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brakes are suspected, allow a 5- to
lo-minute cooling period with the gear
extended before retracting the gear.
If heavy braking is used during landing or
taxiing followed by application of the
parking brake, normal brake operation
may not be available following release of
the parking brake if the brakes are still hot.
Check for normal brake operation after
releasing the parking brake and prior to
commencing taxiing.
2.26.3 Antiskid. The antiskid system operates eleotrohydraulically
in conjunction with the normal mode of
wheelbrake operation to deliver maximum wheelbmking
upon pilot command without causing a skid. EssentialNo.
2 bus dc power for antiskid operation is supplied
through the ANTI SKID/R AICS LKUP PWR circuit
breaker (8El) and controlled by the ANTI SKID
SPOILER BK switch (Figure 2-70). When energized,
approximately 200 milliseconds are required for antiskid
system warmup. Individual wheel rotational velocity
is sensed by skid detectors mounted in the wheel
hubs and transmitted to the skid control box. The control
box detects changes in wheel deceleration and reduces
fluid pressure in the normal brake lines to both wheels,
simultaneously, to prevent a skid.
With the antiskid system srmed in flight, the touchdown
circuit in the control box prevents braking until
weight is on both main gear and the wheels have spun
up, regardless of brake pedal application. The antiskid
system is inoperative at groundspeedso f less than 15
knots. During maximum-effort antiskid braking, expect
a rough, surging deceleration. When the ANTI SKID
SPOILER BK switch is in BOTH during low-speed taxi
(less than 10 knot.9 for more than a few seconds), subsequent
acceleration of the aircraft through approximately
15 knots will cause a temporary loss of brakes
lasting from 2 to 10 seconds. Should this happen, use of
the brakes can be regained instantly by turning antiskid
OFF. To preclude this possibility, antiskid must be OFF
during taxi.
ORIGINAL
NAVAIR Of-FlUAD-1
(WARNING1
a Failure. of the weight-on-wheels switch
results in continuous release signal with
antiskid selected.N ormal braking is available
with antiskid off.
a If the antiskid system fails, allowing antiskid
to operate below 15 knots, place the
ANTI SKID SPOILER BK switch in
OFF; otherwise the aimmA cannot be
stopped using normal braking.
Failure to release brakes prior to deselecting
ANTI SKID may result in blown tires.
The antiskid system is inoperative when the wheelbrakes
are in the auxiliaty or parking modes of operation
since the emergency brake lines bypass the brake valve.
If an electrical failure occurs in the antiskid system or if
hydraulic pressure is withheld from either brake for
greater than 1.2 seconds by the control box, the system
automatically becomes inoperative and iIluminates the
BRAKESwaminglightwiththe ANTISKIDSPOILER
BK switch in BOTH.
2.26.3.1 Antiskid Ground Test. During ground
operation, a self-test of the antiskid system can be
initiated on the face of the control box with the system
energized, parking brake handle released, and the aircraft
in a ground static condition. Before taxiing
(chocks in place), but atter releasing the parking brake
and while the pilot presses the toe pedal brakes, the
plane captain should press the antiskid test pushbutton
on the control box in the nose wheelwell. Approximately
10 seconds is required for self-test, which
checks the operational status of the control box, brake
valve, and wheel sensors. Any discrepancies detected
will be displayed by the BIT flags on the face of the
control box (Figure 2-71).
AvalidBITtestmquiresthatthreecriteriabemetzthe
BIT flags on the face of the control box must check good,
thepilotmustfeelbothb~~releaseduringB~tesfend
the BRAKES warning light must not remain illuminated.
A Sash of the BRAKES light coinciding with brake pedal
thumps during the antiskid BlT check is acceptable.
Figure 2-71. Antiskid BTI Box
2-123 ORIGINAL
NAVAIR Q%Fl4AAD-I
pi---
Before initiating antiskid self-test by pressing
the antiskid pushbutton on the control
box, ensure that the aircratt chocks arc in
place. Initiation of antiskid self-test will release
aircraft brakes.
2.26.4 Auxiliary Brake. Two different auxilimy brake
systems are presently incotpomted in the aimaft. Enby
into the auxiliary brake mode is the same for both systems.
Transfer of normal brake operation to the auxiliary mode
is automatic without the tequirement for pilot action upon
　
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