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Figure 2-57. Longitudinal System Authority
2-99 ORIGINAL
NAVAIR OI-FI4AAD.1
NOMENCLATURE
0 Bomb release button
0 Pitch and roll trim button
0 Weapon Selector switch
@
Maneuver flap, slat, and
DLC command
ORIGINAL
FUNCTION
Pilot control for release of stores. In aircraft with the weapons rail defense
electronic countermeasures (DECM) chaff adapter, the bomb release button
Is used to dispense chaff.
Spring-loaded to (center) off position. Up and down positions control pitch
trim and left and rlght positions control roll trim. Manual trim Is Inoperative
during autopilot operation.
LR- Selects Phoenix missiles.
MR - Selects Sparrow missiles.
SR - Selects Sldewlnder missiles.
GN - Selects gun.
Sprlng-loaded to a neutral posltlon.
With DLC engaged: Forward rotation extends spoilers (aircraft down); afl
rotatlon retracts spoilers (aircraft up).
With gear and flaps up: Forward rotation retracts maneuvering flaps/slats; aft
rotation extends maneuverlng flaps/slats.
Figure2 -58. ControlS ticka ndT rim (Shee1t of 2)
2-100
NAVAIR 0%F14AAD1
NOMENCLATURE FUNCTION
0
DLC engage, disengage, Momentary depression of the switch with flaps greater than 25 degrees
and chaff switch down, throttle less than MIL, and no failures In spoiler system engages DLC.
With flaps up, switch will dispense chaff or flares. DLC is disengaged by
momentarily pressing the switch, raising the flaps, or advancing either throttk
to MIL.
c3
Autopilot reference and With weight on wheels, nosewheel steering can be engaged by depressing
nosewheel steering switch momentarily. Weight off wheels and autopilot engaged; switch
pushbutton engages compatible autopilot modes.
0
Autopilot emergency Disengages all autopilot modes and DLC. Releases all autopilot switches.
disengage paddle Disengages the pitch and roll servos and causes the pitch and roll SAS
switches to move to OFF. The yaw SAS channels In either case are not
affected. Depressing the paddle switch reverts throttle system from AUTO or
BOOST mode to MAN mode only while depressed and with weight on
wheels.
63
Camera and forward Pilot control of CTVS, gun camera, andfor forward firing weapons. First deten
weapon firing trigger of trigger starts gun camera and cockpit television sensor (CTVS).
Figure 2-58. Control Stick sad Trim (Sheet 2 of 2)
2.23.2.1 Preflight. The ITS is automatically eoergized
with hydraulic and electrical power applied. It can
be checked by operatingf laps or speedbrakesa nd observing
a change in indicated stabilizer position.
2.23.3 Lateral Control. Lateral control (Figure 2-60)
is effected by differential displacement of the horizontal
stabilizers and augmented by wing spoilers at wingsweeppositionaoflessthan62°.
A*l/2-inchstickdeadband
is provided to preclude spoiler actuation with small
lateral stick commands. The spoilers are commanded to
the flush-down (O”) position at wing-sweep angles of
greater than 62”, and roll control is provided entirely by
differential stabilizer. At wing-sweep angles of 65’ and
greater, the hydraulic power to the spoiler actuators is
cut ofE, locking the spoilers in the 0” position. Lateral
stick commands are transmitted by pushrods and bellcrankst
o the independents tabilizerp ower actuatorsa nd
electrically to the spoiler actuators. Lateral system
authority is tabulated in Figure 2-61.
2.23.3.1 Lateral Feel. An artificial feel system provides
the pilot with force cues and feedback. The lateral
feel mechanism is a spring roller-cam assembly with a
neutral stick position detent and a constant stick deflection
force gradient.
2.23.3.2 Lateral Trim. Lateral trim is by differential
deflection of the horizontal stabilizers. The wing spoilers
are not actuated for lateral trim control. Trim is provided
by adjusting the neutral position of the spring
roller-cam-feel assembly with an electromechanical
screwjack. Left or right deflection of the roll trim button
on the stick grip produces corresponding stick movement
and letI or right wing-down trim, respectively. The
normal stick grip trim switch is inoperative when the
autopilot is engaged.
Note
With lateral trim set at other than O”, maximum
spoiler deflection is reduced in the direction
of applied trim.
2.23.3.3 Lateral Control Stops. To limit the torsional
fuselage loads, variable lateral control authority
stops are installed. The lateral stick stops vary according
to dynamic pressure airloads from full stick authority at
　
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