COLLEGE OF ENGINEERING
DEPARTMENT OF MECHANICAL & INDUSTRIAL ENGINEERING
BEng (Honours) in Computer Aided Mechanical Engineering
Academic Year: 2018-19 Semester: B
MHH124725: Technical Project
Final Report
Project Title: Corrosion Analysis of Aluminum Alloy 7075.
Student Name: Amani Al Ajmi
Student Number: 140150
Supervisor(s): Mr. Said Al Oraimi
Declaration by the Student
I declare that this project report / dissertation titled _____________________________
________________________________________________________________________
is my own work and has not been submitted in any form for another degree or diploma at any university or other institutions of tertiary education. Information derived from the published work of others has been acknowledged in the text and a list of references is given. I am fully aware of the College’s policy on plagiarism and cheating, and that the penalty for submission of plagiarized report could result in a ‘fail’ in Technical Project / Dissertation. I have submitted a copy of this full report in electronic form to my supervisor.
Signature of the Student: Date:
Name of the Student:
Student Number:
Certificate by the Supervisor
The project report / dissertation titled _________________________________________
_______________________________________________________________________
is the bonafide work of Mr./ Ms. ______________________________________________, and bearing student number ______________ is carried out under my supervision. I certify that the work presented in the project report / dissertation is carried out by him / her, and that he / she has achieved the set objectives of the project / dissertation. Information derived from the published work of others has been acknowledged in the text and a list of references is given at the end of the report. I have personally checked this final report for originality / plagiarism through the Turnitin website and, to the best of my knowledge and belief, satisfied that the report is free from plagiarism.
Signature of the Supervisor: Date:
Name of the Supervisor:
Countersigned by HoD:
ACKNOWLEDGEMENT
The acknowledgement by the candidate for successfully carrying out the project work
ABSTRACT
Aluminum plays an important role in a number of industrial applications such as construction and electrical engineering. It is also quite applicable in the transport industry where it is used in the manufacturing and production of machinery used in the aircraft building. Although aluminum and its alloys are quite useful, they are subject to corrosion as are a result of chemical interaction with the surroundings and hence do not the best materials for engineering applications. One of the main significant problem faced by aluminum components used in the aircraft is pitt.
1. COLLEGE OF ENGINEERING
DEPARTMENT OF MECHANICAL & INDUSTRIAL
ENGINEERING
BEng (Honours) in Computer Aided Mechanical Engineering
Academic Year: 2018-19 Semester: B
MHH124725: Technical Project
Final Report
Project Title: Corrosion Analysis of Aluminum Alloy 7075.
Student Name: Amani Al Ajmi
Student Number: 140150
2. Supervisor(s): Mr. Said Al Oraimi
Declaration by the Student
I declare that this project report / dissertation titled
_____________________________
_____________________________________________________
___________________
is my own work and has not been submitted in any form for
another degree or diploma at any university or other institutions
of tertiary education. Information derived from the published
work of others has been acknowledged in the text and a list of
references is given. I am fully aware of the College’s policy on
plagiarism and cheating, and that the penalty for submission of
plagiarized report could result in a ‘fail’ in Technical Project /
Dissertation. I have submitted a copy of this full report in
electronic form to my supervisor.
Signature of the Student:
Date:
Name of the Student:
Student Number:
3. Certificate by the Supervisor
The project report / dissertation titled
_________________________________________
_____________________________________________________
__________________
is the bonafide work of Mr./ Ms.
______________________________________________, and
bearing student number ______________ is carried out under
my supervision. I certify that the work presented in the project
report / dissertation is carried out by him / her, and that he / she
has achieved the set objectives of the project / dissertation.
Information derived from the published work of others has been
acknowledged in the text and a list of references is given at the
end of the report. I have personally checked this final report for
originality / plagiarism through the Turnitin website and, to the
best of my knowledge and belief, satisfied that the report is free
from plagiarism.
Signature of the Supervisor:
Date:
Name of the Supervisor:
Countersigned by HoD:
4. ACKNOWLEDGEMENT
The acknowledgement by the candidate for successfully
carrying out the project work
ABSTRACT
Aluminum plays an important role in a number of industrial
applications such as construction and electrical engineering. It
is also quite applicable in the transport industry where it is used
in the manufacturing and production of machinery used in the
aircraft building. Although aluminum and its alloys are quite
useful, they are subject to corrosion as are a result of chemical
interaction with the surroundings and hence do not the best
materials for engineering applications. One of the main
significant problem faced by aluminum components used in the
aircraft is pitting corrosion. An experimental analysis of
components of aluminum in aircraft to identify corrosion will be
carried out in this project. Findings indicate severe corrosion of
nose landing component leading to its failure. Pitting corrosion
refers to the restricted high metal dissolution as a result of
depletion of the passive film on the metal surface that acts as a
protective cover. This study aims at bringing into discussion an
analysis of corrosion in the aluminum alloy (7076) mainly used
in aircraft components. Therefore, this project identifies the
details on materials, undertaking taste samples on the identified
materials, and measures are undertaken to improve corrosion
resistance. Hence, development of the two types of coating, and
testing their levels of resistance to corrosion.
This experiment identifies two types of heat treatment
experiments useful in testing samples with and without coating
condition. An examination will be carried out on the behavior of
the metal using hardness testing before and after heat treatment,
5. measurement of the surface roughness, corrosion test under wet
conditions. Analysis of these results finally will be carried out
to achieve the objectives successfully.
Keywords: Aluminum alloy (7076) , Pitting corrosion, Hardness
testing, Heat treatment.
TABLE OF CONTENTS
The content shall follow the abstract and indicate the page
numbers of the chapters, sections, sub-sections, appendices and
references. The number and titles of all the items must be
clearly entered with page numbers against them.
LIST OF TABLES
Table Number
Description
Page No.
Table 1.1
Title of the table
Page No.
6. Inside the body of the report use Table captions: Arial, size 11.
Decimal type notations will be used for numbering the tables in
a chapter (e.g. Table 1.1, Table 4.2 etc.)
LIST OF FIGURES
Figure Number
Description
Page No.
Figure 1.1
Title of the figure
Page No.
Inside the body of the report use Figure captions: Arial, size 11.
Decimal type notations will be used for numbering the
figures/photos, charts and drawings in a chapter (e.g. Figure
3.2 , Figure 4.2 etc.)
7. LIST OF SYMBOLS AND ABBREVIATIONS
Chapter name & title
Nomenclature will follow the contents. Its purpose will be to
define all the symbols, abbreviations, Greek or Latin letters,
superscripts etc.
1
10
CHAPTER 1 INTRODUCTION
1. Introduction.
Corrosion is the deterioration of materials by chemical
interaction with the surrounding environment, it is a natural
phenomenon which can be controlled by correcting the
condition when an early warning signs occurs. Airframe issues
related to corrosion have plagued the aerospace industry for
decades. The metals of aircraft components are exposed to
different forms of corrosion, there are many agents which
accelerates the corrosion process such as prolonged exposure to
corrosive factors including moisture, slats and industrial fluids.
The main source of corrosion is water vapor containing salt that
combines with the oxygen in the air. The appearance of
corrosion differs depending on the type of the metal, on the
aluminum alloy surface it shows as pitting which is combined
with white or gray powdery deposit. This project will provide
an experimental study on the corrosion analysis of aluminum
alloy where 75% of aircraft structures are made of aluminum as
shown in Figure 2.
8. Figure 1.1 Pitting Corrosion
Figure 1.2 Aircraft material
1.1 Problem statement:
Pitting corrosion is one of the most common problems faced by
aluminum components used in aircraft, as the name implies this
type of corrosion means the formation of small holes in the
surface of the material. Due to the high-speed landing of
aircraft on the dusty runway, the protective coating is removed
which lead to the exposure of the metals surface to the corrosive
factors.
1.2 The aim of the project:
To perform an experimental study about corrosion analysis of
aluminum alloy material used in aircraft component. 1.3 The
main objectives:
· Identify the causes of corrosion.
· Carry out the corrosion resistance process experimentally.
· Analyze the obtained result.1.4 Scope of studies:
· Literature review about corrosion in aluminum alloy material.
· Investigate and understand the working principle of the metal
coating and heat treatment to reduce the corrosion in aluminum
alloy.
· Implement roughness measurement of the coated samples
followed by corrosion test with sea water and acid.1.5
Importance of the research:
Understanding and analyzing the corrosion behavior is
important, there are many factors regarding the significance of
corrosion study including economic, by implement corrosion
control process, the useful life of aircraft can be extended,
therefore the maintenance cost will be reduced. Also, the best
insurance against corrosion associated failures is studying and
9. testing the metals used in the design of the planes in order to
select the proper ways to control the problem to increase the
safety of public.
CHAPTER SUMMARY
CHAPTER 2: LITERATURE REVIEW
2. Introduction.
2.1 Effect of heat treatment on some mechanical properties of
7075 aluminium alloy.
Adeyemi Dayo Isadare, Bolaji Aremo, Mosobalaje Oyebamiji
Adeoye, Oluyemi John Olawale, Moshood Dehinde Shittu,
(2013) work entails a detailed explanation of their experiment
which involved an examination of annealing on micro-structural
morphology as well as mechanical properties of 7075 Al alloy.
Additionally, the experiment evaluated the relationship between
age hardening on microstructural characteristics of 7075 alloy.
The researchers concluded from the experiment results that
annealing heat treatment had the power to do away with micro-
segregation. Age hardening heat treatment was also observed to
bring an improvement on mechanical characteristics of the
Alloy (Isadare, Aremo, Adeoye, Olawale & Shittu, 2013). This
work perfectly fits the topic since it shed light on how the
project topic can be handled. This stem from the fact that the
work reveals that age hardening heat treatment can improve the
mechanical property of the aluminum alloy. One such
characteristic is resistance to corrosion. To make the allow
resistant to corrosion by other elements or acids using the
10. results from Adeyemi Dayo Isadare, Bolaji Aremo, Mosobalaje
Oyebamiji Adeoye, Oluyemi John Olawale, Moshood Dehinde
Shittu (2013) work it’s hence recommendable to do age
hardening heat treatment.
2.2 Quenching of aluminum alloys: cooling rate, strength, and
inter-granular corrosion‖.
Patricia Kavalco, Canale Lauralice and George Totten (2009)
research entails the study of intergranular corrosion (IGC). The
researchers investigated how intergranular corrosion could be
used to reduce corrosion. In the study, it was found out that the
cooling rate of any aluminum alloy determined the rate of
pitting corrosion. The slower the rate of cooling the fewer
chances an aluminum allow being affected by corrosion. On the
other hand, if an alloy was quickly cooled the impact would be
that the alloy would be easily corroded by corrosive reagents or
chemicals (Kavalco, Lauralice & Totten, 2009). On that note,
the authors recommend that while making any aluminum allow
it was crucial to give attention to the cooling rate. In the event
that the alloy will be exposed to highly corrosive agents, it is
advisable to have the cooling rate very slow and vice versa.
This work is useful in informing the topic that is corrosion in
Aluminum alloy. With the findings from the source, one can
state that corrosion in aluminum alloys is dependent on the rate
of cooling of the alloy during its making.
2.3 Improvement Properties of 7075-T6 Aluminum Alloy by
Quenching in 30% Polyethylene Glycol and Addition 0.1%B‖.
Jasim Salman, Shaymaa Alsada and Khadim Al-Sultani (2013)
work discusses the results of their experiment. The experiment
was set up to investigate the impact of sodium chloride,
polyethylene glycol and boron on aluminum alloy. The authors
wanted to know whether the combination of these solutions or
elements could improve the feature of the 7075-T6 alloy. The
target features were corrosion resistance, toughness as well as
11. thermal aging behavior. The researchers took 3.5% NaCl, 30%
polyethylene glycol and Boron solution and treated 7075- T6
alloy with. The results indicated that the solution improved the
toughness feature of the alloy by 50%. However, the corrosion
property was not significantly influenced by the solution. This
indicates that the solution cannot be used to improve the
corrosion resistance of the alloy (Salman, Alsada& Al-Sultani,
2013). Generalizing the case to other types of aluminum alloys
one can draw an insight that a mixture of boron, sodium
chloride and polyethylene glycol have no properties in
improving the corrosive resistance feature of an aluminum
alloy. On that note, the work is significant in this topic since it
gives direction on elements and solution which should not be
used while improving the resistance features of an aluminum
alloy.
2.4 Recent developments in advanced aircraft aluminum alloys.
Tolga Dursun and Costas Soutis (2014) work is about their
review on the recent aluminum technology employed in aircraft
industry which is one area aluminum alloys are industrially
exploited. The authors learned that the technology has led to
having damage tolerant, strong, tough and corrosion resistant
alloys. The review shows that a combination of Aluminum and
zinc leads to a very strong alloy. Mixing Aluminum and copper
results to a high damage resistant alloy. Of key importance in
this context is mixing aluminum and lithium that is AL-Li. The
outcome is an alloy with improved properties such that the alloy
is has higher fracture toughness and is corrosion resistant
(Dursun& Soutis, 2014). This work is essential in the study of
this topic from the angle that it shows the right chemical
composition that can be used to have a high corrosion resistant
12. alloy.
2.5 Aluminum Alloys for Aerospace Applications‖, Aerospace
Materials, and Material Technologies.
The work entails a history of aerospace technology with
aluminum alloys in focus. Also, entails classification of
aluminum alloys. The classification is based on temperatures
used to heat and cool the alloys. This is because the
temperatures are a significant determinant of the strength
property as well as other features (Rambabu, Prasad& Wanhill,
2017). Additionally, the work entails weaknesses or gaps in the
current aluminum technology used in aerospace. These gaps are
crucial in handling the topic given that they will show areas that
require more research in improving the corrosion resistance
feature of aluminum alloys.
2.6 Aluminium alloy corrosion of aircraft structures: modelling
and simulation.
To prevent corrosion occurrences, Aluminum and its alloys
were properly handled using various protection methods that
prevent corrosion of the aircraft. These methods include:
waxing, painting, zinc-chromate priming, coating using thin
layer of Alclad, anodizing and coating with a liquid protective
solution (DeRose, 2013 pg. 23-29).
Barrier coating using materials such as paint, plastic, wax or
powder was applied and left out for some time for later
observations. Aluminum was also coated using a thin layer of
pure aluminum. Pure aluminum was successfully sprayed on the
aluminum flat and round coupons at low temperatures. Hardness
test was then carried out before and after the heat treatment
Demo, (Steiner, Friedersdorf, and Putic, 2010 pg. 1-9).
Aluminum specimen was heated at 500 Celsius and then
quenched in cold oil. Hardness of the heat-treated specimen and
those without heat treated specimen was measured in and
recorded. Resistance to corrosion of the samples was evaluated
in 3.5 % sodium chloride solution by weight loss method.
Corrosion test was also conducted in wet conditions which
13. included seawater and hydrochloric water conditions.
Roughness measurements were also conducted on the final
product.
2.7 Milestone case histories in aircraft structural integrity.
We found out that epoxy, nylon and urethane which are types of
powders, which were heated and placed on the aluminum
surface to form a thin film layer offered protection from
corrosion. Plastic and waxes which were sprayed onto the
aluminum surfaces acted as a coating to offer protection to
aluminum surface from mixing with other corrosive elements
that lead to corrosion (Wanhill, Molent, Barter and Amsterdam,
2015 pg. 346) People have come up with current painting
systems in the aircraft components that combine different
painting layers which have been designed to serve different
functions. They are usually applied in three layers. The first
spray paint acts as the inhibitor which decreases the activity of
the aluminum and its alloys or blocks it from combining or
reacting with other corrosive elements. The second and
intermediate layers of paint coats are applied to add to the
overall thickness of the paint and to make sure that no
aluminum surface is left exposed (Kiyak, 2012 pg. 9-16) The
last and finish coat is primarily designed to offer resistance to
the environmental factors such as humidity, pH concentration
and alkaline concentration of the surrounding.We also found out
that pure aluminum coating component insulates and protects
aluminum from corroding. This helped in reducing the extent of
corrosion.
2.8 Can pitting corrosion change the location of fatigue failures
in aircraft?
14. Regarding hardness test, it was found out that after heat
treatment at 500 °C and subsequent quenching in oil of
aluminum component the hardness and corrosion resistance of
pure aluminum improved whereas before heat treatment, the
hardness and corrosion resistance of the material was low.
Concerning corrosion in wet areas, we found out that aluminum
corrodes faster or quicker when placed in wet areas. This is
because the water component acts as a catalyst in the process of
corrosion (Crawford, Loader, Liu, Harrison, and Sharp, 2014
pg. 304-314). When Aluminum, which is the material used to
make aircrafts, is left unprotected in certain areas such as salty
areas near the ocean or sea waters, it will form an oxide layer
and corrodes almost immediately. Because of the corrosive
action of this strongest of acids like hydrochloric acid on metals
like aluminum, normally, non-metal materials are preferred,
when possible (Jaya, Tiong, and Clark, 2012 pg. 64-73).
Aluminum have useful corrosion resistance in low
concentrations of HCl. The corrosivity increases dramatically as
the concentration of HCl and temperature increase. This led to
an increased rate and extent of corrosion. Therefore, the extent
of destruction was higher in wet areas as compared to that one
in dry areas.
2.9 Recent developments in advanced aircraft aluminium
alloys. Materials & Design.
The main disadvantage of using coating as a method of
preventing corrosion is that the coating components need to be
reapplied over and over again which is tiring and expensive.
Poorly applied coatings always fail and can lead to increased
rate and increased extent of corrosion (Dursun and Soutis, 2014
pg. 862-871). Sometimes, there might exist some volatile
organic components in certain coatings which make them
vulnerable to corrosion.
2.10
15. Chapter Summary.
This section provides some past researches and works related to
corrosion; each author studied the topic from different areas
including the relationship between age hardening on
microstructural characteristics of Al 7075 alloy which
concluded from the experiment results that annealing heat
treatment had the power to do away with micro-segregation.
Also, investigation on how intergranular corrosion could be
used to reduce corrosion where the authors recommend that
while making any aluminum allow it was crucial to give
attention to the cooling rate. Moreover, another author
discussed the impact of sodium chloride, polyethylene glycol
and boron on aluminum allow. In addition to another review
shows that a combination of Aluminum and zinc leads to a very
strong alloy. As well as the classification of aluminum alloy
were studied, and the author concluded that the classification is
based on temperatures used to heat and cool the alloys. This is
because the temperatures are a significant determinant of the
strength property as well as other features. Also, barrier coating
is one of the easiest and cheapest methods in preventing
corrosion in aircraft components made of aluminum. It was very
effective in preventing corrosion but only if proper procedures
were carried out carefully. Coating, therefore, insulates,
beautifies and increases the aircraft’s life expectancy. It is also
easy to apply and reflects 80% of ultraviolet rays. Though it
faces certain challenges, it is very effective in preventing
corrosion in aluminum, an aircraft component.
CHAPTER 3 EXPERIMENTAL SETUP
16. 3. Introduction.
This chapter includes the steps
3.1 Samples preparation.
For an accurate and fast cutting of the Aluminum alloy sheet, a
mechanical guillotine called Morgan Rushworth RGMS is used.
Figure 3.2 Aluminum alloy sheet before cutting
Figure 3.1 Morgen Rushworth RGMS
The working principle of this machine is:
1. Place the Aluminum sheet on the
17. Figure 3.3 Aluminum alloy sample after cutting
Then, using metal stamps and hammer the numbering step is
done by applying the following procedure:
1. Place the desired number stamp on the sample.
2. Strike twice on the stamp using the hammer.
3. The number will appear on the sample.
4. Repeat the steps using different numbers for different
samples.
Figure 3.4 Metallic Stamp
Figure 3.5 Hammer
18. Figure 3.6 Samples After Numbering
3.2 Coating step.
In this step I used three types of coating: Al2O3 (Aluminum
Oxide), Zinc and Underbody Rubber coating.
3.2.1 Aluminum Oxide coating:
To achieve this type of coating an Aluminum Oxide powder,
Aluminum paint and a brush is needed. The procedure is:
1. Prepare a mixture of 25 ml of Aluminum paint with 250 g of
Al2O3.
2. Place the mixture in the rotary shaker for one hour.
3. Apply the Aluminum oxide mixture on the sample using a
brush.
4. Put the coated sample in a place to be exposed to air for three
hours in order to dry then apply an extra layer if needed.
Figure 3.7 Aluminum Oxide and Aluminum paint.
Figure 3.8 During the painting step.
19. Figure 3.9 Sample after applying the first layer of coating.
3.2.2 Zinc coating:
Zinc spray provide …….
The following is the procedure for Zinc coating:
1. Shake the can well before using.
2. Spray evenly on the samples about 20 cm distance from the
surface.
3. Put the coated sample in a place to be exposed to air for three
hours in order to dry.
4. Repeat the second step until the desired thickness is obtained.
20. Figure 3.11 The samples after zinc coating.
Figure 3.10 Zinc spray and the samples before coating.
3.2.3 Underbody Rubber coating:
This type of coating is………………………..
The following is the procedure for underbody rubber coating:
1. Shake the can well before using.
2. Spray evenly on the samples about 20 cm distance from the
surface.
3. Put the coated sample in a place to be exposed to air for three
hours in order to dry.
4. Repeat the second step until the desired thickness is obtained.
Figure 3.12 Underbody Rubber Spray.
21. Figure 3.13 Samples after rubber coating.
3.3 Heat Treatment.
Heat treatment is …………………………
3.3.1 Annealing.
Metallographic and hardness test piece samples to 470 °C,
soaking them at this temperature for 2 hours and then furnace
cooled.(paraphrase this paragraph)
3.3.2 Precipitation hardening.
Metallographic and hardness test piece samples at a temperature
of 465 °C for 2 hours followed by rapid quenching in cold
water. These quenched samples were then subjected to a
precipitation hardening treatment (age hardening) by heating
them to 120 °C, holding them at this temperature for 3 hours
and then followed by air cooling to room temperature. As shown
in figures below. (paraphrase this paragraph).
3.4 Hardness Test.
Using Rockwell hardness test which is …………………..
The working principle of this device as following:
1. Select the proper indenter depending on the type of the alloy
to be measured, for Aluminum Alloy 1/8 ball is used.
2. Turn the device on.
3. Place the sample to be measured on top of the anvil.
22. 4. Rotate the anvil adjustment clock wise in order to rise the
anvil till it touch the surface of the sample.
5. The reading will appear on the screen, write it down and
repeat the steps using different coating samples.
Figure 3.15 Indenter used for testing.
Figure 3.14 Rockwell hardness tester.
3.5 Roughness Measurements.
Roughness is ……
The following are steps to measure the roughness of the
samples:
1. This device is connected to the computer software, first turn
on the computer.
2. Place the sample to be measured as shown on Figure, notice
the movement of the tip on the surface of the sample for about 5
23. seconds.
3. The surface roughness measurements will show on the
computer screen.
4. Repeat the steps using different coating samples.
Figure 3.17 During roughness measurement for zinc sample.
Figure 3.16 Roughness device (Mitutoyo) connected to
computer software.
3.6 Corrosion Test in sea water.
Sea water ……………………
The samples with and without coating were immersed in sea
water for 8 days and the weight was measured.
24. 3.7 Corrosion Test in Hydrochloric Acid (HCl).
In this step, a solution of 100ml of HCl and 900ml of H2O was
prepared and the samples with and without coating were treated
with the solution for 10 minutes and the weight of the sample
before and after the test were measured in order to monitor the
weight loss.
Figure 3.18 Apparatus used.
Figure 3.19 HCl solution.
25. Figure 3.20 Sample initial weight.
Figure 3.21 Sample weight after sea water test.
Figure 3.22 Sample weight after HCl test.
27. 4.1 Hardness Test (before and after heat treatment).
Type of Coating
Reading (g)
Aluminum Oxide (AlO2)
129.6
Zinc
130
Underbody Rubber
129.8
Without coating
129.5
Table 4.1 Hardness readings before heat treatment.
Type of Coating
Reading (g)
Aluminum Oxide
132.1
Zinc
139.8
Underbody Rubber
135.2
Without coating
129.6
Table 4.2 Hardness readings after heat treatment.
Figure 4.1 Hardness Readings Before Heat Treatment.
28. Figure 4.2 Hardness Readings After Heat Treatment.
As a result, the hardness after heat treatment increase……….
Observed that zinc has highest hardness value…….
4.2 Roughness measurements.
Type of coating
Rz (µm)
Rq (µm)
Zinc
7.06
1.32
Aluminum Oxide
8.44
2.70
Underbody Rubber
11.18
1.44
Without coating
1.81
0.35
Figure 4.1 Zinc Sample Roughness Profile.
Figure 4.2 Underbody Rubber Sample Roughness Profile.
Figure 4.3 Aluminum Oxide Sample Roughness Profile.
29. Figure 4.4 Without Coating Sample Roughness Profile.
4.3 Weight loss.
This step involves two parts, sea water for 8 days followed by
hydrochloric solution for about 5 minutes. The following table
shows the weight loss of each coating type.
Type of Coating
Initial weight (g)
Weight after the test (g)
Weight loss
(g)
Zinc
17.531
17.529
2 x 10-3
Aluminum Oxide
17.451
31. CHAPTER 7 CONCLUSIONS
Present the conclusions based on the results
CHAPTER 8 RECOMMENDATIONS/FUTURE WORK
Give suggestions for future work based on conclusions
REFERENCE
1. Aircraft Material, 2015. [Online]. Available from:
https://image.slidesharecdn.com/presentation-
thehistoryofaircraft-151221144928/95/presentation-the-history-
of-aircraft-20-638.jpg?cb=1450709452 [Accessed: 6 December
2018].
2. Dursun, T. & Soutis, C., 2014. Recent developments in
advanced aircraft aluminum alloys, Materials and design, 18(2),
pp.23-29.
3. Isadare, A., Aremo, B., Adeoye, M., Olawale, O. & Shittu,
M., 2012. Effect of heat treatment on some mechanical
properties of 7075 aluminium alloy. Materials Research, 16(1),
pp.190-194.
4. Kavalco, P., Lauralice, C.& Totten, G., 2009. Quenching of
aluminum alloys: cooling rate, strength, and inter-granular
corrosion‖, Heat treating progress, 11(2), pp.44-52.
5. Pitting Corrosion on aircraft engine crankshaft, 2017.
[Online]. Available from:
32. https://publicapps.caa.co.uk/docs/33/CAP1570_Corrosion.jpg.
[Accessed: 8 December 2018].
6. Publicapps.caa.co.uk, 2017. Corrosion and Inspection of
General Aviation Aircraft. [Online] Available at:
https://publicapps.caa.co.uk/docs/33/CAP1570_Corrosion.pdf
[Accessed: 8 December 2018].
7. Rambabu, P., Prasad, E. & Wanhill, S., 2017.Aluminium
Alloys for Aerospace Applications‖, Aerospace Materials, and
Material Technologies, Indian Institute of Metals Series, 14(1),
pp.12-16.
8. Salman, J., Alsada, S. & Al-Sultani, K., 2013. Improvement
Properties of 7075-T6 Aluminum Alloy by Quenching in 30%
Polyethylene Glycol and Addition 0.1%B‖, Research Journal of
Material Sciences, 15(4), pp.32-42.
9. Dursun, T. and Soutis, C., 2014. Recent developments in
advanced aircraft aluminium alloys. Materials & Design (1980-
2015), 56, pp.862-871
10. Crawford, B.R., Loader, C., Liu, Q., Harrison, T.J. and
Sharp, P.K., 2014. Can pitting corrosion change the location of
fatigue failures in aircraft?. International Journal of Fatigue, 61,
pp.304-314.
11. Wanhill, R.J.H., Molent, L., Barter, S.A. and Amsterdam,
E., 2015. Milestone case histories in aircraft structural integrity.
12. Crawford, B.R., Loader, C., Liu, Q., Harrison, T.J. and
Sharp, P.K., 2014. Can pitting corrosion change the location of
fatigue failures in aircraft?. International Journal of Fatigue, 61,
pp.304-314.
13. Demo, J., Steiner, A., Friedersdorf, F. and Putic, M., 2010,
March. Development of a wireless miniaturized smart sensor
network for aircraft corrosion monitoring. In 2010 IEEE
Aerospace Conference (pp. 1-9). IEEE.
14.
APPENDIX I
33. Use extra appendixes or sections as per your requirements, the
appendix may contain data, formula sheet, programmes, and
extra diagrams which is required for the work and etc. as
applicable for the work.
TURNITIN REPORT
Provide the first page of the Turnitin report
34. TECHNICAL PROJECT PROPOSAL
Provide the revised / approved TP proposal
Hardness Readings Before Heat Treatment.
Reading (g) Aluminum Oxide Zinc Underbody Rubber
Without coating 132.1 139.80000000000001
135.19999999999999 129.6
Hardness Test After Heat Treatment
Reading (g) Aluminum Oxide Zinc Underbody Rubber
Without coating 132.1 139.80000000000001
135.19999999999999 129.6
RProfile
5.0000000000000001E-4 1E-3 1.5E-3 2E-3
2.5000000000000001E-3 3.0000000000000001E-3
3.5000000000000001E-3 4.0000000000000001E-3
