Operating procedures, techniques, etc., which could result in damage to equipment if not carefully followed is a________.
Normal operation of the NTS system does not commit the propeller to feather. However, a malfunctioning NTS system may completely feather the propeller or cause the engine to:
The hydromechanical fuel control senses ________ and varies fuel flow accordingly.
C. Inlet temperature, inlet pressure altitude, RPM, and throttle position
The Temperature Datum Control Valve switches lock a fuel correction only when they are positioned at LOCKED/LKD while the:
D. Throttle is in the temperature controlling range and the fuel correction light is out
In most cases degradation of an individual thermocouple assembly would affect each circuit equally. The indicating signal will be lower (_________ degrees C) than that actual temperature experienced by each thermocouple sensing element.
B. 3.5 to 22
The engine low oil quantity warning light illuminates when an oil tank quantity level drops to approximately:
B. 4 gallons
The PROPELLER LOW OIL WARNING light and the PROP LOW OIL QUANTITY light will illuminate when the oil quantity for any propeller drops approximately ________ below normal in the pressurized sump.
B. 2 quarts
Early stage thermocouple decay may be difficult to identify, due to:
D. No change in TIT and minimal increase in fuel flow and torque
During the landing approach, ________before the throttles are retarded should give more equal power distribution on all engines.
B. Locking the TD valve
In case of power failure, the cross feed valves:
B. Hold the last energized position
The fuel low pressure warning light is turned on when fuel supply pressure at the point where fuel enters the engine pump falls below approximately ________ PSI
When operating with less than 6,000 pounds of total fuel in the main fuel tanks:
-Place the crossfeed valve switches to OPEN for tanks containing fuel
-Place the BOOST PUMP switches to ON for all tanks containing fuel
-Place the CROSSFEED SEPARATION valve switch to open
The 28 volt external DC source should have a capacity of ________ amperes.
The battery is disconnected from all DC buses except the _______ when external DC power is being used.
The engine hydraulic pump pressure warning light will illuminate whenever the pump output pressure drops below approximately 1,000 PSI or:
Engine pump switch is placed in the OFF position
The ADS control panel ramp and door control switch must be set to OFF, and the ramp manual control knob, above the ramp control panel, must be set at the ________ position before operating the pump switch on the ramp control panel.
Prior to raising the ramp, ensure that:
Locks are retracted and the ramp seal area is clear
If an individual landing gear position indicator becomes inoperative because of a faulty grounding circuit, the warning horn and warning light will indicate the position of:
The other two gear only.
After any full anti-skid braking operation above 130,000 pounds (aborted takeoff, engine-out/flaps-up landing, etc.), the approximate ground cooling time is ________ minutes.
Elevator trim tab travel is controlled by limit switches set at ________ degrees nose down and ________ degrees nose up.
The landing gear warning horn cannot be silenced until the landing gear is down and locked or the flap lever is retracted above ________ % or more.
When the flight station air conditioning is on, the bleed air pressure gage reads ________ than the actual pressure in the cross wing manifold.
6 PSI lower
Cabin differential pressure will be zero for landing. If the differential pressure is less than ________ Hg, no discomfort will be experienced if the air conditioning master switch is turned to a nonpressure position.
When the leading edge temperature reaches approximately ________ the overheat warning light for that area is energized and the light illuminates.
200 degrees F
Operation of the NESA anti-icing when outside air temperature is above ________ degrees C will increase the possibility of delamination within the NESA panels.
In any airplane configuration that could limit the normal climb capability of the airplane (such as engine out, ramp door open, etc) or operational situation where an RA maneuver is prohibited, the TCAS should be placed in:
It is possible for the (TCAS) system to issue a RA advisory command that would put the airplane outside the performance envelope
Ensure that the secure voice system mode switch is in the ________ position to provide normal operation (plain text) of the UHF radio when secure voice is not to be used.
Ensure all personnel are clear of the area between the cargo and the open ramp/door before placing the airdrop/troop jump computer-manual select switch to the:
-AD/TJ CMPTR position
- TJ-CMPTR AD-MAN position
The electrical control system of the ramp and door is inactivated when the:
Anchor line support arms are not in the up position
The LAPES/CDS switches must remain _________ in the NORMAL/OFF (guarded) position except when required to be in ARM for operational check or mission requirements.
When 100 percent oxygen is being supplied, _________ oxygen is consumed per person as altitude ________.
The AERP system ________ protect the user against ammonia fumes or carbon monoxide gas and _______ be used without an oxygen source in an oxygen deficient atmosphere
Will not, shall not
Do not enter/exit from the ________ side of the nose wheel well due to possible hazard of venting liquid oxygen.
The high pressure of the Halon fire extinguisher can spread a class ________ fire.
Do not operate ________ lights for prolonged periods while the airplane is on the ground.
During ground operations, avoid direct viewing of the strobe lights within a distance of________ feet to prevent eye damage.
The CVR is operational anytime the ________ bus is powered by any source other than external power.
With the escape ladder installed, it is impossible to exit the airplane from the center escape hatch using the ________ side of the ladder
In emergencies, MIL-L-7808 and MIL-L-23699 may be mixed. The amount of emergency oil added should not exceed ________ tank capacity.
During the BEFORE EXTERIOR INSPECTION and before any electrical power is applied to the airplane, the engineer will:
-Ensure that all locking pins are removed from doors and hatches
-Check the form 781
-Ensure that all aircraft switches and circuit breakers are in their normal shutdown position
While accomplishing the POWER ON INSPECTION, if a light in the overheat test panel fails to illuminate during testing, bleed air systems:
Should not be pressurized until proper inspection and repairs have been made
During the POWER ON INSPECTION, movement of the flaps is essential at this time to enable detection of ________ or malfunctions during the walk-around inspection.
Do not ________ or open the ground test valve if ramp hydraulic actuators are preloaded or cargo loading operations are in progress.
Deplete hydraulic pressure
Depletion of the emergency brake hydraulic system pressure with the brake select switch in normal is an indication of a(n) ________ failure.
Emergency brake selector valve
During EXTERIOR INSPECTION, if not previously checked by maintenance, a work stand/ladder will be required to check:
-External tank caps
Quick Don oxygen mask system is the _______ use equipment unless dictated otherwise
After moving the condition lever to ground stop, do not move the lever from this position until ________.
Engine rotation has stopped
During low air density conditions (high temperature above approximately 28 degrees C/high altitude), if the engine accelerates smoothly with no indication of stall and TIT limits are not exceeded, time to stabilize on speed is ________ seconds.
The throttles must not be moved out of the ________ detent during engine starting.
During engine start, a positive indication of hydraulic pressure must be observed by:
The time the engine is on speed
You must have positive oil pressure on the engine and reduction gear by _________ percent rpm, or immediately discontinue the start.
A positive hydraulic pressure indication must be noted by the time the engine is on speed. Normal operating pressure should be indicated within ________ after on speed.
If start TIT is less than _________degrees C, record in AFTO Form 781. Maintenance action is required prior to flight.
If auxiliary feather motor operation is not indicated for a propeller:
The malfunction will be corrected prior to flight
When down-shifting from normal to low-speed ground idle, the engineer will monitor the engine instruments and be prepared to shut down the engine by placing the condition lever to GROUND STOP if the temperature exceeds ________ degrees C or a stall occurs.
If a stop, sudden or severe braking application has occurred during turns:
Record in Form 781
The use of brakes during reverse taxiing should be ________ to prevent the airplane from setting on the tail.
Do not hold the ice detector TEST switch in the No. 2 or No. 3 position longer than five seconds. The test cycle may be repeated once, but then wait ________ minutes for the ice detector to cool before performing this test again.
With engines running, never operate the propeller anti-icing or de-icing system for more than ________ cycles while the airplane is on the ground.
If the BLADE DE-ICING ammeter falls below________, do not fly into icing conditions.
Observe engine torque and TIT when placing each ________ switch in the ON position when accomplishing the Before Takeoff checklist.
ENGINE INLET AIR DUCT ANTI-ICING
Main tank boost pump switches ________ be turned off in-flight unless directed by a specific procedure in the flight manual
Above crossover, if the engine instruments are not similar in ________, with throttles aligned, a propulsion system malfunction may exist.
Fuel flow, TIT, or torque
If indicated torque exceeds 19,600 inch pounds:
An entry in the FORM 781 is required noting the highest torque value observed and describing the runway and/or flight conditions
Never place the throttles in the TAKEOFF position without monitoring the ________, since it is possible to exceed the maximum allowable torque.
The minimum flap retraction speed for a maximum effort takeoff is:
Obstacle clearance speed plus 10 knots
For GCAS ESCAPE MANEUVERS; Crewmembers will back up the pilot who is performing the escape maneuver. The __________ and ____________ the airplane will confirm escape maneuver is being properly flown.
Flight Engineer, Pilot not flying
The PF will advise the engineer of the landing field conditions:
when initiating the Descent Checklist
New TOLD will be required any time gross weight changes 5,000 pounds or more, outside temperature changes ________ degrees C or more, or pressure altitude changes 1,000 feet or more.
Higher than normal ________ system pressure may be encountered in-flight.
At high airspeeds, abrupt movement of the throttles into the ground range could result in:
The two common types of wind shear phenomena found on final approach are:
Decreasing headwind, increasing headwind
During landing, at the first indication of directional control difficulties during reversing, immediately:
Return all throttles to GROUND IDLE
The nose gear must be on the ground prior to _________.
When moving the flaps at low airspeed, an asymmetrical flap may go undetected until near or above ___________.
If a go-around is accomplished, retracting flaps from 100 to 50 percent will:
Increase stall speed
The flight engineer should monitor engine instruments during shutdown for:
Zero fuel flow and TIT and RPM decrease
If NTS advisory lights do not illuminate when shutting down engines from low-speed ground idle:
A recheck of the NTS system must be made before the next flight
Regardless of specific emergency encountered:
-Maintain airplane control
-Analyze the situation
-Take coordinated corrective action
When pulling the condition lever to FEATHER, pull it all the way to the detent to assure that the propeller is fully feathered when the engine fuel is shut off. If the lever is left at a mid-position, and NTS is inoperative, a(n)
Engine decoupling is possible
In the event of a throttle control cable failure, ________ attempt to move the condition lever due to the possibility of cable fouling.
If on cross feed during ENGINE SHUTDOWN PROCEDURE, ________ before shutting off the fuel boost pump and closing the cross feed valve for the affected engine.
Ensure source of fuel to operate engines
If cabin pressure increases at an excessive rate and cannot be reduced by normal means then:
-Immediately shut off engine bleed air, one at a time, until the rate of pressure increase is at a safe value
-Control pressure by using engine bleed air as necessary to vary the amount of conditioned air supplied for pressurization
-If necessary for further control when descending, one of the air conditioning systems can be shut down to expedite depressurization of the airplane
If either the left or right wheel well overheat light illuminates after takeoff and the condition persists after isolation procedures have been accomplished, it may be indicative of:
The correct procedure for high TIT on the ground is:
Move affected throttle to "ground idle" and place the affected engine TD switch to NULL. If condition persist place condition lever to "ground stop"
If a tailpipe fire occurs in-flight, follow the ENGINE SHUTDOWN PROCEDURE. If the fire persists:
The airplane should be accelerated as rapidly as possible, not exceeding maximum airspeed
If a turbine overheat occurs in-flight:
Retard the throttle toward FLIGHT IDLE. If the condition persists, proceed with the ENGINE SHUTDOWN PROCEDURE
During GROUND EVACUATION; if pyrotechnics are loaded on the airplane, evacuate a minimum of ______ feet from the airplane
Do not exceed ________ KIAS with the ramp (or ramp and cargo door) open regardless of whether the paratroop doors are open or closed or the position of the air deflectors.
Maximum airspeed with the paratroop doors open and locked is:
If parking brake handle does not properly retract and requires additional force to fully seat:
Document in Form 781
If aborting for a propeller malfunction or any other malfunction which could result in asymmetric power causing directional control problems when the throttles are placed in the ground range, shut down the affected engine while throttle is in:
For malfunctions which result in asymmetric thrust, the airplane will attempt to ________ the malfunctioning power plant during airplane acceleration
For a takeoff continued after engine failure, flap retraction should be accomplished in ______ percent increments with airspeed increasing approximately ________ knots between retraction increments.
In all combinations of two engine failures, monitor ________ to keep it within the range of available output.
Two-engine operation above ________ pounds gross weight or at high density altitude is marginal.
If a propeller malfunction occurs after refusal speed and there is no indication of fire, it is recommended that the engine be allowed to run until at least ________ is reached.
Two-engine inoperative air minimum control speed
During pitchlocked propeller operation, the engine should be shutdown when
-Reaching 150 KTAS
-RPM cannot be maintained with the throttles
-Reaching a suitable landing area
If a propeller fails to feather in flight, it is critical to restore oil to the ________ of the windmilling propeller as soon as possible
For PROPELLER BRAKE FAILURE; if the propeller does counter-rotate, and the procedures are ineffective:
Land as soon as practical
If throttle control cable failure is suspected, do not move the throttle prior to engine shutdown. To do so could cause:
The propeller to go into reverse pitch or to full power
Any time an IGNITION CONTROL circuit breaker is pulled on an inboard engine, the ________ for that engine is inoperative
Ice detection system
A sheared shaft on the speed sensitive control with the throttle above 65 degrees travel may be indicated by:
-Momentary illumination of the SECONDARY FUEL PUMP PRESSURE light
-ELECTRONIC FUEL CORRECTION light
-TIT will not exceed start limiting temperature of 830 degrees C
In case of loss of oil pressure:
Shut down the engine by using ENGINE SHUTDOWN PROCEDURE
Following a negative G condition, closely monitor gearbox and engine oil pressure for ________.
A negative G condition may allow air to enter the engine oil supply line resulting in a loss of oil pressure approximately ________ later due to oil pump cavitation.
30 to 90 seconds
If a Tachometer Generator Failure occurs on the engine selected as the master engine, first
Place the synchrophaser master switch to OFF/other master
When operating in tank-to-engine position with an inoperative fuel boost pump, avoid:
Rapid acceleration or nose low attitudes
Do not select ________ unless the crossfeed system is pressurized by operating fuel boost pumps in other tanks.