Term
Ground Evacuation
Abandon Airplane: |
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Definition
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Term
Bailout
Prepare to abandon airplane |
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Definition
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Term
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Definition
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Term
Ditching or Crash Landing
Prepare for ditching or crash landing |
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Definition
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Term
Ditching or Crash Landing
Brace for Impact |
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Definition
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Term
| Engine Shutdown Conditions |
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Definition
1.Engine Fire
2.Turbine Overheat
3.Start Valve Open light illuminates
4.Nacelle Overheat
5.Uncontrollable Power
6.Certain Propeller Malfunctions
7.An Uncontrollable rise in TIT
8.An uncontrollable drop in oil pressure
9.An uncontrollable rise in oil temperature
10.Unusual vibration or roughness
11.Throttle control cable failure
12.Excessive visible fluid leak |
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Term
| Engine Shutdown Procedure |
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Definition
1.Condition Lever "Feather" (CP)
WARNING-Throttle Cable Failure
WARNING-Pull feather to detent
2.Fire Handle "Pulled" (CP)
3.Agent "Discharged" (CP)
WARNING- If condition persists, bleed air leak.
CAUTION- On H1, do not hold discharge switch
NOTE-Agent should be discharged when condition persists after fire handle pulled. |
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Term
Auxiliary Power Unit Emergency Shutdown
Ground/In-Flight |
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Definition
1.Fire Handle "Pulled" (CP)
2.Agent "Discharged" (CP)
WARNING- If condition persists, bleed air leak.
CAUTION- On H1, do not hold discharge switch
NOTE-Agent should be discharged when condition persists after fire handle pulled. |
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Term
| Bleed Air System Failure (Ground/In-flight) |
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Definition
1. Engine bleed air switches on the affected wing – OFF
2. Bleed air divider valve switch – CLOSED
If the uncontrolled loss of bleed air cannot be isolated,
proceed as follows:
1. All engine bleed air switches – OFF
WARNING-With bleed air off, air condition is lost, thus depressurizing the aircraft.
CAUTION-If an engine bleed air regulator cannot be closed and the bleed air system is leaking, it
may be necessary to shut down the engine. |
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Term
Wing/Empennage and Wheel Well
Overtemperature (Ground/Inflight) |
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Definition
| Isolate the affected area. |
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Term
Emergency Operation of Cabin Pressurization (Ground/Inflight)
Pressure Increase |
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Definition
1. Immediately shut off engine bleed air, one at a time, until the rate of pressure increase is at a safe value.
2. Control pressure by using engine bleed air as necessary to vary the amount of conditioned air supplied for
pressurization.
3. If necessary for further control when descending, one of
the air conditioning systems can be shut down to expedite depressurization of the airplane. |
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Term
Emergency Operation of Cabin Pressurization (Ground/Inflight)
Pressure Decrease |
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Definition
1. The crew should don oxygen masks immediately while instituting a descent.
2. Descend to or maintain an airplane altitude where oxygen is not required.
3. Check for excessive cabin leakage, by checking doors, windows, hatches, and the safety valve.
4. Check for Excessive leakage by doing a bleed down check. |
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Term
| Start Valve Open Light Illumination (Ground/Inflight) |
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Definition
Ground- Ground Stop on affected engine
In-Flight- ESP |
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Term
| Engine Fire (Ground/Inflight) |
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Definition
ON THE GROUND: Move all throttles to GROUND IDLE
and ESP
INFLIGHT: ESP |
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Term
| Tailpipe Fires or Torching (Ground/Inflight) |
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Definition
During Start prior to release of Start switch- Ground Stop and Motor Engine.
If Flames spread beyond tailpipe, ESP.
Inflight- ESP
On Shutdown- Continue shutdown and notify fire dept.
CAUTION-Do not motor engine on shutdown. |
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Term
Turbine Overheat Warning
(Ground/Inflight) |
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Definition
Ground-All throttles to ground idle and affected engine to ground stop.
INFLIGHT: Retard the throttle toward FLIGHT IDLE. If condition persists, proceed with the ESP |
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Term
Nacelle Overheat Warning
(Ground/Inflight) |
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Definition
ON THE GROUND: Move all throttles to GROUND IDLE
and proceed with the ESP.
INFLIGHT: ESP |
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Term
| High TIT (Ground/Inflight) |
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Definition
ON THE GROUND: Retard the throttle toward GROUND IDLE, and place the temp datum control valve switch to the
NULL position. If this fails to eliminate the over temperature
condition, place the condition lever to GROUND STOP.
INFLIGHT: Retard the throttle toward FLIGHT IDLE, and
place the temp datum control valve switch to the NULL position. If this fails to eliminate the over temperature condition, proceed with the ESP. |
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Term
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Definition
1.Parking Brake (P)
CAUTION-Hot Brakes
2.Notify Tower (CP)
3.Tie BUS tie switch (E)
4.Feather all (CP)
5.Notify PAX (P)
WARNING-Don't Lock E and N Seats
WARNING-Evacuate area 300 ft (600 if pyro)
6. DC power switch – OFF (E)
7. SCNS power switch – OFF (N/E)
8. Chock airplane (if time and conditions permit) (LM)
WARNING-If main fire chock nose only |
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Term
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Definition
| 1. Brake select switch – EMERGENCY (CP) |
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Term
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Definition
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Term
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Definition
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Term
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Definition
1. Throttles – FLIGHT IDLE (P)
2. Condition lever – FEATHER (CP)
WARNING- If Prop malf. shut down that engine in flight idle.
3. Throttles – GROUND IDLE (P)
4. Reverse symmetrical engines and apply brakes as required. (P)
5. If required, initiate or continue with ESP after safe control of the airplane is ensured.(P) |
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Term
| Directional Control Problems with Throttles in Ground Range |
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Definition
1. Throttles – GROUND IDLE (P)
2. Condition lever – FEATHER (CP)
3. Reverse symmetrical engines and apply brakes as required. (P) |
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Term
| Takeoff Continued after Engine Failure |
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Definition
1. Maintain directional control with flight controls and engine power as necessary.
2. When safely airborne and certain that the airplane will not touch down, raise gear while accelerating to flap retraction speed.
3. After gear is up, and airspeed permits, commence flap retraction.
WARNING- Obtain 2VMCA prior to reducing flaps below 15%.
NOTE- Retract gear 3 seconds after takeoff, initiate prop feather within 6 seconds after takeoff. Retract flaps 10% for every 5knots.
4. After gear and flaps are up, continue as a normal takeoff, accelerating to three-engine climb speed. |
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Term
| Multiple Engine Power Loss/Stall/Flameout |
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Definition
1. Temperature datum control valve switches -“NULL” (E)
2. Propeller governor control switches - “MECH
GOV” (CP/E)
3. Synchrophaser master switch - OFF (E)
4. Engine bleed air switches- OFF/CLOSED (E)
5. DC bus tie switch - TIED (E)
6. SCNS/INS/ALT battery switch - Engage (E)
7. Main tank boost pump switches - ON (E)
8. Main tank crossfeed valves - CLOSED (E)
9. Generator supplying the essential AC bus - OFF (E)
10. Synchrophaser essential AC/essential avionics AC and
essential DC circuit breakers - Pulled (E) |
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Term
Prop Malfunctions During Takeoff
After Refusal Speed |
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Definition
1. Continue the takeoff, maintaining directional control with flight controls and engine power as necessary.
2. When safely airborne, raise the gear while accelerating
to two-engine inoperative air minimum control speed.
3. If RPM is out of limits, place the propeller governor control switch to MECH GOV.
a. If malfunction is eliminated, continue operation in
MECH GOV.
b. If malfunction persists, accelerate to and maintain as near 150 KTAS as possible. If immediate landing is feasible, follow the Engine Shutdown Procedure. If immediate landing is not feasible, continue with the Propeller Malfunctions During Flight procedure. |
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Term
| Propeller Low Oil Quantity Warning Light |
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Definition
1. Overspeed, underspeed, fluctuation?
2. If not, continue operation while monitoring.
3. If out of limits- Mech Gov. |
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Term
| Propeller RPM Outside Allowable Limits |
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Definition
1. Place on Mech Gov.
2. If good, continue.
3. If not, perform Pitchlock Check. |
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Term
| Pitchlock Check Procedure |
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Definition
1. Propeller governor control switch – MECH GOV(CP/E)
2. Temperature datum control valve switch for affected engine – LOCKED (E)
3. Slowly move throttle (until TIT change is noted) while
maintaining constant TAS.
A. If a change is not noted, ESP.
B. If a change is noted, continue operation. |
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Term
| Pitchlocked Propeller Operation |
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Definition
1. Propeller governor control switch – MECH GOV(CP/E)
2. Temperature datum control valve switch – LOCKED (E)
3. Engine bleed air switch – OFF (E)
4. Establish 96 to 98% RPM with throttle and/or airspeed
adjustment and continue to operate at this RPM. (P)
5. Upon reaching a suitable landing area, attain 150 KTAS(if possible). (P) |
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Term
| Propeller Fails to Feather |
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Definition
1. Reset fire handle if no indication of fire exists.
2. Hold propeller feather override button in for 30 seconds
and then pull out.
3. Attain 150 KTAS (if possible).
4. Land as soon as practical. |
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Term
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Definition
1. Reduce airspeed to 160 KIAS.
a. If the propeller brake does not engage, maintain this speed or lower (above 2 engine V MCA ) until
landing.
b. Once the propeller has stopped rotating, determine if accelerating is appropriate.
2. If acceleration is appropriate, increase airspeed in 10 knot increments to 200 KIAS. |
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Term
| TD Control Valve System Malfunction |
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Definition
1. Go to Null
2. Good? If yes go to LOCKED
3. Not good? Treat as a throttle cable malfunction. |
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Term
| TIT Indication System Malfunction |
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Definition
1.Go to Null
2. Good? Maintain fuel flow at or below other engines.
3. If not good, ESP. |
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Term
| Secondary Fuel Pump Pressure Light |
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Definition
1. Pull Ignition Control C/B
2. If light is extinguished, failure of 65% switch is indicated. Leave out and shut down after landing by replacing C/B and Ground Stop.
3. If light is not extinguished, more serious problems have occured. Replace C/B and ESP. |
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Term
| Speed Sensitive Control Failure (Sheared Shaft) |
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Definition
1. Temperature datum control valve switch – NULL (E)
2. Ignition control circuit breaker – Pull (E)
After landing, use normal ground idle only and shut down the engine as follows:
1. Ignition control circuit breaker – Reset (E)
2. Condition lever – GROUND STOP (CP) |
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Term
| Tachometer Generator Failure |
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Definition
1. Synchrophase master switch (if the affected engine is selected) – OFF/other master
2. Propeller governor control switch – MECH GOV |
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Term
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Definition
1. Advise an air traffic control facility of intentions to
dump fuel. (CP)
2. Defensive system arming switch (some airplanes) – SAFE/OFF (N)
3. Fuel system – Tank to engine. (E)
4. Dump valve switches – OPEN
5. Dump pump switches (desired tank(s)) – DUMP (E) |
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Term
| Illumination of a GEN OUT Light with GCU |
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Definition
1. Check out the volts/Freqs. Good? Leave ON.
2.No Good? Reset.
3. Reset bad? GEN DISC. |
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Term
| Illumination of an AC Bus Off Light With GCU |
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Definition
Gen Out light on also? If yes, Off and GEN DISC.
If Not,Check BUS, if looks good, just a bad indicator relay. If not, that BUS can not be restored, check bad Current Limiters at 245. |
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Term
| Illumination of the ISOL DC ON BAT/BAT DISCH Light |
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Definition
1. Select INS BUS position with the STBY ATTD switch
(some airplanes).
2. Land as soon as possible. |
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Term
| Loss of the Essential AC Bus |
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Definition
1. Antiskid switch - OFF (CP)
2. Pilot’s and copilot’s vertical reference switches - VG
3. All FCS-105 modes - Disengaged
4. Inverter switch(es) - DC BUS (some airplanes) (E)
5. All propeller governor control switches - to MECH GOV (E/CP)
6. Reduce load on the essential AC bus to the minimum.
Do not operate the auxiliary hydraulic pump. (E/CP)
7. When modified by TO 1C-130-1486, turn off one of the
INUs to reduce the load on the essential AC bus. (E)
8. Check all A, B, and C phase essential AC bus power circuit breakers on the pilot’s side circuit breaker panel and on the upper main AC distribution panel at FS 245.
Reset any tripped breakers.
9. If the circuit breakers are in, will not reset, or trip again,
start the APU and place the APU generator switch to ON. Again attempt to reset any tripped circuit breakers.
(E)
10. If circuit breakers still will not reset or trip again, isolate
the AC bus and review Section 1 to ascertain which systems have been lost. (E)
11. If an essential AC bus malfunction is experienced, the
airplane will be landed as soon as possible, regardless of the apparent success of the corrective action. (P) |
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Term
| Illumination of CP AC Instrument Sel Pwr Out Light |
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Definition
1. Check the FLT DIR NO. 2 circuit breaker – Checked/Reset (E)
2. Pilot’s and copilot’s VERT REF switches – VG (P)(CP)
3. All FCS-105 modes (some airplanes) – Disengaged
4. Copilot’s inverter – DC bus position (E) |
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Term
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Definition
1. Main tank boost pumps – ON
2. Main tank crossfeed valves – CLOSED
3. Propeller governor control switches – MECH GOV
4. APU switch – START, RUN
5. APU generator switch – ON
6. All engine generator switches – OFF or OFF/RESET
7. All FCS-105 modes – Disengaged
8. Pilot’s and Copilot’s VERT REF switch (some airplanes) – VG (P)(CP)
9. Copilot’s inverter switch (some airplanes) – DC bus (E)
10. Oil cooler flap switches – OPEN, FIXED
11. APU generator switch – OFF
12. APU switch – STOP
If fire goes out, determine the malfunctioning bus and
proceed with the Electrical Bus Isolation procedures.
13. Land as soon as possible |
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Term
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Definition
1. Engine bleed air switches on the affected wing – OFF (E)
2. Bleed air divider valve switch – CLOSED (E)
3. Sideslip the airplane to keep the fire away from the fuselage. (P)
4. Land the airplane as soon as possible. (P) |
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Term
| Fuselage Fire/Smoke and Fume Elimination |
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Definition
1. OXYGEN “ON, 100%” (ALL)
2. Autopilot “As required” (P)
3. Pressurization (on command of the pilot) “Emergency depressurization”
4. Descent “As required” (P)
5. Engine bleed air switches (if source of smoke or “OFF” (E)
fumes has not been isolated)
6. Air conditioning master switch. “AUX VENT” (E)
7. Forward escape hatch. “Open” (E)
8. Paratroop doors (on command of pilot) “Open” (LM) |
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Term
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Definition
1. Oxygen (on command of pilot) “ON, 100%” (P)
2. Pressurization “Depressurizing” (E)
3. Descent “As required” (P)
4. Air conditioning master switch “AUX VENT” (E)
5. Doors “Checked” (E)
6. Master door warning light switch “OFF” (E) |
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Term
| Inflight Release of Life Raft |
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Definition
1. Retard power and decrease airspeed. (P)
2. Lower flaps and visually check for raft.
3. Fishtail or turn slightly.
4.Land as soon as possible. (P) |
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Term
| Windshield and Window Failure |
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Definition
1. Reduce the cabin differential pressure to 10 inches of mercury or less.
2. If both panes of a windshield or flight station window crack, flight may be continued at 10 inches of mercury or less.
3. If both panes of a cargo compartment window crack,
reduce the cabin differential pressure to zero. |
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Term
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Definition
1. Oxygen - “ON, 100%” (ALL)
2. Seat belts – As required (ALL)
3. Descent – As required (P) |
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Term
Hydraulic System Failure
Loss of System Pressure |
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Definition
1. Hydraulic ENGINE PUMP switches – OFF (affected system only) (CP)
2. Hydraulic SUCTION BOOST PUMP switch – OFF (affected system only)
3. Hydraulic reservoir level – Checked (E/LM)
If Low:
4. Check for fluid loss at units being supplied by malfunctioning system. (E/LM)
5. Isolate units causing trouble if possible, re-service reservoir and return unaffected systems to normal operation. If not possible, leave pump switches OFF. |
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Term
Hydraulic System Failure
Engine Driven Pump Failure |
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Definition
1. Hydraulic engine pump switch – OFF
2. Hydraulic reservoir level – Checked (E/LM)
a. If fluid level is normal, no further corrective action is necessary.
b. If fluid level is decreasing, follow Loss of System Pressure procedure.
If the pressure exceeds 3900, find out which engine is causing this by shutting one down. If that's not the one, restart and shut down the other. |
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