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a switching valve failing to switch to the backup
circuit following a HYD circuit failure. (The
speedbrake function and autopilot are inoperative.)
Following an aileron actuator failure, the surface
is driven to a faired position by air loads and is
damped to prevent oscillations. If the ailerons were
drooped, the opposite aileron is driven to the undrooped
position. With both ailerons undrooped,
approach speed is somewhat higher. The operating
aileron continues to provide roll control. Roll damping
is noticeably less. Use care to prevent overcontrol
and resulting lateral PIO, especially when approaching
touchdown.
When FCS/FCES procedures complete -
6. Make a controllability check at safe altitude.
For landing -
7. FLAP switch - HALF
8. Fly a straight-in approach (if practical).
9. Fly on-speed AOA to touchdown.
FC AIR DAT
FCES
Caution Light
· Left and right pitot-static probes are reporting in
the valid range but disagree. FCCs use the highest
total pressure input.
With an FC AIR DAT caution, HUD displayed airspeed
may be in error. Fly an on-speed AOA approach
(GAIN ORIDE selected).
With the GAIN switch in ORIDE, the FCCs use
fixed values for speed, altitude, and AOA depending
on FLAP switch position. These fixed gains cause
the LEFs, TEFs, and aileron droop to be driven to
fixed positions. Noticeable transients may occur
when selecting GAIN ORIDE. Longitudinal and lateral
response is more sluggish as airspeed is reduced
below the gain values and is more sensitive as airspeed
is increased above the gain values. Do not
lower the flaps in a turn as higher than normal aft
stick forces are required and sideslip excursions
may occur due to fixed gains logic. Avoid overcontrol
and resulting PIO during flap transition.
Flaps Mach KTAS Feet °AOA
AUTO 0.80 459 39,000 3.5
HALF 0.23 151 500 8.1
FULL 0.21 139 500 8.1
When FCS/FCES procedures complete -
6. Airspeed - Maintain below 350 KCAS
7. GAIN switch - ORIDE
For landing -
8. Slow below 180 KCAS.
In straight and level flight (if possible) -
9. LDG GEAR handle - DN
10. FLAP switch - HALF or FULL
11. Fly a straight-in approach (if practical).
12. Fly on-speed AOA to touchdown.
(ATC is not available)
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 34 of 55)
V-12-36 ORIGINAL
FCES CAUTIONS
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
Rud Fail
FCS
FCES
Caution Light
²Flight Controls,
Flight Controls²
RUDDER ACTUATOR FAILURE
· Rudder failures may be caused by an actuator
failure (mechanical or two channel failure) or by
a switching valve failing to switch to the backup
circuit following a HYD circuit failure. (The
speedbrake function, autopilot, and rudder toe/
flare are inoperative.)
Following a rudder actuator failure, the surface is
driven to a faired position by air loads and is
damped to prevent oscillations. With one rudder
failed, the rolling surface to rudder interconnect
(RSRI) may not have sufficient rudder authority to
coordinate lateral stick inputs. Countering a rolloff
with lateral stick alone increases adverse yaw and
aggravates the rolloff. The only way to ensure balanced
flight is to minimize sideslip by the early and
proper use of the operating rudder.
With a failed rudder, lineup control is degraded.
Make lineup corrections slowly and smoothly, particularly
when single engine. When single engine,
large throttle transients can cause significant yaw
and roll, making heading control difficult. Departure
resistance is degraded above on-speed AOA.
Full opposing rudder may not be sufficient to prevent
a departure when single engine with MAX
power selected. Bolter performance may be degraded
due to the lack of rudder toe-in.
When FCS/FCES procedures complete -
6. Make a controllability check at safe altitude.
For landing -
7. FLAP switch - HALF
8. Fly a straight-in approach (if practical)
9. Fly on-speed AOA to touchdown.
(DO NOT EXCEED ONSPEED AOA)
A1-F18EA-NFM-000
Figure 12-1. Warning/Caution/Advisory Displays (Sheet 35 of 55)
V-12-37 ORIGINAL
FCES CAUTIONS
INDICATOR · CAUSE / REMARKS CORRECTIVE ACTION
Stab Fail
FCS
FCES
Caution Light
²Flight Controls,
Flight Controls²
STABILATOR ACTUATOR FAILURE
· Stabilator failures may be caused by an actuator
failure (mechanical or three-four channel failure)
or by a dual HYD circuit failure (1B/2A or 1A/
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊(cè) 2(35)