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Honda Aircraft Company
HA-420
SYSTEMS
POM
DESCRIPTION
The primary refueling tube extends from the filler port on the aft fuselage
to the bladder tank. Connecting the bladder tank and the carry-through
tank is a tube containing the fuel isolation valve which is open during
refueling operations. An interconnect tube with a one-way check valve
installed allows fuel to gravity feed from the C/T tank into the wing
tanks during refuel operations.
The refueling system also incorporates an integral check valve in the fuel
filler adapter and a flapper valve at the fuselage tank. The integral check
valve prevents fuel from siphoning overboard should the fuel cap be
inadvertently left off after fueling, and the flapper valve limits the
amount of fuel that could leak into the tailcone in the event of a leak or
separation of the refuel line.
Fuel Gauging System
The fuel system incorporates a fuel gauging system to measure and
display the quantity of fuel in the tanks for cockpit and external fuel
gauge indication purposes. The system incorporates a series of fuel
quantity probes and a fuel quantity signal conditioner unit. The system
also uses an optical low fuel level sensor in each wing that detects when
the fuel quantity in the wing tank is less than approximately 150 lbs. The
carry-through and fuselage bladder tanks are combined into a single
center tank for fuel gauging purposes.
The fuel quantity gauging system incorporates 15 capacitance type
probes (5 per tank) distributed throughout the fuel tanks. There are 5
probes located in each Wing Tank (L and R) and 5 probes located in the
Center Tank (4 probes in the Carry-through Tank and one probe in the
Fuselage Bladder Tank). The locations of the fuel quantity probes in the
fuel tanks were selected to allow the system to accurately sense the
quantity of fuel in the tanks under a wide range of aircraft attitudes.
HJ1-29000-005-001
October 30, 2016
1-101
FOR TRAINING PURPOSES ONLY
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