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UH-60M Blackhawk Helicopter > Chapter 9 - Emergency Procedures > Flashcards

Chapter 9 - Emergency Procedures Flashcards

1
Q

The term EMER ENG SHUTDOWN is defined as engine shutdown without delay. Engine shutdown in flight is usually not an immediate-action item unless a fire exists. Before attempting an engine shutdown, identify the affected engine by checking ENG OUT warning lights, NP, NR, Q (torque), P (engine oil pressure), TGT, and NG.

  1. _____________ — OFF.
  2. _____________ — OFF.
  3. _____________ — OFF.
A

The term EMER ENG SHUTDOWN is defined as engine shutdown without delay. Engine shutdown in flight is usually not an immediate-action item unless a fire exists. Before attempting an engine shutdown, identify the affected engine by checking ENG OUT warning lights, NP, NR, Q (torque), P (engine oil pressure), TGT, and NG.

  1. ENG POWER CONT lever(s) — OFF.
  2. ENG FUEL SYS selector(s) — OFF.
  3. FUEL BOOST PUMP switch(es) — OFF.
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2
Q

CAUTION

When engine is controlled with ENG
POWER CONT lever in LOCKOUT,
engine response is much _____ and TGT
limiting system is inoperative. Care must
be taken not to exceed ____ limits and
keeping ___ and ___ and ___ in operating range.

A

CAUTION
When engine is controlled with ENG
POWER CONT lever in LOCKOUT,
engine response is much faster and TGT
limiting system is inoperative. Care must
be taken not to exceed TGT limits and
keeping NR and NP 1 and 2 in operating
range.

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3
Q

CAUTION
If TGT rises above ____°C after
shutdown, place AIR SCE HT/START
switch as required, turn ENGINE IGNITION
switch OFF, and press starter to
motor engine for ___ seconds or until TGT
decreases below ____°C.

A

CAUTION
If TGT rises above 500°C after
shutdown, place AIR SCE HT/START
switch as required, turn ENGINE IGNITION
switch OFF, and press starter to
motor engine for 30 seconds or until TGT
decreases below 500°C.

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4
Q

The term _______ is defined as manual control of
engine RPM while bypassing ____/_____ functions.
Bypass of the engine control will be required when NP1 or
2 decreases below normal demand speed due to a
malfunction of the DEC.

A

The term LOCKOUT is defined as manual control of
engine RPM while bypassing DEC/EDECU functions.
Bypass of the engine control will be required when NP1 or
2 decreases below normal demand speed due to a
malfunction of the DEC.

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5
Q

WARNING
Going to DEC LOCKOUT to obtain additional
power does not remove Maximum
Fuel Flow or NG limits. NR will
______ ______ normal operating range if
Maximum Fuel Flow or NG limits are
______.

A

WARNING
Going to DEC LOCKOUT to obtain additional
power does not remove Maximum
Fuel Flow or NG limits. NR will
decrease below normal operating range if
Maximum Fuel Flow or NG limits are
exceeded.

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6
Q

ENG POWER CONT lever (lock out procedure) -

_________________________________________________________

___________________________________________.

A

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

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7
Q

The term EMER APU START is defined as APU
start to accomplish an emergency procedure.

  1. FUEL PUMP switch — __________
  2. APU CONT switch — ___.
A
  1. FUEL PUMP switch — APU BOOST.
  2. APU CONT switch — ON.
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8
Q

SINGLE-ENGINE FAILURE

  1. Collective — _______________
  2. External cargo/stores — _____________.
  3. ________________________

If continued flight is not possible:

4._______________________

A

SINGLE-ENGINE FAILURE

  1. Collective — Adjust to maintain NR
  2. External cargo/stores — Jettison (if required).
  3. Establish single-engine airspeed.

If continued flight is not possible:

  1. LAND AS SOON AS POSSIBLE.
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9
Q

DUAL-ENGINE FAILURE

WARNING
Do not respond to ENG OUT warning
lights and audio until checking TGT and
NR.
1. _____________

A

WARNING
Do not respond to ENG OUT warning
lights and audio until checking TGT and
NR.
AUTOROTATE.

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10
Q

DECREASING NR.

  1. ________ — ________________.
    1. ___________________________

If single engine flight cannot be achieved or maintained:

  1. __________________— _________ Maintain Q
    approximately 10% below other engine.
A
  1. Collective — Adjust to control NR.
    1. Establish single-engine airspeed.

If single engine flight cannot be achieved or maintained:

  1. _ENG POWER CONT lever (low Q/TGT
    TEMP engine)    _ — LOCKOUT. Maintain Q
    approximately 10% below other engine.
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11
Q

WARNING
NR can also ________ as a result of
exceeding the Maximum Torque Available
due to reaching TGT limiting, Maximum
Fuel Flow, or NG limiting without
an associated hardware failure.

A

WARNING
NR can also decrease as a result of
exceeding the Maximum Torque Available
due to reaching TGT limiting, Maximum
Fuel Flow, or NG limiting without
an associated hardware failure.

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12
Q

CAUTION
When engine is controlled with ENG
POWER CONT lever in LOCKOUT,
engine response is much _____ and the
TGT limiting system is _______. Care
must be taken not to exceed TGT limits
and keeping NR, NP1 and NP2 in
operating range.

A

CAUTION
When engine is controlled with ENG
POWER CONT lever in LOCKOUT,
engine response is much faster and the
TGT limiting system is inoperative. Care
must be taken not to exceed TGT limits
and keeping NR, NP1 and NP2 in
operating range.

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13
Q

INCREASING NR

  1. ____________ — ______ Maintain Q approximately 10% below other engine.
  2. 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:

  1. _______________
  2. Perform ____________ (affected engine).
  3. Refer to single-engine failure emergency procedure.
A
  1. _ENG POWER CONT lever (high Q/TGT
    engine)    _— Retard. Maintain Q approximately 10% below other engine.
  2. 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:
  3. Establish single engine airspeed.
  4. Perform EMER ENG SHUTDOWN (affected engine).
  5. Refer to single-engine failure emergency procedure.
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14
Q

ENGINE COMPRESSOR STALL

  1. _________________
    2._________— ______.
    If condition persists:
  2. __________________ — ______(TGT 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
  1. Establish single engine airspeed.
  2. Collective — Reduce.
    If condition persists:
  3. ENG POWER CONT lever (affected engine) — Retard (TGT should decrease).
  4. ENG POWER CONT lever (affected engine) — FLY.
    If stall condition recurs:
  5. EMER ENG SHUTDOWN (affected engine).
  6. Refer to single-engine failure emergency
    procedure.
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15
Q

ENG 1 OIL BYPASS OR ENG 2 OIL BYPASS
CAUTION APPEARS

  1. ___________________________.
  2. ENG POWER CONT lever — Retard.
  3. LAND AS SOON AS PRACTICABLE
A
  1. Establish single engine airspeed.
  2. ENG POWER CONT lever — Retard.
  3. LAND AS SOON AS PRACTICABLE
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16
Q

CHIP ENG 1 OR CHIP ENG 2, ENG 1 OIL
PRESS OR ENG 2 OIL PRESS, ENG 1 OIL HOT OR
ENG 2 OIL HOT CAUTION APPEARS

  1. _________________________________.
  2. ENG POWER CONT lever (affected engine) — Retard (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
  1. Establish single engine airspeed.
  2. ENG POWER CONT lever (affected engine) — Retard (to reduce torque).
    If oil pressure is below minimum limits or if oil temperature remains above maximum limits:
  3. EMER ENG SHUTDOWN (affected engine).
  4. Refer to single engine failure emergency
    procedure.
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17
Q

ENGINE HIGH-SPEED SHAFT FAILURE

  1. __________________________.
  2. ______________ — ________
  3. _____________ (affected engine).
    Do not attempt to restart.
  4. Refer to single-engine failure emergency
    procedure.
A
  1. Establish single engine airspeed.
  2. Collective — Adjust.
  3. EMER ENG SHUTDOWN (affected engine).
    Do not attempt to restart.
  4. Refer to single-engine failure emergency
    procedure.
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18
Q

LIGHTNING STRIKE

  1. _________________ — __________ (as
    required to control NP and NR).
  2. ___________________________._
A

LIGHTNING STRIKE

  1. ENG POWER CONT levers — Adjust (as
    required to control NP and NR).
  2. LAND AS SOON AS POSSIBLE.
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19
Q

Loss of Tail Rotor Thrust in Cruise Flight

  1. ______________ — Adjust to 80 KIAS or above.
  2. ______________ — Maintain airspeed at or
    above 80 KIAS.
  3. ______________ — OFF (during
    deceleration when intended point of landing is
    assured).
A
  1. Airspeed — Adjust to 80 KIAS or above.
  2. _AUTOROTATE — Maintain airspeed at or
    above 80 KIAS    _.
  3. _ENG POWER CONT levers — OFF (during
    deceleration when intended point of landing is
    assured)    _.
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20
Q

Loss of Tail Rotor Thrust or T/R QUAD FAIL Caution Appears with Loss of Control at Low Airspeed/Hover (Right Rotation)

  1. _______________ — ________________
  2. __________________ — ____________________________
A
  1. Collective — Reduce.
  2. _ENG POWER CONT levers — OFF (5 to 10
    feet above touchdown).    _
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21
Q

T/R QUAD FAIL Caution Appears in Cruise Flight

  1. ___________ — ___________\__(_\___________).
  2. LAND AS SOON AS PRACTICABLE
A
  • *1. Collective — Adjust to determine controllability (Fixed Right or Left).**
    2. LAND AS SOON AS PRACTICABLE
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22
Q

Loss of Control at Low Airspeed/Hover or T/R QUAD FAIL Caution Appears (Left Rotation)

  1. ENG POWER CONT lever(s) — _____________.
  2. Collective — __________________.
  3. ENG POWER CONT levers — _________________.
  4. Collective — ________________ .
A
  1. ENG POWER CONT lever(s) — Retard to decrease NR below 100% and begin a partial power descent.
  2. Collective — Adjust to preserve NR.
  3. ENG POWER CONT levers — OFF (5 to 10 feet above touchdown).
  4. Collective — Adjust for landing.
23
Q

Pedal Bind/Restriction or Drive With No Accompanying Caution

  1. ____________________________.
  2. Check other pedals for proper operation.
  3. TAIL SERVO switch — BACKUP.
    If normal control authority is not restored:
  4. TAIL SERVO switch — NORMAL.
  5. SAS/BOOST switch — OFF.
    If normal control forces are not restored:
  6. SAS/BOOST switch — ON.
  7. Collective — Adjust to determine controllability
    for landing.
  8. LAND AS SOON AS PRACTICABLE.
A
  1. Apply pedal force to oppose the drive.
24
Q

T/R SERVO 1 FAIL Caution Appears and BACK UP PUMP ON Advisory Does Not Appear or T/R SERVO 2 ON Advisory Does Not Appear

  1. ______________ — ___________
  2. BACKUP HYD PUMP switch — ON.
  3. LAND AS SOON AS PRACTICABLE
A
  1. TAIL SERVO switch — BACKUP.
25
Q

MAIN XMSN PRESS Caution Appears/MAIN
XMSN OIL HOT Caution Appears.

  1. ______________.
    If time permits:
  2. Slow to 80 KIAS.
  3. _____________.
  4. GENERATORS NO. 1 and NO. 2 switches — OFF.
A
  1. LAND AS SOON AS POSSIBLE.
    If time permits:
  2. Slow to 80 KIAS.
  3. EMER APU START.
  4. GENERATORS NO. 1 and NO. 2 switches
    — OFF.
26
Q

CHIP L INPUT MDL or CHIP R INPUT MDL Caution Appears.

  1. ___________________________
  2. ____________________ — IDLE.
  3. ___________________________
A
  1. Establish single engine airspeed.
  2. ENG POWER CONT lever (affected engine) — IDLE.
  3. LAND AS SOON AS POSSIBLE.
27
Q

CHIP MAIN MDL SUMP, CHIP L ACC MDL or CHIP R ACC MDL, CHIP TAIL XMSN, TAIL XMSN OIL HOT, CHIP INT XMSN or INT XMSN OIL
HOT Caution Appears.

  1. _____________________
A

LAND AS SOON AS POSSIBLE.

28
Q

Main Transmission Failure

  1. Collective — _______________

__________________________

__________________________
2. _________________________.

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.
29
Q

Engine/Fuselage Fire On Ground

  1. _________________ — ________.
  2. _________________ — ________.
  3. ________________ — _________.
  4. ________________ — _________.
A
  1. ENG POWER CONT levers — OFF.
  2. ENG EMER OFF T-handle — Pull if applicable.
  3. FIRE EXTGH switch — MAIN/RESERVE as required.
  4. Rotor Brake — As required.
30
Q

APU Compartment Fire.

  1. _______________ — __________.
  2. _______________ — __________.
A
  1. APU fire T-handle — Pull.
  2. FIRE EXTGH switch — MAIN/RESERVE as required.
31
Q

Engine Fire In Flight

WARNING
Attempt to visually confirm fire before engine shutdown or discharging extinguishing agent.
1. ________________________.
2. __________________— ___.
3. _____________ — ________.
4. _____________ — _______________.
5. _____________________.

A
  1. Establish single engine airspeed.
  2. ENG POWER CONT lever (affected engine) — OFF.
  3. ENG EMER OFF handle — Pull.
  4. FIRE EXTGH switch — MAIN/RESERVE as required.
  5. LAND AS SOON AS POSSIBLE.
32
Q

Electrical Fire In Flight

  1. ___________ — ______
  2. __________________.
A
  1. BATT and GENERATORS switches — OFF.
  2. LAND AS SOON AS POSSIBLE.
33
Q

FUEL 1 BYPASS and FUEL 2 BYPASS Cautions Appear

  1. ______________________
A
  1. LAND AS SOON AS POSSIBLE
34
Q

FUEL 1 PRESS LOW or FUEL 2 PRESS LOW Caution Appears

If the caution appears and the situation is critical:

  1. ___________________________–_________.
  2. ____________________ — ________.
  3. ______________________________.
  4. _____________________________.
A

If the caution appears and the situation is critical:

_**1. ENG FUEL SYS selector on affected engine — XFD.

  1. FUEL BOOST PUMP switch on side being used — ON.
  2. LAND AS SOON AS POSSIBLE.
  3. EMER ENG SHUTDOWN after landing.**_
35
Q

FUEL 1 PRESS LOW and FUEL 2 PRESS LOW Cautions Appear

  1. ____________________________.
  2. ____________________________.
A

_1. LAND AS SOON AS POSSIBLE.
2. EMER ENG SHUTDOWN after landing._

36
Q

GEN 1 FAIL and GEN 2 FAIL (No. 1 & No. 2 CONV and AC REF BUS DEGRAD) Cautions Appear.

  1. Airspeed — Adjust (80 KIAS or less).
  2. GENERATORS NO. 1 and NO. 2 switches — RESET; then ON.
    If electrical power is not restored:
  3. GENERATORS NO. 1 and NO. 2 switches — OFF.
  4. MCUs and ECS — OFF prior to EMER APU START.
  5. ______________________.
  6. LAND AS SOON AS PRACTICABLE.
  7. If APU GEN ON advisory light extinguishes, ensure MCUs and ECS — OFF prior to resetting the APU generator.
A

5. EMER APU START.

37
Q

HYD PUMP 1 FAIL and HYD PUMP 2 FAIL Cautions Appear

_______________________. Restrict
control movement to moderate rates.

A

LAND AS SOON AS POSSIBLE. Restrict
control movement to moderate rates.

38
Q

HYD PUMP 1 FAIL or HYD PUMP 2 FAIL Caution Appears and BACK UP PUMP ON Advisory Does Not Appear

  1. ________ — _______ to a comfortable airspeed.
  2. __________________ — ______.
    If BACKUP PUMP ON advisory still does not appear:
  3. ___________ — ________ (________).
  4. _________________________.
A
  1. Airspeed — Adjust to a comfortable airspeed.
  2. BACKUP HYD PUMP switch — ON.
    If BACKUP PUMP ON advisory still does not appear:
  3. FPS and SAS/BOOST switches — _Press off
    (switch lights off, for HYD PUMP 2 FAIL caution)    _.
  4. LAND AS SOON AS POSSIBLE.
39
Q

PRI SERVO 1 FAIL or PRI SERVO 2 FAIL Caution Appears.

  1. ___________ — Check centered.
  2. __________________________

__________________________.
3. _________________________.

A
  1. SERVO OFF switch — Check centered.
  2. _If the caution appears with the SERVO OFF
    switch centered, move the SERVO OFF
    switch to turn off the malfunctioning servo.    _
  3. LAND AS SOON AS POSSIBLE.
40
Q

RSVR 1 LOW and HYD PUMP 1 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 PRI SERVO 2 FAIL caution appears, establish landing attitude, minimize control inputs, and begin a descent.
3. _____________________.

A
  1. SERVO OFF switch — 1ST STG.
  2. LAND AS SOON AS POSSIBLE.
41
Q

RSVR 2 LOW and HYD PUMP 2 FAIL Cautions Appear With BACK UP PUMP ON Advisory Appearing.

  1. AUTO FLIGHT CONTROL panel CPTR 1 and/or CPTR 2 switches (if illuminated) — Press to reset FCC.
  2. LAND AS SOON AS PRACTICABLE.
    If BACK UP RSVR LOW caution also appears:
  3. ____________ — _________.

WARNING
If PRI SERVO 1 FAIL caution appears, establish landing attitude, minimize control inputs, and begin a descent.
4. ____________________.

A
  1. SERVO OFF switch — 2ND STG.
  2. LAND AS SOON AS POSSIBLE.
42
Q

Collective Boost Servo Hardover/Power Piston Failure.

  1. ______________ — ____.
  2. FPS switch — Off.
  3. LAND AS SOON AS PRACTICABLE.
A
  1. SAS/BOOST switch — Off.
  2. FPS switch — Off.
  3. LAND AS SOON AS PRACTICABLE.
43
Q

BOOST SERVO OFF Caution Appears.

  1. __________ — ____.
  2. FPS switch — Off.
  3. LAND AS SOON AS PRACTICABLE
A
  1. SAS/BOOST switch — Off.
  2. FPS switch — Off.
  3. LAND AS SOON AS PRACTICABLE
44
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

  1. AUTOROTATE Decelerate helicopter to stop all forward speed at treetop level.
  2. Collective adjust to maximum before main rotor contacts tree branches.
45
Q

Ditching — Power Off

  1. ________________.
  2. Cockpit doors jettison and cabin doors open prior to entering water.
  3. Apply full collective to decay rotor rpm as helicopter settles.
  4. Position cyclic in direction of roll.
  5. Exit when main rotor has stopped.
A
  1. AUTOROTATE
46
Q

FLIGHT CONTROL/MAIN-ROTOR SYSTEM MALFUNCTIONS.

WARNING
Danger exists that the main rotor system
could collapse or separate from the
helicopter after landing. Exit when main
rotor has stopped.
1. __________________.
2. __________________.
3. _______ — ________.

A
  1. LAND AS SOON AS POSSIBLE.
  2. EMER ENG(S) SHUTDOWN after landing.
  3. Rotor Brake — As required.
47
Q

ROTOR BRAKE ON Advisory Appears in Flight.

  1. Rotor brake handle — Check in detent and gage pressure at zero.
  2. Check for secondary indications of brake pad dragging (smoke, smell, noise, etc.).
    If secondary indications present:
  3. ___________________________.
    If no secondary indications present:
  4. LAND AS SOON AS PRACTICABLE.
A
  1. LAND AS SOON AS POSSIBLE.
48
Q

STABILATOR MALFUNCTION — AUTO MODE FAILURE.

  1. _____________________ to arrest or prevent nose down pitch rate.
  2. ____________________________________________________.
    If automatic control is not regained:
  3. Manually slew stabilator — Adjust to 0° for flight above 40 KIAS or full down when airspeed is below 40 KIAS. The preferred method of manually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.
  4. LAND AS SOON AS PRACTICABLE.
    If manual control is not possible, the airspeed limit indication will show the adjusted airspeed limit with a red arc.
  5. Airspeed indicator — Check and fly at or
    below red arc shown on the indicator.
  6. LAND AS SOON AS PRACTICABLE.
A
  1. _Cyclic mounted stabilator slew-up switch —
    Adjust if necessary    _ to arrest or prevent nose
    down pitch rate.
  2. _AUTO CONTROL RESET switch — Press
    ON once after establishing a comfortable airspeed.    _
    .
49
Q

UNCOMMANDED NOSE DOWN/UP PITCH ATTITUDE CHANGE

If an uncommanded nose down pitch attitude occurs:

  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 below 40 KIAS.
  5. LAND AS SOON AS PRACTICABLE.
    If an uncommanded nose up pitch attitude occurs:
  6. _______ — ________________.
  7. _________ — ______________.
  8. MAN SLEW switch — Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds below 40 KIAS.
  9. LAND AS SOON AS PRACTICABLE.
A
  1. Cyclic — Adjust as required.
  2. Collective — Maintain or increase.
  3. Cyclic mounted stabilator slew-up switch — Adjust as required to arrest nose down pitch rate.

If an uncommanded nose up pitch attitude occurs:

  1. Cyclic — Adjust as required.
  2. Collective — Reduce as required.
50
Q

STAB UNLOCKED Caution Appears.

In flight — __________________\_.

A

In flight — LAND AS SOON AS POSSIBLE.

51
Q

INTEGRATED AVIONICS SYSTEM MALFUNCTIONS

The following component failures will result in — ________________

A

The following component failures will result in — LAND AS SOON AS POSSIBLE

52
Q

FLT DIR FAIL, FD COUPLE FAIL Cautions Appear

  1. ___________________________________________________.
  2. FAILURE RESET CPTR 1 and/or CPTR 2 — Press to clear flight director cautions.
  3. Check AFCS and FCC status page. Clear BITE codes if necessary.
  4. Reengage affected mode when able.
  5. Fly affected axis manually if not restored.
A
  1. Check FD/DCP to verify which flight director modes are functioning.
53
Q

M/R DE-ICE FAULT, M/R DE-ICE FAIL, or T/R DE-ICE FAIL Caution Appears

  1. Icing conditions — Exit.
  2. BLADE DEICE POWER switch — OFF, when out of icing conditions. If vibrations increase:
  3. ________________________.
A
  1. LAND AS SOON AS POSSIBLE.
54
Q

Loss of NO. 1 or NO. 2 Generator During Blade Deice Operation

Pilot not on the controls:

  1. ___________.
  2. ____________ — ______________.
A

Pilot not on the controls:
1. EMER APU START.
2. _BLADE DE-ICE POWER switch — OFF
then ON._

UH-60M Blackhawk Helicopter (2 decks)

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