An auxiliary electric fuel pump is provided in case the engine-driven
pump fails. The electric pump should be ON for all takeoffs and landings
and when switching tanks. The fuel pump switch is located in the switch
panel to the left of the throttle quadrant.
The fuel drains should be opened daily prior to the first flight to check
for water or sediment. Each tank has an individual drain at the bottom
inboard rear corner.
A fuel strainer, located on the lower left front of the fire wall, has a drain
which is accessible from outside the left nose section. The strainer should
also be drained before the first flight of the day. Refer to paragraph 8.21 for
the complete fuel draining procedure.
The fuel pressure gauge is mounted in a gauge cluster located to the right
of the control quadrant (refer to Figure 7-13).
An engine priming system is installed to facilitate starting. The primer
pump is located to the lower right of the control quadrant.
7.15 ELECTRICAL SYSTEM
The electrical system includes a 14-volt, 60-ampere alternator, a voltage
regulator, an over voltage relay, a battery contactor and a 12-volt,
25-ampere hour battery (Figure 7-9). The battery is entirely enclosed in a
vented stainless steel box mounted in the engine compartment on the upper
right forward side of the firewall. The voltage regulator and overvoltage
relay are located on the right aft side of the firewall behind the instrument
panel.
Electrical switches are located on the lower part of the instrument panel
just left of center, and the circuit breakers are located on the lower right of
the instrument panel. Each circuit breaker on the panel is of the push to reset
type and is clearly marked as to its function and amperage. Circuit
provisions have been included to handle the addition of various items of
optional equipment (Figure 7-11). If a breaker pops, it should be allowed to
cool for a couple of minutes before resetting the breaker.
Rheostat knobs to the left of the circuit breakers control the intensity of
of instrument and radio lights. The master switch and magneto switch are on
the lower left instrument panel below the left control wheel.
SECTION 7 PIPER AIRCRAFT CORPORATION
DESCRIPTION & OPERATION PA-38-112, TOMAHAWK
REPORT: 2126 ISSUED: JANUARY 20, 1978
7-8 REVISED: MAY 10, 1982
An auxiliary electric fuel pump is provided in case the engine-driven
pump fails. The electric pump should be ON for all takeoffs and landings
and when switching tanks. The fuel pump switch is located in the switch
panel to the left of the throttle quadrant.
The fuel drains should be opened daily prior to the first flight to check
for water or sediment. Each tank has an individual drain at the bottom
inboard rear corner.
A fuel strainer, located on the lower left front of the fire wall, has a drain
which is accessible from outside the left nose section. The strainer should
also be drained before the first flight of the day. Refer to paragraph 8.21 for
the complete fuel draining procedure.
The fuel pressure gauge is mounted in a gauge cluster located to the right
of the control quadrant (refer to Figure 7-13).
An engine priming system is installed to facilitate starting. The primer
pump is located to the lower right of the control quadrant.
7.15 ELECTRICAL SYSTEM
The electrical system includes a 14-volt, 60-ampere alternator, a voltage
regulator, an over voltage relay, a battery contactor and a 12-volt,
25-ampere hour battery (Figure 7-9). The battery is entirely enclosed in a
vented stainless steel box mounted in the engine compartment on the upper
right forward side of the firewall. The voltage regulator and overvoltage
relay are located on the right aft side of the firewall behind the instrument
panel.
Electrical switches are located on the lower part of the instrument panel
just left of center, and the circuit breakers are located on the lower right of
the instrument panel. Each circuit breaker on the panel is of the push to reset
type and is clearly marked as to its function and amperage. Circuit
provisions have been included to handle the addition of various items of
optional equipment (Figure 7-11). If a breaker pops, it should be allowed to
cool for a couple of minutes before resetting the breaker.
Rheostat knobs to the left of the circuit breakers control the intensity of
of instrument and radio lights. The master switch and magneto switch are on
the lower left instrument panel below the left control wheel.
SECTION 7 PIPER AIRCRAFT CORPORATION
DESCRIPTION & OPERATION PA-38-112, TOMAHAWK
REPORT: 2126 ISSUED: JANUARY 20, 1978
7-8 REVISED: MAY 10, 1982
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