AFS

Self Ignition when the charging process is not properly controlled -> Thermal runaway

it is most likely to be hazardous -> with an extreme internal pressure

P = E/t

flight idle to maximum power

SAT * (1 + 0,2*M^2)

FEAT

Flux Valve -> Error Detector -> Amplifier -> Torque Motor

Gyros and accelerometers on a stabilized plattform

plattform is kept level and north aligned

uses:

• two accelerometers

• three gyros

stringers / longerons

Non return Valve / Check valve

Check valves stop the flow in one direction and allow free flow in the opposite direction

• Normal law:

  • system mode which is active throughout the flight

• Alternate Law

  • provides most features of the normal law

  • some features suchs as automatic stall protection are lost -> conventional warnings

  • flight envelope protection is degraded

• Direct Law

  • failure conditions prevent operation in Alternate Law

  • Auto pilot funcitons are lost

  • no flight envelope protection anymore

• Mechanical Backuo

Self Ignition when the charging process is not properly controlled -> Thermal runaway

house in vented metal box

it is most likely to be hazardous -> with an extreme internal pressure

drehung um die Achse

along entlang der Achse

a starter generator

Real load sharing is achieved by increasing the torque to the lower speed aleternator.

Reactive load are balanced by regulating the energizing current (exiter field current).

• retard the spark during engine start

• provide a stronger spark on TDC

15:1

also the theoretical best economy

Piston engine

• process is intermittent

• combustion is at a constant volume

Jet engine

• process is continous

• combustion is at a constant pressure

SFC is the mass of fuel consumed for each unit of power output per unit of time.

• all types of turbines rely on a stator to accelerate the airflow and to direc the air properly towards the rotor.

• stator nozzle guide vane -> rotor extracts gas energy and converts it into mechanical work

impulse turbine

• airflow direction changes

• causes a change in the impulse of the gas flow, causing the force on the blades

• constant passage of the rotor blades -> no change in temp/pressure

reaction turbine

• direction of the airflow changes similar to the impulse turbine

• passage between the rotor baldes convereges -> forming a nozzle

• leads to aceceleration of the gas and expansion (?) druck sinkt

expansion of hot gas followed by conversion of kinetic energy (velocity) into (mechanical) work

Fail safe:

when a structure fails there is an alternative load path privided by an adjacent part whic his able to take over the loads for a limited amount of time

-> multiple load paths

Safe Life

limited life time, during which the assembly will be free of fatigue or failure

-> only one load path

Power Control Unit

-> are operated by analagoue signals.

measures the resonant vobratoin frequency

baffle: damp spanwise fuel motion

baffle valves: prevent outward movements

Integrated Drive Generator

Kombination aus Generator und Constant Speed Drive

lubricated by an internal oil system

Full Authority Digital Engine Control

-> digital control system mounted on the engine’s fan case -> performs the entire engine management task

> FADEC has a dual channel Electronic Control Unit for redundancy, with ine channel always active and a second one on standby.

single fault tolerant

can be expressed in kg per

hour per unit of shaft power

LP fuel pump low pressure boost pumps -> fuel-oil heat exchanger - > filtered and pressurized under high pressure pump -> delivered to a number of fuel nozzles

between fuel control unit and the fuel nozzle, a fuel flow transmitter and a fuel nozzle filter (letzter feiner Filter) a fitted.

below the Flat Rated Temperature, EGT is below its limit, thrust is strucutrally limited flat rated

limited by maximum mass flow of the engine/ of air?

Above the Flat Rated Temperature, EGT is at its limit and limits the the Thrust of the engine temperature limited

constant amount of thrust up to a certain temperature, then thrust decresases

power reduced, because the air is less dense -> less performance

unterhalb der Temperatur muss der thrust konstant gehalten werden, da sonst Belastung für den Engine zu groß werden würde

• some part of local disruption of airflow occurs

• individual compressor blades stalling

-> when the stall spreads out other turbine blades and stages -> full surge of the compressor

-> disruption of airflow in a compressor stall reduces the cooling airflow into the turbine, causing a rise in TGT (turbine Gas temp)

(before and between the individual turbines)

> RPM of the turbines/compressors will fluctuate, and the EPR will drop

stators in der turbine

Bypass Mass Flow / HP compressor mass flow

immer mass flow

it is the ratio between the low pressure turbine exhaust total total (the engine’s last stage) and the engnine inlet total pressrue (the fan’s pressure)

durck hinten durch Druck vorne

• höhere Machnumber, mehr druck vorne -> geringeres EPR

• höhere Höhe -> geringere Dichte -> weniger thrust bei gleichem EPR (total pressure Verhältnis bleibt gleich, vllt durch höhere Geschwindigkeit bei geringerer Dichte ?)

• predictive manintance that involces replacement or ovehaul of components before failure happens. regular inspections

  “monitoring of ciritcal parameters of a component or a piece of equipment and its replacement if a limit value is exceeded”

• hard time maintenance: component is replaced after a fixed amount of hours

Rudder ratio changer

the rudder deflection is reduced at higher IAS, despite the pedal being able to move the same amount all the time

Variable Stop System

the movement of the rudder pedals and rudder is always proportional. The distance the pedals and rudder can move reduces with higher IAS

advisory

• the crew activates ice protections systems based in the standard flight manual critera if total temperature reading and the sighting of moisture

• ice detector signal (kann auch der stab sein?) serves as a back up indicator

• monitor icing using primary methode as stated in the AFM

primary

automatic

• ice detector system automatically activates ice protection systems at the optimal moment.

• takes full advante of the ice detector’s capabilities and proved the most benefit to the operator

manual

• the flight crew manually activates ice protection systems based on ice detector signals

=> relying on indications of ice detectors rather than observing potential icing conditions (advisory)

blue

green

green

= Governor pump / hydro mechanical unit

there is always a fuel filter before the FCU, either only before the HP pump or before and after the HP pump.

The FCU or governor pump comes after the HP pump

SPFC = mass of fuel required to produce unit power for unit time

static load:

constant loads, that do not change in size, position or direciton

dynamic load:

are laods that do change in size, position and direciton

parallel to provide maximum power

• N2

• compressor discharge pressure

• compressor inlet temeprature

• fuel shut off

• thrust lever angle

a torsion box is formed by wing spars, ribs and wing skin reiforced by stringers

vertical

longitudial

Fluss nur in eine Richtung

Flussrichtung muss gecheckt werden

open centre hydraulic system

wandelt den gemessenen Druck in eine Anzeige um

neutral position changes for ailerons, rudder

remains constant for: elevator

AC 3 phase at 400HZ

brauch viel Strom

Freezing Point

Jet A: -40

Jet A1: -47

Jet B: -60

Flash Point

Jet A: 38

Jet A1: 38

Jet B: -20

Density:

Jet A1 0.8kg/l

zwischen generator and bus

simpel, wie bei einem Verbrennungsmotor

P = torque * RPM

(U * I) / RPM = Torque

throttle control:

controls the Power output of the engine manifold pressure indication

RPM lever:

controls the Engine RPM by changing the blade angle

in order to reduce power when reaching the desired altitude:

reduce manifold pressure and adjust RPM to a lower RPM

scavenge pump, pumps the oil from the sump into a tank

pressure pump, from tank to engine

scavenge pump must have a greater volume in comparison

diffuser (compensating jet)

glaube das ist einfach das Hauptrohr

hung start:

N2 stabilizing at a lower than normal RPM and a subseqeuent increase in EGT.

The engine fails to accelerate sufficiently because of a too low peneumatic starter pressure before fuel is supplied to sustain combustion.

-> shut down engine -> cranking -> cooling

hung -> to low

Hot start:

• early starter cut out or fuel messcheduling (excessive fuel in the combustion), strong tailwinds

• light up ath ery low rpm > sudden increase in EGT

• continues to accelerate

arming

executing

Emergency -> pressuirzed 100% oxygen

-> should be used when there is smoke on the flight deck

• n position: diluter demand ->mixed with surrounding air and on demand

• 100%: pure oxygen -> on demand

• Emergency: continous flow of 100% oxygen at positive pressure

deformation caused by the action of stress on a material

-> stress is the internal force per unit area inside a structural part as a result of external loads

Zugfestigkeit

occurs as a result of the combined effect of sustained tensile stresses and a corrosive environment

• Verformung die bleibt

im Gegensatz zu elastic deformation

Emergency use, weil noch fluid enthalten ist.

normal use

• short cylindrical probe mounted on a vibrator housing

3000 PSi and higher

a specific decelration rate, if this cannot be achieved because of slippery RWY, brake pressure is increased

only in the RTO mode, maximum brake pressure is applied, so here not the deceleration rate, but the pressure is decisve (?)

• no selection of autobrake -> no takeoff warning

• for a given touchdown speed, no reverse, dry RWY and a given ABS setting -> constant deceleration rate

• higher risk of ice in carburettor

• lower octane -> higher risk of detonation

10 degrees increase > double life

Joule

AC Gen Putput frequency [Hz] = (Rotor RPM) * (number of pole pairs) / 60

pressure indicator nach der pressure pump und vor dem Motor

Oil cooler nach dem Motor

waste gate controls the amount of exhaust gas that goes to the turbine -> fully open -> no supply to the turbo charger

Thrust = M * (Vjet - Vflight) + A (P - P0)

M mass of the air

Vjet exhaust nozzle gas velocity

Vflight flight forward speed

A nozzle area

P nozzle static pressure

P0 ambient static pressure

-> static thrust

F = (M x V) + (A x P)

4:1

entsteht wenn die axial velocity im Verhältnis zur RPM zu klein ist.

Emtscheidend ist dabei aber die axial velocity und nicht die RPM bei den Fragen

geringe axial velocity

• entsteht bspw. durch zu starkes Gas geben, rise in the combustion chamber pressure -> kann zu zu starker Durck zunahme in der combustion chamber führen und dadurch den axial airflow verlangsamen zum Stall

• Die luft muss entlang des compressors immer weiter komprimiert werden. Das design compression ratio wird dabei bei der design RPM erreicht.

• at low compressor RPM, compression is low, reduciton in volume of air reicht nicht aus to pass through the small section at the end of the compressor -> airflow restriction in the rear stages -> axial velocity in the front stages is reduced -> compressor stall in the frontal stages

just before the soray nozzle, after the passage of the fuel control unit

verdrehung des Flügels bspw.

to prevent cavitation in the pump

cavitation -> air bubbles

hydraulic system air bubbles at high altitudes for example

vapour lock

fuel system -> Wasserdampf entsteht

no direct linkage between control column and control surfaces

either mechanically actuated fully powered flight control system

control column moves valves which then controls the pressure onto the hydraulic actuators

• redundancy can here be achieved for jammed or broken controls

• one control axis on two separate control runs which translate the pilot’s movements into useful movements of the servo valves via the power control units.

electrically actuated fly by wire control system

input is given into a computer, which eletronically transmits the actuation signals to the hydraulic actuators

atmospheric pressure

at the outlet of the low pressure fuel pump (booster pump) or at the outlet of the the outlet of the high pressure filter

voltage and phase

only pressure pump and filter

supercharger is powered by the engine

turbocharger is powered by exhaust gases

der mit Löchern

small holes vorne und ein großes vorne, hinten größere Löcher

der differential pressure, vorne total pressure hinten ambient pressure wird gemessen.

Wenn die kleinen Löcher vorne zu eisen sinkt der total pressure ?, difference in differential pressure -> ice indicaiton

will smith likes small holes

decrease in dynamic pressure

rated power

AIRSPEED indicator: PA and OAT

DEnsity altitude window: density altitude

120ft adjustment per degree off the isa

• rotor seizure: current and torque increase to try and get it going faster

• rotor runaway: current and troque decrease to dry to slow it down

Fire warning should sound

if system is broken: either no indication or fault alert

• Normal

• Utility

• Aerobatic

• Commuter

• low compressiblity

• good lubricaiton and anti corrosion

• high flashpoint and low falmmability

• low volatility

• adequate viscosity

• thermal stability

shielding: no electromagnetic interference

-> braided wire

insulation: no short circuit etc

low pitch -> forward

high pitch -> rearward.. feather position -> full rearward

mass of fuel and mass of air entering the cylinder

the low speed shaft

first accessory gearbox -> high pressure shaft

der zweite ist immer langsamer

Gernerator:

fixed / stationary magnetic field and rotating amarture (where the current is induced)

Alternator:

stationary amature and rotating field

the other of the two is used for testing

-> when both values are low -> fault

same voltage and phase

Knocking / detonation

• mixture is ignited

• fuel burns at a normal rate

• all of a sudden all explodes at once

preignition

• the fuel air mixture explodes before the ignition of the fuel air mixture because of a hot spark plug for example

fuel

power is proporitonal to torque

nickel cadmium maintain a constant output voltage during discharge

Nickel Cadmium batteries

• made of a potassium hydoxice solution

• constant voltage during discharge

• more prone to thermal runaway

• lower internal resistance

• require venting

range of power lever positions between flight idle and mx reveresse

from just below flight idle to full reverse

alpha range -> fwd

presurized air and electrical power

when the fuel and air are completely used up

• constant volume

• constant pressure

• prevent low or over pressure

• to prevent vapour lock

• to check the fuel

im Falle einer constant displacement pump

regelt den Druck in einem System mit einer constant delivery pump

8 to 9 psi

keine zusätzliche Verbindung zum Flügel

direct system pressure to either side of the piston of an actuator

first stage tubine nozzle guide vanes

first stage of the HP turbine

electrically detonated

1: Takeoff

2: max. Power

3: Economy Rich

4: chemically correct (EGT max)

5: econonmy lean

increased range due to more efficient transfer of energy

it increases the fuel level at the boost pump location

richer

Thrust decreases

TSFC: remains fairly constant

• flow can be regulated

• greater capacity

electric motors (inductive load)

imbalance: tie breaker

underspeed: gen breaker

all else: gen exceiter breaker

ERP decreases (beim Gas geben, more air at the inlet than at the outlet) and EGT increases (weil weniger cooling)

• mass flow through the engine is lower -> lower thrust

• higher EGT because the amount of cooling air in the combustion chamber is reduced

-> lower thrust can be compensated by more fuel as long as the engine operates below its maxiumum EGT limit

• decrease the airflow across the rear stages whilst that across the early stages is increased

im Rad gegen Explosion

off load and on load battery voltage check

hydraulic fluid

turbo prop:

fuel flow per unit of power kg/h per unit of power

turbine:

fuel flow per unit of thrust

increases turbine efficiency

direct system pressure to either side of the actuator

convergent duct which accelerates the airflow

auch exhaust-propelling nozzle

-> increases the airflow thus the thrust

the pump pressure output being insufficient

a hyprobhobic layer is created causing the water to form beads and roll off the window

tank sump pads