Systems Descriptions Flashcards
Describe the Airframe of the Cessna 172.
All metal, four place, high wing, single engine airplane equipped with a tricycle landing gear.
What does Semimonocoque mean?
It si a contructrion of the fuselage that is formed sheet metal bulkhead, stringer and skin.
Designed to be strong but light.
What is the skin of the Cessna 172 made of?
Aluminum Skin
How are the Aileron, Rudder, and Elevator controlled?
Through cables and mechanical linkages/ Pulleys
How is the Elevator Trim System Operated?
Using the vertically mounted trim control wheel. Down trim will pull the nose up, and up trim will pull the nose down.
Overview: What does the Instrument Panel consist of?
Garmin Display Unit (GDU), Primary Flight Display (PFD), Multifunction Display (MFD), and the Garmin Audio Panel
Tell me about the Landing Gear
The landing gear is a tricycle type with a steerable nose wheel and two main wheels.
We have hydraulically actuated disk breaks, and a shimmy dampener to absorb shock and prevent oscillation.
Tell me about the baggage compartment.
Consists of Two Areas:
Baggage A (the bigger one): can hold up to 120lbs
Baggage B (the smaller shelf): can hold up to 50lbs
Total weight must be 120lbs.
If in Utility catageory NOBoth Baggage compartments must be empty as well as the backseat
Describe the Engine/Power-plant to me.
The engine is a Lycoming Model IO-360-L2A with 180 BHP and 2700 RPM.
I: fuel injected
O: Oxygen
360: cubic inches of displacement
L2A: Major accessories include a starter and belt driven alternator mounted on the front of the engine, and dual magnetos, dual vacuum pumps, and a full flow oil filter mounted on the rear of the engine accessory case.
What does the mixture do?
What does the throttle do?
The mixture controls the fuel to air ratio.
The throttle controls the engine power.
What is the G1000 EIS?
The Engine Indication System (EIS) provides information for the pilot from/for the engine, fuel and electrical system.
The engine and airframe unit provide data to the EIS, which displays the data.
What does the tachometer display?
Engine rotation or RPM
Tell me about the Engine Lubrication System.
The engine uses a wet sump system, excess oil is kept in the sump located at the base of the engine.
**Capacity: 8 Quarts with an Additional quart is kept in the engines oil filter*
Sump, Filter, Pump, Filter, Relief Valve, Oil Cooler, Engine (lubricate), Sump (Via Gravity)
Oil Flow:
1) Leaves the Sump, Goes through Filter
2) goes to engine driven oil pump
3)then passes through full-flow oil filter
4) pressure relief valve
5) remote oil cooler
6) Then to the engine to lubricate
7) Returns to the Sump Via Gravity
Bypass Valve (full-flow filter):
Should the Filter be clogged the bypass valve will allow the oil to pass by when it is very cold, or if the filter becomes clogged.
How much oil should you not fly with?
Less than 5 quarts of oil.
Explain these Terms:
Horizontally Opposed
Direct Drive
Naturally Aspirated
Air cooled
Four Cylinder
Fuel Injected
Flat engine
One gear
No turbo or super charger
Baffling and fins to cool
4 cylinder cycle (intake, compress, combust, exhaust)
Fuel injected directly into cylinders (no carburetor)
What are the positives to a 4 cylinder system?
More efficient as every cylinder is functioning on a different cycle; so the engine is always generating power.
What happens when you turn the key in the ignition?
Before:
1) Master Switch is on which connects to the boost pump
2) The boost pump provides power to the starter motor
3) The Starter Motor is connected to the flywheel via the bendix gear, the flywheel turns the engine’s crank shaft, which turns the propeller
4) As the Engine turns over the magnetos provide energy to the spark plugs which ignites the fuel-air mixture
Master, Boost pump, Starter, Bendix Gear, flywheel, crankshaft, turns prop, turns engine, starts mags, starts spark plugs
Tell me about the Air Induction System.
The engine receives ram air via the air intake valve located at the front of the engine cowling. It is covered by an air intake filter which removes dust and other foreign matter from the induction air.
Should the filter become clogged a spring loaded alternate air door will be opened via suction and draw in unflitered air into the engine.
this will cause a 10% loss of engine power
Tell me about the Exhaust System.
Exhaust gas from the cylinder passes through the muffler, located below the engine, and then is vented outside through the singular tailpipe.
For the Cabin Heat: Ram air is supplied though the Muffler Shroud (heating the air) and then supplied to the chamber as the aircrafts heater.
becuase of this cracks in the exhaust pipe can cause exhasut to leak into the cabin*
Things to Look Out For:
CO2 strips, the smell of exhaust, feelings of hypoxia/dizziness
Tell me about the Fuel Injection System. (ENGINE COMPONENTS ONLY)
The Fuel InJection System is comprised of:
1. The Engine Driven Fuel Pump
2. Fuel/Air Control Unit
3. Fuel Mainfold
4. Fuel Flow Indicator
5. Injector Nozzles
The Flow:
Fuel is Pulled from the fuel tanks on the wings by the Engine Driven Fuel Pump, it is then fed into the Fuel/Air Control Unit (correctly proportions the fuel to air ratio), the fuel is then delivered to the Fuel Manifold (where it is evenly distributed to the Fuel Injector Nozzles, which delivers the Fuel Directly into the Cylinder.
The Fuel Flow Indicator monitors the flow and produces the digital display on the Engine Indication System (EIS).
What are the Positives to a Fuel Injected System?
Improved Fuel Efficiency, Reduced Emissions, Better Engine Performance, More Precise Fuel Delivery, Better Starting in Cold Weather, Resistant to Icing!!!!
Dis:
Harder to Hot Start.
Tell me about Carburators.
What are their weaknesses?
How is that Combatted? Had when to use those defenses?
Usually “Float-Type” where ram air creates a low pressure area within a Venturi, drawing fuel from a float-regulated chamber, mixing it with the air ad delivering the fuel-air mixture into the engine cylinders.
Disadvantages:
1. Less Fuel Efficient
2. Prone to Icing (at 50F with high humidity)
3. Not As Precise
Pros:
1. Less Expensive
Icing: Can Occur a Temps of 50F or less on High Humidity Days
- Carb Heat is Used to Combat this Issue
-Melts ice, that water then runs through engine causing engine roughness and up to a 10% loss of engine RPM. Maintain use or the engine will subsequently ice over
Use Carb Heat when the RPM is lowered, such as, Landing or Idling the Engine, as Icing wont be Noticed Until the Throttle is re-engaged.
Fuel System Continued (the more in depth)
Fuel Quanitiy: Each Tank 28
Total: 56
Unusable: 3
Totals Useable: 53
Reduced: Each Tank 19
Total: 38
Unusable: 3
Total Useable: 35
Consists of:
1. Two Vented Fuel Tanks
2. 3 Position Selector Valve
3. Fuel Reservior Tank
4. Electrically Driven Aux Fuel Tank
5. Fuel Shutoff Valve
6. Fuel Strainer
DISTRIBUTION:
1. Fuel Flows from tanks via Gravity.
2. To the Fuel Selector Valve B, R, L and into the Fuel Reservior Tank.
3. Fuel Flows from there into the Aux Fuel Pump, through the Fuel Shutoff Valve, the Fuel Strainer, and the Engine Driven Fuel Pump.
4. Then onto the Fuel-Air Control Unit, (bottom of engine) Or Fuel Servo. Which meters the Fuel Flow.
5. The Fuel then goes into the Fuel Distribution Valve (flow divider) located at the top of the engine.
6. Fuel is then Routed into the injector nozzles and delivered into the intake of each individual cylinder.
Tell Me about the Propeller.
It is a two bladed, fixed pitch, aluminum alloy prop which is 76in in diameter made by McCauley Propeller Systems
The Ground Clearance is: 11.25 inches
How does the Propeller Work?
By acting like a rotary wing.
The angled blades of the prop act as an air foil, generating LIFT as it spins,
This creates THRUST by pushing air backward as it spins (creating low pressure in front of the prop and high pressure behind the prop, pushing it forward)
All of this is Due to:
Newton’s Third Law: every action has an equal and opposite reaction.
Bernoulli’s Principle: As the speed of a fluid increases the pressure decreases.
Magnus Effect: a force that occurs when a spinning object moves through a fluid or gas.
Can you break down Bernoulli’s Principle for me? And How it Develops Lift over an Airfoil.
A Study of how fluids react when in a vacuum. The key idea is that the faster a liquid moves the lower the pressure, the higher the pressure the slower the liquid moves.
Example of Generated Lift:
Fuel Indicating System:
The Fuel Quantity is measured by two fuel sensors; one in each fuel tank. (Is displayed on the EIS page).
-when indicator shows an empty 1.5 gallons of unusable fuel remain in the tank.
Sensor Limit 24 gallons (can add more, sensor will not pick it up)
Sensors will indicate a low fuel condition: (is less than 5 gallons and remains this low for 60 secs) LOW FUEL L and LOW FUEL R will be displayed in Amber on the PFD and Tone will Sound
When the fuel indicator reaches the calibrated useable empty fuel level, the LOW FUEL L and LOW FUEL R will steadily change from White to Amber and remain Amber and the Indicators will Flash Red
A VISUAL CHECK OF EACH FUEL TANK LEVEL MUST BE PERFORMED BEFORE FLIGHT!!!
Fuel Flow is Measured How?
Fuel Flow is measured by use of a turbine transducer mounted on top of the engine between the fuel air control unit and the fuel distribution unit.
What is the Auxiliary Fuel Pump used for?
Priming the engine before starting.
(engine will be flooded if left on for prolonged periods, with Master Switch ON and Mixture Rich with the engine stopped.
Also used for vapor suppression in hot weather. Can be used if engine driven fuel pump fails. Can also be used under hot conditions, or during conditions that would lead to fuel vapor forming.
What does the Fuel Return System help to do?
It was incorporated to improve engine operation during extended idle operations in hot weather environments; and minimizes the amount of fuel vapor generated in the fuel lines during hot weather operations.
What happens if the fuel venting system is blocked?
Should the overboard vent in the left fuel tank, become blocked the fuel filler caps are vacuumed vented; so the fuel cap vents will open and allow air to enter the fuel tanks in case the overboard vents become blocked.
Why do we use more fuel in the Left Wing Tank?
The fuel vent is located there and increases the fuel flow rate.
ASLO: Unequal fuel flow from each tank can occur if the wings are not maintained exactly level.
What are the sounds of possible brake failure?
Gradual decrease in braking action, noisy or dragging brakes, soft or spongy pedals, excessive travel and weak braking action.
What is the ACU?
Alternator Control Unit, meters the current to the batteries so as to not under or over volt them
What is included in the Essential Bus?
Primary Flight Display, Air Data Computer, Nav 1, COMM1, Standby Indicator Lights, Standby Batt AHRS
Electrical System Explain It… General
The airplane is equipped with a 28 volt (DC) electrical system.
Powered by a 60 ampere engine driven alternator.
A 24 voltage main storage battery is located inside the engine cowling on the left firewall.
BOTH ARE CONTROLLED VIA THE MASTER
Tell me About the Electrical Buses
Power is supplied to most electrical circuits through two primary buses (ELECTRICAL BUS 1 AND ELECTRICAL BUS 2), with an essential bus and a crossfeed bus.
The STBY BATT switch controls the to or from the standby battery. The Standby Battery is available to provide power to the ESSENTIAL BUS in the event the alternator and main battery fails.
The Primary Buses are supplied with Power whenever the MASTER switch is turned on, and is NOT affected by starter or external power usage. Each Primary Bus Is ALSO connected to an avionics bus through a circuit breaker and the AVIONICS BUS 1 and AVIONICS BUS 2 switches.
Each is Powered when BOTH the Master and the Avionics Switch is on.
Over Voltage vs Low Voltage
Low Voltage
24 (Below 24.5, Low VOLTS WARNing )
Normal
28 (normal)
30 (slightly high)
High Voltage
32 (High Volt Warning)
Electrical System Indicators
(G1000 Annunciator Panel)
Oil Pressure, Low Fuel (L&R), Low Volts, STBY BATT, Low Vacuum, High Volts, CO LvL High
Voltmeters
Main Bus and Essential Bus are measured in Volts below the Symbols M and E on the PFD.
Normal Bus Operation: 28 volts (when alternator on)
High Volts: 32 Volts
Low Volts: 24.5 and below (can be displayed at low RPM settings)
Ammeters
Located beneath the M BATT S displayed beneath each indicator(-1.5). A positive indicator shows the battery is charging, negative and the battery is discharging.
Circuit Breakers vs Fuses
CESSNA 172S: Circuit Breakers
Found on the circuit breaker panel, can be disengaged from the electrical system by pulling straight out, (will pop out if electrical system sparks) You get one reset.
Fuses: Inside the Garmin, Not field replaceable, when fuses pop, DO NOT PISH THEM BACK IN!!
External Power Receptacle
Way to reach the electrical and aviation equipment (battery jumped if can’t start).
External Lights Location
Nav Lights: on wing tips and tip of the rudder
Landing/Taxi Lights: Left Wing Leading Edge
Landing/Recognition/Taxi Lights: on left and right wings
Flashing Beacon: on top of the vertical stabilizer
Strobe: on each wing tip
Cabin Heating and Cooling
Volume and Temperature of Airflow can be controlled from the Cabin Ht and Cabin Air control Knob.
All Ram air brought from cabin vent inlets (wings), ventilating air door (side of engine), and from the air filter (nose of plane, cabin Heat)
What is the difference between a mode A, C and S transponder?
Mode A: Provides a basic identification code.
Mode C: Adds altitude reporting to the identification code.
Mode S: Enhances Mode C with additional data exchange capabilities, including traffic information services.
What is the Difference between ADSB-OUT and ADSB- IN?
Required in Controlled airspace’s.
It improves air traffic control’s ability to track aircraft and provides pilots with traffic and weather information.
The ADS-B Out component broadcasts the aircraft’s position, while ADS-B In allows the reception of traffic and weather data.
Where/What do the antennas on the plane do?
Com 1 and GPS 1: on the right side (top)
Com 2 and GPS 2: on the left side (top)
VOR & GlideSlope: Blade Type on Vertical Stabilizer
Marker Beacon: mounted on the bottom of the tailcone
Bottom of the Cabin/ ModeS Transponder: Bottom of the cabin
Mounted to the Bottom of the tailcone: DME
What is the G1000?
an integrated flight control and navigational system. PFD Flight Information; MFD GPS Information
What is the Air Data Computer?
compiles information from the airplanes pitot static system, calculates pressure altitude, airspeed, true airspeed, vertical speed, and outside air temperature.
What is the Atitude Heading and Reference System (AHRS)?
provide attitude and flight characteristics information on the G1000 displays, containing sensors that replace the spinning gyros used in other planes.
The magnetometer (in left wing) (flap motor right wing) interfaces with AHRS to provide heading information
What kind of transponder do we have?
Mode S transponder provides Mode A, C and S functions. Mounted in the tail racks.
What is ADSB-Out?
Automatic Dependant Surveillance Broadcast: a surveillance that automatically transmits aircraft data without pilot involvement. Automatically broadcasts information about aircrafts GPS, altitude, ground speed, and other data to ground stations and other aircraft. ATC can immediately receive this information.
Required for aircraft flying in most controlled U.S. airspace;
positives: more precise tracking of aircraft, better visibility, and increased pilot situational awareness.
Limited to Line of Sight transmissions (not through ground obstructions)
What does the Vacuum System consist of?
Engine Driven Vacuum Pump, a vacuum regulator, standby attitude indicator, a vacuum system air filter, and a vacuum transducer.
Low Vacuum Annunciator: below 3.5hg
Stall Warning System
A pneumatic type stall warning that operates off of a pressure difference which draws air into the warning horn that goes off at 5 to 10 knots above stall speed in all flight conditions.
Walk me through the thought processes in some typical general emergencies? Be VERY general.
Engine Failure: Establish best glide speed, identify a suitable landing area, and attempt to restart the engine if time permits.
Electrical Failure: Conserve battery power, use standby instruments, and land as soon as practical.
Instrument Failure: Use backup instruments and seek assistance from air traffic control for navigation and landing.
