oil Pressure or Main XMSN Oil Temp Caution Appears / XMSN Oil Pressure Low / XMSN Oil Temp High

A
  1. Land as soon as possible
  2. If time permits, slow to 80 KIAS
  3. Emergency APU Start
  4. Gen #1 and #2 switches - OFF
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15
Q

Chip Input MDL LH or RH Caution Appears

A
  1. Establish Single - Engine Airspeed
    (2). ENG CONT Lever (affected engine) - Idle
  2. Land as soon as possible
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16
Q

Chip Main MDL Sump, Chip Access MDL LH or RH, Chip Tail XMSN or Chip Int XMSN / Tail XSMN Oil Temp or Int XMSN Oil Temp Caution Appears

A
  1. Land as soon as possible
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17
Q

Tail Rotor Quatrant Caution Appears in Cruise Flight

A
  1. Collective - adjust to determine controllability (fixed right or left)
  2. Land as soon as practicable

*If the helicopter is shut down and/or hydraulic power is removed with one tail rotor cable failure, disconnection of the other tail rotor cable will occur.

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18
Q

Loss of Control at Low Airspeed / Hover or Tail Rotor Quadrant Caution Appears (Left Rotation)

A
  1. ENG Cont Levers - Retard to decrease % RPM R below 100% and begin a partial power descent
  2. Collective - Adjust to preserve % RPM R
  3. ENG Power Control Levers - OFF (5-10’ AGL)
  4. Collective - Adjust for landing

*Reducing collective in a left rotation will increase rate of turn with the ENG Cont Levers of fly depending on the rate at which the ENG Cont Levers are retarded. It is critical that the pilot on the controls maintain a level attitude, preserve RPM R, and apply cushion for landing.

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19
Q

Main Transmission Failure

A
  1. Collective - Adjust only enough to begin a descent with power remaining applied to the main transmission throughout the descent and landing
  2. Land as soon as possible
  • If % RPM R decreases from 100% to below 96% with an increase in torque during steady state flight with no engine malfunction, the main transmission planetary carrier may have failed. During a main transmission planetary carrier failure, it may be impossible to maintain to maintain % RPM R at 100%
  • Decreasing % RPM R may be accompanied by a drop in transmission oil pressure of 10 PSI or more and possible unusual vibrations
20
Q

1 or #2 Fuel FLTR Bypass Caution

A

(1). ENG fuel sys selector on affected engine - XFD
2. Land as soon as practicable

21
Q

1 and #2 Fuel FLTR Bypass Cautions

A
  1. Land as soon as possible
22
Q

1 and #2 Fuel Low Cautions

A
  1. Land as soon as practicable
23
Q

1 or #2 Fuel Pressure Caution

A

*If critical situation:
(1). ENG fuel sys selector on affected engine - XFD
(2). Fuel boost pump control switch on side being used - ON
3. Land as soon as possible
(4). Emergency engine shutdown after landing

*If not critical
(1). ENG fuel sys selector on affected engine- XFD
(2). Fuel boost pump control switches - #1 or #2 Pump -OFF (as applicable)
3. Land as soon as practicable

*Consideration must be given to a possible fuel leak. If around oil cooler access area, may result in fire due to proximity of APU.

24
Q

1 and #2 Fuel Pressure Cautions

A
  1. Land as soon as possible
    (2). Emergency shutdown after landing

*Flameout is possible. Emergency shutdown of both engines due to possibility of fire.

25
#1 and #2 Gen Failure (#1 and #2 Conv and AC ESS Bus Cautions)
(1). SAS 1 switch - Press OFF 2. Airspeed - 80 KIAS or less (3). Gen #1 and #2 switches - Reset, then ON (4). If caution still appears - switches OFF (5). Emergency APU start (6). SAS 1 switch - ON 7. Land as soon as practicable *Following the loss of DC pri 1 and 2 bus power, both engines anti-ice valves will open, resulting in reduction of max torque available (18%)
26
#1 or #2 Gen Caution
(1). Affected Gen switch - Reset, then ON (2). If caution still appears - switches OFF * Caution: When the #1 ac gen is failed and the backup pump circuit breaker is out, turn off ac electrical power before resetting the backup pump power circuit breaker to avoid damaging to circuit limiters.
27
#1 and #2 Conv Caution
(1). Unnecessary DC electrical equipment - OFF 2. Land as soon as practicable
28
Battery Low Charge Caution
*If caution appears after AC power applied: (1). Batt switch - OFF, then ON. (About 30 minutes required to recharge battery) *If caution appears in flight (2). Batt switch - OFF, to conserve remaining battery charge
29
#1 HYD Pump Caution
(1). Tail Servo switch - Backup, then Normal 2. Land as soon as practicable
30
#2 HYD Pump Caution
(1). Power on reset switches - simultaneously press then release 2. Land as soon as practicable
31
#1 and #2 HYD Pump Cautions
1. Land as soon as possible - Restrict control movements to moderate rates * Not included in -10 Emergency Procedures: 2. Power on reset switches - simultaneously press, then release 3. Tail servo switch - Backup, then Normal
32
#1 HYD Pump Caution and Backup Pump Does Not Appear
1. Airspeed - Adjust to a comfortable airspeed (2). Backup HYD Pump switch - ON *if backup pump ON advisory appears: (3). Refer to #1 HYD pump caution emergency procedure * If backup pump ON advisory still does not appear: (3). Land as soon as possible
33
#2 HYD Pump Caution and Backup Pump Does Not Appear
1. Airspeed - Adjust to a comfortable airspeed (2). Backup HYD pump switch - ON *If backup pump ON advisory appears: (3). Refer to #2 HYD pump caution emergency procedure *If backup pump ON advisory does not appear: (4). FPS and Boost switches - OFF 5. Land as soon as possible
34
#1 or #2 Pri Servo Pressure Caution
1. SVO OFF switches - check both are centered 2. If caution appears with the SVO OFF switches centered, move the SVO OFF switch to turn off the malfunctioning servo 3. Land as soon as possible
35
#1 RSVR Low and #1 HYD Pump Cautions w/ Backup Pump On Advisory
1. Land as soon as practicable *If backup RSVR low caution appears: (2). SVO OFF switches centered - 1st stage 3. Land as soon as possible *Warning: if #2 pri servo pressure caution appears, establish landing attitude, minimize control inputs, and begin in a descent
36
#2 RSVR Low and #2 HYD Pump Cautions with Backup Pump On Advisory
(1). Power on reset switches - Simultaneously press then release 2. Land as soon as practicable *If the backup RSVR low caution appears (2). SVO OFF switches centered - 2nd stage 3. Land as soon as possible * Warning: if #1 pri servo pressure caution appears, establish landing attitude, minimize control inputs, and begin in a landing descent
37
#2 RSVR Low Caution
* Pilot assist servos will be isolated; if they remain isolated, proceed as follows: (1). Boost switch - OFF (2). FPS switch - OFF 3. Land as soon as practicable *Note: Because the logic module will close the valve supplying pressure to the pilot assist servos, boost servo OFF, SAS OFF and Trim Fail cautions will appear.
38
Boost Servo OFF
Appearance of the Boost Servo OFF caution with not other cautions appearing indicates a pilot valve jam in either the collective or yaw boost servo. Control forces in the affected axis will be similar to flight with boost off. (1). Boost switch - OFF 2. Land as soon as practicable
39
SAS 2 Failure Advisory Light On
(1). Power on reset switches - simultaneously press and then release
40
SAS Off Caution
(1). SAS1 and SAS2 switches - OFF (2). FPS switches - OFF 3. Land as soon as practicable
41
FLT Path Stab Caution
(1). Power on reset switches - Simultaneously press and then release *If the failure returns, control the affected axis manually *Warning: If the airspeed fault advisory light is illuminated, continued flight above 70 KIAS with the stabilator in the Auto mode is unsafe since a loss of the airspeed sensor would result in the stabilator slewing full down. *If the airspeed fault light remains illuminated on the AFCs panel: 2. Manually slew stabilator - Adjust to 0° if above 40 KIAS. 3. Land as soon as practicable * Use of cyclic mounted stabilator slew - up switch should be announced to the crew to minimize cockpit confusion.
42
Stabilator Malfunction - Auto Mode Failure
1. Cyclic mounted stabilator slew - up switch - Adjust if required to arrest or prevent nose down pitch rate (2). Auto control switch - Press ON once after establishing a comfortable airspeed * If automatic control is not regained: (3). Manually slew stabilator - Adjust to 0° for flight above 40 KIAS or full down when airspeed 40 KIAS or less 4. Land as soon as practicable *If manual control is not possible: 5. STAB POS indicator - check and duly at or below KIAS limits shown on placard. 6. Land as soon as practicable *Use of cyclic mounted stabilator slew- up switch should be announced to the crew to minimize cockpit confusion. *Warning: Pressing the auto control reset after a failure occurs results in the automatic mode coming on for one second. If a hard over signal to one actuator is present, the stabilator could move approximately 4° to 5° in that one second before another auto mode failure occurs. Subsequent reset attempts could result in the stabilator moving to an unsafe position.
43
% RPM Increasing/Decreasing (Oscillation)
1. Establish single engine airspeed. (2). Slowly retard Engine Power Control lever on the suspected engine. *If the oscillation stops and partial power flight cannot be maintained: (3). Place that engine in lockout and manually control the power. 4. Land as soon as practicable. * If the oscillation continues: (3). Place the Engine Power Control lever back to fly and retard the other engine. * If partial power flight cannot be maintained: (4). Place the engine in Lockout and manually control the power. 5. Land as soon as practicable.
44
Load Demand System Malfunction
* On Ground: Shut down and consult maintenance. * In flight: 1. Land as soon as practicable. 2. Preformed a normal approach, avoiding low power autorotative descents.
45
Engine Compressor Stall
1. Establish Single Engine Airspeed (2). Engine power control lever (affected engine) - Retard (3). Engine Power Control lever (affected engine) - FLY If stall condition recurs: (4). Emergency Engine Shutdown (affected engine) (5). Refer to single engine failure emergency procedure.
46
Lightning Strike
1. Establish single engine airspeed (2). Eng Power Cont levers - Adjust as required to control % RPM 3. Land as soon as possible

UH-60A+ (2 decks)

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