ESV Study Guide Aircraft General, Air Conditioning, Flight Controls Flashcards by Bobby Rommo

The minimum pavement width required for a 180 degree turn is _____ feet.
79
88
57
65

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What are the thrust ratings of the CFM 56-7B26 engine?
27K Bump
26K & 24K
22K
All of the above.

All of the above.

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The system that controls and monitors engine parameters is the _____.
Autothrottles
FMC
EEC
FCC

EEC

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The B737-800 is limited to a maximum takeoff weight of _____ pounds.
144,000
174,200
172,500
168,000

174,200

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The B737-800 is limited to a maximum landing weight of _____ pounds.
146,300
136,000
150,000
137,000

146,300

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What is the maximum operating altitude for the B737-800?
42,000 ft.
41,000 ft.
35,000 ft.
37,000 ft.

41,000 ft

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What is the maximum zero fuel weight of the B737-800?
144,000
140,000
138,300
136,000

138,300

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How many escape slides are on the B-737?
8, one at each entry and service door and one at each overwing exit.
6, one at each entry and service door and one at each wing.
2, only one at each forward entry and service door.
4, one at each entry and service door.

4, one at each entry and service door.

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MAX: PSEU Light has been replaced with the ____ light:
MAINT
UNIT
ALERT
SYSTEM

MAINT

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End of AIRCRAFT GENERAL

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Beginning of AIR CONDITIONING

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The ram air doors normally modulate to full OPEN when the aircraft is ____.

operating both packs in high flow

in flight with flaps not fully retracted or on the ground

in flight with flaps retracted

on the ground only

in flight with flaps not fully retracted or on the ground

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The APU can supply bleed air for the pack up to ____.

41,000 feet under all conditions

20,000 feet or 12,000 feet if the APU is also providing electricity

17,000 feet or 10,000 feet if the APU is also providing electricity

20,000 feet or 8000 feet if the APU is also providing electricity

17,000 feet or 10,000 feet if the APU is also providing electricity

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The mix manifold receives air from the ____.

left pack, right pack, and pre-conditioned air only

left pack, right pack, recirculation fan, and pre-conditioned air

right pack, recirculation fan, and pre-conditioned air only

left pack and right pack only

left pack, right pack, recirculation fan, and pre-conditioned air

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What is the primary source of conditioned air for the cockpit?

Mix manifold

Both packs

Left pack

Right pack

Left pack

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The primary purpose of the recirculation fans is to ____.

provide overheat detection down stream of the packs

reduce air conditioning pack load

increase airflow at greater cabin differential pressure

filter air for contaminants

reduce air conditioning pack load

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Equipment cooling is provided for electronic equipment in the ____.

E & E bay and forward cargo compartment

E & E bay and flight deck area

E & E bay only

E & E bay and aft cargo compartment

E & E bay and flight deck area

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The equipment cooling system has ___________ fan(s).

1 supply and 2 exhaust

2 supply and 1 exhaust

1 supply and 1 exhaust

2 supply and 2 exhaust

2 supply and 2 exhaust

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Air from the preconditioned ground source enters the air conditioning system through the ____.

left pack valve

mix manifold

bleed valve

right pack valve

mix manifold

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Engine low pressure bleed air is provided by the ____ stage, and engine high pressure bleed air is provided by the ____ stage air.

5th/12th

5th/9th

9th/13th

8th/12th

5th/9th

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Each A/C pack has ____ controllers for pack temperature control.

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If the primary equipment cooling fan fails, what indications would be displayed?

No indications - the standby fan turns on automatically.

Master Caution light and horn

Warning horn only (Ground Ops)

Master Caution light, the related equipment cooling OFF light, and the OVERHEAD annunciator light on the System Annunciator Panel

Master Caution light, the related equipment cooling OFF light, and the OVERHEAD annunciator light on the System Annunciator Panel

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In the event of a single pack failure at altitude, the remaining pack is capable of maintaining cabin pressure and comfort at an airplane altitude of _____.

37,000 feet

41,000 feet

35,000 feet

25,000 feet

41,000 feet

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The APU will supply bleed air for ____ pack(s) ____.
1) one, only in flight
2) both, on the ground
3) all three, in flight
4) both 1 & 2

both 1 & 2

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Inflight, normal air conditioning system operation would be ____. Both PACKs from APU one pack from two engine bleed sources two packs from one engine bleed source each pack from its associated engine bleed source

each pack from its associated engine bleed source

Which single bleed source is permitted to supply air to both packs on the ground? None Engine only An engine bleed or APU. The APU only.

The APU only.

The ram air system operates automatically to provide cooling for ____. emergency cooling needs the E & E compartment on the ground the PACK heat exchangers the right pack alternate air source

the PACK heat exchangers

For maximum cooling (of the pack) the ram air inlet doors modulate toward the _________ . a mid position full open position full closed position ram air inlet doors do not modulate

full open position

Deflector doors on the ram air system are used on the ground to __________. prevent backflow of air over the heat exchangers increase airflow through the ram air doors prevent slush ingestion on takeoff or landing allow for smooth air flow over the heat exchangers

prevent slush ingestion on takeoff or landing

The deflector doors on the ram air system are fully extended ____. on the ground only on the ground, or inflight with the flaps extended inflight with the flaps extended inflight with the gear extended

on the ground only

Zone temperature is controlled by introducing the proper amount of trim air into the______________. individual zone supply duct the mix manifold the pack temp control valve modulating the ram air inlet doors

individual zone supply duct

Failure of the primary and standby flight deck zone temperature controls will cause the ____ to illuminate. ZONE TEMP, MASTER CAUTION, and AIR COND annunciator lights ZONE TEMP light only PACK light MASTER CAUTION light only

ZONE TEMP, MASTER CAUTION, and AIR COND annunciator lights

Inflight, the forward cargo compartment is heated by air drawn around it by the ____. 1) outflow valves 2) recirculation fan system 3) equipment cooling system 4) Both 2 & 3

Both 2 & 3

The temperature selector adjusts the desired zone temperature between a range of approximately ____ degrees. 75-85 60-80 65-85 70-80

65-85

When either the primary or standby pack temperature controller fails, what indications will be displayed? PACK and ZONE TEMP lights PACK and MASTER CAUTION lights only MASTER CAUTION, and AIR COND SYSTEM ANNUNCIATOR lights PACK, MASTER CAUTION, and AIR COND SYSTEM ANNUNCIATOR lights on recall

PACK, MASTER CAUTION, and AIR COND SYSTEM ANNUNCIATOR lights on recall

If the FWD or AFT Cab ZONE TEMP lights illuminate indicating an overheat, this will cause the associated ____ valve to close. trim air modulating emergency relief pressure regulating pack

trim air modulating

The associated PACK light, Master Caution, and AIR COND annunciator will illuminate when ______. pack trips caused by primary controller failure all temperature selectors are placed OFF pack controller failure and all temperature selectors placed OFF pack overheats or dual pack controller failure

pack overheats or dual pack controller failure

What fault indication(s) cannot be reset with the trip reset button? BLEED TRIP OFF PACK ZONE TEMP Wing body overheat

Wing body overheat

The ZONE TEMP light, Master Caution, and AIR COND annunciator lights will illuminate for an overheat in the duct leading to any of the three zones a dual temperature controller failure in the CONTROL CAB zone any single temperature controller failure in any zone during a RECALL test any of the above

any of the above

What will cause the left Wing-Body Overheat light to illuminate? A bleed air duct leak in the left engine strut, left inboard wing leading edge, left air conditioning bay, keel beam or APU bleed air duct A bleed air duct leak in the left wing anti-ice Only a bleed air leak in the left air conditioning bay A bleed air leak in the Trim-Air Manifold

A bleed air duct leak in the left engine strut, left inboard wing leading edge, left air conditioning bay, keel beam or APU bleed air duct

Taking off with one or both PACK switches in HIGH is allowed with the engine bleed air switches on. True False

False

While accomplishing the QRH procedure for a PACK light illuminated, why do you select a warmer temperature on all three temperature selectors? Open the pack valve This causes the pack to revert to high flow Reduce the workload on the affected air conditioning pack To extinguish the Pack light

Reduce the workload on the affected air conditioning pack

Placing the trim air switch off will: Cause both packs switch to high flow Close the trim pressure regulating and shutoff valve Cause the left pack temp to be controlled by the Cont Cab temp selector and the right pack by the Fwd and Aft temp selectors Both 2 and 3 are correct

Both 2 and 3 are correct

If a PACK light illuminates while performing a before taxi check, and resets with master caution reset, you should: Perform the PACK QRH procedure Consult the PACK MEL procedure for single channel fault Contact load agent and perform an bleeds off takeoff Both one and two are correct

Consult the PACK MEL procedure for single channel fault

Landing with PACK switches in HIGH: Will automatically revert to normal flow with flaps extended Is not authorized with engine bleeds on Is authorized if a QRH checklist calls for it Both two and three are correct

Both two and three are correct

In order to do a bleeds off takeoff: Only the left PACK is switched to AUTO The right PACK switch must turned OFF Put both PACK switches to HIGH Put both PACK switches to AUTO

Put both PACK switches to AUTO

At the same time this light illuminates, what other indications do you get? AIR COND will illuminate on the left System Annunciator Panel. The right System Annunciator Panel will illuminate AIR COND on recall only. The Master Caution lights illuminate and the right System Annunicator Panel shows AIR COND. Only the Master Caution light will illuminate.

The Master Caution lights illuminate and the right System Annunicator Panel shows AIR COND.

On the NG, both this light and the Master Caution lights are illuminated. What might happen to the left pack next under these circumstances? The left pack valve will close due to pack underpressure. The left pack valve will close if sensors have detected excessive temperature in that pack. The left pack valve will close due to pack overpressure. The left pack valve will stay open even if the left pack overheats.

The left pack valve will close if sensors have detected excessive temperature in that pack.

Inflight, with the left pack valve closed due to excessive temperature, what other actions automatically occur in the Air Conditioning System? The right pack switches to high air flow regardless of flap position. The right pack switches to high air flow only if flaps are extended. The right pack stays at normal air flow rate until the left Engine Bleed Air Switch is selected OFF. The right pack switches to high air flow if flaps are up.

The right pack switches to high air flow if flaps are up.

What effect will this condition have on the left pack? Produces a preset temperature of 65 degrees Output temperatures is controlled by Cont.Cab temperature selector Output temperature is controlled by the Fwd and Aft temperature selectors Pack output temperature cannot be controlled

Output temperatures is controlled by Cont.Cab temperature selector

If this light illuminated only on Recall, ____. both the Right and Left primary Electronic Controllers have failed an overheat has occurred in the CONT Cabin Trim Air Supply Duct both the Primary and Back-Up Flight Deck Zone Temperature Controllers have failed only one of the CONT CAB Zone Temperature Controllers has failed

only one of the CONT CAB Zone Temperature Controllers has failed

If this light extinguishes when the master caution light is pressed: Air conditioning is not available from the left pack. The system will operate normally. A zone overheat was indicated. The trim air system is inoperative.

The system will operate normally.

If this light illuminated due to an overheat condition in the applicable zone supply duct, the Master Caution Lights will also illuminate; and ____. the FWD CAB trim air modulating valve closes none of the trim air modulating valves close the CONT CAB trim air modulating valve closes the AFT CAB trim air modulating valve closes

the CONT CAB trim air modulating valve closes

With all the temperature selectors positioned as above, the packs will adjust for cabin demand. In this case, which statement is most correct? The left pack controls will cause the left pack to maintain a fixed temperature of 75 degrees, and the right pack to maintain 65 degrees as measured at the pack temperature sensor. The pack outputs will average. System operation is normal. The left pack controls will cause the left pack to maintain a fixed temperature of 65 degrees, and the right pack maintain 85 degrees as measured at the pack temperature sensor.

The left pack controls will cause the left pack to maintain a fixed temperature of 75 degrees, and the right pack to maintain 65 degrees as measured at the pack temperature sensor.

End of AIR CONDITIONING

Beginning of ACARS

The engine takeoff report is sent approximately 30 seconds after takeoff. If the PACK/BLEED configurations are set to inadvertently cause a CABIN ALTITUDE warning if left unchanged, after how long and how will the crew receive an alert? 45 seconds; SELCAL chime and NON-STANDARD BLEEDS/PACKS message is printed 2 minutes; SELCAL chime and NON-STANDARD BLEEDS/PACKS message is printed 45 seconds; SELCAL chime and BLEEDS and/or PACK lights will illuminate 2 minutes; SELCAL chime and NON-STANDARD BLEEDS/PACKS message displayed in scratchpad

2 minutes; SELCAL chime and NON-STANDARD BLEEDS/PACKS message is printed

What should be entered in the flap setting when trying to get FOS to search for a TPS using standard thrust? Enter “13” in the flap field. Leave blank or put in ‘99’ to allow search for standard thrust if possible Push the Flap Request button Push the ‘ANY’ button

Leave blank or put in ‘99’ to allow search for standard thrust if possible

To obtain a TPS via ACARS, what is the minimum input information required for a TPS request? Runway and OAT No entries required. Just press the "TPS request" line select button Runway and flap settings Only Runway is required. FOS will optimize for any fields left blank

Only Runway is required. FOS will optimize for any fields left blank

The initial load closeout will be sent to the ACARS printer. The only data uplinked to the FMS is _____? ZFW and takeoff CG. Only ZFW, all other values must be reset. ZFW, takeoff CG, and V-speeds. Nothing will be uplinked to the FMS, the TPS only outputs to the printer.

ZFW and takeoff CG.

End of ACARS

Beginning FLIGHT CONTROLS

The primary flight controls consist of _____. elevators, yaw damper, and ailerons ailerons, elevators, and spoilers stabilizer, rudder, and spoilers ailerons, elevators, and rudder

ailerons, elevators, and rudder

The primary flight controls are normally powered by hydraulic system(s) ____. A and Standby A only A & B B only

A & B

____ can be extended by the Standby Hydraulic System in Alternate mode. Elevators Leading edge flaps/slats Ailerons Trailing edge flaps

Leading edge flaps/slats

If a FEEL DIFF PRESS light illuminates, ____. place both Flt Control switches to STBY RUDDER immediately turn off the associated flight control switch no crew action is required in flight. Continue normal operations. depressurize the A or B hydraulic system

no crew action is required in flight. Continue normal operations.

When the Flaps/Slats Electronics Unit (FSEU) detects a trailing edge asymmetry or skew condition, the FSEU closes the TE Flap Bypass Valve, ____. illuminates the green EXT light, and displays a needle split on the flap position indicator and displays a needle split on the Flap Position Indicator and freezes the TE Flap needles in place, not showing a split illuminates the amber FLT CONT annunciator light, and displays a needle split on the Flap Position Indicator

and displays a needle split on the Flap Position Indicator

On aircraft 3AA - 3LB, load relief for the Trailing edge flaps is only provided for flaps ____. 30 and 40 25 and 30 25, 30 and 40 15

30 and 40

During alternate flap operation, the TE flaps are positioned using ____ power. electrical or hydraulic manual hydraulic electrical

electrical

The SPEED BRAKE lever will automatically move to the down detent, and all spoilers will retract, if ____. the TOGA button is pressed either throttle is advanced after landing wheel spinup drops below 50 knots wheel spinup drops below 60 knots

either throttle is advanced after landing

In the event hydraulic systems A and B fail, the ailerons and elevators can be operated ____ and the rudder must be operated by the ____ system. mechanically (manually), standby automatically, mechanical mechanically (manually), pneumatic electrically, alternate

mechanically (manually), standby

Normally, the ailerons, elevators, and rudder are powered by the _____. A hydraulic system only A & B hydraulic systems Standby system B hydraulic system only

A & B hydraulic systems

Hydraulic System A and B pressure to the Main Rudder PCU is reduced at airspeeds above approximately ____ knots. 150 140 120 135

135

If the aileron control system is jammed, the ____ can still fly the aircraft using the ____ after force is applied to the control wheels and they break free. FO, ailerons Captain, spoilers Captain, control tabs FO, spoilers

FO, spoilers

With the trailing edge flaps at 1, the leading edge slats are ____. in the extend position in the full extend position retracted none of the above

in the extend position

The horizontal stabilizer is normally powered _____, but may also be operated _____. manually, electrically automatically, pneumatically electrically, manually none of the above

electrically, manually

On the ground, speed brakes normally use ____ to destroy lift and make braking more effective. flight spoilers only both flight and ground spoilers ground spoilers only compression of the left main landing gear strut to deploy the ground spoilers

both flight and ground spoilers

Leading edge devices can be _____ by the Standby Hydraulic System if System B fails. extended and retracted extended retracted none of the above

extended

The ____ of the Stab Trim Indicator corresponds to the allowable range of trim settings for takeoff. green band 5 to 10 unit range marks entire scale APL NOSE UP selection settings

green band

On aircraft 3AA - 3LB, the autoslat feature is available in flight _____. with trailing edge flaps selected to 30-40 with trailing edge flaps selected to 1, 2, or 5 at landing flap settings at all flap settings

with trailing edge flaps selected to 1, 2, or 5

In aircraft 3AA-3LB, the LE devices will go to the full extend position when you select _____ or greater with the flap handle. 5 10 1 2

If we move the flap lever from 5 to 10, but the leading edge devices all stay in the extend position, the ____ Light will be illuminated. LE FLAPS TRANSIT LE FLAPS EXT AUTO SLAT FAIL SLATS EXTEND

LE FLAPS TRANSIT

The maximum altitude for extension of flaps is ____ feet. 30,000 11,000 20,000 15,000

20,000

Leading edge devices are normally operated by ____. Hydraulic System B only Hydraulic System A only Standby Hydraulic System Hydraulic Systems A and B

Hydraulic System B only

Roll control is normally provided by the ailerons, assisted by _____. flight spoilers ground spoilers autoslats both 1 & 2 above

flight spoilers

With the SPEED BRAKE Lever in the DOWN detent, how can the speedbrakes be deployed on landing? The pilot can raise the lever manually. The speedbrake is not available. The speedbrake lever will automatically move to full up position when the reverse thrust levers are moved to reverse when above 60 knots. Both 1 and 3 are correct.

Both 1 and 3 are correct.

When using the SPEED BRAKE in flight, the speedbrake lever should ____. be moved to any setting be moved to the UP position be moved to the DOWN position not be moved beyond the flight detent

not be moved beyond the flight detent

The LE FLAPS TRANSIT light illuminated indicates _____. Select the most correct answer. leading edge devices are in transit leading edge devices are not in the programmed position with respect to the trailing edge flaps a leading edge device asymmetry any of the above

any of the above

If wheel spin-up is not detected by the air/ground sensors, the flight spoilers will deploy when ____. any main gear strut compresses thrust reverser extension occurs the right main gear strut compresses the left main gear strut compresses

any main gear strut compresses

Prior to what altitude should the Speed Brakes be Down or Armed? 1000 FT AGL 500 FT AGL 2500 FT AGL 5000 FT AGL

1000 FT AGL

MAX 8: Fly-by-wire Spoiler system provides the following new features. Maneuver Load Alleviation (MLA), Landing Attitude Modifier (LAM) and Coordinated Flare Cue landing assistance. Emergency Descent Spoilers (EDS). Elevator Jam Landing Assist System. Both 2 and 3 above.

Both 2 and 3 above.

MAX 8: Emergency Descent Speed Brakes system (EDS): Generates additional drag to allow the Max to capture and maintain a glidepath similar to the NG. Armed when the airplane is above 30,000 feet and the cabin altitude warning is active. Fully automatic with operation transparent to the crew. Both 2 and 3 above.

Both 2 and 3 above.

MAX 8: The Spoiler Control Electronics Unit (SCE): One sensor is applied to the Captains yoke and provides input for Coordination with the HUD Flare Cue during landing. Translates signals from the speedbrake lever position sensor, the First Officer’s control wheel and other airplane data inputs. Must be selected on during initial FMC setup. Both 1 and 2 are correct.

Translates signals from the speedbrake lever position sensor, the First Officer’s control wheel and other airplane data inputs.

MAX 8: The Spoiler light indicates: The ground spoilers are armed. A fault in the spoiler system. The ground spoilers are deployed. The flight spoilers are deployed.

A fault in the spoiler system.

MAX 8: The Elevator Jam Landing Assist Switch is located on: Aft Overhead Panel E/E Compartment First Class Seating Area Fwd Attendant Panel

Aft Overhead Panel

During the origination preflight, this light illuminates after the IRS Mode Selectors are moved to NAV. The “Flight Control Panel . . . CHECK” item is accomplished by _____ calling Maintenance. The Speed Trim System has failed resetting the Stab Trim to Zero doing nothing. This is a normal indication while the IRUs are aligning resetting the light with the Press-To-Test Switch

doing nothing. This is a normal indication while the IRUs are aligning

This light, and the Master Caution Lights, illuminate during initial taxi-out. No action is required. The Speed Trim System only works with the autopilot engaged. Reset the SPEED TRIM FAIL light by setting the parking brake. Check the MEL or call Maintenance. There is a dual channel failure of the Speed Trim System. No action is required. The Speed Trim System will operate 10 seconds after takeoff.

Check the MEL or call Maintenance. There is a dual channel failure of the Speed Trim System.

If, instead, this light illuminates once you are in flight, the autopilot ____. can only be engaged in CWS P Mode if engaged, has now disengaged and cannot be re-engaged is still fully operational has lost the ability to trim the aircraft

is still fully operational

While extending the flaps electrically through the 5 degree flap position, if you still observe these lights, ____. the flap gage is indicating an erroneous position there is a disagreement between the flap handle and the LEDs the LEDs are still in transit the flaps have not approached the flaps 10 degree position or beyond in aircraft 3AA-3LB

the flaps have not approached the flaps 10 degree position or beyond in aircraft 3AA-3LB

When the flaps have been lowered to 15 degrees with the ALT system and a missed approach has been executed, the ____. TE flaps can be retracted with the ALT system but not the LE devices TE and LE flaps will retract with the ALT system TE flaps can be retracted with the ALT system while the LE devices will retract with the PTU flaps cannot be retracted

TE flaps can be retracted with the ALT system but not the LE devices

When positioning the flaps for takeoff from UP to 1, the crew noticed this condition. What could have caused this malfunction? Skewed L.E. Devices Jammed Rudder Jammed L.E. Devices Skewed T.E. Flap

Skewed T.E. Flap

The ____ protects the flaps in this condition. FSEU DEU EEC FCC

FSEU

The FSEU protects the flaps during ____ operation. Alternate Flap Normal Flap Speed Trim operation both Normal and Alternate Flap

Normal Flap

As you advance the thrust lever for takeoff, would you get an intermittent horn with the LEDs positioned as indicated? No. The TE Flaps are set at 5 Degrees. No. The LEDs are not part of the takeoff warning system. No. If the parking brake is released. Yes. The LEDs are not in the proper position.

Yes. The LEDs are not in the proper position.

The previous condition has now been corrected. The takeoff warning sounds again. Why? Stab Trim in green band and Stab Trim Cutout Switches in normal. Stab Trim not in green band or parking brake lever set. Parking brake released and RTO not selected. Stab trim in green band and auto throttle switch not armed.

Stab Trim not in green band or parking brake lever set.

With the TE Flaps and Leading Edge Devices in the correct position, the Stab Trim set in the green band, the parking brake released, and the speed brake handle stowed you still have a Takeoff Warning Horn. What other scenario(s) could be causing this? Spoiler(s) are not fully down. Trailing Edge Flaps are at a 15 degree setting. An Overwing Exit Door did not lock properly. You must press TO/GA to silence the horn.

Spoiler(s) are not fully down.

During normal operations with these two FLT CONTROL switches in the ON position, they control pressure to the respective ____. aileron only rudder, aileron, and elevator rudder only elevator only

rudder, aileron, and elevator

After loss of system A, the QRH directs you to move the A FLT CONTROL switch to STBY RUD. This action will pressurize the ____. landing gear transfer unit A system PCU Standby hydraulic pump and Standby rudder PCU aileron, elevator, and rudder systems

Standby hydraulic pump and Standby rudder PCU

With the loss of B Hydraulic System, the yaw damper will ____. cause the Yaw Damper Switch to trip off be inoperative causing the Yaw Damper Light to illuminate remain operating from the A hydraulic System be inoperative, but the Yaw Damper Light will not be illuminated until the Flt control B switch is moved to STBY RUD

be inoperative, but the Yaw Damper Light will not be illuminated until the Flt control B switch is moved to STBY RUD

Placing the B FLT CONTROL switch to STBY RUD will cause the YAW DAMPER switch to ____. allow you to reconnect the Yaw Damper by selecting the Yaw Damper switch on pressurize the A Hydraulic system making it fully operational trip OFF and illuminate the Yaw Damper Light operate the standby FSEU

trip OFF and illuminate the Yaw Damper Light

Subsequently, the A Hydraulic System also fails. How would you gain control of the Standby Yaw Damper? Check that the B System Low Pressure Light is Illuminated. You cannot recover the Standby Yaw Damper with a Feel Diff Light illuminated. Turn the Yaw Damper Switch ON. Ensure both A and B Flight Control Switches are in the Standby Rudder Position and then place the Yaw Damper Switch ON.

Ensure both A and B Flight Control Switches are in the Standby Rudder Position and then place the Yaw Damper Switch ON.

With the STAB TRIM positioned as indicated, what would happen when the throttles are advanced for TO with all other systems set properly? radio A steady horn would sound. radio An intermittent horn would sound. radio There would be no alert since this is the proper setting for TO. radio The trim would automatically go to the proper setting.

There would be no alert since this is the proper setting for TO.

If the trim was set to 10 units nose up and then the throttles are advanced for takeoff, what alert would occur? A steady horn An intermittent warning horn and takeoff config lights A flashing red light A Stab out of Trim Light

An intermittent warning horn and takeoff config lights

While applying nose down trim, the electric trim stops. How can you continue to trim if you need more nose down trim? Have the other pilot push the yoke forward. Speed trim system will activate and apply trim. Trim manually, using the manual trim wheel. Engage autopilot and trim again.

Trim manually, using the manual trim wheel.

End of FLIGHT CONTROLS

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ESV Study Guide Aircraft General, Air Conditioning, Flight Controls Flashcards

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