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All Journal JURNAL INTEGRASI Jurnal Teknologi dan Riset Terapan (JATRA) Jurnal Pengabdian kepada Masyarakat Politeknik Negeri Batam
Lalu Giat Juangsa Putra
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Aerospace Engineering Computer Science & IT Economics, Econometrics & Finance Electrical & Electronics Engineering Engineering Mechanical Engineering Other

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Journal : JURNAL INTEGRASI

 1 
Metode Balancing Jig Procedure pada Tab Elevator Pesawat Boeing 737-800 untuk Mengurangi Dampak Flutter Lalu Giat Juangsa Putra; Dian Saputra; Achmad Zahir Saputra
JURNAL INTEGRASI Vol 10 No 2 (2018): Jurnal Integrasi - Oktober 2018
Publisher : Politeknik Negeri Batam

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30871/ji.v10i2.845

Abstract

Primary flight control in aircraft consist of aileron, rudder and elevator, secondary flight control consist of flaps, slats, spoiler and trim tab. Before aircraft in flight, the primary and secondary flight con trol must be confirmed in balanced condition. If in unbalanced condition, flutter will occur when aircraft in flight. Flutter is an aeroelasticity phenomenon, it is a vibration phenomenon that caused aircraft wings "flapping" like a bird.This is because combination from stiffness of the wing structure, aerodynamic, and inertia (weight) from the structure. To avoid the occurrence of flutter, balancing flight control should be done, one of them is elevator tab. Elevator tab often called trim tab in elevator. Trim tab is attached to elevator that located in horizontal stabilizer. It must be confirmed in balanced condition even though elevator tab is a secondary flight control. Balancing tab elevator is by jig method procedure, which is tab must be removed first. Whether the elevator is balanced or not are determined by the value of Tab Assembly Moment (TAM) which is the result gained from this research is 15.22 lbfinch and the tab can be said balance, because according to SRM boeing 737-800 the maximum TAM range is 15.48 lbfinch. If the research obtained a result more than 15.48 lbfinch, the tab must be returned to paint shop, decreasing the load weight from the tab by peeling paint coating. If the decreasing load weight from tab can't be done, the tab is considered "rejected", so it must be replaced with the new one.
RANCANG BANGUN SIMULASI PERGERAKAN HIGH LIFT DEVICE PADA PESAWAT lalu giat juangsa putra; James Siregar; Dedy Syarif Qusyairi
JURNAL INTEGRASI Vol 12 No 2 (2020): Jurnal Integrasi - Oktober 2020
Publisher : Politeknik Negeri Batam

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30871/ji.v12i2.2204

Abstract

The most high lift device modifying, for small airplanes and large, is the wing flap. Flaps can be installed on the leading edge or trailing edge (only for large airplane) aircraft. To make a simulator, the design and also the drive system are needed which will form the movement as in the real flap. As a driving mode, the system which designed on this flap simulator will use an electronic system. By using a servo motor as a drive and Arduino as a microcontroller that will be programmed according to the planned movement. The flap simulator can produce angles formed on servo motors such as 5º, 14º, 19º, 25º and 30º its moving flaps on flap level 0, 1, 2, 3 and 4 in extend and retract movement modes.
Identifikasi Penyebab Terjadinya Landing Gear Indication Tidak Berfungsi Normal pada Pesawat Boeing 737-900 ER Mohamad Alif Dzulfiqar; Nabila Ayu Saputri; Nova, Muhammad Andi; James Siregar; Lalu Giat Juangsa Putra; Nur Rafia Dija; Meilani Mandhalena
JURNAL INTEGRASI Vol. 17 No. 1 (2025): Jurnal Integrasi - April 2025
Publisher : Pusat Penelitian dan Pengabdian Masyarakat Politeknik Negeri Batam

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30871/ji.v17i1.9510

Abstract

The Boeing 737-900 ER aircraft has a system called landing gear indication which in its application uses a proximity sensor that is useful in providing information about the position of the landing gear. However, this system can experience problems where if the landing gear indication does not function, the pilot cannot obtain information from the instrument that ensures the position of the landing gear. The purpose of this study is to identify problems that often occur in the landing gear indication system on the aircraft. The analysis was carried out using the Root Cause Analysis (RCA) method with the Fishbone Diagram approach. From the identification results, it was found that the main cause was a problem with the proximity switch sensor experiencing corrosion and changes in position which caused the signal reading to be inaccurate. For this reason, it is necessary to replace components and adjust the sensor position so that the system can run properly.
Co-Authors Achmad Zahir Saputra Aziz Nur Rahman Benny Haddli Irawan Billi Aldin Sumadireja Budi Baharudin Dedy Syarif Qusyairi Dian Saputra Dicky Reza Prawira Dija, Nur Rafia Hanifah Widiastuti Ihsan Saputra James Siregar Meilani Mandhalena Mohamad Alif Dzulfiqar Mufti Fathonah Muvariz Muhammad Andi Nova Muhammad Zainuddin Lubis Nabila Ayu Saputri Naufal Abdurrahman Nova, Muhammad Andi Nur Rafia Dija Rahman Hakim Rizky Pratama Hudhajanto Sapto Wiratno Satoto Yattawuri Arinta Timur