Study Guide Master

8/14/2019 Study Guide Master

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Copyright 2008 - Learn the Mad Dog & AWSD LLC. For simulation use only.


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For Flight Simulator Use Only Copyright 2008 - Learn the Mad Dog & AWSD LLC

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Document Purpose

We thank you for your purchase of the Learn the Mad Dog Study Guide and ReferenceManual. This guide is not meant to be a stand-alone document, but rather is designedto enhance your learning experience as you watch the DVD, serve as a source ofreference information during your flights, and contains a section to test your knowledgebased on the information presented in Learn the Mad Dog.

Although there is a great deal of information presented in this guide, please refer to theLearn the Mad Dog DVD for complete and detailed information relating to each of theaircrafts systems.

We hope you enjoy Learn the Mad Dog and that the knowledge and skills you gainfrom it will enhance your flight simulator experience!

If you havent picked up the Learn the Mad Dog DVD,get it today at www.learnthemaddog.com!


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Table of Contents

Panel Introduction (LTMD Section 1) ...................................................................... 1

Electrical System (LTMD Section 2)........................................................................ 7

Aircraft Lighting (LTMD Section 3) ........................................................................ 10Fire Detection & Suppression (LTMD Section 4)................................................... 12

Air & Pneumatic Systems (LTMD Section 5)......................................................... 13

Ice & Rain Protection (LTMD Section 6)................................................................ 15

Hydraulic System (LTMD Section 7) ..................................................................... 17

Landing Gear & Brakes (LTMD Section 8) ............................................................ 18

Fuel Systems (LTMD Section 9)............................................................................ 19

Flight Controls (LTMD Section 10) ........................................................................ 20

Power Plant & Engine Controls (LTMD Section 11) .............................................. 23

Flight Instruments (LTMD Section 12)................................................................... 25

Warning & Caution Systems (LTMD Section 13)................................................... 29

Auto Flight Systems (LTMD Section 14) ............................................................... 31

Radios & Communications (LTMD Section 15) ..................................................... 33

Flight Management System (FMS) (LTMD Section 16)......................................... 34

Study Guide Questions ......................................................................................... 35


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1

Panel Introduction (LTMD Section 1)

Aft Overhead Panel

1. Ground Service Electrical Panel2. Radio/Audio Control Panel3. Emergency Lights (peanut bulbs)4. Oxygen Supply Gauge5. Fire Detector Loop Panel6. Cargo Fire Detection and Suppression

Panel

7. Mechanic Call Button8. Circuit Breakers9. Flight Display System

Selectors10. Cockpit Voice Recorder11. EFIS System Selectors12. Engine Synchronizer Control


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Lower (Main) Overhead Panel

1. Engine Generators (with CSD) Panel2. A/C & D/C Power Meters & Selector3. Electrical Panel4. APU Panel5. Emergency Power Control & Battery

Switch6. Fuel Pumps and Engine Start Panel7. Emergency Lighting and Cabin Signs

8. Anti-Ice Panel9. Flight Recorder10. Caution & Warning Systems11. Flight Deck Lighting Controls12. Air Conditioning Panel13. Pressurization Controls14. Overhead Annunciator Panel


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Captains PanelThe Captains panel represents the left side of the flight deck.

1. Master Caution and Master WarningLights

2. Nose Gear & Landing Lights3. Flight Guidance Control Panel (FGCP)4. Clock & Chronograph5. Airspeed Indicator6. RDMI7. Primary Flight Display (PFD)8. Navigation Display (ND)9. Brake Pressure10. Flight Mode Annunciator (FMA)11. Altimeter

12. Traffic Collision and Avoidance System (TCAS) &Vertical Speed Indicator (VSI)

13. Standby Horizon14. Standby Altimeter & Airspeed

Indicator15. Flight Management System

(FMS) Hotspot16. Engine Displays17. Fire Suppression Handles18. Oil & Hydraulic Displays19. Weather Radar20. Thrust Rating Panel (TRP)21. Landing Gear Handle22. Fuel Displays


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First Officers PanelThe First Officers panel represents the right side of the flight deck. Although you will notice that the majority ofinstruments and controls on this panel are identical to those on the Captains panel, there are someexceptions.

1. Exterior Lighting Controls2. True and Static Air Temperature3. Hydraulic Panel4. Clock & Chronograph

5. Brake Temperature Panel


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Throttle PedestalThis panel represents the area between the two flight crew members.

1. Take Off Condition Computer2. Stabilizer Trim3. Spoiler Handle4. Rudder Power5. Throttle Levers6. Fuel Cross-feed Lever7. Outflow Valve Control8. Flap Handle9. Fuel Flow Levers & Trim Fine

Adjust10. Communications Radio11. VHF Radio12. ADF13. TCAS & Transponder Controls14. Flight Deck Lighting Controls

15. SELCAL16. Elevator Trim Brake Switch17. Pneumatic Cross-feed Valve

Levers18. Rudder and Aileron Trim


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Glareshield PanelsThe Glareshield panels are actually groupings of the controls found on the far left and far right of the flightdeck. Both left and right side glareshield panels are identical, but mirrored.

1. Navigation Display Controls2. Rudder Pedal/Floor Lights3. Static Air Selector4. Flight Deck Lighting Controls5. Audio Selector Panel


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7

Electrical System (LTMD Section 2)This aircrafts electrical system consists of an A/C system and a D/C system, both divided into left and rightindependent systems which can be manually connected if the need arises.

A/C power can be generated via either engines generator or by the Auxiliary Power Unit (APU). This system isalso designed to ensure that one side is never powered by two separate sources at one time.

D/C power is provided by two batteries located behind the nose gear. In the event of A/C power failure, D/Cpower can be inverted to A/C to power the rest of the aircraft.


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Electrical System (LTMD Section 2) continued

When starting a cold and dark aircraft:1. Check Volt/Freq of external power.2. Left & right external bus switches ON.3. External power switch (Aft Overhead) OFF.4. Check battery volts at 25V minimum.5. Battery switch ON & LOCKED.6. Perform fire warning test.7. Start APU if necessary.

The Ground Service Electrical panel is used toconnect either APU or ground power to the groundservice bus and should be activated while the aircraft isbeing serviced.

Frequency Meter

Ext / engine: 400 +/- 4 APU (grnd): 396 +/- 8 APU (flt): 400 +/- 10

L&R CSD Oil TempCSD Temp pushfor rise button

L&R CSD DisconnectIf disconnected, can only bereconnected on the ground.

A/C Vol ts Meter APU/Eng/Ext115 +/- 3

D/C Volts Meter

APU Gener ator Sw itch

L&RGeneratorSw itch

L&R GenLoad Meter1.0 = 100%

APU Pow er Avai lab le

Power In UseLight (x4)

Galley PowerSwitch

External Power Avai lab le

L&R DCLoad Meter1. 0 = 100%

A/C BusCross Tie

D/C Bus Cros sTie*manually only

External PowerL&R BusSwitch

APU Pow erL&R BusSwitch

Meter IndicatorSelector


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Electrical System (LTMD Section 2) - continued

Circuit Breakers

Circuit Breakers are located in the aft overhead panel and behind the pilot in the actual aircraft. Preflight checks includechecking all breakers to ensure they are pushed in.

Emergency Power Activating Emergency Power inverts the D/C battery power foruse in the A/C system. A test of the Emergency Power systemconsists of:

1. Move the Meter Indicator selector to Battery Ampand monitor the amps meter. The indicator needleshould be straight up.

2. Move the Emergency Power switch to the ONposition and ensuring that the white indicator lightilluminates. The battery amps indicator needle shouldmove to the left (discharge position).

3. Move the Emergency Power switch to OFF. Thebatter amps should move to the right (charging) andthen back to the straight up position.

Galley Power

The Galley power switch activeselectrical power to the food service areaof the aircraft. This should bedeactivated for engine start.

Electrical System Li mitations

A/C Volts: 115 +/- 3

A/C Frequency: 400 +/- 4

D/C Loads: 0 to 1.5 +/- .3

APU Generator Freq: Ground 396 +/- 8 Flight 400 +/- 10

APU Generator Load: Ground 1.25 Flight 1.0

Engine Generator Load: Cont. 0 to 1.0 5 min - >1.0 to 1.55 sec - >1.5


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Aircraft L ighting (LTMD Sect ion 3)

Interior LightingThis aircrafts interior lighting can be adjusted via several different controls located throughout the flight deck.

The lights on either side of the flight deck can beadjusted via the controls on that specific sidesglareshield panel. For example, the left glareshieldpanel controls the left sides lights.

The center instrument panels lights and pedestallights are controlled from the throttle pedestal.

The overhead integral and flood lights, flight deck flood lights,circuit breaker lights and standby compass lights controls arelocated in the overhead panel.

Circuit BreakerLights

StandbyCom ass Li ht

Cockpit FloodLights andThunderstormLights

Panel Lights

Digital Lights

Flood Lights

Instrument paneland pedestallights


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Aircraft L ighting (LTMD Sect ion 3) - continued

Exterior LightingThe lights on the outside of the aircraft can be activated via glareshield groupings on the Captains and First

Officers panels. These are not mirrored and each side features different controls.

Nose Gear Lights

Landing Lights(left & right wings)

FloodLights

Wing &NacelleLights

Anti -Collision

Lights

Position & StrobeLights

(left & right wings)


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Fire Detection & Suppression (LTMD Section 4)

This aircrafts fire detection system consists of two loops ina parallel configuration located in both engine nacelles and

APU. The system also contains two extinguisher bottlesthat can be used in either engine or the APU.

Both loops must detect a fire to initiate the fire warning.

There is no fire detection or protection located in theengines exhaust area.

The fire handles located in the center of the instrument panelare used to activate the extinguisher bottles Fire detection loop indicators and

controls are located in the AftOverhead Panel. Switches to bepositioned at BOTH for flight.

The Cargo Fire Detection and Suppression panel islocated in the Aft Overhead Panel. The APU Fire Suppression panel is located inthe Main (lower) Overhead)

L & RFire

Handles

LoopTest

Buttons

Detection SquibLi hts

Test Button

AgentLowLights


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Air & Pneumatic Systems (LTMD Sect ion 5)

The aircrafts Air and Pneumatics system provides air conditioned air and cabin climate control, aircraftpressurization, certain areas of ice protection, and is used for engine start.

The APUs air output can beactivated via the APU Air switch on

the APU Panel.

Moving the APU Air switch to theON position opens APU air

movement into the central duct.

Pneumatic pressure in thecentral duct is shown on the

Pneumatic Pressure Indicatorlocated on the Main Overhead

Panel.

Pneumatic Crossfeed Levers

Opening the Pneumatic Crossfeed Levers located atthe rear of the throttle pedestal will allow air pressureto move from the central duct to either or both sides ofthe aircrafts pneumatic system.

Central Duct


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Air & Pneumatic Systems (LTMD Sect ion 5) - continued

The aircrafts Outflow valve, which regulates thecabin pressure, can be manually adjusted via theCabin Altitude Control Wheel located on thethrottle pedestal.

The Outflow Valve Position Indicator shows

whether the valve is open, closed, or any positionin between. Upward movement of the PositionIndicator indicates a closed or closing of thevalve.

NOTE: The Cabin Altitud e w arning will soun d inthe event the cabin altitude is g reater than 10,000feet.

L & R TempControlRight = HotLeft = Cold

L & R PneumaticPressure Indicator

TemperatureDisplay Selector

Radio RackFan Switc h

L&R A/C PackSupplySwitches

Cockpit TempSelector

Cabin TempSelector

Cabin TempGauge

PressurizationSystemSelector

Landing AltitudeDisplay and Selector

Landing BarometricPressure Display andSelector

Cabin Altitude /Differential PressureGauge

Rate Limit Control

OutflowValvePositionIndicator

Cabin Alti tudeControlWheel


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Ice & Rain Protection (LTMD Section 6)

Ice protection is provided by two general systems: Hot Bleed Air and Electrical Resistance Heating

Hot Bleed Air

L &R Forward Strakes

L & R Wing Slats

RAM Air Inlet

L & R Engines

Leading Edge of Stabilizer

Electrical Resistance

Pitot Tubes

Angle of Attack Vanes

RAT Probe

Windshields

Static Ports

L & R Overwing

Heaters

Rudder Limiter Pitot

Bleed Air Heat is activated via the Ice Protectionpanel on the Main Overhead Panel.

Air Foil Anti Ice (In-flight only): Provides heat for theForward Strakes and Wing Slats during a 15-minutecycle then opens at the leading edge of the Stabilizerfor a 2.5 minute cycle. Also provides heat to the RAM

Air Inlet continuously.

Minimum of 20 psi needed for bleed air heating.

Windshield Anti-Ice and Anti-Fog is providedby Electrical Resistance Heating.

The Meter Select and Heat selector activatesall of the heating circuits (CAPT), all exceptthe RAT probe on the ground (out of offposition), or all deactivated (OFF).


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Ice & Rain Protection (LTMD Section 6) - continued

Ground Icing ConditionsOutside air temperature


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Hydraulic System (LTMD Section 7)

The Hydraulic system consists of a Right and Left Main Pump, Auxiliary Pump located on the right side, and aTransfer Pump. Further, there are also 5 accumulators (2 x brakes, each thrust reverser, and elevator)

Left Hydraulic System Left Thrust Reversers Inboard Spoilers Elevators

Left Hydraulic System Left Thrust Reversers Landing Gear

Airstairs Outboard Spoilers Rudder

Both Hydraulic Systems Flaps Brake Anti-Skid System Nose Gear Steering Ground Spoilers Slats

First Officers Panel Normal Engine/Aux Hyd pump pressure: 3000 PSI

Typical Transfer Hyd pump pressure: 2500 PSI

Transfer Pump

Left Hyd.Pum

Right Hyd.Pum

Auxi liaryH d. Pu m

L&R HydPumpSwitches

TransferPumpSwitch

AuxiliaryPumpSwitch

Hyd.Pressure

Hyd.Quantit


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Landing Gear & Brakes (LTMD Section 8)

This aircraft is equipped with a typical tricycle style landing gear configuration consisting of a nose gear (2xwheels) and two main gear (2x wheels each) in the wing area. All three feature spray deflectors to limit spray

debris ingestion by the engines during take off and landing.

The Brake Pressure Indicator located on theCaptains panel provides brake hydraulicpressure for both sets of main gear brakes. Aminimum of 1400 PSI is required to set brakes.

Gear Indicator s Indicators near the gear handle (bothCaptains & First Officers panel) providegear retraction and extension information.The amber Gear Door Open lightilluminates whenever the main gear doorsare open.

Green lights indicate the landing gear isdown and locked.

Red lights indicate the landing gear is intransition either up or down. No lights

indicate the landing gear is full retracted.Brake temperature can be viewed via the BrakeTemperature panel on the First Officers panel.Brakes that are hotter than the acceptablerange will be less effective.

An ti -Ski d System

1. When active, the Anti-Skidsystem detects if one wheel isrotating at a different rate than theothers.

2. In that scenario, brakingpressure is reduced to thatwheel

3. Until the rotation is equal withthe others. At that point, normalbraking pressure is re-applied tothat wheel.


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Fuel Systems (LTMD Section 9)

This aircraft features three fuel tanks (Left, Center & Right) equipped with two A/C boost pumps each (Forward& Aft). The engines can be fed by any of the three fuel tanks by opening the Fuel Cross-Feed Valve. The

Cross-feed lever is located on the throttle pedestal. The right side fuel tank is equipped with a D/C Start Pumpfor starting the APU or engine when no A/C power is available on the aircraft.

Fuel flow and fuel used information be foundat the bottom of the Electronic SystemDisplay Panel (ESDP).

Fuel temperature information is also providedto determine the need for fuel heat use. Thefuel heat controls are located in the mainoverhead and should activated one side at atime.

A/C Bo ostPumps x6

D/C StartPump

Fuel CrossFeed Valve


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Fuel Systems (LTMD Section 9) - continued

Fuel Pump Contro ls (Main Overhead)

Left Main FuelQuantity

Right Main FuelQuantity

Center FuelQuantity

Total FuelQuantity

Zero Fuel Weight(ZFW) Select &Toggle Button

Gross AircraftWeight

Aft A/C BoostPumps X3

Aft A/C BoostPumps X3

D/C Start Pump

Fuel Heat


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Flight Controls (LTMD Section 10)

The Flight control services are arranged into three separate categories: Roll Control, Pitch Control, and YawControl.

Inboard &Outboard FlightSpoilers (Roll)

Aileron (Rol l)

Aileron TrimTab (Roll)

Ail eronControl Tab(Roll)

Elevator (Pitch)

Rudder (Yaw) Elevator TabsPitch

Side to side movement of t he yokemoves the aileron control tabs.

Forward and back movement of theoke moves the elevator co ntrol tabs.


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Flight Controls (LTMD Section 10) continued

Part of the flight controls system, this aircraft features two trailing edge flaps and leading edge slats on eachwing. The flaps and slats can be deployed via the flap handle on the throttle pedestal. Flap & Slat position canbe monitored using the Flap Position Indicator and Slat Advisory Lights on the on the Electronic SystemDisplay Panel (ESDP). Flap position is indicated in degrees.

Blue Indicator - Flaps and Slats intake-off configuration.

Yellow Indicator Slats position isin disagreement with handleposition or L/R slats are split.

Green Indicator Flaps andSlats in landing configuration.

(Not pictured) Blue Indicator Slats auto extended as aircraft nears stall scenario.


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Power Plant & Engine Controls (LTMD Section 11)

This aircraft is equipped with two Pratt & Whitney JT8D engines with a maximum thrust rating of 20,850pounds. The engines are started with pneumatic pressure which can be provided by 1) a ground starter unit, 2)the APU, 3) the opposite engine. When starting the engines, the Pneumatic Cross-feed valve levers must beopened to allow pressure to pass from the central duct to the engine or pressure from the other engine.

Pneumatic pressure travels from the central duct, through the open starter valve, and into theengine for start.


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Power Plant & Engine Controls (LTMD Section 11) continued

Each engine is equipped with two igniters (A & B) which can be activated via the engine start panel in theLower Overhead.

Engine Igniters Control OFF All Igniters Off. Sys A or B Activates the

corresponding igniter whenthe fuel lever (throttlepedestal) is activated.

BOTH Activates bothigniters when the fuel leveris activated.

OVRD Igniters areactivated regardless of fuellever position.

Thrust Rating Panel (TRP)Provides engine thrust (EPR) limits as calculated by the Flight Guidance Computer.

Left & Right EngineStart ValveControls

TO EPR for

takeoff thr ustmode.

MCT EPR forMaximumcontinuous thrust.

No Modeannunciator

TO FLX Forassumed tempreduced EPR.

Ass umed Tempselector for usewith TO FLX mode.

GA EPR limit forGo Around

CL EPR limit forclimb thrust.

CR EPR limit f orcruise thrust.

TRP Test But ton


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Flight Instruments (LTMD Section 12)

Al ti met er

Reference Airspeed Bugs

Takeoff1. V12. V2+203. Slat Retract4. Clean Speed

Landing1. Go Around2. Flap 15 Maneuver3. Slat Extend

4. Clean Speed

Ai rspeed Ind icato r

Radio Distance Magnetic Indicator (RDMI)

Alti tudeReference Bu g

Alt itude AlertLight

Barometricpressure setknob

Digital Alt itudeReadout

MB/IN HGReadout

VMO /OverspeedIndicator

A/T CommandBug

MACH Readout

ReferenceBu s x4

DME 1 & 2Display

VOR 2 / ADFSelector

VOR 1 / ADF

Selector


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Flight Instruments (LTMD Section 12) continued

Both sides of the flight deck feature an Electronic Flight Instrument System (EFIS) which consists of a Primary FlightDisplay (PFD) on top and the Navigation Display (ND) on the bottom.

Rose Mode

Arc Mode

Map Mode

Controls for the ND are located on the sideglareshield panel.

Plan Mode


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Flight Instruments (LTMD Section 12) continued

Weather, Turbulence and Terrain Topography can also be displayed on the ND. Controls for the weather radarare located between the FMS screens on both the Captains and First Officers Panel. The weather radarcontrols are arranged in a left and right configuration with the toggle buttons for the Captains ND locatedtowards the top and left of the panel and those for the First Officers ND on the lower and right side portion.The Power and Test buttons are located in the middle area of the panel and affect both NDs.

NOTE: Radar is never to be used while in the airport terminal area or within 100 feet of people.

Takeoff & Climb Settings

Tilt set to 4 up and reduced gain. During initial climb and below 10K feet, lower

tilt to 2 up and increase gain. Once about 10K feet, lower tilt and increase

gain as necessary. If cruise is above FL300, use down tilt to

ensure proper weather tracking.

Descent and Landin g Settings

Raise tilt as necessary to maintain weatherreturns during initial descent.

When below 10K feet, raise tilt to 2 and reducegain.

On final approach, raise tilt to 10 up andreduced gain.

Power OFF prior to approaching terminal areaor ground crew.

Transfer button changes theleft side display mode tomatch those set on the right.

TogglesWeathermode only.

IndicatorPower togg le.

Toggles GroundClutter Suppression.

Radar Tiltand Gaincontrols.

Toggles Weatherand Turbulencemode

Toggles RadarMap Mode. Toggles test

mode.


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Flight Instruments (LTMD Section 12 ) continued

Electron ic Engine Disp lay Panel (EEDP)

Electron ic System Display Panel (ESDP)

L & R ReverseThrust Light

L & R Reverse Thru stUnlock Light

L & R Engine EPR

L & R N2 Display

Fuel Flow & FuelUsed Display

L & R N1 Display

L & R EGT Display

EPR Limi t Readout

RAT Readout L & R FuelTemp

L & R OilPressure L & R Oil

Temperature

L & R OilQuantityMinimum fordispatch:12 qts

L & R HydPressure

L & R HydQuantity

Flap PositionIndicator

SlatsConditionIndicator


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Warning & Caution Systems (LTMD Section 13)

This aircraft features numerous visual and aural warning and caution alerts to ensure the flight crew is quicklyinformed of any problems. The majority of visual caution and warning messages can be found on the

Overhead Annunciator Panel (OAP).

The left side consists of two screens cable of displaying up to 6 messages in each in no priority based order. Any messages over the 12 message limit can be viewed by pressing the scroll buttons to the right of thescreens. Below the screens is a series of cue lights that flash when a related message is displayed. Pressingthese buttons will display messages to that specific system group.

On the far right of the OAP are the Warning and Advisory Lights. Red lights will also trigger the MasterWarning lights on the glareshield, blue lights indicate the specific systems status.

Master Warning & Master Caution Ligh tsLocated on both sides of the flight deck, these lights are quick indicators to anyspecific problems.


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Warning & Caution Systems (LTMD Section 13 ) continued

Warning systems controls (main overhead panel)

Stall Warning

Ground ProximityWarning System(GPWS)

Windshear AlertSystem

Overspeed WarningSystem


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Auto Flight Systems (LTMD Sect ion 14)

Located in the center area of the glareshield, is the Flight Guidance Control Panel (FGCP). This panelis divided into four main areas.

1. Speed

2. Lateral Aircraft Guidance3. Vertical Aircraft Guidance4. Altitude Hold

Flight DirectorSwitch

IAS SpeedSelect

FMSOverride

MACH SpeedSelect

EPR Limi t

SpeedSelectionKnob

Auto Throt tleEngage Swit ch

FMS NavMode

FMS NavMode

SelectedSpeedReadout

VOR NavMode

Auto LandSelect

HeadingReadout

ILS NavMode Turbulence

Mode

Alti tudeSelection Kno b

Selected Alti tude

Readout

Master Autopi lo tEngage

VerticalSpeedSelect Dial

VNAVMode

VerticalSpeedReadout

IAS /MACHMode

VerticalSpeed Mode

Alti tudeHold


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Auto Flight Systems (LTMD Sect ion 14) continued

A Flight Mode Annunciator (FMA) is located on both the Captains Panel and the First Officers Panel. Key autoflight related information is displayed on this panel, organized into four different parts: Throttle, Arm, Roll, &Pitch.

Comparator LightsThe FMA features (4) comparator lights which aremeant to indicate setting differences between thepilots. An illuminated light indicates a difference.

Engage LightsThe three engage lights on the right side of the FMAindicate whether the Flight Directory has beenengaged and which Auto Pilot system is currentlyselected.

A/TDisengageWarning

Autopi lo tDisengageWarning

SystemCautionLights

EngageLights

ResetButton

ComparatorLights x4


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Radios & Communications (LTMD Section 15)

Located in the Upper Overhead panel and on each Side Glareshield panel is the Audio Control Panel.

VHF Comm RadiosLocated on the Throttle Pedestal are the controls for the aircrafts VHF radios used to communicate with Air TrafficControllers. The desired frequency is tuned into the right side window, and then the transfer button is pressed toactivate the frequency.

AudioTransmitToggleButtons x7

AudioReceiveToggleButtons x1

ADF Recei veToggleSwitches x2


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Flight Management System (FMS) (LTMD Section 16)

The Mode Control and Display Unit (MCDU) is located on both Captains and First Officers panels and is usedto enter data into the Flight Management System (FMS).

Menu Ligh t Pending non-active change. Message Light System message in scratchpad. Display Light Current display not related to active route. Offset Light Indicated a NAV route offset.

Left LineSelect KeysX 6

Display Area

Right LineSelect KeysX 6

DisplayBrightnessControl

Page SelectKeys x 14

Execute Key

Menu Lig ht

MessageLight

Display Light

Offset Ligh t

NumericKeys

Alph a Keys


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Study Guide QuestionsIn this section, you will find a selection of questions based on the information presented within this Study Guideand the Learn the Mad Dog DVD.

Electrical System (LTMD Chapter 2)

1. What is the voltage limit for each engine generator?a. 110 +/- 5b. 115 +/- 3c. 120 +/- 2

2. What is the frequency limit for each engine generator?a. 400 +/- 4b. 415 +/- 5c. 315 +/- 5

3. Which power source has priority over ground power?

a. Auxiliary Power Unit (APU)b. Engine Generatorsc. Both A & B

4. When activating APU power, which APU bus switch must be moved to the ON position?a. Leftb. Rightc. Both

5. Emergency power is provided from the aircrafts battery.a. Trueb. False

Ai rc raf t Ligh ti ng (LTMD Chapter 3)

6. Which aircraft lights are mainly used for night time terminal servicing?a. Ground Flood Lightsb. Anti-Collision Lightsc. Wing & Nacelle Lights

7. Upon entering the aircraft, what lights should be confirmed on?a. Anti-Collision Lightsb. Position Lightsc. Flight Deck Flood Lights

8. How many positions do the landing light switches have?a. Oneb. Twoc. Three


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9. Thunderstorm lights are used to illuminate the clouds in the vicinity of the aircraft while operating duringstorms.

a. Trueb. False

10. What interior lighting system must be armed prior to departure?a. Emergency Lightsb. Flight Deck Flood Lightsc. Instrument Panel Integral Lights

Fire Detection & Suppression (LTMD Chapter 4)

11. The engine fire detection system consists of two detection loops in the engine nacelles and two in theengine exhaust area.

a. Trueb. False

12. During an engine fire, which fire suppression bottle should be discharged first?a. Left (Engine #1)b. Right (Engine #2)c. Either

13. What light will illuminate when a fire suppression bottle has been discharged?a. Master Warning Lightb. Caution Lightc. Agent Low Light

14. Where is the Cargo Fire Detection & Suppression panel located?a. Captains panelb. Aft Overhead Panelc. Glareshield Panel

15. Which position should the Fire Detection Loop switches be in prior to flight?a. Loop Ab. Bothc. Either Loop A or Loop B

Ai r & Pneu mat ic Sys tems (LTMD Chapt er 5)

16. Opening what valves will allow air pressure to move from the central duct to either side of the aircraftspneumatic system?

a. Outflow valveb. Bleed valvec. Crossfeed valve

17. Where are the controls for the Outflow valve found?a. Captains panelb. Main Overhead panelc. Throttle Pedestal


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18. What will cause the Cabin Altitude aural warning to sound?a. Cabin altitude greater than 10,000 feet.b. Malfunction of altitude holdc. Excessive climb rate

19. The Rate Limit Control can be used to limit the aircrafts angle of climb.a. Trueb. False

20. The Pressurization Panel is located where?a. First Officers Panelb. Main Overhead Panelc. Aft Overhead Panel

Ice & Rain Protect ion (LTMD Chapter 6)

21. What two types of systems provide ice protection?a. Hot Bleed Air & Cold Bleed Airb. Static Electricity & Hot Bleed Airc. Electrical Resistance Heating & Hot Bleed Air

22. What is the minimum pneumatic pressure needed for bleed air heating?a. 20 psib. 30 psic. 34 psi

23. Conditions at the departing airport are: 3 C and falling snow. Are icing precautions necessary?a. Yesb. No

24. Air Foil Anti-ice should be:a. Used in flight onlyb. Used whenever icing conditions are present (ground or air)c. Used only when near clouds

25. What part of the aircraft receives continuous bleed heat with Air Foil Anti-ice active?a. Forward strakesb. RAM air inletc. Wings

Hydraulic System (LTMD Chapter 7)

26. The normal operating pressure for both systems is:a. 3000 PSIb. 2500 PSIc. 2000 PSI


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27. Which side of the hydraulic system is also equipped with an auxiliary pump?a. Leftb. Rightc. Both

28. The transfer pump moves hydraulic fluid from one system to the othera. Trueb. False

29. How many accumulators are on this aircraft?a. Twob. Fivec. Eight

30. The left Thrust Reversers are powered by which side of the Hydraulic system?a. Leftb. Rightc. Both

Landing Gear & Brakes (LTMD Chapter 8)

31. What does the amber Gear Door Open light indicate?a. The nose and main gear doors are openb. The main gear doors are openc. A malfunction in the gear doors

32. What do red landing gear lights indicate?a. The landing gear is downb. The landing gear is upc. A disagreement between the gear position and the gear handle

33. When the aircraft is operating on a single hydraulic system, nose gear steering is restricted to:a. 45 degreesb. 55 degreesc. 65 degrees

34. If flaps are set greater than ____, the gear horn can not be silenced.a. 15 degreesb. 26 degreesc. 28 degrees

35. The Brake Temperature panel is located on what panel?

a. Main Overhead panelb. Captains panelc. First Officers panel


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Fuel Systems (LTMD Chapter 9)

36. How many fuel tanks is this aircraft equipped with?a. Twob. Threec. Five

37. Fuel can be cross-fed from the left tank to feed the right engine.a. Trueb. False

38. What is the maximum lateral fuel imbalance that is allowed?a. 1000 lbsb. 1500 lbsc. 2000 lbs

39. Fuel flow information can be found on the:a. Electronic System Display Panel (ESDP)b. Fuel Quantity Displayc. Primary Flight Display (PFD)

40. What fuel pump is typically activated when the APU is running?a. Left / Aftb. Right / Aftc. Center / Aft

Flight Contro ls (LTMD Chapter 10)

41. Aileron movement is achieved with the use of:a. Control Tabs

b. Elevator Tabsc. Direct input to the ailerons

42. Where are the aircrafts flaps located?a. Leading edge of each wingb. Trailing edge of each wingc. Trailing edge of the stabilizer

43. What does the Yaw Damper prevent?a. Rudder over controlb. A stall scenarioc. Dutch roll

44. What is the primary function of the elevators anti-float tabs?a. Prevent the aircraft from floating above the set altitudeb. Assist in moving the elevatorc. Improve pitch trim at high angles


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54. What should the Weather Radar tilt be set for take-off?a. +4 degreesb. +10 degreesc. -5 degrees

55. How many manual reference bugs are featured on the Airspeed Indicator?a. Twob. Fourc. Six

Warning & Caution Syst ems (LTMD Chapter 13)

56. What is also illuminated when any red warning light on the Overhead Annunciator Panel (OAP) istriggered?

a. Caution Lightsb. Master Warning Lightsc. Flight Deck Flood Lights

57. There are two systems as part of the aircrafts Stall Alert.a. Trueb. False

58. To display the door messages, the door cue light can be pressed on the:a. Aft Overhead Panelb. TRPc. Overhead Annunciator Panel (OAP)

59. How many messages can the Overhead Annunciator Panel (OAP) display at once?a. 12b. 10

c. 6

60. The Wind shear Alert system can be tested via a switch on the:a. Captains panelb. Main Overhead panelc. Glareshield panel

Au to Fli gh t Sys tem s (LTMD Chapter 14)

61. What forms of flight guidance can be controlled through the Flight Guidance Control Panel (FGCP)?a. Speed, Lateral, Vertical, Altitude Holdb. Speed, Vertical, Yaw, Altitude Hold

c. Speed, Altitude Hold

62. The Flight Director must be active to use the Flight Guidance Control Panel (FGCP).a. Trueb. False


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63. What acronym is used to identify the different parts of the Flight Mode Annunciator (FMA)?a. FIRPb. TRIPc. TARP

64. The Flight Mode Annunciator (FMA) is located on what panels?a. Main Overhead and Aft Overheadb. Captains & First Officersc. Side Glareshield Panels

65. Level 2 Flight Guidance Control consists of using what system(s)?a. Auto Throttle & Flight Directorb. Flight Director & Altitude Holdc. Flight Director only

Radios & Comm unic ations (LTMD Chapter 15)

66. What is used to select the auto input & output system to be used?a. Audio Control Panelb. FMSc. FMA

67. How many VHF radios is this aircraft equipped with?a. Oneb. Twoc. Three

68. The Audio Control Panel can be accessed via what two panel views?a. Aft Overhead & Glareshield panelsb. Main Overhead & Aft Overhead panelsc. Throttle Pedestal & Main Overhead panels

69. What navigation instrument displays information received from the ADF radio?a. RDMIb. VSIc. Altimeter

70. This aircraft is equipped with Selective Calling (SELCAL) equipment.a. Trueb. False


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Flight Management System (FMS) (LTMD Chapter 16)

71. The equipment used for input into the FMS is called:a. RDMI b. FMA c. MCDU

72. What two modes can the FMS operate in?a. LNAV & VNAV b. Flight Director & Auto Throttle c. Manual & Automatic

73. What is the bottom line of the MCDU display called?a. Enter Line b. Scratchpad c. Input Zone

74. What button must be pressed to approve any flight plan changes?a. Execute Keyb. Hold Keyc. Delete Key

75. The FMS can hold only one flight route at any one time.a. Trueb. False


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Answers1 B2 A3 C4 C

5 A

6 C7 B8 C9 B10 A

11 B12 C13 C

14 B15 B

16 C17 C18 A19 B20 B

21 C22 A

23 A24 A25 B

26 A27 B28 B29 B

30 A

31 B32 C33 B34 B35 C

36 B37 A38 B

39 A40 B

41 A42 B43 C44 C45 B

46 A47 B

48 B49 A50 C

51 B52 A53 C54 A

55 B

56 B57 A58 C59 A60 B

61 A62 A63 C

64 - B65 A

66 A67 B68 A69 A70 A

71 C72 A

73 B74 A75 - B


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NOTES


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NOTES

Study Guide Master

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