Malibu Boats PA-46-310P, Pilot Operating Handbook

Page: 174 / 355

PIPER AIRCRAFT CORPORATION SECTION 7
PA-46-310P, MALIBU DESCR/OPERATION
from overboost damage by limiting manifold pressure to 38 in. Hg. In the event
of a controller malfunction, there is a pressure relief valve on the induction
manifold which will relieve manifold pressure at 42 in. Hg.
Manifold pressure limits can be exceeded with full throttle operation
during certain off standard ambient conditions and low engine oil tempera-
ture. During such conditions limit manifold pressure to 38 in. Hg maximum.
When descending from altitude, care should be exercised to maintain
engine power and temperatures (oil, CHT). Turbocharger compressors
supply air for cabin pressurization and power reduction below that recom-
mended could cause a decrease in cabin pressure. Sudden cooling or gradual
extreme cooling of engine cylinders will accelerate engine wear. Follow
normal descent procedures described in Section 4.
The fuel injection system has four basic components and one continually
moving part in the fuel pump. The primary functions of the engine driven
pump include supplying fuel under pressure to the injection system and
performing certain metering functions. The metering unit controls the
proportioning of fuel to air. The manifold valve divides metered fuel flow
equally between the six nozzles in the system. The nozzles continuously
spray and atomize metered fuel into the intake valve port of the engine
cylinder head.
Fuel is supplied to the engine driven pump at a greater rate than
required. The excess is returned to the wing tank selected.
To assist engine starting, an injection primer button can be found to the
right of the starter button, just left of the pilot’s control column. The primer
system diverts a large percentage of fuel intended for injection nozzles into
the intake manifold pipes through a single primer nozzle, just aft and down-
stream of the throttle valve.
Engine oil sump capacity is 8 quarts. Maximum endurance flights
should begin with 8 quarts of oil. Oil is drawn from the sump through a
suction tube to the intake side of the engine driven oil pump. Outlet oil is
directed to a full-flow, replaceable-element oil filter. A bypass valve
incorporated in the filter opens in the event it becomes clogged. The oil
pump has an oil pressure relief valve in the housing. A second gear-driven
pump, located below the starter, scavenges oil from the turbochargers.
Engine oil is cooled by ram air passing through the oil cooler on the left rear
of the engine. Oil is distributed throughout the engine, providing lubrication,
cooling, and oil to the propeller governor and turbocharger waste gate. Oil
ISSUED: JULY 1, 1986 REPORT: VB-1300
7-5
PIPER AIRCRAFT CORPORATION SECTION 7
PA-46-310P, MALIBU DESCR/OPERATION
from overboost damage by limiting manifold pressure to 38 in. Hg. In the event
of a controller malfunction, there is a pressure relief valve on the induction
manifold which will relieve manifold pressure at 42 in. Hg.
Manifold pressure limits can be exceeded with full throttle operation
during certain off standard ambient conditions and low engine oil tempera-
ture. During such conditions limit manifold pressure to 38 in. Hg maximum.
When descending from altitude, care should be exercised to maintain
engine power and temperatures (oil, CHT). Turbocharger compressors
supply air for cabin pressurization and power reduction below that recom-
mended could cause a decrease in cabin pressure. Sudden cooling or gradual
extreme cooling of engine cylinders will accelerate engine wear. Follow
normal descent procedures described in Section 4.
The fuel injection system has four basic components and one continually
moving part in the fuel pump. The primary functions of the engine driven
pump include supplying fuel under pressure to the injection system and
performing certain metering functions. The metering unit controls the
proportioning of fuel to air. The manifold valve divides metered fuel flow
equally between the six nozzles in the system. The nozzles continuously
spray and atomize metered fuel into the intake valve port of the engine
cylinder head.
Fuel is supplied to the engine driven pump at a greater rate than
required. The excess is returned to the wing tank selected.
To assist engine starting, an injection primer button can be found to the
right of the starter button, just left of the pilot’s control column. The primer
system diverts a large percentage of fuel intended for injection nozzles into
the intake manifold pipes through a single primer nozzle, just aft and down-
stream of the throttle valve.
Engine oil sump capacity is 8 quarts. Maximum endurance flights
should begin with 8 quarts of oil. Oil is drawn from the sump through a
suction tube to the intake side of the engine driven oil pump. Outlet oil is
directed to a full-flow, replaceable-element oil filter. A bypass valve
incorporated in the filter opens in the event it becomes clogged. The oil
pump has an oil pressure relief valve in the housing. A second gear-driven
pump, located below the starter, scavenges oil from the turbochargers.
Engine oil is cooled by ram air passing through the oil cooler on the left rear
of the engine. Oil is distributed throughout the engine, providing lubrication,
cooling, and oil to the propeller governor and turbocharger waste gate. Oil
ISSUED: JULY 1, 1986 REPORT: VB-1300
7-5
FOR REFERENCE ONLY
NOT FOR FLIGHT