About Me



My name is Muhammad Bagus Rizqi Perdana, I was born on 10th October 1995 in Sidoarjo, East Java Indonesia. I am currently a 2nd year Aerospace Technology(B.Eng) student at Coventry University. I have always been interested in physics and natural science during my high school time in Indonesia, this has brought me to choose an engineering course for my further study. I have interest in Music and Automotive, I have been playing and practicing guitar for 10 years. My hobby in automotive does not just limited to the product but also I have been practicing maintenance on automotive product. I took Aerospace Technology course because I would like to develop the aerospace industry in my country which is currently not making a big progress. I believe by having experience of studying in the UK and have an insight of the aerospace industry in this country, I could be a pioneer in Indonesia to expand the aerospace industry.






Aircraft System Lab: Depth Maintenance

Compressor Blade

This is the second part of the Harrier Jumpjet lab series which is the depth maintenance. Depth maintenance is one of the maintenance process which taken place off-aircraft and take a longer time than a daily maintenance. During the fault diagnosis I found out that damaged compressor blade is a possible cause for compressor surge. In this depth maintenance activity, my group were given three damaged compressor blade and we have been given a full authority and responsibility to do anything with the blades to complete the activity . The task was to find out which of the compressor blades are repairable or need to be replaced. We identified each blade by noting their production code.

1st Blade : NR 1424 UN

2nd Blade : NR 1513 VS

3rd Blade : QB 3734 VQ

Within the metrology lab, shadowgraph is a very useful tool to detect damage along the blade edge but there will be not enough time to finish the activity if we have to do a detailed check with shadowgraph for each blades. My team decided to do a visual check for each blades to see which of these blades are not repairable. There is a critical rule for a compressor blades, if there any damage within 30% length of the compressor blade from the root it is considered as not repairable. With the help of ruler, we measure each blade length and try to locate any damage along the blade’s edge. The result of our finding can be seen below:

1st Blade

Length : 20 cm

Visible damage at : 2 cm (10 %)

2nd Blade

Length : 16 cm

No visible damage along its 30 % length from the root

3rd Blade

Length : 20 cm

Visible damage at : 2.4 cm (12%) and 5.6 cm (28%)

Shadowgraph or also known as profile projector

Based on this result and in regards to the 30% length principle of compressor blades, my team decided that the 1st Blade and 3rd Blade are not repairable and must be replaced. For the 2nd blade we used shadowgraph to have a detailed view along the blade’s edges(leading and trailing edge).  A detailed view is needed to note any damage along its edges and to be reported for the repair process. Our finding on the 2nd blade with the shadowgraph can be found below.



From the shadowgraph result I found out that the 2nd blade is also not repairable because there is damage within 30 % of its length on the trailing edge. The damage was not visible when we do the initial check but we could see it clearly with the shadowgraph. We tried to improve the result by using the form tracer to check along the blade skin but we realized that this method is not effective because the shape of the blades itself is not completely flat and to be kept in mind that formtracer remove 10 microns thick of material from the blades. Within several repeated usage it could affect the surface smoothness of the blade and will also contribute to disrupt the airflow along the blade.

Formtracer result

Reflection :

This activity introduces me to the depth maintenance process in aerospace industry by giving a hands-on experience on the depth maintenance and also a full authority and responsibility. During this activity I had a chance to apply my knowledge and logical decision-making in order to complete the task. We were not given any procedure and have to complete the task based on our knowledge. Without any knowledge and experience about metrology I will not be able to know which tool should be used to complete this task, however I had a chance to learn about the metrology lab during the first semester. I have also developed my critical and logical thinking during this activity. If my team did not decide to have an initial check and try to examine all the blade with the shadowgraph, I believe we will not be able to complete the task within 2 hours. From this activity I also learned how to use a shadowgraph to have a detailed view of an object along its edges. Shadowgraph is a very useful tool to improve the result of a depth maintenance. For example, I was not able to find any visible damage along the 2nd blade’s edges but with the shadowgraph I can easily spot the dent.

As this is a group activity I am developing my teamworking and communication skills during the depth maintenance. It is very essential to be able to work efficiently with my team in order to have a satisfying result within the given time. With a good communication skill we will work more effectively. My team could complete the task without any serious problem because we have a very good teamwork, none of us acted as a weaklink to the team.

If i were to undertake this activity again I would like to improve my finding on the compressor blade with a NDT test. Using a Dye penetrant inpection technique I could check for any crack along the blade’s body which are not visible to the naked eye. I would also like to have more information related to the damage tolerance, because along the edges i found there are damages with different depth and width it would be really helpful to know the tolerance for these dents and would improve our decision and conclusion.

I am very satisfied with the way Coventry university giving a chance for every students to have a hands-on experience to some of the important maintenance process The critical thinking and the experience I have acquired during this activity will help me toward my further study on the coming year and also my future career.


Depth Maintenance Laboratory Worksheet

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Aircraft Systems Lab: Fault Diagnosis


The first activity within the harrier jump jet lab series is the fault diagnosis. My group was assigned to examine the engine of the aircraft given the report from pilot that compressor surge occasionally happens during the last flight. Compressor surge is a condition where the engine is rumbling because of the air flow within the compressor was being pushed back towards the inlet of the engine. I will write further about this phenomena in this article.

Before the activity starts, we were given a mini lecture about aircraft engine and we have some trivia or quiz to challenge our knowledge on this area. I found out that the handout for the aircraft engine topic has been released several days before the activity and I took my chance to read through the handout a day prior the activity. This has helped me to be on advantage during the activity and I was capable to answer most of the trivia.

The mini lecture was very helpful towards completing the activity, we were given knowledge of how air flowing throughout the engine according to the engine cycle or as known as “suck squeeze bang blow”. The thing I learned is that an axial compressor stages are composed of stator and rotor. The rotor is connected to the engine shaft which is supplying energy from turbine in order to rotate the compressor blade. The Stator is not connected to the shaft, hence is not rotating. Throughout each stage, air is  altered with different angles of the stator and rotor working in concept of convergent and divergent to vary its pressure and velocity in regards to the Bernoulli’s principle on fluid dynamics. In regards to the theory, the flow must be as smooth as possible to keep the pressure varying process on its optimum state. This is why the laminar flow is favoured throughout these stages because the flow is more predictable compared to the turbulent flow in order to define the angle for each compressor blade.

Compressor Surge

Compressor surge is a breakdown of flow in a turbine engine. The video above has a comprehensive explanation of compressor surge phenomenon and how the flight crews should react to it. The compressor surge is noticeable from lost of thrust, vibration and yaw depending on how severe it is. The most noticeable effect will be at low altitude and high power setting, hence compressor surge can be dangerous during take-off. There are a couple of factors that could cause compressor surge such as bird ingestion, pneumatic bleed malfunctions and internal engine failures. I would recommend to watch the video in order to see how the compressor surge could affect the engine.

Fault Diagnosis

According to the report from the pilot, the compressor surge happens occasionally and recoverable during flight, this leads to a conclusion that bird ingestion and pneumatic bleed malfunction is not the causing factor here. The compressor surge is also known as compressor stall as it can be caused by disruption to the airflow within the compressor. The remaining possible cause is a damaged compressor blade disrupting the laminar flow within the compressor and resulting a push back of air flow towards the front of the engine.  The compressor section of a turbofan engine consists of low pressure and high pressure compressor. The low pressure is located closer to the front of the engine and high pressure compressor is closer to the combustion chamber. In the Harrier Jump Jet, the low pressure compressor is accessible from the front part of the engine while the high pressure compressor is not accessible.


If the fault is within the low pressure compressor, the maintenance crew can remove the damaged blade without removing the whole engine and repair it if possible. The blade is serviceable if the damages are not within the 30% of the blade length starting from the root. The figure below is an illustration of damaged blade.

Damaged blade illustration (TPUB.com n.d. )

The 30% length of the compressor blade is a critical area where the blade is considered as not serviceable because of the centrifugal force acting on it during the compressor rotation can tear the blade apart along its damaged location. The figure below is an illustration of centrifugal force.

Centrifugal force illustration (CalcTool 2008)

The high pressure compressor is located closer towards the combustion chamber and not accessible on Harrier Jumpjet. The procedure to examine the high pressure compressor require a borescope which is a very small camera capable of taking picture and record video in a less accessible area.

The borescope controller was connected to an external monitor.

The aircraft has access for the borescope to reach the high pressure compressor through a small hole available for each high pressure compressor fan. This holes can be found by removing the forward thrust vector of the engine. The access holes can be seen on the figure below.


Access holes for the borescope to the high pressure compressor, notice the small yellow ring.

 If there any damage found within the high pressure compressor blade, the available option is to swap the whole engine with the spare engine and then the depth maintenance needs to take place. This is because the aircraft will not be operable for up to five days during the maintenance and through aviation industry view, an inoperable aircraft is a big loss. The engine swap only takes a whole day and the aircraft can continue its operation, hence this is considered as the most efficient option.

List of Hazards Involved in This Activity

List of Hazards -1

Examining Compressor Blades.

Before the compressor blade examination starts, we applied barrier cream to our hands in order to protect it from dangerous substances and then tool check need to be completed in the beginning to find out if there any missing tools within the toolbox. The tool check in the beginning is important to make sure that we have the same number of tools inside the toolbox after we have done with the activity. If there any difference between the check-out and check-in, it is possible that the tool is left behind somewhere within the aircraft and it is very dangerous for the aircraft.  I was the person doing the tool check before and after the activity. I found out that several tool checks before have not specified the missing tools, It is important to specify the missing tools during the tool check in order to inform the next people doing the tool check which tools are missing.

Tool check out and check in book.

Our team were divided into two groups for this activity, 2 persons working in front of the engine to examine the low pressure compressor and 2 others remove the forward thrust vector for the borescope. I was assigned to remove the forward thrust vector. To remove the forward thrust vector, there are two other panels need to be removed which can be seen below.

These two panels need to be removed to gain access to the forward thrust vector
After the two panels are removed, the thrust vector can be removed.

After the forward thrust vector removed, the borescope can be inserted to the four available holes for each compressor fan. To check each blade, the compressor was rotated manually from the panel on top of the engine. I took pictures of each blade with the borescope in order to investigate the damage on each blade.

The top panel of the engine to move the compressor manually


This activity gives me a hands on experience of aircraft maintenance process. It taught me on how to make decision based on the condition and what matters the most. Although it is a military aircraft, it has the same philosophy with a civil aircraft it should worth the amount of money your company invested to it. Having an inoperable aircraft for a couple of days is considered as losing your investment.

From this activity, I learnt how to use a borescope properly and how it should be used on an aircraft especially during maintenance. One thing that i think could be improved is the quality of the borescope, It appears that the picture taken by the borescope is not really clear and detail. It is possible to identify a major damage to the blade with the borescope but it is also possible to miss small dent on the blades. By having a good initial analysis on compressor blades I can come up with a better decision whether engine swap is necessary or not.

I also learned that preparing before any lab activities will give you a boost during the activity, although as simple as reading through the handout. With a comprehensive knowledge on the subject you will also get the most out of the activities. It also works on a real life work of maintenance, most of the times you have to make a decision for every action you need to take during the maintenance. In conclusion, a good theoretical knowledge will result in a better decision and you could save your company from losing money or even a fatal accident.


Fault Diagnosis Laboratory Worksheet

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CalcTool (2008) Centrifugal Force[online] available from <http://www.calctool.org/CALC/phys/newtonian/centrifugal&gt; [4th March 2016]

tpub.com (n.d.) COMPRESSOR ROTOR BLADES[online] available from <http://aviationmiscmanuals.tpub.com/TM-55-2840-251-23/css/TM55-2840-251-23_219.htm&gt; [4th March 2016]