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60's > 60L chapter 9 > Flashcards

60L chapter 9 Flashcards

1
Q

The urgency of certain emergencies requires immediate and instinctive action by the pilot e.g., Dual-Engine Failure, Engine Fire in Flight, Loss of Tail Rotor Thrust. The most important single consideration is ______________ ______________. All procedures are subordinate to this requirement. The _____________ _____________ should be reset after each malfunction to allow systems to respond to subsequent malfunctions. If time permits during a critical emergency, transmit ____________ call, set transponder to ________________, ________________ external stores if required, turn off _____________ _____________, and lock _________________ ______________.

A

helicopter control

MASTER CAUTION

MAYDAY

emergency

jettison

boost pumps

shoulder harnesses

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2
Q

Define LAND AS SOON AS POSSIBLE:

A

landing at the nearest suitable landing area (e.g., open field) without delay. (The primary consideration is to ensure the survival of occupants.)

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3
Q

Define LAND AS SOON AS PRACTICABLE:

A

landing at a suitable landing area. (The primary consideration is the urgency of the emergency.)

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4
Q

Define AUTOROTATE:

A

adjusting the flight controls as necessary to establish an auto-rotational descent and landing.

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5
Q

In autorotation, as airspeed increases above ____- ____ KIAS, the rate of descent and glide distance ​______________ significantly. As airspeed decreases below _____ KIAS, the rate of descent will ​___________ and glide distance will _____________.

A

70 - 80

increase

64

increase

decrease

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6
Q

The recommended airspeed for autorotation is _____ KIAS. Autorotation below _____knots is not recommended because the deceleration does not effectively arrest the __________________________.

A

80

80

rate of descent

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7
Q

Define ESTABLISH SINGLE-ENGINE AIRSPEED:

A

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

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8
Q

ESTABLISH SINGLE-ENGINE AIRSPEED procedure:

(1) _____________________________________________________________________________
(2) _____________________________________________________________________________
(3) _____________________________________________________________________________

A
  1. Cyclic — Adjust as required.
  2. Collective—Adjustasrequiredtomaintain % RPM R within normal operating range.
  3. Establish appropriate airspeed.
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9
Q

Define EMER ENG SHUTDOWN:

A

engine shutdown without delay.

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10
Q

Engine shutdown in flight is usually not an immediate-action item unless a ________ exists. Before attempting an engine shutdown, identify the affected engine by checking _____________ ​warnings, ​% ________, % _______, ENG OIL __________, _________ TEMP, ​and_________SPEED.

A

fire

ENG OUT

RPM

TRQ

PRESS

TGT

Ng

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11
Q

EMER ENG SHUTDOWN procedure:

(1) _____________________________________________________________________________
(2) _____________________________________________________________________________
(3) _____________________________________________________________________________

A

ENG POWER CONT lever(s) — OFF.

ENG FUEL SYS selector(s) — OFF.

FUEL BOOST PUMP switch(es) — OFF.

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12
Q

CAUTION: If TGT is above 538°C after shutdown: place ___________________________________ switch as required, turn ENGINE IGNITION switch _______, and press starter to motor engine for _____ seconds or until TGT TEMP decreases below _______°C.

A

AIR SOURCE HEAT/START

OFF

30

500

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13
Q

Define LOCKOUT:

A

manual control of engine RPM while bypassing DEC/EDECU functions.

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14
Q

LOCKOUT procedure: ​______________________________________________________________________________________​______________________________________________________________________________________

The most reliable indication of engine power will be ______________.

A

ENG POWER CONT lever — Pull down and advance full forward while maintaining downward pressure, then adjust to set % RPM R as required.

TGT TEMP

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15
Q

WARNING: Going to ECU/DEC/EDECU LOCKOUT to obtain additional power does not remove _____________ _________ ___________or _______ ______. %RPM R will decrease below normal operating range if the above are exceeded.

A

Maximum Fuel Flow

Ng limits

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16
Q

CAUTION: When engine is controlled with ENG POWER CONT lever in LOCKOUT, engine response is much ___________ and _____ ____________ system is inoperative. Care must be taken not to exceed _______ limits and keeping % __________ and % _____ ___ and ___ in operating range.

A

faster

TGT limiting

TGT

% RPM R

% RPM 1 and 2

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17
Q

Define EMER APU START:

A

APU start to accomplish an emergency procedure.

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18
Q

EMER APU START procedure:

(1) _____________________________________________________________________________
(2) _____________________________________________________________________________

A

FUEL PUMP switch — APU BOOST.

APU CONTR switch — ON.

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19
Q

CAUTION: Ensure that the mask blowers are disconnected and position the BCA MCU control knobs to ____ prior to switching from main power to APU power.

A

OFF

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20
Q

After a malfunction of equipment has occurred, appropriate emergency actions have been taken and the ​helicopter is on the ground, an entry shall be made in the Remarks Section of DA Form 2408-___-___ ​describing the malfunction. Ground and flight operations shall be ________________ until corrective ​action has been taken.

A

13 - 1

discontinued

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21
Q

WARNING: For helicopters with a non-operational roll-trim actuator, the cyclic shall be held at all times with the rotor turning. In cases where emergency exit is required prior to rotor coasting to a stop, make sure that the cyclic stick is centered until the last crewmember can depart the cockpit. Since the main rotor shaft has a 3° forward tilt, an exit to the _______ _______or _________ ________will provide the greatest rotor clearance safety.

A

right rear

left rear

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22
Q

To release the cockpit door (emergency release of the door), the jettison handle is pulled ​________________; the door may then be jettisoned by kicking the ___________________________ ​of the door. If the door fails to jettison, egress ______ through the cabin or through the ___________ ______________ door.

A

to the rear

lower forward

aft

opposite cockpit

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23
Q

Cabin door window jettison. To provide emergency exit from the cabin, two jettisonable windows are ​installed in each cabin door. To release the windows, a handle (under a jettison lever guard) marked ​EMERGENCY EXIT PULL AFT, (left side; right side, PULL FWD) on the inside of the cabin door, is ​moved in the direction of the __________, releasing the windows. The windows can then be _________________.

A

arrow

pushed out

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24
Q

Emergency equipment consists of two hand held ______________________, one _______________, and ​three __________________________.

A

fire extinguishers

crash ax

first aid kits

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25
Q

WARNING: Prior to movement of either power control lever, it is imperative that the _________________ and the corresponding ______________ ______________ be identified. If the decision is made to shut down an engine, take at least _______ full seconds while retarding the ENG POWER CONT lever from FLY to IDLE, monitoring % TRQ, Ng SPEED, TGT TEMP, % RPM, and ENG OUT warning appearance.

A

malfunctioning engine

ENG POWER CONT lever

five

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26
Q

WARNING: Significant rotor droop that results in the generators dropping off line or a dual generator or converter failure will result in a partial power loss. This power loss will be due to the opening of engine anti-ice valves and will result in a loss of maximum torque available of _____%.

A

18

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27
Q

WARNING: When the power available during single engine operation is marginal or less, consideration ​should be given to ____________________________________. The _______________________ and ​_____________________________should be turned off as necessary to ensure maximum power is ​available on the remaining engine.

A

jettisoning the external stores

engine anti-ice

cockpit heater switches

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28
Q

WARNING: Do not respond to ______________________ and _____________ until checking TGT ​TEMP, Ng SPEED, and % RPM 1 and 2.

A

ENG OUT warning

audio

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29
Q

SINGLE ENGINE FAILURE
​1. _____________________________________________________________________________
(2) _____________________________________________________________________________
If continued flight is not possible:
3. _____________________________________________________________________________
If continued flight is possible:
4. LAND AS SOON AS PRACTICABLE.

A
  1. ESTABLISH SINGLE-ENGINE AIRSPEED.
  2. External cargo/stores — Jettison (if required). If continued flight is not possible:
  3. LAND AS SOON AS POSSIBLE.
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30
Q

Use of a crossbleed start could result in a power loss of up to ______% TRQ on the operational engine.

A

18

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31
Q

DUAL ENGINE FAILURE

_____________________________________________________________________________

A

AUTOROTATE

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32
Q

WARNING: Do not respond to ENG OUT warnings and audio until checking ________ and _________.

A

TGT TEMP

% RPM R.

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33
Q

ECU/DEC/EDECU LOW SIDE FAILURE
1. _________________________________________________________.
(2) ________________________________________________________. Maintain % TRQ approximately
10% below other engine.
3. LAND AS SOON AS PRACTICABLE

A
  1. ESTABLISHSINGLE-ENGINEAIRSPEED.

2. ENG POWER CONT lever (low % TRQ/ TGT TEMP engine) — LOCKOUT.

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34
Q

NOTE: If %RPM R reduces from 100% to 95-96% during steady flight, check %TRQ 1 and 2. If %TRQ ​1 and 2 are equal and below _______________________________, attempt to increase %RPM R with __________________________________________.

A

Maximum Torque Available

ENG RPM trim switch

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35
Q

ECU/DEC/EDECU HIGH SIDE FAILURE
1. _________________________________________________________.

(2) _________________________________________________________. Maintain % TRQ approximately 10% below other engine.
3. LAND AS SOON AS PRACTICABLE

If the affected engine does not respond to ENG POWER CONT lever movement in the range between FLY and IDLE, the HMU may be malfunctioning internally. If this occurs:

(4) Perform___________________________________________.
(5) Refer to single-engine failure emergency procedure.

A

ESTABLISH SINGLE-ENGINE AIRSPEED.

ENG POWER CONT lever (high % TRQ/TGT TEMP engine) — Retard

EMER ENG SHUTDOWN (affected engine)

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36
Q

Increasing the collective (during a high side failure) will probably ____________ the malfunctioning engine’s TGT TEMP above ______°C.

A

increase

900

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37
Q

% RPM INCREASING/DECREASING (OSCILLATION)

(Step 1)____________________________________________.

A

ESTABLISH SINGLE-ENGINE AIRSPEED

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38
Q

% TRQ SPLIT BETWEEN ENGINES 1 AND 2

(Step 1)__________________________________________.

A

ESTABLISH SINGLE-ENGINE AIRSPEED

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39
Q

LOAD DEMAND SYSTEM MALFUNCTION

A

Refer to checklist

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40
Q

ENGINE COMPRESSOR STALL

  1. _____________________________________________________________________________

If condition persists:
(2) ____________________________________________(TGT TEMP should decrease)

(3) ENG POWER CONT lever (affected engine) - FLY
If stall condition recurs:

(4) _______________________________ (affected engine).
(5) Refer to single engine failure emergency procedure.

A

ESTABLISH SINGLE-ENGINE AIRSPEED

ENG POWER CONT lever (affected engine) — Retard

EMER ENG SHUTDOWN

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41
Q

1 OIL FLTR BYPASS OR #2 OIL FLTR BYPASS CAUTION APPEARS

(Step 1) _____________________________________________________

A
  1. ESTABLISH SINGLE-ENGINE AIRSPEED.
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42
Q

CHIP #1 ENGINE OR CHIP #2 ENGINE, #1 ENGINE OIL PRESS OR #2 ENGINE OIL PRESS, #1 ENGINE OIL TEMP OR #2 ENGINE OIL TEMP CAUTION APPEARS

  1. _____________________________________________________________________________
    (2) _______________________________________________________________ (to reduce torque).

If oil pressure is below minimum limits or if oil temperature remains above maximum limits:

(3) ______________________________________________ (affected engine).
(4) Refer to single-engine failure emergency procedure.

A

ESTABLISH SINGLE-ENGINE AIRSPEED.

ENG POWER CONT lever (affected engine) — Retard

EMER ENG SHUTDOWN

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43
Q

ENGINE HIGH-SPEED SHAFT FAILURE

  1. _____________________________________________________________________________
    (2) ________________________________ (affected engine). Do not attempt to restart.
    (3) Refer to single-engine failure emergency procedure.
A

ESTABLISH SINGLE-ENGINE AIRSPEED.

EMER ENG SHUTDOWN

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44
Q

LIGHTNING STRIKE

  1. _____________________________________________________________________________
    (2) _____________________________________________________________________________
  2. _____________________________________________________________________________

WARNING: Lightning strikes may result in loss of automatic flight control functions, engine controls, ​and/or electric power.

A

ESTABLISH SINGLE-ENGINE AIRSPEED

ENG POWER CONT levers — Adjust as required to control % RPM.

LAND AS SOON AS POSSIBLE.

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45
Q

After a lightning strike, if practical, the pilot should reduce speed to _____ KIAS. This will reduce the criticality of having exactly ​the correct rotor speed 100%.

A

80

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46
Q

LOSS OF TAIL ROTOR THRUST IN CRUISE FLIGHT

  1. _____________________________________________________________________________
    (2) _____________________________________________________________________________
A

AUTOROTATE — Maintain airspeed at or above 80 KIAS.

ENG POWER CONT levers — OFF (during deceleration when intended point of landing is assured).

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47
Q

LOSS OF TAIL ROTOR THRUST OR TAIL ROTOR QUADRANT CAUTION APPEARS WITH LOSS OF CONTROL AT LOW AIRSPEED/HOVER (RIGHT ROTATION)

  1. _____________________________________________________________________________
    (2) _____________________________________________________________________________
A

Collective — Reduce.

ENG POWER CONT levers — OFF (5 to 10 feet above touchdown).

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48
Q

TAIL ROTOR QUADRANT CAUTION APPEARS IN CRUISE FLIGHT

  1. _____________________________________________________________________________
  2. LAND AS SOON AS PRACTICABLE
A
  1. Collective — Adjust to determine controllability (Fixed Right or Left).
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49
Q

WARNING: 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 when force from the boost servo cannot react ​against control cable quadrant spring tension. The quadrant spring will ___________ the cable and boost ​servo piston enough to _____________ the quadrant cable.

A

displace

unlatch

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50
Q

Loss of one tail rotor cable will be indicated by ​appearance of the _________________________ caution. No change in handling characteristics should occur if only one cable fails.

A

TAIL ROTOR QUADRANT

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51
Q

If both tail rotor control cables fail, a centering spring will position the tail rotor servo linkage to provide ​_____ degrees of pitch. This will allow trimmed flight at about _____ KIAS and _____ KIAS (these speeds ​will vary with gross weight). At airspeeds below _____ KIAS and above_____ KIAS, right yaw can be controlled by ___________the collective. Between _____ KIAS and _____ KIAS, left yaw can be controlled by ____________ collective.

A

10½

25

up to 145

25

145

reducing

25

145

increasing

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52
Q

LOSS OF CONTROL AT LOW AIRSPEED/HOVER OR TAIL ROTOR QUADRANT CAUTION APPEARS (LEFT ROTATION)

A
  1. ENG POWER CONT lever(s) — Retard to decrease % RPM R below 100% and begin a partial power descent.
  2. Collective—Adjusttopreserve % RPM R.
  3. ENG POWER CONT levers — OFF (5 to 10 feet above touchdown).
  4. Collective — Adjust for landing.
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53
Q

WARNING: Reducing collective in a left rotation will __________ rate of turn with the ENG
POWER CONT lever(s) ___ ______ depending on the rate at which the ENG POWER CONT lever(s) are retarded. It is critical that the pilot on the controls maintain a ______ __________, preserve RPM R, and apply cushion for the landing.

A

increase

at fly

level attitude

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54
Q

PEDAL BIND/RESTRICTION OR DRIVE WITH NO ACCOMPANYING CAUTION

(Step 1) ___________________________________________________________________________

A
  1. Apply pedal force to oppose the drive.
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55
Q

A malfunction within the yaw boost servo or tail rotor servo can produce much higher force at the pedals and the affected servo must be turned off. A hard over failure of the yaw boost servo will ___________ control forces as much as ______ pounds on the pedals.

A

increase

250

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56
Q

1 TAIL RTR SERVO CAUTION APPEARS AND BACK-UP PUMP ON ADVISORY DOES NOT APPEAR OR #2 TAIL RTR SERVO ON ADVISORY DOES NOT APPEAR

(1) _____________________________________________________________________________
(2) BACKUP HYD PUMP switch – ON
3. LAND AS SOON AS PRACTICABLE

A

TAIL SERVO switch — BACKUP.

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57
Q

During # 1 TAIL RTR SERVO CAUTION APPEARS AND BACK-UP PUMP ON ADVISORY DOES NOT APPEAR OR #2 TAIL RTR SERVO ON ADVISORY DOES NOT APPEAR, ____________ _________________ did not take place. Loss of both the No. 1 hydraulic pump and backup pump results in both stages of the tail-rotor servo being unpressurized. The yaw boost servo is still pressurized and the mechanical control system is still intact allowing limited tail-rotor control. Because of the limited yaw control range available, a roll-on landing at approximately _____ KIAS is required.

A

Automatic switch over

40 KIAS or above

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58
Q

MAIN XMSN OIL PRESS OR MAIN XMSN OIL TEMP CAUTION APPEARS, XMSN OIL PRESS LOW, XMSN OIL TEMP HIGH.

  1. _____________________________________________________________________________

If time permits:

  1. Slow to 80 KIAS.
    (3) _____________________________________________________________________________
    (4) GENERATORS NO. 1 and NO. 2 switches – OFF
A

LAND AS SOON AS POSSIBLE

EMER APU START

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59
Q

Loss of transmission cooling oil supply will lead to _________________ and/or ____________________ failure of main generators. If the malfunction is such that oil pressure decays slowly, the generators may fail __________ MAIN XMSN OIL PRESS caution appears.

A

electrical

mechanical

before

60
Q

CHIP INPUT MDL LH OR RH CAUTION APPEARS

A
  1. ESTABLISH SINGLE-ENGINE AIRSPEED.
  2. ENG POWER CONT lever (affected engine) — IDLE.
  3. LAND AS SOON AS POSSIBLE.
61
Q

CHIP MAIN MDL SUMP, CHIP ACCESS MDL LH or RH, CHIP TAIL XMSN, CHIP INT XMSN, TAIL XMSN OIL TEMP, INT XMSN OIL TEMP CAUTION APPEARS

A

LAND AS SOON AS POSSIBLE

62
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.
63
Q

WARNING: If % RPM R decreases from 100% to below 96% with an increase in torque during steady ​flight with no engine malfunction, the main transmission ______________ ____________ may have failed. During a ​main transmission ______________ ____________ failure, it may be impossible to maintain % RPM R at 100%.

A

planetary carrier

planetary carrier

64
Q

NOTE: Decreasing % RPM R may be accompanied by a drop in transmission oil pressure of _____ psi or ​more, and possible unusual helicopter vibrations.

A

10

65
Q

WARNING: If No. 2 DC primary bus electrical power is not available, only the __________fire bottle can be discharged and ​fire extinguishing capability for the #______ engine will be lost.

A

reserve

2

66
Q

The _____________________________ is the primary consideration when a fire occurs; therefore, it is imperative that every effort be made to extinguish the fire.

A

safety of helicopter occupants

67
Q

ENGINE FIRE IN FLIGHT

A
  1. ESTABLISHSINGLE-ENGINEAIRSPEED.
  2. ENG POWER CONT lever — OFF (affected engine).
  3. ENG EMER OFF handle — Pull.
  4. FIRE EXTGH switch — MAIN/RESERVE as required.
  5. LAND AS SOON AS POSSIBLE.
68
Q

WARNING: Attempt to ____________ ______________ fire before engine shutdown or discharging ​extinguishing agent.

A

visually confirm

69
Q

If the helicopter is airborne when a fire occurs, the most important single action that can be taken by the pilot is to _________. Consideration must be given to _________________________________ and turning _________ _________________ and XFER PUMPS off prior to landing.

A

land

jettisoning external stores

FUEL BOOST PUMPS

70
Q

ENGINE/FUSELAGE FIRE ON GROUND

A
  1. ENG POWER CONT levers — OFF.
  2. ENG EMER OFF handle(s) — Pull if applicable.
  3. FIRE EXTGH switch — MAIN/RESERVE as required.
71
Q

During a fire on the ground, it is essential to shut down the engine, evacuate crew and passengers, and begin fire fighting immediately. If time permits, a _______________________ should be made before the electrical power is OFF to expedite assistance from firefighting equipment and personnel.

A

“Mayday” radio call

72
Q

APU COMPARTMENT FIRE

A
  1. APU fire T-handle — Pull.

2. FIRE EXTGH switch — MAIN/RESERVE as required.

73
Q

APU OIL TEMP HI CAUTION APPEARS

A

NOTHING UNDERLINED

74
Q

ELECTRICAL FIRE IN FLIGHT

A
  1. BATT and GENERATORS switches — OFF.

2. LAND AS SOON AS POSSIBLE.

75
Q

SMOKE AND FUME ELIMINATION

A

NOTHING UNDERLINED

76
Q

WARNING: If battery overheats, do not _______________________________ or attempt to disconnect or ​remove battery. ​Battery fluid will cause burns, and an overheated battery could cause thermal burns and ​may explode.

A

remove battery cover

77
Q

1 OR #2 FUEL FLTR BYPASS CAUTION APPEARS

A

NOTHING UNDERLINED

78
Q

1 AND #2 FUEL FLTR BYPASS CAUTIONS APPEAR

A

LAND AS SOON AS POSSIBLE

79
Q

1 FUEL LOW AND #2 FUEL LOW CAUTION APPEARS

A

NOTHING UNDERLINED

80
Q

1 OR #2 FUEL PRESS CAUTIONS APPEAR

If the caution appears and the situation is critical:
(1) _____________________________________________________________________________
(2) _____________________________________________________________________________
3. _____________________________________________________________________________
(4) _____________________________________________________________________________

Non-critical situations are those where single engine flight is possible. If the situation is not critical:

NOTHING UNDERLINED

A

ENG FUEL SYS selector on affected engine — XFD.

FUEL BOOST PUMP switch on side being used — ON.

LAND AS SOON AS POSSIBLE.

EMER ENG SHUTDOWN after landing.

81
Q

WARNING: Consideration must be given to any suspected fuel system compromise if #1 OR #2 FUEL PRESS CAUTIONS APPEAR. If a compromise is suspected, the pilot must make every attempt to avoid or reduce the possibility of an ____________ _____________. A _______ ________ occurring in the oil cooler access area may result in fuel and/or fumes accumulating in or around the APU/engine compartments. In such cases, APU/engine operation may result in fire.

A

ignition source

fuel leak

82
Q

1 AND #2 FUEL PRESS CAUTIONS APPEAR

A
  1. LAND AS SOON AS POSSIBLE.

2. EMER ENG SHUTDOWN after landing.

83
Q

1 AND #2 GENERATOR FAILURE (#1 AND #2 CONV AND AC ESS BUS OFF CAUTIONS APPEAR)

(Step 6) __________________________________

A

EMER APU START

84
Q

1 or #2 GEN CAUTION APPEARS

A

NOTHING UNDERLINED

85
Q

CAUTION: When the #1 ac generator is failed, and the backup pump circuit breaker is out, ___________
____________ before resetting the backup pump power circuit breaker, to avoid damaging the ​current limiters.

A

turn off ac electrical power

86
Q

1 AND #2 CONV CAUTIONS APPEAR

A

NOTHING UNDERLINED

87
Q

Following the loss of DC PRI 1 and 2 bus power, both engine anti-ice valves will open, resulting in a loss of maximum torque available of UH−60L _____%.

A

18

88
Q

NOTE: When only battery power is available, NICAD battery life is about ___ minutes day and ___ ​minutes ​night for a battery 80% charged. SLAB battery life is about ___ minutes day and ___ minutes ​night for a battery 80% charged.

A

22

14

38

24

89
Q

BATTERY FAULT CAUTION APPEARS

A

NOTHING UNDERLINED

90
Q

BATT LOW CHARGE CAUTION APPEARS

A

NOTHING UNDERLINED

91
Q

LFT OR RT PITOT HEAT AND MASTER CAUTIONS APPEAR OR ARE FLASHING.

(Step 4) __________________________________

A

LAND AS SOON AS POSSIBLE

92
Q

CAUTION: LFT or RT PITOT HEAT and MASTER cautions appearing, with the PITOT HEAT switch in the OFF position, indicates ______________ failure of 5 Vdc power in the corresponding left or right relay panel. Do not ______ the helicopter.

• Flashing LFT or RT PITOT HEAT and MASTER cautions indicates a failure of a 5 Vdc power ______________ in the corresponding solid state left or right relay panel. Do not ______ the helicopter.

A

complete

fly

supply

fly

93
Q

1 HYD PUMP CAUTION APPEARS

A

NOTHING UNDERLINED

94
Q

2 HYD PUMP CAUTION APPEARS

A

NOTHING UNDERLINED

95
Q

1 AND #2 HYD PUMP CAUTIONS APPEAR

_________________________________ Restrict control movement to moderate rates.

A

LAND AS SOON AS POSSIBLE

96
Q

1 OR #2 HYD PUMP CAUTION APPEARS AND BACKUP PUMP ON ADVISORY DOES NOT APPEAR

  1. ____________________________ to a comfortable airspeed.
    (2) _____________________________________________________________________________
    (3) Refer to #1 HYD PUMP or #2 HYD PUMP caution appears emergency procedure.

If BACKUP-PUMP ON advisory still does not appear:

(4) _____________________________________________________________________________
5. _____________________________________________________________________________

A

Airspeed — Adjust

BACKUP HYD PUMP switch — ON. If BACK-UP PUMP ON advisory appears:

FPS and BOOST switches — Off (for #2 HYD PUMP caution).

LAND AS SOON AS POSSIBLE

97
Q

1 OR #2 PRI SERVO PRESS CAUTION APPEARS

  1. ___________________________________________________________________________
  2. _____________________________________________________________________________
    _______________________________________________________________________
  3. _____________________________________________________________________________
A
  1. SVO OFF switch — Check both are centered.
  2. If the caution appears with the SVO OFF switch centered, move the SVO OFF switch to turn off the malfunctioning servo.
  3. LAND AS SOON AS POSSIBLE.
98
Q

Appearance of #1 or #2 PRI SERVO PRESS caution can be caused by inadvertently placing the SVO OFF switch on either collective control head in 1ST STG or 2ND STG position. Before initiating emergency procedure action, the pilots should _______________________________________________________________.

A

check that both SVO OFF switches are centered.

99
Q

1 RSVR LOW AND #1 HYD PUMP CAUTIONS APPEAR WITH BACK-UP PUMP ON ADVISORY APPEARING

  1. LAND AS SOON AS PRACTICABLE.

If the BACK-UP RSVR LOW caution also appears:

(2) _____________________________________________________________________________

WARNING: If #2 PRI SERVO PRESS caution appears, establish landing attitude, minimize control ​inputs, and begin a ________________________.

  1. _____________________________________________________________________________
A

SVO OFF switch — 1ST STG.

descent

LAND AS SOON AS POSSIBLE

100
Q

2 RSVR LOW AND #2 HYD PUMP CAUTIONS APPEAR WITH BACK-UP PUMP ON ADVISORY APPEARING

(1) POWER ON RESET switches – Simultaneously press then release.
2. LAND AS SOON AS PRACTICABLE.

If BACK-UP RSVR LOW caution also appears:

(3) _____________________________________________________________________________

WARNING: If #1 PRI SERVO PRESS caution appears, establish landing attitude, ___________ control ​inputs, and begin a descent.

  1. _____________________________________________________________________________
A

SVO OFF switch — 2ND STG.

minimize

LAND AS SOON AS POSSIBLE

101
Q

2 RSVR LOW CAUTION APPEARS

A

NOTHING UNDERLINED

102
Q

NOTE: Because the logic module will close the valve supplying pressure to the ____________________, ​BOOST SERVO OFF, SAS OFF, and TRIM FAIL cautions will appear.

A

pilot-assist servos

103
Q

COLLECTIVE BOOST SERVO HARDOVER/POWER PISTON FAILURE

(1) _____________________________________________________________________________
2. LAND AS SOON AS PRACTICABLE

A

BOOST switch — Off

104
Q

Hardover failure of the collective boost servo will increase control forces (as much as _____ pounds) in the ​collective.

A

150

105
Q

PITCH BOOST SERVO HARDOVER

A

NOTHING UNDERLINED

106
Q

Hardover failure of the pitch boost servo will increase the longitudinal cyclic control forces (approximately ​______ pounds).

A

20

107
Q

BOOST SERVO OFF CAUTION APPEARS

A

NOTHING UNDERLINED

108
Q

Appearance of the BOOST SERVO OFF caution with no other cautions appearing indicates a ​___________ ____________ jam in either the collective or yaw boost servo.

A

pilot valve

109
Q

EMERGENCY LANDING IN WOODED AREAS - POWER OFF

  1. ___________________________. Decelerate helicopter to stop all forward speed at treetop level.
  2. ___________________________________________to maximum before main rotor contacts tree branches.
A

AUTOROTATE

Collective adjust

110
Q

DITCHING – POWER ON

A

NOTHING UNDERLINED

111
Q

DITCHING – POWER OFF

(Step 1) ____________________

A

AUTOROTATE

112
Q

FLIGHT CONTROL/MAIN ROTOR SYSTEM MALFUNCTIONS

  1. _____________________________________________________________________________
    (2) _____________________________________________________________________________
A

LAND AS SOON AS POSSIBLE.

EMER ENG(S) SHUTDOWN after landing

113
Q

Failure of a main rotor component may be indicated by the sudden onset or steady increase in main rotor vibration, transient aircraft motions, or unusual noise, including a ‘bang’. These conditions can occur due to ______ ________ _________, blade strikes, skin separation, shift or loss of balance weights, or other material. Malfunctions may result in severe main rotor flapping. The severity of vibrations may be minimized by _________________ _____________________.

A

blade cuff failure

reducing airspeed

114
Q

NOTE: Blade cuff failure is typically a _______ wise crack of the cuff through the blade attachment bolt holes on the upper or lower ligament.

A

chord

115
Q

WARNING: Danger exists that the main rotor system could collapse or separate from the aircraft after ​landing. Exit when _______________________________________.

A

main rotor has stopped

116
Q

SAS FAILURE WITH NO FAILURE/ADVISORY INDICATION

A

NOTHING UNDERLINED

117
Q

Erratic electrical input to a SAS actuator can result in moderate rotor tip path oscillations that are often accompanied with ___________ sounds or “knocking” which may be felt in the cyclic or pedal controls. No SAS malfunction, however, can physically _________________________ flight controls. Failure of SAS 2 is usually, but not necessarily, followed by a failure/advisory indication. Failure of a SAS 1 component will _____ be accompanied by a failure/advisory indication as SAS 1 does not contain _______________ ________________.

A

pounding

drive the pilots’

not

diagnostic capabilities

118
Q

SAS 2 FAILURE ADVISORY LIGHT ON

A

NOTHING UNDERLINED

119
Q

SAS OFF CAUTION APPEARS

A

NOTHING UNDERLINED

120
Q

FLT PATH STAB CAUTION APPEARS

A

NOTHING UNDERLINED

121
Q

WARNING: If the airspeed fault advisory light is illuminated, continued flight above _______ KIAS with ​the stabilator in the AUTO MODE is unsafe since a loss of the airspeed signal from the remaining airspeed ​sensor would result in the stabilator slewing ______________________.

A

70

full-down

122
Q

NOTE: Use of the cyclic mounted stabilator slewup switch should be __________________ to the crew to ​minimize cockpit confusion.

A

announced

123
Q

PITCH ROLL OR YAW/TRIM HARDOVER

A

NOTHING UNDERLINED

124
Q

TRIM ACTUATOR JAMMED

A

NOTHING UNDERLINED

125
Q

STABILATOR MALFUNCTION – AUTO MODE FAILURE

If AUTO Mode failure occurs:

  1. ________________________________________________________________to arrest or prevent nose down pitch rate.
    (2) _____________________________________________________________________________

If automatic control is not regained:

  1. Manually slew stabilator – Adjust to 0o for flight above 40 KIAS or full down when airspeed is 40 KIAS or less. The preferred method of manually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.
  2. LAND AS SOON AS PRACTICABLE

If manual control is not possible:

  1. STAB POS indicator – Check and fly at or below KIAS LIMITS shown on placard.
  2. LAND AS SOON AS PRACTICABLE
A

Cyclic mounted stabilator slew-up switch — Adjust as required

AUTO CONTROL RESET switch — Press ON once after establishing a comfortable airspeed.

126
Q

WARNING: If ________________ is continued or collective is ______________ with the stabilator in a trailing edge down position, longitudinal control will be lost. The stabilator shall be slewed to 0° above 40 KIAS and full down when airspeed is 40 KIAS or less. If the stabilator is slewed up to the 0° position and the AUTO CONTROL switch is pressed during acceleration, the helicopter may pitch to a nose down attitude.

Pressing the AUTO CONTROL RESET button after a failure occurs results in the automatic mode ​coming on for one second. If a hardover signal to one actuator is present, the stabilator could move ​approximately ___° to ___° in that one second before another auto mode failure occurs. Subsequent reset ​attempts could result in the stabilator moving to an _____________ position.

If the stabilator AUTO mode repeatedly disengages during a flight, flight above _____ KIAS is prohibited ​with the stabilator in __________ mode

A

acceleration

decreased

4°

5°

unsafe

70

AUTO

127
Q

NOTE: Use of the cyclic mounted stabilator slewup switch should be __________________ to the crew to ​minimize cockpit confusion.

A

announced

128
Q

UNCOMMANDED NOSE DOWN PITCH ATTITUDE CHANGE

  1. _____________________________________________________________________________
  2. _____________________________________________________________________________
  3. _____________________________________________________________to arrest nose down pitch rate
    (4) MAN SLEW switch – Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds 40 KIAS or less.
  4. LAND AS SOON AS PRACTICABLE
A

Cyclic — Adjust as required

Collective — Maintain or increase

Cyclic mounted stabilator slew-up switch — Adjust as required

129
Q

UNCOMMANDED NOSE UP PITCH ATTITUDE CHANGE

  1. _____________________________________________________________________________
  2. _____________________________________________________________________________
    (3) MAN SLEW switch – adjust to 0 at airspeeds above 40 KIAS and full down at airspeeds 40 KIAS or less.
  3. LAND AS SOON AS PRACTICABLE
A

Cyclic — Adjust as required

Collective — Reduce as required

130
Q

ATTITUDE HEADING REFERENCE SYSTEM (AHRS) HEADING DEVIATIONS.

A

NOTHING UNDERLINED

131
Q

The AHRS can operate in either Slave or DG mode. In Slave mode, AHRS is updated with magnetic heading information from the MDU to automatically correct and prevent heading precession on HSIs. In the event of total failure of the MDU, AHRS reverts to _____ mode, requiring frequent manual updating to prevent HSI precession. If a discrete (partial) failure of the MDU occurs, where one or more outputs from the MDU remain, and certain magnetic strength thresholds are maintained, significant _____________ ___________ may occur without alert to the pilot.

A

DG

heading deviations

132
Q

EMERGENCY JETTISONING

_____________________________________________________________________________

A

CARGO REL or HOOK EMER REL switch — Press

133
Q

MR DE-ICE FAULT, MR DE-ICE FAIL, TR DE-ICE FAIL CAUTION APPEARS

  1. Icing conditions - Exit.
    (2) BLADE DEICE POWER switch - OFF, when out of icing conditions.

If vibrations increase:

  1. _____________________________________________________________________________
A

LAND AS SOON AS POSSIBLE

134
Q

If the MR DE-ICE FAULT caution appears, the system will continue to function in a ______________ mode. The pilot must be aware of vibration levels and % TRQ requirements, which could be a result of ice buildup.

A

degraded

135
Q

If the MR DE-ICE FAIL caution appears, the main rotor deice will automatically _______ _______. Tail rotor deice will remain on.

A

turn off

136
Q

If the TR DE-ICE FAIL caution appears, tail rotor deice will automatically _______ _______. Main rotor deice will remain on.

A

turn off

137
Q

PWR MAIN RTR AND/OR TAIL RTR MONITOR LIGHT ON

A

NOTHING UNDERLINED

138
Q

ICE RATE METER OR DCIU FAIL OR INACCURATE

A

NOTHING UNDERLINED

139
Q

Failure of the ice rate meter or DCIU should be indicated by appearance of the FAIL flag on the ice rate meter face or FAIL light on the DCIU. Inaccuracy of the meter or DCIU will be indicated by increased _______________ required and/or increase of ____________ levels due to ice buildup. If failure or inaccuracy is suspected, with no other indicated failures, the system can be manually controlled.

A

torque

vibration

140
Q

LOSS OF NO. 1 OR NO.2 GENERATOR DURING BLADE DEICE OPERATION

(1) _____________________________________________________________________________
(2) BLADE DE-ICE POWER switch - OFF then ON.

A

EMER APU START

141
Q

AAR-57 FAILURE CMWS

A

NOTHING UNDERLINED

142
Q

WARNING: CMWS During power up process, performing IBIT, or rebooting during flight, the CMWS / ICMD will be offline for approximately ___ to ___ minutes and unable to protect the aircraft until completion.

Selecting ____________ mode during startup, reboot, or IBIT will result in the system entering a mode where no system degrade or failure is noted; but the CMWS will _____ fire munitions either manually or automatically.

A

2

5

BYPASS

not

143
Q

NOTE: Should the system inadvertently be placed in the BYPASS mode during startup, reboot, or IBIT, wait until the system completes startup or reboot (approximately 2 to 5 minutes). Set the CI PWR switch to ______, wait 5 seconds, and then set the switch to ______. This PWR process may take up to 5 minutes to reboot.

A

OFF

ON

144
Q

After IBIT completes, a message will indicate whether system passed (SYSTEM PASS), failed (SYSTEM FAIL), or is degraded (SYSTEM DEGR). NOTE: The CI will display failure items as ________________ or __________________.

A

XXXX DEGR

XXXX FAIL

145
Q

AAR-57 FIRE IN CHAFF OR FLARE MUNITION DISPENSERS. CMWS

A

NOTHING UNDERLINED

60's (12 decks)

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