曝光台 注意防骗
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gradually decreasing with increased pedal travel.
2.23.5.2 Z&&B T&c. Rudder trim is effected by
varying the neutral position of the feel assembly with an
electromechanicasl crewjack actuator.R uddert rim control
is actuated by a three-position switch on the left
console outboard of the throttle quadrant. L&I (L) and
right @) lateral switch movement commands left and
right rudder trim, respectively. The switch is spring
loaded to the center off position. Trini actuation produces
an associated movement of the rudder pedals,
rudders, and rudder indicator.
OWlelNAL 2.106
NAVAIR 0%F14AAD-1
NOMENCLATURE
@ ;;;poiler override
FUNCTION
ORIDE - Overrides inboard spoiler symmetry protection logic. If an
inboard spoiler fails more than lSO up, allows remaining inboard
spoilers to operate after MASTER RESET is depressed.
NORM - Safety guard down. Allows inboard spoiler symmetry protection.
(guarded - If an inboard spoiler falls up, all inboard spoilers are
position) commanded to the droop position and the SPOILERS light
illuminates.
0
OUTED spoiler override ORIDE - Overrides outboard spoiler symmetry protection logic. If an
switch outboard spoiler fails more than 18” up, allows remaining
outboard spoilers to operate afler MASTER RESET Is depressed.
NORM - Safety guard down. Allows outboard spoiler symmetry
(guarded protection. If an outboard spoiler fails up, all outboard spoilers
position) are commanded to the droop position and the SPOILERS light
illuminates.
Figure 2-64. Spoiler Failure Override Panel
2-107 ORIGINAL
m*icE S”J-“T
PARALLEL FEEL CAM
TRIM AN0 ROLLER
ACCNATOR
COCKPIT CONT
_p
Figure 2-65. Yaw Control System
OL RUDDER SURFACE PARALLEL TRIM
MOTION 1 AUTHORllY 1 RATE 1 AUTHORITY 1 AVERAGE RATE
I
3 Inches left, f300 1OW per 70 1.13O per second
3 Inches right maximum second
1 Inches left 1
~ inches, right
f9.50 106” per 70
minimum second
None **19o 60° per - -
second
*Stops programmed by CADC (rudder authority) as a function of dynamic pressure.
ORIGINAL 2-108
Figure 2-66. Yaw System Authority
2.23.5.3 Rudder Authority Stops. Rudder authority
control stops limit rudder throws in the high-Q flight
environment.R udder deflection limits are scheduledb y
the CADC, commencing at about 250 knots. Above
approximately 400 knots, the stops are fully engaged,
restricting manual rudder deflection to 9.5”. Disagreement
between command and position removes power
from the motor and illuminates the RUDDER AUTH
caution light.
A CADC failure may drive the rudder
authority stops to 9.S’. This condition
should be determined prior to making a single-
engine or crosswind landing. With the
9.5” stops in, rudder control may be insufficient
to maintain directional control with
single-engine afterburner operation or during
crosswind conditions. Nosewheel
steering authority is greatly reduced with
the 9.5” stops engaged.
2.23.5.4 Rudder Pedal Shaker. The rudder pedal
shaker operates only during OBCNAW BIT and is disabled
during flight.
2.23.6 Direct Lift Control. During landing approaches,
the inboard spoiles and horizontal stabilizers
can be controlled simultaneously to provide vertical
glidepathcorrectionwithout changingenginepowersetting
or angle of attack.
Before DLC can be engaged, the following conditions
are required:
1. Flaps down greater than 25’.
2. Throttles less than MIL power.
3. Inboard spoilers operational.
4. Pitch and roll AFCS computers operational.
5. Operable combined hydraulic pump.
2.23.6.4 DLC Operation. DLC is engaged with the
control stick DLC switch and commanded by the
thumbwheel. The thumbwheel is spring loaded to a neutral
position. Forward rotation of the wheel extends
spoilers and aft rotation retracts them proportionally to
the degree of thumbwheel rotation. DLC is provided by
the pitch and roll computers.
NAVAIR 0%F14AAD-I
Upon engagemenot f DLC, the roll computere xtends
the inboard spoilers from the landing flaps down
drooped(4-1/2”)positionto+17.5”abovetheflush(O”)
position. The pitch computer displaces the trailing edges
of the horizontal stabilizers 2.75” down from their trim
position. If the thumbwheel control is rotated fully forward,
the spoilers extend to their 55O position and the
stabilizer trailing edges remain at 2.75”. This increases
the rate of descent. If the thumbwheel control is rotated
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F-14D 飞行手册 Flight Manual 1(114)
