100+ Free SACAA PPL (H) Aircraft Technical Practice Questions

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2026 Statistics

Key Facts: SACAA PPL (H) Aircraft Technical Exam

75%

Passing Score

SACAA CAR 61.01.10

60 Mins

Exam Duration

SACAA Examination Regulations

R425-R450

Sitting Fee

SACAA Fee Schedule

CBT

Exam Delivery

SACAA E-Exams System

36 Months

PPL Theory Validity Window

SACAA FCL CAR Part 61

100

Practice Questions

SACAA PPL (H) Question Bank

Prepare for the SACAA PPL (H) Aircraft Technical & General exam with 100 practice questions covering swashplates, teetering hubs, sprag clutches, governors, tail rotor drives, autorotation, and low RPM horn warnings.

Sample SACAA PPL (H) Aircraft Technical Practice Questions

Try these sample questions to test your SACAA PPL (H) Aircraft Technical exam readiness. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1In a semi-rigid teetering rotor hub design, how are flapping movements of the main rotor blades accommodated during flight?

A.Each blade flaps independently around its own individual flapping hinge pin

B.The entire rotor head teeters as a single unit around a central trunnion and teeter hinge pin

C.Flapping motion is absorbed entirely through flexible composite elastomeric drag hinges

D.Flapping movements are eliminated by rigid titanium root fittings

Explanation: A semi-rigid teetering rotor system features a two-bladed rotor disc attached to the mast via a central teeter hinge pin and trunnion. When one blade flaps up, the opposite blade automatically teeters down by an equal amount as a single unified assembly.

2Which set of mechanical hinges is present on each blade root of a conventional fully articulated rotor hub?

A.Teeter hinge and pitch change bearings only

B.Flapping hinge, drag (lead-lag) hinge, and feathering (pitch change) axis

C.Drag hinge and fixed teeter pin only

D.Elastomeric flexure beam and pitch lock pin

Explanation: A fully articulated rotor hub (typically three or more blades) provides three distinct axes of motion for each individual blade: a flapping hinge for up-and-down motion, a drag/lead-lag hinge for fore-and-aft motion, and a feathering axis for pitch angle changes.

3What structural feature enables a rigid rotor system to allow blade flapping and feathering without traditional mechanical hinge pins?

A.High-pressure hydraulic actuators mounted directly inside the rotor mast

B.Flexible composite blade roots and elastomeric bearings that absorb bending and torsional loads

C.Floating swashplate rings connected directly to the rotor hub casing

D.Counter-rotating upper and lower rotor blade retention pins

Explanation: Rigid (or hingeless) rotor systems eliminate physical mechanical hinge pins by utilizing flexible composite materials in the blade root section and advanced elastomeric bearings. These components bend flexurally to accommodate flapping and lead-lag movements while twisting to allow feathering.

4Why are hydraulic or mechanical drag dampers installed on the drag hinges of a fully articulated main rotor hub?

A.To prevent the blades from teetering into the tail boom during low RPM shutdown

B.To control and damp lead-lag oscillations caused by Coriolis effect, preventing ground resonance

C.To lock the blade pitch angle during high-speed autorotative descents

D.To balance aerodynamic lift between advancing and retreating blades in forward flight

Explanation: In fully articulated rotors, blade flapping alters the blade's distance from the axis of rotation, causing acceleration and deceleration (lead-lag) due to the Coriolis effect. Drag dampers suppress violent lead-lag oscillations and prevent blade hunting that could trigger destructive ground resonance.

5How does a swashplate assembly convert non-rotating pilot flight control inputs into rotating main rotor pitch changes?

A.By tilting and sliding a non-rotating inner ring that transfers movement through a bearing to a rotating outer ring

B.By varying the electrical current sent to individual rotor blade root servo motors

C.By altering the hydraulic pressure inside the main transmission reduction gear casing

D.By shifting the physical center of gravity of the rotor mast via counterweights

Explanation: The swashplate assembly consists of a stationary (non-rotating) ring connected to pilot flight control rods (cyclic and collective) and a rotating ring connected to the blade pitch horns via pitch links. As the stationary ring tilts or slides, it transmits these movements through a bearing to the rotating ring.

6What is the primary function of the drive scissor (or torque link) attached to the rotating swashplate ring?

A.To prevent the stationary swashplate ring from moving vertically during collective inputs

B.To drive and rotate the upper swashplate ring at the same speed as the main rotor mast

C.To dampen high-frequency vibrations originating in the tail rotor drive shaft

D.To lock the pitch change links during engine starting procedures

Explanation: The rotating swashplate ring must rotate synchronously with the rotor mast and blades. The drive scissor (torque link) connects the main rotor hub/mast directly to the rotating swashplate ring, driving it around at rotor RPM while allowing it to tilt and slide.

7When the cyclic pitch control stick is moved forward by the pilot, how does the swashplate affect the pitch angle of individual main rotor blades?

A.It increases the pitch angle equally on all blades simultaneously around the entire 360-degree disc

B.It tilts the swashplate, varying each blade's pitch angle sinusoidally as it rotates around the azimuth

C.It locks the advancing blade pitch while feathering only the retreating blade

D.It disconnects the rotating swashplate ring from the pitch control horns

Explanation: Cyclic control inputs tilt the swashplate assembly. As each rotor blade rotates around the disc azimuth, its pitch horn follows the tilted swashplate, continuously varying the pitch angle sinusoidally (increasing pitch at one side of the disc and decreasing pitch 180 degrees opposite).

8What mechanical action occurs at the swashplate when the pilot raises the collective pitch lever?

A.The swashplate tilts laterally to the left without changing vertical position

B.The entire swashplate assembly slides uniformly up or down along the main rotor mast

C.The stationary swashplate rotates in the opposite direction to the main rotor disc

D.The pitch control links are disengaged from the blade pitch horns

Explanation: Raising the collective lever causes the swashplate assembly (both stationary and rotating rings together) to slide vertically along the rotor mast or sliding sleeve. This raises all pitch change links equally, increasing the pitch angle of all blades simultaneously.

9According to the principle of gyroscopic precession in a rotating main rotor disc, where does maximum aerodynamic displacement occur after a force is applied?

A.At the exact point where the force is applied (0 degrees phase angle)

B.Approximately 90 degrees later in the direction of rotor rotation

C.180 degrees opposite to the point of force application

D.45 degrees prior to the point of force application

Explanation: A rotating rotor disc behaves as a gyroscope. When an aerodynamic force (pitch change) is applied to the disc, the maximum physical displacement (flapping response) occurs approximately 90 degrees later in the direction of rotation (phase lag).

10How do helicopter mechanical flight control designers compensate for the 90-degree phase lag caused by gyroscopic precession?

A.By rigging pitch control linkage inputs to actuate blade pitch horns approximately 90 degrees before the desired disc displacement point

B.By instructing pilots to apply cyclic control inputs 90 degrees out of phase manually

C.By installing counter-rotating flywheels inside the swashplate ring assembly

D.By advancing engine ignition timing by 90 crankshaft degrees

Explanation: To ensure that pushing the cyclic stick forward tilts the rotor disc forward, mechanical control linkages or swashplate pitch horn geometry are rigged so that pitch changes are applied to the blade approximately 90 degrees before the point where maximum displacement is required.

About the SACAA PPL (H) Aircraft Technical Exam

The SACAA Private Pilot Licence (Helicopter) Aircraft Technical & General Knowledge examination evaluates a candidate's mastery of rotorcraft mechanics, engine systems, transmission gearing, antitorque systems, flight instruments, and critical emergency procedures under South African civil aviation regulations.

Assessment

Multiple-choice examination covering Rotor Systems (30%), Powerplants & Transmission (25%), Tail Rotor & Antitorque (20%), and Instruments & Emergency Systems (25%).

Time Limit

60 minutes

Passing Score

75% (CAR 61.01.10)

Exam Fee

Approximately R425–R450 per subject sitting (South African Civil Aviation Authority (SACAA))

SACAA PPL (H) Aircraft Technical Exam Content Outline

30%

Rotor Systems and Flight Controls (Swashplate/Pitch)

Teetering, fully articulated, and rigid rotor hubs, stationary and rotating swashplate rings, cyclic vs collective pitch, gyroscopic precession, phase lag, mast bumping, and aerodynamic flap-pitch coupling.

25%

Helicopter Powerplants and Transmission Systems

Reciprocating piston and turboshaft engines, main rotor transmission gearboxes, belt drive/centrifugal clutches, freewheeling units (sprag clutch), correlators/governors, cooling fans, and magnetic chip detectors.

20%

Tail Rotor Systems and Antitorque Drives

Torque reaction, tail rotor drive shafts and gearboxes, anti-torque pitch sliders, Delta-3 hinges, translating tendency, Loss of Tail Rotor Effectiveness (LTE), NOTAR, and Fenestron systems.

25%

Helicopter Instruments and Emergency Systems

Dual needle engine/rotor tachometers, low RPM horn and light warning systems, manifold pressure and turbine gas temperature gauges, Height-Velocity diagrams, autorotation airflow dynamics, vortex ring state, ground resonance, and dynamic rollover.

How to Pass the SACAA PPL (H) Aircraft Technical Exam

What You Need to Know

Passing score: 75% (CAR 61.01.10)
Assessment: Multiple-choice examination covering Rotor Systems (30%), Powerplants & Transmission (25%), Tail Rotor & Antitorque (20%), and Instruments & Emergency Systems (25%).
Time limit: 60 minutes
Exam fee: Approximately R425–R450 per subject sitting

Keys to Passing

Complete 500+ practice questions
Score 80%+ consistently before scheduling
Focus on highest-weighted sections
Use our AI tutor for tough concepts

SACAA PPL (H) Aircraft Technical Study Tips from Top Performers

1Understand the functional difference between the stationary swashplate (connected to cyclic/collective linkages) and the rotating swashplate (connected to pitch horns).

2Study how the freewheeling unit (sprag clutch) automatically disengages the engine from the rotor system during engine failure to allow autorotation.

3Memorise the mechanics of mast bumping in semi-rigid rotor systems and the mandatory recovery step: gentle aft cyclic before applying lateral cyclic.

4Know the key indications and recovery procedures for Low Rotor RPM (horn and warning light activation at 97% NR in common light training helicopters).

Frequently Asked Questions

What is the pass mark for the SACAA PPL (H) Aircraft Technical exam?

Under SACAA CAR 61.01.10, candidates must achieve a minimum score of 75% to pass the examination.

How long is the SACAA PPL (H) Aircraft Technical exam?

The official exam duration is 60 minutes for approximately 20 to 40 computer-based multiple-choice questions.

What topics are covered in the helicopter aircraft technical subject?

The syllabus includes main rotor hubs and swashplates, powerplants and transmission drive systems, tail rotor antitorque drives, helicopter flight instruments, and emergency aerodynamic regimes like autorotation and vortex ring state.

Where can I take the SACAA PPL (H) theory examinations?

Examinations are written on computer-based testing terminals at SACAA-approved examination centers across South Africa.

100+ Free SACAA PPL (H) Aircraft Technical Practice Questions

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