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

Aircraft Ice and Rain Protection

Easa Part 66 Maintenance Practices (4664 Questions)

Sample            –  Maintenance Practices Exams ( 40 questions 30 min),
Category A   – Maintenance Practices Exams ( 72 questions 90 min),
Category B1 – Maintenance Practices Exams ( 80 questions 100 min),
Category B2 – Maintenance Practices Exams ( 60 questions 75 min),
Category B3 – Maintenance Practices Exams ( 75 questions 40 min),

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 Ice and Rain Protection

The two types of ice encountered during flight are clear and Ice and Rain Protection rime. Clear ice forms when the remaining liquid portion of the water drop flows out over the aircraft surface, gradually freezing as a smooth sheet of solid ice. Formation occurs Ice and Rain Protection when droplets are large, such as in rain or in cumuliform clouds. Clear ice is hard, heavy, and tenacious aircraft Ice and Rain Protection.

Its removal Ice and Rain Protection by deicing equipment is especially difficult.
Rime ice forms when water drops are small, such as those in stratified clouds or light drizzle. The liquid portion remaining after initial impact freezes rapidly before the drop has time to spread over the aircraft surface. The small frozen droplets
trap air giving the ice a white appearance. Rime ice is lighter in weight than clear ice and its weight is of little significance aircraft ice and rain protection.

 Aircraft Ice and Rain Protection

However, its irregular shape and rough surface decrease the effectiveness of the aerodynamic efficiency of airfoils, Ice and Rain Protection reducing lift and increasing drag. Rime ice is brittle and more easily removed than clear ice .
Mixed clear and rime icing can form rapidly when water drops vary in size or when liquid drops intermingle with snow or ice particles. Ice particles become imbedded in clear ice, building a very rough accumulation sometimes in Ice and Rain Protection a mushroom shape on leading edges. Ice may be expected to form whenever there is visible moisture in the air and temperature is near or below freezing aircraft ice and rain protection.

An exception is carburetor icing, which can occur during warm weather with Ice and Rain Protection no visible moisture present.

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

Aircraft Fuel System

Easa Part 66 Maintenance Practices (4664 Questions)

Sample            –  Maintenance Practices Exams ( 40 questions 30 min),
Category A   – Maintenance Practices Exams ( 72 questions 90 min),
Category B1 – Maintenance Practices Exams ( 80 questions 100 min),
Category B2 – Maintenance Practices Exams ( 60 questions 75 min),
Category B3 – Maintenance Practices Exams ( 75 questions 40 min),

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 Fuel System

Fuel System Independence Aircraft Fuel System Each fuel system for a multiengine airplane must be arranged so that, in at least one system configuration, the failure of any one component (other than a fuel tank) does not result in the loss of power of more than one engine or require immediate action by the pilot to prevent the loss of power of more than  one engine.
If a single fuel tank (or series of fuel tanks interconnected to function as a single fuel tank) is used on a multiengine airplane, independent tank outlets for each engine, each
incorporating a shut-off valve at the tank, must be provided.
The shutoff valves may serve as firewall shutoff valves, which are also required. However, note that if the line between the valve and the engine compartment contains more than one quart of fuel (or any greater amount shown to be safe) Aircraft Fuel System that can escape into the engine compartment, an additional
firewall shutoff valve is needed. Lines and any components from each tank outlet to each engine must be completely independent of each other .
The fuel tank must have at least two vents arranged to Aircraft Fuel System
minimize the probability of both vents becoming obstructed simultaneously. The filler caps must be designed to minimize the probability of incorrect installation or in-flight loss.

Aircraft Fueling System

Fuel System Lightning Protection Aircraft Fuel System The fuel system must be designed and arranged to prevent the ignition of fuel vapor within the system by direct
lightning strikes or swept lightning strokes (where highly probable). Swept strokes occur when the lightning strike is deformed by interaction with aerodynamic forces and propagates in a unique manner due to the material and shape of the airframe surfaces. Corona and streamering Aircraft Fuel System must also be inhibited at fuel vent outlets since they may ignite the fuel-air mixture . A corona is a luminous discharge that occurs as a result of an electrical potential difference between the aircraft and the surrounding area. Streamering Aircraft Fuel System is a branch-like ionized path that occurs in the presence of a direct stroke or under conditions when lightning strokes are imminent.

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

 Aircraft Landing Gear Systems

Materials and Hardware (4164 Questions)

Sample          –  Materials Exams ( 40 questions 30 min),
Category A   – Materials and Hardware Exams ( 52 questions 65 min),
Category B1 – Materials and Hardware Exams ( 72 questions 90 min),
Category B2 – Materials and Hardware Exams ( 60 questions 75 min),
Category B3 – Materials and Hardware Exams ( 60 questions 75 min),

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 Landing Gear Systems

Numerous configurations of landing gear types can be aircraft Landing Gear Systems
found. Additionally, combinations of two types of gear are  common. Amphibious aircraft are designed with gear that allow landings to be made on water or dry land. The gear features pontoons for water landing with extendable wheels aircraft  for landings on hard surfaces. A similar system is used to  allow the use of skis and wheels on aircraft that operate on  both slippery, frozen surfaces and dry runways. Typically, the  skis are retractable to allow use of the wheels when needed.
Figure 13-2 illustrates this type of landing gear.
NOTE: References to auxiliary landing gear refer to the aircraft Landing Gear Systems nose gear, tail gear, or outrigger-type gear on any particular aircraft. Main landing gear are the two or more large gear aircraft Landing Gear Systems located close to the aircraft’s center of gravity.
Landing Gear Arrangement  Three basic arrangements of landing gear are used: tail wheeltype  landing gear (also known as conventional gear), tandem landing gear, and tricycle-type landing gear.

Tail Wheel-Type Landing Gear  Tail wheel-type landing gear is also known as conventional gear because many early aircraft use this type of arrangement.
The main gear are located forward of the center of gravity, causing the tail to require support from a third wheel aircraft Landing Gear Systems assembly. A few early aircraft designs use a skid rather than a tail wheel. This helps slow the aircraft upon landing  and provides directional stability. The resulting angle of  the aircraft fuselage, when fitted with conventional gear, allows the use of a long propeller that compensates for older, underpowered engine design. The increased clearance of the aircraft Landing Gear Systems forward fuselage offered by tail wheel-type landing gear is also advantageous when operating in and out of non-paved  runways. Today, aircraft are manufactured with conventional aircraft gear for this reason and for the weight savings accompanying the relatively light tail wheel assembly.

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