Publication Type:

Journal Article


Jurnal Teknologi IST AKPRIND, Volume 1, Number 2 (2008)


Altitude, Drag, Lift, Manifol pressure


This research aims to discover the influence of altitude to power engine of AS-202/18A3 Bravo air craft. The power engine was needed to run for well beyond their intended lifetimes. Opening up machines for inspection is expensive, and owners need to consider all relevant information in making the decision. Problems in air craft power engine which reduce machine efficiency and output, such as drag on propeller blades and wings, body and fuselage and horizontal and vertical stabilizer, as located the steering system and landing gear.
The methode of this research are by Bravo AS-202 / 18A3 LM 2004 air craft with the engine of Avco Lycoming AEIO-360 BIF as 4 cylinder of four stroke piston engine with maximum power of 180 hp with cylinder volume of 360 cubic inches and maximum speed of 2700 rpm. The Bravo AS-202 / 18A3 LM 2004 air craft use the fuel of AVIGAS 91/96 with 100/130 octane number which flying in Yogyakarta city with 300 feet from sea level at 30 oC temperature. This research look at the instrumentation panel board at the cockpit of Bravo AS-202 / 18A3 LM 2004 air craft, as altimeter, rpm indicator, manifold pressure which can be detected and monitored using condition monitoring by performance analysis.
A performance test is normally carried out before and after flight, so we can observe the degradation of performance during one fuel cycle as well as the effectiveness of maintenance at overhaul. Because we should control some parameters and check the arrangement whenever we want to do a performance test, we cannot do it anytime. In this research we will take a simplified perform.
The result of this research shows that at zero feet and the power engine speed of 2700 rpm, the manifold pressure as 24,6 in Hg, the power engin as 52 hp. The other at the same altitude at 2700 rpm engine speed, the manifold pressure decrease of 23,2 in Hg and the power engine as 51,66 hp. The result of the research obtained that in the higher of altitude makes the manifold pressure decrease but in a greater power, and in the great manifold pressure, the engine power growth lower.
In the zero altitude and the engine speeds of 2700 rpm, the manifold pressure as 23,2 in Hg, and the engine power as 55,75 hp, and at the 8000 ft altitude at the same engine speeds of 2700 rpm, the manifold pressure as 21,5 in Hg, the power engine as 51,66 hp., which means that in higher altitude the manifold pressure is decreased, and the power engine also in lower condition.

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(c) 2009 Jurnal teknologi FTI IST AKPRIND

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