Embraer E190/195 E2 Continuation Training

Embraer E190/195 E2 Continuation Training with PW1900G Powerplants course meets ATA 104 Specification Level I for General Familiarization. It offers a comprehensive overview of the airframe, systems, and powerplant, as outlined in the Aircraft Maintenance Manual (AMM).

The course complies with EASA’s knowledge LEVEL 1, as outlined in Regulation EU No. 1321/2014, Part 66, Appendix III, ensuring participants:

Gain familiarity with the principal elements of the subject.
Are able to describe the subject using common terminology.
Understand key operational and maintenance concepts.

SYSTEM REQUIREMENTS

Compatible with PC, Laptop, tablet, Android, and iPhone devices.
Requires internet access.

STUDY TIME

Approximately 40 hours of self-study.
Students have 6 months to complete the course, with an additional 90-day review period available.

SUPPORT

For any inquiries, support is available during normal business hours.

WHY TRUST US WITH YOUR TRAINING?

This course is developed by EASA and UK CAA-certified B1/B2 engineers, type instructors, and Part 147 Training Managers. Each course thoroughly covers the relevant ATA chapters.

Course Duration

The course takes approximately 40 hours of self-study. Each ATA chapter is unlocked sequentially, with students required to pass a quiz before advancing to the next section. A completion certificate is provided upon successful course completion.

Course Objectives

Upon completion, students will be able to:

Identify safety precautions for the airframe, systems, and powerplant.
Understand key maintenance practices for the Embraer E2 E-jets
Define the general layout of the aircraft’s systems.
Describe the characteristics of the PW1900G powerplant.
Recognize special tooling and test equipment requirements.

Module 1 – Introduction to the Embraer E-Jet E2

Scope:
Covers the development history, design philosophy, and general characteristics of the E190-E2 and E195-E2, with reference to the E175-E2 programme status.

Learning Objectives:

Describe the evolution of the E2 programme, including key milestones and engine selection.
Identify major differences between E2 variants.
Understand basic aircraft configuration, dimensions, performance, and certification standards.
Recognise primary cargo and cabin layouts, zoning, and access panel identification.
Summarise major aircraft systems at a general level, including avionics, engines, APU, air management, fuel, hydraulics, brakes, flight controls, and landing gear.
Outline standard ground handling, servicing, and maintenance concepts.
Identify electronic equipment bay locations and major components.

ATA 21 – AIR CONDITIONING AND PRESSURIZATION

Scope:
Covers the operation, control, and maintenance of the aircraft’s environmental control systems, including air conditioning, pressurization, temperature regulation, ventilation, and air quality management.

Learning Objectives:

Describe the layout and operation of the air conditioning system, including distribution, recirculation, gasper, and ram-air ventilation functions.
Identify the role, location, and redundancy features of Air Management System Controllers (AMSCs).
Explain the pressurization control system (CPCS), including automatic, manual, and dump modes, Outflow Valve (OFV) operation, and relief systems.
Recognise cockpit and passenger cabin temperature control systems, trim air regulation, and control interfaces.
Identify key components and locations, including cooling packs, temperature sensors, trim air valves, ozone converters, and optional air cleaner systems.
Understand ventilation provisions for electronic and cargo compartments, including smoke detection and shutdown logic.
Explain the operation of the low-pressure ground supply system.
Interpret cockpit controls, EICAS alerts, CAS messages, and ECS synoptic indications.
Describe the built-in test (BIT) and maintenance functions available via the Central Maintenance Computer (CMC).

ATA 22 – AUTOFLIGHT

Scope:
Covers the Automatic Flight Control System (AFCS) and its integrated functions for automatic control of aircraft flight path and thrust, including redundancy features, controls, and operational modes.

Learning Objectives:

Describe the AFCS architecture, including dual-channel, dual-lane redundancy, Modular Avionics Unit (MAU) hosting, and communication via eASCB-D and ARINC 429.
Explain the Flight Guidance and Control System (FGCS), Flight Director (FD), Autopilot (AP), and Thrust Management System (TMS) functions.
Recognise AFCS controls and indications, including the Guidance Panel layout, lateral/vertical guidance modes, and speed controls.
Understand Autopilot operation, including engagement/disengagement methods, Breakout Increase Device (BOID) function, and mode annunciation on the Flight Mode Annunciator (FMA).
Describe the Autoland capability, including CAT I and CAT III ILS approach modes, flare, touchdown, rollout phases, and integration with TMS and radar altimeter.
Explain Autothrottle operation, including thrust control logic, TOGA integration, and cockpit interface via the Guidance Panel and Thrust Control Quadrant (TCQ).
Identify component locations and integration points for AFCS functions, including FCCs, MAUs, TCQ, and FADECs.

ATA 23 – COMMUNICATIONS

Scope:
Covers aircraft communication systems for voice, data, and interphone operations, including cockpit audio integration, external communications, and ground crew interfaces.

Learning Objectives:

Describe the role and layout of Modular Radio Cabinets (MRCs) and Mini-MRC, including housing of VHF, navigation, DME, transponder, and optional ADF equipment.
Explain MCDU radio page functions for tuning and control of communication systems.
Understand the VHF communication system, including three independent COMM modules, antenna locations, and tuning via MCDU, CCD/PFD, and Digital Audio Panels (DAPs).
Recognise the operation of data transmission systems including SELCAL, Communication Management Function (CMF), ACARS, and the printer system.
Describe the Audio Integrating System, DAP operation, and backup communication mode.
Understand the Ramp Interphone system, ramp call horn operation, and their integration into ground communication.
Identify the function and importance of static dischargers in preventing interference with communication and navigation systems.

ATA 24 – ELECTRICAL POWER

Scope:
Covers the Electrical Power Generating and Distribution System (EPGDS), including normal, auxiliary, emergency, and external power sources, power conversion, and distribution control.

Learning Objectives:

Describe the layout and operation of AC and DC power generation systems, including Integrated Drive Generators (IDGs), APU generator, and Ram Air Turbine (RAT).
Explain AC and DC power distribution via Integrated Control Centres (ICCs) and Secondary Power Distribution Assemblies (SPDAs), including bus tie logic and redundancy management.
Recognise the role and location of key components such as Generator Control Units (GCUs), Transformer Rectifier Units (TRUs), Power Quality Monitors (PQMs), and batteries.
Understand operation and control of external AC power, including cockpit GPU controls, ground service switches, and electrical synoptic indications.
Describe the function and location of SPDAs and remote electronic circuit breakers, including MCDU maintenance page controls.
Explain RAT deployment logic, manual deployment, and power supply capability for emergency situations.
Identify battery types, capacities, functions, and locations, including their role in standby and emergency power supply.
Recognise built-in test equipment (BITE) functions, CMC message handling, and initiated tests for troubleshooting electrical system faults.

ATA 25 – EQUIPMENT/FURNISHINGS

Scope:
Covers cockpit, passenger cabin, galley, lavatory, emergency equipment, insulation, and furnishings systems, including their layout, operation, and integration with safety features.

Learning Objectives:

Identify cockpit furnishings including seats, linings, consoles, and associated equipment, with emphasis on ergonomic design, insulation, and emergency provisions.
Describe passenger cabin furnishings such as seating, ceilings, sidewall panels, floor finishes, flight attendant panels, closets, partitions, and their role in safety, comfort, and emergency access.
Explain galley layouts, electrical systems, controls, inserts, and safety features including galley master switches and protective mechanisms.
Recognise lavatory features, integration with aircraft systems, accessibility provisions, and emergency access.
Describe emergency equipment locations and functions, including life vests, megaphones, evacuation slides, ELT systems (fixed and portable), and the Low-Frequency Underwater Locator Beacon (LF-ULB).
Explain the operation of the emergency evacuation slide system, including arming/disarming, automatic and manual deployment, and pressure monitoring.
Identify insulation systems for temperature control and noise reduction, and the smoke seal system for aft compartment smoke containment.

ATA 26 – FIRE PROTECTION

Scope:
Covers detection, indication, and extinguishing systems for engines, APU, cargo compartments, lavatories, electronic bays, and cabin areas, as well as portable and automatic extinguishers.

Learning Objectives:

Describe the overall fire protection architecture, including detection loops, extinguishing systems, and crew alerting methods.
Explain engine fire/overheat detection logic, controls, indications, and testing procedures.
Describe APU fire/overheat detection operation, automatic shutdown logic, cockpit controls, and testing.
Identify lavatory smoke detection design, controls, fault indications, and built-in test functions.
Understand cargo compartment smoke detection, detector redundancy logic, indications, and test procedures.
Recognise electronic bay smoke detection and its integration with air management functions.
Describe engine fire extinguishing system configuration, agent routing, cockpit controls, and pressure monitoring.
Explain APU fire extinguishing operation, control logic, and component locations.
Describe cargo compartment fire extinguishing system, including high-rate and low-rate discharge bottles, automatic/manual operation, and agent routing.
Identify location, type, and usage of portable fire extinguishers.
Explain lavatory automatic fire extinguishing system design, activation by temperature, and component placement.

ATA 27 – FLIGHT CONTROLS

Primary Flight Controls

Scope:
Covers fly-by-wire controlled primary surfaces—ailerons, elevators, rudder, and multifunction spoilers in roll augmentation mode—along with their control laws, redundancy, and built-in protections.

Learning Objectives:

Describe the architecture of the fly-by-wire primary flight control system, including the roles of the Flight Control Computers (FCCs), Core Computer Modules (CCMs), and Actuator Control Modules (ACMs).
Explain Normal, Direct, and Ultimate Backup modes of operation and the role of backup battery supply to FCCs.
Identify control inputs (control wheels, columns, rudder pedals), sensing via Rotary Variable Differential Transducers (RVDTs), and trim control interfaces.
Describe aileron system configuration, hydraulic supply, actuator redundancy, disconnect procedures, and cockpit indications.
Explain rudder system operation, thrust asymmetry compensation, yaw damping, and hydraulic segregation for redundancy.
Describe elevator operation, pitch protections, tail-strike avoidance, elevator offload, and disconnect procedures.
Explain multifunction spoiler use in roll augmentation, speed brake function, and lift dumping on landing.
Interpret Flight Control System (FCS) synoptic page indications and Engine Indication and Crew Alerting System (EICAS) messages.
Understand Electrical and Hydraulic Power-up Built-In Tests (PBITs), Integrated Built-In Tests (IBITs), and rigging procedures via the Central Maintenance Computer (CMC).

Secondary Flight Controls

Scope:
Covers high-lift devices (flaps and slats), spoiler systems in speed brake and lift dump modes, horizontal stabilizer trim, and ground spoiler operation.

Learning Objectives:

Describe the flap system configuration, including the Flap/Slat Control Unit (FSCU), Flap Power Drive Unit (FSPDU), and actuator arrangement.
Explain slat system operation, including mechanical drive, symmetry protection, and position monitoring by the FSCU.
Describe spoiler operation in speed brake and ground modes, actuator control, and Ground Spoiler Control Module (GSCM) functions.
Explain horizontal stabilizer trim operation, including normal FCC-controlled trimming, elevator offload, alternate trim control, and position indication.
Identify component locations for flaps, slats, spoilers, stabilizer, and their drive/control units.
Interpret synoptic page displays, EICAS alerts, and control lever positions.
Understand built-in monitoring, automatic and manual tests, rigging procedures, and use of the Flight Controls System Maintenance Switch for maintenance functions.

ATA 28 – FUEL

Scope:
Covers the storage, distribution, transfer, refueling/defueling, and indicating systems that supply fuel to the engines and APU, as well as associated control, monitoring, and warning functions.

Learning Objectives:

Describe the overall fuel system layout, including three main tanks (LH wing, RH wing, center), collector boxes, and vent/surge tanks.
Explain normal and backup fuel feed arrangements, including ejector pumps, AC electrical pumps, and crossfeed operations.
Identify APU feed system operation, including DC and AC pump logic, shrouded feed lines, and shutoff valve control.
Describe pressure refueling/defueling and gravity refueling methods, component locations, and automatic shutoff functions using High Level Sensors (HLS).
Explain the center fuel-transfer system, including automatic and manual control, isolation shutoff valve, and AC center pumps.
Interpret cockpit fuel system controls, Refuel Defuel Panel Indicator (RDPI) functions, and Engine Indication and Crew Alerting System (EICAS) indications for quantity, temperature, and low-level warnings.
Describe the fuel quantity gauging and control system (FQGCS), temperature sensing, and low-level warning logic.
Identify component locations for tanks, pumps, shutoff valves, sensors, and control computers.
Understand maintenance access points, built-in tests, and rigging/check procedures available through the Central Maintenance Computer (CMC).

ATA 29 – HYDRAULIC POWER

Scope:
Covers the three independent hydraulic systems supplying power to primary flight controls, landing gear, brakes, thrust reversers, and other aircraft systems, including redundancy, backup power sources, and ground servicing.

Learning Objectives:

Describe the layout and function of Hydraulic Systems 1, 2, and 3, including normal operating pressure, fluid type, and primary/backup power sources.
Explain the role and operation of Engine Driven Pumps (EDPs), Alternating Current Motor Pumps (ACMPs), the Power Transfer Unit (PTU), and the Ram Air Turbine (RAT) in normal and abnormal operations.
Identify system functions and power supply responsibilities for each hydraulic system, including associated actuators for flight controls, landing gear, brakes, spoilers, and thrust reversers.
Describe cooling, filtering, and fluid management features, including bootstrap reservoirs, accumulators, filter manifolds, and ecology bottles.
Interpret cockpit control panel layout, selector switch functions, guarded pushbuttons, and AUTO/OFF/ON pump settings.
Understand synoptic page indications for pressure, fluid quantity, and temperature, and corresponding Engine Indication and Crew Alerting System (EICAS) messages for low pressure, low quantity, and temperature warnings.
Recognise abnormal condition logic, including automatic backup pump engagement, PTU activation, overheat protections, and isolation valves.
Identify component locations for pumps, valves, reservoirs, and service connections.
Explain ground servicing connection locations, quick-disconnect fittings, and safe replenishment procedures.
Understand automatic Power-up Built-In Tests (PBITs) for ACMPs and PTU, test sequences, and associated EICAS maintenance indications.

ATA 30 – ICE AND RAIN PROTECTION

Scope:
Covers systems that prevent or remove ice, frost, and rain from critical aircraft surfaces and components, including wing and engine anti-ice, windshield and probe heating, water/waste freeze protection, and ice detection.

Learning Objectives:

Describe the Wing Anti-Icing System (WAIS) operation, bleed air source, piccolo tube distribution, automatic/manual control modes, sensors, and leak detection.
Explain the Engine Anti-Icing System (EAIS) bleed air source, valve operation, swirl nozzle function, automatic/manual activation, and overheat protection.
Identify the pitot, static, angle of attack (AOA), and Total Air Temperature (TAT) sensor heating systems, their automatic and manual controls, and fault indications.
Describe windshield rain removal via the Windshield Wiper System (WWS), its modes, and independent subsystem arrangement.
Explain the Windshield Heating System (WHS) temperature control, ramp-up protection, fault monitoring, and built-in test functions.
Recognise passenger door sill heating logic, automatic activation criteria, and overtemperature protection.
Describe potable water and vacuum waste heating systems, including Water & Waste System Controller (WWSC) operation, temperature control set points, and heater locations.
Explain the ice detector system’s vibrating probe principle, automatic activation of WAIS/EAIS, and built-in test capabilities (PBIT, CBIT, IBIT).
Identify component locations for all subsystems, including sensors, valves, controllers, and heaters.
Interpret cockpit ice protection panel controls, anti-ice synoptic page indications, and Crew Alerting System (CAS)/Engine Indication and Crew Alerting System (EICAS) messages.

ATA 31 – INDICATING/RECORDING SYSTEMS

Scope:
Covers the aircraft’s indicating, alerting, recording, and display systems, including central warning functions, cockpit panels, avionics architecture, and built-in test features.

Learning Objectives:

Describe the layout and purpose of cockpit instrument and control panels, including main instrument, glareshield, overhead, lighting control, and control pedestal arrangements.
Explain the function of circuit breaker panels, their location, and fault isolation role.
Understand the chronometer system operation and control via yoke-mounted pushbuttons.
Describe the Digital Voice/Data Recorder (DVDR) system, including Cockpit Voice Recorder (CVR), Flight Data Recorder (FDR), datalink recording, crash-survivable memory, and control panel functions.
Explain the Honeywell Primus Epic Modular Avionics Unit (MAU) architecture, Line Replaceable Modules (LRMs), Integrated Modular Avionics (IMA) concept, and eASCB-D data bus.
Recognise the role of the Aircraft Personality Module and system “strap” configuration for bus channel assignments.
Describe the Central Warning Systems, including Master Warning/Caution indications, Crew Alerting System (CAS) message prioritisation, and aural warning functions.
Identify the Central Display System components: Display Units (DUs), Advanced Graphics Modules (AGMs), Cursor Control Devices (CCDs), and Display Control Panels.
Explain Multi-Function Display (MFD) synoptic and maintenance pages, status pages, and reversionary operation.
Describe the Engine Indication and Crew Alerting System (EICAS) display functions.
Understand system power-up sequences, Built-In Tests (PBIT and CBIT), and manual test initiation via the MCDU for fault isolation.

ATA 32 – LANDING GEAR

Scope:
Covers landing gear structure, operation, control systems, braking systems, nose wheel steering, position indication, and emergency extension, including related safety features and maintenance provisions.

Learning Objectives:

Describe the tricycle-type retractable landing gear configuration, including Main Landing Gear (MLG) and Nose Landing Gear (NLG) assemblies.
Explain normal extension/retraction operation using Hydraulic System 2, electrical control via Proximity Sensor Electronic Modules (PSEMs), and uplock/downlock mechanisms.
Identify the sequence and function of landing gear doors for MLG and NLG, including aerodynamic and clearance considerations.
Describe the alternate mechanical free-fall emergency extension system and its cockpit controls.
Recognise safety features including downlock safety pins, wheel chocks, hydraulic depressurisation procedures, and maintenance lever functions.
Explain MLG and NLG structural components, shock absorber design, side stays, torque links, pintle pins, and attachment to airframe structure.
Describe braking systems:
- Main brake system – hydraulically actuated carbon multi-disc brakes, Brake Control Modules (BCMs), anti-skid, autobrake, and brake temperature monitoring.
- Emergency/parking brake – independent accumulators, Emergency/Parking Brake Valve (EPBV), shuttle valves, and safety protections.
- Brake wear indication and nose wheel spin brake systems.
Explain nose wheel steering (NWS) – hydraulic actuation, control via pedals and handwheel, steering limits, disarming for towing, safety interlocks, and overtravel protection.
Identify component locations for major gear, brake, and steering system elements, including actuators, valves, transducers, and sensors.
Interpret landing gear position and warning system indications, EICAS messages, and audible alerts.

ATA 33 – LIGHTS

Scope:
Covers the aircraft’s interior, exterior, and emergency lighting systems, including control locations, operating logic, and integration with other systems for normal and abnormal conditions.

Learning Objectives:

Describe the interior lighting systems:
- Flight compartment – dome, reading, chart, flood/storm lights, and instrument/panel dimming.
- Passenger cabin – ambient wash lights, mood lighting, spotlights, reading lights, sidewall lighting, and control via Flight Attendant Panels (FAPs) and Cabin Management System (CMS).
- Cargo, service, courtesy, wardrobe/stowage, lavatory, and galley lighting, including automatic activation by microswitches.
Explain the warning sign system (FASTEN SEAT BELT, NO SMOKING, RETURN TO SEAT, TURN OFF ELECTRONIC DEVICES), control locations, automatic functions, and integration with the passenger address system.
Describe the attendant call indicator system – passenger, lavatory, and flight deck call logic, visual and audible indicators, and display of calls on the FAP.
Identify the exterior lighting systems:
- Landing, taxi, navigation, strobe, inspection, red beacon, logo lights – location, control switches, power supply, and SSPC protection.
Explain the emergency lighting system – internal and external lights, exit signs, photoluminescent floor path markings, battery packs, control switches in cockpit and cabin, and automatic activation logic.
Recognise EICAS messages related to lighting system status and readiness, including “EMER LT NOT ARMED.”
Understand maintenance and test procedures for cabin, lavatory, and emergency lights.
Identify the location of major lighting system components, including LEDs, power supplies, and SSPCs.

ATA 34 – NAVIGATION SYSTEMS

Submodule 1 – Air Data and Standby Instruments

Scope:
Covers the Air Data System (ADS), Integrated Pitot/Static/Angle of Attack (AOA) system, Air Data Computers (ADCs), Integrated Electronic Standby System (IES), and Total Air Temperature (TAT) sensors, including controls, indications, redundancy, and failure management.

Learning Objectives:

Describe the Integrated Pitot/Static/AOA system, including Air Data Smart Probes (ADSPs), sideslip compensation, and TAT sensor integration.
Explain the ADC’s role in processing atmospheric data for altitude, airspeed, Mach number, and vertical speed indications.
Recognise redundancy features, sensor heating logic, and Crew Alerting System (CAS) messages for probe/sensor failures.
Identify component locations for ADSPs, TAT sensors, and related avionics modules.
Describe the IES as a self-contained standby display, its independence from primary systems, and backup power supply.
Understand cockpit controls for ADS probe heating, barometric setting, and standby instrument operation.

Submodule 2 – Dependent Position Determining & Landing Aids

Scope:
Covers navigation systems reliant on external signals, including VHF NAV (VOR, ILS, LOC, GS, MB), DME, transponder (Mode S/ADS-B), TCAS, weather radar, EGPWS/windshear detection, and GPS.

Learning Objectives:

Explain VHF NAV operation, frequency tuning, and integration with PFD/MFD displays.
Describe DME operation, pairing with VOR/ILS, and antenna/transceiver locations.
Explain transponder modes, ADS-B functions, redundancy, and MCDU Radio Page operation.
Describe TCAS operation principles, advisories (TA/RA), and display symbology on PFD/MFD.
Identify weather radar functions, display modes, antenna location, and fault indications.
Explain EGPWS and windshear detection logic, alerting, and inhibit controls.
Describe GPS operation, augmentation systems, redundancy, and the MCDU GPS Position Sensor Display.

Submodule 3 – Independent Position Determining

Scope:
Covers navigation systems that operate without external references, including the Inertial Reference System (IRS), Attitude and Heading Reference System (AHRS), and standby compass.

Learning Objectives:

Describe IRS operation using gyroscopes and accelerometers for position, velocity, and attitude data.
Explain IRS alignment, redundancy, and integration with other navigation systems.
Identify IRS component locations, MCDU interface, and PFD/MFD indications.
Describe AHRS function, independence from IRS, and backup role for attitude/heading data.
Identify AHRS component locations and configuration module role.
Recognise standby compass operation, placement, and role during electronic navigation failures.

Submodule 4 – Flight Management Systems (FMS)

Scope:
Covers the integration of navigation and performance data for route planning, guidance, and optimisation via the FMS.

Learning Objectives:

Describe FMS operation, data inputs from GPS, IRS, and ground-based navigation aids.
Explain MCDU flight plan entry, lateral/vertical navigation, and route modification.
Recognise FMS guidance presentation on PFD/MFD, including lateral and vertical deviation indicators.
Interpret VNAV profiles, altitude constraints, and automatic tuning of navigation aids.
Identify component locations for MAUs, MCDUs, GPS receivers, and IRS units supporting FMS operation.

ATA 35 – OXYGEN

Scope:
Covers the crew, passenger, and portable oxygen systems, including oxygen storage, delivery, activation logic, controls, monitoring, safety features, and testing.

Learning Objectives:

Crew Oxygen System – Describe the high-pressure gaseous oxygen supply, components, and operation modes (Normal, 100%, Emergency). Understand mask donning procedures, pressure regulation, cylinder capacity, and EICAS/MFD pressure indications. Recognise overboard discharge indicator purpose, low pressure warnings, and oxygen cylinder bay ventilation system. Identify component locations for cylinders, masks, pressure regulators, sensors, and ventilation equipment.
Passenger Oxygen System – Explain automatic and manual deployment logic via the MASK DEPLOY switch (AUTO, OFF, OVRD) and altimetric switch activation between 14,000–14,750 ft. Describe chemical oxygen generator and gaseous cylinder use in PSUs, galleys, lavatories, and emergency exits. Understand latch operation, EICAS messages, and mask use procedures. Identify component locations in cabin and lavatories.
Portable Oxygen System – Describe portable cylinders and Protective Breathing Equipment (PBE) for medical and firefighting use. Explain flow rate selection, oxygen activation, visual indicators, and protective features. Identify storage locations near crew stations, stowage compartments, and firefighting equipment.
System Tests – Explain preflight and maintenance test procedures for crew masks, regulator flow, communications integration, oxygen pressure checks, passenger system latch testing, and expiration date verification.
Safety Considerations – Recognise hot surface hazards from chemical generators, compartment ventilation requirements, and protective placement of portable units away from heat sources.

ATA 36 – PNEUMATIC

Scope:
Covers the aircraft’s pneumatic system architecture, operation, control, and monitoring, including engine, APU, and external air supply, as well as integration with other aircraft systems such as anti-ice, air conditioning, and potable water pressurisation.

Learning Objectives:

System Overview – Describe the dual independent engine bleed circuits controlled by Air Management System Controllers (AMSCs) with electronic sensing and control for pressure and temperature regulation, overpressure protection, and overheat detection.
Air Bleed Distribution – Explain sources of bleed air (engine LP/HP ports, APU, ground supply) and the role of the Cross Bleed Valve (CBV) in single-bleed operations, isolation, and leak response. Identify duct construction, insulation, anti-flailing devices, and ozone converter installation.
Engine Pneumatic Bleed – Describe LP/HP bleed port selection logic, Pressure-Regulating Shutoff Valve (PRSOV) operation, precooler and Fan Air Valve (FAV) temperature control, and bleed valve prioritisation between APU and engines. Understand leak detection response and cross-bleed operation.
APU Pneumatic Bleed – Explain APU bleed valve and check-valve operation, FADEC control, and flow management for engine starting, ECS supply, and overheat protection.
Ground Air Supply – Describe the High Pressure ground connection, check-valve function, operational logic, and start sequencing using external pneumatic sources.
Water Tank Pressurisation – Explain bleed tap-off from LH manifold, routing, regulator function, and safety features including restrictor orifice and temperature limits.
Air Bleed Control – Identify AMSC location, dual-channel redundancy, Built-In Test (BIT) logic, and cockpit controls for BLEED 1/2, XBLEED, and BLEED APU. Understand EICAS alerts and synoptic page indications.
Indicating & Leak Detection – Describe the Overheat Detection System (ODS) and Leak Detection Loops (LDLs) for engine, APU, and bleed ducts, including redundancy logic, continuity checks, and fault location measurement.
Component Locations – Identify location of valves, sensors, precoolers, AMSCs, and bleed lines within nacelles, pylons, electronic bays, and wing-to-fuselage fairing areas.
System Tests – Explain preflight checks, Power-Up Built-In Tests (PBIT), leak location diagnostics, and maintenance fault isolation via the Central Maintenance Computer (CMC).

ATA 38 – WATER/WASTE

Scope:
Covers potable water supply, waste collection and disposal, air supply, freeze protection, component control, servicing, and monitoring systems.

Learning Objectives:

System Overview – Describe the integrated water and waste system, its subsystems (Potable Water, Waste Disposal, Air Supply), and the role of the Water & Waste System Controller (WWSC) in system control, fault detection, and maintenance reporting.
Potable Water System – Explain storage, pressurisation via engine/APU bleed air or optional compressor, and distribution to lavatories and galleys. Understand tank capacity, water line routing, insulation, heating, and servicing through the aft fuselage panel.
Water Heater System – Describe operation, temperature control, safety features (over-temperature switches, water level sensor), and installation under lavatory washbasins.
Water Quantity Indication – Explain capacitive level sensing, WWSC processing, CMS display, and servicing panel indications. Identify level sensor, service panel, and Flight Attendant Panel locations.
Waste Disposal System – Describe waste and grey water handling, vacuum waste operation using generator or differential pressure, air/water separation, and tank capacity. Understand waste service panel function, tank level sensors, and flushing inhibition logic.
Gray Water Drain System – Explain forward and aft grey water routing, Gray Water Interface Valve (GWIV) operation, auto-drain valves, manual override procedures, and drain mast heating.
Vacuum Waste System (VWS) – Describe flush cycle sequencing, potable water rinse use, vacuum generation, and waste transport to tank. Understand WWSC control, tank level sensors, service procedures, and maintenance test functions.
Air Supply System – Explain potable water tank pressurisation via bleed air or compressor, air manifold components (pressure regulator, filter, shuttle valve, relief valve), compressor cycling logic, and overheat/overpressure protection.
Component Locations – Identify tank positions, heaters, valves, pumps, manifolds, service panels, and compressor placement.
System Tests – Describe Built-In Test (BIT) functions for potable, waste, grey water, and vacuum systems, as well as in-flight and ground servicing checks.

ATA 44 – CABIN SYSTEMS

Scope:
Covers systems that provide cabin communication, passenger announcements, cabin monitoring, environmental control, and security surveillance.

Learning Objectives:

Passenger Address and Cabin Interphone System (PACIS) – Describe the function of the Passenger Address and Cabin Interphone Controller (PACIC) in managing crew/passenger announcements, cabin interphone calls, audio prioritisation, and speaker zoning. Explain PA/interphone operation from cockpit and flight attendant stations, handset controls, LED indications, and audio routing to cabin areas. Identify PACIC location in the forward electronic compartment and speaker installation in PSUs, lavatories, galleys, and entry panels.
Cabin Management System (CMS) – Explain integration of cabin functions including lighting, water/waste monitoring, galley power control, temperature adjustment, announcements, and entertainment features via forward and aft Flight Attendant Panels (FAPs). Describe CMS architecture (FAPs, Input-Output Distribution Nodes, Ethernet ring topology), interface types (RS485, ARINC 429, discrete, CAN Bus, audio, Ethernet), and power supply via SPDAs. Identify FAP, IODN, and cockpit CMS control locations.
Cabin Surveillance System (CSS) – Describe CSS operation using three video cameras, Video Control Unit (VCU), and cockpit CSS monitor unit to provide real-time monitoring of the cockpit entry area. Explain camera imaging capabilities (normal and IR), manual/automatic selection, power supply, and security enhancement. Identify camera, VCU, and cockpit monitor locations, as well as monitor control functions (ON/OFF, AUTO, MANUAL, FREEZE, brightness control).

ATA 45 – MAINTENANCE DIAGNOSTIC AND MEASURING SYSTEMS

Scope:
Covers the Central Maintenance System (CMS) architecture, functions, data recording, wireless and wired access methods, and integration with aircraft subsystems for fault detection, diagnostics, and maintenance support.

Learning Objectives:

Central Maintenance System Overview – Describe CMS purpose and main functions: Central Maintenance Computer Function (CMCF), Aircraft Condition Monitoring Function (ACMF), Recording Functions (Quick Access Recorder – QAR/TCRF, Data Recording Function – DRF), and Print Server Function (PSF). Explain CMS role in collecting, analysing, and displaying maintenance data without determining airworthiness.
Member Systems – Identify key subsystems providing Built-In Test (BIT) results to CMS (e.g., FMS, FADEC, ADC, FCC, SPDA, IRS, AHRS, CMF). Explain communication via ARINC 429 and eASCB-D, and the role of Loadable Diagnostic Information (LDI) in correlating fault reports with maintenance messages.
Recording and Printing Functions – Describe QAR/TCRF for operational quality assurance, DRF for test data capture, and PSF for printing cockpit system reports.
Major Components and Locations – Identify the CMC Advanced Graphics Module (AGM) in MAU 1, Channel B; the Data LAN Management Unit (DLMU) for storage, LAN switching, and maintenance interface; the External Ethernet Maintenance Port near the GPU connection; and the Wireless Server Unit (WSU) in the Middle Electronic Bay with external and 4G antennas.
System Access and Operation – Explain accessing CMS via cockpit Multi-Function Displays (MFDs) using the Cursor Control Device (CCD), through the External Ethernet Maintenance Port, and via the DLMU front panel connections.
Wireless Data Transfer – Describe WSU operation for Wi-Fi and cellular data transfers during parking, automatic activation logic, internal battery use, and data upload/download processes.
System Tests and Maintenance Functions – Recognise CMS menu navigation (Active, Present Leg, Historical Messages), data retrieval, and update procedures via wired or wireless connections. Understand CMC/WSU operational conditions and their role in reducing maintenance turnaround time.

ATA 46 – INFORMATION SYSTEMS

Scope:
Covers the aircraft’s Flight Deck Information Systems, focusing on the Electronic Flight Bag (EFB) and its integration with avionics and wireless communication systems.

Learning Objectives:

System Overview – Describe the purpose of the Flight Deck Information System and its role in replacing paper manuals and charts with electronic versions. Explain EFB functions such as displaying operational documents, performing flight-related calculations, and accessing up-to-date flight information.
Electronic Flight Bag (EFB) Architecture – Explain how commercially available cockpit tablets interface with the aircraft via the EFB Interface Box (EIB) and connect to the Wireless Server Unit (WSU) for internet access.
Data Integration – Describe how the EIB collects data from the Modular Avionics Units (MAUs) and converts it into a tablet-compatible format, using ARINC data bus protocols for communication.
Component Locations – Identify the location of the EIB in the Forward Electronic Compartment, its internal antennas within cockpit USB panels, and their role in wireless data transfer to cockpit tablets.
Power Supply – Recognise the +28 VDC power source for the EIB and its integration with cockpit wireless communication systems.

ATA 47 – INERT GAS SYSTEM

Scope:
Covers the systems used to generate, distribute, and control Nitrogen Enriched Air (NEA) for fuel tank inerting, including air preparation, gas separation, flow distribution, monitoring, and overheat/leak detection.

Learning Objectives:

System Overview – Describe the purpose of the Inert Gas System (IGS) in reducing oxygen concentration within fuel tanks to create a non-flammable ullage. Understand fully automatic operation requiring no flight crew intervention.
Air Preparation System (APS) – Explain bleed air source selection, pressure/temperature conditioning, ozone removal, and automatic shut-off conditions. Identify APS components: Pressure-Regulating Shutoff Valve (PRSOV), Temperature Control Valve (TCV), heat exchanger, ozone converters, sensors, and insulated ducts. Recognise APS control via AMSC 1, redundancy, and safety channel overtemperature protection.
Nitrogen Enriched Air Generation (NEAGS / OBIGGS) – Describe the process of separating nitrogen and oxygen using Air Separation Modules (ASMs), NEA delivery to fuel tanks, and Oxygen Enriched Air (OEA) overboard discharge. Understand regulation by Flow Control Valve (FCV) in high/low flow modes and integration with Fuel Tank Inerting System (FTIS). Identify OBIGGS pack components and locations.
Fuel Tank Inerting System (FTIS) – Distribution – Explain NEA routing to center and wing tanks, operation of inlet, flow control, and wing isolation valves, and safety features such as check valves and flame arrestors. Recognise oxygen concentration monitoring and FTIC control/monitoring functions, including CAS alerts (“FUEL INERT SYS FAIL”, “OUT FAIL”, “DEGRADED”).
Overheat Detection System (ODS) – Describe leak detection for APS bleed lines, use of redundant sensing loops (A/B), detection principle via eutectic salt conductivity, and system reconfiguration on leak detection. Recognise EICAS indications, CMC fault reporting, and component locations in LH wing-to-fuselage fairing.
Component Locations – Identify APS, OBIGGS, FTIS, valves, sensors, ducts, and exhaust lines in fuselage fairing, wing structure, and fuel tanks.
System Tests – Explain APS and OBIGGS tests via CMC (status screens, ASM tests, flow control valve tests), FTIS distribution tests, and ODS continuity checks. Recognise conditions for initiating tests, displayed parameters, and use of IBIT/PBIT for troubleshooting and clearing latched messages.

ATA 51–57 – STRUCTURES

Scope:
Covers the aircraft’s primary structural components, including fuselage, empennage, wings, control surfaces, nacelles/pylons, and stabilizers, with emphasis on structural layout, materials, and integration with systems.

Learning Objectives:

Fuselage – Describe the division into forward, centre (I, II, III), and aft fuselage sections, including structural elements (frames, stringers, skins), pressure bulkheads, and integration of cockpit, passenger cabin, cargo compartments, and APU. Recognise materials (aluminium alloys, composites) and reinforcement for cutouts such as doors and windows.
Floor Panels – Explain honeycomb sandwich construction, panel locations (cockpit, passenger cabin, cargo), and differences in core density and EMI shielding.
Wing-to-Fuselage Fairing – Describe aerodynamic role, composite construction, internal structural supports, and access provisions.
Forward, Centre, and Aft Fuselage Details – Identify specific structural reinforcements for system installations, wing attachments, cargo areas, and emergency exits.
Radome – Explain composite construction for radar transparency, attachment, sealing, and lightning protection features.
Tail Cone – Describe structure, APU housing, firewall, silencer, and aerodynamic closure.
Nacelles and Pylons – Identify pylon structural layout, engine mount fittings, and load transfer paths.
Stabilizers – Explain horizontal and vertical stabilizer construction, attachment, spars, ribs, skins, and fairings.
Control Surfaces – Describe elevator, rudder, aileron, and spoiler structures, including materials, actuation points, lightning protection, and drainage provisions.
Wing Structure – Identify wing stub, main box, outer wing, wing tip, leading and trailing edges, and their structural integration. Recognise materials (machined aluminium, titanium fittings, composite panels) and functional provisions (fuel storage, control surface attachment, anti-ice, and landing gear integration).
Component Locations – Locate major structural assemblies and access points for inspection/maintenance.

ATA 52 – DOORS

Scope:
Covers all passenger, service, cargo, emergency exit, maintenance, and compartment doors, including their structure, operation, locking mechanisms, emergency systems, sensors, and flight deck indications.

Learning Objectives:

Passenger Doors – Describe forward and aft plug-type passenger door construction, operation sequence, and integration of emergency evacuation slides. Recognise internal/external handle operation, vent flap function, door guidance via support arms/rollers, and EICAS status indications. Identify component locations and proximity sensor arrangements.
Overwing Emergency Exit Doors – Explain plug-type metallic structure, manual actuation, vent flap operation, ice-breaker provisions, and flight lock mechanisms. Recognise status indications on MFD/EICAS and proximity sensor placement.
Cargo Doors – Describe forward and aft cargo door construction, hinge/actuation arrangement, sealing, manual operation, gas-spring assistance, stabilisation devices, and EICAS door status indication. Identify component locations and proximity sensor placement.
Service Doors – Explain forward/aft service door design, opening sequence, stabilisation hooks, integrated emergency slides, and pneumatic actuators for emergency opening. Recognise vent flap function, sealing, and proximity sensor use for lock/latch detection.
Other Service Doors – Identify forward electronics compartment hatch, fueling compartment door, aft-fuselage door, and middle electronics compartment access door. Describe construction, operation, locking methods, and cockpit indications (amber caution, cyan advisory).
RAT Door – Describe structure, location, and operation during RAT deployment or maintenance.
APU Doors – Explain construction, manual operation, and access purpose, noting no cockpit indication.
Fixed Interior Doors – Describe reinforced cockpit door structure, decompression panels, locking system, and emergency cabin crew access procedures.
Doors Warning System – Explain monitoring of latch/lock/open-closed conditions via microswitches and proximity sensors. Describe MAU processing, EICAS/MFD visual indications, aural warning logic, and master caution/warning reset functions. Identify sensor locations for all door types.

ATA 49 – AUXILIARY POWER UNIT (APU)

Scope:
Covers the APU and its subsystems providing electrical and pneumatic power, including control, fuel, ignition/starting, air, indicating, exhaust, and oil systems.

Learning Objectives:

System Overview – Describe the APU’s role in supplying electrical and pneumatic power for aircraft systems, ECS, and engine starting. Explain FADEC-controlled start, run, and shutdown sequences, including automatic fault shutdown logic and cool-down mode.
Controls and Indications – Identify cockpit controls (APU MASTER, BLEED, EMERGENCY STOP, FIRE EXTINGUISHING pushbuttons), operational sequencing, and EICAS indications (speed, EGT, CAS messages with green/amber/red ranges).
Powerplant – Describe APU mounting, vibration isolation, air intake, drain/vent system, and structural arrangement in the tail cone.
APU Engine – Explain compressor, combustor, turbine, and accessory drive functions, including bleed air supply to pneumatic systems via APU bleed SOV.
Fuel and Control System – Describe fuel supply from right wing tank (or via cross-feed), electronic fuel module operation, FOHE function, fuel injectors, and FADEC control of solenoid valves and flow divider. Recognise CAS advisories and failure modes.
Ignition/Starting System – Explain BSG and ESC functions, dual igniters, exciter operation, start power sequencing, and FADEC-controlled energising/de-energising logic.
Air System – Describe cooling airflow via inlet door, ACOC, ESC, and eductor discharge, and surge protection using the Anti-Surge Valve (ASV).
Engine Controls – Explain FADEC’s role in monitoring, controlling, and protecting the APU, and manual emergency shutdown procedures.
Indicating System – Describe RPM and EGT sensing, redundancy, maintenance data logging via Data Memory Module (DMM), and associated EICAS messages.
Exhaust System – Identify eductor and liner roles in gas discharge, noise reduction, and compartment cooling.
Oil System – Explain lubrication, cooling, FOHE integration, oil quantity/pressure/temperature sensing, filter bypass, and FADEC shutdown logic for oil faults.
Component Locations – Identify tail cone installations (APU assembly, inlet door, exhaust, gearbox-mounted components, sensors) and cockpit panel locations for APU control.
System Tests – Recognise FADEC-initiated IBIT for inlet door actuator, DMM data retrieval, and operational limitations for start attempts.

PW1900G GEARED TURBOFAN ENGINE

Scope:
Covers the design, operation, and control of the Pratt & Whitney PW1900G geared turbofan engine, its subsystems, mounting, nacelle, and integrated control/monitoring systems.

Learning Objectives:

Engine Overview – Describe twin-spool axial-flow turbofan layout with Fan Drive Gear System (FDGS), airflow separation into primary/secondary streams, LPC, HPC, combustor, HPT, LPT, and accessory gearbox functions.
Primary Structure – Identify FIC, CIC, TIC, TEC frames, bearing compartments, and power transmission via high- and low-pressure rotors.
Subsystem Locations – Recognise placement of reduction gear, cold/compressor/turbine sections, combustion, and accessory drive.
Nacelle and Mounting – Describe nacelle cowling, inlet design, anti-ice, ventilation, PRD, and fan cowl features. Explain forward and aft engine mount load paths and thermal expansion accommodation.
Fire Safety – Explain fire zone isolation via firewalls, seals, PRD, ventilation, and drain systems.
Fuel and Control System – Describe IFPC layout, fuel filtration, FOHX, fuel nozzles, EEC/FADEC control of metering, limit protection, automatic start, thrust rating, and redundancy.
Ignition System – Explain exciter, cables, igniters, redundancy, auto-relight, and cockpit ignition control modes.
Engine Air Systems – Describe Active Clearance Control (ACC), Turbine Cooling Air (TCA), and Bearing Cooling System operation, including bleed sources and EEC scheduling.
Compressor Control – Explain Variable Stator Vane (VSV) and bleed air system roles in operability/stability.
Thrust Control – Describe Thrust Control Quadrant (TCQ), TLA signal transmission, reverse thrust logic, idle lock, TO/GA selection, and Autothrottle integration.
Electronic Control System (FADEC) – Explain thrust rating modes, reserve thrust, derate/Flex TO, ATTCS logic, thrust asymmetry compensation, and bleed management.
Indicating Systems – Describe N1/N2/Nf speed sensing, ITT measurement, vibration and oil debris monitoring via PHMU, and EICAS colour-coded display logic.
Prognostics and Health Monitoring – Explain ODM, vibration balancing, anomaly detection, and maintenance message generation.
Maintenance Interface – Describe MFD engine/APU maintenance page, exceedance/TLD messages, fault code recall/clearing, and dispatch status indications.

New aviation technology is discussed as part of the continuation training. Students are made aware of recent incidents with this Embraer E2