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by the CADC:
1. RDC SPD (warning legend) - (REDUCE
SPEED) - Indicates flaps down above 225
knots; maximum safe Mach exceeded (2.4 Mach/
total temperature above 388 “F).
2. W/S (caution legend) - (WING SWEEP) -
Indicates dual wing-sweep channel failure or
wing-sweep detent disengaged.
2.19.1 Central Air Data Computer Tests
2.19.1.1 Built-In Test. BIT capabilities provide continuous
monitoring of the CADC and its inputs and
outputs. The failure indicator matrix (Figure 2-45)
tabulates the functions that are monitored andassociated
fail indications.
2-78
NAVAIR Ol-F14AAD-1
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CADC
PROCESSOR
USlNG SYSTEM
Figure 2-43. CADC Functional Relationships
SWEEP
PITOT TOTAL COMPUTER
PRESSURE
TRANSOVCER I b
I ’ I
L--------A
0.F5co366
Figure 2-44. CADC Processor
2-79 ORIGINAL
NAVAIR 01-F14AAD-1
Figure 2-45. CADC Processor Indicators
ORIGINAL 2-80
NAVAIR Ol-Fl4AAD-l
2.19.1.2 On-Board Checkout. TheCADCperforms
a self-test during OBC only with weight on wheels.
When OBC is initiated, normal air data inputs are locked
out and in their place constants from the computer memory
are received. Self-test detected failures may be
manually reset by pressing the MASTER RESET pushbutton.
Pressing the MASTER RESET pushbutton for 1 second
resets transient failures in the CADC. Activating the
master reset circuit recycles the failure detection process
in the CADC. This recycling process puts off the caution
and advisory light(s) and may take as long as 10 seconds
to check out the status of the system. If a failure exists,
the light(s) will illuminate again. If a transient failure
existed, the light(s) will remain off.
The following caution and advisory lights are activated
by the CADC:
1. CADC
2. FLAP
3. WING SWEEP (advisory) - If the WING
SWEEP advisory light does not recycle when
MASTER RESET pushbutton is depressed, the
light is activated by the wing flap controller.
Three independent CADC fail signals drive the
AFCS failure detection circuits. If these signals exist,
the AFCS will illuminate the following lights:
1. CADC fail signal pitch computer - No Light
2. CADC fail signal to yaw computer - RUDDER
AUTH and HZ TAIL AUTH
3. CADC fail signal to roll computer - MACH
TRIM.
Pressing MASTER RESET pushbutton will also update
the wing-sweep and flap commands to their respective
feedback signals. As a result, there may be
movement in the wings and maneuver flaps when MASTER
RESET pushbutton is depressed.
2.20 WING-SWEEP SYSTEM
The variable geometry of the wing-sweep system
providest he pilot with considerablela titude for controllingwingliftanddragcharacterlstics
to optimizeaircraft
performance over a broad flight spectrum.
Under normal operating conditions, the wings are
automatically positioned to the optimum sweep angle
for maximum maneuvering performance. The pilot can
selectively position the wings at sweep angles aft of
optimum.
A mechanical backup control system is provided for
emergency and oversweep operations. Details of the
wing-sweep system are shown in FO-11.
The outboard location of the wing pivot reduces the
change in longitudinal stability as a function of wingsweep
angle. Two independently powered, hydromechanical
screwjack actuators, mechanically
interconnectedf or synchronization,p osition the wings
in responset o pilot or CADC commands. In flight, the
wings can be positioned between 20” and 6S0 wing
leading-edge sweep angle. On the deck, the range is
extendeda tI 75O( oversweepp osition) to reducet he span
for spotting. Such authority results in a variation of wing
span from approximately 64 to 33 feet.
Cavities above the engine nacelles and the midfuselage
accommodate the inboard portions of the wing
panels as they sweep aft. Sealing of the underside is
by a wiper seal and airbag. The bag is pressurized by
engine bleed air. Airbag pressure is released during
oversweep to avoid overloading of the flap mechanism.
An overwing fairing encloses the wing cavity
and provides a con-toured seal along the upper surface
of the wing for the normal range of in-flight sweep
angles. The left and right overwing fairing actuators
are pressurized by the combined and flight hydraulic
systems, respectively.
2.20.1 Wing-Sweep Performance. Maximum
wing-sweep rate (approximately 15’ per second) is adequate
　
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