1C-130H-1 Section 3 Flashcards
“land as soon as possible” expectations
Declare an emergency
Land at the nearest suitable airfield
“Land as soon as practical” expectations
Mission is to be terminated
An immediate landing at the nearest adequate airfield may not be necessary
Ground evacuation alarm bell signal
One long sustained ring
Bailout alarm bell signal
Prepare to bailout - three short rings
Bailout - one long sustained ring
Ditching or crashing landing alarm bell signal
Prepare to ditch/crash land - six short rings
Brace for impact - one long sustained ring
12 Engine shutdown conditions
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
Engine shutdown procedure
CONDITION LEVER “FEATHER” (CP)
FIRE HANDLE “PULLED” (CP)
AGENT “DISCHARGED” (FOR FIRE OR NACELLE OVERHEAT)
- land as soon as practical
If during the ESP, the fire or nacelle overheat condition persists after the first fire bottle is discharged, what should you do?
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
APU EMERGENCY SHUTDOWN
FIRE HANDLE “PULLED” (E)
AGENT “DISCHARGED” (FOR FIRE) (E)
If during the APU EMERGENCY SHUTDOWN, the fire condition persists what should you do?
Isolate #1 and #2 by placing bleed air switches to OFF and closing the divider valve
If fire continues, discharge remaining bottle
Possible indicators of a bleed air leak:
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
Can you maintain aircraft pressurization with the bleed air switches turned OFF?
No, because airflow to both air conditioner units is lost
Should you open the APU bleed air valve after landing with an uncontrolled loss of bleed air that could not be isolated?
No, you could repressurize the leaking area
Steps for wing overtemp indication:
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
Can a single air condition unit, augmented with under floor heat, maintain maximum cabin differential pressure?
Yes
Uncontrolled cabin pressure increase steps and cause:
Will only occur with a stuck outflow valve
- Turn off engine bleed air, one at a time
- Control px by turning bleed air on/off
- Shut down one air conditioning system if necessary to expedite depressurization
START VALVE OPEN LIGHT illuminated on the ground:
GROUND STOP and close the respective bleed air valve
ENGINE FIRE on the ground:
GROUND IDLE, ESP
Tailpipe fire/torching during start:
GROUND STOP, motor the engine
Note: if flames spread beyond the tailpipe, ESP
Tailpipe fire during flight:
Indicated by loss of oil quantity and/or heavy smoke
Monitor during flight and ESP prior to landing
Turbine overheat on the ground:
GROUND IDLE/GROUND STOP
Turbine overheat in the air:
Retard throttle toward FLIGHT IDLE
If condition persists, ESP
Nacelle overheat warning on the ground:
GROUND IDLE, ESP
High TIT on ground:
GROUND IDLE
TD switches NULL
if condition persists, GROUND STOP
High TIT in flight:
FLIGHT IDLE
TD switches to NULL
if condition persists, ESP
GROUND EGRESS
- Set parking brake (P)
- Notify tower (CP)
- DC bus tie switch - TIED (E)
- FEATHER (CP)
- Evacuation command (P)
- DC power switch - OFF (E)
- SCNS power switch - OFF (N/E)
- Chock airplane (LM)
During multiple engine power loss, why are the TD switches placed to NULL?
To remove the starting limiting fuel take that can occur in the AUTO position (at or below 94%, TIT limited to 830)
MULTIPLE ENGINE POWER LOSS/STALL/FLAMEOUT
TEMPERATURE DATUM CONTROL VALVE SWITCHES “NULL” (E)
PROPELLER GOVERNOR CONTROL SWITCHES “MECH GOV” (CP/E)
Note: land as soon as possible
With the loss of essential DC power, the engine bleed air regulator valves are fail safe: open or closed?
Closed
During multiple engine power loss/stall/flameout, why is the DC bus tied?
To power the essential DC bus, because the engine inlet air duct anti-icing valves will de-energize open, and may prevent engine recovery
For propeller malfunctions after takeoff, if no fire indications are present it is recommended to allow the engine to run until reaching what airspeed?
Vmca2
What is considered an uncontrolled propeller over speed?
Greater than 105%
Prop low oil light
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
Pitchlocked propeller
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
Prop fails to feather
Reset fire handle if no fire indication exists
Hold feather override button in for 30 seconds and then pull out
150 KTAS if possible
Decoupled propeller
Near zero torque, TIT, and fuel flow
ESP
Prop brake failure
160 KIAS, not below Vmca2
If needed, accelerate in 10 knot increments to a maximum of 200 KIAS
Throttle control cable failure
Indicated by:
- Throttle moves independently of pilot input
- Throttle frozen or binding
- Power unrelated to throttle position
Shut down using fire handle
TD system malfunction
NULL
LOCKED if fixed
Pull fire handle to shut down if not fixed
SEC FUEL PUMP PRESS light above 65%
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
SSC failure (sheared shaft)
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
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:
2 minutes
10 seconds
Tach generator failure
Indicated by:
- decrease or fluctuation of RPM and/or torque
Synchrophaser OFF
MECH GOVE
If cross feeding is being accomplished with the dump pumps, what should you be cognizant of?
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
An external fuel tank fuel level control valve failure may be indicated by:
Both boost pumps indicating less than 28 PSI
Fuel quantity indicator failure on 84-0206 and up will be indicated by:
Blank display, E6, E8, E9 codes, or totalizer going blank
Two things that you shouldn’t do with a known or suspected fuel leak:
Use reverse thrust on landing
Jettison or dispense flares
Prior to performing any procedure which removes all AC power, how should the fuel system be configured?
Tank to engine
Generator out light with normal frequency, voltage, and load:
Power indicator relay or TRU failure
Leave the generator on and monitor freqs, volts, and load
Generator out light with freqs, volts, but no load:
Indicates a de-energized generator contact
Place generator to OFF and monitor volts and freqs
Generator out light with no freqs, volt, or load:
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)
If phase voltage drops below __ volts for __ seconds or exceeds __ volts for __ seconds, the generator out light will illuminate
95 volts for 4 seconds
130 volts for 5 seconds
Generator failure on the ground
GROUND STOP
Hold the GEN DISC switch to DISC for approximately:
2 seconds
What should you do if a generator cannot be disconnected in flight?
ESP
LH DC BUS TRU FAULT INDICATOR
Deactivate LAIRCM by pulling the LH DC BUS TRU CB to prevent overheating or smoke and fumes
Indications of loss of essential AC bus:
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
Illumination of the ISOL DC ON BAT/BAT DISCH light and/or battery voltage of 24 or less is an indication of:
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
Inflight door warning
Oxygen “ON, 100%” (on command of pilot)
Depressurize
Descend
Aux Vent
Check doors
Master door warning light switch “OFF”
Cabin pressure for flight station windshield cracks or single pane in cargo compartment
10 in hg
Cabin pressure for both panes of cargo compartment window cracked
Zero in hg
If utility or booster hydraulic system pressure exceeds _____ PSI, do not turn off the hydraulic pump switches
3450
If hydraulic system pressure exceeds _____ PSI, follow the cruise engine shutdown procedure on an engine supplying the system
3900
Suction boost pump failure: if system pressure is less than _____ PSI, or hydraulic fluid level is decreasing, follow loss of system pressure procedure
2500
Failure of the utility hydraulic system will result in loss of:
Normal landing gear extension/retraction
Normal brakes
Nose wheel steering
Half the flight controls
Loss of the aux hydraulic system will result in the loss of:
Cargo door and ramp
Emergency brakes
Emergency nose gear extension
Actions after a hard over maneuver in the flight controls:
Place the control boost switches to OFF
Prepare to immediately adjust trim
Recommended control inputs and airspeed during an elevator control system failure:
Inboard engines for pitch
Outboard engines for airspeed
170 KIAS
For aileron and rudder trip runaway:
Hold trim switch in the opposite direction
Pull the CB
Elevator trim runaway
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
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
10%
Two alternate methods for flap operation:
Overriding the flap selector valve on the utility hydraulic panel
Mechanical operation of the flaps
Prior to landing with a known or suspected landing gear malfunction, if time permits, the engineer will visually inspect to confirm that:
The bottom of the ball nuts contact the bumper stops
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:
UP
Pull the landing gear control CB
5 alternate landing gear operation methods:
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
If the electrical landing gear selector button required holding to lower the gear, hydraulic pressure will not be available for:
Nose wheel steering
Nose gear free fall flight parameters:
At or below 120 KIAS, but not below Vmca
Pull the handle
Accelerate quickly, but do not exceed 165 KIAS
How many chains and devices are required if the MLG tie down fixture is not available?
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
Traffic pattern airspeeds when landing with two engines inoperative:
Downwind and base 160 KIAS
Turn to final 150 KIAS or approach speed, whichever is higher
Recommended runway length and max weight for windmill taxi start
7000’
135,000 lbs
Airspeed and termination distance for windmill taxi start
100 KIAS until 4,000’ remaining
