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EPQ Dash 1 Ch 6


(T/F) The aircraft incorporates a reversible flight control system. (-1 pg 6-2) True
As airspeed increases, trim appears to become ___________________.(-1 pg 6-2) More effective
Pulsing the trim control is ___________ to avoid over-trimming at higher airspeeds. (-1 pg 6-2) Necessary
During rapid acceleration from low to high speed, the pilot_______need to initially trim nose down a rapid build up in forces Will
(T/F) The roll trim authority is insufficient to trim the aircraft laterally, with the maximum allowable fuel imbalance of 50 pounds at all airspeeds and configurations. (-1 pg 6-2) False (adequate)
At approach speeds or below with flaps in the LDG position, full nose right trim is required at _____% torque. (-1 pg 6-2) 100
The directional trim is commanded by the trim aid computer as a function of? (-1 pg 6-2) engine torque and indicated airspeed pressure altitude and pitch rate.
(T/F) The trim aid computer will completely trim the aircraft directionally? (-1 pg 6-2) False (will not)
There is _____________ pitch trim change when flaps are selected to the takeoff position. (-1 pg 6-3) Very little
(T/F) Lowering the flaps to the LDG position produces a slight pitch up, which is easily controllable. (-1 pg 6-3) True
(T/F) The stick shaker intensifies noticeably as the flap limit airspeed is approached. (-1 pg 6-3) False (Buffeting intensifies)
(T/F) The pilot is required to change the trim during speed brake operation. (-1 pg 6-3) False – The speed brake-elevator interconnect reduces the pitch tendency.
(T/F) The flap/speed brake interconnect prevents the use of the speed brake with the flaps extended. (-1 pg 6-3) True
(T/F) If the flaps are extended, the speed brake will not retract if extended. (-1 pg 6-3) False – the SB will automatically retract if the flaps are set to any other position than UP.
If the speed brake has been extended, it will automatically retract if the flaps are set to any position other than ________.(-1 pg 6-3) UP
The reversible flight control system becomes more sensitive as airspeed _______.(-1 pg 6-3) Increases
Slight control stick inputs _________ result in airspeed or altitude deviations, from hands off trim condition. (-1 pg 6-3) Can
Frequent cross-checks of airspeed are ____________ during climb out to prevent deviations from the climb airspeed schedule. (-1 pg 6-3) Required
(T/F) The aircraft will decelerate rapidly with power in a dive. (-1 pg 6-3) True
If uncoordinated rolling maneuvers are initiated at –1 G, the maximum bank angle change is ________ degrees. (-1 pg 6-3) 180
Recommended entry speed for a lazy eight is___KIAS(-1 pg 6-3) 200-220
Recommended entry speed for a Loop is ________ KIAS. (-1 pg 6-3) 230-250
Recommended entry speed for a Split S is ________ KIAS. (-1 pg 6-3) 120-140
Recommended entry speed for an Immelmann is ________ KIAS. (-1 pg 6-3) 230-250
Recommended entry speed for a Clover Leaf is ________ KIAS. (-1 pg 6-3) 200-220
Recommended entry speed for a Barrel Roll is ________ KIAS. (-1 pg 6-3) 200-220
Recommended entry speed for a Cuban Eight is ________ KIAS. (-1 pg 6-3) 230-250
Recommended entry speed for an Aileron Roll is ________ KIAS. (-1 pg 6-3) 180-220
Recommended entry speed for a Chandelle is ________ KIAS. (-1 pg 6-3) 200-250
Factor(s) which effect glide performance are________. (-1 pg 6-4) coordinated or uncoordinated flight angle of bank and aircraft configuration airspeed
(T/F) The maximum range power-off glide airspeed remains the same with changes in aircraft configuration. (-1 pg 6-4) False – Clean = 125, Gear = 105, Gear/Flaps = 95
Best glide speed in clean configuration is approximately _____ KIAS with a sink rate of __________ fpm. (-1 pg 6-4) 125, 1350
Best glide speed with gear down, flaps up, and speed brake up is approximately _____ KIAS with a sink rate of __________ fpm. (-1 pg 6-4) 105, 1500
With the engine out, flaps _________ be deployed prior to extending the landing gear in a power-off glide because the engine driven hydraulic pump is not operating. (-1 pg 6-4) Cannot
(T/F) Without normal hydraulic pressure, use of the speed brake in a power-off glide is not possible. (-1 pg 6-4) True
The stick shaker provides artificial stall warning in each cockpit a minimum of _____ knots before the stall is reached. (-1 pg 6-4) 5
Natural stall warning, in the form of light aerodynamic buffet, occurs approximately ____ knots before the stall during power-off stalls in all configurations. (-1 pg 6-4) 3
(T/F) During accelerated/turning entries into a stall, moderate buffet occurs well prior to the actual stall. (-1 pg 6-4) True
(T/F) The stick shaker may mask natural aircraft buffet during stall approach and recovery. (-1 pg 6-4) True
What is the defining characteristic of an upright, wings-level stall? (-1 pg 6-4) Increased buffet Roll off Wing-drop Roll-off and wing-drop
During a wings level power-on stall, _________ rolling tendency is induced at stall by engine torque before reaching full aft stick. (-1 pg 6-4) A left
Above _____% torque, full right rudder and full right aileron may not prevent a left roll off at stall. (-1 pg 6-4) 60
An accelerated stall induced by a turning entry and increased G is preceded by _________ buffet before the stall is reached. (-1 pg 6-7) Pronounced
Altitude lost during recovery from a wings level stall is usually less than ______ feet, assuming a prompt application of recovery power. (-1 pg 6-7) 100
In general, OCF can be divided into which following categories: (-1 pg 6-7) Steady-state spins and incipient spins Poststall gyrations and steady state-spins
Poststall gyrations are the motions of the aircraft about one or more axes immediately following: (-1 pg 6-7) Stall and prior to the incipient spin
(T/F) A poststall gyration can occur at high airspeed but not at low airspeed. (-1 pg 6-7) False (both high and low airspeed)
(T/F) Poststall gyrations may be violent and disorienting. (-1 pg 6-7) True
The spin-like motion that occurs between a postal gyration and a fully-developed spin is called an _____________.(-1 pg 6-8) Incipient spin
An incipient spin is characterized by oscillations in ________. (-1 pg 6-8) Pitch and roll Yaw attitudes and rates
An incipient spin can be identified by an oscillatory spin like motion, ________________ , ______________, and airspeed that is accelerating or decelerating toward the steady-state value. (-1 pg 6-8) a fully-deflected turn needle, a stalled angle of attack
Altitude loss during a typical steady-state spin is approximately ______ feet for a six-turn spin. (-1 pg 6-8) 4500
(T/F) The aircraft has shown an overall capitulation to un-intentional spins. (-1 pg 6-8) False – the aircraft has shown an overall RESISTANCE to un-intentional spins.
(T/F) Recovery from inadvertent loss of aircraft control, including poststall gyrations and incipient spins, can be accomplished by promptly advancing power to MAX, and positively neutralizing flight controls in all axes. (-1 pg 6-8) False – Power to IDLE
A spiral is a rolling and/or yawing motion of the aircraft that is often mistaken for a spin, but is not steady-state in that airspeed is increasing through _____ KIAS and motions are oscillatory. (-1 pg 6-8) 160
A spiral can result from misapplication of ________________. (-1 pg 6-8) pro-spin controls
(T/F) Anti-spin controls may not be effective in arresting the spiral and may actually aggravate the situation. (-1 pg 6-8) True
The best response to a spiral is to neutralize the ___________ and reduce ____________ until motion stops. (-1 pg 6-8) Controls, the power to IDLE
A spin requires ________________ simultaneously with __________________.(-1 pg 6-8) Stalled angle-of-attack, sustained yaw rate
(T/F) Only intentional erect spins with landing gear, flaps, and speed brake up and power at MAX are permitted. (-1 pg 6-9) False
A pitch attitude of __________ degrees nose high provides the best entry into a spin. (-1 pg 6-9) 15-20
Spins below 10,000 feet MSL are prohibited due to ______________________ which occur during the spin maneuver with the propeller RPM below 80%.(-1 pg 6-9) High stresses on the propeller
A spin may be entered by maintaining full aft stick and applying full rudder in the desired spin direction at _____ KIAS. (-1 pg 6-9) 80
Entry into idle power, erect spins are characterized by roll and yaw in the ___________________ is applied. (-1 pg 6-9) Direction rudder
(T/F) After completing the initial turn, of an erect spin, the nose will pitch to approximately 60 below the horizon. (-1 pg 6-9) True
After completing approximately ____ turns, the spin will have entered a near steady state condition. (-1 pg 6-9) 3
Spin rotation rates will stabilize to approximately ____________ seconds per turn with altitude loss of ____________ feet per turn. (-1 pg 6-9) 2-3, 400-500
(T/F) The turn needle will be fully deflected in the opposite direction of the spin. (-1 pg 6-9) False – turn needle will show the direction of the spin.
(T/F) Spins in either direction may exhibit roll and yaw oscillations after three turns with neutral ailerons. (-1 pg 6-9) True
(T/F) Ailerons have pronounced effect on spin characteristics. (-1 pg 6-9) True
With ailerons held in the directions of spin rotation, roll and yaw become noticeably _________________.(-1 pg 6-9) Oscillatory
(T/F) During a spin, oil pressure may decrease below 40 psi with idle power, which is acceptable provided normal indications return after recovery. (-1 pg 6-9) True
T or F A progressive spin is a result of misapplication of recovery controls. (-1 pg 6-9) True
What is the best means of recovery if a progressive spin is inadvertently encountered? (-1 pg 6-9) OCF procedure
An aggravated spin is caused by ____________. (-1 pg 6-9) Maintaining pro-spin rudder Moving the control stick forward of the neutral position
What is the best means of recovery if an aggravated spin is inadvertently encountered? (-1 pg 6-9) OCF procedure
Intentional inverted departures and spins are _____________.(-1 pg 6-9) Prohibited
Intentional spins in other than cruise configuration at idle power are ____________.(-1 pg 6-10) Prohibited
Erect spin recovery is ___________ after recovery controls are applied. (-1 pg 6-10) Prompt
When spin recovery controls are applied the pitch attitude will ___________ and spin rate will initially ____________.(-1 pg 6-10) Steepen, increase
Once recovery controls have been applied, spin rotation will abruptly cease within __________ turns after applying controls. (-1 pg 6-10) 1 ½
Expect to lose approximately _____ feet for every turn of a spin with an additional ___________ feet for a normal dive. (-1 pg 6-10) 500, 1500-2000
(T/F) The aircraft will recover from erect spins with controls free and with the PCL at IDLE. (-1 pg 6-10) True
Altitude loss during dive recovery is determined by the following independent factors. (-1 pg 6-11) Angle of dive, and acceleration maintained during pullout Altitude at start of pullout, airspeed at start of pullout
(T/F) In all cases of inverted or power on departures, the engine shall be inspected by qualified maintenance personnel after flight. (-1 pg 6-11) True
Created by: 1214



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