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Airframes & Systems summary

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In this summary you can find all answers for the easa atpl exam in airframes and systems. The notes are made from courses and exam questions. I used personally these notes to pass all exams.

Last document update: 3 year ago

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  • March 30, 2021
  • April 1, 2021
  • 8
  • 2020/2021
  • Summary
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ATPL THEORY
SUMMARY

, Airframe Design • Static
• dynamic (inflight), cyclic (each leg), vertical load (by lift/weight)

• Stress & Strain Stress (cycle loads, Force/Area):



Tension Compression

Shear Torsion (Torque):
+ sweep
result: Bending (2 forces)
Strain: deformation due stress on material

• Fatigue Continues load cycles (tensile stress) even load remains same
• Increases: Corrosion | High cycles | Poor maintenance | Hard maneuvering

• Corrosion Stress: corrosive environment & tension stress
Highly corrosive: only hydraulic fluid

• Maintenance Never say never:
• Safe Life: replacement after cycles/time (e.g. hydraulic oil)
• Fail Safe/ Redundancy: duplication: > one load path
• Damage Tolerance: capability
• Hard time: fixed intervals | On condition: if necessary

• Failure Minor: slight increase, discomfort
Major: significant reduction
Hazardous: large function reduction
Catastrophic: loss, fatalities

Aircraft
Construction

• Fuselage • Semi-Monocoque: Skin (loads on cylindric), Frames, Stringers
• Monocoque: Skin, Frames & Formers
• Sandwich: unsuitable concentrated loads
• Composite: Matrix & Fibres
➡ Higher strength/weight ratio, strength to direction of load, resistant to
fatigue & corrosion




• Wings • Centre wing box (maximum stressed part)
• Torsion box (spars, ribs, wing skin)
Spars
• Spars (web & girders; load, Mx) | Ribs (aero. shape) | Stringers (assist skin)

• Air: tension lower, compression upper; max. at wing root (CT in Flight)
• Ground: tension upper, compression lower (TC on Ground)

• Aerodynamic Torsion + Bending: Aileron deflects opposite & CG behind hinge
flutter ➡ Avoid: correct mass distribution on controls surface | high stiffness | mass
in front

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