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slats.
Full slat asymmetry (17’) can result in an
out-of-control situation at 15 units AOA or
greater, even with 55” of spoilers available.
2.23.4.2 Ground-Roll Braking. Aerodynamic
ground-roll braking is provided by symmetric deflection
ofall spoilers to +55”. Ground-roll braking is controlled
by the ANTI SKID SPOILER BK switch on the pilot
2.23.4.1 Lateral Trim. As mentioned earlier, lateral
trim is provided by adjusting the neutral position ofthe
ORIGINAL 2-104
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Figure 2-63. Spoiler Gearing Schedule
2-405 GRIGINAL
left vertical console. The three-position switch allows
optional selection of BOTH (spoiler brake and antiskid
wheelbraking), SPOILER BK (spoiler brake only), or
OFF where neither spoilers nor antiskid are armed. With
SPOILER BK or BOTH selected, two conditions are
required to actuate the spoilers:
1. Weight on wheels
2. Both throttles a idle.
Failure lo satisfy any one ofthe above conditions will
cause the spoilers to return to the down position.
During initial spoiler brake operation, it is
normal for the indicators in the SPOILER
window to momentarily flip-flop.
2.23.4.3 Spoiler Fsailure. Simultaneous deflection
ofcorrespondingspoilerpairsgreaterthan lg”,orastick
displacement of 1 inch to oppose a symmetric spoiler
greater than 1 So, will signal a spoiler failure, remove all
electrical commands to the affected spoiler set, hydraulically
power the failed spoiler pairs to the -4-1/2Op osition;
and illuminate the SPOILER caution light.
Transient spoiler failures can be reset by pressing the
MASTER RESET pushbutton. With either SPOTLER
BK or BOTH selected and weight on wheels, the symmetric
spoiler failure logic is disarmed to permit symmetrical
5.5” spoiler deflection for ground-roll braking.
With DLC engaged, inboard symmetric spoiler failure
logic is disarmed.
Failure of the AFCS roll computer fails the inboard
spoiler pairs. An AFCS pitch computer failure renders
tbe outboard spoiler pairs inoperative.
A spoiler failure override (SPOILER FLR ORIDE)
panel on the pilot right inboard console allows the pilot
to manually override the automatic shutdown function.
If a stuckup spoiler failure occurs, selecting the appropriate
INBD or OUTBD spoiler switch to ORIDE
(Figure 2-64) and then depressing MASTER RESET
allows the remaining spoilers in that set to operate.
Varying ac voltage during an electrical short condition
may yield one or more of the following chamcteristics:
1. LOSSo f oneo r both channelso f computer operation.
2. Differential tail and rudder hardovers for up to 3
seconds.
3. Inoperative spoilers and SAS outputs even when
voltage is reset to nominal 115 volts.
4. Inability to reset computers through master reset
and reengagep itch and roll SAS switches.
On deck, when the flap handle is cycled to
UP, the outboard spoiler module is shut
down. This may cause the outboard spoilers
to indicate a droop or down position. If this
occurs, position the flap handle to DN and
move the control stick laterally. This will
result in a proper spoiler indication.
X23.4.4 Spo!ler TIM. The spoiler test provides a
continuity and logic test for the spoiler 18” and stick
switches. The test is conducted with the flaps down and
spoilers up. Select STICK SW on the MASTER TEST
switch (SPOILERS caution light illuminates, spoilers
droop). Move the stick left and right of center 1 inch.
Observe GO light illuminate on the MASTER TEST
panel after moving the stick in each direction. Return
the MASTER TEST switch to off and depressth e MASTER
RESET pushbutton to reset the spoilers.
2.23.5 %\v CspnBroBY. awcontrol(Figure2-65)iseE
fected by twin rudders, one on each vertical tail. The
rudder pedals adjust through a lo-inch range in l-inch
increments with the adjust control on the lower center
pedestal, forward of the control stick.
Yaw commands are transmitted mechanically from
the rudder pedals to tbe rudder power actuators by
pushrods and bellcranks. Tandem power actuators are
powered independently by the flight and combined hydraulic
systems. Yaw system authority is tabulated in
Figure 2-66.
2.23.5.‘I War&& %zi. Artificial feel is provided
with a spring roller-cam mechanism similar to the longitudinal
and lateral feel systems.
Rudder force with pedal deflection is nonlinear with
a relatively steep gradient about the neutral detent and
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F-14D 飞行手册 Flight Manual 1(113)
