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All Journal Jurnal Teknologi Kedirgantaraan (JTK) Bubungan Tinggi: Jurnal Pengabdian Masyarakat Jurnal ComunitA Servizio Jurnal Mahasiswa Dirgantara Jurnal TNI Angkatan Udara Jurnal Bakti Dirgantara

muftiarifin

Universitas Dirgantara Marsekal Suryadarma

Author-ID : 2058744

Aerospace Engineering Humanities Control & Systems Engineering Earth & Planetary Sciences Electrical & Electronics Engineering Engineering Environmental Science Library & Information Science Materials Science & Nanotechnology Mechanical Engineering Nursing Social Sciences Transportation Other

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Analisis Linear Statik Pada Vertical Tail dengan Variasi Defleksi Rudder Rabeta, Bismil; Arifin, Mufti; Fairuza, Syarifah
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 2, No 2 (2017): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Desain ekor vertikal pada pesawat sangat beragam bentuknya, bergantung pada karakteristik dan fungsinya. Pada ekor vertikal tersambung rudder yang merupakan control surface pada sumbu vertikal dengan gerakan menggeleng (yaw). Penulisan tugas akhir ini bertujuan untuk menganalisa beban aerodinamis pada ekor vertikal dengan defleksi rudder yang berbeda. Material yang digunakan pada pemodelan adalah aluminium alloy 7075-T6, merupakan paduan dari zinc dan copper. Pemodelan ekor vertikal dan analisa perhitungan dilakukan menggunakan pendekatan elemen hingga dengan bantuan software solidworks 2016. Dengan menggunakan menu flow simulation dan simulation pada solidworks, dapat diketahui output berupa stress, strain, displacement, dan safety factor. Dari hasil yang didapat distribusi stress dan strain memiliki nilai maksimal pada daerah hinge dan nilai minimal terjadi pada root leading edge dari ekor vertikal. Nilai stress maksimal pada pemodelan semakin meningkat seiring bertambah besarnya defleksi rudder yang diberikan, tetapi tidak melebihi yield strength dari material yang digunakan.

ESTIMASI DISTRIBUSI BERAT SAYAP DAN DISTRIBUSI LIFT UNTUK OPTIMASI BENDING MOMENT DENGAN SISTEM FUEL TRANSFER PADA PESAWAT BOEING 737-500 Arifin, Mufti; Yuniarti, Endah; Sari, Rafika Arum; Said, Ahmad Akmal
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Aside from being a manufacturer of lift force, a wing is functioning hold the load that occurs in the structure of the aircraft, such as the shear load, twist and bending. Of all the load the load bending is the greatest burden are received by the wings. Setting the load bending is one of the major factors in reducing the burden experienced by the wing. However, the optimal value indicated opposite between on land and in the air, to take advantage of the situation to use fuel system transfers the load alleviation. Fuel transfer load alleviation is a system that automatically move the fuel more in the tank at the time in part on land and are on the outside of the tank at the time in the air so that the effect of the load bending bending loads can be reduced, which generated as the result of addition between the weight distribution and the distribution of lift that occurs on the wings so as to calculate the bending data needed weight distribution and the distribution of lift on the wing. This research aims to know the weight distribution occurs on the wings of the Boeing 737-500. The value of the weight distribution and distribution of lift yield optimization moment on two States namely, on land and in the air with three variations of the fuel transfer that is, constant with a value of 40134.53 N, linear with a value of 48059.53 N, and the maximum value of 172386.50 N.

ANALISIS KINERJA PEMELIHARAAN BERDASARKAN SAFETY PERFORMANCE INDICATOR MENGGUNAKAN REALIBILITY MAPPING Arifin, Mufti
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 5, No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

ICAO Annex 19 tentang Safety Management mensyaratkan pengukuran safety menggunakan Safety Performance Indicator (SPI). Parameter SPI ditetapkan oleh operator. Salah satu contoh adalah parameter maintenance (pemeliharaan) yang terkait accident atau incident. SPI maintenance terdiri dari Pilot Report, Dispatch Reliability, Deferred Maintenance (DMI), Service Difficulty Report, Air Turn Back, Rejected Take Off, dan Repeated Defect. Beberapa parameter SPI memiliki korelasi satu sama lain. Simulasi telah dilakukan menggunakan reliability mapping dengan berbagai skenario pemeliharaan untuk melihat hubungan antara parameter Deferred Maintenance Item, Repeated Defect, dan Technical Interruption yang digunakan pada perhitungan Dispatch Reliability. Analisis kinerja pemeliharaan juga disimulasikan dengan metode ini. Hasil simulasi memperlihatkan hubungan sebab akibat dua arah dan satu arah diantara ketiga parameter SPI. Kinerja pemeliharaan dapat diperkirakan dari reliability mapping terutama waktu yang diperlukan untuk penyelesaian defect dan kejadian berulang baik defect, DMI, atau technical interruption.

Rancang Bangun Perangkat Lunak Database Dent and Buckle Chart Pada Pesawat Boeing 737-800 fahmins; muftiarifin; endahyuniarti
Jurnal Teknologi Kedirgantaraan Vol 6 No 1 (2021): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Pemeliharaan pada pesawat terbang harus tercatat rapi dan lengkap menurut CASR Part 145, dimana salah satu pencatatan pemeliharaan yaitu catatan pada setiap komponen yang mengalami kerusakan dan perbaikan. Semua dicatat berdasarkan lokasi komponen, tanggal ditemukan dan dokumen yang berkaitan dengan kerusakan dan perbaikan tersebut. Contoh catatan pemeliharaan adalah dent and buckle chart (DBC). Dent and buckle chart yaitu catatan kerusakan dan perbaikan yang telah dilakukan pada struktur pesawat terbang. Fungsi dari DBC ini yaitu untuk memudahkan dalam pencarian riwayat kerusakan dan perbaikan pada pesawat terbang. Penelitian ini berupa rancang bangun perangkat lunak database DBC, tujuannya memudahkan pencatatan DBC, dan penggunaannya dapat diakses di semua device seperti PC (Personal Computer) dan smartphone. Perangkat lunak ini berupa website yang diberi nama “Sysdnb” dan telah dibuat untuk mencatat kerusakan dan perbaikan yang ada pada pesawat tipe B737-800. Metode yang digunakan dalam penelitian ini adalah pertama mengumpulkan data catatan perbaikan dan kerusakan B737-800, kemudian membuat Sysdnb dan input data catatan ke database. Setelah selesai membuat Sysdnb dan data sudah ter-input adalah trial Sysdnb. Hasil trial menunjukkan pencatatan kerusakan dan perbaikan pada pesawat B737-800. Sysdnb ini berhasil dibuat untuk memudahkan personil lapangan dalam melakukan pencarian riwayat kerusakan dan perbaikan pada pesawat B737-800 dan keterbatasan dari sysdnb ini yaitu tetap harus membuka dokumen SRM secara manual. Abstract - Maintenance on an aircraft must be neatly and completely recorded according to CASR Part 145, where one of the maintenance records is a record of each component that is damaged and repaired. All are recorded based on the location of the component, date found and documents relating to the damage and repair. Examples of maintenance records are the dent and buckle chart (DBC). Dent and buckle chart is a record of damage and repairs that have been made to aircraft structures. The function of this DBC is to facilitate the search for a history of damage and repairs to aircraft. This research is in the form of DBC database software design, its purpose is to make it easier to record DBC, and its use can be accessed on all devices such as PCs (Personal Computers) and smartphones. This software is in the form of a website called "Sysdnb" and has been made to record the damage and repairs that exist on the type B737-800 aircraft. The method used in this study is to first collect the B737-800 repair and damage log data, then create a Sysdnb and input the log data to the database. After completing Sysdnb and the data has been input is a trial Sysdnb. The trial results show the recording of damage and repairs on the B737-800 aircraft. This system was successfully created to facilitate field personnel in searching for a history of damage and repairs on the B737-800 aircraft and the limitation of this system is that it still has to open SRM documents manually.

Estimasi Gaya Dorong Dari Motor Brushless Dengan Variasi Propeller Untuk Pesawat Model X-UAV Mini Talon Dengan Menggunakan Pengukur Massa Ananda Rafi Rijalul Awwal; Mufti Arifin; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 5 No 2 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

One that affects aircraft performance is the thrust. The thrust is determined according to the requirements of the aircraft itself. This study uses a thrust test stand that uses a mass gauge as a thrust gauge, using two brushless motors and five propellers to determine the optimal thrust for X-UAV Mini Talon aircraft flying missions. The thrust required by the X-UAV Mini Talon aircraft - is known to be 0.6755 N for cruise flights and 4.979 N for take-off aircraft. After testing, the smallest thrust is produced by the configuration of the DYS 2826-13 brushless motor with a 5x3 inch propeller, while the biggest thrust by the RacerStar BR2212 brushless motor with a 10x6 inch propeller. Compared to calculations with propeller static thrust equation, the difference in thrust in testing with propeller static thrust ranges from 15% to 25%. Therefore, the optimal configuration for flying cruising is the DYS 2826-13 brushless motor with a 5x3 inch propeller, which produces a thrust of 0.988 N. Then, for the optimal configuration take-off is the Brushless DYS 2826-13 with a 9x5 inch propeller, which results in a thrust of 6,151. The configuration above was chosen because it is more efficient, with smaller current requirements compared to other configurations with more or less equivalent thrust.

Simulasi Pendistribusian Spare Part Oxygen Crew Pesawat Airbus Milik Maskapai X Di Bandara Pattimura Ambon Israq Mifan Junaidi; Mufti Arifin; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 6 No 2 (2021): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Berdasarkan observasi lapangan, ditemukan adanya indikasi kebocoran oxygen crew pada saat pesawat terbang dari Bandara Soekarno Hatta menuju Bandara Pattimura Ambon. Sesuai dengan FCOM (Flight Crew Operating Manual) untuk pesawat airbus jika ada 2 crew dalam cockpit maka minimum tekanan oksigen darurat untuk flight crew adalah 540 PSI. Sehubungan dengan itu, maka diperlukan analisis pengaruh distribusi spare part oxygen crew pesawat airbus milik maskapai X di Bandara Patimura, dengan tujuan untuk mengetahui pendistribusian komponen pada setiap station yang saling berhubungan, mengetahui pengaruh ketersediaan spare part oxygen crew bagi pesawat yang akan beroperasi, dan mengetahui lokasi penyimpanan dan kebutuhan spare part. Penelitian ini menggunakan metode riset operasi yang terdiri dari metode VAM (Vogel Approximation Methode), metode inspeksi (Least Cost) dan metode NWC (North West Corner). Setelah dilakukan perhitungan menggunakan 3 metode tersebut, diperoleh metode yang tepat untuk proses pendistribusian spare part oxygen crew adalah metode VAM (Vogel Approximation Methode) dengan biaya US$ 141 untuk memenuhi seluruh kebutuhan station.

Analisis Kerusakan Trim Air Pressure Regulating and Shutoff Valve Pada Pesawat Boeing 737-800 Menggunakan Metode Failure Mode and Effect Analysis (FMEA) Rizwan Maulana; Freddy Franciscus; Mufti Arifin
Jurnal Teknologi Kedirgantaraan Vol 7 No 1 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i1.48

Air Conditioning (AC) is the one of system in aircraft to make a passanger and all cabin crew comfortable. Trim Air Pressure Regulating and Shutoff Valve or also known as Trim Air PRSOV is a component on the Boeing 737-800 aircraft to regulate flow of hot air constantly before entering the aircraft cabin. Refering to the data for the last 6 years, the replacement of the component belonging to one of the Indonesian national flight carrier using Boeing 737-800 aircraft was the occurance of 84 times the cooling system failure which caused the light indiacator in the cockpit to light up. Among them happened 70 times unscheduled maintenance and 14 times scheduled maintenance. Thus, this essay was made to analyze the causes of the damage that occurred to the Trim Air PRSOV. The method used in this research is Failure Mode and Effect Analysis (FMEA) is the technique used to find, identify and eliminate failures or damage to a system or process. The first step is to analyze using a Pareto diagram and then continue with the FMEA method so that an analysis of the damage that often occurs is damage to the diaphragm with 42% damage with an RPN value of 389.1, erosion on the ring seal with 22% damage with an RPN value of 376 and shaft seal damaged with 12% damage with an RPN value of 295.1 for it requires aggressive treatment. Therefore, repairs with a long TAT of 14 days are expected to increase the reliability of the PRSOV Trim Pressure component. For this reason, repairs are carried out with a long TAT of 14 days, it is hoped that there will be an increase in the reliability of the PRSOV Trim Pressure componen.

PENGUKURAN TINGKAT KEBISINGAN PESAWAT CASA 212-200 SAAT GROUND RUN TEST BERDASARKAN VARIASI SUDUT Adam Wahyu Saputra Adam; Mufti Arifin; Ericko Chandra Utama
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.70

Noise is an unwanted sound, including sound that as a result of side effects from activities such as industrial and transportation activities. The greatest intensity of noise in the aircraft maintenance hangar environment is produced by the operation of the aircraft engine when it is ground or what is often called the Aircraft Ground Run Test. An This study was conducted by taking samples using CASA 212-200 aircraft equipped with a turboprop engine type. The measurement of noise generated by aircraft activity is measured using a tool such as the AS804 Sound Level Meter. This study aims to determine the intensity of aircraft noise when conducting a ground run test which is measured based on variations in the angle of measurement location to the source with a distance of 30 m based on an angular reference of 0o in front of the aircraft nose and 180o is behind the aircraft with a clockwise rotation. The measurement of noise levels is based on three references, namely LAmax, LAmin and LAeq. At idle the variation in the direction of the noise receiver which has the potential to produce the largest LAmax value at an angle (30o) of 97 dB. The lowest LAmin at an angle (180o) and (210o) of 84.6 dB. The largest LAeq at an angle (330o) of 95.3 dB. At the time of max power the variation in the direction of the noise receiver which has the largest potential LAmax value at an angle (45o) of 99.1 dB, the lowest LAmin at an angle (135o) of 94.8 dB. The highest LAeq at an angle (45o) of 97.8 dB.

Rancang Bangun Alat Peraga Up Lock Box Pada Nose Landing Gear Pesawat ATR 72 Untuk Media Pembelajaran Septian, Diaz; Arifin, Mufti; Yuniarti, Endah
Jurnal Teknologi Kedirgantaraan Vol 7 No 2 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i2.54

Abstract - Airplane is a very important mode of transportation, one of which is ATR aircraft. In this study, the type of aircraft used was the ATR 72-600 aircraft. One of the safety factors that need to be considered on aircraft is the landing gear system. The landing gear system regulates the wheel system on the aircraft for landing and also taking off. Given the importance of ensuring that the plane's wheels are securely locked or not, an up lock box system is needed on the landing gear. In the Up Lock Box system, it is not directly visible from the outside so that the working mechanism is not widely known. This study aims to determine the workings of the up lock box nose teaching aid system on the landing gear and to make a trial up lock box nose teaching aid on the landing gear. The research method begins with a literature study, then looks for design references, namely from the ATA 32 training manual. After that, make a design using the image of the up lock box from the ATR 72 aircraft, assemble the demonstran tool, calibrate and test the demonstran tool. The conclusions in this study are, how the up lock box teaching aids work in accordance with the up lock box working concept in the training manual, the results of the design and manufacture of props accompanied by modifications, as well as the test results on up lock box props in accordance with the up lock work concept box. The size of the props that have been made has a length of 37.8 cm and a width of 16.2 cm.

Analisis Angkutan Kargo Antara ATR 72-600 Passenger, ATR 72-600 Freighter Dan ATR 72-600 Converted Pada Rute Makassar – Kendari Somadi, Ridho Misbahudin; Arifin, Mufti; Yuniarti, Endah
Jurnal Teknologi Kedirgantaraan Vol 7 No 2 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i2.57

Delivery of goods (cargo) between islands or between countries is faster by air transportation. Air cargo can use passenger aircraft (bulk cargo), Air freighters, Combined air freighters, Converted freighters for the same type of aircraft, such as ATR 72-600. This study discusses fuel consumption, comparison of payload capacity, and comparison of fuel consumption per payload of ATR 72-600 aircraft for the Makassar – Kendari route. namely the ATR 72-600, ATR 72-600 Freighter and ATR 72-600 Converted aircraft. The method used is a quantitative method. The results of the calculation using the flight crew operation manual for ATR 72-600 passenger fuel carried 1.143,4 kg and fuel consumption of 609.4 kg, ATR 72-600 Freighter and Converted aircraft carried 1.210,3 kg of fuel and 613,3 fuel consumption, 4 kg. Fuel costs per kg of cargo, ATR 72-600 Passenger aircraft are more expensive, namely Rp. 1,279 per kg, freighter Rp. 1,136 per kg, converted bulk cargo Rp. 1,175 per kg, Converted Large cargo door Rp. 1,202 per kg. The largest Cargo capacity is 9,000 kg on ATR 72-600 Freighter aircraft and the smallest is 2,150 on ATR 72-600 Passenger aircraft. If cargo delivery does not exceed 2,150 kg, it is more profitable to use ATR 72-600 passenger aircraft, but if the weight or volume sent much larger should use the ATR 72-600 Freighter.

Co-Authors AA Sudharmawan, AA Adam Wahyu Saputra Adam Ade Julizar Ade Julizar Adri, Raiztama Afid Nurul Anwar Afifah, Atik Ahmad Akmal Said Ahmad Al Muhraj Ahmad Buana Syamra Pratama Rahman Al Farabi, Awfa Azka Alimin, Edy Karyadi amat chaeroni Ananda Rafi Rijalul Awwal Aprila Sakti K Arindho Andrifa Faturrohman Ayu Martina Bayu Wicaksono Belnov, Syaddad Husaini Borris Y Maningka Budi Aji Warsiyanto Chintya Rahmawati Cynthia Rahmawati Daniel Frederick Romulus Ginting Dwiki Fahreza Andreanto Endah Yuniarti, Endah Erna Shevilia Erna Shevilia Agustian Evi Endarti Fadli Hidirsyah fahmins Fairuza, Syarifah Fara Vania Utami FORTUNE JR OMBUH Freddy, Franciscus Gunawan, Gia Aviani Hardanny, Danny Husaini, Fahdli Zulfikar Imron Rosadi Israq Mifan Junaidi K, Aprilia Sakti Kanda Anantariyanto Alam Tasti Madjid, Aldien Galistia Maharani Miranda Saputra Muchammad Furqon Muchaddats Muhamad Jayadi Muhammad Hadi Widanto Muhammad Umar Abdulloh NUR HIDAYAH NINGSIH, Nur Hidayah Ningsih Paramaharta, Izhar Rabeta, Bismil Rafika Arum Sari Raihan Maulana Yahya Reynaldo Mulya Tedja Riskha Agustianingsih Rizwan Maulana Rosalie, Rhea Anggun Said, Ahmad Akmal Saiful Latif, Saiful Sari, Rafika Arum sausan, Misk Sausan Ghina Septian, Diaz Shevillia Agustian, Erna Simon Sindhu H Sofyan, Mohamad Fauzan Somadi, Ridho Misbahudin surya wijaya, Andi Suwardi, Arie Prasetya Syaiful Rifki T. Dikatama Utama, Ericko Chandra venza, Venza Fawwaz Tsulatsa Victory Rumagit, Jodia Vita Kartika Wicaksono , Paulus Hilman

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