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EPQ Dash 1 ch 3

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QuestionAnswer
The decision to takeoff or abort should be based on the following: Runway length and condition, terminal weather conditions and area traffic If any system emergency affecting safety of flight is experienced prior to liftoff Both A and B
(T/F) After a stop which required maximum effort braking and if overheated brakes are suspected, do not taxi into or park in a congested area until brakes have had sufficient time to cool. True
(T/F) With suspected overheated brakes, do not set the parking brake True
Maintain a minimum of ________________KIAS when maneuvering to intercept the Emergency Landing Pattern 120
(T/F) With a loss of hydraulic pressure, landing gear and flaps CANNOT be lowered by normal means. True
Initial indications of engine failure/flameout are: (Dash 1, 3-8) Loss of power and airspeed Rapid decay in N1, torque, and ITT Propeller movement towards feather
Depending on airspeed, N1 will indicate 0% within approximately __________seconds, even though the gas generator core may not have seized. (Dash 1, 3-8) 5
(T/F) Engine failure will result in a loss of bleed air supply to the OBOGS concentrator and environmental control system causing subsequent OBOGS and ECS failure. (Dash 1, 3-8) True
The Emergency Oxygen bottle provides approximately ___________minutes of oxygen. (Dash 1, 3-8) 10
(T/F) The Propeller will NOT feather unless the PCL is in IDLE. FALSE –PCL must be in CUT OFF to feather the prop.
Airstart procedure is not recommended below __________ft AGL, as primary attention should be to eject or safely recover the aircraft. (Dash 1, 3-8) 2,000
Airstarts may be attempted at any altitude and airspeed, although airstarts have only been demonstrated at ___________ft MSL and below. (Dash 1, 3-8) 20,000
Approximately _________ft of altitude will be lost during an airstart attempt performed at best glide speed of 125 KIAS. (Dash 1, 3-10) 1,200
(T/F) Do not delay ejection while attempting airstart at low altitude if below 2000 ft AGL. (Dash 1, 3-11) True
If the generator will not reset, verify the starter switch is in ________. The starter will drain battery power in ________minutes if left in MANUAL. (Dash 1, 3-12) NORM, 10
(T/F) Do not reset circuit breaker in flight after an uncommanded movement of the propeller to feather True
Compressor stalls may be identified by: Change in engine noise (loud bang or backfire) Fluctuating Torque Fluctuating ITT, N1, and Fuel Flow
Recommended minimum altitude for uncontrolled ejection is ____________ft AGL. (Dash 1, 3-13) 6,000
If departure from controlled flight progresses into a steady state spin, typical indications will be Sustained yaw rate AOA 18+
(T/F) Extension of nose gear may establish airflow into the engine compartment that could reignite a smoldering fire or cause a hydraulic fire if a hydraulic leak exists. True
The standby attitude indicator will provide accurate indications for at least _______minutes after a loss of all electrical power. (Dash 1, 3-14) 9
(T/F) To prevent injury, ensure oxygen mask is on and the visor is down prior to actuating the CFS system. (Dash 1, 3-14) True
Illumination of the CHIP annunciator indicates: Possible metal contamination in engine oil supply
(T/F) If the CHIP detector is illuminated, the engine may fail with little or no further warning. (Dash 1, 3-15) True
Standby instruments (and their associated lighting) and UHF tuning (backup UHF control head) will be powered for approximately ________minutes by the auxiliary battery. (Dash 1, 3-16.1) 30
(T/F) Emergency flaps will be powered by the main battery through the auxiliary battery bus as long as the main battery has not failed. (Dash 1, 3-16.1) True
(T/F) If control of EHSI display is lost, it is not possible to control EHSI functions from the other cockpit. (Dash 1, 3-18) FALSE – it MAY BE possible to control the EHSI functions from the other cockpit.
When will the FUEL PX annunciator illuminate? If engine feed fuel pressure drops below 10 psi The boost pump fails to engage automatically
(T/F) If engine fuel feed pressure is fluctuating at or below 10 psi, the boost pump will alternately cycle on and off, illuminating and extinguishing the BOOST PUMP annunciator. (Dash 1, 3-19) True
The automatic fuel balancing system maintains fuel load in each wing to within _______pounds of the other. (Dash 1, 3-20) 20
(T/F) The FUEL BAL annunciator will illuminate when there is greater than a 20 pound difference between the left and right wing tanks for more than two minutes. (Dash 1, 3-20) FALSE –30 pound difference
Illumination of the left or right fuel level low annunciator indicates that approximately _______pounds of usable fuel remains in the affected wing tank. (Dash 1, 3-20) 110
(T/F) With a full lateral fuel imbalance (one tank full, the other tank empty), sufficient lateral authority exists to control the aircraft (no crosswind). (Dash 1, 3-20) TRUE
(T/F) You should attempt to manually balance the fuel load if the alternate engine data display is indicating FP FAIL (Dash 1, 3-20) FALSE – You should NOT manually balance with FP FAIL since the imbalance may be incorrect and it may cause or aggravate a fuel imbalance.
Which systems are inoperative when the HYDR FL LO annunciator is illuminated Landing gear normal extension Flap normal extension Speed brake and NWS
The EHYD PX LO annunciator will illuminate whenever emergency hydraulic pressure drops below __________psi indicated. 2400 ± 150
(T/F) Actuation of landing gear or flaps will normally cause a momentary drop in hydraulic pressure below the green arc. True
In no case should the aircraft be slowed below _______KIAS or to activation of the stick shaker, whichever is higher during a controllability check 90
Landings have been accomplished at touchdown speeds up to approximately _____KIAS in the normal landing configuration. (Dash 1, 3-21) 110
Illumination of the DUCT TEMP annunciator indicates that: Bleed air temp in the environmental systems duct has exceeded 300 deg F Bleed air temp in the defog duct has exceeded 300 deg F
(T/F) Whenever the trim interrupt button is being depressed, or when the trim disconnect switch is set to disconnect, all trim systems are disengaged and the TAD is disconnected True
In a runaway trim situation, except when trim is at full nose down, reducing airspeed to ____________KIAS will reduce control forces. (Dash 1, 3-23) 110-150
(T/F) With a sudden or rapid decompression at altitudes near 20,000 ft MSL, there may be a transient OBOGS FAIL indication as the OBOGS system switches to high altitude mode to compensate for higher cockpit pressure altitudes. (Dash 1, 3-24) True
Recommended minimum altitudes for ejection are _________ft AGL for controlled ejection and __________ft AGL for uncontrolled ejection. 2000, 6000
If PEL is being performed with IDLE power, add _______feet to high, low and base key altitudes to compensate for drag of un-feathered prop. (Dash 1, 3-31) 500
Plan to intercept the emergency landing pattern at or below high key in the appropriate configuration and a minimum airspeed of ________KIAS. (Dash 1, 3-31) 120
(T/F) Do not land or taxi across raised arresting cables with main gear doors open. (Dash 1, 3-35) True
If landing with a known wheel brake failure in one wheel, land on the side of the runway corresponding to the _________brake. (Dash 1, 3-36) Failed
If the following situation(s) occur(s) during ground operations, execute the EMERGENCY ENGINE SHUTDOWN boldface: (Dash 1, 3-4) Engine Fire Prop Strike Chip Light
(T/F) With the ISS selector set to BOTH, both seats will eject, even if one is safely pinned. (Dash 1, 3-4) True
(T/F) With a loss of hydraulic pressure, flaps will extend slowly with residual pressure and may take longer to deploy. (Dash 1, 3-35) True
With the bleed air inflow switch set to OFF position, the following systems will be operational: (Dash 1, 3-24) OBOGS only
The CKPT ALT annunciator light illuminates whenever the cockpit pressure altitude exceeds __________feet. 19,000 feet
Created by: 1214