The FAA requires all planes to have a LOV (limit of validity which can be listed in aircraft flight cycles, flight hours or both.

(a)  

measurement of flight hours normally starts when an aircraft initiates motion through its own power

(a)  

activities encompass ground taxiing, departure, flight and arrival

(a)  

T or F
pilots used to start taking records of flight hours before taxiing prior to takeoff and ends after taxiing after landing the aircraft

(a)  

equivalent to 1 pressurization and 1 depressurization

(a)  

refers to designing and constructing aircraft components and systems with materials and method that ensure durability and extended service life

(a)  

critical aspect of aircraft design and maintenance

(a)  

it involves assessing how well an aircraft structure or component can withstand and continue to function safely after sustaining damage

(a)  

involves preventing or mitigating the effects of corrosion on aircraft structures and components

(a)  

refers to design principle that ensures the safety of the aircraft, passengers, and crew in case of a system/ component failure

(a)  

redundant systems, backup mechanism or design features are in place to allow the aircraft to continue operating safely

(a)  

this involves selecting lightweight materials, optimizing structural components, and minimizing excess weight in systems and equipment

(a)  

choosing the right materials is a crucial aspect of AE

(a)  

involves designing the aircraft's structural layout to distribute loads and stresses effectively

(a)  

refers to the ease with which an aircraft can be maintained and serviced throughout its operational life

(a)  

it involves design considerations that make routine inspections, repairs and maintenance tasks more straightforward, cost-effective and efficient

(a)  

involves tasks like refueling. replenishing hydraulic fluids and other routine procedures necessary to keep an aircraft operational

(a)  

relates to the ability to efficiently fix or replace damaged or worn aircraft components

(a)  

refers to how easily specific components or parts of the aircraft can be reached for maintenance or replacement

(a)  

is a broader concept encompassing the ease with which the entire aircraft can be accessed for maintenance purposes

(a)  

it involves considering the layout and design of the aircraft to enable efficient maintenance activities such as engine removal or major inspections

(a)  

Designing for this ensures that critical parts
can be accessed without extensive
disassembly, reducing maintenance time
and costs.

(a)  

Designing aircraft
with this in mind includes using
modular components, accessible
attachment points, and clear procedures
to reduce downtime and maintenance
costs.

(a)  

Inappropriate maintenance procedures or
task performed on and in the aircraft against,
It is conducted against the Aircraft
Maintenance Manual that leads to the
alteration of the airworthy design of aircraft.

(a)  

Defined
method used to balance many
competing and demanding requirements to
produce an aircraft that is strong, lightweight,
economical and can carry an adequate
payload while being sufficiently reliable to
safely fly for the design life of the aircraft.

(a)  

is
the approval of the design of the aircraft
and
all component parts (including propellers, engines,
control stations, etc.). It signifies the design is in
compliance with applicable airworthiness, noise, fuel
venting, and exhaust emissions standards.

(a)  

is
the approval to manufacture
duplicate
products under an FAA approved type design. It
signifies that an organization and its personnel, facilities, and
quality system can produce a product or article that
conforms to its approved design.

(a)  

An
FAA document which grants authorization to operate an aircraft
in flight.

(a)  

Two
types of Airworthiness Certificate

(a)  

The
FAA's official authorization allowing for the operation of a type
certificated aircraft A standard airworthiness certificate allows the
aircraft to be operated and used with the most minimal restrictions
and for compensation and hire

(a)  

This certificate limits operation and use of the aircraft.

Special airworthiness certificates in the experimental category may be issued for:
-Research and development
-Showing compliance with regulations
-Crew training
-Exhibition
-Market survey

(a)  

-Maximum engine thrust available
-Fuel consumption
-Engine mass
-Engine geometry

(a)  

is the common factor that links all aspects of aircraft design such as aerodynamics, structure, and propulsion, all together. An aircraft's weight is derived from various factors such as empty weight, payload and useful load. The center of mass must fit within the established limits set by the manufacturer.

(a)  

focuses not only on strength, aeroelasticity, durability, damage tolerance, stability, but also on fail safety, corrosion resistance, maintainability and ease of manufacturing. The structure must be able to withstand the stresses caused by cabin pressurization, if fitted, turbulence and engine or rotor vibrations.

(a)  

relies upon a duplication of certain structural members to ensure that if one member failed, the other would assume the load of the failed member

(a)  

requires an evaluation of the structure to ensure that should serious damage, that is cracking or partial failure, occur within the operational life of the aircraft, the remaining structure can withstand reasonable loads without failure until the damage is detected.

(a)  

The period during which it is
considered that failure of a component is
extremely unlikely. Life may be expressed in
flying hours, elapsed time, number of flights or
number of applications of load

(a)  

This phenomenon of fracturing after a
series of cyclic loads, maybe much less
than the ultimate load.

(a)  

Regulated aircraft emissions include raw fuel vented to the atmosphere
during normal engine shutdown, and the following products of
combustion in engine exhaust for certain classes of engines: smoke (SN),
hydrocarbons (HC), carbon monoxide (CO), and oxides of nitrogen (NO x).

(a)  

what decibels FAA identified as the significance threshold of noise effects on the ground as well as for determining whether residential land uses are compatible with operations at a nearby airport.

(a)  

Aerodynamics, Propulsion, Weight, Structure

(a)  

Father of Aeronautics

(a)  

it was the first successful powered aircraft. It was made primarily of wood and fabric

(a)  

all metal construction in 1910

(a)  

As early as 1910, he was able to build an aircraft with metal truss construction.

(a)  

J-1 also had a single set of wings or a ?

(a)  

T or F

Used mostly for reconnaissance, stacked-wing tail draggers with wood and metal truss frames with mostly fabric skin dominated the wartime sky.

(a)  

World War I aircraft were typically (a)   like this Breguet 14(circa 1917).

was an early semimonocoque design like this Curtiss HS-2L

(a)  

T or F

The need for pressurized aircraft pervaded aviation. Semimonocoque construction needed to be made even stronger as a result. Refinements to the all-metal semimonocoque fuselage structure were made to increase strength and combat metal fatigue caused by the pressurization-depressurization cycle.

(a)  

T or F

Rounded windows and door openings were developed to avoid weak areas where cracks could form. Integrally machined copper alloy aluminum skin resisted cracking and allowed thicker skin and controlled tapering.

(a)  

the first aircraft with foam core honeycomb in the fuselage.

(a)  

nearly all composite

(a)  

MAJORSTRUCTURAL STRESSES

(a)  

defined as pull (example fuselage)

(a)  

crashing force (example landing gear & wings)

(a)  

two adjacent part opposite direction (example airframe skin and internal structures)

(a)  

twisting force (powerplant during roll banking to the left and right)

(a)  

combination of tension and compression (wings)

(a)  

basic principle unit of an aircraft

(a)  

is the main structure or body of the aircraft. It provides space for cargo, controls, accessories, passengers, and other equipment

(a)  

longeron, diagonal web member, vertical web member

(a)  

is a rigid framework made up of members, such as beams, struts, and bars to resist deformation by applied loads. The truss-framed fuselage is generally covered with fabric

(a)  

single shell (coca cola can)

(a)  

skin, formers, bulkheads

(a)  

relies largely on the strength of the skin or covering to carry the primary loads.

(a)  

This carries all the loads and stresses imposed to the structure.

(a)  

It provides shape and form to the fuselage.

(a)  

It is a heavy frame and partition that contains pressure and disperses concentrated loads.

(a)  

a modification to the monocoque type wherein the skin is stiffened by longitudinal elements. (stiffeners, stringers, longeron).

(a)  

The principal longitudinal member of the fuselage that helps the skin support primary bending load.

(a)  

Longitudinal member in the fuselage to transmit skin loads to body frames.

(a)  

A metal part, other than flat sheet, used in framing of a structure to provide rigidity.

(a)  

Heavy frame and partition that contains pressure and disperses concentrated loads.

(a)  

It provides shape and form to the fuselage

(a)  

are airfoils that, when moved rapidly through the air, create lift.

(a)  

Spars, Stringers, Ribs, Skin, Struts

(a)  

are the principal structural members of the wing

(a)  

gives the wing rigidity by stiffening the skin in compression

(a)  

carries part of the load imposed during flight and transfers it to the rib.

(a)  

are bracings that carry compressive load. (if semi cantilever configuration

(a)  

components of empennage

(a)  

LANDING GEAR CONFIGURATION

(a)  

most expensive part of the aircraft structures. It produces thrust to propel an aircraft.

(a)  

are the structures in the aircraft that attach the powerplant to the wing part of the aircraft.

(a)  

are the removable (capable of opening and closing) part of the nacelle of an aircraft that covers the engine components. They contains PDOS ( POWER DOOR OPENING SYSTEM)

(a)  

casing that houses the aircraft engine

(a)