MAULE AEROSPACE TECHNOLOGY, INC.
MAINTENANCE MANUAL
FOR
MXT-7-160
Rev. E
32/39
FUEL SYSTEM
Two (2),
23.8
gallon
(or 21.5-gallon)
main fuel tanks, mounted in the inboard end of the
wings, have front and rear outlets.
The fuel lines running from these tanks terminate at the fuel
selector valve on the left side kick panel. The fuel selector valve has four positions: LEFT,
RIGHT, BOTH and OFF. The fuel then runs through the firewall to the fuel gascolator. Fuel
runs from the gascolator to the electric fuel boost pump, to the engine driven fuel pump, and
then to the carburetor. Leave selector valve on LEFT or RIGHT position when airplane is
parked to prevent fuel transfer from one side to the other.
If installed, two (2) auxiliary wing tip fuel tanks,
fifteen (15) gallon (or twenty-one (21) gal-
lon)
capacity, are mounted in the second from the outboard wing bay. They are fuel transfer
tanks and simply supply fuel to the main tank through a small vibrator pump.
The fuel line should be checked for cracks and chafing every 100 hours or annually and
the gascolator should be cleaned at the same time. The auxiliary tank transfer pump strainers
should be cleaned at the same interval. This is done by removing the pump bottom with a 5/8"
wrench. The pump is on the rear spar, inboard of the auxiliary tank, and the bottom is exposed.
ELECTRICAL SYSTEM
The electrical system is a 14 or 28 volt, 50 amp, direct current, single wire circuit using the
airplane structure as a ground return to the battery. All wiring in the airplane is fabricated into
harnesses which are groups of related wires tied together. Most of the harnesses originate at
circuit breakers on the main bus (center of instrument panel) and terminate at the load (light,
pump motor, etc.) Wiring diagrams are shown at the end of this manual.
CAUTION: Addition(s) of electrical equipment must not cause the total load to exceed 50 am-
peres. The total rated alternator capacity is a nominal 63 amperes at cruise rpm. Paragraph 4-
26(d) of FAA AC 43.13-1A limits the total continuous load to 80% of the total rated capacity, or
50 amperes. A 50 amp circuit breaker is installed in aircraft.
BATTERY:
A lead plate type storage battery rated at 12 or 24 volts is installed in the battery box lo-
cated on forward side of firewall. The battery supplies current for the airplane electrical system
when the master switch is in the “ON” position only. A heavy-duty battery solenoid switch is in-
stalled next to the battery and is controlled from the Instrument panel by the battery switch.
The later batteries are the sealed type with the base being integrally vented. Tubes at-
tached to the case vent the battery to the fuselage bottom. Battery caps should be kept tight to
prevent electrolyte spillage. If spillage does occur, the affected area should be cleaned with a
liberal application of an acid neutralizing solution such as baking soda and water.
