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systemT. rim ectuatiotmr oducesB w rrespondingst ick
an8w ntrol surfecem ovement.
2.232 $~QQ@R&K&r h ystem. TheI TS is inwrpored
to redw longituditmtlr im changebse causoef
the exten$i5ne ndr etix&on of Sapse nds pe&mkes.
Disagreemenot f comnnmdp ositionr emovesp ower
from the mot03a ndi lhuninatetsi BITEGT RIM advisoryl
ight.T ransienfta iluresc anb er esebt y pressintgh e
EvllhS~RWES~T:Tgushbutton.ITSschedulesareshown
in Figure 2-59.
Wtm the AIM-54 weapon rail pallet(s) is
installed, the speedbrakec ompensation
,w&dde h the i~tegmted trim cumputa
chmgeeI.f kes than four ADA-54m issiles
areumiedontheweq3onmils,thelTsmay
overcompensatfeo r the speedbrakter im
chaugeI.Q the worst case( low altitude,b etween
0.7 end 0.8 Mach, pitch SAS otf, and
weaponw its withoutA IM-54 missilee)t,h e
llscP!ncauseeQin cmmentaal g QosedowQ
trim changew hen the speedbrakeis extended.
LMertbesewnditionswiththepitch
sAseQ@ge&me$dmmQticluulgeisre
ducedto epproximatel1y~
QRlGlNAh 2-m
a SPOILER positIon
indicators
A right inboard or outboard
spoiler positlon lndlcator
showlng one position hlgher
than the, corresponding
spoilers ac$ual position Indlcates
a posslblllty of
ground roll braking In flight
and loss of spoiler asym
metry protectlon due to a
failed zero degree swkh.
0 RUDDER positlon
Indicator
-Spollers down (flush with wing surface).
-Either spoiler of the approprlate palr
Is extended more than OO.
-Both spoilers of the appropriate pair at
a dropped position (O-4 1/2O below
wing surface)
idlvldual ruddar polnters marked R (right) and L (left) display the
ailing-edge position of the rudders in degrees (0 to 30).
ORIWUU.
NOMENCLATURE
0 HORIZONTAL tail
stabilizers position
@
,WTWT;tKr SPOILER
0 HZ TAIL AUTH
caution light
c9
RUDDER AUTH
caution light
0 EILERS caution
@
INTEG TRIM advisory
light
@
MACH TRIM advisory
light
010 RUDDER TRIM switch
FUNCTION
Indicated by two pointers marked R (tight) and L (left) on a scale 35”
up and 15” down. Scale is graduated in 2” increments. The inner
pointer indicates lefl wing down or right wing down (diierential
stabilizer position).
BOTH -Antiskid activated. Spoiler brakes bperate with weight on
wheels and throttle at IDLE.
OFF -Antiskid and spoiler brakes Inoperative with weight on
wheels.
SPOILER BK - Spoiler brakes operate with weight on wheels and
both throttles at IDLE. Antiskid is deactivated.
Failure of lateral tail authority actuator to follow schedule or CADC
failure.
Disagreement between command and position, failure of rudder
authority actuators to follow schedule, or CADC failure.
Note
The RUDDER AUTH caution light may illuminate when the
in-flight refueling probe is extended. Press the MASTER
RESET button to rese the light.
Spoiler system failure, causing a set of spoilers to be locked down.
Note
SPOILERS caution light will not illuminate with SPOILER
FLR ORIDE switches in ORIDE position.
Discrepancy between input command signal and actuator position
or an electrical power loss within the computer.
Failure of Mach trim actuator to follow schedule.
Note
Transient failures involving HZ TAIL AUTH, RUDDER AUTH,
or SPOILERS caution lights and INTEG TRIM and MACH
TRIM advisory lights can be reset by pressing the MASTER
RESET pushbutton.
Controls the electromechanical actuator that varies the neutral
position of the mechanical linkage for rudder trim.
ORIGINAL
Figure 2-55. Control Surface Indicators (Sheet 2 of 2)
2-98
COCKPIT CONTI
izi%qiF
Maneuver
Flap
Integrated
Trim System
(ITS) and DLC
Thumbwheel
Parallel
Automatic LCarrier
Landing
(ACL only)
Series
Figure 2-56. Longitudinal Control System
OL
MOTION
4 Inches
forward 5.5
inches aft
4 Inches
forward 5.5
inches aft
f450 DLC
Thumbwheel
Mode
f45”
Maneuver
Flap Mode
STABILIZE
AUTHORITV
10’ TED
33’ TEU
f3O
IO’ TED 36” per
33” TEU second
8.4’ TED
Maxlmum
36” per
second
ISURFACE 1 PARALLEL TRIM
RATE 1 AUTHORITY ( AVERAGE RATE
38’ per
second
9’ TED
18O TEU
1 o per second
22: 1 - ( -
9’ TED 0.1 o per second
18’ TEU
　
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