Scction
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7
Systems
Description
Retraction of the landing gear is accomplished by an electric motor and transmission assembly
located under the floorboard, activating push-pull cables to each of the main gear, and a push-pull
tube to the nose gear. Limit switches are installed in the system to cut off the gear motor when the
gear is
hlly extended or retracted.
To guard against inadvertent movement of the landing-gear selector switch while on the ground, a
mechanical guard is positioned just below the switch. On later models the switch handle must also
be pulled aft before being placed in the "gear up" position. Beginning with serial number
656,
a
warning horn will sound if the selector switch is placed in the "gear up" position while the weight
of the airplane is resting on the landing gear.
To prevent inadvertent retraction of the landing gear while the airplane is on the ground, a safety
"squat" switch is installed on the left main gear to open the electric circuit to the landing-gear
motor until the strut is fully extended.
If manifold pressure is reduced below approximately 12-inches, and the landing gear is not down
and locked, a warning horn will sound to alert the pilot to the possibility of a gear-up landing. The
landing-gear warning horn emits a continuous sound.
A
green light on the instrument panel is the primary indication that the landing gear is down and
locked. When the gear is fully extended, the series circuit that lights
this
lamp is completed
through a switch located on each of the three gear. All three gear must be down and locked for
the indicator to light.
An
amber light above the landing-gear selector switch indicates the gear is
up. It is important to note that the landing-gear indication lights are automatically dimmed when
the navigation lights are turned on.
A
telescoping emergency handle is used to manually extend the landing gear in the event of a
malfunction of the electrical system.
BRAKE
SYSTEM
The brakes are activated by a hand lever located below the left center of the instrument panel. The
hydraulic brake system is a self-adjusting, single-disk, double-piston assembly. The master
cylinder reservoir is located in the engine compartment on the firewall.
The parking brake is connected mechanically to the master cylinder and may be set by applying the
hand lever and pulling out the parking brake "T" handle. To prevent inadvertent application of the
parking brake in flight, a safety lock is incorporated to eliminate the possibility of pulling out the
"T" handle until pressure is applied by use of the toe brakes or hand lever. To release the parking
brake, apply the brakes and push in on the parking brake "T" handle.
FUEL SYSTEM
The fuel cells on the Comanche consist of rayon-neoprene bladders which are contained in cavities
in the forward sections of the wing. The cells hold a capacity of
30
gallons
(28
usable) each. It is
important to note that due to several factors, including aircraft attitude while refueling, many fuel
cells do not hold their full rated capacity.
Copyright:
1993
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