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C-130H > 1C-130H-1 Section 3 > Flashcards

1C-130H-1 Section 3 Flashcards

1
Q

“land as soon as possible” expectations

A

Declare an emergency

Land at the nearest suitable airfield

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2
Q

“Land as soon as practical” expectations

A

Mission is to be terminated

An immediate landing at the nearest adequate airfield may not be necessary

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3
Q

Ground evacuation alarm bell signal

A

One long sustained ring

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4
Q

Bailout alarm bell signal

A

Prepare to bailout - three short rings

Bailout - one long sustained ring

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5
Q

Ditching or crashing landing alarm bell signal

A

Prepare to ditch/crash land - six short rings

Brace for impact - one long sustained ring

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6
Q

12 Engine shutdown conditions

A 
Certain propeller malfunctions
Uncontrollable rise in TIT
Uncontrollable rise in oil temperature 
Uncontrollable drop in oil pressure
Uncontrollable power
Unusual vibration or roughness
Nacelle overheat
Turbine overheat
Throttle control cable failure 
START VALVE OPEN light illuminates
Engine fire
Excessive visible fuel leak
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7
Q

Engine shutdown procedure

A

CONDITION LEVER “FEATHER” (CP)

FIRE HANDLE “PULLED” (CP)

AGENT “DISCHARGED” (FOR FIRE OR NACELLE OVERHEAT)

  • land as soon as practical
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8
Q

If during the ESP, the fire or nacelle overheat condition persists after the first fire bottle is discharged, what should you do?

A

Isolate the wing by:

Placing engine bleed air switch to OFF

Closing the divider valve

If condition persists, discharge the remaining bottle on command of the pilot

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9
Q

APU EMERGENCY SHUTDOWN

A

FIRE HANDLE “PULLED” (E)

AGENT “DISCHARGED” (FOR FIRE) (E)

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10
Q

If during the APU EMERGENCY SHUTDOWN, the fire condition persists what should you do?

A

Isolate #1 and #2 by placing bleed air switches to OFF and closing the divider valve

If fire continues, discharge remaining bottle

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11
Q

Possible indicators of a bleed air leak:

A 
Fire warning lights
Low torque
Erratic engine instruments
Erratic electrical equipment
Wing overheat
Reduced bleed air manifold pressure

Note: bleed air failure is a land as soon as possible condition

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12
Q

Can you maintain aircraft pressurization with the bleed air switches turned OFF?

A

No, because airflow to both air conditioner units is lost

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13
Q

Should you open the APU bleed air valve after landing with an uncontrolled loss of bleed air that could not be isolated?

A

No, you could repressurize the leaking area

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14
Q

Steps for wing overtemp indication:

A

Wing anti-icing - OFF

If condition persists after 1 minute…

Affected wing bleed air switches - OFF

Bleed air divider valve - closed

APU/external air - OFF

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15
Q

Can a single air condition unit, augmented with under floor heat, maintain maximum cabin differential pressure?

A

Yes

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16
Q

Uncontrolled cabin pressure increase steps and cause:

A

Will only occur with a stuck outflow valve

  1. Turn off engine bleed air, one at a time
  2. Control px by turning bleed air on/off
  3. Shut down one air conditioning system if necessary to expedite depressurization
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17
Q

START VALVE OPEN LIGHT illuminated on the ground:

A

GROUND STOP and close the respective bleed air valve

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18
Q

ENGINE FIRE on the ground:

A

GROUND IDLE, ESP

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19
Q

Tailpipe fire/torching during start:

A

GROUND STOP, motor the engine

Note: if flames spread beyond the tailpipe, ESP

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20
Q

Tailpipe fire during flight:

A

Indicated by loss of oil quantity and/or heavy smoke

Monitor during flight and ESP prior to landing

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21
Q

Turbine overheat on the ground:

A

GROUND IDLE/GROUND STOP

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22
Q

Turbine overheat in the air:

A

Retard throttle toward FLIGHT IDLE

If condition persists, ESP

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23
Q

Nacelle overheat warning on the ground:

A

GROUND IDLE, ESP

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24
Q

High TIT on ground:

A

GROUND IDLE

TD switches NULL

if condition persists, GROUND STOP

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25
Q

High TIT in flight:

A

FLIGHT IDLE

TD switches to NULL

if condition persists, ESP

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26
Q

GROUND EGRESS

A
  1. Set parking brake (P)
  2. Notify tower (CP)
  3. DC bus tie switch - TIED (E)
  4. FEATHER (CP)
  5. Evacuation command (P)
  6. DC power switch - OFF (E)
  7. SCNS power switch - OFF (N/E)
  8. Chock airplane (LM)
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27
Q

During multiple engine power loss, why are the TD switches placed to NULL?

A

To remove the starting limiting fuel take that can occur in the AUTO position (at or below 94%, TIT limited to 830)

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28
Q

MULTIPLE ENGINE POWER LOSS/STALL/FLAMEOUT

A

TEMPERATURE DATUM CONTROL VALVE SWITCHES “NULL” (E)

PROPELLER GOVERNOR CONTROL SWITCHES “MECH GOV” (CP/E)

Note: land as soon as possible

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29
Q

With the loss of essential DC power, the engine bleed air regulator valves are fail safe: open or closed?

A

Closed

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30
Q

During multiple engine power loss/stall/flameout, why is the DC bus tied?

A

To power the essential DC bus, because the engine inlet air duct anti-icing valves will de-energize open, and may prevent engine recovery

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31
Q

For propeller malfunctions after takeoff, if no fire indications are present it is recommended to allow the engine to run until reaching what airspeed?

A

Vmca2

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32
Q

What is considered an uncontrolled propeller over speed?

A

Greater than 105%

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33
Q

Prop low oil light

A

Check for overspeed, underspeed, or fluctuation

If RPM is within limits, continued operation is permissible

If RPM is out of limits, place in MECH GOV

If out of limits in MECH GOV, perform pitch lock check

34
Q

Pitchlocked propeller

A

Operation in an underspeed condition is desirable (96-98%)

Maintain a constant TAS to maintain constant RPM

150 KTAS if decoupled

Do not allow RPM to decrease below 96%, ESP

35
Q

Prop fails to feather

A

Reset fire handle if no fire indication exists

Hold feather override button in for 30 seconds and then pull out

150 KTAS if possible

36
Q

Decoupled propeller

A

Near zero torque, TIT, and fuel flow

ESP

37
Q

Prop brake failure

A

160 KIAS, not below Vmca2

If needed, accelerate in 10 knot increments to a maximum of 200 KIAS

38
Q

Throttle control cable failure

A

Indicated by:

  • Throttle moves independently of pilot input
  • Throttle frozen or binding
  • Power unrelated to throttle position

Shut down using fire handle

39
Q

TD system malfunction

A

NULL

LOCKED if fixed

Pull fire handle to shut down if not fixed

40
Q

SEC FUEL PUMP PRESS light above 65%

A

May be caused by failure of:

  • engine-driven fuel pump
  • pressure switch
  • paralleling valve stuck closed
  • failure of 65% switch in SSC

Pull the ignition control CB

41
Q

SSC failure (sheared shaft)

A

Indicated by:

  • SEC fuel pump press light
  • Electronic fuel correction light (>65% RPM)
  • TIT start limiting of 830 (>65% RPM)

TD NULL

Pull ignition control CB

42
Q

Following a negative G condition, monitor GB and engine oil pressure for:

If a loss of oil pressure occurs, ESP if oil pressure doesn’t return to normal within:

A

2 minutes

10 seconds

43
Q

Tach generator failure

A

Indicated by:

  • decrease or fluctuation of RPM and/or torque

Synchrophaser OFF

MECH GOVE

44
Q

If cross feeding is being accomplished with the dump pumps, what should you be cognizant of?

A

Fuel transferring to uncommanded tanks. Anytime the dump manifold is pressurized, fuel can transfer into any tank if there is a failure of the check valve, refuel shutoff valve, or fuel line

45
Q

An external fuel tank fuel level control valve failure may be indicated by:

A

Both boost pumps indicating less than 28 PSI

46
Q

Fuel quantity indicator failure on 84-0206 and up will be indicated by:

A

Blank display, E6, E8, E9 codes, or totalizer going blank

47
Q

Two things that you shouldn’t do with a known or suspected fuel leak:

A

Use reverse thrust on landing

Jettison or dispense flares

48
Q

Prior to performing any procedure which removes all AC power, how should the fuel system be configured?

A

Tank to engine

49
Q

Generator out light with normal frequency, voltage, and load:

A

Power indicator relay or TRU failure

Leave the generator on and monitor freqs, volts, and load

50
Q

Generator out light with freqs, volts, but no load:

A

Indicates a de-energized generator contact

Place generator to OFF and monitor volts and freqs

51
Q

Generator out light with no freqs, volt, or load:

A

Place generator to RESET then OFF

If freqs and volts are normal on 3 phases, resume normal operation

If no freqs or volts after RESET on 3 phases, the generator has failed (disconnect)

If freqs and volts are indicated, but volts peak then drop to zero, an over voltage or feeder fault condition occurred (disconnect)

52
Q

If phase voltage drops below __ volts for __ seconds or exceeds __ volts for __ seconds, the generator out light will illuminate

A

95 volts for 4 seconds

130 volts for 5 seconds

53
Q

Generator failure on the ground

A

GROUND STOP

54
Q

Hold the GEN DISC switch to DISC for approximately:

A

2 seconds

55
Q

What should you do if a generator cannot be disconnected in flight?

A

ESP

56
Q

LH DC BUS TRU FAULT INDICATOR

A

Deactivate LAIRCM by pulling the LH DC BUS TRU CB to prevent overheating or smoke and fumes

57
Q

Indications of loss of essential AC bus:

A

Loss of autopilot (if in use)

Heading indicator failure

ESS AVI bus off light

Loss of synchrophaser

Malfunctioning nav equipment

Illumination of th CPs AC instrument SEL PWR OUT light

Loss of pilot’s TCAS display

58
Q

Illumination of the ISOL DC ON BAT/BAT DISCH light and/or battery voltage of 24 or less is an indication of:

A

RCR failure

Note: illumination of the light, for a max of 25 seconds, is normal when high loads are placed on the essential AC or DC bus

59
Q

Inflight door warning

A

Oxygen “ON, 100%” (on command of pilot)

Depressurize

Descend

Aux Vent

Check doors

Master door warning light switch “OFF”

60
Q

Cabin pressure for flight station windshield cracks or single pane in cargo compartment

A

10 in hg

61
Q

Cabin pressure for both panes of cargo compartment window cracked

A

Zero in hg

62
Q

If utility or booster hydraulic system pressure exceeds _____ PSI, do not turn off the hydraulic pump switches

A

3450

63
Q

If hydraulic system pressure exceeds _____ PSI, follow the cruise engine shutdown procedure on an engine supplying the system

A

3900

64
Q

Suction boost pump failure: if system pressure is less than _____ PSI, or hydraulic fluid level is decreasing, follow loss of system pressure procedure

A

2500

65
Q

Failure of the utility hydraulic system will result in loss of:

A

Normal landing gear extension/retraction

Normal brakes

Nose wheel steering

Half the flight controls

66
Q

Loss of the aux hydraulic system will result in the loss of:

A

Cargo door and ramp

Emergency brakes

Emergency nose gear extension

67
Q

Actions after a hard over maneuver in the flight controls:

A

Place the control boost switches to OFF

Prepare to immediately adjust trim

68
Q

Recommended control inputs and airspeed during an elevator control system failure:

A

Inboard engines for pitch

Outboard engines for airspeed

170 KIAS

69
Q

For aileron and rudder trip runaway:

A

Hold trim switch in the opposite direction

Pull the CB

70
Q

Elevator trim runaway

A

Hold the trim switch in the opposite direction

Place the elevator trim switch to OFF

Place the elevator trim switch in the EMER position and use the backup trim for operation of the trim tab

71
Q

During an outboard flap failure that results in binding, do not attempt to move the flaps. If movement is necessary, move the flaps in ____ increments

A

10%

72
Q

Two alternate methods for flap operation:

A

Overriding the flap selector valve on the utility hydraulic panel

Mechanical operation of the flaps

73
Q

Prior to landing with a known or suspected landing gear malfunction, if time permits, the engineer will visually inspect to confirm that:

A

The bottom of the ball nuts contact the bumper stops

74
Q

If a hydraulic leak is the cause of the malfunction, or hydraulic pressure was lost after repositioning the landing gear lever, immediately place the landing gear lever in the ____ position and:

A

UP

Pull the landing gear control CB

75
Q

5 alternate landing gear operation methods:

A

Overriding the landing gear selector valve

Manual gear extension (main gear)

Emergency nose gear hydraulic extension

Nose landing gear manual extension (free fall)

Emergency manual main gear extension

76
Q

If the electrical landing gear selector button required holding to lower the gear, hydraulic pressure will not be available for:

A

Nose wheel steering

77
Q

Nose gear free fall flight parameters:

A

At or below 120 KIAS, but not below Vmca

Pull the handle

Accelerate quickly, but do not exceed 165 KIAS

78
Q

How many chains and devices are required if the MLG tie down fixture is not available?

A

1X 25,000 lb. device and 3X 25,000 lb. chains per pair of struts

OR

3X 10,000 lb. devices and 7X 10,000 lb. chains per pair of struts

79
Q

Traffic pattern airspeeds when landing with two engines inoperative:

A

Downwind and base 160 KIAS

Turn to final 150 KIAS or approach speed, whichever is higher

80
Q

Recommended runway length and max weight for windmill taxi start

A

7000’

135,000 lbs

81
Q

Airspeed and termination distance for windmill taxi start

A

100 KIAS until 4,000’ remaining

C-130H (6 decks)

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