MAULE AEROSPACE TECHNOLOGY, INC.
MAINTENANCE MANUAL
FOR
MXT-7-180
Rev. F
31/37
Remove Heater Shells, check mufflers and tailpipes for cracks. Check attachments for
security. Note that the tailpipe clamps and the muffler-to header attachments should not be
tightened to the point of rigidity, but should be loose enough to be moved easily by hand.
Check the heater shell retaining screws for security and ensure that hot air hoses are
clamped tightly and are not worn or chafed.
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 ex-
posed.
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:
