7
O
WNER
’
S
F
LIGHT
M
ANUAL
6
XL
source.The requirement for cabin heat is far less than convention-
al light planes. Due to the cabin volume and good vent location,
and tinted windows, the Velocity is more comfortable on hot days
than conventional light planes.
Fuel System
The fuel system consists of two 33 gallon wing tanks.There is
no provision for cross feed as fuel is used from both tanks simul-
taneously. A 4 gallon fuel sump is located behind the rear seat to
assure fuel supply to the engine in normal flight attitudes. Each
main tank and sump tank is vented. A mechanical engine-driven
fuel pump transfers fuel from the sump to the injector. An auxil-
iary electric fuel pump provides backup for the engine-driven
pump. Fuel pressure is indicated on a gauge in the cockpit.The
electric pump should be turned on if the engine-driven pump fails
as noted by a loss of fuel pressure.The electric fuel pump should
also be used to provide fuel pressure redundancy during low alti-
tude operation, such as takeoff and landing.
There is one fuel drain on the airplane, under the fuel sump.
CAUTION: Fuel additives should be checked for compatibility
prior to use. Some fuel additives, such as MEK, or de-icing fluids
like “Canned Heat”, auto gas (especially the high aromatic content
no-lead), should NEVER be used.They can dissolve the epoxy in
the fuel tanks.
Control System
Pitch is controlled by a full-span canard slotted flap providing a
large allowable cg range. Roll is controlled by conventional
ailerons on the rear of each wing.The cockpit controls are similar
to most aircraft with pitch and roll controlled by the side stick
and two rudder pedals for yaw.The side stick controller is
employed to give the pilot the smallest workload control arrange-
ment possible.The rudders, located on the winglets at the wing
tips, operate outboard only, providing two totally independent
systems.The rudders are used for yaw control or can be deployed
together as a mild speed brake.
Brake
Brakes are provided on the main wheels.They are used
together for deceleration on the ground and individually for direc-
tional control at low speed on the ground.The brake actuating
mechanism is the rudder pedal: after partial rudder deflection is
reached, the brakes are actuated.The brake master cylinder is the
rudder stop.This system aids in keeping brake maintenance low by
insuring that full aerodynamic control is employed before wheel
brakes are applied.
Trim Systems
Cockpit-adjustable trim is provided for pitch and roll only.
Yaw/rudder trim is ground adjustable only. Pitch and roll trim are
electro/spring systems.Adjustable aerodynamic trim tabs are not
used.The pitch and aileron switches are located on the control
stick and instrument panel.The pilot can safely override any trim
setting even if it is stuck in an extreme position.The pitch trim
can trim to hands-off flight from stall to maximum speed.This fea-
ture allows the pilot to land the aircraft using the pitch trim, rud-
ders and throttle only.This is an excellent backup should a fail-
ure/disconnect occur in the normal control stick.
Electrical Systems
Refer to the wiring diagram (pages 10-11) that shows the
basic electrical power distribution. NOTE: Any builder modifica-
tions should be noted on this diagram.
Normal Operations
This section covers the normal operating procedures for the
Velocity. A summary checklist is provided for more convenient
cockpit use.
Summary of Contents for XL RG
Page 1: ......
