Cessna SKYCATCHER 162 - Landing Gear and Brake System

SECTION 2 CESSNA
AIRPLANE AND SYSTEM DESCRIPTION MODEL 162
GARMIN G300
U.S.
INSTRUMENT PANEL, FLIGHT AND SYSTEM
INSTRUMENTS (Continued)
Behind the instrument panel are the servo units for the optional
autopilot, Garmin ADAHRS (Air Data, Attitude, and Heading Reference
System) Unit, and the Secondary Battery. The ADAHRS unit is a
multifunctional processing unit which takes pitot-static pressures from
the pitot tube on the left wing and the static source button aft of the left
cowl for altitude, airspeed, and vertical speed information, tailcone
mounted magnetometer data for heading, and engine data for display
on the Engine Indication System (EIS) portion of the displays.
Fuel indicators are mounted in each wing root with silver float balls for
visual ease. The fuel placards are differentiated between level-flight
(LVL FLT) and on-ground (GRND). The MIN/TO reference mark on the
GRND side indicates the ¼ fuel requirement for take-off. In-tank fuel
tabs are equipped with indicator holes for full, ¾, ½, and the bottom of
the tab indicates ¼ (minimum takeoff). See Fuel System description
section for more information.
The optional magnetic compass (if installed) is mounted to the airplane
structure above the center of the windshield.
LANDING GEAR AND BRAKE SYSTEM
The tricycle type landing gear on the Model 162 features tapered spring
steel main gear legs and a spring steel nose gear with elastimetric
pucks for shock absorption. The nose gear is free-castoring and
directional control is done via differential braking. This permits very tight
turning and maneuvering in confined spaces. Full rudder deflection can
assist directional control when taxiing.
Disc brakes located on the main gear wheels are hydraulically actuated
by master cylinders on each rudder pedal. A parking brake valve locks
brake pressure to the disc calipers when the parking brake handle on
the lower instrument is pulled with the brake pedals depressed. The
hydraulic brake system is connected in series running from the firewall
mounted reservoir to the copilot's master cylinder then to the pilot's
master cylinder then to the brake caliper through the parking brake
valve.
162PHUS-01
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