Instruments

directly proportional

• electronic magnetic

  • wie ein fahrrad tacho

• electrical

• 3 phase AC tacho generator driven by the engine, and the current is fed to the indicator consisting of a synchornous motor dirven magnet drag cup

• mechanical

• magnetic tachometer

  • consists of a permanent magnet turning inside a non magnetic drag cup

icing conditions exist when the OAT (on the ground) or the TAT (inf light) is at ir below 10 degrees and visible moisture in any form is pressent

Random/Real Wander:

change of direction in space of the rotor’s spin axis due to manufacturing imperfections

apparent wander

due to earth’s rotation

-> initially perfectly alligned with a meridian but over time meridian moves away

Transport Wander

apparent wander due to the change of aircraft position

10 degrees

nose up

3 rate gyros

2 accelerometers

fail passive

an automatic landing system is fail passive, in the event of a failure there is no significant out of trim condition

what to do if the auto pilot system becomes fail passive?

• above 1000ftAGL -> revised minima

• between: go around / full manual

• below Alert height -> continue

fail operational

an automatic landing system is fail operational if in the event of a failure, the approach, flare and landing can be complet by the ramining part of the automatic system (= fail safe)

Basic Modes

stabilizing the ac around its CG. Basic stability funciton of the autopilot are provided by the inner loops.

Guidance Functions

controlling the movement of the center of gravity in three dimensional space.

-> guidance functions of the autopilot that control the path of the aircraft.

-> provided by the outer loops

guidance

sytem was nur warnt aber nicht eingreift

acts on the control column

a frequency modulation wave, for which the frequency difference between the transmitted wave and the received wave after ground reflection is measured.

wie radio altimeter

(nicht eindeutig, ob baro auch benutzt wird)

transfer

• address

• data

• control signal

Attitude Direction Indicator

pilot gives attiude, autopilot holds attitude

automatic syncochronization function

-> in case of failure of the synchronization circuits, the autopilot may be prevented from engaging

automatic pitch trim function

—> both enable a smooth takeover

• angle of attack (AOA)

• aircraft configuration

• airspeed information

the Navigation Computer / FMS

Terrain Awareness warning System

das gleiche wie EGPWS

SHF

4200 - 4400 MHz

> incorporates infromatio from aircraft based sensors (nar infrared cameras etc.) to provide vision in limited visibility environment

> on dedicated display or as a abckground on the PFD or HUD

synthetic vision display

• based on a terrain and ground features database

• pilot pushes button and while button is pushed, auto pilot is disengaged

-> pilot can fly the aircraft

• aneroid capsule

• bellow s tube

  • wie aneroid capsule nur weniger empfindlich (?)

• bourdon tube

  • differential pressure

  • bspw Gas druck an der Gas flasche

  • hinter der Messskala läuft die Röhre, dehnt sich aus

Fahrenheit = 9/5 * c + 32

misst den elektrischen Widerstand der unterschiedlich stark sein kann, abhängig von der Einstellung

kinetic heating due to compressibility

K -> recovery factor -> percentage of the measured ram rise

es kann nicht die ganze TAT gemessen werden, sondern ein geringerer Wert die Ram air temp

(Bank angle + Lat) / 2

-> big error, when turning over the poles

(Bank angle + Lat) / 4

bei kleinem Fehler -> O / W

because of pendulum movement of the errection system

commands for change in pitch / roll attitude

EGPWS caution alert: 40 - 60 seconds

EGPWS warning alert: 20 - 30 sec

20 to 30 seconds

Pitot underreads in descent, static overreads in descent

Attidutde Direction Indicator

RoT = TAS / turn radius

je schneller desto geringer der Rate of Turn

• sinkrate: uses vertical speed from ADC

• closure rate: RA

Type A:

no saftey effects

Type B

• malfunkction: minor failur

• functions which may influence saftey if they fail or malfunction. -> charts speed calc etc.

and we have

• portable

• installed

… EFB systems.

• roll will hold the centerline

• pitch -> remains reference to V2

10 degrees

the rate of change of heading

10 minutes

allignment of IRS

3-10min

• Latitude: can be computed by the system and compared to the one entered by the pilot -> it does not align at all because it doesnt work with the wrong input or it senses the wrong input (?)

• longitude: can not be calculated. So the system relies 100% on the entry of the pilot -> but is still aligns

225227

normal aircraft configuration for the phase of flight

• MINIMUM MINIMUM: Mode 6

5kt or 5% above Vs

• red: terrain is 2000ft an higher above the aeroplane

• amber: 1000 - 2000ft above the aircrafts altitude

• light yellow:

  terrain between 500ft below and 1000ft above the aircrafts altitude

max 8 flights

CAS >200kt

absolute differential pressure because in the capsule is vacuum

• 3 Laser gyros

• 3 accelerometers

• single mode:

  when one FMC fails, the remaining one supplies both MCDUs

• independent mode

  both FMCs are decoupled

• dual mode

  master slave, both working

amber: caution / abnormal sources

red: warnings / flight envelope and system limits

ende des grünen speed bands

… “not be exceeded except in still air and with caution”

a servomechanism

electrical display of calculated value

• 3 gyros

• 3 axis accelerometer

• 3 axis magnetometer

only attitude indicaitons

the horizontal component of magnetic force lines

a transducer that receives an electric signal from a romote pressure sensor

in case landing gear not down

an accelerometer to temporarily change the pressure in the capsule

• DG: 2

• artif. hrpzon: 2

outout: attitude and heading

• adiabatic (compression)

• kinetic (friction)

heating

… still results in a loss of altitude because the elvator nose up direciton is restricted

AOA sensor measured with pentiometer and subjected to position error

directional antenna

topple

drift and topple

air speed indicator