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Key Facts: ATPL Aero & Systems Exam

100

Practice Questions

OpenExamPrep

40

Official Questions

CASA

70%

Pass Mark

CASA

2.5 hrs

Time Limit

CASA

The CASA ATPL Aerodynamics & Systems (AASA) exam is a 40-question test on jet aerodynamics and large aircraft systems. It has a 2.5-hour time limit and a 70% pass mark. This prep contains 100 practice questions.

Sample ATPL Aero & Systems Practice Questions

Try these sample questions to review concepts for the ATPL Aero & Systems exam. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1What is the definition of the critical Mach number (M_crit) for an airfoil?
A.The free-stream Mach number at which the local air velocity at some point on the airfoil first reaches the speed of sound.
B.The Mach number at which the drag coefficient begins to rise rapidly due to shockwave formation.
C.The speed at which the boundary layer separates completely from the upper wing surface.
D.The Mach number at which the aircraft enters a state of uncontrollable nose-down pitch (mach tuck).
Explanation: Critical Mach number (M_crit) is defined as the free-stream Mach number at which the local airflow velocity on the upper surface of the wing first reaches Mach 1.0. This is the threshold at which supersonic flow begins to develop on the airfoil. The rapid rise in drag occurs at a slightly higher Mach number, known as the drag divergence Mach number.
2Which of the following occurs as a primary result of the formation of a normal shockwave on the upper surface of a wing?
A.The local airflow behind the shockwave becomes supersonic and static pressure drops.
B.The local airflow behind the shockwave becomes subsonic, static pressure increases, and density increases.
C.The boundary layer becomes thinner and re-attaches to the wing surface.
D.The total pressure behind the shockwave increases significantly due to compression.
Explanation: Across a normal shockwave, the airflow changes from supersonic to subsonic, static pressure increases sharply, density increases, and velocity decreases. Additionally, total pressure decreases due to the irreversibility of the shock wave.
3What is the primary reason for incorporating wing sweepback on high-speed jet transport aircraft?
A.To increase the lift coefficient at low speeds and improve short-field takeoff performance.
B.To eliminate spanwise flow and prevent wing tip stall at high angles of attack.
C.To delay the onset of compressibility effects and increase the critical Mach number.
D.To reduce structural weight by allowing for a narrower wing root spar.
Explanation: Sweeping a wing reduces the effective chordwise component of the airflow velocity normal to the leading edge. As a result, the wing 'sees' a lower Mach number than the actual free-stream Mach number of the aircraft, which delays the onset of wave drag and increases the critical Mach number.
4What aerodynamic phenomenon is primarily responsible for the rapid increase in drag at Mach numbers above the critical Mach number?
A.Induced drag due to high lift coefficients.
B.Skin friction drag due to turbulent boundary layers.
C.Interference drag between the fuselage and the wing root.
D.Wave drag caused by the energy loss across shockwaves.
Explanation: Once the critical Mach number is exceeded, shockwaves form on the wing surfaces. These shockwaves create wave drag, which is a result of pressure drag from boundary layer separation and thermodynamic energy losses across the shock wave.
5In high-speed flight, what does the term 'Mach Tuck' refer to?
A.An automatic nose-down pitching moment caused by the rearward movement of the center of pressure as shockwaves form.
B.A sudden nose-up pitch caused by the wing tips stalling first on a swept-wing aircraft.
C.The loss of elevator effectiveness due to the shockwave attaching to the trailing edge.
D.A lateral oscillation (yaw/roll coupling) experienced when flying near the maximum operating Mach number.
Explanation: Mach tuck is a nose-down pitching moment that occurs as an aircraft accelerates into transonic speeds. It is caused by the rearward migration of the wing's center of pressure (due to shockwave movement) and a loss of downwash on the horizontal stabilizer (as the wing root shockwaves reduce lift generation at the root).
6What is the primary function of vortex generators installed on the upper surface of a swept wing?
A.To increase the speed of the boundary layer flow, thereby increasing lift in low-speed flight.
B.To energize the boundary layer by mixing high-energy freestream air into it, delaying shock-induced boundary layer separation.
C.To block spanwise airflow and prevent tip stall at high angles of attack.
D.To decrease the critical Mach number of the wing by smoothing the shockwave profile.
Explanation: Vortex generators project into the airflow and create small, high-energy vortices. These vortices mix the fast-moving free-stream air with the slow-moving boundary layer, increasing the kinetic energy of the boundary layer and delaying flow separation behind shockwaves.
7How does increasing the sweepback angle of a wing affect its aspect ratio and aerodynamic efficiency?
A.It increases the effective aspect ratio and improves lift-to-drag ratio.
B.It has no effect on aspect ratio but decreases induced drag.
C.It decreases the effective aspect ratio and reduces the low-speed lift-to-drag ratio.
D.It increases structural rigidity, allowing for longer wings and higher aspect ratios.
Explanation: Sweeping a wing reduces its structural span relative to its area, effectively decreasing the aspect ratio. This, combined with increased spanwise flow, reduces the lift-to-drag ratio (aerodynamic efficiency) at low speeds and requires higher angles of attack for takeoff and landing.
8Which of the following speed ratios defines the Mach number of an aircraft?
A.True Airspeed divided by Calibrated Airspeed.
B.Equivalent Airspeed divided by the local speed of sound.
C.Indicated Airspeed divided by the speed of sound at sea level.
D.True Airspeed divided by the local speed of sound.
Explanation: Mach number (M) is defined as the ratio of the aircraft's True Airspeed (TAS) to the local speed of sound (a) in the surrounding air column: M = TAS / a.
9As an aircraft climbs at a constant Mach number in the troposphere, how do the Calibrated Airspeed (CAS) and True Airspeed (TAS) behave?
A.Both CAS and TAS decrease.
B.CAS decreases while TAS remains constant.
C.CAS remains constant while TAS increases.
D.Both CAS and TAS increase.
Explanation: As altitude increases in the troposphere, ambient temperature decreases, which causes the local speed of sound to decrease. Since Mach number is constant (M = TAS/a), TAS must decrease to match the lower speed of sound. Furthermore, because air density decreases with altitude, CAS must also decrease at a faster rate than TAS to maintain a constant Mach number.
10What is the primary aerodynamic purpose of using a supercritical airfoil profile on modern jet transport aircraft?
A.To eliminate shockwaves completely at supersonic cruise speeds.
B.To delay the onset of wave drag to a higher Mach number by creating a flatter upper surface and aft camber.
C.To increase the critical Mach number by sharpening the wing leading edge.
D.To reduce boundary layer friction by maintaining laminar flow over 90% of the wing chord.
Explanation: A supercritical airfoil has a flatter upper surface, which reduces the acceleration of local airflow and delays the development of a shockwave. When a shockwave does form, it is weaker and located further aft, reducing wave drag and allowing a higher drag divergence Mach number.

About the ATPL Aero & Systems Exam

The CASA ATPL Aerodynamics & Aircraft Systems Exam (AASA) is a mandatory subject for the Airline Transport Pilot Licence in Australia. It tests a pilot's understanding of large aircraft systems and aerodynamics, including high-speed aerodynamics (compressibility, Mach numbers, shockwaves, swept-wing design), airframe structures, gas turbine engines (compressors, combustors, turbines, FADEC), aircraft systems (pneumatic, hydraulic, pressurization, environmental controls), and advanced cockpit instrumentation (FMS, autopilot, flight directors, EFIS, TCAS, GPWS).

Exam sponsor: CASA / ASPEQ Exam Delivery. The requirements and fees below concern the certification or admission exam, separate from our free practice resources.

Assessment

Closed-book computer-based exam administered at approved ASPEQ centers. Candidates are permitted to use a basic calculator.

Time Limit

2.5 hours

Passing Score

70%

Exam / Certification Fees

Approx. $150 - $250 AUD (plus test center provider fees)

Exam sponsor website

Fees, eligibility, and exam policies can change. Confirm them with the exam sponsor before applying or paying.

Our practice resources: topics covered

We aim to reflect publicly available exam outlines and topic information in our study resources. Coverage, format, and difficulty may differ from the actual exam, and we cannot guarantee that every detail is accurate or current. Confirm exam requirements, fees, and policies with the official exam sponsor.

25%

High-Speed Aerodynamics

Mach numbers, wave drag, critical Mach, boundary layer control, and swept-wing effects

20%

Aircraft Structures

Large aircraft structural design, load limits, cabin pressurization fatigue, and primary/secondary flight controls

25%

Gas Turbine Engines

Turbofan and turbojet principles, airflows, compressors, combustors, turbine cooling, FADEC, and APU operation

20%

Large Aircraft Systems

Hydraulics, pneumatics, environmental control (ECS), anti-ice/de-ice, landing gear, and braking systems

10%

Flight Deck Instrumentation

EFIS displays, FMS, autothrottle/autopilot, TCAS, GPWS, and weather radar indications

Preparing for the ATPL Aero & Systems Exam

What You Need to Know

  • Passing score: 70%
  • Assessment: Closed-book computer-based exam administered at approved ASPEQ centers. Candidates are permitted to use a basic calculator.
  • Time limit: 2.5 hours
  • Exam / certification fees: Approx. $150 - $250 AUD (plus test center provider fees) Official sources

Using Our Practice Resources

  • Work through all 100 available questions
  • Review every answer and explanation
  • Track weak areas and revisit them
  • Use our AI tutor for tough concepts

ATPL Aero & Systems: Suggested Study Strategy

1Study swept wing aerodynamics in detail: understand why swept wings delay critical Mach but also cause spanwise flow, necessitating wing fences or vortex generators
2Understand gas turbine compressors: learn the differences between centrifugal and axial compressors, and what causes a compressor stall or surge
3Study large aircraft braking: understand the interaction between anti-skid systems, autobrakes, and fuse plugs (which melt to prevent tire explosions during hot brake events)

Frequently Asked Questions

What is the passing score for the ATPL AASA exam?

The passing score is 70%.

Are calculators allowed in the AASA exam?

Yes, you can bring a basic, non-programmable calculator.