Pilot’s Operating Handbook Section 7
EXTRA 500 Description of Airplane and Systems
7.10.a Components and System Features
The hydraulic pump and sump are located in front of the main
landing gear attachment frame between the keel beams. The
hydraulic valves needed for the sequence operation are located
in the same compartment in front of the hydraulic pump.
Hydraulic fluid level can be checked on ground by means of an
inspection glass with access from the R/H main wheel bay.
The landing gear switch is located on the left main panel (see
figure 7-4) well in reach of both pilot seats and has the positions
UP and DN for retracting and extending the landing gear. It is
necessary to first pull out the landing gear switch handle prior to
moving it up or down. The switch is fitted with a small wheel
for easy identification and assisting in moving the switch in
rough air.
The downlock information is given by three green
GEAR IND
lights located near the landing gear switch for each wheel
separately. The red GEAR WARN light on the annunciator panel
(see figure 7-2) indicates that the landing gear is not completely
retracted or extended.
The entire electric control processes signals from limit switches
indicating the completion of actions of the respective hydraulic
circuits and from the landing gear switches. In emergency case
pulling the
GEAR CTRL circuit breaker can deactivate it.
The directional valves are spring-loaded and will automatically
switch in the gear down position once electric power for the
gear control logic is lost.
As long as the landing gear switch is in
DN position the gear
downlock indication will still be operative, however the
prescribed re-closing of the upper main doors will not happen
and the landing gear extension airspeed limitation needs to be
applied accordingly.
26. January 2011 7-19
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