100+ Free SACAA AME Airframes Practice Questions

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Sample SACAA AME Airframes Practice Questions

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1What primary structural difference distinguishes a semimonocoque fuselage from a pure monocoque fuselage?

A.Semimonocoque designs rely entirely on the outer skin to carry all flight and landing loads.

B.Semimonocoque designs utilize internal longitudinal formers, bulkheads, and stringers to reinforce the skin.

C.Pure monocoque fuselages use heavy internal truss frameworks made of welded steel tubing.

D.Semimonocoque fuselages do not require bulkheads or frames for shape maintenance.

Explanation: A semimonocoque fuselage incorporates internal longitudinal members (stringers and longerons) along with vertical bulkheads and formers to reinforce the thin skin, allowing load distribution between skin and internal framework. Pure monocoque relies almost entirely on the outer skin shell.

2Aluminum alloy 2024-T3 is widely used in airframe skins. What do the primary digit '2' and temper designation 'T3' indicate?

A.Major alloying element zinc; solution heat-treated and naturally aged.

B.Major alloying element copper; strain-hardened and stabilized.

C.Major alloying element copper; solution heat-treated, cold worked, and naturally aged.

D.Major alloying element magnesium; solution heat-treated and artificially aged.

Explanation: In the 4-digit aluminum identification system, 2xxx indicates copper as the principal alloying element. The 'T3' temper designation means the alloy has been solution heat-treated, cold worked, and naturally aged to a substantially stable condition.

3Why is high-strength 7075-T6 aluminum alloy frequently clad with pure aluminum (Alclad 7075) when used for external fuselage skins?

A.To increase the overall tensile strength and fatigue limit of the sheet material.

B.To provide cathodic galvanic corrosion protection over the core alloy susceptible to intergranular corrosion.

C.To improve thermal conductivity during high-speed atmospheric friction.

D.To allow easier spot-welding without removing surface oxide layers.

Explanation: 7075-T6 (zinc-copper-magnesium alloy) offers exceptional yield strength but is susceptible to corrosion. Pure aluminum cladding (approx. 1.5% to 5% total thickness per side) acts as a sacrificial anodic layer, protecting the core alloy against intergranular corrosion and stress corrosion cracking.

4When installing metal fasteners through carbon fiber reinforced polymer (CFRP) composite structures, which metal fastener material must be avoided due to galvanic corrosion potential?

A.Titanium alloy (Ti-6Al-4V)

B.Passivated 300-series Stainless Steel

C.Bare or cadmium-plated Aluminum alloy

D.Inconel 718 nickel-chromium alloy

Explanation: Carbon fibers are noble and electrically conductive. When aluminum fasteners contact carbon fiber in the presence of moisture, severe galvanic corrosion of the aluminum occurs rapidly. Titanium and passivated stainless steel are electrochemically compatible with CFRP.

5During a potted core repair on a damaged sandwich honeycomb panel, what is the primary structural requirement regarding core removal?

A.Remove all damaged core material down to the opposite skin while maintaining a 1:1 bevel ratio on the face sheet.

B.Undercut sound core material by 1.5 times the cell diameter around the perimeter of the damage.

C.Remove damaged core back to sound material, leaving clean vertical edges, and undercut the face sheet to create a mechanical key.

D.Remove only the outer face sheet and inject low-density resin into crushed core cells without removing them.

Explanation: A potted core repair requires routing out damaged honeycomb core back to undamaged cells with clean, perpendicular cuts, followed by thorough cleaning and filling with approved syntactic foam or resin paste potting compound.

6What head marking identifies a 2117-T4 aluminum alloy rivet (commonly known as an 'AD' rivet)?

A.A single raised dot

B.A single recessed dimple

C.Two raised dashes

D.A smooth head with no markings

Explanation: AD rivets (2117-T4 aluminum alloy) are identified by a single recessed dimple in the center of the manufactured head. They are field-driven without prior solution heat treatment ('field rivets').

7According to standard airframe repair practices (AC 43.13-1B), what is the minimum recommended rivet edge distance (distance from rivet hole center to sheet edge)?

A.1.5 times the rivet shank diameter

B.2.0 times the rivet shank diameter

C.3.0 times the rivet shank diameter

D.4.0 times the rivet shank diameter

Explanation: Minimum edge distance for solid shank rivets is 2D (twice the shank diameter) measured from the center of the rivet hole to the edge of the sheet. Less distance risks edge shearing/tear-out under load.

8Calculate the correct total length (L) of a solid shank rivet required to join two sheets of aluminum with a combined thickness of 0.090 inch using a 1/8-inch (0.125 inch) diameter rivet.

A.0.187 inch (3/16 inch)

B.0.215 inch (7/32 inch)

C.0.278 inch (nearest standard 5/16 inch)

D.0.375 inch (3/8 inch)

Explanation: Formula for solid rivet length: L = Grip Length (material thickness) + 1.5 × Rivet Diameter. Here, L = 0.090 in + (1.5 × 0.125 in) = 0.090 + 0.1875 = 0.2775 in. Rounding up to the nearest standard 1/16th rivet length yields 5/16 inch (0.3125 in) or nominal 0.278 in shank allowance.

9What feature of a Hi-Lok structural fastener system ensures precise clamping force without requiring a torque wrench?

A.The thread pitch self-locks at a pre-determined axial tension.

B.The collar has a shear washer that collapses under compression.

C.The collar features a shear nut driving hex that breaks off at the design torque limit.

D.The pin contains an internal micro-switch indicator.

Explanation: Hi-Lok collars feature a wrenching hex section designed to shear off at a calibrated torque level, leaving a installed nut collar with consistent clamp-up tension without needing torque wrench verification.

10Which form of corrosion occurs along the grain boundaries of improperly heat-treated high-strength aluminum alloys and can lead to exfoliation?

A.Galvanic corrosion

B.Intergranular corrosion

C.Fretting corrosion

D.Filiform corrosion

Explanation: Intergranular corrosion attacks the grain boundaries of metals where micro-constituents differ electrochemically from the grains. In severe cases, expanding corrosion products cause surface lifting along grain layers, known as exfoliation corrosion.

About the SACAA AME Airframes Exam

The SACAA AME Airframes examination is a mandatory theoretical knowledge paper for South African AME licensing (CAT A and CAT B). The exam tests airframe structures, sheet metal repair, composite materials, hydraulic and pneumatic systems, flight control rigging, landing gear, environmental control, cabin pressurization, and weight & balance.

Assessment

Question count not published by the exam provider

Time Limit

75 minutes

Passing Score

75%

Exam Fee

~R425–R450 per subject (confirm current SACAA Part 187 fee) (South African Civil Aviation Authority (SACAA))

SACAA AME Airframes Exam Content Outline

25%

Structures & Materials

Fuselage, wings, nacelles, metallic alloys, composite materials, fasteners, rivets, corrosion prevention, and structural repair manual (SRM) guidelines.

25%

Hydraulic & Flight Control Systems

Hydraulic pumps, reservoirs, accumulators, actuators, primary and secondary flight controls, cables, push-pull rods, and rigging procedures.

20%

Landing Gear & Braking Systems

Oleo-pneumatic struts, retraction mechanisms, wheels, tires, anti-skid braking systems, nose-wheel steering, and gear alignment.

15%

Environmental Control & Pressurization

Air cycle and vapor cycle air conditioning, outflow valves, cabin pressurization controllers, oxygen systems, and anti-ice/de-ice systems.

15%

Fuel Systems & Weight and Balance

Aircraft fuel tanks, boost pumps, cross-feed valves, fuel quantity indicating, weight & balance calculations, center of gravity (CG) limits, and weighing procedures.

How to Pass the SACAA AME Airframes Exam

What You Need to Know

Passing score: 75%
Assessment: Question count not published by the exam provider
Time limit: 75 minutes
Exam fee: ~R425–R450 per subject (confirm current SACAA Part 187 fee)

Keys to Passing

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

SACAA AME Airframes Study Tips from Top Performers

1Review oleo strut servicing: oil and nitrogen inflation procedures, safety precautions when deflating.

2Understand hydraulic accumulator pre-charge checking and hydraulic fluid compatibility (Skydrol vs mineral oil).

3Memorise flight control rigging terms: turnbuckles, cable tension charts, safety wiring, and fairleads.

4Practice weight and balance calculations using CG = Total Moment / Total Weight formula.

Frequently Asked Questions

What is the pass mark for the SACAA AME Airframes exam?

The pass mark is 75%, tested centrally via SACAA PEXO multiple-choice exam.

Does this exam cover composite materials and sheet metal repair?

Yes, SA-CATS 66 Appendix 2.0A includes metallic alloys, rivets, composite resin/fiber inspection, structural repairs, and corrosion treatment.

Are weight and balance calculations included?

Yes, calculating center of gravity (CG), datum offsets, tare weight, and ballast adjustments are standard topics.

100+ Free SACAA AME Airframes Practice Questions

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