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Exam (elaborations)

MAC 3701 EXAM PACK (1).pdf School 100% A+

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Section A Multiple Choice Questions 1. A common business decision is the make/buy decision where a manager must choose between buying an item or manufacturing it. The company must evaluate both the qualitative matters, as well as the quantitative matters that deal with costs. The following sta...

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  • November 22, 2021
  • 23
  • 2021/2022
  • Exam (elaborations)
  • Questions & answers
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THE

PILOT


Aircraft
general
knowledge
ATPL
STUDENT
pilot
resume
all info you need to pass atpl exams

, AGK
System design, load, stress & maintenance
• Damage/fault tolerant design:
- Capability to withstand a certain amount of weakening of a structure without catastrophic failure
- Takes cracking of the structure into account
• Fail safe design:
- More than one load carrying component, parallel structural parts, load sharing
- Based on redundancy of components
- Does not imply that the system will never fail despite having backups
• Safe life design:
- Replacement of part after a given number of cycles/flight hours in use
- One load carrying component is sufficient provided it is strong enough
- Does not imply that the system will never fail in the safe life period
There is no most favourable design method, as each component varies
• Maintenance:
1. Hard time: Component overhauled/removed after a set number of hours/cycles regardless of condition
2. On condition: Monitoring of critical parameters & replacement of parts if a limit value is exceeded
• Stress: Force/area
1. Tension: Force resisting from being pulled apart
2. Torsion: Caused by twisting
3. Compression: Push force
4. Torque: Axial rotation force
5. Shear: Force parallel to cross section
6. Buckling: Effect of more than one force
• Strain:
- Deformation due to stress, expressed as a % change of dimension of original dimension
• Elastic deformation
- Tendency of material to return to its original state
- Temporary & reverses when load is removed
• Corrosion: Incorrect metallic bonding
1. Stress: Continuous tensile load + corrosion
2. Intergranular: Grain boundaries inside metal
• Fatigue: Material is continually loaded & unloaded & will eventually break even though load is the same
• Aircraft flies beyond certified load factor: Subject to permanent deformation

No effect Minor Major Hazardous Catastrophic
Qualitive None Probable Remote Extremely remote Extremely improbable
Quantative None 10-3 10-5 10-7 10-9
Flight crew None Slight workload Physical discomfort Physical distress Fatality/Incapacitation
Airplane margins None Slight reduction Significant reduction Large reduction Hull loss
Passengers Inconvenience Physical discomfort Physical distress Serious/fatal injury Multiple fatalities

Airframe
• Engine compartment decking & firewall: Stainless steel/titanium sheet
• Sandwich structure:
- Consists of two thin sheets separated with light core material
- Low mass high stiffness
- Stabilizes covering sheets
- Unsuitable for absorbing concentrated loads
- Does not use resin
• Composite structure:
- Consists of matrix & fibres
- Component strengths can be tailored to the direction of load, not the same in all directions
- Higher strength to weight ratio compared to other metal
• Truss type: Small light aircraft/training planes
• Monocoque:
- Takes all the load on a stressed skin
- Normally uses aluminium/magnesium alloy
• Semi-monocoque:
- Fuselage of transport airplanes

, - Consists of skin, frames & stringers
- Normally uses aluminium/magnesium alloy
• Cantilever:
- Attached to the aircraft at the wing root only (No struts/braces/wires)
- Vertical loads/bending moments highest at wing root
• Wings:
- Torsion box: Consists of spars, ribs, wing skin reinforced by stringers
- Ribs:
• Maintains aerodynamic shape
- Stringers:
• Assists skin to absorb longitudinal compressive loads
- Wing skin:
• When unable to bear load, it transfers them to the spar via ribs & stringers
• Bears cylindrical load during pressurization (TENSION)
- Spar:
• Bears most of the load
• Consists of web & girders (I-beam)
- In the air:
• Lift loads carried by upper/lower skin surfaces & spars
• Tension on lower surface & compression on upper surface
- On the ground:
• Tension in upper surface & compression on lower surface
- Wing bending moments:
• Reduced by installing “upfloat” ailerons, using fuselage fuel first while maintaining fuel in wings as long as
possible
• Torsion: Effect of aileron deflection or positive sweep (As the surfaces hit the air at non uniform levels a
twisting motion is induced)
• From wing root to the tip: First compression then tension
• Aerodynamic flutter:
- Caused by torsion & bending, COP ahead of COG
- Avoided by increasing torsional stiffness & adding balancing mass in front of control surface hinge
- Avoided by ensuring correct mass distribution within the control surface during design
- Wing bends downwards: Flutter may occur if the aileron deflects upwards as aileron COG is behind hinge line
- Wing bends upwards: Flutter may occur if the aileron deflects downwards as aileron COG is behind hinge line
• T – Tail aircraft:
- Vertical stabiliser Is not affected by influence of wing turbulence
• Fuselage:
- Consists of: skin, frames & stringers (No spars/girders)
- Pressurization load = Tension
- Shell structures transmit: Normal bending, tangent bending, tension & torsional stresses (NO SHEAR)
- Torque links: Most stress when making tight turns during taxiing, turning at a small radius
- Floor proximity emergency escape lights: Gives additional guidance during evacuation in reduced visibility
• Cockpit window:
- De-icing provided by electrical heating
- Some aircraft have speed restrictions related to bird impact when window heating inoperative
- Window heating improves strength of cockpit windows
- Cockpit side windows not provided with de-icing, only defoggers
- Made of: Glass & Inner surface made of soft polycarbonate laminate
- Green system “On” information light and an amber failure warning light
• Airplanes designed for long haul cannot be used for short haul flights as lifetime of fatigue sensitive parts have been
determined on a load spectrum
• MZFM: Maximum zero fuel mass – Total maximum permissible mass of the aircraft without usable fuel

Hydraulics
• Pascal’s law: Pressure exerted on hydraulic fluid within an enclosed system the pressure will increase equally throughout
the fluid, and act at right angles to the container walls. Force/area\
• Area(A) x distance(A) = Area(B) x distance(B)
• Most common:
- Phosphate ether based fluids (Skydrol) is purple
- Synthetic oil (Maybe mineral). Synthetic = Highest resistance against cavitation

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