Garuda - Garba Rujukan Digital

ANALISIS SITUASI LINGKUNGAN DAN FORMULASI STRATEGI SEBAGAI TAHAPAN PERENCANAAN STRATEGIS PERSPEKTIF AKREDITASI PROGRAM STUDI Ego Widoro
Langit Biru: Jurnal Ilmiah Aviasi Vol 9 No 1 (2016): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (499.214 KB)

Current condition in aviation require the strategic planning for program of study to be able to improve academic and non-academic quality to facing it by considering internal and external side. Within higher education strategic planning in terms of education remains three aspects that are Education, Research and Community Service are called Tridharma. Higher education strategic planning has been accommodated by accreditation form Badan Akreditasi Nasional Perguruan Tinggi (BAN-PT), so that improving academic and non-academic quality evidenced by rankings of accreditation. Environment analysis is first stage by using Delphi method to summarize the opinions from the experts about external condition to determine opportunity and threat. Internal condition analyzes by assessing using assessment of accreditation to determine strength and weakness. To find strategy in strategy formulation use matrix of opportunities, threats, strengths and weakness. Result of strategy formulation for each accreditation component in Program of Study Aircraft Engineering are: Organization vision, mission and stage time of achievement; improvements in budgeting, feedback and improving the graduates quality and create cooperation and dialogue with users, alumni participation, and study trace; improvement of academic qualifications, scientific activities and ratio of lecturers; number and qualifications of educational personnel; monitoring improvement of academic activities, curriculum development, academic atmosphere, quality of final project and safety culture; improved management, budget structure and budget allocations for the implementation of Tridharma; create scientific activity program, an increase in the interest of lecturer and other lecturer development activities. The next research is implementation and evaluation strategies.

ANALISIS PENGARUH ORIENTASI FASA PENGUAT PADA MATERIAL SANDWICH KOMPOSIT DI PROGRAM STUDI TEKNIK PESAWAT UDARA SEKOLAH TINGGI PENERBANGAN INDONESIA Lilies Esthi Riyanti; Ego Widoro; Yudha Nur Cahyo(
Langit Biru: Jurnal Ilmiah Aviasi Vol 9 No 1 (2016): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (637.897 KB)

The composite material is the result of a combination of macroscopic material from two or more different components. Components of the composite in the form of reinforcement and a binder (matrix). The strength and properties of the composite can be obtained from the phase constituent, the composition and geometry of the reinforcing phase. There are differences in the strength of the composite on any kind of orientation in which the determination of this orientation will also affect the level of force against the load received on the composite. After the manufacture of some types of samples with different orientations and then continued testing the strength of each type of sample using standard tests according to testing for composite materials and then be done with the calculation and analysis of the strength and stiffness of each sample. From these results can be obtained from the data that the sample composite reinforcements phase orientation in the direction of loading levels of strength and stiffness of the greatest, while the orientation phase composite samples reinforcements perpendicular to the direction of loading levels of strength and stiffness of the weakest. Therefore, in the manufacture of composite materials need to be considered in determining the composition of each layer orientation in accordance with the direction of the load that will be accepted in order to generate maximum power level in the composite material.

ANALISIS STRUKTUR VELG PADA MODIFIKASI AIRSIDE INSPECTION VEHICLE MENGGUNAKAN PERANGKAT LUNAK ANSYS Oka Fatra; Ego Widoro; Tony Yudhyika Pradana Gultom
Langit Biru: Jurnal Ilmiah Aviasi Vol 9 No 3 (2016): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1333.272 KB)

Airside Inspection Vehicle is a vehicle designed by cadets of Airport Mechanical Engineering 6 from the vehicle tossa three wheels become the four wheel. The component of vehicle has never been done tested. A strength testing of wheel material against static working load is calculated using static structural and force theory and then compared by using software R17.0 Ansys Workbench. The tested area are flange and hub diameter. The vehicle load of 500 kg, the stress that occurs at flange using theoretical is 0,382 MPa and count software is 0,0002 MPa while stress that happen at hub diameter area is 10,74 MPa and count software is 18,671 with allowable stress of 110 MPa. The Result showed that the stress occurs at the velg considered safe.

MODIFIKASI SPECIAL TOOLS PEMASANG POWER OUTPUT SEAL BERSUDUT 90° PADA ENGINE ALLISON 250 – C20 SERIES DI SEKOLAH TINGGI PENERBANGAN INDONESIA Ego Widoro; Diding Sunardi; Bagas Pradityo
Langit Biru: Jurnal Ilmiah Aviasi Vol 10 No 1 (2017): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar

The schedule maintenance program of Allison 250-C20Series engine is required to keep the engine in airworthy condition. One of the schedule maintenance programs is planned to keep the engine oil flow system. This engine oil flow system can be disrupted if the seal on the power output seal which is keep the oil flow system were leak. The design of special tools modification power output seal installation aims to simplify the installation of power output seal when the engine power output still installed at the helicopter. It’s already made bysafety factor theory, Newton’s IInd law, Weight theory, and others theory which helping for making this modification tools. The purpose of modification is to attach power output seal in order to make it at the perpendicular. This is necessary to avoid tilt while installing seal. By modifying these special tools, there are a lot of free spaces made when installing the seal when the engine still installed at the helicopter, it became more flexible and lighter tools to use, if its compared with the prior modification of special tools. The parts of the special tools modification power output seal installation. The parts of special tools modification power output seal installation are power screw with allowable pressure is 3x10-6 kg/m2 , pusher seal cover with suitable area is 6,6x10-3 m 2 , pusher seal cover with suitable area is 6,4x10-3 m 2 and T-fasten screw with allowable shear stress is 4,15x10- 9 kg/m2 . This modification is capable to make the availability of long free space becomes wider 11 cm, and reduce the weight of the prior tools of up to 4x10-1 kg. The modification helped installation of power output seal esier when the engine is still installed on the Bell 206 helicopter

RANCANGAN SISTEM PEMANAS UNTUK PROSES PENGERASAN PANEL KOMPOSIT DENGAN METODE WET LAY UP DI PROGRAM STUDI TEKNIK PESAWAT UDARA SEKOLAH TINGGI PENERBANGAN INDONESIA I Dewa Gde Darmawan; Ego Widoro; Djoko Herwanto
Langit Biru: Jurnal Ilmiah Aviasi Vol 13 No 01 (2020): Langit Biru: Jurnal Ilmiah Aviasi Vol.13 No.1 [Februari 2020]
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (729.839 KB)

Sistem pemanas yang dimiliki Program Studi Teknik Pesawat Udara Sekolah Tinggi Penerbangan Indonesia menghasilkan panas yang tidak merata sehingga akan berpengaruh pada penyatuan fiber dan matriks pada panel komposit tersebut, tentunya akan lebih baik jika terdapat sistem pemanas yang dapat menghasilkan panas secara menyeluruh dan curing time dari proses pengerasan itu dapat terpenuhi. Tahapan perancangan dimulai dengan perumusan masalah, pengumpulan data, pengolahan data, perancangan dan pemilihan sistem pengatur panas, perakitan komponen, uji coba rancangan, interpretasi dan kesimpulan. Proses perancangan elemen pemanas dimulai dengan menentukan temperatur maksimal proses pengerasan panel komposit yaitu 100 C, penghitungan lama proses pengerasan yaitu 101 menit dan pemilihan elemen pemanas, yaitu 2 buah elemen pemanas tubular dengan panjang 100 cm dan diameter 8 mm. Dan proses pemilihan sistem pengatur panas dimulai dengan pemilihan komponen thermocouple, pengatur temperatur, sakelar, lampu indikator, kabel, circuit breaker, fuse dan yang terakhir adalah contactor. Dari perancangan ini diharapkan mampu mengatasi permasalahan pada alat pemanas sebelumnya.

RANCANGAN SISTEM HIDROLIK ALAT BANTU PENGANGKAT DAN PENURUN INTEGRATED DRIVE GENERATOR PADA PESAWAT AIRBUS 320 DI PT. GARUDA MAINTANANCE FACILITY AERO ASIA Ade Alfiansyah. S; Ego Widoro; Djudjur Prasodjo
Langit Biru: Jurnal Ilmiah Aviasi Vol 12 No 1 (2019): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1114.727 KB)

When lowering and lifting the IDG with a weight of 56 kilograms in the IDG replacement process is done by positioning body that is not in a safe position. This is due to the unavailability of tools for IDG installation on Airbus 320 aircraft. Based on these problems, it is necessary to use IDG lifting and lowering devices with a hydraulic system. The first step to complete the design of the hydraulic system in this tool is to know the weight of the upper frame and the load from IDG so that the hydraulic system components needed such as actuators, hand pumps, flexible hoses, hydraulic fluids and fluid storage tanks can be calculated. The design of this tool uses an actuator with an inside diameter of 2.216 inch, an outside diameter of 2,294 inches and a length of 5 inches. Hydraulic hose with 0.223 inch inside diameter and outside diameter of 0.236 inch. Hand pump with a capacity of 1,376 inch3 and tank volume 19,811 inch3 . This tool can be used to assist the remove and installation of integrated drive generators on Airbus A320 aircraft at PT. Garuda Maintenance Facility after going through several test.

RANCANGAN SISTEM VAKUM UNTUK PROSES PENGERASAN KOMPOSIT DENGAN METODE WET LAY UP DI PROGRAM STUDI TEKNIK PESAWAT UDARA Riyan Maulana Yusuf; Ego Widoro; Djoko Herwanto
Langit Biru: Jurnal Ilmiah Aviasi Vol 12 No 2 (2019): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (795.961 KB)

Composite Curing process is need vacuum system to remove air bubble and heating system to decrease time of curing proses. Vacuum and heating system at composite panel curing practical at program studi teknik pesawat udara conducted separately, so need composite panel curing equipment that have integrated Vacuum and heating system. Vacuum system in this composite panel curing equipment is designed by design step including vacuum pump selection, hose selection, vacuum system design. Discussion results rate of flow of 37 L/min. With the fluid velocity of 20m/s. vacuum pump pressure of 14.5 inHg. Components required for vacuum system is a vacuum pump, vacuum regulator, vacuum gauge, nipple, vacuum bagging port, flexible Teflon hose.

RANCANGAN TUNGKU PEMANAS UNTUK PROSES PENGERASAN KOMPOSIT DENGAN METODE WET LAY UP DI PROGRAM STUDI TEKNIK PESAWAT UDARA SEKOLAH TINGGI PENERBANGAN INDONESIA Muhammad Riezky Utama; Ego Widoro; Djoko Herwanto
Langit Biru: Jurnal Ilmiah Aviasi Vol 12 No 3 (2019): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1190.575 KB)

The final objective of this design is to optimize the curing process in the manufacture and repair of composite panel for interchanges curing process using a heat gun, because by using a heat gun the curing process is not optimal. The design focuses on making the furnace only on the other parts are designed on other designs. The goal that must be achieved is to make optimal heat distribution in the furnace. Tests carried out to get all the components that did not change the shape during the composite curing process that occurred, components that did not change from the shape received, and the length of expansion of the work-piece within the specified range. Will there be one criterion which has not yet been agreed upon, the top surface of the furnace wall is 41.7 ℃ causes the surface of the upper wall to pass through a predetermined range affecting the buoyancy force which causes the air density to decrease and hot air as it moves upward. This is what causes heat transfer to the surface which is higher than the other sides

RANCANGAN MODIFIKASI ALAT PENARIK BETA SISTEM PROPELLER HARTZELL TIPE HC-E4N-3G SERIES DI BALAI BESAR KALIBRASI FASILITAS PENERBANGAN M. Ichwan Ridhani; Ego Widoro; M. Subiat Wiranata Kusuma
Langit Biru: Jurnal Ilmiah Aviasi Vol 11 No 1 (2018): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (810.372 KB)

The removal of HC-E4N-3G type Hartzell propellers at the King Air 200 aircraft own Balai Besar Kalibrasi Fasilitas Penerbangan (BBKFP) is carried out on scheduled and unscheduled maintenance. When removal and installation this propellers using available tools, technicians often have difficulty because requiring large power and unsafe conditions when withdrawing the propeller beta system due to the design of the tool, such need withdrawing tool modifications of HC- E4N-3G type hartzell propeller beta system. Theories relating to modification of this tool include maintenance, hartzell propeller type HC-E4N-3G Series, material selection, load, circle shape, torque, stress, security factor and thread theory. The design of this tool modification is divided into several parts such as puller rod, threaded pressing rod, threaded retaining body, rotating arm and pressing threaded cylinder. Based on the calculation and analysis process all parts of the withdrawing tool are made from S45C material and tool modification with dimensions of all parts according to the calculation and analysis process successfully able to draw HC- E4N-3G type hartzell propeller beta system beta Hartzell propeller

RANCANGAN ALAT BANTU UNTUK MELEPAS DAN MEMASANG MAIN LANDING GEAR DOWNLOCK SPRING BUNGEE PADA PESAWAT BOEING 737-300/400/500 DI PT. AERO NUSANTARA INDONESIA Ego Widoro; Bambang Sutarmadji; Imam Sarwo Aji
Langit Biru: Jurnal Ilmiah Aviasi Vol 11 No 2 (2018): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (755.425 KB)

Process of removal and installation Main Landing Gear downlock Spring Bungee of aircraft Boeing 737 - 300/400/500 at PT. Aero Nusantara Indonesia using a rope as a tool to hold and pull downlock spring bungee. The rope must be pulled with a strong force and requires a minimum two people as well as the processing time of more than four minutes. Another constraint is needed additional pins are mounted on the support shaft uplock holes and the possibility to be separated or broken rope could happen so that it may be accident in its use. The design of this tool consists of four parts, that is a power screw, rod holder, rod player's arm, and frame. Measuring of downlock Spring Bungee dimensions used as a planning and calculation of the design to be created. The calculations results will be used as a design parameter to produce a tool that can be used with just one person and time of use can be speeded up to two minutes as well as lower levels of accidents that may happen.In this design it can be concluded that in general the tools to remove and install the Main Landing Gear downlock Spring Bungee on the Boeing 737-300 / 400/500 is in conformity with the parameters that have been determined so that this design tool can replace previously used and can be done validation can be used in accordance with their purpose

Title

Found 14 Documents
Search

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Title Search

Found 14 Documents Search

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Title

Found 14 Documents
Search