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All Journal Jurnal Teknologi Kedirgantaraan (JTK) International Journal of Aviation Science and Engineering Prosiding Seminar Nasional Sains Teknologi dan Inovasi Indonesia (Senastindo) Jurnal Teknologi Industri Jurnal Mahasiswa Dirgantara Wahana Fisika : Jurnal Fisika dan Terapannya
K, Aprilia Sakti
Fakultas Teknologi Kedirgantaraan, Unsurya, Jakarta, Indonesia
Aerospace Engineering Astronomy Automotive Engineering Computer Science & IT Control & Systems Engineering Earth & Planetary Sciences Electrical & Electronics Engineering Energy Engineering Environmental Science Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Physics Transportation Other

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Rancang Bangun Alat Pencuci untuk Kompresor Mesin Arriel 1S1 pada Helikopter Sikorsky S-76 Di PT. XYZ Silalahi, Sanggam Tuani; Tri Susilo; Aprilia Sakti K
Jurnal Teknologi Kedirgantaraan Vol 2 No 1 (2017): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v2i1.201

Abstract

Sebagai perusahaan penyewaan helikopter, PT. XYZ diwajibkan melaksanakana positioning flight ke berbagai tempat/ bandar udara. Mayoritas konsumen PT. XYZ adalah perusahaan yang bergerak di bidang industri minyak bumi dan gas yang beroperasi di remote area. Dalam melaksanakan positioning flight ke remote area memerlukan waktu beberapa hari karena jarak yang jauh dan daya jelajah yang terbatas dari helikopter Sikorsky S-76 dan juga melewati atmosfir korosif. Pada panduan perawatan mesin Arriel 1S1, jika mesin beroperasi di kondisi atmosfir korosif diharuskan melaksanakan perawatan rinsing pada mesin setelah penerbangan terakhir pada hari tersebut. PT. XYZ harus mempersiapkan alat pencuci kompresor untuk mesin dibeberapa bandar udara tempat helikopter bermalam. Hal ini menyebabkan biaya tambahan untuk penyewaaan maupun pengiriman alat tersebut. Tujuan dirancangnya alat pencuci untuk kompresor mesin adalah: untuk mengurangi biaya tambahan penerbangan dari penyediaan alat tersebut. Hasil perhitungan: dibutuhkan tangki stainless steel 304 dengan ketebalan 1,5 mm, pipa flexible PVC dengan ketebalan 2,75 mm dan pompa torak diaphragm (memiliki kemampuan self-priming) dengan daya 60 watt (12 vdc, 5 A)   – As a air charter company, PT. XYZ required to carry out positioning flights to different places/ airports. The majority of PT. XYZ consumers are oil and gas company which operating in remote areas. Performing positioning flight to the remote areas take several days because of the distance, Sikorsky S-76 helicopter endurance and also passes the saline atmosphere. In the Arriel 1S1 engine maintenance manual, if the engine is operated in a saline atmosphere required to carry out engine rinsing  after the last flight of the day. PT. XYZ must prepare engine compressor washer in some airports where the helicopter remain overnight. This leads to additional costs for rent and delivery of the equipment. The purpose of designed engine compressor washer are: to reduce the additional costs from the provision of the equipment. The results of calculations: it needs stainless steel 304 tank with a thickness of 1.5 mm, flexible PVC pipe with a thickness of 2.75 mm and the piston diaphragm pump (has the ability to self-priming) with a power of 60 watts (12 vdc, 5 A)
Studi Thrust Reverser Illuminate Problem pada Pesawat Boeing 737 – NG dengan Menggunakan Metode Fault Tree Analysis Suwendi; Tri Susilo; Aprilia Sakti K
Jurnal Teknologi Kedirgantaraan Vol 2 No 1 (2017): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v2i1.203

Abstract

Thrust reverser adalah sistem pembalik gaya dorong, yang berfungsi pada proses pengereman saat pesawat terbang mendarat. Penelitian ini membahas mengenai Thrust Reverser Illuminate Problem pada Pesawat Boeing 737 – NG dengan sistem propulsinya berupa mesin jenis turbofan CFM 57 – 7 menggunakan Metode Fault Tree Analysis (FTA). Hasil analisa kualitatif dengan top event yaitu Thrust Reverser Illuminate Problem adalah top event terjadi jika kejadian Kerusakan Relay, Internal Damage sync shaft, sync shaft Tersumbat, Lightning Strike, Kerusakan Proximity Sensor, Wire Failure, Switch Fails Opened, Loose Part, Parts Failure, Defective O-ring Packings, Defective rings, Improper Matching of Slide and Sleeve, Excessive clearance between slide and sleeve, Foreign material in internal passage, Leakage, Defective Spring, , Not Rigged Correctly at Installation sync shaft, Switch terbuka secara tidak tepat terjadi. Penyebabnya bisa salah satu dari kejadian tersebut, sehingga perbaikan dapat dilakukan secara terstruktur pada komponen tersebut. Hasil analisis kuantitatif adalah probabilitas munculnya kejadian Thrust Reverser Illuminate Problem sebesar 0,019734.    
Studi Perhitungan Efektivitas Derate Thrust Engine CFM56-5B Pada Pesawat Airbus A320-200 Pandu Yugo Anggoro; Tri Susilo; Aprilia Sakti K
Jurnal Teknologi Kedirgantaraan Vol 2 No 2 (2017): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v2i2.209

Abstract

Penggunaan gaya dorong secara maksimal secara terus menerus dapat mempersingkat usia mesin pesawat dan juga tentunya akan menambah biaya perawatan pesawat tersebut. Sebuah metode untuk meng-optimalkan pemakaian mesin dengan membatasi kinerja mesin agar mesin tidak bekerja dengan tenaga maksimal dinamakan Derate Thrust. Penelitian ini membahas mengenai perhitungan efektivitas Derate Thrust pada saat  takeoff pada pesawat A320-200 dengan menggunakan engine CFM56-5B pada bulan Januari sampai Maret 2016. Metode yang digunakan dalam penelitian ini adalah metode perhitungan yang menggunakan rumus-rumus Derate Thrust yang dikeluarkan oleh pihak manufaktur engine yaitu CFM. Selanjutnya akan dilakukan perbandingan antara data aktual dengan perhitungan manual. Hasil dari perhitungan manual efektivitas Derate Thrust untuk PK-A1, PK-A2, dan PK-A3 selama bulan Januari sampai Maret 2016 tertinggi yaitu pada bulan Februari sebesar 25.559% dengan EGT 699 0C pada pesawat PK-A1. Berdasarkan hasil tersebut maka temperature berbanding terbalik dengan effektivitas Derate Thrust dan temperature merupakan faktor penting dalam pengoperasian Derate Thrust.   Service life of airplane engine will be shortened by operating maximum thrust at continuous operation and also maintenance cost become higher. A method to optimize engine operation by limiting the maximum thrust is applied during operation called Derate Thrust. This study discusses calculation of Derate Thrust effectiveness at landing operation of A320-200 with CFM56-5B engine during period January until March 2016. Calculation is based on Derate Thrust formulas provided by manufacturer, CFM. Then, comparison between actual data and calculation is shown. The results show the derate thrust effectiveness for PK-A1, PK-A2, and PK-A3 is higher on March with value of 25.559% and EGT 699 0C for PK-A1. Based on the results, temperature is inversely proportional to Derate Thrust effectiveness and temperature is a key factor during application of Derate Thrust.
Perancangan Duct Fan dan Analisa Aliran Pada Hovercraft Dast-13 Dengan Metode Computational Fluida Dynamics Tri Susilo; Aprilia Sakti K; Kartiko Wasis
Jurnal Teknologi Kedirgantaraan Vol 3 No 2 (2018): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v3i2.219

Abstract

Duct fan hovercraft berperan sebagai selubung penutup dari propeller dimana dengan adanya duct fan pusaran udara jadi lebih efisien dan duct fan sendiri dapat meningkatkan thrust maksimum dimana menjaga udara agar tetap di dalam dan keluar dengan thrust yang masimum, untuk memaksimalkan keadaan tersebut duct fan juga harus dibuat atau dirancang sedemikian rupa untuk mendapatkan hasil yang maksimal. Oleh sebab itu penulis membuat perancangan duct fan dalam dua bentuk pemodelan dimana pemodelan pertama berbentuk duct fan accelerating dan pemodelan kedua duct fan decelerating. Material yang digunakan pada pemodelan adalah carbon fiber. Pemodelan duct fan hovercraft dast-13 mengunakan software solidworks. Dengan mengunakan flow simulation, dari hasil simulation flow didapat nilai maksimal pada velocity (x), total pressure dan thrust maksimum pada duct fan decelerating. Dengan hasil  dapat di tersebut dapat di tentukan duct yang akan dipilih adalah duct fan decelerating dengan hasil maksimum pada hasil simulation flow.   The hovercraft fan duct acts as cover cloak from the propeller where the duct fan air velocity becomes more efficient and the duct fan itself can increase the maximum thrust which keeps the air in and out with a maximum thrust, to maximize the state of the duct fan must also be created or designed in such a way to get maximum results. The authors model is a duct fan accelerating and modeling of both duct fan decelerating. The material used in modeling is carbon fiber. Modeling duct fan hovercraft dast-13 using solidworks software. By using flow simulation, from the simulation flow result obtaine the maximum value on velocity (x), total pressure and maximum thrust on duct fan decelerating. With the result can be in the specified duct to be selected is duct fan decelerating with maximum results on the simulation flow results.
Perhitungan Spare Part HPSOV / PRSOV Pesawat Boeing 777 Dengan Metode Economic Order Quantity Herbert Triyogi; Mufti Arifiin; Aprilia Sakti K
Jurnal Teknologi Kedirgantaraan Vol 9 No 2 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i2.186

Abstract

An Indonesian airline, PT. XYZ, performs maintenance on its Boeing 777 aircraft equipped with General Electric GE90 engines at PT. GMF AeroAsia. The aircraft’s Engine Air Supply System utilizes a High Pressure Shutoff Valve (HPSOV) and a Pressure Regulating Shutoff Valve (PRSOV). Between 2019 and 2022, PT. XYZ's Boeing 777 fleet experienced 10 delays and 52 instances of HPSOV/PRSOV replacements due to valve sticking or seizing. This study aims to analyze the reliability of the HPSOV/PRSOV by calculating the Mean Time Between Failures (MTBF) and to optimize spare parts inventory management using the Economic Order Quantity (EOQ) method. The MTBF calculation yielded a value of 8,134.08 Flight Hours (FH). Additionally, the spare parts inventory analysis indicated that the most economical order quantity for each repair is 2 units, with a remaining inventory of 2 units. The total cost of the spare parts inventory is $3,033.66 USD. The findings of this study are expected to provide recommendations for PT. XYZ to improve spare parts inventory management and minimize the risk of delays in aircraft maintenance.    
Analisis Konsep Circular Airport Untuk Wilayah Kepulauan Indonesia Freddy Franciscus; Aprilia Sakti K
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.276

Abstract

The Circular Airport Concept, issued by Hessellink in 2014, attracted the attention and differed opinions of airport experts. Until now this project is still ongoing. This paper makes a preliminary analysis of the application of the concept of a circular airport in the Indonesian Archipelago. Building an airport in a limited area is a big challenge. Development of several pioneering routes that connect the regions with small aircraft continues to be done. Another challenge in airport construction is environmental sustainability. The circular airport concept is expected to be the right solution for the Indonesian Archipelago. Discussion included technical and safety analysis related to airport design, aircraft characteristics, Air Traffic Management [ATM} and also analysis of the environment and regional population to be developed.
Co-Authors AA Sudharmawan, AA Anggoro, Pandu Yugo Budiman, Miftha Hudin Freddy, Franciscus Harry Sudibyo Herbert Triyogi Kartiko Wasis M. Alvin Yulizar Mirino, Nathaniel Ericsson Mufti Arifiin muftiarifin Muhammad Suryanegara Pandu Yugo Anggoro Santoso Soekirno Santoso Soekirno Santoso Sukirno Silalahi, Sanggam Tuani Soekirno, Santoso Suwendi Tri Susilo Tri Susilo