THE INFLUENCE OF ALTITUDE TO POWER ENGINE OF AS-202/18A3 BRAVO AIR CRAFT
ABSTRACT: 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 30oC 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.
Penulis: Khairul Muhajir
Kode Jurnal: jptmesindd080026
