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Key Facts: Part-66 Module 6 Exam

75%

Pass mark per module

EASA Part-66

80 questions / 100 min

B1 Module 6 exam

Reg (EU) 2023/989

3-option MCQ

Real exam question format

EASA Part-66

11 sub-modules

Module 6 content areas (6.1-6.11)

EASA Part-66 Appendix I

12 June 2024

Reg (EU) 2023/989 applicable date

EUR-Lex

12 June 2026

Deadline to finish under old standard

Reg (EU) 2023/989

EASA Part-66 Module 6, Materials and Hardware, is a basic-knowledge module for the B1/B2 aircraft maintenance licence. The B1 paper is 80 multiple-choice questions in 100 minutes; B2 is 60 questions in 75 minutes; the real exam uses 3-option MCQ at about 75 seconds each, with a 75% pass mark and no essays in Module 6 (essays remain only in Module 7). Content spans ferrous alloy steels (SAE 4130/4340) and heat treatment, non-ferrous aluminium (2024, 7075 with T3/T6/T73 tempers), clad sheet, titanium and magnesium; composites (carbon, glass, aramid, honeycomb, delamination); corrosion types (galvanic, intergranular, exfoliation, stress, fretting, pitting) and protection; fasteners, locking devices and rivets; pipes, springs and bearings; and transmissions, control cables and EWIS electrical wiring and connectors. The syllabus follows Commission Implementing Regulation (EU) 2023/989, applicable 12 June 2024, which merged former sub-modules; transition courses must finish under the old standard by 12 June 2026.

Sample Part-66 Module 6 Practice Questions

Try these sample questions to review concepts for the Part-66 Module 6 exam. Each question includes a detailed explanation. Start the interactive quiz above for the full 125+ question experience with AI tutoring.

1In the SAE/AISI four-digit steel designation system used for aircraft alloy steels, what does the FIRST digit of the number '4130' indicate?
A.The carbon content as a percentage of weight
B.The heat-treatment temper applied to the steel
C.The minimum tensile strength in ksi on the label
D.The major alloying element class (chrome-moly group)
Explanation: In the SAE/AISI system the first digit denotes the major alloying class; '4' is the molybdenum group, with 41xx being the chromium-molybdenum (chrome-moly) steels. 4130 is a classic aircraft chrome-moly steel.
2In the steel designation 4130, what do the last two digits ('30') represent?
A.0.30% carbon content
B.30% chromium content
C.A hardness of 30 HRC
D.30 ksi yield strength
Explanation: The last two digits of the SAE four-digit number give the nominal carbon content in hundredths of one percent, so '30' = 0.30% carbon. This places 4130 as a medium-low carbon chrome-moly steel.
3Which heat-treatment process consists of heating a steel to above its critical temperature and then cooling it SLOWLY (typically in the furnace) to produce a soft, ductile, machinable structure and relieve internal stress?
A.Quench hardening
B.Nitriding
C.Annealing
D.Tempering
Explanation: Annealing heats the steel above its upper critical point and cools it very slowly, giving the softest, most ductile and stress-free condition, which improves machinability and cold-working ability.
4After a steel component has been quench-hardened it is too brittle for service. Which process is applied to reduce that brittleness and toughen the part while retaining most of its hardness?
A.Annealing
B.Normalising
C.Tempering
D.Carburising
Explanation: Tempering reheats a hardened (martensitic) steel to a temperature below the lower critical point and holds it, relieving quenching stresses and trading a little hardness for greatly improved toughness and reduced brittleness.
5Nitriding and carburising are both used on aircraft steel parts. What is their primary purpose?
A.To soften the core of the component for machining
B.To increase corrosion resistance by forming an oxide layer
C.To remove all internal stresses before welding
D.To harden the surface (case) while keeping a tough core
Explanation: Carburising (adding carbon) and nitriding (adding nitrogen) are case-hardening processes that diffuse hardening elements into the surface, giving a hard, wear-resistant case while the core remains tough and ductile.
6A Brinell or Rockwell test is performed on a steel component during inspection. Which material property are these tests measuring?
A.Hardness
B.Tensile strength
C.Fatigue life
D.Impact toughness
Explanation: Brinell (ball indenter) and Rockwell (cone/ball with depth measurement) tests both measure hardness by the material's resistance to indentation under a standard load.
7Which destructive test uses a notched specimen struck by a swinging pendulum to measure a metal's resistance to sudden shock loading?
A.Brinell hardness test
B.Tensile test
C.Charpy impact test
D.Fatigue (S-N) test
Explanation: The Charpy (and the similar Izod) impact test strikes a notched specimen with a calibrated pendulum and measures the energy absorbed in fracture, indicating the material's toughness/impact resistance.
8On a tensile stress-strain graph for a ductile steel, what does the 'yield point' represent?
A.The stress at which the material finally fractures
B.The maximum stress the material can withstand
C.The stress where permanent (plastic) deformation begins
D.The stress at which the cross-section first starts to neck
Explanation: The yield point is the stress at which the material stops behaving elastically and begins to deform plastically (permanently); below it, removing the load returns the specimen to its original length.
9Why is alloy steel 4340 frequently chosen for highly stressed aircraft components such as landing-gear legs?
A.It is the lightest of all common aircraft steels
B.It cannot be heat treated, so properties never change
C.It is immune to all forms of corrosion in service
D.Ni-Cr-Mo gives high strength and toughness when heat treated
Explanation: 4340 is a nickel-chromium-molybdenum alloy steel that, after quench and temper, develops very high tensile strength combined with good toughness and fatigue resistance, ideal for landing-gear and other highly stressed forgings.
10What is the principal alloying element that makes a steel 'stainless' (corrosion resistant)?
A.Chromium
B.Carbon
C.Molybdenum
D.Manganese
Explanation: Stainless steels contain at least about 11-12% chromium, which forms a thin, self-healing passive chromium-oxide film on the surface that resists corrosion.

About the Part-66 Module 6 Exam

EASA Part-66 Module 6 (Materials and Hardware) is one of the basic-knowledge modules required for the EASA aircraft maintenance licence (categories B1 and B2). It tests the metals, composites, fasteners and hardware that make up an aircraft: ferrous and non-ferrous alloys and their heat treatment, composite and non-metallic materials, corrosion, fasteners and rivets, pipes, springs, bearings, transmissions, control cables and electrical cables and connectors. The current syllabus follows Commission Implementing Regulation (EU) 2023/989, applicable from 12 June 2024, which merged several former sub-modules. The real examination is closed-book multiple choice with a 75% pass mark.

Exam sponsor: EASA framework - examinations conducted by National Aviation Authorities or approved Part-147 maintenance training organisations. The requirements and fees below concern the certification or admission exam, separate from our free practice resources.

Questions

80 questions

Time Limit

100 minutes (B1 category)

Passing Score

75% per module

Exam / Certification Fees

Varies by NAA/Part-147 organisation (approximately EUR 50-230 per module sitting)

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.

20%

Aircraft Materials - Ferrous and Non-Ferrous (6.1-6.2)

Steels and aluminium/magnesium/titanium/copper/nickel alloys, heat treatment, identification, testing and corrosion characteristics; 16 of 80 B1 questions (AMC1 Appendix II).

22.5%

Composite and Non-Metallic Materials (6.3)

Composite, wood and fabric structures: characteristics, defect detection and repair; 18 of 80 B1 questions.

10%

Corrosion (6.4)

Corrosion types, causes, detection, prevention and treatment; 8 of 80 B1 questions.

18.75%

Fasteners (6.5)

Screw threads, bolts, studs, screws, locking devices and aircraft rivets; 15 of 80 B1 questions.

10%

Pipes, Springs and Bearings (6.6-6.8)

Rigid and flexible pipes and unions, spring types and loading, bearing types and loading; 8 of 80 B1 questions.

18.75%

Transmissions, Control Cables and Electrical Cables (6.9-6.11)

Gears, belts, chains, control cables, swaging and end fittings, electrical cable types and connectors; 15 of 80 B1 questions.

Preparing for the Part-66 Module 6 Exam

What You Need to Know

  • Passing score: 75% per module
  • Exam length: 80 questions
  • Time limit: 100 minutes (B1 category)
  • Exam / certification fees: Varies by NAA/Part-147 organisation (approximately EUR 50-230 per module sitting) Official sources

Using Our Practice Resources

  • Work through all 125 available questions
  • Review every answer and explanation
  • Track weak areas and revisit them
  • Use our AI tutor for tough concepts

Part-66 Module 6: Suggested Study Strategy

1Learn the SAE four-digit steel code: in 4130 the first digit (4) is the molybdenum/chrome-moly class and the last two digits (30) are 0.30% carbon; do not confuse them with alloy percentages
2Memorise aluminium temper codes: T3 = solution treated, cold worked, naturally aged; T6 = solution treated and artificially aged; T73 = over-aged for stress-corrosion resistance at slightly lower strength
3Know the conditions for each corrosion type - galvanic needs dissimilar metals plus an electrolyte, stress-corrosion needs a susceptible alloy plus a corrosive environment plus sustained tensile stress, and fretting needs small repeated movement
4Drill rivet identification: the AD (2117) rivet head carries a small raised dimple, the DD (2024) icebox rivet a raised double dash, and a correct shop head is about 1.5D wide and 0.5D high
5Practise gear ratios: divide driven teeth by driving teeth (60/20 = 3:1 reduction); remember an idler reverses direction but does not change the overall ratio
6Remember the exam logistics - 75% pass mark, B1 is 80 questions in 100 minutes, the real exam is 3-option MCQ at about 75 seconds each, and there are no essays in Module 6

Frequently Asked Questions

What is EASA Part-66 Module 6?

Module 6, Materials and Hardware, is one of the basic-knowledge modules for the EASA aircraft maintenance licence. It covers ferrous and non-ferrous metals, composites, corrosion, fasteners, rivets, pipes, springs, bearings, transmissions, control cables and electrical wiring and connectors used on aircraft.

How many questions are on the Module 6 exam and what is the pass mark?

For category B1 the exam has 80 multiple-choice questions in 100 minutes; for B2 it is 60 questions in 75 minutes. The pass mark is 75% for every Part-66 module. There are no essay questions in Module 6 - essays remain only in Module 7.

How many options do the real exam questions have?

The real EASA Part-66 examination uses 3-option multiple-choice questions, with roughly 75 seconds allowed per question. This OpenExamPrep practice bank uses 4 options for added challenge, so the underlying knowledge tested is the same but each question is slightly harder.

What changed under Commission Implementing Regulation (EU) 2023/989?

The 2023/989 standard, applicable from 12 June 2024, merged several former sub-modules across the Part-66 syllabus and adjusted some question counts (for example Module 6 B1 rose to 80 questions). Pre-2024 courses must finish under the old standard by 12 June 2026.

What are the main topics in Module 6?

The heaviest topics are corrosion (galvanic, intergranular, exfoliation, stress and fretting), fasteners (threads, bolts, nuts, locking devices and rivets) and the heat treatment of ferrous and aluminium alloys. The module also covers composites, pipes, springs, bearings, transmissions, control cables and EWIS wiring.

How long should I study for Module 6?

Most candidates spend about 40-70 hours over four to eight weeks, often alongside a Part-147 course. Because Module 6 is broad and factual, regular practice questions on alloy tempers, corrosion types, rivet markings and gear ratios are an efficient way to prepare.

Is the UK CAA Module 6 the same as EASA?

Since Brexit the UK CAA Part-66 system has diverged from EASA. This practice bank is written to the EASA syllabus under Commission Implementing Regulation (EU) 2023/989. UK CAA candidates should confirm any differences against current UK CAA requirements.