Chapter 5 operation of systems

Question 1

4 main control surfaces

Answer 1

• Elevators— control the movement of the plane about its lateral axis. PITCH
• Ailerons— controls the airplanes movement about its long. Axis
• Rudder— controls movement of the plane about its vertical axis. YAW
• Trim Tabs— are small, adjustable hinged surface on the aileron, rudder, or elevator control surfaces. Labor saving devices allow pilot to release manual pressure on the primary control

Question 2

Flight controls operated

Answer 2

Flight control surfaces are manually actuated through the use of either rod or cable system. Control wheel actuated the ailerons and elevator, rudder/braked pedals actuate the rudder

Question 3

Flaps fucntion

Answer 3

Moveable panels on the inboard trailing edges of the wings. Are hinged so that they may extend downward into the flow of air beneath the wings to increase both lift and drag. Permits slower airspeed and a steeper angle of descent during landing approach. Also shorten takeoff distance

Question 4

Landing gear system

Answer 4

Consist of tricycle system utilizing two main wheels and a steerable nosewheel. Turbulence spring steel main gear struts provide main gear shock absorption, nose gear shock absorption is provided by combination air/oil shock strut

Question 5

Braking system

Answer 5

Hydraulically actuated disc-type brakes are utilized on each main gear wheel. Hydraulic line connects each brake to a master cylinder located on each pilot;s rudder petals. By applying pressure to the top of either the pilot’’s or copilot’s set of rudder pedals, the brakes may be applied

Question 6

Hydraulic fluid

Answer 6

Mineral based hydraulic fluid(MIL-H-5606) odor similar to penetrating oil and dyed red

Question 7

Steering on ground

Answer 7

Nose wheel steering through simple system of mechanical linkage connected to the rudder pedals. When rudder petal depressed, spring loaded bungee(push pull rod) connected to the pivotal portion of a nosewheel strut will turn the nosewheel

Question 8

What engine does plane have

Answer 8

Horizontally opposed four-cylinder, overhead-valve, air cooled carbureted engine

Question 9

4 strokes occur in cylinder

Answer 9

Intake- piston starts its downward travel causing intake valve to open and the fuel air mixture to be drawn into the cylinder

Compression— beings when the intake valve closes, and the piston starts moving back to the top of the cylinder. This phase of cycle is used to obtain a much greater power output from the air mixture once its ignited

Power—begins when the fuel air mixture is ignited which causes tremendous pressure increase in the cylinder and forces the piston downward away from the cylinder head, creating the power that turns the crankshaft

Exhaust— is used to purge the cylinder of burned gases and beings when the exhaust valve opens, and the piston starts to move toward the cylinder head once again

SUCK, SQUEEZE, BANG, BLOW

Question 10

Carburetor

Answer 10

Process of mixing fuel and air in the correct proportions so as to form a combustible mixture. Vaporizes liquid fuel into small particles and mixes it with air. It measures the airflow and meters fuel accordingly

Question 11

Carburetor heat system

Answer 11

Carb. Heat valve (controlled by pilot) allows unfiltered heated air from a shroud located aroun an exhaust riser or muffler to be directed to the induction air manifold prior to the carburetor. Carburetor heat should be used anytime suspected or known carb. Icing conditions exist

Question 12

What change occurs when applying carb heat

Answer 12

Introduction of heated air into the carb. Will result in a richer mixture. Warm air is less dense, resulting in less air from the same amount of fuel. Use of carb can cause a decrease in engine power of up to 15%

Question 13

Throttle function

Answer 13

Allows pilot to manually control the amount of fuel/air charge entering the cylinders. This in turn regulates the engine speed and power

Question 14

Mixture control

Answer 14

Regulates fuel-to-air ratio. All planes incorporate mixture control, which the fuel/air can be controlled by the pilot during flight. Prevents the mixture from becoming too rich at high alts, due to decreasing air density. Lean mixture during cross country to conserve fuel and provide optimum power

Question 15

Fuel injection system

Answer 15

Injects fuel directly into the cylinder or just ahead of the intake valve

1. Engine driven fuel pump- provides fuel under pressure from the fuel tank to the fuel/air control unit
2. Fuel/air control unit- meters fuel based on the mixture control setting and sends it to the fuel manifold valve at a rate controlled by the throttle
3. Fuel manifold valve- distributes fuel to the individual fuel discharge nozzles
4. Discharge nozzles- located in each cylinder head, these inject the fuel /air mixture at the precise time for each cylinder directly into each cylinder intake port
5. Auxiliary fuel pump - Provides fuel under pressure to fuel/air control unit for engine starting and/or emergency use
6. Fuel pressure/flow indicators - measures metered fuel pressure/flow

Question 16

Ignition system the plane has

Answer 16

Engine ignition is provided by 2-engine driven magnetos, and two spark plugs per cylinder. Completely independent of the electrical system. Magnetos are engine-driven self contained units supplying electrical current without using an external source of current.

Question 17

Two main advantages of dual ignition

Answer 17

A. Increased safety in case one system fails the engine may be operated on the on the other
B. More complete and even combustion of the mixture, and consequently, impr9ved engine performance I.e. the fuel/air mixture burn toward the center

Question 18

Fuel system type

Answer 18

Gravity feed. Flows from two wing fuel tanks to a fuel shutoff valve and on the ‘on’ position allows it to flow thru. The fuel is mixed with air and then flows into the cylinders thru the intake manifold tubes

Question 19

Purpose of fuel tank vents

Answer 19

Fuel level in an aircraft fuel tank decreases,, a vacuum would be created within the tank which eventually result in a decreasing fuel flow and finally engine stoppage. Replaces fuel with outside air, prevents vacuum

Question 20

Fuel pump

Answer 20

These plans do not have fuel pump

Question 21

Fuel type

Answer 21

Fuel grade used is 100LL and color blue

Question 22

Manual primer

Answer 22

Primer’s main function is to provide assistance in starting the engine. The primers draws fuel from the fuel strainer and injects it directly into the cylinder intake ports. Results in quicker, more efficient engine start

Question 23

Electrical system

Answer 23

28 volt, direct current system powered by an engine-driven 60 amp alternator and 24 volt battery

Question 24

Circuits

Answer 24

Are protected from an overload condition by either circuit breakers or fuses or both. Same function as fuses except when overload, circuit breakers can be reset

Question 25

Electrical system provides power for

Answer 25

``` Radio Turn coordinator Fuel gauges Pitot heat Landing light Taxi light Strobe lights Interior lights Instrument lights Position lights Flaps (maybe) Stall warning system Oil temperature gauge Electric fuel pump ```

Question 26

Ammeter

Answer 26

Indicates the flow of current in amperes, from the alternator to the battery or from the battery to the electrical system with the engine running and master switch on, ammeter will indicate the charging rate to the battery. If off-line and is no longer functioning or electrical load exceeds output of the alternator. Indicates discharge

Question 27

Voltage regulator

Answer 27

Device which monitors system voltage, detects changes, and makes required adjustments in the output of the alternator to maintain regulated system. Does it a low and high RPM

Question 28

Generator/alternator voltage output slightly higher than battery voltage

Answer 28

The difference in voltage keeps the battery charged, 12 volt battery would be supplied with 14 volts

Question 29

Cabin heat

Answer 29

Fresh air, heated by an exhaust shroud, is directed to the cabin through a serious of ducts

Question 30

How is temp controlled in cabin

Answer 30

Controlled my mixing outside air(cabin air control) with heated air (cabin heat control) in a manifold near the cabin firewall. This air is then ducted to vents located on the cabin floor

Question 31

5 basic functions of aircraft engine oil

Answer 31

Lubricates- the engines moving parts Cools- the engine by reducing friction Removes- heat from the cylinders Seals- provides a seal between the cylinder walls and pistons Cleans - by carrying off metal and carbon particles and other oil contaminants

Question 32

How carb icing occurs

Answer 32

Vaporization of fuel, combined with expansion of air as it passes thru the carb, causing sudden cooling of mixture. The temp of air passing through the carb may drop as much as 60F within a fraction of a second. Water vapor is squeezed out by the cooling and if temp in carb reaches 32F or below, moisture will be deposited as frost or ice inside the carb

Question 33

Indication of carb icing

Answer 33

In fixed pitch plane, first indication is loss of RPM | Controllable pitch, drop in manifold pressure

Question 34

Method in determine carb ice has been eliminated

Answer 34

When heat is first applied will be drop in RPM and if ice is present there will be a rise in RPM (usually with engine roughness) and when carb heat is turned off RPM will rise to a setting greater than that before application of heat and engine should run more smoothly

Question 35

What conditions are favorable for carb icing

Answer 35

When temps are below 70F and the relative humidity is above 80%. But because of sudden cooling that takes place in carb icing can occur even with temp as high as 100F and humidity as low as 50%

Question 36

Anti icing equipment

Answer 36

Prevents ice from forming on certain protected surface. Examples: heated pitot tubes and static ports, carb heat, heated fuel vents, prop bladed with electrothermal boots, and heated windshields

Question 37

Deciding equipment

Answer 37

Removes ice that has already formed on protected surfaces. Pneumatic boots on the wing and tail leading edges

Question 38

How decking system works

Answer 38

Upon actuation, boots attached to the wing leading edges inflate with air from pneumatic pump to break off accumulated ice. After few seconds of inflation they are deflated back to their normal position with vacuum assistance

Question 39

Detonation

Answer 39

Is uncontrolled explosive ignition of the fuel/air mixture within the cylinders combustion chamber. Causing excessive temp and pressure which, if not corrected, can quickly lead to failure of the piston, cylinder, or valves. Can also cause engine overheating, roughness, or loss of power. Detonation is characterized by high cylinder head temperatures and most likely occur at high power settings

Question 40

Operational causes of detonation

Answer 40

A. Using lower fuel grade B. Operating with extremely high manifold pressure in conjunction with low RPM C. Operating the engine at high power settings with an excessively lean mixture D. Extended ground operations or steep climbs where cylinder cooling is reduced

Question 41

What action should be taken if detonation is suspected

Answer 41

A. Ensure that proper grade of fuel is used B. Keep the cowl flaps in full open position while on ground C. Use an enriched fuel mixture, as well as a shallow climb angle, to increase cylinder cooling during takeoff and initial climb D. Avoid extended, high power, steep climbs E. Develop habit of monitoring the engine instruments to verify proper operation according to procedures established by the manufacturer

Question 42

Preignition

Answer 42

When fuel/air mixture ignites prior to the engines normal ignition event resulting in reduced engine power and high operating temp. Premature burning usually caused by a residual hot spot in the combustion chamber, often created by a small carbon deposit on a spark plug, cracked spark insulator or other damage in the cylinder that causes a part to heat sufficiently to ignite the fuel/air charge. Can cause severe engine damage, because the expanding gases exert excessive pressure on the piston while still on its compression stroke

Question 43

Action taken if preignition is suspected

Answer 43

A. Reduce power B. Reduce the climb rate for better cooling C.enrich the fuel/air mixture D. Open cowl flaps

Question 44

If no drop of RPM when a magneto is turned off (example when the right is turned off)

Answer 44

Meaning left P-lead is not grounding, or the engine has been running only on the right magneto because the left has totally failed

Question 45

Ammeter indications

Answer 45

``` Right deflection (positive) - after starting —> power from the battery used for startin is being replenished by the alternator; or if a full-scale charge is indicated for more than 1 min, the starter is still engaged and a shutdown is indicated -during flight —> a faulty voltage regulator is causing the alternator to overcharge the battery. Reset the system and if the condition continues, terminate the flight asap Left deflection (negative) - after starting —> it is normal during start. At other times indicates the alternator is not functioning or an overload condition exists in the system. Battery not receiving charge - during flight —> the alternator is not functioning or an overload exists in the system. Battery is not receiving a charge. Possible causes: master switch was accidentally shut off, or alternator circuit breaker tripped ```

Question 46

If ammeter indicates a continous discharge while in flight

Answer 46

Alternator has quit producing charge, alternator circuit breaker should be checked and reset and if still problem A. Alternator should be turned off, pull the circuit breaker B. All electrical equipment not essential to flight should be turned off C. Flight should be terminated and a landing made as soon as possible

Question 47

Ammeter indicates a continuous charge while in flight

Answer 47

Excessive rate of charge for extended period of time, battery will overheat and possible explosion of battery and electronic components in electrical system would be affected. Overvoltage sensor will shut the alternator dow. Following should be done A.alternator should be turned off; pull the circuit breaker B. All electrical equipment not essential to flight should be be turned off C. The flight should be terminated and a landing made as soon as possible

Question 48

Oil pressure is low and oil temp is normal

Answer 48

Result of: Insufficient oil | Oil temp remains normal, a clogged oil pressure relief valance or an oil pressure gauge malfunction could be culprit

Question 49

Partial loss of power in flight

Answer 49

First priority is to establish and maintain a suitable airspeed (Vg) and select emergency landing and remain with gliding distance Checklist: A. Check carb B. Check amount of fuel and switch tank if necessary C. Check fuel selector valves current position D. Check mixture control E. Check the primer control is all the way in and locked F. Check operation of the magnetos in all 3 positions, both left or right

Question 50

Engine fire in flight

Answer 50

``` A. Set the mixture control “idle cutoff’ B. Set fuel selector valve ‘off’ C. Turn master switch ‘off’ D. Set cabin heat and air vents ‘off’ E. Establish 100 KIAS and increase descent F. Execute forced landing checklist ```

Question 51

Engine fire on ground

Answer 51

``` Continue to attempt an engine start as a start will cause flames and excess fuel to be sucked back through the carb A. If engine starts: - increase power to higher RPM for a few moments and - shut down engine and inspect it B. Engine does not start - set throttle to full position - set mixture control to idle cutoff - continue to try engine start in an attempt to put out the fire by vacuum C. Fire continues - turn ignition ‘off’ - turn master switch ‘off’ - set fuel selector ‘off’ ```

Question 52

Operative off the pitot/static system

Answer 52

Altimeter Vertical speed Airspeed indicator

Question 53

How does altimeter work

Answer 53

Aneroid wafers expand and contract as atmospheric pressure changes, and through a shaft and gear linkage, rotate pointers on the dial of the instrument

Question 54

Limitations of pressure altimeter

Answer 54

non standard temp, temp variation expand or contract the atmosphere and raise or lower pressure levels that the alt senses Warm day — pressure level is higher than on standard day and indicates lower than actual alt Cold day — pressure level is lower than on a standard day. Alt indicates higher than actual

Question 55

Changes in surface pressure affect pressure levels

Answer 55

Higher than standard pressure — pressure level is higher than on a standard day. Alt indicates lower than actual Lower than standard — pressure level is lower than a standard day. Alt indicates higher than actual alt Hot to low or hot to cold, look at below

Question 56

Absolute alt

Answer 56

Vertical distance of an aircraft above the terrain

Question 57

Indicated alt

Answer 57

Alt read directly from the altimeter (uncorrected) after it is set to the current altimeter setting

Question 58

Pressure alt

Answer 58

Alt when the altimeter setting window is adjusted to 29.92. Pressure alt is used for computer solutions to determine density alt, true alt, true airspeed

Question 59

True alt

Answer 59

True vertical distance of the aircraft above sea level. Airport, terrain, and obstacle elevations found on aeronautical charts and true alt

Question 60

Density alt

Answer 60

Pressure alt corrected for nonstandard temp variations. Directly related to an aircrafts takeoff, climb and landing performance

Question 61

Airspeed indicator operate

Answer 61

Sensitive, differential pressure gauge which measures the difference between impact pressure from pito head and undisturbed atmospheric pressure from the static source. Difference registered by the airspeed pointer on the face of the insturment

Question 62

Limitations of IAS

Answer 62

Subject to proper flow of air in the pitot/static system

Question 63

Errors of IAS

Answer 63

Position error — caused by static ports sensing erroneous static pressure, slipstream flow causes disturbances at the static port preventing actual atmospheric pressure measurement. Varies with airspeed, alt, and configuration Density error — changes in alt and temp are not compensated for by the instrument Compressibility error — caused by the packing of air into the pito tube at high airspeeds, resulting in higher than normal indications Usually not factor at low airspeeds

Question 64

IAS

Answer 64

Indicated | What reads on indicator and not corrected

Question 65

CAS

Answer 65

Calibrated Corrected for position and insturment errors Same as TAS on sea level and stand temp

Question 66

EAS

Answer 66

Equivalent Corrected for position and instrument errors And adiabatic compressible flow for particular alt Same as CAS on stand temp and sea level

Question 67

TAS

Answer 67

True Corrected for alt and non standard temp Speed of airplane in relation to the air mass which it is flying thru

Question 68

Airspeed limitations not marked on indicator

Answer 68

Va Vlo Vx Vy

Question 69

Vertical speed indicator operates

Answer 69

Pressure differential insturment. Inside case in an aneriod. Inside aneriod and instrument case are vented to the static system. Case is vented thru a calibrated orifice causes pressure inside the case to change more slowly than the pressure inside the aneroid. Aircraft ascends, static pressure becomes lower and the pressure inside the case compresses the aneroid, moving the pointer upward, showing a climb and indicating number of feet per minute the aircraft is ascending

Question 70

Limitations of VSI

Answer 70

Not accurate until plane is stabilized. Because of restriction in airflow to static Lin, 6-9 second lag is required to stabilize the pressures. Sudden movement will cause crazy reading and unreliable

Question 71

Instruments contain gyroscopes

Answer 71

A. Turn coordinator B. Heading indicator (directional gyro) C. Attitude indicator (artificial horizon)

Question 72

Fundamental properties of a gyroscope

Answer 72

Rigidity in space — gyroscope remains in a fixed position in the plane in which it is spinning Precession — titling or turning of a gyro in response to a deflective force. Reaction to this force does not occur at the point where it was applied. Rather occurs at a point that is 90 degree later in direction of a rotation. Rate at which the gyro precesses is inversely promotional to the speed of the rotor and proportional to the speed of the rotor and proportional to the deflective force

Question 73

Power sources for gyro

Answer 73

Some planes all are vacuum, pressure, or electrical. Others vacuum or pressure proved power for the heading and attitude, while electrical provides the power for the turn coordinator. Most planes have at least two sources of power to ensure at least one source of bank infor if on power source fails

Question 74

Vacuum system operation

Answer 74

Engine driven vacuum pump provides suction which pulls air from the instrument case. Normal pressure entering the case directed against rotor vanes to turn the gyro at high speed. Air drawn thru a filter from cockpit and vented outside

Question 75

Attitude indicator operation

Answer 75

Gyro in the attitude indicator is mounted on horizontal plane and depends upon rigidity in space for its operation. Horizon bar represents the true horizon and is fixed. Plane is pitched or banked about its lateral or longitudinal axis indicating attitude relative to true horizon

Question 76

Limitation of attitude inidcator

Answer 76

Pitch and bank limit depend on make of instrument. Banking limit from 100 -110 and pitch limits from 60 to 70. If exceed the instrument will tumble or spill and give incorrect indications, until reset. Modern ones usually don’t tumble

Question 77

Errors of attitude indicator

Answer 77

Usually free of errors. But depending on speed may be slight nose-up indication during rapid acceleration and nose down during rapid deceleration. And possible small bank angle and pitch error after 180 degree. Small errors and correct themselves

Question 78

Heading indicator operate

Answer 78

Uses rigidity in space. Rotor turns in vertical plane and compass card is fixed to the rotor. Since rotor remains rigid in space, the points on card hold the same position in space relative to vertical plane

Question 79

Limitations of heading

Answer 79

Exceeding 55 degree of pitch or bank it might tumble or spill and wrong indications until reset

Question 80

Errors of heading

Answer 80

Because of precession heading will drift or creep from heading which it is set. Could show 15 degree error every hour

Question 81

Turn coordinator operate

Answer 81

Turn point uses precession to indicate direction and approximate rate of turn. Gyro reacts by trying to move in reaction to the force applied thus moving the needle in proportion to the rate of turn. Slip/skid is a liquid tube with a ball that reacts to centrifugal force and gravity

Question 82

What info does turn coordinator provide

Answer 82

Shows yaw and roll of plane around the vertical and long axis

Question 83

Slip

Answer 83

Ball in tube will be on the inside of the turn , not enough rate of turn for the amount of bank

Question 84

Skid

Answer 84

The ball in the tube will be to the outside of the turn. Too much rate of turn for the amount of bank

Question 85

Magnetic compass operate

Answer 85

Magnetic needles fastened to a float assembly, around which is mounted a compass card, align themselves paralle to the earths lines of magnetic force. Float housed i a bowl filled with acid-free white kerosene

Question 86

Limitations of magnetic compass

Answer 86

Jewel and pivot type mounting allows the float to rotate and tilt up to approx 18 degree angle of bank. Steeper bank angles it is unstable and erratic

Question 87

Oscillation error

Answer 87

Erratic movement of compass card caused by turbulence or rough control technique

Question 88

Deviation error

Answer 88

Due to electrical and magnetic disturbances in plane

Question 89

Variation error

Answer 89

Angular difference between true and magnetic north, reference isotonic lines of variation

Question 90

ANDS

Answer 90

Accelerate North Decelerate South

Question 91

UNOS

Answer 91

Undershoot North Overshoot South

Question 92

AHRS

Answer 92

Attitude and heading reference system. Provide heading, attitude and yaw info

Question 93

ADC

Answer 93

Air data computer. Aircraft computer that receives and processes pitot pressure, static pressure, and temp to calculate precise alt, indicated airspeed, true airspeed, vertical airspeed and air tep

Question 94

PFD

Answer 94

Primary flight controls. Easy to scan display that shows horizon, airspeed, alt, vertical speed, trend, trim, rate of turn and etc

Question 95

MFD

Answer 95

Multi function display. Cockpit display capable of presenting info (navigation data, moving maps and etc

Question 96

FD

Answer 96

Flight director. An electronic flight computer that analyzes the navigation selections, signals, and aircraft parameters. Presents steering instruction on the flight display as command bars or crossbars for pilot to position the nose of the aircraft over to follow

Question 97

FMS

Answer 97

Flight management system. Computer system containing database for programming or routes, approaches and departures that can supply navigation data to the flight director/autopilot from various sources and can calculate flight data such as fuel consumption, time remaining, possible range and other values

Question 98

INS

Answer 98

Inertial navigation system. Computer based tracks the movement of aircraft via signals produced by onboard accelerometers. Initial location is entered and all subsequent movement is then sensed and used to keep the aircrafts position updated

Question 99

Magnetometer fucntion

Answer 99

Device that measures strength of the earths magnetic field to determine aircraft heading. Provides info digitally to the AHRS and sends it to the PFD

Question 100

FMS/RNAV verification effective dates

Answer 100

Dates shown up on start up screen

Question 101

AHRS system initialization

Answer 101

Some must be initialized on the ground prior to departure. Allows it to establish a reference attitude and used as benchmark

Question 102

Standby avionics

Answer 102

Attitude indicator, airspeed indicator, altimeter

Question 103

Display failure occurs

Answer 103

Will result in partial loss of navigation, communication, and gps capability

Question 104

One display fails (PFD or MFD)

Answer 104

Some systems offer a reversion capability to display the primary flight instruments and engine instruments on the remaining operative display

Question 105

ADC fails

Answer 105

Inoperative airspeed, alt, and vertical airspeed indicator shown with red Xs indicates of failure of the air data computer

Question 106

AHRS fails

Answer 106

Inoperative attitude indicator shown with red X

Question 107

Loss of magnemoter

Answer 107

Affects AHRS. Heading info will be lost