VASHON AIRCRAFT RANGER R7, Руководство по обслуживанию

Страница: 212 / 392

Date: 11-15-19 Revision: 2
5.7.12-2 VASHON AIRCRAFT RANGER R7 MAINTENANCE MANUAL
GENERAL
The aircraft is equipped with two 12.5 US gallon main tanks in the leading edge of the wing and
a single non-integral 2.5 US gallon header tank located in the avionics bay. The header tank
fuel sump and the drain are located on the bottom of the fuselage on the copilot side beneath
the firewall. There is a wing tank drain on the bottom of each wing. Fuel samples should be
taken at each of the three drain locations before each flight to verify that there is no water or
sediment in the fuel system.
Fuel flows via gravity from the main tanks to the header tank then through a shut-off valve,
boost pump, filter, fuel flow transducers, and finally to the carburetor. The header tank remains
full whenever there is fuel in either main tank. There is an electric boost pump located just
downstream of the header tank outlet which is to be turned-on any time the header tank is not
full.
The air-spaces at the tops of all three tanks are interconnected and the fuel system is vented
via an aluminum vent tube connected to the top of the outboard end of the passenger-side
main fuel tank that runs along the front side of the main spar to the the pitot/static/aoa mast.
The vent line opening faces downward from the pitot/static/aoa mast to discharge clear of the
leading edge of the wing. The vent line discharge is shielded to prevent in-flight obstruction of
the vent opening due to bird/insect/debris impact or icing. The vent opening should be
inspected for obstruction prior to each flight.
If the aircraft is parked on a slop
e for longer than just a few minutes, the “low - side” tank will
have more fuel tha n the “h igh- side” tank. For this reason, when visually checking the quantity
of the low-side tank it is suggested to first unlatch the filler cap and only if fuel does not flow
out from under the filler cap should it then be slowly removed. When fueling the aircraft, it is
suggested that the low-side tank be filled first to maximize the amount of fuel that may be
added.
The quantity of fuel in each main fuel tank is displayed on the EFIS. The electrical signal to the
EFIS is derived from a float-type variable resistance sender located in each main tank. The
header tank fuel state (“Full” or “Not Full”) is displaye d on the EFIS. The electrical signal to the
EFIS comes from an “on/off” float switch mounted near the top of the header tank.
Prior to refueling the aircra ft, connect the fueling equipment’s grounding cable to either of the
wing tie-downs or to the engine exhaust pipe. This will ensure that there is no difference in
electrical potential between the aircraft and the fueling equipment and will minimize the risk of
electrical sparks when the aircraft is being refueled.