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154 Cards in this Set
- Front
- Back
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Large scale |
Shows small area in more detail |
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Small scale |
Shows large area in less detail |
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Main problem in map construction |
There is always some distortion portraying a round area on a flat surface |
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Cylindrical projection |
Opening a sphere earth over a cylinder for a map |
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Mercator limitations |
Excessive scale expansion Enormous area distortion in higher latitudes Great circles are plotted as curved lines |
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Conformality |
the correct representation of angles -meridians and parallels must intercept at right angles -scale must be the same in all directions or changes at a constant rate |
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Latitude |
Parallel A small circle on the surface of the earth whose plane is parallel to the equator |
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Longitude |
Meridian a semi great circle on the surface of the earth joining the poles of the earth |
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Orthomorphism |
Shapes are correctly defined - Map must be conformal - scale must be same in all directions |
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Map Definition |
A small scale, flat surface representation of some portion of the earths surface |
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SCALE |
A ratio of a given distance on a map to the actual distance on the earth |
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Methods of expressing Scale |
Representative fraction Statement in words graduate scale |
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Which type of map would you use if you were doing a sar mission in the north |
POLAR STEREO |
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Desirable Map Properties |
Great circles Straight Lines Rhumb lines Straight lines Angles Correct Shapes Correct Size Correct Scale Correct and Constant |
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Polar Stereo Limitations |
Used in high altitudes only |
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Desirable Properties of a TOPOGRAPHICAL MAP |
Orthomorphic Conformal Sufficient Details |
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Topographical Maps used in the CF |
LAMBERT CONFORMAL -ONC, VNC TRANSVERSE MERCATOR - VTA (VFR Terminal Chart) -CPC (Canadian pilotage Chart) |
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Methods of Showing Releif |
Contours Spot Heights Layer Tinting Hill Shading Hachures |
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Effective map reading |
WATCH, MAP, GROUND -Orient the map to the direction of flight -find a DR position down track by calculating ---- approximately where you'll be at a given time -Study the map to find the checkpoint -Find the landmark on the ground |
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Oblate Spheroid |
Spherical geometric shape flattened at the poles and bulged at the equator. symmetrical body with shape similar to earth but smooth surface |
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Great Circle |
Circle on surface of a sphere whose center and radius are the same as the sphere itself. Divides sphere into 2 equal parts |
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Small Circle |
Circle on surface of a sphere whose radius and center do not coincide with the sphere |
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Equator |
Particular great circle whose plane is perpendicular to the rotation of the earth |
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Ratio of NM-SM-KM |
66 NM= 76 SM = 122 KM |
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Nautical Mile |
an arc of curvature along the surface of the earth subtending 1 minute from the center of the earth Standard unit of linear measurement in aviation |
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rhumb line |
a regularly curved line on the surface of the earth which cus all meridians at the same angle Constant direction relative to the poles parallels of equator, Latitudes and meridians are all Rhumb lines |
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Direction |
the path pursued by a moving body the point to which one moves or looks |
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Navigation |
the process or activity of accurately ascertaining one's position and planning and following a route. |
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Agonic line |
the line joining points of zero variation |
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isogonal |
points of equal variation joined on a map or chart by lines |
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Formula for finding true bearing |
TB = RB + TH |
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what are the advantages of a Jeppesen computer? |
light, multi purpose, no detachable parts, accurate, lifetime power source |
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Define velocity |
Rate of change of position in a given direction |
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Define Vector |
Graphical representation of a velocity |
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Define true Air speed |
the speed of the aircraft in knots relative to the still air mass surrounding it |
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Speed/ time / distance trick for NM to SM |
add 1/7 of the NM |
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speed time distance trick for SM to NM |
subtract 1/8 of the SM |
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miles per minute at intervals of 30kts |
120 = 2nm/min 150 = 2.5 180=3 210=3.5 240=4 etc |
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Max drift formula |
wind speed X 60 ______________________ TAS (nm a minutes |
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wind effect formula |
Max drift = Wind speed __________________ TAS |
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One in 60 rule |
every 1 degree off course will be 1 nm after traveling 60nm |
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ADF Frequency limits |
Automatic direction finding 190.0 - 1799.0 kHz |
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Feature identification |
Big to small Known to unknown 3 confirming features Far to near |
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What is applied to compass to get true bearing for ADF |
Deviation for RMI variation for AC location |
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VOR unable to receive signal, what will happen |
Needle will park in the horizontal position |
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How is DME calculated |
Transmitts interrogation signal, receives response, calculates the distance for the slant |
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What is the standard circuit height
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1000ft AAE |
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What direction are the turns in a standard circuit |
Left |
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What info is contained in an ATIS |
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What agency controls all RWY and taxiways |
Tower |
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Publication that contains Aerodrome circuit information
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GPH 205 procedure section |
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AMORTTS |
Minimums Overshoot Radios Timings Transition Speeds |
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What aerodrome area is controlled by the Tower
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200ft of all runways and taxiways as well as all airspace in the control zone
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What does clearance delivery do
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deliver clearances for aircraft on flight, as well as the ariways to use |
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what are the frequencies for 17 wing ops
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131.4 (vhf) |
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Main difference between controlled and uncontrolled aerodromes |
uncontrolled have no tower control May have a tower but may not be in operation |
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what is the size and broadcast frequency of MF area |
unless otherwise published in the gph 205 |
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what altitude do you climb to before turning onto the flight plan circuit altitude |
Above circuit Altitude
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What types of transmissions might be made in an uncontrolled aerodrome
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broadcast transmission not directed to a particular location |
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What publs are required to monitor Departure and Arrival
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VTA, GPH 200, FLIPS |
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Dimensions of MF area
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5 NM, 3000 ft, AAE |
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3 main ACSO duties |
ensure clearances are followed ensure above procedures don't present hazards |
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ICAO standard atmosphere
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15 degrees celcius 2 degrees per 1000 ft 1 Millibar = 30 ft 1" Hg = 1000 ft |
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Temperature OAT
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Can be corrected by computer or Jeppeson computer |
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pressure sensitive altimeter |
displays altitude corresponding to ISA |
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Airspeed indicator
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needs the differential pressure to measure airspeed |
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airspeed indicator componants |
aneroid capsule fed with pitot pressure pointer system with calibrated dial |
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Can true OAT be measured in the DASH-8
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no, only the IOAT can be |
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How many air sensors does the DASH 8 have |
2 pitot tubes, 2 static ports, 1 OAT sensor |
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Does change in temperature affect the pressure of a column of air |
yes |
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does pressure sensitive altimeter use pitot pressure or static pressure
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static pressure |
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how do sensors determine airspeed?
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differential pressure q= H-P |
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what are 4 errors in pressure sensitive altimeters
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instrument position mechanical lag |
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What is QNE |
Q code designator for standard pressure 29.92 gives pressure altitude |
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How will the altimeter read in a air mass colder than ISA? Warmer than ISA
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Colder Air Mass = higher reading then actual altitude Warmer air = lower reading than actual altitude |
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Calibrated Airspeed
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IAS corrected for instrument and position error (AKA RAS) |
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Equivalent Airspeed |
CAS corrected for compressibility (omitted below 250 kts)
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True Airspeed
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CAS (or EAS above 250 kts) corrected for pressure and temperature |
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Mach number |
TAS/ Speed of sound |
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Mach meter |
Shows aircraft speed relative to speed of sound |
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Airspeed indicator componants |
Air tight Case with Static pressure anaeroid capsule with pitot pressure pointer system with calibrated dial |
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Errors and corrections for Airspeed indicator
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Position and attitude error density error (most common) Compressibility error |
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4 errors inherent in pressure sensitive altimeters |
temperature error instrument error position error Lag |
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componants of a pressure sensitive altimeter |
airtight casing Aneroid capsule static pressure source mechanical gears and levers display |
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When you are in a warm air mass, what is the relationship between the altimeter reading and absolute altitude |
in a warm air mass, the altimeter will read lower than absolute altitude In a cold air mass the altimeter will read higher than actual altitude (dangerous at low altitudes) |
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How is air speed measured? |
differential pressure q=H-P |
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does change in temperature affect a column of air? |
yes |
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does pressure sensitive altimeter us pitot pressure or static pressure to calculate altitude |
static pressure |
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QNF |
observed pressure above ground (not used in NA) |
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absolute Altitude |
Actual height above terrain |
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what altitude will be displayed on a pressure sensitive altimeter with QNH set while on the ground |
Station elevation |
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Weather Avoidance |
5-10-20-30 5 NM below freeing level 10 NM above freezing level 20 NM when above 30000' |
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Advantages of INS |
Self contained does not radiate unjammable all weather operation worldwide operation very accurate position and altitude information |
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Generic INS componants |
accelerator computers stable platform control display unit |
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Newton's first law |
a body at rest remains at rest; or if in motion, remains in uniform motion with constant speed in straight line unless acted on by external force |
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newton's second law |
acceleration is proportional to magnitude of force and inversely proportional to the mass of a body |
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Desired Cahracteristics of Accelerometer |
Low threshold sensitivity wide range of sensitivity linear output high resolution |
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Strapdown INS system |
Reductions in: - system hardware and weight - power consumption - maintanance - cost Increase in - reliability - service life |
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how does a ring lazer gyro detect changes in motion or location |
- PHASE SHIFT - What is detected when the twoopposing laser beams in a RLG are recombined after an angular displacement ofthe gyro - Aphase difference in the two beams as a result of differing path lengths due toangular rotation of the cavity caused by movement of the gyro |
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how are differential path errors eliminated in RLG |
through the use of one CREVIT cavity ensuring uniform temperature for both lazers |
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what is the largest source of errors in a RLG |
Lock in errors due to non perfect optics within the cavity causing back scattering Back scattering tends to reinforce the energy travelling in the opposite direction |
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how is lock in error eliminated |
mechanical Bias (dithering) where any error caused by vibration of the RLG is averaged out and eliminated (eliminating the Back scattering) |
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main disadvantage of INS systems |
degrading accuracy over time |
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INS integration Advantages |
- much improved accuracy - higher mission completion rate as sensors may be used independently |
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4 INS hybrid systems |
Ground Referenced Hybrid system GPS -INS hybrid Doppler INS hybrid Celestial - INS hybrid |
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Leveling |
no component of gravity sensed by x and Y accelerometers |
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azimuth alignment |
alignment of the azimuth sensitive system axis referenced to TN |
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types of alignment |
self alignment reference alignment moving alignment in flight alignment |
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initialization conditions (10) |
2 initial position coordinates (LAT LONG) 2 initial velocities (N&E) 3 initial orientations (X,Y,Z axis) 3 orientation rates |
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self alignment sequence |
warm up coarse leveling coarse azimuth alignment fine leveling fine alignment |
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high latitude alignment problems |
undetectable tilt preventing initiation of gyro inability to accurately resolve TN problematic at latitudes above 70 degrees |
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unbounded errors |
Unbounded will keep getting worse until corrected leveling gyro drift initial azimuth misalignment azimuth gyro drift |
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bounded errors |
3 main sources of bounded errors - initial leveling (platform tilt computer error) - Accelerator (acceleration errors) - first integrator errors (velocity errors) |
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how long is a schuler cycle and what is it |
84.4 minutes one schuler period is the time it takes for the error to apear and come back to the original value before restarting the error cycle |
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Honeywell YG1854 Laseref componants |
IRS on CT-142 Inertial reference unit Mode selector unit |
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Honeywell YG1854 Laseref power requirements |
The IRU receives AC and DC power from theaircraft, and provides switching to primary AC or secondary DC. NOTE: The IRU can operate with either 115V AC or 28V DC power |
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Honeywell YG1854 Laseref cooling requirements |
The IRUrequires a cooling air supply.
Cool airis supplied via the aircraft air conditioning system or the AC/DC blowerkits. A loss ofcool air will necessitate shutting off the IRU after a specified time. |
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IRU provides 4 inertial modes |
Off Nav Align Attitude |
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Align inertial mode |
Completesalignment in a minimum of 2.5 minutes at the equator and a maximum of 10minutes at 60° to 70° latitude.· Atlatitudes above 70° additional alignment time may be required. |
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Nav inertial mode outputs |
aircraft attitude body rates body accelerations true heading velocity vectors wind data lat and long inertial altitude |
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IRS integration with the ATS |
o Informationis fed from the IRU directly to the ATS. The ATS maintains a data base of inertial information, including:§
True heading§ True track angle (TMG)§ Present latitude and longitude§ Inertial groundspeed§ Wind velocity (speed and direction)§ System status |
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GPS unique capabilites |
-provides highly accurate 3D position -Provides velocity vector and time -global coverage -continuous availability -passive service -unlimited number of users -somewhat resistant to interference -spread spectrum -allows common grid reference |
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GPS distinct Segments |
space segment control segment user segment |
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space segment - how many sattelites in GPS system |
27 active and 4 spare satellites in 6 orbital planes |
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GPS user segment - what are the receiver componants |
antenna signal processing equipment computer oscillator |
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GPS Clock |
each satellite has 4 atomic clocks -2 cesium 2 rubidium margine for error - 1 nanosecond = 1 foot position error |
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GPS receiver Clock |
crystal oscillator pseudo ranging calculates difference in timing accuracy between satellite and receiver clock bias |
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C/A code |
Clear access Code 37 codes assigned to GPS satellites C/A code is 1023 bits long transmitted at rate of 1.023 Mbps provides position accurace of 7.8 meters 95% of time |
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P Code (position code) |
broadcasts on L1 and L2 frequs when encrypted is known as Y code 267 day long code, each satellite has a unique 7 day portion of the code 10.23 Mbps transmission rate |
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GPS operating frequency |
satellite clock operates at 10.23 MHz and L1 is 154 times 10.23 MHz =1575.42 L2 is 120 times 10.23 MHz = 1227.6 |
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GPS Pseudo random codes |
satellites and receivers are synchronized generating the same signal simultaneously receiver then compares the signal to its self generated signal to come up with time difference and thus, a range pseudo random codes repeated every millisecond |
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GPS Navigation Message |
- Contains the info required by the receiver toperform the operations and computations required to navigate using GPS. - The messageis superimposed over the C/A and P codes- It is dividedinto 5 sub-frames and takes 30 seconds to receive
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EPHEMERIS |
prediction and updates for individual satellites orbital position transmitted to receiver in nav message |
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almanac |
catalog of ephemeris data for all satellites continually updated in the user receiver and new ephemeris data is received |
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UNS-1C FMS componants |
2 control display unit 1 Data Transfer Unit 2 Air data converter unit 2 Glareshield advisories 2 Gps Antenna Config Module |
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RNAV: Area Navigation |
“Method of navigation thatpermits aircraft operation on any desired course within the coverage ofstation-referenced navigation signals or within the limits of a self-containedsystem capability, or a combination of both.” |
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RNP |
required NAvigation performance a statement of the navigation performance accuracy necessary for operation within a defined airspace |
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Magnetic variation runs out at what longitude |
73 degrees (CT 142 not certified beyond 73) |
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Code lock |
when two signals match and is also point of highes signal to noise ratio. this point is remained for the remainder of the flight |
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carrier tracker loop[ |
crystal oscillator develops a frequency which it adds to the incoming frequency to compensate for Doppler shifts due to motion |
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User Range Error (URE) |
error in measurement of the distance from the satellite to the receiver P code up to 6.6M 95% of time C/A code up to 13.9 M 95% of the time |
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Dilution of precision DOP |
comes from having a fix geometry of less than 90 degrees error from less than perfect geometry |
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LAAS |
Local area augmentation System Ground Based used for RNAV approaches RAIM Checks required |
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WAAS |
Wide Area Augmentation System Space based must have WAAS capable FMS Both Pilots must be qualified to fly a WAAS approach |
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Aircraft GPS information to Emulated GPS |
GPS position time satellite information system status altitude ground speed ground track |
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control zone |
Class C 7NM centered on aerodrome surface below 3000' controlled by tower |
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TRA |
Class C 13NM centered on VOR 2000-3000ASL controlled by tower |
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terminal control area |
- Class B 35NM centered on VOR above 12500 to 18000ASL extension to 55NM west controlled by winnipeg center - Class C 35NM centered on VOR 3000-12500 ASL extension west to 55NM controlled by terminal |
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Control Area Extension |
Class E 45 NM centered on VOR 6500 - 12500 controlled by terminal Class E 70NM centered on VOR 7000 to 12500 controlled by terminal |
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hourly systems check |
TH TAS FUEL Analysis W/V |
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how often for a systems check |
30Mins + / - 10 min |
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TH check |
when split between compass dev is ≥ 5 when dev on one compass is ≥ 5 when heading changes by >30
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TAS Check |
Derived TAS differs from compass TAS by ≥5kts change in FL |
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S/H check |
-When changing from airway to non airway nav - when arriving at a TP in non airway leg - use best W/V avail, spin for drift remote next WPT to following WPT and adjust for VAR - "O/T ___ at ____, outbound radial/track/hdg ____, next NAVAID/RP ____, distance ___, ETA___, Clnc to FL ____ (As requd)" |
