曝光台 注意防骗
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approach lights.
It is possible to damage and jam an AOA probe such that it continues to send signals to the FCCs.
FCC software is designed to minimize flying qualities degradation in the event of a stuck/jammed AOA
probe. The FCCs incorporate an AOA estimator which is used to identify the good AOA probe if one
is damaged. If an AOA probe split is transient, the estimator is used to identify the good probe and no
cautions are set. If the AOA probe split persists, an FCS caution is set, AOA is Xd in all 4 channels, and
the estimator is used for FCC calculations. See the HUD Symbology Degrades with Air Data Function
Failure paragraph and Part V for more details on AOA failures. Each AOA probe and AOA probe cover
are electrically heated to prevent icing.
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I-2-68 ORIGINAL
2.9.8.3 PITOT ANTI ICE Switch. The PITOT ANTI ICE switch is located on the ECS panel on the
right console. This switch is used to power the electric heaters for the pitot-static/total temperature
probes, the AOA probes, and the AOA probe covers. All heaters are thermostatically controlled to
prevent damage to their corresponding sensors. With WonW, the thermostat set points are reduced to
prevent damage when cooling airflow is not provided.
ON Pitot and AOA heaters on manually (WonW or WoffW).
AUTO Pitot and AOA heaters on automatically with WoffW. Heaters off with WonW.
Failure of both AOA probe heaters in icing conditions may cause a sharp
uncommanded nose down attitude, uncontrollable by normal stick forces
or paddle switch actuation.
2.9.9 Flight Controls.
2.9.9.1 Stick. A traditional center mounted control stick is used to provide pitch and roll inputs to
the FCS. Since there is no mechanical linkage between the stick and the FCCs or the flight control
surfaces, stick feel is provided by two feel-spring assemblies and two eddy current dampers. The feel
spring assemblies provide a linear stick force versus stick displacement gradient in each axis. Two
4-channel position sensors, one in each axis, measure stick displacement and send longitudinal and
lateral stick commands to the FCCs proportional to stick displacement. Stick force and displacement
are listed in figure 2-21 for full stick travel. The eddy current dampers provide stick motion damping
in each axis. Additionally, the control stick is mass balanced to minimize longitudinal stick movement
resulting from accelerations normally experienced during catapult launch.
In the F/A-18F (trainer configuration), a control stick is also fitted in the rear cockpit and is
mechanically linked to the one in the front cockpit.
Direction
Displacement
(in)
Force
(lbs)
Stick
Forward 2.5 20
Aft 5.0 37
Left/Right 3.0 13
Pedal Left/Right 1.0 100
Figure 2-21. Stick and Pedal Travel Limits
2.9.9.2 Rudder Pedals. Two rudder pedals (left and right) are used to provide directional inputs to
the FCS for yaw/roll control inflight or NWS control with WonW. Since there is no mechanical linkage
between the rudder pedals and the FCCs or the flight control surfaces, rudder pedal feel is provided
by two feel-spring assemblies. The feel spring assemblies provide a linear pedal force versus
displacement gradient. Two 4-channel position sensors, one on each pedal, measure pedal displacement
and send directional commands to the FCCs proportional to pedal displacement. Rudder force
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I-2-69 ORIGINAL
and displacement are listed in figure 2-21 for full pedal travel. The rudder pedals are also used to
provide NWS commands and to actuate toe-operated wheel brakes.
In the F/A-18F (trainer configuration), two rudder pedals are also fitted in the rear cockpit but are
not mechanically linked to the rudder pedals in the front cockpit. Pedal inputs from either cockpit are
summed together and transmitted to the FCCs. A half pedal input from the front cockpit and a half
pedal input from the rear cockpit results in a full rudder pedal command to the FCCs. Similarly,
opposing rudder pedal inputs in each cockpit cancel each other.
2.9.9.2.1 RUD PED ADJ Lever. A RUD PED ADJ lever, located on the center pedestal in each
cockpit, is spring loaded to the up and locked position. When the lever is held down, the rudder pedals
are unlocked and can be moved forward and aft in ½ inch increments. Both pedals are spring loaded
to move aft and must be pushed forward to the desired position. Releasing the RUD PED ADJ lever
locks the pedals in the new position.
· Restrain the rudder pedals during adjustment. Unrestrained rudder
pedals may damage the rudder pedal mechanism.
· Ensure the rudder pedals are locked in position after adjustment.
Failure to lock the rudder pedals may result in uncommanded forward
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本文链接地址：
NATOPS Flight Manual 飞行手册 1(66)
