110 terms

Section III N/W/C

Engine Fire During Ground Operations
W 3-4 If the Lh or RH ENG FIRE PUSH annunciator illuminates, the fire has spread beyond the tailpipe. Accomplish the ---- checklist.
Anti-skid protection, emergency
C 3-4 ----is not available during --- braking.
crew and passengers, safely evacuate
W 3-5 Do not endanger ---- in an attempt to accomplish all items of this checklist. Primary considerations should be given to ---- the aircraft. (EGE)
base, 4.5 feet, landing gear, caution, personal injury.
The --- of the escape hatch is --- above the ground with the --- extended. Use --- to avoid ---- when using this exit.
brakes, anti-skid, off, braking, pilot's, co-pilot's, emergency braking system.
W 3-9 If a malfunction occurs with an associated loss of______, immediately place the _________switch to the _____ position and attempt _________ from both the ________ and______ position. If braking is not restored, use the __________________.
malfunction, a loss of brakes, ANTISKID FAIL, complete loss of normal braking.
W 3-9/10 It is possible for an anti-skid ___________ to occur resulting in ____________ without an associated ___________light on the main annunciator panel. The pilot's only indication may be the __________.
speed brake, reset, neutral, weight
W 3-9 When accomplishing an abort, extend the _____________, do not _______ the flaps, and ensure the yoke is in the ________ position in order to maintain ________ on the main wheels
and assist braking efficiency.
exceeding, landing/stopping
W 3-9 Failure to maximum brake properly will result in___________ the computed
___________________ distance.
safe taxi speed, traction, effective braking, directional
W 3-9 Do not attempt to turn off the runway before slowing to a __________. Attempting high speed turns may result in reduced __________, lack of _________ and loss of _____________ control.
brakes, tire, differential, brakes, antiskid, off, braking, emergency
W 3-10 It is possible for loss of _______ to occur following a_____ failure due to the__________ in main wheel speeds. If loss of ______ occur, immediately place the ________switch to the ____ position and attempt ________ from both the pilot's and copilot's position. If braking is not restored, use the ____________ brake system.
possible damage to the wheel well area
W 3-10 C If gear is retracted with a blown tire, _________________ could occur.
bleed air, off, ACM off 2200 clear of obstacles higher
W 3-10/11 If failure/fire (page 3-11) occurs immediately after takeoff when using the ACM OFF TAKEOFF PROCEDURES, the __________ selector must remain the _____ position to assure aircraft performance. The _____ must remain _____ until _______ feet AGL or ______________, whichever is _____ to assure aircraft performance.
trim, laterally, roll, flap retraction, lateral, degrade, climb, cruise, acceleration
W 3-10 It is essential to _____ the aircraft ______ using the ___ trim tabs if single-engine climb gradients are to be met for the climb to altitude after ____________. Holding any _____ control input will significantly _______ single-engine _____, _____, and _____________ performance.
400 ft AGL, clear of obstacles
N 3-10/11 Securing engines should not be accomplished prior to reaching ____________, and ______________.
pilot monitoring, pilot flying
N 3-12 Normally the ___________ will actuate switches after the __________ confirms selection of the proper switch.
fails, possible burn through of the fire detect system, fire
C 3-12 If the fire warning test _____, this indicates _________. A _____ may still exist although no fire warning indications will be present.
throttles, cable, loss, failure, engine shutdown, to retard to idle, flames out, Fuel/Hydraulic valve close switch, Engine Shutdown during Flight
C 3-12 Binding ________ may indicate an impending throttle linkage ______ break with subsequent ____ of throttle authority. Throttle linkage cable _______ usually results in an uncommanded ________; however, it is possible for the engine to remain at the power setting at time of failure, or _______ to ____. If the throttle linkage cable brakes and the engine
______, or if necessary to control the aircraft due to an engine stuck at a high power setting, shut down the engine using the _____________, then accomplish the
__________ checklist.
pilot's prerogative, airspeeds, configurations
N 3-13/24/33/34 These procedures are not intended to limit the ______ to alter ______ and _______ to meet existing conditions.
fuel crossfeed, unless, contamination
N 3-14 Consider the use of ___________ to balance the fuel load, _______ fuel system __________ is suspected.
turbine rotor shaft, loud report, possible, restart, damage
C 3-14 When engine failure is due to a failed _________, a _________ will be audible. Engine restart is not ______, and any attempt to______ could cause further engine or engine component ____.
autopilot, disengage to the autopilot
W 3-14 The potential exists for __________ induced oscillations about the roll axis during asymmetric thrust conditions. Corrective action if oscillations are encountered is to _________. Be prepared for an out-of-trim condition. If autopilot flight is required, retrim the aircraft and select turbulence mode prior to engaging autopilot. If oscillations are
encountered again, continue the flight without the use of autopilot.
Vapp + 5
N 3-14 Maintain a final approach speed of ___________ knots for autopilot coupled approach
autopilot, disabled
N 3-14 Rudder boost is provided by the rudder servo of the __________. The yaw damper is ________ when the rudder boost is activated.
lubrication of the engine-driven high pressure pressure pump.
C 3-14 Keep boost pump operating to ensure ___________.
restart, mechanical difficulty
C 3-15 Do not attempt to ________ an engine that has been shut down due to obvious ___________.
battery, generator
N 3-15 The ______ is used regardless of position of the ________ reset switch for all inflight starter assisted air starts.
60 to 83, 60, 60 undesired, practical
N 3-15 Normal oil pressure is ___ to___ psi at N2 speeds above___%. Oil pressure below ___ psi is ___________. Land as soon as ___________
popped circuit breakers, explosion
W 3-17 Do not reset ______________ in the fuel system. A short circuit and
accompanying arcing in an enclosed fuel cell could result in an ____________.
C 3-17 If the boost pumps begin operation while in the automatic mode for no apparent reason, leave the switches in the AUTO mode and land as soon as ___________.
inoperative, surges, rapid throttle movement
W 3-17 When the EFC is __________, the compressor bleed valve cannot operate to prevent __________ between the low compressor and the high compressor. Avoid _________________
and flight conditions that may contribute to a compressor stall (i.e.) high AOA or wake turbulence.
Engine spool-up time
W 3-17 _________________ will be increased. Do not turn off the other EFC. Anticipate power requirements. Anticipate differential spool-up.
throttle angle
W 3-17 With the EFC off, the __________ to achieve similar thrust settings will be different. Matching the throttles using the engine with the EFC on will yield less than charted %N1 for the other engine
C 3-17 Matching the throttles using the engine with the EFC off may cause ___________ of the other engine.
N 3-17 If attempting to restore normal engine EFC operation, turn the EFC switch ON only with the throttle lever below ________ position. If normal EFC operation is not recovered, then the EFC switch should be placed to OFF and the flight completed in the manual mode.
wing over-pressurization condition
C 3-18 Allow sufficient time for the L or R WG TK OV PRESS annunciator to extinguish before commencing crossfeed operations. Continued operation of crossfeed with a full off- service tank may result in a __________________.
single system failure
W 3-18/21/31 Crossfeed must not be used for final approach or landing to prevent a ___________ from causing a dual engine flameout.
L or R WG TK OV PRESS x2, crossfeed, depleted, fuel imbalance
N 3-18 Once the respective transfer pump stops operation, the _________
annunciator should extinguish. Allow sufficient time for the ___________
annunciator to extinguish before commencing _________ operations. After fuel has been ______ from the mid fuselage tanks, crossfeed must be terminated to avoid a ____________.
erratic operation or fuel starvation
C 3-19 Unfiltered fuel is being supplied to the engine. If ____________ is observed,consider engine shutdown.
W 3-19/21 If under single-engine operation, discontinue ____________ to prevent loss of thrust and possible loss of the operative engine.
crossfeeding to prevent possible reduction
W 3-19/21 If both engines are operating, discontinue _____________ of thrust.
N 3-20 Illumination of the _______________ annunciator is advisory only and indicates
a combination inverter-load bus malfunction that will result in the loss of the flap position
indicator and both oil pressure indicators.
N 3-20 Annunciator illumination indicates a feeder cable circuit breaker has opened between a main bus and its respective load bus. The __________ feeder has been activated.
C 3-20 Do not reset popped _______________ circuit breakers.
windshield heat
W 3-21 The smell of an electrical overheat or observation of smoke and/or fire at the lower outboard corner of either windshield, may indicate an overheat condition in the electrical power
terminals when the pilot's or copilot's ________ is in an operational mode. If this
condition is suspected, turn the windshield anti-ice switches Off.
W 3-21 If it has not or cannot visibly be verified that the fire is extinguished, land as soon as _______________.
toxic effects
W 3-22 The extinguishing agent and its combustion products can produce ______________ if inhaled.
approx 20 seconds
N 3-22 Bleed air source selector must remain in each position long enough
(__________________) to allow adequate system purging to determine the source of smoke.
not, switch, switch, push and hold the interrupt switch
N 3-23 It is ___ necessary for both pilots to simultaneously actuate the _____ {Trim interrupt}. Normally, the PF will actuate the _______. The PNF, however should be prepared to ____________ should the trim continue to run away.
N 3-23 If any trim axis must be disabled, land as soon as ___________.
EMER position
N 3-23 Autopilot engagement is not possible with the pitch trim selector switch in the ______________.
out-of-trim condition
C 3-23 The use of excessive trim in an attempt to release the flight controls may result in an ______________ if the servo clutch releases.
N 3-23 If an aircrew suspects a binding control surface, visually ensure that the __________ switch is disengaged.
avoid overcontrolling the aircraft
C 3-25 When accomplishing the following procedures {elevator/rudder binding}, flight controls may suddenly become free. Care should be taken to ___________.
FCS 1 and FCS 2
N 3-25 Pulling the ________________ circuit breakers will cause loss of autopilot, yaw damper, rudder boost, pilot and copilot flight directors.
differential braking
W 3-26 If the rudder is jammed out of the neutral position, the nosewheel will be cocked on landing. Move CG aft, if possible, and hold nosewheel off as long as possible during the landing roll. Use _______ to maintain directional control.
W 3-26 In the event of flap system malfunction, the circuit breaker placarded FLAP, located in the systems group of the aft circuit breaker panel, should be pulled after the corrective actions have been accomplished. This removes power from the flap handle. When the circuit breaker is pulled, further flap actuation due to air loads or switch contact proximity, etc., is __________.
right flap
C 3-26 Observe maximum speed limits appropriate to flap position of the most extended flaps. The flap position indicator shows position of the __________ only.
Vref + 20, Vref + 10
N 3-26 For _________ KIAS, use flaps 0 landing distance. For _______ KIAS, use flaps 10 landing distance. Refer to TO 1T-1A-1-1
N 3-26 If the asymmetric condition cannot be corrected and conditions permit, land from a _____________ approach (flap system failure).
extend flaps beyond 10 degrees
C 3-27 With speed brakes extended, do not ___________________.
5, 20
N 3-27 (stuck SB) Level flight stall speeds will increase ____ knots and landing distance will increase approximately _______%.
do not move the flaps
W 3-27 If flap damage is known or suspected, _____________. Use the existing flap setting to accomplish the structural damage check.
full control deflection
W 3-27 The aircraft speed must never be decreased to the point at which _______________ is required. An impending control problem may be indicated by excessive rolling, yawing, or
pitching. If experiencing any abnormal flying qualities, unload the aircraft and accelerate to the last tested safe airspeed.
melting of the aircraft trim panels near the rear bulkhead and potential smoke and fumes in the cockpit.
W 3-28 Prolonged use of the emergency pressurization can result in the ______.
has been turned off
N 3-29 Air entering the cabin for pressurization during air conditioning emergency operation will still be hot until the bleed air selector ___________.
on, failure
C 3-29 Do not turn the wing anti-ice back ___ (after bleed air duct_________)
N 3-30 Allow approximately _____ minutes for system purging to allow the bleed air temperature sensors cool (after bleed air duct failure)
N 3-30 Windshield anti-ice may be _____________ in the area of the crack.
W 3-30 If aircraft structural failure is suspected, limit the maximum airspeed to the ______ airspeed or as appropriate.
in lieu, separately
N 3-31 The following procedures incorporate all items of the Before Landing/pattern Checklists
and are ________ of accomplishing those checklists ___________. [loss of airspeed indication]
N 3-31 An AOA of 0.2 (.25 speed brakes extended) will yield an airspeed of _______ knots. Use pitch attitude as primary reference. Make small changes in pitch attitude and wait for AOA to stabilize.
N 3-31 Maintain 0.3 AOA throughout the configuration change to flaps 10, gear down. This will yield an airspeed of about _______ knots.
10 degrees, 10, +10 degrees C, 30 flaps
C 3-31 If icing conditions are encountered during flight, the maximum landing flap is
_________ (0.57 AOA) unless one of the following are met:
The icing conditions are encountered for less than ________ and the RAT during the encounter was warmer than -8 C.
A RAT of ______, or warmer is observed during the descent, approach or landing.

If either of the above two conditions is met, __________ may be utilized for landing.
Vref, 0.57
N 3-31 This will yield an approach speed of _____ (_____ AOA) and normal landing distances.
single-engine go-around
W 3-32 Do not attempt an actual __________ after selecting flaps to 30 degrees.
prior to
N 3-33/34 Appropriate checklists should be completed ----- entering the traffic area.
power, windmilling, Anti-skid, faster, longer
N 3-34 The speed brake and wing flaps may not be operational when engine _______ is lost, depending on remaining electrical power and ________ hydraulic power. ________ brakes will not be available for landing roll. Allow for a _______ touchdown speed and _______ rollout.
idle, extended
N 3-35 Practice dual flameout landings with both engines at ___ and the speedbrakes _______ to simulate the drag of windmilling engines.
N 3-38/40 Pulling the __________ circuit breaker, with the normal aircraft power available, will cause the landing lights to extend and illuminate if the LAND LT switches are in the _______ position
N 3-38 Both the ___________ and ______________ circuit breakers must be pulled to eliminate the gear warning horn with flaps at ___ and landing gear ____ during power on ditching.
skip, being the hardest
W 3-38 Do not unstrap from the seat until all motion stops. The possibility of injury and disorientation requires that evacuation not be attempted until the aircraft comes to a complete stop. A _______ should be expected on initial contact with the second contact _______.
C 3-38 Keep life raft away from any damaged surfaces which might _______ it.
N 3-38 Landing distance will increase approximately ________% (side-window landings)
normal, inadequate
C 3-39 To prevent system damage, consider re-selecting the hydraulic pressure bypass switch to ______ only if available runway without hydraulics is ________ and no other suitable alternate is available. Depending on the situation, utilizing hydraulic power for landing to obtain required flap setting, normal braking, speed brake, or a combination of these controls may be required.
N 3-39 After prolonged flight in cold temperatures, followed by rapid descent, one or both __________ annuncaitors may illuminate momentarily when gear down is selected. Gear extension time may increase slightly. Increasing N2 may assist in recovery. Once hydraulic temperature returns to normal, all hydraulic components should function properly and the mission may be continued.
N 3-40 When retarding the throttle, ensure the landing gear warning __________ switch has not been activated.
N 3-40 Pulling the __________ circuit breaker removes electrical power from the gear system and eliminates gear sequencing.
30 seconds, yaw the aircraft
N 3-40 Landing gear should down lock in approximately __________. It may be necessary to ___________ to fully extend the main gear into position. This can be
accomplished by smoothly applying rudder as required into the unsafe gear.
do not recycle landing gear handle
C 3-40 Once the landing gear has been extended (3 green) and locked down by the auxiliary method, _____________. A second attempt may not provide a complete recycle.
stall warning system
W 3-42 Due to distortion of the wing airfoil, ice formation on the wing leading edges can cause significant losses in rate of climb, cruise speed and range, as well as increase in buffet and stall speed. The __________________ should not be relied upon. However, with ice accumulations on the wing leading edges, significant aerodynamic buffet will occur well in advance of actual stall. Do not attempt flight at speeds below the onset of aerodynamic buffet.
Vapp + 35, Vapp + 35
W 3-42 Approach speed of ________ is required for ice accumulations of approximately 1.5 inches. Accumulation of less than 1.5 may allow approach airspeeds slower than _______ KIAS, if no aerodynamic buffet is observed at those speeds. Do not attempt flight at speeds below the onset of aerodynamic buffet. While decreasing airspeed to Vapp, if aerodynamic buffet is observed, increase approach airspeed as required to stop buffet.
brake energy or tire speed limits
C 3-42 Approach airspeeds may result in touchdown speeds that exceed ________. (landing with ice)
shallow, extended, approach angles
N 3-42 Airplane control input will not be significantly different than required for a normal landing. Use _____ banked turns and an ________ final approach. Avoid steep __________ and large pitch changes at touchdown. Maintain stabilized approach airspeed and power until just prior to touchdown.
skidding tires
W 3-42 Refer to ANTI-SKID OFF landing performance data. Apply brakes gradually,
increasing force slowly to avoid ____________.
tire, differential, wheel speeds, ANTI-SKID, OFF
W 3-43 It is possible for loss of brakes to occur following a ___ failure due to the ______ in main _________. If loss of brakes occur, immediately place the ______ switch to the _____ position and attempt braking from both the pilot's and copilot's position. If braking is not restored, use the emergency brake system.
Significantly higher rudder pedal forces
N 3-44 ______________ will occur during single engine operations with the rudder boost system inoperative.
remain active, VHF
N 3-44 The UHF radio, NAV 2, TACAN, ADF, and DME frequencies and ATC (transponder) cannot be retuned. All frequencies and codes that were tuned at the time of failure will _______________. The VHF radio can be retuned to 121.5 MHz by pulling and resetting the _________ circuit breaker.
still available
N 3-44 If UHF guard mode was on when RTU failure occurred, guard reception is
off squelch
N 3-44 Pulling and resetting the UHF circuit breaker turns _____________ but returns to the frequency tuned at the time of failure.
N 3-44 When not required, the RMT TUNE switch should be in the _________ position. NAV autotuning is disabled when the switch is in the DSABL position.
W 3-45 If an overheat condition occurs, isolate the circuit by pulling the ____ circuit breaker. (Avionics blower failure)
inoperative, cooling air, remain illuminated, blower motor
C 3-45 With the GALLEY circuit breaker pulled, the primary and avionics standby blowers, forward and aft cabin blowers, cold cathode lights, power to the toilet, and the AV BLO FAIL annunciator will be __________. There will be no additional _______ supplied to the avionics rack. The AV STBY BLO button will _______, but no power will be supplied to the
AV BLO FAIL, extinguished
N 3-45 With the GALLEY circuit breaker pulled, the ___________ annunciator will remain _______________.
departure, exceeding, autopilot
N 3-45 Symptoms of a flight director failure include ________ from the intended flight path, failure to follow NAV, LOC, or GS commands , and attitudes _________ defined limits. Attitude information on the EADI should remain usable. The automatic trim system will operate correctly, such that no excessive control wheel loads will be present upon disconnect. Due to the level of redundancy and monitoring in the ________, only flight director malfunctions can occur.
ground, illuminated
N 3-45 If the EFIS master warning reset light is illuminated and the swichlight is pressed, a ________ is applied to the respective DPU, the comparator warning circuits are reset, and the swichlight extinguishes. Each pilot's switchlight must be pressed to extinguish the
respective light. The pilot's switchlight must be pressed for resetting MFD comparator warning indications. The EADI, EHSI, and FMD comparator warning annunciations will automatically
blank if the comparator error condition no longer exists. If the comparator error condition remains, the EFIS master warning reset switchlight and the EADI, EHSI, and MFD comparator annunciations remain______________.
low, high, airspeeds
N 3-45 Avoid ____ indicated airspeeds at _____ altitudes and monitor landing approach _________ closely.
of the cabin in flight
W 3-45 Do not attempt to check the security ______. Remain as far from the door as possible with seat belts securely fastened.
Landing With Ice Accumulation On The Wings
N 3-51 If flight in icing conditions cannot be avoided, refer to ________ procedure.
erratic operation or failure of the following systems: Mach/speed indicator, RA/VSI and Altimeter
W 3-52 Flight in visible moisture without pitot heat may result in _______.
has failed
C 3-52 If either ENG ICE TEMP LO annunciator remains illuminated, assume engine anti-ice system ____________, monitor engine instruments, and avoid further icing condition.