Flight Control & Hydraulic Systems

Flight Control System (FCS)

• Primary Control Surfaces include ailerons, elevator, and rudder
• Primary control surfaces generate roll, pitch, and yaw moments to maneuver the aircraft
• Secondary Control Surfaces include flaps, spoilers, and trim tabs
• Secondary Control Surfaces enhance lift, aid in control and balance with continuous pilot input
• Input Devices encompass sidesticks, yokes, and rudder pedals
• Actuators are hydraulic or electric and are used to move the control surfaces
• Fly-by-Wire (FBW) Components use sensors, computers, and digital systems to process pilot inputs and send commands to actuators, eliminating direct mechanical linkage

Hydraulic System

• Components include hydraulic pumps (typically engine-driven or electric), reservoirs, accumulators, valves, and actuators
• Power Sources include engine-driven pumps, electric pumps, Power Transfer Unit (PTU), and Ram Air Turbine (RAT)
• Circuits consist of multiple independent circuits (e.g., Green, Blue, and Yellow in A320) to ensure redundancy and safety

Electrical System

• Power Sources are generators (engine-driven and APU), batteries, and external power connections
• Distribution includes AC and DC buses, including the Essential (ESS) Bus for critical loads
• Transformers and rectifiers adapt electrical energy to the needs of various subsystems
• Components feature circuit breakers, inverters, static inverters, and load-shedding systems to prioritize essential loads

Pneumatic System

• Sources include bleed air from the engines, APU, or ground air supply
• Applications encompass air conditioning, wing anti-icing, engine starting, and pressurization of hydraulic reservoirs
• Components include bleed valves, pressure regulators, and check valves

Fuel System

• Components feature fuel tanks, pumps, transfer valves, fuel lines, filters, and fuel quantity indicators
• Functions consist of fuel storage, transfer to the engines, and fuel jettison in emergencies

Auxiliary Power Unit (APU)

• Functions include providing bleed air for engine starting and environmental systems, as well as backup electrical power
• Components include load compressor, generator, and fuel control unit

Anti-Ice/De-Ice System

• Components encompass systems to heat the wing leading edges, engine inlets, and propellers (if applicable) via bleed air or electrical heating
• Purpose is to prevent ice formation on critical surfaces

Oxygen System

• Types available are crew oxygen (masks with regulators), passenger oxygen (chemical generators or gaseous systems), and emergency portable oxygen bottles
• Objective is to ensure oxygen supply at high altitudes or during emergencies

Avionics Systems

• Navigation systems include GPS, VOR, DME, ILS, and INS
• Communication utilizes VHF and HF radios, and transponders
• Flight Management & Monitoring systems use Flight Management Systems (FMS), ECAM/EICAS displays, and various sensors to monitor aircraft status

Fire Protection System

• Components include smoke detectors, fire extinguishers (typically halon or alternative agents), and warning lights
• Zones protected are engines, APU, and cargo compartments

Landing Gear System

• Components include wheels, brakes, struts, and retraction mechanisms
• Control utilizes hydraulic or electric actuators and position indicators

Cabin Systems

• Pressurization uses outflow valves and cabin pressure controllers to maintain a comfortable cabin pressure
• Air Conditioning uses packs and air conditioning systems to regulate temperature and air quality
• Other systems are lighting, in-flight entertainment, and environmental controls

Power Plant (Engine System)

• Engines can be a turbofan, turbojet, turboprop, or piston type
• Engines provide the primary power needed for flight
• Accessory Gearbox transmits mechanical power from the engine to auxiliary systems
• The Accessory Gearbox is critical for operating other aircraft systems
• FADEC (Full Authority Digital Engine Control) is a digital control system that manages and optimizes engine performance
• FADEC regulates key parameters like fuel mixture, engine speed, and temperature
• Fuel Filter and Fuel System Components ensure that fuel reaching the engine is free of contaminants, featuring fuel tanks, pumps, valves, and fuel lines
• Lubrication and Oil System distributes oil to lubricate critical engine components, reducing friction and heat and helps dissipate heat and maintain engine performance
• Auxiliary and Safety Systems, such as the Ignition System, provide the initial spark needed for engine start
• Thrust Reversers allow for a reversal of thrust to aid in braking during landing
• Sensors and Monitoring continuously check parameters like pressure, temperature, and engine speed to ensure safe operation

Key Terms and Concepts for Aircraft Systems and Power Plant

• The ESS Bus distributes electrical power to critical loads, ensuring that essential systems continue to operate even if some power sources fail.
• The Power Transfer Unit (PTU) transfers hydraulic pressure between different circuits to maintain hydraulic system operation
• Bleed air is primary source for anti-icing and engine starting, extracted from the engines or the APU
• Fuel Tanks: Store the fuel
• Fuel Pumps: Transfer fuel from the tanks to the engines
• Fuel Filters: Remove impurities to protect the engine
• APUs provide bleed air for engine starting and environmental control systems and backup electrical power
• Traditional hydromechanical flight control systems use mechanical linkages combined with hydraulic actuators
• Fly-by-Wire systems replace mechanical connections with electrical signals, using sensors and computers, offering enhanced precision and redundancy
• Fire protection is ensured by smoke detectors, fire extinguishers, and warning lights in critical areas like engines, the APU, and cargo compartments
• The Accessory Gearbox transmits mechanical power from the engine to auxiliary systems
• The FADEC system controls and optimizes engine performance by managing fuel mixture, engine speed, and temperature
• The engine lubrication system lubricates engine components to reduce friction and wear and dissipates heat to prevent overheating.

Resumen: BLO-6 Navigation & Altimetry

• Accuracy (Precisión): The measure of conformity between the calculated and real position: Related to the "internal tunnel" in RNP (Required Navigation Performance).
• Integrity (Integridad): The system's ability to alert when accuracy cannot be guaranteed: Related to the "external tunnel" in RNP.
• Continuity (Continuidad): The system's ability to function without interruption during operation.
• Availability (Disponibilidad): Guarantee that the system will be operational when needed.
• GNSS (Global Navigation Satellite System): Includes GPS (USA), Galileo (EU), and GLONASS (Russia). Provides global positioning with an accuracy of ~20 m.
• SBAS (Satellite-Based Augmentation System): Improves the accuracy and integrity of GNSS (e.g., EGNOS in Europe).
• ILS (Instrument Landing System): Provides azimuthal (localizer) and vertical (glide slope) guidance for landing.
• VOR (VHF Omnidirectional Range): Emits directional signals referenced to magnetic north.
• DME (Distance Measurement Equipment): Measures the distance between the aircraft and a ground station.
• ADF/NDB (Automatic Direction Finder/Non-Directional Beacon): Uses non-directional signals (190–1750 kHz) to provide direction.
• QNH: Altimeter setting to indicate altitude above sea level. On the runway, it shows the airport elevation.
• QFE: Setting to indicate height above the airfield. On the runway, it shows "0".
• STD (QNE): Standard setting (1013.25 hPa). Used at flight levels (FL) for vertical separation.
• Transition Altitude: Where the setting is changed from QNH to STD.
• Transition Level: Where the setting is changed from STD to QNH during descent.
• Tubo Pitot: Measures total pressure (static + dynamic).
• Fuente Estática: Measures static pressure.
• TAS (True Air Speed): The actual speed relative to the air. Requires a Pitot tube, static source, and density/temperature corrections.
• IAS (Indicated Air Speed): Speed indicated without density corrections.
• Dead Reckoning: Calculation of the current position based on speed, direction, and time from the known position.
• INS (Inertial Navigation System): Self-contained system using gyroscopes and accelerometers. Requires initial alignment, and accuracy degrades over time.
• Error en Altímetro: Depends on pressure/temperature. Does not indicate real altitude with STD.
• Stanford Plot: Compares estimated error vs. real error (Y=X line indicates perfect match).
• RNP (Required Navigation Performance): Defines precision "tunnels" for routes (RNP 0.3 = 0.3 NM required accuracy).
• Anti-hielo/Deshielo: Pneumatic or electrical systems for critical surfaces (wings, engines).