30 Apr

EASA Part 66 Module 13 PDF

Last updated on February 5th, 2022 at 07:05 pm

EASA Part 66 Module 13

Aircraft Structure and Systems.

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EASA PART 66 Module 13 pdf :

13.1 Theory of Flight
airplane aerodynamics and flight controls; high speed flight; rotary wing aerodynamics.

13.2 Structures – General Concepts
fundamentals of structural systems; zonal and station identification systems; electrical bonding, lightening strike protection.

13.3 Autoflight; ATA 52-57
fundamentals of automatic flight controls; command signal processing; modes of operation; yaw dampeners; stability augmentation systems; automatic trim control; autopilot navigation aid interface; autothrottle control; automatic landing systems.

13.4 Communication & Navigation; ATA 23/24
working principles of the following systems:
very high frequency (VHF) communications
high frequency (HF) communications
audio
emergency locator transmitters
cockpit voice recorder
very high frequency omnidirectional range (VOR)
automatic direction finding (ADF)
instrument landing system (ILS)
microwave landing system (MLS)
flight director systems
distance measuring equipment (DME)
very low frequency and hyperbolic navigation (VLF/Omega)
Doppler navigation
area navigation, RNAV systems
flight management systems
global positioning systems (GPS)
global navigation satellite systems (GNSS)
inertial navigation systems
air traffic control transponder, secondary surveillance radar
traffic alert and collision avoidance systems (TCAS)
weather avoidance radar
radio altimeter
ARINC communication and reporting
13.5 Electrical Power; ATA 24
Batteries; DC and AC power generation; emergency power generation; voltage regulation; power distribution; inverters, transformers, rectifiers; circuit protection; external ground power.

13.6 Equipment and Furnishings; ATA 25
emergency equipment requirements; cabin entertainment

13.7 Flight Controls; ATA 27
Primary controls – aileron, elevator, rudder, spoiler; trim control; active load control; high lift devices; lift dump and speed brakes; system operation – manual, hydraulic, pneumatic, artificial feel – yaw damper, Mach trim, rudder limiter, gust lock systems; stall protection; system operation – electrical fly-by-wire.

13.8 Instruments; ATA 31
classification
atmosphere
terminology
pressure measuring devices and systems
pitot-static systems
altimeters
vertical speed indicators
airspeed indicators
machmeters
altitude reporting and alert systems
air data computers
instrument pneumatic systems
direct reading pressure and temperature gauges
temperature indicating systems
fuel quantity indicating systems
gyroscopic principles
artificial horizon
slip indicators
directional gyros
ground proximity warning systems
compass systems
flight data recording systems
electronic flight instruments
instrument warning systems and centralized warning panels
stall warning and angle of attack indicating systems
vibration measurement and indication
glass cockpit

13.9 Lights; ATA 33
external navigation, anti-collision, landing, taxiing, ice; internal cabin, cockpit, cargo; emergency.

13.10 On Board Maintenance System; ATA 45
central maintenance computers, data loading system; electronic library system; printing; structure monitoring.

13.11 Air Conditioning and Cabin Pressurization; ATA 21
air supply; air conditioning; pressurization; cabin pressure controllers; safety and warning devices.

13.12 Fire Protection; ATA 26
fire and smoke detection and warning systems; fire extinguishing systems; system tests; portable fire extinguishers.

13.13 Fuel Systems; ATA 28
system layout; fuel tanks; supply systems; dumping, venting, draining; cross feed and transfer; indications and warning; refueling and defueling; longitudinal balance.

13.14 Hydraulic Power; ATA 29
system layout; hydraulic fluids; reservoirs and accumulators; pressure generation; emergency pressure generation; filters; pressure control; power distribution; indication systems; interface with other systems.

13.15 Ice and Rain Protection; ATA 30
ice formation, classification and detection; anti-icing systems – electrical, hot air, and chemical; de-icing systems,- electrical, hot air, pneumatic, chemical; rain repellent; probe and drain heating; wiper systems.

13.16 Landing Gear; ATA 32
construction; shock absorbing; extension and retraction systems; indications and warning; wheels, brakes, antiskid, and autobraking; tires; steering; air-ground sensing.

13.17 Oxygen; ATA 35
system layout – cockpit and cabin; sources, storage, charging, and distribution; supply regulation; indication and warning.

13.18 Pneumatic/Vacuum; ATA 36
system layout; sources – engine/APU, compressors, reservoirs, ground supply; pressure control; distribution; indications and warning; interface with other systems.

13.19 Water/Waste; ATA 38
system layout, supply, distribution, servicing and draining; toilet system layout, flushing and servicing.

13.20 Integrated Modular Avionics; ATA 42
integrated modular avionic (IMA) modules including bleed management, air pressure control, ventilation control, avionics and cockpit ventilation, temperature control, air traffic communications, avionics communication router, electrical load management, circuit breaker monitoring, electrical system BITE, fuel management, braking control, steering control, oleo pressure, gear retraction, etc; tire pressure indication, brake temperature monitoring, core system network components.

13.21 Cabin Systems; ATA 44
intercommunication data system, cabin network system, cabin core systems; in-flight entertainment; external communications; cabin mass memory system; cabin monitoring systems; miscellaneous cabin systems easa part 66 module 13 pdf.

13.22 Information Systems; ATA 46
aircraft general information system; flight deck information system; maintenance information system; cabin information system; miscellaneous information systems.

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30 Dec

Aircraft Metal Structural Repair

Last updated on January 7th, 2022 at 02:27 pm

Aircraft Metal Structural Repair

Overall rating: ★★★★☆ based on 496 reviews.

Aircraft Aerodynamics, Structures and Systems (3811 Questions)

Category B2 – Aircraft Aerodynamics Exams ( 128 questions 180 min),

easa_part_66_academy Ch04

Chapter 01: Aircraft Structures (70 pages),
Chapter 02: Aerodynamics, Aircraft Assembly, and Rigging (70 pages),
Chapter 03: Aircraft Fabric Covering ( 24 pages),
Chapter 04: Aircraft Metal Structural Repair ( 114pages),
Chapter 05: Aircraft Welding ( 38 pages),
Chapter 06: Aircraft Wood and Structural Repair ( 28 pages),
Chapter 07: Advanced Composite Material ( 58 pages),
Chapter 08: Aircraft Painting and Finishing ( 22 pages),
Chapter 09: Aircraft Electrical System ( 106 pages),
Chapter 10: Aircraft Instrument Systems (86pages),
Chapter 11: Communication and Navigation (78 pages),
Chapter 12: Hydraulic and Pneumatic Power Systems (54 pages),
Chapter 13: Aircraft Landing Gear Systems (96 pages),
Chapter 14: Aircraft Fuel System (62 pages),
Chapter 15: Ice and Rain Protection (32 pages),
Chapter 16: Cabin Environmental Control Systems (62 pages),
Chapter 17: Fire Protection Systems (22 pages),

Aircraft Metal Structural Repair

The satisfactory performance of an aircraft requires continuous maintenance of aircraft structural integrity. It is important that metal structural repairs be made according to the best available techniques because improper repair techniques can pose an immediate or potential danger aircraft metal structural repair.

The reliability of an aircraft depends on the quality of the design, as well as the workmanship used in making the repairs. The design of an aircraft metal structural repair is complicated by the requirement that an aircraft be as light as possible.

If weight were not a critical factor,FAA Airframe Handbook repairs could be made with a large margin of safety. In actual practice, repairs must be strong enough to carry all of the loads with the required factor of safety, but they must not have too much extra strength.

aircraft metal structural repair

For example, FAA Airframe Handbook a joint that is too weak cannot be tolerated, but a joint that is too strong can create stress risers that may cause cracks in other locations.
As discussed in Chapter 3, Aircraft Fabric Covering, sheet metal aircraft construction dominates modern aviation.
Generally, sheet metal made of aluminum alloys is used in airframe sections that serve as both the structure and outer aircraft covering, with the metal parts joined with rivets or other types of fasteners. Sheet metal is used extensively in many types of aircraft from airliners to single engine airplanes, but it may also appear as part of a composite airplane, such as in an instrument panel. FAA Airframe Handbook Sheet metal is obtained by rolling metal into flat sheets of various thicknesses ranging from thin (leaf) to plate (pieces thicker than 6 mm or 0.25 inch).

The thickness of sheet metal, called gauge, ranges from 8 to 30 with the higher gauge denoting thinner metal. Sheet metal can be cut and bent into a variety of shapes.

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30 Dec

Aircraft Fabric Covering

Last updated on January 7th, 2022 at 02:27 pm

Overall rating: ★★★★☆ based on 496 reviews.

Aircraft Aerodynamics, Structures and Systems (3811 Questions)

Category B2 – Aircraft Aerodynamics Exams ( 128 questions 180 min),

easa_part_66_academy Ch03

Chapter 01: Aircraft Structures (70 pages),
Chapter 02: Aerodynamics, Aircraft Assembly, and Rigging (70 pages),
Chapter 03: Aircraft Fabric Covering ( 24 pages),
Chapter 04: Aircraft Metal Structural Repair ( 114pages),
Chapter 05: Aircraft Welding ( 38 pages),
Chapter 06: Aircraft Wood and Structural Repair ( 28 pages),
Chapter 07: Advanced Composite Material ( 58 pages),
Chapter 08: Aircraft Painting and Finishing ( 22 pages),
Chapter 09: Aircraft Electrical System ( 106 pages),
Chapter 10: Aircraft Instrument Systems (86pages),
Chapter 11: Communication and Navigation (78 pages),
Chapter 12: Hydraulic and Pneumatic Power Systems (54 pages),
Chapter 13: Aircraft Landing Gear Systems (96 pages),
Chapter 14: Aircraft Fuel System (62 pages),
Chapter 15: Ice and Rain Protection (32 pages),
Chapter 16: Cabin Environmental Control Systems (62 pages),
Chapter 17: Fire Protection Systems (22 pages),

Aircraft Fabric Covering

Fabric covered aircraft play an important role in the history of aviation. The famous Wright Flyer utilized a fabric-covered wood frame in its design, and continued to be used by many aircraft designers and builders during the early decades of production aircraft. The use of fabric covering on an aircraft offers one primary advantage: light weight. In contrast, fabric coverings have two disadvantages: flammability and lack of durability.

Aircraft Fabric Covering

A Technical Standard Order (TSO) is a minimum performance
standard issued by the FAA for specified materials, parts,
processes, and appliances used on civil aircraft. For example,
TSO-15d, Aircraft Fabric, Grade A, prescribes the minimum
performance standards that approved aircraft fabric must
meet. Fabric that meets or exceeds the TSO can be used as a
covering. Fabric approved to replace Grade-A cotton, such as
polyester, must meet the same criteria. TSO-15d also refers to
another document, Society of Automotive Engineers (SAE)
Aerospace Material Specification (AMS) 3806D, which details
properties a fabric must contain to be an approved fabric for
airplane cloth. Lighter weight fabrics typically adhere to the
specifications.

Fabric

Fabric strength is a major factor in the airworthiness of
an aircraft. Fabric is considered to be airworthy until it
deteriorates to a breaking strength less than 70 percent of
the strength of the new fabric required for the aircraft. For
example, if an aircraft was certificated with Grade-A cotton
fabric that has a new breaking strength of 80 pounds, it
becomes unairworthy when the fabric strength falls to 56
pounds, which is 70 percent of 80 pounds.

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30 Dec

Aircraft Structures

Last updated on January 7th, 2022 at 02:27 pm

Overall rating: ★★★★☆ based on 496 reviews.

Aircraft Structures and Systems (230811 Questions)

Category A – Turbine Aeroplane Exams ( 108 questions 135 min),
Category B1 – Turbine Aeroplane Exams ( 140 questions 175 min),
Category A – Piston Aeroplane Exams ( 72 questions 90 min),
Category B1– Piston Aeroplane Exams ( 100 questions 125 min),
Category B3 – Piston Aeroplane Exams ( 60 questions 75 min),
Category A – Helicopter Aerodynamics Exams ( 100 questions 125 min),
Category B1– Helicopter Aerodynamics Exams ( 128 questions 160 min),
Category B2 – Aircraft Aerodynamics Exams ( 128 questions 180 min),

easa_part_66_academy ch01

Chapter 01: Aircraft Structures (70 pages),
Chapter 02: Aerodynamics, Aircraft Assembly, and Rigging (70 pages),
Chapter 03: Aircraft Fabric Covering ( 24 pages),
Chapter 04: Aircraft Metal Structural Repair ( 114pages),
Chapter 05: Aircraft Welding ( 38 pages),
Chapter 06: Aircraft Wood and Structural Repair ( 28 pages),
Chapter 07: Advanced Composite Material ( 58 pages),
Chapter 08: Aircraft Painting and Finishing ( 22 pages),
Chapter 09: Aircraft Electrical System ( 106 pages),
Chapter 10: Aircraft Instrument Systems (86pages),
Chapter 11: Communication and Navigation (78 pages),
Chapter 12: Hydraulic and Pneumatic Power Systems (54 pages),
Chapter 13: Aircraft Landing Gear Systems (96 pages),
Chapter 14: Aircraft Fuel System (62 pages),
Chapter 15: Ice and Rain Protection (32 pages),
Chapter 16: Cabin Environmental Control Systems (62 pages),
Chapter 17: Fire Protection Systems (22 pages),

aircraft structures

The system of a nacelle for the most part comprises of auxiliary individuals like those of the fuselage. The long way individuals, for example, longerons and stringers, consolidate with level/vertical individuals, for example, rings, formers, and bulkheads, to give the nacelle its shape and basic honesty. A firewall is consolidated to separate the motor compartment from the remainder of the airplane. This is essentially a tempered steel or titanium bulkhead that contains a fire in the bounds of the nacelle as opposed to letting it spread all through the airframe.
Motor mounts are additionally found in the nacelle. These are the auxiliary atherings to which the motor is affixed aircraft structures.
They are generally built from chrome/molybdenum steel tubing in light airplane and manufactured chrome/nickel/ molybdenum congregations in bigger airplane.
The outside of a nacelle is secured with a skin or fitted with a cowling which can be opened to get to the motor and parts inside. Both are typically made of sheet aluminum or then again magnesium combination with treated steel or titanium composites being utilized in high-temperature territories, for example, around the
exhaust exit. Despite the material utilized, the skin is ordinarily connected to the system with bolts aircraft structures.
Cowling alludes to the separable boards covering those zones into which access must be picked up routinely, for example, the motor what’s more, its adornments. It is intended to give a smooth wind current over the nacelle and to shield the motor from harm. Cowl boards are commonly made of aluminum combination development.
Be that as it may, hardened steel is regularly utilized as the internal skin toward the back of the force segment and for cowl folds and close to cowl fold openings. It is likewise utilized for oil cooler pipes. Cowl folds are moveable pieces of the nacelle cowling that open and close to control motor temperature.

Structures Skin

There are numerous motor cowl structures. shows an detonated perspective on the bits of cowling for an on a level plane contradicted motor on a light airplane. It is appended to the nacelle by methods for screws as well as brisk discharge clasp. A few huge responding motors are encased by “orange strip” cowlings which give superb access to parts inside the nacelle. These cowl boards are appended to the forward firewall by mounts which additionally serve as pivots for opening the cowl. The lower cowl mounts are verified to the pivot sections by fast discharge pins. The side what’s more, top boards are held open by bars and the lower board is held in the vacant situation by a spring and a link. All of the cowling boards are secured in the shut situation by overcenter steel hooks which are verified in the shut position
by spring-stacked wellbeing gets aircraft structures.

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easa part 66 module 13 questions

EASA Part 66 Module 13 PDF

EASA Part 66 Module 13

Aircraft Structure and Systems.

Easa Part 66 module 13 pdf Sample Pages

Book Store

EASA Part 66 Module 13 Forum

Module 13: Aircraft Aerodynamics, Structures and Systems

EASA PART 66 Module 13 pdf :

Aircraft Metal Structural Repair

Aircraft Metal Structural Repair

Aircraft Aerodynamics, Structures and Systems (3811 Questions)

Aircraft Metal Structural Repair

aircraft metal structural repair

Aircraft Fabric Covering

Aircraft Aerodynamics, Structures and Systems (3811 Questions)

Aircraft Fabric Covering

Aircraft Fabric Covering

Fabric

Aircraft Structures

Aircraft Structures and Systems (230811 Questions)

aircraft structures

Structures Skin

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