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rudder pedal movement inflight.
2.9.9.3 Stick Grip FCS Controls. The FCS controls located on the stick grip include the pitch and roll
trim switch, the NWS button, and the autopilot/NWS disengage switch. See figure 2-22. In the
F/A-18F (trainer configuration), the FCS controls on the rear cockpit stick grip are identical to those
in the front cockpit.
2.9.9.3.1 Pitch and Roll Trim Switch. The pitch and roll trim switch is located on the top right of the
stick grip. Movement of the pitch and roll trim switch electrically biases the FCCs and does not
reposition the stick.
Forward Trims nose-down.
Aft Trims nose-up.
Left Trims left-wing-down.
Right Trims right-wing-down.
Pitch and roll trim inputs can be made incrementally or held for faster trim rates. In UA, little if any
pitch trim is required due to the automatic trimming function provided by P CAS. In PA, pitch trim
is required to trim for on-speed AOA. Lateral trim is typically only required immediately after takeoff
or following changes in lateral weight asymmetry (fuel and/or stores). Pitch trim is not monitored for
runaway trim. However, roll trim is monitored for a stuck switch. If the trim switch is held or is stuck
in the left or right position for more than 40 seconds, the FCS caution is set and the roll trim function
of the switch is disabled for the remainder of the flight. Roll trim can be faded to zero by pushing and
holding the FCS RESET button or TO/TRIM button for approximately 4 seconds.
A1-F18EA-NFM-000
I-2-70 ORIGINAL
2.9.9.3.2 NWS Button. The undesignate/nosewheel steering button is located on the front of the
stick grip. The NWS button is used to engage NWS modes, as described in the NWS System
paragraphs in the Utility Hydraulic Functions section. The undesignate function of the NWS button
is described in the Weapon Systems Controls section.
2.9.9.3.3 Paddle Switch. The autopilot/NWS disengage switch, commonly called the ²paddle
switch,² is located on the lower front of the stick grip. The paddle switch is used to disengage NWS with
WonW, to disengage all autopilot modes with WoffW, and to enable g-limiter override with WoffW. To
enable g-limiter override, the paddle switch must be momentarily pressed with the stick near the aft
limit.
2.9.9.4 RUD TRIM Knob. The RUD TRIM knob is located on the FCS panel on the left console in the
front cockpit only. Movement of the RUD TRIM knob electrically biases the FCCs and does not
reposition the rudder pedals. Rudder trim authority is ±10° and ±22.5° of rudder surface deflection in
UA and PA, respectively. PA rudder trim authority is set to allow zero pedal forces during a HALF flap,
single engine approach. Yaw trim is zeroed by mechanically centering the RUD TRIM knob when the
T/O TRIM button is pushed with either WonW or WoffW.
2.9.9.5 T/O TRIM Button. The T/O trim button is located in the center of the RUD TRIM knob on
the FCS panel on the left console. With WonW, holding the T/O TRIM button pressed drives pitch
trim to 4° TEU stabilator, roll trim to neutral, and yaw trim to neutral by mechanically centering the
RUD TRIM knob. Depending on initial trim position the T/O TRIM button may need to be pressed
for up to 4 seconds. When these takeoff trim settings are reached, the TRIM advisory is displayed on
the LDDI for as long as the T/O TRIM button is held depressed. With WoffW, pressing the T/O TRIM
Figure 2-22. Stick Grip FCS Controls
A1-F18EA-NFM-000
I-2-71 ORIGINAL
button for as long as 4 seconds drives roll trim to neutral, centers the RUD TRIM knob, but does not
affect pitch trim.
2.9.10 Yaw Rate Warning Tone. In UA (flaps AUTO), a yaw rate warning tone is provided to alert the
pilot of excessive yaw rate that may lead to an aircraft departure. The yaw rate warning tone is
generated by the FCCs and is initiated at 40°/second yaw rate with a 1 Hz pulse rate. The tone pulse
rate increases linearly as yaw rate approaches 60°/second, where the pulse rate remains constant at 10
Hz. There is no yaw rate warning tone in PA.
2.9.11 AOA Warning Tone. In PA (flaps HALF or FULL), an AOA warning tone is provided to alert
the pilot of excessive AOA that may lead to aircraft settle and/or departure. The AOA warning tone is
generated by the FCCs and is initiated at 14° AOA with a 1 Hz pulse rate. The tone pulse rate increases
linearly as AOA approaches 35°, where the pulse rate remains constant at 10 Hz. There is no AOA
warning tone in UA.
2.9.12 Spin Recovery System. The aircraft incorporates an automatic spin detection and recovery
system. A spin is declared when both of the following conditions are met: (1) airspeed is below
approximately 120 ±15 KCAS and (2) the yaw rate threshold is exceeded. The yaw rate threshold is
　
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