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CAA NZ AME Licence Exam - Aircraft Engineering Knowledge (Subject 2, New Zealand)

Practice Questions100 questions

Exam Review

Key Facts: CAA NZ AME Aeroplanes 1 (Subject 4) Exam

50 Qs

Total multiple-choice questions on the exam.

CAA NZ / Aspeq Examination Guidelines

90 Mins

Time allowed for the examination.

Aspeq Exam Schedule

70%

Minimum pass mark required.

CAA NZ Advisory Circular AC66-2.4

$108 NZD

Examination fee per sitting.

Aspeq NZ Fee Schedule

Subject 4

CAA NZ AME Licence Syllabus Module for Aeroplanes 1.

CAA NZ AC66-2.4 Syllabus

CAA NZ AME Aeroplanes 1 (Subject 4) is a 50-question, 90-minute examination with a 70% passing threshold for aircraft maintenance engineer licensing in New Zealand.

Sample CAA NZ AME Aeroplanes 1 (Subject 4) Practice Questions

Try these sample questions to review concepts for the CAA NZ AME Aeroplanes 1 (Subject 4) exam. Each question includes a detailed explanation. Start the interactive quiz above for the full 100+ question experience with AI tutoring.

1What is the primary structural difference between a monocoque and a semi-monocoque fuselage design?

A.Monocoque relies entirely on the outer skin to carry primary loads, whereas semi-monocoque uses internal stringers and longerons to assist the skin

B.Semi-monocoque uses non-metallic composite skins exclusively, while monocoque uses aluminum alloy sheets

C.Monocoque features internal longerons without any bulkheads, whereas semi-monocoque relies solely on frames

D.Semi-monocoque carries zero bending stresses, transferring all loads directly to the wing root fittings

Explanation: In a true monocoque fuselage, the stressed skin carries all primary structural loads (bending, tension, torsion) without longitudinal reinforcement. A semi-monocoque design incorporates internal longitudinal members (stringers and longerons) along with transverse frames/bulkheads to support and stiffen the skin, allowing lighter skin gauges and greater structural redundant strength.

2Which type of structural stress is produced on the top skin of a cantilever wing during normal level flight?

A.Tension stress

B.Compression stress

C.Torsional shear stress

D.Pure bearing stress

Explanation: During upward bending of a cantilever wing under aerodynamic lift in level flight, the upper wing skin and upper spar cap experience compressive stress, while the lower wing skin and lower spar cap experience tensile stress.

3Which aluminum alloy heat treatment designation indicates that the material has been solution heat-treated and artificially aged?

A.O

B.T3

C.T6

D.F

Explanation: In standard aluminum temper designations, 'T6' signifies solution heat treatment followed by artificial aging (precipitation hardening) to reach maximum tensile strength.

4What is the primary function of a sandwich panel honeycomb core in composite aircraft structures?

A.To provide high shear strength and keep the outer face sheets at a fixed distance while keeping weight low

B.To absorb fuel in wet-wing storage compartments

C.To conduct electrical grounding currents across composite panels

D.To eliminate the need for surface resin priming prior to painting

Explanation: Honeycomb core materials provide high strength-to-weight and stiffness-to-weight ratios by separating the structural face sheets and transmitting shear loads between them, acting similarly to the web of an I-beam.

5When driven, what should be the approximate diameter of a properly formed solid rivet shop head relative to its original shank diameter (D)?

A.0.5 times D

B.1.5 times D

C.2.5 times D

D.3.0 times D

Explanation: Standard aviation riveting practice dictates that a properly formed shop head (bucktail) must have a diameter of 1.5 times the original shank diameter (1.5D) and a height of 0.5 times the shank diameter (0.5D).

6What alloy identification mark is raised on the head of a 2117-T4 (AD) solid aluminum rivet?

A.Single dimple

B.Two raised dashes

C.Raised cross

D.Plain head with no marking

Explanation: A 2117-T4 (AD code) rivet is identified by a single dimple in the center of its head. AD rivets are field-driven without requiring solution heat treatment prior to driving.

7What is the grip length of an aviation structural bolt?

A.The total length of the bolt including the head

B.The length of the unthreaded unmanufactured shank

C.The distance from the bottom of the head to the tip of the threads

D.The length of the threaded portion of the bolt shank

Explanation: Grip length is the length of the unthreaded shank of the bolt. It should equal the total thickness of the material being bolted together to prevent threads from bearing against structural hole walls.

8What minimum edge distance (from hole center to sheet edge) is generally required when laying out rivet patterns on sheet metal?

A.1 times rivet shank diameter (1D)

B.2 times rivet shank diameter (2D)

C.4 times rivet shank diameter (4D)

D.6 times rivet shank diameter (6D)

Explanation: Standard sheet metal repair practices specify a minimum edge distance of 2 times the rivet shank diameter (2D) measured from the center of the rivet hole to the edge of the sheet to prevent edge tear-out.

9Which composite matrix resin is most commonly utilized in high-performance structural aircraft laminates?

A.Polyester resin

B.Epoxy resin

C.Acrylic resin

D.Polyvinyl chloride resin

Explanation: Epoxy resin offers superior mechanical strength, excellent adhesion, low shrinkage during cure, and chemical resistance, making it the primary matrix material for structural aircraft composite laminates.

10What simple field inspection method is used to detect subsurface delamination in thin composite sandwich panels?

A.Tap testing (coin tap test)

B.Magnetic particle inspection

C.Eddy current testing

D.Dye penetrant inspection

Explanation: Tap testing with a special hammer or light metallic object produces a clear ringing sound over solid bonded composite panels and a dull thud over delaminated or disbonded areas.

About the CAA NZ AME Aeroplanes 1 (Subject 4) Exam

The CAA NZ AME Aeroplanes 1 (Subject 4) examination tests candidate aircraft maintenance engineers on aeroplane airframe structures, metallic stress, composite materials, structural fasteners, primary/secondary flight control systems, cable tensioning, fly-by-wire, hydraulic, pneumatic, fuel, and environmental control systems according to CAA Advisory Circular AC66-2.4.

Exam sponsor: Civil Aviation Authority of New Zealand (exams via Aspeq). The requirements and fees below concern the certification or admission exam, separate from our free practice resources.

Assessment

50 multiple-choice questions administered electronically in 90 minutes.

Time Limit

90 minutes

Passing Score

70%

Exam / Certification Fees

$108 NZD

Exam sponsor website

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

Official sources

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.

35%

Aeroplane Airframe Structures

Monocoque and semi-monocoque construction, metallic stress analysis (tension, compression, torsion, shear, bending), composite materials, honeycomb structures, and structural fasteners (rivets, bolts, blind fasteners).

30%

Primary & Secondary Flight Control Systems

Primary flight controls (ailerons, elevator, rudder), control cable assemblies, tensioning and turnbuckles, push-pull rods, fly-by-wire actuators, trim tabs, balance tabs, and anti-servo tabs.

35%

Aeroplane Hydraulic, Pneumatic, Fuel & Environmental Systems

Hydraulic pumps, accumulators, power braking, anti-skid systems, landing gear retraction and emergency extension, high-pressure pneumatic systems, fuel tanks, boost pumps, crossfeed, venting, air conditioning, and cabin pressurisation outflow/safety valves.

Preparing for the CAA NZ AME Aeroplanes 1 (Subject 4) Exam

What You Need to Know

Passing score: 70%
Assessment: 50 multiple-choice questions administered electronically in 90 minutes.
Time limit: 90 minutes
Exam / certification fees: $108 NZD Official sources

Using Our Practice Resources

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CAA NZ AME Aeroplanes 1 (Subject 4): Suggested Study Strategy

1Understand the difference between monocoque and semi-monocoque airframe structures and how internal bulkheads and stringers distribute flight loads.

2Master rivet identification, pitch, edge distance, and proper countersinking/dimpling techniques for metallic repairs.

3Learn control cable inspection standards, tensiometer temperature compensation charts, and turnbuckle clip-locking procedures.

4Study hydraulic accumulator pre-charging with nitrogen, anti-skid valve logic, and emergency landing gear extension mechanisms.

5Memorize environmental control system functions, focusing on cabin pressurisation outflow valves, safety relief valves, and negative pressure relief valves.

Frequently Asked Questions

What is the CAA NZ AME Aeroplanes 1 (Subject 4) exam?

It is an essential licence examination administered by Aspeq on behalf of the Civil Aviation Authority of New Zealand (CAA NZ) for Aircraft Maintenance Engineers specializing in aeroplane airframes and systems.

What is the passing score and duration?

The passing score is 70% and candidates are given 90 minutes to complete 50 multiple-choice questions.

What topics are covered in CAA Subject 4?

The exam covers airframe structural design and repairs, composite materials, flight control mechanisms and rigging, hydraulic and pneumatic systems, fuel systems, and cabin pressurisation.

Where can I take the exam?

The exam is delivered electronically via Aspeq examination centres located throughout New Zealand.

What is the examination fee?

The exam fee is $108 NZD per attempt.