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EPQ Dash 1 Ch 6
finished
| Question | Answer |
|---|---|
| (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 |
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